# @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 - NOSE FORWARD FUSELAGE - INSPECTION OF MISSING FASTENER AND DRILLING AT FR 24 STRG 39 RH SIDE. **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During a customer inspection in Final Assembly Line (FAL), one fastener was found missing at Frame 24, Stringer 39 RH side. The hole of the missing fastener was not drilled. A quality investigation has revealed that a fastener is possibly missing on a batch of in-service aircraft. After checking that the fastener is missing, this Service Bulletin calls for the inspection of the fasteners holes surrounding the missing one at Frame 24 Stringer 39 RH side, installation of oversized fasteners, drilling of the missing hole and installation of the missing fastener. Accomplishment of this Service Bulletin will contribute to ensure the structural integrity of the aircraft. 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.

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 1 5

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# @A318/A319/A320/A321 SERVICE BULLETIN SUMMARY MATERIAL PRICE INFORMATION **CONF 001 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 531242A01R01 1 1,900.00 Bolt, nut, rivet **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 531242A02R01 1 1,904.00 Bolt, nut, rivet EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :

08U 31X 74T AAF AAW ADR AFL AVA BAW BEL CHH CSA CSC CSN DLH EZY FFT GWI IAC LJB ONE PJS SLK TAM TJS 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

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 2 5

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# @A318/A319/A320/A321 SERVICE BULLETIN SUMMARY MANPOWER **CONF 001 Task 531242-832-801-001: Inspection TOTAL MANHOURS 26.00 ELAPSED TIME (HOURS) 26.00 **CONF 002 Task 531242-832-801-001: Inspection TOTAL MANHOURS 26.00 ELAPSED TIME (HOURS) 26.00 APPENDICES **CONF ALL Appendix 01 - Inspection Report

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 3 5

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

**CONF ALL

Z130 

### A FR24 FR34



## A ZONE TO BE INSPECTED

**F W**  **D** 

## B **B**

FR24 STGR39

N_SB_531242_5_SAAA_01_00 Figure A-F SAAA - S heet 01
DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 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 - NOSE FORWARD FUSELAGE - INSPECTION OF MISSING FASTENER AND DRILLING AT FR 24 STRG 39 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 318-112 319-111 319-112 319-115 319-132 319-133 (2) Effectivity by MSN 3983 3985 3998 4000 4004 4007 4018 4020 4029 4036 4038-4040 4048 4052 4056 4069 4071 4076 4080 4087 4089 4121 4125 4127 4129 4132 4141 4151 4163-4164 4166 4169 4171 4182 4192 4200 4204 4211 4215 4222 4227-4228 4254 4256 4258-4259 4262 4268 4275 4282 4285 4287 4301 4313 4319 4327 4332 4336 (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 08U 4151 31X 4319 74T 4228 AAF 4268 DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 1 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
OPERATOR MSN AAW 4004 ADR 4282 4301 AFL 3998 AVA 4200 BAW 4007 4039 BEL 4275 CHH 4262 CSA 4258 CSC 4018 CSN 3983 4036 4038 4071 DLH 4141 4182 4332 EZY 4040 4048 4056 4069 4076 4080 4087 4125 4129 4132 4313 4327 FFT 4127 4204 4254 GWI 4166 4227 4256 4285 IAC 4020 4029 4052 4089 4121 4164 LJB 3985 ONE 4222 4287 4336 PJS 4211 SLK 4215 4259 TAM 4000 4163 4171 4192 TJS 4169 (4) Configuration by MSN MSN CONFIGURATION 3983 3998 4000 4004 4018 4020 4029 4036 4038 4040 4048 4052 4056 4069 4071 4076 4080 4087 4089 4121 4125 4127 4129 4132 4141 4151 4163 4164 4166 4171 4182 4192 4200 4204 4215 4222 4227 4228 4254 4256 4258 4259 4262 4268 4275 4282 4285 4287 4301 4313 4319 4327 4332 4336 001

3985 4007 4039 4169 4211 002 (5) Configuration definition **CONF 001 Config. 001 is valid for A319 aircraft. **CONF 002 Config. 002 is valid for A318 aircraft. (6) Material Effectivity **CONF 001 MATERIAL QTY PER A/C SEE NOTES Kit 531242A01R01 1 Consumable CMLA01 1
DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 2 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
**CONF 002 MATERIAL QTY PER A/C SEE NOTES Kit 531242A02R01 1 Consumable CMLA01 1 **CONF ALL B. CONCURRENT REQUIREMENTS None C. REASON (1) History During a customer inspection in Final Assembly Line (FAL), one fastener was found missing at Frame 24, Stringer 39 RH side. The hole of the missing fastener was not drilled.A quality investigation has revealed that a fastener is possibly missing on a batch of inservice aircraft. (2) Objective/Action After checking that the fastener is missing, this Service Bulletin calls for the inspection of the fasteners holes surrounding the missing one at Frame 24 Stringer 39 RH side, installation of oversized fasteners, drilling of the missing hole and installation of the missing fastener. (3) Advantages Accomplishment of this Service Bulletin will contribute to ensure the structural integrity of the aircraft. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 531242-832-801-001: Inspection (1) Do a Detailed Inspection for the missing fastener at nose forward fuselage at Fr 24 Strg 39 (RH Side) (2) Remove the 5 surrounding fasteners at frame 24 stringer 39
DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 3 5

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# @A318/A319/A320/A321 SERVICE BULLETIN (3) Do the inspection of the 5 holes of the removed fasteners (4) Drill one hole in the structure and the fitting and install the new fasteners in the inspected holes **CONF 002 Task 531242-832-801-001: Inspection (1) Do a Detailed Inspection for the missing fastener at nose forward fuselage at Fr 24 Strg 39 (RH Side) (2) Remove the 5 surrounding fasteners at frame 24 stringer 39 (3) Do the inspection of the 5 holes of the removed fasteners (4) Drill one hole in the structure and the fitting and install the new fasteners in the inspected holes **CONF ALL E. COMPLIANCE (1) Classification RECOMMENDED: Service Bulletin recommended to be accomplished to prevent significant operational disruptions. (2) Accomplishment Timescale Accomplishment of this Service Bulletin is recommended: - Before accumulation of 5,000FC (Flight Cycles) since first flight for A319 and A318 PRE-MOD 39195 or within 4,300FC from SB issue date whichever occurs later. - Before accumulation of 3,000FC since first flight for A318 POST-MOD 39195 (Elite) or A318 POST SB A320-00-1219.- Before accumulation of 2,500FC since first flight for A319 operated as CJ (POSTMOD 28238 , 28162 and 28342). Accomplishment of this Service Bulletin is expected to be rendered mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency ( EASA). It is antici pated that the AD will confirm the (thresholds and/or intervals and/or date) given above but reference should be made to the AD for confirmation of the mandated accomplishment timescale. F. APPROVAL Approved under EASA Design Organiza tion Approval No. EASA 21J.031.

