# Airbus Service Bulletin A300-57-0259

Copy: No revision named ("SB A300-57-0259"), 39 pages: PDF https://openairdocs.org/files/sha256/6b/bf/6bbf8202341564c0974e3eee861989a2c816ddcc36e1024bae500efa242c337d; text https://openairdocs.org/service-documents/airbus/a300-57-0259/file/6bbf82023415.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: A300-57-0259
- Page: https://openairdocs.org/service-documents/airbus/a300-57-0259

## 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/a300-57-0259/proposed.md).

## Text (39 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: 57
TITLE: WING - STRUCTURE - WING STRINGER JOINT AT RIB 18 (OVERSIZE
ATTACHMENT HOLES)
**CONF ALL
MODIFICATIONS
MODIFICATION CLASSIFICATION
MAJOR
 13716H5748
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
Following fatigue analysis on the A300-B2/-B4 and A300-600, the Top Skin Stringer Joints at Rib 18
have been identified as an area that is susceptible to Widespread Fatigue Damage (WFD).
As a result of the FAA Part 26 rule change, all wing structural items deemed potentially susceptible to
WFD have been assessed. The top stringer joints at Rib 18 have been highlighted as an area of
uniform stress distribution, indicating that cracks may develop in adjacent stringers at the same time
which is known as Multi Element Damage (MED).
The stringer joint consists of 3 main load transferring parts: an overlapping flange, two straps attached
through the stringer web and a strap on the top flange. All the components of the joint are attached with
fasteners. The fastener holes were the subject of a MED WFD analysis which showed that cracking
could occur from a number of the holes in the joint on Stringers 11, 12, 13, 14, 15, 16, 17 and 18.
This modification consists of a 1st oversize of the critical holes on Stringers 11, 12, 13, 14, 15, 16, 17
and 18. The crown strap does not need to be modified but will be subjected to a detailed inspection
(DET) during the embodiment of this Service Bulletin.
This modification will satisfy the requirements of the FAA Part 26 rule (14 Code of Federal Regulations
(CFR) 26 Subpart C) requiring WFD justification of susceptible items.
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 1
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 2

@A300
SERVICE BULLETIN
SUMMARY
This modification will both re-life (via oversizing) and inspect (via non-destructive) test a defined number
of stringer joint fastener holes at Rib 18. This modification will delay the onset of cracking at the stringer
joint to beyond the LoV providing it is completed at the recommended time.
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.
AIRBUS disclaims any liability for the effect which the Service Bulletin may have on repairs performed
on the aircraft before embodiment of the Service Bulletin.
If the post Service Bulletin repair status is not covered by the SRM and for repairs outside of the SRM
covered by an RAS issued by AIRBUS, AIRBUS Customer Services Repair Engineering Support
(SEER1) s hould be contacted. Repair review will be done by AIRBUS at conditi ons 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
 NO
 VENDOR SB INVOLVED
 NO
DEFUEL/VENTILATION
 YES
 PRE-ENTRY CHECKLIST
 YES
NOTE
 (1)
: Service Bulletin must be accomplished.
MATERIAL PRICE INFORMATION
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
 QTY PER
A/C
PRICE PER
A/C (USD)
MAIN PARTS
Kit 570259B01R01
 2
 9,380.00
 Bolts and Nuts
EFFECTIVITY
This Service Bulletin is applicable to this (these) operator(s) :
50W IRA IRM
CONCURRENT REQUIREMENTS
None
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 2
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 3

@A300
SERVICE BULLETIN
SUMMARY
REFERENCES / REPERCUSSIONS
TFU
 None
OEB
 None
AOT
 None
SIL
 None
LINE MAINTENANCE AFFECTED
 No
LIFE LIMIT
 None
OTHER
 None
NATURE OF THE WORK
AIRCRAFT
 YES
EQUIPMENT
 NO
HARD
 NO
SOFT
 NO
OBRM
 NO
MANPOWER
Task 570259-831-895-001: Modification
TOTAL MANHOURS
 37.00
ELAPSED TIME (HOURS)
 11.50
APPENDICES
Appendix 01 - Elapsed Time Assumption
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 3
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 4

@A300
SERVICE BULLETIN
SUMMARY
**CONF ALL
LH SHOWN
RH SIMILAR
A
FRONT SPAR
REAR SPAR
CENTER SPAR
Z500
Z600
RIB18
A
A
STRINGERS 11
THRU 18 AT RIB 18
A_SB_570259_7_SAAA_01_00
Figure A-USAAA - Sheet 01
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 4
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 5

@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: 57
TITLE: WING - STRUCTURE - WING STRINGER JOINT AT RIB 18 (OVERSIZE
ATTACHMENT HOLES)
MODIFICATION No.: 13716H5748
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
B2-1C B2-203 B2K-3C
(2) Effectivity by MSN
0003 0080 0090 0160 0185 0187 0226 0244
(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
50W
 0003
IRA
 0080 0185 0187 0226
IRM
 0090 0160 0244
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 1
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 6

@A300
SERVICE BULLETIN
(4) Configuration by MSN
MSN
 CONFIGURATION
0003 0080 0090 0160 0185 0187 0226 0244
 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 570259B01R01
 2
 (1)
Consumable CMLB01
 1
NOTE
 (1)
: To accomplish this Service Bulletin on one aircraft you will require two of
Kit 570259B01R01.
B. CONCURRENT REQUIREMENTS
None
C. REASON
(1) History
Following fatigue analysis on the A300-B2/-B4 and A300-600, the Top Skin Stringer
Joints at Rib 18 have been identified as an area that is susceptible to Widespread
Fatigue Damage (WFD).
As a result of the FAA Part 26 rule change, all wing structural items deemed potentially
susceptible to WFD have been assessed. The top stringer joints at Rib 18 have been
highlighted as an area of uniform stress distribution, indicating that cracks may develop
in adjacent stringers at the same time which is known as Multi Element Damage (MED).
The stringer joint consists of 3 main load transferring parts: an overlapping flange,
two straps attached through the stringer web and a strap on the top flange. All the
components of the joint are attached with fasteners. The fastener holes were the subject
of a MED WFD analysis which showed that cracking could occur from a number of the
holes in the joint on Stringers 11, 12, 13, 14, 15, 16, 17 and 18.
(2) Objective/Action
This modification consists of a 1st oversize of the critical holes on Stringers 11, 12, 13,
14, 15, 16, 17 and 18. The crown strap does not need to be modified but will be
subjected to a detailed inspection (DET) during the embodiment of this Service Bulletin.
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 2
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 7

