# Airbus Service Bulletin A300-53-6175

## Copies (2)

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

- No revision named ("A300-53-6175R1 Dec07 2021"), 53 pages: PDF https://openairdocs.org/files/sha256/86/96/8696e7144e25326f53cdbef887e120e647a877c1bb5237ebcbab55e1da4a26d3; text https://openairdocs.org/service-documents/airbus/a300-53-6175/file/8696e7144e25.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2022-1168, the docket of AD 2022-25-03. Not covered by OpenAirDocs’ CC0 dedication.
- No revision named ("SB_A300-53-6175_Rev 00"), 37 pages: PDF https://openairdocs.org/files/sha256/f6/b3/f6b3b343ee2f9f00f89adfd9f5e1d0337625c87ae0b3ef93f2bde3d603ccec6a; text https://openairdocs.org/service-documents/airbus/a300-53-6175/file/f6b3b343ee2f.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2016-0466; AD 2016-16-06 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: A300-53-6175
- Page: https://openairdocs.org/service-documents/airbus/a300-53-6175

## ADs that cite it (1) (OpenAirDocs)

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

- [AD 2016-16-06](https://openairdocs.org/ad/2016-16-06.md), effective Sep 8, 2016: No revision named

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/airbus/a300-53-6175/proposed.md), [5 difficulty reports](https://openairdocs.org/service-documents/airbus/a300-53-6175/reports.md).

## Text (53 pages)

No revision named, the newest copy. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2022-1168, the docket of AD 2022-25-03. 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
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 1
CONF ALL
AIRBUS
2, ROND POINT EMILE DEWOITINE
31700 BLAGNAC
FRANCE
 
The content of this document is the property of Airbus. All rights including copyrights are reserved.
It is supplied in confidence and commercial security on its contents must be maintained.
It must not be used for any purpose other than that for which it is supplied, nor may information
contained in it be disclosed to unauthorized persons.
It must not be reproduced in whole or in part without permission in writing from the owners of the
copyright. Requests for reproduction of any data in this document and the media authorized for it must
be addressed to Airbus.
MANDATORY MANDATORY MANDATORY
ATA SYSTEM: 53
TITLE: FUSELAGE - FUSELAGE - AFT SECTION - INSPECT DOOR FRAME
HOLES AT FR56A, FR57A & FR73A
MODIFICATION No.:
None

### Page 2

A300-600
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 2
ATA SYSTEM: 53
TITLE: FUSELAGE - FUSELAGE - AFT SECTION - INSPECT DOOR FRAME
HOLES AT FR56A, FR57A & FR73A
REVISION TRANSMITTAL SHEET
This page transmits Revision No. 01 of Service Bulletin No. A300-53-6175.
A. ADDITIONAL WORK
No additional work is required by this revision.
B. REASON
Revision No. 01 issued to:
- Transform Service Bulletin data from ATA iSpec 2200 norm to ASD S1000D norm
- Update the applicability
- Create new task to send the inspection report sheet.
C. CHANGES
SERVICE BULLETIN
General Revised text and layout changes of this revision are
not identified with revision bars.
SUMMARY
APPLICABILITY Operators updated.
MANPOWER
T ask set A300-A-53-XX-6175-
01000-93BA-A Inspection
- T otal man-hours updated from "10.75h" to "11.00h"
- Elapsed time updated from "4.50h" to "4.75h".
GENERAL OVERVIEW
Fig.SA Sol.AA General Overview Illustration updated.
PLANNING INFORMATION
APPLICABILITY Applicability updated.
Configuration definition Configuration definition phrasing updated.
DESCRIPTION
T ask set A300-A-53-XX-6175-
01000-93BA-A Inspection
T ask title updated.
COMPLIANCE
Accomplishment Timescale Grace period updated from 36 months to 12 months.
APPROVAL Sentence updated.
MANPOWER
T ask set A300-A-53-XX-6175-
01000-93BA-A Inspection
- T otal man-hours updated from "10.75h" to "11.00h"
- Elapsed time updated from "4.50h" to "4.75h"
- Manpower note updated.
MATERIAL INFORMATION
TOOLING

### Page 3

A300-600
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 3
Referenced tools for task set
A300-A-53-XX-6175-01000-
93BA-A Inspection
Sentence updated.
ACCOMPLISHMENT INSTRUCTIONS
T ask set A300-A-53-XX-6175-01000-93BA-A Inspection
PROCEDURE
T ask A300-A-53-XX-6175-01001-353A-A Do an HFEC inspection for cracks at Frame
56A, LH side
Fig.BB Sol.AA HFEC
Inspection from the Seal
Retainer Run-out Rivet
Hole
Illustration updated.
Fig.FA Sol.AA HFEC
Inspection Flowchart
Illustration updated.
T ask A300-A-53-XX-6175-02001-353A-A Do an HFEC inspection for cracks at Frame
56A, RH side
Fig.BB Sol.AA HFEC
Inspection from the Seal
Retainer Run-out Rivet
Hole
Illustration updated.
Fig.FA Sol.AA HFEC
Inspection Flowchart
Illustration updated.
T ask A300-A-53-XX-6175-03001-353A-A Do an HFEC inspection for cracks at Frame
57A, LH side
Fig.BA Sol.AA HFEC
Inspection from the Seal
Retainer Run-out Rivet
Hole
Illustration updated.
Fig.FA Sol.AA HFEC
Inspection Flowchart
Illustration updated.
T ask A300-A-53-XX-6175-04001-353A-A Do an HFEC inspection for cracks at Frame
57A, RH side
Fig.BA Sol.AA HFEC
Inspection from the Seal
Retainer Run-out Rivet
Hole
Illustration updated.
Fig.FA Sol.AA HFEC
Inspection Flowchart
Illustration updated.
T ask A300-A-53-XX-6175-05001-353A-A Do an HFEC inspection for cracks at Frame
73A, LH side
Fig.BC Sol.AA HFEC
Inspection from the Seal
Retainer Run-out Rivet
Hole
Illustration updated.
Fig.FA Sol.AA HFEC
Inspection Flowchart
Illustration updated.
T ask A300-A-53-XX-6175-06001-353A-A Do an HFEC inspection for cracks at Frame
73A, RH side
Fig.BC Sol.AA HFEC
Inspection from the Seal
Illustration updated.

### Page 4

A300-600
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 4
Retainer Run-out Rivet
Hole
Fig.FA Sol.AA HFEC
Inspection Flowchart
Illustration updated.
A300-A-53-XX-6175-
02001-90AA-A Complete
and Send the Inspection
Report Sheet
New task created for inspection report.
Fig.RA Sol.AA Inspection
Report sheet
Illustration updated.
APPENDIX
MANPOWER GANTT CHART
Fig.AA Sol.AA Manpower Gantt
chart
Illustration updated.
D. FILING INSTRUCTIONS
This Service Bulletin has been generated electronically and is reissued as a complete
document. Replace the complete document.
Put this Revision Transmittal Sheet in front of the Service Bulletin.
E. HISTORY OF PREVIOUS REVISIONS
No previous revision
F. REVISION SEQUENCE
ORIGINAL: May 28/14
REVISION No. : 01 - Dec 07/21

### Page 5

A300-600
SERVICE BULLETIN
SUMMARY
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 5
ATA SYSTEM: 53
TITLE: FUSELAGE - FUSELAGE - AFT SECTION - INSPECT DOOR FRAME
HOLES AT FR56A, FR57A & FR73A
SUMMARY
This summary is for information only and is not approved for modification of the aircraft.
A. MODIFICATIONS
MODIFICATION CLASSIFICATION
MAJOR None
MINOR None
NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the
mass, balance, structural strength, reliability, operational characteristics affecting
the airworthiness of the product. All other changes are major changes.
B. REASON
(1) History
During the aircraft preparation phase for conversion of an A300-600 aircraft from
PAX to Freighter, a crack was detected in Door Frame 73A, between Stringer 24 and
Stringer 25, Left Hand (LH) side / Right Hand (RH) side. The crack initiation was found
on the seal retainer runout rivet hole, near the frame web of door stops No.8. Because
the emergency exit and AFT passenger/crew doors have the same structural door
frame design, AIRBUS has decided to do a special detailed inspection of door Frame
56A, Frame 57A and Frame 73A.
(2) Objective/Action
This Service Bulletin requires the operator to introduce a High Frequency Eddy Current
(HFEC) inspection of the seal retainer runout rivet hole at Frame 56A, Frame 57A and
Frame 73A.
(3) Advantages
Accomplishment of this Service Bulletin will allow early detection of cracks in order to
avoid possible crack propagation and will contribute to ensure the structural integrity
of the door Frame 56A, Frame 57A and Frame 73A.
(4) Operational/Maintenance Consequences
None
C. GENERAL EVALUATION
EVALUATION TABLE
COMPLIANCE MANDATORY COST SAVING NO
A/C OPERATION
AFFECTED
NO VENDOR SB NO
CANCELS INSPECTION SB NO ETOPS AFFECTED NO
PAX COMFORT AFFECTED NO POTENTIAL AD YES
RELIABILITY AFFECTED NO STRUCTURAL LIFE EXTENSION NO
LIFE LIMIT NO LINE MAINTENANCE AFFECTED NO

