# Airbus Service Bulletin A300-53-0246

Copy: Revision 08 ("SB A300-53-0246 R08"), 60 pages: PDF https://openairdocs.org/files/sha256/22/02/22026c7f729eb5dd4c23d2df52570e8d87a519099b5ceebafe2204e6a1e2f81b; text https://openairdocs.org/service-documents/airbus/a300-53-0246/file/22026c7f729e.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2017-0520; AD 2017-17-05 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: A300-53-0246
- Latest revision known: A300-53-0246, Revision 08, dated April 13, 2016 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/airbus/a300-53-0246

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

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

- [AD 2017-17-05](https://openairdocs.org/ad/2017-17-05.md), effective Sep 25, 2017: Revisions 06, 07 and 08
- [AD 2007-26-14](https://openairdocs.org/ad/2007-26-14.md), effective Feb 20, 2008: Revisions 03 and 06
- [AD 2003-06-04](https://openairdocs.org/ad/2003-06-04.md), effective May 1, 2003: Revision 03

Also cited in [2 proposed ADs](https://openairdocs.org/service-documents/airbus/a300-53-0246/proposed.md).

## Text (60 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2017-0520; AD 2017-17-05 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

@A300
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
MANDATORY
 MANDATORY
 MANDATORY
ATA SYSTEM: 53
TITLE: FUSELAGE - FRAME 47 - INSPECTION OF UPPER RADIUS.
MODIFICATION No.: None
This page transmits Revision No.08 of Service Bulletin No.A300-53-0246
ADDITIONAL WORK
**CONF ALL
No additional work is required by this revision for aircraft modified by any previous issue.
REASON
Revision No. 08 issued to replace the NTM procedure for ultrasonic inspection, NTM 53-15-29, Part 4
replaced by NTM 53-15-33, Part 4.
CHANGES
The main changes of this revision are:
- NTM 53-15-29 Part 4 replaced by NTM 53-15-33 Part 4,
- note in the paragraph Reason added,
- illustration updated,
- effectivity updated,
- minor changes applied.
NOTE
: Revised text and layout changes of this revision are not identified with revision bars.
SUMMARY
MODIFICATIONS
 Minor editorial or document structure change
 N
REASON/DESCRIPTION/OPERATIONAL
CONSEQUENCES
Minor editorial or document structure change
 N
GENERAL EVALUATION
 Minor editorial or document structure change
 N
MATERIAL PRICE INFORMATION
 Minor editorial or document structure change
 N
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 1
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
EFFECTIVITY
 Minor editorial or document structure change
 N
CONCURRENT REQUIREMENTS
 Minor editorial or document structure change
 N
REFERENCES / REPERCUSSIONS
 Minor editorial or document structure change
 N
NATURE OF THE WORK
 Minor editorial or document structure change
 N
MANPOWER
 Minor editorial or document structure change
 N
APPENDICES
 Minor editorial or document structure change
 N
Fig. A-FSAAA
 Minor editorial or document structure change
 N
Fig. A-FSAAA Sheet 01
 Minor editorial or document structure change
 N
PLANNING INFORMATION
EFFECTIVITY
 Minor editorial or document structure change
 N
Configuration definition
 Minor editorial or document structure change
 N
CONF 001
 Minor editorial or document structure change
 N
Material Effectivity
 Minor editorial or document structure change
 N
Minor editorial or document structure change
 N
CONCURRENT REQUIREMENTS
 Minor editorial or document structure change
 N
REASON
 Minor editorial or document structure change
 N
History
 Minor editorial or document structure change
 N
Objective/Action
 Minor editorial or document structure change
 N
Advantages
 Minor editorial or document structure change
 N
Operational/Maintenance
Consequences
Minor editorial or document structure change
 N
DESCRIPTION
 Minor editorial or document structure change
 N
COMPLIANCE
 Minor editorial or document structure change
 N
Classification
 Minor editorial or document structure change
 N
Accomplishment Timescale
 Minor editorial or document structure change
 N
APPROVAL
 Minor editorial or document structure change
 N
Minor editorial or document structure change
 N
MANPOWER
 Minor editorial or document structure change
 N
Minor editorial or document structure change
 N
WEIGHT AND BALANCE
 Minor editorial or document structure change
 N
ELECTRICAL LOAD DATA
 Minor editorial or document structure change
 N
REFERENCES
 Minor editorial or document structure change
 N
Minor editorial or document structure change
 N
PUBLICATION AFFECTED
 Minor editorial or document structure change
 N
Minor editorial or document structure change
 N
INTERCHANGEABILITY/MIXABILITY
 Minor editorial or document structure change
 N
SPARES
 Minor editorial or document structure change
 N
MATERIAL INFORMATION
MATERIAL - PRICE AND AVAILABILITY
 Minor editorial or document structure change
 N
Procurement Addresses
 Minor editorial or document structure change
 N
Price and Availability
 Minor editorial or document structure change
 N
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 2
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
INDUSTRY SUPPORT INFORMATION
 Minor editorial or document structure change
 N
LIST OF COMPONENTS
 Minor editorial or document structure change
 N
Kit 530246A01R03
 Minor editorial or document structure change
 N
Kit 530246A02R01
 Minor editorial or document structure change
 N
LIST OF MATERIALS - OPERATOR
SUPPLIED
Minor editorial or document structure change
 N
Consumable Materials
 Minor editorial or document structure change
 N
Consumable CMLA01
 Minor editorial or document structure change
 N
Components
 Minor editorial or document structure change
 N
Equipment
 Minor editorial or document structure change
 N
PARTS TO BE RE-IDENTIFIED BY
OPERATOR
Minor editorial or document structure change
 N
TOOLING
 Minor editorial or document structure change
 N
Tooling - Price and Availability
 Minor editorial or document structure change
 N
Tools
 Minor editorial or document structure change
 N
Special Tools
 Minor editorial or document structure change
 N
ACCOMPLISHMENT INSTRUCTIONS
TASK 530246- 832-801-001-INSPECTION
 Minor editorial or document structure change
 N
Task associated data - 001
 Minor editorial or document structure change
 N
Subtask 530246-900-002-001
 Minor editorial or document structure change
 N
Subtask 530246-832-003-001
 Minor editorial or document structure change
 N
Subtask 530246-941-001-001
 Minor editorial or document structure change
 N
Subtask 530246-832-004-001
 Minor editorial or document structure change
 N
Subtask 530246-832-007-001
 Minor editorial or document structure change
 N
Subtask 530246-700-001-001
 Minor editorial or document structure change
 N
Subtask 530246-832-008-001
 Minor editorial or document structure change
 N
Subtask 530246-942-001-001
 Minor editorial or document structure change
 N
TASK 530246- 833-802-001-REPAIR
 Minor editorial or document structure change
 N
Task associated data - 001
 Minor editorial or document structure change
 N
Subtask 530246-833-009-001
 Minor editorial or document structure change
 N
Subtask 530246-900-010-001
 Minor editorial or document structure change
 N
Subtask 530246-833-011-001
 Minor editorial or document structure change
 N
Subtask 530246-833-012-001
 Minor editorial or document structure change
 N
Subtask 530246-833-013-001
 Minor editorial or document structure change
 N
Subtask 530246-833-014-001
 Minor editorial or document structure change
 N
Subtask 530246-833-015-001
 Minor editorial or document structure change
 N
Subtask 530246-833-016-001
 Minor editorial or document structure change
 N
Subtask 530246-833-017-001
 Minor editorial or document structure change
 N
Subtask 530246-700-002-001
 Minor editorial or document structure change
 N
Subtask 530246-833-018-001
 Minor editorial or document structure change
 N
Fig. A-FBAAA
 Minor editorial or document structure change
 N
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 3
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
Fig. A-FBAAA Sheet 01
 Minor editorial or document structure change
 N
Fig. A-FBBAA
 Minor editorial or document structure change
 N
Fig. A-FBBAA Sheet 01
 Minor editorial or document structure change
 N
Fig. A-FBBAA Sheet 02
 Minor editorial or document structure change
 N
Fig. A-FBCAA
 Minor editorial or document structure change
 N
Fig. A-FBCAA Sheet 01
 Minor editorial or document structure change
 N
Fig. A-FBDAA
 Minor editorial or document structure change
 N
Fig. A-FBDAA Sheet 01
 Minor editorial or document structure change
 N
Fig. A-FBDAA Sheet 02
 Minor editorial or document structure change
 N
Fig. A-FBEAA
 Minor editorial or document structure change
 N
Fig. A-FBEAA Sheet 01
 Minor editorial or document structure change
 N
Fig. A-FBEAA Sheet 02
 Minor editorial or document structure change
 N
Fig. A-FBEAA Sheet 03
 Minor editorial or document structure change
 N
Fig. A-FBFAA
 Minor editorial or document structure change
 N
Fig. A-FBFAA Sheet 01
 Minor editorial or document structure change
 N
Fig. A-FBFAA Sheet 02
 Minor editorial or document structure change
 N
Fig. A-FBGAA
 Minor editorial or document structure change
 N
Fig. A-FBGAA Sheet 01
 Minor editorial or document structure change
 N
Fig. A-FBGAA Sheet 02
 Minor editorial or document structure change
 N
Fig. A-FBGAA Sheet 03
 Minor editorial or document structure change
 N
Fig. A-FFAAA
 Minor editorial or document structure change
 N
Fig. A-FFAAA Sheet 01
 Minor editorial or document structure change
 N
Fig. A-FFAAA Sheet 02
 Minor editorial or document structure change
 N
Appendix 1 - Inspection Report
APPENDIX CONTENT
 Minor editorial or document structure change
 N
Fig. A-FRAAA
 Minor editorial or document structure change
 N
Fig. A-FRAAA Sheet 01
 Minor editorial or document structure change
 N
Fig. A-FRAAA Sheet 02
 Minor editorial or document structure change
 N
Fig. A-FRAAA Sheet 03
 Minor editorial or document structure change
 N
FILLING INSTRUCTIONS
This Service Bulletin has been generated electronically and is reissued as a complete document.
Replace the complete document.
Put this Revision Transmittal Sheet in front of the Service Bulletin.
