# Airbus Service Bulletin A300-53-0393

Copy: No revision named ("SB A300-53-0393"), 36 pages: PDF https://openairdocs.org/files/sha256/34/a7/34a7f147f0fabcc8e1407083535ee442eb4980426f01c1a8aace2e8f261e37fa; text https://openairdocs.org/service-documents/airbus/a300-53-0393/file/34a7f147f0fa.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2016-9298; AD 2017-05-01 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: A300-53-0393
- Page: https://openairdocs.org/service-documents/airbus/a300-53-0393

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

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

- [AD 2017-05-01](https://openairdocs.org/ad/2017-05-01.md), effective Apr 7, 2017: No revision named

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/airbus/a300-53-0393/proposed.md).

## Text (36 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2016-9298; AD 2017-05-01 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

@A300
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 - REINFORCE LO NGITUDINAL BUTT JOINT IN AREA OF
CARGO DOOR FRAME SHELL SECTION 17
**CONF ALL
MODIFICATIONS
MODIFICATION CLASSIFICATION
MAJOR
 13692D23329
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.
REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES
Widespread Fatigue Damage (WFD) analysis has determined that cracks can occur in the area of the
AFT cargo compartment door frame at Frame (FR)59 and FR63 in the area of Stringer (STGR)27 and
STGR39.
This Service Bulletin introduces Modification Number (Mod. No.) 13692D23329 which reinforces the
longitudinal butt joints with additional butt straps at FR59 to FR59A on STGR39 and FR63A to FR64 on
STGR27.
Accomplishment of this Service Bulletin will contribute to the prevention of crack formation in the area of
the AFT cargo compartment door frame. Accomplishment will also satisfy the revised requirements of
the WFD FAR26 rule.
This Service Bulletin is based on the aircraft configuration as known by AIRBUS (first aircraft delivery
configuration and modified by the reported incorporation of AIRBUS Service Bulletins).
Prior to Service Bulletin embodiment, specific attention must be paid to structural damage which may
exist and to repairs which were performed on the aircraft because they may be affected by the Service
Bulletin. It must be verified that all allowable damage limits and repairs performed (both in accordance
with the SRM and outside of the SRM) are still applicable and effective to the new Service Bulletin
configuration.
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 1
6
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SERVICE BULLETIN
SUMMARY
There may be additional or modified maintenance requirements, such as temporary limits or additional
inspections that apply with respect to the Service Bulletin configuration.
If the post Service Bulletin repair status is not covered by the SRM and for repairs outside of the SRM
covered by an RDAS issued by AIRBUS, AIRBUS Customer Services Repair Engineering Support
(SEER) should be c ontacted. Repair review will be done by A IRBUS at conditions of the Customer
Services Catalogue.
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
 YES
 VENDOR SB INVOLVED
 NO
NOTE
 (1)
: Service Bulletin must be accomplished.
MATERIAL PRICE INFORMATION
**CONF 001
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
 QTY PER
A/C
PRICE PER
A/C (USD)
MAIN PARTS
Kit 530393D01R00
 1
 8,650.00
 Doublers, Fasteners, Nuts
**CONF 002
No Material
EFFECTIVITY
**CONF ALL
This Service Bulletin is applicable to this (these) operator(s) :
001 50W 81T ABR AFG F2I IAW IRA IRM KZU MNB MSR RUN
SOP TIW TNO TSY
CONCURRENT REQUIREMENTS
None
REFERENCES / REPERCUSSIONS
TFU
 None
OEB
 None
AOT
 None
SIL
 None
LINE MAINTENANCE AFFECTED
 No
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 2
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SERVICE BULLETIN
SUMMARY
LIFE LIMIT
 None
OTHER
 None
NATURE OF THE WORK
AIRCRAFT
 YES
EQUIPMENT
 NO
HARD
 NO
SOFT
 NO
OBRM
 NO
MANPOWER
**CONF 001
Task 530393-831-848-001: Modification
TOTAL MANHOURS
 24.00
ELAPSED TIME (HOURS)
 24.00
**CONF 002
Task 530393-831-848-001: Modification
TOTAL MANHOURS
 0.00
APPENDICES
**CONF ALL
None
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 3
6
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SERVICE BULLETIN
SUMMARY
**CONF 001
Z150
A
AREA OF
MODIFICATION
AREA OF
MODIFICATION
A
FR64 FR63A FR59FR59A
STGR26
STGR27
STGR28
STGR38
STGR39
STGR40
A_SB_530393_6_SAAA_01_00
Figure A-GSAAA - Sheet 01
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 4
6
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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 - REINFORCE LO NGITUDINAL BUTT JOINT IN AREA OF
CARGO DOOR FRAME SHELL SECTION 17
MODIFICATION No.: 13692D23329
This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the
property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with
any information contained in it. It is delivered on the express condition that said document and the
information contained in it shall be treated as confidential, shall not be used for any purpose other than
that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall
not be duplicated in any manner (except for the purposes of performing the tasks described hereunder
and provided that any recipient of such document shall comply with the conditions herein), without
AIRBUS prior written consent.
1. PLANNING INFORMATION
**CONF ALL
A. EFFECTIVITY
This modification is applicable by Service Bulletin only.
(1) Models
B2-1C B2-203 B2K-3C B4-103 B4-203 B4-2C C4-203 F4-203
(2) Effectivity by MSN
0003 0041 0045 0055 0075 0080 0090 0101 0105 0107 0117 0123 0126 0129 0139
0151-0152 0154 0157 0160 0173 0175 0180 0183 0185 0187 0200 0203-0204 0210
0212 0218 0220 0226-0227 0234-0236 0239 0244 0247 0255-0256 0259 0261 0274
0277 0292 0299 0302 0304
(3) Effectivity by Operator
The Operator/MSN relationship is provided for information only and is correct at the time
of issue in accordance with the information available to AIRBUS. Any future changes
resulting from transfer of an aircraft from one operator to another will not be reflected in
this list unless the Service Bulletin is revised for another reason.
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 1
6
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SERVICE BULLETIN
OPERATOR
 MSN
001
 0157 0203 0218
50W
 0003
81T
 0277 0292
ABR
 0152 0220 0234 0236 0259 0274
AFG
 0180
F2I
 0235
IAW
 0239
IRA
 0080 0139 0151 0173 0185 0187 0226 0256 0299 0302
IRM
 0055 0090 0160 0175 0204 0244
KZU
 0041 0101 0117
MNB
 0123 0212 0304
MSR
 0200 0255
RUN
 0075 0105 0107 0154 0183
SOP
 0126
TIW
 0261
TNO
 0045 0210 0227 0247
TSY
 0129
(4) Configuration by MSN
MSN
 CONFIGURATION
0003
 002
0041 0045 0055 0075 0080 0090 0101 0105 0107 0117 0123
0126 0129 0139 0151 0152 0154 0157 0160 0173 0175 0180
0183 0185 0187 0200 0203 0204 0210 0212 0218 0220 0226
0227 0234 0235 0236 0239 0244 0247 0255 0256 0259 0261
0274 0277 0292 0299 0302 0304
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 with the exception of MSN 0003.
**CONF 002
Config. 002 is valid for MSN 0003 only.
NOTE
: For MSN 0003 a specific solution is required, please contact AIRBUS
engineering support for further instructions.
(6) Material Effectivity
**CONF 001
MATERIAL
 QTY PER A/C
 SEE NOTES
Kit 530393D01R00
 1
Consumable CMLD01
 1
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 2
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SERVICE BULLETIN
**CONF 002
None
NOTE
: For MSN 0003 a specific solution is required, please contact AIRBUS
engineering support for further instructions.
**CONF ALL
B. CONCURRENT REQUIREMENTS
None
