# Airbus Service Bulletin A320-57-1238

Copy: No revision named ("SB_57-1238_r00"), 34 pages: PDF https://openairdocs.org/files/sha256/6c/d0/6cd04711cd54acdf450201d79e64560cbef1b02dcccf76a6b8bfbbc2553bd728; text https://openairdocs.org/service-documents/airbus/a320-57-1238/file/6cd04711cd54.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2024-0757, the docket of AD 2024-12-01. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md)
- Type: Service bulletin (Service Bulletin)
- Number: A320-57-1238
- Page: https://openairdocs.org/service-documents/airbus/a320-57-1238

## Text (34 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2024-0757, the docket of AD 2024-12-01. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jun 09/23 A320-57-1238
Page 1
CONF ALL
AIRBUS
2, ROND POINT EMILE DEWOITINE
31700 BLAGNAC
FRANCE
 
The content of this document is the property of Airbus. All rights including copyrights are reserved.
It is supplied in confidence and commercial security on its contents must be maintained.
It must not be used for any purpose other than that for which it is supplied, nor may information
contained in it be disclosed to unauthorized persons.
It must not be reproduced in whole or in part without permission in writing from the owners of the
copyright. Requests for reproduction of any data in this document and the media authorized for it must
be addressed to Airbus.
MANDATORY MANDATORY MANDATORY
ATA SYSTEM: 57
TITLE: WINGS - CENTER WING - INSPECTION OF FRONT SPAR VERTICAL
STRINGERS IN CENTER WING BOX
MODIFICATION No.:
None

### Page 2

A318/A319/A320/A321
SERVICE BULLETIN
SUMMARY
REV 00 Jun 09/23 A320-57-1238
Page 2
ATA SYSTEM: 57
TITLE: WINGS - CENTER WING - INSPECTION OF FRONT SPAR VERTICAL
STRINGERS IN CENTER WING BOX
SUMMARY
This summary is for information only and is not approved for modification of the aircraft.
A. MODIFICATIONS
MODIFICATION CLASSIFICATION
MAJOR None
MINOR None
NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the
mass, balance, structural strength, reliability, operational characteristics affecting
the airworthiness of the product. All other changes are major changes.
B. REASON
(1) History
During center fuselage certification full scale fatigue test, cracks were found in the
Center Wing Box spar on the external vertical stiffeners at floor beam level, frame 36.
Undetected cracks can propagate and form a long crack in the top end of the front
spar vertical stringers which would require an extensive structural repair.
(2) Objective/Action
This Service Bulletin requires HFEC inspections of the vertical stiffeners radius,
horizontal beam radius and rototest inspection of fasteners holes at FR36 in the
Centre Wing Box front spar area.The aim of this Service bulletin is to inspect A321NEO
post MOD 161349J3974 and pre MOD 155946 P14268 aircraft.
(3) Advantages
Accomplishment of this Service Bulletin will contribute to maintain the structural
integrity of the front spar external vertical stiffeners at floor beam level and to address
Widespread Fatigue Damage (WFD) requirements.
(4) Operational/Maintenance Consequences
The Operational/Maintenance Consequences of this Service Bulletin are covered by
the update of the affected publications detailed in "PLANNING INFORMATION".
C. GENERAL EVALUATION
EVALUATION TABLE
COMPLIANCE MANDATORY COST SAVING NO
A/C OPERATION
AFFECTED
NO VENDOR SB NO
CANCELS INSPECTION SB NO ETOPS AFFECTED NO
PAX COMFORT AFFECTED NO POTENTIAL AD YES
RELIABILITY AFFECTED NO STRUCTURAL LIFE EXTENSION NO
LIFE LIMIT NO LINE MAINTENANCE AFFECTED NO
NOTE: Service Bulletin must be accomplished.

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A318/A319/A320/A321
SERVICE BULLETIN
SUMMARY
REV 00 Jun 09/23 A320-57-1238
Page 3
D. MAINTENANCE CONFIGURATION
No specific aircraft maintenance configuration required.
E. MATERIAL PRICE INFORMATION
(1) Special Detailed Inspection of the Spar Vertical Stringers Radius, the
Horizontal Floor Beam Radius and the Fasteners Holes on FR36
(a) T ask set A320-A-57-XX-1238-01000-93BA-A Special Detailed Inspection of
the Spar Vertical Stringers Radius, the Horizontal Floor Beam Radius and the
Fasteners Holes on FR36
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET QTYPER A/C PRICE PER A/C MAIN PARTS
Part kit 571238A01R00 1 50.00 USD BOLTS, NUTS
F. APPLICABILITY
This Service Bulletin is applicable to this (these) operator(s):
VJC
G. CONCURRENT REQUIREMENTS
None
H. NATURE OF THE WORK
(1) Special Detailed Inspection of the Spar Vertical Stringers Radius, the
Horizontal Floor Beam Radius and the Fasteners Holes on FR36
(a) T ask set A320-A-57-XX-1238-01000-93BA-A Special Detailed Inspection of
the Spar Vertical Stringers Radius, the Horizontal Floor Beam Radius and the
Fasteners Holes on FR36
AIRCRAFT YES
EQUIPMENT NO
I. MANPOWER
(1) Special Detailed Inspection of the Spar Vertical Stringers Radius, the
Horizontal Floor Beam Radius and the Fasteners Holes on FR36
(a) T ask set A320-A-57-XX-1238-01000-93BA-A Special Detailed Inspection of
the Spar Vertical Stringers Radius, the Horizontal Floor Beam Radius and the
Fasteners Holes on FR36
MANPOWER
TOTAL MAN-HOURS 24.25 h
ELAPSED TIME (HOURS) 13.50 h

