# Airbus Service Bulletin A320-53-1274

Copy: Revision 6 ("A320-53-1274 R06"), 692 pages: PDF https://openairdocs.org/files/sha256/3e/64/3e645727a090c9526930f6336bd9819bd4bc724c2805f20c2dd7407bdd2b45c3; text https://openairdocs.org/service-documents/airbus/a320-53-1274/file/3e645727a090.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2020-0451, the docket of AD 2020-22-06. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md)
- Type: Service bulletin (Service Bulletin)
- Number: A320-53-1274
- Latest revision known: A320-53-1274, Revision 6 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/airbus/a320-53-1274

## Text (692 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2020-0451, the docket of AD 2020-22-06. 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 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 1
CONF ALL
AIRBUS
2, ROND POINT EMILE DEWOITINE
31700 BLAGNAC
FRANCE
 
The content of this document is the property of Airbus.
It is supplied in confidence and commercial security on its contents must be maintained.
It must not be used for any purpose other than that for which it is supplied, nor may information
contained in it be disclosed to unauthorized persons.
It must not be reproduced in whole or in part without permission in writing from the owners of the
copyright. Requests for reproduction of any data in this document and the media authorized for it must
be addressed to Airbus.
MANDATORY MANDATORY MANDATORY
ATA SYSTEM: 53
TITLE: FUSELAGE - DOORS - EMERGENCY EXIT - REINFORCE THE UPPER
SIDE OF EMERGENCY EXIT DOOR
MODIFICATION No.:
153834K16159
CONF 003-005
157752K18260

### Page 2

A318/A319/A320/A321
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 2
ATA SYSTEM: 53
TITLE: FUSELAGE - DOORS - EMERGENCY EXIT - REINFORCE THE UPPER
SIDE OF EMERGENCY EXIT DOOR
CONF ALL
REVISION TRANSMITTAL SHEET
This page transmits Revision No. 06 of Service Bulletin No. A320-53-1274.
A. ADDITIONAL WORK
No additional work is required by this revision.
B. REASON
Revision No. 06 issued to add the aircraft for operators CTN, DAL, DLH and SWR.
C. CHANGES
CONF 001
PLANNING INFORMATION
APPLICABILITY
Configuration definition Update of the sentence of the Configuration definition
without technical impact.
WEIGHT AND BALANCE Update of the sentence without technical impact.
MATERIAL INFORMATION
LIST OF NEW PARTS Update of the sentence related to the Material
Information without technical impact.
ACCOMPLISHMENT INSTRUCTIONS
T ask set A320-A-53-
XX-1274-01000-93AA-A Modification
Update of the note in the ACCOMPLISHMENT
INSTRUCTIONS paragraph.
CONF 002
PLANNING INFORMATION
APPLICABILITY
Configuration definition Update of the sentence of the Configuration definition
without technical impact.
WEIGHT AND BALANCE Update of the sentence without technical impact.
MATERIAL INFORMATION
LIST OF NEW PARTS Update of the sentence related to the Material
Information without technical impact.
ACCOMPLISHMENT INSTRUCTIONS
T ask set A320-A-53-
XX-1274-01000-93AA-A Modification
Update of the note in the ACCOMPLISHMENT
INSTRUCTIONS paragraph.
CONF 003
SUMMARY
APPLICABILITY Update of the aircraft operators.
CONCURRENT REQUIREMENTS Addition of new aircraft.
PLANNING INFORMATION
APPLICABILITY

### Page 3

A318/A319/A320/A321
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 3
Configuration definition Addition of new aircraft.
Update of the sentence of the Configuration definition
without technical impact.
CONCURRENT REQUIREMENTS Addition of new aircraft.
WEIGHT AND BALANCE Update of the sentence without technical impact.
MATERIAL INFORMATION
LIST OF NEW PARTS Update of the sentence related to the Material
Information without technical impact.
ACCOMPLISHMENT INSTRUCTIONS
T ask set A320-A-53-
XX-1274-01000-93AA-A Modification
Update of the note in the ACCOMPLISHMENT
INSTRUCTIONS paragraph.
CONF 004
PLANNING INFORMATION
APPLICABILITY
Configuration definition Addition of new aircraft.
Update of the sentence of the Configuration definition
without technical impact.
CONCURRENT REQUIREMENTS Addition of new aircraft.
WEIGHT AND BALANCE Update of the sentence without technical impact.
MATERIAL INFORMATION
LIST OF NEW PARTS Update of the sentence related to the Material
Information without technical impact.
ACCOMPLISHMENT INSTRUCTIONS
T ask set A320-A-53-
XX-1274-01000-93AA-A Modification
Update of the note in the ACCOMPLISHMENT
INSTRUCTIONS paragraph.
CONF 005
SUMMARY
APPLICABILITY Update of the aircraft operators.
CONCURRENT REQUIREMENTS Addition of new aircraft.
PLANNING INFORMATION
APPLICABILITY
Configuration definition Addition of new aircraft.
Addition of aircraft model 320-212.
Update of the sentence of the Configuration definition
without technical impact.
CONCURRENT REQUIREMENTS Addition of new aircraft.
WEIGHT AND BALANCE Update of the sentence without technical impact.
MATERIAL INFORMATION
LIST OF NEW PARTS Update of the sentence related to the Material
Information without technical impact.
ACCOMPLISHMENT INSTRUCTIONS

### Page 4

A318/A319/A320/A321
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 4
T ask set A320-A-53-
XX-1274-01000-93AA-A Modification
Update of the note in the ACCOMPLISHMENT
INSTRUCTIONS paragraph.
CONF ALL
D. FILING INSTRUCTIONS
This Service Bulletin has been generated electronically and is reissued as a complete
document. Replace the complete document.
Put this Revision Transmittal Sheet in front of the Service Bulletin.
E. HISTORY OF PREVIOUS REVISIONS
Revision No. 01 issued to:
Add aircraft with Manufacturer Serial Number (MSN) 0202, 0209, 0216, 0267, 0268, 0346
and 0382 for Operator GWI
Add aircraft with MSN 0269 for Operator DLH
Give new minimum dimensions for edge-margin distance at specific fastener-hole positions.
Revision No. 02 issued to add aircraft MSN 0609, 0610 and 0616 for operator DLH.
Revision No. 03 issued to add aircraft Manufacturer Serial Numbers (MSNs) 0623, 0627,
0636 and 0641 for operator DLH and aircraft MSNs 0646, 0654, 0794, 1016 and 1172 for
operator GWI.
Revision No. 04 issued to add aircraft MSN 0118 for operator DAL and aircraft MSNs 0651,
0679, 0689, 0694, 0717 and 0729 for operator DLH.
Revision No. 05 issued to add the aircraft for operators DLH and SWR.
F. REVISION SEQUENCE
ORIGINAL: Jul 15/14
REVISION No. : 01 - Jun 18/15
REVISION No. : 02 - Sep 16/16
REVISION No. : 03 - Jun 09/17
REVISION No. : 04 - Jun 15/18
REVISION No. : 05 - Mar 15/19
REVISION No. : 06 - Jul 22/19

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A318/A319/A320/A321
SERVICE BULLETIN
SUMMARY
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 5
ATA SYSTEM: 53
TITLE: FUSELAGE - DOORS - EMERGENCY EXIT - REINFORCE THE UPPER
SIDE OF EMERGENCY EXIT DOOR
SUMMARY
This summary is for information only and is not approved for modification of the aircraft.
A. MODIFICATIONS
CONF 001
MODIFICATION CLASSIFICATION
MAJOR None
MINOR 153834K16159
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.
NOTE: This modification related to an Airworthiness issue has been classified by Airbus
and confirmed by EASA as minor in accordance with EU Part 21.A.91. As such, this
minor change is handled by Airbus under its Design Organisation Approval No.
EASA.21J.031.
CONF 002
MODIFICATION CLASSIFICATION
MAJOR None
MINOR 153834K16159
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.
NOTE: This modification related to an Airworthiness issue has been classified by Airbus
and confirmed by EASA as minor in accordance with EU Part 21.A.91. As such, this
minor change is handled by Airbus under its Design Organisation Approval No.
EASA.21J.031.
CONF 003
MODIFICATION CLASSIFICATION
MAJOR None
MINOR 153834K16159 157752K18260
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.
NOTE: This modification related to an Airworthiness issue has been classified by Airbus
and confirmed by EASA as minor in accordance with EU Part 21.A.91. As such, this
minor change is handled by Airbus under its Design Organisation Approval No.
EASA.21J.031.
CONF 004

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A318/A319/A320/A321
SERVICE BULLETIN
SUMMARY
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 6
MODIFICATION CLASSIFICATION
MAJOR None
MINOR 153834K16159 157752K18260
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.
NOTE: This modification related to an Airworthiness issue has been classified by Airbus
and confirmed by EASA as minor in accordance with EU Part 21.A.91. As such, this
minor change is handled by Airbus under its Design Organisation Approval No.
EASA.21J.031.
CONF 005
MODIFICATION CLASSIFICATION
MAJOR None
MINOR 153834K16159 157752K18260
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.
NOTE: This modification related to an Airworthiness issue has been classified by Airbus
and confirmed by EASA as minor in accordance with EU Part 21.A.91. As such, this
minor change is handled by Airbus under its Design Organisation Approval No.
EASA.21J.031.
CONF ALL
B. REASON
(1) History
Full-scale fatigue tests have determined that reinforcement of the fuselage at the
overwing emergency-exit cutouts is necessary for continued aircraft operations up to
the Extended Service Goal (ESG).
(2) Objective/Action
This Service Bulletin introduces reinforcement angles and associated shims at the
overwing emergency-exit cutouts between Frame 38 and Frame 41, LH and RH.
Prior to Service Bulletin embodiment, specific attention must be paid to the
preparation, refer to paragraph 3.B Preparation.
(3) Advantages
Accomplishment of this Service Bulletin will contribute to the continued structural
integrity of the aircraft in the modification area, up to the ESG.
(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".
Accomplishment of this Service Bulletin cancels the requirements of Ref. ALI 533139
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).

