# @A318/A319/A320/A321 SERVICE BULLETIN REVISION TRANSMITTAL SHEET AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51



# MANDATORY MANDATORY MANDATORY
ATA SYSTEM: 53 

### TITLE: FUSELAGE - CENTER FUSELAGE - REINFORCE FORWARD PRESSURE BULKHEAD AT FRAME COUPLING C35 LH/RH MODIFICATION No.: 153832K16057 This page transmits Revision No.03 of Service Bulletin No.A320-53-1268 ADDITIONAL WORK **CONF ALL No additional work is required by this revision for aircraft modified by any previous issue. REASON Revision No. 03 issued to add aircraft with Manufacturer Serial Number (MSN) 0202, 0209, 0216, 0267, 0268, 0269, 0382 and 0346 to the effectivity of this Service Bulletin. CHANGES The main changes of this revision are: - The SB compliance has been updated to MANDATORY - The SB effectivity has been updated - The REFERENCES/REPERCUSSIONS section has been updated - The REFERENCES section has been updated - The ALS has been added in PUBLICATION AFFECTED section. SUMMARY GENERAL EVALUATION GENERAL EVALUATION TABLE UPDATED R REFERENCES / REPERCUSSIONS REFERENCES/REPERCUSSIONS TABLE UPDATED R PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R

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# @A318/A319/A320/A321 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Configuration definition CONF 001 CONFIGURATION DEFINITION UPDATED R COMPLIANCE Classification CLASSIFICATION UPDATED R Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R REFERENCES REFERENCED DOCUMENTATION UPDATED R PUBLICATION AFFECTED PUBLICATIONS AFFECTED UPDATED R PUBLICATIONS AFFECTED ADDED N ACCOMPLISHMENT INSTRUCTIONS TASK 531268- 831-849-001-Modification Subtask 531268-831-005-001 SUBTASK SOLUTION UPDATED NOTE UPDATED R
FILING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS Revision No. 01 issued to: extend the effectivity of this Service Bulletin to include the A319 model and additional A320 aircraft incorporate changes found necessary and carried out during the accomplishment of this Service Bulletin on aircraft with Manufacturer Serial Number (MSN) 0401. Revision No. 02 issued to: add aircraft for operators DLH and GWI remove UAL aircraft from the SB applicability due to the Extended Service Goal (ESG) flexibility which postpones the structure reinforcement requirement from 60000 Flight Hours (FH) up to 96000 FH, without exceeding 48000 Flight Cycles (FC). REVISION SEQUENCE ORIGINAL: Jan 08/13 REVISION No. : 01 - Jul 23/13 REVISION No. : 02 - Jul 15/14 REVISION No. : 03 - May 07/15

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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. 

# MANDATORY MANDATORY MANDATORY
ATA SYSTEM: 53 

### TITLE: FUSELAGE - CENTER FUSELAGE - REINFORCE FORWARD PRESSURE BULKHEAD AT FRAME COUPLING C35 LH/RH **CONF ALL MODIFICATIONS MODIFICATION CLASSIFICATION MAJOR None MINOR 153832K16057 NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the mass, balance, structural strength, reliability, operational characteristics affecting the airworthiness of the product. All other changes are major changes. REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During A320 fatigue testing, damage was found in the area of the pressure bulkhead at Frame 35. Accomplishment of this Service Bulletin will cold expand tooling holes and fastener holes at Frame 35 between STGR28 and STGR31 LH and RH. Accomplishment of this Service Bulletin will contribute to the continued structural integrity in the modification area up to the Extended Service Goal. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO POTENTIAL AD YES A/C OPERATION AFFECTED NO RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO ETOPS AFFECTED NO STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO VALIDATION ON AIRCRAFT YES BOOKLET AVAILABLE YES NOTE (1) : Service Bulletin must be accomplished. NOTE: This Service Bulletin has been validated at original issue on A320 aircraft with DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 1 6

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# @A318/A319/A320/A321 SERVICE BULLETIN SUMMARY Manufacturer Serial Number (MSN) 0401. Aircraft with Manufacturer Serial Number (MSN) 0401 complies fully with the requirements of the current issue of the Service Bulletin. NOTE: A booklet including photographs taken during the validation of this Service Bulletin is available on AIRBUS|World - Maintenance and Engineering - AirN@v engineering (in the concerned SB file). MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 531268D01R00 1 See SB Fasteners Kit 531268A01R00 1 See SB Fasteners Standard tool TOOLA01 1 See SB FTI tools Standard tool TOOLD01 1 See SB FTI tools EFFECTIVITY This Service Bulletin is applicable to this (these) operator(s) :

DLH GWI NOTE: This Service Bulletin is written for the operators listed above. The modification in this Service Bulletin can be done by other operators. If other operators want to do this modification, use the RFC/RMO procedure and write to : AIRBUS CUSTOMER SERVICES DIRECTORATE SC Department 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU None OEB None AOT None SIL 51-012 LINE MAINTENANCE AFFECTED No LIFE LIMIT YES OTHER None NOTE : SIL 51-012 has been migrated into ISI article 51.48.00001.

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# @A318/A319/A320/A321 SERVICE BULLETIN SUMMARY NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER Task 531268-831-849-001: Modification TOTAL MANHOURS 21.00 ELAPSED TIME (HOURS) 15.50 APPENDICES APPENDIX 01: Elapsed Time Assumption

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

**CONF ALL

STGR30LH STGR29LH FR35 825 Z130 

### A

LH SIDE SHOWN RH SIDE SYMMETRICAL 

## A COLD EXPANSION OF THE FASTENER HOLES N_SB_531268_6_SBAA_01_00 Figure A-GSBAA - Sheet 01

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

**CONF ALL



### A Z240

FR35 FR42 

## A

STGR28

STGR29

STGR30

STGR31 Y1282.0 Z140

FR35 

### B B

LH SHOWN, RH SIMILAR 

## B VIEW LOOKING FWD TOOLING HOLE TO BE COLD EXPANDED

RIVET HOLES TO BE

COLD EXPANDED HOLE TO BE COLD EXPANDED

RIVET HOLES TO BE

COLD EXPANDED

RIVET HOLES TO BE

COLD EXPANDED TOOLING

N_SB_531268_6_SAAA_01_01 Figure A-GSAAA - Sheet 01

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

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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