### Page 4

A318/A319/A320/A321
SERVICE BULLETIN
SUMMARY
Figure ICN-A320-A-57XX1238-A-FAPE3-02KO2-A-001-01 Fig.SA Sol.AA SHEET 1/2
REV 00 Jun 09/23 A320-57-1238General Overview
Page 4
J. GENERAL OVERVIEW
CONF ALL
AREA TO BE HFEC INSPECTED
NOTE:
A
A
B
VIEW LOOKING AFT
A
B
B
FR42
FR36Z240
A
ROTOTEST TO BE DONE
TYPICAL VIEW
ICN-A320-A-57XX1238-A-FAPE3-02KO2-A-001-01

### Page 5

A318/A319/A320/A321
SERVICE BULLETIN
SUMMARY
Figure ICN-A320-A-57XX1238-A-FAPE3-02KO3-A-001-01 Fig.SA Sol.AA SHEET 2/2
REV 00 Jun 09/23 A320-57-1238General Overview
Page 5
CONF ALL
DATUM
FWD
FR36
A A
VIEW LOOKING FWD
FLOOR BEAM
B B
B
B
NOTE:
AREA TO BE HFEC INSPECTED
TYPICAL VIEW
TYPICAL VIEW
ICN-A320-A-57XX1238-A-FAPE3-02KO3-A-001-01

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A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jun 09/23 A320-57-1238
Page 6
ATA SYSTEM: 57
TITLE: WINGS - CENTER WING - INSPECTION OF FRONT SPAR VERTICAL
STRINGERS IN CENTER WING BOX
1. PLANNING INFORMATION
A. APPLICABILITY
NOTE: This Service Bulletin is only applicable to aircraft on which MOD No. 161349J3974
(WINGS - GENERAL - Introduce Wing Box reinforcements and associated fittings for
A321 Neo Change) is embodied and MOD No. 155946P14268 (WINGS - CENTER
WING - Update drawing set of drilling template on Rear and Front Spar on Section
21) is not embodied.
(1) Models
ON A/C 06673
321-271N
CONF ALL
(2) Applicability by MSN
06673
(3) MSN by configuration
MSN CONFIGURATION
06673 001
(4) Configuration definition
Configuration 001
CONF 001 is applicable for all the aircraft affected by this Service Bulletin as a
standard configuration.
B. CONCURRENT REQUIREMENTS
None
C. REASON
(1) History
During center fuselage certification full scale fatigue test, cracks were found in the
Center Wing Box spar on the external vertical stiffeners at floor beam level, frame 36.
Undetected cracks can propagate and form a long crack in the top end of the front
spar vertical stringers which would require an extensive structural repair.
(2) Objective/Action
This Service Bulletin requires HFEC inspections of the vertical stiffeners radius,
horizontal beam radius and rototest inspection of fasteners holes at FR36 in the
Centre Wing Box front spar area.The aim of this Service bulletin is to inspect A321NEO
post MOD 161349J3974 and pre MOD 155946 P14268 aircraft.
(3) Advantages
Accomplishment of this Service Bulletin will contribute to maintain the structural
integrity of the front spar external vertical stiffeners at floor beam level and to address
Widespread Fatigue Damage (WFD) requirements.

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A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jun 09/23 A320-57-1238
Page 7
(4) Operational/Maintenance Consequences
The Operational/Maintenance Consequences of this Service Bulletin are covered by
the update of the affected publications detailed in "PLANNING INFORMATION".
D. DESCRIPTION
T o accomplish this Service Bulletin it is necessary to:
(1) Special Detailed Inspection of the Spar Vertical Stringers Radius, the
Horizontal Floor Beam Radius and the Fasteners Holes on FR36
(a) T ask set A320-A-57-XX-1238-01000-93BA-A Special Detailed Inspection of
the Spar Vertical Stringers Radius, the Horizontal Floor Beam Radius and the
Fasteners Holes on FR36
1 Remove the Fasteners of the Spar Vertical Stringers on FR36
2 Do High Frequency Eddy Current (HFEC) Inspection of the Spar Vertical
Stringers Radius and the Horizontal Floor Beam Radius and do a Rototest
Inspection of the Fasteners Holes on FR36
3 Install the new fasteners of the Spar vertical Stringers on FR36
4 Complete and send the Inspection Report Sheet of the Spar Vertical
Stringers
E. COMPLIANCE
(1) Classification
MANDATORY: Service Bulletin must be accomplished.
(2) Accomplishment Timescale
This Service Bulletin has been classified Mandatory. It is expected that an
Airworthiness Directive (AD) published by the European Union Aviation Safety Agency
(EASA) will be issued to confirm this classification. It is anticipated that the AD will
confirm the (thresholds and/or intervals and/or date) given but reference should be
made to the AD for confirmation of the mandated accomplishment timescale.
T able 1, CONF 001 - Do a Special Detailed Inspection (SDI) of the Spar Vertical
Stringers Radius, the Horizontal Floor Beam Radius and the Fasteners Holes on Frame
36
COMPLIANCE TIME
CONDITIONS ACTION
THRESHOLD GRACE PERIOD
REPETITIVE
INTERVAL
All aircraft Do a SDI of the
spar vertical
stringers radius,
the horizontal
floor beam radius
and the fasteners
holes on frame
36 in accordance
with Ref. T ask
set A320-A-
57-XX-1238-
01ZZZ-93BZ-A
44400 Flight
Cycles (FC) /
88900 Flight
Hours (FH)
from first flight,
whichever
occurs first
None None
Crack found Contact AIRBUS
and apply further
instructions
Before next flight None None

