@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

ATA SYSTEM: 53

TITLE: FUSELAGE - WINDSHIELD CENTRAL LOWER NODE - INSPECT

CRACK IN CONTINUITY FITTINGS AND WINDSHIELD FRAMING

MODIFICATION No.: None

This page transmits Revision No.01 of Service Bulletin No.A320-53-1245

ADDITIONAL WORK

**CONF ALL

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

REASON

Effectivity updated. MSN beyond 29000 FC added in the effectivity.

CHANGES

SUMMARY

EFFECTIVITY OPERATOR LIST UPDATED R

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

FILLING 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

No previous revision

REVISION SEQUENCE

ORIGINAL: Mar 02/11

REVISION No. : 01 - May 17/11

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

REVISION No.: 01 - May 17/11 Page: 1

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REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

REVISION No.: 01 - May 17/11 Page: 2

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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 - WINDSHIELD CENTRAL LOWER NODE - INSPECT

CRACK IN CONTINUITY FITTINGS AND WINDSHIELD FRAMING

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

Modification No. 22058 was implemented in production from MSN 259 in order to improve the fatigue

strength of the windshield front framing, following cracks detected on Fuselage Fatigue Test specimen

(EF1) for DSG certification. For the pre-mod 22058 design, ALI tasks 531129-01-1 or 02-1 (alternative

to 01-1): "detailed inspection of windshield center post, lower attachment area" has been defined.

During the new full Scale Fatigue Test specimen (NEF1) supporting Single Aisle Extended Service Goal

activities, which is in the post-mod 22058 design, cracks were detected in the LHS & RHS continuity

fittings, attached to the windshield framing. Moreover an Operator has reported the first in-service

findings on a post-mod 22058 aircraft.

The analysis of the cracks propagation supporting NEF1 findings in the post-mod 22058 or 21999P2000

continuity fittings shows that the damage tolerance and the fatigue requirement of JAR 25.571 (b) are

not fulfilled. The aim of this ISB is therefore to restore the fleet airworthiness for the aircraft approaching

the threshold and to cover by a grace period the aircraft that have already exceeded this defined

threshold.

A new ALI is expected to be defined as well for the post-mod 22058 or 21999P2000 aircraft. The

aircraft already inspected as per this Service Bulletin No. A320-53-1245 at the time of the ALI dispatch,

will have to be reinspected thereafter according to the ALI interval.

An aircraft not yet inspected as per this SB No. A320-53-1245 and beyond the threshold at the time of

the ALI dispatch, will therefore be covered by the defined grace period of this SB No. A320-53-1245

and will have to be reinspected thereafter according to the ALI interval.

An aircraft not yet inspected as per this SB No. A320-53-1245 and below the threshold at the time of

the ALI dispatch, will have to be inspected as per ALI requirements.

This Inspection Service Bulletin (ISB) requires a special detailed inspection of the windshield front frame

and continuity fittings on LH & RH sides by means of:

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

REVISION No.: 01 - May 17/11 Page: 1

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SUMMARY

- High Frequency Eddy Current (HFEC) on windshield front framing lower centre post and continuity

fittings on LH & RH sides (crack detection).

Accomplishment of this ISB allow to find potential cracks on windshield front framing lower centre post

and continuity fittings on LH & RH sides and thus contribute to ensure the structural integrity of the

area.

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.

MATERIAL PRICE INFORMATION

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Component COMPA01 1 See SB Rivets

EFFECTIVITY

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

51X AAR AFR ANA BTV DLH EAA FPY FRN GFA IAC IRA JET

MXA NVD PTR SWR TAM TCW TNA VLG

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

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

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SUMMARY

SOFT NO

OBRM NO

MANPOWER

Task 531245-832-801-001: Inspection

TOTAL MANHOURS 19.50

ELAPSED TIME (HOURS) 19.50

APPENDICES

Appendix 1

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

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SUMMARY

**CONF ALL

N_SB_531245_5_SAAA_01_00

A

A

INSPECTION AREA

(INTERNAL SIDE)