C. REASON
(1) History
Widespread Fatigue Damage (WFD) analysis has determined that cracks can occur in
the area of the AFT cargo compartment door frame at Frame (FR)59 and FR63 in the
area of Stringer (STGR)27 and STGR39.
(2) Objective/Action
This Service Bulletin introduces Modification Number (Mod. No.) 13692D23329 which
reinforces the longitudinal butt joints with additional butt straps at FR59 to FR59A on
STGR39 and FR63A to FR64 on STGR27.
(3) Advantages
Accomplishment of this Service Bulletin will contribute to the prevention of crack
formation in the area of the AFT cargo compartment door frame. Accomplishment will
also satisfy the revised requirements of the WFD FAR26 rule.
(4) Operational/Maintenance Consequences
This Service Bulletin is based on the aircraft configuration as known by AIRBUS (first
aircraft delivery configuration and modified by the reported incorporation of AIRBUS
Service Bulletins).
Prior to Service Bulletin embodiment, specific attention must be paid to structural
damage which may exist and to repairs which were performed on the aircraft because
they may be affected by the Service Bulletin. It must be verified that all allowable
damage limits and repairs performed (both in accordance with the SRM and outside of
the SRM) are still applicable and effective to the new Service Bulletin configuration.
There may be additional or modified maintenance requirements, such as temporary
limits or additional inspections that apply with respect to the Service Bulletin
configuration.
If the post Service Bulletin repair status is not covered by the SRM and for repairs
outside of the SRM covered by an RDAS issued by AIRBUS, AIRBUS Customer
Services Repair Engineering Support (SEER) s hould be contacted. Repair review will be
done by AIRBUS at conditions of the Customer Services Catalogue.
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 3
6
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SERVICE BULLETIN
D. DESCRIPTION
To accomplish this Service Bulletin it is necessary to :
**CONF 001
Task 530393-831-848-001: Modification
(1) Reinforce the longitudinal butt strap between FR63A and FR64 on STGR27
(2) Reinforce the longitudinal butt strap between FR59 and FR59A on STGR39
**CONF 002
Task 530393-831-848-001: Modification
(1) Reinforce the longitudinal butt strap between FR63A and FR64 on STGR27
(2) Reinforce the longitudinal butt strap between FR59 and FR59A on STGR39
**CONF ALL
E. COMPLIANCE
(1) Classification
MANDATORY: Service Bulletin must be accomplished.
(2) Accomplishment Timescale
This Service Bulletin must be accomplished no later than 48,000 FC (FH not relevant).
This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness
Directive (AD) published by the European Av iation Safety Agenc y (EASA) will be issued
to confirm this classification. It is anticipated that the AD will confirm the (thresholds
and/or intervals and/or date) given above but reference should be made to the AD for
confirmation of the mandated accomplishment timescale.
F. APPROVAL
The technical content of this document is approved under the authority of Design
Organization 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.
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 4
6
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SERVICE BULLETIN
G. MANPOWER
The manpower estimates given in this Service Bulletin are based on the direct labor cost to
do the work. These estimates assume that the work will be done by experienced personnel,
and may need to be revised upwards to suit operator’s circumstances. The estimates do not
include the time to prepare, plan or inspect the work. Manufacture and procurement of parts
and tools, drying times for paints, sealants, etc., and general administration work are also not
included.
**CONF 001
Task 530393-831-848-001: Modification
Get Access
 2.00
On Aircraft
Reinforce the longitudinal butt strap between FR63A
and FR64 on STGR27
10.00
Reinforce the longitudinal butt strap between FR59 and
FR59A on STGR39
10.00
Close-Up
 2.00
TOTAL MANHOURS
 24.00
ELAPSED TIME (HOURS)
 24.00
**CONF 002
Task 530393-831-848-001: Modification
On Aircraft
TOTAL MANHOURS
 0.00
NOTE
: For MSN 0003 a specific solution is required, please contact AIRBUS
engineering support for further instructions.
**CONF ALL
H. WEIGHT AND BALANCE
**CONF 001
The weight and balance estimates given in this Service Bulletin are based on the
Manufacturer’s Empty Weight (MEW) and do not include operator’s items. For the definition of
MEW and operator’s items, refer to the Weight and Balance Manual (WBM) Chapter 1-00-07.
Manufacturers Empty Weight +0.924 KG (+2.0370 LB)
Effect on Balance +36.124 KGM (+261.284 LB.FT )
**CONF 002
None
NOTE
: For MSN 0003 a specific solution is required, please contact AIRBUS
engineering support for further instructions.
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 5
6
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SERVICE BULLETIN
**CONF ALL
I. ELECTRICAL LOAD DATA
Not Changed
J. REFERENCES
**CONF 001
Aircraft Maintenance Manual (AMM)
 06-21-00 24-00-00 25-12-11
25-52-12 52-30-00 53-00-00
Elec. Std. Practices Manual (ESPM)
 20-55-00
Standards Manual (SM)
Structural Repair Manual (SRM)
 51-30-30 51-30-31 51-30-40
51-30-45 51-40-12 51-40-13
51-40-20
Weight and Balance Manual (WBM)
 Chapter 1-00-07
**CONF 002
Elec. Std. Practices Manual (ESPM)
 20-55-00
**CONF ALL
K. PUBLICATION AFFECTED
Airworthiness Limitation Section (ALS)
 Airworthiness Limitation Section
(ALS) Part 2
Structural Repair Manual (SRM)
 53-17-00
L. INTERCHANGEABILITY/MIXABILITY
Not Applicable
M. SPARES
None
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 6
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 530393D01R00
 AIRBUS Material, Logistics and Suppliers
Weg beim Jaeger 150
D-22335 HAMBURG
GERMANY
For ordering by internet:
http://spares.airbus.com
For ordering by fax: +49 40 50 76 2590
For ordering by E-mail: airbus.kit@airbus.com
(2) Price and Availability
Kit 530393D01R00
Cost
 8,650.00 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 provide a 10% reduction to the applicable kits sales prices given in the
paragraph Price and Availability for orders placed before Dec 31/19.
C. LIST OF COMPONENTS
Kit 530393D01R00
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
1
 A5398104220000
 1
 DOUBLER
2
 A5398104220200
 1
 DOUBLER
3
 EN6114K3A8
 27
 BOLT
4
 EN6114K3A9
 29
 BOLT
5
 EN6114K3A11
 4
 BOLT
6
 EN6114K4Y9
 17
 BOLT
7
 EN6114K4Y10
 43
 BOLT
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 7
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SERVICE BULLETIN
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
8
 EN6114K4Y11
 10
 BOLT
9
 EN6114K4Y13
 8
 BOLT
10
 ASNA2528-3A
 60
 NUT
11
 ASNA2528-4
 78
 NUT
NOTE
: If you find part numbers of hardware components in the related kit(s) which
you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,
refer to Standards Manual (SM). The SM will give you the correct part number
to part number relationship.
D. LIST OF MATERIALS - OPERATOR SUPPLIED
(1) Consumable Materials
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO CML
MAT. No.
QTY PER A/C
 SEE
NOTES
Wash Primer - Structure
 04CMA2
 As required
Primer Polyurethane Paint -
Corrosion Inhibiting
04EAC2
 As required
Top Coat Polyurethane - External
Structure
04JAA3
 As required
Top Coat Polyurethane - Grey
Internal Structure
04JME4
 As required
Polysulfide Sealant - General
Purpose Brushable
06AAA1
 As required
Polysulfide Sealant - General
Purpose Interfay
06AAC1
 As required
Non Aqueous Cleaner - General
 08BAA9
 As required
Corrosion Preventive Compound -
Water Displacing
12ADB1
 As required
Textile - Lint Free Cotton
 14SBA1
 As required