### Page 7

A318/A319/A320/A321
SERVICE BULLETIN
SUMMARY
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 7
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 Structure Repair
Manual (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 department should be contacted. Repair review will be
done by AIRBUS at conditions of the Customer Services Catalogue.
C. GENERAL EVALUATION
EVALUATION TABLE
COMPLIANCE MANDATORY COST SAVING NO
A/C OPERATION
AFFECTED
NO VENDOR SB NO
CANCELS INSPECTION SB YES 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.
D. MAINTENANCE CONFIGURATION
CONF 001
No specific aircraft maintenance configuration required.
CONF 002
No specific aircraft maintenance configuration required.
CONF 003
No specific aircraft maintenance configuration required.
CONF 004
No specific aircraft maintenance configuration required.
CONF 005
No specific aircraft maintenance configuration required.
CONF ALL
E. MATERIAL PRICE INFORMATION
CONF 001
(1) Modification

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A318/A319/A320/A321
SERVICE BULLETIN
SUMMARY
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 8
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET QTYPER A/C PRICE PER A/C MAIN PARTS
Part kit 531274D01R02 1 See SB Angles
Part kit 531274D02R06 1 See SB Fillers, foils
CONF 002
(1) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET QTYPER A/C PRICE PER A/C MAIN PARTS
Part kit 531274D01R02 1 See SB Angles
Part kit 531274D02R06 1 See SB Fillers, foils
Part kit 531274D12R02 1 See SB Fasteners
Aircraft standard tools See SB See Note Capital tooling, Durable
tooling, Expendable tooling,
WCI cold working tools
NOTE: Price information to be obtained from the given supplier.
CONF 003
(1) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET QTYPER A/C PRICE PER A/C MAIN PARTS
Part kit 531274D24R02 1 See SB Angles
Part kit 531274D37R02 1 See SB Fasteners
Part kit 531274D38R03 1 See SB Fillers, foils
Aircraft standard tools See SB See Note Capital tooling, Durable
tooling, Expendable tooling,
WCI cold working tools
NOTE: Price information to be obtained from the given supplier.
CONF 004
(1) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET QTYPER A/C PRICE PER A/C MAIN PARTS
Part kit 531274D39R02 1 See SB Fillers, foils

### Page 9

A318/A319/A320/A321
SERVICE BULLETIN
SUMMARY
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 9
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET QTYPER A/C PRICE PER A/C MAIN PARTS
Part kit 531274D40R02 1 See SB Fasteners
Part kit 531274D41R06 1 See SB Angles
Part kit 531274D42R01 1 See SB Fasteners
Aircraft standard tools See SB See Note Capital tooling, Durable
tooling, Expendable tooling,
WCI cold working tools
NOTE: Price information to be obtained from the given supplier.
CONF 005
(1) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET QTYPER A/C PRICE PER A/C MAIN PARTS
Part kit 531274D39R02 1 See SB Fillers, foils
Part kit 531274D43R00 1 See SB Fasteners
Part kit 531274D44R00 1 See SB Angles
Aircraft standard tools See SB See Note Capital tooling, Durable
tooling, Expendable tooling,
WCI cold working tools
NOTE: Price information to be obtained from the given supplier.
CONF ALL
F. APPLICABILITY
This Service Bulletin is applicable to this (these) operator(s):
CLH CTN DAL DLH GWI SWR
NOTE: This Service Bulletin is written for the operators listed above. The modification in
this Service Bulletin can be done by other operators. If other operators want to do
this modification, use the RFC/RMO procedure and write to:
AIRBUS
2 ROND POINT EMILE DEWOITINE
31700 BLAGNAC
FRANCE
G. CONCURRENT REQUIREMENTS
ON A/C 00069-00072, 00078, 00083, 00086, 00093, 00094, 00104, 00110, 00111,
00116-00118, 00135, 00137, 00152, 00161, 00162, 00172, 00197, 00200-00202, 00208,
00209, 00213, 00216-00218, 00262, 00263, 00267-00269, 00272, 00273, 00281, 00282,
00297, 00298, 00306, 00307, 00318, 00319, 00329, 00339, 00340, 00346, 00355, 00358,
00360, 00367, 00372, 00380-00382, 00387, 00388, 00399, 00401, 00408, 00410, 00417,
00418, 00577, 00585, 00596, 00603, 00609, 00610, 00616, 00623, 00627, 00635, 00636,
00641, 00643, 00646, 00651, 00654, 00673, 00679, 00681, 00689, 00694, 00700, 00701,

### Page 10

A318/A319/A320/A321
SERVICE BULLETIN
SUMMARY
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 10
00703, 00717, 00723, 00729, 00738, 00744, 00767, 00794, 00833, 00853, 00860, 00875,
01016, 01172
Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment
of the following Service Bulletin(s):
Service Bulletin(s) Modification(s)
Ref. SB A320-53-1277  
NOTE: Service Bulletin No. Ref. SB A320-53-1277 (FUSELAGE - SECTION 15 -INSPECTION
OF THE EMERGENCY EXIT DOOR HATCHES (LH/RH) IN SECTION 15).
CONF ALL
H. NATURE OF THE WORK
CONF 001
(1) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
AIRCRAFT YES
EQUIPMENT NO
CONF 002
(1) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
AIRCRAFT YES
EQUIPMENT NO
CONF 003
(1) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
AIRCRAFT YES
EQUIPMENT NO
CONF 004
(1) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
AIRCRAFT YES
EQUIPMENT NO
CONF 005
(1) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
AIRCRAFT YES
EQUIPMENT NO
CONF ALL
I. MANPOWER
CONF 001

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SUMMARY
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 11
(1) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
MANPOWER
TOTAL MAN-HOURS 42.00 h
ELAPSED TIME (HOURS) 12.00 h
CONF 002
(1) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
MANPOWER
TOTAL MAN-HOURS 102.00
h
ELAPSED TIME (HOURS) 27.00 h
CONF 003
(1) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
MANPOWER
TOTAL MAN-HOURS 52.00 h
ELAPSED TIME (HOURS) 27.00 h
CONF 004
(1) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
MANPOWER
TOTAL MAN-HOURS 102.00
h
ELAPSED TIME (HOURS) 27.00 h
CONF 005
(1) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
MANPOWER
TOTAL MAN-HOURS 102.00
h
ELAPSED TIME (HOURS) 27.00 h

### Page 12

A318/A319/A320/A321
SERVICE BULLETIN
SUMMARY
Figure ICN-A320-A-53XX1274-A-FAPE3-00PME-A-001-01 SHEET 1/1
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19
General Overview
Page 12
CONF ALL
J. GENERAL OVERVIEW
CONF 001 002 004 005
Z834
Z833
Z843
Z844
Z240
A
ICN-A320-A-53XX1274-A-FAPE3-00PME-A-001-01
FR37
FR38
FR39
FR40
FR41
FR42
STGR13LH
STGR15LH
STGR18LH
STGR13RH
STGR15RH
STGR18RH
STGR20RH
A
STGR20LH
NOTE:
AREA OF MODIFICATION

### Page 13

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SERVICE BULLETIN
SUMMARY
Figure ICN-A320-A-53XX1274-A-FAPE3-00PMF-A-001-01 SHEET 1/1
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19
General Overview
Page 13
CONF 003
Z834
Z844
Z240
A
NOTE:
AREA OF MODIFICATION
FR38
FR39
FR40
FR41
FR42
A
STGR13LH
STGR15LH
STGR18LH
STGR20LH
STGR13RH
STGR15RH
STGR18RH
STGR20RH
ICN-A320-A-53XX1274-A-FAPE3-00PMF-A-001-01

### Page 14

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REV 06 Jul 22/19 Page 14
ATA SYSTEM: 53
TITLE: FUSELAGE - DOORS - EMERGENCY EXIT - REINFORCE THE UPPER
SIDE OF EMERGENCY EXIT DOOR
CONF ALL
1. PLANNING INFORMATION
A. APPLICABILITY
(1) Models
ON A/C 00646, 00654, 00767, 00794, 00833, 01016, 01172
319-112
ON A/C 00609, 00610, 00616, 00623, 00627, 00636, 00641, 00651, 00679, 00689, 00694,
00700, 00717, 00723, 00729, 00738, 00744, 00853, 00860, 00875
319-114
ON A/C 00069-00072, 00078, 00083, 00086, 00093, 00094, 00104, 00110, 00111,
00116-00118, 00135, 00137, 00152, 00161, 00162, 00172, 00197, 00200-00202, 00208,
00209, 00213, 00216-00218, 00262, 00263, 00267-00269, 00272, 00273, 00281, 00282,
00297, 00298, 00306, 00307, 00318, 00319, 00329, 00346, 00382, 00401
320-211
ON A/C 00339, 00340, 00355, 00358, 00360, 00367, 00372, 00380, 00381, 00387, 00388,
00399, 00408, 00410, 00417, 00418
320-212
ON A/C 00577, 00585, 00596, 00603, 00635, 00643, 00673, 00681, 00701, 00703
320-214
CONF ALL
(2) Applicability by MSN
00069-00072 00078 00083 00086 00093 00094 00104 00110 00111 00116-00118
00135 00137 00152 00161 00162 00172 00197 00200-00202 00208 00209 00213
00216-00218 00262 00263 00267-00269 00272 00273 00281 00282 00297 00298
00306 00307 00318 00319 00329 00339 00340 00346 00355 00358 00360 00367
00372 00380-00382 00387 00388 00399 00401 00408 00410 00417 00418 00577
00585 00596 00603 00609 00610 00616 00623 00627 00635 00636 00641 00643
00646 00651 00654 00673 00679 00681 00689 00694 00700 00701 00703 00717
00723 00729 00738 00744 00767 00794 00833 00853 00860 00875 01016 01172
(3) MSN by configuration
CONF 001
MSN CONFIGURATION
00069 00070 00071 00072 00078 00083 00086 00093 00094
00104 00110 00111 00116 00117 00135 00137 00161 00162
00172
001
CONF 002
MSN CONFIGURATION
00200 00201 00202 00209 00216 00217 00218 00267 00268
00269 00346 00382 00401
002
CONF 003

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MSN CONFIGURATION
00609 00610 00616 00623 00627 00636 00641 00646 00651
00654 00679 00689 00694 00700 00717 00723 00729 00738
00744 00767 00794 00833 00853 00860 00875 01016 01172
003
CONF 004
MSN CONFIGURATION
00118 00152 004
CONF 005
MSN CONFIGURATION
00197 00208 00213 00262 00263 00272 00273 00281 00282
00297 00298 00306 00307 00318 00319 00329 00339 00340
00355 00358 00360 00367 00372 00380 00381 00387 00388
00399 00408 00410 00417 00418 00577 00585 00596 00603
00635 00643 00673 00681 00701 00703
005
CONF ALL
(4) Configuration definition
CONF 001
Configuration 001
CONF 001 is applicable to A320 from MSN 1 to 178 (178 included) on which
Service Bulletin A320-53-1031 must have been accomplished.
Service Bulletin A320-53-1031 (retrofit solution of mod 21346K1433) includes
the cold working of the emergency exit area.
CONF 001 retrofits following modifications: 153834K16159.
CONF 002
Configuration 002
CONF 002 is applicable to A320 from MSN 179 and onwards on which serial MOD
21346K1433 is embodied.
Additional cold working of the emergency exit area is required for this
configuration as it is not included in the serial solution of MOD 21346K1433.
CONF 002 retrofits following modifications: 153834K16159.
CONF 003
Configuration 003
CONF 003 is applicable to A319 on which serial MOD 21346K1433 is embodied.
Additional cold working of the emergency exit area is required for this
configuration as it is not included in the serial solution of MOD 21346K1433.
CONF 003 retrofits following modifications: 153834K16159, 157752K18260.
CONF 004
Configuration 004
CONF 004 is applicable to A320 MSN 1 to 178 (178 included) on which
Service Bulletin A320-53-1031 has not been accomplished and on which MOD
157752K18260 has to be applied.
Service Bulletin A320-53-1031 (retrofit solution of mod 21346K1433) includes
the cold working of the emergency exit area.