# MANDATORY MANDATORY MANDATORY
ATA SYSTEM: 53 

### TITLE: FUSELAGE - CENTER FUSELAGE - REINFORCE FORWARD PRESSURE BULKHEAD AT FRAME COUPLING C35 LH/RH MODIFICATION No.: 153832K16057 This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without AIRBUS prior written consent. 1. PLANNING INFORMATION **CONF ALL A. EFFECTIVITY This modification is applicable by Service Bulletin only. (1) Models 320-211 (2) Effectivity by MSN 0069-0072 0078 0083 0086 0093-0094 0104 0110-0111 0116-0117 0135 0137 0161-0162 0172 0200-0202 0209 0216-0218 0267-0269 0346 0382 0401 (3) Effectivity by Operator The Operator/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to AIRBUS. Any future changes resulting from transfer of an aircraft from one operator to another will not be reflected in this list unless the Service Bulletin is revised for another reason. OPERATOR MSN DLH 0069 0070 0071 0072 0078 0083 0086 0093 0094 0104 0110 0111 0116 0172 0346 DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 1 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
OPERATOR MSN GWI 0117 0135 0137 0161 0162 0200 0201 0202 0209 0216 0217 0218 0267 0268 0269 0382 0401 (4) Configuration by MSN MSN CONFIGURATION 0069 0070 0071 0072 0078 0083 0086 0093 0094 0104 0110 0111 0116 0117 0135 0137 0161 0162 0172 0200 0201 0202 0209 0216 0217 0218 0267 0268 0269 0346 0382 0401 001
(5) Configuration definition **CONF 001 Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a standard configuration. (6) Material Effectivity MATERIAL QTY PER A/C SEE NOTES Kit 531268D01R00 1 Kit 531268A01R00 1 Standard tool TOOLA01 1 Standard tool TOOLD01 1 Consumable CMLA01 1 Consumable CMLD01 1 B. CONCURRENT REQUIREMENTS None C. REASON (1) History During A320 fatigue testing, damage was found in the area of the pressure bulkhead at Frame 35. (2) Objective/Action Accomplishment of this Service Bulletin will cold expand tooling holes and fastener holes at Frame 35 between STGR28 and STGR31 LH and RH. (3) Advantages Accomplishment of this Service Bulletin will contribute to the continued structural integrity in the modification area up to the Extended Service Goal. (4) Operational/Maintenance Consequences None

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# @A318/A319/A320/A321 SERVICE BULLETIN
D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : Task 531268-831-849-001: Modification (1) Remove the 18 fasteners at FR35, STGR30, LH and RH sides (2) Do a Non Destructive Testing (NDT) on the 18 fastener holes at FR35, STGR30, LH and RH sides (3) Do the cold expansion and ream the 18 holes at FR35, STGR30, LH and RH sides (4) Install the 18 fasteners at FR35, STGR30, LH and RH sides (5) Apply the surface protection to the 18 fasteners at FR35, STGR30, LH and RH sides (6) Remove the Fasteners at FR35, between STGR28 and STGR31, LH and RH (7) Do a Non Destructive Test (NDT) on the Fastener and Tooling Holes (8) Do the Cold Expansion and Ream the Holes at FR35, between STGR28 and STGR31, LH and RH (9) Install the Fasteners at FR35, between STGR28 and STGR31, LH and RH (10) Apply the Surface Protection at FR35, between STGR28 and STGR31, LH and RH E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale Accomplishment of this Service Bulletin is required at or before 48000 FC or 96000 FH, whichever occurs first. This Service Bulletin has been classified Mandatory by the issue of an Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must be used as the reference document for the mandated accomplishment timescale. F. APPROVAL The technical content of this document is approved under the authority of Design Organisation Approval No. EASA.21J.031. If an aircraft listed in the effectivity has a modification or repair embodied that is not of AIRBUS origin, and which affects the content of this Service Bulletin, the operator is responsible for obtaining approval by its airworthiness authority for any adaptation necessary before incorporation of the Service Bulletin.

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# @A318/A319/A320/A321 SERVICE BULLETIN
G. MANPOWER The manpower estimates given in this Service Bulletin are based on the direct labor cost to do the work. These estimates assume that the work will be done by experienced personnel, and may need to be revised upwards to suit operator’s circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufacture and procurement of parts and tools, drying times for paints, sealants, etc., and general administration work are also not included. Task 531268-831-849-001: Modification Get Access 5.00 On Aircraft Remove the 18 fasteners at FR35, STGR30, LH and RH sides 0.50 Do a Non Destructive Testing (NDT) on the 18 fastener holes at FR35, STGR30, LH and RH sides 0.50 Do the cold expansion and ream the 18 holes at FR35, STGR30, LH and RH sides 2.00 Install the 18 fasteners at FR35, STGR30, LH and RH sides 0.75 Apply the surface protection to the 18 fasteners at FR35, STGR30, LH and RH sides 0.25 Remove the Fasteners at FR35, between STGR28 and STGR31, LH and RH 0.50 Do a Non Destructive Test (NDT) on the Fastener and Tooling Holes 0.50 Do the Cold Expansion and Ream the Holes at FR35, between STGR28 and STGR31, LH and RH 2.50 Install the Fasteners at FR35, between STGR28 and STGR31, LH and RH 1.00 Apply the Surface Protection at FR35, between STGR28 and STGR31, LH and RH 0.50 Tests 1.00 Close-Up 6.00 TOTAL MANHOURS 21.00 ELAPSED TIME (HOURS) 15.50 NOTE : For an explanation of the manhours and elapsed time, refer to the Gantt Chart, Fig. A-GAAAA given in APPENDIX 01: Elapsed Time Assumption H. WEIGHT AND BALANCE The weight and balance estimates given in this Service Bulletin are based on the Manufacturer’s Empty Weight (MEW) and do not include operator items. For the definition of MEW and operator’s items refer to the Weight and Balance Manual (WBM) Chapter 1-00-07. Manufacturers Empty Weight +0.029 KG (+0.064 LB) Effect on Balance +0.452 KGM (+3.269 LB.FT )

