# @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



# MANDATORYMANDATORYMANDATORY ATA SYSTEM: 57 

### TITLE: WING - CENTER WING - INSPECTION OF THE LOWER RIBS AT FR36 JUNCTION MODIFICATION No.: None This page transmits Revision No.01 of Service Bulletin No.A320-57-1175 ADDITIONAL WORK **CONF ALL Additional work is required by this revision for aircraft modified by any previous issue and on which: - the removal of the shims and fasteners in inspected area has not been done, - the HFEC inspection of the radius of the rib flanges has not been done, - the rototest inspection has not been done. The additional work consist in: - the removal of the shims and fasteners in inspected area, - the HFEC inspection of the radius of the rib flanges, - the rototest inspection. REASON Revision No. 01 issued to incorporate changes found necessary and carried out during the accomplishment of this Service Bulletin on aircraft with Manufacturer Serial Number (MSN) 0078. This Service Bulletin has been validated at original issue on A320 aircraft with Manufacturer Serial Number (MSN) 0078. Aircraft with Manufacturer Serial Number (MSN) 0078 complies fully with the requirements of the current issue of the Service Bulletin. CHANGES The main changes of this revision are: DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 1 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN REVISION TRANSMITTAL SHEET - add the removal of the shim for the special detailed inspection, - create supplementary tasks ADDITIONAL WORK. SUMMARY GENERAL EVALUATION GENERAL EVALUATION TABLE UPDATED R MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE UPDATED R MATERIAL PRICE INFORMATION TABLE UPDATED R EFFECTIVITY OPERATOR LIST UPDATED R MANPOWER MANPOWER UPDATED R MANPOWER UPDATED R APPENDICES APPENDICES UPDATED R PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R Configuration definition CONF 001 CONFIGURATION DEFINITION UPDATED R Material Effectivity MATERIAL EFFECTIVITY UPDATED MATERIAL SET UPDATED MATERIAL SET QUANTITY UPDATED R
MATERIAL EFFECTIVITY UPDATED MATERIAL SET UPDATED MATERIAL SET QUANTITY UPDATED R
COMPLIANCE Classification CLASSIFICATION UPDATED R Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED CONFIGURATION UPDATED R Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED CONFIGURATION UPDATED R MANPOWER MANPOWER UPDATED CONFIGURATION UPDATED R MANPOWER UPDATED CONFIGURATION UPDATED R REFERENCES REFERENCED DOCUMENTATION UPDATED R REFERENCED DOCUMENTATION UPDATED R PUBLICATION AFFECTED PUBLICATIONS AFFECTED UPDATED R MATERIAL INFORMATION MATERIAL - PRICE AND AVAILABILITY Procurement Addresses PROCUREMENT ADDRESSES UPDATED MATERIAL SET UPDATED R Price and Availability PRICE AND AVAILABILITY UPDATED MATERIAL AVAILABILITY UPDATED MATERIAL PRICE UPDATED MATERIAL SET UPDATED R

LIST OF COMPONENTS LIST OF COMPONENTS UPDATED R Kit 571175A01R00 PART MATERIAL SET ADDED N
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 2 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Kit 571175A02R00 PART MATERIAL SET ADDED N LIST OF MATERIALS - OPERATOR SUPPLIED Consumable Materials Consumable CMLA01 CONSUMABLE MATERIAL SET UPDATED QUANTITY UPDATED CONSUMABLE UPDATED R Components COMPONENTS UPDATED R Component COMPA01 PART MATERIAL SET DELETED D Component COMPA02 PART MATERIAL SET DELETED D TOOLING TOOLING UPDATED R Tooling - Price and Availability TOOLING - PRICE AND AVAILABILITY PARAGRAPH ADDED N Tools TOOLS PARAGRAPH ADDED N Special Tools SPECIAL TOOLS PARAGRAPH ADDED N Kit tool 571175T01R00 TOOL MATERIAL SET ADDED N ACCOMPLISHMENT INSTRUCTIONS TASK 571175- 832-801-001-Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 TASK SOLUTION UPDATED TASK TITLE UPDATED CAUTION UPDATED NOTE UPDATED R

Task associated data - 001 ZONE UPDATED PANEL UPDATED MAN HOURS UPDATED ELAPSED TIME UPDATED R

Task associated data - 002 ZONE UPDATED PANEL UPDATED MAN HOURS UPDATED ELAPSED TIME UPDATED R

Subtask 571175-910-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R
Subtask 571175-910-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R
Subtask 571175-941-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED NOTE UPDATED REFERENCES UPDATED R

Subtask 571175-010-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED PANEL UPDATED REFERENCES UPDATED R

Subtask 571175-941-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED NOTE UPDATED REFERENCES UPDATED R

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 3 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Subtask 571175-010-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED PANEL UPDATED REFERENCES UPDATED R

Subtask 571175-000-003-001 SUBTASK SOLUTION ADDED N Subtask 571175-832-001-001 SUBTASK SOLUTION UPDATED PANEL UPDATED ZONE UPDATED REFERENCED DOCUMENTATION UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED CONSUMABLE UPDATED QUANTITY UPDATED ITEM NUMBER UPDATED PART NUMBER DESCRIPTION UPDATED NOTE UPDATED LOCATION UPDATED MANPOWER RESSOURCE UPDATED REFERENCES UPDATED R

Subtask 571175-831-005-001 SUBTASK SOLUTION ADDED N Subtask 571175-831-006-001 SUBTASK SOLUTION ADDED N Subtask 571175-400-003-001 SUBTASK SOLUTION ADDED N Subtask 571175-000-003-002 SUBTASK SOLUTION ADDED N Subtask 571175-832-001-002 SUBTASK SOLUTION UPDATED PANEL UPDATED ZONE UPDATED QUANTITY UPDATED REFERENCED DOCUMENTATION UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED CONSUMABLE UPDATED ITEM NUMBER UPDATED PART NUMBER DESCRIPTION UPDATED NOTE UPDATED LOCATION UPDATED MANPOWER RESSOURCE UPDATED MATERIAL LIST UPDATED REFERENCES UPDATED R

Subtask 571175-831-005-002 SUBTASK SOLUTION ADDED N Subtask 571175-831-006-002 SUBTASK SOLUTION ADDED N Subtask 571175-400-003-002 SUBTASK SOLUTION ADDED N Subtask 571175-700-001-001 SUBTASK SOLUTION UPDATED CONFIGURATION UPDATED NOTE UPDATED R
Subtask 571175-700-001-001 SUBTASK SOLUTION UPDATED CONFIGURATION UPDATED NOTE UPDATED R

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 4 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN REVISION TRANSMITTAL SHEET
Subtask 571175-942-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED NOTE UPDATED CONFIGURATION UPDATED PANEL UPDATED REFERENCES UPDATED R

Subtask 571175-942-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED NOTE UPDATED CONFIGURATION UPDATED PANEL UPDATED REFERENCES UPDATED R

TASK 571175- 832-802-001-Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 for ADDITIONAL WORK TASK SOLUTION ADDED N

Task associated data - 001 TASK ASSOCIATED DATA ADDED N Task associated data - 002 TASK ASSOCIATED DATA ADDED N Subtask 571175-910-003-001 SUBTASK SOLUTION ADDED N Subtask 571175-839-003-001 SUBTASK SOLUTION ADDED N Subtask 571175-910-003-001 SUBTASK SOLUTION ADDED N Subtask 571175-839-003-001 SUBTASK SOLUTION ADDED N Subtask 571175-941-003-001 SUBTASK SOLUTION ADDED N Subtask 571175-010-003-001 SUBTASK SOLUTION ADDED N Subtask 571175-941-003-001 SUBTASK SOLUTION ADDED N Subtask 571175-010-003-001 SUBTASK SOLUTION ADDED N Subtask 571175-000-004-001 SUBTASK SOLUTION ADDED N Subtask 571175-832-003-001 SUBTASK SOLUTION ADDED N Subtask 571175-831-007-001 SUBTASK SOLUTION ADDED N Subtask 571175-831-008-001 SUBTASK SOLUTION ADDED N Subtask 571175-400-004-001 SUBTASK SOLUTION ADDED N Subtask 571175-000-004-002 SUBTASK SOLUTION ADDED N Subtask 571175-832-003-002 SUBTASK SOLUTION ADDED N Subtask 571175-831-007-002 SUBTASK SOLUTION ADDED N Subtask 571175-831-008-002 SUBTASK SOLUTION ADDED N Subtask 571175-400-004-002 SUBTASK SOLUTION ADDED N Subtask 571175-700-003-001 SUBTASK SOLUTION ADDED N Subtask 571175-700-003-001 SUBTASK SOLUTION ADDED N Subtask 571175-942-003-001 SUBTASK SOLUTION ADDED N Subtask 571175-942-003-001 SUBTASK SOLUTION ADDED N TASK 571175-831-801 TASK DELETED FOR APPLICABLE MSN D Fig. A-FBAAA FIGURE SOLUTION UPDATED R Fig. A-FBAAA Sheet 01 SHEET UPDATED R Fig. A-FBAAA Sheet 02 SHEET UPDATED R Fig. A-FBAAA Sheet 03 SHEET ADDED N Fig. A-FBBAA FIGURE SOLUTION UPDATED R Fig. A-FBBAA Sheet 01 SHEET UPDATED R
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 5 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Fig. A-FBBAA Sheet 02 SHEET UPDATED R Fig. A-FBBAB FIGURE SOLUTION ADDED N Fig. A-FBBAB Sheet 01 SHEET ADDED N Fig. A-FBBAB Sheet 02 SHEET ADDED N Fig. A-FBDAA FIGURE SOLUTION ADDED N Fig. A-FBDAA Sheet 01 SHEET ADDED N Fig. A-FBEAA FIGURE SOLUTION ADDED N Fig. A-FBEAA Sheet 01 SHEET ADDED N Fig. A-FBEAA Sheet 02 SHEET ADDED N Fig. A-FBEAB FIGURE SOLUTION ADDED N Fig. A-FBEAB Sheet 01 SHEET ADDED N Fig. A-FBEAB Sheet 02 SHEET ADDED N Fig. A-FBFAA FIGURE SOLUTION ADDED N Fig. A-FBFAA Sheet 01 SHEET ADDED N Fig. A-FBFAB FIGURE SOLUTION ADDED N Fig. A-FBFAB Sheet 01 SHEET ADDED N Fig. A-FBGAA FIGURE SOLUTION ADDED N Fig. A-FBGAA Sheet 01 SHEET ADDED N Fig. A-FBGAA Sheet 02 SHEET ADDED N Fig. A-FBGAB FIGURE SOLUTION ADDED N Fig. A-FBGAB Sheet 01 SHEET ADDED N Fig. A-FBGAB Sheet 02 SHEET ADDED N Fig. A-FBHAA FIGURE SOLUTION ADDED N Fig. A-FBHAA Sheet 01 SHEET ADDED N Fig. A-FBHAA Sheet 02 SHEET ADDED N Fig. A-FBHAB FIGURE SOLUTION ADDED N Fig. A-FBHAB Sheet 01 SHEET ADDED N Fig. A-FBHAB Sheet 02 SHEET ADDED N Fig. A-FBJAA FIGURE SOLUTION ADDED N Fig. A-FBJAA Sheet 01 SHEET ADDED N Fig. A-FBJAB FIGURE SOLUTION ADDED N Fig. A-FBJAB Sheet 01 SHEET ADDED N Fig. A-FBC FIGURE DELETED FOR APPLICABLE MSN D Fig. A-FFAAA Fig. A-FFAAA Sheet 01 SHEET UPDATED R Fig. A-FFBAA FIGURE SOLUTION ADDED N Fig. A-FFBAA Sheet 01 SHEET ADDED N Fig. A-FRAAA FIGURE SOLUTION UPDATED R Fig. A-FRAAA Sheet 01 SHEET UPDATED R Fig. A-FRAAA Sheet 02 SHEET UPDATED R Fig. A-FRAAA Sheet 03 SHEET ADDED N DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 6 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN REVISION TRANSMITTAL SHEET Appendix 01 - Non-Destructive Test Requirements APPENDIX CONTENT APPENDIX CONTENT ADDED N Fig. A-FAAAA FIGURE SOLUTION ADDED N Fig. A-FAAAA Sheet 01 SHEET ADDED N Appendix 02 - Elapsed Time Assumption APPENDIX CONTENT APPENDIX CONTENT ADDED N Fig. A-FABAA FIGURE SOLUTION ADDED N Fig. A-FABAA Sheet 01 SHEET ADDED N FILLING INSTRUCTIONS This Service Bulletin has been generated electronically and is reissued as a complete document. Replace the complete document. Put this Revision Transmittal Sheet in front of the Service Bulletin. HISTORY OF PREVIOUS REVISIONS No previous revision REVISION SEQUENCE ORIGINAL: Oct 24/13 REVISION No. : 01 - May 28/14

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 7 5

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

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

This Page Intentionally Left Blank

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 8 5

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

# @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. 

# MANDATORYMANDATORYMANDATORY ATA SYSTEM: 57 

### TITLE: WING - CENTER WING - INSPECTION OF THE LOWER RIBS AT FR36 JUNCTION **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During Full Scale Fatigue Tests, cracks were found in the Center Wing Box internal lower ribs flange at front spar level. Cracks initiated from vertical fillets of the lower rib flange. To prevent such damages, Modification No. 20908P1283 was embodied on the aircraft in production (Serial modification) from MSN 0085. It consists in installing reinforced lower rib flanges at front spar level (thickness increase). Note that Mod. No. 20976P1355 was embodied on several aircraft in production prior to MSN 0085. It consists in installing shims to reduce unfolding effects of the lower rib flange to avoid crack initiation. For A/C already in service prior to Mod. No. 20908P1283, accomplishment of Service Bulletin A320-57-1013 (Mod. No. 20976P1355) was rendered mandatory. In the frame of the Extended Service Goal exercise based on new fatigue tests, analyses of finding on MSN 0004 dismantling and following fleet utilization evolution, it has been assessed that an additional inspection is necessary for A/C PostMod No. 20976P1355. This Service Bulletin requires the inspection of the lower ribs flange at front spar level. Accomplishment of this Service Bulletin will contribute to maintain the structural integrity of the lower ribs at front spar level junction. GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO POTENTIAL AD YES A/C OPERATION AFFECTED NO DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 1 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN SUMMARY EVALUATION TABLE RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO ETOPS AFFECTED NO STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO BOOKLET AVAILABLE YES VALIDATION ON AIRCRAFT YES NOTE (1): Service Bulletin must be accomplished. NOTE: This Service Bulletin has been validated at original issue on A320 aircraft with Manufacturer Serial Number (MSN) 0078. Aircraft with Manufacturer Serial Number (MSN) 0078 complies fully with the requirements of the current issue of the Service Bulletin. NOTE: A booklet including photographs taken during the validation of this Service Bulletin is available on AIRBUS|World - Maintenance and Engineering - AirN@v engineering (in the concerned SB file). MATERIAL PRICE INFORMATION **CONF 001 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 571175A01R00 1 1,600.00 Pin, Nut Kit tool 571175T01R00 1 See SB Extractor **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 571175A02R00 1 2,010.00 Pin, Nut Kit tool 571175T01R00 1 See SB Extractor EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :