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REV 06 Jul 22/19 Page 16
Additional cold working of the emergency exit area is required for this
configuration.
CONF 004 retrofits following modifications: 153834K16159, 157752K18260.
CONF 005
Configuration 005
CONF 005 is applicable to A320 from MSN 179 and onwards on which serial mod
21346K1433 is embodied and on which Mod 157752K18260 has to be applied.
Additional cold working of the emergency exit area is required for this
configuration as it is not included in the serial solution of mod 21346K1433.
CONF 005 retrofits following modifications: 153834K16159, 157752K18260.
CONF ALL
B. CONCURRENT REQUIREMENTS
ON A/C 00069-00072, 00078, 00083, 00086, 00093, 00094, 00104, 00110, 00111,
00116-00118, 00135, 00137, 00152, 00161, 00162, 00172, 00197, 00200-00202, 00208,
00209, 00213, 00216-00218, 00262, 00263, 00267-00269, 00272, 00273, 00281, 00282,
00297, 00298, 00306, 00307, 00318, 00319, 00329, 00339, 00340, 00346, 00355, 00358,
00360, 00367, 00372, 00380-00382, 00387, 00388, 00399, 00401, 00408, 00410, 00417,
00418, 00577, 00585, 00596, 00603, 00609, 00610, 00616, 00623, 00627, 00635, 00636,
00641, 00643, 00646, 00651, 00654, 00673, 00679, 00681, 00689, 00694, 00700, 00701,
00703, 00717, 00723, 00729, 00738, 00744, 00767, 00794, 00833, 00853, 00860, 00875,
01016, 01172
Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment
of the following Service Bulletin(s):
Service Bulletin(s) Modification(s)
Ref. SB A320-53-1277  
NOTE: Service Bulletin No. Ref. SB A320-53-1277 (FUSELAGE - SECTION 15 -INSPECTION
OF THE EMERGENCY EXIT DOOR HATCHES (LH/RH) IN SECTION 15).
CONF ALL
C. REASON
(1) History
Full-scale fatigue tests have determined that reinforcement of the fuselage at the
overwing emergency-exit cutouts is necessary for continued aircraft operations up to
the Extended Service Goal (ESG).
(2) Objective/Action
This Service Bulletin introduces reinforcement angles and associated shims at the
overwing emergency-exit cutouts between Frame 38 and Frame 41, LH and RH.
Prior to Service Bulletin embodiment, specific attention must be paid to the
preparation, refer to paragraph 3.B Preparation.
(3) Advantages
Accomplishment of this Service Bulletin will contribute to the continued structural
integrity of the aircraft in the modification area, up to the ESG.
(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".

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REV 06 Jul 22/19 Page 17
Accomplishment of this Service Bulletin cancels the requirements of Ref. ALI 533139
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 Structure Repair
Manual (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 department should be contacted. Repair review will be
done by AIRBUS at conditions of the Customer Services Catalogue.
D. DESCRIPTION
T o accomplish this Service Bulletin it is necessary to:
(1) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
CONF 001 002
1 Remove the Fillers and Shims at the LH Overwing Emergency-Exits
CONF 003
1 Remove the Fillers and Shims at the LH Overwing Emergency-Exit
CONF 004 005
1 Remove the Fillers and Shims at the LH Overwing Emergency-Exits
CONF 001 002
2 Remove the Fillers and Shims at the RH Overwing Emergency-Exits
CONF 003
2 Remove the Fillers and Shims at the RH Overwing Emergency-Exit
CONF 004 005
2 Remove the Fillers and Shims at the RH Overwing Emergency-Exits
CONF 002
3 Remove the Existing Fasteners at the LH Overwing Emergency-Exits
CONF 003
3 Remove the Existing Fasteners at the LH Overwing Emergency-Exit
CONF 004
3 Remove the Existing Fasteners at the LH Overwing Emergency-Exits
CONF 005
3 Remove the Existing Fasteners at the LH Overwing Emergency-Exits
CONF 002
4 Remove the Existing Fasteners at the RH Overwing Emergency-Exits
CONF 003

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4 Remove the Existing Fasteners at the RH Overwing Emergency-Exit
CONF 004
4 Remove the Existing Fasteners at the RH Overwing Emergency-Exits
CONF 005
4 Remove the Existing Fasteners at the RH Overwing Emergency-Exits
CONF 002 005
5 Cold Work the Fastener Holes at the LH Overwing Emergency-Exits
CONF 003
5 Cold Work the Fastener Holes at the LH Overwing Emergency-Exit
CONF 004
5 Cold Work the Fastener Holes at the LH Overwing Emergency-Exits
CONF 002 005
6 Cold Work the Fastener Holes at the RH Overwing Emergency-Exits
CONF 003
6 Cold Work the Fastener Holes at the RH Overwing Emergency-Exit
CONF 004
6 Cold Work the Fastener Holes at the RH Overwing Emergency-Exits
CONF 001
7 Install the Reinforcement Angles at the LH Overwing Emergency-Exits
CONF 002
7 Install the Reinforcement Angles at the LH Overwing Emergency-Exits
CONF 003
7 Install the Reinforcement Angles at the LH Overwing Emergency-Exit
CONF 004
7 Install the Reinforcement Angles at the LH Overwing Emergency-Exits
CONF 005
7 Install the Reinforcement Angles at the LH Overwing Emergency-Exits
CONF 001
8 Install the Reinforcement Angles at the RH Overwing Emergency-Exits
CONF 002
8 Install the Reinforcement Angles at the RH Overwing Emergency-Exits
CONF 003
8 Install the Reinforcement Angles at the RH Overwing Emergency-Exit
CONF 004
8 Install the Reinforcement Angles at the RH Overwing Emergency-Exits
CONF 005
8 Install the Reinforcement Angles at the RH Overwing Emergency-Exits
CONF 002
9 Install the New Fasteners at the LH Overwing Emergency-Exits
CONF 003
9 Install the New Fasteners at the LH Overwing Emergency-Exit
CONF 004
9 Install the New Fasteners at the LH Overwing Emergency-Exits
CONF 005
9 Install the New Fasteners at the LH Overwing Emergency-Exits

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SERVICE BULLETIN
REV 00 Jul 15/14 A320-53-1274
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CONF 002
10 Install the New Fasteners at the RH Overwing Emergency-Exits
CONF 003
10 Install the New Fasteners at the RH Overwing Emergency-Exit
CONF 004
10 Install the New Fasteners at the RH Overwing Emergency-Exits
CONF 005
10 Install the New Fasteners at the RH Overwing Emergency-Exits
CONF 001 002
11 Install the Fillers and Foils at the LH Overwing Emergency-Exits
CONF 003
11 Install the Fillers and Foils at the LH Overwing Emergency-Exit
CONF 004 005
11 Install the Fillers and Foils at the LH Overwing Emergency-Exits
CONF 001 002
12 Install the Fillers and Foils at the RH Overwing Emergency-Exits
CONF 003
12 Install the Fillers and Foils at the RH Overwing Emergency-Exit
CONF 004 005
12 Install the Fillers and Foils at the RH Overwing Emergency-Exits
CONF ALL
E. COMPLIANCE
(1) Classification
MANDATORY: Service Bulletin must be accomplished.
(2) Accomplishment Timescale
This Service Bulletin shall not be embodied before 40000 FC.
This Service Bulletin has been classified Mandatory. It is expected that an
Airworthiness Directive (AD) published by the European 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.
This Service Bulletin has been mandatory for ESG operation above 48000 FC or 96000
FH whichever occurs first. A EASA AD to be issued will confirm this compliance time.
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 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
CONF 001
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

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SERVICE BULLETIN
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 20
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) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
PREPARATION
Job Set-up 1.00 h
PROCEDURE
Remove the Fillers and Shims at the LH Overwing
Emergency-Exits
4.00 h
Remove the Fillers and Shims at the RH Overwing
Emergency-Exits
4.00 h
Install the Reinforcement Angles at the LH Overwing
Emergency-Exits
8.00 h
Install the Reinforcement Angles at the RH Overwing
Emergency-Exits
8.00 h
Install the Fillers and Foils at the LH Overwing Emergency-
Exits
8.00 h
Install the Fillers and Foils at the RH Overwing Emergency-
Exits
8.00 h
PREPARATION FOR TEST
None
TEST
None
CLOSE-UP
Close-up 1.00 h
TOTAL MAN-HOURS 42.00 h
ELAPSED TIME (HOURS) 12.00 h
NOTE: For an explanation of the man-hours and elapsed time, refer to the
Gantt Chart given in Appendix Manpower Gantt Chart.
CONF 002
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) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
PREPARATION
Job Set-up 1.00 h
PROCEDURE
Remove the Fillers and Shims at the LH Overwing
Emergency-Exits
4.00 h

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REV 06 Jul 22/19 Page 21
Remove the Fillers and Shims at the RH Overwing
Emergency-Exits
4.00 h
Remove the Existing Fasteners at the LH Overwing
Emergency-Exits
8.00 h
Remove the Existing Fasteners at the RH Overwing
Emergency-Exits
8.00 h
Cold Work the Fastener Holes at the LH Overwing
Emergency-Exits
12.00 h
Cold Work the Fastener Holes at the RH Overwing
Emergency-Exits
12.00 h
Install the Reinforcement Angles at the LH Overwing
Emergency-Exits
8.00 h
Install the Reinforcement Angles at the RH Overwing
Emergency-Exits
8.00 h
Install the New Fasteners at the LH Overwing Emergency-
Exits
10.00 h
Install the New Fasteners at the RH Overwing Emergency-
Exits
10.00 h
Install the Fillers and Foils at the LH Overwing Emergency-
Exits
8.00 h
Install the Fillers and Foils at the RH Overwing Emergency-
Exits
8.00 h
PREPARATION FOR TEST
None
TEST
None
CLOSE-UP
Close-up 1.00 h
TOTAL MAN-HOURS 102.00 h
ELAPSED TIME (HOURS) 27.00 h
NOTE: For an explanation of the man-hours and elapsed time, refer to the
Gantt Chart given in Appendix Manpower Gantt Chart.
CONF 003
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) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
PREPARATION
Job Set-up 1.00 h
PROCEDURE
Remove the Fillers and Shims at the LH Overwing
Emergency-Exit
2.00 h

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REV 06 Jul 22/19 Page 22
Remove the Fillers and Shims at the RH Overwing
Emergency-Exit
2.00 h
Remove the Existing Fasteners at the LH Overwing
Emergency-Exit
4.00 h
Remove the Existing Fasteners at the RH Overwing
Emergency-Exit
4.00 h
Cold Work the Fastener Holes at the LH Overwing
Emergency-Exit
6.00 h
Cold Work the Fastener Holes at the RH Overwing
Emergency-Exit
6.00 h
Install the Reinforcement Angles at the LH Overwing
Emergency-Exit
4.00 h
Install the Reinforcement Angles at the RH Overwing
Emergency-Exit
4.00 h
Install the New Fasteners at the LH Overwing Emergency-
Exit
5.00 h
Install the New Fasteners at the RH Overwing Emergency-
Exit
5.00 h
Install the Fillers and Foils at the LH Overwing Emergency-
Exit
4.00 h
Install the Fillers and Foils at the RH Overwing Emergency-
Exit
4.00 h
PREPARATION FOR TEST
None
TEST
None
CLOSE-UP
Close-up 1.00 h
TOTAL MAN-HOURS 52.00 h
ELAPSED TIME (HOURS) 27.00 h
NOTE: For an explanation of the man-hours and elapsed time, refer to the
Gantt Chart given in Appendix Manpower Gantt Chart.
CONF 004
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) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
PREPARATION
Job Set-up 1.00 h
PROCEDURE
Remove the Fillers and Shims at the LH Overwing
Emergency-Exits
4.00 h