### Page 6

A300-600
SERVICE BULLETIN
SUMMARY
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 6
NOTE: Service Bulletin must be accomplished.
D. MAINTENANCE CONFIGURATION
No specific aircraft maintenance configuration required.
E. MATERIAL PRICE INFORMATION
(1) Inspection
(a) T ask set A300-A-53-XX-6175-01000-93BA-A Inspection
No material
F. APPLICABILITY
This Service Bulletin is applicable to this (these) operator(s):
34P 34Z 98W AAW ABR AHK BCS BGA F2I FDX IRA IRB IRM KAL MNB MON MRJ MSR QSM SMF
SOP SUD THA TNO UTP
G. CONCURRENT REQUIREMENTS
None
H. NATURE OF THE WORK
(1) Inspection
(a) T ask set A300-A-53-XX-6175-01000-93BA-A Inspection
AIRCRAFT YES
EQUIPMENT NO
I. MANPOWER
(1) Inspection
(a) T ask set A300-A-53-XX-6175-01000-93BA-A Inspection
MANPOWER
TOTAL MAN-HOURS 11.00 h
ELAPSED TIME (HOURS) 4.75 h

### Page 7

A300-600
SERVICE BULLETIN
SUMMARY
Figure ICN-A300-A-53XX6175-A-FAPE3-0001I-A-002-01 Fig.SA Sol.AA SHEET 1/1
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21
General Overview
Page 7
J. GENERAL OVERVIEW
CONF ALL
Z250
Z260
OF DOOR 
FRAME HOLES
INSPECTION
FR76
FR58
A
FR73A
FR57A
FR56A
OF DOOR 
FRAME HOLES
INSPECTION
B
B
A
LH SHOWN
RH SYMMETRICAL
LH SHOWN
RH SYMMETRICAL
ICN-A300-A-53XX6175-A-FAPE3-0001I-A-002-01

### Page 8

A300-600
SERVICE BULLETIN
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 8
ATA SYSTEM: 53
TITLE: FUSELAGE - FUSELAGE - AFT SECTION - INSPECT DOOR FRAME
HOLES AT FR56A, FR57A & FR73A
1. PLANNING INFORMATION
A. APPLICABILITY
(1) Models
ON A/C 0380, 0401, 0405, 0408, 0411, 0414, 0546, 0553, 0618, 0623
B4-603
ON A/C 0464, 0505, 0518, 0521, 0532, 0556, 0558, 0563, 0584, 0603, 0608, 0626, 0632,
0643, 0696, 0701, 0707, 0709, 0713, 0715, 0723, 0725, 0727, 0732, 0741, 0744, 0746,
0749, 0754, 0763, 0764, 0773
B4-605R
ON A/C 0655, 0751, 0765, 0776, 0796
B4-608R
ON A/C 0358, 0361, 0365, 0388, 0417
B4-622
ON A/C 0477, 0479, 0530, 0536, 0543, 0555, 0557, 0559, 0561, 0569, 0572, 0575, 0579,
0581, 0602, 0607, 0611, 0613, 0617, 0621, 0625, 0630, 0631, 0633, 0635, 0637, 0641,
0657, 0659, 0662, 0664, 0666, 0668, 0670, 0677, 0679, 0683, 0685, 0688, 0703, 0711,
0717, 0722, 0724, 0729, 0730, 0733, 0734, 0737, 0739, 0740, 0743, 0750, 0753, 0756,
0762, 0767, 0770, 0775, 0783, 0786, 0788, 0797, 0836-0838
B4-622R
CONF ALL
(2) Applicability by MSN
0358 0361 0365 0380 0388 0401 0405 0408 0411 0414 0417 0464 0477 0479 0505
0518 0521 0530 0532 0536 0543 0546 0553 0555-0559 0561 0563 0569 0572 0575
0579 0581 0584 0602 0603 0607 0608 0611 0613 0617 0618 0621 0623 0625 0626
0630-0633 0635 0637 0641 0643 0655 0657 0659 0662 0664 0666 0668 0670 0677
0679 0683 0685 0688 0696 0701 0703 0707 0709 0711 0713 0715 0717 0722-0725
0727 0729 0730 0732-0734 0737 0739-0741 0743 0744 0746 0749-0751 0753 0754
0756 0762-0765 0767 0770 0773 0775 0776 0783 0786 0788 0796 0797 0836-0838
(3) MSN by configuration
MSN CONFIGURATION
0358 0361 0365 0380 0388 0401 0405 0408 0411 0414 0417
0464 0477 0479 0505 0518 0521 0530 0532 0536 0543 0546
0553 0555 0556 0557 0558 0559 0561 0563 0569 0572 0575
0579 0581 0584 0602 0603 0607 0608 0611 0613 0617 0618
0621 0623 0625 0626 0630 0631 0632 0633 0635 0637 0641
0643 0655 0657 0659 0662 0664 0666 0668 0670 0677 0679
0683 0685 0688 0696 0701 0703 0707 0709 0711 0713 0715
0717 0722 0723 0724 0725 0727 0729 0730 0732 0733 0734
0737 0739 0740 0741 0743 0744 0746 0749 0750 0751 0753
0754 0756 0762 0763 0764 0765 0767 0770 0773 0775 0776
0783 0786 0788 0796 0797 0836 0837 0838
001
(4) Configuration definition

### Page 9

A300-600
SERVICE BULLETIN
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 9
Configuration 001
CONF 001 is applicable for all the aircraft affected by this Service Bulletin as a
standard configuration.
B. CONCURRENT REQUIREMENTS
None
C. REASON
(1) History
During the aircraft preparation phase for conversion of an A300-600 aircraft from
PAX to Freighter, a crack was detected in Door Frame 73A, between Stringer 24 and
Stringer 25, Left Hand (LH) side / Right Hand (RH) side. The crack initiation was found
on the seal retainer runout rivet hole, near the frame web of door stops No.8. Because
the emergency exit and AFT passenger/crew doors have the same structural door
frame design, AIRBUS has decided to do a special detailed inspection of door Frame
56A, Frame 57A and Frame 73A.
(2) Objective/Action
This Service Bulletin requires the operator to introduce a High Frequency Eddy Current
(HFEC) inspection of the seal retainer runout rivet hole at Frame 56A, Frame 57A and
Frame 73A.
(3) Advantages
Accomplishment of this Service Bulletin will allow early detection of cracks in order to
avoid possible crack propagation and will contribute to ensure the structural integrity
of the door Frame 56A, Frame 57A and Frame 73A.
(4) Operational/Maintenance Consequences
None
D. DESCRIPTION
T o accomplish this Service Bulletin it is necessary to:
(1) Inspection
(a) T ask set A300-A-53-XX-6175-01000-93BA-A Inspection
1 Do an HFEC inspection for cracks at Frame 56A, LH side
2 Do an HFEC inspection for cracks at Frame 56A, RH side
3 Do an HFEC inspection for cracks at Frame 57A, LH side
4 Do an HFEC inspection for cracks at Frame 57A, RH side
5 Do an HFEC inspection for cracks at Frame 73A, LH side
6 Do an HFEC inspection for cracks at Frame 73A, RH side
7 Complete and Send the Inspection Report Sheet
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 Union Aviation Safety Agency
(EASA) will be issued to confirm this classification. It is anticipated that the AD will