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 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. **CONF 001 Task 531242-832-801-001: Inspection Get Access 3.00 On Aircraft Do a Detailed Inspection for the missing fastener at nose forward fuselage at Fr 24 Strg 39 (RH Side) 6.00 Remove the 5 surrounding fasteners at frame 24 stringer 39 0.50 Do the inspection of the 5 holes of the removed fasteners 1.50 Drill one hole in the structure and the fitting and install the new fasteners in the inspected holes 1.25 Close-Up 13.75 TOTAL MANHOURS 26.00 ELAPSED TIME (HOURS) 26.00 NOTE : Operators have to consider as a maximum 3.00 hours of Get Access in case that the fastener is not missing. Operators have to consider as a maximum 9.00 hours of Get Access in case that the fastener is missing. **CONF 002 Task 531242-832-801-001: Inspection Get Access 3.00 On Aircraft Do a Detailed Inspection for the missing fastener at nose forward fuselage at Fr 24 Strg 39 (RH Side) 6.00 Remove the 5 surrounding fasteners at frame 24 stringer 39 0.50 Do the inspection of the 5 holes of the removed fasteners 1.50 Drill one hole in the structure and the fitting and install the new fasteners in the inspected holes 1.25 DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 5 5

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# @A318/A319/A320/A321 SERVICE BULLETIN Task 531242-832-801-001: Inspection Close-Up 13.75 TOTAL MANHOURS 26.00 ELAPSED TIME (HOURS) 26.00 NOTE : Operators have to consider as a maximum 3.00 hours of Get Access in case that the fastener is not missing. Operators have to consider as a maximum 9.00 hours of Get Access in case that the fastener is missing. **CONF ALL H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-53 25-54-11 52-30-00 53-12-14 53-22-14 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 Service Bulletin (SB) A320-00-1219 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-24-12 51-42-00 51-42-11 51-43-00 51-44-00 51-46-00 51-47-00 51-75-12 **CONF 002 Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-53 25-54-11 52-30-00 53-12-14 53-22-14 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 Service Bulletin (SB) A320-00-1219 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-24-12 51-42-00 51-42-11 51-43-00 51-44-00 51-46-00 51-47-00 51-75-12
DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 6 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
**CONF ALL K. PUBLICATION AFFECTED None L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 7 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

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DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 8 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses 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: Kit 531242A01R01 Kit 531242A02R01 AIRBUS Material, Logistics and Suppliers Weg beim Jaeger 150 D-22335 Hamburg GERMANY For ordering by internet: http://spares.airbus.com For ordering by fax: +49 40 50 76 25 90 For ordering by E-mail: airbus.kit@airbus.com (2) Price and Availability

Kit 531242A01R01 Cost 1,900.00 USD Availability 90 calendar days from receipt of order Kit 531242A02R01 Cost 1,904.00 USD Availability 90 calendar days from receipt of order The Kit availability given above is the standard lead time from the date of your purchase order. If you require Kits before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions at the issue date of the Service Bulletin. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. B. INDUSTRY SUPPORT INFORMATION AIRBUS will not provide industry support for accomplishment of this Service Bulletin. C. LIST OF COMPONENTS Kit 531242A01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 3 ASNA2528-3 30 Nut 8 NSA5057-4 5 Nut 13 ASNA2049DXJ4820 3 Rivet DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 9 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 14 EN6114V3-7 1 Bolt 15 ASNA2050DXJ4820 2 Rivet 16 EN6114V3X7 5 Bolt 17 EN6115V3X4 19 Bolt 18 EN6114V3X5 2 Bolt 19 EN6114V4X9 9 Bolt 30 ASNA2528-4 9 Nut 41 EN6115V3X6 1 Bolt 60 EN6114V3X3 1 Bolt 70 EN6114V3X4 1 Bolt 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 531242A02R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 3 ASNA2528-3 31 Nut 8 NSA5057-4 5 Nut 13 ASNA2049DXJ4820 3 Rivet 14 EN6114V3-7 1 Bolt 15 ASNA2050DXJ4820 2 Rivet 16 EN6114V3X7 6 Bolt 17 EN6115V3X4 19 Bolt 18 EN6114V3X5 2 Bolt 19 EN6114V4X9 8 Bolt 30 ASNA2528-4 8 Nut 41 EN6115V3X6 1 Bolt 60 EN6114V3X3 1 Bolt 70 EN6114V3X4 1 Bolt 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 DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 10 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Corrosion Inhibitingfillet Consistency 09-016 As required Cleaning Solvent 11-003 As required Cleaning Solvent 11-010 As required Cleaning Solvent 11-016 As required Cleaning Solvent 11-026 As required Corrosion Preventive temporary Protective compound 15-007 As required Anti-Corrosion Primer 16-001 As required Polyurethane Finish Paint 16-018 As required Flexible Polyurethane 16-021 As required (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING None

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 11 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

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DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 12 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 531242-832-801-001 - 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. IF THERE IS CONTAMINATION, ESPM 20-55-00. Task Associated Data **CONF 001 Zone 130 Modified FIN 131AF 131CW 132GG 132MF 131PG Manpower TOTAL MANHOURS 26.00 ELAPSED TIME (HOURS) 26.00 **CONF 002 Zone 130 Modified FIN 131AF 131CW 132GG 132MF 131PG Manpower TOTAL MANHOURS 26.00 ELAPSED TIME (HOURS) 26.00

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 13 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
**CONF ALL A. GENERAL **CONF 001 (1) Subtask 531242-910-002-001 - 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-Brush Consistency 09-013 As required Corrosion Inhibitingfillet Consistency 09-016 As required Corrosion Preventive temporary Protective compound 15-007
Anti-Corrosion Primer 16-001 As required Polyurethane Finish Paint 16-018 As required References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-24-12 51-42-00 51-42-11 51-43-00 51-44-00 51-46-00 51-47-00 51-75-12 (a) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001). (b) For the identification of the Zones (Refer to AMM 06-20-00, Page Block 001). (c) Remove and install the fasteners (Refer to SRM 51-42-11). (d) For the alternative and substitute fasteners (Refer to SRM 51-43-00). (e) Drill and deburr the holes (Refer to SRM 51-44-00). (f) For the space and margin of the fasteners (Refer to SRM 51-47-00). DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 14 5

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# @A318/A319/A320/A321 SERVICE BULLETIN (g) Apply the sealant (Refer to SRM 51-24-00). (h) For the specification of the material numbers (Mat No.), refer to CML. (i) Repair of the paint coating (Refer to SRM 51-75-12). (j) For the countersinking (Refer to SRM 51-46-00). (k) During the installation of the fasteners apply: Sealant-Brush Consistency 09-013 As required (l) After the installation of the fasteners apply: Anti-Corrosion Primer 16-001 As required Polyurethane Finish Paint 16-018 As required (m) Between the fitting and the structure, apply: Corrosion Inhibitingfillet Consistency 09-016 As required
(n) Perform reprotection of the reworked areas as per SRM 51-24-12. (o) Perform protection of reworked areas with: Corrosion Preventive temporary Protective compound 15-007 As required