@A300
SERVICE BULLETIN
(3) Advantages
This modification will satisfy the requirements of the FAA Part 26 rule (14 Code of
Federal Regulations (CFR) 26 Subpart C) requiring WFD justification of susceptible
items.
This modification will both re-life (via oversizing) and inspect (via non-destructive) test a
defined number of stringer joint fastener holes at Rib 18. This modification will delay the
onset of cracking at the stringer joint to beyond the LoV providing it is completed at the
recommended time.
(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.
AIRBUS disclaims any liability for the effect which the Service Bulletin may have on
repairs performed on the aircraft before embodiment of the Service Bulletin.
If the post Service Bulletin repair status is not covered by the SRM and for repairs
outside of the SRM covered by an RAS issued by AIRBUS, AIRBUS Customer Services
Repair Engineering S upport ( SEER1) s hould be contacted. Repair review will be done
by AIRBUS at conditions of the Customer Services Catalogue.
D. DESCRIPTION
To accomplish this Service Bulletin it is necessary to :
Task 570259-831-895-001: Modification
(1) Do a Detailed Visual Inspection of the Top Wing Skin External Surface at Rib 18 LH
Wing
(2) Do a Detailed Visual Inspection of the Stringer Joint (including Attached Flange,
Stringer Web, Side Strap, Free Flange and Crown Strap) at Rib 18 LH Wing
(3) Modify the Stringer Joint Couplings at Rib 18 LH Wing
(4) Do a Detailed Visual Inspection of the Top Wing Skin External Surface at Rib 18 RH
Wing
(5) Do a Detailed Visual Inspection of the Stringer Joint (including Attached Flange,
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 3
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 8

@A300
SERVICE BULLETIN
Stringer Web, Side Strap, Free Flange and Crown Strap) at Rib 18 RH Wing
(6) Modify the Stringer Joint Couplings at Rib 18 RH Wing
E. COMPLIANCE
(1) Classification
MANDATORY: Service Bulletin must be accomplished.
(2) Accomplishment Timescale
Table 1, Config. 001 - Modify the Stringer Joint Couplings at Rib 18 LH and RH Wing
THRESHOLD
 Grace Period (Whichever occurs first from the
issuance of this Service Bulletin)
AIRCRAFT
Flight Cycles
(FC)
Flying Hours
(FH)
Flight Cycles
(FC)
Flying Hours
(FH)
Months
A300B2
 38600 FC
 47700 FH
 700 FC
 750 FH
 12
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
given 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
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 570259-831-895-001: Modification
Get Access
 1.50
On Aircraft
Do a Detailed Visual Inspection of the Top Wing Skin
External Surface at Rib 18 LH Wing
0.50
Do a Detailed Visual Inspection of the Stringer Joint
(including Attached Flange, Stringer Web, Side Strap,
Free Flange and Crown Strap) at Rib 18 LH Wing
0.50
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 4
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 9

@A300
SERVICE BULLETIN
Task 570259-831-895-001: Modification
Modify the Stringer Joint Couplings at Rib 18 LH Wing
 16.00
Do a Detailed Visual Inspection of the Top Wing Skin
External Surface at Rib 18 RH Wing
0.50
Do a Detailed Visual Inspection of the Stringer Joint
(including Attached Flange, Stringer Web, Side Strap,
Free Flange and Crown Strap) at Rib 18 RH Wing
0.50
Modify the Stringer Joint Couplings at Rib 18 RH Wing
 16.00
Close-Up
 1.50
TOTAL MANHOURS
 37.00
ELAPSED TIME (HOURS)
 11.50
NOTE
: For an explanation of the manhours and elapsed time, refer to the Gantt
Chart, Fig. A-UAAAA
 given in Appendix 01 - Elapsed Time Assumption .
H. WEIGHT AND BALANCE
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 +0.07 KG (+0.1543 LB)
Effect on Balance +2.284 KGM (+16.520 LB.FT )
I. ELECTRICAL LOAD DATA
Not Changed
J. REFERENCES
Aircraft Maintenance Manual (AMM)
 24-00-00 28-10-00 28-11-14
28-21-00 28-22-00
Consumable Material List (CML)
Elec. Std. Practices Manual (ESPM)
 20-55-00
Non Destructive Test Manual (NTM)
 51-40-00 57-10-01
Standards Manual (SM)
Structural Repair Manual (SRM)
 51-30-00 51-30-30 51-30-31
51-30-38 51-40-12 51-40-20
51-49-00
Weight and Balance Manual (WBM)
 Chapter 1-00-07
K. PUBLICATION AFFECTED
None
L. INTERCHANGEABILITY/MIXABILITY
Not Applicable
M. SPARES
None
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 5
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 10

@A300
SERVICE BULLETIN
This Page Intentionally Left Blank
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 6
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 11

@A300
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 570259B01R01
 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 570259B01R01
Cost
 4,690.00 USD
Availability
 150 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.
C. LIST OF COMPONENTS
Kit 570259B01R01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
1
 NSA5479BV4-7X
 24
 BOLT
2
 NSA5479BV4-10X
 16
 BOLT
3
 NSA5477VHK4-5
 16
 BOLT
4
 NSA5477VHK4-8
 48
 BOLT
5
 NSA5472-4K7
 104
 NUT
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 7
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 12

@A300
SERVICE BULLETIN
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
: To accomplish this Service Bulletin on one aircraft you will require two of Kit
570259B01R01.
D. LIST OF MATERIALS - OPERATOR SUPPLIED
(1) Consumable Materials
Consumable CMLB01
ITEM
 DESCRIPTION
 REFERENCE TO CML
MAT. No.
QTY PER A/C
 SEE
NOTES
Polysulfide Sealant - Fuel Tank
Fillet
06ABB1
 As required
(2) Components
None
(3) Equipment
None
E. PARTS TO BE RE-IDENTIFIED BY OPERATOR
None
F. TOOLING
None
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 8
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 13

@A300
SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS
Task 570259-831-895-001 - Modification
WARNING
: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS
INCLUDED IN THE REFERENCED PROCEDURES.
WARNING
: THIS PROCEDURE USES A FUEL SYSTEM ITEM THAT IS IN A CATEGORY
KNOWN AS A CRITICAL DESIGN CONFIGURATION CONTROL LIMITATION
(CDCCL) CDCCL IDENTIFIES AN ITEM THAT CAN BE THE SOURCE OF A
POSSIBLE FUEL TANK IGNITION. YOU MUST KEEP ALL CDCCL ITEMS IN
THE APPROVED CONFIGURATION. DAMAGE, WEAR OR CHANGES TO A
CDCCL ITEM CAN CAUSE A POSSIBLE FUEL TANK EXPLOSION.
CAUTION
: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP
ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY
AND MECHANICALLY SERVICEABLE) . WHEN YOU DO MAINTENANCE
WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,
COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO
THIS:
- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS
NECESSARY ON WIRING AND COMPONENTS.
- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND
OTHER CONTAMINATION.
THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION
AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.
IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00.
NOTE
: The accomplishment instructions of this Service Bulletin include procedures given
in other documents or in other sections of the Service Bulletin. When the words
"refer to" are used and the operator has a procedure accepted by the local
authority he belongs to, the accepted alternative procedure can be used. When the
words "in accordance with" are used then the given procedure must be followed.
NOTE
: The access and close-up instructions, not comprising return to service tests, in this
Service Bulletin do not constitute or affect the technical intent of the Service
Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or
close-up steps to add flexibility to their maintenance operations as long as the
technical intent of the Service Bulletin is met within the set parameters.
NOTE
: Manual titles given in the accomplishment instructions are referred to by acronyms.
Refer to paragraph 1.J., References, for the definition of acronyms.
NOTE
: This Service Bulletin is classified mandatory or expected to be classified mandatory
by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these
accomplishment instructions are Required for Compliance (RC) and must be done
to comply with the AD. 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
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 9
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 14

