@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.

ATA SYSTEM: 53

TITLE: FUSELAGE - FORWARD FUSELAGE - FR35 CIRCUMFERENTIAL

JUNCTION - INSPECTION OF 2 ROWS OF 6 FASTENER HOLES

BETWEEN STGR 5 AND STGR 6 LH AND RH SIDE

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

In Final Assembly Line (FAL), on some aircraft, EN6114V3 fasteners were installed on the upper panel

between STR13 left and right sides at FR35.

These fasteners have a medium head, thicker than the head of DAN6-6, or ASNA2657V3, or

ASNA2043-3 fasteners and leading to a deeper countersink in the upper skin panel which has a

reduced thickness.

There is an effect on the panel fatigue life.

This Service Bulletin recommends inspecting two rows of six fasteners on the affected aircraft between

STGR5 and STGR6 LH and RH sides at FR35.

Accomplishment of this Service Bulletin will contribute to ensure the structural integrity of the upper

panel.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE RECOMMENDED (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin recommended to be accomplished to prevent significant operational

disruptions.

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SUMMARY

MATERIAL PRICE INFORMATION

No Material

EFFECTIVITY

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

53U AEE AFL AFR AVA CES CQH CSC CSZ DKH DLH EZY GOW

IGO LTU LZB THY VLG VRD WAN

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

Task 531244-832-801-001: Inspection

TOTAL MANHOURS 3.00

ELAPSED TIME (HOURS) 3.00

APPENDICES

Appendix 1

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SUMMARY

**CONF ALL

FR35

CL

N_SB_531244_5_SAAA_01_00

STGR1LH

STGR2LH

STGR3LH

STGR4LH

STGR5LH

STGR6LH

STGR10LH

STGR9LH

STGR8LH

STGR7LH

STGR10RH

STGR10LH

FR35

A

FASTENERS TO BE INSPECTED

LH SIDE SHOWN A RH SIDE SYMMETRICAL

CL

Figure A-FSAAA - Sheet 01

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SUMMARY

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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

ATA SYSTEM: 53

TITLE: FUSELAGE - FORWARD FUSELAGE - FR35 CIRCUMFERENTIAL

JUNCTION - INSPECTION OF 2 ROWS OF 6 FASTENER HOLES

BETWEEN STGR 5 AND STGR 6 LH AND RH SIDE

MODIFICATION No.: None

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

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

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

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

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

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

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

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

(1) Models

320-214 320-232

(2) Effectivity by MSN

3456 3503 3516 3529 3591 3597 3611 3631 3696 3698 3714 3719 3775 3777 3780

3782 3786 3797 3805 3812 3870 3907 3909 3913 3922 3929 3946 3953 3975 3979

3991 4010 4012 4014 4027 4034 4043 4046 4064-4065 4084 4093-4094 4097

(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

53U 3812 4065 4094

AEE 3714

AFL 3631 3786

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OPERATOR MSN

AFR 3777 4084

AVA 4046

CES 3611 3775 3797 3870 3929 4027 4043

CQH 4093

CSC 3591

CSZ 3456 3696 3698 4010

DKH 4064

DLH 4097

EZY 3805 3909 3913 3922 3946 3953 3975 3979 3991 4012 4014 4034

GOW 3597

IGO 3782

LTU 3516

LZB 3780

THY 3719

VLG 3529

VRD 3503

WAN 3907

(4) Configuration by MSN

MSN CONFIGURATION

3456 3503 3516 3529 3591 3597 3611 3631 3696 3698 3714

3719 3775 3777 3780 3782 3786 3797 3805 3812 3870 3907

3909 3913 3922 3929 3946 3953 3975 3979 3991 4010 4012

4014 4027 4034 4043 4046 4064 4065 4084 4093 4094 4097

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

Consumable CMLA01 As required

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

In Final Assembly Line (FAL), on some aircraft, EN6114V3 fasteners were installed on

the upper panel between STR13 left and right sides at FR35.

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These fasteners have a medium head, thicker than the head of DAN6-6, or

ASNA2657V3, or ASNA2043-3 fasteners and leading to a deeper countersink in the

upper skin panel which has a reduced thickness.

There is an effect on the panel fatigue life.

(2) Objective/Action

This Service Bulletin recommends inspecting two rows of six fasteners on the affected

aircraft between STGR5 and STGR6 LH and RH sides at FR35.

(3) Advantages

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

the upper panel.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 531244-832-801-001: Inspection

(1) Special Detailed Inspection of the Fasteners at LH Side

(2) Special Detailed Inspection of the Fasteners at RH Side

E. COMPLIANCE

(1) Classification

RECOMMENDED: Service Bulletin recommended to be accomplished to prevent

significant operational disruptions.