(2) Subtask 531242-839-003-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 002 (1) Subtask 531242-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 15 5

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# @A318/A319/A320/A321 SERVICE BULLETIN Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required Corrosion Inhibitingfillet Consistency 09-016 As required Corrosion Preventive temporary Protective compound 15-007
Anti-Corrosion Primer 16-001 As required Polyurethane Finish Paint 16-018 As required References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-24-12 51-42-00 51-42-11 51-43-00 51-44-00 51-46-00 51-47-00 51-75-12 (a) For the Frame (FR) identification (Refer to AMM 06-31-53, Page Block 001). (b) For the identification of the Zones (Refer to AMM 06-20-00, Page Block 001). (c) Remove and install the fasteners (Refer to SRM 51-42-11). (d) For the alternative and substitute fasteners (Refer to SRM 51-43-00). (e) Drill and deburr the holes (Refer to SRM 51-44-00). (f) For the space and margin of the fasteners (Refer to SRM 51-47-00). (g) Apply the sealant (Refer to SRM 51-24-00). (h) For the specification of the material numbers (Mat No.), refer to CML. (i) Repair of the paint coating (Refer to SRM 51-75-12). (j) For the countersinking (Refer to SRM 51-46-00).

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 16 5

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# @A318/A319/A320/A321 SERVICE BULLETIN (k) During the installation of the fasteners apply: Sealant-Brush Consistency 09-013 As required (l) After the installation of the fasteners apply: Anti-Corrosion Primer 16-001 As required Polyurethane Finish Paint 16-018 As required (m) Between the fitting and the structure, apply: Corrosion Inhibitingfillet Consistency 09-016 As required
(n) Perform reprotection of the reworked areas as per SRM 51-24-12. (o) Perform protection of reworked areas with: Corrosion Preventive temporary Protective compound 15-007 As required

(2) Subtask 531242-839-003-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 531242-941-002-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 130 Manpower Resources Skills NON SPECIFIC
DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 17 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001 Task 25-54-11-000-001 Task 52-30-00-860-001 Task 53-22-14-000-001 Fig. A-FBDAA Removal and Installation of the Fitting Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FBEAA Removal and installation of the sealant Sheet 01 Sheet 02 (a) Put access platform(s) in position. (b) Open the forward cargo door 825AR (Refer to AMM Task 52-30-00-860-001). (c) Remove the FWD cargo-compartment panel FIN 131CW (Refer to AMM 06-41-53, Page Block 001 and AMM Task 25-54-11-000-001). (d) If the fastener is missing, remove the panels FIN 131AF or FIN 131PG or FIN 132GG or FIN 132MF (Refer to AMM Task 53-22-14-000-001 and AMM 06-41-53, Page Block 001). **CONF 002 (1) Subtask 531242-941-002-002 - Job Set-up Work Zones and Access Panels Zone Access/Work location 130 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001 Task 25-54-11-000-001 Task 52-30-00-860-001 Task 53-22-14-000-001 Fig. A-FBEAA Removal and installation of the sealant Sheet 01 Sheet 02 Fig. A-FBDAB Removal and Installation of the Fitting Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Put access platform(s) in position. (b) Open the forward cargo door 825AR (Refer to AMM Task 52-30-00-860-001). DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 18 5

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# @A318/A319/A320/A321 SERVICE BULLETIN (c) Remove the FWD cargo-compartment panel FIN 131CW (Refer to AMM 06-41-53, Page Block 001 and AMM Task 25-54-11-000-001). (d) If the fastener is missing, remove the panels FIN 131AF or FIN 131PG or FIN 132GG or FIN 132MF (Refer to AMM Task 53-22-14-000-001 and AMM 06-41-53, Page Block 001). **CONF ALL C. PROCEDURE 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 fasteners grip length in accordance with SRM Chapter 51. **CONF 001 (1) Subtask 531242-832-001-001 - Do a Detailed Inspection for the missing fastener at nose forward fuselage at Fr 24 Strg 39 (RH Side) Manpower Resources Manhours 6.00 Minimum number of person 1 Subtask elapsed time 6.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Cleaning Solvent 11-003 Cleaning Solvent 11-010 Cleaning Solvent 11-016 Cleaning Solvent 11-026 References Consumable Material List (CML) Fig. A-FBEAA Removal and installation of the sealant Sheet 01 Sheet 02 Fig. A-FBDAA Removal and Installation of the Fitting Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 19 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
References Fig. A-FBAAA Inspection of the surrounding holes and area to be inspected Sheet 01 Sheet 02 Sheet 03 Fig. A-FFAAA Flow Chart Sheet 01 (a) At the threshold given in the planning information paragraph E.(2): 1 Do a detailed inspection for the missing fastener at nose forward fuselage at Frame 24 string 39 (RH Side). Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 02 , Fig. A-FBAAA Sheet 03 and Fig. A-FFAAA Sheet 01 2 If the fastener is missing:
a Remove the sealant from the lower area of the cargo door. <1> Remove: Refer to Fig. A-FBEAA Sheet 01 Flexible Polyurethane 16-021 Corrosion Inhibiting fillet Consistency 09-016
with: Cleaning Solvent 11-016 As required or Cleaning Solvent 11-003 As required or Cleaning Solvent 11-010 As required or Cleaning Solvent 11-026 As required b Remove fitting for access Refer to Fig. A-FBDAA Sheet 01 thru Fig. A-FBDAA Sheet 05 <1> Remove: 1 Fitting Item (40) Retain attached with:
DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 20 5

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# @A318/A319/A320/A321 SERVICE BULLETIN 2 Rivet ASNA2050DEJ4020 Item (1) Discard 4 Bolt ASNA2026V3-7 Item (2) Discard 4 Nut ASNA2528-3 Item (3) Discard 19 Bolt ASNA2027V3-4 Item (4) Discard 1 Bolt ASNA2027V3-6 Item (100) Discard 20 Nut ASNA2528-3 Item (3) Discard 2 Bolt ASNA2026V3-5 Item (5) Discard 2 Nut ASNA2528-3 Item (3) Discard 1 Bolt ASNA2026V3-7 Item (2) Discard 1 Nut ASNA2528-3 Item (3) Discard 9 Bolt ASNA2026V4-9 Item (6) Discard 9 Nut ASNA2528-4 Item (30) Discard 2 Bolt MS21250-04006 Item (7) Retain 2 Nut NSA5057-4 Item (8) Discard 3 Bolt MS21250-04004 Item (9) Retain 3 Nut NSA5057-4 Item (8) Discard NOTE : The removal of this fitting will allow the access to the modification zone.
c Do SUBTASK 531242-020-002 001 Remove the 5 surrounding fasteners at frame 24 stringer 39 . d Do SUBTASK 531242-220-001 001 Do the inspection of the 5 holes of the removed fasteners . 3 If the fastener is not missing, no further action is needed. 4 Send Inspection Report to Airbus.