ACA AIC DLH GBB JAV USA CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU None OEB None DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 2 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN SUMMARY AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER **CONF 001 Task 571175-832-801-001: Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 TOTAL MANHOURS 45.00 ELAPSED TIME (HOURS) 31.00 Task 571175-832-802-001: Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 for ADDITIONAL WORK TOTAL MANHOURS 45.00 ELAPSED TIME (HOURS) 31.00 **CONF 002 Task 571175-832-801-001: Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 TOTAL MANHOURS 45.00 ELAPSED TIME (HOURS) 31.00 Task 571175-832-802-001: Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 for ADDITIONAL WORK TOTAL MANHOURS 45.00 ELAPSED TIME (HOURS) 31.00 APPENDICES **CONF ALL Appendix 01 - Non-Destructive Test Requirements Appendix 02 - Elapsed Time Assumption

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 3 5

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

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

**CONF ALL



### A FR36 FR42



## A

**B B** 

AREA TO BE INSPECTED

N_SB_571175_5_SAAA_01_00 Figure A-FSAAA - Sheet 01

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 4 5

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

# @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



# MANDATORYMANDATORYMANDATORY ATA SYSTEM: 57 

### TITLE: WING - CENTER WING - INSPECTION OF THE LOWER RIBS AT FR36 JUNCTION MODIFICATION No.: None This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with any information contained in it. It is delivered on the express condition that said document and the information contained in it shall be treated as confidential, shall not be used for any purpose other than that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall not be duplicated in any manner (except for the purposes of performing the tasks described hereunder and provided that any recipient of such document shall comply with the conditions herein), without AIRBUS prior written consent. 1. PLANNING INFORMATION **CONF ALL A. EFFECTIVITY NOTE: This Service Bulletin is only applicable to aircraft on which Mod. No. 20976P1355 (Service Bulletin No. A320-57-1013) is embodied and on which Mod. No. 20908P1283 is not embodied. (1) Models 320-211 320-231 (2) Effectivity by MSN 0029 0045-0047 0049-0057 0059 0064-0078 0080-0084 (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 ACA 0059 0068 0073 0084 DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 1 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
OPERATOR MSN AIC 0045 0046 0047 0049 0050 0051 0056 0057 0074 0075 0080 DLH 0069 0070 0071 0072 0078 0083 GBB 0067 JAV 0029 USA 0052 0053 0054 0055 0064 0065 0066 0076 0077 0081 0082 (4) Configuration by MSN MSN CONFIGURATION 0029 002 0045 0046 0047 0049 0050 0051 0052 0053 0054 0055 0056 0057 0059 0064 0065 0066 0067 0068 0069 0070 0071 0072 0073 0074 0075 0076 0077 0078 0080 0081 0082 0083 0084 001
(5) Configuration definition **CONF 001 Config. 001 is valid for A320 aircraft on which Mod. No. 20976P1355 is embodied and Service Bulletin No. A320-57-1013 is not accomplished. **CONF 002 Config. 002 is valid for A320 aircraft on which Mod. No. 20976P1355 is not embodied and Service Bulletin No. A320-57-1013 is accomplished. (6) Material Effectivity **CONF 001 MATERIAL QTY PER A/C SEE NOTES Kit 571175A01R00 1 Consumable CMLA01 1 Kit tool 571175T01R00 1 **CONF 002 MATERIAL QTY PER A/C SEE NOTES Kit 571175A02R00 1 Consumable CMLA01 1 Kit tool 571175T01R00 1 **CONF ALL B. CONCURRENT REQUIREMENTS None

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 2 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
C. REASON (1) History During Full Scale Fatigue Tests, cracks were found in the Center Wing Box internal lower ribs flange at front spar level. Cracks initiated from vertical fillets of the lower rib flange. To prevent such damages, Modification No. 20908P1283 was embodied on the aircraft in production (Serial modification) from MSN 0085. It consists in installing reinforced lower rib flanges at front spar level (thickness increase). Note that Mod. No. 20976P1355 was embodied on several aircraft in production prior to MSN 0085. It consists in installing shims to reduce unfolding effects of the lower rib flange to avoid crack initiation. For A/C already in service prior to Mod. No. 20908P1283, accomplishment of Service Bulletin A320-57-1013 (Mod. No. 20976P1355) was rendered mandatory. In the frame of the Extended Service Goal exercise based on new fatigue tests, analyses of finding on MSN 0004 dismantling and following fleet utilization evolution, it has been assessed that an additional inspection is necessary for A/C PostMod No. 20976P1355. (2) Objective/Action This Service Bulletin requires the inspection of the lower ribs flange at front spar level. (3) Advantages Accomplishment of this Service Bulletin will contribute to maintain the structural integrity of the lower ribs at front spar level junction. (4) Operational/Maintenance Consequences None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 571175-832-801-001: Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 (1) Remove the Fasteners and the Shims (2) Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 (3) Oversize the Holes of the Shims, on Bench
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 3 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN (4) Oversize the Holes of the Rib Flanges, on Aircraft (5) Install the Shims with the New Fasteners Task 571175-832-802-001: Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 for ADDITIONAL WORK (1) Remove the Fasteners and the Shims (2) Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 (3) Oversize the Holes of the Shims, on Bench (4) Oversize the Holes of the Rib Flanges, on Aircraft (5) Install the Shims with the New Fasteners **CONF 002 Task 571175-832-801-001: Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 (1) Remove the Fasteners and the Shims (2) Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 (3) Oversize the Holes of the Shims, on Bench (4) Oversize the Holes of the Rib Flanges, on Aircraft (5) Install the Shims with the New Fasteners Task 571175-832-802-001: Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 for ADDITIONAL WORK (1) Remove the Fasteners and the Shims (2) Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 (3) Oversize the Holes of the Shims, on Bench (4) Oversize the Holes of the Rib Flanges, on Aircraft (5) Install the Shims with the New Fasteners

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 4 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
**CONF ALL E. COMPLIANCE (1) Classification MANDATORY: Service Bulletin must be accomplished. (2) Accomplishment Timescale **CONF 001 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. Table 1, Config. 001 - Special detailed inspection of the radius and holes of the rib flanges and HFEC Inspection of the Vertical Stiffener at FR36 Compliance Time (whichever occurs later) Condition Action Threshold (whichever occurs first) Grace Period (whichever occurs first) Repetitive interval (whichever occurs first) All Aircraft Do a special detailed inspection of the radius and holes of the rib flanges and vertical stiffener at FR36, in accordance with TASK 571175-832-801 001 Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 47800FC / 95600FH from first flight 850FC / 1700FH from SB rev00 issue date None

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 5 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN Table 1, Config. 001 - Special detailed inspection of the radius and holes of the rib flanges and HFEC Inspection of the Vertical Stiffener at FR36 Compliance Time (whichever occurs later) Condition Action Threshold (whichever occurs first) Grace Period (whichever occurs first) Repetitive interval (whichever occurs first) Oversize holes and install new fasteners, refer to in accordance with SUBTASK 571175-831-005 001 Oversize the Holes of the Shims, on Bench and SUBTASK 571175-831-006 001 Oversize the Holes of the Rib Flanges, on Aircraft and SUBTASK 571175-400-003 001 Install the Shims with the New Fasteners and Before next flight None None No crack found

Repeat the special detailed inspection of the radius and holes of the rib flanges and vertical stiffener at FR36, in accordance with TASK 571175-832-801 001 Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 (See NOTE*) None None 32500FC / 65000FH

Crack found Contact AIRBUS and follow their instructions Before next flight None None NOTE*: For the repetitive inspections it is not necessary to oversize the holes as the holes are in transition fit.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 6 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN Table 2, Config. 001 - Special detailed inspection of the radius and holes of the rib flanges and HFEC Inspection of the Vertical Stiffener at FR36 for ADDITIONAL WORK Compliance Time (whichever occurs later) Condition Action Threshold (whichever occurs first) Grace Period (whichever occurs first) Repetitive interval (whichever occurs first) All Aircraft Do a special detailed inspection of the radius and holes of the rib flanges and vertical stiffener at FR36, in accordance with TASK 571175-832-802 001 Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 for ADDITIONAL WORK 47800FC / 95600FH from first flight 850FC / 1700FH from SB rev00 issue date None

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 7 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN Table 2, Config. 001 - Special detailed inspection of the radius and holes of the rib flanges and HFEC Inspection of the Vertical Stiffener at FR36 for ADDITIONAL WORK Compliance Time (whichever occurs later) Condition Action Threshold (whichever occurs first) Grace Period (whichever occurs first) Repetitive interval (whichever occurs first) Oversize holes and install new fasteners, in accordance with SUBTASK 571175-831-005 001 Oversize the Holes of the Shims, on Bench and SUBTASK 571175-831-006 001 Oversize the Holes of the Rib Flanges, on Aircraft and SUBTASK 571175-400-003 001 Install the Shims with the New Fasteners and Before next flight None None No crack found

Repeat the special detailed inspection of the radius and holes of the rib flanges and vertical stiffener at FR36, in accordance with TASK 571175-832-801 001 Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 (See NOTE*) None None 32500FC / 65000FH

Crack found Contact AIRBUS and follow their instructions Before next flight None None NOTE*: For the repetitive inspections it is not necessary to oversize the holes as the holes are in transition fit.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 8 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
**CONF 002 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. Table 1, Config. 002 - Special detailed inspection of the radius and holes of the rib flanges and HFEC Inspection of the Vertical Stiffener at FR36 Compliance Time (whichever occurs later) Condition Action Threshold (whichever occurs first) Grace Period (whichever occurs first) Repetitive interval (whichever occurs first) All Aircraft Do a special detailed inspection of the radius and holes of the rib flanges and vertical stiffener at FR36, in accordance with TASK 571175-832-801 001 Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 10700FC / 21500FH from MSB A320-57-1013 embodiment 850FC / 1700FH from SB rev00 issue date None

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 9 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN Table 1, Config. 002 - Special detailed inspection of the radius and holes of the rib flanges and HFEC Inspection of the Vertical Stiffener at FR36 Compliance Time (whichever occurs later) Condition Action Threshold (whichever occurs first) Grace Period (whichever occurs first) Repetitive interval (whichever occurs first) Oversize holes and install new fasteners, in accordance with SUBTASK 571175-831-007 002 Oversize the Holes of the Shims, on Bench and SUBTASK 571175-831-008 002 Oversize the Holes of the Rib Flanges, on Aircraft and SUBTASK 571175-400-004 002 Install the Shims with the New Fasteners and Before next flight None None No crack found

Repeat the special detailed inspection of the radius and holes of the rib flanges and vertical stiffener at FR36, in accordance with TASK 571175-832-801 001 Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 (See NOTE*) None None 32500FC / 65000FH

Crack found Contact AIRBUS and follow their instructions Before next flight None None NOTE*: For the repetitive inspections it is not necessary to oversize the holes as the holes are in transition fit.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 10 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN Table 2, Config. 002 - Special detailed inspection of the radius and holes of the rib flanges and HFEC Inspection of the Vertical Stiffener at FR36 for ADDITIONAL WORK Compliance Time (whichever occurs later) Condition Action Threshold (whichever occurs first) Grace Period (whichever occurs first) Repetitive interval (whichever occurs first) All Aircraft Do a special detailed inspection of the radius and holes of the rib flanges and vertical stiffener at FR36, in accordance with TASK 571175-832-802 001 Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 for ADDITIONAL WORK 10700FC / 21500FH from MSB A320-57-1013 embodiment 850FC / 1700FH from SB rev00 issue date None

Oversize holes and install new fasteners, in accordance with SUBTASK 571175-831-007 002 Oversize the Holes of the Shims, on Bench and SUBTASK 571175-831-008 002 Oversize the Holes of the Rib Flanges, on Aircraft and SUBTASK 571175-400-004 002 Install the Shims with the New Fasteners and Before next flight None None No crack found

Repeat special detailed inspection of the radius and holes of the rib flanges and vertical stiffener at FR36, in accordance with TASK 571175-832-801 001 Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 (See NOTE*) None None 32500FC / 65000FH

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 11 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN Table 2, Config. 002 - Special detailed inspection of the radius and holes of the rib flanges and HFEC Inspection of the Vertical Stiffener at FR36 for ADDITIONAL WORK Compliance Time (whichever occurs later) Condition Action Threshold (whichever occurs first) Grace Period (whichever occurs first) Repetitive interval (whichever occurs first) Crack found Contact AIRBUS and follow their instructions Before next flight None None NOTE*: For the repetitive inspections it is not necessary to oversize the holes as the holes are in transition fit. **CONF ALL 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. 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 571175-832-801-001: Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 Get Access 6.00 On Aircraft Remove the Fasteners and the Shims 4.00 Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 13.00 Oversize the Holes of the Rib Flanges, on Aircraft 2.00 Install the Shims with the New Fasteners 10.00 On Bench Oversize the Holes of the Shims, on Bench 2.00 Tests 1.00 Close-Up 7.00 TOTAL MANHOURS 45.00 ELAPSED TIME (HOURS) 31.00
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 12 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
NOTE: For an explanation of the manhours and elapsed time, refer to the Gantt Chart Fig. A-FABAAgiven in Appendix 02 - Elapsed Time Assumption

. NOTE: The minimum manhours necessary to accomplish this Service Bulletin are those for the Inspection. Depending on the inspection result, additional manhours can apply. Task 571175-832-802-001: Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 for ADDITIONAL WORK Get Access 6.00 On Aircraft Remove the Fasteners and the Shims 4.00 Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 13.00 Oversize the Holes of the Rib Flanges, on Aircraft 2.00 Install the Shims with the New Fasteners 10.00 On Bench Oversize the Holes of the Shims, on Bench 2.00 Tests 1.00 Close-Up 7.00 TOTAL MANHOURS 45.00 ELAPSED TIME (HOURS) 31.00 NOTE: For an explanation of the manhours and elapsed time, refer to the Gantt Chart Fig. A-FABAAgiven in Appendix 02 - Elapsed Time Assumption

. NOTE: The minimum manhours necessary to accomplish this Service Bulletin are those for the Inspection. Depending on the inspection result, additional manhours can apply. **CONF 002 Task 571175-832-801-001: Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 Get Access 6.00 On Aircraft Remove the Fasteners and the Shims 4.00 Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 13.00 Oversize the Holes of the Rib Flanges, on Aircraft 2.00 Install the Shims with the New Fasteners 10.00 On Bench Oversize the Holes of the Shims, on Bench 2.00 Tests 1.00 Close-Up 7.00 TOTAL MANHOURS 45.00 ELAPSED TIME (HOURS) 31.00 NOTE: For an explanation of the manhours and elapsed time, refer to the Gantt DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 13 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
Chart Fig. A-FABAA given in Appendix 02 - Elapsed Time Assumption