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A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jun 09/23 A320-57-1238
Page 8
COMPLIANCE TIME
CONDITIONS ACTION
THRESHOLD GRACE PERIOD
REPETITIVE
INTERVAL
No crack found Repeat the SDI
in accordance
with Ref. T ask
set A320-A-
57-XX-1238-
01ZZZ-93BZ-A
None None 10200 FC /
20500 FH
whichever
occurs first
F. APPROVAL
The technical content of this document is approved under the authority of the Design
Organisation Approval ref. EASA.21J.031.
If an aircraft listed in the applicability has a modification or repair embodied that is not
of AIRBUS origin, and which affects the content of this Service Bulletin, the operator
is responsible for obtaining approval by its airworthiness authority for any adaptation
necessary before incorporation of the Service Bulletin.
G. MANPOWER
The manpower estimates given in this Service Bulletin are based on the direct labor cost to
do the work. These estimates assume that the work will be done by experienced personnel,
and may need to be revised upwards to suit operator’s circumstances. The estimates do not
include the time to prepare, plan or inspect the work. Manufacture and procurement of parts
and tools, drying times for paints, sealants, etc., and general administration work are also
not included.
(1) Special Detailed Inspection of the Spar Vertical Stringers Radius, the
Horizontal Floor Beam Radius and the Fasteners Holes on FR36
(a) T ask set A320-A-57-XX-1238-01000-93BA-A Special Detailed Inspection of
the Spar Vertical Stringers Radius, the Horizontal Floor Beam Radius and the
Fasteners Holes on FR36
PREPARATION
Job Set-up 6.00 h
PROCEDURE
Remove the Fasteners of the Spar Vertical Stringers on
FR36
3.00 h
Do High Frequency Eddy Current (HFEC) Inspection of the
Spar Vertical Stringers Radius and the Horizontal Floor
Beam Radius and do a Rototest Inspection of the Fasteners
Holes on FR36
2.00 h
Install the new fasteners of the Spar vertical Stringers on
FR36
5.00 h
Complete and send the Inspection Report Sheet of the Spar
Vertical Stringers
0.25 h
PREPARATION FOR TEST
T est Set-up 0.25 h
TEST
T esting 0.50 h
CLOSE-UP
Close-up 7.25 h

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A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jun 09/23 A320-57-1238
Page 9
TOTAL MAN-HOURS 24.25 h
ELAPSED TIME (HOURS) 13.50 h
H. WEIGHT AND BALANCE
Not changed
I. ELECTRICAL LOAD DATA
Not changed
J. REFERENCES
(1) Special Detailed Inspection of the Spar Vertical Stringers Radius, the
Horizontal Floor Beam Radius and the Fasteners Holes on FR36
(a) T ask set A320-A-57-XX-1238-01000-93BA-A Special Detailed Inspection of
the Spar Vertical Stringers Radius, the Horizontal Floor Beam Radius and the
Fasteners Holes on FR36
AIRCRAFT MAINTENANCE MANUAL (AMM)
06-20-00, Page Block 001 06-31-53, Page Block 001
06-41-53, Page Block 001 T ask 12-34-24-869-002
T ask 20-21-11-911-001 T ask 25-21-41-000-001
T ask 25-21-41-400-001
T ask 25-28-41-000-001
T ask 25-28-41-400-001
T ask 53-00-00-000-801
T ask 53-00-00-400-801
CONSUMABLE MATERIAL LIST (CML)
Full content
ELECTRICAL STANDARD PRACTICES MANUAL (ESPM)
20-55-00
IN SERVICE INFORMATION (ISI)
00.00.00179
NON DESTRUCTIVE TEST MANUAL (NTM)
51-10-01 51-10-08
STANDARDS MANUAL (SM)
Full content
STRUCTURAL REPAIR MANUAL (SRM)
51-40-00 51-42-00
51-43-00 51-75-12
K. PUBLICATION AFFECTED
None
L. INDUSTRY SUPPORT INFORMATION
AIRBUS will not provide industry support for accomplishment of this Service Bulletin.

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A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jun 09/23 A320-57-1238
Page 10
2. MATERIAL INFORMATION
A. MATERIAL APPLICABILITY
Material for task set A320-A-57-XX-1238-01000-93BA-A Special Detailed
Inspection of the Spar Vertical Stringers Radius, the Horizontal Floor Beam
Radius and the Fasteners Holes on FR36
MATERIAL QTY SEE NOTES
Consumables See SB
Referenced consumables See SB
Part kit 571238A01R00 1
B. TOOLING
No tools
C. CONSUMABLES
Consumables for task set A320-A-57-XX-1238-01000-93BA-A Special Detailed
Inspection of the Spar Vertical Stringers Radius, the Horizontal Floor Beam
Radius and the Fasteners Holes on FR36
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
04DAB2
Primer Epoxy Paint -
- Corrosion Inhibiting
Structure
04JME4 T op Coat Polyurethane - -Grey InternalStructure
06AAA1 Polysulfide Sealant -General Purpose Brushable
08BAA9 Non Aqueous Cleaner -General
14SBA1 T extile - Lint free Cotton
Referenced consumables for task set A320-A-57-XX-1238-01000-93BA-A Special
Detailed Inspection of the Spar Vertical Stringers Radius, the Horizontal Floor
Beam Radius and the Fasteners Holes on FR36
T o accomplish this Service Bulletin it is necessary to use the consumable materials listed in:
Ref. AMM T ask 25-28-41-400-001
Ref. AMM T ask 25-21-41-400-001
Ref. AMM T ask 53-00-00-400-801
D. LIST OF NEW PARTS
Part kit 571238A01R00
Cost 50.00 USD
Availability 105 d (calendar days from receipt of order)
NOTE(S)
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 AIRBUS Spares portal or through a request for quotation to
airbus.kit@airbus.com.

