# @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 - CONE/REAR FUSELAGE - REPLACE CLIPS, SHEARWEBS AND ANGLES IN SECTION 19 AT FR 72 AND FR 74 MODIFICATION No.: 153833K16120 This page transmits Revision No.03 of Service Bulletin No.A320-53-1266 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: - update the Accomplishment Timescale in the COMPLIANCE paragraph - add Kit D11 for new Config 004 - add aircraft with the Manufacturer Serial Number (MSN) 0202, 0209, 0216, 0267-0269, 0346 and 0382 to the effectivity of this Service Bulletin - remove aircraft with the MSN 0147 from the effectivity of this Service Bulletin - add ALS in PUBLICATION AFFECTED paragraph. CHANGES FRONT MATTER FUSELAGE - CONE/REAR FUSELAGE - REPLACE CLIPS, SHEARWEBS AND ANGLES IN SECTION 19 AT FR 72 AND FR 74 CONFIGURATION UPDATED R

SUMMARY MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE ADDED N MANPOWER MANPOWER ADDED N

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 1 6

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# @A318/A319/A320/A321 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R Configuration definition CONFIGURATION LIST UPDATED R CONF 002 CONFIGURATION DEFINITION UPDATED CONFIGURATION DESCRIPTION UPDATED R CONF 003 CONFIGURATION DEFINITION UPDATED CONFIGURATION DESCRIPTION UPDATED R CONF 004 CONFIGURATION ADDED N Material Effectivity MATERIAL EFFECTIVITY ADDED N DESCRIPTION DESCRIPTION UPDATED R COMPLIANCE Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R MANPOWER MANPOWER ADDED N WEIGHT AND BALANCE CONFIGURATION UPDATED R Minor editorial or document structure change R Minor editorial or document structure change R REFERENCES REFERENCED DOCUMENTATION ADDED N PUBLICATION AFFECTED PUBLICATIONS AFFECTED UPDATED R MATERIAL INFORMATION MATERIAL - PRICE AND AVAILABILITY Procurement Addresses PROCUREMENT ADDRESSES UPDATED MATERIAL SET UPDATED R LIST OF COMPONENTS LIST OF COMPONENTS UPDATED R Kit 531266D11R02 PART MATERIAL SET ADDED N Kit 531266D14R00 PART MATERIAL SET UPDATED QUANTITY UPDATED R ACCOMPLISHMENT INSTRUCTIONS TASK 531266- 831-848-001-Modification TASK SOLUTION UPDATED NOTE UPDATED R Task associated data - 004 TASK ASSOCIATED DATA ADDED N Subtask 531266-910-201-001 SUBTASK SOLUTION ADDED N Subtask 531266-839-201-001 SUBTASK SOLUTION ADDED N Subtask 531266-941-201-001 SUBTASK SOLUTION ADDED N Subtask 531266-020-203-003 SUBTASK SOLUTION UPDATED QUANTITY UPDATED R Subtask 531266-420-203-003 SUBTASK SOLUTION UPDATED QUANTITY UPDATED MATERIAL LIST UPDATED R
Subtask 531266-020-204-003 SUBTASK SOLUTION UPDATED QUANTITY UPDATED R Subtask 531266-020-201-004 SUBTASK SOLUTION ADDED N Subtask 531266-420-201-004 SUBTASK SOLUTION ADDED N Subtask 531266-020-208-004 SUBTASK SOLUTION ADDED N Subtask 531266-420-202-004 SUBTASK SOLUTION ADDED N Subtask 531266-020-203-004 SUBTASK SOLUTION ADDED N Subtask 531266-420-203-004 SUBTASK SOLUTION ADDED N DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 2 6

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# @A318/A319/A320/A321 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Subtask 531266-020-204-004 SUBTASK SOLUTION ADDED N Subtask 531266-420-204-004 SUBTASK SOLUTION ADDED N Subtask 531266-700-201-001 SUBTASK SOLUTION ADDED N Subtask 531266-942-201-001 SUBTASK SOLUTION UPDATED R Subtask 531266-942-201-001 SUBTASK SOLUTION UPDATED R Subtask 531266-942-201-001 SUBTASK SOLUTION UPDATED R Subtask 531266-942-201-001 SUBTASK SOLUTION ADDED N Fig. A-GBBAE FIGURE SOLUTION ADDED N Fig. A-GBBAE Sheet 01 SHEET ADDED N Fig. A-GBBAE Sheet 02 SHEET ADDED N Fig. A-GBBAE Sheet 03 SHEET ADDED N Fig. A-GBBAE Sheet 04 SHEET ADDED N Fig. A-GBCAE FIGURE SOLUTION ADDED N Fig. A-GBCAE Sheet 01 SHEET ADDED N Fig. A-GBCAE Sheet 02 SHEET ADDED N Fig. A-GBCAE Sheet 03 SHEET ADDED N Fig. A-GBCAE Sheet 04 SHEET ADDED N Fig. A-GBDAA Fig. A-GBDAA Sheet 01 SHEET UPDATED R Fig. A-GBDAB Fig. A-GBDAB Sheet 01 SHEET UPDATED R Fig. A-GBDAD Fig. A-GBDAD Sheet 01 SHEET UPDATED R Fig. A-GBDAE FIGURE SOLUTION ADDED N Fig. A-GBDAE Sheet 01 SHEET ADDED N 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 is issued to incorporate the results from the Service Bulletin validation and to extend the effectivity. The defect reports as described in TA-SEMBN-2013-867945 have been integrated. This Service Bulletin has been validated on A320 aircraft with Manufacturer Serial Number (MSN) 0401. Revision No. 02 issued to: change the compliance of this Service Bulletin to Mandatory 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). DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 3 6

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# @A318/A319/A320/A321 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Kit D13 cancelled and kit D14 added update the aircraft effectivity. REVISION SEQUENCE ORIGINAL: Jan 11/13 REVISION No. : 01 - Jun 20/13 REVISION No. : 02 - Aug 13/14 REVISION No. : 03 - May 07/15

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 4 6

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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 - CONE/REAR FUSELAGE - REPLACE CLIPS, SHEARWEBS AND ANGLES IN SECTION 19 AT FR 72 AND FR 74 **CONF ALL MODIFICATIONS MODIFICATION CLASSIFICATION MAJOR None MINOR 153833K16120 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 damage finding tests on A320 aircraft, a full scale fatigue test specimen was carried out. This was done to enable the Extended Service Goal (ESG) to be effective after reaching an accumulated Flight Cycle/Flight Hours. The analysis identified in the Cone/Rear Fuselage area (Section19, FR72 and FR74) - Clips, Shearwebs and Angles resulted in a non-serviceable condition and needed to be replaced. This Service Bulletin details the instructions to modify the Clips, Shearwebs and Angles in the Cone/Rear Fuselage area (Section19, FR72 and FR74). These parts are supplied with pilot holes. The accomplishment of this Service Bulletin will remove the risk of fatigue failure (identified during the ESG tests), reinforce the Cone/Rear Fuselage area and contribute to ensure that ESG is achieved. This Service Bulletin has been validated at revision No.00 on A320 aircraft with 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. This Service Bulletin is based on the aircraft configuration as known by AIRBUS (first aircraft delivery configuration and modified by the reported incorporation of AIRBUS Service Bulletins).

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 1 6

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# @A318/A319/A320/A321 SERVICE BULLETIN SUMMARY Prior to Service Bulletin embodiment, the operator is reminded to pay specific attention to structural damage which may exist and to repairs which were performed on the aircraft because they may be affected by the Service Bulletin. Operators must verify that all allowable damage limits and repairs performed (both in accordance with the SRM and outside the SRM) are still applicable and effective to the new Service Bulletin configuration. There may be additional or modified maintenance requirements, such as temporary limits or additional inspections, that apply with respect to the Service Bulletin configuration. AIRBUS disclaims any liability for the effect which the Service Bulletin may have on repairs performed on the aircraft before embodiment of the Service Bulletin. If the post Service Bulletin repair status is no more covered by the SRM and for repairs outside of the SRM covered by a RAS issued by AIRBUS, the operator should contact AIRBUS Customer Services Repair Engineering Support (SER1). Repair review will be done by AIRBUS at conditions of the Customer Services Catalogue. 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 SB VALIDATION YES BOOKLET YES NOTE (1) : Service Bulletin must be accomplished. NOTE : This Service Bulletin has been validated at revision No.00 on A320 aircraft with 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. 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 **CONF 001 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 531266D01R04 1 See SB Webs, Clips, Angles and Hardware **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 531266D12R02 1 See SB Webs, Clips, Angles and Hardware
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 2 6

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# @A318/A319/A320/A321 SERVICE BULLETIN SUMMARY **CONF 003 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 531266D14R00 1 See SB Webs, Clips, Angles and Hardware **CONF 004 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 531266D11R02 1 See SB Webs, Clips, Angles and Hardware EFFECTIVITY **CONF ALL 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 None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 3 6

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# @A318/A319/A320/A321 SERVICE BULLETIN SUMMARY SOFT NO OBRM NO MANPOWER **CONF 001 Task 531266-831-848-001: Modification TOTAL MANHOURS 110.00 ELAPSED TIME (HOURS) 106.0 **CONF 002 Task 531266-831-848-001: Modification TOTAL MANHOURS 110.00 ELAPSED TIME (HOURS) 106.0 **CONF 003 Task 531266-831-848-001: Modification TOTAL MANHOURS 110.00 ELAPSED TIME (HOURS) 106.0 **CONF 004 Task 531266-831-848-001 : Modification TOTAL MANHOURS 110.00 ELAPSED TIME (HOURS) 106.0 APPENDICES **CONF ALL Appendix 01: Elapsed Time Assumption

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 4 6

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# @A318/A319/A320/A321 SERVICE BULLETIN SUMMARY
**CONF ALL



### A

N_SB_531266_6_SAAA_01_00 Z310

FR72 FR74

ACCESS DOORS

SKIN PLATES VERTICAL STABILIZER ATTACHMENT FITTING



## A FR77

FR70

Figure A-GSAAA - Sheet 01

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 5 6

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

This Page Intentionally Left Blank

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 6 6

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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 - CONE/REAR FUSELAGE - REPLACE CLIPS, SHEARWEBS AND ANGLES IN SECTION 19 AT FR 72 AND FR 74 MODIFICATION No.: 153833K16120 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 11/13 SERVICE BULLETIN No.: A320-53-1266 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 002 0161 0162 0172 0200 0201 0202 0209 0216 0217 0218 0267 0268 0269 003 0346 0382 004 0401 001 (5) Configuration definition **CONF 001 Config. 001 is valid for aircraft MSN 0401. **CONF 002 Config. 002 is valid for aircraft MSN 0069 , 0070 , 0071 , 0072 , 0078 , 0083 , 0086 , 0093 , 0094 , 0104 , 0110 , 0111 , 0116 , 0117 , 0135 and 0137

. **CONF 003 Config. 003 is valid for aircraft MSN 0161 , 0162 , 0172 , 0200 , 0201 , 0202 , 0209 , 0216 , 0217 , 0218 , 0267 , 0268 and 0269

. **CONF 004 Config. 004 is valid for aircraft MSN 0346 and 0382. (6) Material Effectivity **CONF 001 MATERIAL QTY PER A/C SEE NOTES Kit 531266D01R04 1 Consumable CMLD01 1 **CONF 002 MATERIAL QTY PER A/C SEE NOTES Kit 531266D12R02 1 Consumable CMLD01 1 **CONF 003 MATERIAL QTY PER A/C SEE NOTES Kit 531266D14R00 1 Consumable CMLD01 1

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 2 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
**CONF 004 MATERIAL QTY PER A/C SEE NOTES Kit 531266D11R02 1 Consumable CMLD01 1 **CONF ALL B. CONCURRENT REQUIREMENTS None C. REASON (1) History During damage finding tests on A320 aircraft, a full scale fatigue test specimen was carried out. This was done to enable the Extended Service Goal (ESG) to be effective after reaching an accumulated Flight Cycle/Flight Hours. The analysis identified in the Cone/Rear Fuselage area (Section19, FR72 and FR74) - Clips, Shearwebs and Angles resulted in a non-serviceable condition and needed to be replaced. (2) Objective/Action This Service Bulletin details the instructions to modify the Clips, Shearwebs and Angles in the Cone/Rear Fuselage area (Section19, FR72 and FR74). These parts are supplied with pilot holes. (3) Advantages The accomplishment of this Service Bulletin will remove the risk of fatigue failure (identified during the ESG tests), reinforce the Cone/Rear Fuselage area and contribute to ensure that ESG is achieved. This Service Bulletin has been validated at revision No.00 on A320 aircraft with 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. (4) Operational/Maintenance Consequences This Service Bulletin is based on the aircraft configuration as known by AIRBUS (first aircraft delivery configuration and modified by the reported incorporation of AIRBUS Service Bulletins).

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 3 6

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# @A318/A319/A320/A321 SERVICE BULLETIN Prior to Service Bulletin embodiment, the operator is reminded to pay specific attention to structural damage which may exist and to repairs which were performed on the aircraft because they may be affected by the Service Bulletin. Operators must verify that all allowable damage limits and repairs performed (both in accordance with the SRM and outside the SRM) are still applicable and effective to the new Service Bulletin configuration. There may be additional or modified maintenance requirements, such as temporary limits or additional inspections, that apply with respect to the Service Bulletin configuration. AIRBUS disclaims any liability for the effect which the Service Bulletin may have on repairs performed on the aircraft before embodiment of the Service Bulletin. If the post Service Bulletin repair status is no more covered by the SRM and for repairs outside of the SRM covered by a RAS issued by AIRBUS, the operator should contact AIRBUS Customer Services Repair Engineering Support (SER1). Repair review will be done by AIRBUS at conditions of the Customer Services Catalogue. D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 531266-831-848-001: Modification (1) Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, LH and STGR1, RH (2) Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR1, RH and STGR13, LH (3) Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, RH and STGR3, RH (4) Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR3, RH to STGR13, RH (5) Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, LH and STGR1, RH (6) Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR1, RH and STGR12, LH (7) Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, RH and STGR3, RH (8) Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR3, RH and STGR12, RH **CONF 002 Task 531266-831-848-001: Modification (1) Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, LH and STGR1, RH DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 4 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (2) Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR1, RH and STGR13, LH (3) Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, RH and STGR3, RH (4) Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR3, RH to STGR13, RH (5) Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, LH and STGR1, RH (6) Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR1, RH and STGR12, LH (7) Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, RH and STGR3, RH (8) Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR3, RH and STGR12, RH **CONF 003 Task 531266-831-848-001: Modification (1) Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, LH and STGR1, RH (2) Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR1, RH and STGR13, LH (3) Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, RH and STGR3, RH (4) Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR3, RH to STGR13, RH (5) Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, LH and STGR1, RH (6) Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR1, RH and STGR12, LH (7) Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, RH and STGR3, RH (8) Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR3, RH and STGR12, RH **CONF 004 Task 531266-831-848-001 : Modification (1) Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, LH DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 5 6

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# @A318/A319/A320/A321 SERVICE BULLETIN and STGR1, RH (2) Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR1, RH and STGR13, LH (3) Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, RH and STGR3, RH (4) Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR3, RH to STGR13, RH (5) Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, LH and STGR1, RH (6) Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR1, RH and STGR12, LH (7) Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, RH and STGR3, RH (8) Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR3, RH and STGR12, RH **CONF ALL E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale This Service Bulletin is mandatory for ESG operation above 48000 FC or 96000 FH from aeroplane first flight 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.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 6 6

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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. **CONF 001 Task 531266-831-848-001: Modification Get Access 3.00 On Aircraft Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, LH and STGR1, RH 13.00 Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR1, RH and STGR13, LH 16.00 Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, RH and STGR3, RH 11.00 Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR3, RH to STGR13, RH 14.00 Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, LH and STGR1, RH 11.00 Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR1, RH and STGR12, LH 14.00 Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, RH and STGR3, RH 11.00 Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR3, RH and STGR12, RH 12.00 Tests 1.00 Close-Up 4.00 TOTAL MANHOURS 110.00 ELAPSED TIME (HOURS) 106.0 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 **CONF 002 Task 531266-831-848-001: Modification Get Access 3.00 On Aircraft Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, LH and STGR1, RH 13.00 Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR1, RH and STGR13, LH 16.00 Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, RH and STGR3, RH 11.00

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 7 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
Task 531266-831-848-001: Modification Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR3, RH to STGR13, RH 14.00 Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, LH and STGR1, RH 11.00 Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR1, RH and STGR12, LH 14.00 Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, RH and STGR3, RH 11.00 Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR3, RH and STGR12, RH 12.00 Tests 1.00 Close-Up 4.00 TOTAL MANHOURS 110.00 ELAPSED TIME (HOURS) 106.0 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 **CONF 003 Task 531266-831-848-001: Modification Get Access 3.00 On Aircraft Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, LH and STGR1, RH 13.00 Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR1, RH and STGR13, LH 16.00 Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, RH and STGR3, RH 11.00 Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR3, RH to STGR13, RH 14.00 Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, LH and STGR1, RH 11.00 Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR1, RH and STGR12, LH 14.00 Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, RH and STGR3, RH 11.00 Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR3, RH and STGR12, RH 12.00 Tests 1.00 Close-Up 4.00 TOTAL MANHOURS 110.00 ELAPSED TIME (HOURS) 106.0 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

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 8 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
**CONF 004 Task 531266-831-848-001 : Modification Get Access 3.00 On Aircraft Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, LH and STGR1, RH 13.00 Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR1, RH and STGR13, LH 16.00 Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, RH and STGR3, RH 11.00 Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR3, RH to STGR13, RH 14.00 Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, LH and STGR1, RH 11.00 Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR1, RH and STGR12, LH 14.00 Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, RH and STGR3, RH 11.00 Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR3, RH and STGR12, RH 12.00 Tests 1.00 Close-Up 4.00 TOTAL MANHOURS 110.00 ELAPSED TIME (HOURS) 106.0 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

. **CONF ALL H. WEIGHT AND BALANCE **CONF 001, 004 The weight and balance estimates given in this Service Bulletin are based on the Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition of MEW and operator’s items, refer to Weight and Balance Manual (WBM) Chapter 1-00-07. A320: Manufacturers Empty Weight +0.117 KG (+0.2579 LB) Effect on Balance +4.087 KGM (+29.561 LB.FT ) **CONF 002 The weight and balance estimates given in this Service Bulletin are based on the Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition of MEW and operator’s items, refer to Weight and Balance Manual (WBM) Chapter 1-00-07. A320:DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 9 6

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# @A318/A319/A320/A321 SERVICE BULLETIN Manufacturers Empty Weight +0.145 KG (+0.3196 LB Effect on Balance +5.068 KGM (+36.656 LB.FT ) **CONF 003 The weight and balance estimates given in this Service Bulletin are based on the Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition of MEW and operator’s items, refer to Weight and Balance Manual (WBM) Chapter 1-00-07. A320: Manufacturers Empty Weight +0.115 KG (+0.2535 LB) Effect on Balance +4.014 KGM (+29.033 LB.FT ) **CONF ALL I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-53 12-34-24 20-16-00 20-21-11 29-00-00 29-11-00 29-13-00 36-12-00 36-12-41 52-10-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-33-11 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 51-10-08 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-40-11 51-42-00 51-43-00 51-44-00 51-75-12 Weight and Balance Manual (WBM) Weight and Balance Manual (WBM) Chapter 1-00-07 **CONF 002 Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-53 12-34-24 20-16-00 20-21-11 29-00-00 29-11-00 29-13-00 36-12-00 36-12-41 52-10-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-33-11 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 51-10-08 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-40-11 51-42-00 51-43-00 51-44-00 51-75-12 Weight and Balance Manual (WBM) Weight and Balance Manual (WBM) Chapter 1-00-07
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 10 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
**CONF 003 Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-53 12-34-24 20-16-00 20-21-11 29-00-00 29-11-00 29-13-00 36-12-00 36-12-41 52-10-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-33-11 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 51-10-08 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-40-11 51-42-00 51-43-00 51-44-00 51-75-12 Weight and Balance Manual (WBM) Weight and Balance Manual (WBM) Chapter 1-00-07 **CONF 004 Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-53 12-34-24 20-16-00 20-21-11 29-00-00 29-11-00 29-13-00 36-12-00 36-12-41 52-10-00 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-33-11 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 51-10-08 Standards Manual (SM) Structural Repair Manual (SRM) 51-24-00 51-40-11 51-42-00 51-43-00 51-44-00 51-75-12 Weight and Balance Manual (WBM) Weight and Balance Manual (WBM) Chapter 1-00-07 **CONF ALL K. PUBLICATION AFFECTED

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

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 11 6

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# @A318/A319/A320/A321 SERVICE BULLETIN

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DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 12 6

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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 531266D01R04 Kit 531266D12R02 Kit 531266D14R00 Kit 531266D11R02 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 531266D01R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 D5357113140000 1 ANGLE (1) D5357113140000 2 D5357113140100 1 ANGLE (2) D5357113140100 3 D5357113146800 1 WEB (3) D5357113146800 4 D5357113146900 1 WEB (4) D5357113146900 5 D5357113143800 1 WEB (5) D5357113143800 6 D5357113143900 1 WEB (6) D5357113143900 7 D5357113144000 1 CLIP (7) D5357113144000 8 D5357113144100 1 CLIP (8) D5357113144100 9 D5357113146600 1 CLIP (9) D5357113146600 10 D5357113146700 1 CLIP (10) D5357113146700 11 D5357113143600 1 WEB (11) D5357113143600 12 D5357113143700 1 WEB (12) D5357113143700 13 D5357113145600 1 ANGLE (13) D5357113145600 14 D5357113145700 1 ANGLE (14) D5357113145700 15 D5357113145000 1 CLIP (15) D5357113145000 16 D5357113145100 1 CLIP (16) D5357113145100
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 13 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 17 D5357113145400 1 ANGLE (17) D5357113145400 18 D5357113145500 1 ANGLE (18) D5357113145500 19 D5357113144800 1 CLIP (19) D5357113144800 20 D5357113144900 1 CLIP (20) D5357113144900 21 D5357113144600 1 WEB (21) D5357113144600 22 D5357113144700 1 WEB (22) D5357113144700 23 D5357113145200 1 ANGLE (23) D5357113145200 24 D5357113145300 1 ANGLE (24) D5357113145300 25 D5357113145800 1 ANGLE (25) D5357113145800 26 D5357113145900 1 ANGLE (26) D5357113145900 27 D5357113144400 1 CLIP (27) D5357113144400 28 D5357113144500 1 CLIP (28) D5357113144500 29 D5357072225600 1 ANGLE (29) D5357072225600 30 D5357072225700 1 ANGLE (30) D5357072225700 31 D5357072224400 1 CLIP (31) D5357072224400 32 D5357072224500 1 CLIP (32) D5357072224500 33 D5357072226000 1 ANGLE (33) D5357072226000 34 D5357072226100 1 ANGLE (34) D5357072226100 35 D5357113144200 1 WEB (35) D5357113144200 36 D5357072225400 1 ANGLE (36) D5357072225400 37 D5357072225500 1 ANGLE (37) D5357072225500 38 D5357072225800 1 ANGLE (38) D5357072225800 39 D5357072225900 1 ANGLE (39) D5357072225900 40 D5357072224600 1 CLIP (40) D5357072224600 41 D5357072224700 1 CLIP (41) D5357072224700 42 D5357072225200 1 ANGLE (42) D5357072225200 43 D5357072225300 1 ANGLE (43) D5357072225300 44 D5357072224800 1 WEB (44) D5357072224800 45 D5357072224900 1 WEB (45) D5357072224900 46 D5357072225000 1 CLIP (46) D5357072225000 47 D5357072225100 1 CLIP (47) D5357072225100 48 D5357072224200 2 CLIP (48) D5357072224200 49 D5357072224000 1 WEB (49) D5357072224000 50 D5357116122000 1 WEB (50) D5357116122000 51 D5357113339600 1 ANGLE (51) D5357113339600 52 D5357113339700 1 ANGLE (52) D5357113339700 53 D5357113339800 2 FILLER (53) D5357113339800 54 D5357113321400 1 ANGLE (54) D5357113321400 55 D5357113321500 1 ANGLE (55) D5357113321500 56 D5357113337200 1 ANGLE (56) D5357113337200 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 14 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 57 D5357113337300 1 ANGLE (57) D5357113337300 58 D5357113337000 1 ANGLE (58) D5357113337000 59 D5357113337100 1 ANGLE (59) D5357113337100 60 D5357113340000 1 WEB (60) D5357113340000 61 D5357113340100 1 WEB (61) D5357113340100 62 D5357113339400 1 WEB (62) D5357113339400 63 D5357113339500 1 WEB (63) D5357113339500 64 D5357113339000 1 ANGLE (64) D5357113339000 65 D5357113339100 1 ANGLE (65) D5357113339100 66 D5357113338400 1 CLIP (66) D5357113338400 67 D5357113338500 1 CLIP (67) D5357113338500 68 D5357113337800 1 WEB (68) D5357113337800 69 D5357113337900 1 WEB (69) D5357113337900 70 D5357113338800 1 ANGLE (70) D5357113338800 71 D5357113338900 1 ANGLE (71) D5357113338900 72 D5357113338200 1 CLIP (72) D5357113338200 73 D5357113338300 1 CLIP (73) D5357113338300 74 D5357113338600 1 ANGLE (74) D5357113338600 75 D5357113338700 1 ANGLE (75) D5357113338700 76 D5357113338000 1 CLIP (76) D5357113338000 77 D5357113338100 1 CLIP (77) D5357113338100 78 D5357113339200 1 ANGLE (78) D5357113339200 79 D5357113339300 1 ANGLE (79) D5357113339300 80 D5357072425400 1 ANGLE (80) D5357072425400 81 D5357072425500 1 ANGLE (81) D5357072425500 82 D5357072424200 1 CLIP (82) D5357072424200 83 D5357072424300 1 CLIP (83) D5357072424300 84 D5357113337600 1 WEB (84) D5357113337600 85 D5357113337700 1 WEB (85) D5357113337700 86 D5357072425800 1 ANGLE (86) D5357072425800 87 D5357072425900 1 ANGLE (87) D5357072425900 88 D5357072425200 1 ANGLE (88) D5357072425200 89 D5357072425300 1 ANGLE (89) D5357072425300 90 D5357072425600 1 ANGLE (90) D5357072425600 91 D5357072425700 1 ANGLE (91) D5357072425700 92 D5357072424400 1 CLIP (92) D5357072424400 93 D5357072424500 1 CLIP (93) D5357072424500 94 D5357072425000 1 ANGLE (94) D5357072425000 95 D5357072425100 1 ANGLE (95) D5357072425100 96 D5357072424800 1 WEB (96) D5357072424800 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 15 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 97 D5357072424900 1 WEB (97) D5357072424900 98 D5357072424600 1 CLIP (98) D5357072424600 99 D5357072424700 1 CLIP (99) D5357072424700 100 D5357072424000 1 WEB (100) D5357072424000 102 DAN5-6-4X 104 PIN DAN5-6-4 103 DAN11-6X 485 COLLAR NSA5075-6 104 DAN5-6-5X 88 PIN DAN5-6-6 105 DAN5-6-6X 10 PIN DAN5-6-6 106 EN6081D5-06 116 RIVET LN91984000CF 107 DAN5-6-5 32 PIN DAN5-5-5 108 NSA5075-6 214 COLLAR NSA5075-6 109 DAN5-5-6 60 PIN DAN5-5-6 110 NSA5075-5 106 COLLAR NSA5075-5 111 DAN5-5-5 44 PIN DAN5-5-5 112 DAN5-6-6 52 PIN DAN5-5-6 113 DAN5-6-3X 6 PIN DAN5-6-3 114 DAN5-8-5X 70 PIN DAN5-8-5 115 DAN11-8X 133 COLLAR NSA5057-8 116 DAN5-8-4X 8 PIN DAN5-8-4 117 DAN5-8-7X 18 PIN DAN5-8-7 118 DAN5-8-8X 4 PIN DAN5-8-8 119 DAN6-6-3X 16 PIN DAN6-6-3 120 DAN6-6-4X 112 PIN DAN6-6-4 121 DAN6-6-5X 62 PIN DAN6-6-5 122 EN6069D5-06 30 RIVET NAS1097KE5-00 123 DAN6-8-6X 15 PIN DAN6-8-6 124 DAN6-6-7X 46 PIN DAN6-6-7 125 DAN6-6-7 78 PIN DAN6-5-7 126 DAN6-6-6 20 PIN DAN6-5-6 127 DAN6-6-5 12 PIN DAN6-5-5 128 DAN6-6-3 16 PIN DAN6-5-3 129 DAN5-6-3 6 PIN DAN5-5-3 130 DAN5-6-7X 8 PIN DAN5-6-7 131 DAN5-8-6X 18 PIN DAN5-8-6 132 DAN6-6-6X 24 PIN DAN6-6-6 133 DAN6-5-7 2 PIN DAN6-5-7 135 EN6081D5-08 4 RIVET LN91984000CF 136 EN6069D5-07 134 RIVET NAS1097KE5-00 137 EN6069D5-08 64 RIVET NAS1097KE5-00 144 DAN7-6-11X 2 PIN DAN7-6-11 145 DAN12-6X 2 COLLAR DAN12-6 146 DAN5-6-10X 4 PIN DAN5-6-10 148 DAN5-6-8X 4 PIN DAN5-6-8

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 16 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. Kit 531266D11R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 D5357113140090 1 ANGLE (1 ) D5357113140000 2 D5357113140190 1 ANGLE (2) D5357113140100 3 D5357113146890 1 WEB (3) D5357113146800 4 D5357113146990 1 WEB (4) D5357113146900 5 D5357113143890 1 WEB (5) D5357113143800 6 D5357113143990 1 WEB (6) D5357113143900 7 D5357113144090 1 CLIP (7) D5357113144000 8 D5357113144190 1 CLIP (8) D5357113144100 9 D5357113146690 1 CLIP (9) D5357113146600 10 D5357113146790 1 CLIP (10) D5357113146700 11 D5357113143690 1 WEB (11 ) D5357113143600 12 D5357113143790 1 WEB (12) D5357113143700 13 D5357113145690 1 ANGLE (13) D5357113145600 14 D5357113145790 1 ANGLE (14) D5357113145700 15 D5357113145090 1 CLIP (15) D5357113145000 16 D5357113145190 1 CLIP (16) D5357113145100 17 D5357113145490 1 ANGLE (17) D5357113145400 18 D5357113145590 1 ANGLE (18) D5357113145500 19 D5357113144890 1 CLIP (19) D5357113144800 20 D5357113144990 1 CLIP (20) D5357113144900 21 D5357113144690 1 WEB (21 ) D5357113144600 22 D5357113144790 1 WEB (22) D5357113144700 23 D5357113145290 1 ANGLE (23) D5357113145200 24 D5357113145390 1 ANGLE (24) D5357113145300 25 D5357113145890 1 ANGLE (25) D5357113145800 26 D5357113145990 1 ANGLE (26) D5357113145900 27 D5357113144490 1 CLIP (27) D5357113144400 28 D5357113144590 1 CLIP (28) D5357113144500 29 D5357072225690 1 ANGLE (29) D5357072225600 30 D5357072225790 1 ANGLE (30) D5357072225700 31 D5357072224490 1 CLIP (31 ) D5357072224400 32 D5357072224590 1 CLIP (32) D5357072224500 33 D5357072226090 1 ANGLE (33) D5357072226000 34 D5357072226190 1 ANGLE (34) D5357072226100 35 D5357113144290 1 WEB (35) D5357113144200 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 17 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 36 D5357072225490 1 ANGLE (36) D5357072225400 37 D5357072225590 1 ANGLE (37) D5357072225500 38 D5357072225890 1 ANGLE (38) D5357072225800 39 D5357072225990 1 ANGLE (39) D5357072225900 40 D5357072224690 1 CLIP (40) D5357072224600 41 D5357072224790 1 CLIP (41 ) D5357072224700 42 D5357072225290 1 ANGLE (42) D5357072225200 43 D5357072225390 1 ANGLE (43) D5357072225300 44 D5357072224890 1 WEB (44) D5357072224800 45 D5357072224990 1 WEB (45) D5357072224900 46 D5357072225090 1 CLIP (46) D5357072225000 47 D5357072225190 1 CLIP (47) D5357072225100 48 D5357072224290 2 CLIP (48) D5357072224200 49 D5357072224090 1 WEB (49) D5357072224000 50 D5357116122090 1 WEB (50) D5357116122000 51 D5357113339690 1 ANGLE (51 ) D5357113339600 52 D5357113339790 1 ANGLE (52) D5357113339700 53 D5357113339800 2 FILLER (53) D5357113339800 54 D5357113321490 1 ANGLE (54) D5357113321400 55 D5357113321590 1 ANGLE (55) D5357113321500 56 D5357113337290 1 ANGLE (56) D5357113337200 57 D5357113337390 1 ANGLE (57) D5357113337300 58 D5357113337090 1 ANGLE (58) D5357113337000 59 D5357113337190 1 ANGLE (59) D5357113337100 60 D5357113340090 1 WEB (60) D5357113340000 61 D5357113340190 1 WEB (61 ) D5357113340100 62 D5357113339490 1 WEB (62) D5357113339400 63 D5357113339590 1 WEB (63) D5357113339500 64 D5357113339090 1 ANGLE (64) D5357113339000 65 D5357113339190 1 ANGLE (65) D5357113339100 66 D5357113338490 1 CLIP (66) D5357113338400 67 D5357113338590 1 CLIP (67) D5357113338500 68 D5357113337890 1 WEB (68) D5357113337800 69 D5357113337990 1 WEB (69) D5357113337900 70 D5357113338890 1 ANGLE (70) D5357113338800 71 D5357113338990 1 ANGLE (71 ) D5357113338900 72 D5357113338290 1 CLIP (72) D5357113338200 73 D5357113338390 1 CLIP (73) D5357113338300 74 D5357113338690 1 ANGLE (74) D5357113338600 75 D5357113338790 1 ANGLE (75) D5357113338700 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 18 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 76 D5357113338090 1 CLIP (76) D5357113338000 77 D5357113338190 1 CLIP (77) D5357113338100 78 D5357113339290 1 ANGLE (78) D5357113339200 79 D5357113339390 1 ANGLE (79) D5357113339300 80 D5357072425490 1 ANGLE (80) D5357072425400 81 D5357072425590 1 ANGLE (81 ) D5357072425500 82 D5357072424290 1 CLIP (82) D5357072424200 83 D5357072424390 1 CLIP (83) D5357072424300 84 D5357113337690 1 WEB (84) D5357113337600 85 D5357113337790 1 WEB (85) D5357113337700 86 D5357072425890 1 ANGLE (86) D5357072425800 87 D5357072425990 1 ANGLE (87) D5357072425900 88 D5357072425290 1 ANGLE (88) D5357072425200 89 D5357072425390 1 ANGLE (89) D5357072425300 90 D5357072425690 1 ANGLE (90) D5357072425600 91 D5357072425790 1 ANGLE (91 ) D5357072425700 92 D5357072424490 1 CLIP (92) D5357072424400 93 D5357072424590 1 CLIP (93) D5357072424500 94 D5357072425090 1 ANGLE (94) D5357072425000 95 D5357072425190 1 ANGLE (95) D5357072425100 96 D5357072424890 1 WEB (96) D5357072424800 97 D5357072424990 1 WEB (97) D5357072424900 98 D5357072424690 1 CLIP (98) D5357072424600 99 D5357072424790 1 CLIP (99) D5357072424700 100 D5357072424090 1 WEB (100) D5357072424000 102 DAN5-6-4X 104 PIN DAN5-6-4 103 DAN11-6X 492 COLLAR NSA5075-6 104 DAN5-6-5X 88 PIN DAN5-6-5 105 DAN5-6-6X 14 PIN DAN5-6-6 106 EN6081D5-06 116 RIVET LN91984000CF 107 DAN5-6-5 32 PIN DAN5-5-5 108 NSA5075-6 214 COLLAR NSA5075-6 109 DAN5-5-6 70 PIN DAN5-5-6 110 NSA5075-5 104 COLLAR NSA5075-5 111 DAN5-5-5 34 PIN DAN5-5-5 112 DAN5-6-6 52 PIN DAN5-5-6 113 DAN5-6-3X 6 PIN DAN5-6-3 114 DAN5-8-5X 70 PIN DAN5-8-5 115 DAN11-8X 133 COLLAR NSA5075-8 116 DAN5-8-4X 8 PIN DAN5-8-4 117 DAN5-8-7X 18 PIN DAN5-8-7 118 DAN5-8-8X 4 PIN DAN5-8-8 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 19 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 119 DAN6-6-3X 16 PIN DAN6-6-3 120 DAN6-6-4X 112 PIN DAN6-6-4 121 DAN6-6-5X 56 PIN DAN6-6-5 122 EN6069D5-06 30 RIVET NAS1097KE5-00 123 DAN6-8-6X 15 PIN DAN6-8-6 124 DAN6-6-7X 46 PIN DAN6-6-7 125 DAN6-6-7 76 PIN DAN6-5-7 126 DAN6-6-6 20 PIN DAN6-5-6 127 DAN6-6-5 12 PIN DAN6-5-5 128 DAN6-6-3 16 PIN DAN6-5-3 129 DAN5-6-3 6 PIN DAN5-5-3 130 DAN5-6-7X 8 PIN DAN5-6-7 131 DAN5-8-6X 18 PIN DAN5-8-6 132 DAN6-6-6X 34 PIN DAN6-6-6 135 EN6081D5-08 4 RIVET LN91984000CF 136 EN6069D5-07 134 RIVET NAS1097KE5-00 137 EN6069D5-08 64 RIVET NAS1097KE5-00 144 DAN7-6-11X 2 PIN DAN7-6-11 145 DAN12-6X 2 COLLAR DAN12-6 146 DAN5-6-10X 4 PIN DAN5-6-10 148 DAN5-6-8X 4 PIN DAN5-6-8 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 531266D12R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 D5357113120490 1 ANGLE (1) D5357113120400 2 D5357113120590 1 ANGLE (2) D5357113120500 3 D5357113133090 1 WEB (3) D5357113133000 4 D5357113133190 1 WEB (4) D5357113133100 5 D5357113134690 1 WEB (5) D5357113134600 6 D5357113134790 1 WEB (6) D5357113134700 7 D5357113136690 1 CLIP (7) D5357113136600 8 D5357113136790 1 CLIP (8) D5357113136700 9 D5357113122690 1 CLIP (9) D5357113122600 10 D5357113122790 1 CLIP (10) D5357113122700 11 D5357113134490 1 WEB (11) D5357113134400 12 D5357113134590 1 WEB (12) D5357113134500 13 D5357114726090 1 ANGLE (23) D5357114725600 14 D5357114726190 1 ANGLE (14) D5357114726100 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 20 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 15 D5357113122490 1 CLIP (15) D5357113122400 16 D5357113122590 1 CLIP (16) D5357113122500 17 D5357114725890 1 ANGLE (17) D5357114725800 18 D5357114725990 1 ANGLE (18) D5357114725900 19 D5357113132290 1 CLIP (19) D5357113132200 20 D5357113132390 1 CLIP (20) D5357113132300 21 D5357113134290 1 WEB (21) D5357113134200 22 D5357113134390 1 WEB (22) D5357113134300 23 D5357114725690 1 ANGLE (23) D5357114725600 24 D5357114725790 1 ANGLE (24) D5357114725700 25 D5357114727890 1 ANGLE (25) D5357114727800 26 D5357114727990 1 ANGLE (26) D5357114727900 27 D5357113136490 1 CLIP (27) D5357113136400 28 D5357113136590 1 CLIP (28) D5357113136500 29 D5357114725490 1 ANGLE (29) D5357114725400 30 D5357114725590 1 ANGLE (30) D5357114725500 31 D5357072231090 1 CLIP (32) D5357072231000 32 D5357072231190 1 CLIP (32) D5357072231100 33 D5357114727690 1 ANGLE (33) D5357114727600 34 D5357114727790 1 ANGLE (34) D5357114727700 35 D5357113134090 1 WEB (35) D5357113134000 36 D5357114725290 1 ANGLE (36) D5357114725200 37 D5357114725390 1 ANGLE (37) D5357114725300 38 D5357114727490 1 ANGLE (38) D5357114727400 39 D5357114727590 1 ANGLE (39) D5357114727500 40 D5357072221290 1 CLIP (40) D5357072221200 41 D5357072221390 1 CLIP (41) D5357072221300 42 D5357114725090 1 ANGLE (42) D5357114725000 43 D5357114725190 1 ANGLE (43) D5357114725100 44 D5357072222090 1 WEB (44) D5357072222000 45 D5357072222190 1 WEB (45) D5357072222100 46 D5357072221490 1 CLIP (46) D5357072221400 47 D5357072221590 1 CLIP (47) D5357072221500 48 D5357072221890 2 CLIP (48) D5357072221800 49 D5357072221690 1 WEB (49) D5357072221600 50 D5357116135090 1 WEB (50) D5357116135000 51 D5357113331290 1 ANGLE (51) D5357113331200 52 D5357113331390 1 ANGLE (52) D5357113331300 53 D5357113335400 2 FILLER (53) D5357113335400 54 D5357113321490 1 ANGLE (54) D5357113321400 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 21 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 55 D5357113321590 1 ANGLE (55) D5357113321500 56 D5357113321090 1 ANGLE (56) D5357113321000 57 D5357113321190 1 ANGLE (57) D5357113321100 58 D5357113320890 1 ANGLE (58) D5357113320800 59 D5357113320990 1 ANGLE (59) D5357113320900 60 D5357113336090 1 WEB (60) D5357113336000 61 D5357113336190 1 WEB (61) D5357113336100 62 D5357113330690 1 WEB (62) D5357113330600 63 D5357113330790 1 WEB (63) D5357113330700 64 D5357114727290 1 ANGLE (64) D5357114727200 65 D5357114727390 1 ANGLE (65) D5357114727300 66 D5357113330490 1 CLIP (66) D5357113330400 67 D5357113330590 1 CLIP (67) D5357113330500 68 D5357113336290 1 WEB (68) D5357113336200 69 D5357113336390 1 WEB (69) D5357113336300 70 D5357114727090 1 ANGLE (70) D5357114727000 71 D5357114727190 1 ANGLE (71) D5357114727100 72 D5357113330290 1 CLIP (72) D5357113330200 73 D5357113330390 1 CLIP (73) D5357113330300 74 D5357114726890 1 ANGLE (74) D5357114726800 75 D5357114726990 1 ANGLE (75) D5357114726900 76 D5357113330090 1 CLIP (76) D5357113330000 77 D5357113330190 1 CLIP (77) D5357113330100 78 D5357114728490 1 ANGLE (78) D5357114728400 79 D5357114728590 1 ANGLE (79) D5357114728500 80 D5357114726690 1 ANGLE (80) D5357114726600 81 D5357114726790 1 ANGLE (81) D5357114726700 82 D5357072431090 1 CLIP (82) D5357072431000 83 D5357072431190 1 CLIP (83) D5357072431100 84 D5357113336490 1 WEB (84) D5357113336400 85 D5357113336590 1 WEB (85) D5357113336500 86 D5357114728290 1 ANGLE (64) D5357114727200 87 D5357114728390 1 ANGLE (87) D5357114728300 88 D5357114726490 1 ANGLE (88) D5357114726400 89 D5357114726590 1 ANGLE (89) D5357114726500 90 D5357114728090 1 ANGLE (90) D5357114728000 91 D5357114728190 1 ANGLE (91) D5357114728100 92 D5357072421290 1 CLIP (92) D5357072421200 93 D5357072421390 1 CLIP (93) D5357072421300 94 D5357114726290 1 ANGLE (94) D5357114726200 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 22 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 95 D5357114726390 1 ANGLE (95) D5357114726300 96 D5357072421690 1 WEB (96) D5357072421600 97 D5357072421790 1 WEB (97) D5357072421700 98 D5357072421490 1 CLIP (98) D5357072421400 99 D5357072421590 1 CLIP (99) D5357072421500 100 D5357072421890 1 WEB (100) D5357072421800 102 DAN5-6-4X 104 PIN DAN5-6-4 103 DAN11-6X 474 COLLAR NSA5075-6 104 DAN5-6-5X 88 PIN DAN5-6-5 105 DAN5-6-6X 14 PIN DAN5-6-6 106 EN6081D5-06 116 RIVET LN91984000CF 108 NSA5330-6 104 COLLAR NSA5075-6 109 DAN5-6-6 108 PIN DAN5-5-6 110 NSA5075-6 228 COLLAR NSA5075-6 111 DAN5-6-5 74 PIN DAN5-5-5 112 DAN6-6-5 2 PIN DAN6-5-5 113 DAN5-6-3X 6 PIN DAN5-6-3 114 DAN5-8-5X 70 PIN DAN5-8-5 115 DAN11-8X 133 COLLAR NSA5057-8 116 DAN5-8-4X 8 PIN DAN5-8-4 117 DAN5-8-7X 18 PIN DAN5-8-7 118 DAN5-8-8X 4 PIN DAN5-8-8 119 DAN6-6-3X 16 PIN DAN6-6-3 120 DAN6-6-4X 112 PIN DAN6-6-4 121 DAN6-6-5Y 50 PIN DAN6-6-5 122 EN6069D5-06 30 RIVET NAS1097KE5-00 123 DAN6-8-6X 15 PIN DAN6-8-6 124 DAN6-6-6Y 54 PIN DAN5-8-4 125 DAN6-6-7X 84 PIN DAN6-6-7 126 DAN6-6-6 20 PIN DAN6-5-6 127 DAN6-6-5X 26 PIN DAN6-6-5 128 DAN6-6-3 16 PIN DAN6-5-3 129 DAN5-6-3 6 PIN DAN5-5-3 130 DAN5-6-7X 8 PIN DAN5-6-7 131 DAN5-8-6X 18 PIN DAN5-8-6 132 DAN6-6-6X 8 PIN DAN6-6-6 133 DAN6-5-7 2 PIN DAN6-5-7 134 DAN6-6-7 2 PIN DAN6-6-7 135 EN6081D5-07 4 RIVET LN91984000CF 136 EN6069D5-07 134 RIVET NAS1097KE5-00 137 EN6069D5-08 64 RIVET NAS1097KE5-00 144 DAN7-6-11X 2 PIN DAN7-6-11 145 DAN12-6X 2 COLLAR DAN12-6 146 DAN5-6-10X 4 PIN DAN5-6-10 148 DAN5-6-8X 4 PIN DAN5-6-8 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 23 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 160 NSA5075-5 2 COLLAR NSA5075-5 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 531266D14R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 D5357113120490 1 ANGLE (1) D5357113120400 2 D5357113120590 1 ANGLE (2) D5357113120500 3 D5357113133090 1 WEB (3) D5357113133000 4 D5357113133190 1 WEB (4) D5357113133100 5 D5357113134690 1 WEB (5) D5357113134600 6 D5357113134790 1 WEB (6) D5357113134700 7 D5357113136690 1 CLIP (7) D5357113136600 8 D5357113136790 1 CLIP (8) D5357113136700 9 D5357113122690 1 CLIP (9) D5357113122600 10 D5357113122790 1 CLIP (10) D5357113122700 11 D5357113134490 1 WEB (11) D5357113134400 12 D5357113134590 1 WEB (12) D5357113134500 13 D5357113138290 1 ANGLE (13) D5357113138200 14 D5357113138390 1 ANGLE (14) D5357113138300 15 D5357113137690 1 CLIP (15) D5357113137600 16 D5357113137790 1 CLIP (16) D5357113137700 17 D5357113138090 1 ANGLE (17) D5357113138000 18 D5357113138190 1 ANGLE (18) D5357113138100 19 D5357113137490 1 CLIP (19) D5357113137400 20 D5357113137590 1 CLIP (20) D5357113137500 21 D5357113137290 1 WEB (21) D5357113137200 22 D5357113137390 1 WEB (22) D5357113137300 23 D5357113137890 1 ANGLE (23) D5357113137800 24 D5357113137990 1 ANGLE (24) D5357113137900 25 D5357113138490 1 ANGLE (25) D5357113138400 26 D5357113138590 1 ANGLE (26) D5357113138500 27 D5357113137090 1 CLIP (27) D5357113137000 28 D5357113137190 1 CLIP (28) D5357113137100 29 D5357072223490 1 ANGLE (29) D5357072223400 30 D5357072223590 1 ANGLE (30) D5357072223500 31 D5357072222290 1 CLIP (31) D5357072222200
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 24 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 32 D5357072222390 1 CLIP (32) D5357072222300 33 D5357072223890 1 ANGLE (33) D5357072223800 34 D5357072223990 1 ANGLE (34) D5357072223900 35 D5357113136890 1 WEB (35) D5357113136800 36 D5357072223290 1 ANGLE (36) D5357072223200 37 D5357072223390 1 ANGLE (37) D5357072223300 38 D5357072223690 1 ANGLE (38) D5357072223600 39 D5357072223790 1 ANGLE (39) D5357072223700 40 D5357072222490 1 CLIP (40) D5357072222400 41 D5357072222590 1 CLIP (41) D5357072222500 42 D5357072223090 1 ANGLE (42) D5357072223000 43 D5357072223190 1 ANGLE (43) D5357072223100 44 D5357072222690 1 WEB (44) D5357072222600 45 D5357072222790 1 WEB (45) D5357072222700 46 D5357072222890 1 CLIP (46) D5357072222800 47 D5357072222990 1 CLIP (47) D5357072222900 48 D5357072221890 2 CLIP (48) D5357072221800 49 D5357072221690 1 WEB (49) D5357072221600 50 D5357116135490 1 WEB (50) D5357116135400 51 D5357113331290 1 ANGLE (51) D5357113331200 52 D5357113331390 1 ANGLE (52) D5357113331300 53 D5357113335400 2 FILLER (53) D5357113335400 54 D5357113321490 1 ANGLE (54) D5357113321400 55 D5357113321590 1 ANGLE (55) D5357113321500 56 D5357113321090 1 ANGLE (56) D5357113321000 57 D5357113321190 1 ANGLE (57) D5357113321100 58 D5357113320890 1 ANGLE (58) D5357113320800 59 D5357113320990 1 ANGLE (59) D5357113320900 60 D5357113336090 1 WEB (60) D5357113336000 61 D5357113336190 1 WEB (61) D5357113336100 62 D5357113330690 1 WEB (62) D5357113330600 63 D5357113330790 1 WEB (63) D5357113330700 64 D5357113327090 1 ANGLE (64) D5357113327000 65 D5357113327190 1 ANGLE (65) D5357113327100 66 D5357113326490 1 CLIP (66) D5357113326400 67 D5357113326590 1 CLIP (67) D5357113326500 68 D5357113325890 1 WEB (68) D5357113325800 69 D5357113325990 1 WEB (69) D5357113325900 70 D5357113326890 1 ANGLE (70) D5357113326800 71 D5357113326990 1 ANGLE (71) D5357113326900 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 25 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 72 D5357113326290 1 CLIP (72) D5357113326200 73 D5357113326390 1 CLIP (73) D5357113326300 74 D5357113326690 1 ANGLE (74) D5357113326600 75 D5357113326790 1 ANGLE (75) D5357113326700 76 D5357113326090 1 CLIP (76) D5357113326000 77 D5357113326190 1 CLIP (77) D5357113326100 78 D5357113327290 1 ANGLE (78) D5357113327200 79 D5357113327390 1 ANGLE (79) D5357113327300 80 D5357072423490 1 ANGLE (80) D5357072423400 81 D5357072423590 1 ANGLE (81) D5357072423500 82 D5357072422090 1 CLIP (82) D5357072422000 83 D5357072422190 1 CLIP (83) D5357072422100 84 D5357113325690 1 WEB (84) D5357113325600 85 D5357113325790 1 WEB (85) D5357113325700 86 D5357072423890 1 ANGLE (86) D5357072423800 87 D5357072423990 1 ANGLE (87) D5357072423900 88 D5357072423290 1 ANGLE (88) D5357072423200 89 D5357072423390 1 ANGLE (89) D5357072423300 90 D5357072423690 1 ANGLE (90) D5357072423600 91 D5357072423790 1 ANGLE (91) D5357072423700 92 D5357072422290 1 CLIP (92) D5357072422200 93 D5357072422390 1 CLIP (93) D5357072422300 94 D5357072423090 1 ANGLE (94) D5357072423000 95 D5357072423190 1 ANGLE (95) D5357072423100 96 D5357072422690 1 WEB (96) D5357072422600 97 D5357072422790 1 WEB (97) D5357072422700 98 D5357072422490 1 CLIP (98) D5357072422400 99 D5357072422590 1 CLIP (99) D5357072422500 100 D5357072421890 1 WEB (100) D5357072421800 102 DAN5-6-4X 104 PIN DAN5-6-4 103 DAN11-6X 488 COLLAR NSA5075-6 104 DAN5-6-5X 88 PIN DAN5-6-5 105 DAN5-6-6X 10 PIN DAN5-6-6 107 DAN5-6-5 32 PIN DAN5-5-5 108 NSA5075-6 214 COLLAR NSA5075-6 109 DAN5-5-6 70 PIN DAN5-5-6 111 DAN5-5-5 34 PIN DAN5-5-5 112 DAN5-6-6 52 PIN DAN5-5-6 113 DAN5-6-3X 6 PIN DAN5-6-3 114 DAN5-8-5X 70 PIN DAN5-8-5 115 DAN11-8X 133 COLLAR NSA5057-8
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 26 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 116 DAN5-8-4X 8 PIN DAN5-8-4 117 DAN5-8-7X 18 PIN DAN5-8-7 118 DAN5-8-8X 4 PIN DAN5-8-8 119 DAN6-6-3X 16 PIN DAN6-6-3 120 DAN6-6-4X 112 PIN DAN6-6-4 121 DAN6-6-5X 56 PIN DAN6-6-5 123 DAN6-8-6X 15 PIN DAN6-8-6 125 DAN6-6-7X 46 PIN DAN6-6-7 126 DAN6-6-6 20 PIN DAN6-5-6 127 DAN6-6-5 12 PIN DAN6-5-5 128 DAN6-6-3 16 PIN DAN6-5-3 129 DAN5-6-3 6 PIN DAN5-5-3 130 DAN5-6-7X 8 PIN DAN5-6-7 131 DAN5-8-6X 18 PIN DAN5-8-6 132 DAN6-6-6X 34 PIN DAN6-6-6 134 DAN6-6-7 76 PIN DAN6-6-7 135 EN6081D5-07 116 RIVET LN91984000CF 137 EN6069D5-08 228 RIVET NAS1097KE5-00 144 DAN7-6-11X 2 PIN DAN7-6-11 145 DAN12-6X 2 COLLAR DAN12-6 146 DAN5-6-10X 4 PIN DAN5-6-10 148 DAN5-6-8X 4 PIN DAN5-6-8 160 NSA5075-5 104 COLLAR NSA5075-5 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 CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant, Brush Consistency 09-013 As required Corrosion Preventative Compound, Temporary 15-009 As required Anti-Corrosion Primer Polyurethane 16-001 As required Polyurethane Finish Paint 16-018 As required (2) Components None