. NOTE: The minimum manhours necessary to accomplish this Service Bulletin are those for the Inspection. Depending on the inspection result, additional manhours can apply. Task 571175-832-802-001: Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 for ADDITIONAL WORK Get Access 6.00 On Aircraft Remove the Fasteners and the Shims 4.00 Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 13.00 Oversize the Holes of the Rib Flanges, on Aircraft 2.00 Install the Shims with the New Fasteners 10.00 On Bench Oversize the Holes of the Shims, on Bench 2.00 Tests 1.00 Close-Up 7.00 TOTAL MANHOURS 45.00 ELAPSED TIME (HOURS) 31.00 NOTE: For an explanation of the manhours and elapsed time, refer to the Gantt Chart Fig. A-FABAAgiven in Appendix 02 - Elapsed Time Assumption

. NOTE: The minimum manhours necessary to accomplish this Service Bulletin are those for the Inspection. Depending on the inspection result, additional manhours can apply. **CONF ALL H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-52 06-41-53 12-34-24 20-28-00 21-20-00 21-21-41 25-54-12 25-80-00 28-25-00 32-12-00 38-11-41 52-30-00 57-17-11 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 51-10-08 DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 14 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN Service Bulletin (SB) A320-57-1013 Standards Manual (SM) Structural Repair Manual (SRM) 51-23-12 51-24-00 51-40-00 51-42-00 51-43-00 51-44-00 51-75-12 51-76-11 **CONF 002 Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-52 06-41-53 12-34-24 20-28-00 21-20-00 21-21-41 25-54-12 25-80-00 28-25-00 32-12-00 38-11-41 52-30-00 57-17-11 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 51-10-08 Service Bulletin (SB) A320-57-1013 Standards Manual (SM) Structural Repair Manual (SRM) 51-23-12 51-24-00 51-40-00 51-42-00 51-43-00 51-44-00 51-75-12 51-76-11 **CONF ALL K. PUBLICATION AFFECTED

Maintenance Planning Document (MPD) 571197-01-1 L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 15 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 16 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
2. MATERIAL INFORMATION **CONF ALL A. MATERIAL - PRICE AND AVAILABILITY (1) Procurement Addresses Customers with aircraft shown in the effectivity of this Service Bulletin should send a purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is: Kit 571175A01R00 Kit 571175A02R00 AIRBUS Material, Logistics and Suppliers Weg beim Jaeger 150 D-22335 HAMBURG GERMANY For ordering by internet: http://spares.airbus.com For ordering by fax: +49 40 50 76 2590 For ordering by E-mail: airbus.kit@airbus.com (2) Price and Availability

Kit 571175A01R00 Cost 1,600.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. Kit 571175A02R00 Cost 2,010.00 USD Availability 180 calendar days from receipt of order The availability given above is the standard lead time from the date of your purchase order. If items are required before this time, please include a retrofit planning schedule with your order so that we can try to comply with your requirements. The sales terms (costs and availability) are estimated in relation to economic conditions. The latest valid price and lead time for ordering purposes shall be obtained through the AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com. B. INDUSTRY SUPPORT INFORMATION AIRBUS will not provide industry support for accomplishment of this Service Bulletin.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 17 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
C. LIST OF COMPONENTS Kit 571175A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 3 EN6115V5X15 24 BOLT 4 ASNA2536-5 24 NUT 9 MS24665-153 6 PIN 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 571175A02R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 4 ASNA2536-5 24 NUT 5 EN6115V5Y15 24 BOLT 9 MS24665-153 6 PIN NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Epoxy Primer 04DAB2 As required Anti-Vapor Paint 04PAF8 As required Polysulfide Sealant-General Purpose Brushable 06AAA1 As required Polysulfide Sealant-Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant-Fuel Tank Fillet 06ABB1 As required Non Aqueous Cleaner-General 08BAA9 As required (2) Components None (3) Equipment None DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 18 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING (1) Tooling - Price and Availability None (2) Tools None (3) Special Tools Kit tool 571175T01R00 ITEM PART N ̊ KEYWORD QTY SEE NOTES 98D57103003000 TOOL 1

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 19 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 20 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS Task 571175-832-801-001 - Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING: MAKE SURE THAT THE FORWARD CARGO DOOR IS OPEN BEFORE YOU REMOVE A PARTITION PANEL IN THE FORWARD CARGO COMPARTMENT. AIR FROM THE FUEL TANK INERTING SYSTEM CAN COLLECT IN THE AREA BEHIND THE PANEL. AIR FROM THIS SYSTEM HAS A LOW OXYGEN CONTENT AND CAN CAUSE INJURY OR DEATH. WARNING: MAKE SURE THAT YOU DO THE REFUEL PANEL TEST BEFORE OR DURING THE REFUEL PROCEDURE. DEFECTIVE HIGH-LEVEL SENSORS CAN CAUSE FUEL TO SPILL OVERBOARD. MAKE SURE THAT YOU COMPLETE THE REFUEL PANEL TEST BEFORE THE FUEL TANK IS 70 PERCENT FULL. WARNING: YOU MUST WEAR SAFETY BREATHING EQUIPMENT WHEN YOU DO WORK IN A FUEL TANK. THE TANKS CAN CONTAIN AIR FROM THE TANK INERTING SYSTEM. AIR FROM THIS SYSTEM HAS A LOW-OXYGEN CONTENT AND CAN CAUSE INJURY AND DEATH. WARNING: BEFORE YOU DO WORK IN OR NEAR A FUEL TANK, MAKE SURE THAT YOU OBEY ALL THE SAFETY PROCEDURES. THIS WILL PREVENT INJURY TO PERSONS AND/OR DAMAGE TO THE AIRCRAFT. CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS. - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IF THERE IS CONTAMINATION REFER TO ESPM 20-55-00. NOTE: The accomplishment instructions of this Service Bulletin include procedures given in other documents or in other sections of the Service Bulletin. When the words "refer to" are used and the operator has a procedure accepted by the local authority he belongs to, the accepted alternative procedure can be used. When the words "in accordance with" are used then the given procedure must be followed. NOTE: The access and close-up instructions, not comprising return to service tests, in this

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 21 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
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: The purpose of flow charts is to supplement the information given in the Procedure and Compliance paragraphs and not to serve as the primary source for tasks or compliance times given in this Service Bulletin. NOTE: This Service Bulletin is mandated or expected to be mandated by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions are Required for Compliance (RC) and must be done to comply with the AD. Other paragraphs are recommended and may be deviated from, done as part of other actions or done with accepted methods different from those given in the Service Bulletin, as long as the RC paragraphs can be done and the aircraft can be put back into a serviceable condition. Task Associated Data **CONF 001 Zone 130 140 Access Panel 131NW 131PW 132PW 147AZ 148AZ Manpower TOTAL MANHOURS 45.00 ELAPSED TIME (HOURS) 31.00 **CONF 002 Zone 130 140 Access Panel 131NW 131PW 132PW 147AZ 148AZ Manpower TOTAL MANHOURS 45.00 ELAPSED TIME (HOURS) 31.00

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 22 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
**CONF ALL A. GENERAL **CONF 001 (1) Subtask 571175-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 06-41-52, Page Block 001 06-41-53, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-40-00 51-42-00 51-43-00 51-44-00 51-75-12 51-76-11 (a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Material 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 06-41-52, Page Block 001 and AMM 06-41-53, Page Block 001. (e) Remove and install fasteners in accordance with SRM 51-42-00. (f) Apply sealant in accordance with SRM 51-24-00. (g) Renew the protective finish in accordance with SRM 51-75-12. (h) If alternative and substitute fasteners have to be used, you must make sure that the associated nut/collar are compatible in accordance with SRM 51-40-00 "Mating Part" column. (i) 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. (j) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00.
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 23 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN (k) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00. (l) Do the repair of fuel tank sealing in accordance with SRM 51-76-11. (2) Subtask 571175-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. **CONF 002 (1) Subtask 571175-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 06-41-52, Page Block 001 06-41-53, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-40-00 51-42-00 51-43-00 51-44-00 51-75-12 51-76-11 (a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Material 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 06-41-52, Page Block 001 and AMM 06-41-53, Page Block 001. (e) Remove and install fasteners in accordance with SRM 51-42-00. (f) Apply sealant in accordance with SRM 51-24-00. (g) Renew the protective finish in accordance with SRM 51-75-12. (h) If alternative and substitute fasteners have to be used, you must make sure that the associated nut/collar are compatible in accordance with SRM 51-40-00 "Mating Part" column.
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 24 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN (i) 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. (j) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00. (k) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00. (l) Do the repair of fuel tank sealing in accordance with SRM 51-76-11. (2) Subtask 571175-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 571175-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002 Task 21-20-00-010-001 Task 25-54-12-000-001 Task 32-12-00-010-001 Task 52-30-00-860-001 Task 57-17-11-000-001 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

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 25 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN - 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) Put an access platform in position at door 825. (c) Open the FWD cargo compartment door 825, refer to AMM Task 52-30-00-860-001. (d) Open the main landing gear doors, refer to AMM Task 32-12-00-010-001. (e) Put an access platform in position at zones 147 and 148. (f) Do the preparation procedure as specified in the Removal of the Access Covers 147AZ and 148AZ, refer to AMM Task 57-17-11-000-001. (g) Do the preparation procedure as specified in the Removal of the Air-Conditioning Distribution Ducts, refer to AMM Task 21-20-00-010-001.(h) Do the preparation procedure as specified in the Removal of the Forward CargoCompartment Partition panels at Frame 34, refer to AMM Task 25-54-12-000-001. (2) Subtask 571175-010-001-001 - Remove/Open for Access Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-001 Task 21-21-41-000-001 Task 25-54-12-000-001 Task 25-80-00-000-001 Task 28-25-00-650-001 Task 28-25-00-869-001 Task 38-11-41-000-001 Task 57-17-11-000-001 (a) Defuel the center tank, refer to AMM Task 28-25-00-650-001 or move the fuel into a different tank, refer to AMM Task 28-25-00-869-001. (b) Open access covers 147AZ and 148AZ, refer to AMM Task 57-17-11-000-001. (c) Remove the Forward Cargo-Compartment Partition panels 131PW, 132PW and 131NW at Frame 34, refer to AMM Task 25-54-12-000-001.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 26 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN (d) If necessary remove the recirculation filters LH and RH sides, refer to AMM Task 21-21-41-000-001

. (e) If necessary, remove the Air-Conditioning Distribution Ducts to get access to the working area, refer to AMM Task 21-20-00-010-001. (f) If necessary remove the potable water tank 3000MM, refer to AMM Task 38-11-41-000-001. (g) Remove insulation blankets around working areas between Frame 35 and Frame 36 LH and RH sides for access, refer to AMM Task 25-80-00-000-001. (h) If necessary, remove electrical bundle clamps and push the bundles aside without disconnection in order to be able to get them out of the working area. **CONF 002 (1) Subtask 571175-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002 Task 21-20-00-010-001 Task 25-54-12-000-001 Task 32-12-00-010-001 Task 52-30-00-860-001 Task 57-17-11-000-001 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

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 27 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN (a) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-869-002

. (b) Put an access platform in position at door 825. (c) Open the FWD cargo compartment door 825, refer to AMM Task 52-30-00-860-001. (d) Open the main landing gear doors, refer to AMM Task 32-12-00-010-001. (e) Put an access platform in position at zones 147 and 148. (f) Do the preparation procedure as specified in the Removal of the Access Covers 147AZ and 148AZ, refer to AMM Task 57-17-11-000-001. (g) Do the preparation procedure as specified in the Removal of the Air-Conditioning Distribution Ducts, refer to AMM Task 21-20-00-010-001.(h) Do the preparation procedure as specified in the Removal of the Forward CargoCompartment Partition panels at Frame 34, refer to AMM Task 25-54-12-000-001. (2) Subtask 571175-010-001-001 - Remove/Open for Access Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-001 Task 21-21-41-000-001 Task 25-54-12-000-001 Task 25-80-00-000-001 Task 28-25-00-650-001 Task 28-25-00-869-001 Task 38-11-41-000-001 Task 57-17-11-000-001 (a) Defuel the center tank, refer to AMM Task 28-25-00-650-001 or move the fuel into a different tank, refer to AMM Task 28-25-00-869-001. (b) Open access covers 147AZ and 148AZ, refer to AMM Task 57-17-11-000-001. (c) Remove the Forward Cargo-Compartment Partition panels 131PW, 132PW and 131NW at Frame 34, refer to AMM Task 25-54-12-000-001. (d) If necessary remove the recirculation filters LH and RH sides, refer to AMM Task 21-21-41-000-001

. (e) If necessary, remove the Air-Conditioning Distribution Ducts to get access to the working area, refer to AMM Task 21-20-00-010-001. (f) If necessary remove the potable water tank 3000MM, refer to AMM Task 38-11-41-000-001.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 28 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN (g) Remove insulation blankets around working areas between Frame 35 and Frame 36 LH and RH sides for access, refer to AMM Task 25-80-00-000-001. (h) If necessary, remove electrical bundle clamps and push the bundles aside without disconnection in order to be able to get them out of the working area. **CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 571175-000-003-001 - Remove the Fasteners and the Shims Work Zones and Access Panels Zone Access/Work location 130 Access Panel 131PW, Panel 132PW, Panel 131NW 140 Access Panel 147AZ, Panel 148AZ Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9
Kit tool 571175T01R00 ITEM PART N ̊ KEYWORD QTY SEE NOTES 98D57103003000 TOOL 1 References Structural Repair Manual (SRM) 51-42-00 51-44-00 Fig. A-FBBAA Removal/Installation of the Shims Sheet 01 Sheet 02 Fig. A-FBDAA Removal/Installation of the Rods Sheet 01
Refer to Fig. A-FBBAA Refer to Fig. A-FBDAA In accordance with SRM 51-42-00, SRM 51-44-00 DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 29 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN (a) Remove the sealant around the nuts: 1 If necessary, use a non-metallic spatula to remove the sealant and clean the areas with solvent: Non Aqueous Cleaner-General 08BAA9 As required (b) Remove the nuts: Refer to Fig. A-FBBAA Sheet 01 and Fig. A-FBBAA Sheet 02 24 Nut Item (2) Discard (c) Remove the bottom attachment bolt of the rod: Refer to Fig. A-FBDAA Sheet 01 NOTE: The quantities are given as a maximum for all ribs, it is not allowed to have 2 rods removed at the same time. 6 Bolt Item (6) Retain 6 Washer Item (7) Retain 6 Nut Item (8) Retain 6 Cotter Pin Item (9) Discard (d) Push the rod out of the working area: 6 Rod Item (10) Retain (e) From inside the tank push back the fasteners until they are flush. NOTE: Do not remove the fasteners by pushing them through the stack up, there is a risk of damaging the hole and contaminating it with steel particles. (f) Install temporarily the rod in initial position before to do the next rod: Refer to Fig. A-FBDAA Sheet 01 6 Rod Item (10) Retained at removal 6 Bolt Item (6) Retained at removal 6 Washer Item (7) Retained at removal