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A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jun 09/23 A320-57-1238
Page 11
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.
Procurement address D4296
AIRBUS
Material, Logistics and Suppliers ATP II B,
Hein-Sass-Weg 24
21129 HAMBURG
GERMANY
Phone: +49 40 743 51660
E-mail: airbus.kit@airbus.com
Internet: http://spares.airbus.com
NOTE(S)
Customers with aircraft shown in the applicability of this Service Bulletin should send
a purchase order to AIRBUS at the address given above and quote the number of this
Service Bulletin.
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
1 EN6115V4-8 12 BOLT
2 ASNA2536-4 12 NUT
NOTE(S)
Refer to the AIRBUS Ref. SM if you find part numbers of hardware components which
you cannot identify. The SM will give you the correct part number to part number
relationship.
E. LIST OF EXISTING PARTS
No parts

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A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jun 09/23 A320-57-1238
Page 12
3. ACCOMPLISHMENT INSTRUCTIONS
Task set A320-A-57-XX-1238-01000-93BA-A (A320-A-57-XX-1238-01ZZZ-93BZ-A)
Special Detailed Inspection of the Spar Vertical Stringers Radius, the Horizontal Floor Beam
Radius and the Fasteners Holes on FR36
WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS
INCLUDED IN THE REFERENCED PROCEDURES.
CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL
WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY
SERVICEABLE). WHEN YOU DO A MAINTENANCE WORK, REPAIRS OR
MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND
THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS:
- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC., AS
NECESSARY ON WIRING AND COMPONENTS.
- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND
OTHER CONTAMINATION.
THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND
DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.
IF THERE IS CONTAMINATION, REFER TO Ref. ESPM 20-55-00.
NOTE: The accomplishment instructions of this Service Bulletin include procedures given in
other documents or in other sections of the Service Bulletin. When the words “refer to”
are used and the operator has a procedure accepted by the local authority he belongs to,
the accepted alternative procedure can be used. When the words “in accordance with”
are used then the given procedure must be followed.
NOTE: The access and close-up instructions, not comprising return to service tests, in this
Service Bulletin do not constitute or affect the technical intent of the Service Bulletin.
Operators can therefore, as deemed necessary, omit or add access and/or close-up steps
to add flexibility to their maintenance operations as long as the technical intent of the
Service Bulletin is met within the set parameters.
NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms. Refer
to paragraph 1.J., References, for the definition of acronyms.
NOTE: This Service Bulletin contains the instructions for the on-aircraft maintenance necessary
to ensure the continued airworthiness of the aircraft.
For any deviations to the instructions, including RC paragraph contained herein, contact
AIRBUS for further instructions and approval.
NOTE: The purpose of flowcharts is to supplement the information given in the Procedure and
Compliance paragraphs and not to serve as the primary source for tasks or compliance
times given in this Service Bulletin.
NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory by
an Airworthiness Directive (AD). The paragraphs 3.C. and 3.E. in these accomplishment
instructions are Required for Compliance (RC) and must be done to comply with the AD.
T o allow more flexibility, the rule "refer to" and "in accordance with" will apply to these
paragraphs 3.C. and 3.E. Other paragraphs are recommended and may be deviated from,
done as part of other actions or done with accepted methods different from those given
in the Service Bulletin, as long as the RC paragraphs can be done and the aircraft can be
put back into a serviceable condition.
NOTE: Discarded parts must be managed at the operator's discretion.

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A318/A319/A320/A321
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Page 13
A. TASK SET ASSOCIATED INFORMATION
Task Manpower
TOTAL MAN-HOURS 24.25 h
ELAPSED TIME (HOURS) 13.50 h
B. PREPARATION
(1) Task A320-A-57-XX-1238-01001-540A-A (A320-A-57-XX-1238-01ZZZ-540Z-A)
Job Set-up
Job Set-Up Information
Manpower/Resources/Skills
Man-hours 6.00 h
Minimum Number of person 2
Elapsed Time 3.00 h
Skills Airframe
Referenced Information
Manuals/Drawings References/Sheets
AMM
T ask 12-34-24-869-002
T ask 25-21-41-000-001
T ask 25-28-41-000-001
T ask 53-00-00-000-801
Procedure
NOTE: For the basic Aircraft configuration, refer to AMM Chapter "Introduction -
Aircraft status for maintenance" in Manual Front Matter section.
(a) Make sure that the aircraft is electrically grounded, refer to Ref. AMM T ask 12-34-
24-869-002
(b) Remove the passengers Seats between Frame 35 and Frame 36 refer to Ref.
AMM T ask 25-21-41-000-001
(c) Remove the textile floor covering between Frame 35 and Frame 36 refer to Ref.
AMM T ask 25-28-41-000-001
(d) Remove the floor Panel 242DF Panel 242CF Panel 242BF Panel 241DF Panel
241CF Panel 241BF and Panel 241AF refer to Ref. AMM T ask 53-00-00-000-801
(e) If necessary, remove and retain the hydraulic pipes clamps and move the pipes
without disconnecting them in order to facilitate the access of the working area.
C. PROCEDURE
(1) Task A320-A-57-XX-1238-01001-920A-A (A320-A-57-XX-1238-01ZZZ-920Z-A)
Remove the Fasteners of the Spar Vertical Stringers on FR36
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
Access Panel 241AF, Panel 241BF, Panel 241CF, Panel241DF241
Work location Frame 36

### Page 14

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Impacted Zone Access / Work Location
Access Panel 242BF, Panel 242CF, Panel 242DF242
Work location Frame 36
Manpower/Resources/Skills
Man-hours 3.00 h
Minimum Number of person 2
Elapsed Time 1.50 h
Skills Airframe
Material necessary to do the job
Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
08BAA9 Non Aqueous Cleaner -General
14SBA1 T extile - Lint free Cotton
Referenced Information
Manuals/Drawings References/Sheets
AMM
06-20-00, Page Block 001
06-31-53, Page Block 001
06-41-53, Page Block 001
CML CONSUMABLE MATERIAL LIST (CML)
SRM 51-42-00
Procedure
Ref. Fig.BA Removal of the Fasteners
(a) Standard Practices:
1 For the specification of Material application codes given in this Service
Bulletin, refer to Ref. CML
2 For the Frame (FR) identification, refer to Ref. AMM 06-31-53, Page Block
001.
3 For the identification of zones, refer to Ref. AMM 06-20-00, Page Block 001.
4 For the identification of access panels, refer to Ref. AMM 06-41-53, Page
Block 001.
5 Remove and install fasteners in accordance with Ref. SRM 51-42-00.
(b) Remove the fasteners of the spar vertical Stringers and the horizontal floor
beam.
12 Fasteners     Discard
(c) Clean the work area and fastener holes with:
  T extile - Lint free Cotton14SBA1  
made moist with
  Non Aqueous Cleaner -
General
08BAA9  
NOTE: If necessary, use a non-metallic spatula to remove the sealant.