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 27 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING None

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 28 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 531266-831-848-001 - Modification WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR: - THE FLIGHT CONTROLS - THE FLIGHT CONTROL SURFACES - THE LANDING GEAR AND THE RELATED DOORS - COMPONENTS THAT MOVE. 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 ELECTRICAL 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 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 29 6

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# @A318/A319/A320/A321 SERVICE BULLETIN 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. NOTE: Discarded parts must be managed at the operator’s discretion. Task Associated Data **CONF 001 Zone 310 Manpower TOTAL MANHOURS 110.00 ELAPSED TIME (HOURS) 106.0 **CONF 002 Zone 310 Manpower TOTAL MANHOURS 110.00 ELAPSED TIME (HOURS) 106.0 **CONF 003 Zone 310 Manpower TOTAL MANHOURS 110.00 ELAPSED TIME (HOURS) 106.0 **CONF 004 Zone 310 Manpower TOTAL MANHOURS 110.00 ELAPSED TIME (HOURS) 106.0

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 30 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
**CONF ALL A. GENERAL **CONF 001 (1) Subtask 531266-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 Task 20-16-00-912-001 Task 20-21-11-911-801 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-33-11 Non Destructive Test Manual (NTM) Task 51-10-01-250-801 Task 51-10-01-250-802 Structural Repair Manual (SRM) 51-24-00 51-40-11 51-42-00 51-43-00 51-44-00 51-75-12 (a) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (c) For the identification of zones, refer to AMM 06-20-00, Page Block 001. (d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001. (e) Apply sealant in accordance with SRM 51-24-00. (f) Renew the protective finish in accordance with SRM 51-75-12. (g) Remove and install fasteners in accordance with SRM 51-42-00 and SRM 51-40-11. (h) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00. (i) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 31 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (j) 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. (k) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-801. (l) For the drilling of rivet holes: - Use a soft lead pencil and make marks to show the position of the rivet holes - Make sure that you have the correct edge clearance before you drill the fastener holes - If not shown otherwise the tolerance for rivet holes is +0.1 mm (+0.004 in.) - Transfer-drill the existing holes with a pilot hole drill and a drill bush - Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in.) diameter. Increase the hole diameter to the correct size for the fastener which you must install - Deburr the holes after you have drilled them. (m) Cut the rivets to the necessary length. (n) Install rivets immediately after you position the components with sealant. If not, tacking pins must be installed temporarily in every third hole. (o) Tag the parts that you must remove and retain to make the subsequent installation easier. (p) Put all the retained hardware in identified plastic bags and attach the bags to the related unit. (q) For the installation of the wiring, refer to ESPM 20-33-11. (r) For rotating probe inspection of the holes, refer to NTM Task 51-10-01-250-801. If the access is difficult use the manual probe, refer to NTM Task 51-10-01-250-802. (2) Subtask 531266-839-201-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 32 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
**CONF 002 (1) Subtask 531266-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 Task 20-16-00-912-001 Task 20-21-11-911-801 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-33-11 Non Destructive Test Manual (NTM) Task 51-10-01-250-801 Task 51-10-01-250-802 Structural Repair Manual (SRM) 51-24-00 51-40-11 51-42-00 51-43-00 51-44-00 51-75-12 (a) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (c) For the identification of zones, refer to AMM 06-20-00, Page Block 001. (d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001. (e) Apply sealant in accordance with SRM 51-24-00. (f) Renew the protective finish in accordance with SRM 51-75-12. (g) Remove and install fasteners in accordance with SRM 51-42-00 and SRM 51-40-11. (h) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00. (i) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00. (j) 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. (k) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-801. DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 33 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (l) For the drilling of rivet holes: - Use a soft lead pencil and make marks to show the position of the rivet holes - Make sure that you have the correct edge clearance before you drill the fastener holes - If not shown otherwise the tolerance for rivet holes is +0.1 mm (+0.004 in.) - Transfer-drill the existing holes with a pilot hole drill and a drill bush - Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in.) diameter. Increase the hole diameter to the correct size for the fastener which you must install - Deburr the holes after you have drilled them. (m) Cut the rivets to the necessary length. (n) Install rivets immediately after you position the components with sealant. If not, tacking pins must be installed temporarily in every third hole. (o) Tag the parts that you must remove and retain to make the subsequent installation easier. (p) Put all the retained hardware in identified plastic bags and attach the bags to the related unit. (q) For the installation of the wiring, refer to ESPM 20-33-11. (r) For rotating probe inspection of the holes, refer to NTM Task 51-10-01-250-801. If the access is difficult use the manual probe, refer to NTM Task 51-10-01-250-802. (2) Subtask 531266-839-201-001 - 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 003 (1) Subtask 531266-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 34 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 Task 20-16-00-912-001 Task 20-21-11-911-801 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-33-11 Non Destructive Test Manual (NTM) Task 51-10-01-250-801 Task 51-10-01-250-802 Structural Repair Manual (SRM) 51-24-00 51-40-11 51-42-00 51-43-00 51-44-00 51-75-12 (a) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (c) For the identification of zones, refer to AMM 06-20-00, Page Block 001. (d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001. (e) Apply sealant in accordance with SRM 51-24-00. (f) Renew the protective finish in accordance with SRM 51-75-12. (g) Remove and install fasteners in accordance with SRM 51-42-00 and SRM 51-40-11. (h) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00. (i) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00. (j) 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. (k) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-801. (l) For the drilling of rivet holes: - Use a soft lead pencil and make marks to show the position of the rivet holes - Make sure that you have the correct edge clearance before you drill the fastener holes
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 35 6

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# @A318/A319/A320/A321 SERVICE BULLETIN - If not shown otherwise the tolerance for rivet holes is +0.1 mm (+0.004 in.) - Transfer-drill the existing holes with a pilot hole drill and a drill bush - Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in.) diameter. Increase the hole diameter to the correct size for the fastener which you must install - Deburr the holes after you have drilled them. (m) Cut the rivets to the necessary length. (n) Install rivets immediately after you position the components with sealant. If not, tacking pins must be installed temporarily in every third hole. (o) Tag the parts that you must remove and retain to make the subsequent installation easier. (p) Put all the retained hardware in identified plastic bags and attach the bags to the related unit. (q) For the installation of the wiring, refer to ESPM 20-33-11. (r) For rotating probe inspection of the holes, refer to NTM Task 51-10-01-250-801. If the access is difficult use the manual probe, refer to NTM Task 51-10-01-250-802. (2) Subtask 531266-839-201-001 - 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 004 (1) Subtask 531266-910-201-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 Task 20-16-00-912-001 Task 20-21-11-911-801 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-33-11 Non Destructive Test Manual (NTM) Task 51-10-01-250-801 Task 51-10-01-250-802

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 36 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-24-00 51-40-11 51-42-00 51-43-00 51-44-00 51-75-12 (a) For the specification of the materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Materials List (CML). (b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (c) For the identification of zones, refer to AMM 06-20-00, Page Block 001. (d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001. (e) Apply sealant in accordance with SRM 51-24-00. (f) Renew the protective finish in accordance with SRM 51-75-12. (g) Remove and install fasteners in accordance with SRM 51-42-00 and SRM 51-40-11. (h) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00. (i) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00. (j) 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. (k) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-801. (l) For the drilling of rivet holes: - Use a soft lead pencil and make marks to show the position of the rivet holes - Make sure that you have the correct edge clearance before you drill the fastener holes - If not shown otherwise the tolerance for rivet holes is +0.1 mm (+0.004 in.) - Transfer-drill the existing holes with a pilot hole drill and a drill bush - Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in.) diameter. Increase the hole diameter to the correct size for the fastener which you must install - Deburr the holes after you have drilled them. DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 37 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (m) Cut the rivets to the necessary length. (n) Install rivets immediately after you position the components with sealant. If not, tacking pins must be installed temporarily in every third hole. (o) Tag the parts that you must remove and retain to make the subsequent installation easier. (p) Put all the retained hardware in identified plastic bags and attach the bags to the related unit. (q) For the installation of the wiring, refer to ESPM 20-33-11. (r) For rotating probe inspection of the holes, refer to NTM Task 51-10-01-250-801. If the access is difficult use the manual probe, refer to NTM Task 51-10-01-250-802. (2) Subtask 531266-839-201-001 - 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 531266-941-201-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 310 Work location from Frame 70 to Frame 77 from Stringer 1 to Stringer 13 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002 Task 29-00-00-864-001 Task 36-12-41-000-001 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
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 38 6

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# @A318/A319/A320/A321 SERVICE BULLETIN - Aircraft in clean configuration - Parking brake applied - Aircraft electrical network de-energized - Hydraulic systems depressurized - 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) Open, safety/lock and tag this (these) circuit breaker(s): PANEL DESIGNATION FIN LOCATION SEE NOTES 49VU AIR BLEED/X FEED/VALVE/BAT 2HV D13 49VU AIR BLEED/ENG 1/CTL 3HA1 D12 49VU AIR BLEED/ENG 1/MONG 2HA1 D11 122VU AIR BLEED/ENG 2/CTL 3HA2 Z23 122VU AIR BLEED/ENG 2/MONG 2HA2 Z22 122VU AIR BLEED/X FEED VALVE/NORM 1HV Z20 (c) Put the access platform in position below the access doors 312AR and 314AR. (d) Open the access doors 312AR and 314AR. (e) Put access platform(s) in the location Frame 70 thru Frame 77. (f) Make sure that the pressure is released from the green and yellow hydraulic systems, refer to AMM Task 29-00-00-864-001. (g) Put warning notices in position to tell persons not to operate the hydraulic systems. (h) Carefully loosen the hydraulic lines at Frame 72 to gain access to the modified areas. (i) Carefully loosen the wire and remove all wire clamps to gain access to the modified areas. (j) Carefully loosen the light 4LJ to gain access to the modified areas. (k) Remove the APU bleed air duct between frame 71 and frame 77 to get access to the modified areas, refer to AMM Task 36-12-41-000-001. (l) Protect the THS upper panel to avoid unwanted delamination caused by tools.
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 39 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
**CONF 002 (1) Subtask 531266-941-201-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 310 Work location from Frame 70 to Frame 77 from Stringer 1 to Stringer 13 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002 Task 29-00-00-864-001 Task 36-12-41-000-001 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 - 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) Open, safety/lock and tag this (these) circuit breaker(s): PANEL DESIGNATION FIN LOCATION SEE NOTES 49VU AIR BLEED/X FEED/VALVE/BAT 2HV D13 49VU AIR BLEED/ENG 1/CTL 3HA1 D12 49VU AIR BLEED/ENG 1/MONG 2HA1 D11 122VU AIR BLEED/ENG 2/CTL 3HA2 Z23 122VU AIR BLEED/ENG 2/MONG 2HA2 Z22
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 40 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
PANEL DESIGNATION FIN LOCATION SEE NOTES 122VU AIR BLEED/X FEED VALVE/NORM 1HV Z20 (c) Put the access platform in position below the access doors 312AR and 314AR. (d) Open the access doors 312AR and 314AR. (e) Put access platform(s) in the location Frame 70 thru Frame 77. (f) Make sure that the pressure is released from the green and yellow hydraulic systems, refer to AMM Task 29-00-00-864-001. (g) Put warning notices in position to tell persons not to operate the hydraulic systems. (h) Carefully loosen the hydraulic lines at Frame 72 to gain access to the modified areas. (i) Carefully loosen the wire and remove all wire clamps to gain access to the modified areas. (j) Carefully loosen the light 4LJ to gain access to the modified areas. (k) Remove the APU bleed air duct between frame 71 and frame 77 to get access to the modified areas, refer to AMM Task 36-12-41-000-001. (l) Protect the THS upper panel to avoid unwanted delamination caused by tools. **CONF 003 (1) Subtask 531266-941-201-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 310 Work location from Frame 70 to Frame 77 from Stringer 1 to Stringer 13 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002 Task 29-00-00-864-001 Task 36-12-41-000-001 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 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 41 6

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# @A318/A319/A320/A321 SERVICE BULLETIN - Aircraft in clean configuration - Parking brake applied - Aircraft electrical network de-energized - Hydraulic systems depressurized - 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) Open, safety/lock and tag this (these) circuit breaker(s): PANEL DESIGNATION FIN LOCATION SEE NOTES 49VU AIR BLEED/X FEED/VALVE/BAT 2HV D13 49VU AIR BLEED/ENG 1/CTL 3HA1 D12 49VU AIR BLEED/ENG 1/MONG 2HA1 D11 122VU AIR BLEED/ENG 2/CTL 3HA2 Z23 122VU AIR BLEED/ENG 2/MONG 2HA2 Z22 122VU AIR BLEED/X FEED VALVE/NORM 1HV Z20 (c) Put the access platform in position below the access doors 312AR and 314AR. (d) Open the access doors 312AR and 314AR. (e) Put access platform(s) in the location Frame 70 thru Frame 77. (f) Make sure that the pressure is released from the green and yellow hydraulic systems, refer to AMM Task 29-00-00-864-001. (g) Put warning notices in position to tell persons not to operate the hydraulic systems. (h) Carefully loosen the hydraulic lines at Frame 72 to gain access to the modified areas. (i) Carefully loosen the wire and remove all wire clamps to gain access to the modified areas. (j) Carefully loosen the light 4LJ to gain access to the modified areas. (k) Remove the APU bleed air duct between frame 71 and frame 77 to get access to the modified areas, refer to AMM Task 36-12-41-000-001. (l) Protect the THS upper panel to avoid unwanted delamination caused by tools.
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 42 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
**CONF 004 (1) Subtask 531266-941-201-001 - Job Set-up Work Zones and Access Panels Zone Access/Work location 310 Work location from Frame 70 to Frame 77 from Stringer 1 to Stringer 13 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002 Task 29-00-00-864-001 Task 36-12-41-000-001 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 - 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) Open, safety/lock and tag this (these) circuit breaker(s): PANEL DESIGNATION FIN LOCATION SEE NOTES 49VU AIR BLEED/X FEED/VALVE/BAT 2HV D13 49VU AIR BLEED/ENG 1/CTL 3HA1 D12 49VU AIR BLEED/ENG 1/MONG 2HA1 D11 122VU AIR BLEED/ENG 2/CTL 3HA2 Z23 122VU AIR BLEED/ENG 2/MONG 2HA2 Z22
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 43 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
PANEL DESIGNATION FIN LOCATION SEE NOTES 122VU AIR BLEED/X FEED VALVE/NORM 1HV Z20 (c) Put the access platform in position below the access doors 312AR and 314AR. (d) Open the access doors 312AR and 314AR. (e) Put access platform(s) in the location Frame 70 thru Frame 77. (f) Make sure that the pressure is released from the green and yellow hydraulic systems, refer to AMM Task 29-00-00-864-001. (g) Put warning notices in position to tell persons not to operate the hydraulic systems. (h) Carefully loosen the hydraulic lines at Frame 72 to gain access to the modified areas. (i) Carefully loosen the wire and remove all wire clamps to gain access to the modified areas. (j) Carefully loosen the light 4LJ to gain access to the modified areas. (k) Remove the APU bleed air duct between frame 71 and frame 77 to get access to the modified areas, refer to AMM Task 36-12-41-000-001. (l) Protect the THS upper panel to avoid unwanted delamination caused by tools. **CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 531266-020-201-001 - Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, LH and STGR1, RH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 72 from Stringer 13 LH to Stringer 1 RH

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 44 6

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# @A318/A319/A320/A321 SERVICE BULLETIN Manpower Resources Manhours 13.00 Minimum number of person 1 Subtask elapsed time 13.00 Skills AIRFRAME NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) Task 51-10-01-250-801 51-10-08 Fig. A-GBAAA Location of Inspection Area for Clips at FR72/FR74 Sheet 01 Fig. A-GBBAA Removal/Installation of Angles, Webs, Brackets and Clips at FR72 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Remove the items between STGR13 and STGR11 LH, refer to Fig. A-GBBAA Sheet 01 and Fig. A-GBBAA Sheet 02

. 1 As shown in View B, remove: 26 Pin-Rivet Discard 26 Collar Discard 6 Rivet Discard 2 As shown in Section B-B, remove: 2 Pin-Rivet Discard 2 Collar Discard 3 As shown in View D, remove: 16 Pin-Rivet Discard 16 Collar Discard 4 Remove: 1 Angle D5357113140000 Item (1) Discard 1 Web D5357113146800 Item (3) Discard 1 Web D5357113143800 Item (5) Discard 1 Bracket-Z D9357073720000 Item (133) Retain DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 45 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
5 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (b) Remove the items between STGR11 and STGR9 LH, refer to Fig. A-GBBAA Sheet 01 and Fig. A-GBBAA Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STRG11 (Section A-A) and 2 Rivet Discard from the angle at STGR10 (Section A-A). Remove: 23 Pin-Rivet Discard 23 Collar Discard 11 Rivet Discard from View B. 2 As shown in View F, remove: 19 Pin-Rivet Discard 19 Collar Discard 16 Rivet Discard 3 Remove: 1 Clip D5357113144000 Item (7) Discard 1 Clip D5357113146600 Item (9) Discard 1 Web D5357113143600 Item (11) Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 46 6

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# @A318/A319/A320/A321 SERVICE BULLETIN 1 Bracket-Z D9357073720000 Item (133) Retain 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (c) Remove the items between STGR9 and STGR7 LH, refer to Fig. A-GBBAA Sheet 01 and Fig. A-GBBAA Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR9 (Section A-A) and 2 Rivet Discard from the angle at STGR8 (Section A-A). Remove: 31 Pin-Rivet Discard 31 Collar Discard from View B. 2 As shown in View F, remove: 21 Pin-Rivet Discard 21 Collar Discard 14 Rivet Discard 3 Remove: 1 Angle D5357113145600 Item (13) Discard 1 Clip D5357113145000 Item (15) Discard 1 Angle D5357113145400 Item (17) Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 47 6

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# @A318/A319/A320/A321 SERVICE BULLETIN 1 Clip D5357113144800 Item (19) Discard 1 Web D5357113144600 Item (21) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (d) Remove the items between STGR7 and STGR5 LH, refer to Fig. A-GBBAA Sheet 01 and Fig. A-GBBAA Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR7 (Section A-A) and 2 Rivet Discard from the angle at STGR6 (Section A-A). Remove: 33 Pin-Rivet Discard 33 Collar Discard 2 Rivet Discard from View B. 2 As shown in View F, remove: 28 Pin-Rivet Discard 28 Collar Discard 10 Rivet Discard 3 Remove: 1 Angle D5357113145200 Item (23) Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 48 6

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# @A318/A319/A320/A321 SERVICE BULLETIN 1 Angle D5357113145800 Item (25) Discard 1 Clip D5357113144400 Item (27) Discard 1 Angle D5357072225600 Item (29) Discard 1 Clip D5357072224400 Item (31) Discard 1 Angle D5357072226000 Item (33) Discard 1 Web D5357113144200 Item (35) Discard 1 Bracket-Z D9357073720000 Item (133) Retain 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (e) Remove the items between STGR5 and STGR3 LH, refer to Fig. A-GBBAA Sheet 01 and Fig. A-GBBAA Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR5 (Section A-A) and 2 Rivet Discard from the angle at STGR4 (Section A-A). Remove: 20 Pin-Rivet Discard 8 Collar Discard 12 Nut Discard from View B.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 49 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
2 As shown in View F, remove: 19 Pin-Rivet Discard 19 Collar Discard 14 Rivet Discard 3 Remove: 1 Angle D5357072225400 Item (36) Discard 1 Angle D5357072225800 Item (38) Discard 1 Clip D5357072224600 Item (40) Discard 1 Angle D5357072225200 Item (42) Discard 1 Web D5357072224800 Item (44) Discard 1 Clip D5357072225000 Item (46) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (f) Remove the items at STGR1 RH and LH, refer to Fig. A-GBBAA Sheet 01 and Fig. A-GBBAA Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR1 (Section A-A). 10 Pin-Rivet Discard 10 Nut Discard from View B.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 50 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
2 As shown in View E, remove: 7 Pin-Rivet Discard 7 Nut Discard 8 Rivet Discard 3 Remove: 1 Clip D5357072224200 Item (48) Discard 1 Web D5357072224000 Item (49) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (2) Subtask 531266-420-201-001 - Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR1, RH and STGR13, LH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 72 from Stringer 1 RH to Stringer 13 LH Manpower Resources Manhours 16.00 Minimum number of person 1 Subtask elapsed time 16.00 Skills AIRFRAME Material necessary to do the job Kit 531266D01R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 D5357113140000 1 ANGLE 3 D5357113146800 1 WEB 5 D5357113143800 1 WEB 7 D5357113144000 1 CLIP DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 51 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 9 D5357113146600 1 CLIP 11 D5357113143600 1 WEB 13 D5357113145600 1 ANGLE 15 D5357113145000 1 CLIP 17 D5357113145400 1 ANGLE 19 D5357113144800 1 CLIP 21 D5357113144600 1 WEB 23 D5357113145200 1 ANGLE 25 D5357113145800 1 ANGLE 27 D5357113144400 1 CLIP 29 D5357072225600 1 ANGLE 31 D5357072224400 1 CLIP 33 D5357072226000 1 ANGLE 35 D5357113144200 1 WEB 36 D5357072225400 1 ANGLE 38 D5357072225800 1 ANGLE 40 D5357072224600 1 CLIP 42 D5357072225200 1 ANGLE 44 D5357072224800 1 WEB 46 D5357072225000 1 CLIP 48 D5357072224200 1 CLIP 49 D5357072224000 1 WEB 102 DAN5-6-4X 31 PIN 103 DAN11-6X 143 COLLAR 104 DAN5-6-5X 40 PIN 106 EN6081D5-06 33 RIVET 107 DAN5-6-5 16 PIN 108 NSA5075-6 55 COLLAR 109 DAN5-5-6 15 PIN 110 NSA5075-5 27 COLLAR 111 DAN5-5-5 12 PIN 112 DAN5-6-6 2 PIN 113 DAN5-6-3X 3 PIN 114 DAN5-8-5X 10 PIN 115 DAN11-8X 29 COLLAR 116 DAN5-8-4X 2 PIN 117 DAN5-8-7X 8 PIN 118 DAN5-8-8X 2 PIN 119 DAN6-6-3X 8 PIN 120 DAN6-6-4X 29 PIN 121 DAN6-6-5X 16 PIN 122 EN6069D5-06 12 RIVET 123 DAN6-8-6X 7 PIN 124 DAN6-6-7X 10 PIN 125 DAN6-6-7 19 PIN 126 DAN6-6-6 4 PIN DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 52 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 127 DAN6-6-5 3 PIN 128 DAN6-6-3 8 PIN 129 DAN5-6-3 4 PIN 132 DAN6-6-6X 6 PIN 135 EN6081D5-08 2 RIVET 136 EN6069D5-07 33 RIVET 137 EN6069D5-08 17 RIVET Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant, Brush Consistency 09-013 As required Corrosion Preventative Compound, Temporary 15-009 As required Anti-Corrosion Primer Polyurethane 16-001 As required Polyurethane Finish Paint 16-018 As required References Consumable Material List (CML) Fig. A-GBBAA Removal/Installation of Angles, Webs, Brackets and Clips at FR72 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-GBDAA Fastener Symbol Identification Sheet 01
NOTE: The structural parts listed in the above kit are defined with suffix 00 and include pilot holes. Alternatively, the equivalent parts may be supplied without holes for ease of installation. The alternative parts will have suffix 90 and are fully interchangeable. (a) Install the items between STGR1 LH and RH, refer to Fig. A-GBBAA Sheet 03 and Fig. A-GBDAA Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Web D5357072224000 Item 49 with: 8 Pin DAN5-8-7X Item 117 8 Collar DAN11-8X Item 115 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 53 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
and then install: 1 Clip D5357072224200 Item 48 with: 2 PIN DAN5-8-8X Item 118 2 Collar DAN11-8X Item 115 2 As shown in Section E-E, install: 2 Pin DAN5-6-3 Item 129 2 Collar NSA5075-6 Item 108 3 As shown in View K, install: 7 Pin DAN6-8-6X Item 123 7 Collar DAN11-8X Item 115 5 Rivet EN6069D5-07 Item 136 3 Rivet EN6069D5-08 Item 137 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 115,117, 118 and 123. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 106, 115, 117, 118, 123, 136 and 137. (b) Install the items between STGR3 and STGR4 on the LH Side, refer to Fig. AGBBAA Sheet 03, Fig. A-GBBAA Sheet 04 and Fig. A-GBDAA Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 54 6

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# @A318/A319/A320/A321 SERVICE BULLETIN to wet install on Frame 72, as shown in View G: 1 Angle D5357072225200 Item 42 1 Clip D5357072225000 Item 46 with: 4 Pin DAN5-8-5X Item 114 4 Collar DAN11-8X Item 115 3 Pin DAN5-5-5 Item 111 3 Collar NSA5075-5 Item 110 2 As shown in Section C-C, STGR4 install: 2 Rivet EN6081D5-06 Item 106 3 As shown in View L, install between STGR3 and STGR4: 3 Pin DAN6-6-5X Item 121 4 Pin DAN6-6-7X Item 124 7 Collar DAN11-6X Item 103 7 Rivet EN6069D5-08 Item 137 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 103, 109, 110, 114, 115, 124 and 132. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 103, 106, 109, 110, 114, 115, 124, 132 and 137.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 55 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (c) Install the items between STGR4 and STGR5 on the LH Side, refer to Fig. AGBBAA Sheet 03, Fig. A-GBBAA Sheet 04 and Fig. A-GBDAA Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357072225400 Item 36 1 Web D5357072224800 Item 44 with: 2 Pin DAN5-8-4X Item 116 2 Collar DAN11-8X Item 115 and then install: 1 Clip D5357072224600 Item 40 with: 6 Pin DAN5-8-5X Item 114 6 Collar DAN11-8X Item 115 and then install: 1 Angle D5357072225800 Item 38 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 110 2 As shown in Section, C-C at STGR5, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in View L, between STGR4 and STGR5, install: 6 Pin DAN6-6-6X Item 132 6 Pin DAN6-6-7X Item 124 12 Collar DAN11-6X Item 103 7 Rivet EN6069D5-08 Item 137

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 56 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 103, 109, 110, 114, 115, 116, 124 and 132. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 103, 106, 109, 110, 114, 115, 116, 124, 122, 132 and 137. (d) Install the items between STGR5 and STGR7 on the LH Side, refer to Fig. AGBBAA Sheet 03, Fig. A-GBBAA Sheet 04 and Fig. A-GBDAA Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357072225600 Item 29 1 Angle D5357113145200 Item 23 1 Web D5357113144200 Item 35 with: 9 Pin DAN5-6-4X Item 102 9 Collar DAN11-6X Item 103 2 Rivet EN6081D5-08 Item 135 and then between STGR5 and STGR6 install: 1 Clip D5357072224400 Item 31 with: 7 Pin DAN5-6-5X Item 104

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 57 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
7 Collar DAN11-6X Item 103 and then between STGR5 and STGR6 install: 1 Angle D5357072226000 Item 33 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 110 and then between STGR6 and STGR7 install: 1 Clip D5357113144400 Item 27 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 and then between STGR6 and STGR7 install: 1 Angle D5357113145800 Item 25 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 110 2 As shown in Section C-C, at STGR6, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section C-C, at STGR7, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View L, between STGR5 and STGR7, install: 19 Pin DAN6-6-7 Item 125 23 Collar NSA5075-6 Item 108 9 Rivet EN6069D5-07 Item 136 4 Pin DAN6-6-6 Item 126 4 Pin DAN6-6-5X Item 121 4 Collar DAN11-6X Item 103

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 58 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
1 Pin DAN6-6-5 Item 127 1 Rivet EN6069D5-06 Item 122 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 109, 110, 121, 125, 108, 126 and 127. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 109, 110, 121, 122, 125, 126, 127 and 136. (e) Install the items between STGR7 and STGR9 on the LH Side, refer to Fig. AGBBAA Sheet 03, Fig. A-GBBAA Sheet 04 and Fig. A-GBDAA Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357113145600 Item 13 1 Angle D5357113145400 Item 17 NOTE : Item 13 and Item 17 are temporally held in place. Then between STGR7 and STGR9 install: 1 Web D5357113144600 Item 21 with: 10 Pin DAN5-6-4X Item 102 10 Collar DAN11-6X Item 103 and then between STGR7 and STGR8 install:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 59 6

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# @A318/A319/A320/A321 SERVICE BULLETIN 1 Clip D5357113144800 Item 19 with: 5 Pin DAN5-6-5X Item 104 5 Collar DAN11-6X Item 103 4 Pin DAN5-5-5 Item 111 4 Collar NSA5075-5 Item 110 and then between Stringer STGR8 and STGR9 install: 1 Clip D5357113145000 Item 15 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 5 Pin DAN5-5-5 Item 111 5 Collar NSA5075-5 Item 110 2 As shown in Section C-C, at STGR8, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section C-C, at STGR9, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View L, between STGR7 and STGR9, install: 10 Pin DAN6-6-4X Item 120 19 Collar DAN11-6X Item 103 12 Rivet EN6069D5-07 Item 136 2 Rivet EN6069D5-06 Item 122 2 Pin DAN6-6-5 Item 127 9 Pin DAN6-6-5X Item 121 2 Collar NSA5075-6 Item 108

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 60 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 110, 111, 120, 122, and 127. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 110, 111, 120, 121, 122, 127 and 136. (f) Install the items between STGR9 and STGR11 on the LH Side, refer to Fig. AGBBAA Sheet 03, Fig. A-GBBAA Sheet 04 and Fig. A-GBDAA Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Bracket-Z D9357073720000 Item (133) Retained at removal 1 Web D5357113143600 Item 11 with: 2 Rivet EN6081D5-06 Item 106 9 Pin DAN5-6-4X Item 102 9 Collar DAN11-6X Item 103 and then STGR9 and STGR10, install: 1 Clip D5357113146600 Item 9 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 61 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
5 Rivet EN6081D5-06 Item 106 and then between STGR10 and STGR11, install: 1 Clip D5357113144000 Item 7 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 4 Rivet EN6081D5-06 Item 106 2 As shown in Section C-C, at STGR10 install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section C-C, at STGR11 install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View L, between STGR9 and STGR11, install: 10 Pin DAN6-6-4X Item 120 19 Collar DAN11-6X Item 103 7 Rivet EN6069D5-07 Item 136 9 Rivet EN6069D5-06 Item 122 9 Pin DAN6-6-4X Item 120 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 120. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 106, 120, 122 and 136.
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 62 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (g) Install the items between STGR11 and STGR13 on the LH Side, refer to Fig. AGBBAA Sheet 03 and Fig. A-GBDAA Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Bracket-Z D9357073720000 Item (133) Retained at removal 1 Web D5357113143800 Item 5 with: 2 Rivet EN6081D5-06 Item 106 3 Pin DAN5-6-3X Item 113 3 Collar DAN11-6X Item 103 and then install: 1 Web D5357113146800 Item 3 with: 3 Pin DAN5-6-4X Item 102 3 Collar DAN11-6X Item 103 4 Rivet EN6081D5-06 Item 106 and then install: 1 Angle D5357113140000 Item 1 with: 16 Pin DAN5-6-5 Item 107 18 Collar NSA5075-6 Item 108 2 Pin DAN5-6-6 Item 112 2 As shown in Section D-D, at STGR12, install: 2 Pin DAN5-6-3 Item 129 2 Collar NSA5075-6 Item 108

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 63 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
3 As shown in View J, install: 8 Pin DAN6-6-3X Item 119 8 Collar DAN11-6X Item 103 8 Pin DAN6-6-3 Item 128 8 Collar NSA5075-6 Item 108 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 107, 108, 113, 119, 112 and 128. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 106, 107, 108, 113, 119, 112 and 128. (3) Subtask 531266-020-208-001 - Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, RH and STGR3, RH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 72 from Stringer 13 RH to Stringer 3 RH Manpower Resources Manhours 11.00 Minimum number of person 1 Subtask elapsed time 11.00 Skills AIRFRAME NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) Task 51-10-01-250-801 51-10-08

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 64 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
References Fig. A-GBAAA Location of Inspection Area for Clips at FR72/FR74 Sheet 01 Fig. A-GBBAA Removal/Installation of Angles, Webs, Brackets and Clips at FR72 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Remove the items between STGR13 and STGR11 RH, refer to Fig. A-GBBAA Sheet 01 and Fig. A-GBBAA Sheet 02

. 1 As shown in View B, remove: 26 Pin-Rivet Discard 26 Collar Discard 6 Rivet Discard 2 As shown in Section B-B, remove: 2 Pin-Rivet Discard 2 Collar Discard 3 As shown in View D, remove: 16 Pin-Rivet Discard 16 Collar Discard 4 Remove: 1 Angle D5357113140100 Item (2) Discard 1 Web D5357113146900 Item (4) Discard 1 Web D5357113143900 Item (6) Discard 1 Bracket-Z D9357073720000 Item (133) Retain 5 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 65 6

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# @A318/A319/A320/A321 SERVICE BULLETIN - If no cracks are found, do the worksteps that follow. (b) Remove the items between STGR11 and STGR9 RH, refer to Fig. A-GBBAA Sheet 01 and Fig. A-GBBAA Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STRG11 (Section A-A) and 2 Rivet Discard from the angle at STGR10 (Section A-A). Remove: 23 Pin-Rivet Discard 23 Collar Discard 11 Rivet Discard from View B. 2 As shown in View F, remove: 19 Pin-Rivet Discard 19 Collar Discard 16 Rivet Discard 3 Remove: 1 Clip D5357113144100 Item (8) Discard 1 Clip D5357113146700 Item (10) Discard 1 Web D5357113143700 Item (12) Discard 1 Bracket-Z D9357073720000 Item (133) Retain 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 66 6

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# @A318/A319/A320/A321 SERVICE BULLETIN - If no cracks are found, do the worksteps that follow. (c) Remove the items between STGR9 and STGR7 RH, refer to Fig. A-GBBAA Sheet 01 and Fig. A-GBBAA Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR9 (Section A-A) and 2 Rivet Discard from the angle at STGR8 (Section A-A). Remove: 31 Pin-Rivet Discard 31 Collar Discard from View B. 2 As shown in View F, remove: 21 Pin-Rivet Discard 21 Collar Discard 14 Rivet Discard 3 Remove: 1 Angle D5357113145700 Item (14) Discard 1 Clip D5357113145100 Item (16) Discard 1 Angle D5357113145500 Item (18) Discard 1 Clip D5357113144900 Item (20) Discard 1 Web D5357113144700 Item (22) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 67 6

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# @A318/A319/A320/A321 SERVICE BULLETIN

c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (d) Remove the items between STGR7 and STGR5 RH, refer to Fig. A-GBBAA Sheet 01 and Fig. A-GBBAA Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR7 (Section A-A) and 2 Rivet Discard from the angle at STGR6 (Section A-A). Remove: 33 Pin-Rivet Discard 33 Collar Discard 2 Rivet Discard from View B. 2 As shown in View F, remove: 28 Pin-Rivet Discard 28 Collar Discard 10 Rivet Discard 3 As shown in View C, remove: 1 Angle D5357113145300 Item (24) Discard 1 Angle D5357113145900 Item (26) Discard 1 Clip D5357113144500 Item (28) Discard 1 Angle D5357072225700 Item (30) Discard 1 Clip D5357072224500 Item (32) Discard 1 Angle D5357072226100 Item (34) Discard 1 Web D5357116122000 Item (50) Discard
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 68 6

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# @A318/A319/A320/A321 SERVICE BULLETIN 1 Bracket-Z D9357073720000 Item (133) Retain 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (e) Remove the items between STGR5 and STGR3 RH, refer to Fig. A-GBBAA Sheet 01 and Fig. A-GBBAA Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR5 (Section A-A) and 2 Rivet Discard from the angle at STGR4 (Section A-A). Remove: 20 Pin-Rivet Discard 8 Collar Discard 12 Nut Discard from View B. 2 As shown in View F, remove: 19 Pin-Rivet Discard 19 Collar Discard 14 Rivet Discard 3 Remove: 1 Angle D5357072225500 Item (37) Discard 1 Angle D5357072225900 Item (39) Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 69 6

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# @A318/A319/A320/A321 SERVICE BULLETIN 1 Clip D5357072224700 Item (41) Discard 1 Angle D5357072225300 Item (43) Discard 1 Web D5357072224900 Item (45) Discard 1 Clip D5357072225100 Item (47) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (4) Subtask 531266-420-202-001 - Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR3, RH to STGR13, RH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 72 from Stringer 3 RH to Stringer 13 RH Manpower Resources Manhours 14.00 Minimum number of person 1 Subtask elapsed time 14.00 Skills AIRFRAME Material necessary to do the job Kit 531266D01R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 D5357113140100 1 ANGLE 4 D5357113146900 1 WEB 6 D5357113143900 1 WEB 8 D5357113144100 1 CLIP 10 D5357113146700 1 CLIP 12 D5357113143700 1 WEB 14 D5357113145700 1 ANGLE 16 D5357113145100 1 CLIP
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 70 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 18 D5357113145500 1 ANGLE 20 D5357113144900 1 CLIP 22 D5357113144700 1 WEB 24 D5357113145300 1 ANGLE 26 D5357113145900 1 ANGLE 28 D5357113144500 1 CLIP 30 D5357072225700 1 ANGLE 32 D5357072224500 1 CLIP 34 D5357072226100 1 ANGLE 37 D5357072225500 1 ANGLE 39 D5357072225900 1 ANGLE 41 D5357072224700 1 CLIP 43 D5357072225300 1 ANGLE 45 D5357072224900 1 WEB 47 D5357072225100 1 CLIP 50 D5357116122000 1 WEB 102 DAN5-6-4X 31 PIN 103 DAN11-6X 140 COLLAR 104 DAN5-6-5X 40 PIN 106 EN6081D5-06 33 RIVET 107 DAN5-6-5 16 PIN 108 NSA5075-6 53 COLLAR 109 DAN5-5-6 15 PIN 110 NSA5075-5 27 COLLAR 111 DAN5-5-5 12 PIN 112 DAN5-6-6 2 PIN 113 DAN5-6-3X 3 PIN 114 DAN5-8-5X 10 PIN 115 DAN11-8X 12 COLLAR 116 DAN5-8-4X 2 PIN 119 DAN6-6-3X 8 PIN 120 DAN6-6-4X 29 PIN 121 DAN6-6-5X 12 PIN 122 EN6069D5-06 12 RIVET 124 DAN6-6-7X 10 PIN 125 DAN6-6-7 19 PIN 126 DAN6-6-6 4 PIN 127 DAN6-6-5 3 PIN 128 DAN6-6-3 8 PIN 129 DAN5-6-3 2 PIN 132 DAN6-6-6X 6 PIN 135 EN6081D5-08 2 RIVET 136 EN6069D5-07 28 RIVET 137 EN6069D5-08 14 RIVET