(2) Accomplishment Timescale

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 below but reference should be made to the AD for

confirmation of the mandated accomplishment timescale.

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COMPLIANCE TIME (whichever occurs

first)

CONDITION ACTION

THRESHOLD GRACE PERIOD

REPETITIVE

INTERVAL NOT

TO EXCEED

(whichever occurs

first)

CONF 001 Do a HFEC

inspection in

accordance with

SUBTASK

531244-250-004

001 Special

Detailed Inspection

of the Fasteners at

LH Side and

SUBTASK

531244-250-003

001 Special

Detailed Inspection

of the Fasteners at

RH Side .

35,900 Flight

Cycles (FC) /

88,100 Flight

Hours (FH)

- -

Crack is found Contact AIRBUS

and apply

corrective action

defined by AIRBUS

Before next flight - -

No crack is found Do the inspection

again.

- - 28,100 FC / 56,300

FH

F. APPROVAL

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

Organisation Approval No. EASA.21J.031.

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

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

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

before incorporation of the Service Bulletin.

G. MANPOWER

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

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

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

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

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

included.

Task 531244-832-801-001: Inspection

Get Access 0.50

On Aircraft

Special Detailed Inspection of the Fasteners at LH

Side

1.00

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Task 531244-832-801-001: Inspection

Special Detailed Inspection of the Fasteners at RH

Side

1.00

Close-Up 0.50

TOTAL MANHOURS 3.00

ELAPSED TIME (HOURS) 3.00

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 12-34-24

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

Non Destructive Test Manual (NTM) 51-10-08

K. PUBLICATION AFFECTED

Impact on scheduled maintenance : Refer to Maintenance Planning Document (MPD).

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

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2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

None

(2) Price and Availability

None

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will not provide industry support for accomplishment of this Service Bulletin.

C. LIST OF COMPONENTS

No Kit

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Solvent General Purpose 11-026 As required

(2) Components

None

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

None

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 531244-832-801-001 - Inspection

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.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.

Task Associated Data

Zone

From 230 to 240

Manpower

TOTAL MANHOURS 3.00

ELAPSED TIME (HOURS) 3.00

A. GENERAL

(1) Subtask 531244-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

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

(a) Clean the area to be inspected with :

Solvent General

Purpose

11-026 As required

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(2) Subtask 531244-839-001-001 - 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 531244-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

(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. PROCEDURE

(1) Subtask 531244-250-004-001 - Special Detailed Inspection of the Fasteners at LH

Side

Work Zones and Access Panels

Zone Access/Work location

From 230 Work location Frame 35

from Stringer 5 to Stringer 6

To 240

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) 51-10-08

Fig. A-FBAAA

Area to be Inspected

Sheet 01

Sheet 02

Fig. A-FBBAA

Flow Chart

Sheet 01

(a) For the area to be inspected, refer to Fig. A-FBAAA.

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(b) Do a special detailed inspection (HFEC) as per NTM 51-10-08 of the two rows of

six fasteners at FR35 between STGR5 and STGR6 at LH side.

Refer to Fig. A-FBBAA.

1 If crack is found, contact AIRBUS and apply corrective action defined by

AIRBUS before next flight.

2 If no crack is found, do the inspection again at interval given in Planning

Information Paragraph E.(2).

(c) For the inspection report, refer to Appendix 1 .

(2) Subtask 531244-250-003-001 - Special Detailed Inspection of the Fasteners at RH

Side

Work Zones and Access Panels

Zone Access/Work location

From 230 Work location Frame 35

from Stringer 5 to Stringer 6

To 240

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) 51-10-08

Fig. A-FBAAA

Area to be Inspected

Sheet 01

Sheet 02

Fig. A-FBBAA

Flow Chart

Sheet 01

(a) For the area to be inspected, refer to Fig. A-FBAAA.

(b) Do a special detailed inspection (HFEC) as per NTM 51-10-08 of the two rows of

six fasteners at FR35 between STGR5 and STGR6 at RH side.

Refer to Fig. A-FBBAA.

1 If crack is found, contact AIRBUS and apply corrective action defined by

AIRBUS before next flight.

2 If no crack is found, do the inspection again at interval given in Planning

Information Paragraph E.(2).

(c) For the inspection report, refer to Appendix 1 .

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D. TEST

None

E. CLOSE-UP

(1) Subtask 531244-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

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

equipment.

(b) Remove the access platform(s).