### Page 15

A318/A319/A320/A321
SERVICE BULLETIN
Figure ICN-A320-A-57XX1238-A-FAPE3-02KO7-A-001-01 Fig.BA Sol.AA SHEET 1/1
REV 00 Jun 09/23 A320-57-1238Removal of the Fasteners
Page 15
CONF ALL
DATUMFR36
A A
B
VIEW LOOKING AFT
FLOOR BEAM
A
A
A
B
B
Z240
A
FR36
FR42
FASTENER TABLE
REMOVE AND DISCARD
TYPICAL VIEW FWD
TYPICAL VIEW
FASTENER
ICN-A320-A-57XX1238-A-FAPE3-02KO7-A-001-01

### Page 16

A318/A319/A320/A321
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Page 16
(2) Task A320-A-57-XX-1238-01001-300A-A (A320-A-57-XX-1238-01ZZZ-300Z-A)
Do High Frequency Eddy Current (HFEC) Inspection of the Spar Vertical
Stringers Radius and the Horizontal Floor Beam Radius and do a Rototest
Inspection of the Fasteners Holes on FR36
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
Access Panel 241AF, Panel 241BF, Panel 241CF, Panel241DF241
Work location Frame 36
Access Panel 242BF, Panel 242CF, Panel 242DF242
Work location Frame 36
Manpower/Resources/Skills
Man-hours 2.00 h
Minimum Number of person 1
Elapsed Time 2.00 h
Skills Airframe
Referenced Information
Manuals/Drawings References/Sheets
AMM
06-20-00, Page Block 001
06-31-53, Page Block 001
06-41-53, Page Block 001
CML CONSUMABLE MATERIAL LIST (CML)
NTM 51-10-0151-10-08
Procedure
Ref. Fig.FA Flow Chart
Ref. Fig.BB Inspection Area
Ref. Fig.BD Inspection of the Fasteners Holes
(a) Standard Practices:
1 For the specification of Material application codes given in this Service
Bulletin, refer to Ref. CML.
2 For the Frame (FR) identification, refer to Ref. AMM 06-31-53, Page Block
001.
3 For the identification of zones, refer to Ref. AMM 06-20-00, Page Block 001.
4 For the identification of access panels, refer to Ref. AMM 06-41-53, Page
Block 001.
(b) Do SDI at the threshold given in PLANNING INFORMATION paragraph E.(2):
1 Do an HFEC Inspection of the Front Spar Vertical Stringer Radius at the
threshold given in the PLANNING INFORMATION paragraph E. (2), refer to
Ref. NTM 51-10-08 and Ref. Fig.BB Inspection Area Sheet 01, View B.
2 Do an HFEC Inspection of the Horizontal Floor Beam Radius at the
threshold given in the PLANNING INFORMATION paragraph E. (2), refer to

### Page 17

A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jun 09/23 A320-57-1238
Page 17
Ref. NTM 51-10-08 and Ref. Fig.BB Inspection Area Sheet 02, Section View
B-B.
3 Do a Rototest Inspection of the fastener holes of the Spar Vertical Stringers
Radius in the Center Fuselage on Frame 36 at the threshold given in the
PLANNING INFORMATION paragraph E. (2), refer to Ref. NTM 51-10-01 and
Ref. Fig.BD Inspection of the Fasteners Holes.
4 If crack is found in any inspections:
a Contact AIRBUS and apply further instructions before next flight.
5 If no crack is found in any inspections:
a Install the fasteners on the inspected holes Ref. T ask A320-A-57-XX-
1238-03ZZZ-920Z-A.
b Repeat the SDI at the interval given in PLANNING INFORMATION
paragraph E.(2) in accordance with Ref. T ask set A320-A-57-XX-1238-
01ZZZ-93BZ-A.
(c) After completion of all inspections, complete and send the Inspection Report
sheet in accordance with Ref. T ask A320-A-57-XX-1238-03ZZZ-90AZ-A.

### Page 18

A318/A319/A320/A321
SERVICE BULLETIN
Figure ICN-A320-A-57XX1238-A-FAPE3-02KO1-A-002-01 Fig.FA Sol.AA SHEET 1/1
REV 00 Jun 09/23 A320-57-1238Flow Chart
Page 18
CONF ALL
NOTE:
THE PURPOSE OF FLOWCHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE
AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR
COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN.
FOR THE ACCOMPLISHMENT TIMESCALE, REFER TO PARAGRAPH 1.E (2).01
DO A HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTION OF THE
FRONT SPAR VERTICAL STRINGER RADIUS AND THE HORIZONTAL FLOOR
BEAM RADIUS AND DO A ROTOTEST OF THE FASTENER HOLES OF THE
FRONT SPAR VERTICAL STRINGERS ON FRAME 36
01
CRACK FOUND?NO YES
CONTACT AIRBUS AND APPLY
FURTHER INSTRUCTIONS
0101
REPEAT THE HFEC AND
ROTOTEST INSPECTION
ICN-A320-A-57XX1238-A-FAPE3-02KO1-A-002-01