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 71 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant, Brush Consistency 09-013 As required Corrosion Preventative Compound, Temporary 15-009 As required Anti-Corrosion Primer Polyurethane 16-001 As required Polyurethane Finish Paint 16-018 As required References Consumable Material List (CML) Fig. A-GBBAA Removal/Installation of Angles, Webs, Brackets and Clips at FR72 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-GBDAA Fastener Symbol Identification Sheet 01
NOTE: The structural parts listed in the above kit are defined with suffix 00 and include pilot holes. Alternatively, the equivalent parts may be supplied without holes for ease of installation. The alternative parts will have suffix 90 and are fully interchangeable. (a) Install the items between STGR3 and STGR4 on the RH Side, refer to Fig. AGBBAA Sheet 03, Fig. A-GBBAA Sheet 04 and Fig. A-GBDAA Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357072225300 Item 43 1 Clip D5357072225100 Item 47 with: 4 Pin DAN5-8-5X Item 114 4 Collar DAN11-8X Item 115 3 Pin DAN5-5-5 Item 111 3 Collar NSA5075-5 Item 110 2 As shown in Section C-C at STGR4, install: 2 Rivet EN6081D5-06 Item 106 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 72 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
3 As shown in View L, at STGR3 and STGR4, install: 3 Pin DAN6-6-5X Item 121 7 Collar DAN11-6X Item 103 4 Pin DAN6-6-7X Item 124 7 Rivet EN6069D5-08 Item 137 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 109, 110, 114, 115, 124 and 132. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 106, 109, 110, 114, 115, 124, 132 137. (b) Install the items between STGR4 and STGR5 on the RH Side, refer to Fig. AGBBAA Sheet 03, Fig. A-GBBAA Sheet 04 and Fig. A-GBDAA Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357072225500 Item 37 1 Web D5357072224900 Item 45 with: 2 Pin DAN5-8-4X Item 116 2 Collar DAN11-8X Item 115 and then install: 1 Clip D5357072224700 Item 41
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 73 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
with: 6 Pin DAN5-8-5X Item 114 6 Collar DAN11-8X Item 115 and then install: 1 Angle D5357072225900 Item 39 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 110 2 As shown in Section C-C at STGR5, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in View L, at STGR4 and STGR5, install: 6 Pin DAN6-6-6X Item 132 12 Collar DAN11-6X Item 103 6 Pin DAN6-6-7X Item 124 7 Rivet EN6069D5-08 Item 137 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 103, 109, 110, 114, 115, 116, 124 and 132. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 103, 106, 109, 110, 114, 115, 116, 122, 124, 132 and 137.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 74 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (c) Install the items between STGR5 and STGR7 on the RH Side, refer to Fig. AGBBAA Sheet 03, Fig. A-GBBAA Sheet 04 and Fig. A-GBDAA Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357072225700 Item 30 1 Angle D5357113145300 Item 24 1 Bracket-Z D9357073720000 Item (133) Retained at removal 1 Web D5357116122000 Item 50 with: 9 Pin DAN5-6-4X Item 102 9 Collar DAN11-6X Item 103 2 Rivet EN6081D5-08 Item 135 and between STGR5 and STGR7, as shown in View H, install: 1 Clip D5357072224500 Item 32 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 and between STGR5 and STGR7, install: 1 Angle D5357072226100 Item 34 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 110 and between STGR6 and STGR7, install: 1 Clip D5357113144500 Item 28 with: 7 Pin DAN5-6-5X Item 104 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 75 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
7 Collar DAN11-6X Item 103 and between STGR6 and STGR7 install: 1 Angle D5357113145900 Item 26 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 110 2 As shown in Section C-C at STGR6, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section C-C at STGR7, install: 2 Rivet EN6081D5-06 Item 106 4 Install to the fuselage skin between STGR5 and STGR7, refer to Fig. AGBBAA Sheet 04, View L: 19 Pin DAN6-6-7 Item 125 24 Collar NSA5075-6 Item 108 9 Rivet EN6069D5-07 Item 136 4 Pin DAN6-6-6 Item 126 4 Pin DAN6-6-5X Item 121 4 Collar DAN11-6X Item 103 1 Pin DAN6-6-5 Item 127 1 Rivet EN6069D5-06 Item 122 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 109, 110, 121, 125, 126 and 127.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 76 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 109, 110, 121, 122, 125, 126, 127 and 136. (d) Install the items between STGR7 and STGR9 on the RH Side, refer to Fig. AGBBAA Sheet 03, Fig. A-GBBAA Sheet 04 and Fig. A-GBDAA Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357113145700 Item 14 1 Angle D5357113145500 Item 18 NOTE : Item 14 and Item 18 are temporally held in place. Then between STGR7 and STGR9 install: 1 Web D5357113144700 Item 22 with: 10 Pin DAN5-6-4X Item 102 10 Collar DAN11-6X Item 103 and then between STGR7 and STGR8 install: 1 Clip D5357113144900 Item 20 with: 5 Pin DAN5-6-5X Item 104 5 Collar DAN11-6X Item 103 4 Pin DAN5-5-5 Item 111 4 Collar NSA5075-5 Item 110 and then between Stringer STGR8 and STGR9 install: 1 Clip D5357113145100 Item 16
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 77 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 5 Pin DAN5-5-5 Item 111 5 Collar NSA5075-5 Item 110 2 As shown in Section C-C at STGR8, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section C-C at STGR9, install: 2 Rivet EN6081D5-06 Item 106 4 Install to the fuselage skin between STGR7 and STGR9, refer to Fig. AGBBAA Sheet 04, View L: 10 Pin DAN6-6-4X Item 120 16 Collar DAN11-6X Item 103 12 Rivet EN6069D5-07 Item 136 2 Rivet EN6069D5-06 Item 122 2 Pin DAN6-6-5 Item 127 5 Pin DAN6-6-5X Item 121 1 Collar NSA5075-6 Item 108 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 110, 111, 120 and 127. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 78 6

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# @A318/A319/A320/A321 SERVICE BULLETIN to the fasteners, Items 102, 103, 104, 106, 108, 110, 111, 120, 122, 127 and 136. (e) Install the items between STGR9 and STGR11 on the RH Side, refer to Fig. AGBBAA Sheet 03, Fig. A-GBBAA Sheet 04 and Fig. A-GBDAA Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Bracket-Z D9357073720000 Item (133) Retained at removal 1 Web D5357113143700 Item 12 with: 2 Rivet EN6081D5-06 Item 106 9 Pin DAN5-6-4X Item 102 9 Collar DAN11-6X Item 103 and then STGR9 and STGR10, install: 1 Clip D5357113146700 Item 10 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 5 Rivet EN6081D5-06 Item 106 and then between STGR10 and STGR11, install: 1 Clip D5357113144100 Item 8 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 4 Rivet EN6081D5-06 Item 106 2 As shown in Section C-C, at STGR 10, install: 2 Rivet EN6081D5-06 Item 106
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 79 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
3 As shown in Section C-C, at STGR 11, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View L, between STGR9 and STGR11, install: 19 Pin DAN6-6-4X Item 120 19 Collar DAN11-6X Item 103 7 Rivet EN6069D5-07 Item 136 9 Rivet EN6069D5-06 Item 122 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104 and 120. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 106, 120, 122 and 136. (f) Install the items between STGR11 and STGR13 on the RH Side, refer to Fig. AGBBAA Sheet 03 and Fig. A-GBDAA Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Bracket-Z D9357073720000 Item (133) Retained at removal 1 Web D5357113143900 Item 6 with: 2 Rivet EN6081D5-06 Item 106 3 Pin DAN5-6-3X Item 113 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 80 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
3 Collar DAN11-6X Item 103 and then install: 1 Web D5357113146900 Item 4 with: 3 Pin DAN5-6-4X Item 102 3 Collar DAN11-6X Item 103 4 Rivet EN6081D5-06 Item 106 and then install: 1 Angle D5357113140100 Item 2 with: 16 Pin DAN5-6-5 Item 107 18 Collar NSA5075-6 Item 108 2 Pin DAN5-6-6 Item 112 2 As shown in Section D-D, at STGR12, install: 2 Pin DAN5-6-3 Item 129 2 Collar NSA5075-6 Item 108 3 As shown in View J, install: 8 Pin DAN6-6-3X Item 119 8 Collar DAN11-6X Item 103 8 Pin DAN6-6-3 Item 128 8 Collar NSA5075-6 Item 108 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 107, 108, 113, 119, 112 and 128.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 81 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 106, 107, 108, 113, 119, 112 and 128. (5) Subtask 531266-020-203-001 - Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, LH and STGR1, RH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 74 from Stringer 12 LH to Stringer 1 RH Manpower Resources Manhours 11.00 Minimum number of person 1 Subtask elapsed time 11.00 Skills AIRFRAME NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) Task 51-10-01-250-801 51-10-08 Fig. A-GBAAA Location of Inspection Area for Clips at FR72/FR74 Sheet 01 Fig. A-GBCAA Removal/Installation of Angles, Webs, Brackets and Clips at FR74 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Remove the items between STGR12 and STGR9 LH, refer to Fig. A-GBCAA Sheet 01 and Fig. A-GBCAA Sheet 02

. 1 As shown in Section A-A, remove: 2 Rivet Discard from the angle at STGR11 (Section A-A) and 2 Rivet Discard from the angle at STGR10 (Section A-A). Remove: 42 Pin-Rivet Discard DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 82 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
42 Collar Discard 8 Rivet Discard from View B. 2 As shown in View E, remove: 27 Pin-Rivet Discard 27 Collar Discard 16 Rivet Discard 3 Remove: 1 Angle D5357113339600 Item (51) Discard 1 Filler D5357113339800 Item (53) Discard 1 Angle D5357113321400 Item (54) Discard 1 Angle D5357113337200 Item (56) Discard 1 Angle D5357113337000 Item (58) Discard 1 Web D5357113340000 Item (60) Discard 1 Web D5357113339400 Item (62) Discard 4 As shown in View F, remove: 5 Pin-Rivet Discard 5 Collar Discard 5 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 83 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (b) Remove the items between STGR9 and STGR7 LH, refer to Fig. A-GBCAA Sheet 01 and Fig. A-GBCAA Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STRG9 (Section A-A) and 2 Rivet Discard from the angle at STRG8 (Section A-A). Remove: 27 Pin-Rivet Discard 27 Collar Discard from View B. 2 As shown in View E, remove: 19 Pin-Rivet Discard 19 Collar Discard 14 Rivet Discard 3 Remove: 1 Angle D5357113339000 Item (64) Discard 1 Clip D5357113338400 Item (66) Discard 1 Web D5357113337800 Item (68) Discard 1 Angle D5357113338800 Item (70) Discard 1 Clip D5357113338200 Item (72) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 84 6

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# @A318/A319/A320/A321 SERVICE BULLETIN - If no cracks are found, do the worksteps that follow. (c) Remove the items between STGR7 and STGR5 LH, refer to Fig. A-GBCAA Sheet 01
. 1 Remove: 2 Rivet Discard from the angle at STRG7 (Section A-A) and 2 Rivet Discard from the angle at STRG6 (Section A-A). Remove: 32 Pin-Rivet Discard 32 Collar Discard from View B. 2 As shown in View C, remove: 30 Pin-Rivet Discard 30 Collar Discard 8 Rivet Discard 3 Remove: 1 Angle D5357113338600 Item (74) Discard 1 Clip D5357113338000 Item (76) Discard 1 Angle D5357113339200 Item (78) Discard 1 Angle D5357072425400 Item (80) Discard 1 Clip D5357072424200 Item (82) Discard 1 Web D5357113337600 Item (84) Discard 1 Angle D5357072425800 Item (86) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 85 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (d) Remove the items between STGR5 and STGR3, refer to Fig. A-GBCAA Sheet 01

. 1 Remove: 2 Rivet Discard from the angle at STRG5 (Section A-A) and 2 Rivet Discard from the angle at STRG4 (Section A-A). Remove: 18 Pin-Rivet Discard 18 Collar Discard from View B. 2 As shown in View C, remove: 17 Pin-Rivet Discard 17 Collar Discard 14 Rivet Discard 3 Remove: 1 Angle D5357072425200 Item (88) Discard 1 Angle D5357072425600 Item (90) Discard 1 Clip D5357072424400 Item (92) Discard 1 Angle D5357072425000 Item (94) Discard 1 Web D5357072424800 Item (96) Discard 1 Clip D5357072424600 Item (98) Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 86 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (e) Remove the items between STGR2 LH and STGR1 RH, refer to Fig. A-GBCAA Sheet 01 and Fig. A-GBCAA Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STRG1 (Section A-A). Remove: 12 Pin-Rivet Discard 12 Collar Discard from View B. 2 As shown in View D, remove: 8 Pin-Rivet Discard 8 Collar Discard 8 Pin-Rivet Discard 3 Remove: 1 Clip D5357072224200 Item (48) Discard 1 Web D5357072424000 Item (100) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 87 6

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# @A318/A319/A320/A321 SERVICE BULLETIN

c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (6) Subtask 531266-420-203-001 - Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR1, RH and STGR12, LH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 74 from Stringer 1 RH to Stringer 12 LH Manpower Resources Manhours 14.00 Minimum number of person 1 Subtask elapsed time 14.00 Skills AIRFRAME Material necessary to do the job Kit 531266D01R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 48 D5357072224200 1 CLIP 51 D5357113339600 1 ANGLE 53 D5357113339800 1 FILLER 54 D5357113321400 1 ANGLE 56 D5357113337200 1 ANGLE 58 D5357113337000 1 ANGLE 60 D5357113340000 1 WEB 62 D5357113339400 1 WEB 64 D5357113339000 1 ANGLE 66 D5357113338400 1 CLIP 68 D5357113337800 1 WEB 70 D5357113338800 1 ANGLE 72 D5357113338200 1 CLIP 74 D5357113338600 1 ANGLE 76 D5357113338000 1 CLIP 78 D5357113339200 1 ANGLE 80 D5357072425400 1 ANGLE 82 D5357072424200 1 CLIP 84 D5357113337600 1 WEB 86 D5357072425800 1 ANGLE 88 D5357072425200 1 ANGLE 90 D5357072425600 1 ANGLE 92 D5357072424400 1 CLIP 94 D5357072425000 1 ANGLE DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 88 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 96 D5357072424800 1 WEB 98 D5357072424600 1 CLIP 100 D5357072424000 1 WEB 102 DAN5-6-4X 21 PIN 103 DAN11-6X 101 COLLAR 104 DAN5-6-5X 4 PIN 105 DAN5-6-6X 5 PIN 106 EN6081D5-06 26 RIVET 108 NSA5075-6 53 COLLAR 109 DAN5-5-6 15 PIN 110 NSA5075-5 26 COLLAR 111 DAN5-5-5 10 PIN 112 DAN5-6-6 24 PIN 114 DAN5-8-5X 25 PIN 115 DAN11-8X 56 COLLAR 116 DAN5-8-4X 2 PIN 117 DAN5-8-7X 10 PIN 118 DAN5-8-8X 2 PIN 120 DAN6-6-4X 27 PIN 121 DAN6-6-5X 17 PIN 122 EN6069D5-06 3 RIVET 123 DAN6-8-6X 8 PIN 124 DAN6-6-7X 13 PIN 125 DAN6-6-7 20 PIN 126 DAN6-6-6 6 PIN 127 DAN6-6-5 3 PIN 130 DAN5-6-7X 4 PIN 131 DAN5-8-6X 9 PIN 132 DAN6-6-6X 6 PIN 133 DAN6-5-7 1 PIN 136 EN6069D5-07 38 RIVET 137 EN6069D5-08 19 RIVET 144 DAN7-6-11X 1 PIN 145 DAN12-6X 1 COLLAR 146 DAN5-6-10X 2 PIN 148 DAN5-6-8X 2 PIN Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant, Brush Consistency 09-013 As required Corrosion Preventative Compound, Temporary 15-009 As required Anti-Corrosion Primer Polyurethane 16-001 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 89 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polyurethane Finish Paint 16-018 As required References Consumable Material List (CML) Fig. A-GBCAA Removal/Installation of Angles, Webs, Brackets and Clips at FR74 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-GBDAA Fastener Symbol Identification Sheet 01
NOTE: The structural parts listed in the above kit are defined with suffix 00 and include pilot holes. Alternatively, the equivalent parts may be supplied without holes for ease of installation. The alternative parts will have suffix 90 and are fully interchangeable. (a) Install the items between STGR2 on the RH Side and STGR2 on the LH Side, refer to Fig. A-GBCAA Sheet 03, Fig. A-GBCAA Sheet 04 and Fig. A-GBDAA Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Web D5357072424000 Item 100 with: 10 Pin DAN5-8-7X Item 117 10 Collar DAN11-8X Item 115 and then install: 1 Clip D5357072224200 Item 48 with: 2 PIN DAN5-8-8X Item 118 2 Collar DAN11-8X Item 115 2 As shown in Section B-B, at STGR1, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in View J, install: 8 Pin DAN6-8-6X Item 123 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 90 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
8 Collar DAN11-8X Item 115 3 Rivet EN6069D5-07 Item 136 5 Rivet EN6069D5-08 Item 137 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 117, 115, 123, 118 and 122. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 117, 115, 123, 118 and 122. (b) Install the items between STGR3 and STGR5 on the LH Side, refer to Fig. AGBCAA Sheet 03, Fig. A-GBCAA Sheet 04 and Fig. A-GBDAA Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Angle D5357072425000 Item 94 1 Angle D5357072425200 Item 88 1 Clip D5357072424600 Item 98 1 Web D5357072424800 Item 96 with: 3 Pin DAN5-8-6X Item 131 5 Collar DAN11-8X Item 115 2 Pin DAN5-5-5 Item 111

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 91 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
2 Collar NSA5075-5 Item 110 2 Pin DAN5-8-4X Item 116 and install: 1 Clip D5357072424400 Item 92 with: 6 Pin DAN5-8-5X Item 114 6 Collar DAN11-8X Item 115 and install: 1 Angle D5357072425600 Item 90 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 110 2 As shown in Section B-B, at STGR4, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section B-B, at STGR5, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View H, install: 2 Pin DAN6-6-5X Item 121 6 Pin DAN6-6-6X Item 132 17 Collar DAN11-6X Item 103 9 Pin DAN6-6-7X Item 124 14 Rivet EN6069D5-08 Item 137 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 131, 115, 109, 110, 132, 124, 122, 116, 114 and 103. DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 92 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 131, 115, 109, 110, 132, 124, 122, 116, 114 and 103. (c) Install the items between STGR5 and STGR7 on the LH Side, refer to Fig. AGBCAA Sheet 03, Fig. A-GBCAA Sheet 04 and Fig. A-GBDAA Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Angle D5357072425400 Item 80 1 Angle D5357113338600 Item 74 NOTE : Item 80 and Item 74 are temporally held in place. Then between STGR5 and STGR7 install: 1 Web D5357113337600 Item 84 with: 10 Pin DAN5-6-4X Item 102 10 Collar DAN11-6X Item 103 and then between Stringer STGR5 and STGR6 install: 1 Clip D5357072424200 Item 82 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 5 Pin DAN5-8-5X Item 114 5 Collar DAN11-8X Item 115 and then between Stringer STGR5 and STGR6 install: 1 Angle D5357072425800 Item 86 with: DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 93 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 110 and then between Stringer STGR6 and STGR7 install: 1 Clip D5357113338000 Item 76 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 5 Pin DAN5-8-5X Item 114 5 Collar DAN11-8X Item 115 and then between Stringer STGR6 and STGR7 install: 1 Angle D5357113339200 Item 78 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 110 2 As shown in Section B-B at STGR6, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section B-B, at STGR7, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View H, install: 19 Pin DAN6-6-7 Item 125 26 Collar NSA5075-6 Item 108 6 Pin DAN6-6-6 Item 126 7 Rivet EN6069D5-07 Item 136 4 Pin DAN6-6-5X Item 121 4 Collar DAN11-6X Item 103 1 Pin DAN6-6-5 Item 127 1 Rivet EN6069D5-06 Item 122 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 94 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 114, 115, 109, 110, 125, 108, 126, 122, and 127. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 114, 115, 109, 110, 125, 108, 126, 122, and 127. (d) Install the items between Stringer STGR7 and STGR9 on the LH Side, refer to Fig. A-GBCAA Sheet 03, Fig. A-GBCAA Sheet 04 and Fig. A-GBDAA Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Angle D5357113338800 Item 70 1 Angle D5357113339000 Item 64 NOTE : Item 70 and Item 64 are temporally held in place. Then between STGR7 and STGR9 install: 1 Web D5357113337800 Item 68 with: 8 Pin DAN5-6-4X Item 102 8 Collar DAN11-6X Item 103 and install: 1 Clip D5357113338200 Item 72 with:
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 95 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 4 Pin DAN5-8-5X Item 114 4 Collar DAN11-8X Item 115 4 Pin DAN5-5-5 Item 111 4 Collar NSA5075-5 Item 110 and install: 1 Clip D5357113338400 Item 66 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 5 Pin DAN5-8-5X Item 114 5 Collar DAN11-8X Item 115 4 Pin DAN5-5-5 Item 111 4 Collar NSA5075-5 Item 110 2 As shown in Section B-B, at STGR8, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section B-B, at STGR9, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View K, install: 8 Pin DAN6-6-5X Item 121 17 Collar DAN11-6X Item 103 9 Pin DAN6-6-4X Item 120 2 Pin DAN6-6-5 Item 127 2 Collar NSA5075-6 Item 108 2 Rivet EN6069D5-06 Item 122 12 Rivet EN6069D5-07 Item 136 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 96 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 114, 115, 111, 110, 121, 127, 108, 122 and 120. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 114, 115, 111, 110, 121, 127, 108, 122 and 120. (e) Install the items between Stringer STGR9 and STGR12 on the LH Side, refer to Fig. A-GBCAA Sheet 03, Fig. A-GBCAA Sheet 04 and Fig. A-GBDAA Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Web D5357113339400 Item 62 with: 3 Pin DAN5-6-4X Item 102 3 Collar DAN11-6X Item 103 and install: 1 Angle D5357113339600 Item 51 1 Filler D5357113339800 Item 53 1 Angle D5357113321400 Item 54 with: 24 Pin DAN5-6-6 Item 112 24 Collar NSA5075-6 Item 108
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 97 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
and install: 1 Web D5357113340000 Item 60 with: 6 Pin DAN5-8-6X Item 131 6 Collar DAN11-8X Item 115 8 Rivet EN6081D5-06 Item 106 5 Pin DAN5-6-6X Item 105 5 Collar DAN11-6X Item 103 and install: 1 Angle D5357113337000 Item 58 1 Angle D5357113337200 Item 56 with: 4 Pin DAN5-6-7X Item 130 4 Collar DAN11-6X Item 103 2 As shown in Section B-B, at STGR10, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section B-B, at STGR11, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View K, install: 18 Pin DAN6-6-4X Item 120 25 Collar DAN11-6X Item 103 16 Rivet EN6069D5-07 Item 136 3 Pin DAN6-6-5X Item 121 4 Pin DAN6-6-7X Item 124 1 Pin DAN6-6-7 Item 125 1 Collar NSA5075-6 Item 108 1 Pin DAN6-5-7 Item 133
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 98 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
1 Collar NSA5075-5 Item 110 5 As shown in View L, install: 1 Pin DAN7-6-11X Item 144 1 Collar DAN12-6X Item 145 2 Pin DAN5-6-10X Item 146 2 Pin DAN5-6-8X Item 148 4 Collar DAN11-6X Item 103 6 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 112, 108, 121, 124, 131, 115, 106, 105, 120, 130 and 122. 7 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 112, 108, 121, 124, 131, 115, 106, 105, 120, 130 and 122. (7) Subtask 531266-020-204-001 - Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, RH and STGR3, RH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 74 from Stringer 12RH to Stringer 3RH

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 99 6

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# @A318/A319/A320/A321 SERVICE BULLETIN Manpower Resources Manhours 11.00 Minimum number of person 1 Subtask elapsed time 11.00 Skills AIRFRAME NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) Task 51-10-01-250-801 51-10-08 Fig. A-GBAAA Location of Inspection Area for Clips at FR72/FR74 Sheet 01 Fig. A-GBCAA Removal/Installation of Angles, Webs, Brackets and Clips at FR74 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Remove the items between STGR12 and STGR9 RH, refer to Fig. A-GBCAA Sheet 01 and Fig. A-GBCAA Sheet 02

. 1 As shown in Section A-A, remove: 2 Rivet Discard from the angle at STGR11 (Section A-A) and 2 Rivet Discard from the angle at STGR10 (Section A-A). Remove: 42 Pin-Rivet Discard 42 Collar Discard 8 Rivet Discard from View B. 2 As shown in View E, remove: 27 Pin-Rivet Discard 27 Collar Discard 16 Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 100 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
3 Remove: 1 Angle D5357113339700 Item (52) Discard 1 Filler D5357113339800 Item (53) Discard 1 Angle D5357113321500 Item (55) Discard 1 Angle D5357113337300 Item (57) Discard 1 Angle D5357113337100 Item (59) Discard 1 Web D5357113340100 Item (61) Discard 1 Web D5357113339500 Item (63) Discard 4 As shown in View F, remove: 5 Pin-Rivet Discard 5 Collar Discard 5 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (b) Remove the items between STGR9 and STGR7 RH, refer to Fig. A-GBCAA Sheet 01 and Fig. A-GBCAA Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STRG9 (Section A-A) and 2 Rivet Discard from the angle at STRG8 (Section A-A). Remove: 27 Pin-Rivet Discard
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 101 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
27 Collar Discard from View B. 2 As shown in View E, remove: 19 Pin-Rivet Discard 19 Collar Discard 14 Rivet Discard 3 Remove: 1 Angle D5357113339100 Item (65) Discard 1 Clip D5357113338500 Item (67) 1 Web D5357113337900 Item (69) Discard 1 Angle D5357113338900 Item (71) Discard 1 Clip D5357113338300 Item (73) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (c) Remove the items between STGR7 and STGR5, refer to Fig. A-GBCAA Sheet 01

. 1 Remove: 2 Rivet Discard from the angle at STRG7 (Section A-A) and 2 Rivet Discard from the angle at STRG6 (Section A-A). Remove: 32 Pin-Rivet Discard DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 102 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
32 Collar Discard from View B. 2 As shown in View C, remove: 30 Pin-Rivet Discard 30 Collar Discard 8 Rivet Discard 3 Remove: 1 Angle D5357113338700 Item (75) Discard 1 Clip D5357113338100 Item (77) Discard 1 Angle D5357113339300 Item (79) Discard 1 Angle D5357072425500 Item (81) Discard 1 Clip D5357072424300 Item (83) Discard 1 Web D5357113337700 Item (85) Discard 1 Angle D5357072425900 Item (87) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (d) Remove the items between STGR5 and STGR3, refer to Fig. A-GBCAA Sheet 01

. 1 Remove: 2 Rivet Discard from the angle at STRG5 (Section A-A) and 2 Rivet Discard from the angle at STRG4 (Section A-A). DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 103 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
Remove: 18 Pin-Rivet Discard 18 Collar Discard from View B. 2 As shown in View C, remove: 17 Pin-Rivet Discard 17 Collar Discard 14 Rivet Discard 3 Remove: 1 Angle D5357072425300 Item (89) Discard 1 Angle D5357072425700 Item (91) Discard 1 Clip D5357072424500 Item (93) Discard 1 Angle D5357072425100 Item (95) Discard 1 Web D5357072424900 Item (97) Discard 1 Clip D5357072424700 Item (99) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (8) Subtask 531266-420-204-001 - Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR3, RH and STGR12, RH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 74 from Stringer 3 RH to Stringer 12 RH

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 104 6

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# @A318/A319/A320/A321 SERVICE BULLETIN Manpower Resources Manhours 12.00 Minimum number of person 1 Subtask elapsed time 12.00 Skills AIRFRAME Material necessary to do the job Kit 531266D01R04 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 52 D5357113339700 1 ANGLE 53 D5357113339800 1 FILLER 55 D5357113321500 1 ANGLE 57 D5357113337300 1 ANGLE 59 D5357113337100 1 ANGLE 61 D5357113340100 1 WEB 63 D5357113339500 1 WEB 65 D5357113339100 1 ANGLE 67 D5357113338500 1 CLIP 69 D5357113337900 1 WEB 71 D5357113338900 1 ANGLE 73 D5357113338300 1 CLIP 75 D5357113338700 1 ANGLE 77 D5357113338100 1 CLIP 79 D5357113339300 1 ANGLE 81 D5357072425500 1 ANGLE 83 D5357072424300 1 CLIP 85 D5357113337700 1 WEB 87 D5357072425900 1 ANGLE 89 D5357072425300 1 ANGLE 91 D5357072425700 1 ANGLE 93 D5357072424500 1 CLIP 95 D5357072425100 1 ANGLE 97 D5357072424900 1 WEB 99 D5357072424700 1 CLIP 102 DAN5-6-4X 21 PIN 103 DAN11-6X 101 COLLAR 104 DAN5-6-5X 4 PIN 105 DAN5-6-6X 5 PIN 106 EN6081D5-06 24 RIVET 108 NSA5075-6 53 COLLAR 109 DAN5-5-6 15 PIN 110 NSA5075-5 26 COLLAR 111 DAN5-5-5 10 PIN 112 DAN5-6-6 24 PIN 114 DAN5-8-5X 25 PIN DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 105 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 115 DAN11-8X 36 COLLAR 116 DAN5-8-4X 2 PIN 120 DAN6-6-4X 27 PIN 121 DAN6-6-5X 17 PIN 122 EN6069D5-06 3 RIVET 124 DAN6-6-7X 13 PIN 125 DAN6-6-7 20 PIN 126 DAN6-6-6 6 PIN 127 DAN6-6-5 3 PIN 130 DAN5-6-7X 4 PIN 131 DAN5-8-6X 9 PIN 132 DAN6-6-6X 6 PIN 133 DAN6-5-7 1 PIN 136 EN6069D5-07 35 RIVET 137 EN6069D5-08 14 RIVET 144 DAN7-6-11X 1 PIN 145 DAN12-6X 1 COLLAR 146 DAN5-6-10X 2 PIN 148 DAN5-6-8X 2 PIN Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant, Brush Consistency 09-013 As required Corrosion Preventative Compound, Temporary 15-009 As required Anti-Corrosion Primer Polyurethane 16-001 As required Polyurethane Finish Paint 16-018 As required References Consumable Material List (CML) Fig. A-GBCAA Removal/Installation of Angles, Webs, Brackets and Clips at FR74 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-GBDAA Fastener Symbol Identification Sheet 01
NOTE: The structural parts listed in the above kit are defined with suffix 00 and include pilot holes. Alternatively, the equivalent parts may be supplied without holes for ease of installation. The alternative parts will have suffix 90 and are fully interchangeable.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 106 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (a) Install the items between STGR3 and STGR5 on the RH Side, refer to Fig. AGBCAA Sheet 03, Fig. A-GBCAA Sheet 04 and Fig. A-GBDAA Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Angle D5357072425100 Item 95 1 Angle D5357072425300 Item 89 1 Clip D5357072424700 Item 99 1 Web D5357072424900 Item 97 with: 3 Pin DAN5-8-6X Item 131 5 Collar DAN11-8X Item 115 2 Pin DAN5-5-5 Item 111 2 Collar NSA5075-5 Item 110 2 Pin DAN5-8-4X Item 116 and install: 1 Clip D5357072424500 Item 93 with: 6 Pin DAN5-8-5X Item 114 6 Collar DAN11-8X Item 115 and install: 1 Angle D5357072425700 Item 91 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 110 2 As shown in Section B-B, at STGR4, install: 2 Rivet EN6081D5-06 Item 106
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 107 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
3 As shown in Section B-B, at STGR5, install: 2 Rivet EN6081D5-06 Item 106 4 Install: 2 Pin DAN6-6-5X Item 121 6 Pin DAN6-6-6X Item 132 17 Collar DAN11-6X Item 103 9 Pin DAN6-6-7X Item 124 14 Rivet EN6069D5-08 Item 137 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 131, 115, 109, 110, 132, 124, 122, 116, 114 and 103. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 131, 115, 109, 110, 132, 124, 122, 116, 114 and 103. (b) Install the items between STGR5 and STGR7 on the RH Side, refer to Fig. AGBCAA Sheet 03, Fig. A-GBCAA Sheet 04 and Fig. A-GBDAA Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Angle D5357072425500 Item 81 1 Angle D5357113338700 Item 75 NOTE : Item 81 and Item 75 are temporally held in place. Then between STGR5 and STGR7 install: DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 108 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
1 Web D5357113337700 Item 85 with: 10 Pin DAN5-6-4X Item 102 10 Collar DAN11-6X Item 103 and between Stringer STGR5 and STGR6 install: 1 Clip D5357072424300 Item 83 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 5 Pin DAN5-8-5X Item 114 5 Collar DAN11-8X Item 115 and between Stringer STGR5 and STGR6 install: 1 Angle D5357072425900 Item 87 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 110 and between Stringer STGR6 and STGR7 install: 1 Clip D5357113338100 Item 77 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 5 Pin DAN5-8-5X Item 114 5 Collar DAN11-8X Item 115 and between Stringer STGR6 and STGR7 install: 1 Angle D5357113339300 Item 79 with: 5 Pin DAN5-5-6 Item 109
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 109 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
5 Collar NSA5075-5 Item 110 2 As shown in Section B-B, at STGR6, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section B-B, at STGR7, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View H, install: 19 Pin DAN6-6-7 Item 125 26 Collar NSA5075-6 Item 108 6 Pin DAN6-6-6 Item 126 7 Rivet EN6069D5-07 Item 136 4 Pin DAN6-6-5X Item 121 4 Collar DAN11-6X Item 103 1 Pin DAN6-6-5 Item 127 1 Rivet EN6069D5-06 Item 122 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 114, 115, 109, 110, 125, 108, 126, 122 and 127. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 114, 115, 109, 110, 125, 108, 126, 122 and 127.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 110 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (c) Install the items between Stringer STGR7 and STGR9 on the RH Side, refer to Fig. A-GBCAA Sheet 03, Fig. A-GBCAA Sheet 04 and Fig. A-GBDAA Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Angle D5357113338900 Item 71 1 Angle D5357113339100 Item 65 NOTE : Item 71 and Item 64 are temporally held in place. Then between STGR7 and STGR9 install: 1 Web D5357113337900 Item 69 with: 8 Pin DAN5-6-4X Item 102 8 Collar DAN11-6X Item 103 and install: 1 Clip D5357113338300 Item 73 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 4 Pin DAN5-8-5X Item 114 4 Collar DAN11-8X Item 115 4 Pin DAN5-5-5 Item 111 4 Collar NSA5075-5 Item 110 and install: 1 Clip D5357113338500 Item 67 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 111 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
5 Pin DAN5-8-5X Item 114 5 Collar DAN11-8X Item 115 4 Pin DAN5-5-5 Item 111 4 Collar NSA5075-5 Item 110 2 As shown in Section B-B, at STGR8, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section B-B, at STGR9, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View K, install: 8 Pin DAN6-6-5X Item 121 17 Collar DAN11-6X Item 103 9 Pin DAN6-6-4X Item 120 2 Pin DAN6-6-5 Item 127 2 Collar NSA5075-6 Item 108 2 Rivet EN6069D5-06 Item 122 12 Rivet EN6069D5-07 Item 136 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 114, 115, 111, 110, 121, 127, 108, 122 and 120. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 114, 115, 111, 110, 121, 127, 108, 122 and 120. DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 112 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (d) Install the items between STGR9 and STGR12 on the RH Side, refer to Fig. AGBCAA Sheet 03, Fig. A-GBCAA Sheet 04 and Fig. A-GBDAA Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Web D5357113339500 Item 63 with: 3 Pin DAN5-6-4X Item 102 3 Collar DAN11-6X Item 103 and install: 1 Angle D5357113339700 Item 52 1 Filler D5357113339800 Item 53 1 Angle D5357113321500 Item 55 with: 24 Pin DAN5-6-6 Item 112 24 Collar NSA5075-6 Item 108 and install: 1 Web D5357113340100 Item 61 with: 6 Pin DAN5-8-6X Item 131 6 Collar DAN11-8X Item 115 8 Rivet EN6081D5-06 Item 106 5 Pin DAN5-6-6X Item 105 5 Collar DAN11-6X Item 103 and install: 1 Angle D5357113337100 Item 59 1 Angle D5357113337300 Item 57
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 113 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
with: 4 Pin DAN5-6-7X Item 130 4 Collar DAN11-6X Item 103 2 As shown in Section B-B, at STGR10, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section B-B, at STGR11, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View K, install: 18 Pin DAN6-6-4X Item 120 25 Collar DAN11-6X Item 103 16 Rivet EN6069D5-07 Item 136 3 Pin DAN6-6-5X Item 121 4 Pin DAN6-6-7X Item 124 1 Pin DAN6-6-7 Item 125 1 Collar NSA5075-6 Item 108 1 Pin DAN6-5-7 Item 133 1 Collar NSA5075-5 Item 110 5 As shown in View L, install: 1 Pin DAN7-6-11X Item 144 1 Collar DAN12-6X Item 145 2 Pin DAN5-6-10X Item 146 2 Pin DAN5-6-8X Item 148 4 Collar DAN11-6X Item 103 6 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 114 6

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# @A318/A319/A320/A321 SERVICE BULLETIN Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 112, 108, 121, 124, 131, 115, 106, 105, 120, 130 and 122. 7 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 112, 108, 121, 124, 131, 115, 106, 105, 120, 130 and 122. **CONF 002 (1) Subtask 531266-020-201-002 - Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, LH and STGR1, RH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 72 from Stringer 13 LH to Stringer 1 RH Manpower Resources Manhours 13.00 Minimum number of person 1 Subtask elapsed time 13.00 Skills AIRFRAME NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) Task 51-10-01-250-801 51-10-08 Fig. A-GBAAA Location of Inspection Area for Clips at FR72/FR74 Sheet 01 Fig. A-GBBAB Removal/Installation of Angles, Webs, Brackets and Clips at FR72 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Remove the items between STGR13 and STGR11 LH, refer to Fig. A-GBBAB Sheet 01 and Fig. A-GBBAB Sheet 02

. 1 As shown in View B, remove: 26 Pin-Rivet Discard
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 115 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
26 Collar Discard 6 Rivet Discard 2 As shown in Section B-B, remove: 2 Pin-Rivet Discard 2 Collar Discard 3 As shown in View D, remove: 16 Pin-Rivet Discard 16 Collar Discard 4 Remove: 1 Angle D5357113120400 Item (1) Discard 1 Web D5357113133000 Item (3) Discard 1 Web D5357113134600 Item (5) Discard 1 Bracket-Z D9357073720000 Item (133) Retain 5 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (b) Remove the items between STGR11 and STGR9 LH, refer to Fig. A-GBBAB Sheet 01 and Fig. A-GBBAB Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STRG11 (Section A-A) and 2 Rivet Discard from the angle at STGR10 (Section A-A). Remove: DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 116 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
23 Pin-Rivet Discard 23 Collar Discard 11 Rivet Discard from View B. 2 As shown in View F, remove: 19 Pin-Rivet Discard 19 Collar Discard 16 Rivet Discard 3 Remove: 1 Clip D5357113136600 Item (7) Discard 1 Clip D5357113122600 Item (9) Discard 1 Web D5357113134400 Item (11) Discard 1 Bracket-Z D9357073720000 Item (133) Retain 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (c) Remove the items between STGR9 and STGR7 LH, refer to Fig. A-GBBAB Sheet 01 and Fig. A-GBBAB Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR9 (Section A-A) and 2 Rivet Discard from the angle at STGR8 (Section A-A).
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 117 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
Remove: 31 Pin-Rivet Discard 31 Collar Discard from View B. 2 As shown in View F, remove: 21 Pin-Rivet Discard 21 Collar Discard 14 Rivet Discard 3 Remove: 1 Angle D5357114726000 Item (13) Discard 1 Clip D5357113122400 Item (15) Discard 1 Angle D5357114725800 Item (17) Discard 1 Clip D5357113132200 Item (19) Discard 1 Web D5357113134200 Item (21) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (d) Remove the items between STGR7 and STGR5 LH, refer to Fig. A-GBBAB Sheet 01 and Fig. A-GBBAB Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR7 (Section A-A) and 2 Rivet Discard
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 118 6

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# @A318/A319/A320/A321 SERVICE BULLETIN from the angle at STGR6 (Section A-A). Remove: 33 Pin-Rivet Discard 33 Collar Discard 2 Rivet Discard from View B. 2 As shown in View F, remove: 28 Pin-Rivet Discard 28 Collar Discard 10 Rivet Discard 3 Remove: 1 Angle D5357114725600 Item (23) Discard 1 Angle D5357114727800 Item (25) Discard 1 Clip D5357113136400 Item (27) Discard 1 Angle D5357114725400 Item (29) Discard 1 Clip D5357072231000 Item (32) Discard 1 Angle D5357114727600 Item (33) Discard 1 Web D5357113134000 Item (35) Discard 1 Bracket-Z D9357073720000 Item (133) Retain 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow.
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 119 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (e) Remove the items between STGR5 and STGR3 LH, refer to Fig. A-GBBAB Sheet 01 and Fig. A-GBBAB Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR5 (Section A-A) and 2 Rivet Discard from the angle at STGR4 (Section A-A). Remove: 17 Pin-Rivet Discard 17 Collar Discard from View B. 2 As shown in View F, remove: 19 Pin-Rivet Discard 19 Collar Discard 14 Rivet Discard 3 Remove: 1 Angle D5357114725200 Item (36) Discard 1 Angle D5357114727400 Item (38) Discard 1 Clip D5357072221200 Item (40) Discard 1 Angle D5357114725000 Item (42) Discard 1 Web D5357072222000 Item (44) Discard 1 Clip D5357072221400 Item (46) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 120 6