HISTORY OF PREVIOUS REVISIONS
This is only applicable for Revision No. 02 and subsequent. If information is required for Revisions
issued previous to this, please check your copies of Revision Transmittal Sheets or contact AIRBUS.
Revision No. 02 issued to modify technical information in Para. Reason/description/operational
consequences.
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 4
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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@A300
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
Revision No. 03 issued to inform the operators to add the threshold and interv al values in flight cycles
(FC) and to modify the corresponding values in flight hours (FH). In the case of ultrasonic inspection, 3
solutions are proposed :
crack included between 8mm (0.315in.) and 20mm (0.79in.)
crack included between 20mm (0.79in.) and 50mm (1.97in.), visual detailed inspection and eddy current
inspection added
crack more than 50mm (1.97in.).
Revision No. 04 is issued to inform the operators :
of a change in the inspection intervals depending on the length of the crack found
in the case when no crack is discovered, the accesses are modified (fairing attachment profile : kit A02,
keel beam) to allow inspecting a larger area. In some cases, it was found that the access was not
sufficient.
Revision No. 05 issued in order to change the Airworthiness Directive/Consigne de Navigabilite
reference and modify the rework to be made to the keel beam.
Revision No. 06 issued to modify the flow chart and the inspection threshold and interval.
Revision No. 07 issued to update the effectivity, to modify the threshold and interval table and to
redefine the crack measurement criterion.
REVISION SEQUENCE
ORIGINAL: Nov 30/89
REVISION No.: 01 - Mar 21/92
REVISION No.: 02 - Aug 23/93
REVISION No.: 03 - Apr 11/01
REVISION No.: 04 - Nov 12/02
REVISION No.: 05 - Jan 19/04
REVISION No.: 06 - Oct 19/05
REVISION No.: 07 - Sep 09/08
REVISION No. : 08 - Apr 13/16
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 5
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
This Page Intentionally Left Blank
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 6
5
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@A300
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 - FRAME 47 - INSPECTION OF UPPER RADIUS.
**CONF ALL
MODIFICATIONS
None
REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES
The current requirements are issued within the evaluation made for the A300 Supplemental Structural
Inspection Program (SSIP-SSD 53-65-16) to comply with FAA advisory circular 91-56 and CAA
airworthiness Notice 89.
During A300 full scale fatigue test, cracks were found at 48,000 simulated flights on left and right upper
radius at Frame 47 and at 18,000 flights on in-service aircraft.
This Service Bulletin allows detecting and monitoring possible cracks at Frame 47 forward fitting.
Undetected or non monitored cracks could propagate to the rear fitting and consequently reduce the
residual strength of the aircraft.
Accomplishment of this Service Bulletin will allow monitoring structure cracking until accomplishment at
Frame 47 repair (Service Bulletin No. A300-53-0370).
NOTE
: Until the new NTM 53-15-33 is published, please refer to OIT 999.0168/15 where NTM
procedure is attached.
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.
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 1
5
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SERVICE BULLETIN
SUMMARY
MATERIAL PRICE INFORMATION
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
 QTY PER
A/C
PRICE PER
A/C (USD)
MAIN PARTS
Kit 530246A01R03
 2
 2,760.00
 Pins, Bolt, Nuts and Washer
Kit 530246A02R01
 1
 240.00
 Splices and Rivets
TOTAL
 3,000.00
EFFECTIVITY
This Service Bulletin is applicable to this (these) operator(s) :
001 22P 81T AFG CEL F2I IAW IRA IRM MSR RUN TIW TNO
CONCURRENT REQUIREMENTS
None
REFERENCES / REPERCUSSIONS
TFU
 53.15.00.046
OEB
 None
AOT
 A300-53A0362
SIL
 None
ISI
 None
LINE MAINTENANCE AFFECTED
 No
LIFE LIMIT
 None
NATURE OF THE WORK
AIRCRAFT
 YES
EQUIPMENT
 NO
HARD
 NO
SOFT
 NO
OBRM
 NO
MANPOWER
Task 530246-832-801-001: INSPECTION
TOTAL MANHOURS
 19.00
ELAPSED TIME (HOURS)
 19.00
Task 530246-833-802-001: REPAIR
TOTAL MANHOURS
 21.00
ELAPSED TIME (HOURS)
 21.00
APPENDICES
Appendix 1 - Inspection Report
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 2
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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SERVICE BULLETIN
SUMMARY
**CONF ALL
STA2982/FR47
FORWARD FITTING
OF FR47
NOTE : RH SHOWN, SAME LOCATION FOR LH
INSPECTED AREA
A
A
A
A_SB_530246_5_SAAA_01_00
Figure A-FSAAA - Sheet 01
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 3
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SERVICE BULLETIN
SUMMARY
This Page Intentionally Left Blank
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 4
5
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@A300
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 - FRAME 47 - INSPECTION OF UPPER RADIUS.
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
B2-203 B2K-3C B4-103 B4-203 B4-2C C4-203 F4-203
(2) Effectivity by MSN
0045 0075 0080 0090 0105 0107 0126 0139 0151-0152 0154 0157 0160 0173 0175
0180 0183 0185 0203 0210 0212 0218 0220 0226-0227 0234-0236 0239 0244 0247
0255-0256 0259 0261 0274 0277 0292 0299 0302
(3) Effectivity by Operator
The Operator/MSN relationship is provided for information only and is correct at the time
of issue in accordance with the information available to AIRBUS. Any future changes
resulting from transfer of an aircraft from one operator to another will not be reflected in
this list unless the Service Bulletin is revised for another reason.
OPERATOR
 MSN
001
 0203 0218
22P
 0236
81T
 0126 0157 0277 0292
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 1
5
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SERVICE BULLETIN
OPERATOR
 MSN
AFG
 0180
CEL
 0212
F2I
 0235
IAW
 0239
IRA
 0080 0139 0151 0173 0185 0226 0256 0299 0302
IRM
 0090 0160 0175 0244
MSR
 0255
RUN
 0075 0105 0107 0154 0183
TIW
 0152 0220 0234 0259 0261 0274
TNO
 0045 0210 0227 0247
(4) Configuration by MSN
MSN
 CONFIGURATION
0045 0075 0080 0090 0105 0107 0126 0139 0151 0152 0154
0157 0160 0173 0175 0180 0183 0185 0203 0210 0212 0218
0220 0226 0227 0234 0235 0236 0239 0244 0247 0255 0256
0259 0261 0274 0277 0292 0299 0302
001
(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
Kit 530246A01R03
 2
Kit 530246A02R01
 1
Consumable CMLA01
 As required
B. CONCURRENT REQUIREMENTS
None
C. REASON
(1) History
The current requirements are issued within the evaluation made for the A300
Supplemental Structural Inspection Program (SSIP-SSD 53-65-16) to comply with FAA
advisory circular 91-56 and CAA airworthiness Notice 89.
During A300 full scale fatigue test, cracks were found at 48,000 simulated flights on left
and right upper radius at Frame 47 and at 18,000 flights on in-service aircraft.
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 2
5
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SERVICE BULLETIN
(2) Objective/Action
This Service Bulletin allows detecting and monitoring possible cracks at Frame 47
forward fitting. Undetected or non monitored cracks could propagate to the rear fitting
and consequently reduce the residual strength of the aircraft.
(3) Advantages
Accomplishment of this Service Bulletin will allow monitoring structure cracking until
accomplishment at Frame 47 repair (Service Bulletin No. A300-53-0370).
(4) Operational/Maintenance Consequences
NOTE
: Until the new NTM 53-15-33 is published, please refer to OIT
999.0168/15 where NTM procedure is attached.
D. DESCRIPTION
To accomplish this Service Bulletin it is necessary to :
Task 530246-832-801-001: INSPECTION
(1) Inspection
Task 530246-833-802-001: REPAIR
(1) If no crack, cut and remove the fairing attachment profile between FR47 and FR48
(LH and RH sides)
(2) If no crack, trim the keel beam at FR47
(3) If crack more than 8 mm (0.315in.), remove and modify the sealing fitting Item (13) or
(14)
(4) If crack more than 8 mm (0.315in.) and if it was removed during step 3, install the
sealing fitting Item (13) or (14)
(5) If it was removed during step 1, install the fairing attachment profile between FR47
and FR48 (LH and RH sides)
E. COMPLIANCE
(1) Classification
MANDATORY: Service Bulletin must be accomplished.
(2) Accomplishment Timescale
- So that any crack is left unrepaired and is monitored during the remaining life of the
aircraft, it is mandatory to report all inspection results including the repetitive one to
AIRBUS SEES1. This report must be done by usin g the record form attached.
- Refer to the SSID Section 9 for instructions on dealing with touch and go flights.
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 3
5
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SERVICE BULLETIN
- Inspection requirements given in this Service Bulletin are for unrepaired areas,
unless otherwise stated.
NOTE
: In case of crack finding, additional inspections are to be accomplished in
case of an abnormal loading event.
In case of hard landing or a flight in excessive turbulence event obey the
inspection requirement of this Service Bulletin within 3 months and report
this event to AIRBUS SEES1 or AIRTAC.
However if a flight in excessive turbulence or a hard landing event
occurs during the 3 months of grace period (with inspection not yet
accomplished), contact AIRBUS SEES1 or AIRTAC before next flight.
For the threshold and intervals of the inspection: Refer to Fig. A-FBAAA
.
European Aviation Safety Agenc y (EASA) r egulatory action is expec ted for this Service
Bulletin by the issue of a Consigne de Navigabilite (CN) (Airworthiness Directive (AD)). It
is anticipated that the CN will confirm the thresholds and intervals given above but
reference should be made to the CN for confirmation of the mandated accomplishment
timescale.
F. APPROVAL
Approved under EASA Design Organisation Approval No. EASA.21J.031.
If an aircraft listed in the effectivity has a modification or repair embodied that is not of