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SERVICE BULLETIN
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 23
Remove the Fillers and Shims at the RH Overwing
Emergency-Exits
4.00 h
Remove the Existing Fasteners at the LH Overwing
Emergency-Exits
8.00 h
Remove the Existing Fasteners at the RH Overwing
Emergency-Exits
8.00 h
Cold Work the Fastener Holes at the LH Overwing
Emergency-Exits
12.00 h
Cold Work the Fastener Holes at the RH Overwing
Emergency-Exits
12.00 h
Install the Reinforcement Angles at the LH Overwing
Emergency-Exits
8.00 h
Install the Reinforcement Angles at the RH Overwing
Emergency-Exits
8.00 h
Install the New Fasteners at the LH Overwing Emergency-
Exits
10.00 h
Install the New Fasteners at the RH Overwing Emergency-
Exits
10.00 h
Install the Fillers and Foils at the LH Overwing Emergency-
Exits
8.00 h
Install the Fillers and Foils at the RH Overwing Emergency-
Exits
8.00 h
PREPARATION FOR TEST
None
TEST
None
CLOSE-UP
Close-up 1.00 h
TOTAL MAN-HOURS 102.00 h
ELAPSED TIME (HOURS) 27.00 h
NOTE: For an explanation of the man-hours and elapsed time, refer to the
Gantt Chart given in Appendix Manpower Gantt Chart.
CONF 005
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) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
PREPARATION
Job Set-up 1.00 h
PROCEDURE
Remove the Fillers and Shims at the LH Overwing
Emergency-Exits
4.00 h

### Page 24

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SERVICE BULLETIN
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 24
Remove the Fillers and Shims at the RH Overwing
Emergency-Exits
4.00 h
Remove the Existing Fasteners at the LH Overwing
Emergency-Exits
8.00 h
Remove the Existing Fasteners at the RH Overwing
Emergency-Exits
8.00 h
Cold Work the Fastener Holes at the LH Overwing
Emergency-Exits
12.00 h
Cold Work the Fastener Holes at the RH Overwing
Emergency-Exits
12.00 h
Install the Reinforcement Angles at the LH Overwing
Emergency-Exits
8.00 h
Install the Reinforcement Angles at the RH Overwing
Emergency-Exits
8.00 h
Install the New Fasteners at the LH Overwing Emergency-
Exits
10.00 h
Install the New Fasteners at the RH Overwing Emergency-
Exits
10.00 h
Install the Fillers and Foils at the LH Overwing Emergency-
Exits
8.00 h
Install the Fillers and Foils at the RH Overwing Emergency-
Exits
8.00 h
PREPARATION FOR TEST
None
TEST
None
CLOSE-UP
Close-up 1.00 h
TOTAL MAN-HOURS 102.00 h
ELAPSED TIME (HOURS) 27.00 h
NOTE: For an explanation of the man-hours and elapsed time, refer to the
Gantt Chart given in Appendix Manpower Gantt Chart.
CONF ALL
H. WEIGHT AND BALANCE
CONF 001
The weight and balance estimates given in this Service Bulletin are based on the
Manufacturer's Empty Weight (MEW) and do not include operator's items. The definition of
MEW and operator's items is given in the Weight and Balance Manual (WBM), Ref. WBM.
Manufacturer's Empty Weight +2.1 kg (+4.630 lb)
Effect on Balance +36.5 kg.m (+264.005 lb.ft)
CONF 002
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. The definition of
MEW and operator's items is given in the Weight and Balance Manual (WBM), Ref. WBM.
Manufacturer's Empty Weight +2.6 kg (+5.732 lb)

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REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 25
Effect on Balance +45.5 kg.m (+329.102 lb.ft)
CONF 003
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. The definition of
MEW and operator's items is given in the Weight and Balance Manual (WBM), Ref. WBM.
Manufacturer's Empty Weight +1.2 kg (+2.646 lb)
Effect on Balance +20.2 kg.m (+146.107 lb.ft)
CONF 004
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. The definition of
MEW and operator's items is given in the Weight and Balance Manual (WBM), Ref. WBM.
Manufacturer's Empty Weight +2.3 kg (+5.071 lb)
Effect on Balance +39.2 kg.m (+283.534 lb.ft)
CONF 005
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. The definition of
MEW and operator's items is given in the Weight and Balance Manual (WBM), Ref. WBM.
Manufacturer's Empty Weight +1.9 kg (+4.189 lb)
Effect on Balance +32.2 kg.m (+232.903 lb.ft)
CONF ALL
I. ELECTRICAL LOAD DATA
Not changed
J. REFERENCES
ON A/C 00069-00072, 00078, 00083, 00086, 00093, 00094, 00104, 00110, 00111,
00116-00118, 00135, 00137, 00152, 00161, 00162, 00172, 00197, 00200-00202, 00208,
00209, 00213, 00216-00218, 00262, 00263, 00267-00269, 00272, 00273, 00281, 00282,
00297, 00298, 00306, 00307, 00318, 00319, 00329, 00339, 00340, 00346, 00355, 00358,
00360, 00367, 00372, 00380-00382, 00387, 00388, 00399, 00401, 00408, 00410, 00417,
00418, 00577, 00585, 00596, 00603, 00609, 00610, 00616, 00623, 00627, 00635, 00636,
00641, 00643, 00646, 00651, 00654, 00673, 00679, 00681, 00689, 00694, 00700, 00701,
00703, 00717, 00723, 00729, 00738, 00744, 00767, 00794, 00833, 00853, 00860, 00875,
01016, 01172
CONCURRENT SERVICE BULLETIN (SB)
A320-53-1277
CONF 001
(1) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
AIRWORTHINESS LIMITATION ITEMS (ALI)
533139
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 25-23-47-000-002

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SERVICE BULLETIN
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 26
AIRCRAFT MAINTENANCE MANUAL (AMM)
T ask 25-23-47-400-002
T ask 52-21-11-000-001
T ask 52-21-11-400-001
ELECTRICAL STANDARD PRACTICES MANUAL (ESPM)
20-55-00
SERVICE BULLETIN (SB)
A320-53-1032
STRUCTURAL REPAIR MANUAL (SRM)
51-24-00 51-42-00
51-44-00 51-46-00
51-47-00 51-75-12
WEIGHT AND BALANCE MANUAL (WBM)
STANDARDS MANUAL (SM)
CONSUMABLE MATERIAL LIST (CML)
CONF 002
(1) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
AIRWORTHINESS LIMITATION ITEMS (ALI)
533139
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 25-23-47-000-002
T ask 25-23-47-400-002
T ask 52-21-11-000-001
T ask 52-21-11-400-001
ELECTRICAL STANDARD PRACTICES MANUAL (ESPM)
20-55-00
IN SERVICE INFORMATION (ISI)
51.48.00001
STRUCTURAL REPAIR MANUAL (SRM)
51-24-00 51-42-00
51-44-00 51-46-00
51-47-00 51-48-00
51-75-12
WEIGHT AND BALANCE MANUAL (WBM)

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SERVICE BULLETIN
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 27
STANDARDS MANUAL (SM)
CONSUMABLE MATERIAL LIST (CML)
CONF 003
(1) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
AIRWORTHINESS LIMITATION ITEMS (ALI)
533139
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 25-23-47-000-002
T ask 25-23-47-400-002
T ask 52-21-11-000-001
T ask 52-21-11-400-001
ELECTRICAL STANDARD PRACTICES MANUAL (ESPM)
20-55-00
IN SERVICE INFORMATION (ISI)
51.48.00001
STRUCTURAL REPAIR MANUAL (SRM)
51-24-00 51-42-00
51-44-00 51-46-00
51-47-00 51-48-00
51-75-12
WEIGHT AND BALANCE MANUAL (WBM)
STANDARDS MANUAL (SM)
CONSUMABLE MATERIAL LIST (CML)
CONF 004
(1) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
AIRWORTHINESS LIMITATION ITEMS (ALI)
533139
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 25-23-47-000-002
T ask 25-23-47-400-002
T ask 52-21-11-000-001

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REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 28
AIRCRAFT MAINTENANCE MANUAL (AMM)
T ask 52-21-11-400-001
ELECTRICAL STANDARD PRACTICES MANUAL (ESPM)
20-55-00
IN SERVICE INFORMATION (ISI)
51.48.00001
SERVICE BULLETIN (SB)
A320-53-1032
STRUCTURAL REPAIR MANUAL (SRM)
51-24-00 51-42-00
51-44-00 51-46-00
51-47-00 51-48-00
51-75-12
WEIGHT AND BALANCE MANUAL (WBM)
STANDARDS MANUAL (SM)
CONSUMABLE MATERIAL LIST (CML)
CONF 005
(1) Modification
(a) T ask set A320-A-53-XX-1274-01000-93AA-A Modification
AIRWORTHINESS LIMITATION ITEMS (ALI)
533139
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 25-23-47-000-002
T ask 25-23-47-400-002
T ask 52-21-11-000-001
T ask 52-21-11-400-001
ELECTRICAL STANDARD PRACTICES MANUAL (ESPM)
20-55-00
IN SERVICE INFORMATION (ISI)
51.48.00001
STRUCTURAL REPAIR MANUAL (SRM)
51-24-00 51-42-00
51-44-00 51-46-00
51-47-00 51-48-00

### Page 29

A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 29
STRUCTURAL REPAIR MANUAL (SRM)
51-75-12
WEIGHT AND BALANCE MANUAL (WBM)
STANDARDS MANUAL (SM)
CONSUMABLE MATERIAL LIST (CML)
CONF ALL
K. PUBLICATION AFFECTED
AIRWORTHINESS LIMITATION SECTION (ALS)
MAINTENANCE PLANNING DOCUMENT (MPD)
STRUCTURAL REPAIR MANUAL (SRM)
L. INDUSTRY SUPPORT INFORMATION
Industry Support terms must be agreed between the Customer and AIRBUS in accordance
with the RFC (or RFC/RMO) procedure.