### Page 10

A300-600
SERVICE BULLETIN
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 10
confirm the (thresholds and/or intervals and/or date) given but reference should be
made to the AD for confirmation of the mandated accomplishment timescale.
T able 01, CONF 001 - Inspection of seal retainer runout rivet hole at Frame 56A, Frame
57A and Frame 73A
COMPLIANCE TIME
CONDITIONS ACTION
THRESHOLD GRACE PERIOD
REPETITIVE
INTERVAL
Aircraft not
covered by
special detailed
inspection
TD_K4_S1_43707
_2013 (*) at
frame 56A,
57A and 73A
Do an HFEC
inspection of
the seal retainer
runout rivet hole
at frame 56A,
57A and 73A
32000 Flight
Cycle (FC) from
aircraft first flight
12 months from
Service Bulletin
revision issuance
date or before
36000 FC from
A/C first flight
(whichever
occurs first)
7500 FC
Aircraft covered
by special
detailed
inspection
TD_K4_S1_43707
_2013 (*) at
frame 56A,
57A and 73A
Do an HFEC
inspection of
the seal retainer
runout rivet hole
at frame 56A,
57A and 73A
7500 FC from
TD’s embodiment
None 7500 FC
Crack findings Contact AIRBUS
Repair Support
Before the
next flight
None None
  Report inspection
result to AIRBUS
Within 10 days None None
No crack findings Report inspection
result to AIRBUS
Within 1 month None None
  Next HFEC
inspection of
the seal retainer
runout rivet hole
None None 7500 FC
NOTE: (*) TD_K4_S1_43707_2013 is applicable for MSN 0553 only.
F. APPROVAL
The technical content of this document is approved under the authority of the Design
Organisation Approval ref. EASA.21J.031.
If an aircraft listed in the applicability 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.
(1) Inspection

### Page 11

A300-600
SERVICE BULLETIN
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 11
(a) T ask set A300-A-53-XX-6175-01000-93BA-A Inspection
PREPARATION
Job set-up 3.00 h
PROCEDURE
Do an HFEC inspection for cracks at Frame 56A, LH side 0.50 h
Do an HFEC inspection for cracks at Frame 56A, RH side 0.50 h
Do an HFEC inspection for cracks at Frame 57A, LH side 0.50 h
Do an HFEC inspection for cracks at Frame 57A, RH side 0.50 h
Do an HFEC inspection for cracks at Frame 73A, LH side 0.50 h
Do an HFEC inspection for cracks at Frame 73A, RH side 0.50 h
Complete and Send the Inspection Report Sheet 0.25 h
PREPARATION FOR TEST
None
TEST
Functional T est 4.50 h
CLOSE-UP
Close-up 0.25 h
TOTAL MAN-HOURS 11.00 h
ELAPSED TIME (HOURS) 4.75 h
NOTE: For an explanation of the man-hours and elapsed time, refer to the
Gantt Chart given in Appendix A.
H. WEIGHT AND BALANCE
Not changed
I. ELECTRICAL LOAD DATA
Not changed
J. REFERENCES
(1) Inspection
(a) T ask set A300-A-53-XX-6175-01000-93BA-A Inspection
AIRCRAFT MAINTENANCE MANUAL (AMM)
06-21-00, Page Block 001 06-31-53, Page Block 001
06-41-00, Page Block 001 24-00-00, Page Block 301
24-41-00, Page Block 301 25-00-00, Page Block 801
25-12-11, Page Block 401 25-22-11, Page Block 401
25-23-41, Page Block 401
ELECTRICAL STANDARD PRACTICES MANUAL (ESPM)
20-55-00
IN SERVICE INFORMATION (ISI)
00.00.00179

### Page 12

A300-600
SERVICE BULLETIN
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 12
NON DESTRUCTIVE TEST MANUAL (NTM)
51-10-08, Page Block 601
CONSUMABLE MATERIAL LIST (CML)
K. PUBLICATION AFFECTED
None
L. INDUSTRY SUPPORT INFORMATION
AIRBUS will not provide industry support for accomplishment of this Service Bulletin.

### Page 13

A300-600
SERVICE BULLETIN
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 13
2. MATERIAL INFORMATION
A. MATERIAL APPLICABILITY
Material for task set A300-A-53-XX-6175-01000-93BA-A Inspection
MATERIAL QTY SEE NOTES
Referenced tools See SB
Consumables See SB
B. TOOLING
Referenced tools for task set A300-A-53-XX-6175-01000-93BA-A Inspection
T o accomplish this Service Bulletin it is necessary to use the tools listed in:
Ref. NTM 51-10-08, Page Block 601
C. CONSUMABLES
Consumables for task set A300-A-53-XX-6175-01000-93BA-A Inspection
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
08BAA9 Non Aqueous Cleaner-General
14SBA1 T extile-Lint free-Cotton
D. LIST OF NEW PARTS
No parts
E. LIST OF EXISTING PARTS
No parts

### Page 14

A300-600
SERVICE BULLETIN
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 14
3. ACCOMPLISHMENT INSTRUCTIONS
Task set A300-A-53-XX-6175-01000-93BA-A (A300-A-53-XX-6175-01ZZZ-93BZ-A)
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 A 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 Ref. 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: 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.
NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory by
an Airworthiness Directive (AD). The paragraphs 3.C. and 3.E. in these accomplishment
instructions are Required for Compliance (RC) and must be done to comply with the AD.
T o allow more flexibility, the rule "refer to" and "in accordance with" will apply to these
paragraphs 3.C. and 3.E. 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.
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, including Required for Compliance paragraph
contained herein, contact AIRBUS for further instructions and approval.
A. TASK SET ASSOCIATED INFORMATION
Task Manpower
TOTAL MAN-HOURS 11.00 h
ELAPSED TIME (HOURS) 4.75 h

### Page 15

A300-600
SERVICE BULLETIN
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 15
B. PREPARATION
(1) Task A300-A-53-XX-6175-01001-540A-A (A300-A-53-XX-6175-01ZZZ-540Z-A)
Job set-up
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
260 Work location Frame 73A LH/RH
250 Work location Frame 57A LH/RHFrame 56A LH/RH
Manpower/Resources/Skills
Man-hours 3.00 h
Minimum Number of person 2
Elapsed Time 1.50 h
Referenced Information
Manuals/Drawings References/Sheets
AMM
24-00-00, Page Block 301
24-41-00, Page Block 301
25-00-00, Page Block 801
25-22-11, Page Block 401
25-23-41, Page Block 401
Procedure
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 Ref. AMM 24-00-00,
Page Block 301.
(b) Energize the ground service network, refer to Ref. AMM 24-41-00, Page Block
301.
(c) Put an access platform in position of the MID and AFT Door 834, Door 844, Door
833 and Door 843.
(d) Open, safety/lock and tag the applicable circuit breakers as specified in the
removal of door frame linings, refer to Ref. AMM 25-23-41, Page Block 401.
(e) At Frame 56A, Frame 57A and Frame 73A LH/RH side, remove the door frame
linings for access, refer to Ref. AMM 25-23-41, Page Block 401.
(f) Put blanking caps on the disconnected electrical connectors.
(g) Between Frame 56 and Frame 56A, Frame 57 and Frame 57A and between Frame
73 and Frame 73A, remove the heat and sound insulation blankets for access,
refer to Ref. AMM 25-22-11, Page Block 401.
(h) If necessary for repair of insulation blankets, refer to Ref. AMM 25-00-00, Page
Block 801.
C. PROCEDURE
(1) Task A300-A-53-XX-6175-01001-353A-A (A300-A-53-XX-6175-01ZZZ-353Z-A)
Do an HFEC inspection for cracks at Frame 56A, LH side

### Page 16

A300-600
SERVICE BULLETIN
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 16
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
250 Work location Frame 56A LHFrom Stringer 24 to Stringer 25
Manpower/Resources/Skills
Man-hours 0.50 h
Minimum Number of person 1
Elapsed Time 0.50 h
Skills Non-Destructive T esting
Material necessary to do the job
Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
08BAA9 Non Aqueous Cleaner-General
14SBA1 T extile-Lint free-Cotton
Referenced Information
Manuals/Drawings References/Sheets
AMM
06-21-00, Page Block 001
06-31-53, Page Block 001
06-41-00, Page Block 001
CML CONSUMABLE MATERIAL LIST (CML)
NTM 51-10-08, Page Block 601
Procedure
(a) Standard Practices given in this procedure:
1 For the specification of Material application codes given in this Service
Bulletin, refer to Ref. CML.
2 For the Frame (FR) identification, refer to Ref. AMM 06-31-53, Page Block
001.
3 For the identification of zones, refer to Ref. AMM 06-21-00, Page Block 001.
4 For the identification of access panels, refer to Ref. AMM 06-41-00, Page
Block 001.
(b) At Frame 56A, LH side, between Stringer 25 and Stringer 25A, refer to Ref. Fig.BB
Sol.AA SHEET 1 HFEC Inspection from the Seal Retainer Run-out Rivet Hole, view
A and Ref. Fig.BB Sol.AA SHEET 2 HFEC Inspection from the Seal Retainer Run-
out Rivet Hole, view B, clean the inspection surface area with:
  T extile-Lint free-Cotton 14SBA1  
  Non Aqueous Cleaner-
General
08BAA9  
(c) Do an HFEC inspection for cracks around the rivet head of seal retainer runout
hole at Frame 56A LH side, refer to Ref. NTM 51-10-08, Page Block 601, Ref.
Fig.BB Sol.AA SHEET 1 HFEC Inspection from the Seal Retainer Run-out Rivet