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 21 5

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# @A318/A319/A320/A321 SERVICE BULLETIN (2) Subtask 531242-020-002- 001 - Remove the 5 surrounding fasteners at frame 24 stringer 39 Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 24 to Frame 24A Stringer 39 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Fig. A-FBAAA Inspection of the surrounding holes and area to be inspected Sheet 01 Sheet 02 Sheet 03 (a) Remove: Refer to Fig. A-FBAAA Sheet 01 thru Fig. A-FBAAA Sheet 03 3 Rivet ASNA2049DXJ4020 Item (10) Discard 1 Rivet EN6100P040A040G Item (11) Discard 1 Rivet EN6100P040A030G Item (50) Discard 2 Collar EN6051-040A Item (12) Discard

(3) Subtask 531242-220-001-001 - Do the inspection of the 5 holes of the removed fasteners Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 24 to Frame 24A Stringer 39 Manpower Resources Manhours 1.50 Minimum number of person 1 Subtask elapsed time 1.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 22 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
References Fig. A-FBAAA Inspection of the surrounding holes and area to be inspected Sheet 01 Sheet 02 Sheet 03 Fig. A-FFAAA Flow Chart Sheet 01 (a) Do a check of the 5 hole diameters of the removed fasteners. Fig. A-FBAAA Sheet 03 for diameter values. 1 If the diameter is not correct, contact AIRBUS and apply corrective action before next flight. 2 If the diameter is correct, do the following instructions:
a For the inspection area, Fig. A-FBAAA Sheet 01 thru Fig. A-FBAAA Sheet 03

. b Do a rototest inspection of the 5 holes of the removed fasteners as per NTM 51-10-01 part 6 procedure A, refer to Fig. A-FFAAA Sheet 01

. <1> If crack found, contact AIRBUS and apply corrective action before next flight. <2> If no crack found, do SUBTASK 531242-420-003 001 Drill one hole in the structure and the fitting and install the new fasteners in the inspected holes .
c For the inspection report, refer to Appendix 01 - Inspection Report . (4) Subtask 531242-420-003-001 - Drill one hole in the structure and the fitting and install the new fasteners in the inspected holes Work Zones and Access Panels Zone Access/Work location 130 Manpower Resources Manhours 1.25 Minimum number of person 1 Subtask elapsed time 1.25 Skills AIRFRAME Material necessary to do the job Kit 531242A01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 ASNA2528-3 2 Nut 13 ASNA2049DXJ4820 3 Rivet 60 EN6114V3X3 1 Bolt DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 23 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 70 EN6114V3X4 1 Bolt References Fig. A-FBCAA Installation of the fasteners Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Oversize the 5 inspected holes on the structure at FR24, STGR39 to the dimensions given in Fig. A-FBCAA Sheet 03

. (b) Drill 1 hole on the structure at FR24, STGR39 to the dimensions given in Fig. AFBCAA Sheet 03

. NOTE : Drill the hole from the outside of the aircraft. (c) Temporarily put the fitting Item (40) in position. (d) Counterdrill one hole in the fitting Item (40). (e) Remove the fitting Item (40) and deburr the hole. (f) Wet install with sealant: 3 Rivet ASNA2049DXJ4820 Item 13 1 Bolt EN6114V3X3 Item 60 1 Bolt EN6114V3X4 Item 70 2 Nut ASNA2528-3 Item 3 **CONF 002 (1) Subtask 531242-832-001-002 - Do a Detailed Inspection for the missing fastener at nose forward fuselage at Fr 24 Strg 39 (RH Side) Manpower Resources Manhours 6.00 Minimum number of person 1 Subtask elapsed time 6.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Cleaning Solvent 11-003 DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 24 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Cleaning Solvent 11-010 Cleaning Solvent 11-016 Cleaning Solvent 11-026 References Consumable Material List (CML) Fig. A-FBEAA Removal and installation of the sealant Sheet 01 Sheet 02 Fig. A-FBDAB Removal and Installation of the Fitting Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FBAAA Inspection of the surrounding holes and area to be inspected Sheet 01 Sheet 02 Sheet 03 Fig. A-FFAAB Flow Chart Sheet 01 (a) At the threshold given in the planning information paragraph E.(2): 1 Do a detailed inspection for the missing fastener at nose forward fuselage at Frame 24 string 39 (RH Side). Refer to Fig. A-FBAAA Sheet 01 , Fig. A-FBAAA Sheet 02 , Fig. A-FBAAA Sheet 03 and Fig. A-FFAAB Sheet 01 2 If the fastener is missing:
a Remove the sealant from the lower area of the cargo door. <1> Remove: Refer to Fig. A-FBEAA Sheet 01 Flexible Polyurethane 16-021 Corrosion Inhibiting fillet Consistency 09-016
with: Cleaning Solvent 11-016 As required or Cleaning Solvent 11-003 As required or DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 25 5

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# @A318/A319/A320/A321 SERVICE BULLETIN Cleaning Solvent 11-010 As required or Cleaning Solvent 11-026 As required b Remove fitting for access Fig. A-FBDAB Sheet 01 thru Fig. A-FBDAB Sheet 05 <1> Remove: 1 Fitting Item (40) Retain attached with: 2 Rivet ASNA2050DEJ4020 Item (1) Discard 4 Bolt ASNA2026V3-7 Item (2) Discard 4 Nut ASNA2528-3 Item (3) Discard 19 Bolt ASNA2027V3-4 Item (4) Discard 1 Bolt ASNA2027V3-6 Item (100) Discard 20 Nut ASNA2528-3 Item (3) Discard 2 Bolt ASNA2026V3-5 Item (5) Discard 2 Nut ASNA2528-3 Item (3) Discard 1 Bolt ASNA2026V3-7 Item (2) Discard 1 Nut ASNA2528-3 Item (3) Discard 8 Bolt ASNA2026V4-9 Item (6) Discard 8 Nut ASNA2528-4 Item (30) Discard 1 Bolt EN6114V3-7 Item (14) Discard 1 Nut ASNA2528-3 Item (3) Discard 2 Bolt MS21250-04006 Item (7) Retain 2 Nut NSA5057-4 Item (8) Discard 3 Bolt MS21250-04004 Item (9) Retain DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 26 5

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# @A318/A319/A320/A321 SERVICE BULLETIN 3 Nut NSA5057-4 Item (8) Discard NOTE : The removal of this fitting will allow the access to the modification zone.
c Do SUBTASK 531242-020-002 002 Remove the 5 surrounding fasteners at frame 24 stringer 39 . d Do SUBTASK 531242-220-001 003 Do the inspection of the 5 holes of the removed fasteners . 3 If the fastener is not missing, no further action is needed. 4 Send Inspection Report to Airbus. (2) Subtask 531242-020-002- 002 - Remove the 5 surrounding fasteners at frame 24 stringer 39 Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 24 to Frame 24A Stringer 39 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME References Fig. A-FBAAA Inspection of the surrounding holes and area to be inspected Sheet 01 Sheet 02 Sheet 03 (a) Remove: Refer to Fig. A-FBAAA Sheet 01 thru Fig. A-FBAAA Sheet 03 3 Rivet ASNA2049DXJ4020 Item (10) Discard 1 Rivet EN6100P040A040G Item (11) Discard 1 Rivet EN6100P040A030G Item (50) Discard 2 Collar EN6051-040A Item (12) Discard