@A300
SERVICE BULLETIN
the aircraft can be put back into a serviceable condition.
Task Associated Data
Zone
500 550 600 650
Access
Door
 550CB 650CB
Panel
 550BB 650BB
Manpower
TOTAL MANHOURS
 37.00
ELAPSED TIME (HOURS)
 11.50
A. GENERAL
(1) Subtask 570259-910-401-001 - Standard Practices
Manpower Resources
Skills
 NON SPECIFIC
References
Consumable Material List (CML)
Structural Repair Manual (SRM)
 51-30-00
51-30-30
51-30-31
51-30-38
51-40-12
51-40-20
51-49-00
(a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to
Consumable Material List (CML).
(b) To torque tighten the standard threaded fasteners in accordance with SRM
51-49-00.
(c) Remove and install fasteners in metallic structure in accordance with SRM
51-30-31.
(d) Apply sealant in accordance with SRM 51-40-20.
(e) Renew protective finish in accordance with SRM 51-40-12.
(f) Obtain fastener hole diameters and drill and "de-burr" data in accordance with SRM
51-30-38.
(g) If alternative and substitute fasteners have to be used, you must make sure that the
associated nut/collar are compatible in accordance with SRM 51-30-31 ’ Mating
Part’ column.
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 10
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 15

@A300
SERVICE BULLETIN
(h) 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 570259-839-401-001 - Administrative
Manpower Resources
Skills
 NON SPECIFIC
Write in the applicable aircraft records that you have done all the work given in this
Service Bulletin.
B. PREPARATION
(1) Subtask 570259-941-402-001 - Job Set-up
Work Zones and Access Panels
Zone
 Access/Work location
550
 Access
 Door 550CB
650
 Access
 Door 650CB
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 24-00-00, Page Block 301
28-10-00, Page Block 301
28-22-00, Page Block 301
NOTE
: The items given in this note shall be considered as the basic Aircraft
configuration before you start a maintenance task:
- Aircraft on the ground resting on landing gear (the ground safety
locks and the wheel chocks are in position on the landing gear)
- Engine shut down, thrust reversers closed and locked
- Aircraft in clean configuration
- Parking brake applied
- Aircraft electrical network de-energized
- Hydraulic system s depressurized
- Access to the cockpit and cabin is available
- All circuit breakers are in closed position
- All controls in NORM, AUTO or OFF position.
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 11
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 16

@A300
SERVICE BULLETIN
(a) Make sure that the aircraft is electrically grounded, refer to AMM 24-00-00, Page
Block 301.
(b) Defuel all of the aircraft fuel tanks, refer to AMM 28-22-00, Page Block 301.
(c) Prepare the aircraft as specified in AMM Task ’STORAGE - SERVICING (Fuel
Tank Draining, Venting and Entry)’, refer to AMM 28-10-00, Page Block 301.
1
 Before you go into a fuel tank you must complete the Pre-Entry Checklist,
refer to AMM 28-10-00, Page Block 301.
(2) Subtask 570259-010-402-001 - Remove/Open for Access
Work Zones and Access Panels
Zone
 Access/Work location
550
 Access
 Panel 550BB
650
 Access
 Panel 650BB
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 28-11-14, Page Block 401
28-21-00, Page Block 601
(a) Put platforms in position to get access to the wing tanks outer - Zones 550 LH (650
RH), refer to AMM 28-11-14, Page Block 401 and AMM 28-21-00, Page Block 601.
(b) Remove the manhole covers for the wing tanks outer 550BB LH and (650BB RH),
refer to AMM 28-11-14, Page Block 401 and AMM 28-21-00, Page Block 601.
C. PROCEDURE
(1) Subtask 570259-220-403-001 - Do a Detailed Visual Inspection of the Top Wing
Skin External Surface at Rib 18 LH Wing
Work Zones and Access Panels
Zone
 Access/Work location
500
 Work location
 Rib 18
from Stringer 11 to Stringer 18
Manpower Resources
Manhours
 0.50
Minimum number of person
 1
Subtask elapsed time
 0.50
Skills
 AIRFRAME
References
Non Destructive Test Manual (NTM)
 51-40-00
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 12
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 17

@A300
SERVICE BULLETIN
References
Fig. A-UBBAA
Detailed Visual Inspection of the Top
Wing Skin and Stringer Joint at Rib 18
Sheet 01
Sheet 02
(a) As shown in Fig. A-UBBAA Sheet 01
 and Fig. A-UBBAA Sheet 02
 , inspect the wing
skin:
1
 At Rib 18, STGR 11 to STRG 18, do a Detailed Visual Inspection (DET) of the
top wing skin external surface in accordance with NTM 51-40-00.
- If damage is found contact AIRBUS
- If no damage is found continue with the worksteps below.
(2) Subtask 570259-220-401-001 - Do a Detailed Visual Inspection of the Stringer Joint
(including Attached Fla nge, Stringer Web, Side Strap, Free Flange and Crown
Strap) at Rib 18 LH Wing
Work Zones and Access Panels
Zone
 Access/Work location
500
Manpower Resources
Manhours
 0.50
Minimum number of person
 1
Subtask elapsed time
 0.50
Skills
 AIRFRAME
References
Non Destructive Test Manual (NTM)
 51-40-00
Fig. A-UBBAA
Detailed Visual Inspection of the Top
Wing Skin and Stringer Joint at Rib 18
Sheet 01
Sheet 02
(a) As shown in Fig. A-UBBAA Sheet 01
 and Fig. A-UBBAA Sheet 02
 , inspect the
stringer joint:
1
 At Rib 18, STGR 11 to STRG 18, do a DET of the stringer joint (including
attached flange, stringer web, side strap, free flange and crown strap) in
accordance with NTM 51-40-00.
- If damage is found contact AIRBUS
- If no damage is found continue with the worksteps below.
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 13
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 18