### Page 17

A300-600
SERVICE BULLETIN
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 17
Hole, view A, Ref. Fig.BB Sol.AA SHEET 2 HFEC Inspection from the Seal Retainer
Run-out Rivet Hole, view B and refer to Ref. Fig.FA HFEC Inspection Flowchart, at
the threshold given in Para 1.E.(2).
1 Scanning probe to be circled around the rivet head of seal retainer runout
hole within an area of 10.0 mm (0.39 in.), refer to Ref. Fig.BB Sol.AA SHEET
2 HFEC Inspection from the Seal Retainer Run-out Rivet Hole, view B.
2 If there are no cracks:
a After completion of all inspections, complete and send the Inspection
Report sheet in accordance with Ref. T ask A300-A-53-XX-6175-02ZZZ-
90AZ-A and report the inspection results within 1 month to AIRBUS.
b Repeat the HFEC inspection at intervals given in Para 1.E.(2).
3 If there are cracks:
a Contact AIRBUS repair support for further instructions, before next
flight.
b After completion of all inspections, complete and send the Inspection
Report sheet in accordance with Ref. T ask A300-A-53-XX-6175-02ZZZ-
90AZ-A and report the inspection results within 10 days to AIRBUS.

### Page 18

A300-600
SERVICE BULLETIN
Figure ICN-A300-A-53XX6175-A-FAPE3-0001C-A-002-01 Fig.BB Sol.AA SHEET 1/2
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21
HFEC Inspection from the Seal Retainer Run-out Rivet Hole
Page 18
CONF ALL
STGR26
STGR27
STGR25A
STGR30
STGR29
STGR25
FR56A
FR57A
FR58
FR57.3
FR57.2
FR57.1
FR57
FR56
STGR28
A
SEAL
RETAINER
Z250
A
B
LH SHOWN
RH SYMMETRICAL
ICN-A300-A-53XX6175-A-FAPE3-0001C-A-002-01

### Page 19

A300-600
SERVICE BULLETIN
Figure ICN-A300-A-53XX6175-A-FAPE3-0001D-A-002-01 Fig.BB Sol.AA SHEET 2/2
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21
HFEC Inspection from the Seal Retainer Run-out Rivet Hole
Page 19
CONF ALL
DOOR
STGR23A
STGR24
STGR25
STGR25A
STOP 8
10 mm
(0.393 in)
SEAL 
RETAINER FR56A
AREA TO BE INSPECTED.
MINIMUM 10 mm (0.393 in) AROUND RIVET HEAD.
BINBD
EXISTING FASTENER
NOTE:
VIEW LOOKING FWD
LH SHOWN
RH SYMMETRICAL
ICN-A300-A-53XX6175-A-FAPE3-0001D-A-002-01

### Page 20

A300-600
SERVICE BULLETIN
Figure ICN-A300-A-53XX6175-A-FAPE3-0001G-A-004-01 Fig.FA Sol.AA SHEET 1/1
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21
HFEC Inspection Flowchart
Page 20
CONF ALL
COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN.
AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR
THE PURPOSE OF FLOWCHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE
FOR THE ACCOMPLISHMENT TIMESCALE, REFER TO PARAGRAPH 1.E.(2).01
NOTE:
CONTACT AIRBUS REPAIR SUPPORT
BEFORE NEXT FLIGHT
REPORT INSPECTION RESULT WITHIN
10 DAYS TO AIRBUS
1 MONTH TO AIRBUS
REPORT INSPECTION RESULT WITHIN
AT INTERVAL 01
DO A REPETITIVE INSPECTION
ON NON-REPAIRED FRAME(S)
DO A SPECIAL DETAILED INSPECTION (HFEC) OF
THE HOLES AT THRESHOLD 01
FOR THE CRACKED FRAME(S)
ARE THERE
ANY
CRACKS FOUND?
NOYES
ICN-A300-A-53XX6175-A-FAPE3-0001G-A-004-01

### Page 21

A300-600
SERVICE BULLETIN
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 21
(2) Task A300-A-53-XX-6175-02001-353A-A (A300-A-53-XX-6175-02ZZZ-353Z-A)
Do an HFEC inspection for cracks at Frame 56A, RH side
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
250 Work location Frame 56A RHFrom Stringer 24 to Stringer 25
Manpower/Resources/Skills
Man-hours 0.50 h
Minimum Number of person 1
Elapsed Time 0.50 h
Skills Non-Destructive T esting
Material necessary to do the job
Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
08BAA9 Non Aqueous Cleaner-General
14SBA1 T extile-Lint free-Cotton
Referenced Information
Manuals/Drawings References/Sheets
AMM
06-21-00, Page Block 001
06-31-53, Page Block 001
06-41-00, Page Block 001
CML CONSUMABLE MATERIAL LIST (CML)
NTM 51-10-08, Page Block 601
Procedure
(a) Standard Practices given in this procedure:
1 For the specification of Material application codes given in this Service
Bulletin, refer to Ref. CML.
2 For the Frame (FR) identification, refer to Ref. AMM 06-31-53, Page Block
001.
3 For the identification of zones, refer to Ref. AMM 06-21-00, Page Block 001.
4 For the identification of access panels, refer to Ref. AMM 06-41-00, Page
Block 001.
(b) At Frame 56A, RH side, between Stringer 25 and Stringer 25A, refer to Ref. Fig.BB
Sol.AA SHEET 1 HFEC Inspection from the Seal Retainer Run-out Rivet Hole, view
A and Ref. Fig.BB Sol.AA SHEET 2 HFEC Inspection from the Seal Retainer Run-
out Rivet Hole, view B, clean the inspection surface area with:
  T extile-Lint free-Cotton 14SBA1  
  Non Aqueous Cleaner-
General
08BAA9

### Page 22

A300-600
SERVICE BULLETIN
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 22
(c) Do an HFEC inspection for cracks around the rivet head of seal retainer runout
hole at Frame 56A RH side, refer to Ref. NTM 51-10-08, Page Block 601, Ref.
Fig.BB Sol.AA SHEET 1 HFEC Inspection from the Seal Retainer Run-out Rivet
Hole, view A, Ref. Fig.BB Sol.AA SHEET 2 HFEC Inspection from the Seal Retainer
Run-out Rivet Hole, view B and refer to Ref. Fig.FA HFEC Inspection Flowchart, at
the threshold given in Para 1.E.(2).
1 Scanning probe to be circled around the rivet head of seal retainer runout
hole within an area of 10.0 mm (0.39 in.), refer to Ref. Fig.BB Sol.AA SHEET
2 HFEC Inspection from the Seal Retainer Run-out Rivet Hole, view B.
2 If there are no cracks:
a After completion of all inspections, complete and send the Inspection
Report sheet in accordance with Ref. T ask A300-A-53-XX-6175-02ZZZ-
90AZ-A and report the inspection results within 1 month to AIRBUS.
b Repeat the HFEC inspection at intervals given in Para 1.E.(2).
3 If there are cracks:
a Contact AIRBUS repair support for further instructions, before next
flight.
b After completion of all inspections, complete and send the Inspection
Report sheet in accordance with Ref. T ask A300-A-53-XX-6175-02ZZZ-
90AZ-A and report the inspection results within 10 days to AIRBUS.