(2) Components
None
(3) Equipment
None
E. PARTS TO BE RE-IDENTIFIED BY OPERATOR
None
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 8
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SERVICE BULLETIN
F. TOOLING
(1) Tooling - Price and Availability
None
(2) Tools
To accomplish this Service Bulletin it is necessary to use the tools listed in AMM
52-30-00, Page Block 301.
(3) Special Tools
None
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 9
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SERVICE BULLETIN
This Page Intentionally Left Blank
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 10
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SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS
Task 530393-831-848-001 - Modification
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.
NOTE
: The accomplishment instructions of this Service Bulletin refer to procedures
included in other AIRBUS documents. When the words ’refer to’ are used and the
operator has an accepted alternative procedure, the accepted alternative procedure
can be used. When the words ’in accordance with’ are included in the instruction,
the procedure in the AIRBUS document must be used.
NOTE
: The access and close-up instructions, not comprising return to service tests, in this
Service Bulletin do not constitute or affect the technical intent of the Service
Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or
close-up steps to add flexibility to their maintenance operations as long as the
technical intent of the Service Bulletin is met within the set parameters.
NOTE
: Manual titles given in the accomplishment instructions are referred to by acronyms.
Refer to paragraph 1.J., References, for the definition of acronyms.
NOTE
: This Service Bulletin is classified mandatory or expected to be classified mandatory
by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these
accomplishment instructions are Required for Compliance (RC) and must be done
to comply with the AD. Other paragraphs are recommended and may be deviated
from, done as part of other actions or done with accepted methods different from
those given in the Service Bulletin, as long as the RC paragraphs can be done and
the aircraft can be put back into a serviceable condition.
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 11
6
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SERVICE BULLETIN
Task Associated Data
**CONF 001
Zone
150
Access
Door
 812
Manpower
TOTAL MANHOURS
 24.00
ELAPSED TIME (HOURS)
 24.00
**CONF 002
Manpower
TOTAL MANHOURS
 0.00
**CONF ALL
A. GENERAL
**CONF 001
(1) Subtask 530393-910-201-001 - Standard Practices
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 06-21-00, Page Block 001
53-00-00, Page Block 001
Structural Repair Manual (SRM)
 51-30-31
51-30-40
51-30-45
51-40-12
51-40-13
51-40-20
(a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to
the Consumable Materials List (CML).
(b) For the identification of zones, refer to AMM 06-21-00, Page Block 001.
(c) For the Frame (FR) identification, refer to AMM 53-00-00, Page Block 001.
(d) Apply sealant in accordance with SRM 51-40-20.
(e) Obtain fastener hole and drill data in accordance with SRM 51-30-40.
(f) Countersink fastener holes in accordance with SRM 51-30-45.
(g) Obtain alternative and substitute fastener data in accordance with SRM 51-30-31.
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 12
6
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SERVICE BULLETIN
(h) If alternative and substitute fasteners have to be used, you must make sure that the
associated nut/collar are compatible in accordance with SRM 51-40-00 ’Mating Part’
column.
(i) Fill existing countersinks in accordance with SRM 51-30-45.
(j) Restore surface protection in accordance with SRM 51-40-12.
(k) Restore the fastener water repellent coatings in accordance with SRM 51-40-13.
(l) If the length of any fastener specified in this Service Bulletin does not meet
installation standards given in SRM Chapter 51, then a fastener of the same
specification, or an approved substitute, with a length which meets the installation
standards given in SRM Chapter 51 may be used. In addition, washers may be
installed for fastener grip length in accordance with SRM Chapter 51.
(2) Subtask 530393-839-201-001 - Administrative
Manpower Resources
Skills
 NON SPECIFIC
Write in the applicable aircraft records that you have done all the work given in this
Service Bulletin.
**CONF 002
None
**CONF ALL
B. PREPARATION
**CONF 001
(1) Subtask 530393-941-201-001 - Job Set-up
Work Zones and Access Panels
Zone
 Access/Work location
150
 Access
 Door 812
Work location
 Stringer 27
Stringer 39
from Frame 59 to Frame 59A
from Frame 63A to Frame 64
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 24-00-00, Page Block 301
25-12-11, Page Block 401
25-52-12, Page Block 401
52-30-00, Page Block 301
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 13
6
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SERVICE BULLETIN
(a) The following items shall be considered as the basic Aircraft configuration before
you start a maintenance task:
- Aircraft on the ground resting on landing gear (the ground safety locks and the
wheel chocks are in position on the landing gear).
- Engine shut down, thrust reversers closed and locked.
- Parking brake applied.
- Aircraft electrical network de-energized.
- Hydraulic systems depressurized.
- Access to cockpit and cabin is available.
- All circuit breakers are in closed position.
- All controls in NORM, AUTO or OFF position.
(b) Put access platform(s) in position below the AFT cargo compartment door 812.
(c) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page
Block 301.
(d) Open the AFT cargo compartment door 812, refer to AMM 52-30-00, Page Block
301.
(e) Make sure that the AFT cargo compartment door 812 is safely held in the open
position, refer to AMM 52-30-00, Page Block 301.
(f) Remove the cargo compartment sidewall panels as necessary to access the
modification areas, refer to AMM 25-52-12, Page Block 401.
(g) Remove the cargo compartment insulation as necessary to access the modification
areas, refer to AMM 25-12-11, Page Block 401.
**CONF 002
(1) Subtask 530393-941-201-002 - Job Set-up
For MSN 0003 a specific solution is required, please contact AIRBUS engineering
support for further instructions.
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 14
6
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@A300
SERVICE BULLETIN
**CONF ALL
C. PROCEDURE
**CONF 001
(1) Subtask 530393-831- 201-001 - Reinforce the longitudi nal butt strap between FR63A
a n dF R 6 4o nS T G R 2 7
Work Zones and Access Panels
Zone
 Access/Work location
150
 Access
 Door 812
Work location
 from Frame 63A to Frame 64
Stringer 27
Manpower Resources
Manhours
 10.00
Minimum number of person
 1
Subtask elapsed time
 10.00
Skills
 AIRFRAME
Material necessary to do the job
Kit 530393D01R00
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
1
 A5398104220000
 1
 DOUBLER
4
 EN6114K3A9
 20
 BOLT
5
 EN6114K3A11
 4
 BOLT
6
 EN6114K4Y9
 8
 BOLT
7
 EN6114K4Y10
 31
 BOLT
8
 EN6114K4Y11
 7
 BOLT
9
 EN6114K4Y13
 4
 BOLT
10
 ASNA2528-3A
 24
 NUT
11
 ASNA2528-4
 50
 NUT
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Wash Primer - Structure
 04CMA2
 As required
Primer Polyurethane Paint -
Corrosion Inhibiting
04EAC2
 As required
Top Coat Polyurethane -
External Structure
04JAA3
 As required
Top Coat Polyurethane -
Grey Internal Structure
04JME4
 As required
Polysulfide Sealant -
General Purpose Brushable
06AAA1
 As required
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 15
6
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### Page 20