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 27 5

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# @A318/A319/A320/A321 SERVICE BULLETIN (3) Subtask 531242-220-001-003 - Do the inspection of the 5 holes of the removed fasteners Work Zones and Access Panels Zone Access/Work location 130 Work location from Frame 24 to Frame 24A Stringer 39 Manpower Resources Manhours 1.50 Minimum number of person 1 Subtask elapsed time 1.50 Skills AIRFRAME References Non Destructive Test Manual (NTM) 51-10-01 Fig. A-FBAAA Inspection of the surrounding holes and area to be inspected Sheet 01 Sheet 02 Sheet 03 Fig. A-FFAAB Flow Chart Sheet 01 (a) Do a check of the 5 hole diameters of the removed fasteners. Fig. A-FBAAA Sheet 03 for diameter values. 1 If the diameter is not correct, contact AIRBUS and apply corrective action before next flight. 2 If the diameter is correct, do the following instructions:
a For the inspection area, Fig. A-FBAAA Sheet 01 thru Fig. A-FBAAA Sheet 03

. b Do a rototest inspection of the 5 holes of the removed fasteners as per NTM 51-10-01 part 6 procedure A, refer to Fig. A-FFAAB Sheet 01

. <1> If crack found, contact AIRBUS and apply corrective action before next flight. <2> If no crack found, do SUBTASK 531242-420-003 002 Drill one hole in the structure and the fitting and install the new fasteners in the inspected holes .
c For the inspection report, refer to Appendix 01 - Inspection Report . (4) Subtask 531242-420-003-002 - Drill one hole in the structure and the fitting and install the new fasteners in the inspected holes Work Zones and Access Panels Zone Access/Work location 130 DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 28 5

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# @A318/A319/A320/A321 SERVICE BULLETIN Manpower Resources Manhours 1.25 Minimum number of person 1 Subtask elapsed time 1.25 Skills AIRFRAME Material necessary to do the job Kit 531242A02R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 ASNA2528-3 2 Nut 13 ASNA2049DXJ4820 3 Rivet 60 EN6114V3X3 1 Bolt 70 EN6114V3X4 1 Bolt References Fig. A-FBCAA Installation of the fasteners Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Oversize the 5 inspected holes on the structure at FR24, STGR39 to the dimensions given in Fig. A-FBCAA Sheet 03

. (b) Drill 1 hole on the structure at FR24, STGR39 to the dimensions given in Fig. AFBCAA Sheet 03

. NOTE : Drill the hole from the outside of the aircraft. (c) Temporarily put the fitting Item (40) in position. (d) Counterdrill one hole in the fitting Item (40). (e) Remove the fitting Item (40) and deburr the hole. (f) Wet install with sealant: 3 Rivet ASNA2049DXJ4820 Item 13 1 Bolt EN6114V3X3 Item 60 1 Bolt EN6114V3X4 Item 70 2 Nut ASNA2528-3 Item 3

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 29 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
**CONF ALL D. TEST **CONF 001 None **CONF 002 None **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 531242-010-001-001 - Install items removed for access (Only necessary when the fastener was missing) Manpower Resources Skills AIRFRAME Material necessary to do the job Kit 531242A01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 ASNA2528-3 28 Nut 8 NSA5057-4 5 Nut 14 EN6114V3-7 1 Bolt 15 ASNA2050DXJ4820 2 Rivet 16 EN6114V3X7 5 Bolt 17 EN6115V3X4 19 Bolt 18 EN6114V3X5 2 Bolt 19 EN6114V4X9 9 Bolt 30 ASNA2528-4 9 Nut 41 EN6115V3X6 1 Bolt Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Corrosion Inhibiting fillet Consistency 09-016 As required Flexible Polyurethane 16-021 As required References Consumable Material List (CML)
DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 30 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
References Fig. A-FBCAA Installation of the fasteners Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FBEAA Removal and installation of the sealant Sheet 01 Sheet 02 Fig. A-FBDAA Removal and Installation of the Fitting Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Install the removed fitting and the missing fastener. 1 Temporarily put in position the fitting Item (40). 2 Oversize the 38 holes on the structure and the fitting between FR24 and FR25, STGR39 to the dimensions given in Fig. A-FBDAA Sheet 05

. 3 Remove the fitting Item (40) and deburr the holes. 4 Wet install with sealant: 1 Fitting Item (40) Retained at removal attached with 2 Rivet ASNA2050DXJ4820 Item 15 4 Bolt EN6114V3X7 Item 16 4 Nut ASNA2528-3 Item 3 19 Bolt EN6115V3X4 Item 17 1 Bolt EN6115V3X6 Item 41 20 Nut ASNA2528-3 Item 3 2 Bolt EN6114V3X5 Item 18 2 Nut ASNA2528-3 Item 3 1 Bolt EN6114V3X7 Item 16 1 Nut ASNA2528-3 Item 3 9 Bolt EN6114V4X9 Item 19 9 Nut ASNA2528-4 Item 30 DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 31 5

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# @A318/A319/A320/A321 SERVICE BULLETIN 2 Bolt MS21250-04006 Item (7) Retained at removal 2 Nut NSA5057-4 Item 8 3 Bolt MS21250-04004 Item (9) Retained at removal 3 Nut NSA5057-4 Item 8 5 Install the missing fastener: Fig. A-FBCAA Sheet 03 1 Bolt EN6114V3-7 Item 14 1 Nut ASNA2528-3 Item 3 (b) Install the sealant on the lower area of the cargo door. 1 Apply sealant on the lower area of the cargo door: Fig. A-FBEAA Sheet 01 and Fig. A-FBEAA Sheet 02
a Do a block of: Corrosion Inhibiting fillet Consistency 09-016 As required at dimensions given in Fig. A-FBEAA Sheet 02 and make it dry out. b Over the block already cured, apply (Refer to Fig. A-FBEAA Sheet 02 ): Corrosion Inhibiting fillet Consistency 09-016 As required