@A300
SERVICE BULLETIN
(3) Subtask 570259-831-401-001 - Modify the Str inger Joint Couplings at Rib 18 LH
Wing
Work Zones and Access Panels
Zone
 Access/Work location
500
 Work location
 Rib 18
from Stringer 11 to Stringer 18
Manpower Resources
Manhours
 16.00
Minimum number of person
 2
Subtask elapsed time
 8.00
Skills
 AIRFRAME
Material necessary to do the job
Kit 570259B01R01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
1
 NSA5479BV4-7X
 24
 BOLT
2
 NSA5479BV4-10X
 16
 BOLT
3
 NSA5477VHK4-5
 16
 BOLT
4
 NSA5477VHK4-8
 48
 BOLT
5
 NSA5472-4K7
 104
 NUT
NOTE
: To accomplish this Service Bulletin on one aircraft you will require two of
Kit 570259B01R01.
Consumable CMLB01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Polysulfide Sealant - Fuel
Tank Fillet
06ABB1
 As required
References
Non Destructive Test Manual (NTM)
 57-10-01
Structural Repair Manual (SRM)
 51-30-38
Fig. A-UBAAA
Modification of the Stringer Joint
Couplings at Rib 18
Sheet 01
Sheet 02
Sheet 03
(a) As shown in Fig. A-UBAAA Sheet 01
 and Fig. A-UBAAA Sheet 02
 , modify the
stringer joint couplings:
1
 At Rib 18, STGR 11 and STGR 14, remove:
4 Rivet Discard
12 Bolt Discard
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 14
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 19

@A300
SERVICE BULLETIN
12 Nut Discard
2
 As shown in Fig. A-UBAAA Sheet 01
 , View B and Fig. A-UBAAA Sheet
02
, View F, drill the fastener holes to first oversize in the upper wing skin
in accordance with SRM 51-30-38 and the fastener table on Fig. A-UBAAA
Sheet 03
.
3
 As shown in Fig. A-UBAAA Sheet 01
 ,V i e wBa n d Fig. A-UBAAA Sheet 02
 ,
View F, do a Special Detailed Inspection (SDET) (Roto-probe) of the fastener
holes in the upper wing skin, refer to NTM 57-10-01.
- If damage is found contact AIRBUS
- If no damage is found continue with the worksteps below.
4
 At Rib 18, STGR 11 and STGR 14, refer to Fig. A-UBAAA Sheet 01
 ,V i e wB
and Fig. A-UBAAA Sheet 02
 ,V i e wG ,u s e :
Polysulfide Sealant
- Fuel Tank Fillet
06ABB1 As required
and wet install:
4 Bolt NSA5477VHK4-5 Item 3
12 Bolt NSA5477VHK4-8 Item 4
16 Nut NSA5472-4K7 Item 5
5
 At Rib 18, STGR 12 and STGR 15, remove:
4 Rivet Discard
12 Bolt Discard
12 Nut Discard
6
 As shown in Fig. A-UBAAA Sheet 01
 , View B and Fig. A-UBAAA Sheet
02
, View F, drill the fastener holes to first oversize in the upper wing skin
in accordance with SRM 51-30-38 and the fastener table on Fig. A-UBAAA
Sheet 03
.
7
 As shown in Fig. A-UBAAA Sheet 01
 ,V i e wBa n d Fig. A-UBAAA Sheet 02
 ,
View F, do a SDET (Roto-probe) of the fastener holes in the upper wing skin,
refer to NTM 57-10-01.
- If damage is found contact AIRBUS
- If no damage is found continue with the worksteps below.
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 15
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 20

@A300
SERVICE BULLETIN
8
 At Rib 18, STGR 12 and STGR 15, refer to Fig. A-UBAAA Sheet 01
 ,V i e wB
and Fig. A-UBAAA Sheet 02
 ,V i e wG ,u s e :
Polysulfide Sealant
- Fuel Tank Fillet
06ABB1 As required
and wet install:
4 Bolt NSA5477VHK4-5 Item 3
12 Bolt NSA5477VHK4-8 Item 4
16 Nut NSA5472-4K7 Item 5
9
 At Rib 18, STGR 13 and STGR 17, remove:
4 Rivet Discard
12 Bolt Discard
12 Nut Discard
10
 As shown in Fig. A-UBAAA Sheet 01
 , View B and Fig. A-UBAAA Sheet
02
, View F, drill the fastener holes to first oversize in the upper wing skin
in accordance with SRM 51-30-38 and the fastener table on Fig. A-UBAAA
Sheet 03
.
11
 As shown in Fig. A-UBAAA Sheet 01
 ,V i e wBa n d Fig. A-UBAAA Sheet 02
 ,
View F, do a SDET (Roto-probe) of the fastener holes in the upper wing skin,
refer to NTM 57-10-01.
- If damage is found contact AIRBUS
- If no damage is found continue with the worksteps below.
12
 At Rib 18, STGR 13 and STGR 17, refer to Fig. A-UBAAA Sheet 01
 ,V i e wB
and Fig. A-UBAAA Sheet 02
 ,V i e wG ,u s e :
Polysulfide Sealant
- Fuel Tank Fillet
06ABB1 As required
and wet install:
4 Bolt NSA5477VHK4-5 Item 3
12 Bolt NSA5477VHK4-8 Item 4
16 Nut NSA5472-4K7 Item 5
13
 At Rib 18, STGR 16 and STGR 18, remove:
4 Rivet Discard
12 Bolt Discard
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 16
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 21

@A300
SERVICE BULLETIN
12 Nut Discard
14
 As shown in Fig. A-UBAAA Sheet 01
 , View B and Fig. A-UBAAA Sheet
02
, View F, drill the fastener holes to first oversize in the upper wing skin
in accordance with SRM 51-30-38 and the fastener table on Fig. A-UBAAA
Sheet 03
.
15
 As shown in Fig. A-UBAAA Sheet 01
 ,V i e wBa n d Fig. A-UBAAA Sheet 02
 ,
View F, do a SDET (Roto-probe) of the fastener holes in the upper wing skin,
refer to NTM 57-10-01.
- If damage is found contact AIRBUS
- If no damage is found continue with the worksteps below.
16
 At Rib 18, STGR 16 and STGR 18, refer to Fig. A-UBAAA Sheet 01
 ,V i e wB
and Fig. A-UBAAA Sheet 02
 ,V i e wG ,u s e :
Polysulfide Sealant
- Fuel Tank Fillet
06ABB1 As required
and wet install:
4 Bolt NSA5477VHK4-5 Item 3
12 Bolt NSA5477VHK4-8 Item 4
16 Nut NSA5472-4K7 Item 5
(b) As shown in Fig. A-UBAAA Sheet 01
 , View B and Fig. A-UBAAA Sheet 02
 ,V i e wD ,
modify the rib cleat couplings:
1
 At Rib 18, STGR 11 and STGR 14, remove:
10 Bolt Discard
10 Nut Discard
2
 As shown in Fig. A-UBAAA Sheet 01
 ,V i e wBa n d Fig. A-UBAAA Sheet 02
 ,
View D, drill the fastener holes to first oversize in the cleat in accordance with
SRM 51-30-38 and the fastener table on Fig. A-UBAAA Sheet 03
 .
3
 As shown in Fig. A-UBAAA Sheet 01
 ,V i e wBa n d Fig. A-UBAAA Sheet 02
 ,
View D, do a SDET (Roto-probe) of the fastener holes in the cleat, refer to
NTM 57-10-01.
- If damage is found contact AIRBUS
- If no damage is found continue with the worksteps below.
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 17
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 22