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# @A318/A319/A320/A321 SERVICE BULLETIN
I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES

Aircraft Maintenance Manual (AMM) 06-20-00 06-30-00 06-31-53 06-41-53 12-34-24 20-21-11 21-21-41 25-54-12 25-80-00 38-11-41 52-30-00 53-35-11 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-33-00 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 Service Information Letter (SIL) SIL 51-012 Standards Manual (SM) Structural Repair Manual (SRM) 51-23-12 51-42-00 51-44-00 51-48-00 51-75-12 Weight and Balance Manual (WBM) Chapter 1-00-07 NOTE : SIL 51-012 has been migrated into ISI article 51.48.00001. K. PUBLICATION AFFECTED

Airworthiness Limitation Section (ALS) Part 2 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

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# @A318/A319/A320/A321 SERVICE BULLETIN

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# @A318/A319/A320/A321 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses The AIRBUS material is included in the commercial offer of the Letter Agreement, and as such will be supplied by AIRBUS Upgrade Services. To facilitate the material reception, Airline Customers are requested to send a Customer Purchase Order to: Kit 531268D01R00 Kit 531268A01R00 AIRBUS Upgrade Services Attn. Key Account Manager (KAM) (2) Price and Availability Sales terms must be agreed between the Customer and AIRBUS in accordance with the RFC (or RFC/RMO) procedure. B. INDUSTRY SUPPORT INFORMATION Industry Support terms must be agreed between the Customer and AIRBUS in accordance with the RFC (or RFC/RMO) procedure. C. LIST OF COMPONENTS Kit 531268A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 2 EN6115K3A7 2 BOLT 4 EN6115K3A8 2 BOLT 6 EN6115K3A10 10 BOLT 8 EN6115K3A12 4 BOLT 10 ASNA2536-3A 18 NUT NOTE : If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. Kit 531268D01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 14 EN6115K3A4 10 BOLT (12) DAN5-6-4 15 EN6115K3A3 8 BOLT (11) EN6081D6-03 16 ASNA2536-3A 18 NUT (13) NSA5075-6

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# @A318/A319/A320/A321 SERVICE BULLETIN
NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required Solvent General Purpose 11-026 As required Corrosion Preventive Compound, Temporary 15-009 As required Polyurethane Top Coat (Grey) 16-002 As required Anti Corrosion Primer Epoxy 16-006 As required Lint-Free Cotton Cloth 19-003 As required Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required Solvent General Purpose 11-026 As required Corrosion Preventive Compound, Temporary 15-009 As required Anti-Corrosion Primer (Polyurethane) 16-001 As required Polyurethane Top Coat (Grey) 16-002 As required Lint-Free Cotton Cloth 19-003 As required (2) Components None (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None

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# @A318/A319/A320/A321 SERVICE BULLETIN
F. TOOLING (1) Tooling - Price and Availability (a) Procurement Addresses Operators interested in obtaining the FTI tool kits should contact: Standard tool TOOLA01 Standard tool TOOLD01 401 Andover Park East SEATTLE WA 98188-7605 USA Internet: www.fatiguetech.com Phone: (206) 2462010 Fax: (206) 2449886 (b) Price and Availability None (2) Tools To accomplish this Service Bulletin it is necessary to use these tools and equipment: - Equipment and materials to do a check of fastener holes as per NTM Task 51-10-01-250-801. NOTE: FTI has allocated the following tool kit numbers for cold expansion. For the definition of the capital, durable and expendable tools, refer to SIL 51-012. Standard tool TOOLA01 ITEM TOOL N ̊ TOOL NAME QTY SEE NOTES DKA320531268-1 Durable tooling 1 (1) EKA320531268-1 Expendable tooling 1 (2) FTIA320531268-1 Capital tooling 1 (3) NOTE (1) : The durable tool kit contains the minimum quantity of durable tools necessary to accomplish the Service Bulletin on one aircraft. If the Service Bulletin is to be accomplished on more than one aircraft, the number of durable kits required can be established by reference to SIL 51-012. NOTE (2) : The expendable tool kit contains the quantity of expendable tools required to accomplish the Service Bulletin on one aircraft. Order one expendable tool kit for every aircraft on which this Service Bulletin is to be accomplished. NOTE (3) : The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operator’s stock as a long term investment or can be loaned from FTI. DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 9 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
Standard tool TOOLD01 ITEM TOOL N ̊ TOOL NAME QTY SEE NOTES DKA320531268-1 Durable tooling 1 (1) EKA320531268-1 Expendable tooling 1 (2) FTIA320531268-1 Capital tooling 1 (3) NOTE: The operator should make sure that Tool PN LBRA-7 has been delivered with the FTI tool DKA320531268-1. NOTE (1) : The durable tool kit contains the minimum quantity of durable tools necessary to accomplish the Service Bulletin on one aircraft. If the Service Bulletin is to be accomplished on more than one aircraft, the number of durable kits required can be established by reference to SIL 51-012. NOTE (2) : The expendable tool kit contains the quantity of expendable tools required to accomplish the Service Bulletin on one aircraft. Order one expendable tool kit for every aircraft on which this Service Bulletin is to be accomplished. NOTE (3) : The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operator’s stock as a long term investment or can be loaned from FTI. (3) Special Tools None