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# @A318/A319/A320/A321 SERVICE BULLETIN

c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (f) Remove the items at STGR1 RH and LH, refer to Fig. A-GBBAB Sheet 01 and Fig. A-GBBAB Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR1 (Section A-A). 10 Pin-Rivet Discard 10 Nut Discard from View B. 2 As shown in View E, remove: 7 Pin-Rivet Discard 7 Nut Discard 8 Rivet Discard 3 Remove: 1 Clip D5357072221800 Item (48) Discard 1 Web D5357072221600 Item (49) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 121 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (2) Subtask 531266-420-201-002 - Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR1, RH and STGR13, LH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 72 from Stringer 1 RH to Stringer 13 LH Manpower Resources Manhours 16.00 Minimum number of person 1 Subtask elapsed time 16.00 Skills AIRFRAME Material necessary to do the job Kit 531266D12R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 D5357113120490 1 ANGLE 3 D5357113133090 1 WEB 5 D5357113134690 1 WEB 7 D5357113136690 1 CLIP 9 D5357113122690 1 CLIP 11 D5357113134490 1 WEB 13 D5357114726090 1 ANGLE 15 D5357113122490 1 CLIP 17 D5357114725890 1 ANGLE 19 D5357113132290 1 CLIP 21 D5357113134290 1 WEB 23 D5357114725690 1 ANGLE 25 D5357114727890 1 ANGLE 27 D5357113136490 1 CLIP 29 D5357114725490 1 ANGLE 31 D5357072231090 1 CLIP 33 D5357114727690 1 ANGLE 35 D5357113134090 1 WEB 36 D5357114725290 1 ANGLE 38 D5357114727490 1 ANGLE 40 D5357072221290 1 CLIP 42 D5357114725090 1 ANGLE 44 D5357072222090 1 WEB 46 D5357072221490 1 CLIP 48 D5357072221890 1 CLIP 49 D5357072221690 1 WEB 102 DAN5-6-4X 31 PIN 103 DAN11-6X 140 COLLAR 104 DAN5-6-5X 40 PIN DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 122 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 105 DAN5-6-6X 2 PIN 106 EN6081D5-06 33 RIVET 108 NSA5330-6 27 COLLAR 109 DAN5-6-6 16 PIN 110 NSA5075-6 59 COLLAR 111 DAN5-6-5 27 PIN 113 DAN5-6-3X 3 PIN 114 DAN5-8-5X 10 PIN 115 DAN11-8X 29 COLLAR 116 DAN5-8-4X 2 PIN 117 DAN5-8-7X 8 PIN 118 DAN5-8-8X 2 PIN 119 DAN6-6-3X 8 PIN 120 DAN6-6-4X 29 PIN 121 DAN6-6-5Y 13 PIN 122 EN6069D5-06 12 RIVET 123 DAN6-8-6X 7 PIN 124 DAN6-6-6Y 14 PIN 125 DAN6-6-7X 19 PIN 126 DAN6-6-6 4 PIN 127 DAN6-6-5X 4 PIN 128 DAN6-6-3 8 PIN 129 DAN5-6-3 4 PIN 132 DAN6-6-6X 2 PIN 135 EN6081D5-07 2 RIVET 136 EN6069D5-07 33 RIVET 137 EN6069D5-08 17 RIVET Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant, Brush Consistency 09-013 As required Corrosion Preventative Compound, Temporary 15-009 As required Anti-Corrosion Primer Polyurethane 16-001 As required Polyurethane Finish Paint 16-018 As required References Consumable Material List (CML) Fig. A-GBBAB Removal/Installation of Angles, Webs, Brackets and Clips at FR72 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-GBDAB Fastener Symbol Identification Sheet 01
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 123 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (a) Install the items between STGR1 LH and RH, refer to Fig. A-GBBAB Sheet 03 and Fig. A-GBDAB Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Web D5357072221690 Item 49 with: 8 Pin DAN5-8-7X Item 117 8 Collar DAN11-8X Item 115 and then install: 1 Clip D5357072221890 Item 48 with: 2 PIN DAN5-8-8X Item 118 2 Collar DAN11-8X Item 115 2 As shown in Section E-E, install: 2 Pin DAN5-6-3 Item 129 2 Collar NSA5075-6 Item 110 3 As shown in View K, install: 7 Pin DAN6-8-6X Item 123 7 Collar DAN11-8X Item 115 5 Rivet EN6069D5-07 Item 136 3 Rivet EN6069D5-08 Item 137 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 115,117, 118 and 123. DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 124 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 106, 115, 117, 118, 123, 136 and 137. (b) Install the items between STGR3 and STGR4 on the LH Side, refer to Fig. AGBBAB Sheet 03, Fig. A-GBBAB Sheet 04 and Fig. A-GBDAB Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357114725090 Item 42 1 Clip D5357072221490 Item 46 with: 4 Pin DAN5-8-5X Item 114 4 Collar DAN11-8X Item 115 2 Pin DAN5-6-5 Item 111 2 Collar NSA5075-6 Item 110 2 As shown in Section C-C, STGR4 install: 2 Rivet EN6081D5-06 Item 106 3 As shown in View L, install between STGR3 and STGR4: 3 Pin DAN6-6-5X Item 127 3 Collar DAN11-6X Item 103 3 Pin DAN6-6-6Y Item 124 3 Collar NSA5330-6 Item 108 1 Pin DAN6-6-6X Item 132 1 Collar DAN11-6X Item 103 7 Rivet EN6069D5-08 Item 137
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 125 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 103, 109, 110, 114, 115, 124 and 132. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 103, 106, 109, 110, 114, 115, 124, 132 and 137. (c) Install the items between STGR4 and STGR5 on the LH Side, refer to Fig. AGBBAB Sheet 03, Fig. A-GBBAB Sheet 04 and Fig. A-GBDAB Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357114725290 Item 36 1 Web D5357072222090 Item 44 with: 2 Pin DAN5-8-4X Item 116 2 Collar DAN11-8X Item 115 and then install: 1 Clip D5357072221290 Item 40 with: 6 Pin DAN5-8-5X Item 114 6 Collar DAN11-8X Item 115 and then install: 1 Angle D5357114727490 Item 38
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 126 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN
with: 4 Pin DAN5-6-6 Item 109 4 Collar NSA5075-6 Item 110 2 As shown in Section, C-C at STGR5, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in View L, between STGR4 and STGR5, install: 11 Pin DAN6-6-6Y Item 124 11 Collar NSA5330-6 Item 108 1 Pin DAN6-6-6X Item 132 1 Collar DAN11-6X Item 103 7 Rivet EN6069D5-08 Item 137 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 103, 109, 110, 114, 115, 116, 124 and 132. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 103, 106, 109, 110, 114, 115, 116, 124, 122, 132 and 137. (d) Install the items between STGR5 and STGR7 on the LH Side, refer to Fig. AGBBAB Sheet 03, Fig. A-GBBAB Sheet 04 and Fig. A-GBDAB Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 127 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN 1 Angle D5357114725490 Item 29 1 Angle D5357114725690 Item 23 1 Web D5357113134090 Item 35 with: 9 Pin DAN5-6-4X Item 102 9 Collar DAN11-6X Item 103 2 Rivet EN6081D5-07 Item 135 and then between STGR5 and STGR6 install: 1 Clip D5357072231090 Item 31 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 and then between STGR5 and STGR6 install: 1 Angle D5357114727690 Item 33 with: 5 Pin DAN5-6-6 Item 109 5 Collar NSA5075-6 Item 110 and then between STGR6 and STGR7 install: 1 Clip D5357113136490 Item 27 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 and then between STGR6 and STGR7 install: 1 Angle D5357114727890 Item 25 with: 5 Pin DAN5-6-6 Item 109 5 Collar NSA5075-6 Item 110
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 128 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN
2 As shown in Section C-C, at STGR6, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section C-C, at STGR7, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View L, between STGR5 and STGR7, install: 19 Pin DAN6-6-7X Item 125 20 Collar DAN11-6X Item 103 9 Rivet EN6069D5-07 Item 136 4 Pin DAN6-6-6 Item 126 4 Collar NSA5075-6 Item 110 4 Pin DAN6-6-5Y Item 121 4 Collar NSA5330-6 Item 108 1 Pin DAN6-6-5X Item 127 1 Rivet EN6069D5-06 Item 122 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 109, 110, 121, 125, 108, 126 and 127. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 109, 110, 121, 122, 125, 126, 127 and 136.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 129 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN (e) Install the items between STGR7 and STGR9 on the LH Side, refer to Fig. AGBBAB Sheet 03, Fig. A-GBBAB Sheet 04 and Fig. A-GBDAB Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357114725890 Item 17 1 Angle D5357114726090 Item 13 NOTE : Item 17 and Item 13 are temporally held in place. Then between STGR7 and STGR9 install: 1 Web D5357113134290 Item 21 with: 10 Pin DAN5-6-4X Item 102 10 Collar DAN11-6X Item 103 and then between STGR7 and STGR8 install: 1 Clip D5357113132290 Item 19 with: 5 Pin DAN5-6-5X Item 104 5 Collar DAN11-6X Item 103 4 Pin DAN5-6-5 Item 111 4 Collar NSA5075-6 Item 110 and then between Stringer STGR8 and STGR9 install: 1 Clip D5357113122490 Item 15 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 5 Pin DAN5-6-5 Item 111 5 Collar NSA5075-6 Item 110
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 130 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN
2 As shown in Section C-C, at STGR8, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section C-C, at STGR9, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View L, between STGR7 and STGR9, install: 10 Pin DAN6-6-4X Item 120 2 Pin DAN6-6-5X Item 127 12 Collar DAN11-6X Item 103 9 Pin DAN6-6-5Y Item 121 9 Collar NSA5330-6 Item 108 12 Rivet EN6069D5-07 Item 136 2 Rivet EN6069D5-06 Item 122 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 110, 111, 120, 122, and 127. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 110, 111, 120, 121, 122, 127 and 136. (f) Install the items between STGR9 and STGR11 on the LH Side, refer to Fig. AGBBAB Sheet 03, Fig. A-GBBAB Sheet 04 and Fig. A-GBDAB Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 131 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN to wet install on Frame 72, as shown in View G: 1 Bracket-Z D9357073720000 Item (133) Retained at removal 1 Web D5357113134490 Item 11 with: 2 Rivet EN6081D5-06 Item 106 9 Pin DAN5-6-4X Item 102 9 Collar DAN11-6X Item 103 and then STGR9 and STGR10, install: 1 Clip D5357113122690 Item 9 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 5 Rivet EN6081D5-06 Item 106 and then between STGR10 and STGR11, install: 1 Clip D5357113136690 Item 7 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 4 Rivet EN6081D5-06 Item 106 2 As shown in Section C-C, at STGR10 install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section C-C, at STGR11 install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View L, between STGR9 and STGR11, install: 19 Pin DAN6-6-4X Item 120 19 Collar DAN11-6X Item 103 7 Rivet EN6069D5-07 Item 136 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 132 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
9 Rivet EN6069D5-06 Item 122 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 120. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 106, 120, 122 and 136. (g) Install the items between STGR11 and STGR13 on the LH Side, refer to Fig. AGBBAB Sheet 03 and Fig. A-GBDAB Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Bracket-Z D9357073720000 Item (133) Retained at removal 1 Web D5357113134690 Item 5 with: 2 Rivet EN6081D5-06 Item 106 3 Pin DAN5-6-3X Item 113 3 Collar DAN11-6X Item 103 and then install: 1 Web D5357113133090 Item 3 with: 3 Pin DAN5-6-4X Item 102 3 Collar DAN11-6X Item 103 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 133 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
4 Rivet EN6081D5-06 Item 106 and then install: 1 Angle D5357113120490 Item 1 with: 16 Pin DAN5-6-5 Item 111 18 Collar NSA5075-6 Item 110 2 Pin DAN5-6-6 Item 109 2 Pin DAN5-6-6X Item 105 2 Collar DAN11-6X Item 103 2 As shown in Section D-D, at STGR12, install: 2 Pin DAN5-6-3 Item 129 2 Collar NSA5075-6 Item 110 3 As shown in View J, install: 8 Pin DAN6-6-3X Item 119 8 Collar DAN11-6X Item 103 8 Pin DAN6-6-3 Item 128 8 Collar NSA5075-6 Item 110 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 107, 108, 113, 119, 112 and 128. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 106, 107, 108, 113, 119, 112 and 128. DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 134 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN (3) Subtask 531266-020-208-002 - Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, RH and STGR3, RH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 72 from Stringer 13 RH to Stringer 3 RH Manpower Resources Manhours 11.00 Minimum number of person 1 Subtask elapsed time 11.00 Skills AIRFRAME NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) Task 51-10-01-250-801 51-10-08 Fig. A-GBAAA Location of Inspection Area for Clips at FR72/FR74 Sheet 01 Fig. A-GBBAB Removal/Installation of Angles, Webs, Brackets and Clips at FR72 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Remove the items between STGR13 and STGR11 RH, refer to Fig. A-GBBAB Sheet 01 and Fig. A-GBBAB Sheet 02

. 1 As shown in View B, remove: 26 Pin-Rivet Discard 26 Collar Discard 6 Rivet Discard 2 As shown in Section B-B, remove: 2 Pin-Rivet Discard 2 Collar Discard 3 As shown in View D, remove: 16 Pin-Rivet Discard 16 Collar Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 135 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
4 Remove: 1 Angle D5357113120500 Item (2) Discard 1 Web D5357113133100 Item (4) Discard 1 Web D5357113134700 Item (6) Discard 1 Bracket-Z D9357073720000 Item (133) Retain 5 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (b) Remove the items between STGR11 and STGR9 RH, refer to Fig. A-GBBAB Sheet 01 and Fig. A-GBBAB Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STRG11 (Section A-A) and 2 Rivet Discard from the angle at STGR10 (Section A-A). Remove: 23 Pin-Rivet Discard 23 Collar Discard 11 Rivet Discard from View B. 2 As shown in View F, remove: 19 Pin-Rivet Discard 19 Collar Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 136 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
16 Rivet Discard 3 Remove: 1 Clip D5357113136700 Item (8) Discard 1 Clip D5357113122700 Item (10) Discard 1 Web D5357113134500 Item (12) Discard 1 Bracket-Z D9357073720000 Item (133) Retain 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (c) Remove the items between STGR9 and STGR7 RH, refer to Fig. A-GBBAB Sheet 01 and Fig. A-GBBAB Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR9 (Section A-A) and 2 Rivet Discard from the angle at STGR8 (Section A-A). Remove: 31 Pin-Rivet Discard 31 Collar Discard from View B. 2 As shown in View F, remove: 21 Pin-Rivet Discard 21 Collar Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 137 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
14 Rivet Discard 3 Remove: 1 Angle D5357114726100 Item (14) Discard 1 Clip D5357113122500 Item (16) Discard 1 Angle D5357114725900 Item (18) Discard 1 Clip D5357113132300 Item (20) Discard 1 Web D5357113134300 Item (22) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (d) Remove the items between STGR7 and STGR5 RH, refer to Fig. A-GBBAB Sheet 01 and Fig. A-GBBAB Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR7 (Section A-A) and 2 Rivet Discard from the angle at STGR6 (Section A-A). Remove: 33 Pin-Rivet Discard 33 Collar Discard 2 Rivet Discard from View B.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 138 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
2 As shown in View F, remove: 28 Pin-Rivet Discard 28 Collar Discard 10 Rivet Discard 3 As shown in View C, remove: 1 Angle D5357114725700 Item (24) Discard 1 Angle D5357114727900 Item (26) Discard 1 Clip D5357113136500 Item (28) Discard 1 Angle D5357114725500 Item (30) Discard 1 Clip D5357072231000 Item (32) Discard 1 Angle D5357114727700 Item (34) Discard 1 Web-Shear D5357116135000 Item (50) Discard 1 Bracket-Z D9357073720000 Item (133) Retain 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (e) Remove the items between STGR5 and STGR3 RH, refer to Fig. A-GBBAB Sheet 01 and Fig. A-GBBAB Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR5 (Section A-A) and 2 Rivet Discard from the angle at STGR4 (Section A-A). DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 139 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
Remove: 14 Pin-Rivet Discard 14 Collar Discard 3 Rivet Discard from View B. 2 As shown in View F, remove: 19 Pin-Rivet Discard 19 Collar Discard 14 Rivet Discard 3 Remove: 1 Angle D5357114725300 Item (37) Discard 1 Angle D5357114727500 Item (39) Discard 1 Clip D5357072221300 Item (41) Discard 1 Angle D5357114725100 Item (43) Discard 1 Web D5357072222100 Item (45) Discard 1 Clip D5357072221500 Item (47) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 140 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN (4) Subtask 531266-420-202-002 - Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR3, RH to STGR13, RH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 72 from Stringer 3 RH to Stringer 13 RH Manpower Resources Manhours 14.00 Minimum number of person 1 Subtask elapsed time 14.00 Skills AIRFRAME Material necessary to do the job Kit 531266D12R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 D5357113120590 1 ANGLE 4 D5357113133190 1 WEB 6 D5357113134790 1 WEB 8 D5357113136790 1 CLIP 10 D5357113122790 1 CLIP 12 D5357113134590 1 WEB 14 D5357114726190 1 ANGLE 16 D5357113122590 1 CLIP 18 D5357114725990 1 ANGLE 20 D5357113132390 1 CLIP 22 D5357113134390 1 WEB 24 D5357114725790 1 ANGLE 26 D5357114727990 1 ANGLE 28 D5357113136590 1 CLIP 30 D5357114725590 1 ANGLE 32 D5357072231190 1 CLIP 34 D5357114727790 1 ANGLE 37 D5357114725390 1 ANGLE 39 D5357114727590 1 ANGLE 41 D5357072221390 1 CLIP 43 D5357114725190 1 ANGLE 45 D5357072222190 1 WEB 47 D5357072221590 1 CLIP 50 D5357116135090 1 WEB 102 DAN5-6-4X 31 PIN 103 DAN11-6X 140 COLLAR 104 DAN5-6-5X 40 PIN 105 DAN5-6-6X 2 PIN 106 EN6081D5-06 33 RIVET DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 141 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 108 NSA5330-6 27 COLLAR 109 DAN5-6-6 16 PIN 110 NSA5075-6 57 COLLAR 111 DAN5-6-5 27 PIN 113 DAN5-6-3X 3 PIN 114 DAN5-8-5X 10 PIN 115 DAN11-8X 12 COLLAR 116 DAN5-8-4X 2 PIN 119 DAN6-6-3X 8 PIN 120 DAN6-6-4X 29 PIN 121 DAN6-6-5Y 13 PIN 122 EN6069D5-06 12 RIVET 124 DAN6-6-6Y 14 PIN 125 DAN6-6-7X 19 PIN 126 DAN6-6-6 4 PIN 127 DAN6-6-5X 6 PIN 128 DAN6-6-3 8 PIN 129 DAN5-6-3 2 PIN 132 DAN6-6-6X 2 PIN 135 EN6081D5-07 2 RIVET 136 EN6069D5-07 28 RIVET 137 EN6069D5-08 14 RIVET Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant, Brush Consistency 09-013 As required Corrosion Preventative Compound, Temporary 15-009 As required Anti-Corrosion Primer Polyurethane 16-001 As required Polyurethane Finish Paint 16-018 As required References Consumable Material List (CML) Fig. A-GBBAB Removal/Installation of Angles, Webs, Brackets and Clips at FR72 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-GBDAB Fastener Symbol Identification Sheet 01

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 142 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN (a) Install the items between STGR3 and STGR4 on the RH Side, refer to Fig. AGBBAB Sheet 03, Fig. A-GBBAB Sheet 04 and Fig. A-GBDAB Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357114725190 Item 43 1 Clip D5357072221590 Item 47 with: 4 Pin DAN5-8-5X Item 114 4 Collar DAN11-8X Item 115 2 Pin DAN5-6-5 Item 111 2 Collar NSA5075-6 Item 110 2 As shown in Section C-C at STGR4, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in View L, at STGR3 and STGR4, install: 3 Pin DAN6-6-6Y Item 124 3 Collar NSA5330-6 Item 108 3 Pin DAN6-6-5X Item 127 4 Collar DAN11-6X Item 103 1 Pin DAN6-6-6X Item 132 7 Rivet EN6069D5-08 Item 137 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 103, 108, 110, 111, 114, 115, 124, 127 and 132.
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 143 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN
5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 103, 106, 108, 110, 111, 114, 115, 124, 127, 132 and 137. (b) Install the items between STGR4 and STGR5 on the RH Side, refer to Fig. AGBBAB Sheet 03, Fig. A-GBBAB Sheet 04 and Fig. A-GBDAB Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357114725390 Item 37 1 Web D5357072222190 Item 45 with: 2 Pin DAN5-8-4X Item 116 2 Collar DAN11-8X Item 115 and then install: 1 Clip D5357072221390 Item 41 with: 6 Pin DAN5-8-5X Item 114 6 Collar DAN11-8X Item 115 and then install: 1 Angle D5357114727590 Item 39 with: 4 Pin DAN5-6-6 Item 109 4 Collar NSA5075-6 Item 110 2 As shown in Section C-C at STGR5, install: 2 Rivet EN6081D5-06 Item 106

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 144 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN
3 As shown in View L, at STGR4 and STGR5, install: 11 Pin DAN6-6-6Y Item 124 11 Collar NSA5330-6 Item 108 1 Pin DAN6-6-6X Item 132 1 Collar DAN11-6X Item 103 7 Rivet EN6069D5-08 Item 137 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 103, 108, 109, 110, 114, 115, 116, 124 and 132. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 103, 106, 108, 109, 110, 114, 115, 116, 124, 132 and 137. (c) Install the items between STGR5 and STGR7 on the RH Side, refer to Fig. AGBBAB Sheet 03, Fig. A-GBBAB Sheet 04 and Fig. A-GBDAB Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View H: 1 Angle D5357114725590 Item 30 1 Angle D5357114725790 Item 24 1 Bracket-Z D9357073720000 Item (133) Retained at removal 1 Web D5357116135090 Item 50 with: DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 145 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN
9 Pin DAN5-6-4X Item 102 9 Collar DAN11-6X Item 103 2 Rivet EN6081D5-07 Item 135 and between STGR5 and STGR7, as shown in View H, install: 1 Clip D5357072231190 Item 32 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 and between STGR5 and STGR7, install: 1 Angle D5357114727790 Item 34 with: 5 Pin DAN5-6-6 Item 109 5 Collar NSA5075-6 Item 110 and between STGR6 and STGR7, install: 1 Clip D5357113136590 Item 28 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 and between STGR6 and STGR7 install: 1 Angle D5357114727990 Item 26 with: 5 Pin DAN5-6-6 Item 109 5 Collar NSA5075-6 Item 110 2 As shown in Section C-C at STGR6, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section C-C at STGR7, install: 2 Rivet EN6081D5-06 Item 106

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 146 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
4 Install to the fuselage skin between STGR5 and STGR7, refer to Fig. AGBBAB Sheet 04, View L: 19 Pin DAN6-6-7X Item 125 1 Pin DAN6-6-5X Item 127 20 Collar DAN11-6X Item 103 4 Pin DAN6-6-6 Item 126 4 Collar NSA5075-6 Item 110 9 Rivet EN6069D5-07 Item 136 4 Pin DAN6-6-5Y Item 121 4 Collar NSA5330-6 Item 108 1 Rivet EN6069D5-06 Item 122 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 109, 110, 121, 125, 126 and 127. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 109, 110, 121, 122, 125, 126, 127, 135 and 136. (d) Install the items between STGR7 and STGR9 on the RH Side, refer to Fig. AGBBAB Sheet 03, Fig. A-GBBAB Sheet 04 and Fig. A-GBDAB Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357114725990 Item 18 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 147 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN 1 Angle D5357114726190 Item 14 NOTE : Item 18 and Item 14 are temporally held in place. Then between STGR7 and STGR9 install: 1 Web D5357113134390 Item 22 with: 10 Pin DAN5-6-4X Item 102 10 Collar DAN11-6X Item 103 and then between STGR7 and STGR8 install: 1 Clip D5357113132390 Item 20 with: 5 Pin DAN5-6-5X Item 104 5 Collar DAN11-6X Item 103 4 Pin DAN5-6-5 Item 111 4 Collar NSA5075-6 Item 110 and then between Stringer STGR8 and STGR9 install: 1 Clip D5357113122590 Item 16 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 5 Pin DAN5-6-5 Item 111 5 Collar NSA5075-6 Item 110 2 As shown in Section C-C at STGR8, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section C-C at STGR9, install: 2 Rivet EN6081D5-06 Item 106 4 Install to the fuselage skin between STGR7 and STGR9, refer to Fig. AGBBAB Sheet 04, View L: 10 Pin DAN6-6-4X Item 120 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 148 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
2 Pin DAN6-6-5X Item 127 12 Collar DAN11-6X Item 103 9 Pin DAN6-6-5Y Item 121 9 Collar NSA5330-6 Item 108 12 Rivet EN6069D5-07 Item 136 2 Rivet EN6069D5-06 Item 122 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 110, 111, 120, 121 and 127. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 108, 110, 111, 120, 121, 122, 127 and 136. (e) Install the items between STGR9 and STGR11 on the RH Side, refer to Fig. AGBBAB Sheet 03, Fig. A-GBBAB Sheet 04 and Fig. A-GBDAB Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Bracket-Z D9357073720000 Item (133) Retained at removal 1 Web D5357113134590 Item 12 with: 2 Rivet EN6081D5-06 Item 106 9 Pin DAN5-6-4X Item 102 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 149 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
9 Collar DAN11-6X Item 103 and then STGR9 and STGR10, install: 1 Clip D5357113122790 Item 10 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 5 Rivet EN6081D5-06 Item 106 and then between STGR10 and STGR11, install: 1 Clip D5357113136790 Item 8 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 4 Rivet EN6081D5-06 Item 106 2 As shown in Section C-C, at STGR 10, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section C-C, at STGR 11, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View L, between STGR9 and STGR11, install: 19 Pin DAN6-6-4X Item 120 19 Collar DAN11-6X Item 103 7 Rivet EN6069D5-07 Item 136 9 Rivet EN6069D5-06 Item 122 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, and 120. DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 150 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 106, 120, 122 and 136. (f) Install the items between STGR11 and STGR13 on the RH Side, refer to Fig. AGBBAB Sheet 03 and Fig. A-GBDAB Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Bracket-Z D9357073720000 Item (133) Retained at removal 1 Web D5357113134790 Item 6 with: 2 Rivet EN6081D5-06 Item 106 3 Pin DAN5-6-3X Item 113 3 Collar DAN11-6X Item 103 and then install: 1 Web D5357113133190 Item 4 with: 3 Pin DAN5-6-4X Item 102 3 Collar DAN11-6X Item 103 4 Rivet EN6081D5-06 Item 106 and then install: 1 Angle D5357113120590 Item 2 with: 16 Pin DAN5-6-5 Item 111 2 Pin DAN5-6-6 Item 109

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 151 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
18 Collar NSA5075-6 Item 110 2 Pin DAN5-6-6X Item 105 2 Collar DAN11-6X Item 103 2 As shown in Section D-D, at STGR12, install: 2 Pin DAN5-6-3 Item 129 2 Collar NSA5075-6 Item 110 3 As shown in View J, install: 8 Pin DAN6-6-3X Item 119 8 Collar DAN11-6X Item 103 8 Pin DAN6-6-3 Item 128 8 Collar NSA5075-6 Item 110 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 105, 107, 108, 110, 111, 112, 113, 119, 128 and 129. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 105, 106, 107, 108, 110, 111, 112, 113, 119, 128 and 129. (5) Subtask 531266-020-203-002 - Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, LH and STGR1, RH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 74 from Stringer 12 LH to Stringer 1 RH

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 152 6

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# @A318/A319/A320/A321 SERVICE BULLETIN Manpower Resources Manhours 11.00 Minimum number of person 1 Subtask elapsed time 11.00 Skills AIRFRAME NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) Task 51-10-01-250-801 51-10-08 Fig. A-GBAAA Location of Inspection Area for Clips at FR72/FR74 Sheet 01 Fig. A-GBCAB Removal/Installation of Angles, Webs, Brackets and Clips at FR74 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Remove the items between STGR12 and STGR9 LH, refer to Fig. A-GBCAB Sheet 01 and Fig. A-GBCAB Sheet 02

. 1 As shown in Section A-A, remove: 2 Rivet Discard from the angle at STGR11 (Section A-A) and 2 Rivet Discard from the angle at STGR10 (Section A-A). Remove: 42 Pin-Rivet Discard 42 Collar Discard 8 Rivet Discard from View B. 2 As shown in View E, remove: 27 Pin-Rivet Discard 27 Collar Discard 16 Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 153 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
3 Remove: 1 Angle D5357113331200 Item (51) Discard 1 Filler D5357113335400 Item (53) Discard 1 Angle D5357113321400 Item (54) Discard 1 Angle D5357113321000 Item (56) Discard 1 Angle D5357113320800 Item (58) Discard 1 Web D5357113336000 Item (60) Discard 1 Web D5357113330600 Item (62) Discard 4 As shown in View F, remove: 5 Pin-Rivet Discard 5 Collar Discard 5 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (b) Remove the items between STGR9 and STGR7 LH, refer to Fig. A-GBCAB Sheet 01 and Fig. A-GBCAB Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STRG9 (Section A-A) and 2 Rivet Discard from the angle at STRG8 (Section A-A). Remove: 27 Pin-Rivet Discard
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 154 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
27 Collar Discard from View B. 2 As shown in View E, remove: 19 Pin-Rivet Discard 19 Collar Discard 14 Rivet Discard 3 Remove: 1 Angle D5357114727200 Item (64) Discard 1 Clip D5357113330400 Item (66) Discard 1 Web D5357113336200 Item (68) Discard 1 Angle D5357114727000 Item (70) Discard 1 Clip D5357113330200 Item (72) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (c) Remove the items between STGR7 and STGR5 LH, refer to Fig. A-GBCAB Sheet 01
. 1 Remove: 2 Rivet Discard from the angle at STRG7 (Section A-A) and 2 Rivet Discard from the angle at STRG6 (Section A-A). Remove:
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 155 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
32 Pin-Rivet Discard 32 Collar Discard from View B. 2 As shown in View C, remove: 30 Pin-Rivet Discard 30 Collar Discard 8 Rivet Discard 3 Remove: 1 Angle D5357114726800 Item (74) Discard 1 Clip D5357113330000 Item (76) Discard 1 Angle D5357114728400 Item (78) Discard 1 Angle D5357114726600 Item (80) Discard 1 Clip D5357072431000 Item (82) Discard 1 Web D5357113336400 Item (84) Discard 1 Angle D5357114728200 Item (86) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (d) Remove the items between STGR5 and STGR3, refer to Fig. A-GBCAB Sheet 01

. 1 Remove: 2 Rivet Discard from the angle at STRG5 (Section A-A) and

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 156 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
2 Rivet Discard from the angle at STRG4 (Section A-A). Remove: 16 Pin-Rivet Discard 16 Collar Discard from View B. 2 As shown in View C, remove: 17 Pin-Rivet Discard 17 Collar Discard 14 Rivet Discard 3 Remove: 1 Angle D5357114726400 Item (88) Discard 1 Angle D5357114728000 Item (90) Discard 1 Clip D5357072421200 Item (92) Discard 1 Angle D5357114726200 Item (94) Discard 1 Web D5357072421600 Item (96) Discard 1 Clip D5357072421400 Item (98) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 157 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (e) Remove the items between STGR2 LH and STGR1 RH, refer to Fig. A-GBCAB Sheet 01 and Fig. A-GBCAB Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STRG1 (Section A-A) and 12 Pin-Rivet Discard 12 Collar Discard from View B. 2 As shown in View D, remove: 8 Pin-Rivet Discard 8 Collar Discard 8 Rivet Discard 3 Remove: 1 Clip D5357072221800 Item (48) Discard 1 Web D5357072421800 Item (100) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (6) Subtask 531266-420-203-002 - Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR1, RH and STGR12, LH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 74 from Stringer 1 RH to Stringer 12 LH

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 158 6

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# @A318/A319/A320/A321 SERVICE BULLETIN Manpower Resources Manhours 14.00 Minimum number of person 1 Subtask elapsed time 14.00 Skills AIRFRAME Material necessary to do the job Kit 531266D12R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 48 D5357072221890 1 CLIP 51 D5357113331290 1 ANGLE 53 D5357113335400 1 FILLER 54 D5357113321490 1 ANGLE 56 D5357113321090 1 ANGLE 58 D5357113320890 1 ANGLE 60 D5357113336090 1 WEB 62 D5357113330690 1 WEB 64 D5357114727290 1 ANGLE 66 D5357113330490 1 CLIP 68 D5357113336290 1 WEB 70 D5357114727090 1 ANGLE 72 D5357113330290 1 CLIP 74 D5357114726890 1 ANGLE 76 D5357113330090 1 CLIP 78 D5357114728490 1 ANGLE 80 D5357114726690 1 ANGLE 82 D5357072431090 1 CLIP 84 D5357113336490 1 WEB 86 D5357114728290 1 ANGLE 88 D5357114726490 1 ANGLE 90 D5357114728090 1 ANGLE 92 D5357072421290 1 CLIP 94 D5357114726290 1 ANGLE 96 D5357072421690 1 WEB 98 D5357072421490 1 CLIP 100 D5357072421890 1 WEB 102 DAN5-6-4X 21 PIN 103 DAN11-6X 97 COLLAR 104 DAN5-6-5X 4 PIN 105 DAN5-6-6X 5 PIN 106 EN6081D5-06 26 RIVET 108 NSA5330-6 25 COLLAR 109 DAN5-6-6 38 PIN 110 NSA5075-6 56 COLLAR 111 DAN5-6-5 10 PIN DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 159 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 112 DAN6-6-5 1 PIN 114 DAN5-8-5X 25 PIN 115 DAN11-8X 56 COLLAR 116 DAN5-8-4X 2 PIN 117 DAN5-8-7X 10 PIN 118 DAN5-8-8X 2 PIN 120 DAN6-6-4X 27 PIN 121 DAN6-6-5Y 12 PIN 122 EN6069D5-06 3 RIVET 123 DAN6-8-6X 8 PIN 124 DAN6-6-6Y 13 PIN 125 DAN6-6-7X 23 PIN 126 DAN6-6-6 6 PIN 127 DAN6-6-5X 7 PIN 130 DAN5-6-7X 4 PIN 131 DAN5-8-6X 9 PIN 132 DAN6-6-6X 2 PIN 133 DAN6-5-7 1 PIN 134 DAN6-6-7 1 PIN 136 EN6069D5-07 38 RIVET 137 EN6069D5-08 19 RIVET 144 DAN7-6-11X 1 PIN 145 DAN12-6X 1 COLLAR 146 DAN5-6-10X 2 PIN 148 DAN5-6-8X 2 PIN 160 NSA5075-5 1 COLLAR Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant, Brush Consistency 09-013 As required Corrosion Preventative Compound, Temporary 15-009 As required Anti-Corrosion Primer Polyurethane 16-001 As required Polyurethane Finish Paint 16-018 As required References Consumable Material List (CML) Fig. A-GBCAB Removal/Installation of Angles, Webs, Brackets and Clips at FR74 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-GBDAB Fastener Symbol Identification Sheet 01

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 160 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (a) Install the items between STGR2 on the RH Side and STGR2 on the LH Side, refer to Fig. A-GBCAB Sheet 03, Fig. A-GBCAB Sheet 04 and Fig. A-GBDAB Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Web D5357072421890 Item 100 with: 10 Pin DAN5-8-7X Item 117 10 Collar DAN11-8X Item 115 and then install: 1 Clip D5357072221890 Item 48 with: 2 PIN DAN5-8-8X Item 118 2 Collar DAN11-8X Item 115 2 As shown in Section B-B, at STGR1, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in View J, install: 8 Pin DAN6-8-6X Item 123 8 Collar DAN11-8X Item 115 3 Rivet EN6069D5-07 Item 136 5 Rivet EN6069D5-08 Item 137 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 115, 117, 118 and 123.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 161 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 106, 115, 117, 118, 122, 123, 136 and 137. (b) Install the items between STGR3 and STGR5 on the LH Side, refer to Fig. AGBCAB Sheet 03, Fig. A-GBCAB Sheet 04 and Fig. A-GBDAB Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Angle D5357114726290 Item 94 1 Angle D5357114726490 Item 88 1 Clip D5357072421490 Item 98 1 Web D5357072421690 Item 96 with: 3 Pin DAN5-8-6X Item 131 2 Pin DAN5-8-4X Item 116 5 Collar DAN11-8X Item 115 2 Pin DAN5-6-5 Item 111 2 Collar NSA5075-6 Item 110 and install: 1 Clip D5357072421290 Item 92 with: 6 Pin DAN5-8-5X Item 114 6 Collar DAN11-8X Item 115 and install: 1 Angle D5357114728090 Item 90 with: DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 162 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
4 Pin DAN5-6-6 Item 109 4 Collar NSA5075-6 Item 110 2 As shown in Section B-B, at STGR4, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section B-B, at STGR5, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View H, install: 13 Pin DAN6-6-6Y Item 124 13 Collar NSA5330-6 Item 108 2 Pin DAN6-6-6X Item 132 2 Pin DAN6-6-5X Item 127 4 Collar DAN11-6X Item 103 14 Rivet EN6069D5-08 Item 137 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 103, 108, 109, 110, 111, 114, 115, 116, 124, 127, 131, and 132 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 103, 106, 108, 109, 110, 111, 114, 115, 116, 122, 124, 127, 131, 132 and 137

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 163 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (c) Install the items between STGR5 and STGR7 on the LH Side, refer to Fig. AGBCAB Sheet 03, Fig. A-GBCAB Sheet 04 and Fig. A-GBDAB Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Angle D5357114726690 Item 80 1 Angle D5357114726890 Item 74 NOTE : Item 80 and Item 74 are temporally held in place. Then between STGR5 and STGR7 install: 1 Web D5357113336490 Item 84 with: 10 Pin DAN5-6-4X Item 102 10 Collar DAN11-6X Item 103 and then between Stringer STGR5 and STGR6 install: 1 Clip D5357072431090 Item 82 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 5 Pin DAN5-8-5X Item 114 5 Collar DAN11-8X Item 115 and then between Stringer STGR5 and STGR6 install: 1 Angle D5357114728290 Item 86 with: 5 Pin DAN5-6-6 Item 109 5 Collar NSA5075-6 Item 110 and then between Stringer STGR6 and STGR7 install: 1 Clip D5357113330090 Item 76
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 164 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 5 Pin DAN5-8-5X Item 114 5 Collar DAN11-8X Item 115 and then between Stringer STGR6 and STGR7 install: 1 Angle D5357114728490 Item 78 with: 5 Pin DAN5-6-6 Item 109 5 Collar NSA5075-6 Item 110 2 As shown in Section B-B at STGR6, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section B-B, at STGR7, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View H, install: 19 Pin DAN6-6-7X Item 125 1 Pin DAN6-6-5X Item 127 20 Collar DAN11-6X Item 103 6 Pin DAN6-6-6 Item 126 6 Collar NSA5075-6 Item 110 4 Pin DAN6-6-5Y Item 121 4 Collar NSA5330-6 Item 108 7 Rivet EN6069D5-07 Item 136 1 Rivet EN6069D5-06 Item 122 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 165 6

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# @A318/A319/A320/A321 SERVICE BULLETIN Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 109, 110, 114, 115, 121, 125, 126, and 127. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 109, 110, 114, 115, 121, 125, 126, 127 and 136. (d) Install the items between Stringer STGR7 and STGR9 on the LH Side, refer to Fig. A-GBCAB Sheet 03, Fig. A-GBCAB Sheet 04 and Fig. A-GBDAB Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Angle D5357114727090 Item 70 1 Angle D5357114727290 Item 64 NOTE : Item 70 and Item 64 are temporally held in place. Then between STGR7 and STGR9 install: 1 Web D5357113336290 Item 68 with: 8 Pin DAN5-6-4X Item 102 8 Collar DAN11-6X Item 103 and install: 1 Clip D5357113330290 Item 72 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 4 Pin DAN5-8-5X Item 114
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 166 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
4 Collar DAN11-8X Item 115 4 Pin DAN5-6-5 Item 111 4 Collar NSA5075-6 Item 110 and install: 1 Clip D5357113330490 Item 66 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 5 Pin DAN5-8-5X Item 114 5 Collar DAN11-8X Item 115 4 Pin DAN5-6-5 Item 111 4 Collar NSA5075-6 Item 110 2 As shown in Section B-B, at STGR8, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section B-B, at STGR9, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View K, install: 8 Pin DAN6-6-5Y Item 121 8 Collar NSA5330-6 Item 108 9 Pin DAN6-6-4X Item 120 1 Pin DAN6-6-5X Item 127 10 Collar DAN11-6X Item 103 1 Pin DAN6-6-5 Item 112 1 Collar NSA5075-6 Item 110 2 Rivet EN6069D5-06 Item 122 12 Rivet EN6069D5-07 Item 136

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 167 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 110, 111, 112, 114, 115, 120, 121 and 127 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 110, 111, 112, 114, 115, 120, 121, 122, 127 and 136. (e) Install the items between Stringer STGR9 and STGR12 on the LH Side, refer to Fig. A-GBCAB Sheet 03, Fig. A-GBCAB Sheet 04 and Fig. A-GBDAB Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Web D5357113330690 Item 62 with: 3 Pin DAN5-6-4X Item 102 3 Collar DAN11-6X Item 103 and install: 1 Angle D5357113331290 Item 51 1 Filler D5357113335400 Item 53 1 Angle D5357113321490 Item 54 with: 24 Pin DAN5-6-6 Item 109 24 Collar NSA5075-6 Item 110
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 168 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
and install: 1 Web D5357113336090 Item 60 with: 6 Pin DAN5-8-6X Item 131 6 Collar DAN11-8X Item 115 8 Rivet EN6081D5-06 Item 106 5 Pin DAN5-6-6X Item 105 5 Collar DAN11-6X Item 103 and install: 1 Angle D5357113320890 Item 58 1 Angle D5357113321090 Item 56 with: 4 Pin DAN5-6-7X Item 130 4 Collar DAN11-6X Item 103 2 As shown in Section B-B, at STGR10, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section B-B, at STGR11, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View K, install: 18 Pin DAN6-6-4X Item 120 3 Pin DAN6-6-5X Item 127 4 Pin DAN6-6-7X Item 125 25 Collar DAN11-6X Item 103 16 Rivet EN6069D5-07 Item 136 1 Pin DAN6-6-7 Item 134 1 Collar NSA5075-6 Item 110 1 Pin DAN6-5-7 Item 133
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 169 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
1 Collar NSA5075-5 Item 160 5 As shown in View L, install: 1 Pin DAN7-6-11X Item 144 1 Collar DAN12-6X Item 145 2 Pin DAN5-6-10X Item 146 2 Pin DAN5-6-8X Item 148 4 Collar DAN11-6X Item 103 6 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 105, 108, 110, 112, 115, 120, 121, 124, 130 and 131 7 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 105, 106, 108, 110, 112, 115, 120, 121, 124, 130, 131 and 136 (7) Subtask 531266-020-204-002 - Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, RH and STGR3, RH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 74 from Stringer 12 RH to Stringer 3 RH

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 170 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN Manpower Resources Manhours 11.00 Minimum number of person 1 Subtask elapsed time 11.00 Skills AIRFRAME NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) Task 51-10-01-250-801 51-10-08 Fig. A-GBAAA Location of Inspection Area for Clips at FR72/FR74 Sheet 01 Fig. A-GBCAB Removal/Installation of Angles, Webs, Brackets and Clips at FR74 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Remove the items between STGR12 and STGR9 RH, refer to Fig. A-GBCAB Sheet 01 and Fig. A-GBCAB Sheet 02

. 1 As shown in Section A-A, remove: 2 Rivet Discard from the angle at STGR11 (Section A-A) and 2 Rivet Discard from the angle at STGR10 (Section A-A). Remove: 42 Pin-Rivet Discard 42 Collar Discard 8 Rivet Discard from View B. 2 As shown in View E, remove: 27 Pin-Rivet Discard 27 Collar Discard 16 Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 171 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
3 Remove: 1 Angle D5357113331300 Item (52) Discard 1 Filler D5357113335400 Item (53) Discard 1 Angle D5357113321500 Item (55) Discard 1 Angle D5357113321100 Item (57) Discard 1 Angle D5357113320900 Item (59) Discard 1 Web D5357113336100 Item (61) Discard 1 Web D5357113330700 Item (63) Discard 4 As shown in View F, remove: 5 Pin-Rivet Discard 5 Collar Discard 5 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (b) Remove the items between STGR9 and STGR7 RH, refer to Fig. A-GBCAB Sheet 01 and Fig. A-GBCAB Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STRG9 (Section A-A) and 2 Rivet Discard from the angle at STRG8 (Section A-A). Remove: 27 Pin-Rivet Discard
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 172 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
27 Collar Discard from View B. 2 As shown in View E, remove: 19 Pin-Rivet Discard 19 Collar Discard 14 Rivet Discard 3 Remove: 1 Angle D5357114727300 Item (65) Discard 1 Clip D5357113330500 Item (67) Discard 1 Web D5357113336300 Item (69) Discard 1 Angle D5357114727100 Item (71) Discard 1 Clip D5357113330300 Item (73) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (c) Remove the items between STGR7 and STGR5, refer to Fig. A-GBCAB Sheet 01

. 1 Remove: 2 Rivet Discard from the angle at STRG7 (Section A-A) and 2 Rivet Discard from the angle at STRG6 (Section A-A). Remove: 32 Pin-Rivet Discard DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 173 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
32 Collar Discard from View B. 2 As shown in View C, remove: 30 Pin-Rivet Discard 30 Collar Discard 8 Rivet Discard 3 Remove: 1 Angle D5357114726900 Item (75) Discard 1 Clip D5357113330100 Item (77) Discard 1 Angle D5357114728500 Item (79) Discard 1 Angle D5357114726700 Item (81) Discard 1 Clip D5357072431100 Item (83) Discard 1 Web D5357113336500 Item (85) Discard 1 Angle D5357114728300 Item (87) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (d) Remove the items between STGR5 and STGR3, refer to Fig. A-GBCAB Sheet 01

. 1 Remove: 2 Rivet Discard from the angle at STRG5 (Section A-A) and 2 Rivet Discard from the angle at STRG4 (Section A-A). DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 174 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
Remove: 16 Pin-Rivet Discard 16 Collar Discard from View B. 2 As shown in View C, remove: 17 Pin-Rivet Discard 17 Collar Discard 14 Rivet Discard 3 Remove: 1 Angle D5357114726500 Item (89) Discard 1 Angle D5357114728100 Item (91) Discard 1 Clip D5357072421300 Item (93) Discard 1 Angle D5357114726300 Item (95) Discard 1 Web D5357072421700 Item (97) Discard 1 Clip D5357072421500 Item (99) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (8) Subtask 531266-420-204-002 - Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR3, RH and STGR12, RH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 74 from Stringer 3 RH to Stringer 12 RH

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 175 6

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# @A318/A319/A320/A321 SERVICE BULLETIN Manpower Resources Manhours 12.00 Minimum number of person 1 Subtask elapsed time 12.00 Skills AIRFRAME Material necessary to do the job Kit 531266D12R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 52 D5357113331390 1 ANGLE 53 D5357113335400 1 FILLER 55 D5357113321590 1 ANGLE 57 D5357113321190 1 ANGLE 59 D5357113320990 1 ANGLE 61 D5357113336190 1 WEB 63 D5357113330790 1 WEB 65 D5357114727390 1 ANGLE 67 D5357113330590 1 CLIP 69 D5357113336390 1 WEB 71 D5357114727190 1 ANGLE 73 D5357113330390 1 CLIP 75 D5357114726990 1 ANGLE 77 D5357113330190 1 CLIP 79 D5357114728590 1 ANGLE 81 D5357114726790 1 ANGLE 83 D5357072431190 1 CLIP 85 D5357113336590 1 WEB 87 D5357114728390 1 ANGLE 89 D5357114726590 1 ANGLE 91 D5357114728190 1 ANGLE 93 D5357072421390 1 CLIP 95 D5357114726390 1 ANGLE 97 D5357072421790 1 WEB 99 D5357072421590 1 CLIP 102 DAN5-6-4X 21 PIN 103 DAN11-6X 97 COLLAR 104 DAN5-6-5X 4 PIN 105 DAN5-6-6X 5 PIN 106 EN6081D5-06 24 RIVET 108 NSA5330-6 25 COLLAR 109 DAN5-6-6 38 PIN 110 NSA5075-6 56 COLLAR 111 DAN5-6-5 10 PIN 112 DAN6-6-5 1 PIN 114 DAN5-8-5X 25 PIN DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 176 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 115 DAN11-8X 36 COLLAR 116 DAN5-8-4X 2 PIN 120 DAN6-6-4X 27 PIN 121 DAN6-6-5Y 12 PIN 122 EN6069D5-06 3 RIVET 124 DAN6-6-6Y 13 PIN 125 DAN6-6-7X 23 PIN 126 DAN6-6-6 6 PIN 127 DAN6-6-5X 7 PIN 130 DAN5-6-7X 4 PIN 131 DAN5-8-6X 9 PIN 132 DAN6-6-6X 2 PIN 133 DAN6-5-7 1 PIN 134 DAN6-6-7 1 PIN 136 EN6069D5-07 35 RIVET 137 EN6069D5-08 14 RIVET 144 DAN7-6-11X 1 PIN 145 DAN12-6X 1 COLLAR 146 DAN5-6-10X 2 PIN 148 DAN5-6-8X 2 PIN 160 NSA5075-5 1 COLLAR Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant, Brush Consistency 09-013 As required Corrosion Preventative Compound, Temporary 15-009 As required Anti-Corrosion Primer Polyurethane 16-001 As required Polyurethane Finish Paint 16-018 As required References Consumable Material List (CML) Fig. A-GBCAB Removal/Installation of Angles, Webs, Brackets and Clips at FR74 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-GBDAB Fastener Symbol Identification Sheet 01

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 177 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (a) Install the items between STGR3 and STGR5 on the RH Side, refer to Fig. AGBCAB Sheet 03, Fig. A-GBCAB Sheet 04 and Fig. A-GBDAB Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Angle D5357114726390 Item 95 1 Angle D5357114726590 Item 89 1 Clip D5357072421590 Item 99 1 Web D5357072421790 Item 97 with: 3 Pin DAN5-8-6X Item 131 2 Pin DAN5-8-4X Item 116 5 Collar DAN11-8X Item 115 2 Pin DAN5-6-5 Item 111 2 Collar NSA5075-6 Item 110 and install: 1 Clip D5357072421390 Item 93 with: 6 Pin DAN5-8-5X Item 114 6 Collar DAN11-8X Item 115 and install: 1 Angle D5357114728190 Item 91 with: 4 Pin DAN5-6-6 Item 109 4 Collar NSA5075-6 Item 110 2 As shown in Section B-B, at STGR4, install: 2 Rivet EN6081D5-06 Item 106
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 178 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
3 As shown in Section B-B, at STGR5, install: 2 Rivet EN6081D5-06 Item 106 4 Install, as shown in view H: 13 Pin DAN6-6-6Y Item 124 13 Collar NSA5330-6 Item 108 2 Pin DAN6-6-6X Item 132 2 Pin DAN6-6-5X Item 127 4 Collar DAN11-6X Item 103 14 Rivet EN6069D5-08 Item 137 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 103, 109, 110, 111 114, 115, 116, 124, 131 and 132. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 103, 106, 109, 110, 111, 114, 115, 116, 122, 124, 131, 132 and 137. (b) Install the items between STGR5 and STGR7 on the RH Side, refer to Fig. AGBCAB Sheet 03, Fig. A-GBCAB Sheet 04 and Fig. A-GBDAB Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Angle D5357114726790 Item 81 1 Angle D5357114726990 Item 75
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 179 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
NOTE : Item 81 and Item 75 are temporally held in place. Then between STGR5 and STGR7 install: 1 Web D5357113336590 Item 85 with: 10 Pin DAN5-6-4X Item 102 10 Collar DAN11-6X Item 103 and between Stringer STGR5 and STGR6 install: 1 Clip D5357072431190 Item 83 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 5 Pin DAN5-8-5X Item 114 5 Collar DAN11-8X Item 115 and between Stringer STGR5 and STGR6 install: 1 Angle D5357114728390 Item 87 with: 5 Pin DAN5-6-6 Item 109 5 Collar NSA5075-6 Item 110 and between Stringer STGR6 and STGR7 install: 1 Clip D5357113330190 Item 77 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 5 Pin DAN5-8-5X Item 114 5 Collar DAN11-8X Item 115 and between Stringer STGR6 and STGR7 install: 1 Angle D5357114728590 Item 79
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 180 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
with: 5 Pin DAN5-6-6 Item 109 5 Collar NSA5075-6 Item 110 2 As shown in Section B-B, at STGR6, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section B-B, at STGR7, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View H, install: 19 Pin DAN6-6-7X Item 125 1 Pin DAN6-6-5X Item 127 20 Collar DAN11-6X Item 103 6 Pin DAN6-6-6 Item 126 6 Collar NSA5075-6 Item 110 4 Pin DAN6-6-5Y Item 121 4 Collar NSA5330-6 Item 108 7 Rivet EN6069D5-07 Item 136 1 Rivet EN6069D5-06 Item 122 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 109, 110, 114, 115, 121, 125, 126 and 127. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 181 6