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**CONF ALL

FR35

CL

STGR1LH

STGR2LH

STGR3LH

STGR4LH

STGR5LH

STGR6LH

STGR10LH

STGR9LH

STGR8LH

STGR7LH

STGR10RH

STGR10LH

FR35

A

LH SIDE SHOWN A RH SIDE SYMMETRICAL

CL

B

N_SB_531244_5_BAAA_01_01

Figure A-FBAAA - Sheet 01

Area to be Inspected

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**CONF ALL

LH SIDE SHOWN

RH SIDE SYMMETRICAL

FR35

STGR5

STGR6

FASTENERS TO BE INSPECTED

FWD B

NOTE:

N_SB_531244_5_BAAA_02_01

Figure A-FBAAA - Sheet 02

Area to be Inspected

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**CONF ALL

QUESTION

ACTION

FINDING

AS PER NTM 51−10−08 OF THE TWO ROWS OF SIX FASTENERS

DO A SPECIAL DETAILED INSPECTION (HFEC INSPECTION)

(REFER TO FIG. A−FBAAA)

AT THRESHOLD GIVEN IN PLANNING INFORMATION

AT FR35 BETWEEN STGR5 AND STGR6 LH AND RH SIDE

YES CRACK

CONTACT AIRBUS

AND APPLY CORRECTIVE

ACTION DEFINED BY

PARAGRAPH E.(2).

NO

DO THE INSPECTION AGAIN AT

INTERVAL GIVEN IN PLANNING

INFORMATION PARAGRAPH E.(2).

N_SB_531244_5_BBAA_01_02

AIRBUS BEFORE

NEXT FLIGHT

Figure A-FBBAA - Sheet 01

Flow Chart

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Appendix 1

**CONF ALL

(1) The result of the inspection, including no findings, replacement or actions to be done, must be

forwarded to AIRBUS Department SEES4, on the attached inspection report sheet.

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Appendix 1

**CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−53−1244

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES4

PAX DOORS − FUSELAGE (SA/LA) − WINDOWS −

INSPECTION METHOD : SPECIAL DETAILED

INSPECTION

CENTER WING BOX (SA/LA)

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

CRACK

YES

N_SB_531244_5_AAAA_01_02

LH SIDE RH SIDE

1

NO

HOLE No.

YES

2

NO

YES

3

NO

YES

4

NO

YES

5

NO

YES

6

NO

YES

7

NO

YES

8

NO

YES

9

NO

YES

10

NO

YES

11

NO

YES

12

NO

CRACK DIMENSION

LH SIDE RH SIDE

1

HOLE No.

2

3

4

5

6

7

8

9

10

11

12

FOR HOLE NUMBERING REFER TO SHEETS 03 AND 04.

NOTE:

Figure A-FAAAA - Sheet 01

Inspection Report

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Appendix 1

**CONF ALL

FR35

CL

STGR1LH

STGR2LH

STGR3LH

STGR4LH

STGR5LH

STGR6LH

STGR10LH

STGR9LH

STGR8LH

STGR7LH

STGR10RH

STGR10LH

FR35

A

LH SIDE SHOWN A RH SIDE SYMMETRICAL

CL

N_SB_531244_5_AAAA_02_00

B C

Figure A-FAAAA - Sheet 02

Inspection Report

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Appendix 1

**CONF ALL

REPORT THE DIRECTION OF THE CRACKS ON VIEW B.

NOTE:

FR35

STGR5

STGR6

FWD

11

12

10

9

8

7

5

6

4

3

2

1

N_SB_531244_5_AAAA_03_00

LH SIDE

B

Figure A-FAAAA - Sheet 03

Inspection Report

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Appendix 1

**CONF ALL

REPORT THE DIRECTION OF THE CRACKS ON VIEW C.

NOTE:

RH SIDE

FR35

STGR5

STGR6

11

12

10

9

8

7

5

6

4

3

2

1

C FWD

N_SB_531244_5_AAAA_04_01

Figure A-FAAAA - Sheet 04

Inspection Report

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REPORTING SHEET

TITLE: FUSELAGE - FORWARD FUSELAGE - FR35 CIRCUMFERENTIAL

JUNCTION - INSPECTION OF 2 ROWS OF 6 FASTENER HOLES

BETWEEN STGR 5 AND STGR 6 LH AND RH SIDE

MODIFICATION No.: None

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: Mar 17/11 SERVICE BULLETIN No.: A320-53-1244

REVISION No.: 00 - Mar 17/11 Page: 1

5

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 4 3 2 1

- Quality rating of the Accomplishment Instructions 4 3 2 1

- Quality rating of the Illustrations 4 3 2 1

- Is this SB easy to understand ? Y / N

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: Mar 17/11 SERVICE BULLETIN No.: A320-53-1244

REVISION No.: 00 - Mar 17/11 Page: 1

5

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