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



# MANDATORY MANDATORY MANDATORY
ATA SYSTEM: 57 

### TITLE: WINGS - INSPECTION OF FRONT SPAR VERTICAL STRINGERS MODIFICATION No.: None This page transmits Revision No.01 of Service Bulletin No.A320-57-1178 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 vertical stiffener radius has not been done, - the rototest inspection has not been done. Additional work consists in: - The removal of the shims and fasteners in inspected area on which it has not been done, - Addition of the HFEC Inspection of the vertical stiffener and horizontal Floor Beam Radius, - Addition of the rototest inspection of the upper fasteners holes. REASON Revision No. 01 issued to: - Remove and install the fasteners for the Inspection of front spar vertical stringers radius - Add HFEC Inspection of the horizontal floor beam radius - Add the rototest inspection of the fasteners holes of front spar vertical stringers radius 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. DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 CHANGES The main changes of this revision are: - Removal and installation of the fasteners for the Inspection of front spar vertical stringers radius for conf 001 - Removal, oversizing and installation of the shims for the Inspection of front spar vertical stringers radius, only for the configurations 002 - Removal and installation of the shims for the Inspection of front spar vertical stringers radius, only for the configurations 003 - Modification of job set-up and close-up procedures of the Inspection Task - Creation of the Additional work Task - Addition of the HFEC Inspection of the horizontal floor beam radius - Addition of the rototest inspection of the fasteners holes of front spar vertical stringers radius - Modification of the NTM reference to perform HFEC Inspection SUMMARY REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES REASON UPDATED R GENERAL EVALUATION GENERAL EVALUATION TABLE UPDATED R MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE UPDATED R MATERIAL PRICE INFORMATION TABLE UPDATED R MATERIAL PRICE INFORMATION TABLE UPDATED R EFFECTIVITY OPERATOR LIST UPDATED R MANPOWER MANPOWER UPDATED R MANPOWER UPDATED R MANPOWER UPDATED R APPENDICES APPENDICES UPDATED R Fig. A-FSAAA FIGURE SOLUTION UPDATED R Fig. A-FSAAA Sheet 01 SHEET UPDATED R Fig. A-FSAAA Sheet 02 SHEET ADDED N Fig. A-FSAAB FIGURE SOLUTION UPDATED R Fig. A-FSAAB Sheet 01 SHEET UPDATED R Fig. A-FSAAB Sheet 02 SHEET ADDED N PLANNING INFORMATION EFFECTIVITY EFFECTIVITY RELATED INFORMATION UPDATED R Configuration definition CONF 001 CONFIGURATION DEFINITION UPDATED R
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
CONF 002 CONFIGURATION DEFINITION UPDATED R CONF 003 CONFIGURATION DEFINITION UPDATED R Material Effectivity MATERIAL EFFECTIVITY UPDATED MATERIAL SET QUANTITY UPDATED CONFIGURATION UPDATED MATERIAL SET UPDATED R

MATERIAL EFFECTIVITY ADDED N MATERIAL EFFECTIVITY ADDED N REASON History HISTORY UPDATED R Objective/Action OBJECTIVE/ACTION UPDATED R Operational/Maintenance Consequences OPERATIONAL/MAINTENANCE CONSEQUENCES UPDATED R COMPLIANCE Classification CLASSIFICATION UPDATED R Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED CONFIGURATION 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 MANPOWER UPDATED CONFIGURATION UPDATED R REFERENCES REFERENCED DOCUMENTATION UPDATED R 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 571178A01R01 PART MATERIAL SET ADDED N Kit 571178A02R01 PART MATERIAL SET ADDED N Kit 571178A03R01 PART MATERIAL SET ADDED N LIST OF MATERIALS - OPERATOR SUPPLIED Consumable Materials CONSUMABLE MATERIALS UPDATED R

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
Consumable CMLA01 CONSUMABLE MATERIAL SET UPDATED QUANTITY UPDATED CONSUMABLE UPDATED R Components COMPONENTS UPDATED R ACCOMPLISHMENT INSTRUCTIONS TASK 571178- 832-801-001-Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 TASK SOLUTION UPDATED TASK TITLE UPDATED CAUTION UPDATED NOTE UPDATED R