### Page 30

A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 30
2. MATERIAL INFORMATION
A. MATERIAL APPLICABILITY
CONF 001
Material for task set A320-A-53-XX-1274-01000-93AA-A Modification
MATERIAL QTY SEE NOTES
Consumables See SB
Part kit 531274D01R02 1
Part kit 531274D02R06 1
CONF 002
Material for task set A320-A-53-XX-1274-01000-93AA-A Modification
MATERIAL QTY SEE NOTES
Aircraft standard tools See SB
Consumables See SB
Part kit 531274D01R02 1
Part kit 531274D02R06 1
Part kit 531274D12R02 1
CONF 003
Material for task set A320-A-53-XX-1274-01000-93AA-A Modification
MATERIAL QTY SEE NOTES
Aircraft standard tools See SB
Consumables See SB
Part kit 531274D24R02 1
Part kit 531274D37R02 1
Part kit 531274D38R03 1
CONF 004
Material for task set A320-A-53-XX-1274-01000-93AA-A Modification
MATERIAL QTY SEE NOTES
Aircraft standard tools See SB
Consumables See SB
Part kit 531274D39R02 1
Part kit 531274D40R02 1
Part kit 531274D41R06 1
Part kit 531274D42R01 1
CONF 005
Material for task set A320-A-53-XX-1274-01000-93AA-A Modification
MATERIAL QTY SEE NOTES
Aircraft standard tools See SB
Consumables See SB
Part kit 531274D39R02 1
Part kit 531274D43R00 1

### Page 31

A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 31
MATERIAL QTY SEE NOTES
Part kit 531274D44R00 1
CONF ALL
B. TOOLING
CONF 002
Aircraft standard tools for task set A320-A-53-XX-1274-01000-93AA-A
Modification
Procurement address
51439
Fatigue T echnology Inc.
401 Andover Park East
SEATTLE, WA 98188-7605
USA
Phone: (206) 2462010
Fax: (206) 2449886
Internet: http://www.fatiguetech.com
66136
West Coast Industries Inc.
14900 Whitman Ave. N
Seattle, Washington 98133
USA
Phone: (206) 365-7513
Fax: (206) 365-7483
E-mail: info@coldwork.com
NOTE(S)
Fatigue T echnology Inc.
401 Andover Park East
SEATTLE, WA 98188-7605
USA
Phone: (206) 2462010
Fax: (206) 2449886
Internet: http://www.fatiguetech.com
Operators interested in obtaining the Fatigue T echnology Incorporated (FTI) tool kit
part numbers listed below should contact FTI at the address given above.
Operators interested in obtaining the West Coast Industries (WCI) tool kit part
numbers listed below should contact WCI at the address given above.
WCI contact for operators in Europe, Middle-East, Africa, India and Russia:
Phone: +33 5 61 92 04 91 (France)
E-MAIL: customer@capaero.com
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
DKA320531274-1
(51439) (66136) 2 TOOLKIT (1) (2)
EKA320531274-1
(51439) (66136) 2 TOOLKIT (3) (2)
FTIA320531274-1
(51439) 1 TOOLKIT (4) (5) (2)
WCIA320531274-1
(66136) 1 TOOLKIT (2) (6) (7)
NOTE(S)
(1): Durable tooling. Ref: DK-A320-53-1274-1

### Page 32

A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 32
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
The durable tool kit contains the minimum quantity of durable tools necessary
to accomplish the Service Bulletin on one aircraft. If the Service Bulletin is to be
accomplished on more than one aircraft, the number of durable kits required can be
established by reference to Ref. ISI 51.48.00001.
(2): The components listed above are not an AIRBUS Kit, the required parts must be
ordered as necessary through the given channel.
(3): Expendable tooling. Ref: EK-A320-53-1274-1
The expendable tool kit contains the quantity of expendable tools required to
accomplish the Service Bulletin on one aircraft. Order one expendable tool kit for
every aircraft on which this Service Bulletin is to be accomplished.
(4): Capital tooling. Ref: FTI-A320-53-1274-1
The capital tools provided in this kit are not specific to this Service Bulletin and are
normally already available in operators' stock as a long-term investment or can be
loaned from Fatigue T echnology Incorporated (FTI).
(5): Fatigue T echnology Incorporated (FTI) has allocated these tool kit part numbers for
cold expansion:
For the definition of capital, durable and expendable tools, refer to Ref. ISI
51.48.00001.
(6): West Coast Industries (WCI) has allocated these tool kit part numbers for cold
expansion:
For the definition of capital, durable and expendable tools, refer to Ref. ISI
51.48.00001.
(7): Capital tooling. Ref: WCI-A320-53-1274-1
The capital tools provided in this kit are not specific to this Service Bulletin and are
normally already available in operators' stock as a long-term investment or can be
loaned from West Coast Industries (WCI).
CONF 003
Aircraft standard tools for task set A320-A-53-XX-1274-01000-93AA-A
Modification
Procurement address
51439
Fatigue T echnology Inc.
401 Andover Park East
SEATTLE, WA 98188-7605
USA
Phone: (206) 2462010
Fax: (206) 2449886
Internet: http://www.fatiguetech.com
66136
West Coast Industries Inc.
14900 Whitman Ave. N
Seattle, Washington 98133
USA
Phone: (206) 365-7513
Fax: (206) 365-7483
E-mail: info@coldwork.com
NOTE(S)
Fatigue T echnology Inc.
401 Andover Park East
SEATTLE, WA 98188-7605
USA

### Page 33

A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 33
Phone: (206) 2462010
Fax: (206) 2449886
Internet: http://www.fatiguetech.com
Operators interested in obtaining the Fatigue T echnology Incorporated (FTI) tool kit
part numbers listed below should contact FTI at the address given above.
Operators interested in obtaining the West Coast Industries (WCI) tool kit part
numbers listed below should contact WCI at the address given above.
WCI contact for operators in Europe, Middle-East, Africa, India and Russia:
Phone: +33 5 61 92 04 91 (France)
E-MAIL: customer@capaero.com
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
DKA320531274-1
(51439) (66136) 2 TOOLKIT (1) (2)
EKA320531274-1
(51439) (66136) 2 TOOLKIT (3) (2)
FTIA320531274-1
(51439) 1 TOOLKIT (4) (5) (2)
WCIA320531274-1
(66136) 1 TOOLKIT (2) (6) (7)
NOTE(S)
(1): Durable tooling. Ref: DK-A320-53-1274-1
The durable tool kit contains the minimum quantity of durable tools necessary
to accomplish the Service Bulletin on one aircraft. If the Service Bulletin is to be
accomplished on more than one aircraft, the number of durable kits required can be
established by reference to Ref. ISI 51.48.00001.
(2): The components listed above are not an AIRBUS Kit, the required parts must be
ordered as necessary through the given channel.
(3): Expendable tooling. Ref: EK-A320-53-1274-1
The expendable tool kit contains the quantity of expendable tools required to
accomplish the Service Bulletin on one aircraft. Order one expendable tool kit for
every aircraft on which this Service Bulletin is to be accomplished.
(4): Capital tooling. Ref: FTI-A320-53-1274-1
The capital tools provided in this kit are not specific to this Service Bulletin and are
normally already available in operators' stock as a long-term investment or can be
loaned from Fatigue T echnology Incorporated (FTI).
(5): Fatigue T echnology Incorporated (FTI) has allocated these tool kit part numbers for
cold expansion:
For the definition of capital, durable and expendable tools, refer to Ref. ISI
51.48.00001.
(6): West Coast Industries (WCI) has allocated these tool kit part numbers for cold
expansion:
For the definition of capital, durable and expendable tools, refer to Ref. ISI
51.48.00001.
(7): Capital tooling. Ref: WCI-A320-53-1274-1

### Page 34

A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 34
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
The capital tools provided in this kit are not specific to this Service Bulletin and are
normally already available in operators' stock as a long-term investment or can be
loaned from West Coast Industries (WCI).
CONF 004
Aircraft standard tools for task set A320-A-53-XX-1274-01000-93AA-A
Modification
Procurement address
51439
Fatigue T echnology Inc.
401 Andover Park East
SEATTLE, WA 98188-7605
USA
Phone: (206) 2462010
Fax: (206) 2449886
Internet: http://www.fatiguetech.com
66136
West Coast Industries Inc.
14900 Whitman Ave. N
Seattle, Washington 98133
USA
Phone: (206) 365-7513
Fax: (206) 365-7483
E-mail: info@coldwork.com
NOTE(S)
Fatigue T echnology Inc.
401 Andover Park East
SEATTLE, WA 98188-7605
USA
Phone: (206) 2462010
Fax: (206) 2449886
Internet: http://www.fatiguetech.com
Operators interested in obtaining the Fatigue T echnology Incorporated (FTI) tool kit
part numbers listed below should contact FTI at the address given above.
Operators interested in obtaining the West Coast Industries (WCI) tool kit part
numbers listed below should contact WCI at the address given above.
WCI contact for operators in Europe, Middle-East, Africa, India and Russia:
Phone: +33 5 61 92 04 91 (France)
E-MAIL: customer@capaero.com
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
DKA320531274-1
(51439) (66136) 2 TOOLKIT (1) (2)
EKA320531274-1
(51439) (66136) 2 TOOLKIT (3) (2)
FTIA320531274-1
(51439) 1 TOOLKIT (4) (5) (2)
WCIA320531274-1
(66136) 1 TOOLKIT (2) (6) (7)
NOTE(S)
(1): Durable tooling. Ref: DK-A320-53-1274-1

### Page 35

A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 35
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
The durable tool kit contains the minimum quantity of durable tools necessary
to accomplish the Service Bulletin on one aircraft. If the Service Bulletin is to be
accomplished on more than one aircraft, the number of durable kits required can be
established by reference to Ref. ISI 51.48.00001.
(2): The components listed above are not an AIRBUS Kit, the required parts must be
ordered as necessary through the given channel.
(3): Expendable tooling. Ref: EK-A320-53-1274-1
The expendable tool kit contains the quantity of expendable tools required to
accomplish the Service Bulletin on one aircraft. Order one expendable tool kit for
every aircraft on which this Service Bulletin is to be accomplished.
(4): Capital tooling. Ref: FTI-A320-53-1274-1
The capital tools provided in this kit are not specific to this Service Bulletin and are
normally already available in operators' stock as a long-term investment or can be
loaned from Fatigue T echnology Incorporated (FTI).
(5): Fatigue T echnology Incorporated (FTI) has allocated these tool kit part numbers for
cold expansion:
For the definition of capital, durable and expendable tools, refer to Ref. ISI
51.48.00001.
(6): West Coast Industries (WCI) has allocated these tool kit part numbers for cold
expansion:
For the definition of capital, durable and expendable tools, refer to Ref. ISI
51.48.00001.
(7): Capital tooling. Ref: WCI-A320-53-1274-1
The capital tools provided in this kit are not specific to this Service Bulletin and are
normally already available in operators' stock as a long-term investment or can be
loaned from West Coast Industries (WCI).
CONF 005
Aircraft standard tools for task set A320-A-53-XX-1274-01000-93AA-A
Modification
Procurement address
51439
Fatigue T echnology Inc.
401 Andover Park East
SEATTLE, WA 98188-7605
USA
Phone: (206) 2462010
Fax: (206) 2449886
Internet: http://www.fatiguetech.com
66136
West Coast Industries Inc.
14900 Whitman Ave. N
Seattle, Washington 98133
USA
Phone: (206) 365-7513
Fax: (206) 365-7483
E-mail: info@coldwork.com
NOTE(S)
Fatigue T echnology Inc.
401 Andover Park East
SEATTLE, WA 98188-7605
USA