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# @A318/A319/A320/A321 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 531268-831-849-001 - Modification WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE) . WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS. - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00. NOTE: The accomplishment instructions of this Service Bulletin include procedures given in other documents or in other sections of the Service Bulletin. When the words "refer to" are used and the operator has a procedure accepted by the local authority he belongs to, the accepted alternative procedure can be used. When the words "in accordance with" are used then the given procedure must be followed. NOTE: The access and close-up instructions, not comprising return to service tests, in this Service Bulletin do not constitute or affect the technical intent of the Service Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or close-up steps to add flexibility to their maintenance operations as long as the technical intent of the Service Bulletin is met within the set parameters. NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms. Refer to paragraph 1.J., References, for the definition of acronyms. NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions are Required for Compliance (RC) and must be done to comply with the AD. Other paragraphs are recommended and may be deviated from, done as part of other actions or done with accepted methods different from those given in the Service Bulletin, as long as the RC paragraphs can be done and the aircraft can be put back into a serviceable condition. Task Associated Data Zone 130 From 130 to 190
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# @A318/A319/A320/A321 SERVICE BULLETIN
Modified FIN 4012HM 4013HM 3000MM Access Door 825 Panel 131PW 132PW 191BT 192BT Manpower TOTAL MANHOURS 21.00 ELAPSED TIME (HOURS) 15.50 A. GENERAL NOTE : The listed subtasks are not in sequence with the work steps. The operator can change the sequence. (1) Subtask 531268-910-202-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-30-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 Task 20-21-11-911-001 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-33-00 Structural Repair Manual (SRM) 51-23-12 51-42-00 51-44-00 51-48-00 51-75-12 (a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to Consumable Materials List (CML). (b) For the identification of access panels, refer to AMM 06-41-53, Page Block 001. (c) Tag the parts that you must remove and retain to make the subsequent installation easier. (d) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (e) For the Stringer (STGR) identification, refer to AMM 06-30-00, Page Block 001. (f) For the identification of zones, refer to AMM 06-20-00, Page Block 001. (g) Remove and install fasteners in accordance with SRM 51-42-00. (h) For the general installation of electrical wire harnesses, refer to ESPM 20-33-00.

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 12 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (i) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-001. (j) Cold expand the fastener holes in accordance with SRM 51-48-00. (k) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00. (l) Renew the protective finish in accordance with SRM 51-75-12. (m) Renew the special protection in accordance with SRM 51-23-12. NOTE: If the length of any fastener specified in this Service Bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. (2) Subtask 531268-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. B. PREPARATION (1) Subtask 531268-941-202-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002 Task 52-30-00-860-001 NOTE: The items given in this note shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear) - Engine shut down, thrust reversers closed and locked - Aircraft in clean configuration - Parking brake applied - Aircraft electrical network de-energized - Hydraulic systems depressurized

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 13 6

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# @A318/A319/A320/A321 SERVICE BULLETIN - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position. (a) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-869-002. (b) Put access platform(s) in position. (c) Open the FWD cargo compartment door 825, refer to AMM Task 52-30-00-860-001. (2) Subtask 531268-010-201-001 - Remove/Open for Access Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-21-41-000-001 Task 25-54-12-000-001 Task 25-80-00-000-001 Task 38-11-41-000-001 Task 53-35-11-000-001 (a) Remove the wing-to-fuselage fairings 191BT and 192BT, refer to AMM Task 53-35-11-000-001. (b) At FR34, remove the FWD cargo-compartment partitions 131PW, 132PW and if necessary 131NW, refer to AMM Task 25-54-12-000-001. (c) If necessary, remove the air conditioning recirculation filters 4012HM LH and 4013HM RH, refer to AMM Task 21-21-41-000-001. (d) If necessary, remove the potable water tank 3000MM and ventilation ducts, refer to AMM Task 38-11-41-000-001. (e) Remove the heat and sound insulation blankets in the area between Frame 35 and Frame 36 LH and RH, refer to AMM Task 25-80-00-000-001. (f) If necessary, remove electrical bundle clamps and push bundles aside, without disconnection to get them out of the working area.

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 14 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
C. PROCEDURE (1) Subtask 531268-831-001-001 - Remove the 18 fasteners at FR35, STGR30, LH and RH sides Work Zones and Access Panels Zone Access/Work location From 130 Access Door 825 Panel 131PW, Panel 132PW Work location from Frame 34 to Frame 35 Stringer 30 To 190 Access Panel 191BT, Panel 192BT Work location from Frame 34 to Frame 35 Stringer 30 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required References Structural Repair Manual (SRM) 51-42-00 Fig. A-FBAAA Cold Expansion of the Fasteners Holes at FR35, STGR30, LH and RH sides Sheet 01 Sheet 02 (a) Remove the fasteners in accordance with SRM 51-42-00 1 From the LH and RH sides, remove: 18 Nut ASNA2528-3 Item (9) Discard 2 Bolt ASNA2027V3-7 Item (1) Discard 2 Bolt ASNA2027V3-8 Item (3) Discard 10 Bolt ASNA2027V3-10 Item (5) Discard 4 Bolt ASNA2027V3-12 Item (7) Discard
DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 15 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (b) Clean the work area with: Solvent General Purpose 11-026 As required
Lint-Free Cotton Cloth 19-003 As required (2) Subtask 531268-831-004-001 - Do a Non Destructive Testing (NDT) on the 18 fastener holes at FR35, STGR30, LH and RH sides Work Zones and Access Panels Zone Access/Work location From 130 Access Door 825 Panel 131PW, Panel 132PW Work location from Frame 34 to Frame 35 Stringer 30 To 190 Access Panel 191BT, Panel 192BT Work location from Frame 34 to Frame 35 Stringer 30 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) Task 51-10-01-250-801 Fig. A-FBAAA Cold Expansion of the Fasteners Holes at FR35, STGR30, LH and RH sides Sheet 01 Sheet 02 (a) Do the checks of the holes 1 Make sure that the diameter of the hole is not more than the maximum starting hole diameter given in Fig. A-FBAAA Sheet 02

. - If the hole diameter is more than the maximum starting hole diameter, contact AIRBUS. - If the hole diameter is not more than the maximum starting hole diameter, do the operation given below. 2 Do a rotating probe testing of the holes (Refer to NTM Task 51-10-01-250-801). - If crack is found, contact AIRBUS. - If crack is not found, do the operations given below. DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 16 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (3) Subtask 531268-831-005-001 - Do the cold expansion and ream the 18 holes at FR35, STGR30, LH and RH sides Work Zones and Access Panels Zone Access/Work location From 130 Access Door 825 Panel 131PW, Panel 132PW Work location from Frame 34 to Frame 35 Stringer 30 To 190 Access Panel 191BT, Panel 192BT Work location from Frame 34 to Frame 35 Stringer 30 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required Standard tool TOOLA01 ITEM TOOL N ̊ TOOL NAME QTY SEE NOTES DKA320531268-1 Durable tooling 1 (1) EKA320531268-1 Expendable tooling 1 (2) FTIA320531268-1 Capital tooling 1 (3) NOTE (1) : The durable tool kit contains the minimum quantity of durable tools necessary to accomplish the Service Bulletin on one aircraft. If the Service Bulletin is to be accomplished on more than one aircraft, the number of durable kits required can be established by reference to SIL 51-012. NOTE (2) : The expendable tool kit contains the quantity of expendable tools required to accomplish the Service Bulletin on one aircraft. Order one expendable tool kit for every aircraft on which this Service Bulletin is to be accomplished. NOTE (3) : The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operator’s stock as a long term investment or can be loaned from FTI.