c Do the protection with: Flexible Polyurethane 16-021 As required (c) Make sure that the work areas are clean and clear of tools and other items of equipment. (2) Subtask 531242-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 32 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001 Task 25-54-11-400-001 Task 52-30-00-860-002 Task 53-12-14-400-001 Fig. A-FBDAA Removal and Installation of the Fitting Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FBEAA Removal and installation of the sealant Sheet 01 Sheet 02 Fig. A-FBCAA Installation of the fasteners Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Install the FWD cargo-compartment panel FIN 131CW (Refer to AMM 06-41-53, Page Block 001 and AMM Task 25-54-11-400-001). (b) Install the panels FIN 131AF or FIN 131PG or FIN 132GG or FIN 132MF (Refer to AMM Task 53-12-14-400-001). (c) Close the forward cargo-compartment door 825AR (Refer to AMM Task 52-30-00-860-002). (d) Remove the access platform(s). **CONF 002 (1) Subtask 531242-010-001-002 - Install items removed for access (Only necessary when the fastener was missing) Manpower Resources Skills AIRFRAME Material necessary to do the job Kit 531242A02R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 ASNA2528-3 29 Nut 8 NSA5057-4 5 Nut 14 EN6114V3-7 1 Bolt 15 ASNA2050DXJ4820 2 Rivet 16 EN6114V3X7 6 Bolt 17 EN6115V3X4 19 Bolt 18 EN6114V3X5 2 Bolt 19 EN6114V4X9 8 Bolt 30 ASNA2528-4 8 Nut 41 EN6115V3X6 1 Bolt DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 33 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Corrosion Inhibiting fillet Consistency 09-016 As required Flexible Polyurethane 16-021 As required References Consumable Material List (CML) Fig. A-FBCAA Installation of the fasteners Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FBEAA Removal and installation of the sealant Sheet 01 Sheet 02 Fig. A-FBDAB Removal and Installation of the Fitting Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 (a) Install the removed fitting and the missing fastener. 1 Temporarily put in position the fitting Item (40). 2 Oversize the 38 holes on the structure and the fitting between FR24 and FR25, STGR39 to the dimensions given in Fig. A-FBDAB Sheet 05

. 3 Remove the fitting Item (40) and deburr the holes. 4 Wet install with sealant: 1 Fitting Item (40) Retained at removal attached with 2 Rivet ASNA2050DXJ4820 Item 15 4 Bolt EN6114V3X7 Item 16 4 Nut ASNA2528-3 Item 3 19 Bolt EN6115V3X4 Item 17 1 Bolt EN6115V3X6 Item 41 20 Nut ASNA2528-3 Item 3 2 Bolt EN6114V3X5 Item 18 2 Nut ASNA2528-3 Item 3 DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 34 5

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# @A318/A319/A320/A321 SERVICE BULLETIN
1 Bolt EN6114V3X7 Item 16 1 Nut ASNA2528-3 Item 3 8 Bolt EN6114V4X9 Item 19 8 Nut ASNA2528-4 Item 30 1 Bolt EN6114V3X7 Item 16 1 Nut ASNA2528-3 Item 3 2 Bolt MS21250-04006 Item (7) Retained at removal 2 Nut NSA5057-4 Item 8 3 Bolt MS21250-04004 Item (9) Retained at removal 3 Nut NSA5057-4 Item 8 5 Install the missing fastener: Fig. A-FBCAA Sheet 03 1 Bolt EN6114V3-7 Item 14 1 Nut ASNA2528-3 Item 3 (b) Install the sealant on the lower area of the cargo door. 1 Apply sealant on the lower area of the cargo door: Fig. A-FBEAA Sheet 01 and Fig. A-FBEAA Sheet 02
a Do a block of: Corrosion Inhibiting fillet Consistency 09-016 As required at dimensions given in Fig. A-FBEAA Sheet 02 and make it dry out. b Over the block already cured, apply (Refer to Fig. A-FBEAA Sheet 02 ): Corrosion Inhibiting fillet Consistency 09-016 As required

c Do the protection with: Flexible Polyurethane 16-021 As required
DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 35 5

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# @A318/A319/A320/A321 SERVICE BULLETIN (c) Make sure that the work areas are clean and clear of tools and other items of equipment. (2) Subtask 531242-942-002-002 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-41-53, Page Block 001 Task 25-54-11-400-001 Task 52-30-00-860-002 Task 53-12-14-400-001 Fig. A-FBDAB Removal and Installation of the Fitting Sheet 01 Sheet 02 Sheet 03 Sheet 04 Sheet 05 Fig. A-FBEAA Removal and installation of the sealant Sheet 01 Sheet 02 Fig. A-FBCAA Installation of the fasteners Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Install the FWD cargo-compartment panel FIN 131CW (Refer to AMM 06-41-53, Page Block 001 and AMM Task 25-54-11-400-001). (b) Install the panels FIN 131AF or FIN 131PG or FIN 132GG or FIN 132MF (Refer to AMM Task 53-12-14-400-001). (c) Close the forward cargo-compartment door 825AR (Refer to AMM Task 52-30-00-860-002). (d) Remove the access platform(s).

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 36 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL
FR24 FR26 FR35 FR29



### A



## A FR24A



### B

N_SB_531242_5_BEAA_01_03 Figure A-F BEAA - S heet 01 Removal and installation of the sealant DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 37 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

131 mm (5.16 in)

MIN 40 mm MIN (1.57 in) 30 mm (1.18 in)

VIEW LOOKING FORWARD **F W**  **D** 01

01 02 02

BLOCK OF MAT. No. 09−016 01 APPLY MAT. No. 09−016 OVER THE BLOCK 02 **NOTES:**
AND PROTECT WITH MAT. No; 16.021 ALREADY CURED 

## B

**A A**  FR24

95 mm (3.74 in) 95 mm (3.74 in)



### A **A**

N_SB_531242_5_BEAA_02_00 Figure A-F BEAA - S heet 02 Removal and installation of the sealant DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 38 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

Z130 

### A FR24 FR34



### B



## A

**C**



## B N_SB_531242_5_BDAA_01_00 Figure A-FBDAA - Sheet 01 Removal and Installation of the Fitting DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 39 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

FASTENERS TO BE REMOVED FASTENERS TO BE REMOVED 

### F

**E D** 

**G H**  STGR39

FR24



## C

**D E**  **J F**  **W D** 

**FWD FWD**  N_SB_531242_5_BDAA_02_01 FR24A FR24A

Figure A-FBDAA - Sheet 02 Removal and Installation of the Fitting DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 40 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001 FR24 FR24A FR25

FR24 FR24A FR24 FR24A 

## F

**G H**  **FWD**

**FWD**
**FWD**



## J (40) FITTING 

### L **K**

**NOTES:** DURING THE FASTENERS INSTALLATION APPLY MATSET No. 09−013. AFTER THE INSTALLATION OF THE FASTENERS APPLY MATSET No. 16−001 AND 16−018. BETWEEN THE FITTING AND THE STRUCTURE APPLY MATSET No. 09−016. N_SB_531242_5_BDAA_03_05 Figure A-FBDAA - Sheet 03 Removal and Installation of the Fitting DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 41 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