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 30 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

6 Nut Item (8) Retained at removal (g) When all bolts are pushed back, use the special extraction tool, from the forward cargo area, to remove these fasteners: 98D57103003000 Extractor 1 (h) From the tank, remove the shims with non-metallic spatula and identify their position: Refer to Fig. A-FBBAA Sheet 02 12 Shim Item (11) Retain attached with: 24 Bolt Item (1) Discard

(2) Subtask 571175-832-001-001 - Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 Work Zones and Access Panels Zone Access/Work location 130 Access Panel 131PW, Panel 132PW, Panel 131NW 140 Access Panel 147AZ, Panel 148AZ Manpower Resources Manhours 13.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9 As required
References Non Destructive Test Manual (NTM) 51-10-01 51-10-08 Structural Repair Manual (SRM) 51-42-00 51-44-00 Fig. A-FBAAA Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 Sheet 01 Sheet 02 Sheet 03

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 31 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
References Fig. A-FRAAA Inspection Report Sheet 01 Sheet 02 Sheet 03 Fig. A-FFAAA Flow Chart Sheet 01 (a) At threshold given in the table 1 of the PLANNING INFORMATION Paragraph E.(2): Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36. Refer to Fig. A-FFAAA Refer to Fig. A-FBAAA 1 Remove the fasteners from the holes to be inspected as described in SUBTASK 571175-000-003 001 Remove the Fasteners and the Shims

. 2 Do a High Frequency Eddy Current (HFEC) inspection of the radius of the rib flanges and vertical stiffener and a rototest Inspection of the holes at FR36. Refer to Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 02
a If necessary, use a non-metallic spatula to remove the sealant and clean the areas with solvent: Non Aqueous Cleaner-General 08BAA9 As required
b Deburr all the holes before inspection.
c Do a High Frequency Eddy Current (HFEC) inspection of the radius of the rib flanges and vertical stiffener and a rototest inspection of the holes as specified in NTM 51-10-08 and NTM 51-10-01. NOTE: For additional information of procedure NTM 51-10-01 refer to Appendix 01 - Non-Destructive Test Requirements. <1> If no crack is found: <a> Oversize the holes of the rib flanges and the shims, refer to SUBTASK 571175-831-005 001 Oversize the Holes of the Shims, on Bench and SUBTASK 571175-831-006 001 Oversize the Holes of the Rib Flanges, on Aircraft

. and

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 32 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN Repeat the inspection of the radius and holes in the rib flanges on front spar side at the interval given in the table 1 of the PLANNING INFORMATION Paragraph E.(2), refer to TASK 571175-832-801 001 Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36

. NOTE: For the repetitive inspections it is not necessary to oversize the holes as the holes are in transition fit. <2> If crack is found: <a> Contact Airbus before next flight and follow their instructions. 3 For the inspection report, refer to Fig. A-FRAAA

. (3) Subtask 571175-831-005-001 - Oversize the Holes of the Shims, on Bench Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9 As required
References Structural Repair Manual (SRM) 51-44-00 Fig. A-FBFAA Oversizing of the Holes of the Shims, on Bench Sheet 01

Refer to Fig. A-FBFAA In accordance with SRM 51-44-00 (a) Oversize the holes of the shims to the diameter given in Fig. A-FBFAA Sheet 01

. (b) Deburr and clean the holes with: Non Aqueous Cleaner-General 08BAA9 As required

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 33 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN (4) Subtask 571175-831-006-001 - Oversize the Holes of the Rib Flanges, on Aircraft Work Zones and Access Panels Zone Access/Work location 140 Access Panel 147AZ, Panel 148AZ Work location Frame 42 130 Access Panel 131PW, Panel 132PW, Panel 131NW Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9 As required
References Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 Fig. A-FBEAA Oversizing of the Holes of the Rib Flanges, on Aircraft Sheet 01 Sheet 02
Refer to Fig. A-FBEAA In accordance with SRM 51-24-00, SRM 51-42-00, SRM 51-43-00, SRM 51-44-00 NOTE: This procedure must be applied to one rib at a time. (a) Disengage the rod. (b) Oversize the holes of the rib flanges to the diameter given in Fig. A-FBEAA Sheet 02

. (c) Deburr and clean the drilled area with: Non Aqueous Cleaner-General 08BAA9 As required

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 34 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN (5) Subtask 571175-400-003-001 - Install the Shims with the New Fasteners Work Zones and Access Panels Zone Access/Work location 140 Access Panel 147AZ, Panel 148AZ Work location Frame 42 130 Access Panel 131PW, Panel 132PW, Panel 131NW Manpower Resources Manhours 10.00 Minimum number of person 2 Subtask elapsed time 5.00 Skills AIRFRAME Material necessary to do the job Kit 571175A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 EN6115V5X15 24 BOLT 4 ASNA2536-5 24 NUT 9 MS24665-153 6 PIN Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Epoxy Primer 04DAB2 As required Anti-Vapor Paint 04PAF8 As required Polysulfide Sealant-General Purpose Brushable 06AAA1 As required Polysulfide Sealant-Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant-Fuel Tank Fillet 06ABB1 As required
References Structural Repair Manual (SRM) 51-23-12 51-24-00 51-42-00 51-43-00 51-75-12 Fig. A-FBBAA Removal/Installation of the Shims Sheet 01 Sheet 02 Fig. A-FBDAA Removal/Installation of the Rods Sheet 01
Refer to Fig. A-FBBAA Refer to Fig. A-FBDAA DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 35 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN In accordance with SRM 51-24-00, SRM 51-42-00, SRM 51-43-00, SRM 51-75-12 (a) Install the shims: Refer to Fig. A-FBBAA Sheet 02 12 Shim Item (11) Retained at removal with: 24 Bolt EN6115V5X15 Item 3 24 Nut ASNA2536-5 Item 4 NOTE: Apply sealant on all contact surface between the shims Item (11) and front spar:Polysulfide SealantFuel Tank Fillet 06ABB1 As required

NOTE: Wet install the fasteners with:Polysulfide SealantGeneral Purpose Brushable 06AAA1 As required
(b) After installation: 1 Over coat the fastener tails and nuts in the tank and perform sealing of the shims and inspection area with:Polysulfide SealantFuel Tank Brushable 06ABA1 As required
(c) In the cargo area: 1 Apply epoxy primer and anti-vapor paint: Epoxy Primer 04DAB2 As required and Anti-Vapor Paint 04PAF8 As required

2 Renew the special protection around the fastener heads in accordance with SRM 51-23-12. (d) Install the rod in initial position and install the attachment fastener. Refer to Fig. A-FBDAA Sheet 01

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 36 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
1 Install: 6 Rod Item (10) Retained at removal Attached with: 6 Bolt Item (6) Retained at removal 6 Washer Item (7) Retained at removal 6 Nut Item (8) Retained at removal 6 Cotter Pin MS24665-153 Item 9 NOTE: The quantities are given as a maximum for all ribs, it is not allowed to have 2 rods removed at the same time. 2 Perform over coating of nuts and bolts head with:Polysulfide SealantFuel Tank Brushable 06ABA1 As required

**CONF 002 (1) Subtask 571175-000-003-002 - Remove the Fasteners and the Shims Work Zones and Access Panels Zone Access/Work location 130 Access Panel 131PW, Panel 132PW, Panel 131NW 140 Access Panel 147AZ, Panel 148AZ Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 37 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
Kit tool 571175T01R00 ITEM PART N ̊ KEYWORD QTY SEE NOTES 98D57103003000 TOOL 1 References Structural Repair Manual (SRM) 51-42-00 51-44-00 Fig. A-FBBAB Removal/Installation of the Shims Sheet 01 Sheet 02 Fig. A-FBDAA Removal/Installation of the Rods Sheet 01
Refer to Fig. A-FBBAB Refer to Fig. A-FBDAA In accordance with SRM 51-42-00, SRM 51-44-00 (a) Remove the sealant around the nuts: 1 If necessary, use a non-metallic spatula to remove the sealant and clean the areas with solvent: Non Aqueous Cleaner-General 08BAA9 As required (b) Remove the nuts: Refer to Fig. A-FBBAB Sheet 01 and Fig. A-FBBAB Sheet 02 24 Nut Item (2) Discard (c) Remove the bottom attachment bolt of the rod: Refer to Fig. A-FBDAA Sheet 01 NOTE: The quantities are given as a maximum for all ribs, it is not allowed to have 2 rods removed at the same time. 6 Bolt Item (6) Retain 6 Washer Item (7) Retain 6 Nut Item (8) Retain 6 Cotter Pin Item (9) Discard (d) Push the rod out of the working area: 6 Rod Item (10) Retain

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 38 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN (e) From inside the tank push back the fasteners until they are flush. NOTE: Do not remove the fasteners by pushing them through the stack up, there is a risk of damaging the hole and contaminating it with steel particles. (f) Install temporarily the rod in initial position before to do the next rod: Refer to Fig. A-FBDAA Sheet 01 6 Rod Item (10) Retained at removal 6 Bolt Item (6) Retained at removal 6 Washer Item (7) Retained at removal 6 Nut Item (8) Retained at removal (g) When all bolts are pushed back, use the special extraction tool, from the forward cargo area, to remove these fasteners: 98D57103003000 Extractor 1 (h) From the tank, remove shims with non-metallic spatula and identify their position: Refer to Fig. A-FBBAB Sheet 02 12 Shim Item (11) Retain attached with: 24 Bolt Item (1) Discard

(2) Subtask 571175-832-001-002 - Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 Work Zones and Access Panels Zone Access/Work location 130 Access Panel 131PW, Panel 132PW, Panel 131NW 140 Access Panel 147AZ, Panel 148AZ Manpower Resources Manhours 13.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 39 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9
References Non Destructive Test Manual (NTM) 51-10-01 51-10-08 Structural Repair Manual (SRM) 51-42-00 51-44-00 Fig. A-FBAAA Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 Sheet 01 Sheet 02 Sheet 03 Fig. A-FFAAA Flow Chart Sheet 01 Fig. A-FRAAA Inspection Report Sheet 01 Sheet 02 Sheet 03 (a) At threshold given in the table 1 of the PLANNING INFORMATION Paragraph E.(2): Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36. Refer to Fig. A-FFAAA Refer to Fig. A-FBAAA 1 Remove the fasteners from the holes to be inspected as described in SUBTASK 571175-000-003 002 Remove the Fasteners and the Shims

. 2 Do a High Frequency Eddy Current (HFEC) inspection of the radius of the rib flanges and vertical stiffener and a rototest Inspection of the holes at FR36. Refer to Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 02
a If necessary, use a non-metallic spatula to remove the sealant and clean the areas with solvent: Non Aqueous Cleaner-General 08BAA9 As required
b Deburr all the holes before inspection.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 40 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

c Do a High Frequency Eddy Current (HFEC) inspection of the radius of the rib flanges and vertical stiffener and a rototest inspection of the holes as specified in NTM 51-10-08 and NTM 51-10-01. NOTE: For additional information of procedure NTM 51-10-01 refer to Appendix 01 - Non-Destructive Test Requirements. <1> If no crack is found: <a> Oversize the holes of the rib flanges and shims, refer to SUBTASK 571175-831-005 002 Oversize the Holes of the Shims, on Bench and SUBTASK 571175-831-006 002 Oversize the Holes of the Rib Flanges, on Aircraft

. and Repeat the inspection of the radius and holes in the rib flanges on front spar side at the interval given in the table 1 of the PLANNING INFORMATION Paragraph E.(2), refer to TASK 571175-832-801 001 Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36

. NOTE: For the repetitive inspections it is not necessary to oversize the holes as the holes are in transition fit. <2> If crack is found: <a> Contact Airbus before next flight and follow their instructions. 3 For the inspection report, refer to Fig. A-FRAAA

. (3) Subtask 571175-831-005-002 - Oversize the Holes of the Shims, on Bench Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9 As required
References Structural Repair Manual (SRM) 51-44-00
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 41 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
References Fig. A-FBFAB Oversizing of the Holes of the Shims, on Bench Sheet 01

Refer to Fig. A-FBFAB In accordance with SRM 51-44-00 (a) Oversize the holes of the shims to the diameter given in Fig. A-FBFAB Sheet 01

. (b) Deburr and clean the holes with: Non Aqueous Cleaner-General 08BAA9 As required (4) Subtask 571175-831-006-002 - Oversize the Holes of the Rib Flanges, on Aircraft Work Zones and Access Panels Zone Access/Work location 140 Access Panel 147AZ, Panel 148AZ Work location Frame 42 130 Access Panel 131PW, Panel 132PW, Panel 131NW Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9 As required
References Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 Fig. A-FBEAB Oversizing of the Holes of the Rib Flanges, on Aircraft Sheet 01 Sheet 02
Refer to Fig. A-FBEAB In accordance with SRM 51-24-00, SRM 51-42-00, SRM 51-43-00, SRM 51-44-00
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 42 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
NOTE: This procedure must be applied to one rib at a time. (a) Disengage the rod. (b) Oversize the holes of the rib flanges to the diameter given in Fig. A-FBEAB Sheet 02

. (c) Deburr and clean the drilled area with: Non Aqueous Cleaner-General 08BAA9 As required (5) Subtask 571175-400-003-002 - Install the Shims with the New Fasteners Work Zones and Access Panels Zone Access/Work location 140 Access Panel 147AZ, Panel 148AZ Work location Frame 42 130 Access Panel 131PW, Panel 132PW, Panel 131NW Manpower Resources Manhours 10.00 Minimum number of person 2 Subtask elapsed time 5.00 Skills AIRFRAME Material necessary to do the job Kit 571175A02R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 4 ASNA2536-5 24 NUT 5 EN6115V5Y15 24 BOLT 9 MS24665-153 6 PIN Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Epoxy Primer 04DAB2 As required Anti-Vapor Paint 04PAF8 As required Polysulfide Sealant-General Purpose Brushable 06AAA1 As required Polysulfide Sealant-Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant-Fuel Tank Fillet 06ABB1 As required

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 43 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-23-12 51-24-00 51-42-00 51-43-00 51-75-12 Fig. A-FBBAB Removal/Installation of the Shims Sheet 01 Sheet 02 Fig. A-FBDAA Removal/Installation of the Rods Sheet 01
Refer to Fig. A-FBBAB Refer to Fig. A-FBDAA In accordance with SRM 51-24-00, SRM 51-42-00, SRM 51-43-00, SRM 51-75-12 (a) Install the shims: Refer to Fig. A-FBBAB Sheet 02 12 Shim Item (11) Retained at removal with: 24 Bolt EN6115V5Y15 Item 5 24 Nut ASNA2536-5 Item 4 NOTE: Apply sealant on all contact surface between the shims Item (11) and front spar:Polysulfide SealantFuel Tank Fillet 06ABB1 As required