### Page 19

A318/A319/A320/A321
SERVICE BULLETIN
Figure ICN-A320-A-57XX1238-A-FAPE3-02KNZ-A-001-01 Fig.BB Sol.AA SHEET 1/2
REV 00 Jun 09/23 A320-57-1238Inspection Area
Page 19
CONF ALL
HFEC INSPECTION AREA
NOTE:
A
A
B
A
VIEW LOOKING AFT
B
B
FR42
FR36Z240
A
TYPICAL VIEW
ICN-A320-A-57XX1238-A-FAPE3-02KNZ-A-001-01

### Page 20

A318/A319/A320/A321
SERVICE BULLETIN
Figure ICN-A320-A-57XX1238-A-FAPE3-02KO0-A-001-01 Fig.BB Sol.AA SHEET 2/2
REV 00 Jun 09/23 A320-57-1238Inspection Area
Page 20
CONF ALL
HFEC INSPECTION AREA
NOTE:
A A
VIEW LOOKING FWD
B B
FWD
TYPICAL VIEW
TYPICAL VIEW
DATUMFR36FLOOR BEAM
B
B
ICN-A320-A-57XX1238-A-FAPE3-02KO0-A-001-01

### Page 21

A318/A319/A320/A321
SERVICE BULLETIN
Figure ICN-A320-A-57XX1238-A-FAPE3-02KO4-A-001-01 Fig.BD Sol.AA SHEET 1/1
REV 00 Jun 09/23 A320-57-1238Inspection of the Fasteners Holes
Page 21
CONF ALL
B
TYPICAL VIEW
DO A ROTOTEST INSPECTION
A
B
B
Z240
A
FR36
FR42
VIEW LOOKING AFT
ICN-A320-A-57XX1238-A-FAPE3-02KO4-A-001-01

### Page 22

A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jun 09/23 A320-57-1238
Page 22
(3) Task A320-A-57-XX-1238-03001-920A-A (A320-A-57-XX-1238-03ZZZ-920Z-A)
Install the new fasteners of the Spar vertical Stringers on FR36
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
Access Panel 241AF, Panel 241BF, Panel 241CF, Panel241DF241
Work location Frame 36
Access Panel 242BF, Panel 242CF, Panel 242DF242
Work location Frame 36
Manpower/Resources/Skills
Man-hours 5.00 h
Minimum Number of person 2
Elapsed Time 2.50 h
Skills Airframe
Material necessary to do the job
Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
04DAB2
Primer Epoxy Paint -
- Corrosion Inhibiting
Structure
04JME4 T op Coat Polyurethane - -Grey InternalStructure
06AAA1 Polysulfide Sealant -General Purpose Brushable
Part kit 571238A01R00
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
1 EN6115V4-8 12 BOLT
2 ASNA2536-4 12 NUT
Referenced Information
Manuals/Drawings References/Sheets
AMM
06-20-00, Page Block 001
06-31-53, Page Block 001
06-41-53, Page Block 001
T ask 20-21-11-911-001
CML CONSUMABLE MATERIAL LIST (CML)
SRM
51-40-00
51-42-00
51-43-00
51-75-12
Procedure
Ref. Fig.BC Installation of the Fasteners
(a) Standard Practices:

### Page 23

A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jun 09/23 A320-57-1238
Page 23
1 For the specification of Material application codes given in this Service
Bulletin, refer to Ref. CML.
2 For the Frame (FR) identification, refer to Ref. AMM 06-31-53, Page Block
001.
3 For the identification of zones, refer to Ref. AMM 06-20-00, Page Block 001.
4 For the identification of access panels, refer to Ref. AMM 06-41-53, Page
Block 001.
5 T o torque tighten the standard threaded fasteners, refer to Ref. AMM T ask
20-21-11-911-001.
6 Remove and install fasteners in accordance with Ref. SRM 51-42-00.
7 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.
8 Get alternative and substitute fastener data in accordance with Ref. SRM
51-43-00.
9 If alternative and substitute fasteners have to be used, you must make
sure that the associated nut/collar are compatible in accordance with refer
to Ref. SRM 51-40-00 'Mating Part' column.
10 Repair the paint coating in accordance with Ref. SRM 51-75-12.
(b) Wet install the new fasteners of the spar vertical Stringers and the horizontal
floor beam.
12 BOLT EN6115V4-8 Item 1
12 NUT ASNA2536-4 Item 2
with:
  Polysulfide Sealant
- General Purpose
Brushable
06AAA1  
1 After the installation of the new fasteners, apply:
  Primer Epoxy Paint -
- Corrosion Inhibiting
Structure
04DAB2  
and
  T op Coat Polyurethane -
- Grey InternalStructure
04JME4

### Page 24

A318/A319/A320/A321
SERVICE BULLETIN
Figure ICN-A320-A-57XX1238-A-FAPE3-02KO5-A-001-01 Fig.BC Sol.AA SHEET 1/2
REV 00 Jun 09/23 A320-57-1238Installation of the Fasteners
Page 24
CONF ALL
DATUM
FWD
FR36
A A
B
VIEW LOOKING AFT
FLOOR BEAM
A
A
A
B
B
Z240
A
FR36
FR42
TYPICAL VIEW
REFER TO SHEET 02 FOR THE APPLICABLE FASTENERS 
NOTE:
FASTENER
TYPICAL VIEW
ICN-A320-A-57XX1238-A-FAPE3-02KO5-A-001-01