Figure A-FSAAA - Sheet 01

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

REVISION No.: 01 - May 17/11 Page: 4

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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 - WINDSHIELD CENTRAL LOWER NODE - INSPECT

CRACK IN CONTINUITY FITTINGS AND WINDSHIELD FRAMING

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

319-112 319-113 319-132 320-211 320-212 320-214 320-231 320-232

321-111 321-131

(2) Effectivity by MSN

0259-0260 0264 0266-0270 0275-0276 0278 0287 0296 0300 0303 0312 0320-0321

0323 0325 0328 0332 0334-0335 0337 0346 0352-0353 0356 0365 0369 0375 0377

0382-0383 0396 0398 0401 0412-0413 0416 0419 0421 0431-0432 0438 0440-0441

0445 0453 0458-0459 0466 0468 0473-0474 0482 0484 0491 0493 0497-0498

0501-0502 0505 0507 0509 0518 0520-0521 0529 0531 0534 0537-0538 0544 0549

0554-0555 0560 0563 0577-0578 0585 0598 0600 0608 0612 0618 0621 0625 0637

0660 0685 0976 1010 1092 1096 1103 1139 1143 1158 1251 1356 1511

(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.

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

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OPERATOR MSN

51X 0325

AAR 1356 1511

AFR 0270 0278 0287 0337 0352 0377 0491 0498 0509 0521 0529 0544

0598 0600 0608 0618 0625 0637

ANA 0300 0328 0365 0383 0413 0482 0501 0507 0531 0534 0549 0554

0685

BTV 0441

DLH 0267 0268 0269 0346 0382 0401 0412 0458 0468 0473 0474 0484

0493 0502 0505 0518 0560 0563

EAA 0445

FPY 0438

FRN 0466 0497

GFA 0419

IAC 0396 0398 0416 0431 0432

IRA 0303 0312

JET 0421 0660

MXA 0259 0260 0275 0276 0296 0320 0321 0332 0353 0369

NVD 0375

PTR 0459 0537

SWR 0520 0577 0578 0585 0612 0621

TAM 0334 0335 0440 0976 1010 1092 1096 1103 1139 1143 1158 1251

TCW 0453

TNA 0538 0555

VLG 0264 0266 0323 0356

(4) Configuration by MSN

MSN CONFIGURATION

0259 0260 0264 0266 0267 0268 0269 0270 0275 0276 0278

0287 0296 0300 0303 0312 0320 0321 0323 0325 0328 0332

0334 0335 0337 0346 0352 0353 0356 0365 0369 0375 0377

0382 0383 0396 0398 0401 0412 0413 0416 0419 0421 0431

0432 0438 0440 0441 0445 0453 0458 0459 0466 0468 0473

0474 0482 0484 0491 0493 0497 0498 0501 0502 0505 0507

0509 0518 0520 0521 0529 0531 0534 0537 0538 0544 0549

0554 0555 0560 0563 0577 0578 0585 0598 0600 0608 0612

0618 0621 0625 0637 0660 0685 0976 1010 1092 1096 1103

1139 1143 1158 1251 1356 1511

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 1

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

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MATERIAL QTY PER A/C SEE NOTES

Component COMPA01 1

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

Modification No. 22058 was implemented in production from MSN 259 in order to

improve the fatigue strength of the windshield front framing, following cracks detected on

Fuselage Fatigue Test specimen (EF1) for DSG certification. For the pre-mod 22058

design, ALI tasks 531129-01-1 or 02-1 (alternative to 01-1): "detailed inspection of

windshield center post, lower attachment area" has been defined.

During the new full Scale Fatigue Test specimen (NEF1) supporting Single Aisle

Extended Service Goal activities, which is in the post-mod 22058 design, cracks were

detected in the LHS & RHS continuity fittings, attached to the windshield framing.