NOTE: Wet install the fasteners with:Polysulfide SealantGeneral Purpose Brushable 06AAA1 As required
(b) After installation: 1 Over coat the fastener tails and nuts in the tank and perform sealing of the shims and inspection area with:Polysulfide SealantFuel Tank Brushable 06ABA1 As required

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 44 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN (c) In the cargo area: 1 Apply epoxy primer and anti-vapor paint: Epoxy Primer 04DAB2 As required and Anti-Vapor Paint 04PAF8 As required

2 Renew the special protection around the fastener heads in accordance with SRM 51-23-12. (d) Install the rod in initial position and install the attachment fastener. Refer to Fig. A-FBDAA Sheet 01 1 Install: 6 Rod Item (10) Retained at removal Attached with: 6 Bolt Item (6) Retained at removal 6 Washer Item (7) Retained at removal 6 Nut Item (8) Retained at removal 6 Cotter Pin MS24665-153 Item 9 NOTE: The quantities are given as a maximum for all ribs, it is not allowed to have 2 rods removed at the same time. 2 Perform over coating of nuts and bolts head with:Polysulfide SealantFuel Tank Brushable 06ABA1 As required

**CONF ALL D. TEST **CONF 001 (1) Subtask 571175-700-001-001 - Testing Manpower Resources Skills NON SPECIFIC DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 45 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) 20-28-00, Page Block 501 Task 21-20-00-410-001 Task 25-54-12-400-001 Task 52-30-00-860-002 Task 57-17-11-400-001 NOTE: This Service Bulletin requires the accomplishment of the following Tests which are given in subtasks included in the topic Close-up. The manhours for the tests are included in the referenced Service Bulletin subtask. - Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air-Conditioning Distribution Ducts, refer to AMM Task 21-20-00-410-001. - Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Access Covers 147AZ and 148AZ, refer to AMM Task 57-17-11-400-001. - Remove the Safety clips and tags and close the circuit breakers as specified after Closing the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump, refer to AMM Task 52-30-00-860-002. - Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of Forward Cargo-Compartment Partition panels at Frame 34, refer to AMM Task 25-54-12-400-001. - Do the test procedure as specified after the installation of the access covers 147AZ and 148AZ, refer to AMM Task 57-17-11-400-001. - Do the test procedure as specified after the installation of the Air-Conditioning Distribution Ducts, refer to AMM Task 21-20-00-410-001. **CONF 002 (1) Subtask 571175-700-001-001 - Testing Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 20-28-00, Page Block 501 Task 21-20-00-410-001 Task 25-54-12-400-001 Task 52-30-00-860-002 Task 57-17-11-400-001 NOTE: This Service Bulletin requires the accomplishment of the following Tests which are given in subtasks included in the topic Close-up. The manhours for the tests are included in the referenced Service Bulletin subtask.
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 46 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN - Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air-Conditioning Distribution Ducts, refer to AMM Task 21-20-00-410-001. - Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Access Covers 147AZ and 148AZ, refer to AMM Task 57-17-11-400-001. - Remove the Safety clips and tags and close the circuit breakers as specified after Closing the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump, refer to AMM Task 52-30-00-860-002. - Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of Forward Cargo-Compartment Partition panels at Frame 34, refer to AMM Task 25-54-12-400-001. - Do the test procedure as specified after the installation of the access covers 147AZ and 148AZ, refer to AMM Task 57-17-11-400-001. - Do the test procedure as specified after the installation of the Air-Conditioning Distribution Ducts, refer to AMM Task 21-20-00-410-001. **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 571175-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-001 Task 21-21-41-400-001 Task 25-54-12-400-001 Task 25-80-00-400-001 28-25-00, Page Block 301 Task 32-12-00-410-001 Task 38-11-41-400-001 Task 52-30-00-860-002 Task 57-17-11-400-801 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the access cover 147AZ and 148AZ, refer to AMM Task 57-17-11-400-801. (c) Install the Air-Conditioning Distribution Ducts removed for access to the working area, AMM Task 21-20-00-410-001.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 47 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN (d) If removed, install the recirculation filters LH and RH sides , refer to AMM Task 21-21-41-400-001. (e) If removed, install the potable water tank 3000MM, refer to AMM Task 38-11-41-400-001. (f) Install the removed insulation blankets around working areas, refer to AMM Task 25-80-00-400-001. 1 Install the heat and sound insulation in the area between Frame 35 and Frame 36 LH and RH sides removed for access 2 If removed, install electrical bundle clamps removed for access. (g) Install the removed Forward Cargo-Compartment Partition 131PW, 132PW and 131NW at Frame 34, refer to AMM Task 25-54-12-400-001. (h) Refuel the center tank, refer to AMM 28-25-00, Page Block 301. (i) Close the FWD cargo compartment door 825, refer to AMM Task 52-30-00-860-002. (j) Close the main landing gear doors, refer to AMM Task 32-12-00-410-001. (k) Restore the systems and the aircraft to normal operating condition. (l) Remove the access platform(s). **CONF 002 (1) Subtask 571175-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-001 Task 21-21-41-400-001 Task 25-54-12-400-001 Task 25-80-00-400-001 28-25-00, Page Block 301 Task 32-12-00-410-001 Task 38-11-41-400-001 Task 52-30-00-860-002 Task 57-17-11-400-801 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the access cover 147AZ and 148AZ, refer to AMM Task 57-17-11-400-801. (c) Install the Air-Conditioning Distribution Ducts removed for access to the working area, AMM Task 21-20-00-410-001. DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 48 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN (d) If removed, install the recirculation filters LH and RH sides , refer to AMM Task 21-21-41-400-001. (e) If removed, install the potable water tank 3000MM, refer to AMM Task 38-11-41-400-001. (f) Install the removed insulation blankets around working areas, refer to AMM Task 25-80-00-400-001. 1 Install the heat and sound insulation in the area between Frame 35 and Frame 36 LH and RH sides removed for access 2 If removed, install electrical bundle clamps removed for access. (g) Install the removed Forward Cargo-Compartment Partition 131PW, 132PW and 131NW at Frame 34, refer to AMM Task 25-54-12-400-001. (h) Refuel the center tank, refer to AMM 28-25-00, Page Block 301. (i) Close the FWD cargo compartment door 825, refer to AMM Task 52-30-00-860-002. (j) Close the main landing gear doors, refer to AMM Task 32-12-00-410-001. (k) Restore the systems and the aircraft to normal operating condition. (l) Remove the access platform(s).

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 49 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 50 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN Task 571175-832-802-001 - Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 for ADDITIONAL WORK **CONF ALL WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. WARNING: MAKE SURE THAT THE FORWARD CARGO DOOR IS OPEN BEFORE YOU REMOVE A PARTITION PANEL IN THE FORWARD CARGO COMPARTMENT. AIR FROM THE FUEL TANK INERTING SYSTEM CAN COLLECT IN THE AREA BEHIND THE PANEL. AIR FROM THIS SYSTEM HAS A LOW OXYGEN CONTENT AND CAN CAUSE INJURY OR DEATH. WARNING: MAKE SURE THAT YOU DO THE REFUEL PANEL TEST BEFORE OR DURING THE REFUEL PROCEDURE. DEFECTIVE HIGH-LEVEL SENSORS CAN CAUSE FUEL TO SPILL OVERBOARD. MAKE SURE THAT YOU COMPLETE THE REFUEL PANEL TEST BEFORE THE FUEL TANK IS 70 PERCENT FULL. WARNING: YOU MUST WEAR SAFETY BREATHING EQUIPMENT WHEN YOU DO WORK IN A FUEL TANK. THE TANKS CAN CONTAIN AIR FROM THE TANK INERTING SYSTEM. AIR FROM THIS SYSTEM HAS A LOW-OXYGEN CONTENT AND CAN CAUSE INJURY AND DEATH. WARNING: BEFORE YOU DO WORK IN OR NEAR A FUEL TANK, MAKE SURE THAT YOU OBEY ALL THE SAFETY PROCEDURES. THIS WILL PREVENT INJURY TO PERSONS AND/OR DAMAGE TO THE AIRCRAFT. CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS. - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IF THERE IS CONTAMINATION REFER TO ESPM 20-55-00. NOTE: The accomplishment instructions of this Service Bulletin refer to procedures included in other AIRBUS documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the AIRBUS document must be used. NOTE: The access and close-up instructions, not comprising return to service tests, in this

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 51 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
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: The purpose of flow charts is to supplement the information given in the Procedure and Compliance paragraphs and not to serve as the primary source for tasks or compliance times given in this Service Bulletin. NOTE: This Service Bulletin is mandated or expected to be mandated by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions are Required for Compliance (RC) and must be done to comply with the AD. Other paragraphs are recommended and may be deviated from, done as part of other actions or done with accepted methods different from those given in the Service Bulletin, as long as the RC paragraphs can be done and the aircraft can be put back into a serviceable condition. Task Associated Data **CONF 001 Zone 130 140 Access Door 131NW 131PW 132PW Panel 131NW 131PW 132PW 147AZ 148AZ Manpower TOTAL MANHOURS 45.00 ELAPSED TIME (HOURS) 31.00 **CONF 002 Zone 130 140 Access Panel 131NW 131PW 132PW 147AZ 148AZ Manpower TOTAL MANHOURS 45.00 ELAPSED TIME (HOURS) 31.00

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 52 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
**CONF ALL A. GENERAL **CONF 001 (1) Subtask 571175-910-003-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 06-41-52, Page Block 001 06-41-53, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-40-00 51-42-00 51-43-00 51-44-00 51-75-12 51-76-11 (a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Material 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 06-41-52, Page Block 001 and AMM 06-41-53, Page Block 001. (e) Remove and install fasteners in accordance with SRM 51-42-00. (f) Apply sealant in accordance with SRM 51-24-00. (g) Renew the protective finish in accordance with (h) If alternative and substitute fasteners have to be used, you must make sure that the associated nut/collar are compatible in accordance with SRM 51-40-00 "Mating Part" column. (i) 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. (j) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00.
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 53 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN (k) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00. (l) Do the repair of fuel tank sealing in accordance with SRM 51-76-11. (2) Subtask 571175-839-003-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. **CONF 002 (1) Subtask 571175-910-003-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 06-41-52, Page Block 001 06-41-53, Page Block 001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-24-00 51-40-00 51-42-00 51-43-00 51-44-00 51-75-12 51-76-11 (a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to the Consumable Material 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 06-41-52, Page Block 001 and AMM 06-41-53, Page Block 001. (e) Remove and install fasteners in accordance with SRM 51-42-00. (f) Apply sealant in accordance with SRM 51-24-00. (g) Renew the protective finish in accordance with (h) If alternative and substitute fasteners have to be used, you must make sure that the associated nut/collar are compatible in accordance with SRM 51-40-00 "Mating Part" column.
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 54 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN (i) 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. (j) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00. (k) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00. (l) Do the repair of fuel tank sealing in accordance with SRM 51-76-11. (2) Subtask 571175-839-003-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in the Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 571175-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002 Task 21-20-00-010-001 Task 25-54-12-000-001 Task 32-12-00-010-001 Task 52-30-00-860-001 Task 57-17-11-000-001 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

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 55 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN - 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) Put an access platform in position at door 825. (c) Open the FWD cargo compartment door 825, refer to AMM Task 52-30-00-860-001. (d) Open the main landing gear doors, refer to AMM Task 32-12-00-010-001. (e) Put an access platform in position at zones 147 and 148. (f) Do the preparation procedure as specified in the Removal of the Access Covers 147AZ and 148AZ, refer to AMM Task 57-17-11-000-001. (g) Do the preparation procedure as specified in the Removal of the Air-Conditioning Distribution Ducts, refer to AMM Task 21-20-00-010-001.(h) Do the preparation procedure as specified in the Removal of the Forward CargoCompartment Partition panels at Frame 34, refer to AMM Task 25-54-12-000-001. (2) Subtask 571175-010-003-001 - Remove/Open for Access Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-001 Task 21-21-41-000-001 Task 25-54-12-000-001 Task 25-80-00-000-001 Task 28-25-00-650-001 Task 28-25-00-869-001 Task 38-11-41-000-001 Task 57-17-11-000-001 (a) Defuel the center tank, refer to AMM Task 28-25-00-650-001 or move the fuel into a different tank, refer to AMM Task 28-25-00-869-001. (b) Open access covers 147AZ and 148AZ, refer to AMM Task 57-17-11-000-001. (c) Remove the Forward Cargo-Compartment Partition panels 131PW, 132PW and 131NW at Frame 34, refer to AMM Task 25-54-12-000-001.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 56 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN (d) If necessary remove the recirculation filters LH and RH sides, refer to AMM Task 21-21-41-000-001. (e) If necessary, remove the Air-Conditioning Distribution Ducts to get access to the working area, refer to AMM Task 21-20-00-010-001. (f) If necessary remove the potable water tank 3000MM, refer to AMM Task 38-11-41-000-001. (g) Remove insulation blankets around working areas between Frame 35 and Frame 36 LH and RH sides for access, refer to AMM Task 25-80-00-000-001. (h) If necessary, remove electrical bundle clamps and push the bundles aside without disconnection in order to be able to get them out of the working area. **CONF 002 (1) Subtask 571175-941-003-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002 Task 21-20-00-010-001 Task 25-54-12-000-001 Task 32-12-00-010-001 Task 52-30-00-860-001 Task 57-17-11-000-001 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

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 57 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN (a) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-869-002. (b) Put an access platform in position at door 825. (c) Open the FWD cargo compartment door 825, refer to AMM Task 52-30-00-860-001. (d) Open the main landing gear doors, refer to AMM Task 32-12-00-010-001. (e) Put an access platform in position at zones 147 and 148. (f) Do the preparation procedure as specified in the Removal of the Access Covers 147AZ and 148AZ, refer to AMM Task 57-17-11-000-001. (g) Do the preparation procedure as specified in the Removal of the Air-Conditioning Distribution Ducts, refer to AMM Task 21-20-00-010-001.(h) Do the preparation procedure as specified in the Removal of the Forward CargoCompartment Partition panels at Frame 34, refer to AMM Task 25-54-12-000-001. (2) Subtask 571175-010-003-001 - Remove/Open for Access Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 21-20-00-010-001 Task 21-21-41-000-001 Task 25-54-12-000-001 Task 25-80-00-000-001 Task 28-25-00-650-001 Task 28-25-00-869-001 Task 38-11-41-000-001 Task 57-17-11-000-001 (a) Defuel the center tank, refer to AMM Task 28-25-00-650-001 or move the fuel into a different tank, refer to AMM Task 28-25-00-869-001. (b) Open access covers 147AZ and 148AZ, refer to AMM Task 57-17-11-000-001. (c) Remove the Forward Cargo-Compartment Partition panels 131PW, 132PW and 131NW at Frame 34, refer to AMM Task 25-54-12-000-001. (d) If necessary remove the recirculation filters LH and RH sides, refer to AMM Task 21-21-41-000-001. (e) If necessary, remove the Air-Conditioning Distribution Ducts to get access to the working area, refer to AMM Task 21-20-00-010-001. (f) If necessary remove the potable water tank 3000MM, refer to AMM Task 38-11-41-000-001.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 58 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN (g) Remove insulation blankets around working areas between Frame 35 and Frame 36 LH and RH sides for access, refer to AMM Task 25-80-00-000-001. (h) If necessary, remove electrical bundle clamps and push the bundles aside without disconnection in order to be able to get them out of the working area. **CONF ALL C. PROCEDURE NOTE: This Additional Work is necessary in case of the fasteners and the shims have not been removed to perform the rototest inspection of the holes and inspection of the radius of the rib flange during accomplishment of Service Bulletin No. A320-57-1175 at original issue. **CONF 001 (1) Subtask 571175-000-004-001 - Remove the Fasteners and the Shims Work Zones and Access Panels Zone Access/Work location 130 Access Door 131PW, Door 132PW, Door 131NW 140 Access Panel 147AZ, Panel 148AZ Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9
Kit tool 571175T01R00 ITEM PART N ̊ KEYWORD QTY SEE NOTES 98D57103003000 TOOL 1 References Structural Repair Manual (SRM) 51-42-00 51-44-00 Fig. A-FBGAA Removal/Installation of the Shims for ADDITIONAL WORK Sheet 01 Sheet 02