@A300
SERVICE BULLETIN
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Polysulfide Sealant -
General Purpose Interfay
06AAC1
 As required
Non Aqueous Cleaner -
General
08BAA9
 As required
Corrosion Preventive
Compound - Water
Displacing
12ADB1
 As required
Textile - Lint Free Cotton
 14SBA1
 As required
References
Structural Repair Manual (SRM)
 51-30-30
51-30-40
51-30-45
51-40-12
51-40-13
51-40-20
Fig. A-GBAAA
Modification of the Longitudinal Butt
Joints at FR59 to FR59A on STGR39
and FR63A to FR64 on STGR27
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
(a) Between Frame 63A and Frame 64 on STGR27 identify, remove and discard the
fasteners in accordance with SRM 51-30-30.
Refer to Fig. A-GBAAA Sheet 01
 and Fig. A-GBAAA Sheet 02
 .
1
 Remove:
70 Bolt Discard
70 Nut Discard
NOTE
: Be careful not to damage the holes.
(b) Do a check of the edge distance from the fastener hole to the door frame edge.
1
 If the edge distance is less than 12.0 mm (0.472 in.) contact AIRBUS before
aircraft next flight for further instruction.
(c) Temporarily put the doubler, Item 1, in position on the outer fuselage skin between
Frame 63A and Frame 64 on STGR27.
Refer to Fig. A-GBAAA Sheet 04
 .
1
 Put in position:
1 Doubler A5398104220000 Item 1
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 16
6
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SERVICE BULLETIN
(d) Transfer drill the existing fastener holes to the doubler, Item 1, and open to the final
hole diameter in accordance with SRM 51-30-40.
Refer to Fig. A-GBAAA Sheet 06
 .
(e) Countersink the holes in the doubler, Item 1, in accordance with SRM 51-30-45.
(f) Remove the doubler, Item 1, deburr all holes and clean.
1
 Clean using:
Textile - Lint Free
Cotton
14SBA1 As required
made moist with:
Non Aqueous
Cleaner - General
08BAA9 As required
(g) If necessary fill the existing countersink(s) in the fuselage skin with countersink
repair washer(s) in accordance with SRM 51-30-45.
(h) Apply a thin layer of sealant to all the mating surfaces in accordance with SRM
51-40-20.
1
 Apply:
Polysulfide Sealant
- General Purpose
Brushable
06AAA1 As required
(i) Wet install the doubler, Item 1, and the fasteners between Frame 63A and Frame
64 on STGR27.
Refer to Fig. A-GBAAA Sheet 04
 and Fig. A-GBAAA Sheet 06
 .
1
 Install:
20 Bolt EN6114K3A9 Item 4
4 Bolt EN6114K3A11 Item 5
24 Nut ASNA2528-3A Item 10
8 Bolt EN6114K4Y9 Item 6
31 Bolt EN6114K4Y10 Item 7
7 Bolt EN6114K4Y11 Item 8
4 Bolt EN6114K4Y13 Item 9
50 Nut ASNA2528-4 Item 11
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 17
6
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### Page 22