### Page 23

A300-600
SERVICE BULLETIN
Figure ICN-A300-A-53XX6175-A-FAPE3-0001C-A-002-01 Fig.BB Sol.AA SHEET 1/2
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21
HFEC Inspection from the Seal Retainer Run-out Rivet Hole
Page 23
CONF ALL
STGR26
STGR27
STGR25A
STGR30
STGR29
STGR25
FR56A
FR57A
FR58
FR57.3
FR57.2
FR57.1
FR57
FR56
STGR28
A
SEAL
RETAINER
Z250
A
B
LH SHOWN
RH SYMMETRICAL
ICN-A300-A-53XX6175-A-FAPE3-0001C-A-002-01

### Page 24

A300-600
SERVICE BULLETIN
Figure ICN-A300-A-53XX6175-A-FAPE3-0001D-A-002-01 Fig.BB Sol.AA SHEET 2/2
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21
HFEC Inspection from the Seal Retainer Run-out Rivet Hole
Page 24
CONF ALL
DOOR
STGR23A
STGR24
STGR25
STGR25A
STOP 8
10 mm
(0.393 in)
SEAL 
RETAINER FR56A
AREA TO BE INSPECTED.
MINIMUM 10 mm (0.393 in) AROUND RIVET HEAD.
BINBD
EXISTING FASTENER
NOTE:
VIEW LOOKING FWD
LH SHOWN
RH SYMMETRICAL
ICN-A300-A-53XX6175-A-FAPE3-0001D-A-002-01

### Page 25

A300-600
SERVICE BULLETIN
Figure ICN-A300-A-53XX6175-A-FAPE3-0001G-A-004-01 Fig.FA Sol.AA SHEET 1/1
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21
HFEC Inspection Flowchart
Page 25
CONF ALL
COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN.
AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR
THE PURPOSE OF FLOWCHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE
FOR THE ACCOMPLISHMENT TIMESCALE, REFER TO PARAGRAPH 1.E.(2).01
NOTE:
CONTACT AIRBUS REPAIR SUPPORT
BEFORE NEXT FLIGHT
REPORT INSPECTION RESULT WITHIN
10 DAYS TO AIRBUS
1 MONTH TO AIRBUS
REPORT INSPECTION RESULT WITHIN
AT INTERVAL 01
DO A REPETITIVE INSPECTION
ON NON-REPAIRED FRAME(S)
DO A SPECIAL DETAILED INSPECTION (HFEC) OF
THE HOLES AT THRESHOLD 01
FOR THE CRACKED FRAME(S)
ARE THERE
ANY
CRACKS FOUND?
NOYES
ICN-A300-A-53XX6175-A-FAPE3-0001G-A-004-01

### Page 26

A300-600
SERVICE BULLETIN
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 26
(3) Task A300-A-53-XX-6175-03001-353A-A (A300-A-53-XX-6175-03ZZZ-353Z-A)
Do an HFEC inspection for cracks at Frame 57A, LH side
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
250 Work location Frame 57A LHFrom Stringer 24 to Stringer 25
Manpower/Resources/Skills
Man-hours 0.50 h
Minimum Number of person 1
Elapsed Time 0.50 h
Skills Non-Destructive T esting
Material necessary to do the job
Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
08BAA9 Non Aqueous Cleaner-General
14SBA1 T extile-Lint free-Cotton
Referenced Information
Manuals/Drawings References/Sheets
AMM
06-21-00, Page Block 001
06-31-53, Page Block 001
06-41-00, Page Block 001
CML CONSUMABLE MATERIAL LIST (CML)
NTM 51-10-08, Page Block 601
Procedure
(a) Standard Practices given in this procedure:
1 For the specification of Material application codes given in this Service
Bulletin, refer to Ref. CML.
2 For the Frame (FR) identification, refer to Ref. AMM 06-31-53, Page Block
001.
3 For the identification of zones, refer to Ref. AMM 06-21-00, Page Block 001.
4 For the identification of access panels, refer to Ref. AMM 06-41-00, Page
Block 001.
(b) At Frame 57A, LH side, between Stringer 25 and Stringer 25A, refer to Ref. Fig.BA
Sol.AA SHEET 1 HFEC Inspection from the Seal Retainer Run-out Rivet Hole, view
A and Ref. Fig.BA Sol.AA SHEET 2 HFEC Inspection from the Seal Retainer Run-
out Rivet Hole, view B, clean the inspection surface area with:
  T extile-Lint free-Cotton 14SBA1  
  Non Aqueous Cleaner-
General
08BAA9

### Page 27

A300-600
SERVICE BULLETIN
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 27
(c) Do an HFEC inspection for cracks around the rivet head of seal retainer runout
hole at Frame 57A LH side, refer to Ref. NTM 51-10-08, Page Block 601, Ref.
Fig.BA Sol.AA SHEET 1 HFEC Inspection from the Seal Retainer Run-out Rivet
Hole, view A, Ref. Fig.BA Sol.AA SHEET 2 HFEC Inspection from the Seal Retainer
Run-out Rivet Hole, view B and refer to Ref. Fig.FA HFEC Inspection Flowchart, at
the threshold given in Para 1.E.(2).
1 Scanning probe to be circled around the rivet head of seal retainer runout
hole within an area of 10.0 mm (0.39 in.), refer to Ref. Fig.BA Sol.AA SHEET
2 HFEC Inspection from the Seal Retainer Run-out Rivet Hole, view B.
2 If there are no cracks:
a After completion of all inspections, complete and send the Inspection
Report sheet in accordance with Ref. T ask A300-A-53-XX-6175-02ZZZ-
90AZ-A and report the inspection results within 1 month to AIRBUS.
b Repeat the HFEC inspection at intervals given in Para 1.E.(2).
3 If there are cracks:
a Contact AIRBUS repair support for further instructions, before next
flight.
b After completion of all inspections, complete and send the Inspection
Report sheet in accordance with Ref. T ask A300-A-53-XX-6175-02ZZZ-
90AZ-A and report the inspection results within 10 days to AIRBUS.

### Page 28

A300-600
SERVICE BULLETIN
Figure ICN-A300-A-53XX6175-A-FAPE3-0001A-A-005-01 Fig.BA Sol.AA SHEET 1/2
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21
HFEC Inspection from the Seal Retainer Run-out Rivet Hole
Page 28
CONF ALL
STGR26
STGR27
STGR25A
STGR30
STGR29
STGR25
FR56A
FR57A
FR58
FR57.3
FR57.2
FR57.1
FR57
FR56
STGR28
A
SEAL
RETAINER
Z250
A
B
LH SHOWN
RH SYMMETRICAL
ICN-A300-A-53XX6175-A-FAPE3-0001A-A-005-01

### Page 29

A300-600
SERVICE BULLETIN
Figure ICN-A300-A-53XX6175-A-FAPE3-0001B-A-004-01 Fig.BA Sol.AA SHEET 2/2
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21
HFEC Inspection from the Seal Retainer Run-out Rivet Hole
Page 29
CONF ALL
STGR25
STGR25A
STGR26
FR57A
DOOR
STOP 8
10 mm
(0.393 in)
SEALANT
RETAINER
STGR24
AREA TO BE INSPECTED.
MINIMUM 10 mm (0.393 in) AROUND RIVET HEAD.
BINBD
EXISTING FASTENER
NOTE:
VIEW LOOKING FWD
LH SHOWN
RH SYMMETRICAL
ICN-A300-A-53XX6175-A-FAPE3-0001B-A-004-01

### Page 30

A300-600
SERVICE BULLETIN
Figure ICN-A300-A-53XX6175-A-FAPE3-0001G-A-004-01 Fig.FA Sol.AA SHEET 1/1
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21
HFEC Inspection Flowchart
Page 30
CONF ALL
COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN.
AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR
THE PURPOSE OF FLOWCHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE
FOR THE ACCOMPLISHMENT TIMESCALE, REFER TO PARAGRAPH 1.E.(2).01
NOTE:
CONTACT AIRBUS REPAIR SUPPORT
BEFORE NEXT FLIGHT
REPORT INSPECTION RESULT WITHIN
10 DAYS TO AIRBUS
1 MONTH TO AIRBUS
REPORT INSPECTION RESULT WITHIN
AT INTERVAL 01
DO A REPETITIVE INSPECTION
ON NON-REPAIRED FRAME(S)
DO A SPECIAL DETAILED INSPECTION (HFEC) OF
THE HOLES AT THRESHOLD 01
FOR THE CRACKED FRAME(S)
ARE THERE
ANY
CRACKS FOUND?
NOYES
ICN-A300-A-53XX6175-A-FAPE3-0001G-A-004-01