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# @A318/A319/A320/A321 SERVICE BULLETIN to the fasteners, Items 102, 103, 104, 106, 108, 109, 110, 114, 115, 121, 122, 125, 126, 127 and 136. (c) Install the items between Stringer STGR7 and STGR9 on the RH Side, refer to Fig. A-GBCAB Sheet 03, Fig. A-GBCAB Sheet 04 and Fig. A-GBDAB Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Angle D5357114727190 Item 71 1 Angle D5357114727390 Item 65 NOTE : Item 71 and Item 65 re temporally held in place. Then between STGR7 and STGR9 install: 1 Web D5357113336390 Item 69 with: 8 Pin DAN5-6-4X Item 102 8 Collar DAN11-6X Item 103 and install: 1 Clip D5357113330390 Item 73 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 4 Pin DAN5-8-5X Item 114 4 Collar DAN11-8X Item 115 4 Pin DAN5-6-5 Item 111 4 Collar NSA5075-6 Item 110 and install: 1 Clip D5357113330590 Item 67 with: 1 Pin DAN5-6-5X Item 104 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 182 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
1 Collar DAN11-6X Item 103 5 Pin DAN5-8-5X Item 114 5 Collar DAN11-8X Item 115 4 Pin DAN5-6-5 Item 111 4 Collar NSA5075-6 Item 110 2 As shown in Section B-B, at STGR8, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section B-B, at STGR9, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View K, install: 9 Pin DAN6-6-4X Item 120 1 Pin DAN6-6-5X Item 127 10 Collar DAN11-6X Item 103 8 Pin DAN6-6-5Y Item 121 8 Collar NSA5330-6 Item 108 1 Pin DAN6-6-5 Item 112 1 Collar NSA5075-6 Item 110 2 Rivet EN6069D5-06 Item 122 12 Rivet EN6069D5-07 Item 136 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 110, 111, 112, 114, 115, 120, 121 and 127.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 183 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 110, 111, 112, 114, 115, 120, 121, 122, 127 and 136. (d) Install the items between STGR9 and STGR12 on the RH Side, refer to Fig. AGBCAB Sheet 03, Fig. A-GBCAB Sheet 04 and Fig. A-GBDAB Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Web D5357113330790 Item 63 with: 3 Pin DAN5-6-4X Item 102 3 Collar DAN11-6X Item 103 and install: 1 Angle D5357113331390 Item 52 1 Filler D5357113335400 Item 53 1 Angle D5357113321590 Item 55 with: 24 Pin DAN5-6-6 Item 109 24 Collar NSA5075-6 Item 110 and install: 1 Web D5357113336190 Item 61 with: 6 Pin DAN5-8-6X Item 131 6 Collar DAN11-8X Item 115 8 Rivet EN6081D5-06 Item 106
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 184 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
5 Pin DAN5-6-6X Item 105 5 Collar DAN11-6X Item 103 and install: 1 Angle D5357113320990 Item 59 1 Angle D5357113321190 Item 57 with: 4 Pin DAN5-6-7X Item 130 4 Collar DAN11-6X Item 103 2 As shown in Section B-B, at STGR10, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section B-B, at STGR11, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View K, install: 18 Pin DAN6-6-4X Item 120 3 Pin DAN6-6-5X Item 127 4 Pin DAN6-6-7X Item 125 25 Collar DAN11-6X Item 103 16 Rivet EN6069D5-07 Item 136 1 Pin DAN6-6-7 Item 134 1 Collar NSA5075-6 Item 110 1 Pin DAN6-5-7 Item 133 1 Collar NSA5075-5 Item 160 5 As shown in View L, install: 1 Pin DAN7-6-11X Item 144 1 Collar DAN12-6X Item 145 2 Pin DAN5-6-10X Item 146 2 Pin DAN5-6-8X Item 148 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 185 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
4 Collar DAN11-6X Item 103 6 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 105, 108, 110, 112, 115, 120, 121, 124, 125, 130 and 131 7 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 105, 106, 108, 110, 112, 115, 120, 121, 124, 125, 130, 131 and 136 **CONF 003 (1) Subtask 531266-020-201-003 - Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, LH and STGR1, RH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 72 from Stringer 13 LH to Stringer 1 RH Manpower Resources Manhours 13.00 Minimum number of person 1 Subtask elapsed time 13.00 Skills AIRFRAME NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) Task 51-10-01-250-801 51-10-08 Fig. A-GBBAD Removal/Installation of Angles, Webs, Brackets and Clips at FR72 Sheet 01 Sheet 02 Sheet 03 Sheet 04

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 186 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
References Fig. A-GBAAA Location of Inspection Area for Clips at FR72/FR74 Sheet 01
(a) Remove the items between STGR13 and STGR11 LH, refer to Fig. A-GBBAD Sheet 01 and Fig. A-GBBAD Sheet 02

. 1 As shown in View B, remove: 26 Pin-Rivet Discard 26 Collar Discard 6 Rivet Discard 2 As shown in Section B-B, remove: 2 Pin-Rivet Discard 2 Collar Discard 3 As shown in View D, remove: 16 Pin-Rivet Discard 16 Collar Discard 4 Remove: 1 Angle D5357113120400 Item (1) Discard 1 Web D5357113133000 Item (3) Discard 1 Web D5357113134600 Item (5) Discard 1 Bracket-Z D9357073720000 Item (133) Retain 5 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01 c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 187 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (b) Remove the items between STGR11 and STGR9 LH, refer to Fig. A-GBBAD Sheet 01 and Fig. A-GBBAD Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STRG11 (Section A-A) and 2 Rivet Discard from the angle at STGR10 (Section A-A). Remove: 23 Pin-Rivet Discard 23 Collar Discard 11 Rivet Discard from View B. 2 As shown in View F, remove: 19 Pin-Rivet Discard 19 Collar Discard 16 Rivet Discard 3 Remove: 1 Clip D5357113136600 Item (7) Discard 1 Clip D5357113122600 Item (9) Discard 1 Web D5357113134400 Item (11) Discard 1 Bracket-Z D9357073720000 Item (133) Retain 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 188 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (c) Remove the items between STGR9 and STGR7 LH, refer to Fig. A-GBBAD Sheet 01 and Fig. A-GBBAD Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR9 (Section A-A) and 2 Rivet Discard from the angle at STGR8 (Section A-A). Remove: 31 Pin-Rivet Discard 31 Collar Discard from View B. 2 As shown in View F, remove: 21 Pin-Rivet Discard 21 Collar Discard 14 Rivet Discard 3 Remove: 1 Angle D5357113138200 Item (13) Discard 1 Clip D5357113137600 Item (15) Discard 1 Angle D5357113138000 Item (17) Discard 1 Clip D5357113137400 Item (19) Discard 1 Web D5357113137200 Item (21) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 189 6

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# @A318/A319/A320/A321 SERVICE BULLETIN - If no cracks are found, do the worksteps that follow. (d) Remove the items between STGR7 and STGR5 LH, refer to Fig. A-GBBAD Sheet 01 and Fig. A-GBBAD Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR7 (Section A-A) and 2 Rivet Discard from the angle at STGR6 (Section A-A). Remove: 33 Pin-Rivet Discard 33 Collar Discard 2 Rivet Discard from View B. 2 As shown in View F, remove: 28 Pin-Rivet Discard 28 Collar Discard 10 Rivet Discard 3 Remove: 1 Angle D5357113137800 Item (23) Discard 1 Angle D5357113138400 Item (25) Discard 1 Clip D5357113137000 Item (27) Discard 1 Angle D5357072223400 Item (29) Discard 1 Clip D5357072222200 Item (31) Discard 1 Angle D5357072223800 Item (33) Discard 1 Web D5357113136800 Item (35) Discard 1 Bracket-Z D9357073720000 Item (133) Retain

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 190 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (e) Remove the items between STGR5 and STGR3 LH, refer to Fig. A-GBBAD Sheet 01 and Fig. A-GBBAD Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR5 (Section A-A) and 2 Rivet Discard from the angle at STGR4 (Section A-A). Remove: 20 Pin-Rivet Discard 8 Collar Discard 12 Nut Discard from View B. 2 As shown in View F, remove: 19 Pin-Rivet Discard 19 Collar Discard 14 Rivet Discard 3 Remove: 1 Angle D5357072223200 Item (36) Discard 1 Angle D5357072223600 Item (38) Discard 1 Clip D5357072222400 Item (40) Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 191 6

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# @A318/A319/A320/A321 SERVICE BULLETIN 1 Angle D5357072223000 Item (42) Discard 1 Web D5357072222600 Item (44) Discard 1 Clip D5357072222800 Item (46) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (f) Remove the items at STGR1 RH and LH, refer to Fig. A-GBBAD Sheet 01 and Fig. A-GBBAD Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR1 (Section A-A). 10 Pin-Rivet Discard 10 Nut Discard from View B. 2 As shown in View E, remove: 7 Pin-Rivet Discard 7 Nut Discard 8 Rivet Discard 3 Remove: 1 Clip D5357072221800 Item (48) Discard 1 Web D5357072221600 Item (49) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 192 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (2) Subtask 531266-420-201-003 - Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR1, RH and STGR13, LH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 72 from Stringer 1 RH to Stringer 13 LH Manpower Resources Manhours 16.00 Minimum number of person 1 Subtask elapsed time 16.00 Skills AIRFRAME Material necessary to do the job Kit 531266D14R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 D5357113120490 1 ANGLE 3 D5357113133090 1 WEB 5 D5357113134690 1 WEB 7 D5357113136690 1 CLIP 9 D5357113122690 1 CLIP 11 D5357113134490 1 WEB 13 D5357113138290 1 ANGLE 15 D5357113137690 1 CLIP 17 D5357113138090 1 ANGLE 19 D5357113137490 1 CLIP 21 D5357113137290 1 WEB 23 D5357113137890 1 ANGLE 25 D5357113138490 1 ANGLE 27 D5357113137090 1 CLIP 29 D5357072223490 1 ANGLE 31 D5357072222290 1 CLIP 33 D5357072223890 1 ANGLE 35 D5357113136890 1 WEB 36 D5357072223290 1 ANGLE 38 D5357072223690 1 ANGLE 40 D5357072222490 1 CLIP DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 193 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 42 D5357072223090 1 ANGLE 44 D5357072222690 1 WEB 46 D5357072222890 1 CLIP 48 D5357072221890 1 CLIP 49 D5357072221690 1 WEB 102 DAN5-6-4X 31 PIN 103 DAN11-6X 143 COLLAR 104 DAN5-6-5X 40 PIN 107 DAN5-6-5 16 PIN 108 NSA5075-6 56 COLLAR 109 DAN5-5-6 18 PIN 111 DAN5-5-5 9 PIN 112 DAN5-6-6 2 PIN 113 DAN5-6-3X 3 PIN 114 DAN5-8-5X 10 PIN 115 DAN11-8X 29 COLLAR 116 DAN5-8-4X 2 PIN 117 DAN5-8-7X 8 PIN 118 DAN5-8-8X 2 PIN 119 DAN6-6-3X 8 PIN 120 DAN6-6-4X 29 PIN 121 DAN6-6-5X 13 PIN 123 DAN6-8-6X 7 PIN 125 DAN6-6-7X 10 PIN 126 DAN6-6-6 4 PIN 127 DAN6-6-5 3 PIN 128 DAN6-6-3 8 PIN 129 DAN5-6-3 4 PIN 132 DAN6-6-6X 9 PIN 134 DAN6-6-7 19 PIN 135 EN6081D5-07 35 RIVET 137 EN6069D5-08 62 RIVET 160 NSA5075-5 27 COLLAR Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant, Brush Consistency 09-013 As required Corrosion Preventative Compound, Temporary 15-009 As required Anti-Corrosion Primer Polyurethane 16-001 As required Polyurethane Finish Paint 16-018 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 194 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
References Consumable Material List (CML) Fig. A-GBBAD Removal/Installation of Angles, Webs, Brackets and Clips at FR72 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-GBDAD Fastener Symbol Identification Sheet 01 (a) Install the items between STGR1 LH and RH, refer to Fig. A-GBBAD Sheet 03 and Fig. A-GBDAD Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Web D5357072221690 Item 49 with: 8 Pin DAN5-8-7X Item 117 8 Collar DAN11-8X Item 115 and then install: 1 Clip D5357072221890 Item 48 with: 2 PIN DAN5-8-8X Item 118 2 Collar DAN11-8X Item 115 2 As shown in Section E-E, install: 2 Pin DAN5-6-3 Item 129 2 Collar NSA5075-6 Item 108 3 As shown in View K, install: 7 Pin DAN6-8-6X Item 123 7 Collar DAN11-8X Item 115 8 Rivet EN6069D5-08 Item 137

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 195 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 115, 117, 118 and 123. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 106, 115, 117, 118, 123 and 137. (b) Install the items between STGR3 and STGR4 on the LH Side, refer to Fig. AGBBAD Sheet 03, Fig. A-GBBAD Sheet 04 and Fig. A-GBDAD Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357072223090 Item 42 1 Clip D5357072222890 Item 46 with: 4 Pin DAN5-8-5X Item 114 4 Collar DAN11-8X Item 115 3 Pin DAN5-5-6 Item 109 3 Collar NSA5075-5 Item 160 2 As shown in Section C-C, STGR4 install: 2 Rivet EN6081D5-07 Item 135 3 As shown in View L, install between STGR3 and STGR4: 3 Pin DAN6-6-6X Item 132 4 Pin DAN6-6-7X Item 125 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 196 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
7 Collar DAN11-6X Item 103 7 Rivet EN6069D5-08 Item 137 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 103, 109, 114, 115, 125, 132 and 160. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 103, 109, 114, 115, 125, 132, 135, 137 and 160. (c) Install the items between STGR4 and STGR5 on the LH Side, refer to Fig. AGBBAD Sheet 03, Fig. A-GBBAD Sheet 04 and Fig. A-GBDAD Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357072223290 Item 36 1 Web D5357072222690 Item 44 with: 2 Pin DAN5-8-4X Item 116 2 Collar DAN11-8X Item 115 and then install: 1 Clip D5357072222490 Item 40 with: 6 Pin DAN5-8-5X Item 114 6 Collar DAN11-8X Item 115
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 197 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
and then install: 1 Angle D5357072223690 Item 38 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 160 2 As shown in Section, C-C at STGR5, install: 2 Rivet EN6081D5-07 Item 135 3 As shown in View L, between STGR4 and STGR5, install: 6 Pin DAN6-6-6X Item 132 6 Pin DAN6-6-7X Item 125 12 Collar DAN11-6X Item 103 7 Rivet EN6069D5-08 Item 137 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 103, 109, 114, 115, 116, 124, 132 and 160. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 103, 109, 114, 115, 116, 124, 122, 132, 135, 137 and 160. (d) Install the items between STGR5 and STGR7 on the LH Side, refer to Fig. AGBBAD Sheet 03, Fig. A-GBBAD Sheet 04 and Fig. A-GBDAD Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 198 6

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# @A318/A319/A320/A321 SERVICE BULLETIN 1 Angle D5357072223490 Item 29 1 Angle D5357113137890 Item 23 1 Web D5357113136890 Item 35 with: 9 Pin DAN5-6-4X Item 102 9 Collar DAN11-6X Item 103 2 Rivet EN6081D5-07 Item 135 and then between STGR5 and STGR6 install: 1 Clip D5357072222290 Item 31 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 and then between STGR5 and STGR6 install: 1 Angle D5357072223890 Item 33 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 160 and then between STGR6 and STGR7 install: 1 Clip D5357113137090 Item 27 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 and then between STGR6 and STGR7 install: 1 Angle D5357113138490 Item 25 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 160
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 199 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
2 As shown in Section C-C, at STGR6, install: 2 Rivet EN6081D5-07 Item 135 3 As shown in Section C-C, at STGR7, install: 2 Rivet EN6081D5-07 Item 135 4 As shown in View L, between STGR5 and STGR7, install: 19 Pin DAN6-6-7 Item 134 24 Collar NSA5075-6 Item 108 10 Rivet EN6069D5-08 Item 137 4 Pin DAN6-6-6 Item 126 4 Pin DAN6-6-5X Item 121 4 Collar DAN11-6X Item 103 1 Pin DAN6-6-5 Item 127 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 109, 110, 121, 126, 127 and 134. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 109, 110, 121, 126, 127, 134, 135 and 137. (e) Install the items between STGR7 and STGR9 on the LH Side, refer to Fig. AGBBAD Sheet 03, Fig. A-GBBAD Sheet 04 and Fig. A-GBDAD Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 200 6

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# @A318/A319/A320/A321 SERVICE BULLETIN to wet install on Frame 72, as shown in View G: 1 Angle D5357113138290 Item 13 1 Angle D5357113138090 Item 17 NOTE : Item 13 and Item 17 are temporally held in place. Then between STGR7 and STGR9 install: 1 Web D5357113137290 Item 21 with: 10 Pin DAN5-6-4X Item 102 10 Collar DAN11-6X Item 103 and then between STGR7 and STGR8 install: 1 Clip D5357113137490 Item 19 with: 5 Pin DAN5-6-5X Item 104 5 Collar DAN11-6X Item 103 4 Pin DAN5-5-5 Item 111 4 Collar NSA5075-5 Item 160 and then between Stringer STGR8 and STGR9 install: 1 Clip D5357113137690 Item 15 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 5 Pin DAN5-5-5 Item 111 5 Collar NSA5075-5 Item 160 2 As shown in Section C-C, at STGR8, install: 2 Rivet EN6081D5-07 Item 135 3 As shown in Section C-C, at STGR9, install: 2 Rivet EN6081D5-07 Item 135
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 201 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
4 As shown in View L, between STGR7 and STGR9, install: 10 Pin DAN6-6-4X Item 120 19 Collar DAN11-6X Item 103 14 Rivet EN6069D5-08 Item 137 9 Pin DAN6-6-5X Item 121 2 Collar NSA5075-6 Item 108 2 Pin DAN6-6-5 Item 127 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 110, 111, 120 and 127. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 108, 110, 111, 120, 121, 127, 135 and 137. (f) Install the items between STGR9 and STGR11 on the LH Side, refer to Fig. AGBBAD Sheet 03, Fig. A-GBBAD Sheet 04 and Fig. A-GBDAD Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Bracket-Z D9357073720000 Item (133) Retained at removal 1 Web D5357113134490 Item 11 with: 2 Rivet EN6081D5-07 Item 135 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 202 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
9 Pin DAN5-6-4X Item 102 9 Collar DAN11-6X Item 103 and then STGR9 and STGR10, install: 1 Clip D5357113122690 Item 9 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 5 Rivet EN6081D5-07 Item 135 and then between STGR10 and STGR11, install: 1 Clip D5357113136690 Item 7 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 4 Rivet EN6081D5-07 Item 135 2 As shown in Section C-C, at STGR10 install: 2 Rivet EN6081D5-07 Item 135 3 As shown in Section C-C, at STGR11 install: 2 Rivet EN6081D5-07 Item 135 4 As shown in View L, between STGR9 and STGR11, install: 10 Pin DAN6-6-4X Item 120 19 Collar DAN11-6X Item 103 16 Rivet EN6069D5-08 Item 137 9 Pin DAN6-6-4X Item 120 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 203 6

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# @A318/A319/A320/A321 SERVICE BULLETIN Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104 and 120. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners Items 102, 103, 104, 120, 135 and 137. (g) Install the items between STGR11 and STGR13 on the LH Side, refer to Fig. AGBBAD Sheet 03 and Fig. A-GBDAD Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Bracket-Z D9357073720000 Item (133) Retained at removal 1 Web D5357113134690 Item 5 with: 2 Rivet EN6081D5-07 Item 135 3 Pin DAN5-6-3X Item 113 3 Collar DAN11-6X Item 103 and then install: 1 Web D5357113133090 Item 3 with: 3 Pin DAN5-6-4X Item 102 3 Collar DAN11-6X Item 103 4 Rivet EN6081D5-07 Item 135 and then install: 1 Angle D5357113120490 Item 1 with: DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 204 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
16 Pin DAN5-6-5 Item 107 18 Collar NSA5075-6 Item 108 2 Pin DAN5-6-6 Item 112 2 As shown in Section D-D, at STGR12, install: 2 Pin DAN5-6-3 Item 129 2 Collar NSA5075-6 Item 108 3 As shown in View J, install: 8 Pin DAN6-6-3X Item 119 8 Collar DAN11-6X Item 103 8 Pin DAN6-6-3 Item 128 8 Collar NSA5075-6 Item 108 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 107, 108, 112, 113, 119 and 128. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 107, 108, 112, 113, 119, 128 and 135. (3) Subtask 531266-020-208-003 - Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, RH and STGR3, RH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 72 from Stringer 13 RH to Stringer 3 RH

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 205 6

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# @A318/A319/A320/A321 SERVICE BULLETIN Manpower Resources Manhours 11.00 Minimum number of person 1 Subtask elapsed time 11.00 Skills AIRFRAME NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) Task 51-10-01-250-801 51-10-08 Fig. A-GBAAA Location of Inspection Area for Clips at FR72/FR74 Sheet 01 Fig. A-GBBAD Removal/Installation of Angles, Webs, Brackets and Clips at FR72 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Remove the items between STGR13 and STGR11 RH, refer to Fig. A-GBBAD Sheet 01 and Fig. A-GBBAD Sheet 02

. 1 As shown in View B, remove: 26 Pin-Rivet Discard 26 Collar Discard 6 Rivet Discard 2 As shown in Section B-B, remove: 2 Pin-Rivet Discard 2 Collar Discard 3 As shown in View D, remove: 16 Pin-Rivet Discard 16 Collar Discard 4 Remove: 1 Angle D5357113120500 Item (2) Discard 1 Web D5357113133100 Item (4) Discard 1 Web D5357113134700 Item (6) Discard 1 Bracket-Z D9357073720000 Item (133) Retain DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 206 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
5 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (b) Remove the items between STGR11 and STGR9 RH, refer to Fig. A-GBBAD Sheet 01 and Fig. A-GBBAD Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STRG11 (Section A-A) and 2 Rivet Discard from the angle at STGR10 (Section A-A). Remove: 23 Pin-Rivet Discard 23 Collar Discard 11 Rivet Discard from View B. 2 As shown in View F, remove: 19 Pin-Rivet Discard 19 Collar Discard 16 Rivet Discard 3 Remove: 1 Clip D5357113136700 Item (8) Discard 1 Clip D5357113122700 Item (10) Discard 1 Web D5357113134500 Item (12) Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 207 6

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# @A318/A319/A320/A321 SERVICE BULLETIN 1 Bracket-Z D9357073720000 Item (133) Retain 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (c) Remove the items between STGR9 and STGR7 RH, refer to Fig. A-GBBAD Sheet 01 and Fig. A-GBBAD Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR9 (Section A-A) and 2 Rivet Discard from the angle at STGR8 (Section A-A). Remove: 31 Pin-Rivet Discard 31 Collar Discard from View B. 2 As shown in View F, remove: 21 Pin-Rivet Discard 21 Collar Discard 14 Rivet Discard 3 Remove: 1 Angle D5357113138300 Item (14) Discard 1 Clip D5357113137700 Item (16) Discard 1 Angle D5357113138100 Item (18) Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 208 6

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# @A318/A319/A320/A321 SERVICE BULLETIN 1 Clip D5357113137500 Item (20) Discard 1 Web D5357113137300 Item (22) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (d) Remove the items between STGR7 and STGR5 RH, refer to Fig. A-GBBAD Sheet 01 and Fig. A-GBBAD Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR7 (Section A-A) and 2 Rivet Discard from the angle at STGR6 (Section A-A). Remove: 33 Pin-Rivet Discard 33 Collar Discard 2 Rivet Discard from View B. 2 As shown in View F, remove: 28 Pin-Rivet Discard 28 Collar Discard 10 Rivet Discard 3 As shown in View C, remove: 1 Angle D5357113137900 Item (24) Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 209 6

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# @A318/A319/A320/A321 SERVICE BULLETIN 1 Angle D5357113138500 Item (26) Discard 1 Clip D5357113137100 Item (28) Discard 1 Angle D5357072223500 Item (30) Discard 1 Clip D5357072222300 Item (32) Discard 1 Angle D5357072223900 Item (34) Discard 1 Web-Shear D5357116135400 Item (50) Discard 1 Bracket-Z D9357073720000 Item (133) Retain 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (e) Remove the items between STGR5 and STGR3 RH, refer to Fig. A-GBBAD Sheet 01 and Fig. A-GBBAD Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR5 (Section A-A) and 2 Rivet Discard from the angle at STGR4 (Section A-A). Remove: 20 Pin-Rivet Discard 8 Collar Discard 12 Nut Discard from View B.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 210 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
2 As shown in View F, remove: 19 Pin-Rivet Discard 19 Collar Discard 14 Rivet Discard 3 Remove: 1 Angle D5357072223300 Item (37) Discard 1 Angle D5357072223700 Item (39) Discard 1 Clip D5357072222500 Item (41) Discard 1 Angle D5357072223100 Item (43) Discard 1 Web D5357072222700 Item (45) Discard 1 Clip D5357072222900 Item (47) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (4) Subtask 531266-420-202-003 - Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR3, RH to STGR13, RH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 72 from Stringer 3 RH to Stringer 13 RH Manpower Resources Manhours 14.00 Minimum number of person 1 Subtask elapsed time 14.00 Skills AIRFRAME

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 211 6

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# @A318/A319/A320/A321 SERVICE BULLETIN Material necessary to do the job Kit 531266D14R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 D5357113120590 1 ANGLE 4 D5357113133190 1 WEB 6 D5357113134790 1 WEB 8 D5357113136790 1 CLIP 10 D5357113122790 1 CLIP 12 D5357113134590 1 WEB 14 D5357113138390 1 ANGLE 16 D5357113137790 1 CLIP 18 D5357113138190 1 ANGLE 20 D5357113137590 1 CLIP 22 D5357113137390 1 WEB 24 D5357113137990 1 ANGLE 26 D5357113138590 1 ANGLE 28 D5357113137190 1 CLIP 30 D5357072223590 1 ANGLE 32 D5357072222390 1 CLIP 34 D5357072223990 1 ANGLE 37 D5357072223390 1 ANGLE 39 D5357072223790 1 ANGLE 41 D5357072222590 1 CLIP 43 D5357072223190 1 ANGLE 45 D5357072222790 1 WEB 47 D5357072222990 1 CLIP 50 D5357116135490 1 WEB 102 DAN5-6-4X 31 PIN 103 DAN11-6X 143 COLLAR 104 DAN5-6-5X 40 PIN 107 DAN5-6-5 16 PIN 108 NSA5075-6 54 COLLAR 109 DAN5-5-6 18 PIN 111 DAN5-5-5 9 PIN 112 DAN5-6-6 2 PIN 113 DAN5-6-3X 3 PIN 114 DAN5-8-5X 10 PIN 115 DAN11-8X 12 COLLAR 116 DAN5-8-4X 2 PIN 119 DAN6-6-3X 8 PIN 120 DAN6-6-4X 29 PIN 121 DAN6-6-5X 13 PIN 125 DAN6-6-7X 10 PIN 126 DAN6-6-6 4 PIN 127 DAN6-6-5 3 PIN
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 212 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 128 DAN6-6-3 8 PIN 129 DAN5-6-3 2 PIN 132 DAN6-6-6X 9 PIN 134 DAN6-6-7 19 PIN 135 EN6081D5-07 35 RIVET 137 EN6069D5-08 54 RIVET 160 NSA5075-5 27 COLLAR Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant, Brush Consistency 09-013 As required Corrosion Preventative Compound, Temporary 15-009 As required Anti-Corrosion Primer Polyurethane 16-001 As required Polyurethane Finish Paint 16-018 As required References Consumable Material List (CML) Fig. A-GBBAD Removal/Installation of Angles, Webs, Brackets and Clips at FR72 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-GBDAD Fastener Symbol Identification Sheet 01 (a) Install the items between STGR3 and STGR4 on the RH Side, refer to Fig. AGBBAD Sheet 03, Fig. A-GBBAD Sheet 04 and Fig. A-GBDAD Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357072223190 Item 43 1 Clip D5357072222990 Item 47 with: 4 Pin DAN5-8-5X Item 114 4 Collar DAN11-8X Item 115 3 Pin DAN5-5-6 Item 109 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 213 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
3 Collar NSA5075-5 Item 160 2 As shown in Section C-C at STGR4, install: 2 Rivet EN6081D5-07 Item 135 3 As shown in View L, at STGR3 and STGR4, install: 3 Pin DAN6-6-6X Item 132 7 Collar DAN11-6X Item 103 4 Pin DAN6-6-7X Item 125 7 Rivet EN6069D5-08 Item 137 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 109, 114, 115, 125, 132 and 160. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 111, 114, 115, 121, 125, 135, 137 and 160. (b) Install the items between STGR4 and STGR5 on the RH Side, refer to Fig. AGBBAD Sheet 03, Fig. A-GBBAD Sheet 04 and Fig. A-GBDAD Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357072223390 Item 37 1 Web D5357072222790 Item 45 with: 2 Pin DAN5-8-4X Item 116
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 214 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
2 Collar DAN11-8X Item 115 and then install: 1 Clip D5357072222590 Item 41 with: 6 Pin DAN5-8-5X Item 114 6 Collar DAN11-8X Item 115 and then install: 1 Angle D5357072223790 Item 39 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 160 2 As shown in Section C-C at STGR5, install: 2 Rivet EN6081D5-07 Item 135 3 As shown in View L, at STGR4 and STGR5, install: 6 Pin DAN6-6-6X Item 132 12 Collar DAN11-6X Item 103 6 Pin DAN6-6-7X Item 125 7 Rivet EN6069D5-08 Item 137 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fastener, Items 103, 109, 114, 115, 116, 125, 132 and 160. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 215 6

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# @A318/A319/A320/A321 SERVICE BULLETIN to the fasteners, 103, 109, 114, 115, 116, 125, 132, 135, 137 and 160. (c) Install the items between STGR5 and STGR7 on the RH Side, refer to Fig. AGBBAD Sheet 03, Fig. A-GBBAD Sheet 04 and Fig. A-GBDAD Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357072223590 Item 30 1 Angle D5357113137990 Item 24 1 Bracket-Z D9357073720000 Item (133) Retained at removal 1 Web D5357116135490 Item 50 with: 9 Pin DAN5-6-4X Item 102 9 Collar DAN11-6X Item 103 2 Rivet EN6081D5-07 Item 135 and between STGR5 and STGR7, as shown in View H, install: 1 Clip D5357072222390 Item 32 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 and between STGR5 and STGR7, install: 1 Angle D5357072223990 Item 34 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 160 and between STGR6 and STGR7, install: 1 Clip D5357113137190 Item 28 with: DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 216 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 and between STGR6 and STGR7 install: 1 Angle D5357113138590 Item 26 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 160 2 As shown in Section C-C at STGR6, install: 2 Rivet EN6081D5-07 Item 135 3 As shown in Section C-C at STGR7, install: 2 Rivet EN6081D5-07 Item 135 4 Install to the fuselage skin between STGR5 and STGR7, refer to Fig. AGBBAD Sheet 04, View L: 19 Pin DAN6-6-7 Item 134 24 Collar NSA5075-6 Item 108 10 Rivet EN6069D5-08 Item 137 4 Pin DAN6-6-6 Item 126 4 Pin DAN6-6-5X Item 121 4 Collar DAN11-6X Item 103 1 Pin DAN6-6-5 Item 127 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 109, 121, 125, 126, 127 and 160.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 217 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, 102, 103, 104, 108, 109, 121, 126, 127, 134, 135, 137 and 160. (d) Install the items between STGR7 and STGR9 on the RH Side, refer to Fig. AGBBAD Sheet 03, Fig. A-GBBAD Sheet 04 and Fig. A-GBDAD Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357113138390 Item 14 1 Angle D5357113138190 Item 18 NOTE : Item 14 and Item 18 are temporally held in place. Then between STGR7 and STGR9 install: 1 Web D5357113137390 Item 22 with: 10 Pin DAN5-6-4X Item 102 10 Collar DAN11-6X Item 103 and then between STGR7 and STGR8 install: 1 Clip D5357113137590 Item 20 with: 5 Pin DAN5-6-5X Item 104 5 Collar DAN11-6X Item 103 4 Pin DAN5-5-5 Item 111 4 Collar NSA5075-5 Item 160 and then between Stringer STGR8 and STGR9 install: 1 Clip D5357113137790 Item 16
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 218 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 5 Pin DAN5-5-5 Item 111 5 Collar NSA5075-5 Item 160 2 As shown in Section C-C at STGR8, install: 2 Rivet EN6081D5-07 Item 135 3 As shown in Section C-C at STGR9, install: 2 Rivet EN6081D5-07 Item 135 4 Install to the fuselage skin between STGR7 and STGR9, refer to Fig. AGBBAD Sheet 04, View L: 10 Pin DAN6-6-4X Item 120 19 Collar DAN11-6X Item 103 14 Rivet EN6069D5-08 Item 137 9 Pin DAN6-6-5X Item 121 2 Collar NSA5075-6 Item 108 2 Pin DAN6-6-5 Item 127 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 110, 111, 120 and 127. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 106, 110, 111, 120, 127, 135 and 137.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 219 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (e) Install the items between STGR9 and STGR11 on the RH Side, refer to Fig. AGBBAD Sheet 03, Fig. A-GBBAD Sheet 04 and Fig. A-GBDAD Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Bracket-Z D9357073720000 Item (133) Retained at removal 1 Web D5357113134590 Item 12 with: 2 Rivet EN6081D5-07 Item 135 9 Pin DAN5-6-4X Item 102 9 Collar DAN11-6X Item 103 and then STGR9 and STGR10, install: 1 Clip D5357113122790 Item 10 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 5 Rivet EN6081D5-07 Item 135 and then between STGR10 and STGR11, install: 1 Clip D5357113136790 Item 8 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 4 Rivet EN6081D5-07 Item 135 2 As shown in Section C-C, at STGR 10, install: 2 Rivet EN6081D5-07 Item 135 3 As shown in Section C-C, at STGR 11, install: 2 Rivet EN6081D5-07 Item 135 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 220 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
4 As shown in View L, between STGR9 and STGR11, install: 19 Pin DAN6-6-4X Item 120 19 Collar DAN11-6X Item 103 16 Rivet EN6069D5-08 Item 137 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104 and 120. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 120, 135, 136 and 137. (f) Install the items between STGR11 and STGR13 on the RH Side, refer to Fig. AGBBAD Sheet 03 and Fig. A-GBDAD Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Bracket-Z D9357073720000 Item (133) Retained at removal 1 Web D5357113134790 Item 6 with: 2 Rivet EN6081D5-07 Item 135 3 Pin DAN5-6-3X Item 113 3 Collar DAN11-6X Item 103 and then install: 1 Web D5357113133190 Item 4 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 221 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
with: 3 Pin DAN5-6-4X Item 102 3 Collar DAN11-6X Item 103 4 Rivet EN6081D5-07 Item 135 and then install: 1 Angle D5357113120590 Item 2 with: 16 Pin DAN5-6-5 Item 107 18 Collar NSA5075-6 Item 108 2 Pin DAN5-6-6 Item 112 2 As shown in Section D-D, at STGR12, install: 2 Pin DAN5-6-3 Item 129 2 Collar NSA5075-6 Item 108 3 As shown in View J, install: 8 Pin DAN6-6-3X Item 119 8 Collar DAN11-6X Item 103 8 Pin DAN6-6-3 Item 128 8 Collar NSA5075-6 Item 108 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fastener, Items 102, 103, 107, 108, 112, 113, 119 and 128. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 222 6

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# @A318/A319/A320/A321 SERVICE BULLETIN to the fasteners, Items 102, 103, 107, 108, 112, 113, 119, 128 and 135. (5) Subtask 531266-020-203-003 - Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, LH and STGR1, RH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 74 from Stringer 12 LH to Stringer 1 RH Manpower Resources Manhours 11.00 Minimum number of person 1 Subtask elapsed time 11.00 Skills AIRFRAME NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) Task 51-10-01-250-801 51-10-08 Fig. A-GBAAA Location of Inspection Area for Clips at FR72/FR74 Sheet 01 Fig. A-GBCAD Removal/Installation of Angles, Webs, Brackets and Clips at FR74 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Remove the items between STGR12 and STGR9 LH, refer to Fig. A-GBCAD Sheet 01 and Fig. A-GBCAD Sheet 02

. 1 As shown in Section A-A, remove: 2 Rivet Discard from the angle at STGR11 (Section A-A) and 2 Rivet Discard from the angle at STGR10 (Section A-A). Remove: 42 Pin-Rivet Discard 42 Collar Discard 8 Rivet Discard from View B.
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 223 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
2 As shown in View E, remove: 25 Pin-Rivet Discard 25 Collar Discard 16 Rivet Discard 3 Remove: 1 Angle D5357113331200 Item (51) Discard 1 Filler D5357113335400 Item (53) Discard 1 Angle D5357113321400 Item (54) Discard 1 Angle D5357113321000 Item (56) Discard 1 Angle D5357113320800 Item (58) Discard 1 Web D5357113336000 Item (60) Discard 1 Web D5357113330600 Item (62) Discard 4 As shown in View F, remove: 5 Pin-Rivet Discard 5 Collar Discard 5 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (b) Remove the items between STGR9 and STGR7 LH, refer to Fig. A-GBCAD Sheet 01 and Fig. A-GBCAD Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STRG9 (Section A-A) and
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 224 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
2 Rivet Discard from the angle at STRG8 (Section A-A). Remove: 27 Pin-Rivet Discard 27 Collar Discard from View B. 2 As shown in View E, remove: 19 Pin-Rivet Discard 19 Collar Discard 14 Rivet Discard 3 Remove: 1 Angle D5357113327000 Item (64) Discard 1 Clip D5357113326400 Item (66) Discard 1 Web D5357113325800 Item (68) Discard 1 Angle D5357113326800 Item (70) Discard 1 Clip D5357113326200 Item (72) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (c) Remove the items between STGR7 and STGR5 LH, refer to Fig. A-GBCAD Sheet 01
. 1 Remove: 2 Rivet Discard
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 225 6

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# @A318/A319/A320/A321 SERVICE BULLETIN from the angle at STRG7 (Section A-A) and 2 Rivet Discard from the angle at STRG6 (Section A-A). Remove: 32 Pin-Rivet Discard 32 Collar Discard from View B. 2 As shown in View C, remove: 30 Pin-Rivet Discard 30 Collar Discard 8 Rivet Discard 3 Remove: 1 Angle D5357113326600 Item (74) Discard 1 Clip D5357113326000 Item (76) Discard 1 Angle D5357113327200 Item (78) Discard 1 Angle D5357072423400 Item (80) Discard 1 Clip D5357072422000 Item (82) Discard 1 Web D5357113325600 Item (84) Discard 1 Angle D5357072423800 Item (86) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 226 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (d) Remove the items between STGR5 and STGR3, refer to Fig. A-GBCAD Sheet 01

. 1 Remove: 2 Rivet Discard from the angle at STRG5 (Section A-A) and 2 Rivet Discard from the angle at STRG4 (Section A-A). Remove: 18 Pin-Rivet Discard 18 Collar Discard from View B. 2 As shown in View C, remove: 17 Pin-Rivet Discard 17 Collar Discard 14 Rivet Discard 3 Remove: 1 Angle D5357072423200 Item (88) Discard 1 Angle D5357072423600 Item (90) Discard 1 Clip D5357072422200 Item (92) Discard 1 Angle D5357072423000 Item (94) Discard 1 Web D5357072422600 Item (96) Discard 1 Clip D5357072422400 Item (98) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 227 6

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# @A318/A319/A320/A321 SERVICE BULLETIN - If no cracks are found, do the worksteps that follow. (e) Remove the items between STGR2 LH and STGR1 RH, refer to Fig. A-GBCAD Sheet 01 and Fig. A-GBCAD Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STRG1 (Section A-A). Remove: 12 Pin-Rivet Discard 12 Collar Discard from View B. 2 As shown in View D, remove: 8 Pin-Rivet Discard 8 Collar Discard 8 Pin-Rivet Discard 3 Remove: 1 Clip D5357072221800 Item (48) Discard 1 Web D5357072421800 Item (100) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (6) Subtask 531266-420-203-003 - Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR1, RH and STGR12, LH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 74 from Stringer 1 RH to Stringer 12 LH DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 228 6

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# @A318/A319/A320/A321 SERVICE BULLETIN Manpower Resources Manhours 14.00 Minimum number of person 1 Subtask elapsed time 14.00 Skills AIRFRAME Material necessary to do the job Kit 531266D14R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 48 D5357072221890 1 CLIP 51 D5357113331290 1 ANGLE 53 D5357113335400 1 FILLER 54 D5357113321490 1 ANGLE 56 D5357113321090 1 ANGLE 58 D5357113320890 1 ANGLE 60 D5357113336090 1 WEB 62 D5357113330690 1 WEB 64 D5357113327090 1 ANGLE 66 D5357113326490 1 CLIP 68 D5357113325890 1 WEB 70 D5357113326890 1 ANGLE 72 D5357113326290 1 CLIP 74 D5357113326690 1 ANGLE 76 D5357113326090 1 CLIP 78 D5357113327290 1 ANGLE 80 D5357072423490 1 ANGLE 82 D5357072422090 1 CLIP 84 D5357113325690 1 WEB 86 D5357072423890 1 ANGLE 88 D5357072423290 1 ANGLE 90 D5357072423690 1 ANGLE 92 D5357072422290 1 CLIP 94 D5357072423090 1 ANGLE 96 D5357072422690 1 WEB 98 D5357072422490 1 CLIP 100 D5357072421890 1 WEB 102 DAN5-6-4X 21 PIN 103 DAN11-6X 101 COLLAR 104 DAN5-6-5X 4 PIN 105 DAN5-6-6X 5 PIN 108 NSA5075-6 52 COLLAR 109 DAN5-5-6 17 PIN 111 DAN5-5-5 8 PIN 112 DAN5-6-6 24 PIN 114 DAN5-8-5X 25 PIN DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 229 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 115 DAN11-8X 56 COLLAR 116 DAN5-8-4X 2 PIN 117 DAN5-8-7X 10 PIN 118 DAN5-8-8X 2 PIN 120 DAN6-6-4X 27 PIN 121 DAN6-6-5X 15 PIN 123 DAN6-8-6X 8 PIN 125 DAN6-6-7X 13 PIN 126 DAN6-6-6 6 PIN 127 DAN6-6-5 3 PIN 130 DAN5-6-7X 4 PIN 131 DAN5-8-6X 9 PIN 132 DAN6-6-6X 8 PIN 134 DAN6-6-7 19 PIN 135 EN6081D5-07 26 RIVET 137 EN6069D5-08 60 RIVET 144 DAN7-6-11X 1 PIN 145 DAN12-6X 1 COLLAR 146 DAN5-6-10X 2 PIN 148 DAN5-6-8X 2 PIN 160 NSA5075-5 25 COLLAR Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant, Brush Consistency 09-013 As required Corrosion Preventative Compound, Temporary 15-009 As required Anti-Corrosion Primer Polyurethane 16-001 As required Polyurethane Finish Paint 16-018 As required References Consumable Material List (CML) Fig. A-GBCAD Removal/Installation of Angles, Webs, Brackets and Clips at FR74 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-GBDAD Fastener Symbol Identification Sheet 01

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 230 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (a) Install the items between STGR2 on the RH Side and STGR2 on the LH Side, refer to Fig. A-GBCAD Sheet 03, Fig. A-GBCAD Sheet 04 and Fig. A-GBDAD Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Web D5357072421890 Item 100 with: 10 Pin DAN5-8-7X Item 117 10 Collar DAN11-8X Item 115 and then install: 1 Clip D5357072221890 Item 48 with: 2 PIN DAN5-8-8X Item 118 2 Collar DAN11-8X Item 115 2 As shown in Section B-B, at STGR1, install: 2 Rivet EN6081D5-07 Item 135 3 As shown in View J, install: 8 Pin DAN6-8-6X Item 123 8 Collar DAN11-8X Item 115 8 Rivet EN6069D5-08 Item 137 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 115,, 117, 118, 123, 135 and 137.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 231 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 115, 117, 118, 123, 135 and 137. (b) Install the items between STGR3 and STGR5 on the LH Side, refer to Fig. AGBCAD Sheet 03, Fig. A-GBCAD Sheet 04 and Fig. A-GBDAD Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Angle D5357072423090 Item 94 1 Angle D5357072423290 Item 88 1 Clip D5357072422490 Item 98 1 Web D5357072422690 Item 96 with: 3 Pin DAN5-8-6X Item 131 5 Collar DAN11-8X Item 115 2 Pin DAN5-5-6 Item 109 2 Collar NSA5075-5 Item 160 2 Pin DAN5-8-4X Item 116 and install: 1 Clip D5357072422290 Item 92 with: 6 Pin DAN5-8-5X Item 114 6 Collar DAN11-8X Item 115 and install: 1 Angle D5357072423690 Item 90 with: DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 232 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 160 2 As shown in Section B-B, at STGR4, install: 2 Rivet EN6081D5-07 Item 135 3 As shown in Section B-B, at STGR5, install: 2 Rivet EN6081D5-07 Item 135 4 As shown in View H, install: 8 Pin DAN6-6-6X Item 132 17 Collar DAN11-6X Item 103 9 Pin DAN6-6-7X Item 125 14 Rivet EN6069D5-08 Item 137 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 103, 109, 110, 114, 115, 116, 125, 131 and 132. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 103, 109, 110, 114, 115, 116, 125, 131, 132, 135 and 137. (c) Install the items between STGR5 and STGR7 on the LH Side, refer to Fig. AGBCAD Sheet 03, Fig. A-GBCAD Sheet 04 and Fig. A-GBDAD Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 233 6

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# @A318/A319/A320/A321 SERVICE BULLETIN 1 Angle D5357072423490 Item 80 1 Angle D5357113326690 Item 74 NOTE : Item 80 and Item 74 are temporally held in place. Then between STGR5 and STGR7 install: 1 Web D5357113325690 Item 84 with: 10 Pin DAN5-6-4X Item 102 10 Collar DAN11-6X Item 103 and then between Stringer STGR5 and STGR6 install: 1 Clip D5357072422090 Item 82 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 5 Pin DAN5-8-5X Item 114 5 Collar DAN11-8X Item 115 and then between Stringer STGR5 and STGR6 install: 1 Angle D5357072423890 Item 86 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 160 and then between Stringer STGR6 and STGR7 install: 1 Clip D5357113326090 Item 76 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 5 Pin DAN5-8-5X Item 114 5 Collar DAN11-8X Item 115
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 234 6