AIRBUS origin, and which affects the content of this Service Bulletin, the operator is
responsible for obtaining approval by its airworthiness authority for any adaptation necessary
before incorporation of the Service Bulletin.
G. 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 530246-832-801-001: INSPECTION
Get Access
 6.00
On Aircraft
Inspection
 2.00
Tests
 4.00
Close-Up
 7.00
TOTAL MANHOURS
 19.00
ELAPSED TIME (HOURS)
 19.00
Task 530246-833-802-001: REPAIR
On Aircraft
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 4
5
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@A300
SERVICE BULLETIN
Task 530246-833-802-001: REPAIR
If no crack, cut and remove the fairing attachment
profile between FR47 and FR48 (LH and RH sides)
6.00
If no crack, trim the keel beam at FR47
 4.00
If crack more than 8 mm (0.315in.), remove and modify
the sealing fitting Item (13) or (14)
4.00
If crack more than 8 mm (0.315in.) and if it was
removed during step 3, install the sealing fitting Item
(13) or (14)
3.00
If it was removed during step 1, install the fairing
attachment profile between FR47 and FR48 (LH and
RH sides)
3.00
Tests
 1.00
TOTAL MANHOURS
 21.00
ELAPSED TIME (HOURS)
 21.00
H. WEIGHT AND BALANCE
Not Changed
I. ELECTRICAL LOAD DATA
Not Changed
J. REFERENCES
Aircraft Maintenance Manual (AMM)
 06-21-53 06-41-52 06-41-53
06-41-57 20-21-12 24-00-00
25-13-31 25-21-00 25-22-11
25-23-31 25-28-11 28-00-00
28-10-00 28-11-00 28-11-14
28-22-00 52-10-00 53-22-11
Consumable Material List (CML)
Elec. Std. Practices Manual (ESPM)
 20-55-00
Non Destructive Test Manual (NTM)
 53-15-29 53-15-33
Service Bulletin (SB)
 A300-28-0033
A300-53-0370
Standards Manual (SM)
Structural Repair Manual (SRM)
 51-30-31 51-30-38 51-30-43
51-30-50 51-40-12 51-40-20
K. PUBLICATION AFFECTED
Maintenance Planning Document (MPD)
 536516-0606-1
536516-0606-4
536516-0606-6
L. INTERCHANGEABILITY/MIXABILITY
Not Applicable
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 5
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SERVICE BULLETIN
M. SPARES
None
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 6
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SERVICE BULLETIN
2. MATERIAL INFORMATION
**CONF ALL
A. MATERIAL - PRICE AND AVAILABILITY
(1) Procurement Addresses
Customers with aircraft shown in the effectivity of this Service Bulletin should send a
purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is:
Kit 530246A01R03
Kit 530246A02R01
AIRBUS Material, Logistics and Suppliers
ATP II B
Hein-Sass-Weg 24
21129 HAMBURG
GERMANY
For ordering by internet:
http://spares.airbus.com
For ordering by E-mail: airbus.kit@airbus.com
Telephone Hotlines:
A350/A380: +494074351775
A330/340, A300/310: +49 40 743 51616
A318/319/320/321: +49 40 743 51660
(2) Price and Availability
Kit 530246A01R03
Cost
 1,380.00 USD
Availability
 90 calendar days from receipt of order
The availability given above is the standard lead time from the date of your purchase
order. If items are required before this time, please include a retrofit planning schedule
with your order so that we can try to comply with your requirements.
The sales terms (costs and availability) are estimated in relation to economic conditions.
The latest valid price and lead time for ordering purposes shall be obtained through the
AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.
Kit 530246A02R01
Cost
 240.00 USD
Availability
 90 calendar days from receipt of order
The availability given above is the standard lead time from the date of your purchase
order. If items are required before this time, please include a retrofit planning schedule
with your order so that we can try to comply with your requirements.
The sales terms (costs and availability) are estimated in relation to economic conditions.
The latest valid price and lead time for ordering purposes shall be obtained through the
AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.
B. INDUSTRY SUPPORT INFORMATION
AIRBUS will not provide industry support for accomplishment of this Service Bulletin.
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 7
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SERVICE BULLETIN
C. LIST OF COMPONENTS
Kit 530246A01R03
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
1
 NSA5351V5-23
 1
 Pin
1
 NSA5351V5-26
 1
 Pin
2
 NSA5351V6-23
 1
 Pin
2
 NSA5351V6-26
 1
 Pin
3
 NSA5351V7-22
 1
 Pin
4
 NSA5351V7-24
 1
 Pin
6
 NSA5351V9-36
 1
 Pin
6
 NSA5351V9-37
 1
 Pin
7
 NAS1726-5E
 1
 Nut
8
 NAS1726-6E
 1
 Nut
9
 NAS1726-7E
 2
 Nut
11
 NAS1726-9E
 1
 Nut
12
 NSA5354-716
 1
 Washer
NOTE
: If you find part numbers of hardware components in the related kit(s) which
you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,
refer to Standards Manual (SM). The SM will give you the correct part number
to part number relationship.
NOTE
: Kit 530246A01R03 concerns the modification of sealing fitting in case of crack
length between 8mm (0.315in.) and 50mm (1.97in.) for one side only.
Kit 530246A02R01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
13
 A5351008420895
 1
 Splice
14
 A5351008420995
 1
 Splice
15
 ASNA2050DCJ3620
 32
 Rivet
16
 ASNA2051DCJ3620
 8
 Rivet
17
 LN9198-4020B
 12
 Rivet
18
 VFN15202-4420C
 4
 Rivet
NOTE
: If you find part numbers of hardware components in the related kit(s) which
you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,
refer to Standards Manual (SM). The SM will give you the correct part number
to part number relationship.
NOTE
: Kit 530246A02R01 concerns the modification of the fairing attachment profile
between FR47 and FR48 (LH and RH sides) in case of no crack found.
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 8
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D. LIST OF MATERIALS - OPERATOR SUPPLIED
(1) Consumable Materials
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO CML
MAT. No.
QTY PER A/C
 SEE
NOTES
Fuel Tank Sealant Polysulfide
 09-001
 As required
Fuel Tank Sealant Polysulfide
 09-002
 As required
Brushable Fuel Resistant Coating
 09-007
 As required
Corrosion Inhibiting Brush
Consistency
09-013
 As required
Adhesion Promoter For Polysulfide
Sealant
09-028
 As required
Solvant General Purpose
 11-026
 As required
Anti-Corrosion Primer
(Polyurethane)
16-001
 As required
Polyurethane Topcoatgrey (For
Internal Applic.)
16-002
 As required
External Top Coat (Polyurethane)
 16-018
 As required
Wash Primer
 16-020
 As required
(2) Components
None
(3) Equipment
None
E. PARTS TO BE RE-IDENTIFIED BY OPERATOR
None
F. TOOLING
(1) Tooling - Price and Availability
None
(2) Tools
To accomplish this Service Bulletin it is necessary to use the following tools and
equipment:
- Equipment and materials for inspection on upper radius of forward fitting of Frame
47 as per NTM 53-15-29, Part 6 and NTM 53-15-33, Part 4.
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 9
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SERVICE BULLETIN
(3) Special Tools
None
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 10
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SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS
Task 530246-832-801-001 - IN SPECTION
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.
IF THERE IS CONTAMINATION REFER TO ESPM 20-55-00.
Task Associated Data
Manpower
TOTAL MANHOURS
 19.00
ELAPSED TIME (HOURS)
 19.00
A. GENERAL
(1) Subtask 530246-900-002-001 - Documentation
Manpower Resources
Skills
 NON SPECIFIC
Write in the applicable aircraft records that you have done all the work given in the
Service Bulletin.
B. PREPARATION
(1) Subtask 530246-832-003-001 - Access for Eddy Current inspection only
Manpower Resources
Skills
 NON SPECIFIC
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 11
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SERVICE BULLETIN
Material necessary to do the job
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Solvent General Purpose
 11-026
 As required
References
Aircraft Maintenance Manual (AMM)
 06-41-57, Page Block 001
24-00-00, Page Block 301
28-00-00
28-10-00, Page Block 301
28-11-14, Page Block 401
28-22-00, Page Block 301
Service Bulletin (SB)
 A300-28-0033
Fig. A-FBCAA
Location of Area of Ultrasonic Inspection
Sheet 01
(a) Make sure that the aircraft is electrically grounded (Refer to AMM 24-00-00, Page
Block 301).
(b) Put access platform(s) in position.
(c) Remove wing root upper fillet fairings 577BT and 677BT (Refer to AMM 06-41-57,
Page Block 001).
(d) If necessary, remove the wing root upper fillet fairings 577CT and 677CT (Refer to
AMM 06-41-57, Page Block 001).
(e) Remove PR sealant and clean working areas using
Solvent General
Purpose
11-026 As required
NOTE
: To remove PR sealant, use exclusively a non-metallic spatula. In
the event of scratches, polish surface and perform protection.
(2) Subtask 530246-941-001-001 - Access for ultrasonic inspection only
Manpower Resources
Skills
 NON SPECIFIC
Material necessary to do the job
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Solvant General Purpose
 11-026
 As required
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 12
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SERVICE BULLETIN
References
Aircraft Maintenance Manual (AMM)
 06-21-53, Page Block 401
25-21-00, Page Block 401
25-22-11, Page Block 401
25-23-31, Page Block 401
25-28-11, Page Block 401
52-10-00, Page Block 001
Fig. A-FBCAA
Location of Area of Ultrasonic Inspection
Sheet 01
(a) Open the passenger/crew door 831 (Refer to AMM 52-10-00 Page Block 001).
(b) Remove row of passenger seats at Frame 47 on left or/and right side (Refer to
AMM 25-21-00 Page Block 401).
(c) Remove carpet floor covering (Refer to AMM 25-28-11 Page Block 401).
(d) Remove lower sidewall panels at Frame 47 on left or/and right side (Refer to AMM
25-23-31 Page Block 401).
(e) Remove heat and sound insulation blankets at Frame 47 on left or/and right side
(Refer to AMM 25-22-11 Page Block 401).
(f) In zones 241 or/and 242, remove floor panels AJF, APF or/and ACE, AGF (Refer to
AMM 06-21-53 Page Block 401).
(g) Remove PR sealant and clean working areas using:
Solvant General
Purpose
11-026 As required
NOTE