@A300
SERVICE BULLETIN
with:
Polysulfide Sealant
- General Purpose
Brushable
06AAA1 As required
(j) Remove any excess sealant.
(k) Restore the fuselage internal surface protection on the fasteners in accordance with
SRM 51-40-12.
1
 Apply:
Wash Primer -
Structure
04CMA2 As required
Primer
Polyurethane Paint
- Corrosion
Inhibiting
04EAC2 As required
Top Coat
Polyurethane - Grey
Internal Structure
04JME4 As required
(l) Restore the water repellent coating on the fasteners in accordance with SRM
51-40-13.
1
 Apply:
Corrosion
Preventive
Compound - Water
Displacing
12ADB1 As required
(m) Apply sealant to the edges of the doubler in accordance with SRM 51-40-20.
1
 Apply:
Polysulfide Sealant
- General Purpose
Interfay
06AAC1 As required
(n) Restore the external surface finish in accordance with SRM 51-40-12.
1
 Apply:
Wash Primer -
Structure
04CMA2 As required
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 18
6
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### Page 23

@A300
SERVICE BULLETIN
Primer
Polyurethane Paint
- Corrosion
Inhibiting
04EAC2 As required
Top Coat
Polyurethane -
External Structure
04JAA3 As required
(2) Subtask 530393-831- 202-001 - Reinforce the longitudi nal butt strap between FR59
and FR59A on STGR39
Work Zones and Access Panels
Zone
 Access/Work location
150
 Work location
 from Frame 59 to Frame 59A
Stringer 39
Manpower Resources
Manhours
 10.00
Minimum number of person
 1
Subtask elapsed time
 10.00
Skills
 AIRFRAME
Material necessary to do the job
Kit 530393D01R00
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
2
 A5398104220200
 1
 DOUBLER
3
 EN6114K3A8
 27
 BOLT
4
 EN6114K3A9
 9
 BOLT
6
 EN6114K4Y9
 9
 BOLT
7
 EN6114K4Y10
 12
 BOLT
8
 EN6114K4Y11
 3
 BOLT
9
 EN6114K4Y13
 4
 BOLT
10
 ASNA2528-3A
 36
 NUT
11
 ASNA2528-4
 28
 NUT
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Wash Primer - Structure
 04CMA2
 As required
Primer Polyurethane Paint -
Corrosion Inhibiting
04EAC2
 As required
Top Coat Polyurethane -
External Structure
04JAA3
 As required
Top Coat Polyurethane -
Grey Internal Structure
04JME4
 As required
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 19
6
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### Page 24