### Page 25

A318/A319/A320/A321
SERVICE BULLETIN
Figure ICN-A320-A-57XX1238-A-FAPE3-02KO6-A-002-01 Fig.BC Sol.AA SHEET 2/2
REV 00 Jun 09/23 A320-57-1238Installation of the Fasteners
Page 25
CONF ALL
HOLE PN DESCRIPTION REMARKSSYMBOL
1
2
BOLT
NUTASNA2536-4
EN6115V4-8
PROTECT THE FASTENERS WITH INTERIOR FINISH MATERIAL No 04JME402
01
02
INSTALL THE FASTENERS WITH MATERIAL No 06AAA1 (WET ASSEMBLY)01
AND APPLY PROTECTIVE FINISH WITH MATERIAL No 04DAB2
F
HEAD ON FAR SIDE
NOTE:
F
NEW
ITEM
ICN-A320-A-57XX1238-A-FAPE3-02KO6-A-002-01

### Page 26

A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jun 09/23 A320-57-1238
Page 26
(4) Task A320-A-57-XX-1238-03001-90AA-A (A320-A-57-XX-1238-03ZZZ-90AZ-A)
Complete and send the Inspection Report Sheet of the Spar Vertical
Stringers
Job Set-Up Information
Manpower/Resources/Skills
Man-hours 0.25 h
Minimum Number of person 1
Elapsed Time 0.25 h
Skills Cabin
Referenced Information
Manuals/Drawings References/Sheets
ISI 00.00.00179
Procedure
(a) Complete the inspection report sheet, refer to Ref. Fig.RB Inspection report
(b) Send the completed inspection report sheet in accordance with Ref. ISI
00.00.00179
NOTE: T o send the Inspection Report sheet is not Required for Compliance (RC).

### Page 27

A318/A319/A320/A321
SERVICE BULLETIN
Figure ICN-A320-A-57XX1238-A-FAPE3-02LWD-A-001-01 Fig.RB Sol.AA SHEET 1/4
REV 00 Jun 09/23 A320-57-1238Inspection report
Page 27
CONF ALL
INSPECTION REPORT
SERVICE BULLETIN No :
A/C MSN :
FLIGHT CYCLES :
FLIGHT HOURS :
A320-57-1238
DATE OF INSPECTION :
INSPECTION METHOD : SPECIAL DETAILED
INSPECTION
FR42
FR36
A
A
A
A
A
ZONE 1 ZONE 2
6 5
4
3
2
1
VIEW LOOKING AFT
TYPICALINSPECTION AREA.
NOTE:
FASTENER HOLES TO BE INSPECTED.
SEND THE COMPLETED INSPECTION REPORT
SHEET IN ACCORDANCE WITH ISI 00.00.00179
ICN-A320-A-57XX1238-A-FAPE3-02LWD-A-001-01

### Page 28

A318/A319/A320/A321
SERVICE BULLETIN
Figure ICN-A320-A-57XX1238-A-FAPE3-02LWE-A-002-01 Fig.RB Sol.AA SHEET 2/4
REV 00 Jun 09/23 A320-57-1238Inspection report
Page 28
CONF ALL
INSPECTION REPORT
SERVICE BULLETIN No :
A/C MSN :
FLIGHT CYCLES :
FLIGHT HOURS :
A320-57-1238
DATE OF INSPECTION :
INSPECTION METHOD : SPECIAL DETAILED
INSPECTION
VIEW LOOKING FWD
B BFWD A A
DATUMFR36FLOOR BEAM
FASTENER HOLE
B
B
INSPECTION AREA.
NOTE:
TYPICAL
TO BE INSPECTED 
SEND THE COMPLETED INSPECTION REPORT
SHEET IN ACCORDANCE WITH ISI 00.00.00179
TYPICAL
ICN-A320-A-57XX1238-A-FAPE3-02LWE-A-002-01

### Page 29

A318/A319/A320/A321
SERVICE BULLETIN
Figure ICN-A320-A-57XX1238-A-FAPE3-02LWF-A-002-01 Fig.RB Sol.AA SHEET 3/4
REV 00 Jun 09/23 A320-57-1238Inspection report
Page 29
CONF ALL
INSPECTION REPORT
SERVICE BULLETIN No :
A/C MSN :
FLIGHT CYCLES :
FLIGHT HOURS :
A320-57-1238
DATE OF INSPECTION :
INSPECTION METHOD : SPECIAL DETAILED
INSPECTION
YES NO
CRACK FOUND?NUMBER
1
2
3
4
5
6
HF EDDY CURRENT
INSPECTION
FRONT SPAR
VERTICAL
VERTICAL STRINGERS SIDE
FRONT SPAR
BEAM SIDE
FLOOR
YES NO
CRACK FOUND?
SEND THE COMPLETED INSPECTION REPORT
SHEET IN ACCORDANCE WITH ISI 00.00.00179
STRINGERS/
FLOOR BEAMS
ICN-A320-A-57XX1238-A-FAPE3-02LWF-A-002-01

### Page 30

A318/A319/A320/A321
SERVICE BULLETIN
Figure ICN-A320-A-57XX1238-A-FAPE3-02LWG-A-002-01 Fig.RB Sol.AA SHEET 4/4
REV 00 Jun 09/23 A320-57-1238Inspection report
Page 30
CONF ALL
INSPECTION REPORT
SERVICE BULLETIN No :
A/C MSN :
FLIGHT CYCLES :
FLIGHT HOURS :
A320-57-1238
DATE OF INSPECTION :
INSPECTION METHOD : SPECIAL DETAILED
INSPECTION
YES NO
CRACK FOUND?
YES NO
CRACK FOUND?NUMBER
1
2
3
4
5
6
ROTOTEST
INSPECTION
FRONT SPAR
VERTICAL
ZONE 1 HOLE ZONE 2 HOLE
SEND THE COMPLETED INSPECTION REPORT
SHEET IN ACCORDANCE WITH ISI 00.00.00179
STRINGERS/
FLOOR BEAMS
ICN-A320-A-57XX1238-A-FAPE3-02LWG-A-002-01