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 17 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-48-00 Fig. A-FBAAA Cold Expansion of the Fasteners Holes at FR35, STGR30, LH and RH sides Sheet 01 Sheet 02 (a) Do the cold expansion of the holes in accordance with SRM 51-48-00 1 Oversize the holes to the starting hole diameter given in Fig. A-FBAAA Sheet 02

. Use FTI tool list No.: DKA320531268-1 Durable tooling 1 2 Clean the drilled area with: Solvent General Purpose 11-026 As required
Lint-Free Cotton Cloth 19-003 As required

3 Install the sleeves and obey the split direction given in Fig. A-FBAAA Sheet 02, View B. 4 Do the cold expansion of the holes Use FTI tool list No.: FTIA320531268-1 Capital tooling 1 DKA320531268-1 Durable tooling 1 EKA320531268-1 Expendable tooling 1 5 Remove the sleeves. 6 Ream the holes to the final diameter given in Fig. A-FBAAA Sheet 02

. NOTE : The final hole diameter gives an interference fit of the fasteners between -35 μm and -85 μmm (-0.0014 in and -0.0033 in). 7 Deburr the holes and clean the drilled areas with: Solvent General Purpose 11-026 As required
Lint-Free Cotton Cloth 19-003 As required

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 18 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (4) Subtask 531268-831-006-001 - Install the 18 fasteners at FR35, STGR30, LH and RH sides Work Zones and Access Panels Zone Access/Work location From 130 Access Door 825 Panel 131PW, Panel 132PW Work location from Frame 34 to Frame 35 Stringer 30 To 190 Access Panel 191BT, Panel 192BT Work location from Frame 34 to Frame 35 Stringer 30 Manpower Resources Manhours 0.75 Minimum number of person 1 Subtask elapsed time 0.75 Skills AIRFRAME Material necessary to do the job Kit 531268A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 EN6115K3A7 2 BOLT 4 EN6115K3A8 2 BOLT 6 EN6115K3A10 10 BOLT 8 EN6115K3A12 4 BOLT 10 ASNA2536-3A 18 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001 Structural Repair Manual (SRM) 51-42-00 Fig. A-FBAAA Cold Expansion of the Fasteners Holes at FR35, STGR30, LH and RH sides Sheet 01 Sheet 02 (a) On the LH and RH sides, wet install the fasteners in accordance with SRM 51-42-00 Refer to AMM Task 20-21-11-911-001

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 19 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
1 Apply: Sealant-Brush Consistency 09-013 As required
and install: 2 Bolt EN6115K3A7 Item 2 2 Bolt EN6115K3A8 Item 4 10 Bolt EN6115K3A10 Item 6 4 Bolt EN6115K3A12 Item 8 18 Nut ASNA2536-3A Item 10

(5) Subtask 531268-831-007-001 - Apply the surface protection to the 18 fasteners at FR35, STGR30, LH and RH sides Work Zones and Access Panels Zone Access/Work location From 130 Access Door 825 Panel 131PW, Panel 132PW Work location from Frame 34 to Frame 35 Stringer 30 To 190 Access Panel 191BT, Panel 192BT Work location from Frame 34 to Frame 35 Stringer 30 Manpower Resources Manhours 0.25 Minimum number of person 1 Subtask elapsed time 0.25 Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Corrosion Preventive Compound, Temporary 15-009 As required Polyurethane Top Coat (Grey) 16-002 As required Anti Corrosion Primer Epoxy 16-006 As required

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 20 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (a) Apply to the fasteners: Anti Corrosion Primer Epoxy 16-006 As required Polyurethane Top Coat (Grey) 16-002 As required (b) Then apply to the work areas: Corrosion Preventive Compound, Temporary 15-009 As required

(6) Subtask 531268-831-202-001 - Remove the Fasteners at FR35, between STGR28 and STGR31, LH and RH Work Zones and Access Panels Zone Access/Work location 130 Access Door 825 Panel 131PW, Panel 132PW Work location Frame 35 from Stringer 28 to Stringer 31 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills AIRFRAME Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required References Structural Repair Manual (SRM) 51-42-00 Fig. A-GBAAA Modify the fastener Holes at Frame 35, between STGR28 and STGR31, LH and RH Sheet 01 Sheet 02
Do the steps that follow for the LH and RH side of the aircraft. Refer to Fig. A-GBAAA Sheet 01

.
DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 21 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (a) At Frame 35 between STGR28 and STGR31, remove the fasteners, in accordance with SRM 51-42-00. 1 Remove: 8 Rivet EN6081D6-03 Item (11) Discard 10 Pin-Rivet DAN5-6-4 Item (12) Discard 10 Collar NSA5075-6 Item (13) Discard 2 Clean the work area with: Solvent General Purpose 11-026 As required
Lint-Free Cotton Cloth 19-003 As required (7) Subtask 531268-250-201-001 - Do a Non Destructive Test (NDT) on the Fastener and Tooling Holes Work Zones and Access Panels Zone Access/Work location 130 Access Door 825 Panel 131PW, Panel 132PW Work location Frame 35 from Stringer 28 to Stringer 31 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) Task 51-10-01-250-801 Fig. A-GBAAA Modify the fastener Holes at Frame 35, between STGR28 and STGR31, LH and RH Sheet 01 Sheet 02
Do the steps that follow for the LH and RH side of the aircraft.