@A300
SERVICE BULLETIN
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Polysulfide Sealant -
General Purpose Brushable
06AAA1
 As required
Polysulfide Sealant -
General Purpose Interfay
06AAC1
 As required
Non Aqueous Cleaner -
General
08BAA9
 As required
Corrosion Preventive
Compound - Water
Displacing
12ADB1
 As required
Textile - Lint Free Cotton
 14SBA1
 As required
References
Structural Repair Manual (SRM)
 51-30-30
51-30-40
51-30-45
51-40-12
51-40-13
51-40-20
Fig. A-GBAAA
Modification of the Longitudinal Butt
Joints at FR59 to FR59A on STGR39
and FR63A to FR64 on STGR27
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
(a) Between Frame 59 and Frame 59A on STGR39 identify, remove and discard the
fasteners in accordance with SRM 51-30-30.
Refer to Fig. A-GBAAA Sheet 01
 and Fig. A-GBAAA Sheet 03
 .
1
 Remove:
64 Bolt Discard
64 Nut Discard
NOTE
: Be careful not to damage the holes.
(b) Do a check of the edge distance from the fastener hole to the door frame edge.
1
 If the edge distance is less than 12.0 mm (0.472 in.) contact AIRBUS before
aircraft next flight for further instruction.
(c) Temporarily put the doubler, Item 2, in position on the outer fuselage skin between
Frame 59 and Frame 59A on STGR39.
Refer to Fig. A-GBAAA Sheet 05
 .
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 20
6
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### Page 25