@A300
SERVICE BULLETIN
4
 At Rib 18, STGR 11 and STGR 14, refer to Fig. A-UBAAA Sheet 01
 ,V i e wB
and Fig. A-UBAAA Sheet 02
 ,V i e wE ,u s e :
Polysulfide Sealant
- Fuel Tank Fillet
06ABB1 As required
and wet install:
6 Bolt NSA5479BV4-7X Item 1
4 Bolt NSA5479BV4-10X Item 2
10 Nut NSA5472-4K7 Item 5
5
 At Rib 18, STGR 12 and STGR 15, remove:
10 Bolt Discard
10 Nut Discard
6
 As shown in Fig. A-UBAAA Sheet 01
 ,V i e wBa n d Fig. A-UBAAA Sheet 02
 ,
View D, drill the fastener holes to first oversize in the cleat in accordance with
SRM 51-30-38 and the fastener table on Fig. A-UBAAA Sheet 03
 .
7
 As shown in Fig. A-UBAAA Sheet 01
 ,V i e wBa n d Fig. A-UBAAA Sheet 02
 ,
View D, do a SDET (Roto-probe) of the fastener holes in the cleat, refer to
NTM 57-10-01.
- If damage is found contact AIRBUS
- If no damage is found continue with the worksteps below.
8
 At Rib 18, STGR 12 and STGR 15, refer to Fig. A-UBAAA Sheet 01
 ,V i e wB
and Fig. A-UBAAA Sheet 02
 ,V i e wE ,u s e :
Polysulfide Sealant
- Fuel Tank Fillet
06ABB1 As required
and wet install:
6 Bolt NSA5479BV4-7X Item 1
4 Bolt NSA5479BV4-10X Item 2
10 Nut NSA5472-4K7 Item 5
9
 At Rib 18, STGR 13 and STGR 17, remove:
10 Bolt Discard
10 Nut Discard
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 18
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 23

@A300
SERVICE BULLETIN
10
 As shown in Fig. A-UBAAA Sheet 01
 ,V i e wBa n d Fig. A-UBAAA Sheet 02
 ,
View D, drill the fastener holes to first oversize in the cleat in accordance with
SRM 51-30-38 and the fastener table on Fig. A-UBAAA Sheet 03
 .
11
 As shown in Fig. A-UBAAA Sheet 01
 ,V i e wBa n d Fig. A-UBAAA Sheet 02
 ,
View D, do a SDET (Roto-probe) of the fastener holes in the cleat, refer to
NTM 57-10-01.
- If damage is found contact AIRBUS
- If no damage is found continue with the worksteps below.
12
 At Rib 18, STGR 13 and STGR 17, refer to Fig. A-UBAAA Sheet 01
 ,V i e wB
and Fig. A-UBAAA Sheet 02
 ,V i e wE ,u s e :
Polysulfide Sealant
- Fuel Tank Fillet
06ABB1 As required
and wet install:
6 Bolt NSA5479BV4-7X Item 1
4 Bolt NSA5479BV4-10X Item 2
10 Nut NSA5472-4K7 Item 5
13
 At Rib 18, STGR 16 and STGR 18, remove:
10 Bolt Discard
10 Nut Discard
14
 As shown in Fig. A-UBAAA Sheet 01
 ,V i e wBa n d Fig. A-UBAAA Sheet 02
 ,
View D, drill the fastener holes to first oversize in the cleat in accordance with
SRM 51-30-38 and the fastener table on Fig. A-UBAAA Sheet 03
 .
15
 As shown in Fig. A-UBAAA Sheet 01
 ,V i e wBa n d Fig. A-UBAAA Sheet 02
 ,
View D, do a SDET (Roto-probe) of the fastener holes in the cleat, refer to
NTM 57-10-01.
- If damage is found contact AIRBUS
- If no damage is found continue with the worksteps below.
16
 At Rib 18, STGR 16 and STGR 18 Fig. A-UBAAA Sheet 01
 , View B and Fig.
A-UBAAA Sheet 02
,V i e wE ,u s e :
Polysulfide Sealant
- Fuel Tank Fillet
06ABB1 As required
and wet install:
6 Bolt NSA5479BV4-7X Item 1
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 19
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 24

@A300
SERVICE BULLETIN
4 Bolt NSA5479BV4-10X Item 2
10 Nut NSA5472-4K7 Item 5
(4) Subtask 570259-220-404-001 - Do a Detailed Visual Inspection of the Top Wing
Skin External Surface at Rib 18 RH Wing
Work Zones and Access Panels
Zone
 Access/Work location
600
 Work location
 Rib 18
from Stringer 11 to Stringer 18
Manpower Resources
Manhours
 0.50
Minimum number of person
 1
Subtask elapsed time
 0.50
Skills
 AIRFRAME
References
Non Destructive Test Manual (NTM)
 51-40-00
Fig. A-UBBAA
Detailed Visual Inspection of the Top
Wing Skin and Stringer Joint at Rib 18
Sheet 01
Sheet 02
(a) As shown in Fig. A-UBBAA Sheet 01
 and Fig. A-UBBAA Sheet 02
 , inspect the wing
skin:
1
 At Rib 18, STGR 11 to STRG 18, do a DET of the top wing skin external
surface in accordance with NTM 51-40-00.
- If damage is found contact AIRBUS
- If no damage is found continue with the worksteps below.
(5) Subtask 570259-220-402-001 - Do a Detailed Visual Inspection of the Stringer Joint
(including Attached Fla nge, Stringer Web, Side Strap, Free Flange and Crown
Strap) at Rib 18 RH Wing
Work Zones and Access Panels
Zone
 Access/Work location
600
Manpower Resources
Manhours
 0.50
Minimum number of person
 1
Subtask elapsed time
 0.50
Skills
 AIRFRAME
References
Non Destructive Test Manual (NTM)
 51-40-00
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 20
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 25

@A300
SERVICE BULLETIN
References
Fig. A-UBBAA
Detailed Visual Inspection of the Top
Wing Skin and Stringer Joint at Rib 18
Sheet 01
Sheet 02
(a) As shown in Fig. A-UBBAA Sheet 01
 and Fig. A-UBBAA Sheet 02
 , inspect the
stringer joint:
1
 At Rib 18, STGR 11 to STRG 18, do a DET of the stringer joint (including
attached flange, stringer web, side strap, free flange and crown strap) in
accordance with NTM 51-40-00.
- If damage is found contact AIRBUS
- If no damage is found continue with the worksteps below.
(6) Subtask 570259-831-402-001 - Modify the Str inger Joint Couplings at Rib 18 RH
Wing
Work Zones and Access Panels
Zone
 Access/Work location
600
 Work location
 Rib 18
from Stringer 11 to Stringer 18
Manpower Resources
Manhours
 16.00
Minimum number of person
 2
Subtask elapsed time
 8.00
Skills
 AIRFRAME
Material necessary to do the job
Kit 570259B01R01
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
1
 NSA5479BV4-7X
 24
 BOLT
2
 NSA5479BV4-10X
 16
 BOLT
3
 NSA5477VHK4-5
 16
 BOLT
4
 NSA5477VHK4-8
 48
 BOLT
5
 NSA5472-4K7
 104
 NUT
NOTE
: To accomplish this Service Bulletin on one aircraft you will require two of
Kit 570259B01R01.
Consumable CMLB01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Polysulfide Sealant - Fuel
Tank Fillet
06ABB1
 As required
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 21
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 26