: To remove PR sealant, use exclusively a non-metallic spatula. In
the event of scratches, polish surface and perform protection.
NOTE
: Fasteners of holes A and B (refer to Figure Fig. A-FBCAA
) have to
be removed (and retain) at each repetitive ultrasonic inspection.
If the hole(s) is (are) damaged, contact AIRBUS.
If the holes are free of damage:
- If the fasteners are not damaged, same fasteners can be re-
installed.
- If the fasteners are damaged, new fasteners with same part
number (same diameter, same length) have to be re-installed.
C. PROCEDURE
NOTE
: The following operations are described for one side only. Repeat the same
operations for the other side.
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 13
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SERVICE BULLETIN
(1) Subtask 530246-832-004-001 - Inspection
Manpower Resources
Manhours
 2.00
Minimum number of person
 1
Subtask elapsed time
 2.00
Skills
 NON SPECIFIC
References
Fig. A-FBBAA
Location of Area of Eddy Current
Inspection
Sheet 01
Sheet 02
Fig. A-FBCAA
Location of Area of Ultrasonic Inspection
Sheet 01
Fig. A-FBDAA
Location of Area of Detailed Visual
Inspection
Sheet 01
Sheet 02
Fig. A-FFAAA
Flow Chart
Sheet 01
Sheet 02
(a) For the inspection area, refer to Fig. A-FBBAA
, Fig. A-FBCAA
 and Fig. A-FBDAA
(b) Perform special detailed inspection by Eddy Current on upper radius on left and
right forward fitting of Frame 47.
(Refer to Fig. A-FFAAA
)
NOTE
: Depending on the first Eddy Current inspection as per Fig. A-
FFAAA
, some additional inspections like HFEC, US or detailed
visual inspection are also necessary.
(c) For the inspection report, refer to Appendix 1.
D. TEST
(1) Subtask 530246-832-007-001 - Close-up before the test
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 25-13-31, Page Block 401
25-21-00, Page Block 401
25-22-11, Page Block 401
25-23-31, Page Block 401
(a) Install heat and sound insulation blankets at Frame 47 on LH or/and RH sides
(Refer to AMM 25-22-11, Page Block 401).
(b) Install lower sidewall panels at Frame 47 on LH or/and RH sides (Refer to AMM
25-23-31 Page Block 401 and Refer to AMM 25-13-31 Page Block 401).
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 14
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SERVICE BULLETIN
(c) Install row of passenger seats at Frame 47 on LH or/and RH sides (Refer to AMM
25-21-00 Page Block 401).
(2) Subtask 530246-700-001-001 - Testing
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 25-21-00, Page Block 401
25-23-31, Page Block 401
(a) Do the test after removal/installation of the passenger seats (Refer to AMM
25-21-00 Page Block 401), if applicable.
(b) Do the test after removal/installation of the lower sidewall panels at Frame 47 on
LH or/and RH sides (Refer to AMM 25-23-31 Page Block 401), if applicable.
E. CLOSE-UP
(1) Subtask 530246-832-008-001 - Close-up after Eddy Current inspection
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 06-41-57, Page Block 001
53-22-11, Page Block 401
(a) Make sure that the work areas are clean and clear of tools and other items of
equipment.
(b) Install wing to fuselage fillets 577BT and 677BT (Refer to AMM 53-22-11 Page
Block 401).
(c) If removed, install wing to fuselage fillets 577CT and 677CT (Refer to AMM
06-41-57, Page Block 001).
(d) Remove the access platforms.
(e) Restore the systems and the aircraft to normal operating condition.
(2) Subtask 530246-942-001-001 - Close-up after ultrasonic inspection
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 06-41-52, Page Block 001
06-41-53, Page Block 001
25-28-11, Page Block 401
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 15
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(a) In zones 241 or/and 242, install floor panels DG and HG or GG and MG (Refer to
AMM 06-41-53, Page Block 001).
(b) Install carpet floor covering (Refer to AMM 25-28-11, Page Block 401).
(c) Close access door 831 or 841 (Refer to AMM 06-41-52, Page Block 001).
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 16
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SERVICE BULLETIN
Task 530246-833-802-001 - REPAIR
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.
IF THERE IS CONTAMINATION REFER TO ESPM 20-55-00.
Task Associated Data
Manpower
TOTAL MANHOURS
 21.00
ELAPSED TIME (HOURS)
 21.00
A. GENERAL
(1) Subtask 530246-833-009-001 - Standard Practices
Manpower Resources
Skills
 NON SPECIFIC
Material necessary to do the job
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Anti-Corrosion Primer
(Polyurethane)
16-001
 As required
Polyurethane Topcoatgrey
(For Internal Applic.)
16-002
 As required
Wash Primer
 16-020
 As required
References
Aircraft Maintenance Manual (AMM)
 20-21-12, Page Block 001
Consumable Material List (CML)
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 17
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References
Structural Repair Manual (SRM)
 51-30-31
51-30-38
51-30-43
51-30-50
51-40-12
51-40-20
Fig. A-FBCAA
Location of Area of Ultrasonic Inspection
Sheet 01
(a) For the specification of the material numbers (Mat. No.), refer to the CML.
(b) SRM references:
1
 Fastener hole and drill data (Refer to SRM 51-30-38).
2
 Fastener oversize (Refer to SRM 51-30-31).
3
 For alternative and substitute fasteners (Refer to SRM 51-30-31).
4
 Fastener spacing and margin data (Refer to SRM 51-30-50).
5
 Paint coating (Refer to SRM 51-40-12).
6
 Sealing process (Refer to SRM 51-40-20).
7
 Countersinking (Refer to SRM 51-30-43).
(c) For the modification of the sealing fitting and the upper cross fitting.
1
 Renew protective finish using
Anti-Corrosion
Primer
(Polyurethane)
16-001 As required
and
Polyurethane
Topcoatgrey (For
Internal Applic.)
16-002 As required
and
Wash Primer 16-020 As required
2
 Torque the standard threaded fasteners (Refer to AMM 20-21-12, Page Block
001).
(2) Subtask 530246-900-010-001 - Documentation
Manpower Resources
Skills
 NON SPECIFIC
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 18
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SERVICE BULLETIN
Write in the applicable aircraft records that you have done all the work given in the
Service Bulletin.
B. PREPARATION
(1) Subtask 530246-833-011-001 - Access to modification of sealing fitting
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 28-00-00
28-10-00, Page Block 301
28-11-14, Page Block 401
28-22-00, Page Block 301
Service Bulletin (SB)
 A300-28-0033
Fig. A-FBCAA
Location of Area of Ultrasonic Inspection
Sheet 01
WARNING
: MAKE CERTAIN THAT SAFETY PRECAUTIONS REGARDING
ACCESS TO AND WORKING IN CENTER FUEL TANK ARE STRICTLY
COMPLIED WITH (Refer to AMM 28-00-00).
(a) Access to modification of sealing fitting.
1
 For B4 type, defuel center tank (Refer to AMM 28-22-00 Page Block 301) and
degas it (Refer to AMM 28-10-00 Page Block 301).
2
 For A/C without modification No. 01511S02240 A300-28-0033 remove vapor
seals in concerned areas.
3
 In center wing box, open access doors 147AZ or/and 148AZ (Refer to AMM
28-11-14 Page Block 401).
C. PROCEDURE
NOTE
: The following operations are described for one side only. Repeat the same
operations for the other side.
NOTE
: Steps 1 and 2 are not required if a crack has already been detected during
previous inspection in accordance with this SB or AOT A300-53A0362.
(1) Subtask 530246-833-012-001 - If no crack, cut and remove the fairing attachment
profile between FR47 and FR48 (LH and RH sides)
Manpower Resources
Manhours
 6.00
Minimum number of person
 1
Subtask elapsed time
 6.00
Skills
 NON SPECIFIC
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 19
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References
Fig. A-FBEAA
Cutting of fairing attachment profile
between FR47 and FR48
Sheet 01
Sheet 02
Sheet 03
(a) Between Frame 47 and Frame 48, cut fairing attachment profile (Refer to Fig. A-
FBEAA Sheet 02
 and Fig. A-FBEAA Sheet 03
 ).
(b) Remove the fairing attachment profile (Refer to Fig. A-FBEAA Sheet 02
 and Fig. A-
FBEAA Sheet 03
).
NOTE
: For the repetitive inspection, it is necessary to remove rivets Items
15, 16, 17 and 18 (the rivets Items 15 and 16 are to be removed
only on the forward splice part).
(2) Subtask 530246-833-013-001 - If no crack, trim the keel beam at FR47
Manpower Resources
Manhours
 4.00
Minimum number of person
 1
Subtask elapsed time
 4.00
Skills
 NON SPECIFIC
Material necessary to do the job
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Solvant General Purpose
 11-026
 As required
Anti-Corrosion Primer
(Polyurethane)
16-001
 As required
Wash Primer
 16-020
 As required
References
Structural Repair Manual (SRM)
 51-40-12
51-40-20
Fig. A-FBFAA
FR47 Upper Surface, Trimming of Keel
Beam
Sheet 01
Sheet 02
(a) Perform trimming 10 mm (0.394in.) parallel to existing radius 65 mm (2.56in.) and
tangential to minimum edge distance at both holes (shown with circle in figure Fig.
A-FBFAA Sheet 02
).
NOTE
: A metallic foil should be used to avoid damage to the structure
behind keel beam.
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 20
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(b) Clean and protect trimmed area with
Solvant General
Purpose
11-026 As required
and
Wash Primer 16-020 As required
and
Anti-Corrosion
Primer
(Polyurethane)
16-001 As required
1
 Paint coating : Refer to SRM 51-40-12
2
 Sealing process : Refer to SRM 51-40-20
(3) Subtask 530246-833-014-001 - If crack more than 8 mm (0.315in.), remove and
modify the sealing fitting Item (13) or (14)
Manpower Resources
Manhours
 4.00
Minimum number of person
 1
Subtask elapsed time
 4.00
Skills
 NON SPECIFIC
Material necessary to do the job
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Anti-Corrosion Primer
(Polyurethane)
16-001
 As required
Polyurethane Topcoatgrey
(For Internal Applic.)
16-002
 As required
Wash Primer
 16-020
 As required
References
Fig. A-FBGAA
Modificatin of Sealing Fitting and Sealing
Shim
Sheet 01
Sheet 02
Sheet 03
(a) Remove sealing fitting.
1 Sealing fitting (LH side) Item (13) Retain
or
1 Sealing fitting (RH side) Item (14) Retain
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 21
5
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### Page 32