Moreover an Operator has reported the first in-service findings on a post-mod 22058

aircraft.

The analysis of the cracks propagation supporting NEF1 findings in the post-mod 22058

or 21999P2000 continuity fittings shows that the damage tolerance and the fatigue

requirement of JAR 25.571 (b) are not fulfilled. The aim of this ISB is therefore to restore

the fleet airworthiness for the aircraft approaching the threshold and to cover by a grace

period the aircraft that have already exceeded this defined threshold.

A new ALI is expected to be defined as well for the post-mod 22058 or 21999P2000

aircraft. The aircraft already inspected as per this Service Bulletin No. A320-53-1245 at

the time of the ALI dispatch, will have to be reinspected thereafter according to the ALI

interval.

An aircraft not yet inspected as per this SB No. A320-53-1245 and beyond the threshold

at the time of the ALI dispatch, will therefore be covered by the defined grace period of

this SB No. A320-53-1245 and will have to be reinspected thereafter according to the

ALI interval.

An aircraft not yet inspected as per this SB No. A320-53-1245 and below the threshold

at the time of the ALI dispatch, will have to be inspected as per ALI requirements.

(2) Objective/Action

This Inspection Service Bulletin (ISB) requires a special detailed inspection of the

windshield front frame and continuity fittings on LH & RH sides by means of:

- High Frequency Eddy Current (HFEC) on windshield front framing lower centre post

and continuity fittings on LH & RH sides (crack detection).

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

REVISION No.: 01 - May 17/11 Page: 3

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(3) Advantages

Accomplishment of this ISB allow to find potential cracks on windshield front framing

lower centre post and continuity fittings on LH & RH sides and thus contribute to ensure

the structural integrity of the area.

(4) Operational/Maintenance Consequences

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

Task 531245-832-801-001: Inspection

(1) Do an inspection of the Windshield Central Lower Node

E. COMPLIANCE

(1) Classification

RECOMMENDED: Service Bulletin recommended to be accomplished to prevent

significant operational disruptions.

(2) Accomplishment Timescale

The following table is representing Flow Chart 1 of Fig. A-FBBAA.

COMPLIANCE TIME

(Whichever occurs later)

AREA TO BE

INSPECTED

CONDITION ACTION

THRESHOLD GRACE

PERIOD

REPETITIVE

INTERVAL

NOT TO

EXCEED

NOT

APPLICABLE

Do a HFEC

Inspection, NTM

53-11-29 in

accordance with

SUBTASK

531245-280-001 001

Do an inspection of

the Windshield

Central Lower Node .

34,000FC

since A/C first

flight

4,500FC If no crack

finding : No

WINDSHIELD

CENTRAL

LOWER NODE

CRACK

FINDING

Contact Airbus and

apply corrective

action defined by

Airbus.

Before next

flight

Not

applicable

Not

applicable

Inspection of the Windshield Central Lower Node.

F. APPROVAL

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

Organisation Approval No. EASA.21J.031.

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

REVISION No.: 01 - May 17/11 Page: 4

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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 531245-832-801-001: Inspection

Get Access 8.00

On Aircraft

Do an inspection of the Windshield Central Lower

Node

1.00

Tests 0.50

Close-Up 10.00

TOTAL MANHOURS 19.50

ELAPSED TIME (HOURS) 19.50

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-63

12-34-24 20-21-11 31-63-22

52-10-00 56-11-11

Consumable Material List (CML)

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

Non Destructive Test Manual (NTM) 53-11-29

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-12 51-42-00 51-43-00

51-44-00 51-75-12

K. PUBLICATION AFFECTED

No

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

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M. SPARES

None

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

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2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Component COMPA01 Customers with aircraft shown in the

effectivity of this Service Bulletin should send

a purchase order to AIRBUS. Quote the

number of this Service Bulletin. The address

is:

AIRBUS Material logistics and Suppliers

IFD - In Flight Desk

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

For ordering by internet:

http://spares.airbus.com

For ordering by fax: +49 40 50 76 4012

For ordering by E-mail:

ifd.spares@airbus.com

(2) Price and Availability

No AIRBUS kit will be provided. Parts required to accomplish this Service Bulletin are to

be purchased by a Spares Purchase Order.