@A300
SERVICE BULLETIN
References
Non Destructive Test Manual (NTM)
 57-10-01
Structural Repair Manual (SRM)
 51-30-38
Fig. A-UBAAA
Modification of the Stringer Joint
Couplings at Rib 18
Sheet 01
Sheet 02
Sheet 03
(a) As shown in Fig. A-UBAAA Sheet 01
 and Fig. A-UBAAA Sheet 02
 , modify the
stringer joint couplings:
1
 At Rib 18, STGR 11 and STGR 14, remove:
4 Rivet Discard
12 Bolt Discard
12 Nut Discard
2
 As shown in Fig. A-UBAAA Sheet 01
 , View B and Fig. A-UBAAA Sheet
02
, View F, drill the fastener holes to first oversize in the upper wing skin
in accordance with SRM 51-30-38 and the fastener table on Fig. A-UBAAA
Sheet 03
.
3
 As shown in Fig. A-UBAAA Sheet 01
 ,V i e wBa n d Fig. A-UBAAA Sheet 02
 ,
View F, do a Special Detailed Inspection (SDET) (Roto-probe) of the fastener
holes in the upper wing skin, refer to NTM 57-10-01.
- If damage is found contact AIRBUS
- If no damage is found continue with the worksteps below.
4
 At Rib 18, STGR 11 and STGR 14, refer to Fig. A-UBAAA Sheet 01
 ,V i e wB
and Fig. A-UBAAA Sheet 02
 ,V i e wG ,u s e :
Polysulfide Sealant
- Fuel Tank Fillet
06ABB1 As required
and wet install:
4 Bolt NSA5477VHK4-5 Item 3
12 Bolt NSA5477VHK4-8 Item 4
16 Nut NSA5472-4K7 Item 5
5
 At Rib 18, STGR 12 and STGR 15, remove:
4 Rivet Discard
12 Bolt Discard
12 Nut Discard
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 22
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 27

@A300
SERVICE BULLETIN
6
 As shown in Fig. A-UBAAA Sheet 01
 , View B and Fig. A-UBAAA Sheet
02
, View F, drill the fastener holes to first oversize in the upper wing skin
in accordance with SRM 51-30-38 and the fastener table on Fig. A-UBAAA
Sheet 03
.
7
 As shown in Fig. A-UBAAA Sheet 01
 ,V i e wBa n d Fig. A-UBAAA Sheet 02
 ,
View F, do a SDET (Roto-probe) of the fastener holes in the upper wing skin,
refer to NTM 57-10-01.
- If damage is found contact AIRBUS
- If no damage is found continue with the worksteps below.
8
 At Rib 18, STGR 12 and STGR 15, refer to Fig. A-UBAAA Sheet 01
 ,V i e wB
and Fig. A-UBAAA Sheet 02
 ,V i e wG ,u s e :
Polysulfide Sealant
- Fuel Tank Fillet
06ABB1 As required
and wet install:
4 Bolt NSA5477VHK4-5 Item 3
12 Bolt NSA5477VHK4-8 Item 4
16 Nut NSA5472-4K7 Item 5
9
 At Rib 18, STGR 13 and STGR 17, remove:
4 Rivet Discard
12 Bolt Discard
12 Nut Discard
10
 As shown in Fig. A-UBAAA Sheet 01
 , View B and Fig. A-UBAAA Sheet
02
, View F, drill the fastener holes to first oversize in the upper wing skin
in accordance with SRM 51-30-38 and the fastener table on Fig. A-UBAAA
Sheet 03
.
11
 As shown in Fig. A-UBAAA Sheet 01
 ,V i e wBa n d Fig. A-UBAAA Sheet 02
 ,
View F, do a SDET (Roto-probe) of the fastener holes in the upper wing skin,
refer to NTM 57-10-01.
- If damage is found contact AIRBUS
- If no damage is found continue with the worksteps below.
12
 At Rib 18, STGR 13 and STGR 17, refer to, Fig. A-UBAAA Sheet 01
 ,V i e wB
and Fig. A-UBAAA Sheet 02
 ,V i e wG ,u s e :
Polysulfide Sealant
- Fuel Tank Fillet
06ABB1 As required
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 23
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 28

@A300
SERVICE BULLETIN
and wet install:
4 Bolt NSA5477VHK4-5 Item 3
12 Bolt NSA5477VHK4-8 Item 4
16 Nut NSA5472-4K7 Item 5
13
 At Rib 18, STGR 16 and STGR 18, remove:
4 Rivet Discard
12 Bolt Discard
12 Nut Discard
14
 As shown in Fig. A-UBAAA Sheet 01
 , View B and Fig. A-UBAAA Sheet
02
, View F, drill the fastener holes to first oversize in the upper wing skin
in accordance with SRM 51-30-38 and the fastener table on Fig. A-UBAAA
Sheet 03
.
15
 As shown in Fig. A-UBAAA Sheet 01
 ,V i e wBa n d Fig. A-UBAAA Sheet 02
 ,
View F, do a SDET (Roto-probe) of the fastener holes in the upper wing skin,
refer to NTM 57-10-01.
- If damage is found contact AIRBUS
- If no damage is found continue with the worksteps below.
16
 At Rib 18, STGR 16 and STGR 18, refer to Fig. A-UBAAA Sheet 01
 ,V i e wB
and Fig. A-UBAAA Sheet 02
 ,V i e wG ,u s e :
Polysulfide Sealant
- Fuel Tank Fillet
06ABB1 As required
and wet install:
4 Bolt NSA5477VHK4-5 Item 3
12 Bolt NSA5477VHK4-8 Item 4
16 Nut NSA5472-4K7 Item 5
(b) As shown in Fig. A-UBAAA Sheet 01
 , View B and Fig. A-UBAAA Sheet 02
 ,V i e wD ,
modify the rib cleat couplings:
1
 At Rib 18, STGR 11 and STGR 14, remove:
10 Bolt Discard
10 Nut Discard
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 24
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 29