### Page 31

A300-600
SERVICE BULLETIN
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 31
(4) Task A300-A-53-XX-6175-04001-353A-A (A300-A-53-XX-6175-04ZZZ-353Z-A)
Do an HFEC inspection for cracks at Frame 57A, RH side
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
250 Work location Frame 57A RHFrom Stringer 24 to Stringer 25
Manpower/Resources/Skills
Man-hours 0.50 h
Minimum Number of person 1
Elapsed Time 0.50 h
Skills Non-Destructive T esting
Material necessary to do the job
Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
08BAA9 Non Aqueous Cleaner-General
14SBA1 T extile-Lint free-Cotton
Referenced Information
Manuals/Drawings References/Sheets
AMM
06-21-00, Page Block 001
06-31-53, Page Block 001
06-41-00, Page Block 001
CML CONSUMABLE MATERIAL LIST (CML)
NTM 51-10-08, Page Block 601
Procedure
(a) Standard Practices given in this procedure:
1 For the specification of Material application codes given in this Service
Bulletin, refer to Ref. CML.
2 For the Frame (FR) identification, refer to Ref. AMM 06-31-53, Page Block
001.
3 For the identification of zones, refer to Ref. AMM 06-21-00, Page Block 001.
4 For the identification of access panels, refer to Ref. AMM 06-41-00, Page
Block 001.
(b) At Frame 57A, RH side, between Stringer 25 and Stringer 25A, refer to Ref. Fig.BA
Sol.AA SHEET 1 HFEC Inspection from the Seal Retainer Run-out Rivet Hole, view
A and Ref. Fig.BA Sol.AA SHEET 2 HFEC Inspection from the Seal Retainer Run-
out Rivet Hole, view B, clean the inspection surface area with:
  T extile-Lint free-Cotton 14SBA1  
  Non Aqueous Cleaner-
General
08BAA9

### Page 32

A300-600
SERVICE BULLETIN
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 32
(c) Do an HFEC inspection for cracks around the rivet head of seal retainer runout
hole at Frame 57A RH side, refer to Ref. NTM 51-10-08, Page Block 601, Ref.
Fig.BA Sol.AA SHEET 1 HFEC Inspection from the Seal Retainer Run-out Rivet
Hole, view A, Ref. Fig.BA Sol.AA SHEET 2 HFEC Inspection from the Seal Retainer
Run-out Rivet Hole, view B and refer to Ref. Fig.FA HFEC Inspection Flowchart, at
the threshold given in Para 1.E.(2).
1 Scanning probe to be circled around the rivet head of seal retainer runout
hole within an area of 10.0 mm (0.39 in.), refer to Ref. Fig.BA Sol.AA SHEET
2 HFEC Inspection from the Seal Retainer Run-out Rivet Hole, view B.
2 If there are no cracks:
a After completion of all inspections, complete and send the Inspection
Report sheet in accordance with Ref. T ask A300-A-53-XX-6175-02ZZZ-
90AZ-A and report the inspection results within 1 month to AIRBUS.
b Repeat the HFEC inspection at intervals given in Para 1.E.(2).
3 If there are cracks:
a Contact AIRBUS repair support for further instructions, before next
flight.
b After completion of all inspections, complete and send the Inspection
Report sheet in accordance with Ref. T ask A300-A-53-XX-6175-02ZZZ-
90AZ-A and report the inspection results within 10 days to AIRBUS.

### Page 33

A300-600
SERVICE BULLETIN
Figure ICN-A300-A-53XX6175-A-FAPE3-0001A-A-005-01 Fig.BA Sol.AA SHEET 1/2
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21
HFEC Inspection from the Seal Retainer Run-out Rivet Hole
Page 33
CONF ALL
STGR26
STGR27
STGR25A
STGR30
STGR29
STGR25
FR56A
FR57A
FR58
FR57.3
FR57.2
FR57.1
FR57
FR56
STGR28
A
SEAL
RETAINER
Z250
A
B
LH SHOWN
RH SYMMETRICAL
ICN-A300-A-53XX6175-A-FAPE3-0001A-A-005-01

### Page 34

A300-600
SERVICE BULLETIN
Figure ICN-A300-A-53XX6175-A-FAPE3-0001B-A-004-01 Fig.BA Sol.AA SHEET 2/2
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21
HFEC Inspection from the Seal Retainer Run-out Rivet Hole
Page 34
CONF ALL
STGR25
STGR25A
STGR26
FR57A
DOOR
STOP 8
10 mm
(0.393 in)
SEALANT
RETAINER
STGR24
AREA TO BE INSPECTED.
MINIMUM 10 mm (0.393 in) AROUND RIVET HEAD.
BINBD
EXISTING FASTENER
NOTE:
VIEW LOOKING FWD
LH SHOWN
RH SYMMETRICAL
ICN-A300-A-53XX6175-A-FAPE3-0001B-A-004-01

### Page 35

A300-600
SERVICE BULLETIN
Figure ICN-A300-A-53XX6175-A-FAPE3-0001G-A-004-01 Fig.FA Sol.AA SHEET 1/1
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21
HFEC Inspection Flowchart
Page 35
CONF ALL
COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN.
AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR
THE PURPOSE OF FLOWCHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE
FOR THE ACCOMPLISHMENT TIMESCALE, REFER TO PARAGRAPH 1.E.(2).01
NOTE:
CONTACT AIRBUS REPAIR SUPPORT
BEFORE NEXT FLIGHT
REPORT INSPECTION RESULT WITHIN
10 DAYS TO AIRBUS
1 MONTH TO AIRBUS
REPORT INSPECTION RESULT WITHIN
AT INTERVAL 01
DO A REPETITIVE INSPECTION
ON NON-REPAIRED FRAME(S)
DO A SPECIAL DETAILED INSPECTION (HFEC) OF
THE HOLES AT THRESHOLD 01
FOR THE CRACKED FRAME(S)
ARE THERE
ANY
CRACKS FOUND?
NOYES
ICN-A300-A-53XX6175-A-FAPE3-0001G-A-004-01

### Page 36

A300-600
SERVICE BULLETIN
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 36
(5) Task A300-A-53-XX-6175-05001-353A-A (A300-A-53-XX-6175-05ZZZ-353Z-A)
Do an HFEC inspection for cracks at Frame 73A, LH side
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
260 Work location Frame 73A LHFrom Stringer 24 to Stringer 25
Manpower/Resources/Skills
Man-hours 0.50 h
Minimum Number of person 1
Elapsed Time 0.50 h
Skills Non-Destructive T esting
Material necessary to do the job
Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
08BAA9 Non Aqueous Cleaner-General
14SBA1 T extile-Lint free-Cotton
Referenced Information
Manuals/Drawings References/Sheets
AMM
06-21-00, Page Block 001
06-31-53, Page Block 001
06-41-00, Page Block 001
CML CONSUMABLE MATERIAL LIST (CML)
NTM 51-10-08, Page Block 601
Procedure
(a) Standard Practices given in this procedure:
1 For the specification of Material application codes given in this Service
Bulletin, refer to Ref. CML.
2 For the Frame (FR) identification, refer to Ref. AMM 06-31-53, Page Block
001.
3 For the identification of zones, refer to Ref. AMM 06-21-00, Page Block 001.
4 For the identification of access panels, refer to Ref. AMM 06-41-00, Page
Block 001.
(b) At Frame 73A, LH side, between Stringer 25 and Stringer 25A, refer to Ref. Fig.BC
Sol.AA SHEET 1 HFEC Inspection from the Seal Retainer Run-out Rivet Hole, view
A and Ref. Fig.BC Sol.AA SHEET 2 HFEC Inspection from the Seal Retainer Run-
out Rivet Hole, view B, clean the inspection surface area with:
  T extile-Lint free-Cotton 14SBA1  
  Non Aqueous Cleaner-
General
08BAA9

### Page 37

A300-600
SERVICE BULLETIN
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 37
(c) Do an HFEC inspection for cracks around the rivet head of seal retainer runout
hole at Frame 73A LH side, refer to Ref. NTM 51-10-08, Page Block 601, Ref.
Fig.BC Sol.AA SHEET 1 HFEC Inspection from the Seal Retainer Run-out Rivet
Hole, view A, Ref. Fig.BC Sol.AA SHEET 2 HFEC Inspection from the Seal Retainer
Run-out Rivet Hole, view B and refer to Ref. Fig.FA HFEC Inspection Flowchart, at
the threshold given in Para 1.E.(2).
1 Scanning probe to be circled around the rivet head of seal retainer runout
hole within an area of 10.0 mm (0.39 in.), refer to Ref. Fig.BC Sol.AA SHEET
2 HFEC Inspection from the Seal Retainer Run-out Rivet Hole, view B.
2 If there are no cracks:
a After completion of all inspections, complete and send the Inspection
Report sheet in accordance with Ref. T ask A300-A-53-XX-6175-02ZZZ-
90AZ-A and report the inspection results within 1 month to AIRBUS.
b Repeat the HFEC inspection at intervals given in Para 1.E.(2).
3 If there are cracks:
a Contact AIRBUS repair support for further instructions, before next
flight.
b After completion of all inspections, complete and send the Inspection
Report sheet in accordance with Ref. T ask A300-A-53-XX-6175-02ZZZ-
90AZ-A and report the inspection results within 10 days to AIRBUS.