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 22 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (a) At Frame 35 between STGR28 and STGR31, inspect the fastener and tooling holes, refer to Fig. A-GBAAA Sheet 01 and Fig. A-GBAAA Sheet 02

. 1 Make sure that the diameter of the holes is not more than the maximum starting hole diameter given in Fig. A-GBAAA Sheet 02

. - If the hole diameter is more than the maximum starting hole diameter, contact AIRBUS - If the hole diameter is not more than the maximum starting hole diameter, do the operation given below. 2 Do a rotating probe test of the holes in accordance with NTM Task 51-10-01-250-801. - If cracks are found, contact AIRBUS. - If no cracks are found, do the operations given below. (8) Subtask 531268-831-204-001 - Do the Cold Expansion and Ream the Holes at FR35, between STGR28 and STGR31, LH and RH Work Zones and Access Panels Zone Access/Work location 130 Access Door 825 Panel 131PW, Panel 132PW Work location Frame 35 from Stringer 28 to Stringer 31 Manpower Resources Manhours 2.50 Minimum number of person 1 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Solvent General Purpose 11-026 As required Lint-Free Cotton Cloth 19-003 As required Standard tool TOOLD01 ITEM TOOL N ̊ TOOL NAME QTY SEE NOTES DKA320531268-1 Durable tooling 1 (1) EKA320531268-1 Expendable tooling 1 (2) FTIA320531268-1 Capital tooling 1 (3)
DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 23 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
NOTE: The operator should make sure that Tool PN LBRA-7 has been delivered with the FTI tool DKA320531268-1. NOTE (1) : The durable tool kit contains the minimum quantity of durable tools necessary to accomplish the Service Bulletin on one aircraft. If the Service Bulletin is to be accomplished on more than one aircraft, the number of durable kits required can be established by reference to SIL 51-012. NOTE (2) : The expendable tool kit contains the quantity of expendable tools required to accomplish the Service Bulletin on one aircraft. Order one expendable tool kit for every aircraft on which this Service Bulletin is to be accomplished. NOTE (3) : The capital tools provided in this kit are not specific to this Service Bulletin and are normally already available in operator’s stock as a long term investment or can be loaned from FTI. References Structural Repair Manual (SRM) 51-48-00 Fig. A-GBAAA Modify the fastener Holes at Frame 35, between STGR28 and STGR31, LH and RH Sheet 01 Sheet 02
Do the steps that follow for the LH and RH of the aircraft. Refer to Fig. A-GBAAA Sheet 01 and Fig. A-GBAAA Sheet 02

. (a) At Frame 35 between STGR28 and STGR31, do the cold the cold expansion of the tooling holes, refer to SRM 51-48-00. 1 Over size the holes to the starting diameter, refer to Fig. A-GBAAA Sheet 02

. Use FTI tool list No.: DKA320531268-1 Durable tooling 1 2 Clean the drilled area with: Solvent General Purpose 11-026 As required
Lint-Free Cotton Cloth 19-003 As required

3 Install the sleeves and obey the split direction given in Fig. A-GBAAA Sheet 02

. 4 Do the cold expansion of the holes. Use FTI tool list No.:

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 24 6

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# @A318/A319/A320/A321 SERVICE BULLETIN FTIA320531268-1 Capital tooling 1 DKA320531268-1 Durable tooling 1 EKA320531268-1 Expendable tooling 1 5 Remove the sleeves. 6 Ream the holes to the final diameter given in Fig. A-GBAAA Sheet 02

. 7 Deburr the holes and clean the drilled area with: Solvent General Purpose 11-026 As required
Lint-Free Cotton Cloth 19-003 As required (b) At Frame 35 between STGR28 and STGR30, do the cold the cold expansion of the fastener holes, refer to SRM 51-48-00. Refer to Fig. A-GBAAA Sheet 01 and Fig. A-GBAAA Sheet 02

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

. Use FTI tool list No.: DKA320531268-1 Durable tooling 1 2 Clean the drilled area with: Solvent General Purpose 11-026 As required
Lint-Free Cotton Cloth 19-003 As required

3 Install the sleeves and obey the split direction given in Fig. A-GBAAA Sheet 02

. 4 Do the cold expansion of the holes. Use FTI tool list No.: DKA320531268-1 Durable tooling 1 FTIA320531268-1 Capital tooling 1 EKA320531268-1 Expendable tooling 1 5 Remove the sleeves.

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 25 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
6 Ream the holes to the final diameter given in Fig. A-GBAAA Sheet 02

. NOTE : The final hole diameter gives an interference fit of the fasteners between -35 μm and -85 μm (-0.0014 in and -0.0033 in). 7 Deburr the holes and clean the drilled area with: Solvent General Purpose 11-026 As required
Lint-Free Cotton Cloth 19-003 As required (c) At Frame 35 between STGR30 and STGR31, do the cold expansion of the fastener holes, refer to SRM 51-48-00. Refer to Fig. A-GBAAA Sheet 01 and Fig. A-GBAAA Sheet 02

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

. Use FTI tool list No.: DKA320531268-1 Durable tooling 1 2 Clean the drilled area with: Solvent General Purpose 11-026 As required
Lint-Free Cotton Cloth 19-003 As required

3 Install the sleeves and obey the split direction given in Fig. A-GBAAA Sheet 02

. 4 Do the cold expansion of the holes. Use FTI tool list No.: FTIA320531268-1 Capital tooling 1 DKA320531268-1 Durable tooling 1 EKA320531268-1 Expendable tooling 1 NOTE : It is necessary to use, FTI Tool LBRA-7, right angled adaptor, to cold expand two holes, refer to Fig. A-GBAAA Sheet 02

. 5 Remove the sleeves.