@A300
SERVICE BULLETIN
2
 As shown in Fig. A-UBAAA Sheet 01
 ,V i e wBa n d Fig. A-UBAAA Sheet 02
 ,
View D, drill the fastener holes to first oversize in the cleat in accordance with
SRM 51-30-38 and the fastener table on Fig. A-UBAAA Sheet 03
 .
3
 As shown in Fig. A-UBAAA Sheet 01
 ,V i e wBa n d Fig. A-UBAAA Sheet 02
 ,
View D, do a SDET (Roto-probe) of the fastener holes in the cleat, refer to
NTM 57-10-01.
- If damage is found contact AIRBUS
- If no damage is found continue with the worksteps below.
4
 At Rib 18, STGR 11 and STGR 14, refer to Fig. A-UBAAA Sheet 01
 ,V i e wB
and Fig. A-UBAAA Sheet 02
 ,V i e wE ,u s e :
Polysulfide Sealant
- Fuel Tank Fillet
06ABB1 As required
and wet install:
6 Bolt NSA5479BV4-7X Item 1
4 Bolt NSA5479BV4-10X Item 2
10 Nut NSA5472-4K7 Item 5
5
 At Rib 18, STGR 12 and STGR 15, remove:
10 Bolt Discard
10 Nut Discard
6
 As shown in Fig. A-UBAAA Sheet 01
 ,V i e wBa n d Fig. A-UBAAA Sheet 02
 ,
View D, drill the fastener holes to first oversize in the cleat in accordance with
SRM 51-30-38 and the fastener table on Fig. A-UBAAA Sheet 03
 .
7
 As shown in Fig. A-UBAAA Sheet 01
 ,V i e wBa n d Fig. A-UBAAA Sheet 02
 ,
View D, do a SDET (Roto-probe) of the fastener holes in the cleat, refer to
NTM 57-10-01.
- If damage is found contact AIRBUS
- If no damage is found continue with the worksteps below.
8
 At Rib 18, STGR 12 and STGR 15, refer to Fig. A-UBAAA Sheet 01
 ,V i e wB
and Fig. A-UBAAA Sheet 02
 ,V i e wE ,u s e :
Polysulfide Sealant
- Fuel Tank Fillet
06ABB1 As required
and wet install:
6 Bolt NSA5479BV4-7X Item 1
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 25
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 30

@A300
SERVICE BULLETIN
4 Bolt NSA5479BV4-10X Item 2
10 Nut NSA5472-4K7 Item 5
9
 At Rib 18, STGR 13 and STGR 17, remove:
10 Bolt Discard
10 Nut Discard
10
 As shown in Fig. A-UBAAA Sheet 01
 ,V i e wBa n d Fig. A-UBAAA Sheet 02
 ,
View D, drill the fastener holes to first oversize in the cleat in accordance with
SRM 51-30-38 and the fastener table on Fig. A-UBAAA Sheet 03
 .
11
 As shown in Fig. A-UBAAA Sheet 01
 ,V i e wBa n d Fig. A-UBAAA Sheet 02
 ,
View D, do a SDET (Roto-probe) of the fastener holes in the cleat, refer to
NTM 57-10-01.
- If damage is found contact AIRBUS
- If no damage is found continue with the worksteps below.
12
 At Rib 18, STGR 13 and STGR 17, refer to Fig. A-UBAAA Sheet 01
 ,V i e wB
and Fig. A-UBAAA Sheet 02
 ,V i e wE ,u s e :
Polysulfide Sealant
- Fuel Tank Fillet
06ABB1 As required
and wet install:
6 Bolt NSA5479BV4-7X Item 1
4 Bolt NSA5479BV4-10X Item 2
10 Nut NSA5472-4K7 Item 5
13
 At Rib 18, STGR 16 and STGR 18, remove:
10 Bolt Discard
10 Nut Discard
14
 As shown in Fig. A-UBAAA Sheet 01
 ,V i e wBa n d Fig. A-UBAAA Sheet 02
 ,
View D, drill the fastener holes to first oversize in the cleat in accordance with
SRM 51-30-38 and the fastener table on Fig. A-UBAAA Sheet 03
 .
15
 As shown in Fig. A-UBAAA Sheet 01
 ,V i e wBa n d Fig. A-UBAAA Sheet 02
 ,
View D, do a SDET (Roto-probe) of the fastener holes in the cleat, refer to
NTM 57-10-01.
- If damage is found contact AIRBUS
- If no damage is found continue with the worksteps below.
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 26
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 31

@A300
SERVICE BULLETIN
16
 At Rib 18, STGR 16 and STGR 18 Fig. A-UBAAA Sheet 01
 , View B and Fig.
A-UBAAA Sheet 02
,V i e wE ,u s e :
Polysulfide Sealant
- Fuel Tank Fillet
06ABB1 As required
and wet install:
6 Bolt NSA5479BV4-7X Item 1
4 Bolt NSA5479BV4-10X Item 2
10 Nut NSA5472-4K7 Item 5
D. TEST
None
E. CLOSE-UP
(1) Subtask 570259-942-401-001 - Close-up
Work Zones and Access Panels
Zone
 Access/Work location
550
 Access
 Panel 550BB
650
 Access
 Panel 650BB
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 28-10-00, Page Block 301
28-11-14, Page Block 401
28-21-00, Page Block 601
(a) Make sure that the work areas are clean and clear of tools and other items of
equipment.
(b) Install the manhole covers for the wing tanks outer 550BB LH and (650BB RH),
refer to AMM 28-11-14, Page Block 401 and AMM 28-21-00, Page Block 601.
(c) Do the Close Up procedure as specified in AMM Task ’STORAGE - SERVICING
(Fuel Tank Draining, Venting and Entry - Leaving a Fuel Tank)’, refer to AMM
28-10-00, Page Block 301.
(d) Remove the access platforms from the wing tanks outer - Zones 550 LH (650 RH),
refer to AMM 28-11-14, Page Block 401 and AMM 28-21-00, Page Block 601.
(e) Put the aircraft back to its initial configuration.
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 27
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 32

@A300
SERVICE BULLETIN
**CONF ALL
LH SHOWN
RH SIMILAR
A
FRONT SPAR
REAR SPAR
CENTER SPAR
Z500
Z600
NOTE:
AREA OF MODIFICATION
RIB18
A
A
STRINGERS 11
THRU 18 AT RIB 18
STGR11
STGR12
STGR13
STGR14
STGR15
STGR16
STGR17
STGR18
RIB18
C
B
FIGURE 2
TOP SKIN PANEL 3 IN THE AREA OF THE STRINGER JOINTS
B
F G
C
RIB18
FWD
D E
A_SB_570259_7_BAAA_01_02
Figure A-UBAAA - Sheet 01
Modification of the Stringer Joint Couplings at Rib 18
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 28
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 33