@A300
SERVICE BULLETIN
1 Bolt Item (1) Discard
1 Bolt Item (2) Discard
1 Bolt Item (3) Discard
1 Bolt Item (4) Discard
1 Bolt Item (6) Discard
1 Nut Item (7) Discard
1 Nut Item (8) Discard
1 Nut Item (9) Discard
1 Nut Item (11) Discard
(b) Removal of sealing shim.
1 Sealing shim (LH side) Item (15) Discard
or
1 Sealing shim (RH side) Item (16) Discard
(c) Modify sealing fitting as per views D, E and F of the figure Fig. A-FBGAA
.
(d) Perform protection using
Anti-Corrosion
Primer
(Polyurethane)
16-001 As required
and
Polyurethane
Topcoatgrey (For
Internal Applic.)
16-002 As required
and
Wash Primer 16-020 As required
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 22
5
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### Page 33

@A300
SERVICE BULLETIN
(4) Subtask 530246-833-015-001 - If crack more than 8 mm (0.315in.) and if it was
removed during step 3, install the sealing fitting Item (13) or (14)
Manpower Resources
Manhours
 3.00
Minimum number of person
 1
Subtask elapsed time
 3.00
Skills
 NON SPECIFIC
Material necessary to do the job
Kit 530246A01R03
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
1
 NSA5351V5-23
 1
 Pin
1
 NSA5351V5-26
 1
 Pin
2
 NSA5351V6-23
 1
 Pin
2
 NSA5351V6-26
 1
 Pin
3
 NSA5351V7-22
 1
 Pin
4
 NSA5351V7-24
 1
 Pin
6
 NSA5351V9-36
 1
 Pin
6
 NSA5351V9-37
 1
 Pin
7
 NAS1726-5E
 1
 Nut
8
 NAS1726-6E
 1
 Nut
9
 NAS1726-7E
 2
 Nut
11
 NAS1726-9E
 1
 Nut
12
 NSA5354-716
 1
 Washer
NOTE
: Kit 530246A01R03 concerns the modification of sealing fitting in case of
crack length between 8mm (0.315in.) and 50mm (1.97in.) for one side
only.
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Fuel Tank Sealant
Polysulfide
09-001
 As required
Fuel Tank Sealant
Polysulfide
09-002
 As required
Brushable Fuel Resistant
Coating
09-007
 As required
Adhesion Promoter For
Polysulfide Sealant
09-028
 As required
Solvant General Purpose
 11-026
 As required
References
Fig. A-FBGAA
Modificatin of Sealing Fitting and Sealing
Shim
Sheet 01
Sheet 02
Sheet 03
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 23
5
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### Page 34

