# @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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

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# @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 - 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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN 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
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# @A318/A319/A320/A321 SERVICE BULLETIN 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 REVISION No.: 01 - May 17/11 Page: 3 5

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# @A318/A319/A320/A321 SERVICE BULLETIN 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 5

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# @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 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 REVISION No.: 01 - May 17/11 Page: 1 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

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 REVISION No.: 01 - May 17/11 Page: 2 5

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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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN (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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN 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 REVISION No.: 01 - May 17/11 Page: 5 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
M. SPARES None

DATE: Mar 02/11 SERVICE BULLETIN No.: A320-53-1245 REVISION No.: 01 - May 17/11 Page: 6 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
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 REVISION No.: 01 - May 17/11 Page: 7 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

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 REVISION No.: 01 - May 17/11 Page: 8 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
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

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# @A318/A319/A320/A321 SERVICE BULLETIN

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 REVISION No.: 01 - May 17/11 Page: 10 5

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# @A318/A319/A320/A321 SERVICE BULLETIN (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 REVISION No.: 01 - May 17/11 Page: 11 5

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# @A318/A319/A320/A321 SERVICE BULLETIN (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

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# @A318/A319/A320/A321 SERVICE BULLETIN
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 REVISION No.: 01 - May 17/11 Page: 13 5

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# @A318/A319/A320/A321 SERVICE BULLETIN (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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

. (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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

Z210 

### A



## A **B**

VIEW LOOKING FORWARD 

## B C L

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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

QUESTION ACTION FINDING SEND TO AIRBUS THE INSPECTION REPORT SHEET CRACK FINDING YES 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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

Z210 

### A



## A **B**

VIEW LOOKING FORWARD 

## B C L

1 (1) (1) 1

(2) 

### A

**A A** 

**A B**  **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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

N_SB_531245_5_BEAA_02_00 

## A **A**

**B B**  **NOTE:** APPLY MAT. No. 09−015 01 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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN 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 5

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# @A318/A319/A320/A321 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: DESCRIPTION OF CRACK FOUND : SKETCH OF DAMAGE 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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN Appendix 1

**CONF ALL

Z210 

### A



## A **B**

VIEW LOOKING FORWARD 

## B C L

INSPECTED AREA 

### D

**C 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 5

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# @A318/A319/A320/A321 SERVICE BULLETIN 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 5

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# @A318/A319/A320/A321 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 5

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# @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 02/11 SERVICE BULLETIN No.: A320-53-1245 REVISION No.: 01 - May 17/11 Page: 1 5

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