@A318/A319/A320/A321

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 53

TITLE: FUSELAGE - CENTER FUSELAGE - REINFORCE FORWARD

PRESSURE BULKHEAD AT FRAME COUPLING C35 LH/RH

MODIFICATION No.: 153832K16057

This page transmits Revision No.03 of Service Bulletin No.A320-53-1268

ADDITIONAL WORK

**CONF ALL

No additional work is required by this revision for aircraft modified by any previous issue.

REASON

Revision No. 03 issued to add aircraft with Manufacturer Serial Number (MSN) 0202, 0209, 0216, 0267,

0268, 0269, 0382 and 0346 to the effectivity of this Service Bulletin.

CHANGES

The main changes of this revision are:

- The SB compliance has been updated to MANDATORY

- The SB effectivity has been updated

- The REFERENCES/REPERCUSSIONS section has been updated

- The REFERENCES section has been updated

- The ALS has been added in PUBLICATION AFFECTED section.

SUMMARY

GENERAL EVALUATION GENERAL EVALUATION TABLE UPDATED R

REFERENCES / REPERCUSSIONS REFERENCES/REPERCUSSIONS TABLE

UPDATED

R

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 1

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Configuration definition

CONF 001 CONFIGURATION DEFINITION UPDATED R

COMPLIANCE

Classification CLASSIFICATION UPDATED R

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R

REFERENCES REFERENCED DOCUMENTATION UPDATED R

PUBLICATION AFFECTED PUBLICATIONS AFFECTED UPDATED R

PUBLICATIONS AFFECTED ADDED N

ACCOMPLISHMENT INSTRUCTIONS

TASK 531268- 831-849-001-Modification

Subtask 531268-831-005-001 SUBTASK SOLUTION UPDATED

NOTE UPDATED

R

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.

HISTORY OF PREVIOUS REVISIONS

Revision No. 01 issued to:

extend the effectivity of this Service Bulletin to include the A319 model and additional A320 aircraft

incorporate changes found necessary and carried out during the accomplishment of this Service Bulletin

on aircraft with Manufacturer Serial Number (MSN) 0401.

Revision No. 02 issued to:

add aircraft for operators DLH and GWI

remove UAL aircraft from the SB applicability due to the Extended Service Goal (ESG) flexibility which

postpones the structure reinforcement requirement from 60000 Flight Hours (FH) up to 96000 FH,

without exceeding 48000 Flight Cycles (FC).

REVISION SEQUENCE

ORIGINAL: Jan 08/13

REVISION No. : 01 - Jul 23/13

REVISION No. : 02 - Jul 15/14

REVISION No. : 03 - May 07/15

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 2

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

This summary is for information only and is not approved for modification of the aircraft.

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 53

TITLE: FUSELAGE - CENTER FUSELAGE - REINFORCE FORWARD

PRESSURE BULKHEAD AT FRAME COUPLING C35 LH/RH

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR None

MINOR 153832K16057

NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the

mass, balance, structural strength, reliability, operational characteristics affecting the

airworthiness of the product. All other changes are major changes.

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During A320 fatigue testing, damage was found in the area of the pressure bulkhead at Frame 35.

Accomplishment of this Service Bulletin will cold expand tooling holes and fastener holes at Frame 35

between STGR28 and STGR31 LH and RH.

Accomplishment of this Service Bulletin will contribute to the continued structural integrity in the

modification area up to the Extended Service Goal.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO

VALIDATION ON AIRCRAFT YES BOOKLET AVAILABLE YES

NOTE (1): Service Bulletin must be accomplished.

NOTE: This Service Bulletin has been validated at original issue on A320 aircraft with

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 1

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

SUMMARY

Manufacturer Serial Number (MSN) 0401.

Aircraft with Manufacturer Serial Number (MSN) 0401 complies fully with the

requirements of the current issue of the Service Bulletin.

NOTE: A booklet including photographs taken during the validation of this Service Bulletin is

available on AIRBUS|World - Maintenance and Engineering - AirN@v engineering (in

the concerned SB file).

MATERIAL PRICE INFORMATION

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 531268D01R00 1 See SB Fasteners

Kit 531268A01R00 1 See SB Fasteners

Standard tool TOOLA01 1 See SB FTI tools

Standard tool TOOLD01 1 See SB FTI tools

EFFECTIVITY

This Service Bulletin is applicable to this (these) operator(s) :

DLH GWI

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

CUSTOMER SERVICES DIRECTORATE

SC Department

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL 51-012

LINE MAINTENANCE AFFECTED No

LIFE LIMIT YES

OTHER None

NOTE: SIL 51-012 has been migrated into ISI article 51.48.00001.

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 2

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

SUMMARY

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

Task 531268-831-849-001: Modification

TOTAL MANHOURS 21.00

ELAPSED TIME (HOURS) 15.50

APPENDICES

APPENDIX 01: Elapsed Time Assumption

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 3

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

SUMMARY

**CONF ALL

STGR30LH

STGR29LH

FR35

825

Z130

A

LH SIDE SHOWN

RH SIDE SYMMETRICAL

A

COLD EXPANSION OF THE FASTENER HOLES

N_SB_531268_6_SBAA_01_00

Figure A-GSBAA - Sheet 01

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 4

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

SUMMARY

**CONF ALL

A

Z240

FR35

FR42

A

STGR28

STGR29

STGR30

STGR31

Y1282.0

Z140

FR35

B

B

LH SHOWN, RH SIMILAR

B

VIEW LOOKING FWD

TOOLING HOLE TO

BE COLD EXPANDED

RIVET HOLES TO BE

COLD EXPANDED

HOLE TO BE

COLD EXPANDED

RIVET HOLES TO BE

COLD EXPANDED

RIVET HOLES TO BE

COLD EXPANDED

TOOLING

N_SB_531268_6_SAAA_01_01

Figure A-GSAAA - Sheet 01

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 5

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

SUMMARY

This Page Intentionally Left Blank

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 6

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 53

TITLE: FUSELAGE - CENTER FUSELAGE - REINFORCE FORWARD

PRESSURE BULKHEAD AT FRAME COUPLING C35 LH/RH

MODIFICATION No.: 153832K16057

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the

property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with

any information contained in it. It is delivered on the express condition that said document and the

information contained in it shall be treated as confidential, shall not be used for any purpose other than

that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall

not be duplicated in any manner (except for the purposes of performing the tasks described hereunder

and provided that any recipient of such document shall comply with the conditions herein), without

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

This modification is applicable by Service Bulletin only.