### Page 38

A300-600
SERVICE BULLETIN
Figure ICN-A300-A-53XX6175-A-FAPE3-0001E-A-002-01 Fig.BC Sol.AA SHEET 1/2
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21
HFEC Inspection from the Seal Retainer Run-out Rivet Hole
Page 38
CONF ALL
B
STGR18
STGR22X
STGR22A
STGR23
STGR24
STGR25
STGR26
STGR27
STGR28
STGR29
FR73
FR73A
FR74
FR75
FR75A
FR76
SEAL
REATAINER
Z260
A
A
LH SHOWN
RH SYMMETRICAL
ICN-A300-A-53XX6175-A-FAPE3-0001E-A-002-01

### Page 39

A300-600
SERVICE BULLETIN
Figure ICN-A300-A-53XX6175-A-FAPE3-0001F-A-002-01 Fig.BC Sol.AA SHEET 2/2
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21
HFEC Inspection from the Seal Retainer Run-out Rivet Hole
Page 39
CONF ALL
STGR22A
STGR23
STGR24
STGR25
FR73A
DOOR STOP 8
10 mm
(0.393 in)
SEAL RETAINER
AREA TO BE INSPECTED.
MINIMUM 10 mm (0.393 in) AROUND RIVET HEAD.
BINBD
EXISTING FASTENER
NOTE:
VIEW LOOKING FWD
LH SHOWN
RH SYMMETRICAL
ICN-A300-A-53XX6175-A-FAPE3-0001F-A-002-01

### Page 40

A300-600
SERVICE BULLETIN
Figure ICN-A300-A-53XX6175-A-FAPE3-0001G-A-004-01 Fig.FA Sol.AA SHEET 1/1
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21
HFEC Inspection Flowchart
Page 40
CONF ALL
COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN.
AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR
THE PURPOSE OF FLOWCHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE
FOR THE ACCOMPLISHMENT TIMESCALE, REFER TO PARAGRAPH 1.E.(2).01
NOTE:
CONTACT AIRBUS REPAIR SUPPORT
BEFORE NEXT FLIGHT
REPORT INSPECTION RESULT WITHIN
10 DAYS TO AIRBUS
1 MONTH TO AIRBUS
REPORT INSPECTION RESULT WITHIN
AT INTERVAL 01
DO A REPETITIVE INSPECTION
ON NON-REPAIRED FRAME(S)
DO A SPECIAL DETAILED INSPECTION (HFEC) OF
THE HOLES AT THRESHOLD 01
FOR THE CRACKED FRAME(S)
ARE THERE
ANY
CRACKS FOUND?
NOYES
ICN-A300-A-53XX6175-A-FAPE3-0001G-A-004-01

### Page 41

A300-600
SERVICE BULLETIN
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 41
(6) Task A300-A-53-XX-6175-06001-353A-A (A300-A-53-XX-6175-06ZZZ-353Z-A)
Do an HFEC inspection for cracks at Frame 73A, RH side
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
260 Work location Frame 53A RHFrom Stringer 24 to Stringer 25
Manpower/Resources/Skills
Man-hours 0.50 h
Minimum Number of person 1
Elapsed Time 0.50 h
Skills Non-Destructive T esting
Material necessary to do the job
Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
08BAA9 Non Aqueous Cleaner-General
14SBA1 T extile-Lint free-Cotton
Referenced Information
Manuals/Drawings References/Sheets
AMM
06-21-00, Page Block 001
06-31-53, Page Block 001
06-41-00, Page Block 001
CML CONSUMABLE MATERIAL LIST (CML)
NTM 51-10-08, Page Block 601
Procedure
(a) Standard Practices given in this procedure:
1 For the specification of Material application codes given in this Service
Bulletin, refer to Ref. CML.
2 For the Frame (FR) identification, refer to Ref. AMM 06-31-53, Page Block
001.
3 For the identification of zones, refer to Ref. AMM 06-21-00, Page Block 001.
4 For the identification of access panels, refer to Ref. AMM 06-41-00, Page
Block 001.
(b) At Frame 73A, RH side, between Stringer 25 and Stringer 25A, refer to Ref. Fig.BC
Sol.AA SHEET 1 HFEC Inspection from the Seal Retainer Run-out Rivet Hole, view
A and Ref. Fig.BC Sol.AA SHEET 2 HFEC Inspection from the Seal Retainer Run-
out Rivet Hole, view B, clean the inspection surface area with:
  T extile-Lint free-Cotton 14SBA1  
  Non Aqueous Cleaner-
General
08BAA9

### Page 42

A300-600
SERVICE BULLETIN
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 42
(c) Do an HFEC inspection for cracks around the rivet head of seal retainer runout
hole at Frame 73A RH side, refer to Ref. NTM 51-10-08, Page Block 601, Ref.
Fig.BC Sol.AA SHEET 1 HFEC Inspection from the Seal Retainer Run-out Rivet
Hole, view A, Ref. Fig.BC Sol.AA SHEET 2 HFEC Inspection from the Seal Retainer
Run-out Rivet Hole, view B and refer to Ref. Fig.FA HFEC Inspection Flowchart, at
the threshold given in Para 1.E.(2).
1 Scanning probe to be circled around the rivet head of seal retainer runout
hole within an area of 10.0 mm (0.39 in.), refer to Ref. Fig.BC Sol.AA SHEET
2 HFEC Inspection from the Seal Retainer Run-out Rivet Hole, view B.
2 If there are no cracks:
a After completion of all inspections, complete and send the Inspection
Report sheet in accordance with Ref. T ask A300-A-53-XX-6175-02ZZZ-
90AZ-A and report the inspection results within 1 month to AIRBUS.
b Repeat the HFEC inspection at intervals given in Para 1.E.(2).
3 If there are cracks:
a Contact AIRBUS repair support for further instructions, before next
flight.
b After completion of all inspections, complete and send the Inspection
Report sheet in accordance with Ref. T ask A300-A-53-XX-6175-02ZZZ-
90AZ-A and report the inspection results within 10 days to AIRBUS.

### Page 43

A300-600
SERVICE BULLETIN
Figure ICN-A300-A-53XX6175-A-FAPE3-0001E-A-002-01 Fig.BC Sol.AA SHEET 1/2
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21
HFEC Inspection from the Seal Retainer Run-out Rivet Hole
Page 43
CONF ALL
B
STGR18
STGR22X
STGR22A
STGR23
STGR24
STGR25
STGR26
STGR27
STGR28
STGR29
FR73
FR73A
FR74
FR75
FR75A
FR76
SEAL
REATAINER
Z260
A
A
LH SHOWN
RH SYMMETRICAL
ICN-A300-A-53XX6175-A-FAPE3-0001E-A-002-01

### Page 44

A300-600
SERVICE BULLETIN
Figure ICN-A300-A-53XX6175-A-FAPE3-0001F-A-002-01 Fig.BC Sol.AA SHEET 2/2
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21
HFEC Inspection from the Seal Retainer Run-out Rivet Hole
Page 44
CONF ALL
STGR22A
STGR23
STGR24
STGR25
FR73A
DOOR STOP 8
10 mm
(0.393 in)
SEAL RETAINER
AREA TO BE INSPECTED.
MINIMUM 10 mm (0.393 in) AROUND RIVET HEAD.
BINBD
EXISTING FASTENER
NOTE:
VIEW LOOKING FWD
LH SHOWN
RH SYMMETRICAL
ICN-A300-A-53XX6175-A-FAPE3-0001F-A-002-01

### Page 45

A300-600
SERVICE BULLETIN
Figure ICN-A300-A-53XX6175-A-FAPE3-0001G-A-004-01 Fig.FA Sol.AA SHEET 1/1
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21
HFEC Inspection Flowchart
Page 45
CONF ALL
COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN.
AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR
THE PURPOSE OF FLOWCHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE
FOR THE ACCOMPLISHMENT TIMESCALE, REFER TO PARAGRAPH 1.E.(2).01
NOTE:
CONTACT AIRBUS REPAIR SUPPORT
BEFORE NEXT FLIGHT
REPORT INSPECTION RESULT WITHIN
10 DAYS TO AIRBUS
1 MONTH TO AIRBUS
REPORT INSPECTION RESULT WITHIN
AT INTERVAL 01
DO A REPETITIVE INSPECTION
ON NON-REPAIRED FRAME(S)
DO A SPECIAL DETAILED INSPECTION (HFEC) OF
THE HOLES AT THRESHOLD 01
FOR THE CRACKED FRAME(S)
ARE THERE
ANY
CRACKS FOUND?
NOYES
ICN-A300-A-53XX6175-A-FAPE3-0001G-A-004-01

### Page 46

A300-600
SERVICE BULLETIN
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 46
(7) Task A300-A-53-XX-6175-02001-90AA-A (A300-A-53-XX-6175-02ZZZ-90AZ-A)
Complete and Send the Inspection Report Sheet
Job Set-Up Information
Manpower/Resources/Skills
Man-hours 0.25 h
Minimum Number of person 1
Elapsed Time 0.25 h
Referenced Information
Manuals/Drawings References/Sheets
ISI 00.00.00179
Procedure
(a) Complete the Inspection Report sheet, refer to Ref. Fig.RA Inspection Report
sheet.
(b) Send the completed Inspection Report sheet in accordance with Ref. ISI
00.00.00179.