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 59 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
References Fig. A-FBDAA Removal/Installation of the Rods Sheet 01
Refer to Fig. A-FBDAA Refer to Fig. A-FBGAA In accordance with SRM 51-42-00, SRM 51-44-00 (a) Remove the sealant around the nuts: 1 If necessary, use a non-metallic spatula to remove the sealant and clean the areas with solvent: Non Aqueous Cleaner-General 08BAA9 As required (b) Remove the nuts: Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02 24 Nut Item (4) Discard (c) Remove the bottom attachment bolt of the rod: Refer to Fig. A-FBDAA Sheet 01 NOTE: The quantities are given as a maximum for all ribs, it is not allowed to have 2 rods removed at the same time. 6 Bolt Item (6) Retain 6 Washer Item (7) Retain 6 Nut Item (8) Retain 6 Cotter Pin Item (9) Discard (d) Push the rod out of the working area: 6 Rod Item (10) Retain (e) From inside the tank push back the fasteners until they are flush. NOTE: Do not remove the fasteners by pushing them through the stack up, there is a risk of damaging the hole and contaminating it with steel particles. (f) Install temporarily the rod in initial position before to do the next rod: Refer to Fig. A-FBDAA Sheet 01

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 60 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

6 Rod Item (10) Retained at removal 6 Bolt Item (6) Retained at removal 6 Washer Item (7) Retained at removal 6 Nut Item (8) Retained at removal (g) When all bolts are pushed back, use the special extraction tool, from the forward cargo area, to remove these fasteners: 98D57103003000 Extractor 1 (h) From the tank, remove the shims with non-metallic spatula and identify their position: Refer to Fig. A-FBGAA Sheet 02 12 Shim Item (11) Retain attached with: 24 Bolt Item (3) Discard

(2) Subtask 571175-832-003-001 - Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 Work Zones and Access Panels Zone Access/Work location 130 Access Panel 131PW, Panel 132PW, Panel 131NW 140 Access Panel 147AZ, Panel 148AZ Manpower Resources Manhours 13.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9 As required

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 61 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
References Non Destructive Test Manual (NTM) 51-10-01 51-10-08 Structural Repair Manual (SRM) 51-42-00 51-44-00 Fig. A-FBAAA Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 Sheet 01 Sheet 02 Sheet 03 Fig. A-FRAAA Inspection Report Sheet 01 Sheet 02 Sheet 03 Fig. A-FFBAA Flow Chart for ADDITIONAL WORK Sheet 01 (a) At threshold given in the table 2 of the PLANNING INFORMATION Paragraph E.(2): Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36. Refer to Fig. A-FFBAA Refer to Fig. A-FBAAA 1 Remove the fasteners from the holes to be inspected as described in SUBTASK 571175-000-004 001 Remove the Fasteners and the Shims

. 2 Do a High Frequency Eddy Current (HFEC) inspection of the radius of the rib flanges and vertical stiffener and a rototest Inspection of the holes at FR36. Refer to Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 02
a If necessary, use a non-metallic spatula to remove the sealant and clean the areas with solvent: Non Aqueous Cleaner-General 08BAA9 As required
b Deburr all the holes before inspection.
c Do a High Frequency Eddy Current (HFEC) inspection of the radius of the rib flanges and vertical stiffener and a rototest inspection of the holes as specified in NTM 51-10-08 and NTM 51-10-01. NOTE: For additional information of procedure NTM 51-10-01 refer to Appendix 01 - Non-Destructive Test Requirements.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 62 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
<1> If no crack is found: <a> Oversize the holes of the rib flanges and the shims, refer to SUBTASK 571175-831-007 001 Oversize the Holes of the Shims, on Bench and SUBTASK 571175-831-008 001 Oversize the Holes of the Rib Flanges, on Aircraft

. and Repeat the inspection of the radius and holes in the rib flanges on front spar side at the interval given in the table 2 of the PLANNING INFORMATION Paragraph E.(2), refer to TASK 571175-832-801 001 Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36

. NOTE: For the repetitive inspections it is not necessary to oversize the holes as the holes are in transition fit. <2> If crack is found: <a> Contact Airbus before next flight and follow their instructions. 3 For the inspection report, refer to Fig. A-FRAAA

. (3) Subtask 571175-831-007-001 - Oversize the Holes of the Shims, on Bench Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON SPECIFIC Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9 As required
References Structural Repair Manual (SRM) 51-44-00 Fig. A-FBJAA Oversizing of the Holes of the Shims for ADDITIONAL WORK, on Bench Sheet 01

Refer to Fig. A-FBJAA In accordance with SRM 51-44-00 (a) Oversize the holes of the shims to the diameter given in Fig. A-FBJAA Sheet 01

. DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 63 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN (b) Deburr and clean the holes with: Non Aqueous Cleaner-General 08BAA9 As required (4) Subtask 571175-831-008-001 - Oversize the Holes of the Rib Flanges, on Aircraft Work Zones and Access Panels Zone Access/Work location 140 Access Panel 147AZ, Panel 148AZ Work location Frame 42 130 Access Panel 131PW, Panel 132PW, Panel 131NW Work location Frame 36 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9 As required
References Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 Fig. A-FBHAA Oversizing of the Holes of the Rib Flanges for ADDITIONAL WORK, on Aircraft Sheet 01 Sheet 02

Refer to Fig. A-FBHAA In accordance with SRM 51-24-00, SRM 51-42-00, SRM 51-43-00, SRM 51-44-00 NOTE: This procedure must be applied to one rib at a time. (a) Disengage the rod. (b) Oversize the holes of the rib flanges to the diameter given in Fig. A-FBHAA Sheet 02

.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 64 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN (c) Deburr and clean the holes with: Non Aqueous Cleaner-General 08BAA9 As required (5) Subtask 571175-400-004-001 - Install the Shims with the New Fasteners Work Zones and Access Panels Zone Access/Work location 140 Access Panel 147AZ, Panel 148AZ Work location Frame 42 130 Access Panel 131PW, Panel 132PW, Panel 131NW Work location Frame 36 Manpower Resources Manhours 10.00 Minimum number of person 2 Subtask elapsed time 5.00 Skills AIRFRAME Material necessary to do the job Kit 571175A01R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 3 EN6115V5X15 24 BOLT 4 ASNA2536-5 24 NUT 9 MS24665-153 6 PIN Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Epoxy Primer 04DAB2 As required Anti-Vapor Paint 04PAF8 As required Polysulfide Sealant-General Purpose Brushable 06AAA1 As required Polysulfide Sealant-Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant-Fuel Tank Fillet 06ABB1 As required
References Structural Repair Manual (SRM) 51-23-12 51-24-00 51-42-00 51-43-00 51-75-12

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 65 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
References Fig. A-FBGAA Removal/Installation of the Shims for ADDITIONAL WORK Sheet 01 Sheet 02 Fig. A-FBDAA Removal/Installation of the Rods Sheet 01
Refer to Fig. A-FBDAA Refer to Fig. A-FBGAA In accordance with SRM 51-24-00, SRM 51-42-00, SRM 51-43-00, SRM 51-75-12 (a) Install the shims: Refer to Fig. A-FBGAA Sheet 02 12 Shim Item (11) Retained at removal with: 24 Bolt EN6115V5X15 Item 3 24 Nut ASNA2536-5 Item 4 NOTE: Apply sealant on all contact surface between the shims Item (11) and front spar:Polysulfide SealantFuel Tank Fillet 06ABB1 As required

NOTE: Wet install the fasteners with:Polysulfide SealantGeneral Purpose Brushable 06AAA1 As required
(b) After installation: 1 Over coat the fastener tails and nuts in the tank and perform sealing of the shims and inspection area with:Polysulfide SealantFuel Tank Brushable 06ABA1 As required
(c) In the cargo area: 1 Apply epoxy primer and anti-vapor paint: Epoxy Primer 04DAB2 As required and DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 66 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN Anti-Vapor Paint 04PAF8 As required

2 Renew the special protection around the fastener heads in accordance with SRM 51-23-12. (d) Install the rod in initial position and install the attachment fastener. Refer to Fig. A-FBDAA Sheet 01 1 Install: 6 Rod Item (10) Retained at removal Attached with: 6 Bolt Item (6) Retained at removal 6 Washer Item (7) Retained at removal 6 Nut Item (8) Retained at removal 6 Cotter Pin MS24665-153 Item 9 NOTE: The quantities are given as a maximum for all ribs, it is not allowed to have 2 rods removed at the same time. 2 Perform over coating of nuts and bolts head with:Polysulfide SealantFuel Tank Brushable 06ABA1 As required

**CONF 002 (1) Subtask 571175-000-004-002 - Remove the Fasteners and the Shims Work Zones and Access Panels Zone Access/Work location 130 Access Panel 131PW, Panel 132PW, Panel 131NW 140 Access Panel 147AZ, Panel 148AZ Manpower Resources Manhours 4.00 Minimum number of person 2 Subtask elapsed time 2.00 Skills NON SPECIFIC

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 67 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9
Kit tool 571175T01R00 ITEM PART N ̊ KEYWORD QTY SEE NOTES 98D57103003000 TOOL 1 References Structural Repair Manual (SRM) 51-42-00 51-44-00 Fig. A-FBGAB Removal/Installation of the Shims for ADDITIONAL WORK Sheet 01 Sheet 02 Fig. A-FBDAA Removal/Installation of the Rods Sheet 01
Refer to Fig. A-FBDAA Refer to Fig. A-FBGAB In accordance with SRM 51-42-00, SRM 51-44-00 (a) Remove the sealant around the nuts: 1 If necessary, use a non-metallic spatula to remove the sealant and clean the areas with solvent: Non Aqueous Cleaner-General 08BAA9 As required (b) Remove the nuts: Refer to Fig. A-FBGAB Sheet 01 and Fig. A-FBGAB Sheet 02 24 Nut Item (4) Discard (c) Remove the bottom attachment bolt of the rod: Refer to Fig. A-FBDAA Sheet 01 NOTE: The quantities are given as a maximum for all ribs, it is not allowed to have 2 rods removed at the same time. 6 Bolt Item (6) Retain 6 Washer Item (7) Retain
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 68 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

6 Nut Item (8) Retain 6 Cotter Pin Item (9) Discard (d) Push the rod out of the working area: 6 Rod Item (10) Retain (e) From inside the tank push back the fasteners until they are flush. NOTE: Do not remove the fasteners by pushing them through the stack up, there is a risk of damaging the hole and contaminating it with steel particles. (f) Install temporarily the rod in initial position before to do the next rod: Refer to Fig. A-FBDAA Sheet 01 6 Rod Item (10) Retained at removal 6 Bolt Item (6) Retained at removal 6 Washer Item (7) Retained at removal 6 Nut Item (8) Retained at removal (g) When all bolts are pushed back, use the special extraction tool, from the forward cargo area, to remove these fasteners: 98D57103003000 Extractor 1 (h) From the tank, remove shims with non-metallic spatula and identify their position: Refer to Fig. A-FBGAB Sheet 02 12 Shim Item (11) Retain attached with: 24 Bolt Item (5) Discard

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 69 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN (2) Subtask 571175-832-003-002 - Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 Manpower Resources Manhours 13.00 Minimum number of person 2 Subtask elapsed time 8.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9
References Non Destructive Test Manual (NTM) 51-10-01 51-10-08 Structural Repair Manual (SRM) 51-42-00 51-44-00 Fig. A-FBAAA Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 Sheet 01 Sheet 02 Sheet 03 Fig. A-FRAAA Inspection Report Sheet 01 Sheet 02 Sheet 03 Fig. A-FFBAA Flow Chart for ADDITIONAL WORK Sheet 01 (a) At threshold given in the table 2 of the PLANNING INFORMATION Paragraph E.(2): Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36. Refer to Fig. A-FFBAA Refer to Fig. A-FBAAA NOTE: The following part of the SUBTASK 571175-832-003 002 Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36 must be applied to one rib at a time. It is not allowed to have 2 rods removed at the same time. 1 Remove the fasteners from the holes to be inspected as described in SUBTASK 571175-000-004 002 Remove the Fasteners and the Shims

.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 70 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
2 Do a High Frequency Eddy Current (HFEC) inspection of the radius of the rib flanges and vertical stiffener and a rototest Inspection of the holes at FR36. Refer to Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 02
a If necessary, use a non-metallic spatula to remove the sealant and clean the areas with solvent: Non Aqueous Cleaner-General 08BAA9 As required
b Deburr all the holes before inspection.
c Do a High Frequency Eddy Current (HFEC) inspection of the radius of the rib flanges and vertical stiffener and a rototest inspection of the holes as specified in NTM 51-10-08 and NTM 51-10-01. NOTE: For additional information of procedure NTM 51-10-01 refer to Appendix 01 - Non-Destructive Test Requirements. <1> If no crack is found: <a> Oversize the holes of the rib flanges and the shims, refer to SUBTASK 571175-831-007 002 Oversize the Holes of the Shims, on Bench and SUBTASK 571175-831-008 002 Oversize the Holes of the Rib Flanges, on Aircraft

. and Repeat the inspection of the radius and holes in the rib flanges on front spar side at the interval given in the table 2 of the PLANNING INFORMATION Paragraph E.(2), refer to TASK 571175-832-801 001 Special Detailed Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36

. NOTE: For the repetitive inspections it is not necessary to oversize the holes as the holes are in transition fit. <2> If crack is found: <a> Contact Airbus before next flight and follow their instructions. 3 For the inspection report, refer to Fig. A-FRAAA

. (3) Subtask 571175-831-007-002 - Oversize the Holes of the Shims, on Bench Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills NON SPECIFIC DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 71 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9 As required
References Structural Repair Manual (SRM) 51-44-00 Fig. A-FBJAB Oversizing of the Holes of the Shims for ADDITIONAL WORK, on Bench Sheet 01