(1) Models

320-211

(2) Effectivity by MSN

0069-0072 0078 0083 0086 0093-0094 0104 0110-0111 0116-0117 0135 0137

0161-0162 0172 0200-0202 0209 0216-0218 0267-0269 0346 0382 0401

(3) Effectivity by Operator

The Operator/MSN relationship is provided for information only and is correct at the time

of issue in accordance with the information available to AIRBUS. Any future changes

resulting from transfer of an aircraft from one operator to another will not be reflected in

this list unless the Service Bulletin is revised for another reason.

OPERATOR MSN

DLH 0069 0070 0071 0072 0078 0083 0086 0093 0094 0104 0110 0111

0116 0172 0346

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 1

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

OPERATOR MSN

GWI 0117 0135 0137 0161 0162 0200 0201 0202 0209 0216 0217 0218

0267 0268 0269 0382 0401

(4) Configuration by MSN

MSN CONFIGURATION

0069 0070 0071 0072 0078 0083 0086 0093 0094 0104 0110

0111 0116 0117 0135 0137 0161 0162 0172 0200 0201 0202

0209 0216 0217 0218 0267 0268 0269 0346 0382 0401

001

(5) Configuration definition

**CONF 001

Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a

standard configuration.

(6) Material Effectivity

MATERIAL QTY PER A/C SEE NOTES

Kit 531268D01R00 1

Kit 531268A01R00 1

Standard tool TOOLA01 1

Standard tool TOOLD01 1

Consumable CMLA01 1

Consumable CMLD01 1

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During A320 fatigue testing, damage was found in the area of the pressure bulkhead at

Frame 35.

(2) Objective/Action

Accomplishment of this Service Bulletin will cold expand tooling holes and fastener holes

at Frame 35 between STGR28 and STGR31 LH and RH.

(3) Advantages

Accomplishment of this Service Bulletin will contribute to the continued structural integrity

in the modification area up to the Extended Service Goal.

(4) Operational/Maintenance Consequences

None

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 2

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 531268-831-849-001: Modification

(1) Remove the 18 fasteners at FR35, STGR30, LH and RH sides

(2) Do a Non Destructive Testing (NDT) on the 18 fastener holes at FR35, STGR30, LH

and RH sides

(3) Do the cold expansion and ream the 18 holes at FR35, STGR30, LH and RH sides

(4) Install the 18 fasteners at FR35, STGR30, LH and RH sides

(5) Apply the surface protection to the 18 fasteners at FR35, STGR30, LH and RH sides

(6) Remove the Fasteners at FR35, between STGR28 and STGR31, LH and RH

(7) Do a Non Destructive Test (NDT) on the Fastener and Tooling Holes

(8) Do the Cold Expansion and Ream the Holes at FR35, between STGR28 and

STGR31, LH and RH

(9) Install the Fasteners at FR35, between STGR28 and STGR31, LH and RH

(10) Apply the Surface Protection at FR35, between STGR28 and STGR31, LH and RH

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

Accomplishment of this Service Bulletin is required at or before 48000 FC or 96000 FH,

whichever occurs first.

This Service Bulletin has been classified Mandatory by the issue of an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must

be used as the reference document for the mandated accomplishment timescale.

F. APPROVAL

The technical content of this document is approved under the authority of Design

Organisation Approval No. EASA.21J.031.

If an aircraft listed in the effectivity has a modification or repair embodied that is not of

AIRBUS origin, and which affects the content of this Service Bulletin, the operator is

responsible for obtaining approval by its airworthiness authority for any adaptation necessary

before incorporation of the Service Bulletin.

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 3

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

G. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labor cost to

do the work. These estimates assume that the work will be done by experienced personnel,

and may need to be revised upwards to suit operator’s circumstances. The estimates do not

include the time to prepare, plan or inspect the work. Manufacture and procurement of parts

and tools, drying times for paints, sealants, etc., and general administration work are also not

included.

Task 531268-831-849-001: Modification

Get Access 5.00

On Aircraft

Remove the 18 fasteners at FR35, STGR30, LH and

RH sides

0.50

Do a Non Destructive Testing (NDT) on the 18 fastener

holes at FR35, STGR30, LH and RH sides

0.50

Do the cold expansion and ream the 18 holes at FR35,

STGR30, LH and RH sides

2.00

Install the 18 fasteners at FR35, STGR30, LH and RH

sides

0.75

Apply the surface protection to the 18 fasteners at

FR35, STGR30, LH and RH sides

0.25

Remove the Fasteners at FR35, between STGR28 and

STGR31, LH and RH

0.50

Do a Non Destructive Test (NDT) on the Fastener and

Tooling Holes

0.50

Do the Cold Expansion and Ream the Holes at FR35,

between STGR28 and STGR31, LH and RH

2.50

Install the Fasteners at FR35, between STGR28 and

STGR31, LH and RH

1.00

Apply the Surface Protection at FR35, between

STGR28 and STGR31, LH and RH

0.50

Tests 1.00

Close-Up 6.00

TOTAL MANHOURS 21.00

ELAPSED TIME (HOURS) 15.50

NOTE: For an explanation of the manhours and elapsed time, refer to the Gantt

Chart, Fig. A-GAAAA given in APPENDIX 01: Elapsed Time Assumption

H. WEIGHT AND BALANCE

The weight and balance estimates given in this Service Bulletin are based on the

Manufacturer’s Empty Weight (MEW) and do not include operator items. For the definition of

MEW and operator’s items refer to the Weight and Balance Manual (WBM) Chapter 1-00-07.