### Page 47

A300-600
SERVICE BULLETIN
Figure ICN-A300-A-53XX6175-A-FAPE3-0001H-A-004-01 Fig.RA Sol.AA SHEET 1/1
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21
Inspection Report sheet
Page 47
CONF ALL
INSPECTION REPORT
SERVICE BULLETIN No :
A/C MSN :
FLIGHT CYCLES (FC) :
FLIGHT HOURS (FH) :
A300-53-6175
DATE OF INSPECTION :
INSPECTION METHOD : SPECIAL DETAILED
INSPECTION
SEND THE COMPLETED INSPECTION REPORT
SHEET IN ACCORDANCE WITH ISI 00.00.00179
YES NO
RESULT OF INSPECTION
CRACK ON
FRAME No
LEFT SIDE RIGHT SIDE
73A
YES NO
57A
56A
DISCRIPTION OF FINDINGS
ICN-A300-A-53XX6175-A-FAPE3-0001H-A-004-01

### Page 48

A300-600
SERVICE BULLETIN
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 48
D. PREPARATION FOR TEST
None
E. TEST
(1) Task A300-A-53-XX-6175-01001-340A-A (A300-A-53-XX-6175-01ZZZ-340Z-A)
Functional Test
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
260 Work location Frame 73A LH/RH
250
Manpower/Resources/Skills
Man-hours 4.50 h
Minimum Number of person 2
Elapsed Time 0.75 h
Referenced Information
Manuals/Drawings References/Sheets
AMM 25-12-11, Page Block 40125-23-41, Page Block 401
Procedure
(a) Between Frame 56 and Frame 56A, Frame 57 and Frame 57A and between,
Frame 73 and Frame 73A LH/RH side, install the heat and insulation blankets,
refer to Ref. AMM 25-12-11, Page Block 401.
(b) Remove the blanking caps from the disconnected electrical connectors.
(c) At Frame 56A, Frame 57A and Frame 73A, install the door frame linings, refer to
Ref. AMM 25-23-41, Page Block 401.
(d) Remove the safety clips and/or the tags and close/unlock the applicable circuit
breakers as specified after installation of door frame linings, refer to Ref. AMM
25-23-41, Page Block 401.
(e) Do the applicable tests of exit lights as specified after installation of door frame
linings, refer to Ref. AMM 25-23-41, Page Block 401.
F. CLOSE-UP
(1) Task A300-A-53-XX-6175-01001-740A-A (A300-A-53-XX-6175-01ZZZ-740Z-A)
Close-up
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
260
Manpower/Resources/Skills
Man-hours 0.25 h
Minimum Number of person 1
Elapsed Time 0.25 h

### Page 49

A300-600
SERVICE BULLETIN
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 49
Procedure
(a) Make sure that the work areas are clean and clear of tools and other items of
equipment.
(b) Close the passenger MID and AFT passenger/crew Door 834, Door 844, Door 833
and Door 843.
(c) Remove the access platform(s).
G. ADMINISTRATIVE
(1) Task A300-A-53-XX-6175-01001-90AA-A (A300-A-53-XX-6175-01ZZZ-90AZ-A)
Administrative
Procedure
Confirm in the applicable aircraft records that you have completed all the work defined
in this Service Bulletin task set as required.

### Page 50

A300-600
SERVICE BULLETIN
APPENDIX
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 50
APPENDIX
A. MANPOWER GANTT CHART
MANPOWER GANTT CHART
For an explanation of the man-hours and elapsed time, refer to the next page(s).

### Page 51

A300-600
SERVICE BULLETIN
APPENDIX
Figure ICN-A300-A-53XX6175-A-FAPE3-00019-A-004-01 Fig.AA Sol.AA SHEET 1/1
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21
Manpower Gantt chart
Page 51
CONF ALL
ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A300-53-6175
SB ELAPSED TIME
(HOURS)
REMOVE FRAME LININGS ON DOOR 833
REMOVE FRAME LININGS ON DOOR 843
REMOVE FRAME LININGS ON DOOR 844
INSPECTION DOOR 843
INSTALL FRAME LININGS ON DOOR 834
INSPECTION DOOR 844
0.50 0.501
MH ET/S
TOTAL MANHOURS
SB ELAPSED TIME
11.00
4.75
STEPS
0
MH
ET/S:
PER
MANHOURS
ELAPSED TIME PER STEP
NUMBER OF PERSONS
01
02
THIS CHART IS ONLY A PROPOSAL.
OPERATORS MAY DETERMINE THAT ANOTHER WAY
TO DO THE WORK IS MORE SUITABLE FOR THEM.
01
02
NOTE:
PER
:
:
IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS
ARE NOT REFLECTED IN THIS GANTT CHART.
2 3 4
0.50 0.501
1.50 0.752
1.00 1.001
REMOVE FRAME LININGS ON DOOR 834
INSPECTION DOOR 833
INSPECTION DOOR 834
1.00 0.502
1.00 0.502
0.50 0.501
0.50 0.501
1.00 1.001
4.503.502.501.500.50 1.00
0.25 0.251
INSTALL FRAME LININGS ON DOOR 833 0.75 1
INSTALL FRAME LININGS ON DOOR 843 0.75 1
INSTALL FRAME LININGS ON DOOR 844 1.50 0.752
0.25 0.251
CLOSE UP
COMPLETE AND SEND THE INSPECTION REPORT
SHEET
0.75
0.75
5.00
ICN-A300-A-53XX6175-A-FAPE3-00019-A-004-01

### Page 52

A300-600
SERVICE BULLETIN
APPENDIX
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 52
B. REPORTING SHEET
TITLE: FUSELAGE - FUSELAGE - AFT SECTION - INSPECT DOOR FRAME HOLES
AT FR56A, FR57A & FR73A
MODIFICATION No.: None
(1) SB Reporting status
This Service Bulletin will only be incorporated into affected customized Maintenance
and Flight Operations Products if it is duly reported to Airbus.
(2) GENERAL information
The SB Reporting policy is published in ISI 00.00.00135. This document provides
information regarding: the SB Reporting means and benefits, the update of
customized Maintenance Products and customized Flight Operations Products.
If this Service Bulletin has an operational impact, refer to paragraph "Flight Operations
Products" for further information on the update of affected Flight Operations Products.
(3) SB Reporting procedure
Standard practice to report SB is to use the online reporting application on
AirbusWorld.
Refer to ISI 00.00.00179:
- For complete information on reporting means to Airbus, Question 2 "What are
the standard practices for SB Reporting?"
- If this SB requires previous or simultaneous accomplishment of other SBs,
Question 3 "What about the reporting of prerequisite Service Bulletins?"
NOTE: ISI 00.00.00179 covers all the frequently asked questions about SB Reporting.
It is revised on a regular basis.

### Page 53

A300-600
SERVICE BULLETIN
APPENDIX
REV 00 May 28/14 A300-53-6175
REV 01 Dec 07/21 Page 53
C. 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 Bulletin.
We thank you for the time you have taken in completing this form.
Quality rating of this SB 4 3 2 1
Quality rating of the Accomplishment Instructions 4 3 2 1
Quality rating of the Illustrations 4 3 2 1
Is this SB easy to understand ? Y / N
NOTE: Please rate on a scale of 1 to 4, with 4 being the highest score
If you have 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 Applicability X T ooling X Preparation
X Reason X List of Materials
Operator Supplied
X Mod/Inspection
X Manpower X Kit content X T est
X References X Re-identification X Close-up
X Publication X Illustrations
X Industry Support
Comments :
Operator : Date :
Name/Title
Please return this form to :
AIRBUS
2, ROND POINT EMILE DEWOITINE
31700 BLAGNAC
FRANCE
Or via your Resident Customer Support Office.

---
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