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# @A318/A319/A320/A321 SERVICE BULLETIN and then between Stringer STGR6 and STGR7 install: 1 Angle D5357113327290 Item 78 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 160 2 As shown in Section B-B at STGR6, install: 2 Rivet EN6081D5-07 Item 135 3 As shown in Section B-B, at STGR7, install: 2 Rivet EN6081D5-07 Item 135 4 As shown in View H, install between STGR5 and STGR7 19 Pin DAN6-6-7 Item 134 26 Collar NSA5075-6 Item 108 6 Pin DAN6-6-6 Item 126 8 Rivet EN6069D5-08 Item 137 4 Pin DAN6-6-5X Item 121 4 Collar DAN11-6X Item 103 1 Pin DAN6-6-5 Item 127 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 109, 114, 115, 121, 126, 127, 132, 134 and 160. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 235 6

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# @A318/A319/A320/A321 SERVICE BULLETIN to the fasteners, Items 102, 103, 104, 109, 114, 115, 121, 125, 126, 127, 132, 134, 135, 137 and 160. (d) Install the items between Stringer STGR7 and STGR9 on the LH Side, refer to Fig. A-GBCAD Sheet 03, Fig. A-GBCAD Sheet 04 and Fig. A-GBDAD Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Angle D5357113326890 Item 70 1 Angle D5357113327090 Item 64 NOTE : Item 70 and Item 64 are temporally held in place. Then between STGR7 and STGR9 install: 1 Web D5357113325890 Item 68 with: 8 Pin DAN5-6-4X Item 102 8 Collar DAN11-6X Item 103 and install: 1 Clip D5357113326290 Item 72 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 4 Pin DAN5-8-5X Item 114 4 Collar DAN11-8X Item 115 4 Pin DAN5-5-5 Item 111 4 Collar NSA5075-5 Item 160 and install: 1 Clip D5357113326490 Item 66 with: 1 Pin DAN5-6-5X Item 104 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 236 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
1 Collar DAN11-6X Item 103 5 Pin DAN5-8-5X Item 114 5 Collar DAN11-8X Item 115 4 Pin DAN5-5-5 Item 111 4 Collar NSA5075-5 Item 160 2 As shown in Section B-B, at STGR8, install: 2 Rivet EN6081D5-07 Item 135 3 As shown in Section B-B, at STGR9, install: 2 Rivet EN6081D5-07 Item 135 4 As shown in View K, install: 8 Pin DAN6-6-5X Item 121 17 Collar DAN11-6X Item 103 9 Pin DAN6-6-4X Item 120 14 Rivet EN6069D5-08 Item 137 2 Pin DAN6-6-5 Item 127 2 Collar NSA5075-6 Item 108 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 111, 114, 115, 120, 121, 127 and 160. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 108, 111, 114, 115, 120, 121, 127, 135, 137 and 160. DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 237 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (e) Install the items between Stringer STGR9 and STGR12 on the LH Side, refer to Fig. A-GBCAD Sheet 03, Fig. A-GBCAD Sheet 04 and Fig. A-GBDAD Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Web D5357113330690 Item 62 with: 3 Pin DAN5-6-4X Item 102 3 Collar DAN11-6X Item 103 and install: 1 Angle D5357113331290 Item 51 1 Filler D5357113335400 Item 53 1 Angle D5357113321490 Item 54 with: 24 Pin DAN5-6-6 Item 112 24 Collar NSA5075-6 Item 108 and install: 1 Web D5357113336090 Item 60 with: 6 Pin DAN5-8-6X Item 131 6 Collar DAN11-8X Item 115 8 Rivet EN6081D5-07 Item 135 5 Pin DAN5-6-6X Item 105 5 Collar DAN11-6X Item 103 and install: 1 Angle D5357113320890 Item 58 1 Angle D5357113321090 Item 56
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 238 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
with: 4 Pin DAN5-6-7X Item 130 4 Collar DAN11-6X Item 103 2 As shown in Section B-B, at STGR10, install: 2 Rivet EN6081D5-07 Item 135 3 As shown in Section B-B, at STGR11, install: 2 Rivet EN6081D5-07 Item 135 4 As shown in View K, install: 18 Pin DAN6-6-4X Item 120 25 Collar DAN11-6X Item 103 16 Rivet EN6069D5-08 Item 137 3 Pin DAN6-6-5X Item 121 4 Pin DAN6-6-7X Item 125 5 As shown in View L, install: 1 Pin DAN7-6-11X Item 144 1 Collar DAN12-6X Item 145 2 Pin DAN5-6-10X Item 146 2 Pin DAN5-6-8X Item 148 4 Collar DAN11-6X Item 103 6 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 105, 108, 112, 115, 120, 121, 122, 125, 130 and 131.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 239 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
7 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 105, 108, 112, 115, 120, 121, 122, 124, 125, 130, 131, 135 and 137. (7) Subtask 531266-020-204-003 - Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, RH and STGR3, RH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 74 from Stringer 12 RH to Stringer 3 RH Manpower Resources Manhours 11.00 Minimum number of person 1 Subtask elapsed time 11.00 Skills AIRFRAME NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) Task 51-10-01-250-801 51-10-08 Fig. A-GBAAA Location of Inspection Area for Clips at FR72/FR74 Sheet 01 Fig. A-GBCAD Removal/Installation of Angles, Webs, Brackets and Clips at FR74 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Remove the items between STGR12 and STGR9 RH, refer to Fig. A-GBCAD Sheet 01 and Fig. A-GBCAD Sheet 02

. 1 As shown in Section A-A, remove: 2 Rivet Discard from the angle at STGR11 (Section A-A) and 2 Rivet Discard from the angle at STGR10 (Section A-A). Remove:
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 240 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
42 Pin-Rivet Discard 42 Collar Discard 8 Rivet Discard from View B. 2 As shown in View E, remove: 25 Pin-Rivet Discard 25 Collar Discard 16 Rivet Discard 3 Remove: 1 Angle D5357113331300 Item (52) Discard 1 Filler D5357113335400 Item (53) Discard 1 Angle D5357113321500 Item (55) Discard 1 Angle D5357113321100 Item (57) Discard 1 Angle D5357113320900 Item (59) Discard 1 Web D5357113336100 Item (61) Discard 1 Web D5357113330700 Item (63) Discard 4 As shown in View F, remove: 5 Pin-Rivet Discard 5 Collar Discard 5 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow.
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 241 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (b) Remove the items between STGR9 and STGR7 RH, refer to Fig. A-GBCAD Sheet 01 and Fig. A-GBCAD Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STRG9 (Section A-A) and 2 Rivet Discard from the angle at STRG8 (Section A-A). Remove: 27 Pin-Rivet Discard 27 Collar Discard from View B. 2 As shown in View E, remove: 19 Pin-Rivet Discard 19 Collar Discard 14 Rivet Discard 3 Remove: 1 Angle D5357113327100 Item (65) Discard 1 Clip D5357113326500 Item (67) Discard 1 Web D5357113325900 Item (69) Discard 1 Angle D5357113326900 Item (71) Discard 1 Clip D5357113326300 Item (73) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 242 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN - If no cracks are found, do the worksteps that follow. (c) Remove the items between STGR7 and STGR5, refer to Fig. A-GBCAD Sheet 01

. 1 Remove: 2 Rivet Discard from the angle at STRG7 (Section A-A) and 2 Rivet Discard from the angle at STRG6 (Section A-A). Remove: 32 Pin-Rivet Discard 32 Collar Discard from View B. 2 As shown in View C, remove: 30 Pin-Rivet Discard 30 Collar Discard 8 Rivet Discard 3 Remove: 1 Angle D5357113326700 Item (75) Discard 1 Clip D5357113326100 Item (77) Discard 1 Angle D5357113327300 Item (79) Discard 1 Angle D5357072423500 Item (81) Discard 1 Clip D5357072422100 Item (83) Discard 1 Web D5357113325700 Item (85) Discard 1 Angle D5357072423900 Item (87) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 243 6

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# @A318/A319/A320/A321 SERVICE BULLETIN

c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (d) Remove the items between STGR5 and STGR3, refer to Fig. A-GBCAD Sheet 01

. 1 Remove: 2 Rivet Discard from the angle at STRG5 (Section A-A) and 2 Rivet Discard from the angle at STRG4 (Section A-A). Remove: 18 Pin-Rivet Discard 18 Collar Discard from View B. 2 As shown in View C, remove: 17 Pin-Rivet Discard 17 Collar Discard 14 Rivet Discard 3 Remove: 1 Angle D5357072423300 Item (89) Discard 1 Angle D5357072423700 Item (91) Discard 1 Clip D5357072422300 Item (93) Discard 1 Angle D5357072423100 Item (95) Discard 1 Web D5357072422700 Item (97) Discard 1 Clip D5357072422500 Item (99) Discard 4 Inspection: a Do a rotating probe testing of the fastener holes, refer to NTM Task 51-10-01-250-801.
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 244 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (8) Subtask 531266-420-204-003 - Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR3, RH and STGR12, RH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 74 from Stringer 3 RH to Stringer 12 RH Manpower Resources Manhours 12.00 Minimum number of person 1 Subtask elapsed time 12.00 Skills AIRFRAME Material necessary to do the job Kit 531266D14R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 52 D5357113331390 1 ANGLE 53 D5357113335400 1 FILLER 55 D5357113321590 1 ANGLE 57 D5357113321190 1 ANGLE 59 D5357113320990 1 ANGLE 61 D5357113336190 1 WEB 63 D5357113330790 1 WEB 65 D5357113327190 1 ANGLE 67 D5357113326590 1 CLIP 69 D5357113325990 1 WEB 71 D5357113326990 1 ANGLE 73 D5357113326390 1 CLIP 75 D5357113326790 1 ANGLE 77 D5357113326190 1 CLIP 79 D5357113327390 1 ANGLE 81 D5357072423590 1 ANGLE 83 D5357072422190 1 CLIP 85 D5357113325790 1 WEB 87 D5357072423990 1 ANGLE 89 D5357072423390 1 ANGLE 91 D5357072423790 1 ANGLE DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 245 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 93 D5357072422390 1 CLIP 95 D5357072423190 1 ANGLE 97 D5357072422790 1 WEB 99 D5357072422590 1 CLIP 102 DAN5-6-4X 21 PIN 103 DAN11-6X 101 COLLAR 104 DAN5-6-5X 4 PIN 105 DAN5-6-6X 5 PIN 108 NSA5075-6 52 COLLAR 109 DAN5-5-6 17 PIN 111 DAN5-5-5 8 PIN 112 DAN5-6-6 24 PIN 114 DAN5-8-5X 25 PIN 115 DAN11-8X 36 COLLAR 116 DAN5-8-4X 2 PIN 120 DAN6-6-4X 27 PIN 121 DAN6-6-5X 15 PIN 125 DAN6-6-7X 13 PIN 126 DAN6-6-6 6 PIN 127 DAN6-6-5 3 PIN 130 DAN5-6-7X 4 PIN 131 DAN5-8-6X 9 PIN 132 DAN6-6-6X 8 PIN 134 DAN6-6-7 19 PIN 135 EN6081D5-07 20 RIVET 137 EN6069D5-08 52 RIVET 144 DAN7-6-11X 1 PIN 145 DAN12-6X 1 COLLAR 146 DAN5-6-10X 2 PIN 148 DAN5-6-8X 2 PIN 160 NSA5075-5 25 COLLAR Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant, Brush Consistency 09-013 As required Corrosion Preventative Compound, Temporary 15-009 As required Anti-Corrosion Primer Polyurethane 16-001 As required Polyurethane Finish Paint 16-018 As required References Consumable Material List (CML)

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 246 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
References Fig. A-GBCAD Removal/Installation of Angles, Webs, Brackets and Clips at FR74 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-GBDAD Fastener Symbol Identification Sheet 01 (a) Install the items between STGR3 and STGR5 on the RH Side, refer to Fig. AGBCAD Sheet 03, Fig. A-GBCAD Sheet 04 and Fig. A-GBDAD Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Angle D5357072423190 Item 95 1 Angle D5357072423390 Item 89 1 Clip D5357072422590 Item 99 1 Web D5357072422790 Item 97 with: 3 Pin DAN5-8-6X Item 131 5 Collar DAN11-8X Item 115 2 Pin DAN5-5-6 Item 109 2 Collar NSA5075-5 Item 160 2 Pin DAN5-8-4X Item 116 and install: 1 Clip D5357072422390 Item 93 with: 6 Pin DAN5-8-5X Item 114 6 Collar DAN11-8X Item 115 and install: 1 Angle D5357072423790 Item 91 with: DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 247 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 160 2 As shown in Section B-B, at STGR4, install: 2 Rivet EN6081D5-07 Item 135 3 As shown in Section B-B, at STGR5, install: 2 Rivet EN6081D5-07 Item 135 4 As shown in View H, install: 8 Pin DAN6-6-6X Item 132 17 Collar DAN11-6X Item 103 9 Pin DAN6-6-7X Item 125 14 Rivet EN6069D5-08 Item 137 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 103, 109, 114, 115, 116, 122, 124, 131, 132 and 160. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 103, 109, 114, 115, 116, 122, 124, 131, 132 and 160. (b) Install the items between STGR5 and STGR7 on the RH Side, refer to Fig. AGBCAD Sheet 03, Fig. A-GBCAD Sheet 04 and Fig. A-GBDAD Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Angle D5357072423590 Item 81
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 248 6

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# @A318/A319/A320/A321 SERVICE BULLETIN 1 Angle D5357113326790 Item 75 NOTE : Item 81 and Item 75 are temporally held in place. Then between STGR5 and STGR7 install: 1 Web D5357113325790 Item 85 with: 10 Pin DAN5-6-4X Item 102 10 Collar DAN11-6X Item 103 and between Stringer STGR5 and STGR6 install: 1 Clip D5357072422190 Item 83 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 5 Pin DAN5-8-5X Item 114 5 Collar DAN11-8X Item 115 and between Stringer STGR5 and STGR6 install: 1 Angle D5357072423990 Item 87 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 160 and between Stringer STGR6 and STGR7 install: 1 Clip D5357113326190 Item 77 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 5 Pin DAN5-8-5X Item 114 5 Collar DAN11-8X Item 115 and between Stringer STGR6 and STGR7 install:
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 249 6

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# @A318/A319/A320/A321 SERVICE BULLETIN 1 Angle D5357113327390 Item 79 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 160 2 As shown in Section B-B, at STGR6, install: 2 Rivet EN6081D5-07 Item 135 3 As shown in Section B-B, at STGR7, install: 2 Rivet EN6081D5-07 Item 135 4 As shown in View H, install between STGR5 and STGR7 19 Pin DAN6-6-7 Item 134 26 Collar NSA5075-6 Item 108 6 Pin DAN6-6-6 Item 126 8 Rivet EN6069D5-08 Item 137 4 Pin DAN6-6-5X Item 121 4 Collar DAN11-6X Item 103 1 Pin DAN6-6-5 Item 127 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 109, 114, 115, 122, 134, 126, 127 and 160. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 108, 109, 114, 115, 134, 126, 127 and 160. DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 250 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (c) Install the items between Stringer STGR7 and STGR9 on the RH Side, refer to Fig. A-GBCAD Sheet 03, Fig. A-GBCAD Sheet 04 and Fig. A-GBDAD Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Angle D5357113326990 Item 71 1 Angle D5357113327190 Item 65 NOTE : Item 71 and Item 64 are temporally held in place. Then between STGR7 and STGR9 install: 1 Web D5357113325990 Item 69 with: 8 Pin DAN5-6-4X Item 102 8 Collar DAN11-6X Item 103 and install: 1 Clip D5357113326390 Item 73 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 4 Pin DAN5-8-5X Item 114 4 Collar DAN11-8X Item 115 4 Pin DAN5-5-5 Item 111 4 Collar NSA5075-5 Item 160 and install: 1 Clip D5357113326590 Item 67 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 251 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
5 Pin DAN5-8-5X Item 114 5 Collar DAN11-8X Item 115 4 Pin DAN5-5-5 Item 111 4 Collar NSA5075-5 Item 160 2 As shown in Section B-B, at STGR8, install: 1 Rivet EN6081D5-07 Item 135 3 As shown in Section B-B, at STGR9, install: 1 Rivet EN6081D5-07 Item 135 4 As shown in View K, install: 8 Pin DAN6-6-5X Item 121 17 Collar DAN11-6X Item 103 9 Pin DAN6-6-4X Item 120 2 Collar NSA5075-6 Item 108 14 Rivet EN6069D5-08 Item 137 2 Pin DAN6-6-5 Item 127 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 111, 114, 115, 120, 121, 127 and 160. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 108, 111, 114, 115, 120, 121, 122, 127, 135, 137 and 160.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 252 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (d) Install the items between STGR9 and STGR12 on the RH Side, refer to Fig. AGBCAD Sheet 03, Fig. A-GBCAD Sheet 04 and Fig. A-GBDAD Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Web D5357113330790 Item 63 with: 3 Pin DAN5-6-4X Item 102 3 Collar DAN11-6X Item 103 and install: 1 Angle D5357113331390 Item 52 1 Filler D5357113335400 Item 53 1 Angle D5357113321590 Item 55 with: 24 Pin DAN5-6-6 Item 112 24 Collar NSA5075-6 Item 108 and install: 1 Web D5357113336190 Item 61 with: 6 Pin DAN5-8-6X Item 131 6 Collar DAN11-8X Item 115 8 Rivet EN6081D5-07 Item 135 5 Pin DAN5-6-6X Item 105 5 Collar DAN11-6X Item 103 and install: 1 Angle D5357113320990 Item 59 1 Angle D5357113321190 Item 57
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 253 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
with: 4 Pin DAN5-6-7X Item 130 4 Collar DAN11-6X Item 103 2 As shown in Section B-B, at STGR10, install: 1 Rivet EN6081D5-07 Item 135 3 As shown in Section B-B, at STGR11, install: 1 Rivet EN6081D5-07 Item 135 4 As shown in View K, install: 18 Pin DAN6-6-4X Item 120 25 Collar DAN11-6X Item 103 16 Rivet EN6069D5-08 Item 137 3 Pin DAN6-6-5X Item 121 4 Pin DAN6-6-7X Item 125 5 As shown in View L, install: 1 Pin DAN7-6-11X Item 144 1 Collar DAN12-6X Item 145 2 Pin DAN5-6-10X Item 146 2 Pin DAN5-6-8X Item 148 4 Collar DAN11-6X Item 103 6 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 105, 108, 112, 115, 120, 121, 124, 130 and 131.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 254 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
7 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 105, 108, 112, 115, 120, 121, 122, 125, 130, 131 and 135. **CONF 004 (1) Subtask 531266-020-201-004 - Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, LH and STGR1, RH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 72 from Stringer 13 LH to Stringer 1 RH Manpower Resources Manhours 13.00 Minimum number of person 1 Subtask elapsed time 13.00 Skills AIRFRAME NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) Task 51-10-01-250-801 51-10-08 Fig. A-GBAAA Location of Inspection Area for Clips at FR72/FR74 Sheet 01 Fig. A-GBBAE Removal/Installation of Angles, Webs, Brackets and Clips at FR72 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Remove the items between STGR13 and STGR11 LH, refer to Fig. A-GBBAE Sheet 01 and Fig. A-GBBAE Sheet 02

. 1 As shown in View B, remove: 26 Pin-Rivet Discard 26 Collar Discard 6 Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 255 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
2 As shown in Section B-B, remove: 2 Pin-Rivet Discard 2 Collar Discard 3 As shown in View D, remove: 16 Pin-Rivet Discard 16 Collar Discard 4 Remove: 1 Angle D5357113140000 Item (1 ) Discard 1 Web D5357113146800 Item (3) Discard 1 Web D5357113143800 Item (5) Discard 1 Bracket-Z D9357073720000 Item (133) Retain 5 Inspection: a Do a rotating probe test of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found, contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (b) Remove the items between STGR11 and STGR9 LH, refer to Fig. A-GBBAE Sheet 01 and Fig. A-GBBAE Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR11 (Section A-A) and 2 Rivet Discard from the angle at STGR10 (Section A-A). 2 Remove: 23 Pin-Rivet Discard
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 256 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
23 Collar Discard 11 Rivet Discard from View B. 3 As shown in View F, remove: 19 Pin-Rivet Discard 19 Collar Discard 16 Rivet Discard 4 Remove: 1 Clip D5357113144000 Item (7) Discard 1 Clip D5357113146600 Item (9) Discard 1 Web D5357113143600 Item (11 ) Discard 1 Bracket-Z D9357073720000 Item (133) Retain 5 Inspection: a Do a rotating probe test of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found, contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (c) Remove the items between STGR9 and STGR7 LH, refer to Fig. A-GBBAE Sheet 01 and Fig. A-GBBAE Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR9 (Section A-A) and 2 Rivet Discard from the angle at STGR8 (Section A-A).

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 257 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
2 Remove: 31 Pin-Rivet Discard 31 Collar Discard from View B. 3 As shown in View F, remove: 21 Pin-Rivet Discard 21 Collar Discard 14 Rivet Discard 4 Remove: 1 Angle D5357113145600 Item (13) Discard 1 Clip D5357113145000 Item (15) Discard 1 Angle D5357113145400 Item (17) Discard 1 Clip D5357113144800 Item (19) Discard 1 Web D5357113144600 Item (21 ) Discard 5 Inspection: a Do a rotating probe test of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found, contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (d) Remove the items between STGR7 and STGR5 LH, refer to Fig. A-GBBAE Sheet 01 and Fig. A-GBBAE Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR7 (Section A-A) and 2 Rivet Discard DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 258 6

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# @A318/A319/A320/A321 SERVICE BULLETIN from the angle at STGR6 (Section A-A). 2 Remove: 33 Pin-Rivet Discard 33 Collar Discard 2 Rivet Discard from View B. 3 As shown in View F, remove: 28 Pin-Rivet Discard 28 Collar Discard 10 Rivet Discard 4 Remove: 1 Angle D5357113145200 Item (23) Discard 1 Angle D5357113145800 Item (25) Discard 1 Clip D5357113144400 Item (27) Discard 1 Angle D5357072225600 Item (29) Discard 1 Clip D5357072224400 Item (31 ) Discard 1 Angle D5357072226000 Item (33) Discard 1 Web D5357113144200 Item (35) Discard 1 Bracket-Z D9357073720000 Item (133) Retain 5 Inspection: a Do a rotating probe test of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found, contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 259 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (e) Remove the items between STGR5 and STGR3 LH, refer to Fig. A-GBBAE Sheet 01 and Fig. A-GBBAE Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR5 (Section A-A) and 2 Rivet Discard from the angle at STGR4 (Section A-A). 2 Remove: 20 Pin-Rivet Discard 20 Collar Discard from View B. 3 As shown in View F, remove: 19 Pin-Rivet Discard 19 Collar Discard 14 Rivet Discard 4 Remove: 1 Angle D5357072225400 Item (36) Discard 1 Angle D5357072225800 Item (38) Discard 1 Clip D5357072224600 Item (40) Discard 1 Angle D5357072225200 Item (42) Discard 1 Web D5357072224800 Item (44) Discard 1 Clip D5357072225000 Item (46) Discard 5 Inspection: a Do a rotating probe test of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 260 6

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# @A318/A319/A320/A321 SERVICE BULLETIN

c Findings: - If cracks are found, contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (f) Remove the items at STGR1 RH and LH, refer to Fig. A-GBBAE Sheet 01 and Fig. A-GBBAE Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR1 (Section A-A). 2 Remove: 10 Pin-Rivet Discard 10 Nut Discard 3 As shown in View E, remove: 7 Pin-Rivet Discard 7 Collar Discard 8 Rivet Discard 4 Remove: 1 Clip D5357072224200 Item (48) Discard 1 Web D5357072224000 Item (49) Discard 5 Inspection: a Do a rotating probe test of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found, contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 261 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (2) Subtask 531266-420-201-004 - Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR1, RH and STGR13, LH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 72 from Stringer 1 RH to Stringer 13 LH Manpower Resources Manhours 16.00 Minimum number of person 1 Subtask elapsed time 16.00 Skills AIRFRAME Material necessary to do the job Kit 531266D11R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 D5357113140090 1 ANGLE 3 D5357113146890 1 WEB 5 D5357113143890 1 WEB 7 D5357113144090 1 CLIP 9 D5357113146690 1 CLIP 11 D5357113143690 1 WEB 13 D5357113145690 1 ANGLE 15 D5357113145090 1 CLIP 17 D5357113145490 1 ANGLE 19 D5357113144890 1 CLIP 21 D5357113144690 1 WEB 23 D5357113145290 1 ANGLE 25 D5357113145890 1 ANGLE 27 D5357113144490 1 CLIP 29 D5357072225690 1 ANGLE 31 D5357072224490 1 CLIP 33 D5357072226090 1 ANGLE 35 D5357113144290 1 WEB 36 D5357072225490 1 ANGLE 38 D5357072225890 1 ANGLE 40 D5357072224690 1 CLIP 42 D5357072225290 1 ANGLE 44 D5357072224890 1 WEB 46 D5357072225090 1 CLIP 48 D5357072224290 1 CLIP 49 D5357072224090 1 WEB 102 DAN5-6-4X 31 PIN 103 DAN11-6X 145 COLLAR 104 DAN5-6-5X 40 PIN DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 262 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 105 DAN5-6-6X 2 PIN 106 EN6081D5-06 33 RIVET 107 DAN5-6-5 16 PIN 108 NSA5075-6 56 COLLAR 109 DAN5-5-6 18 PIN 110 NSA5075-5 27 COLLAR 111 DAN5-5-5 9 PIN 112 DAN5-6-6 2 PIN 113 DAN5-6-3X 3 PIN 114 DAN5-8-5X 10 PIN 115 DAN11-8X 29 COLLAR 116 DAN5-8-4X 2 PIN 117 DAN5-8-7X 8 PIN 118 DAN5-8-8X 2 PIN 119 DAN6-6-3X 8 PIN 120 DAN6-6-4X 29 PIN 121 DAN6-6-5X 13 PIN 122 EN6069D5-06 12 RIVET 123 DAN6-8-6X 7 PIN 124 DAN6-6-7X 10 PIN 125 DAN6-6-7 19 PIN 126 DAN6-6-6 4 PIN 127 DAN6-6-5 3 PIN 128 DAN6-6-3 8 PIN 129 DAN5-6-3 4 PIN 132 DAN6-6-6X 9 PIN 135 EN6081D5-08 2 RIVET 136 EN6069D5-07 33 RIVET 137 EN6069D5-08 17 RIVET Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant, Brush Consistency 09-013 As required Corrosion Preventative Compound, Temporary 15-009 As required Anti-Corrosion Primer Polyurethane 16-001 As required Polyurethane Finish Paint 16-018 As required References Consumable Material List (CML) Fig. A-GBBAE Removal/Installation of Angles, Webs, Brackets and Clips at FR72 Sheet 01 Sheet 02 Sheet 03 Sheet 04 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 263 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
References Fig. A-GBDAE Fastener Symbol Identification Sheet 01 (a) Install the items between STGR1 LH and RH, refer to Fig. A-GBBAE Sheet 01 , View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04 and Fig. A-GBDAE Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Web D5357072224090 Item 49 with: 8 Pin DAN5-8-7X Item 117 8 Collar DAN11-8X Item 115 and then install: 1 Clip D5357072224290 Item 48 with: 2 PIN DAN5-8-8X Item 118 2 Collar DAN11-8X Item 115 2 As shown in Section E-E, install: 2 Pin DAN5-6-3 Item 129 2 Collar NSA5075-6 Item 108 3 As shown in View K, install: 7 Pin DAN6-8-6X Item 123 7 Collar DAN11-8X Item 115 5 Rivet EN6069D5-07 Item 136 3 Rivet EN6069D5-08 Item 137 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 264 6

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# @A318/A319/A320/A321 SERVICE BULLETIN Polyurethane Finish Paint 16-018 As required to the fasteners, Items 108, 115, 117, 118, 123 and 129. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 108, 115, 117, 118, 123, 129, 136 and 137. (b) Install the items between STGR3 and STGR4 on the LH side, refer to Fig. AGBBAE Sheet 01 , View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04 and Fig. A-GBDAE Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357072225290 Item 42 1 Clip D5357072225090 Item 46 with: 4 Pin DAN5-8-5X Item 114 4 Collar DAN11-8X Item 115 3 Pin DAN5-5-6 Item 109 3 Collar NSA5075-5 Item 110 2 As shown in Section C-C, at STGR4, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in View L, install between STGR3 and STGR4: 3 Pin DAN6-6-6X Item 132 4 Pin DAN6-6-7X Item 124 7 Collar DAN11-6X Item 103 7 Rivet EN6069D5-08 Item 137
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 265 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 103, 109, 110, 114, 115, 124 and 132. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items, 103, 106, 109, 110, 114, 115, 124, 132 and 137. (c) Install the items between STGR4 and STGR5 on the LH side, refer to Fig. AGBBAE Sheet 01 , View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04 and Fig. A-GBDAE Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357072225490 Item 36 1 Web D5357072224890 Item 44 with: 2 Pin DAN5-8-4X Item 116 2 Collar DAN11-8X Item 115 and then install: 1 Clip D5357072224690 Item 40 with: 6 Pin DAN5-8-5X Item 114 6 Collar DAN11-8X Item 115 and then install: 1 Angle D5357072225890 Item 38 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 266 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 110 2 As shown in Section C-C, at STGR5, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in View L, between STGR4 and STGR5, install: 6 Pin DAN6-6-6X Item 132 6 Pin DAN6-6-7X Item 124 12 Collar DAN11-6X Item 103 7 Rivet EN6069D5-08 Item 137 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 103, 109, 110, 114, 115, 116, 124 and 132. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 103, 106, 109, 110, 114, 115, 116, 124, 132 and 137. (d) Install the items between STGR5 and STGR7 on the LH side, refer to Fig. AGBBAE Sheet 01 , View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04 and Fig. A-GBDAE Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357072225690 Item 29

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 267 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
1 Angle D5357113145290 Item 23 1 Bracket-Z D9357073720000 Item (133) Retained at removal 1 Web D5357113144290 Item 35 with: 9 Pin DAN5-6-4X Item 102 9 Collar DAN11-6X Item 103 2 Rivet EN6081D5-08 Item 135 and then between STGR5 and STGR6, install: 1 Clip D5357072224490 Item 31 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 and then between STGR5 and STGR6, install: 1 Angle D5357072226090 Item 33 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 110 and then between STGR6 and STGR7, install: 1 Clip D5357113144490 Item 27 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 and then between STGR6 and STGR7, install: 1 Angle D5357113145890 Item 25 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 110 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 268 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
2 As shown in Section C-C, at STGR6, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section C-C, at STGR7, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View L, between STGR5 and STGR7, install: 19 Pin DAN6-6-7 Item 125 4 Pin DAN6-6-6 Item 126 1 Pin DAN6-6-5 Item 127 24 Collar NSA5075-6 Item 108 4 Pin DAN6-6-5X Item 121 4 Collar DAN11-6X Item 103 9 Rivet EN6069D5-07 Item 136 1 Rivet EN6069D5-06 Item 122 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 109, 110, 121, 125, 126 and 127. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 109, 110, 121, 122, 125, 126, 127, 135 and 136.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 269 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (e) Install the items between STGR7 and STGR9 on the LH side, refer to Fig. AGBBAE Sheet 01 , View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04 and Fig. A-GBDAE Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357113145690 Item 13 1 Angle D5357113145490 Item 17 NOTE : Items 13 and 17 are temporarily held in place. Then between STGR7 and STGR9, install: 1 Web D5357113144690 Item 21 with: 10 Pin DAN5-6-4X Item 102 10 Collar DAN11-6X Item 103 and then between STGR7 and STGR8, install: 1 Clip D5357113144890 Item 19 with: 5 Pin DAN5-6-5X Item 104 5 Collar DAN11-6X Item 103 4 Pin DAN5-5-5 Item 111 4 Collar NSA5075-5 Item 110 and then between STGR8 and STGR9, install: 1 Clip D5357113145090 Item 15 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 5 Pin DAN5-5-5 Item 111 5 Collar NSA5075-5 Item 110 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 270 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
2 As shown in Section C-C, at STGR8, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section C-C, at STGR9, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View L, between STGR7 and STGR9, install: 10 Pin DAN6-6-4X Item 120 9 Pin DAN6-6-5X Item 121 19 Collar DAN11-6X Item 103 12 Rivet EN6069D5-07 Item 136 2 Rivet EN6069D5-06 Item 122 2 Pin DAN6-6-5 Item 127 2 Collar NSA5075-6 Item 108 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 110, 111, 120, 121 and 127. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 110, 111, 120, 121, 122, 127 and 136. (f) Install the items between STGR9 and STGR11 on the LH side, refer to Fig. AGBBAE Sheet 01 , View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04 and Fig. A-GBDAE Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 271 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN to wet install on Frame 72, as shown in View G: 1 Bracket-Z D9357073720000 Item (133) Retained at removal 1 Web D5357113143690 Item 11 with: 2 Rivet EN6081D5-06 Item 106 9 Pin DAN5-6-4X Item 102 9 Collar DAN11-6X Item 103 and then between STGR9 and STGR10, install: 1 Clip D5357113146690 Item 9 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 5 Rivet EN6081D5-06 Item 106 and then between STGR10 and STGR11, install: 1 Clip D5357113144090 Item 7 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 4 Rivet EN6081D5-06 Item 106 2 As shown in Section C-C, at STGR10, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section C-C, at STGR11, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View L, between STGR9 and STGR11, install: 19 Pin DAN6-6-4X Item 120 19 Collar DAN11-6X Item 103 7 Rivet EN6069D5-07 Item 136 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 272 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
9 Rivet EN6069D5-06 Item 122 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104 and 120. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 106, 120, 122 and 136. (g) Install the items between STGR11 and STGR13 on the LH side, refer to Fig. AGBBAE Sheet 01 , View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04 and Fig. A-GBDAE Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Bracket-Z D9357073720000 Item (133) Retained at removal 1 Web D5357113143890 Item 5 with: 2 Rivet EN6081D5-06 Item 106 3 Pin DAN5-6-3X Item 113 3 Collar DAN11-6X Item 103 and then between STGR11 and STGR12, install: 1 Web D5357113146890 Item 3 with: 3 Pin DAN5-6-4X Item 102
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 273 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
3 Collar DAN11-6X Item 103 4 Rivet EN6081D5-06 Item 106 and then install: 1 Angle D5357113140090 Item 1 with: 16 Pin DAN5-6-5 Item 107 2 Pin DAN5-6-6 Item 112 18 Collar NSA5075-6 Item 108 2 Pin DAN5-6-6X Item 105 2 Collar DAN11-6X Item 103 2 As shown in Section D-D, at STGR12, install: 2 Pin DAN5-6-3 Item 129 2 Collar NSA5075-6 Item 108 3 As shown in View J, install: 8 Pin DAN6-6-3X Item 119 8 Collar DAN11-6X Item 103 8 Pin DAN6-6-3 Item 128 8 Collar NSA5075-6 Item 108 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 105, 107, 108, 112, 113, 119, 128 and 129. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 274 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN to the fasteners, Items 102, 103, 105, 106, 107, 108, 112, 113, 119, 128 and 129. (3) Subtask 531266-020-208-004 - Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, RH and STGR3, RH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 72 from Stringer 13 LH to Stringer 1 RH Manpower Resources Manhours 11.00 Minimum number of person 1 Subtask elapsed time 11.00 Skills AIRFRAME NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) Task 51-10-01-250-801 51-10-08 Fig. A-GBAAA Location of Inspection Area for Clips at FR72/FR74 Sheet 01 Fig. A-GBBAE Removal/Installation of Angles, Webs, Brackets and Clips at FR72 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Remove the items between STGR13 and STGR11 RH, refer to Fig. A-GBBAE Sheet 01 and Fig. A-GBBAE Sheet 02

. 1 As shown in View B, remove: 26 Pin-Rivet Discard 26 Collar Discard 6 Rivet Discard 2 As shown in Section B-B, remove: 2 Pin-Rivet Discard 2 Collar Discard 3 As shown in View D, remove: 16 Pin-Rivet Discard 16 Collar Discard DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 275 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
4 Remove: 1 Angle D5357113140100 Item (2) Discard 1 Web D5357113146900 Item (4) Discard 1 Web D5357113143900 Item (6) Discard 1 Bracket-Z D9357073720000 Item (133) Retain 5 Inspection: a Do a rotating probe test of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found, contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (b) Remove the items between STGR11 and STGR9 RH, refer to Fig. A-GBBAE Sheet 01 and Fig. A-GBBAE Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR11 (Section A-A) and 2 Rivet Discard from the angle at STGR10 (Section A-A). 2 Remove: 23 Pin-Rivet Discard 23 Collar Discard 11 Rivet Discard from View B. 3 As shown in View F, remove: 19 Pin-Rivet Discard 19 Collar Discard
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 276 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
16 Rivet Discard 4 Remove: 1 Clip D5357113144100 Item (8) Discard 1 Clip D5357113146700 Item (10) Discard 1 Web D5357113143700 Item (12) Discard 1 Bracket-Z D9357073720000 Item (133) Retain 5 Inspection: a Do a rotating probe test of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection of the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found, contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (c) Remove the items between STGR9 and STGR7 RH, refer to Fig. A-GBBAE Sheet 01 and Fig. A-GBBAE Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR9 (Section A-A) and 2 Rivet Discard from the angle at STGR8 (Section A-A). 2 Remove: 31 Pin-Rivet Discard 31 Collar Discard from View B. 3 As shown in View F, remove: 21 Pin-Rivet Discard 21 Collar Discard
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 277 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
14 Rivet Discard 4 Remove: 1 Angle D5357113145700 Item (14) Discard 1 Clip D5357113145100 Item (16) Discard 1 Angle D5357113145500 Item (18) Discard 1 Clip D5357113144900 Item (20) Discard 1 Web D5357113144700 Item (22) Discard 5 Inspection: a Do a rotating probe test of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found, contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (d) Remove the items between STGR7 and STGR5 RH, refer to Fig. A-GBBAE Sheet 01 and Fig. A-GBBAE Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR7 (Section A-A) and 2 Rivet Discard from the angle at STGR6 (Section A-A). 2 Remove: 33 Pin-Rivet Discard 33 Collar Discard 2 Rivet Discard from View B.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 278 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
3 As shown in View F, remove: 28 Pin-Rivet Discard 28 Collar Discard 10 Rivet Discard 4 As shown in View C, remove: 1 Angle D5357113145300 Item (24) Discard 1 Angle D5357113145900 Item (26) Discard 1 Clip D5357113144500 Item (28) Discard 1 Angle D5357072225700 Item (30) Discard 1 Clip D5357072224500 Item (32) Discard 1 Angle D5357072226100 Item (34) Discard 1 Web D5357116122000 Item (50) Discard 1 Bracket-Z D9357073720000 Item (133) Retain 5 Inspection: a Do a rotating probe test of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection of the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found, contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (e) Remove the items between STGR5 and STGR3 RH, refer to Fig. A-GBBAE Sheet 01 and Fig. A-GBBAE Sheet 02

. 1 Remove: 2 Rivet Discard from the angle at STGR5 (Section A-A) and 2 Rivet Discard
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 279 6

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# @A318/A319/A320/A321 SERVICE BULLETIN from the angle at STGR4 (Section A-A). 2 Remove: 20 Pin-Rivet Discard 20 Collar Discard from View B. 3 As shown in View F, remove: 19 Pin-Rivet Discard 19 Collar Discard 14 Rivet Discard 4 Remove: 1 Angle D5357072225500 Item (37) Discard 1 Angle D5357072225900 Item (39) Discard 1 Clip D5357072224700 Item (41 ) Discard 1 Angle D5357072225300 Item (43) Discard 1 Web D5357072224900 Item (45) Discard 1 Clip D5357072225100 Item (47) Discard 5 Inspection: a Do a rotating probe test of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found, contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 280 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (4) Subtask 531266-420-202-004 - Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR3, RH to STGR13, RH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 72 from Stringer 3 RH to Stringer 13 RH Manpower Resources Manhours 14.00 Minimum number of person 1 Subtask elapsed time 14.00 Skills AIRFRAME Material necessary to do the job Kit 531266D11R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 D5357113140190 1 ANGLE 4 D5357113146990 1 WEB 6 D5357113143990 1 WEB 8 D5357113144190 1 CLIP 10 D5357113146790 1 CLIP 12 D5357113143790 1 WEB 14 D5357113145790 1 ANGLE 16 D5357113145190 1 CLIP 18 D5357113145590 1 ANGLE 20 D5357113144990 1 CLIP 22 D5357113144790 1 WEB 24 D5357113145390 1 ANGLE 26 D5357113145990 1 ANGLE 28 D5357113144590 1 CLIP 30 D5357072225790 1 ANGLE 32 D5357072224590 1 CLIP 34 D5357072226190 1 ANGLE 37 D5357072225590 1 ANGLE 39 D5357072225990 1 ANGLE 41 D5357072224790 1 CLIP 43 D5357072225390 1 ANGLE 45 D5357072224990 1 WEB 47 D5357072225190 1 CLIP 50 D5357116122090 1 WEB 102 DAN5-6-4X 31 PIN 103 DAN11-6X 145 COLLAR 104 DAN5-6-5X 40 PIN 105 DAN5-6-6X 2 PIN 106 EN6081D5-06 33 RIVET DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 281 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 107 DAN5-6-5 16 PIN 108 NSA5075-6 54 COLLAR 109 DAN5-5-6 18 PIN 110 NSA5075-5 27 COLLAR 111 DAN5-5-5 9 PIN 112 DAN5-6-6 2 PIN 113 DAN5-6-3X 3 PIN 114 DAN5-8-5X 10 PIN 115 DAN11-8X 12 COLLAR 116 DAN5-8-4X 2 PIN 119 DAN6-6-3X 8 PIN 120 DAN6-6-4X 29 PIN 121 DAN6-6-5X 13 PIN 122 EN6069D5-06 12 RIVET 124 DAN6-6-7X 10 PIN 125 DAN6-6-7 19 PIN 126 DAN6-6-6 4 PIN 127 DAN6-6-5 3 PIN 128 DAN6-6-3 8 PIN 129 DAN5-6-3 2 PIN 132 DAN6-6-6X 9 PIN 135 EN6081D5-08 2 RIVET 136 EN6069D5-07 28 RIVET 137 EN6069D5-08 14 RIVET Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant, Brush Consistency 09-013 As required Corrosion Preventative Compound, Temporary 15-009 As required Anti-Corrosion Primer Polyurethane 16-001 As required Polyurethane Finish Paint 16-018 As required References Consumable Material List (CML) Fig. A-GBBAE Removal/Installation of Angles, Webs, Brackets and Clips at FR72 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-GBDAE Fastener Symbol Identification Sheet 01

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 282 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (a) Install the items between STGR3 and STGR4 on the RH side, refer to Fig. AGBBAE Sheet 01 , View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04 and Fig. A-GBDAE Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357072225390 Item 43 1 Clip D5357072225190 Item 47 with: 4 Pin DAN5-8-5X Item 114 4 Collar DAN11-8X Item 115 3 Pin DAN5-5-6 Item 109 3 Collar NSA5075-5 Item 110 2 As shown in Section C-C, at STGR4, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in View L, between STGR3 and STGR4, install: 4 Pin DAN6-6-7X Item 124 3 Pin DAN6-6-6X Item 132 7 Collar DAN11-6X Item 103 7 Rivet EN6069D5-08 Item 137 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 103, 109, 110, 114, 115, 124 and 132.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 283 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 103, 106, 109, 110, 114, 115, 124, 132 and 137. (b) Install the items between STGR4 and STGR5 on the RH side, refer to Fig. AGBBAE Sheet 01 , View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04and Fig. A-GBDAE Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357072225590 Item 37 1 Web D5357072224990 Item 45 with: 2 Pin DAN5-8-4X Item 116 2 Collar DAN11-8X Item 115 and then install: 1 Clip D5357072224790 Item 41 with: 6 Pin DAN5-8-5X Item 114 6 Collar DAN11-8X Item 115 and then install: 1 Angle D5357072225990 Item 39 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 110 2 As shown in Section C-C, at STGR5, install: 2 Rivet EN6081D5-06 Item 106