Manufacturers Empty Weight +0.029 KG (+0.064 LB)

Effect on Balance +0.452 KGM (+3.269 LB.FT )

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 4

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-20-00 06-30-00 06-31-53

06-41-53 12-34-24 20-21-11

21-21-41 25-54-12 25-80-00

38-11-41 52-30-00 53-35-11

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-00 20-55-00

Non Destructive Test Manual (NTM) 51-10-01

Service Information Letter (SIL) SIL 51-012

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-12 51-42-00 51-44-00

51-48-00 51-75-12

Weight and Balance Manual (WBM) Chapter 1-00-07

NOTE: SIL 51-012 has been migrated into ISI article 51.48.00001.

K. PUBLICATION AFFECTED

Airworthiness Limitation Section (ALS) Part 2

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 5

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 6

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

The AIRBUS material is included in the commercial offer of the Letter Agreement,

and as such will be supplied by AIRBUS Upgrade Services. To facilitate the material

reception, Airline Customers are requested to send a Customer Purchase Order to:

Kit 531268D01R00

Kit 531268A01R00

AIRBUS Upgrade Services

Attn. Key Account Manager (KAM)

(2) Price and Availability

Sales terms must be agreed between the Customer and AIRBUS in accordance with the

RFC (or RFC/RMO) procedure.

B. INDUSTRY SUPPORT INFORMATION

Industry Support terms must be agreed between the Customer and AIRBUS in accordance

with the RFC (or RFC/RMO) procedure.

C. LIST OF COMPONENTS

Kit 531268A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

2 EN6115K3A7 2 BOLT

4 EN6115K3A8 2 BOLT

6 EN6115K3A10 10 BOLT

8 EN6115K3A12 4 BOLT

10 ASNA2536-3A 18 NUT

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 531268D01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

14 EN6115K3A4 10 BOLT (12) DAN5-6-4

15 EN6115K3A3 8 BOLT (11) EN6081D6-03

16 ASNA2536-3A 18 NUT (13) NSA5075-6

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 7

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

Solvent General Purpose 11-026 As required

Corrosion Preventive Compound,

Temporary

15-009 As required

Polyurethane Top Coat (Grey) 16-002 As required

Anti Corrosion Primer Epoxy 16-006 As required

Lint-Free Cotton Cloth 19-003 As required

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

Solvent General Purpose 11-026 As required

Corrosion Preventive Compound,

Temporary

15-009 As required

Anti-Corrosion Primer

(Polyurethane)

16-001 As required

Polyurethane Top Coat (Grey) 16-002 As required

Lint-Free Cotton Cloth 19-003 As required

(2) Components

None

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 8

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

F. TOOLING

(1) Tooling - Price and Availability

(a) Procurement Addresses

Operators interested in obtaining the FTI tool kits should contact:

Standard tool TOOLA01

Standard tool TOOLD01

401 Andover Park

East SEATTLE

WA 98188-7605

USA

Internet: www.fatiguetech.com

Phone: (206) 2462010 Fax: (206) 2449886

(b) Price and Availability

None

(2) Tools

To accomplish this Service Bulletin it is necessary to use these tools and equipment:

- Equipment and materials to do a check of fastener holes as per NTM Task

51-10-01-250-801.

NOTE: FTI has allocated the following tool kit numbers for cold expansion. For

the definition of the capital, durable and expendable tools, refer to SIL

51-012.

Standard tool TOOLA01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

DKA320531268-1 Durable tooling 1 (1)

EKA320531268-1 Expendable tooling 1 (2)

FTIA320531268-1 Capital tooling 1 (3)

NOTE (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 SIL

51-012.

NOTE (2): 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.

NOTE (3): The capital tools provided in this kit are not specific to this Service

Bulletin and are normally already available in operator’s stock as a long

term investment or can be loaned from FTI.

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 9

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

Standard tool TOOLD01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

DKA320531268-1 Durable tooling 1 (1)

EKA320531268-1 Expendable tooling 1 (2)

FTIA320531268-1 Capital tooling 1 (3)

NOTE: The operator should make sure that Tool PN LBRA-7 has been delivered

with the FTI tool DKA320531268-1.

NOTE (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 SIL

51-012.

NOTE (2): 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.

NOTE (3): The capital tools provided in this kit are not specific to this Service

Bulletin and are normally already available in operator’s stock as a long

term investment or can be loaned from FTI.

(3) Special Tools

None

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 10

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 531268-831-849-001 - Modification

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS:

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00.

NOTE: The accomplishment instructions of this Service Bulletin include procedures given

in other documents or in other sections of the Service Bulletin. When the words

"refer to" are used and the operator has a procedure accepted by the local

authority he belongs to, the accepted alternative procedure can be used. When the

words "in accordance with" are used then the given procedure must be followed.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory

by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these

accomplishment instructions are Required for Compliance (RC) and must be done

to comply with the AD. Other paragraphs are recommended and may be deviated

from, done as part of other actions or done with accepted methods different from

those given in the Service Bulletin, as long as the RC paragraphs can be done and

the aircraft can be put back into a serviceable condition.

Task Associated Data

Zone

130

From 130 to 190

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 11

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

Modified FIN

4012HM 4013HM 3000MM

Access

Door 825

Panel 131PW 132PW 191BT 192BT

Manpower

TOTAL MANHOURS 21.00

ELAPSED TIME (HOURS) 15.50

A. GENERAL

NOTE: The listed subtasks are not in sequence with the work steps. The operator

can change the sequence.