@A300
SERVICE BULLETIN
1
 Put in position:
1 Doubler A5398104220200 Item 2
(d) Transfer drill the existing fastener holes and open to the final hole diameter in
accordance with SRM 51-30-40.
Refer to Fig. A-GBAAA Sheet 06
 .
(e) Countersink the holes in the doubler, Item 2, in accordance with SRM 51-30-45.
(f) Remove the doubler, Item 2, deburr all holes and clean.
1
 Clean using:
Textile - Lint Free
Cotton
14SBA1 As required
made moist with:
Non Aqueous
Cleaner - General
08BAA9 As required
(g) If necessary fill the existing countersink(s) in the fuselage skin with countersink
repair washer(s) in accordance with SRM 51-30-45.
(h) Apply a thin layer of sealant to all the mating surfaces.
1
 Apply:
Polysulfide Sealant
- General Purpose
Brushable
06AAA1 As required
(i) Wet install the doubler, Item 2, and the fasteners between Frame 59 and Frame
59A on STGR39.
Refer to Fig. A-GBAAA Sheet 05
 and Fig. A-GBAAA Sheet 06
 .
1
 Wet install:
27 Bolt EN6114K3A8 Item 3
9 Bolt EN6114K3A9 Item 4
36 Nut ASNA2528-3A Item 10
9 Bolt EN6114K4Y9 Item 6
12 Bolt EN6114K4Y10 Item 7
3 Bolt EN6114K4Y11 Item 8
4 Bolt EN6114K4Y13 Item 9
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 21
6
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@A300
SERVICE BULLETIN
28 Nut ASNA2528-4 Item 11
with:
Polysulfide Sealant
- General Purpose
Brushable
06AAA1 As required
(j) Remove any excess sealant.
(k) Restore the fuselage internal surface protection on the fasteners in accordance with
SRM 51-40-12.
1
 Apply:
Wash Primer -
Structure
04CMA2 As required
Primer
Polyurethane Paint
- Corrosion
Inhibiting
04EAC2 As required
Top Coat
Polyurethane - Grey
Internal Structure
04JME4 As required
(l) Restore the water repellent coating on the fasteners in accordance with SRM
51-40-13.
1
 Apply:
Corrosion
Preventive
Compound - Water
Displacing
12ADB1 As required
(m) Apply sealant to the edges of the doubler in accordance with SRM 51-40-20.
1
 Apply:
Polysulfide Sealant
- General Purpose
Interfay
06AAC1 As required
(n) Restore the external surface finish in accordance with SRM 51-40-12.
1
 Apply:
Wash Primer -
Structure
04CMA2 As required
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 22
6
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### Page 27

@A300
SERVICE BULLETIN
Primer
Polyurethane Paint
- Corrosion
Inhibiting
04EAC2 As required
Top Coat
Polyurethane -
External Structure
04JAA3 As required
**CONF 002
(1) Subtask 530393-831- 201-003 - Reinforce the longitudi nal butt strap between FR63A
a n dF R 6 4o nS T G R 2 7
For MSN 0003 a specific solution is required, please contact AIRBUS engineering
support for further instructions.
(2) Subtask 530393-831- 202-003 - Reinforce the longitudi nal butt strap between FR59
and FR59A on STGR39
For MSN 0003 a specific solution is required, please contact AIRBUS engineering
support for further instructions.
**CONF ALL
D. TEST
**CONF 001
None
**CONF 002
None
**CONF ALL
E. CLOSE-UP
**CONF 001
(1) Subtask 530393-942-201-001 - Close-up
Work Zones and Access Panels
Zone
 Access/Work location
150
 Access
 Door 812
Manpower Resources
Skills
 NON SPECIFIC
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 23
6
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### Page 28