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

To accomplish this Service Bulletin it is necessary to use the expendable parts listed in

AMM tasks AMM Task 56-11-11-400-001.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Sealant 09-019 As required

Solvent General Purpose 11-026 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

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ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Polyurethane Finish Paint 16-018 As required

(2) Components

Component COMPA01

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

NOTES

1 ASNA2051DXJ4020 8 RIVET

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.

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

(2) Tools

To accomplish this Service Bulletin it is necessary to use the tool listed in AMM tasks

mentioned in paragraph:

- SUBTASK 531245-941-002 001 Job Set-up

- SUBTASK 531245-280-001 001 Do an inspection of the Windshield Central Lower

Node

(3) Special Tools

None

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 531245-832-801-001 - 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

210

Access

Door 831

Manpower

TOTAL MANHOURS 19.50

ELAPSED TIME (HOURS) 19.50

A. GENERAL

(1) Subtask 531245-910-002-001 - 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

Sealant 09-019 As required

Solvent General Purpose 11-026 As required

Anti-Corrosion Primer

(polyurethane)

16-001 As required

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

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ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polyurethane Finish Paint 16-018 As required

References

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

06-31-53, Page Block 001

06-41-63, Page Block 001

Task 20-21-11-911-001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-23-12

51-42-00

51-43-00

51-44-00

51-75-12

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

Refer to Consumable Materials List (CML).

(b) Protect the areas to prevent damage to the equipment, structure and all the parts.

(c) For the identification of the Zones:

Refer to AMM 06-20-00, Page Block 001.

(d) Clean the surface with:

Solvent General

Purpose

11-026 As required

(e) For Frame (FR) identification:

Refer to AMM 06-31-53, Page Block 001.

(f) For the removal and installation of fasteners:

Refer to SRM 51-42-00.

(g) For alternative and substitute fasteners:

Refer to SRM 51-43-00.

(h) For fastener hole diameter and drill and deburr data:

Refer to SRM 51-44-00.

(i) To torque tighten the standard threaded fasteners:

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

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

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(j) Install the fasteners (wet assembly) with:

Sealant 09-019 As required

(k) Apply,

Sealant 09-019 As required

to the interfaces of the structure and the reinstalled parts.

(l) Renew the protective coating:

Refer to SRM 51-23-12.

(m) Renew the protective finish with:

Anti-Corrosion

Primer

(polyurethane)

16-001 As required

Polyurethane Finish

Paint

16-018 As required

Refer to SRM 51-75-12.

(2) Subtask 531245-839-002-001 - 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 531245-941-002-001 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Skills NON SPECIFIC

References

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

Task 31-63-22-000-001

Task 52-10-00-010-001

Task 56-11-11-000-001

Fig. A-FBEAA

Installation/Removal of the Shims

Sheet 01

Sheet 02

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

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(a) Make sure that the aircraft is electrically grounded:

Refer to AMM Task 12-34-24-869-002.

(b) Put access platform in position in zone 831.

(c) Put access platform in position at zone 210 in front of the windshield.

(d) Open the passenger/crew door(s) 831:

Refer to AMM Task 52-10-00-010-001.

(e) Do the preparation procedure as specified in the removal of the Display Unit

(4WT1):

Refer to AMM Task 31-63-22-000-001.

(f) Do the preparation procedure as specified in the removal of the Windshields:

Refer to AMM Task 56-11-11-000-001.

(g) Remove the Display Unit 4WT1:

Refer to AMM Task 31-63-22-000-001.

(h) Remove the RH and LH Windshields:

Refer to AMM Task 56-11-11-000-001.

(i) Remove:

Refer to Fig. A-FBEAA.