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 284 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
3 As shown in View L, between STGR4 and STGR5, install: 6 Pin DAN6-6-7X Item 124 6 Pin DAN6-6-6X Item 132 12 Collar DAN11-6X Item 103 7 Rivet EN6069D5-08 Item 137 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 103, 109, 110, 114, 115, 116, 124 and 132. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 103, 106, 109, 110, 114, 115, 116, 124, 132 and 137. (c) Install the items between STGR5 and STGR7 on the RH side, refer to Fig. AGBBAE Sheet 01 , View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04 and Fig. A-GBDAE Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357113145390 Item 24 1 Angle D5357072225790 Item 30 1 Bracket-Z D9357073720000 Item (133) Retained at removal 1 Web D5357116122090 Item 50 with: 9 Pin DAN5-6-4X Item 102 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 285 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
9 Collar DAN11-6X Item 103 2 Rivet EN6081D5-08 Item 135 and between STGR5 and STGR6, as shown in View H, install: 1 Clip D5357072224590 Item 32 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 and between STGR5 and STGR6, install: 1 Angle D5357072226190 Item 34 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 110 and between STGR6 and STGR7, install: 1 Clip D5357113144590 Item 28 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 and between STGR6 and STGR7, install: 1 Angle D5357113145990 Item 26 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 110 2 As shown in Section C-C, at STGR6, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section C-C, at STGR7, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View L, between STGR5 and STGR7, install: 19 Pin DAN6-6-7 Item 125 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 286 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
4 Pin DAN6-6-6 Item 126 1 Pin DAN6-6-5 Item 127 24 Collar NSA5075-6 Item 108 4 Pin DAN6-6-5X Item 121 4 Collar DAN11-6X Item 103 9 Rivet EN6069D5-07 Item 136 1 Rivet EN6069D5-06 Item 122 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 109, 110, 121, 125, 126 and 127. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 109, 110, 121, 122, 125, 126, 127, 135 and 136. (d) Install the items between STGR7 and STGR9 on the RH side, refer to Fig. AGBBAE Sheet 01 , View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04 and Fig. A-GBDAE Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Angle D5357113145790 Item 14 1 Angle D5357113145590 Item 18 NOTE : Items 14 and 18 are temporarily held in place. Then between STGR7 and STGR9, install: DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 287 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
1 Web D5357113144790 Item 22 with: 10 Pin DAN5-6-4X Item 102 10 Collar DAN11-6X Item 103 and then between STGR7 and STGR8, install: 1 Clip D5357113144990 Item 20 with: 5 Pin DAN5-6-5X Item 104 5 Collar DAN11-6X Item 103 4 Pin DAN5-5-5 Item 111 4 Collar NSA5075-5 Item 110 and then between STGR8 and STGR9, install: 1 Clip D5357113145190 Item 16 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 5 Pin DAN5-5-5 Item 111 5 Collar NSA5075-5 Item 110 2 As shown in Section C-C, at STGR8, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section C-C, at STGR9, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View L, between STGR7 and STGR9, install: 10 Pin DAN6-6-4X Item 120 9 Pin DAN6-6-5X Item 121 19 Collar DAN11-6X Item 103 2 Pin DAN6-6-5 Item 127
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 288 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
2 Collar NSA5075-6 Item 108 12 Rivet EN6069D5-07 Item 136 2 Rivet EN6069D5-06 Item 122 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 110, 111, 120, 121 and 127. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 110, 111, 120, 121, 122, 127 and 136. (e) Install the items between STGR9 and STGR11 on the RH side, refer to Fig. AGBBAE Sheet 01 , View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04 and Fig. A-GBDAE Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Bracket-Z D9357073720000 Item (133) Retained at removal 1 Web D5357113143790 Item 12 with: 2 Rivet EN6081D5-06 Item 106 9 Pin DAN5-6-4X Item 102 9 Collar DAN11-6X Item 103 and then between STGR9 and STGR10, install:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 289 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
1 Clip D5357113146790 Item 10 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 5 Rivet EN6081D5-06 Item 106 and then between STGR10 and STGR11, install: 1 Clip D5357113144190 Item 8 with: 7 Pin DAN5-6-5X Item 104 7 Collar DAN11-6X Item 103 4 Rivet EN6081D5-06 Item 106 2 As shown in Section C-C, at STGR10, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section C-C, at STGR11, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View L, between STGR9 and STGR11, install: 19 Pin DAN6-6-4X Item 120 19 Collar DAN11-6X Item 103 7 Rivet EN6069D5-07 Item 136 9 Rivet EN6069D5-06 Item 122 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104 and 120.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 290 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 106, 120, 122 and 136. (f) Install the items between STGR11 and STGR13 on the RH side, refer to Fig. AGBBAE Sheet 01 , View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04 and Fig. A-GBDAE Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 72, as shown in View G: 1 Bracket-Z D9357073720000 Item (133) Retained at removal 1 Web D5357113143990 Item 6 with 2 Rivet EN6081D5-06 Item 106 3 Pin DAN5-6-3X Item 113 3 Collar DAN11-6X Item 103 and then install: 1 Web D5357113146990 Item 4 with: 3 Pin DAN5-6-4X Item 102 3 Collar DAN11-6X Item 103 4 Rivet EN6081D5-06 Item 106 and then install: 1 Angle D5357113140190 Item 2 with: 2 Pin DAN5-6-6X Item 105 2 Collar DAN11-6X Item 103 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 291 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
16 Pin DAN5-6-5 Item 107 2 Pin DAN5-6-6 Item 112 18 Collar NSA5075-6 Item 108 2 As shown in Section D-D, at STGR12, install: 2 Pin DAN5-6-3 Item 129 2 Collar NSA5075-6 Item 108 3 As show in View J, install: 8 Pin DAN6-6-3X Item 119 8 Collar DAN11-6X Item 103 8 Pin DAN6-6-3 Item 128 8 Collar NSA5075-6 Item 108 4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 105, 107, 108, 112, 113, 119, 128 and 129. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 105, 106, 107, 108, 112, 113, 119, 128 and 129. (5) Subtask 531266-020-203-004 - Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, LH and STGR1, RH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 74 from Stringer 12 LH to Stringer 1 RH

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 292 6

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# @A318/A319/A320/A321 SERVICE BULLETIN Manpower Resources Manhours 11.00 Minimum number of person 1 Subtask elapsed time 11.00 Skills AIRFRAME NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) Task 51-10-01-250-801 51-10-08 Fig. A-GBAAA Location of Inspection Area for Clips at FR72/FR74 Sheet 01 Fig. A-GBCAE Removal/Installation of Angles, Webs, Brackets and Clips at FR74 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Remove the items between STGR12 and STGR9 LH, refer to Fig. A-GBCAE Sheet 01 and Fig. A-GBCAE Sheet 02

. 1 As shown in Section A-A, remove: 2 Rivet Discard from the angle at STGR11 and 2 Rivet Discard from the angle at STGR10. 2 Remove: 42 Pin-Rivet Discard 42 Collar Discard 8 Rivet Discard from View B. 3 As shown in View E, remove: 25 Pin-Rivet Discard 25 Collar Discard 16 Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 293 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
4 Remove: 1 Angle D5357113339600 Item (51 ) Discard 1 Filler D5357113339800 Item (53) Discard 1 Angle D5357113321400 Item (54) Discard 1 Angle D5357113337200 Item (56) Discard 1 Angle D5357113337000 Item (58) Discard 1 Web D5357113340000 Item (60) Discard 1 Web D5357113339400 Item (62) Discard 5 As shown in View F, remove: 5 Pin-Rivet Discard 5 Collar Discard 6 Inspection: a Do a rotating probe test of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found, contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (b) Remove the items between STGR9 and STGR7 LH, refer to Fig. A-GBCAE Sheet 01 and Fig. A-GBCAE Sheet 02

. 1 As shown in Section A-A, remove: 2 Rivet Discard from the angle at STGR9 and 2 Rivet Discard from the angle at STGR8. 2 Remove: 27 Pin-Rivet Discard DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 294 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
27 Collar Discard from View B. 3 As shown in View E, remove: 19 Pin-Rivet Discard 19 Collar Discard 14 Rivet Discard 4 Remove: 1 Angle D5357113339000 Item (64) Discard 1 Clip D5357113338400 Item (66) Discard 1 Web D5357113337800 Item (68) Discard 1 Angle D5357113338800 Item (70) Discard 1 Clip D5357113338200 Item (72) Discard 5 Inspection: a Do a rotating probe test of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found, contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (c) Remove the items between STGR7 and STGR5 LH, refer to Fig. A-GBCAE Sheet 01 and Fig. A-GBCAE Sheet 02

. 1 As shown in Section A-A, remove: 2 Rivet Discard from the angle at STGR7 and 2 Rivet Discard from the angle at STGR6.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 295 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
2 Remove: 32 Pin-Rivet Discard 32 Collar Discard from View B. 3 As shown in View C, remove: 30 Pin-Rivet Discard 30 Collar Discard 8 Rivet Discard 4 Remove: 1 Angle D5357113338600 Item (74) Discard 1 Clip D5357113338000 Item (76) Discard 1 Angle D5357113339200 Item (78) Discard 1 Angle D5357072425400 Item (80) Discard 1 Clip D5357072424200 Item (82) Discard 1 Web D5357113337600 Item (84) Discard 1 Angle D5357072425800 Item (86) Discard 5 Inspection: a Do a rotating probe test of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found, contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 296 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (d) Remove the items between STGR5 and STGR3 LH, refer to Fig. A-GBCAE Sheet 01 and Fig. A-GBCAE Sheet 02

. 1 As shown in Section A-A, remove: 2 Rivet Discard from the angle at STGR5 and 2 Rivet Discard from the angle at STGR4. 2 Remove: 18 Pin-Rivet Discard 18 Collar Discard from View B. 3 As shown in View C, remove: 17 Pin-Rivet Discard 17 Collar Discard 14 Rivet Discard 4 Remove: 1 Angle D5357072425200 Item (88) Discard 1 Angle D5357072425600 Item (90) Discard 1 Clip D5357072424400 Item (92) Discard 1 Angle D5357072425000 Item (94) Discard 1 Web D5357072424800 Item (96) Discard 1 Clip D5357072424600 Item (98) Discard 5 Inspection: a Do a rotating probe test of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 297 6

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# @A318/A319/A320/A321 SERVICE BULLETIN

c Findings: - If cracks are found, contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (e) Remove the items between STGR2 LH and STGR1 RH, refer to Fig. A-GBCAE Sheet 01 and Fig. A-GBCAE Sheet 02

. 1 As shown in Section A-A, remove: 2 Rivet Discard from the angle at STGR1. 2 Remove: 12 Pin-Rivet Discard 12 Collar Discard from View B. 3 As shown in View D, remove: 8 Pin-Rivet Discard 8 Collar Discard 8 Rivet Discard 4 Remove: 1 Clip D5357072224200 Item (48) Discard 1 Web D5357072424000 Item (100) Discard 5 Inspection: a Do a rotating probe test of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found, contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 298 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (6) Subtask 531266-420-203-004 - Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR1, RH and STGR12, LH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 74 from Stringer 1 RH to Stringer 12 LH Manpower Resources Manhours 14.00 Minimum number of person 1 Subtask elapsed time 14.00 Skills AIRFRAME Material necessary to do the job Kit 531266D11R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 48 D5357072224290 1 CLIP 51 D5357113339690 1 ANGLE 53 D5357113339800 1 FILLER 54 D5357113321490 1 ANGLE 56 D5357113337290 1 ANGLE 58 D5357113337090 1 ANGLE 60 D5357113340090 1 WEB 62 D5357113339490 1 WEB 64 D5357113339090 1 ANGLE 66 D5357113338490 1 CLIP 68 D5357113337890 1 WEB 70 D5357113338890 1 ANGLE 72 D5357113338290 1 CLIP 74 D5357113338690 1 ANGLE 76 D5357113338090 1 CLIP 78 D5357113339290 1 ANGLE 80 D5357072425490 1 ANGLE 82 D5357072424290 1 CLIP 84 D5357113337690 1 WEB 86 D5357072425890 1 ANGLE 88 D5357072425290 1 ANGLE 90 D5357072425690 1 ANGLE 92 D5357072424490 1 CLIP 94 D5357072425090 1 ANGLE 96 D5357072424890 1 WEB 98 D5357072424690 1 CLIP 100 D5357072424090 1 WEB 102 DAN5-6-4X 21 PIN 103 DAN11-6X 101 COLLAR DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 299 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 104 DAN5-6-5X 4 PIN 105 DAN5-6-6X 5 PIN 106 EN6081D5-06 26 RIVET 108 NSA5075-6 52 COLLAR 109 DAN5-5-6 17 PIN 110 NSA5075-5 25 COLLAR 111 DAN5-5-5 8 PIN 112 DAN5-6-6 24 PIN 114 DAN5-8-5X 25 PIN 115 DAN11-8X 56 COLLAR 116 DAN5-8-4X 2 PIN 117 DAN5-8-7X 10 PIN 118 DAN5-8-8X 2 PIN 120 DAN6-6-4X 27 PIN 121 DAN6-6-5X 15 PIN 122 EN6069D5-06 3 RIVET 123 DAN6-8-6X 8 PIN 124 DAN6-6-7X 13 PIN 125 DAN6-6-7 19 PIN 126 DAN6-6-6 6 PIN 127 DAN6-6-5 3 PIN 130 DAN5-6-7X 4 PIN 131 DAN5-8-6X 9 PIN 132 DAN6-6-6X 8 PIN 136 EN6069D5-07 38 RIVET 137 EN6069D5-08 19 RIVET 144 DAN7-6-11X 1 PIN 145 DAN12-6X 1 COLLAR 146 DAN5-6-10X 2 PIN 148 DAN5-6-8X 2 PIN Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant, Brush Consistency 09-013 As required Corrosion Preventative Compound, Temporary 15-009 As required Anti-Corrosion Primer Polyurethane 16-001 As required Polyurethane Finish Paint 16-018 As required References Consumable Material List (CML)

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 300 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
References Fig. A-GBCAE Removal/Installation of Angles, Webs, Brackets and Clips at FR74 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-GBDAE Fastener Symbol Identification Sheet 01 (a) Install the items between STGR2 on the RH side and STGR2 on the LH side, refer to Fig. A-GBCAE Sheet 01 , View A, Fig. A-GBCAE Sheet 03, Fig. A-GBCAE Sheet 04 and Fig. A-GBDAE Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Web D5357072424090 Item 100 with: 10 Pin DAN5-8-7X Item 117 10 Collar DAN11-8X Item 115 and then install: 1 Clip D5357072224290 Item 48 with: 2 PIN DAN5-8-8X Item 118 2 Collar DAN11-8X Item 115 2 As shown in Section B-B, at STGR1, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in View J, install: 8 Pin DAN6-8-6X Item 123 8 Collar DAN11-8X Item 115 3 Rivet EN6069D5-07 Item 136 5 Rivet EN6069D5-08 Item 137 XXXX

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 301 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
4 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 115, 117, 118 and 123. 5 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 106, 115, 117, 118, 123, 136 and 137. (b) Install the items between STGR3 and STGR5 on the LH side, refer to Fig. AGBCAE Sheet 01 , View A, Fig. A-GBCAE Sheet 03, Fig. A-GBCAE Sheet 04 and Fig. A-GBDAE Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Angle D5357072425090 Item 94 1 Angle D5357072425290 Item 88 1 Clip D5357072424690 Item 98 1 Web D5357072424890 Item 96 with: 2 Pin DAN5-5-6 Item 109 2 Collar NSA5075-5 Item 110 3 Pin DAN5-8-6X Item 131 2 Pin DAN5-8-4X Item 116 5 Collar DAN11-8X Item 115 and then install:
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 302 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
1 Clip D5357072424490 Item 92 with: 6 Pin DAN5-8-5X Item 114 6 Collar DAN11-8X Item 115 and then install: 1 Angle D5357072425690 Item 90 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 110 2 As shown in Section B-B, at STGR4, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section B-B, at STGR5, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View H, install: 9 Pin DAN6-6-7X Item 124 8 Pin DAN6-6-6X Item 132 17 Collar DAN11-6X Item 103 14 Rivet EN6069D5-08 Item 137 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 103, 109, 110, 114, 115, 116, 124, 131 and 132. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 303 6

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# @A318/A319/A320/A321 SERVICE BULLETIN to the fasteners, Items 103, 106, 109, 110, 114, 115, 116, 124, 131, 132 and 137. (c) Install the items between STGR5 and STGR7 on the LH side, refer to Fig. AGBCAE Sheet 01 , View A, Fig. A-GBCAE Sheet 03, Fig. A-GBCAE Sheet 04 and Fig. A-GBDAE Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Angle D5357072425490 Item 80 1 Angle D5357113338690 Item 74 NOTE : Items 74 and 80 are temporarily held in place. Then between STGR5 and STGR7, install: 1 Web D5357113337690 Item 84 with: 10 Pin DAN5-6-4X Item 102 10 Collar DAN11-6X Item 103 and then between STGR5 and STGR6, install: 1 Clip D5357072424290 Item 82 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 5 Pin DAN5-8-5X Item 114 5 Collar DAN11-8X Item 115 and then between STGR5 and STGR6, install: 1 Angle D5357072425890 Item 86 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 110
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 304 6

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# @A318/A319/A320/A321 SERVICE BULLETIN and then between STGR6 and STGR7, install: 1 Clip D5357113338090 Item 76 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 5 Pin DAN5-8-5X Item 114 5 Collar DAN11-8X Item 115 and then between STGR6 and STGR7, install: 1 Angle D5357113339290 Item 78 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 110 2 As shown in Section B-B, at STGR6, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section B-B, at STGR7, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View H, install: 19 Pin DAN6-6-7 Item 125 6 Pin DAN6-6-6 Item 126 1 Pin DAN6-6-5 Item 127 26 Collar NSA5075-6 Item 108 4 Pin DAN6-6-5X Item 121 4 Collar DAN11-6X Item 103 7 Rivet EN6069D5-07 Item 136 1 Rivet EN6069D5-06 Item 122

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 305 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 109, 110, 114, 115, 121, 125, 126 and 127. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 109, 110, 114, 115, 121, 122, 125, 126, 127 and 136. (d) Install the items between STGR7 and STGR9 on the LH side, refer to Fig. AGBCAE Sheet 01 , View A, Fig. A-GBCAE Sheet 03, Fig. A-GBCAE Sheet 04 and Fig. A-GBDAE Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Angle D5357113338890 Item 70 1 Angle D5357113339090 Item 64 NOTE : Items 64 and 70 are temporarily held in place. Then between STGR7 and STGR9, install: 1 Web D5357113337890 Item 68 with: 8 Pin DAN5-6-4X Item 102 8 Collar DAN11-6X Item 103 and then between STGR7 and STGR8, install: 1 Clip D5357113338290 Item 72 with: DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 306 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 4 Pin DAN5-8-5X Item 114 4 Collar DAN11-8X Item 115 4 Pin DAN5-5-5 Item 111 4 Collar NSA5075-5 Item 110 and then between STGR8 and STGR9, install: 1 Clip D5357113338490 Item 66 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 5 Pin DAN5-8-5X Item 114 5 Collar DAN11-8X Item 115 4 Pin DAN5-5-5 Item 111 4 Collar NSA5075-5 Item 110 2 As shown in Section B-B, at STGR8, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section B-B, at STGR9, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View K, install: 9 Pin DAN6-6-4X Item 120 8 Pin DAN6-6-5X Item 121 17 Collar DAN11-6X Item 103 2 Pin DAN6-6-5 Item 127 2 Collar NSA5075-6 Item 108 2 Rivet EN6069D5-06 Item 122 12 Rivet EN6069D5-07 Item 136 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 307 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 110, 111, 114, 115, 120, 121 and 127. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 110, 111, 114, 115, 120, 121, 122, 127 and 136. (e) Install the items between STGR9 and STGR12 on the LH side, refer to Fig. AGBCAE Sheet 01 , View A, Fig. A-GBCAE Sheet 03, Fig. A-GBCAE Sheet 04 and Fig. A-GBDAE Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Web D5357113339490 Item 62 with: 3 Pin DAN5-6-4X Item 102 3 Collar DAN11-6X Item 103 and then install: 1 Angle D5357113339690 Item 51 1 Filler D5357113339800 Item 53 1 Angle D5357113321490 Item 54 with: 24 Pin DAN5-6-6 Item 112 24 Collar NSA5075-6 Item 108 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 308 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
and then install: 1 Web D5357113340090 Item 60 with: 5 Pin DAN5-6-6X Item 105 5 Collar DAN11-6X Item 103 6 Pin DAN5-8-6X Item 131 6 Collar DAN11-8X Item 115 8 Rivet EN6081D5-06 Item 106 and then install: 1 Angle D5357113337290 Item 56 1 Angle D5357113337090 Item 58 with: 4 Pin DAN5-6-7X Item 130 4 Collar DAN11-6X Item 103 2 As shown in Section B-B, at STGR10, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section B-B, at STGR11, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View K, install: 18 Pin DAN6-6-4X Item 120 18 Collar DAN11-6X Item 103 3 Pin DAN6-6-5X Item 121 3 Collar DAN11-6X Item 103 4 Pin DAN6-6-7X Item 124 4 Collar DAN11-6X Item 103 16 Rivet EN6069D5-07 Item 136

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 309 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
5 As shown in View L, install: 1 Pin DAN7-6-11X Item 144 1 Collar DAN12-6X Item 145 2 Pin DAN5-6-10X Item 146 2 Collar DAN11-6X Item 103 2 Pin DAN5-6-8X Item 148 2 Collar DAN11-6X Item 103 6 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 105, 108, 112, 115, 120, 121, 124, 130, 131, 144, 145, 146 and 148. 7 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 105, 106, 108, 112, 115, 120, 121, 124, 130, 131, 136, 144, 145, 146 and 148. (7) Subtask 531266-020-204-004 - Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, RH and STGR3, RH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 74 from Stringer 3RH to Stringer 12RH

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 310 6

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# @A318/A319/A320/A321 SERVICE BULLETIN Manpower Resources Manhours 11.00 Minimum number of person 1 Subtask elapsed time 11.00 Skills AIRFRAME NON DESTRUCTIVE TESTING References Non Destructive Test Manual (NTM) Task 51-10-01-250-801 51-10-08 Fig. A-GBAAA Location of Inspection Area for Clips at FR72/FR74 Sheet 01 Fig. A-GBCAE Removal/Installation of Angles, Webs, Brackets and Clips at FR74 Sheet 01 Sheet 02 Sheet 03 Sheet 04 (a) Remove the items between STGR12 and STGR9 RH, refer to Fig. A-GBCAE Sheet 01 and Fig. A-GBCAE Sheet 02

. 1 As shown in Section A-A, remove: 2 Rivet Discard from the angle at STGR11 and 2 Rivet Discard from the angle at STGR10. 2 Remove: 42 Pin-Rivet Discard 42 Collar Discard 8 Rivet Discard from View B. 3 As shown in View E, remove: 25 Pin-Rivet Discard 25 Collar Discard 16 Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 311 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
4 Remove: 1 Angle D5357113339700 Item (52) Discard 1 Filler D5357113339800 Item (53) Discard 1 Angle D5357113321500 Item (55) Discard 1 Angle D5357113337300 Item (57) Discard 1 Angle D5357113337100 Item (59) Discard 1 Web D5357113340100 Item (61 ) Discard 1 Web D5357113339500 Item (63) Discard 5 As shown in View F, remove: 5 Pin-Rivet Discard 5 Collar Discard 6 Inspection: a Do a rotating probe test of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found, contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (b) Remove the items between STGR9 and STGR7 RH, refer to Fig. A-GBCAE Sheet 01 and Fig. A-GBCAE Sheet 02

. 1 As shown in Section A-A, remove: 2 Rivet Discard from the angle at STGR9 and 2 Rivet Discard from the angle at STGR8. 2 Remove: 27 Pin-Rivet Discard DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 312 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
27 Collar Discard from View B. 3 As shown in View E, remove: 19 Pin-Rivet Discard 19 Collar Discard 14 Rivet Discard 4 Remove: 1 Angle D5357113339100 Item (65) Discard 1 Clip D5357113338500 Item (67) Discard 1 Web D5357113337900 Item (69) Discard 1 Angle D5357113338900 Item (71 ) Discard 1 Clip D5357113338300 Item (73) Discard 5 Inspection: a Do a rotating probe test of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found, contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (c) Remove the items between STGR7 and STGR5 RH, refer to Fig. A-GBCAE Sheet 01 and Fig. A-GBCAE Sheet 02

. 1 As shown in Section A-A, remove: 2 Rivet Discard from the angle at STGR7 and 2 Rivet Discard from the angle at STGR6.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 313 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
2 Remove: 32 Pin-Rivet Discard 32 Collar Discard from View B. 3 As shown in View C, remove: 30 Pin-Rivet Discard 30 Collar Discard 8 Rivet Discard 4 Remove: 1 Angle D5357113338700 Item (75) Discard 1 Clip D5357113338100 Item (77) Discard 1 Angle D5357113339300 Item (79) Discard 1 Angle D5357072425500 Item (81 ) Discard 1 Clip D5357072424300 Item (83) Discard 1 Web D5357113337700 Item (85) Discard 1 Angle D5357072425900 Item (87) Discard 5 Inspection: a Do a rotating probe test of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Fequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

. c Findings: - If cracks are found, contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 314 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (d) Remove the items between STGR5 and STGR3 RH, refer to Fig. A-GBCAE Sheet 01 and Fig. A-GBCAE Sheet 02

. 1 As shown in Section A-A, remove: 2 Rivet Discard from the angle at STGR5 and 2 Rivet Discard from the angle at STGR4. 2 Remove: 18 Pin-Rivet Discard 18 Collar Discard from View B. 3 As shown in View C, remove: 17 Pin-Rivet Discard 17 Collar Discard 14 Rivet Discard 4 Remove: 1 Angle D5357072425300 Item (89) Discard 1 Angle D5357072425700 Item (91 ) Discard 1 Clip D5357072424500 Item (93) Discard 1 Angle D5357072425100 Item (95) Discard 1 Web D5357072424900 Item (97) Discard 1 Clip D5357072424700 Item (99) Discard 5 Inspection: a Do a rotating probe test of the fastener holes, refer to NTM Task 51-10-01-250-801. b Do a High Frequency Eddy Current (HFEC) crack inspection on the stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 315 6

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# @A318/A319/A320/A321 SERVICE BULLETIN

c Findings: - If cracks are found, contact AIRBUS and apply the repair instructions. - If no cracks are found, do the worksteps that follow. (8) Subtask 531266-420-204-004 - Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR3, RH and STGR12, RH Work Zones and Access Panels Zone Access/Work location 310 Work location Frame 74 from Stringer 3 RH to Stringer 12 RH Manpower Resources Manhours 12.00 Minimum number of person 1 Subtask elapsed time 12.00 Skills AIRFRAME Material necessary to do the job Kit 531266D11R02 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 52 D5357113339790 1 ANGLE 53 D5357113339800 1 FILLER 55 D5357113321590 1 ANGLE 57 D5357113337390 1 ANGLE 59 D5357113337190 1 ANGLE 61 D5357113340190 1 WEB 63 D5357113339590 1 WEB 65 D5357113339190 1 ANGLE 67 D5357113338590 1 CLIP 69 D5357113337990 1 WEB 71 D5357113338990 1 ANGLE 73 D5357113338390 1 CLIP 75 D5357113338790 1 ANGLE 77 D5357113338190 1 CLIP 79 D5357113339390 1 ANGLE 81 D5357072425590 1 ANGLE 83 D5357072424390 1 CLIP 85 D5357113337790 1 WEB 87 D5357072425990 1 ANGLE 89 D5357072425390 1 ANGLE 91 D5357072425790 1 ANGLE 93 D5357072424590 1 CLIP 95 D5357072425190 1 ANGLE DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 316 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 97 D5357072424990 1 WEB 99 D5357072424790 1 CLIP 102 DAN5-6-4X 21 PIN 103 DAN11-6X 101 COLLAR 104 DAN5-6-5X 4 PIN 105 DAN5-6-6X 5 PIN 106 EN6081D5-06 24 RIVET 108 NSA5075-6 52 COLLAR 109 DAN5-5-6 17 PIN 110 NSA5075-5 25 COLLAR 111 DAN5-5-5 8 PIN 112 DAN5-6-6 24 PIN 114 DAN5-8-5X 25 PIN 115 DAN11-8X 36 COLLAR 116 DAN5-8-4X 2 PIN 120 DAN6-6-4X 27 PIN 121 DAN6-6-5X 15 PIN 122 EN6069D5-06 3 RIVET 124 DAN6-6-7X 13 PIN 125 DAN6-6-7 19 PIN 126 DAN6-6-6 6 PIN 127 DAN6-6-5 3 PIN 130 DAN5-6-7X 4 PIN 131 DAN5-8-6X 9 PIN 132 DAN6-6-6X 8 PIN 136 EN6069D5-07 35 RIVET 137 EN6069D5-08 14 RIVET 144 DAN7-6-11X 1 PIN 145 DAN12-6X 1 COLLAR 146 DAN5-6-10X 2 PIN 148 DAN5-6-8X 2 PIN Consumable CMLD01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Sealant, Brush Consistency 09-013 As required Corrosion Preventative Compound, Temporary 15-009 As required Anti-Corrosion Primer Polyurethane 16-001 As required Polyurethane Finish Paint 16-018 As required References Consumable Material List (CML)

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 317 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
References Fig. A-GBCAE Removal/Installation of Angles, Webs, Brackets and Clips at FR74 Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-GBDAE Fastener Symbol Identification Sheet 01 (a) Install the items between STGR3 and STGR5 on the RH side, refer to Fig. AGBCAE Sheet 01 , View A, Fig. A-GBCAE Sheet 03, Fig. A-GBCAE Sheet 04 and Fig. A-GBDAE Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Angle D5357072425190 Item 95 1 Angle D5357072425390 Item 89 1 Clip D5357072424790 Item 99 1 Web D5357072424990 Item 97 with: 2 Pin DAN5-5-6 Item 109 2 Collar NSA5075-5 Item 110 3 Pin DAN5-8-6X Item 131 2 Pin DAN5-8-4X Item 116 5 Collar DAN11-8X Item 115 and then install: 1 Clip D5357072424590 Item 93 with: 6 Pin DAN5-8-5X Item 114 6 Collar DAN11-8X Item 115 and then install: 1 Angle D5357072425790 Item 91
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 318 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 110 2 As shown in Section B-B, at STGR4, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section B-B, at STGR5, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View H, install: 9 Pin DAN6-6-7X Item 124 8 Pin DAN6-6-6X Item 132 17 Collar DAN11-6X Item 103 14 Rivet EN6069D5-08 Item 137 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 103, 109, 110, 114, 115, 116, 124, 131 and 132. 6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 103, 106, 109, 110, 114, 115, 116, 124, 131, 132 and 137. (b) Install the items between STGR5 and STGR7 on the RH side, refer to Fig. AGBCAE Sheet 01 , View A, Fig. A-GBCAE Sheet 03, Fig. A-GBCAE Sheet 04 and Fig. A-GBDAE Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 319 6

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# @A318/A319/A320/A321 SERVICE BULLETIN to wet install on Frame 74, as shown in View G: 1 Angle D5357113338790 Item 75 1 Angle D5357072425590 Item 81 NOTE : Items 75 and 81 are temporarily held in place. Then between STGR5 and STGR7, install: 1 Web D5357113337790 Item 85 with: 10 Pin DAN5-6-4X Item 102 10 Collar DAN11-6X Item 103 and between STGR5 and STGR6, install: 1 Clip D5357072424390 Item 83 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 5 Pin DAN5-8-5X Item 114 5 Collar DAN11-8X Item 115 and between STGR5 and STGR6, install: 1 Angle D5357072425990 Item 87 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 110 and between STGR6 and STGR7, install: 1 Clip D5357113338190 Item 77 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 5 Pin DAN5-8-5X Item 114
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 320 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
5 Collar DAN11-8X Item 115 and between STGR6 and STGR7, install: 1 Angle D5357113339390 Item 79 with: 5 Pin DAN5-5-6 Item 109 5 Collar NSA5075-5 Item 110 2 As shown in Section B-B, at STGR6, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section B-B, at STGR7, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View H, install: 19 Pin DAN6-6-7 Item 125 6 Pin DAN6-6-6 Item 126 1 Pin DAN6-6-5 Item 127 26 Collar NSA5075-6 Item 108 4 Pin DAN6-6-5X Item 121 4 Collar DAN11-6X Item 103 7 Rivet EN6069D5-07 Item 136 1 Rivet EN6069D5-06 Item 122 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 109, 110, 114, 115, 121, 125, 126 and 127.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 321 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 109, 110, 114, 115, 121, 122, 125, 126, 127 and 136. (c) Install the items between STGR7 and STGR9 on the RH side, refer to Fig. AGBCAE Sheet 01 , View A, Fig. A-GBCAE Sheet 03, Fig. A-GBCAE Sheet 04 and Fig. A-GBDAE Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required
to wet install on Frame 74 as shown in View G: 1 Angle D5357113338990 Item 71 1 Angle D5357113339190 Item 65 NOTE : Items 65 and 71 are temporarily held in place. Then between STGR7 and STGR9, install: 1 Web D5357113337990 Item 69 with: 8 Pin DAN5-6-4X Item 102 8 Collar DAN11-6X Item 103 and then install: 1 Clip D5357113338390 Item 73 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 4 Pin DAN5-8-5X Item 114 4 Collar DAN11-8X Item 115 4 Pin DAN5-5-5 Item 111 4 Collar NSA5075-5 Item 110 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 322 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
and then install: 1 Clip D5357113338590 Item 67 with: 1 Pin DAN5-6-5X Item 104 1 Collar DAN11-6X Item 103 5 Pin DAN5-8-5X Item 114 5 Collar DAN11-8X Item 115 4 Pin DAN5-5-5 Item 111 4 Collar NSA5075-5 Item 110 2 As shown in Section B-B, at STGR8, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section B-B, at STGR9, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View K, install: 9 Pin DAN6-6-4X Item 120 8 Pin DAN6-6-5X Item 121 17 Collar DAN11-6X Item 103 2 Pin DAN6-6-5 Item 127 2 Collar NSA5075-6 Item 108 2 Rivet EN6069D5-06 Item 122 12 Rivet EN6069D5-07 Item 136 5 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required
Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 104, 108, 110, 111, 114, 115, 120, 121 and 127. DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 323 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
6 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 110, 111, 114, 115, 120, 121, 122, 127 and 136. (d) Install the items between STGR9 and STGR12 on the RH side, refer to Fig. AGBCAE Sheet 01 , View A, Fig. A-GBCAE Sheet 03, Fig. A-GBCAE Sheet 04 and Fig. A-GBDAE Sheet 01

. 1 Use Sealant, Brush Consistency 09-013 As required to wet install on Frame 74, as shown in View G: 1 Web D5357113339590 Item 63 with: 3 Pin DAN5-6-4X Item 102 3 Collar DAN11-6X Item 103 and then install: 1 Angle D5357113339790 Item 52 1 Filler D5357113339800 Item 53 1 Angle D5357113321590 Item 55 with: 24 Pin DAN5-6-6 Item 112 24 Collar NSA5075-6 Item 108 and then install: 1 Web D5357113340190 Item 61 with: 5 Pin DAN5-6-6X Item 105 5 Collar DAN11-6X Item 103 6 Pin DAN5-8-6X Item 131 DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 324 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
6 Collar DAN11-8X Item 115 8 Rivet EN6081D5-06 Item 106 and then install: 1 Angle D5357113337390 Item 57 1 Angle D5357113337190 Item 59 with: 4 Pin DAN5-6-7X Item 130 4 Collar DAN11-6X Item 103 2 As shown in Section B-B, at STGR10, install: 2 Rivet EN6081D5-06 Item 106 3 As shown in Section B-B, at STGR11, install: 2 Rivet EN6081D5-06 Item 106 4 As shown in View K, install: 18 Pin DAN6-6-4X Item 120 3 Pin DAN6-6-5X Item 121 4 Pin DAN6-6-7X Item 124 25 Collar DAN11-6X Item 103 16 Rivet EN6069D5-07 Item 136 5 As shown in View L, install: 1 Pin DAN7-6-11X Item 144 1 Collar DAN12-6X Item 145 2 Pin DAN5-6-10X Item 146 2 Pin DAN5-6-8X Item 148 4 Collar DAN11-6X Item 103 6 Apply: Anti-Corrosion Primer Polyurethane 16-001 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 325 6

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# @A318/A319/A320/A321 SERVICE BULLETIN Polyurethane Finish Paint 16-018 As required to the fasteners, Items 102, 103, 105, 108, 112, 115, 120, 121, 124, 130, 131, 144, 145, 146 and 148. 7 Apply: Corrosion Preventative Compound, Temporary 15-009 As required

to the fasteners, Items 102, 103, 105, 106, 108, 112, 115, 120, 121, 124, 130, 131, 136, 144, 145, 146 and 148. **CONF ALL D. TEST **CONF 001 (1) Subtask 531266-700-201-001 - Test Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) Task 36-12-00-790-001 Task 36-12-41-400-001 (a) Preparation: 1 Install the APU bleed air duct between frame 71 and frame 77, refer to AMM Task 36-12-41-400-001. (b) Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit breaker(s): PANEL DESIGNATION FIN LOCATION SEE NOTES 49VU AIR BLEED/X FEED/VALVE/BAT 2HV D13 49VU AIR BLEED/ENG 1/CTL 3HA1 D12 49VU AIR BLEED/ENG 1/MONG 2HA1 D11 122VU AIR BLEED/ENG 2/CTL 3HA2 Z23 122VU AIR BLEED/ENG 2/MONG 2HA2 Z22 122VU AIR BLEED/X FEED VALVE/NORM 1HV Z20 (c) Do the leak test of the APU bleed air supply system, refer to AMM Task 36-12-00-790-001.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 326 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
**CONF 002 (1) Subtask 531266-700-201-001 - Test Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) Task 36-12-00-790-001 Task 36-12-41-400-001 (a) Preparation: 1 Install the APU bleed air duct between frame 71 and frame 77, refer to AMM Task 36-12-41-400-001. (b) Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit breaker(s): PANEL DESIGNATION FIN LOCATION SEE NOTES 49VU AIR BLEED/X FEED/VALVE/BAT 2HV D13 49VU AIR BLEED/ENG 1/CTL 3HA1 D12 49VU AIR BLEED/ENG 1/MONG 2HA1 D11 122VU AIR BLEED/ENG 2/CTL 3HA2 Z23 122VU AIR BLEED/ENG 2/MONG 2HA2 Z22 122VU AIR BLEED/X FEED VALVE/NORM 1HV Z20 (c) Do the leak test of the APU bleed air supply system, refer to AMM Task 36-12-00-790-001. **CONF 003 (1) Subtask 531266-700-201-001 - Test Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) Task 36-12-00-790-001 Task 36-12-41-400-001 (a) Preparation: 1 Install the APU bleed air duct between frame 71 and frame 77, refer to AMM Task 36-12-41-400-001.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 327 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (b) Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit breaker(s): PANEL DESIGNATION FIN LOCATION SEE NOTES 49VU AIR BLEED/X FEED/VALVE/BAT 2HV D13 49VU AIR BLEED/ENG 1/CTL 3HA1 D12 49VU AIR BLEED/ENG 1/MONG 2HA1 D11 122VU AIR BLEED/ENG 2/CTL 3HA2 Z23 122VU AIR BLEED/ENG 2/MONG 2HA2 Z22 122VU AIR BLEED/X FEED VALVE/NORM 1HV Z20 (c) Do the leak test of the APU bleed air supply system, refer to AMM Task 36-12-00-790-001. **CONF 004 (1) Subtask 531266-700-201-001 - Test Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) Task 36-12-00-790-001 Task 36-12-41-400-001 (a) Preparation: 1 Install the APU bleed air duct between frame 71 and frame 77, refer to AMM Task 36-12-41-400-001. (b) Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit breaker(s): PANEL DESIGNATION FIN LOCATION SEE NOTES 49VU AIR BLEED/X FEED/VALVE/BAT 2HV D13 49VU AIR BLEED/ENG 1/CTL 3HA1 D12 49VU AIR BLEED/ENG 1/MONG 2HA1 D11 122VU AIR BLEED/ENG 2/CTL 3HA2 Z23 122VU AIR BLEED/ENG 2/MONG 2HA2 Z22 122VU AIR BLEED/X FEED VALVE/NORM 1HV Z20 (c) Do the leak test of the APU bleed air supply system, refer to AMM Task 36-12-00-790-001.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 328 6

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# @A318/A319/A320/A321 SERVICE BULLETIN
**CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 531266-942-201-001 - Close-up Work Zones and Access Panels Zone Access/Work location 310 Work location from Frame 70 to Frame 77 from Stringer 1 to Stringer 13 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 29-11-00, Page Block 001 29-13-00, Page Block 001 Task 52-10-00-410-001 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Put the affected hydraulic lines which were loosened for access back in position at Frame 72. (c) Install the loosened wire and wire clamps. (d) Install the light 4LJ. (e) Pressurize the green and yellow hydraulic systems, refer to AMM 29-11-00, Page Block 001 and AMM 29-13-00, Page Block 001. (f) Close the access doors 312AR and 314AR. (g) Close the passenger/crew door 831, refer to AMM Task 52-10-00-410-001. (h) Remove the access platform(s). (i) Put the aircraft back to its initial configuration. **CONF 002 (1) Subtask 531266-942-201-001 - Close-up Work Zones and Access Panels Zone Access/Work location 310 Work location from Frame 70 to Frame 77 from Stringer 1 to Stringer 13

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 329 6

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# @A318/A319/A320/A321 SERVICE BULLETIN Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 29-11-00, Page Block 001 29-13-00, Page Block 001 Task 52-10-00-410-001 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Put the affected hydraulic lines which were loosened for access back in position at Frame 72. (c) Install the loosened wire and wire clamps. (d) Install the light 4LJ. (e) Pressurize the green and yellow hydraulic systems, refer to AMM 29-11-00, Page Block 001 and AMM 29-13-00, Page Block 001. (f) Close the access doors 312AR and 314AR. (g) Close the passenger/crew door 831, refer to AMM Task 52-10-00-410-001. (h) Remove the access platform(s). (i) Put the aircraft back to its initial configuration. **CONF 003 (1) Subtask 531266-942-201-001 - Close-up Work Zones and Access Panels Zone Access/Work location 310 Work location from Frame 70 to Frame 77 from Stringer 1 to Stringer 13 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 29-11-00, Page Block 001 29-13-00, Page Block 001 Task 52-10-00-410-001 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Put the affected hydraulic lines which were loosened for access back in position at Frame 72.
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 330 6

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# @A318/A319/A320/A321 SERVICE BULLETIN (c) Install the loosened wire and wire clamps. (d) Install the light 4LJ. (e) Pressurize the green and yellow hydraulic systems, refer to AMM 29-11-00, Page Block 001 and AMM 29-13-00, Page Block 001. (f) Close the access doors 312AR and 314AR. (g) Close the passenger/crew door 831, refer to AMM Task 52-10-00-410-001. (h) Remove the access platform(s). (i) Put the aircraft back to its initial configuration. **CONF 004 (1) Subtask 531266-942-201-001 - Close-up Work Zones and Access Panels Zone Access/Work location 310 Work location from Frame 70 to Frame 77 from Stringer 1 to Stringer 13 Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 29-11-00, Page Block 001 29-13-00, Page Block 001 Task 52-10-00-410-001 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Put the affected hydraulic lines which were loosened for access back in position at Frame 72. (c) Install the loosened wire and wire clamps. (d) Install the light 4LJ. (e) Pressurize the green and yellow hydraulic systems, refer to AMM 29-11-00, Page Block 001 and AMM 29-13-00, Page Block 001. (f) Close the access doors 312AR and 314AR. (g) Close the passenger/crew door 831, refer to AMM Task 52-10-00-410-001. (h) Remove the access platform(s). (i) Put the aircraft back to its initial configuration.
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 331 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL



### A Z310 FR72 FR74

FR77

FR70 

## A A A A A

FWD FR72 FR74 90.0 mm (3.54 in) 90.0 mm (3.54 in)

TYPICAL FOR STGR11LH

−STGR11RH

PERFORM CRACK DETECTION ON STRINGER USING NOTE: 01 DYNAMIC EDDY CURRENT ACC. TO NTM 51

−10

−08. SURFACE TO BE CHECKED. 02 

### B



## A A
02 

## B VIEW LOOKING FWD

N_SB_531266_6_BAAA_01_02 01

Figure A-GBAAA - Sheet 01 Location of Inspection Area for Clips at FR72/FR74
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 332 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

STGR4 STGR5
STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

STGR13 AD

STGR12 STGR3 STGR2

FR72 

### BEFORE

LH SHOWN RH SYMMETRICAL VIEW LOOKING FWD

STGR5RH
STGR6RH

STGR7RH

VIEW LOOKING FWD (5) (6) LH RH

(1) (2) LH RH (3) (4) LH RH (7) (8) LH RH (9) (10) LH RH

(11) (12) LH RH (13) (14) LH RH (17) (18) LH RH

(15) (16) LH RH

(19) (20) LH RH (23) (25) (29) (33) (38) (39) LH RH (36) (37) LH RH (42) (43) LH RH

RH SIDE ONLY FR72 (24) (26) (30) (34)

(50)

(28) (32) (48) (49)

(46) (47) LH RH (40) (41) LH RH (44) (45) LH RH LH ONLY

(35)

(27) (31)



## B

C C A Z310

FR72 FR74

FR77

FR70 

## A B

REMOVE AND DISCARD EXSISTING FASTENERS FASTENER TABLE (133)

(133)

(133)

(133) STGR12

FR72



## B B F W D FR72 STGR



## A A B B A

A (21) (22)LH RH

F W D 

### D E

F G

TYPICAL FOR STGR1 (AD) AND STGR4

−STGR11

N_SB_531266_6_BBAA_01_01 Figure A-GBBAA - Sheet 01 Removal/Installation of Angles, Webs, Brackets and Clips at FR72
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 333 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

FWD FR72 N_SB_531266_6_BBAA_02_00 FR72

STGR13 STGR12 STGR11

FWD

F W D AD

FR72 

## D

E

F REMOVE AND DISCARD EXSISTING FASTENERS FASTENER TABLE

Figure A-GBBAA - Sheet 02 Removal/Installation of Angles, Webs, Brackets and Clips at FR72
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 334 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

(133)
(133)

(133)

(133) FR72

STGR13 STGR12 STGR11

FWD STGR4 STGR5
STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

STGR13 AD

STGR12 STGR3 STGR2

FR72 

### AFTER

LH SHOWN RH SYMMETRICAL VIEW LOOKING FWD STGR5RH
STGR6RH

STGR7RH

VIEW LOOKING FWD

5 6 LH

RH

1 2 LH

RH 3 4 LH RH 7 8 LH RH 9 10 LH RH

11 12 LH RH 13 14 LH RH 17 18 LH RH

15 16 LH RH 19 20 LH RH 21 22 LH RH 23 25 29 33 38 39 LH RH 36 37 LH RH

40 41 LH RH 44 45 LH RH 46 47 LH RH 42 43 LH RH

RH SIDE ONLY FR72 24 26 30 34

50

28 32 48

LH ONLY

27 35 31

STGR12

FR72

F W D FR72

TYPICAL FOR F W D AD

FR72 

## G H

J K C C D D F W D 

### C C

D D H

J K

L

STGR4

−STGR11

N_SB_531266_6_BBAA_03_02 

### E

E 49

FOR FASTENER SYMBOLS, REFER TO FIG. N_SB_531266_6_BDAA SHEET 1 NOTE: STGR4 STGR11
− STGR1 (AD)

F W D 

## E E FR72

Figure A-GBBAA - Sheet 03 Removal/Installation of Angles, Webs, Brackets and Clips at FR72
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 335 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

FWD FR72 

## L N_SB_531266_6_BBAA_04_01 FOR FASTENER SYMBOLS, REFER NOTE: TO FIG. N_SB_531266_6_BDAA SHEET 1 Figure A-GBBAA - Sheet 04 Removal/Installation of Angles, Webs, Brackets and Clips at FR72
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 336 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002

STGR4 STGR5
STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

STGR13 AD

STGR12 STGR3 STGR2

FR72 

### BEFORE

LH SHOWN RH SYMMETRICAL VIEW LOOKING FWD

STGR5RH
STGR6RH

STGR7RH

VIEW LOOKING FWD (5) (6) LH RH

(1) (2) LH RH (3) (4) LH RH (7) (8) LH RH (9) (10) LH RH

(11) (12) LH RH (13) (14) LH RH (17) (18) LH RH

(15) (16) LH RH

(19) (20) LH RH (23) (25) (29) (33) (38) (39) LH RH (36) (37) LH RH (42) (43) LH RH

RH SIDE ONLY FR72 (24) (26) (30) (34)

(50)

(28) (32) (48) (49)

(46) (47) LH RH (40) (41) LH RH (44) (45) LH RH LH ONLY

(35)

(27) (31)



## B

C C A Z310

FR72 FR74

FR77

FR70 

## A B (133)

(133)

(133)

(133) STGR12

FR72



## B B F W D FR72 STGR



## A A B B A

A (21) (22)LH RH

F W D 

### D E

F G

REMOVE AND DISCARD EXISTING FASTENERS FASTENER TABLE TYPICAL FOR STGR1 (AD) AND STGR4

−STGR11

N_SB_531266_6_BBAB_01_01 Figure A-GBBAB - Sheet 01 Removal/Installation of Angles, Webs, Brackets and Clips at FR72
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 337 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