(1) Subtask 531268-910-202-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-30-00, Page Block 001

06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-21-11-911-001

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-00

Structural Repair Manual (SRM) 51-23-12

51-42-00

51-44-00

51-48-00

51-75-12

(a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to

Consumable Materials List (CML).

(b) For the identification of access panels, refer to AMM 06-41-53, Page Block 001.

(c) Tag the parts that you must remove and retain to make the subsequent installation

easier.

(d) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(e) For the Stringer (STGR) identification, refer to AMM 06-30-00, Page Block 001.

(f) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(g) Remove and install fasteners in accordance with SRM 51-42-00.

(h) For the general installation of electrical wire harnesses, refer to ESPM 20-33-00.

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 12

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

(i) To torque tighten the standard threaded fasteners, refer to AMM Task

20-21-11-911-001.

(j) Cold expand the fastener holes in accordance with SRM 51-48-00.

(k) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00.

(l) Renew the protective finish in accordance with SRM 51-75-12.

(m) Renew the special protection in accordance with SRM 51-23-12.

NOTE: If the length of any fastener specified in this Service Bulletin does not

meet installation standards given in SRM Chapter 51, then a fastener of

the same specification, or an approved substitute, with a length which

meets the installation standards given in SRM Chapter 51 may be

used. In addition, washers may be installed for fastener grip length in

accordance with SRM Chapter 51.

(2) Subtask 531268-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

B. PREPARATION

(1) Subtask 531268-941-202-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002

Task 52-30-00-860-001

NOTE: The items given in this note shall be considered as the basic Aircraft

configuration before you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety

locks and the wheel chocks are in position on the landing gear)

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

- Hydraulic systems depressurized

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 13

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position.

(a) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-869-002.

(b) Put access platform(s) in position.

(c) Open the FWD cargo compartment door 825, refer to AMM Task

52-30-00-860-001.

(2) Subtask 531268-010-201-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-21-41-000-001

Task 25-54-12-000-001

Task 25-80-00-000-001

Task 38-11-41-000-001

Task 53-35-11-000-001

(a) Remove the wing-to-fuselage fairings 191BT and 192BT, refer to AMM Task

53-35-11-000-001.

(b) At FR34, remove the FWD cargo-compartment partitions 131PW, 132PW and if

necessary 131NW, refer to AMM Task 25-54-12-000-001.

(c) If necessary, remove the air conditioning recirculation filters 4012HM LH and

4013HM RH, refer to AMM Task 21-21-41-000-001.

(d) If necessary, remove the potable water tank 3000MM and ventilation ducts, refer to

AMM Task 38-11-41-000-001.

(e) Remove the heat and sound insulation blankets in the area between Frame 35 and

Frame 36 LH and RH, refer to AMM Task 25-80-00-000-001.

(f) If necessary, remove electrical bundle clamps and push bundles aside, without

disconnection to get them out of the working area.

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 14

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

C. PROCEDURE

(1) Subtask 531268-831-001-001 - Remove the 18 fasteners at FR35, STGR30, LH and

RH sides

Work Zones and Access Panels

Zone Access/Work location

From 130 Access Door 825

Panel 131PW, Panel 132PW

Work location from Frame 34 to Frame 35

Stringer 30

To 190 Access Panel 191BT, Panel 192BT

Work location from Frame 34 to Frame 35

Stringer 30

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

Lint-Free Cotton Cloth 19-003 As required

References

Structural Repair Manual (SRM) 51-42-00

Fig. A-FBAAA

Cold Expansion of the Fasteners Holes

at FR35, STGR30, LH and RH sides

Sheet 01

Sheet 02

(a) Remove the fasteners in accordance with SRM 51-42-00

1 From the LH and RH sides, remove:

18 Nut ASNA2528-3 Item (9) Discard

2 Bolt ASNA2027V3-7 Item (1) Discard

2 Bolt ASNA2027V3-8 Item (3) Discard

10 Bolt ASNA2027V3-10 Item (5) Discard

4 Bolt ASNA2027V3-12 Item (7) Discard

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 15

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

(b) Clean the work area with:

Solvent General

Purpose

11-026 As required

Lint-Free Cotton

Cloth

19-003 As required

(2) Subtask 531268-831-004-001 - Do a Non Destructive Testing (NDT) on the 18

fastener holes at FR35, STGR30, LH and RH sides

Work Zones and Access Panels

Zone Access/Work location

From 130 Access Door 825

Panel 131PW, Panel 132PW

Work location from Frame 34 to Frame 35

Stringer 30

To 190 Access Panel 191BT, Panel 192BT

Work location from Frame 34 to Frame 35

Stringer 30

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) Task 51-10-01-250-801

Fig. A-FBAAA

Cold Expansion of the Fasteners Holes

at FR35, STGR30, LH and RH sides

Sheet 01

Sheet 02

(a) Do the checks of the holes

1 Make sure that the diameter of the hole is not more than the maximum

starting hole diameter given in Fig. A-FBAAA Sheet 02.

- If the hole diameter is more than the maximum starting hole diameter,

contact AIRBUS.

- If the hole diameter is not more than the maximum starting hole diameter,

do the operation given below.

2 Do a rotating probe testing of the holes (Refer to NTM Task

51-10-01-250-801).

- If crack is found, contact AIRBUS.

- If crack is not found, do the operations given below.

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 16

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

(3) Subtask 531268-831-005-001 - Do the cold expansion and ream the 18 holes at

FR35, STGR30, LH and RH sides

Work Zones and Access Panels

Zone Access/Work location

From 130 Access Door 825

Panel 131PW, Panel 132PW

Work location from Frame 34 to Frame 35

Stringer 30

To 190 Access Panel 191BT, Panel 192BT

Work location from Frame 34 to Frame 35

Stringer 30

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

Lint-Free Cotton Cloth 19-003 As required

Standard tool TOOLA01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

DKA320531268-1 Durable tooling 1 (1)

EKA320531268-1 Expendable tooling 1 (2)

FTIA320531268-1 Capital tooling 1 (3)

NOTE (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 SIL

51-012.