1 Shim Item (2) Retain

and

1 Shim Item (3) Retain

attached with:

8 Rivet Item (1) Discard

C. PROCEDURE

(1) Subtask 531245-280-001-001 - Do an inspection of the Windshield Central Lower

Node

Work Zones and Access Panels

Zone Access/Work location

210 Access Door 831

Work location Frame 2

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

REVISION No.: 01 - May 17/11 Page: 12

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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) 53-11-29

Fig. A-FBAAA

Special Detailed Inspection Area.

Sheet 01

Sheet 02

Fig. A-FBBAA

Flow Chart.

Sheet 01

Do an inspection of the windshield center lower node.

(a) For the inspection area:

Refer to Fig. A-FBAAA.

(b) Do a Special Detailed Inspection of the windshield central lower node.

Refer to flow chart Fig. A-FBBAA.

1 For the Hight-Frequency Eddy Current (HFEC) Inspection:

Refer to NTM 53-11-29.

(c) For the inspection report:

Refer to Appendix 1 .

D. TEST

(1) Subtask 531245-941-003-001 - Test Job Set-up

Work Zones and Access Panels

Zone Access/Work location

210 Access Door 831

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-400-001

Task 56-11-11-400-001

NOTE: Before the tests, do not forget to install the parts and/or equipment as

requires in SUBTASK 531245-942-001 001 Close-up .

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

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(a) Remove the safety clips and tags and close the circuit breakers as specified after

the installation of the windshield:

Refer to AMM Task 56-11-11-400-001.

(b) Remove the safety clips and tags and close the circuit breakers as specified after

the installation of the Display Unit (4WT1):

Refer to AMM Task 31-63-22-400-001.

(2) Subtask 531245-710-001-001 - Operational

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-400-001

Task 56-11-11-400-001

(a) Do the test procedure as specified after the installation of the windshield:

Refer to AMM Task 56-11-11-400-001.

(b) Do the test procedure as specified after the installation of the Display Unit (4WT1):

Refer to AMM Task 31-63-22-400-001.

E. CLOSE-UP

(1) Subtask 531245-942-001-001 - Close-up

Work Zones and Access Panels

Zone Access/Work location

210

Manpower Resources

Skills AIRFRAME

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 ASNA2051DXJ4020 8 RIVET

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-400-001

Task 52-10-00-410-001

Task 56-11-11-400-001

NOTE: Parts and/or equipment removed for access, to be installed before

SUBTASK 531245-941-003 001 Test Job Set-up

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

REVISION No.: 01 - May 17/11 Page: 14

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.

(a) Install:

1 Shim Item (2) Retained at

removal

and

1 Shim Item (3) Retained at

removal

attached with:

8 Rivet ASNA2051DXJ4020 Item 1

(b) Install the RH and LH windshields:

Refer to AMM Task 56-11-11-400-001.

(c) Install the Display Unit 4WT1:

Refer to AMM Task 31-63-22-400-001.

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

equipment.

(e) Close the passenger/crew door 831:

Refer to AMM Task 52-10-00-410-001.

(f) Restore the systems and the aircraft to normal operating condition.

(g) Remove the access platforms.

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

REVISION No.: 01 - May 17/11 Page: 15

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SERVICE BULLETIN

**CONF ALL

Z210 A

A

B

VIEW LOOKING FORWARD

B

CL

INSPECTED AREA

C D

N_SB_531245_5_BAAA_01_00

Figure A-FBAAA - Sheet 01

Special Detailed Inspection Area.

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

REVISION No.: 01 - May 17/11 Page: 16

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**CONF ALL

INSPECTED AREA

INSPECTED AREA

C

D

N_SB_531245_5_BAAA_02_00

Figure A-FBAAA - Sheet 02

Special Detailed Inspection Area.