@A300
SERVICE BULLETIN
(a) Check the good quality of bores and install sealing fitting modified.
Fig. A-FBGAA
1 Sealing fitting (LH side) Item (13)
or
1 Sealing fitting (RH side) Item (14)
1 Bolt NSA5351V5-26 Item 1
or
1 Bolt NSA5351V5-23 Item 1
1 Bolt NSA5351V6-26 Item 2
or
1 Bolt NSA5351V6-23 Item 2
1 Bolt NSA5351V7-22 Item 3
1 Bolt NSA5351V7-24 Item 4
1 Bolt NSA5351V9-36 Item 6
or
1 Bolt NSA5351V9-37 Item 6
1 Nut NAS1726-5E Item 7
1 Nut NAS1726-6E Item 8
2 Nut NAS1726-7E Item 9
1 Nut NAS1726-9E Item 11
1 Washer NSA5354-716 Item 12
NOTE
: Washer Item 12 to be adjusted.
(b) On sealing fitting, perform PR sealing using
Fuel Tank Sealant
Polysulfide
09-001 As required
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 24
5
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### Page 35

@A300
SERVICE BULLETIN
(c) Perform sealing on fasteners inside the center wing box (for B2 type only).
1
 Apply PR sealant using
Fuel Tank Sealant
Polysulfide
09-001 As required
(d) Perform sealing on fasteners inside the center wing box (for B4 type only).
1
 Clean area using
Solvant General
Purpose
11-026 As required
2
 Paint fasteners, including a small overlap using
Adhesion Promoter
For Polysulfide
Sealant
09-028 As required
3
 Apply PR sealant using
Fuel Tank Sealant
Polysulfide
09-001 As required
Fuel Tank Sealant
Polysulfide
09-002 As required
and
Brushable Fuel
Resistant Coating
09-007 As required
(e) Perform sealing on fasteners outside the center wing box.
1
 Apply PR sealant using
Fuel Tank Sealant
Polysulfide
09-001 As required
(5) Subtask 530246-833-016-001 - If it was removed during step 1, install the fairing
attachment profile between FR47 and FR48 (LH and RH sides)
Manpower Resources
Manhours
 3.00
Minimum number of person
 1
Subtask elapsed time
 3.00
Skills
 NON SPECIFIC
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 25
5
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### Page 36

@A300
SERVICE BULLETIN
Material necessary to do the job
Kit 530246A02R01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
13
 A5351008420895
 1
 Splice
14
 A5351008420995
 1
 Splice
15
 ASNA2050DCJ3620
 32
 Rivet
16
 ASNA2051DCJ3620
 8
 Rivet
17
 LN9198-4020B
 12
 Rivet
18
 VFN15202-4420C
 4
 Rivet
NOTE
: Kit 530246A02R01 concerns the modification of the fairing attachment
profile between FR47 and FR48 (LH and RH sides) in case of no crack
found.
Consumable CMLA01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Corrosion Inhibiting Brush
Consistency
09-013
 As required
External Top Coat
(Polyurethane)
16-018
 As required
Wash Primer
 16-020
 As required
References
Fig. A-FBEAA
Cutting of fairing attachment profile
between FR47 and FR48
Sheet 01
Sheet 02
Sheet 03
(a) Position
Refer to Fig. A-FBEAA
1 Splice (LH side) A5351008420895 Item 13
1 Splice (RH side) A5351008420995 Item 14
(b) Drill holes in fairing attachment profile to match existing holes in splices (at the first
inspection without crack only).
(c) On cut out and on countersinks apply
Wash Primer 16-020 As required
and
External Top Coat
(Polyurethane)
16-018 As required
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 26
5
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### Page 37