FWD FR72 FR72

STGR13 STGR12 STGR11

FWD

F W D AD

FR72 

## D

E

F REMOVE AND DISCARD EXISTING FASTENERS FASTENER TABLE

N_SB_531266_6_BBAB_02_00 Figure A-GBBAB - Sheet 02 Removal/Installation of Angles, Webs, Brackets and Clips at FR72
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 338 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002

FOR FASTENER SYMBOLS, REFER TO FIG. N_SB_531266_6_BDAB SHEET 1 NOTE: STGR1 (AD)

F W D 

## E E FR72 (133)
(133)

(133)

(133) FR72

STGR13 STGR12 STGR11

FWD STGR4 STGR5
STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

STGR13 AD

STGR12 STGR3 STGR2

FR72 

### AFTER

LH SHOWN RH SYMMETRICAL VIEW LOOKING FWD STGR5RH
STGR6RH

STGR7RH

VIEW LOOKING FWD

5 6 LH

RH

1 2 LH

RH 3 4 LH RH 7 8 LH RH 9 10 LH RH

11 12 LH RH 13 14 LH RH 17 18 LH RH

15 16 LH RH 19 20 LH RH 21 22 LH RH 23 25 29 33 38 39 LH RH 36 37 LH RH

40 41 LH RH 44 45 LH RH 46 47 LH RH 42 43 LH RH

RH SIDE ONLY FR72 24 26 30 34

50

28 32 48

LH ONLY

27 35 31

STGR12

FR72

F W D FR72

TYPICAL FOR F W D AD

FR72 

## G H

J K C C D D F W D 

### C C

D D H

J K

L

STGR4

−STGR11

N_SB_531266_6_BBAB_03_01 

### E

E 49

STGR4 STGR11
−

Figure A-GBBAB - Sheet 03 Removal/Installation of Angles, Webs, Brackets and Clips at FR72
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 339 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

FWD FR72 

## L FOR FASTENER SYMBOLS, REFER NOTE: TO FIG. N_SB_531266_6_BDAB SHEET 1 N_SB_531266_6_BBAB_04_02 Figure A-GBBAB - Sheet 04 Removal/Installation of Angles, Webs, Brackets and Clips at FR72
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 340 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 003

STGR4 STGR5
STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

STGR13 AD

STGR12 STGR3 STGR2

FR72 

### BEFORE

LH SHOWN RH SYMMETRICAL VIEW LOOKING FWD

STGR5RH
STGR6RH

STGR7RH

VIEW LOOKING FWD (5) (6) LH RH

(1) (2) LH RH (3) (4) LH RH (7) (8) LH RH (9) (10) LH RH

(11) (12) LH RH (13) (14) LH RH (17) (18) LH RH

(15) (16) LH RH

(19) (20) LH RH (23) (25) (29) (33) (38) (39) LH RH (36) (37) LH RH (42) (43) LH RH

RH SIDE ONLY FR72 (24) (26) (30) (34)

(50)

(28) (32) (48) (49)

(46) (47) LH RH (40) (41) LH RH (44) (45) LH RH LH ONLY

(35)

(27) (31)



## B

C C A Z310

FR72 FR74

FR77

FR70 

## A B (133)

(133)

(133)

(133) STGR12

FR72



## B B F W D FR72 STGR



## A A B B A

A (21) (22)LH RH

F W D 

### D E

F G

REMOVE AND DISCARD EXISTING FASTENERS FASTENER TABLE TYPICAL FOR STGR1 (AD) AND STGR4

−STGR11

N_SB_531266_6_BBAD_01_00 Figure A-GBBAD - Sheet 01 Removal/Installation of Angles, Webs, Brackets and Clips at FR72
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 341 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 003

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

FWD FR72 FR72

STGR13 STGR12 STGR11

FWD

F W D AD

FR72 

## D

E

F REMOVE AND DISCARD EXISTING FASTENERS FASTENER TABLE

N_SB_531266_6_BBAD_02_00 Figure A-GBBAD - Sheet 02 Removal/Installation of Angles, Webs, Brackets and Clips at FR72
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 342 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 003

FOR FASTENER SYMBOLS, REFER TO FIG. N_SB_531266_6_BDAD SHEET 1 NOTE: STGR1 (AD)

F W D 

## E E FR72 (133)
(133)

(133)

(133) FR72

STGR13 STGR12 STGR11

FWD STGR4 STGR5
STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

STGR13 AD

STGR12 STGR3 STGR2

FR72 

### AFTER

LH SHOWN RH SYMMETRICAL VIEW LOOKING FWD STGR5RH
STGR6RH

STGR7RH

VIEW LOOKING FWD

5 6 LH

RH

1 2 LH

RH 3 4 LH RH 7 8 LH RH 9 10 LH RH

11 12 LH RH 13 14 LH RH 17 18 LH RH

15 16 LH RH 19 20 LH RH 21 22 LH RH 23 25 29 33 38 39 LH RH 36 37 LH RH

40 41 LH RH 44 45 LH RH 46 47 LH RH 42 43 LH RH

RH SIDE ONLY FR72 24 26 30 34

50

28 32 48

LH ONLY

27 35 31

STGR12

FR72

F W D FR72

TYPICAL FOR 

## G H

J C C D D F W D 

### C C

D D H

J K

L

STGR4

−STGR11 

### E

E 49

STGR4 STGR11
−

F W D AD

FR72



## K

N_SB_531266_6_BBAD_03_02 Figure A-GBBAD - Sheet 03 Removal/Installation of Angles, Webs, Brackets and Clips at FR72
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 343 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 003

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

FWD FR72 

## L FOR FASTENER SYMBOLS, REFER NOTE: TO FIG. N_SB_531266_6_BDAD SHEET 1 N_SB_531266_6_BBAD_04_00 Figure A-GBBAD - Sheet 04 Removal/Installation of Angles, Webs, Brackets and Clips at FR72
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 344 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 004

STGR4 STGR5
STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

STGR13 AD

STGR12 STGR3 STGR2

FR72 

### BEFORE

LH SHOWN RH SYMMETRICAL VIEW LOOKING FWD

STGR5RH
STGR6RH

STGR7RH

VIEW LOOKING FWD (5) (6) LH RH

(1) (2) LH RH (3) (4) LH RH (7) (8) LH RH (9) (10) LH RH

(11) (12) LH RH (13) (14) LH RH (17) (18) LH RH

(15) (16) LH RH

(19) (20) LH RH (23) (25) (29) (33) (38) (39) LH RH (36) (37) LH RH (42) (43) LH RH

RH SIDE ONLY FR72 (24) (26) (30) (34)

(50)

(28) (32) (49)

(46) (47) LH RH (40) (41) LH RH (44) (45) LH RH LH ONLY

(35)

(27) (31)



## B

C C A Z310

FR72 FR74

FR77

FR70 

## A

REMOVE AND DISCARD EXSISTING FASTENERS FASTENER TABLE (133)

(133)

(133)

(133) STGR12

FR72



## B B F W D FR72 STGR



## A A B B A

A (21) (22)LH RH

F W D 

### D E

F

TYPICAL FOR STGR1 (AD) AND STGR4

−STGR11 

### B G (48)

N_SB_531266_6_BBAE_01_00 Figure A-GBBAE - Sheet 01 Removal/Installation of Angles, Webs, Brackets and Clips at FR72
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 345 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 004

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

FWD FR72 FR72

STGR13 STGR12 STGR11

FWD

F W D AD

FR72 

## D

E

F REMOVE AND DISCARD EXSISTING FASTENERS FASTENER TABLE

N_SB_531266_6_BBAE_02_00 Figure A-GBBAE - Sheet 02 Removal/Installation of Angles, Webs, Brackets and Clips at FR72
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 346 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 004

(133)
(133)

(133)

(133) FR72

STGR13 STGR12 STGR11

FWD STGR4 STGR5
STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

STGR13 AD

STGR12 STGR3 STGR2

FR72 

### AFTER

LH SHOWN RH SYMMETRICAL VIEW LOOKING FWD STGR5RH
STGR6RH

STGR7RH

VIEW LOOKING FWD

5 6 LH

RH

1 2 LH

RH 3 4 LH RH 7 8 LH RH 9 10 LH RH

11 12 LH RH 13 14 LH RH 17 18 LH RH

15 16 LH RH 19 20 LH RH 21 22 LH RH 23 25 29 33 38 39 LH RH 36 37 LH RH

40 41 LH RH 44 45 LH RH 46 47 LH RH 42 43 LH RH

RH SIDE ONLY FR72 24 26 30 34

50

28 32 48

LH ONLY

27 35 31

STGR12

FR72

F W D FR72

TYPICAL FOR F W D AD

FR72 

## G H

J K C C D D F W D 

### C C

D D H

J K

L

STGR4

−STGR11 

### E

E 49

FOR FASTENER SYMBOLS, REFER TO FIG. N_SB_531266_6_BDAE SHEET 1 NOTE: STGR4 STGR11
− STGR1 (AD)

F W D 

## E E FR72

N_SB_531266_6_BBAE_03_00 Figure A-GBBAE - Sheet 03 Removal/Installation of Angles, Webs, Brackets and Clips at FR72
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 347 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 004

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

FWD FR72 

## L FOR FASTENER SYMBOLS, REFER NOTE: TO FIG. N_SB_531266_6_BDAE SHEET 1 N_SB_531266_6_BBAE_04_00 Figure A-GBBAE - Sheet 04 Removal/Installation of Angles, Webs, Brackets and Clips at FR72
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 348 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

STGR4
STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11 AD

STGR12 STGR3 STGR2

FR74 

### BEFORE

LH SHOWN RH SYMMETRICAL VIEW LOOKING FWD

(53) (54) (55) LH RH (51) (52) LH RH (56) (57) LH RH (58) (59) LH RH (60) (61) LH RH

(62) (63) LH RH

(64) (65) LH RH (68) (69) LH RH (66) (67) LH RH (72) (73) LH RH (74) (75) LH RH (78) (79) LH RH (80) (81) LH RH (86) (87) LH RH (88) (89) LH RH (90) (91) LH RH (48) (100)

(94) (95) LH RH

(70) (71) LH RH (76) (77) LH RH (84) (85) LH RH (82) (83) LH RH (98) (99) LH RH (96) (97) LH RH (92) (93) LH RH



## B A Z310

FR72 FR74

FR77

FR70 

## A B

REMOVE AND DISCARD EXSISTING FASTENERS FASTENER TABLE F W D STGR4 STGR5 STGR6 STGR7

FR74

F W D FR74 STGR



## A A C A

A C D

E

TYPICAL FOR STGR1 (AD) AND STGR4

−STGR11 N_SB_531266_6_BCAA_01_02 

### F G

Figure A-GBCAA - Sheet 01 Removal/Installation of Angles, Webs, Brackets and Clips at FR74
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 349 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

FWD STGR7

STGR8

STGR9

STGR10

STGR11

STGR12 FR74

REMOVE AND DISCARD EXSISTING FASTENERS FASTENER TABLE F W D AD

FR74



## D

E

N_SB_531266_6_BCAA_02_01 F W D STGR12



## F FR74

Figure A-GBCAA - Sheet 02 Removal/Installation of Angles, Webs, Brackets and Clips at FR74
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 350 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

STGR4
STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11 AD

STGR12 STGR3 STGR2

FR74 

### AFTER

LH SHOWN RH SYMMETRICAL VIEW LOOKING FWD

53 54 55 LH RH 51 52 LH RH 56 57 LH RH 58 59 LH RH 60 61 LH RH

62 63 LH RH 64 65 LH RH 68 69 LH RH 66 67 LH RH 72 73 LH RH 74 75 LH RH 78 79 LH RH 80 81 LH RH 86 87 LH RH 88 89 LH RH 90 91 LH RH 100

92 93 LH RH

70 71 LH RH 76 77 LH RH 84 85 LH RH 82 83 LH RH 94 95 LH RH 98 99 LH RH 96 97 LH RH

F W D AD

FR74

F W D STGR4

STGR5 STGR6 STGR7

FR74 F W D FR74 STGR



## B B

B B TYPICAL FOR STGR1 (AD) AND STGR4

−STGR11 48

FOR FASTENER SYMBOLS, REFER TO FIG. N_SB_531266_6_BDAA SHEET 1 NOTE: 

## G

H J J
H

K

L
N_SB_531266_6_BCAA_03_03 Figure A-GBCAA - Sheet 03 Removal/Installation of Angles, Webs, Brackets and Clips at FR74
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 351 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

FWD STGR7

STGR8

STGR9

STGR10

STGR11

STGR12 FR74

N_SB_531266_6_BCAA_04_01 FOR FASTENER SYMBOLS, REFER TO FIG. N_SB_531266_6_BDAA SHEET 1 NOTE: F W D STGR12

FR74 

## K

L

Figure A-GBCAA - Sheet 04 Removal/Installation of Angles, Webs, Brackets and Clips at FR74
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 352 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002

STGR4
STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11 AD

STGR12 STGR3 STGR2

FR74 

### BEFORE

LH SHOWN RH SYMMETRICAL VIEW LOOKING FWD

(53) (54) (55) LH RH (51) (52) LH RH (56) (57) LH RH (58) (59) LH RH (60) (61) LH RH

(62) (63) LH RH

(64) (65) LH RH (68) (69) LH RH (66) (67) LH RH (72) (73) LH RH (74) (75) LH RH (78) (79) LH RH (80) (81) LH RH (86) (87) LH RH (88) (89) LH RH (90) (91) LH RH (48) (100)

(94) (95) LH RH

(70) (71) LH RH (76) (77) LH RH (84) (85) LH RH (82) (83) LH RH (98) (99) LH RH (96) (97) LH RH (92) (93) LH RH



## B A Z310

FR72 FR74

FR77

FR70 

## A B

F W D STGR4 STGR5 STGR6 STGR7

FR74

F W D FR74 STGR



## A A C A

A C D

E

REMOVE AND DISCARD EXISTING FASTENERS FASTENER TABLE TYPICAL FOR STGR1 (AD) AND STGR4

−STGR11 N_SB_531266_6_BCAB_01_02 

### F G

Figure A-GBCAB - Sheet 01 Removal/Installation of Angles, Webs, Brackets and Clips at FR74
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 353 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002

FWD STGR7

STGR8

STGR9

STGR10

STGR11

STGR12 FR74

F W D AD

FR74



## D

E

REMOVE AND DISCARD EXISTING FASTENERS FASTENER TABLE

N_SB_531266_6_BCAB_02_01 F W D STGR12



## F FR74

Figure A-GBCAB - Sheet 02 Removal/Installation of Angles, Webs, Brackets and Clips at FR74
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 354 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002

STGR4
STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11 AD

STGR12 STGR3 STGR2

FR74 

### AFTER

LH SHOWN RH SYMMETRICAL VIEW LOOKING FWD

53 54 55 LH RH 51 52 LH RH 56 57 LH RH 58 59 LH RH 60 61 LH RH

62 63 LH RH 64 65 LH RH 68 69 LH RH 66 67 LH RH 72 73 LH RH 74 75 LH RH 78 79 LH RH 80 81 LH RH 86 87 LH RH 88 89 LH RH 90 91 LH RH 100

92 93 LH RH

70 71 LH RH 76 77 LH RH 84 85 LH RH 82 83 LH RH 94 95 LH RH 98 99 LH RH 96 97 LH RH

F W D AD

FR74

F W D STGR4

STGR5 STGR6 STGR7

FR74 F W D FR74 STGR



## B B

B B TYPICAL FOR STGR1 (AD) AND STGR4

−STGR11 48

N_SB_531266_6_BCAB_03_01 FOR FASTENER SYMBOLS, REFER TO FIG. N_SB_531266_6_BDAB SHEET 1 NOTE: 

## G J
H

K

L 

## H J

Figure A-GBCAB - Sheet 03 Removal/Installation of Angles, Webs, Brackets and Clips at FR74
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 355 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002

FWD STGR7

STGR8

STGR9

STGR10

STGR11

STGR12 FR74

N_SB_531266_6_BCAB_04_01 FOR FASTENER SYMBOLS, REFER TO FIG. N_SB_531266_6_BDAB SHEET 1 NOTE: F W D STGR12

FR74 

## K

L

Figure A-GBCAB - Sheet 04 Removal/Installation of Angles, Webs, Brackets and Clips at FR74
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 356 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 003

STGR4
STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11 AD

STGR12 STGR3 STGR2

FR74 

### BEFORE

LH SHOWN RH SYMMETRICAL VIEW LOOKING FWD

(53) (54) (55) LH RH (51) (52) LH RH (56) (57) LH RH (58) (59) LH RH (60) (61) LH RH

(62) (63) LH RH

(64) (65) LH RH (68) (69) LH RH (66) (67) LH RH (72) (73) LH RH (74) (75) LH RH (78) (79) LH RH (80) (81) LH RH (86) (87) LH RH (88) (89) LH RH (90) (91) LH RH (48) (100)

(94) (95) LH RH

(70) (71) LH RH (76) (77) LH RH (84) (85) LH RH (82) (83) LH RH (98) (99) LH RH (96) (97) LH RH (92) (93) LH RH



## B A Z310

FR72 FR74

FR77

FR70 

## A B

F W D STGR4 STGR5 STGR6 STGR7

FR74

F W D FR74 STGR



## A A C A

A C D

E

REMOVE AND DISCARD EXISTING FASTENERS FASTENER TABLE TYPICAL FOR STGR1 (AD) AND STGR4

−STGR11 

### F G

N_SB_531266_6_BCAD_01_00 Figure A-GBCAD - Sheet 01 Removal/Installation of Angles, Webs, Brackets and Clips at FR74
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 357 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 003

FWD STGR7

STGR8

STGR9

STGR10

STGR11

STGR12 FR74

F W D AD

FR74



## D

E

REMOVE AND DISCARD EXISTING FASTENERS FASTENER TABLE F W D STGR12



## F FR74

N_SB_531266_6_BCAD_02_00 Figure A-GBCAD - Sheet 02 Removal/Installation of Angles, Webs, Brackets and Clips at FR74
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 358 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 003

STGR4
STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11 AD

STGR12 STGR3 STGR2

FR74 

### AFTER

LH SHOWN RH SYMMETRICAL VIEW LOOKING FWD

53 54 55 LH RH 51 52 LH RH 56 57 LH RH 58 59 LH RH 60 61 LH RH

62 63 LH RH 64 65 LH RH 68 69 LH RH 66 67 LH RH 72 73 LH RH 74 75 LH RH 78 79 LH RH 80 81 LH RH 86 87 LH RH 88 89 LH RH 90 91 LH RH 100

92 93 LH RH

70 71 LH RH 76 77 LH RH 84 85 LH RH 82 83 LH RH 94 95 LH RH 98 99 LH RH 96 97 LH RH F W D FR74 STGR



## B B

B B TYPICAL FOR STGR1 (AD) AND STGR4

−STGR11 48

FOR FASTENER SYMBOLS, REFER TO FIG. N_SB_531266_6_BDAD SHEET 1 NOTE: 

## G J
H

K

L F W D STGR4

STGR5 STGR6 STGR7

FR74

F W D AD

FR74



## H J

N_SB_531266_6_BCAD_03_01 Figure A-GBCAD - Sheet 03 Removal/Installation of Angles, Webs, Brackets and Clips at FR74
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 359 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 003

FWD

FOR FASTENER SYMBOLS, REFER TO FIG. N_SB_531266_6_BDAD SHEET 1 NOTE: F W D STGR12

FR74 

## K

L STGR7

STGR8

STGR9

STGR10

STGR11

STGR12 FR74

N_SB_531266_6_BCAD_04_00 Figure A-GBCAD - Sheet 04 Removal/Installation of Angles, Webs, Brackets and Clips at FR74
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 360 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 004

STGR4
STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11 AD

STGR12 STGR3 STGR2

FR74 

### BEFORE

LH SHOWN RH SYMMETRICAL VIEW LOOKING FWD

(53) (54) (55) LH RH (51) (52) LH RH (56) (57) LH RH (58) (59) LH RH (60) (61) LH RH

(62) (63) LH RH

(64) (65) LH RH (68) (69) LH RH (66) (67) LH RH (72) (73) LH RH (74) (75) LH RH (78) (79) LH RH (80) (81) LH RH (86) (87) LH RH (88) (89) LH RH (90) (91) LH RH (48) (100)

(94) (95) LH RH

(70) (71) LH RH (76) (77) LH RH (84) (85) LH RH (82) (83) LH RH (98) (99) LH RH (96) (97) LH RH (92) (93) LH RH



## B A Z310

FR72 FR74

FR77

FR70 

## A

REMOVE AND DISCARD EXSISTING FASTENERS FASTENER TABLE F W D STGR4 STGR5 STGR6 STGR7

FR74

F W D FR74 STGR



## A A C A

A C D

E

TYPICAL FOR STGR1 (AD) AND STGR4

−STGR11 

### F B G

N_SB_531266_6_BCAE_01_00 Figure A-GBCAE - Sheet 01 Removal/Installation of Angles, Webs, Brackets and Clips at FR74
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 361 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 004

FWD STGR7

STGR8

STGR9

STGR10

STGR11

STGR12 FR74

REMOVE AND DISCARD EXSISTING FASTENERS FASTENER TABLE F W D AD

FR74



## D

E F W D STGR12



## F FR74

N_SB_531266_6_BCAE_02_00 Figure A-GBCAE - Sheet 02 Removal/Installation of Angles, Webs, Brackets and Clips at FR74
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 362 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 004

STGR4
STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11 AD

STGR12 STGR3 STGR2

FR74 

### AFTER

LH SHOWN RH SYMMETRICAL VIEW LOOKING FWD

53 54 55 LH RH 51 52 LH RH 56 57 LH RH 58 59 LH RH 60 61 LH RH

62 63 LH RH 64 65 LH RH 68 69 LH RH 66 67 LH RH 72 73 LH RH 74 75 LH RH 78 79 LH RH 80 81 LH RH 86 87 LH RH 88 89 LH RH 90 91 LH RH 100

92 93 LH RH

70 71 LH RH 76 77 LH RH 84 85 LH RH 82 83 LH RH 94 95 LH RH 98 99 LH RH 96 97 LH RH

F W D AD

FR74

F W D STGR4

STGR5 STGR6 STGR7

FR74 F W D FR74 STGR



## B B

B B TYPICAL FOR STGR1 (AD) AND STGR4

−STGR11 48

FOR FASTENER SYMBOLS, REFER TO FIG. N_SB_531266_6_BDAE SHEET 1 NOTE: 

## G

H J J
H

K

L
N_SB_531266_6_BCAE_03_00 Figure A-GBCAE - Sheet 03 Removal/Installation of Angles, Webs, Brackets and Clips at FR74
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 363 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 004

FWD STGR7

STGR8

STGR9

STGR10

STGR11

STGR12 FR74

FOR FASTENER SYMBOLS, REFER TO FIG. N_SB_531266_6_BDAE SHEET 1 NOTE: F W D STGR12

FR74 

## K

L

N_SB_531266_6_BCAE_04_00 Figure A-GBCAE - Sheet 04 Removal/Installation of Angles, Webs, Brackets and Clips at FR74
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 364 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

ITEM PART NUMBER DESCRIPTION DAN5

−6

−4X PIN, HI

−LOK COLLAR, HI

−LOK DAN11

−6X 102 103 DAN5

−6

−5X DAN11

−6X 104 103 DAN5

−6

−6X DAN11

−6X 105 103

EN6081D5

−06 RIVET 106 DAN5

−6

−5 NSA5075

−6 107 108 DAN5

−5

−6 NSA5075

−5 109 110 DAN5

−5

−5 NSA5075

−5 111 110 DAN5

−6

−6 NSA5075

−6 112 108 DAN5

−6

−3X DAN11

−6X 113 103 DAN5

−8

−5X DAN11

−8X 114 115 DAN5

−8

−4X DAN11

−8X 116 115 DAN5

−8

−7X DAN11

−8X 117 115 DAN5

−8

−8X DAN11

−8X 118 115 DAN6

−6

−3X DAN11

−6X 119 103 DAN6

−6

−4X DAN11

−6X 120 103 DAN6

−6

−5X DAN11

−6X 121 103 EN6069D5

−06 RIVET 122

DAN6

−8

−6X DAN11

−8X 123 115 DAN6

−6

−7X DAN11

−6X 124 103 DAN6

−6

−7 NSA5075

−6 125 108 DAN6

−6

−6 NSA5075

−6 126 108 DAN6

−6

−5 NSA5075

−6 127 108 DAN6

−6

−3 NSA5075

−6 128 108 DAN5

−6

−3 NSA5075

−6 129 108 DAN5

−6

−7X DAN11

−6X 130 103 DAN5

−8

−6X DAN11

−8X 131 115 DAN6

−6

−6X DAN11

−6X 132 103

EN6081D5

−07 RIVET 135 EN6069D5

−07 RIVET 136 EN6069D5

−08 RIVET 137 FINAL HOLE DIAMETER MIN MAX HOLE SYMBOL 5.113 mm (0.201 in) 5.152 mm (0.203 in) PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK 5.113 mm (0.201 in) 5.152 mm (0.203 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in)

4.060 mm (0.160 in) 4.170 mm (0.164 in) 4.125 mm (0.162 in) 4.160 mm (0.164 in) 4.125 mm (0.162 in) 4.160 mm (0.164 in)

5.113 mm (0.201 in) 5.152 mm (0.203 in) 6.706 mm (0.264 in) 6.747 mm (0.266 in) 6.706 mm (0.264 in) 6.747 mm (0.266 in) 6.706 mm (0.264 in) 6.747 mm (0.266 in) 6.706 mm (0.264 in) 6.747 mm (0.266 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in)

5.113 mm (0.201 in) 5.152 mm (0.203 in) 4.780 mm (0.188 in) 4.821 mm (0.190 in) 4.780 mm (0.188 in) 4.821 mm (0.190 in) 4.780 mm (0.188 in) 4.821 mm (0.190 in) 4.780 mm (0.188 in) 4.821 mm (0.190 in)

5.113 mm (0.201 in) 5.152 mm (0.203 in) 6.706 mm (0.264 in) 6.747 mm (0.266 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in) ITEM PART NUMBER DESCRIPTION FINAL HOLE DIAMETER MIN MAX HOLE SYMBOL

6.706 mm (0.264 in) 6.747 mm (0.266 in) MIN PITCH MIN EDGE MARGIN MIN PITCH MIN EDGE MARGIN

15.600 mm (0.614 in) 8.000 mm (0.315 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in)

15.600 mm (0.614 in) 8.000 mm (0.315 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in)

16.600 mm (0.653 in) 9.600 mm (0.378 in)

16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in)

16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in)

21.800 mm (0.858 in) 12.800 mm (0.504 in) 21.800 mm (0.858 in) 12.800 mm (0.504 in) 21.800 mm (0.858 in) 12.800 mm (0.504 in) 21.800 mm (0.858 in) 12.800 mm (0.504 in)

21.800 mm (0.858 in) 12.800 mm (0.504 in)

NOTE: UNLESS OTHERWISE STATED

− MINIMUM EDGE DISTANCE HAVE TO BE ACHIEVED FOR INSTALLATION OF CLIPS, SHEAR WEBS AND ANGLES. 4.060 mm (0.160 in) 4.170 mm (0.164 in) 4.060 mm (0.160 in) 4.170 mm (0.164 in) 4.060 mm (0.160 in) 4.170 mm (0.164 in) 4.060 mm (0.160 in) 4.170 mm (0.164 in) DAN6

−5

−7 NSA5075

−5 DAN7

−6

−11X

DAN12

−6X DAN5

−6

−10X

DAN11

−6X DAN5

−6

−8X DAN11

−6X PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK 5.113 mm (0.201 in) 5.152 mm (0.203 in)

5.113 mm (0.201 in) 5.152 mm (0.203 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 4.780 mm (0.188 in) 4.821 mm (0.190 in) 4.780 mm (0.188 in) 4.821 mm (0.190 in)

4.780 mm (0.188 in) 4.821 mm (0.190 in)

133 110 144 145 146 103 148 103 4.125 mm (0.162 in) 4.160 mm (0.164 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in)

5.113 mm (0.201 in) 5.152 mm (0.203 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 21.800 mm (0.858 in) 12.800 mm (0.504 in)

N_SB_531266_6_BDAA_01_05 Figure A-GBDAA - Sheet 01 Fastener Symbol Identification
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 365 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002

ITEM PART NUMBER DESCRIPTION DAN5

−6

−4X PIN, HI

−LOK COLLAR, HI

−LOK DAN11

−6X 102 103 DAN5

−6

−5X DAN11

−6X 104 103 DAN5

−6

−6X DAN11

−6X 105 103

EN6081D5

−06 RIVET 106 DAN5

−6

−6 NSA5075

−6 109 110 DAN5

−6

−5 NSA5075

−6 111 110 DAN6

−6

−5 NSA5075

−6 112 110 DAN5

−6

−3X DAN11

−6X 113 103 DAN5

−8

−5X DAN11

−8X 114 115 DAN5

−8

−4X DAN11

−8X 116 115 DAN5

−8

−7X DAN11

−8X 117 115 DAN5

−8

−8X DAN11

−8X 118 115 DAN6

−6

−3X DAN11

−6X 119 103 DAN6

−6

−4X DAN11

−6X 120 103 DAN6

−6

−5Y NSA5330

−6 121 108 EN6069D5

−06 RIVET 122 DAN6

−8

−6X DAN11

−8X 123 115 DAN6

−6

−6Y NSA5330

−6 124 108 DAN6

−6

−7X DAN11

−6X 125 103 DAN6

−6

−6 NSA5075

−6 126 110 DAN6

−6

−5X DAN11

−6X 127 103 DAN6

−6

−3 NSA5075

−6 128 110 DAN5

−6

−3 NSA5075

−6 129 110 DAN5

−6

−7X DAN11

−6X 130 103 DAN5

−8

−6X DAN11

−8X 131 115 DAN6

−6

−6X DAN11

−6X 132 103

EN6081D5

−07 RIVET 135 FINAL HOLE DIAMETER MIN MAX HOLE SYMBOL 5.113 mm (0.201 in) 5.152 mm (0.203 in) PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK 5.113 mm (0.201 in) 5.152 mm (0.203 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in)

4.060 mm (0.160 in) 4.170 mm (0.164 in) 4.780 mm (0.188 in) 4.821 mm (0.190 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in) 6.706 mm (0.264 in) 6.747 mm (0.266 in) 6.706 mm (0.264 in) 6.747 mm (0.266 in) 6.706 mm (0.264 in) 6.747 mm (0.266 in) 6.706 mm (0.264 in) 6.747 mm (0.266 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in) 5.509 mm (0.217 in) 5.549 mm (0.219 in) 4.060 mm (0.160 in) 4.170 mm (0.164 in)

5.509 mm (0.217 in) 5.549 mm (0.219 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in) 4.780 mm (0.188 in) 4.821 mm (0.190 in)

4.780 mm (0.188 in) 4.821 mm (0.190 in)

5.113 mm (0.201 in) 5.152 mm (0.203 in) 6.706 mm (0.264 in) 6.747 mm (0.266 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in)

4.060 mm (0.160 in) 4.170 mm (0.164 in) ITEM PART NUMBER DESCRIPTION FINAL HOLE DIAMETER MIN MAX HOLE SYMBOL

6.706 mm (0.264 in) 6.747 mm (0.266 in) MIN PITCH MIN EDGE MARGIN MIN PITCH MIN EDGE MARGIN

15.600 mm (0.614 in) 8.000 mm (0.315 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in)

16.600 mm (0.653 in) 9.600 mm (0.378 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in)

16.600 mm (0.653 in) 9.600 mm (0.378 in)

17.900 mm (0.705 in) 10.200 mm (0.402 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in)

17.900 mm (0.705 in) 10.200 mm (0.402 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in)

21.800 mm (0.858 in) 12.800 mm (0.504 in) 21.800 mm (0.858 in) 12.800 mm (0.504 in) 21.800 mm (0.858 in) 12.800 mm (0.504 in) 21.800 mm (0.858 in) 12.800 mm (0.504 in)

21.800 mm (0.858 in) 12.800 mm (0.504 in)

NOTE: UNLESS OTHERWISE STATED

− MINIMUM EDGE DISTANCE HAVE TO BE ACHIEVED FOR INSTALLATION OF CLIPS, SHEAR WEBS AND ANGLES. 5.113 mm (0.201 in) 5.152 mm (0.203 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in)

EN6069D5

−07 RIVET 136 EN6069D5

−08 RIVET 137 4.060 mm (0.160 in) 4.170 mm (0.164 in) 4.060 mm (0.160 in) 4.170 mm (0.164 in) DAN6

−5

−7 NSA5075

−5

DAN7

−6

−11X

DAN12

−6X DAN5

−6

−10X

DAN11

−6X DAN5

−6

−8X DAN11

−6X PIN, HI

−LOK COLLAR, HI

−LOK
PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK 5.113 mm (0.201 in) 5.152 mm (0.203 in)

5.113 mm (0.201 in) 5.152 mm (0.203 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 133

144 145 146 148 4.125 mm (0.162 in) 4.160 mm (0.164 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in)

5.113 mm (0.201 in) 5.152 mm (0.203 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 4.780 mm (0.188 in) 4.821 mm (0.190 in) 4.780 mm (0.188 in) 4.821 mm (0.190 in) 4.780 mm (0.188 in) 4.821 mm (0.190 in)

160

103 103 DAN6

−6

−7 NSA5075

−6 PIN, HI

−LOK COLLAR, HI

−LOK 4.780 mm (0.188 in) 4.821 mm (0.190 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in) 134 110 21.800 mm (0.858 in) 12.800 mm (0.504 in)

N_SB_531266_6_BDAB_01_02 Figure A-GBDAB - Sheet 01 Fastener Symbol Identification
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 366 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 003

ITEM PART NUMBER DESCRIPTION DAN5

−6

−4X PIN, HI

−LOK COLLAR, HI

−LOK DAN11

−6X 102 103 DAN5

−6

−5X DAN11

−6X 104 103 DAN5

−6

−6X DAN11

−6X 105 103

EN6081D5

−06 RIVET 106 DAN5

−5

−6 NSA5075

−5 109 160 DAN5

−5

−5 NSA5075

−5 111 160

DAN6

−6

−5 NSA5075

−6 127 108 DAN5

−6

−3X DAN11

−6X 113 103 DAN5

−8

−5X DAN11

−8X 114 115 DAN5

−8

−4X DAN11

−8X 116 115 DAN5

−8

−7X DAN11

−8X 117 115 DAN5

−8

−8X DAN11

−8X 118 115 DAN6

−6

−3X DAN11

−6X 119 103 DAN6

−6

−4X DAN11

−6X 120 103 DAN6

−8

−6X DAN11

−8X 123 115 DAN6

−6

−7X DAN11

−6X 125 103 DAN6

−6

−6 NSA5075

−6 126 108 DAN6

−6

−5X DAN11

−6X 121 103 DAN6

−6

−3 NSA5075

−6 128 108 DAN5

−6

−3 NSA5075

−6 129 108 DAN5

−6

−7X DAN11

−6X 130 103 DAN5

−8

−6X DAN11

−8X 131 115 DAN6

−6

−6X DAN11

−6X 132 103

EN6081D5

−07 RIVET 135 FINAL HOLE DIAMETER MIN MAX HOLE SYMBOL 5.113 mm (0.201 in) 5.152 mm (0.203 in) PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK
PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK
PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK 5.113 mm (0.201 in) 5.152 mm (0.203 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in)

4.060 mm (0.160 in) 4.170 mm (0.164 in) 4.780 mm (0.188 in) 4.821 mm (0.190 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in) 6.706 mm (0.264 in) 6.747 mm (0.266 in) 6.706 mm (0.264 in) 6.747 mm (0.266 in) 6.706 mm (0.264 in) 6.747 mm (0.266 in) 6.706 mm (0.264 in) 6.747 mm (0.266 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in)

5.113 mm (0.201 in) 5.152 mm (0.203 in) 4.780 mm (0.188 in) 4.821 mm (0.190 in)

4.780 mm (0.188 in) 4.821 mm (0.190 in)

5.113 mm (0.201 in) 5.152 mm (0.203 in) 6.706 mm (0.264 in) 6.747 mm (0.266 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in)

4.060 mm (0.160 in) 4.170 mm (0.164 in) ITEM PART NUMBER DESCRIPTION FINAL HOLE DIAMETER MIN MAX HOLE SYMBOL

6.706 mm (0.264 in) 6.747 mm (0.266 in) MIN PITCH MIN EDGE MARGIN MIN PITCH MIN EDGE MARGIN

15.600 mm (0.614 in) 8.000 mm (0.315 in)

15.600 mm (0.614 in) 8.000 mm (0.315 in)

16.600 mm (0.653 in) 9.600 mm (0.378 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in)

16.600 mm (0.653 in) 9.600 mm (0.378 in)

16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in)

21.800 mm (0.858 in) 12.800 mm (0.504 in) 21.800 mm (0.858 in) 12.800 mm (0.504 in) 21.800 mm (0.858 in) 12.800 mm (0.504 in) 21.800 mm (0.858 in) 12.800 mm (0.504 in)

21.800 mm (0.858 in) 12.800 mm (0.504 in)

NOTE: UNLESS OTHERWISE STATED

− MINIMUM EDGE DISTANCE HAVE TO BE ACHIEVED FOR INSTALLATION OF CLIPS, SHEAR WEBS AND ANGLES. 5.113 mm (0.201 in) 5.152 mm (0.203 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in)

EN6069D5

−08 RIVET 137 4.060 mm (0.160 in) 4.170 mm (0.164 in) DAN7

−6

−11X

DAN12

−6X DAN5

−6

−10X

DAN11

−6X DAN5

−6

−8X DAN11

−6X PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK 5.113 mm (0.201 in) 5.152 mm (0.203 in)

5.113 mm (0.201 in) 5.152 mm (0.203 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 144 145 146 148 5.113 mm (0.201 in) 5.152 mm (0.203 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 4.780 mm (0.188 in) 4.821 mm (0.190 in) 4.125 mm (0.162 in) 4.160 mm (0.164 in)

103 103 DAN6

−6

−7 NSA5075

−6 PIN, HI

−LOK COLLAR, HI

−LOK 4.780 mm (0.188 in) 4.821 mm (0.190 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in) 134 108 15.600 mm (0.614 in) 8.000 mm (0.315 in) 4.125 mm (0.162 in) 4.160 mm (0.164 in) DAN5

−6

−5 NSA5075

−6 107 108 PIN, HI

−LOK COLLAR, HI

−LOK

DAN5

−6

−6 NSA5075

−6 112 108 PIN, HI

−LOK COLLAR, HI

−LOK 4.780 mm (0.188 in) 4.821 mm (0.190 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in)

4.780 mm (0.188 in) 4.821 mm (0.190 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in) 21.800 mm (0.858 in) 12.800 mm (0.504 in)

N_SB_531266_6_BDAD_01_02 Figure A-GBDAD - Sheet 01 Fastener Symbol Identification
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 367 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 004

ITEM PART NUMBER DESCRIPTION DAN5

−6

−4X PIN, HI

−LOK COLLAR, HI

−LOK DAN11

−6X 102 103 DAN5

−6

−5X DAN11

−6X 104 103 DAN5

−6

−6X DAN11

−6X 105 103

EN6081D5

−06 RIVET 106 DAN5

−6

−5 NSA5075

−6 107 108 DAN5

−5

−6 NSA5075

−5 109 110 DAN5

−5

−5 NSA5075

−5 111 110 DAN5

−6

−6 NSA5075

−6 112 108 DAN5

−6

−3X DAN11

−6X 113 103 DAN5

−8

−5X DAN11

−8X 114 115 DAN5

−8

−4X DAN11

−8X 116 115 DAN5

−8

−7X DAN11

−8X 117 115 DAN5

−8

−8X DAN11

−8X 118 115 DAN6

−6

−3X DAN11

−6X 119 103 DAN6

−6

−4X DAN11

−6X 120 103 DAN6

−6

−5X DAN11

−6X 121 103 EN6069D5

−06 RIVET 122

DAN6

−8

−6X DAN11

−8X 123 115 DAN6

−6

−7X DAN11

−6X 124 103 DAN6

−6

−7 NSA5075

−6 125 108 DAN6

−6

−6 NSA5075

−6 126 108 DAN6

−6

−5 NSA5075

−6 127 108 DAN6

−6

−3 NSA5075

−6 128 108 DAN5

−6

−3 NSA5075

−6 129 108 DAN5

−6

−7X DAN11

−6X 130 103 DAN5

−8

−6X DAN11

−8X 131 115 DAN6

−6

−6X DAN11

−6X 132 103

EN6081D5

−08 RIVET 135 EN6069D5

−07 RIVET 136 EN6069D5

−08 RIVET 137 FINAL HOLE DIAMETER MIN MAX HOLE SYMBOL 5.113 mm (0.201 in) 5.152 mm (0.203 in) PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK 5.113 mm (0.201 in) 5.152 mm (0.203 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in)

4.060 mm (0.160 in) 4.170 mm (0.164 in) 4.125 mm (0.162 in) 4.160 mm (0.164 in) 4.125 mm (0.162 in) 4.160 mm (0.164 in)

5.113 mm (0.201 in) 5.152 mm (0.203 in) 6.706 mm (0.264 in) 6.747 mm (0.266 in) 6.706 mm (0.264 in) 6.747 mm (0.266 in) 6.706 mm (0.264 in) 6.747 mm (0.266 in) 6.706 mm (0.264 in) 6.747 mm (0.266 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in)

5.113 mm (0.201 in) 5.152 mm (0.203 in) 4.780 mm (0.188 in) 4.821 mm (0.190 in) 4.780 mm (0.188 in) 4.821 mm (0.190 in) 4.780 mm (0.188 in) 4.821 mm (0.190 in) 4.780 mm (0.188 in) 4.821 mm (0.190 in)

5.113 mm (0.201 in) 5.152 mm (0.203 in) 6.706 mm (0.264 in) 6.747 mm (0.266 in) 5.113 mm (0.201 in) 5.152 mm (0.203 in) ITEM PART NUMBER DESCRIPTION FINAL HOLE DIAMETER MIN MAX HOLE SYMBOL

6.706 mm (0.264 in) 6.747 mm (0.266 in) MIN PITCH MIN EDGE MARGIN MIN PITCH MIN EDGE MARGIN

15.600 mm (0.614 in) 8.000 mm (0.315 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in)

15.600 mm (0.614 in) 8.000 mm (0.315 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in) 15.600 mm (0.614 in) 8.000 mm (0.315 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in)

16.600 mm (0.653 in) 9.600 mm (0.378 in)

16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in)

16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 21.800 mm (0.858 in) 12.800 mm (0.504 in)

21.800 mm (0.858 in) 12.800 mm (0.504 in) 21.800 mm (0.858 in) 12.800 mm (0.504 in) 21.800 mm (0.858 in) 12.800 mm (0.504 in) 21.800 mm (0.858 in) 12.800 mm (0.504 in)

21.800 mm (0.858 in) 12.800 mm (0.504 in)

NOTE: UNLESS OTHERWISE STATED

− MINIMUM EDGE DISTANCE HAVE TO BE ACHIEVED FOR INSTALLATION OF CLIPS, SHEAR WEBS AND ANGLES. 4.060 mm (0.160 in) 4.170 mm (0.164 in) 4.060 mm (0.160 in) 4.170 mm (0.164 in) 4.060 mm (0.160 in) 4.170 mm (0.164 in) 4.060 mm (0.160 in) 4.170 mm (0.164 in) DAN7

−6

−11X

DAN12

−6X DAN5

−6

−10X

DAN11

−6X DAN5

−6

−8X DAN11

−6X PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK PIN, HI

−LOK COLLAR, HI

−LOK 5.113 mm (0.201 in) 5.152 mm (0.203 in)

5.113 mm (0.201 in) 5.152 mm (0.203 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in) 4.780 mm (0.188 in) 4.821 mm (0.190 in) 4.780 mm (0.188 in) 4.821 mm (0.190 in)

4.780 mm (0.188 in) 4.821 mm (0.190 in)

144 145 146 103 148 103 5.113 mm (0.201 in) 5.152 mm (0.203 in) 16.600 mm (0.653 in) 9.600 mm (0.378 in)

N_SB_531266_6_BDAE_01_01 Figure A-GBDAE - Sheet 01 Fastener Symbol Identification
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 368 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN Appendix 01: Elapsed Time Assumption
**CONF ALL

ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A320−53−1266

GET ACCESS MH ET/S STEPS

3.00 1.50 13.00 13.00 16.00 16.00

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 1 1

: : IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS ARE NOT REFLECTED IN THIS GANTT CHART. SB ELAPSED TIME (HOURS) SB ELAPSED TIME 110.00 106.00 110 100 90 80 70 60 50 40 30 20 10 REMOVE THE ANGLES, WEBS, BRACKETS LH AND STGR1, RH STGR13, LH AND STGR1, RH INSTALL THE ANGLES, WEBS, BRACKETS AND CLIPS AT FRAME 72, BETWEEN STGR1, RH AND STGR13, LH REMOVE THE ANGLES, WEBS, BRACKETS AND CLIPS AT FRAME 72, BETWEEN STGR13, RH AND STGR3, RH INSTALL THE ANGLES, WEBS, BRACKETS AND CLIPS AT FRAME 72, BETWEEN STGR3, RH TO STGR13, RH REMOVE THE ANGLES, WEBS, BRACKETS AND CLIPS AT FRAME 74, BETWEEN STGR12, LH AND STGR1, RH

TEST CLOSE

−UP INSTALL THE ANGLES, WEBS, BRACKETS AND CLIPS AT FRAME 74, BETWEEN STGR1, RH AND STGR12, LH REMOVE THE ANGLES, WEBS, BRACKETS AND CLIPS AT FRAME 74, BETWEEN STGR12, RH AND STGR3, RH INSTALL THE ANGLES, WEBS, BRACKETS AND CLIPS AT FRAME 74, BETWEEN STGR3, RH AND STGR12, RH 11.00 11.00 1 14.00 14.00 1 11.00 11.00 1 14.00 14.00 1 11.00 11.00 1 12.00 12.00 1 1.00 0.50 2 4.00 2.00 2

TOTAL MANHOURS 0

N_SB_531266_6_AAAA_01_00 Figure A-GAAAA - Sheet 01 Gantt Chart
DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 1 6

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

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

### TITLE: FUSELAGE - CONE/REAR FUSELAGE - REPLACE CLIPS, SHEARWEBS AND ANGLES IN SECTION 19 AT FR 72 AND FR 74 MODIFICATION No.: 153833K16120 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 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 1 6

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

# @A318/A319/A320/A321 SERVICE BULLETIN QUALITY PERCEPTION FORM Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data that you provide us will be used to analyse areas of difficulties and to take corrective action to further improve the quality of our Service Bulletins. We thank you for the time you have taken in completing this form. (Please rate on a scale of 1 to 4, with 4 being the highest score) - Quality rating of this SB 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 11/13 SERVICE BULLETIN No.: A320-53-1266 REVISION No.: 03 - May 07/15 Page: 1 6

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