Refer to Fig. A-FBJAB In accordance with SRM 51-44-00 (a) Oversize the holes of the shims to the diameter given in Fig. A-FBJAB Sheet 01

. (b) Deburr and clean the holes with: Non Aqueous Cleaner-General 08BAA9 As required (4) Subtask 571175-831-008-002 - Oversize the Holes of the Rib Flanges, on Aircraft Work Zones and Access Panels Zone Access/Work location 140 Access Panel 147AZ, Panel 148AZ Work location Frame 42 130 Access Panel 131PW, Panel 132PW, Panel 131NW Work location Frame 36 Manpower Resources Manhours 2.00 Minimum number of person 2 Subtask elapsed time 1.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9 As required

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 72 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
References Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00 51-44-00 Fig. A-FBHAB Oversizing of the Holes of the Rib Flanges for ADDITIONAL WORK, on Aircraft Sheet 01 Sheet 02

Refer to Fig. A-FBHAB In accordance with SRM 51-24-00, SRM 51-42-00, SRM 51-43-00, SRM 51-44-00 NOTE: This procedure must be applied to one rib at a time. (a) Disengage the rod. (b) Oversize the holes of the rib flanges to the diameter given in Fig. A-FBHAB Sheet 02

. (c) Deburr and clean the holes with: Non Aqueous Cleaner-General 08BAA9 As required (5) Subtask 571175-400-004-002 - Install the Shims with the New Fasteners Work Zones and Access Panels Zone Access/Work location 140 Access Panel 147AZ Work location Frame 42 130 Access Panel 131PW, Panel 132PW, Panel 131NW Work location Frame 36 Manpower Resources Manhours 10.00 Minimum number of person 2 Subtask elapsed time 5.00 Skills AIRFRAME Material necessary to do the job Kit 571175A02R00 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 4 ASNA2536-5 24 NUT 5 EN6115V5Y15 24 BOLT 9 MS24665-153 6 PIN

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 73 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Epoxy Primer 04DAB2 As required Anti-Vapor Paint 04PAF8 As required Polysulfide Sealant-General Purpose Brushable 06AAA1 As required Polysulfide Sealant-Fuel Tank Brushable 06ABA1 As required Polysulfide Sealant-Fuel Tank Fillet 06ABB1 As required
References Structural Repair Manual (SRM) 51-23-12 51-24-00 51-42-00 51-43-00 51-75-12 Fig. A-FBGAB Removal/Installation of the Shims for ADDITIONAL WORK Sheet 01 Sheet 02 Fig. A-FBDAA Removal/Installation of the Rods Sheet 01
Refer to Fig. A-FBDAA Refer to Fig. A-FBGAB In accordance with SRM 51-24-00, SRM 51-42-00, SRM 51-43-00, SRM 51-75-12 (a) Install the shims: Refer to Fig. A-FBGAB Sheet 02 12 Shim Item (11) Retained at removal with: 24 Bolt EN6115V5Y15 Item 5 24 Nut ASNA2536-5 Item 4 NOTE: Apply sealant on all contact surface between the shims Item (11) and front spar:Polysulfide SealantFuel Tank Fillet 06ABB1 As required

NOTE: Wet install the fasteners with:

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 74 5

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

# @A318/A319/A320/A321 SERVICE BULLETINPolysulfide SealantGeneral Purpose Brushable 06AAA1 As required
(b) After installation: 1 Over coat the fastener tails and nuts in the tank and perform sealing of the shims and inspection area with:Polysulfide SealantFuel Tank Brushable 06ABA1 As required
(c) In the cargo area: 1 Apply epoxy primer and anti-vapor paint: Epoxy Primer 04DAB2 As required and Anti-Vapor Paint 04PAF8 As required

2 Renew the special protection around the fastener heads in accordance with SRM 51-23-12. (d) Install the rod in initial position and install the attachment fastener. Refer to Fig. A-FBDAA Sheet 01 1 Install: 6 Rod Item (10) Retained at removal Attached with: 6 Bolt Item (6) Retained at removal 6 Washer Item (7) Retained at removal 6 Nut Item (8) Retained at removal 6 Cotter Pin MS24665-153 Item 9 NOTE: The quantities are given as a maximum for all ribs, it is not allowed to have 2 rods removed at the same time.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 75 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
2 Perform over coating of nuts and bolts head with:Polysulfide SealantFuel Tank Brushable 06ABA1 As required

**CONF ALL D. TEST **CONF 001 (1) Subtask 571175-700-003-001 - Testing Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 20-28-00, Page Block 501 Task 21-20-00-410-001 Task 25-54-12-400-001 Task 52-30-00-860-002 Task 57-17-11-400-001 NOTE: This Service Bulletin requires the accomplishment of the following Tests which are given in subtasks included in the topic Close-up. The manhours for the tests are included in the referenced Service Bulletin subtask. - Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air-Conditioning Distribution Ducts, refer to AMM Task 21-20-00-410-001. - Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Access Covers 147AZ and 148AZ, refer to AMM Task 57-17-11-400-001. - Remove the Safety clips and tags and close the circuit breakers as specified after Closing the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump, refer to AMM Task 52-30-00-860-002. - Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of Forward Cargo-Compartment Partition panels at Frame 34, refer to AMM Task 25-54-12-400-001. - Do the test procedure as specified after the installation of the access covers 147AZ and 148AZ, refer to AMM Task 57-17-11-400-001. - Do the test procedure as specified after the installation of the Air-Conditioning Distribution Ducts, refer to AMM Task 21-20-00-410-001.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 76 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
**CONF 002 (1) Subtask 571175-700-003-001 - Testing Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 20-28-00, Page Block 501 Task 21-20-00-410-001 Task 25-54-12-400-001 Task 52-30-00-860-002 Task 57-17-11-400-001 NOTE: This Service Bulletin requires the accomplishment of the following Tests which are given in subtasks included in the topic Close-up. The manhours for the tests are included in the referenced Service Bulletin subtask. - Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Air-Conditioning Distribution Ducts, refer to AMM Task 21-20-00-410-001. - Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of the Access Covers 147AZ and 148AZ, refer to AMM Task 57-17-11-400-001. - Remove the Safety clips and tags and close the circuit breakers as specified after Closing the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump, refer to AMM Task 52-30-00-860-002. - Remove the Safety clips and tags and close the circuit breakers as specified after the Installation of Forward Cargo-Compartment Partition panels at Frame 34, refer to AMM Task 25-54-12-400-001. - Do the test procedure as specified after the installation of the access covers 147AZ and 148AZ, refer to AMM Task 57-17-11-400-001. - Do the test procedure as specified after the installation of the Air-Conditioning Distribution Ducts, refer to AMM Task 21-20-00-410-001. **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 571175-942-003-001 - Close-up Manpower Resources Skills NON SPECIFIC

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 77 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-001 Task 21-21-41-400-001 Task 25-54-12-400-001 Task 25-80-00-400-001 28-25-00, Page Block 301 Task 32-12-00-410-001 Task 38-11-41-400-001 Task 52-30-00-860-002 Task 57-17-11-400-801 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the access cover 147AZ and 148AZ, refer to AMM Task 57-17-11-400-801. (c) Install the Air-Conditioning Distribution Ducts removed for access to the working area, AMM Task 21-20-00-410-001. (d) If removed, install the recirculation filters LH and RH sides, refer to AMM Task 21-21-41-400-001. (e) If removed, install the potable water tank 3000MM, refer to AMM Task 38-11-41-400-001. (f) Install the removed insulation blankets around working areas, refer to AMM Task 25-80-00-400-001. 1 Install the heat and sound insulation in the area between Frame 35 and Frame 36 LH and RH sides removed for acces. 2 If removed, install electrical bundle clamps removed for access. (g) Install the removed Forward Cargo-Compartment Partition 131PW, 132PW and 131NW at Frame 34, refer to AMM Task 25-54-12-400-001. (h) Refuel the center tank, refer to AMM 28-25-00, Page Block 301. (i) Close the FWD cargo compartment door 825, refer to AMM Task 52-30-00-860-002. (j) Close the main landing gear doors, refer to AMM Task 32-12-00-410-001. (k) Restore the systems and the aircraft to normal operating condition. (l) Remove the access platform(s). **CONF 002 (1) Subtask 571175-942-003-001 - Close-up Manpower Resources Skills NON SPECIFIC DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 78 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN
References Aircraft Maintenance Manual (AMM) Task 21-20-00-410-001 Task 21-21-41-400-001 Task 25-54-12-400-001 Task 25-80-00-400-001 28-25-00, Page Block 301 Task 32-12-00-410-001 Task 38-11-41-400-001 Task 52-30-00-860-002 Task 57-17-11-400-801 (a) Make sure that the work areas are clean and clear of tools and other items of equipment. (b) Install the access cover 147AZ and 148AZ, refer to AMM Task 57-17-11-400-801. (c) Install the Air-Conditioning Distribution Ducts removed for access to the working area, AMM Task 21-20-00-410-001. (d) If removed, install the recirculation filters LH and RH sides, refer to AMM Task 21-21-41-400-001. (e) If removed, install the potable water tank 3000MM, refer to AMM Task 38-11-41-400-001. (f) Install the removed insulation blankets around working areas, refer to AMM Task 25-80-00-400-001. 1 Install the heat and sound insulation in the area between Frame 35 and Frame 36 LH and RH sides removed for acces. 2 If removed, install electrical bundle clamps removed for access. (g) Install the removed Forward Cargo-Compartment Partition 131PW, 132PW and 131NW at Frame 34, refer to AMM Task 25-54-12-400-001. (h) Refuel the center tank, refer to AMM 28-25-00, Page Block 301. (i) Close the FWD cargo compartment door 825, refer to AMM Task 52-30-00-860-002. (j) Close the main landing gear doors, refer to AMM Task 32-12-00-410-001. (k) Restore the systems and the aircraft to normal operating condition. (l) Remove the access platform(s).

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 79 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 80 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

FR36 FR42



## A

**B C**  **C C**  **C C**  **C** Y−1292
Y−765
Y−254
Y 254
Y 765
Y 1292 

### D **D D**  **D D**  **D E**  **E E**  **E E**  **E B**  **A**

N_SB_571175_5_BAAA_01_03 Figure A-FBAAA - Sheet 01 Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 81 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

HOLES TO BE INSPECTED VIEW LOOKING FORWARD

LH SHOWN RH SYMMETRICAL INSPECTION AREA **NOTE:** 

## C

**D**

N_SB_571175_5_BAAA_02_02 Figure A-FBAAA - Sheet 02 Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 82 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL



## E VIEW LOOKING BACK

INSPECTION AREA **NOTE:**

N_SB_571175_5_BAAA_03_00 Figure A-FBAAA - Sheet 03 Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 83 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001



### A FR36 FR42



## A

**B B** 

**C C**  **C C**  **C C**  Y−1292
Y−765
Y−254
Y 254
Y 765
Y 1292

N_SB_571175_5_BBAA_01_02 Figure A-FBBAA - Sheet 01 Removal/Installation of the Shims
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 84 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

HOLE SYMBOLE ITEM PN DESCRIPTION EN6115V5X15 BOLT ASNA2536−5 NUT **NOTE:** WET INSTALL WITH MAT. No 06AAA1 01 03

AFTER INSTALLATION, APPLY: 03 − ON THE FASTENER HEAD MAT. No 04DAB2 AND MAT. No 04PAF8 − ON THE NUT MAT. No 06ABA1 01 F

HEAD ON HIDDEN SIDE F REMARKS 

## C VIEW LOOKING FORWARD (11) (11) 02 02

(1) (2)3 4

SEALANT MUST BE APPLIED ON ALL CONTACT SURFACE BETWEEN SHIM 02 AND FRONT SPAR WITH MAT. No 06ABB1 FIRST OVERSIZE DIAMETER IN TRANSITION FIT

N_SB_571175_5_BBAA_02_05 Figure A-FBBAA - Sheet 02 Removal/Installation of the Shims
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 85 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002



### A FR36 FR42



## A

**B B** 

**C C**  **C C**  **C C**  Y−1292
Y−765
Y−254
Y 254
Y 765
Y 1292

N_SB_571175_5_BBAB_01_01 Figure A-FBBAB - Sheet 01 Removal/Installation of the Shims
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 86 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002

HOLE SYMBOLE ITEM PN DESCRIPTION EN6115V5Y15 BOLT ASNA2536−5 NUT **NOTE:** WET INSTALL WITH MAT. No 06AAA1 01 03

AFTER INSTALLATION, APPLY: 03 − ON THE FASTENER HEAD MAT. No 04DAB2 AND MAT. No 04PAF8 − ON THE NUT MAT. No 06ABA1 01

F

HEAD ON HIDDEN SIDE F REMARKS 

## C VIEW LOOKING FORWARD (11) (11) 02 02

(1) (2)5 4

SEALANT MUST BE APPLIED ON ALL CONTACT SURFACE BETWEEN SHIM 02 AND FRONT SPAR WITH MAT. No 06ABB1 SECOND OVERSIZE DIAMETER IN TRANSITION FIT

N_SB_571175_5_BBAB_02_00 Figure A-FBBAB - Sheet 02 Removal/Installation of the Shims
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 87 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

(10)

TYPICAL VIEW (6) (7) (8) 9 (9)



## A **A FWD**  

### A

**A** FR36 FR42



## B **A B** 

01

**NOTE:** AFTER INSTALATION OF THE FASTENER APPLY: 01 − ON THE FASTENER HEAD MAT. No 04EAC2 − ON THE NUT MAT. No 06ABA1 0/+ 0.2 mm (0/+0.0079 in) 

### A

N_SB_571175_5_BDAA_01_01 Figure A-FBDAA - Sheet 01 Removal/Installation of the Rods
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 88 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

FR36 FR42



## A

**B C**  **C C**  **C C**  **C** Y−1292
Y−765
Y−254
Y 254
Y 765
Y 1292 

### A

**B**

N_SB_571175_5_BEAA_01_01 Figure A-FBEAA - Sheet 01 Oversizing of the Holes of the Rib Flanges, on Aircraft
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 89 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001



## C VIEW LOOKING FORWARD

HOLE HOLE DIAMETER MIN MAX 8.296 mm (0.327 in) 8.335 mm (0.328 in) SYMBOLE FIRST OVERSIZE DIAMETER IN TRANSITION FIT REMARKS

N_SB_571175_5_BEAA_02_00 Figure A-FBEAA - Sheet 02 Oversizing of the Holes of the Rib Flanges, on Aircraft
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 90 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002



### A FR36 FR42



## A

**B B** 

**C C**  **C C**  **C C**  Y−1292
Y−765
Y−254
Y 254
Y 765
Y 1292

N_SB_571175_5_BEAB_01_01 Figure A-FBEAB - Sheet 01 Oversizing of the Holes of the Rib Flanges, on Aircraft
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 91 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002



## C VIEW LOOKING FORWARD

HOLE SYMBOL HOLE DIAMETER MIN MAX 8.692 mm (0.342 in) 8.732 mm (0.344 in) SECOND OVERSIZE DIAMETER IN TRANSITION FIT REMARKS