### Page 36

A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 36
Phone: (206) 2462010
Fax: (206) 2449886
Internet: http://www.fatiguetech.com
Operators interested in obtaining the Fatigue T echnology Incorporated (FTI) tool kit
part numbers listed below should contact FTI at the address given above.
Operators interested in obtaining the West Coast Industries (WCI) tool kit part
numbers listed below should contact WCI at the address given above.
WCI contact for operators in Europe, Middle-East, Africa, India and Russia:
Phone: +33 5 61 92 04 91 (France)
E-MAIL: customer@capaero.com
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
DKA320531274-1
(51439) (66136) 2 TOOLKIT (1) (2)
EKA320531274-1
(51439) (66136) 2 TOOLKIT (3) (2)
FTIA320531274-1
(51439) 1 TOOLKIT (4) (5) (2)
WCIA320531274-1
(66136) 1 TOOLKIT (2) (6) (7)
NOTE(S)
(1): Durable tooling. Ref: DK-A320-53-1274-1
The durable tool kit contains the minimum quantity of durable tools necessary
to accomplish the Service Bulletin on one aircraft. If the Service Bulletin is to be
accomplished on more than one aircraft, the number of durable kits required can be
established by reference to Ref. ISI 51.48.00001.
(2): The components listed above are not an AIRBUS Kit, the required parts must be
ordered as necessary through the given channel.
(3): Expendable tooling. Ref: EK-A320-53-1274-1
The expendable tool kit contains the quantity of expendable tools required to
accomplish the Service Bulletin on one aircraft. Order one expendable tool kit for
every aircraft on which this Service Bulletin is to be accomplished.
(4): Capital tooling. Ref: FTI-A320-53-1274-1
The capital tools provided in this kit are not specific to this Service Bulletin and are
normally already available in operators' stock as a long-term investment or can be
loaned from Fatigue T echnology Incorporated (FTI).
(5): Fatigue T echnology Incorporated (FTI) has allocated these tool kit part numbers for
cold expansion:
For the definition of capital, durable and expendable tools, refer to Ref. ISI
51.48.00001.
(6): West Coast Industries (WCI) has allocated these tool kit part numbers for cold
expansion:
For the definition of capital, durable and expendable tools, refer to Ref. ISI
51.48.00001.
(7): Capital tooling. Ref: WCI-A320-53-1274-1

### Page 37

A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 37
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
The capital tools provided in this kit are not specific to this Service Bulletin and are
normally already available in operators' stock as a long-term investment or can be
loaned from West Coast Industries (WCI).
CONF 001
No tools
CONF ALL
C. CONSUMABLES
CONF 001
Consumables for task set A320-A-53-XX-1274-01000-93AA-A Modification
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
04DAB2
Primer Epoxy Paint-
Corrosion Inhibiting-
tructure
04JME4 T op Coat Polyurethane-Grey-Internal Struture
05EJL9 Epoxy Adhesive-Metal tometal-Legacy
06AAA1 Polysulfide Sealant-GeneralPurpose-Brusable
06AAC1 Polysulfide Sealant-GeneralPurpose-Intefay
06AAE1 Polysulfide Sealant-GeneralPurpose-Smooher
08BAA9 Non Aqueous Cleaner-General
14SBA1 T extile-Lint free-Cotton
CONF 002
Consumables for task set A320-A-53-XX-1274-01000-93AA-A Modification
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
04DAB2
Primer Epoxy Paint-
Corrosion Inhibiting-
tructure
04JME4 T op Coat Polyurethane-Grey-Internal Struture
05EJL9 Epoxy Adhesive-Metal tometal-Legacy
06AAA1 Polysulfide Sealant-GeneralPurpose-Brusable
06AAC1 Polysulfide Sealant-GeneralPurpose-Intefay
06AAE1 Polysulfide Sealant-GeneralPurpose-Smooher
08BAA9 Non Aqueous Cleaner-General
14SBA1 T extile-Lint free-Cotton

### Page 38

A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 38
CONF 003
Consumables for task set A320-A-53-XX-1274-01000-93AA-A Modification
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
04DAB2
Primer Epoxy Paint-
Corrosion Inhibiting-
tructure
04JME4 T op Coat Polyurethane-Grey-Internal Struture
05EAT1 Epoxy Adhesive-General-Upto 135°C
06AAA1 Polysulfide Sealant-GeneralPurpose-Brusable
06AAC1 Polysulfide Sealant-GeneralPurpose-Intefay
08BAA9 Non Aqueous Cleaner-General
14SBA1 T extile-Lint free-Cotton
CONF 004
Consumables for task set A320-A-53-XX-1274-01000-93AA-A Modification
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
04DAB2
Primer Epoxy Paint-
Corrosion Inhibiting-
tructure
04JME4 T op Coat Polyurethane-Grey-Internal Struture
05EJL9 Epoxy Adhesive-Metal tometal-Legacy
06AAA1 Polysulfide Sealant-GeneralPurpose-Brusable
06AAC1 Polysulfide Sealant-GeneralPurpose-Intefay
06AAE1 Polysulfide Sealant-GeneralPurpose-Smooher
08BAA9 Non Aqueous Cleaner-General
14SBA1 T extile-Lint free-Cotton
CONF 005
Consumables for task set A320-A-53-XX-1274-01000-93AA-A Modification
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
04DAB2
Primer Epoxy Paint-
Corrosion Inhibiting-
tructure
04JME4 T op Coat Polyurethane-Grey-Internal Struture
05EJL9 Epoxy Adhesive-Metal tometal-Legacy

### Page 39

A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 39
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
06AAA1 Polysulfide Sealant-GeneralPurpose-Brusable
06AAC1 Polysulfide Sealant-GeneralPurpose-Intefay
06AAE1 Polysulfide Sealant-GeneralPurpose-Smooher
08BAA9 Non Aqueous Cleaner-General
14SBA1 T extile-Lint free-Cotton
CONF ALL
D. LIST OF NEW PARTS
CONF 001 002
Part kit 531274D01R02
Availability
NOTE(S)
Sales terms must be agreed between the Customer and AIRBUS in accordance with
the RFC (or RFC/RMO) procedure.
Procurement address  
NOTE(S)
The AIRBUS material is included in the commercial offer and as such will be supplied
by AIRBUS Upgrade Services. T o facilitate the material reception, Airline Customers
are requested to contact:
AIRBUS Upgrade Services
Attn. Sales Manager
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
1 D5337034420000 1 ANGLE
2 D5337034420100 1 ANGLE
3 D5337034420200 1 ANGLE
4 D5337034420300 1 ANGLE
5 D5337034420400 1 ANGLE
6 D5337034420500 1 ANGLE
7 D5337034420700 2 ANGLE
8 D5337034420600 2 ANGLE
9 D5337034420800 1 ANGLE
10 D5337034420900 1 ANGLE
13 D5337034421000 1 ANGLE
14 D5337034421100 1 ANGLE
15 D5337034421200 1 ANGLE
16 D5337034421300 1 ANGLE
17 DAN6-5-4 128 PIN
18 NSA5075-5 258 COLLAR
19 NSA5076-5 36 COLLAR

### Page 40

A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 40
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
20 DAN6-5-5 158 PIN
21 DAN6-5-6 8 PIN
22 ABS0213-6-10R 12 RIVET
23 ABS0213-6-9R 18 RIVET
24 ABS1155-7WA9 24 RIVET
25 ABS1155-7WA8 32 RIVET
26 ABS1155-7WA6 28 RIVET
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.
Part kit 531274D02R06
Availability
NOTE(S)
Sales terms must be agreed between the Customer and AIRBUS in accordance with
the RFC (or RFC/RMO) procedure.
Procurement address  
NOTE(S)
The AIRBUS material is included in the commercial offer and as such will be supplied
by AIRBUS Upgrade Services. T o facilitate the material reception, Airline Customers
are requested to contact:
AIRBUS Upgrade Services
Attn. Sales Manager
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
99 D5337625020800 4 FILLER
100 D5337625021000 2 FILLER
101 D5337625021200 2 FILLER
102 DAN155A38 6 (m) FOIL (1)
103 DAN155A64 6 (m) FOIL (1)
104 DAN155A79 6 (m) FOIL (1)
105 D5337625021400 2 FILLER
106 D5337625021500 2 FILLER
107 D5337625000400 2 FILLER
108 D5337625000500 2 FILLER
109 D5337625021600 1 FILLER
110 D5337625021700 1 FILLER
111 D5337625000800 1 FILLER
112 D5337625000900 1 FILLER
113 D5337625021800 1 FILLER
114 D5337625021900 1 FILLER
115 D5337625020200 1 FILLER

### Page 41

A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 41
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
116 D5337625020300 1 FILLER
117 D5337625020000 1 FILLER
118 D5337625020100 1 FILLER
119 D5337625020400 1 FILLER
120 D5337625020500 1 FILLER
121 D5337625020600 1 FILLER
122 D5337625020700 1 FILLER
124 EN6101AD4-13 110 RIVET
125 DAN6-6-10 14 PIN
126 NSA5075-6 14 COLLAR
NOTE(S)
Kit D02R04 is still applicable in this Service Bulletin, there is no technical change
between kit D02R04 and kit D02R06.
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.
(1): Select correct foil thickness and cut to length during assembly.
CONF 002
Part kit 531274D12R02
Availability
NOTE(S)
Sales terms must be agreed between the Customer and AIRBUS in accordance with
the RFC (or RFC/RMO) procedure.
Procurement address  
NOTE(S)
The AIRBUS material is included in the commercial offer and as such will be supplied
by AIRBUS Upgrade Services. T o facilitate the material reception, Airline Customers
are requested to contact:
AIRBUS Upgrade Services
Attn. Sales Manager
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
1 EN6114K3A7 64 BOLT
2 EN6114K3A9 70 BOLT
3 EN6114K3A11 20 BOLT
4 EN6114K3A13 6 BOLT
5 ASNA2528-3A 160 NUT
NOTE(S)
Kit D12R00 is still applicable in this Service Bulletin, there is no technical change
between kit D12R00 and kit D12R02.
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.

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CONF 003
Part kit 531274D24R02
Availability
NOTE(S)
Sales terms must be agreed between the Customer and AIRBUS in accordance with
the RFC (or RFC/RMO) procedure.
Procurement address  
NOTE(S)
The AIRBUS material is included in the commercial offer and as such will be supplied
by AIRBUS Upgrade Services. T o facilitate the material reception, Airline Customers
are requested to contact:
AIRBUS Upgrade Services
Attn. Sales Manager
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
17 DAN6-5-4 50 PIN
18 NSA5075-5 118 COLLAR
19 NSA5076-5 20 COLLAR
20 DAN6-5-5 84 PIN
21 DAN6-5-6 4 PIN
22 ABS0213-6-10R 4 RIVET
23 ABS0213-6-9R 10 RIVET
24 ABS1155-7WA9 10 RIVET
25 ABS1155-7WA8 16 RIVET
26 ABS1155-7WA6 14 RIVET
27 D5337034423000 1 ANGLE
28 D5337034423100 1 ANGLE
29 D5337034422800 1 ANGLE
30 D5337034422900 1 ANGLE
31 D5337034423200 1 ANGLE
32 D5337034423300 1 ANGLE
33 D5337034423400 1 ANGLE
34 D5337034423500 1 ANGLE
NOTE(S)
Kit D24R00 is still applicable in this Service Bulletin, there is no technical change
between kit D24R00 and kit D24R02.
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.
Part kit 531274D37R02
Availability
NOTE(S)

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Sales terms must be agreed between the Customer and AIRBUS in accordance with
the RFC (or RFC/RMO) procedure.
Procurement address  
NOTE(S)
The AIRBUS material is included in the commercial offer and as such will be supplied
by AIRBUS Upgrade Services. T o facilitate the material reception, Airline Customers
are requested to contact:
AIRBUS Upgrade Services
Attn. Sales Manager
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
1 EN6114K3A7 32 BOLT
2 EN6114K3A9 32 BOLT
3 EN6114K3A11 12 BOLT
4 EN6114K3A13 6 BOLT
5 ASNA2528-3A 82 NUT
NOTE(S)
Kit D37R00 is still applicable in this Service Bulletin, there is no technical change
between kit D37R00 and kit D37R02.
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.
Part kit 531274D38R03
Availability
NOTE(S)
Sales terms must be agreed between the Customer and AIRBUS in accordance with
the RFC (or RFC/RMO) procedure.
Procurement address  
NOTE(S)
The AIRBUS material is included in the commercial offer and as such will be supplied
by AIRBUS Upgrade Services. T o facilitate the material reception, Airline Customers
are requested to contact:
AIRBUS Upgrade Services
Attn. Sales Manager
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
102 DAN155A38 3 (m) FOIL (1)
103 DAN155A64 3 (m) FOIL (1)
104 DAN155A79 3 (m) FOIL (1)
105 D5337625021400 1 FILLER
106 D5337625021500 1 FILLER
107 D5337625000400 1 FILLER
108 D5337625000500 1 FILLER
113 D5337625021800 1 FILLER