NOTE (2): 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.

NOTE (3): The capital tools provided in this kit are not specific to this Service

Bulletin and are normally already available in operator’s stock as a long

term investment or can be loaned from FTI.

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 17

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-48-00

Fig. A-FBAAA

Cold Expansion of the Fasteners Holes

at FR35, STGR30, LH and RH sides

Sheet 01

Sheet 02

(a) Do the cold expansion of the holes in accordance with SRM 51-48-00

1 Oversize the holes to the starting hole diameter given in Fig. A-FBAAA Sheet

02.

Use FTI tool list No.:

DKA320531268-1 Durable tooling 1

2 Clean the drilled area with:

Solvent General

Purpose

11-026 As required

Lint-Free Cotton

Cloth

19-003 As required

3 Install the sleeves and obey the split direction given in Fig. A-FBAAA Sheet

02, View B.

4 Do the cold expansion of the holes

Use FTI tool list No.:

FTIA320531268-1 Capital tooling 1

DKA320531268-1 Durable tooling 1

EKA320531268-1 Expendable tooling 1

5 Remove the sleeves.

6 Ream the holes to the final diameter given in Fig. A-FBAAA Sheet 02.

NOTE: The final hole diameter gives an interference fit of the

fasteners between -35 μm and -85 μmm (-0.0014 in and

-0.0033 in).

7 Deburr the holes and clean the drilled areas with:

Solvent General

Purpose

11-026 As required

Lint-Free Cotton

Cloth

19-003 As required

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 18

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

(4) Subtask 531268-831-006-001 - Install the 18 fasteners at FR35, STGR30, LH and RH

sides

Work Zones and Access Panels

Zone Access/Work location

From 130 Access Door 825

Panel 131PW, Panel 132PW

Work location from Frame 34 to Frame 35

Stringer 30

To 190 Access Panel 191BT, Panel 192BT

Work location from Frame 34 to Frame 35

Stringer 30

Manpower Resources

Manhours 0.75

Minimum number of person 1

Subtask elapsed time 0.75

Skills AIRFRAME

Material necessary to do the job

Kit 531268A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 EN6115K3A7 2 BOLT

4 EN6115K3A8 2 BOLT

6 EN6115K3A10 10 BOLT

8 EN6115K3A12 4 BOLT

10 ASNA2536-3A 18 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Structural Repair Manual (SRM) 51-42-00

Fig. A-FBAAA

Cold Expansion of the Fasteners Holes

at FR35, STGR30, LH and RH sides

Sheet 01

Sheet 02

(a) On the LH and RH sides, wet install the fasteners in accordance with SRM

51-42-00

Refer to AMM Task 20-21-11-911-001

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 19

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

1 Apply:

Sealant-Brush

Consistency

09-013 As required

and install:

2 Bolt EN6115K3A7 Item 2

2 Bolt EN6115K3A8 Item 4

10 Bolt EN6115K3A10 Item 6

4 Bolt EN6115K3A12 Item 8

18 Nut ASNA2536-3A Item 10

(5) Subtask 531268-831-007-001 - Apply the surface protection to the 18 fasteners at

FR35, STGR30, LH and RH sides

Work Zones and Access Panels

Zone Access/Work location

From 130 Access Door 825

Panel 131PW, Panel 132PW

Work location from Frame 34 to Frame 35

Stringer 30

To 190 Access Panel 191BT, Panel 192BT

Work location from Frame 34 to Frame 35

Stringer 30

Manpower Resources

Manhours 0.25

Minimum number of person 1

Subtask elapsed time 0.25

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Preventive

Compound, Temporary

15-009 As required

Polyurethane Top Coat

(Grey)

16-002 As required

Anti Corrosion Primer

Epoxy

16-006 As required

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 20

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

(a) Apply to the fasteners:

Anti Corrosion

Primer Epoxy

16-006 As required

Polyurethane Top

Coat (Grey)

16-002 As required

(b) Then apply to the work areas:

Corrosion

Preventive

Compound,

Temporary

15-009 As required

(6) Subtask 531268-831-202-001 - Remove the Fasteners at FR35, between STGR28

and STGR31, LH and RH

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 825

Panel 131PW, Panel 132PW

Work location Frame 35

from Stringer 28 to Stringer 31

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

Lint-Free Cotton Cloth 19-003 As required

References

Structural Repair Manual (SRM) 51-42-00

Fig. A-GBAAA

Modify the fastener Holes at Frame 35,

between STGR28 and STGR31, LH and

RH

Sheet 01

Sheet 02

Do the steps that follow for the LH and RH side of the aircraft.

Refer to Fig. A-GBAAA Sheet 01.

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 21

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

(a) At Frame 35 between STGR28 and STGR31, remove the fasteners, in accordance

with SRM 51-42-00.

1 Remove:

8 Rivet EN6081D6-03 Item (11) Discard

10 Pin-Rivet DAN5-6-4 Item (12) Discard

10 Collar NSA5075-6 Item (13) Discard

2 Clean the work area with:

Solvent General

Purpose

11-026 As required

Lint-Free Cotton

Cloth

19-003 As required

(7) Subtask 531268-250-201-001 - Do a Non Destructive Test (NDT) on the Fastener

and Tooling Holes

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 825

Panel 131PW, Panel 132PW

Work location Frame 35

from Stringer 28 to Stringer 31

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) Task 51-10-01-250-801

Fig. A-GBAAA

Modify the fastener Holes at Frame 35,

between STGR28 and STGR31, LH and

RH

Sheet 01

Sheet 02

Do the steps that follow for the LH and RH side of the aircraft.

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 22

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

(a) At Frame 35 between STGR28 and STGR31, inspect the fastener and tooling

holes, refer to Fig. A-GBAAA Sheet 01 and Fig. A-GBAAA Sheet 02.