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 26 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
6 Ream the holes to the final diameter given in Fig. A-GBAAA Sheet 02

. NOTE : The final hole diameter gives an interference fit of the fasteners between -35 μm and -85 μm (-0.0014 in and -0.0033 in). 7 Deburr the holes and clean the drilled area with: Solvent General Purpose 11-026 As required
Lint-Free Cotton Cloth 19-003 As required (9) Subtask 531268-831-205-001 - Install the Fasteners at FR35, between STGR28 and STGR31, LH and RH Work Zones and Access Panels Zone Access/Work location 130 Access Door 825 Panel 131PW, Panel 132PW Work location Frame 35 from Stringer 28 to Stringer 31 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Kit 531268D01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 14 EN6115K3A4 10 BOLT 15 EN6115K3A3 8 BOLT 16 ASNA2536-3A 18 NUT Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant-Brush Consistency 09-013 As required References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001 Structural Repair Manual (SRM) 51-42-00

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 27 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
References Fig. A-GBAAA Modify the fastener Holes at Frame 35, between STGR28 and STGR31, LH and RH Sheet 01 Sheet 02
Do the steps that follow for the LH and RH of the aircraft Refer to Fig. A-GBAAA Sheet 01 and Fig. A-GBAAA Sheet 02

. (a) At Frame 35 between STGR28 and STGR31, install the fasteners, in accordance with SRM 51-42-00. Refer to Fig. A-GBAAA Sheet 02

. 1 Use: Sealant-Brush Consistency 09-013 As required
to wet install: 10 Bolt EN6115K3A4 Item 14 8 Bolt EN6115K3A3 Item 15 18 Nut ASNA2536-3A Item 16 2 Torque tighten the fasteners refer to AMM Task 20-21-11-911-001. (10) Subtask 531268-831-206-001 - Apply the Surface Protection at FR35, between STGR28 and STGR31, LH and RH Work Zones and Access Panels Zone Access/Work location 130 Access Door 825 Panel 131PW, Panel 132PW Work location Frame 35 from Stringer 28 to Stringer 31 Manpower Resources Manhours 0.50 Minimum number of person 1 Subtask elapsed time 0.50 Skills NON SPECIFIC

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 28 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
Material necessary to do the job Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Corrosion Preventive Compound, Temporary 15-009 As required Anti-Corrosion Primer (Polyurethane) 16-001 As required Polyurethane Top Coat (Grey) 16-002 As required
References Structural Repair Manual (SRM) 51-23-12 51-75-12 Fig. A-GBAAA Modify the fastener Holes at Frame 35, between STGR28 and STGR31, LH and RH Sheet 01 Sheet 02
Do the steps that follow for the LH and RH of the aircraft. Refer to Fig. A-GBAAA Sheet 01 and Fig. A-GBAAA Sheet 02

. (a) At Frame 35 between STGR28 and STGR31, renew the protective finish in accordance with SRM 51-75-12. 1 Apply: Anti-Corrosion Primer (Polyurethane) 16-001 As required
Polyurethane Top Coat (Grey) 16-002 As required (b) Renew the special protection in accordance with SRM 51-23-12. 1 Apply: Corrosion Preventive Compound, Temporary 15-009 As required

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 29 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
D. TEST (1) Subtask 531268-720-201-001 - Testing Work Zones and Access Panels Zone Access/Work location 130 Access Door 825 Panel 131PW, Panel 132PW Manpower Resources Skills UTILITY References Aircraft Maintenance Manual (AMM) Task 38-11-41-400-002 (a) If the potable water tank 3000MM was removed for access, do a leak test of the potable water system, refer to AMM Task 38-11-41-400-002. E. CLOSE-UP (1) Subtask 531268-410-201-001 - Install/Close Items Removed/Opened for access Work Zones and Access Panels Zone Access/Work location 130 Access Door 825 Panel 131PW, Panel 132PW Manpower Resources Manhours 3.00 Minimum number of person 2 Subtask elapsed time 1.50 Skills AIRFRAME References Aircraft Maintenance Manual (AMM) Task 21-21-41-400-001 Task 25-80-00-400-001 Task 38-11-41-400-002 (a) If removed, install electrical bundle clamps. (b) Install the heat and sound insulation blankets in the area between Frame 35 and Frame 36 LH and RH, refer to AMM Task 25-80-00-400-001. (c) If removed, install the potable water tank 3000MM and ventilation ducts, refer to AMM Task 38-11-41-400-002. (d) If removed, install the air conditioning recirculation filters 4012HM LH and 4013HM RH, refer to AMM Task 21-21-41-400-001.

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 30 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (2) Subtask 531268-942-202-001 - Close-up Work Zones and Access Panels Zone Access/Work location 130 Access Door 825 Panel 131PW, Panel 132PW, Panel 191BT, Panel 192BT Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) Task 25-54-12-400-001 Task 52-30-00-860-002 Task 53-35-11-400-001 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) At FR34 install the FWD cargo compartment partitions 131PW, 132PW and if removed 131NW, refer to AMM Task 25-54-12-400-001. (c) Install the wing-to-fuselage fairings 191BT and 192BT, refer to AMM Task 53-35-11-400-001. (d) Close the FWD cargo compartment door.825, refer to AMM Task 52-30-00-860-002. (e) Remove the access platform(s).

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 31 6

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

STGR30LH STGR29LH FR35 825 Z130 

### A

LH SIDE SHOWN RH SIDE SYMMETRICAL 

## A B

N_SB_531268_5_BAAA_01_01 Figure A-FBAAA - Sheet 01 Cold Expansion of the Fasteners Holes at FR35, STGR30, LH and RH sides
DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 32 6

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

VIEW LOOKING OUTSIDE LH SIDE SHOWN RH SIDE SYMMETRICAL

HEAD ON THE HIDDEN SIDE FASTENER NOT AFFECTED IF THE EXISTING HOLE DIAMETER IS MORE THAN THE MAX. STARTING HOLE DIAMETER OR IF CRACK IS FOUND IN THE HOLE, CONTACT AIRBUS FASTENER

SYMBOL ITEM PN KEYWORD REMARK STDN STARTING HOLE DIAMETER FINAL HOLE DIAMETER MIN MAX (1) 2 (9) 10 (3) 4 (9) 10 (5) 6 (9) 10 (7) 8 (9) 10 EN6115K3A7 ASNA2536

−3A EN6115K3A8 ASNA2536

−3A EN6115K3A10 ASNA2536

−3A AN6115K3A12 ASNA2536

−3A BOLT NUT BOLT NUT BOLT NUT BOLT NUT 6

−1

−N 4.88 mm (0.1921 in) 4.93 mm (0.1941 in) 5.452 mm (0.2146 in) 5.487 mm (0.2160 in) MIN MAX

EXPANSION SLEEVE INSTALLATION ORIENTATION SCHEMATIC DIAGRAM F
F
F
F

F FWD STGR29

STGR30

FR35

NOTE: 01 01 

## B

N_SB_531268_5_BAAA_02_01

Figure A-FBAAA - Sheet 02 Cold Expansion of the Fasteners Holes at FR35, STGR30, LH and RH sides
DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 33 6