@A300
SERVICE BULLETIN
**CONF ALL
RIB18
CLEAT
BEFORE AFTER
BEFORE AFTER
TOP SKIN NOT SHOWN FOR CLARITY
RIB18
TOP SKIN NOT SHOWN FOR CLARITY
RIB18
RIB18
CLEAT
NOTE: FOR FASTENER IDENTIFICATION TABLE SEE SHEET 3.
F
W
D
F
W
D
F
W
D
F
W
D
RIVET
D
FIGURE 4
STRINGERS 11 TO 18 BOLTING AT RIB 18 SHOWING BOLT POSITIONS
THAT ARE TO BE REMOVED AND HOLES SDET INSPECTED
FIGURE 4
E
F G
FIGURE 5FIGURE 5
STRINGERS 11 TO 18 BOLTING AT RIB 18 SHOWING BOLT POSITIONS
THAT ARE TO BE REMOVED AND HOLES SDET INSPECTED
STRINGERS 11 TO 18 BOLTING AT RIB 18 SHOWING BOLT
POSITIONS THAT ARE TO BE INSTALLED
STRINGERS 11 TO 18 BOLTING AT RIB 18 SHOWING BOLT
POSITIONS THAT ARE TO BE INSTALLED
SIDE STRAP
FREE FLANGE STRINGER WEB CROWN STRAP
TOP SKIN ATTACHED FLANGE SIDE STRAP
FREE FLANGE STRINGER WEB CROWN STRAP
TOP SKIN ATTACHED FLANGE
A_SB_570259_7_BAAA_02_02
Figure A-UBAAA - Sheet 02
Modification of the Stringer Joint Couplings at Rib 18
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 29
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 34

@A300
SERVICE BULLETIN
**CONF ALL
BOLT
NUT
NSA5479BV4−7X
NSA5472−4K7
6.746 mm
(0.2656 in)
6.797 mm
(0.2676 in)
1st OVERSIZE
CLEARANCE FIT
1
5
BOLT
NUT
NSA5479BV4−10X
NSA5472−4K7
6.746 mm
(0.2656 in)
6.797 mm
(0.2676 in)
1st OVERSIZE
CLEARANCE FIT
2
5
BOLT
NUT
NSA5477VHK4−5
NSA5472−4K7
6.607 mm
(0.2601 in)
6.657 mm
(0.2621 in)
1st OVERSIZE
INTERFERENCE FIT
3
5
BOLT
NUT
NSA5477VHK4−8
NSA5472−4K7
1st OVERSIZE
INTERFERENCE FIT
4
5
6.607 mm
(0.2601 in)
6.657 mm
(0.2621 in)
DESC PART NO. FINAL HOLE DIAMETER REMARKSITEM NO.SYMBOL
MINIMUM MAXIMUM
EXISTING FASTENERS
FASTENERS REMOVED
FASTENER TABLE
STRINGERS 11 TO 18 FASTENERS AT RIB 18 SHOWING
FASTENER TYPES THAT ARE TO BE INSTALLED
A_SB_570259_7_BAAA_03_03
Figure A-UBAAA - Sheet 03
Modification of the Stringer Joint Couplings at Rib 18
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 30
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 35

@A300
SERVICE BULLETIN
**CONF ALL
LH SHOWN
RH SIMILAR
A
FRONT SPAR
REAR SPAR
CENTER SPAR
Z500
Z600
RIB18
A
A
STRINGERS 11
THRU 18 AT RIB 18
STGR11
STGR12
STGR13
STGR14
STGR15
STGR16
STGR17
STGR18
RIB18
C
B
C
RIB18
FIGURE 2
TOP SKIN PANEL 3 IN THE AREA OF THE STRINGER JOINTS
B
FWD
D
TYPICAL
C
C
C
C
C
C
C
ATTACHED
E
FLANGE
A_SB_570259_7_BBAA_01_01
Figure A-UBBAA - Sheet 01
Detailed Visual Inspection of the Top Wing Skin and Stringer Joint at Rib 18
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 31
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 36

@A300
SERVICE BULLETIN
**CONF ALL
NOTE:
AREA TO BE INSPECTED
STRINGERS 11 TO 18 AT RIB 18
SHOWING AREA TO BE INSPECTED
D
SIDE STRAP TOP SKIN ATTACHED FLANGE
FREE FLANGESTRINGER WEB CROWN STRAP
TOP SKIN NOT SHOWN FOR CLARITY
RIB18
F
W
D E
A_SB_570259_7_BBAA_02_01
Figure A-UBBAA - Sheet 02
Detailed Visual Inspection of the Top Wing Skin and Stringer Joint at Rib 18
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 32
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 37

@A300
SERVICE BULLETIN
Appendix 01 - Elapsed Time Assumption
**CONF ALL
ELAPSED TIME ASSUMPTION SERVICE BULLETIN No. A300−57−0259
MH
ET/S:
PER
MANHOURS
ELAPSED TIME PER STEP
NUMBER OF PERSONS
01
02
THIS CHART IS ONLY A PROPOSAL.
OPERATORS MAY DETERMINE THAT ANOTHER WAY
TO DO THE WORK IS MORE SUITABLE FOR THEM.
01
02
NOTES:
:
:
IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS
ARE NOT REFLECTED IN THIS GANTT CHART.
SB ELAPSED TIME
(HOURS)
GET ACCESS
MH ET/S
TOTAL MANHOURS
SB ELAPSED TIME
37.00
11.50
STEPS
1.50 1.50
0
16.00 8.00
CLOSE−UP
PER
1
2
8.00216.00
MODIFY THE STRINGER JOINT COUPLINGS AT
MODIFY THE STRINGER JOINT COUPLINGS AT
RIB 18 RH WING
1.50 1.50 1
1234567 891 0 1 1 1 2 1 3
RIB 18 LH WING
0.50 0.501DO A DETAILED VISUAL INSPECTION OF THE TOP WING SKIN
AT RIB 18 LH WING
0.50 0.501
0.50 0.501
0.50 0.501DO A DETAILED VISUAL INSPECTION OF THE STRINGER JOINT
(INCLUDING ATTACHED FLANGE, STRINGER WEB, SIDE STRAP,
FREE FLANGE AND CROWN STRAP) AT RIB 18 LH WING
DO A DETAILED VISUAL INSPECTION OF THE TOP WING SKIN
AT RIB 18 RH WING
DO A DETAILED VISUAL INSPECTION OF THE STRINGER JOINT
(INCLUDING ATTACHED FLANGE, STRINGER WEB, SIDE STRAP,
FREE FLANGE AND CROWN STRAP) AT RIB 18 RH WING
A_SB_570259_7_AAAA_01_02
Figure A-UAAAA - Sheet 01
Elapsed Time Assumption
DATE: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 1
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 38

@A300
SERVICE BULLETIN
REPORTING SHEET
TITLE: WING - STRUCTURE - WING STRINGER JOINT AT RIB 18 (OVERSIZE
ATTACHMENT HOLES)
MODIFICATION No.: 13716H5748
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 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 1
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 39

@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: Sep 30/14 SERVICE BULLETIN No.: A300-57-0259
REVISION No.: 00 - Sep 30/14 Page: 1
7
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

---
OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.