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

REVISION No.: 01 - May 17/11 Page: 17

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SERVICE BULLETIN

**CONF ALL

QUESTION

ACTION

FINDING

SEND TO AIRBUS THE

INSPECTION REPORT SHEET

YES CRACK FINDING NO

CONTACT AIRBUS AND APPLY THE

CORRECTIVE ACTION DEFINED BY

AIRBUS BEFORE THE NEXT FLIGHT

PERFORM HFEC INSPECTION AS PER NTM 53−11−29

OF THE WINDSHIELD FRAMING LOWER CENTRE POST

AND CONTINUITY FITTINGS LHS AND RHS.

REFER TO FIG. A−FBAAA AT THE THRESHOLD GIVEN

IN PLANNING INFORMATION PARAGRAPH E.(2).

N_SB_531245_5_BBAA_01_01

Figure A-FBBAA - Sheet 01

Flow Chart.

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

REVISION No.: 01 - May 17/11 Page: 18

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**CONF ALL

Z210 A

A

B

VIEW LOOKING FORWARD

B

CL

1

(1) (1)

1

(2)

A

A

A

B A B

N_SB_531245_5_BEAA_01_01

(3)

Figure A-FBEAA - Sheet 01

Installation/Removal of the Shims

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

REVISION No.: 01 - May 17/11 Page: 19

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**CONF ALL

N_SB_531245_5_BEAA_02_00

A A

B B

NOTE:

01 APPLY MAT. No. 09−015

01

01

01

FILL THE REMAINING SPACES AND MAKE SURE THAT THE BEAD

OF SEALANT IS CONTINOUS.

TYPICAL SECTION

TYPICAL SECTION

Figure A-FBEAA - Sheet 02

Installation/Removal of the Shims

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

REVISION No.: 01 - May 17/11 Page: 20

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Appendix 1

**CONF ALL

(1) Inspection Report

The results of the inspection, including no findings, must be forwarded to AIRBUS Department

SEES4, on the attached inspection report sheet.

NOTE: Indicate on the report sheet the location and max sizes of the crack.

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

REVISION No.: 01 - May 17/11 Page: 1

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SERVICE BULLETIN

Appendix 1

**CONF ALL

YES NO

INSPECTION REPORT

SERVICE BULLETIN No. :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−53−1245

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES4

FUSELAGE (SA/LA) − WINDOWS

INSPECTION METHOD :

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

FAX +33 (0)5 61 93 36 14

CRACK:

SKETCH OF DAMAGE FOUND : DESCRIPTION OF CRACK FOUND :

(USE FIGURE HEREAFTER AND/OR SEND PHOTOS)

N_SB_531245_5_AAAA_01_01

(AFFECTED PARTS, CRACK DIMENSIONS,

CRACK DIRECTION)

Figure A-FAAAA - Sheet 01

Inspection Report

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

REVISION No.: 01 - May 17/11 Page: 2

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Appendix 1

**CONF ALL

Z210 A

A

B

VIEW LOOKING FORWARD

B

CL

INSPECTED AREA

C D

INSPECTION REPORT

N_SB_531245_5_AAAA_02_00

Figure A-FAAAA - Sheet 02

Inspection Report

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

REVISION No.: 01 - May 17/11 Page: 3

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Appendix 1

**CONF ALL

INSPECTED AREA

INSPECTED AREA

C

D

INSPECTION REPORT

N_SB_531245_5_AAAA_03_00

Figure A-FAAAA - Sheet 03

Inspection Report

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245

REVISION No.: 01 - May 17/11 Page: 4

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SERVICE BULLETIN

REPORTING SHEET

TITLE: FUSELAGE - WINDSHIELD CENTRAL LOWER NODE - INSPECT

CRACK IN CONTINUITY FITTINGS AND WINDSHIELD FRAMING

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 02/11 SERVICE BULLETIN No.: A320-53-1245

REVISION No.: 01 - May 17/11 Page: 1

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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 02/11 SERVICE BULLETIN No.: A320-53-1245

REVISION No.: 01 - May 17/11 Page: 1

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