Task associated data - 001 MAN HOURS UPDATED ELAPSED TIME UPDATED R Task associated data - 002 MAN HOURS UPDATED ELAPSED TIME UPDATED R Task associated data - 003 MAN HOURS UPDATED ELAPSED TIME UPDATED R Subtask 571178-910-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R
Subtask 571178-910-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R
Subtask 571178-910-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED REFERENCES UPDATED R
Subtask 571178-941-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED NOTE UPDATED PANEL UPDATED REFERENCES UPDATED R

Subtask 571178-941-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED NOTE UPDATED PANEL UPDATED REFERENCES UPDATED R

Subtask 571178-941-001-001 SUBTASK SOLUTION UPDATED REFERENCED DOCUMENTATION UPDATED NOTE UPDATED PANEL UPDATED REFERENCES UPDATED R

Subtask 571178-831-001-001 SUBTASK SOLUTION ADDED N Subtask 571178-832-001-001 SUBTASK SOLUTION UPDATED QUANTITY UPDATED CONSUMABLE UPDATED REFERENCED DOCUMENTATION UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED REFERENCES UPDATED R

Subtask 571178-831-003-001 SUBTASK SOLUTION ADDED N Subtask 571178-831-001-003 SUBTASK SOLUTION ADDED N DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 571178-832-001-002 SUBTASK SOLUTION UPDATED QUANTITY UPDATED CONSUMABLE UPDATED REFERENCED DOCUMENTATION UPDATED CONFIGURATION UPDATED FIGURE REFERENCE UPDATED NOTE UPDATED REFERENCES UPDATED R

Subtask 571178-831-002-003 SUBTASK SOLUTION ADDED N Subtask 571178-831-003-003 SUBTASK SOLUTION ADDED N Subtask 571178-831-001-002 SUBTASK SOLUTION ADDED N Subtask 571178-832-001-003 SUBTASK SOLUTION ADDED N Subtask 571178-831-003-002 SUBTASK SOLUTION ADDED N Subtask 571178-832-001-002 SUBTASK SOLUTION DELETED FOR APPLICABLE MSN D Subtask 571178-700-001-001 SUBTASK SOLUTION UPDATED NOTE UPDATED R Subtask 571178-700-001-001 SUBTASK SOLUTION UPDATED NOTE UPDATED R Subtask 571178-700-001-001 SUBTASK SOLUTION UPDATED NOTE UPDATED R Subtask 571178-942-001-001 SUBTASK SOLUTION UPDATED R Subtask 571178-942-001-001 SUBTASK SOLUTION UPDATED R Subtask 571178-942-001-001 SUBTASK SOLUTION UPDATED R TASK 571178- 832-802-001-Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK TASK SOLUTION ADDED N