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ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
114 D5337625021900 1 FILLER
119 D5337625020400 1 FILLER
120 D5337625020500 1 FILLER
124 EN6101AD4-13 54 RIVET
125 DAN6-6-10 6 PIN
126 NSA5075-6 6 COLLAR
161 D5337625120000 1 FILLER
162 D5337625120100 1 FILLER
165 DAN155A317 2.500 (m) FOIL (2)
NOTE(S)
Kit D38R01 is still applicable in this Service Bulletin, there is no technical change
between kit D38R01 and kit D38R03.
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.
(1): Select correct foil thickness and cut to length during assembly.
(2): Cut to length during assembly.
CONF 004 005
Part kit 531274D39R02
Availability
NOTE(S)
Sales terms must be agreed between the Customer and AIRBUS in accordance with
the RFC (or RFC/RMO) procedure.
Procurement address  
NOTE(S)
The AIRBUS material is included in the commercial offer and as such will be supplied
by AIRBUS Upgrade Services. T o facilitate the material reception, Airline Customers
are requested to contact:
AIRBUS Upgrade Services
Attn. Sales Manager
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
99 D5337625020800 4 FILLER
100 D5337625021000 2 FILLER
101 D5337625021200 2 FILLER
102 DAN155A38 6 (m) FOIL (1)
103 DAN155A64 6 (m) FOIL (1)
104 DAN155A79 6 (m) FOIL (1)
105 D5337625021400 2 FILLER
106 D5337625021500 2 FILLER
107 D5337625000400 2 FILLER
108 D5337625000500 2 FILLER

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ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
109 D5337625021600 1 FILLER
110 D5337625021700 1 FILLER
111 D5337625000800 1 FILLER
112 D5337625000900 1 FILLER
113 D5337625021800 1 FILLER
114 D5337625021900 1 FILLER
115 D5337625020200 1 FILLER
116 D5337625020300 1 FILLER
117 D5337625020000 1 FILLER
118 D5337625020100 1 FILLER
119 D5337625020400 1 FILLER
120 D5337625020500 1 FILLER
121 D5337625020600 1 FILLER
122 D5337625020700 1 FILLER
124 EN6101AD4-13 110 RIVET
125 DAN6-6-10 14 PIN
126 NSA5075-6 14 COLLAR
NOTE(S)
Kit D39R00 is still applicable in this Service Bulletin, there is no technical change
between kit D39R00 and kit D39R02.
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.
(1): Select correct foil thickness and cut to length during assembly.
CONF 004
Part kit 531274D40R02
Availability
NOTE(S)
Sales terms must be agreed between the Customer and AIRBUS in accordance with
the RFC (or RFC/RMO) procedure.
Procurement address  
NOTE(S)
The AIRBUS material is included in the commercial offer and as such will be supplied
by AIRBUS Upgrade Services. T o facilitate the material reception, Airline Customers
are requested to contact:
AIRBUS Upgrade Services
Attn. Sales Manager
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
2 EN6114K3A9 6 BOLT
4 EN6114K3A13 6 BOLT
5 ASNA2528-3A 162 NUT

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ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
11 EN6114K3A6 66 BOLT
12 EN6114K3A8 64 BOLT
35 EN6114K3A10 20 BOLT
NOTE(S)
Kit D40R00 is still applicable in this Service Bulletin, there is no technical change
between kit D40R00 and kit D40R02.
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.
Part kit 531274D41R06
Availability
NOTE(S)
Sales terms must be agreed between the Customer and AIRBUS in accordance with
the RFC (or RFC/RMO) procedure.
Procurement address  
NOTE(S)
The AIRBUS material is included in the commercial offer and as such will be supplied
by AIRBUS Upgrade Services. T o facilitate the material reception, Airline Customers
are requested to contact:
AIRBUS Upgrade Services
Attn. Sales Manager
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
17 DAN6-5-4 128 PIN
18 NSA5075-5 258 COLLAR
19 NSA5076-5 36 COLLAR
20 DAN6-5-5 158 PIN
21 DAN6-5-6 8 PIN
22 ABS0213-6-10R 8 RIVET
23 ABS0213-6-9R 16 RIVET
24 ABS1155-7WA9 14 RIVET
25 ABS1155-7WA8 32 RIVET
26 ABS1155-7WA6 28 RIVET
27 D5337034423000 1 ANGLE
28 D5337034423100 1 ANGLE
29 D5337034422800 2 ANGLE
30 D5337034422900 2 ANGLE
31 D5337034423200 1 ANGLE
32 D5337034423300 1 ANGLE
33 D5337034423400 1 ANGLE
34 D5337034423500 1 ANGLE
36 D5337034424400 1 ANGLE

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ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
37 D5337034424500 1 ANGLE
40 D5337034424800 1 ANGLE
41 D5337034424900 1 ANGLE
42 D5337034425100 2 ANGLE
43 D5337034425000 2 ANGLE
44 D5337034425200 1 ANGLE
45 D5337034425300 1 ANGLE
48 D5337034425400 1 ANGLE
49 D5337034425500 1 ANGLE
50 D5337034425600 1 ANGLE
51 D5337034425700 1 ANGLE
171 D5337034422200 1 ANGLE
172 D5337034422300 1 ANGLE
173 D5337034422400 1 ANGLE
174 D5337034422500 1 ANGLE
175 D5337034422600 1 ANGLE
176 D5337034422700 1 ANGLE
NOTE(S)
Kit D41R05 is still applicable in this Service Bulletin, there is no technical change
between kit D41R05 and kit D41R06.
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.
Part kit 531274D42R01
Availability
NOTE(S)
Sales terms must be agreed between the Customer and AIRBUS in accordance with
the RFC (or RFC/RMO) procedure.
Procurement address  
NOTE(S)
The AIRBUS material is included in the commercial offer and as such will be supplied
by AIRBUS Upgrade Services. T o facilitate the material reception, Airline Customers
are requested to contact:
AIRBUS Upgrade Services
Attn. Sales Manager
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
5 ASNA2528-3A 152 NUT
53 DAN11-6X 60 COLLAR
177 DAN6-6-7X 56 PIN
178 DAN6-6-6X 6 PIN
179 DAN6-6-8X 14 PIN

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ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
180 NSA5076-6 16 COLLAR
181 EN6114K3AX8 12 BOLT
182 EN6114K3AX9 34 BOLT
183 EN6114K3AX10 2 BOLT
184 EN6114K3AX11 48 BOLT
185 EN6114K3AX12 8 BOLT
186 EN6114K3AX13 28 BOLT
187 EN6114K3AX14 2 BOLT
188 EN6114K3AX16 18 BOLT
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.
CONF 005
Part kit 531274D43R00
Availability
NOTE(S)
Sales terms must be agreed between the Customer and AIRBUS in accordance with
the RFC (or RFC/RMO) procedure.
Procurement address  
NOTE(S)
The AIRBUS material is included in the commercial offer and as such will be supplied
by AIRBUS Upgrade Services. T o facilitate the material reception, Airline Customers
are requested to contact:
AIRBUS Upgrade Services
Attn. Sales Manager
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
1 EN6114K3A7 66 BOLT
2 EN6114K3A9 70 BOLT
3 EN6114K3A11 20 BOLT
4 EN6114K3A13 6 BOLT
5 ASNA2528-3A 162 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.
Part kit 531274D44R00
Availability
NOTE(S)
Sales terms must be agreed between the Customer and AIRBUS in accordance with
the RFC (or RFC/RMO) procedure.

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Procurement address  
NOTE(S)
The AIRBUS material is included in the commercial offer and as such will be supplied
by AIRBUS Upgrade Services. T o facilitate the material reception, Airline Customers
are requested to contact:
AIRBUS Upgrade Services
Attn. Sales Manager
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
17 DAN6-5-4 128 PIN
18 NSA5075-5 258 COLLAR
19 NSA5076-5 36 COLLAR
20 DAN6-5-5 158 PIN
21 DAN6-5-6 8 PIN
22 ABS0213-6-10R 12 RIVET
23 ABS0213-6-9R 18 RIVET
24 ABS1155-7WA9 24 RIVET
25 ABS1155-7WA8 32 RIVET
26 ABS1155-7WA6 28 RIVET
27 D5337034423000 1 ANGLE
28 D5337034423100 1 ANGLE
29 D5337034422800 2 ANGLE
30 D5337034422900 2 ANGLE
31 D5337034423200 1 ANGLE
32 D5337034423300 1 ANGLE
33 D5337034423400 1 ANGLE
34 D5337034423500 1 ANGLE
171 D5337034422200 1 ANGLE
172 D5337034422300 1 ANGLE
173 D5337034422400 1 ANGLE
174 D5337034422500 1 ANGLE
175 D5337034422600 1 ANGLE
176 D5337034422700 1 ANGLE
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.
CONF ALL
E. LIST OF EXISTING PARTS
No parts

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REV 06 Jul 22/19 Page 50
3. ACCOMPLISHMENT INSTRUCTIONS
Task set A320-A-53-XX-1274-01000-93AA-A
Modification
WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS
INCLUDED IN THE REFERENCED PROCEDURES.
CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL
WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY
SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR
MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND
THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS:
- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC., AS
NECESSARY ON WIRING AND COMPONENTS.
- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND
OTHER CONTAMINATION.
THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND
DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.
IF THERE IS CONTAMINATION, REFER TO 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: 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 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.
A. TASK SET ASSOCIATED INFORMATION
Task Manpower
CONF 001
TOTAL MAN-HOURS 42.00 h
CONF 002
TOTAL MAN-HOURS 102.00 h

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CONF 003
TOTAL MAN-HOURS 52.00 h
CONF 004
TOTAL MAN-HOURS 102.00 h
CONF 005
TOTAL MAN-HOURS 102.00 h
CONF 001
ELAPSED TIME (HOURS) 12.00 h
CONF 002
ELAPSED TIME (HOURS) 27.00 h
CONF 003
ELAPSED TIME (HOURS) 27.00 h
CONF 004
ELAPSED TIME (HOURS) 27.00 h
CONF 005
ELAPSED TIME (HOURS) 27.00 h
CONF ALL
B. PREPARATION
CONF 001 002 004 005
(1) Task A320-A-53-XX-1274-01001-540A-A - Job Set-up
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
833
834
843
844
Manpower/Resources/Skills
Man-hours 1.00 h
Minimum Number of person 1
Elapsed Time 1.00 h
Referenced Information
Manuals/Drawings References/Sheets
AMM
T ask 12-34-24-869-002
T ask 25-23-47-000-002
T ask 52-21-11-000-001
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 upper sidewall-panels ( Panel 241CW, Panel 241LW, Panel 242CW
and Panel 242LW), refer to Ref. AMM T ask 25-23-47-000-002.