### Page 31

A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jun 09/23 A320-57-1238
Page 31
D. PREPARATION FOR TEST
(1) Task A320-A-57-XX-1238-01001-332A-A (A320-A-57-XX-1238-01ZZZ-332Z-A)
Test Set-up
Job Set-Up Information
Manpower/Resources/Skills
Man-hours 0.25 h
Minimum Number of person 1
Elapsed Time 0.25 h
Skills Airframe
Referenced Information
Manuals/Drawings References/Sheets
AMM T ask 25-21-41-400-001
Procedure
(a) Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit
breaker(s) as specified after the installation of the passenger seats, refer to Ref.
AMM T ask 25-21-41-400-001.
E. TEST
(1) Task A320-A-57-XX-1238-01001-390A-A (A320-A-57-XX-1238-01ZZZ-390Z-A)
Testing
Job Set-Up Information
Manpower/Resources/Skills
Man-hours 0.50 h
Minimum Number of person 1
Elapsed Time 0.50 h
Skills Airframe
Referenced Information
Manuals/Drawings References/Sheets
AMM T ask 25-21-41-400-001
Procedure
NOTE: This Service Bulletin requires the accomplishment of T ests given in other
topics which are referenced in the table below:.
Ref. T ask A320-A-57-XX-1238-01ZZZ-390Z-A Ref. AMM T ask 25-21-41-400-001
(a) Do the test procedure as specified after the installation of the passenger seats,
refer to Ref. AMM T ask 25-21-41-400-001.
F. CLOSE-UP
(1) Task A320-A-57-XX-1238-01001-740A-A (A320-A-57-XX-1238-01ZZZ-740Z-A)
Close-up

### Page 32

A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jun 09/23 A320-57-1238
Page 32
Job Set-Up Information
Manpower/Resources/Skills
Man-hours 7.25 h
Minimum Number of person 2
Elapsed Time 3.75 h
Referenced Information
Manuals/Drawings References/Sheets
AMM
T ask 25-21-41-400-001
T ask 25-28-41-400-001
T ask 53-00-00-400-801
Procedure
(a) If removed, install hydraulic pipes and clamps back in initial position.
(b) Make sure that the work areas are clean and clear of tools and other items of
equipment.
(c) Install the floor Panel 242DF, Panel 242CF, Panel 242BF, Panel 241DF, Panel
241CF, Panel 241BF and Panel 241AF, refer to Ref. AMM T ask 53-00-00-400-801.
(d) Install the textile floor covering between Frame 35 and Frame 36, refer to Ref.
AMM T ask 25-28-41-400-001.
(e) Install the passengers Seats between Frame 35 and Frame 36, refer to Ref. AMM
T ask 25-21-41-400-001.
(f) Remove the access platform(s).
(g) Disconnect the aircraft electrical ground-connection.
(h) Put the aircraft back to its initial configuration.
G. ADMINISTRATIVE
(1) Task A320-A-57-XX-1238-02001-90AA-A (A320-A-57-XX-1238-02ZZZ-90AZ-A)
Administrative
Procedure
Confirm in the applicable aircraft records that you have completed all the work defined
in this Service Bulletin task set as required.

### Page 33

A318/A319/A320/A321
SERVICE BULLETIN
APPENDIX
REV 00 Jun 09/23 A320-57-1238
Page 33
APPENDIX
A. REPORTING SHEET
TITLE: WINGS - CENTER WING - INSPECTION OF FRONT SPAR VERTICAL
STRINGERS IN CENTER WING BOX
MODIFICATION No.: None
(1) SB Reporting status
This Service Bulletin will only be incorporated into affected customized Maintenance
and Flight Operations Products if it is duly reported to Airbus.
(2) GENERAL information
The SB Reporting policy is published in ISI 00.00.00135. This document provides
information regarding: the SB Reporting means and benefits, the update of
customized Maintenance Products and customized Flight Operations Products.
If this Service Bulletin has an operational impact, refer to paragraph "Flight Operations
Products" for further information on the update of affected Flight Operations Products.
(3) SB Reporting procedure
Standard practice to report SB is to use the online reporting application on
AirbusWorld.
Refer to ISI 00.00.00179:
- For complete information on reporting means to Airbus, Question 2 "What are
the standard practices for SB Reporting?"
- If this SB requires previous or simultaneous accomplishment of other SBs,
Question 3 "What about the reporting of prerequisite Service Bulletins?"
NOTE: ISI 00.00.00179 covers all the frequently asked questions about SB Reporting.
It is revised on a regular basis.

### Page 34

A318/A319/A320/A321
SERVICE BULLETIN
APPENDIX
REV 00 Jun 09/23 A320-57-1238
Page 34
B. QUALITY PERCEPTION FORM
Use this form to tell us what is your perception of the quality of this Service Bulletin.
The reported data that you provide us will be used to analyse areas of difficulties and to
take corrective action to further improve the quality of our Service Bulletin.
We thank you for the time you have taken in completing this form.
Quality rating of this SB 4 3 2 1
Quality rating of the Accomplishment Instructions 4 3 2 1
Quality rating of the Illustrations 4 3 2 1
Is this SB easy to understand ? Y / N
NOTE: Please rate on a scale of 1 to 4, with 4 being the highest score
If you have difficulties in the accomplishment of this SB please quote below the area(s) and
give a short description of the issue.
Planning Material Instructions
X Applicability X T ooling X Preparation
X Reason X List of Materials
Operator Supplied
X Mod/Inspection
X Manpower X Kit content X T est
X References X Re-identification X Close-up
X Publication X Illustrations
X Industry Support
Comments :
Operator : Date :
Name/Title
Please return this form to :
AIRBUS
2, ROND POINT EMILE DEWOITINE
31700 BLAGNAC
FRANCE
Or via your Resident Customer Support Office.

---
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