@A300
SERVICE BULLETIN
(d) Fix fairing attachment profile and coat fairing attachment profile and rivets with
Corrosion Inhibiting
Brush Consistency
09-013 As required
32 Rivets ASNA2050DCJ3620 Item 15
8 Rivets ASNA2051DCJ3620 Item 16
12 Rivets LN9198-4020B Item 17
4 Rivets VFN15202-4420C Item 18
D. TEST
(1) Subtask 530246-833-017-001 - Close-up before the test
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 28-11-14, Page Block 401
28-22-00, Page Block 301
(a) Close access doors 147AZ and 148AZ (Refer to AMM 28-11-14 Page Block 401).
(b) Refuel center tank (Refer to AMM 28-22-00 Page Block 301).
(2) Subtask 530246-700-002-001 - Testing
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 28-11-00, Page Block 501
28-11-14, Page Block 401
(a) Do the test after removal/installation of the manhole cover (Refer to AMM 28-11-14
Page Block 401).
(b) Do a leak test of the center tank (Refer to AMM 28-11-00 Page Block 501).
NOTE
: Do a check of the modified sealing fitting area for the leakage.
E. CLOSE-UP
(1) Subtask 530246-833-018-001 - Close-up after modification of the sealing fitting
Manpower Resources
Skills
 NON SPECIFIC
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 27
5
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### Page 38

@A300
SERVICE BULLETIN
References
Aircraft Maintenance Manual (AMM)
 24-00-00, Page Block 301
(a) Disconnect aircraft from ground (Refer to AMM 24-00-00 Page Block 301).
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 28
5
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### Page 39

@A300
SERVICE BULLETIN
**CONF ALL
FLIGHT CYCLES
THRESHOLD
TABLE 1
10000FC
INTERVAL
30 mm
(1.181 in)
40 mm
(1.574 in)D 40 mm(1.574 in) 50 mm(1.97 in)DD      30 mm(1.181 in)
NO
CRACK
A/C
4150FC 1400FC 750FC 250FC
TABLE 2
A300
L     8 mm
(0.315 in)
1400FC
L     8 mm
(0.315 in)
AND
L     8 mm
(0.315 in)
AND
L     8 mm
(0.315 in)
AND
A_SB_530246_5_BAAA_01_01
Figure A-FBAAA - Sheet 01
Threshold and Interval of Inspection
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 29
5
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### Page 40

@A300
SERVICE BULLETIN
**CONF ALL
AA
A
A
STA2982/FR47
FORWARD FITTING
OF FR47
NOTE : RH SHOWN, SAME LOCATION FOR LH
INSPECTED AREA
A_SB_530246_5_BBAA_01_00
Figure A-FBBAA - Sheet 01
Location of Area of Eddy Current Inspection
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 30
5
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### Page 41

@A300
SERVICE BULLETIN
**CONF ALL
L
D
CRACK SIZE
CHECK THE CRACK LENGTH
(EDDY CURRENT)
CHECK THE CRACK
DEPTH
(ULTRASONIC
INSPECTION)
A_SB_530246_5_BBAA_02_00
Figure A-FBBAA - Sheet 02
Location of Area of Eddy Current Inspection
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 31
5
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### Page 42

@A300
SERVICE BULLETIN
**CONF ALL
A
B
A
A
MOVEMENT AREA OF ULTRASONIC PROBE
KEEL DOUBLER
MODIFIED SEALING FITTING
FORWARD FITTING OF FR47
INTERNAL ANGLE
REAR SPAR DATUM
RIB 1 DATUM
CRUCIFORM
FITTING
A_SB_530246_5_BCAA_01_00
Figure A-FBCAA - Sheet 01
Location of Area of Ultrasonic Inspection
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 32
5
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### Page 43

@A300
SERVICE BULLETIN
**CONF ALL
A
A
FR47
RH SHOWN
LH SYMMETRICAL
AREA TO BE
INSPECTED
FROM CABIN
A_SB_530246_5_BDAA_01_00
Figure A-FBDAA - Sheet 01
Location of Area of Detailed Visual Inspection
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 33
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 44

@A300
SERVICE BULLETIN
**CONF ALL
FRAME 47 AFT FACE FROM MLG COMPARTMENT
RH SHOWN
LH SYMMETRICAL
AREA TO BE INSPECTED
A_SB_530246_5_BDAA_02_00
Figure A-FBDAA - Sheet 02
Location of Area of Detailed Visual Inspection
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 34
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 45 (OCR)

©A300
SERVICE BULLETIN
**CONF ALL
FR47
WING ROOT UPPER FILLET FAIRINGS
ALREADY REMOVED
FR46  FR47  FR48
A_SB_530246_5_BEAA_01_00
Figure A-FBEAA - Sheet 01
Cutting of fairing attachment profile between FR47 and FR48
5  DATE: Nov 30/89  SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16  Page: 35
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 46 (OCR)

©A300
SERVICE BULLETIN
**CONF ALL
LH SHOWN
RH SYMMETRICAL
FR46
D
- SPAR
FR48
18-
FAIRING ATTACHMENT PROFILE
TO BE CUT AT THIS POINT
A_SB_530246_5_BEAA_02_00
Figure A-FBEAA - Sheet 02
Cutting of fairing attachment profile between FR47 and FR48
5 DATE: Nov 30/89  SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16  Page: 36
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 47 (OCR)

© A300
SERVICE BULLETIN
**CONF ALL
D
LH SHOWN
RH SYMMETRICAL
1 mm
(0.039 in)
FR48
13 LH -
14 RH
TN HEAD ON VISIBLE SIDE
A_SB_530246_5_BEAA_03_00
Figure A-FBEAA - Sheet 03
Cutting of fairing attachment profile between FR47 and FR48
DATE: Nov 30/89  SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16  Page: 37
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 48 (OCR)

© A300
SERVICE BULLETIN
**CONF ALL
FR54
FR40
LH SHOWN
RH SYMMETRICAL
FR47
FR48
| LINE Z3
A_SB_530246_5_BFAA_01_00
Figure A-FBFAA - Sheet 01
FR47 Upper Surface, Trimming of Keel Beam
5 DATE: Nov 30/89  SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16  Page: 38
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 49 (OCR)

©A300
SERVICE BULLETIN
**CONF ALL
B
FR47
MINIMUM
EDGE DISTANCE 14.9 mm (0.586 in)
TRIMMING 10 mm
+  (0.394 in)
LINE Z1-Z3.
LINE Z3
MINIMUM
R 65 mm (2.56 in)  EDGE DISTANCE 14.9 mm (0.586 in)
(FOR MEMORY)
+
A_SB_530246_5_BFAA_02_00
Figure A-FBFAA - Sheet 02
FR47 Upper Surface, Trimming of Keel Beam
5 DATE: Nov 30/89  SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16  Page: 39
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 50

@A300
SERVICE BULLETIN
**CONF ALL
A
B
A
B
B
C
STA2983/FR47
RIB 1 DATUM
REAR SPAR DATUM
STA2983/FR47
A_SB_530246_5_BGAA_01_00
Figure A-FBGAA - Sheet 01
Modificatin of Sealing Fitting and Sealing Shim
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 40
5
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### Page 51

@A300
SERVICE BULLETIN
**CONF ALL
C
D
F
E
F
D
E
BEFORE
(1)
(7)
(2)
(8)
(6)
(11)
OR
(15)
(16)OR
(3)
(9)
(4)
(9)
BEFORE
BEFORE BEFORE
(13)
(14)
OR
(13)
(14)
A_SB_530246_5_BGAA_02_00
Figure A-FBGAA - Sheet 02
Modificatin of Sealing Fitting and Sealing Shim
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 41
5
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### Page 52

@A300
SERVICE BULLETIN
**CONF ALL
C
DEF
D
E
F
AFTER 12
2
8
6
11
1
7
3
9
4
9
AFTER AFTER AFTER
OR
(13)
(14)
SPOT FACING
DIA.34 mm (1.34 in)
R: 2 mm (0.08 in)
A_SB_530246_5_BGAA_03_00
Figure A-FBGAA - Sheet 03
Modificatin of Sealing Fitting and Sealing Shim
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 42
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 53