1 Make sure that the diameter of the holes is not more than the maximum

starting hole diameter given in Fig. A-GBAAA Sheet 02.

- If the hole diameter is more than the maximum starting hole diameter,

contact AIRBUS

- If the hole diameter is not more than the maximum starting hole diameter,

do the operation given below.

2 Do a rotating probe test of the holes in accordance with NTM Task

51-10-01-250-801.

- If cracks are found, contact AIRBUS.

- If no cracks are found, do the operations given below.

(8) Subtask 531268-831-204-001 - Do the Cold Expansion and Ream the Holes at

FR35, between STGR28 and STGR31, LH and RH

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 825

Panel 131PW, Panel 132PW

Work location Frame 35

from Stringer 28 to Stringer 31

Manpower Resources

Manhours 2.50

Minimum number of person 1

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

Lint-Free Cotton Cloth 19-003 As required

Standard tool TOOLD01

ITEM TOOL N ̊ TOOL NAME QTY SEE

NOTES

DKA320531268-1 Durable tooling 1 (1)

EKA320531268-1 Expendable tooling 1 (2)

FTIA320531268-1 Capital tooling 1 (3)

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 23

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

NOTE: The operator should make sure that Tool PN LBRA-7 has been delivered

with the FTI tool DKA320531268-1.

NOTE (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 SIL

51-012.

NOTE (2): 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.

NOTE (3): The capital tools provided in this kit are not specific to this Service

Bulletin and are normally already available in operator’s stock as a long

term investment or can be loaned from FTI.

References

Structural Repair Manual (SRM) 51-48-00

Fig. A-GBAAA

Modify the fastener Holes at Frame 35,

between STGR28 and STGR31, LH and

RH

Sheet 01

Sheet 02

Do the steps that follow for the LH and RH of the aircraft.

Refer to Fig. A-GBAAA Sheet 01 and Fig. A-GBAAA Sheet 02.

(a) At Frame 35 between STGR28 and STGR31, do the cold the cold expansion of the

tooling holes, refer to SRM 51-48-00.

1 Over size the holes to the starting diameter, refer to Fig. A-GBAAA Sheet 02.

Use FTI tool list No.:

DKA320531268-1 Durable tooling 1

2 Clean the drilled area with:

Solvent General

Purpose

11-026 As required

Lint-Free Cotton

Cloth

19-003 As required

3 Install the sleeves and obey the split direction given in Fig. A-GBAAA Sheet

02.

4 Do the cold expansion of the holes.

Use FTI tool list No.:

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 24

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

FTIA320531268-1 Capital tooling 1

DKA320531268-1 Durable tooling 1

EKA320531268-1 Expendable tooling 1

5 Remove the sleeves.

6 Ream the holes to the final diameter given in Fig. A-GBAAA Sheet 02.

7 Deburr the holes and clean the drilled area with:

Solvent General

Purpose

11-026 As required

Lint-Free Cotton

Cloth

19-003 As required

(b) At Frame 35 between STGR28 and STGR30, do the cold the cold expansion of the

fastener holes, refer to SRM 51-48-00.

Refer to Fig. A-GBAAA Sheet 01 and Fig. A-GBAAA Sheet 02.

1 Over size the holes to the starting diameter, refer to Fig. A-GBAAA Sheet 02.

Use FTI tool list No.:

DKA320531268-1 Durable tooling 1

2 Clean the drilled area with:

Solvent General

Purpose

11-026 As required

Lint-Free Cotton

Cloth

19-003 As required

3 Install the sleeves and obey the split direction given in Fig. A-GBAAA Sheet

02.

4 Do the cold expansion of the holes.

Use FTI tool list No.:

DKA320531268-1 Durable tooling 1

FTIA320531268-1 Capital tooling 1

EKA320531268-1 Expendable tooling 1

5 Remove the sleeves.

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 25

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

6 Ream the holes to the final diameter given in Fig. A-GBAAA Sheet 02.

NOTE: The final hole diameter gives an interference fit of the

fasteners between -35 μm and -85 μm (-0.0014 in and -0.0033

in).

7 Deburr the holes and clean the drilled area with:

Solvent General

Purpose

11-026 As required

Lint-Free Cotton

Cloth

19-003 As required

(c) At Frame 35 between STGR30 and STGR31, do the cold expansion of the fastener

holes, refer to SRM 51-48-00.

Refer to Fig. A-GBAAA Sheet 01 and Fig. A-GBAAA Sheet 02.

1 Over size the holes to the starting diameter, refer to Fig. A-GBAAA Sheet 02.

Use FTI tool list No.:

DKA320531268-1 Durable tooling 1

2 Clean the drilled area with:

Solvent General

Purpose

11-026 As required

Lint-Free Cotton

Cloth

19-003 As required

3 Install the sleeves and obey the split direction given in Fig. A-GBAAA Sheet

02.

4 Do the cold expansion of the holes.

Use FTI tool list No.:

FTIA320531268-1 Capital tooling 1

DKA320531268-1 Durable tooling 1

EKA320531268-1 Expendable tooling 1

NOTE: It is necessary to use, FTI Tool LBRA-7, right angled adaptor,

to cold expand two holes, refer to Fig. A-GBAAA Sheet 02.

5 Remove the sleeves.

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 26

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

6 Ream the holes to the final diameter given in Fig. A-GBAAA Sheet 02.

NOTE: The final hole diameter gives an interference fit of the

fasteners between -35 μm and -85 μm (-0.0014 in and -0.0033

in).