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(c) Remove the emergency exit hatches, refer to Ref. AMM T ask 52-21-11-000-001.
CONF 003
(1) Task A320-A-53-XX-1274-01002-540A-A - Job Set-up
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
834
844
Manpower/Resources/Skills
Man-hours 1.00 h
Minimum Number of person 1
Elapsed Time 1.00 h
Referenced Information
Manuals/Drawings References/Sheets
AMM
T ask 12-34-24-869-002
T ask 25-23-47-000-002
T ask 52-21-11-000-001
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 upper sidewall-panels ( Panel 241FW and Panel 242FW), refer to Ref.
AMM T ask 25-23-47-000-002.
(c) Remove the emergency exit hatches, refer to Ref. AMM T ask 52-21-11-000-001.
CONF ALL
C. PROCEDURE
CONF 001 002
(1) Task A320-A-53-XX-1274-01001-520A-A - Remove the Fillers and Shims at the
LH Overwing Emergency-Exits
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
833 Access Door 831Panel 241CW
834 Access Panel 241LW
Manpower/Resources/Skills
Man-hours 4.00 h
Minimum Number of person 2
Elapsed Time 2.00 h

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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
(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 existing fillers and shims from the LH overwing emergency-exit Door
833.
Refer to Ref. Fig. Removal and Installation of the Fillers and Shims.
1 Remove as shown in view A and B and section A-A:
2 FILLER D5337043500200 Item (30) Discard
1 FILLER D5337043620000 Item (32) Discard
1 FILLER D5337043700000 Item (34) Discard
and their fasteners.
2 Remove as shown in view A thru C and section C-C and F-F:
1 FILLER D5337044300000 Item (44) Discard
1 FILLER D5337044520000 Item (81) Discard
and their fasteners.
3 Remove as shown in view A and C and section B-B:
1 FILLER D5337043920400 Item (51) Discard
1 FILLER D5337043920600 Item (53) Discard
1 FILLER D5337044000200 Item (36) Discard

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1 FILLER D5337044120000 Item (38) Discard
and their fasteners.
4 Remove as shown in view A thru C and section D-D and E-E:
1 FILLER D5337044300400 Item (45) Discard
1 FILLER D5337044520200 Item (80) Discard
and their fasteners.
5 Remove as shown in view A and B and section C-C:
1 SHIM D5337044424600 Item (48) Discard
1 SHIM D5337044424400 Item (49) Discard
1 SHIM D5337044424200 Item (50) Discard
1 SHIM D5337044422200 Item (54) Discard
1 SHIM D5337044422000 Item (55) Discard
1 SHIM D5337044421800 Item (56) Discard
and their fasteners.
6 Remove as shown in view A, C and section F-F:
1 SHIM D5337044422800 Item (57) Discard
1 SHIM D5337044422600 Item (58) Discard
1 SHIM D5337044422400 Item (59) Discard
and their fasteners.
7 Remove as shown in view A and B and section D-D:
1 SHIM D5337044420400 Item (60) Discard
1 SHIM D5337044420200 Item (61) Discard
1 SHIM D5337044420000 Item (62) Discard
and their fasteners.
8 Remove as shown in view A and C and section E-E:
1 SHIM D5337044424000 Item (63) Discard
1 SHIM D5337044423800 Item (64) Discard
1 SHIM D5337044423600 Item (65) Discard
and their fasteners.
(c) Remove the fasteners for the installation of the reinforcement angles, as shown
in Ref. Fig. Removal and Installation of the Fillers and Shims, view B and C.
(d) Remove the existing fillers and shims from the LH overwing emergency-exit Door
834.
Refer to Ref. Fig. Removal and Installation of the Fillers and Shims.
1 Remove as shown in view A and G and section P-P:
2 FILLER D5337043500200 Item (30) Discard
1 FILLER D5337043620000 Item (32) Discard

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1 FILLER D5337043700000 Item (34) Discard
and their fasteners.
2 Remove as shown in view A, G, H and J and section V-V:
1 FILLER D5337044300600 Item (46) Discard
1 FILLER D5337044520400 Item (79) Discard
and their fasteners.
3 Remove as shown in view A and H and section Q-Q:
1 FILLER D5337044220000 Item (40) Discard
1 FILLER D5337043920200 Item (42) Discard
and their fasteners.
4 Remove as shown in view A , G and H and section R-R and T-T:
1 FILLER D5337044300200 Item (47) Discard
1 FILLER D5337044520600 Item (78) Discard
and their fasteners.
5 Remove as shown in view A, G and J:
1 SHIM D5337044424600 Item (48) Discard
1 SHIM D5337044424400 Item (49) Discard
1 SHIM D5337044424200 Item (50) Discard
and their fasteners.
6 Remove as shown in view A and G and section S-S:
1 SHIM D5337044422200 Item (54) Discard
1 SHIM D5337044422000 Item (55) Discard
1 SHIM D5337044421800 Item (56) Discard
and their fasteners.
7 Remove as shown in view A and H and section V-V:
1 SHIM D5337044424000 Item (63) Discard
1 SHIM D5337044423800 Item (64) Discard
1 SHIM D5337044423600 Item (65) Discard
and their fasteners.
8 Remove as shown in view A and G and section R-R:
1 SHIM D5337044421600 Item (66) Discard
1 SHIM D5337044421400 Item (67) Discard
1 SHIM D5337044421200 Item (68) Discard
and their fasteners.
9 Remove as shown in view A and H and section T-T:
1 SHIM D5337044423400 Item (69) Discard
1 SHIM D5337044423200 Item (70) Discard

### Page 56

A318/A319/A320/A321
SERVICE BULLETIN
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19 Page 56
1 SHIM D5337044423000 Item (71) Discard
and their fasteners.
10 Remove as shown in view A and H and section U-U:
1 SHIM D5337044425200 Item (72) Discard
1 SHIM D5337044425000 Item (73) Discard
1 SHIM D5337044424800 Item (74) Discard
and their fasteners.
11 Remove as shown in view A, G and J:
1 SHIM D5337044421000 Item (75) Discard
1 SHIM D5337044420800 Item (76) Discard
1 SHIM D5337044420600 Item (77) Discard
and their fasteners.
(e) Remove the fasteners for the installation of the reinforcement angles, as shown
in Ref. Fig. Removal and Installation of the Fillers and Shims, view G and H.
(f) Remove the old sealant with a non-metallic spatula and clean the work area
with:
  Non Aqueous Cleaner-
General
08BAA9  
  T extile-Lint free-Cotton 14SBA1  
(g) Make sure that the heads of the existing rivets are not more than 1.8 mm (0.071
in.) above the surrounding structure in the areas where you have removed the
fillers and the shims.

### Page 57

A318/A319/A320/A321
SERVICE BULLETIN
Figure ICN-A320-A-53XX1274-A-FAPE3-00PK4-A-001-01 SHEET 1/12
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19
Removal and Installation of the Fillers and Shims
Page 57
CONF 001 002
FR37
FR38
FR39
FR40
FR41
FR42
STGR13LH
STGR15LH
STGR18LH
STGR20LH
STGR13RH
STGR15RH
STGR18RH
STGR20RH
Z834
Z833
Z843
Z844
Z240
A
A
B
C
B
C G
H
G
H
ICN-A320-A-53XX1274-A-FAPE3-00PK4-A-001-01

### Page 58

A318/A319/A320/A321
SERVICE BULLETIN
Figure ICN-A320-A-53XX1274-A-FAPE3-00PK5-A-001-01 SHEET 2/12
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19
Removal and Installation of the Fillers and Shims
Page 58
CONF 001 002
BEFORE
FD
STGR13
STGR18
STGR14
WINDOW
CENTER
FR39 FR38
STGR19
STGR20
STGR20A
BEFORE
FR38FR39
FWD
LH SHOWN
RH SYMMETRICAL
C
A A
E
(45)
(80)
(44)
(81)
(45)
(80)
(44)
(81)
DD
F F
BB
EE
C
C
(30)
(31)
(30)
LH
RH
LH
(31)
(32)
RH
LH
(33) RH
(34)
(35)
LH
RH
(36)
(37)
(38)
LH
RH
LH
(39) RH
(51)
(52)
(53)
LH
RH
D F
FWD
LH SHOWN
RH SYMMETRICAL
B
FASTENERS TO BE REMOVED
FASTENERS TO REMAIN IN PLACE
FASTENER TABLE
STGR15
FASTENERS TO BE REMOVED FOR THE
INSTALLATION OF REINFORCED ANGLES
ICN-A320-A-53XX1274-A-FAPE3-00PK5-A-001-01

### Page 59

A318/A319/A320/A321
SERVICE BULLETIN
Figure ICN-A320-A-53XX1274-A-FAPE3-00PK6-A-001-01 SHEET 3/12
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19
Removal and Installation of the Fillers and Shims
Page 59
CONF 001 002
STGR13
STGR14
C C
A A
B B
FR39 FR38FR39
FR39
FR39
FR38
FR38
VIEW LOOKING FWD
(44)
(53)
(60)
(61)
(62)
(45)
(63)
(64)
(65)
(80)
(57)
(58)
(59)
(81)
D D E E F F
(54)
(55)
(56)
(48)
(49)
(50)
(30) LH
(31) RH
(32) LH
(33) RH
(38) LH
(39) RH
(51) LH
(52) RH
(34) LH
(35) RH
(36) LH
(37) RH
ON FR38
ICN-A320-A-53XX1274-A-FAPE3-00PK6-A-001-01

### Page 60

A318/A319/A320/A321
SERVICE BULLETIN
Figure ICN-A320-A-53XX1274-A-FAPE3-00PK7-A-001-01 SHEET 4/12
REV 00 Jul 15/14 A320-53-1274
REV 06 Jul 22/19
Removal and Installation of the Fillers and Shims
Page 60
CONF 001 002
07
AFTER
FD
STGR13
STGR18
1.5 mm
(0.059 in)
2.0 mm ± 0.5 mm
(0.078 in ± 0.019 in)
2.0 mm ± 0.5 mm
(0.078 in ± 0.019 in)
2.0 mm
(0.078 in)
2.0 mm
(0.078 in)
2.5 mm
(0.098 in)
STGR14
WINDOW
CENTER
FR39 FR38
STGR19
STGR20
STGR20A
AFTER
1.5 mm ± 0.5 mm
(0.059 in ± 0.019 in)
2.0 mm
(0.078 in)
2.0 mm
2.5 mm
(0.098 in)
2.0 mm
(0.078 in)
2.0 mm ± 0.5 mm
(0.078 in ± 0.019 in)
FR38
0607
07
07
06
060505
(0.078 in)
FR39
FWD
LH SHOWN
RH SYMMETRICAL
FWD
LH SHOWN
RH SYMMETRICAL
D E
NOTE:
SEE SHEET 12 FOR NOTES AND FASTENER TABLE.
2.0 mm
(0.078 in)
L L
N
N
07
M
M
G
G
H H
J J
K
K
07
08
08
09
09
09
105 LH
106 RH
115 LH
116 RH
117LH
118RH
09 107LH 108RH
09115 LH116 RH
09109 LH110 RH 09 111LH 112RH
09 117LH 118RH
R R
S
T
08
ICN-A320-A-53XX1274-A-FAPE3-00PK7-A-001-01

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