@A300
SERVICE BULLETIN
**CONF ALL
OR
QUESTION
FINDING
ACTION
NO YESCRACK
NO YESCRACK
CRACK LENGTH
L    8 mm
(0.315 in)
CRACK LENGTH
L    8 mm
(0.315 in)
SEE
 SHEET 2
INSPECTION BY EDDY CURRENT
ON UPPER RADUIS FOLLOWING
NTM 53−15−29 PART 6,
PROCEDURE A.
MODIFICATION AT THE
FIRST INSPECTION ONLY
IF MORE THAN ONE CRACK IS
FOUND, CONTACT AIRBUS (SEES1)
FOR FURTHER INFORMATION
SPECIAL DETAILED INSPECTION BY EDDY CURRENT ON UPPER RADIUS
OF LEFT AND RIGHT FWD FITTING OF FR47 FOLLOWING
NTM 53−15−29 PART 6, PROCEDURE A. REFER TO
PARA. 3.B.(1) AND FIGURE A−FBBAA
REINSPECT AT:
SEE TABLE 2
FIGURE A−FBAAA
REINSPECT AT:
SEE TABLE 2
FIGURE A−FBAAA
REMOVE THE FASTENERS A
AND B EVERY TIME.
REFER TO FIGURE A−FBCAA
DO ULTRASONIC INSPECTION ON
THE FWD FACE OF FWD FITTING
FOLLOWING NTM 53−15−33
PART. 4.
REFER TO FIGURE A−FBCAA
AND PARA. 3.A.(1)(b)
CUT AND REMOVE THE
FAIRING ATTACHMENT PROFILE.
REFER TO PARA. 3.C.(1)
AND FIGURE A−FBEAA
TRIM THE KEEL BEAM
REFER TO PARA. 3.C.(2)
AND FIGURE A−FBFAA
INSTALL THE FAIRING
ATTACHMENT PROFILE
REFER TO PARA. 3.C.(5)
AND FIGURE A−FBEAA
REMOVE AND MODIFY THE
SEALING FITTING AND
SEALING SHIM.
REFER TO PARA. 3.A.(1)(c)
AND PARA. 3.C.(3)
AND FIGURE A−FBGAA
INSTALL THE SEALING FITTING
REFER TO PARA. 3.C.(4)
AND FIGURE A−FBGAA
*
**
*
*
*
**
A_SB_530246_5_FAAA_01_02
Figure A-FFAAA - Sheet 01
Flow Chart
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 43
5
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### Page 54

@A300
SERVICE BULLETIN
**CONF ALL
FROM SHEET 1
OR
CONTACT AIB
BEFORE
NEXT FLIGHT
CRACK DEPTH
D    50 mm
(1.97 in)
CRACK DEPTH
20 mm    D    50 mm
(0.79 in)      (1.97 in)
CRACK DEPTH
D    20 mm
(0.79 in)
CRACKS
OR
OR
CRACK DEPTH
20 mm    D    30 mm
(0.79 in)      (1.18 in)
CRACK DEPTH
30 mm    D    50 mm
(1.18 in)      (1.97 in)
YES NO
DETAILED
VISUAL INSPECTION
OF THE AFT FITTING
AROUND FASTENERS
REF. TO FIGURE A−FBDAA
− HOWEVER IF A FLIGHT IN EXCESSIVE TURBULENCE OR A HARD LANDING EVENT
  OCCURS DURING THE 3 MONTHS OF GRACE PERIOD (WITH INSPECTION NOT YET
  ACCOMPLISHED), CONTACT AIRBUS SEES1 OR AIRTAC BEFORE NEXT FLIGHT.
THE ABOVE INSPECTION REQUIREMENTS IN CASE OF HARD LANDING OR FLIGHT
IN EXCESSIVE TURBULENCE ARE INCLUDED IN AMM 05−51−11 PAGE BLOCK 001
AND AMM 05−51−17 PAGE BLOCK 001 RESPECTIVELY.
REPAIR BEFORE
NEXT FLIGHT
REFER TO SB 53−0370
− IN CASE OF A HARD LANDING OR A FLIGHT IN EXCESSIVE TURBULENCE EVENT
  OBEY THE INSPECTION REQUIREMENT OF SB 53−0246 (A300), WITHIN 3 MONTHS
  AND REPORT THIS EVENT TO AIRBUS SEES1 OR AIRTAC.
NOTE:
REPAIR BEFORE
THE NEXT
INSPECTION
REFER TO
SB 53−0370
FURTHER INSPECTION
PROGRAM IS DEVELOPED
IN THE CONCERNED RAS
REINSPECT AT:
SEE TABLE 2,
FIGURE A−FBAAA
REINSPECT AT:
SEE TABLE 2,
FIGURE A−FBAAA
IF REMOVED
INSTALL THE FAIRING
ATTACHMENT PROFILE.
REFER TO PARA. 3.C.(5)
AND FIGURE A−FBEAA
IF REMOVED INSTALL FAIRING
ATTACHMENT PROFILE.
REFER TO PARA. 3.C.(5)
AND FIGURE A−FBEAA
IN CASE OF CRACK FINDING, ADDITIONAL INSPECTIONS ARE TO BE ACCOMPLISHED
IN CASE OF AN ABNORMAL LOADING EVENT:
FURTHER INSPECTION
PROGRAM IS DEVELOPED
IN THE CONCERNED RDAS
A_SB_530246_5_FAAA_02_01
Figure A-FFAAA - Sheet 02
Flow Chart
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 44
5
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### Page 55

@A300
SERVICE BULLETIN
Appendix 1 - Inspection Report
**CONF ALL
(1) The results of the inspection, including no findings, replacement or actions to be done, must be
forwarded to AIRBUS Dept . SEES1, on the attached inspection report sheet.
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 1
5
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### Page 56

@A300
SERVICE BULLETIN
Appendix 1 - Inspection Report
**CONF ALL
SERVICE BULLETIN N°:
A/C MSN:
FLIGHT CYCLES:
FLIGHT HOURS:
FINDING: YES NO
DATE OF INSPECTION:
INSPECTION METHOD: EDDY CURRENT
ULTRASONIC
DETAILED VISUAL
FR47 NO CRACK
LEFT UPPER
RADIUS
RIGHT UPPER
RADIUS
CRACK
EDDY CURRENT
INSPECTION
ULTRASONIC
INSPECTION
DETAILED VISUAL INSPECTION
AREA 1
YES NO
CRACK
YES NO
CRACK
AREA 2
LENGTH
(L)
DEPTH
(D)
A_SB_530246_5_RAAA_01_00
Figure A-FRAAA - Sheet 01
Appendix 1
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 2
5
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### Page 57

@A300
SERVICE BULLETIN
Appendix 1 - Inspection Report
**CONF ALL
NOTE : LH SHOWN SAME LOCATION FOR RH
MODIFIED
SEALING FITTING
FORWARD FITTING
OF FR47
INTERNAL
ANGLE
KEEL DOUBLER
EDDY CURRENT INSPECTION
LENGTH
ULTRASONIC INSPECTION
CRUCIFORM
FITTING
DEPTH
A_SB_530246_5_RAAA_02_00
Figure A-FRAAA - Sheet 02
Appendix 1
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 3
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 58

@A300
SERVICE BULLETIN
Appendix 1 - Inspection Report
**CONF ALL
AREA 1
VIEW LOOKING FORWARD − RH
FROM CABIN
VIEW LOOKING FORWARD − RH
FROM MLG COMPARTMENT
AREA 2
A_SB_530246_5_RAAA_03_00
Figure A-FRAAA - Sheet 03
Appendix 1
DATE: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 4
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 59

@A300
SERVICE BULLETIN
REPORTING SHEET
TITLE: FUSELAGE - FRAME 47 - INSPECTION OF UPPER RADIUS.
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: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 1
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 60

@A300
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: Nov 30/89 SERVICE BULLETIN No.: A300-53-0246
REVISION No.: 08 - Apr 13/16 Page: 1
5
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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