7 Deburr the holes and clean the drilled area with:

Solvent General

Purpose

11-026 As required

Lint-Free Cotton

Cloth

19-003 As required

(9) Subtask 531268-831-205-001 - Install the Fasteners at FR35, between STGR28 and

STGR31, LH and RH

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 825

Panel 131PW, Panel 132PW

Work location Frame 35

from Stringer 28 to Stringer 31

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Kit 531268D01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

14 EN6115K3A4 10 BOLT

15 EN6115K3A3 8 BOLT

16 ASNA2536-3A 18 NUT

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant-Brush Consistency 09-013 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Structural Repair Manual (SRM) 51-42-00

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 27

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

References

Fig. A-GBAAA

Modify the fastener Holes at Frame 35,

between STGR28 and STGR31, LH and

RH

Sheet 01

Sheet 02

Do the steps that follow for the LH and RH of the aircraft

Refer to Fig. A-GBAAA Sheet 01 and Fig. A-GBAAA Sheet 02.

(a) At Frame 35 between STGR28 and STGR31, install the fasteners, in accordance

with SRM 51-42-00.

Refer to Fig. A-GBAAA Sheet 02.

1 Use:

Sealant-Brush

Consistency

09-013 As required

to wet install:

10 Bolt EN6115K3A4 Item 14

8 Bolt EN6115K3A3 Item 15

18 Nut ASNA2536-3A Item 16

2 Torque tighten the fasteners refer to AMM Task 20-21-11-911-001.

(10) Subtask 531268-831-206-001 - Apply the Surface Protection at FR35, between

STGR28 and STGR31, LH and RH

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 825

Panel 131PW, Panel 132PW

Work location Frame 35

from Stringer 28 to Stringer 31

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 28

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

Material necessary to do the job

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Corrosion Preventive

Compound, Temporary

15-009 As required

Anti-Corrosion Primer

(Polyurethane)

16-001 As required

Polyurethane Top Coat

(Grey)

16-002 As required

References

Structural Repair Manual (SRM) 51-23-12

51-75-12

Fig. A-GBAAA

Modify the fastener Holes at Frame 35,

between STGR28 and STGR31, LH and

RH

Sheet 01

Sheet 02

Do the steps that follow for the LH and RH of the aircraft.

Refer to Fig. A-GBAAA Sheet 01 and Fig. A-GBAAA Sheet 02.

(a) At Frame 35 between STGR28 and STGR31, renew the protective finish in

accordance with SRM 51-75-12.

1 Apply:

Anti-Corrosion

Primer

(Polyurethane)

16-001 As required

Polyurethane Top

Coat (Grey)

16-002 As required

(b) Renew the special protection in accordance with SRM 51-23-12.

1 Apply:

Corrosion

Preventive

Compound,

Temporary

15-009 As required

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 29

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

D. TEST

(1) Subtask 531268-720-201-001 - Testing

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 825

Panel 131PW, Panel 132PW

Manpower Resources

Skills UTILITY

References

Aircraft Maintenance Manual (AMM) Task 38-11-41-400-002

(a) If the potable water tank 3000MM was removed for access, do a leak test of the

potable water system, refer to AMM Task 38-11-41-400-002.

E. CLOSE-UP

(1) Subtask 531268-410-201-001 - Install/Close Items Removed/Opened for access

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 825

Panel 131PW, Panel 132PW

Manpower Resources

Manhours 3.00

Minimum number of person 2

Subtask elapsed time 1.50

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 21-21-41-400-001

Task 25-80-00-400-001

Task 38-11-41-400-002

(a) If removed, install electrical bundle clamps.

(b) Install the heat and sound insulation blankets in the area between Frame 35 and

Frame 36 LH and RH, refer to AMM Task 25-80-00-400-001.

(c) If removed, install the potable water tank 3000MM and ventilation ducts, refer to

AMM Task 38-11-41-400-002.

(d) If removed, install the air conditioning recirculation filters 4012HM LH and 4013HM

RH, refer to AMM Task 21-21-41-400-001.

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 30

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

(2) Subtask 531268-942-202-001 - Close-up

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 825

Panel 131PW, Panel 132PW, Panel 191BT,

Panel 192BT

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 25-54-12-400-001

Task 52-30-00-860-002

Task 53-35-11-400-001

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) At FR34 install the FWD cargo compartment partitions 131PW, 132PW and if

removed 131NW, refer to AMM Task 25-54-12-400-001.

(c) Install the wing-to-fuselage fairings 191BT and 192BT, refer to AMM Task

53-35-11-400-001.

(d) Close the FWD cargo compartment door.825, refer to AMM Task

52-30-00-860-002.

(e) Remove the access platform(s).

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 31

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

**CONF ALL

STGR30LH

STGR29LH

FR35

825

Z130

A

LH SIDE SHOWN

RH SIDE SYMMETRICAL

A

B

N_SB_531268_5_BAAA_01_01

Figure A-FBAAA - Sheet 01

Cold Expansion of the Fasteners Holes at FR35, STGR30, LH and RH sides

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 32

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

**CONF ALL

VIEW LOOKING OUTSIDE

LH SIDE SHOWN

RH SIDE SYMMETRICAL

HEAD ON THE HIDDEN SIDE

FASTENER NOT AFFECTED

IF THE EXISTING HOLE DIAMETER IS MORE THAN THE MAX. STARTING HOLE DIAMETER

OR IF CRACK IS FOUND IN THE HOLE, CONTACT AIRBUS

FASTENER

SYMBOL

ITEM PN KEYWORD STDN REMARK

STARTING HOLE

DIAMETER

FINAL HOLE

DIAMETER

MIN MAX

(1) 2

(9) 10

(3) 4

(9) 10

(5) 6

(9) 10

(7) 8

(9) 10

EN6115K3A7

ASNA2536−3A

EN6115K3A8

ASNA2536−3A

EN6115K3A10

ASNA2536−3A

AN6115K3A12

ASNA2536−3A

BOLT

NUT

BOLT

NUT

BOLT

NUT

BOLT

NUT

6−1−N 4.88 mm

(0.1921 in)

4.93 mm

(0.1941 in)