@A300
SERVICE BULLETIN
References
Aircraft Maintenance Manual (AMM)
 25-12-11, Page Block 401
25-52-12, Page Block 401
52-30-00, Page Block 301
(a) Make sure that the work areas are clean and clear of tools and other items of
equipment.
(b) Install the cargo compartment insulation as necessary, refer to AMM 25-12-11,
Page Block 401.
(c) Install the cargo compartment sidewall linings as necessary, refer to AMM
25-52-12, Page Block 401.
(d) Close the AFT cargo compartment door 812, refer to AMM 52-30-00, Page Block
301.
(e) Remove the access platform(s).
**CONF 002
(1) Subtask 530393-942-201-003 - Close-up
For MSN 0003 a specific solution is required, please contact AIRBUS engineering
support for further instructions.
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 24
6
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### Page 29

@A300
SERVICE BULLETIN
**CONF 001
Z150
A
A
FR64 FR63A FR59FR59A
STGR26
STGR27
STGR28
STGR38
STGR39
STGR40
C E
B D
A_SB_530393_6_BAAA_01_00
Figure A-GBAAA - Sheet 01
Modification of the Longitudinal Butt Joints at FR59 to FR59A on STGR39 and FR63A to FR64 on
STGR27
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 25
6
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### Page 30

@A300
SERVICE BULLETIN
**CONF 001
NOTE:
FASTENERS TO BE REMOVED SHOWN THUS     .01
BEFORE
B
FR63AFR64
STGR27
01
A_SB_530393_6_BAAA_02_00
Figure A-GBAAA - Sheet 02
Modification of the Longitudinal Butt Joints at FR59 to FR59A on STGR39 and FR63A to FR64
on STGR27
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 26
6
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### Page 31

@A300
SERVICE BULLETIN
**CONF 001
NOTE:
FASTENERS TO BE REMOVED SHOWN THUS     .01
BEFORE
C
FR59A FR59
STGR39
01
A_SB_530393_6_BAAA_03_00
Figure A-GBAAA - Sheet 03
Modification of the Longitudinal Butt Joints at FR59 to FR59A on STGR39 and FR63A to FR64
on STGR27
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 27
6
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@A300
SERVICE BULLETIN
**CONF 001
AFTER FR63AFR64
STGR27
D
1
A_SB_530393_6_BAAA_04_00
Figure A-GBAAA - Sheet 04
Modification of the Longitudinal Butt Joints at FR59 to FR59A on STGR39 and FR63A to FR64
on STGR27
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 28
6
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### Page 33

@A300
SERVICE BULLETIN
**CONF 001
AFTER
FR59A FR59
STGR39
E
2
A_SB_530393_6_BAAA_05_01
Figure A-GBAAA - Sheet 05
Modification of the Longitudinal Butt Joints at FR59 to FR59A on STGR39 and FR63A to FR64
on STGR27
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 29
6
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### Page 34

@A300
SERVICE BULLETIN
**CONF 001
SYMBOL ITEM PART NUMBER DESCRIPTION MIN MAX
EN6114K3A8 PIN 5.529 mm 5.542 mm
ASNA2528−3A NUT (0.217 in) (0.218 in)
EN6114K3A9 PIN 5.529 mm 5.542 mm
ASNA2528−3A NUT (0.217 in) (0.218 in)
EN6114K3A11 PIN 5.529 mm 5.542 mm
ASNA2528−3A NUT (0.217 in) (0.218 in)
EN6114K4Y9 PIN 7.118 mm 7.130 mm
ASNA2528−4 NUT (0.280 in) (0.281 in)
EN6114K4Y10 PIN 7.118 mm 7.130 mm
ASNA2528−4 NUT (0.280 in) (0.281 in)
EN6114K4Y11 PIN 7.118 mm 7.130 mm
ASNA2528−4 NUT (0.280 in) (0.281 in)
EN6114K4Y13 PIN 7.118 mm 7.130 mm
ASNA2528−4 NUT (0.280 in) (0.281 in)
3
10
4
10
5
10
6
11
7
11
8
11
9
11
HOLE SIZE HOLE SIZE SIZE/FIT TYPE
1ST OVERSIZE
TRANSITION FIT
1ST OVERSIZE
TRANSITION FIT
1ST OVERSIZE
TRANSITION FIT
1ST OVERSIZE
TRANSITION FIT
1ST OVERSIZE
TRANSITION FIT
1ST OVERSIZE
TRANSITION FIT
1ST OVERSIZE
TRANSITION FIT
A_SB_530393_6_BAAA_06_01
Figure A-GBAAA - Sheet 06
Modification of the Longitudinal Butt Joints at FR59 to FR59A on STGR39 and FR63A to FR64 on
STGR27
DATE: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 30
6
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### Page 35

@A300
SERVICE BULLETIN
REPORTING SHEET
TITLE: FUSELAGE - REINFORCE LO NGITUDINAL BUTT JOINT IN AREA OF
CARGO DOOR FRAME SHELL SECTION 17
MODIFICATION No.: 13692D23329
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: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 1
6
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### Page 36

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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
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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: Sep 27/13 SERVICE BULLETIN No.: A300-53-0393
REVISION No.: 00 - Sep 27/13 Page: 1
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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