FR24A FR25

FR24A

**FWD FWD**  

## K

**L**

**NOTES:** DURING THE FASTENERS INSTALLATION APPLY MATSET No. 09−013. AFTER THE INSTALLATION OF THE FASTENERS APPLY MATSET No. 16−001 AND 16−018. BETWEEN THE FITTING AND THE STRUCTURE APPLY MATSET No. 09−016. N_SB_531242_5_BDAA_04_04 Figure A-FBDAA - Sheet 04 Removal and Installation of the Fitting DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 42 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001HOLESYMBOLITEMOLD PNASNA2050DEJ4020ASNA2026V3−7ASNA2528−3ITEMNEW PNDESCRIPTIONREMARKSHOLE DIAMETERMINMAX5.113 mm(0.2012 in)5.152 mm(0.2028 in)DIAMETERRIVETEN6114V3X7BOLTASNA2528−3NUTOLDNEW(1)(2)(3)15163OVERSIZEASNA2027V3−4ASNA2528−35.113 mm(0.2012 in)5.152 mm(0.2028 in)DIAMETEREN6115V3X4BOLTASNA2528−3NUT(4)(3)173OVERSIZEASNA2026V3−5ASNA2528−35.113 mm(0.2012 in)5.152 mm(0.2028 in)DIAMETEREN6114V3X5BOLTASNA2528−3NUT(5)(3)183OVERSIZEASNA2026V4−9ASNA2528−4DIAMETEREN6114V4X9BOLTASNA2528−4NUT(6)(30)1930OVERSIZEMS21250−04006NSA5057−4DIAMETERSCREWNUT(7)(8)(7)8NOMINALMS21250−04004NSA5057−4DIAMETERSCREWNUT(9)(8)(9)8NOMINAL6.706 mm(0.264 in)6.747 mm(0.2653 in)MS21250−04006NSA5057−4MS21250−04004NSA5057−4ASNA2050DXJ48204.78 mm(0.188 in)4.82 mm(0.189 in)DIAMETEROVERSIZEASNA2027V3−6ASNA2528−3DIAMETEREN6115V3X6BOLTASNA2528−3NUT(100)(3)413OVERSIZE5.113 mm(0.2012 in)5.152 mm(0.2028 in)

N_SB_531242_5_BDAA_05_02 Figure A-FBDAA - Sheet 05 Removal and Installation of the Fitting DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 43 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002

Z130 

### A FR24 FR34



### B



## A

**C**



## B N_SB_531242_5_BDAB_01_00 Figure A-FBDAB - Sheet 01 Removal and Installation of the Fitting DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 44 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002

FASTENERS TO BE REMOVED FASTENERS TO BE REMOVED 

### F

**E D** 

**G H**  STGR39

FR24



## C

**D E**  **J F**  **W D** 

**FWD FWD**  N_SB_531242_5_BDAB_02_00 Figure A-FBDAB - Sheet 02 Removal and Installation of the Fitting DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 45 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002 FR24 FR24A FR25

FR24 FR24A FR24 FR24A 

## F

**G H**  **FWD**

**FWD**
**FWD** (40) FITTING 

### L **K**



## J **NOTES:** DURING THE FASTENERS INSTALLATION APPLY MATSET No. 09−013. AFTER THE INSTALLATION OF THE FASTENERS APPLY MATSET No. 16−001 AND 16−018. BETWEEN THE FITTING AND THE STRUCTURE APPLY MATSET No. 09−016. N_SB_531242_5_BDAB_03_03 Figure A-FBDAB - Sheet 03 Removal and Installation of the Fitting DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 46 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002

FR24A FR25

FR24A

**FWD FWD**  

## K

**L**
**NOTES:** DURING THE FASTENERS INSTALLATION APPLY MATSET No. 09−013. AFTER THE INSTALLATION OF THE FASTENERS APPLY MATSET No. 16−001 AND 16−018. BETWEEN THE FITTING AND THE STRUCTURE APPLY MATSET No. 09−016. N_SB_531242_5_BDAB_04_02 Figure A-FBDAB - Sheet 04 Removal and Installation of the Fitting DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 47 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002HOLESYMBOLITEMOLD PNASNA2050DXJ4020ASNA2026V3−7ASNA2528−3ITEMNEW PNDESCRIPTIONREMARKSHOLE DIAMETERMINMAX5.113 mm(0.2012 in)5.152 mm(0.2028 in)DIAMETERRIVETEN6114V3X7BOLTASNA2528−3NUTOLDNEW(1)(2)(3)15163OVERSIZEASNA2027V3−4ASNA2528−35.113 mm(0.2012 in)5.152 mm(0.2028 in)DIAMETEREN6115V3X4BOLTASNA2528−3NUT(4)(3)173OVERSIZEASNA2026V3−5ASNA2528−35.113 mm(0.2012 in)5.152 mm(0.2028 in)DIAMETEREN6114V3X5BOLTASNA2528−3NUT(5)(3)183OVERSIZEASNA2026V4−9ASNA2528−4DIAMETEREN6114V4X9BOLTASNA2528−4NUT(6)(30)1930OVERSIZEMS21250−04006NSA5057−4DIAMETERSCREWNUT(7)(8)(7)8NOMINALMS21250−04004NSA5057−4DIAMETERSCREWNUT(9)(8)(9)8NOMINAL6.706 mm(0.264 in)6.747 mm(0.2653 in)MS21250−04006NSA5057−4MS21250−04004NSA5057−4ASNA2050DXJ48204.78 mm(0.188 in)4.82 mm(0.189 in)DIAMETEROVERSIZEEN6114V3−7ASNA2528−3DIAMETEREN6114V3X7BOLTASNA2528−3NUT(14)(3)163OVERSIZE5.113 mm(0.2012 in)5.152 mm(0.2028 in)ASNA2528−3DIAMETEREN6115V3X6BOLTASNA2528−3NUT(100)(3)413OVERSIZE5.113 mm(0.2012 in)5.152 mm(0.2028 in)ASNA2027V3−6

N_SB_531242_5_BDAB_05_02 Figure A-FBDAB - Sheet 05 Removal and Installation of the Fitting DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 48 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

N_SB_531242_5_BAAA_01_00 Z130 

### A FR24 FR34



### B



## A

**C**



## B
Figure A-F BAAA - S heet 01 Inspection of the surrounding holes and area to be inspected DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 49 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

FR24 STGR39

FR24 STGR39

HOLES TO BE INSPECTED 

### E **F**

**D** STGR39

FR24



## D **E F**  **W D**  

## C

N_SB_531242_5_BAAA_02_02 Figure A-F BAAA - S heet 02 Inspection of the surrounding holes and area to be inspected DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 50 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

STGR39 STGR38

HOLE SYMBOL ITEM HOLE DIAMETER MIN MAX 4.06 mm (0.160 in) 4.17 mm (0.164 in) 4.125 mm (0.162 in) 4.160 mm (0.1637 in) FR24 STGR40 HOLES TO BE INSPECTED

(10) (11) (12) 

## F
**F W**  **D**

EXISTING NOMINAL DIAMETER REMARKS DESCRIPTION
RIVET
PIN COLLAR EXISTING NOMINAL DIAMETER 4.125 mm (0.162 in) 4.160 mm (0.1637 in) (50) (12) PIN COLLAR EXISTING NOMINAL DIAMETER MISSING HOLE POSITION

N_SB_531242_5_BAAA_03_02 Figure A-F BAAA - S heet 03 Inspection of the surrounding holes and area to be inspected DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 51 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