5.452 mm

(0.2146 in)

5.487 mm

(0.2160 in)

MIN MAX

EXPANSION SLEEVE INSTALLATION

ORIENTATION SCHEMATIC DIAGRAM

F

F

F

F

F

FWD

STGR29

STGR30

FR35

NOTE:

01

01

B

N_SB_531268_5_BAAA_02_01

Figure A-FBAAA - Sheet 02

Cold Expansion of the Fasteners Holes at FR35, STGR30, LH and RH sides

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 33

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

**CONF ALL

A

Z240

FR35

FR42

A

Z140

B C

B C

BEFORE

STGR28

STGR29

STGR30

STGR31

Y1282.0 FR35

LH SHOWN, RH SIMILAR

B

VIEW LOOKING FWD

ITEM DESCRIPTION HOLE

SYMBOL

(11) RIVET

(12) RIVET, HI−LOK

(13) COLLAR, HI−LOK

TOOLING

HOLE

TOOLING

HOLE

N_SB_531268_6_BAAA_01_03

Figure A-GBAAA - Sheet 01

Modify the fastener Holes at Frame 35, between STGR28 and STGR31, LH and RH

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 34

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

**CONF ALL

LH SHOWN, RH SIMILAR

VIEW LOOKING FWD

P/N DESCRIPTION

MIN MAX

ITEM STDN HOLE

SYMBOL

HOLE DIAMETER

14 EN6115K3A4 BOLT 4.93 mm

(0.192 in) (0.195 in)

6−1−N

4.88 mm

MIN MAX

HOLE DIAMETER

5.452 mm 5.487 mm

(0.2146 in) (0.2160 in)

STARTING FINAL

FASTENER NOT AFFECTED.

NOTE:

01 COLD EXPAND TWO TOOLING HOLES IN ACCORDANCE WITH SRM 51−48−00.

02 COLD EXPAND NINE RIVET HOLES IN ACCORDANCE WITH SRM 51−48−00.

01

02

02

16 ASNA2536−3A NUT

15 EN6115K3A3 BOLT

16 ASNA2536−3A NUT

STGR28

STGR29

STGR30

STGR31

Y1282.0 FR35

AFTER

02

TOOLING HOLE 8−1−N 7 mm

(0.276 in)

4.93 mm

(0.192 in) (0.195 in)

4.88 mm 5.452 mm 5.487 mm

(0.2146 in) (0.2160 in)

C

TOOLING HOLE

01

TOOLING HOLE

6.45 mm

(0.254 in)

6.38 mm

(0.251 in)

ORIENTATION SCHEMATIC DIAGRAM

=

EXPANSION SLEEVE INSTALLATION.

03 IT IS NECESSARY TO USE FTI TOOL LBRA−7, RIGHT ANGLED ADAPTOR,

TO COLD EXPAND THESE HOLES.

03

02

N_SB_531268_6_BAAA_02_04

Figure A-GBAAA - Sheet 02

Modify the fastener Holes at Frame 35, between STGR28 and STGR31, LH and RH

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 35

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 36

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

APPENDIX 01: Elapsed Time Assumption

**CONF ALL

ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A320−53−1268

SB ELAPSED TIME

(HOURS)

JOB SET UP

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

21.00

15.50

STEPS

5.00 2.50

CLOSE−UP 6.00 3.00

MH

ET/S:

PER

MANHOURS

ELAPSED TIME PER STEP

NUMBER OF PERSONS

01

02

THIS CHART IS ONLY A PROPOSAL.

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM.

01

02

NOTE:

PER

2

2

:

: IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS

ARE NOT REFLECTED IN THIS GANTT CHART.

REMOVE THE 18 FASTENERS AT FR35, STGR30, 0.50 0.50 1

0.50 0.50 1

0.50 0.50 1

0.50 0.50 1

2.00 2.00 1

2.50 2.50 1

0.75 0.75 1

1.00 1.00 1

0.25 0.25 1

0.50 0.50 1

TEST 1.00 1.00 1

LH AND RH

REMOVE THE FASTENERS AT FR35, BETWEEN

STGR28 AND STGR31 LH AND RH

DO THE NDT ON THE 18 FASTENER HOLES AT FR35,

STGR30, LH AND RH

DO THE NDT ON THE FASTENER AND TOOLING HOLES

AT FR35 BETWEEN STGR28 AND STGR31 LH AND RH

DO THE COLD EXPANSION AND REAM THE 18 HOLES

AT FR35, STGR30, LH AND RH

DO THE COLD EXPANSION AND REAM THE HOLES AT

FR35, BETWEEN STGR28 AND STGR31 LH AND RH

INSTALL THE 18 FASTENER HOLES AT FR35, STGR30,

LH AND RH

INSTALL THE FASTENERS AT FR35, BETWEEN STGR28

AND STGR31 LH AND RH

APPLY SURFACE PROTECTION TO THE 18 FASTENER

HOLES AT FR35, STGR30, LH AND RH

APPLY SURFACE PROTECTION AT FR35 BETWEEN

STGR28 AND STGR31 LH AND RH

0 5 10 15 20

N_SB_531268_6_AAAA_01_01

Figure A-GAAAA - Sheet 01

Gantt Chart

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 1

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

REPORTING SHEET

TITLE: FUSELAGE - CENTER FUSELAGE - REINFORCE FORWARD

PRESSURE BULKHEAD AT FRAME COUPLING C35 LH/RH

MODIFICATION No.: 153832K16057

Please complete the appropriate item (A or B):

A - SB WILL BE embodied YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to

next normal revision or prior to SB embodiment, please indicate required service(s):

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational

documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With

the next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.

- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 1

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data

that you provide us will be used to analyse areas of difficulties and to take corrective action to further

improve the quality of our Service Bulletins.

We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

X Reason X List of Materials Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268

REVISION No.: 03 - May 07/15 Page: 1

6

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.