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL



### A Z240

FR35 FR42 

## A Z140 

### B C B C


### BEFORE

STGR28

STGR29

STGR30

STGR31 Y1282.0 FR35

LH SHOWN, RH SIMILAR 

## B VIEW LOOKING FWD DESCRIPTION ITEM HOLE SYMBOL (11) RIVET (12) RIVET, HI

−LOK (13) COLLAR, HI

−LOK TOOLING HOLE TOOLING

HOLE

N_SB_531268_6_BAAA_01_03 Figure A-GBAAA - Sheet 01 Modify the fastener Holes at Frame 35, between STGR28 and STGR31, LH and RH
DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 34 6

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# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

LH SHOWN, RH SIMILAR VIEW LOOKING FWD

P/N DESCRIPTION MIN MAX ITEM STDN HOLE SYMBOL HOLE DIAMETER
14 EN6115K3A4 BOLT 4.93 mm (0.192 in) (0.195 in) 6

−1

−N 4.88 mm MIN MAX HOLE DIAMETER
5.452 mm 5.487 mm (0.2146 in) (0.2160 in) STARTING FINAL

FASTENER NOT AFFECTED. NOTE: 01 COLD EXPAND TWO TOOLING HOLES IN ACCORDANCE WITH SRM 51

−48

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

−48

−00. 01 02

02

16 ASNA2536

−3A NUT 15 EN6115K3A3 BOLT 16 ASNA2536

−3A NUT STGR28

STGR29

STGR30

STGR31 Y1282.0 FR35 

### AFTER

02

TOOLING HOLE 8

−1

−N 7 mm (0.276 in) 4.93 mm (0.192 in) (0.195 in) 4.88 mm 5.452 mm 5.487 mm (0.2146 in) (0.2160 in) 

## C TOOLING HOLE 01 TOOLING HOLE

6.45 mm (0.254 in) 6.38 mm (0.251 in) ORIENTATION SCHEMATIC DIAGRAM

= EXPANSION SLEEVE INSTALLATION.

03 IT IS NECESSARY TO USE FTI TOOL LBRA

−7, RIGHT ANGLED ADAPTOR, TO COLD EXPAND THESE HOLES. 03 02

N_SB_531268_6_BAAA_02_04 Figure A-GBAAA - Sheet 02 Modify the fastener Holes at Frame 35, between STGR28 and STGR31, LH and RH
DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 35 6

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# @A318/A319/A320/A321 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 36 6

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# @A318/A319/A320/A321 SERVICE BULLETIN APPENDIX 01: Elapsed Time Assumption

**CONF ALL

ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A320−53−1268

SB ELAPSED TIME (HOURS) JOB SET UP MH ET/S

TOTAL MANHOURS SB ELAPSED TIME 21.00 15.50 STEPS
5.00 2.50

CLOSE

−UP 6.00 3.00

MH ET/S: PER MANHOURS ELAPSED TIME PER STEP NUMBER OF PERSONS 01 02

THIS CHART IS ONLY A PROPOSAL. OPERATORS MAY DETERMINE THAT ANOTHER WAY TO DO THE WORK IS MORE SUITABLE FOR THEM. 01
02 NOTE: PER

2

2

: : IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS ARE NOT REFLECTED IN THIS GANTT CHART. REMOVE THE 18 FASTENERS AT FR35, STGR30, 0.50 0.50 1 0.50 0.50 1 0.50 0.50 1 0.50 0.50 1 2.00 2.00 1 2.50 2.50 1 0.75 0.75 1 1.00 1.00 1 0.25 0.25 1 0.50 0.50 1 TEST 1.00 1.00 1 LH AND RH REMOVE THE FASTENERS AT FR35, BETWEEN STGR28 AND STGR31 LH AND RH DO THE NDT ON THE 18 FASTENER HOLES AT FR35, STGR30, LH AND RH DO THE NDT ON THE FASTENER AND TOOLING HOLES AT FR35 BETWEEN STGR28 AND STGR31 LH AND RH DO THE COLD EXPANSION AND REAM THE 18 HOLES AT FR35, STGR30, LH AND RH DO THE COLD EXPANSION AND REAM THE HOLES AT FR35, BETWEEN STGR28 AND STGR31 LH AND RH INSTALL THE 18 FASTENER HOLES AT FR35, STGR30, LH AND RH INSTALL THE FASTENERS AT FR35, BETWEEN STGR28 AND STGR31 LH AND RH APPLY SURFACE PROTECTION TO THE 18 FASTENER HOLES AT FR35, STGR30, LH AND RH APPLY SURFACE PROTECTION AT FR35 BETWEEN STGR28 AND STGR31 LH AND RH

5 10 15 20 0

N_SB_531268_6_AAAA_01_01 Figure A-GAAAA - Sheet 01 Gantt Chart
DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 1 6

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

### TITLE: FUSELAGE - CENTER FUSELAGE - REINFORCE FORWARD PRESSURE BULKHEAD AT FRAME COUPLING C35 LH/RH MODIFICATION No.: 153832K16057 Please complete the appropriate item (A or B): A - SB WILL BE embodied YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiment:

B - SB HAS BEEN embodied on aircraft: Operator comments:
From Airline: Name/Title: Signature: Date: If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to next normal revision or prior to SB embodiment, please indicate required service(s): Either: Modification Operational Impact (MOI), if available YES/NO Or : Intermediate revision YES/NO Important Information: This SB will only be incorporated in your maintenance and operational documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With the next feasible revision, this will result in - Updating of maintenance documentation to show pre and post SB data. - Updating of maintenance and operational documentation to show post SB data after embodiment. If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically include them in the manual revisions. Refer to SIL 00-037 for detailed information. Please return this completed sheet to: AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Attn: SDC32 Technical Data and Documentation Services FAX: (+33) 5 61 93 28 06 e-mail: sb.reporting@airbus.com or via your Resident Customer Support Office. Alternatively, SB lists via letters or fax are also accepted.

DATE: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 1 6

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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: Jan 08/13 SERVICE BULLETIN No.: A320-53-1268 REVISION No.: 03 - May 07/15 Page: 1 6

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