N_SB_571175_5_BEAB_02_00 Figure A-FBEAB - Sheet 02 Oversizing of the Holes of the Rib Flanges, on Aircraft
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 92 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

ON BENCH

HOLE HOLE DIAMETER MIN MAX 8.321 mm (0.328 in) 8.345 mm (0.329 in) SYMBOLE (11) (11)

N_SB_571175_5_BFAA_01_00 Figure A-FBFAA - Sheet 01 Oversizing of the Holes of the Shims, on Bench
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 93 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002

HOLE SYMBOL HOLE DIAMETER MIN MAX 8.717 mm (0.343 in) 8.742 mm (0.344 in) 

## ON BENCH (11) (11)

N_SB_571175_5_BFAB_01_00 Figure A-FBFAB - Sheet 01 Oversizing of the Holes of the Shims, on Bench
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 94 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001



### A FR36 FR42



## A

**B B** 

**C C**  **C C**  **C C**  Y−1292
Y−765
Y−254
Y 254
Y 765
Y 1292

N_SB_571175_5_BGAA_01_01 Figure A-FBGAA - Sheet 01 Removal/Installation of the Shims for ADDITIONAL WORK
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 95 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

HOLE SYMBOLE ITEM PN DESCRIPTION EN6115V5X15 BOLT ASNA2536−5 NUT **NOTE:** WET INSTALL WITH MAT. No 06AAA1 01 03

AFTER INSTALLATION, APPLY: 03 − ON THE FASTENER HEAD MAT. No 04DAB2 AND MAT. No 04PAF8 − ON THE NUT MAT. No 06ABA1 01

F

HEAD ON HIDDEN SIDE F REMARKS 

## C VIEW LOOKING FORWARD (11) (11) 02 02

(3) (4)5 4

SEALANT MUST BE APPLIED ON ALL CONTACT SURFACE BETWEEN SHIM 02 AND FRONT SPAR WITH MAT. No 06ABB1 FIRST OVERSIZE DIAMETER IN TRANSITION FIT

N_SB_571175_5_BGAA_02_01 Figure A-FBGAA - Sheet 02 Removal/Installation of the Shims for ADDITIONAL WORK
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 96 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002



### A FR36 FR42



## A

**B B** 

**C C**  **C C**  **C C**  Y−1292
Y−765
Y−254
Y 254
Y 765
Y 1292

N_SB_571175_5_BGAB_01_01 Figure A-FBGAB - Sheet 01 Removal/Installation of the Shims for ADDITIONAL WORK
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 97 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002

HOLE SYMBOLE ITEM PN DESCRIPTION EN6115V5Y15 BOLT ASNA2536−5 NUT **NOTE:** WET INSTALL WITH MAT. No 06AAA1 01 03

AFTER INSTALLATION, APPLY: 03 − ON THE FASTENER HEAD MAT. No 04DAB2 AND MAT. No 04PAF8 − ON THE NUT MAT. No 06ABA1 01

F

HEAD ON HIDDEN SIDE F REMARKS 

## C VIEW LOOKING FORWARD (11) (11) 02 02

(5) (4)6 7

SEALANT MUST BE APPLIED ON ALL CONTACT SURFACE BETWEEN SHIM 02 AND FRONT SPAR WITH MAT. No 06ABB1 SECOND OVERSIZE DIAMETER IN TRANSITION FIT

N_SB_571175_5_BGAB_02_01 Figure A-FBGAB - Sheet 02 Removal/Installation of the Shims for ADDITIONAL WORK
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 98 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001



### A FR36 FR42



## A

**B B** 

**C C**  **C C**  **C C**  Y−1292
Y−765
Y−254
Y 254
Y 765
Y 1292

N_SB_571175_5_BHAA_01_01 Figure A-FBHAA - Sheet 01 Oversizing of the Holes of the Rib Flanges for ADDITIONAL WORK, on Aircraft
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 99 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001



## C VIEW LOOKING FORWARD

HOLE SYMBOL HOLE DIAMETER MIN MAX 8.296 mm (0.327 in) 8.335 mm (0.328 in) FIRST OVERSIZE DIAMETER IN TRANSITION FIT REMARKS

N_SB_571175_5_BHAA_02_01 Figure A-FBHAA - Sheet 02 Oversizing of the Holes of the Rib Flanges for ADDITIONAL WORK, on Aircraft
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 100 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002



### A FR36 FR42



## A

**B B** 

**C C**  **C C**  **C C**  Y−1292
Y−765
Y−254
Y 254
Y 765
Y 1292

N_SB_571175_5_BHAB_01_01 Figure A-FBHAB - Sheet 01 Oversizing of the Holes of the Rib Flanges for ADDITIONAL WORK, on Aircraft
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 101 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002



## C VIEW LOOKING FORWARD

HOLE SYMBOL HOLE DIAMETER MIN MAX 8.692 mm (0.342 in) 8.732 mm (0.344 in) SECOND OVERSIZE DIAMETER IN TRANSITION FIT REMARKS

N_SB_571175_5_BHAB_02_01 Figure A-FBHAB - Sheet 02 Oversizing of the Holes of the Rib Flanges for ADDITIONAL WORK, on Aircraft
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 102 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 001

HOLE SYMBOL HOLE DIAMETER MIN MAX 8.321 mm (0.328 in) 8.345 mm (0.329 in) 

## ON BENCH (11) (11)

N_SB_571175_5_BJAA_01_01 Figure A-FBJAA - Sheet 01 Oversizing of the Holes of the Shims for ADDITIONAL WORK, on Bench
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 103 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF 002

HOLE SYMBOL HOLE DIAMETER MIN MAX 8.717 mm (0.343 in) 8.742 mm (0.344 in) 

## ON BENCH (11) (11)

N_SB_571175_5_BJAB_01_01 Figure A-FBJAB - Sheet 01 Oversizing of the Holes of the Shims for ADDITIONAL WORK, on Bench
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 104 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

QUESTION ACTION FINDING AT THE THRESHOLD GIVEN IN THE TABLE 1 OF THE PLANNING INFORMATION PARAGRAPH E.(2) REFER TO TASK 571175−832−801

CRACKS FOUND YES NO

OVERSIZE AND INSTALL NEW FASTENERS DO A SPECIAL DETAILED INSPECTION OF THE RADUIS AND HOLES OF THE RIB FLANGES AND VERTICAL STIFFENER AT FR36

BEFORE NEXT FLIGHT AND FOLLOW CONTACT AIRBUS THEIR INSTRUCTIONS REFER TO SUBTASK 571175−831−005

HOLES OF THE RIB FLANGES AND VERTICAL REPEAT THE INSPECTION OF THE RADIUS AND
THE TABLE 1 OF THE PLANNING INFORMATION PARAGRAPH E.(2) STIFFENER AT FR36 AT THE INTERVAL GIVEN IN
REFER TO TASK 571175−832−801

**NOTE:** THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN 01

FOR REPETITIVE INSPECTION IT IS NOT NECESSARY TO OVERSIZE THE HOLES AS THE HOLES ARE 01 IN TANSITION FIT AND SUBTASK 571175−831−006 AND SUBTASK 571175−400−003

N_SB_571175_5_FAAA_01_06 Figure A-FFAAA - Sheet 01 Flow Chart
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 105 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL

QUESTION ACTION FINDING AT THE THRESHOLD GIVEN IN THE TABLE 2 OF THE PLANNING INFORMATION PARAGRAPH E.(2) REFER TO TASK 571175−832−802

CRACKS FOUND YES NO

OVERSIZE AND INSTALL NEW FASTENERS DO A SPECIAL DETAILED INSPECTION OF THE RADUIS AND HOLES OF THE RIB FLANGES AND VERTICAL STIFFENER AT FR36

BEFORE NEXT FLIGHT AND FOLLOW CONTACT AIRBUS THEIR INSTRUCTIONS

AND HOLES OF THE RIB FLANGES AND VERTICAL REPEAT THE INSPECTION OF THE RADIUS THE TABLE 1 OF THE PLANNING INFORMATION PARAGRAPH E.(2) STIFFENER AT FR36 AT THE INTERVAL GIVEN IN
REFER TO TASK 571175−832−801

**NOTE:** THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN 01

FOR REPETITIVE INSPECTION IT IS NOT NECESSARY TO OVERSIZE THE HOLES AS THE HOLES ARE 01 IN TANSITION FIT REFER TO SUBTASK 571175−831−007 AND SUBTASK 571175−831−008 AND SUBTASK 571175−400−004

N_SB_571175_5_FBAA_01_03 Figure A-FFBAA - Sheet 01 Flow Chart for ADDITIONAL WORK
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 106 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL **INSPECTION REPORT** SERVICE BULLETIN No : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A320−57−1175

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

INSPECTION METHOD : 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE E−mail: structure.sbinspectionresult@airbus.com SPECIAL DETAILED INSPECTION FAX: +33 (0)5 61 93 36 14 CENTER WING BOX (SA/LA)

LOWER RIB Y 1292 LOWER RIB Y 765 LOWER RIB Y 254 LOWER RIB Y −254 LOWER RIB Y −765 LOWER RIB Y −1292 CRACK FOUND VIEW LOOKING FORWARD

**NOTE:** IN CASE OF CRACK FOUND, GIVE HOLE NUMBER TYPICAL

NO CRACK

FOUND H2 H1

H3 H4

N_SB_571175_5_RAAA_01_03 Figure A-FRAAA - Sheet 01 Inspection Report
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 107 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL **INSPECTION REPORT** SERVICE BULLETIN No : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A320−57−1175

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

INSPECTION METHOD : 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE E−mail: structure.sbinspectionresult@airbus.com SPECIAL DETAILED INSPECTION FAX: +33 (0)5 61 93 36 14 CENTER WING BOX (SA/LA)

LOWER RIB Y 1292 LOWER RIB Y 765 LOWER RIB Y 254 LOWER RIB Y −254 LOWER RIB Y −765 LOWER RIB Y −1292

CRACK FOUND

**NOTE:** TYPICAL

NO CRACK

FOUND LH SHOWN RH SYMMETRICAL

INSPECTION AREA LH RH LH RH LH RH LH RH LH RH LH RH

N_SB_571175_5_RAAA_02_01 Figure A-FRAAA - Sheet 02 Inspection Report
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 108 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

**CONF ALL **INSPECTION REPORT** SERVICE BULLETIN No : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A320−57−1175

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

INSPECTION METHOD : 1 ROND POINT MAURICE BELLONTE 31707 BLAGNAC CEDEX FRANCE E−mail: structure.sbinspectionresult@airbus.com SPECIAL DETAILED INSPECTION FAX: +33 (0)5 61 93 36 14 CENTER WING BOX (SA/LA)

INSPECTION AREA **NOTE:** VIEW LOOKING BACK TYPICAL CRACK FOUND NO CRACK

FOUND LH LOWER RIB Y 1292
TOP BOTTOM RH TOP BOTTOM LH LOWER RIB Y 765
TOP BOTTOM RH TOP BOTTOM LH LOWER RIB Y 254
TOP BOTTOM RH TOP BOTTOM

CRACK FOUND

NO CRACK

FOUND LH LOWER RIB Y−254
TOP BOTTOM RH TOP BOTTOM LH LOWER RIB Y−765
TOP BOTTOM RH TOP BOTTOM LH LOWER RIB Y−1292
TOP BOTTOM RH TOP BOTTOM

N_SB_571175_5_RAAA_03_00 Figure A-FRAAA - Sheet 03 Inspection Report
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 109 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 110 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN Appendix 01 - Non-Destructive Test Requirements **CONF ALL For the non-destructive test requirements refer to the following sheet.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 1 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN Appendix 01 - Non-Destructive Test Requirements

**CONF ALL

DURING THE ACCOMPLISHMENT OF HFEC ROTO TEST HOLE INSPECTION (NTM 51−10−01), DEFECT SIGNALS IDENTIFIED AS COMING FROM THE INTERFACE OF THE RIB FLANGE AND THE ANGLE FITTING (SEE FIGURE 1) MAYBE A RESULT OF BURRING. TYPICAL SIGNALS ARE SHOWN IN FIGURES 2 & 3. **CAUTION:**

FIGURE 1: STRUCTURAL CONFIGURATION OF INSPECTED HOLES SB 57−1175 THE SIGNAL MAY BE LARGER AND NOISIER WITH THE ADDITIONAL DB’S AS REQUIRED **NOTE:** BY NTM 51−10−01 (FIG 2 & 3).

FIGURE 2: TYPICAL BURR SIGNAL +6DB Y/T FIGURE 3: TYPICAL BURR SIGNAL +6DB

FIGURE 4: TYPICAL BURR SIGNAL Y/X−T NO DB ADDED 1. LOCALLY POLISH THE INTERFACE WITH A NON METALLIC ABRASIVE TO REDUCE THE AMPLITUDE. 2. USE NTM 51−10−01 BUT DO NOT ADD THE ADDITIONAL **TASK:**
DB’S (B. INSTRUMENT ADJUSTMENT (6) (A) 5). 3. RE−INSPECT. 4. APPLY ACCEPTANCE CRITERIA (C. INSPECTION (6) (A) & (B)) (SEE FIG 4). N_SB_571175_5_AAAA_01_00 Figure A-FAAAA - Sheet 01 Non-Destructive Test Requirements
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 2 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN Appendix 02 - Elapsed Time Assumption **CONF ALL For an explanation of the manhours and elapsed time, refer to the following Gantt Chart.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 1 5

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

# @A318/A319/A320/A321 SERVICE BULLETIN Appendix 02 - Elapsed Time Assumption

**CONF ALL

**ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A320−57−1175**

SB ELAPSED TIME (HOURS) GET ACCESS MH ET/S

TOTAL MANHOURS SB ELAPSED TIME 45.00 31.00 STEPS

6.00 6.00

5 10 15 0

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

1

: : IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS ARE NOT REFLECTED IN THIS GANTT CHART 20 25 REMOVE THE FASTENERS 4.00 2.00 2
DO A SPECIAL DETAILED 13.00 8.00 2
OVERSIZE THE HOLES OF 2.00 1.00 2
OVERSIZE THE HOLES OF THE 2.00 1.00 2
INSTALL THE SHIMS WITH NEW 10.00 5.00 2
TEST 1.00 1.00 1
CLOSED−UP 7.00 7.00 1 INSPECTION
THE SHIMS
RIB FLANGES
FASTENERS

30 AND THE SHIMS

N_SB_571175_5_ABAA_01_01 Figure A-FABAA - Sheet 01 Elapsed Time Assumption
DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 2 5

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

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

### TITLE: WING - CENTER WING - INSPECTION OF THE LOWER RIBS AT FR36 JUNCTION MODIFICATION No.: None Please complete the appropriate item (A or B): A - SB WILL BE embodied YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of embodiment:

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

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 1 5

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: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175 REVISION No.: 01 - May 28/14 Page: 1 5

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