QUESTION ACTION FINDING REMOVE THE 5 SURROUNDING FASTENERS

OF THE REMOVED FASTENERS NO YES

AS PER NTM 51−10−01 PART 6 PROCEDURE A OF THE 5 HOLES DO A ROTOTEST INSPECTION

CONTACT AIRBUS AND APPLY CORRECTIVE ACTION CRACKS FINDING YES NO

OVERSIZE THE 5 HOLES AND INSTALL NEW FASTENERS INSTALL THE MISSING FASTENER

DRILL THE MISSING HOLE AND

REFER TO APPENDIX 01

NO FURTHER ACTION SEND TO AIRBUS THE INSPECTION REPORT HOLES AT NOMINAL DIAMETER DO A DETAILED INSPECTION AT NOSE FORWARD FUSELAGE AT FR24

STRG39 (RH SIDE) FOR MISSING FASTENER AND DRILLING AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2)

REFER TO SUBTASK 531242−020−002−001

REFER TO SUBTASK 531242−420−003−001 DEFINED BY AIRBUS BEFORE NEXT FLIGHT MISSING YES FASTENER NO

REFER TO SUBTASK 531242−220−001−001

N_SB_531242_5_FAAA_01_01

Figure A-FFAAA - Sheet 01 Flow Chart DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 52 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002

QUESTION ACTION FINDING REMOVE THE 5 SURROUNDING FASTENERS

OF THE REMOVED FASTENERS NO YES

AS PER NTM 51−10−01 PART 6 PROCEDURE A OF THE 5 HOLES DO A ROTOTEST INSPECTION

CONTACT AIRBUS AND APPLY CORRECTIVE ACTION CRACKS FINDING YES NO

OVERSIZE THE 5 HOLES AND INSTALL NEW FASTENERS INSTALL THE MISSING FASTENER

DRILL THE MISSING HOLE AND

REFER TO APPENDIX 01

NO FURTHER ACTION SEND TO AIRBUS THE INSPECTION REPORT HOLES AT NOMINAL DIAMETER DO A DETAILED INSPECTION AT NOSE FORWARD FUSELAGE AT FR24

STRG39 (RH SIDE) FOR MISSING FASTENER AND DRILLING AT THE THRESHOLD GIVEN IN THE PLANNING INFORMATION PARAGRAPH E.(2)

REFER TO SUBTASK 531242−020−002−001

REFER TO SUBTASK 531242−420−003−002 DEFINED BY AIRBUS BEFORE NEXT FLIGHT MISSING YES FASTENER NO

REFER TO SUBTASK 531242−220−001−003

N_SB_531242_5_FAAB_01_00

Figure A-FFAAB - Sheet 01 Flow Chart DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 53 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

Z130 

### A FR24 FR34



### B



## A

**C**



## B N_SB_531242_5_BCAA_01_00 Figure A-FBCAA - Sheet 01 Installation of the fasteners DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 54 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

FR24 STGR39

FR24 STGR39 

### E **F**

**D** STGR39

FR24



## D **E**
N_SB_531242_5_BCAA_02_01 **F W**  **D** 

## C

Figure A-FBCAA - Sheet 02 Installation of the fasteners DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 55 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

HOLE SYMBOL ITEM PN DESCRIPTION HOLE DIAMETER MIN MAX 4.85 mm (0.191 in) 4.95 mm (0.195 in) ASNA2049DXJ4820 RIVET STGR39 STGR38

FR24

STGR40

EN6114V3−7 BOLT ASNA2528−3 NUT 4.78 mm (0.188 in) 4.82 mm (0.190 in) 13 14 3 

## F
**F W**  **D**

NEXT NOMINAL DIAMETER NOMINAL DIAMETER REMARKS (40) FITTING

EN6114V3X3 BOLT ASNA2528−3 NUT 5.113 mm (0.2012 in) 5.152 mm (0.2028 in) 60 3 NEXT NOMINAL DIAMETER 

### A **A**

**NOTES:** DURING THE FASTENERS INSTALLATION AFTER THE INSTALLATION OF THE FASTENERS APPLY MATSET No. 16−001 AND 16−018. HOLE TO BE

APPLY MATSET No. 09−013. FR24 FR24A

RIVETS UNDER THE FITTING 

## A **A**

EN6114V3X4 BOLT ASNA2528−3 NUT 5.113 mm (0.2012 in) 5.152 mm (0.2028 in) 70 3 NEXT NOMINAL DIAMETER DRILLED

N_SB_531242_5_BCAA_03_07 Figure A-FBCAA - Sheet 03 Installation of the fasteners DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 56 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL
FR24 MISSING FASTENER

VIEW FROM THE OUTSIDE OF

THE AIRCRAFT

**NOTE:** DRILL FROM THE OUTSIDE OF THE AIRCRAFT.
N_SB_531242_5_BCAA_04_00 DRILL THE MISSING HOLE TO THE SAME DISTANCE FROM THE SURROUDING HOLE. **FWD**

Figure A-FBCAA - Sheet 04 Installation of the fasteners DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 57 5

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# @A318/A319/A320/A321 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 58 5

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# @A318/A319/A320/A321 SERVICE BULLETIN Appendix 01 - Inspection Report **CONF ALL The results of the inspection, including no findings, replacement or action to be done, must be forwarded to AIRBUS department SEES4, on the attached inspec tion report sheet.

DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 1 5

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# @A318/A319/A320/A321 SERVICE BULLETIN Appendix 01 - Inspection Report

**CONF ALL

HOLE H1
HOLE H2
HOLE H3
HOLE H4 NO CRACK CRACK LENGTH
mm

HOLE H5 **INSPECTION REPORT** SERVICE BULLETIN No. : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A320−53A1242

DATE OF INSPECTION : RETURN TO : AIRBUS CUSTOMER SERVICES ENGINEERING − SEES4 PAX DOORS − FUSELAGE (SA/LA) − WINDOWS −

INSPECTION METHOD : CENTER WING BOX (SA/LA)

ROTATING PROBE TESTING 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE FAX +33 (0)5 61 93 36 14

in Structure.sbinspectionresult@airbus.com

FASTENER MISSING YES NO

N_SB_531242_5_RAAA_01_01 Figure A-FRAAA - Sheet 01 Inspection Report DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 2 5

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# @A318/A319/A320/A321 SERVICE BULLETIN Appendix 01 - Inspection Report

**CONF ALL

STGR39 STGR38

FR24 STGR40 SURROUNDING HOLES TO BE INSPECTED



## F
**F W**  **D** H2 H1 H5 H4 H3

CHECK FOR MISSING FASTENER

N_SB_531242_5_RAAA_02_01 Figure A-FRAAA - Sheet 02 Inspection Report DATE: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 3 5

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# @A318/A319/A320/A321 SERVICE BULLETIN REPORTING SHEET 

### TITLE: FUSELAGE - NOSE FORWARD FUSELAGE - INSPECTION OF MISSING FASTENER AND DRILLING AT FR 24 STRG 39 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 concer ned (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: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 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 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: May 22/12 SERVICE BULLETIN No.: A320-53-1242 REVISION No.: 00 - May 22/12 Page: 1 5

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