Task associated data - 001 TASK ASSOCIATED DATA ADDED N Task associated data - 002 TASK ASSOCIATED DATA ADDED N Task associated data - 003 TASK ASSOCIATED DATA ADDED N Subtask 571178-910-002-001 SUBTASK SOLUTION ADDED N Subtask 571178-839-002-001 SUBTASK SOLUTION ADDED N Subtask 571178-910-002-001 SUBTASK SOLUTION ADDED N Subtask 571178-839-002-001 SUBTASK SOLUTION ADDED N Subtask 571178-910-002-001 SUBTASK SOLUTION ADDED N Subtask 571178-839-002-001 SUBTASK SOLUTION ADDED N Subtask 571178-941-002-001 SUBTASK SOLUTION ADDED N Subtask 571178-941-002-001 SUBTASK SOLUTION ADDED N Subtask 571178-941-002-001 SUBTASK SOLUTION ADDED N Subtask 571178-831-004-001 SUBTASK SOLUTION ADDED N Subtask 571178-832-002-001 SUBTASK SOLUTION ADDED N Subtask 571178-831-006-001 SUBTASK SOLUTION ADDED N Subtask 571178-831-004-003 SUBTASK SOLUTION ADDED N Subtask 571178-832-002-002 SUBTASK SOLUTION ADDED N Subtask 571178-831-005-003 SUBTASK SOLUTION ADDED N Subtask 571178-831-006-003 SUBTASK SOLUTION ADDED N
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
Subtask 571178-831-004-002 SUBTASK SOLUTION ADDED N Subtask 571178-832-002-003 SUBTASK SOLUTION ADDED N Subtask 571178-831-006-002 SUBTASK SOLUTION ADDED N Subtask 571178-700-002-001 SUBTASK SOLUTION ADDED N Subtask 571178-700-002-001 SUBTASK SOLUTION ADDED N Subtask 571178-700-002-001 SUBTASK SOLUTION ADDED N Subtask 571178-942-002-001 SUBTASK SOLUTION ADDED N Subtask 571178-942-002-001 SUBTASK SOLUTION ADDED N Subtask 571178-942-002-001 SUBTASK SOLUTION ADDED N Fig. A-FBAAA FIGURE SOLUTION UPDATED R Fig. A-FBAAA Sheet 01 SHEET UPDATED R Fig. A-FBAAA Sheet 02 SHEET ADDED N Fig. A-FBAAB FIGURE SOLUTION UPDATED R Fig. A-FBAAB Sheet 01 SHEET UPDATED R Fig. A-FBAAB Sheet 02 SHEET ADDED N Fig. A-FBBAA FIGURE SOLUTION ADDED N Fig. A-FBBAA Sheet 01 SHEET ADDED N Fig. A-FBCAA FIGURE SOLUTION ADDED N Fig. A-FBCAA Sheet 01 SHEET ADDED N Fig. A-FBCAA Sheet 02 SHEET ADDED N Fig. A-FBCAB FIGURE SOLUTION ADDED N Fig. A-FBCAB Sheet 01 SHEET ADDED N Fig. A-FBCAB Sheet 02 SHEET ADDED N Fig. A-FBCAC FIGURE SOLUTION ADDED N Fig. A-FBCAC Sheet 01 SHEET ADDED N Fig. A-FBCAC Sheet 02 SHEET ADDED N Fig. A-FFAAA Fig. A-FFAAA Sheet 01 SHEET UPDATED R Fig. A-FFAAB Fig. A-FFAAB Sheet 01 SHEET UPDATED R Fig. A-FFBAA FIGURE SOLUTION ADDED N Fig. A-FFBAA Sheet 01 SHEET ADDED N Fig. A-FFBAB FIGURE SOLUTION ADDED N Fig. A-FFBAB 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 Fig. A-FRAAA Sheet 04 SHEET ADDED N Appendix 01 - Elapsed Time Assumption APPENDIX CONTENT APPENDIX CONTENT ADDED N Fig. A-FAAAA FIGURE SOLUTION ADDED N
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 Fig. A-FAAAA Sheet 01 SHEET ADDED N Fig. A-FAAAC FIGURE SOLUTION ADDED N Fig. A-FAAAC Sheet 01 SHEET ADDED N Fig. A-FAAAB FIGURE SOLUTION ADDED N Fig. A-FAAAB 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 29/13 REVISION No. : 01 - May 28/14

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 29/13 SERVICE BULLETIN No.: A320-57-1178 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. 

# MANDATORY MANDATORY MANDATORY
ATA SYSTEM: 57 

### TITLE: WINGS - INSPECTION OF FRONT SPAR VERTICAL STRINGERS **CONF ALL MODIFICATIONS None REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES During Full Scale Fatigue Tests, cracks were found in the Centre Wing Box front spar external vertical stiffeners at floor beam level. Cracks initiated from vertical fillets of the vertical stiffeners flange. To prevent such damages, modification No. 21290P1547 was embodied on the aircraft in production (Serial modification) from MSN 0156. It consists in installing reinforced vertical stiffener at floor beam level (thickness increase). Note that modification No. 21290P1546 was embodied on Aicraft in production from MSN 0080 to 0155. It consists in installing shims to reduce unfolding effects of the vertical stiffener flange to avoid crack initiation. ISB No. A320-57-1016 was issued for Aircraft already delivered. It consists in a repetitive High Frequency Eddy Current inspection of front spar vertical stiffeners at floor beam level. This inspection was rendered mandatory by EASA AD 97-311-105 (B). Note that accomplishment of Service Bulletin No. A320-57-1017 (similar to modification No. 21290P1546) was proposed to cancel the repetitive inspection. 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 aircraft POST modification No. 21290P1546. This ISB No. A320-57-1178 cancels and supersedes ISB No. A320-57-1016. This Service Bulletin requires at the front external upper spar the inspection of vertical stiffeners radius with floor beams radius and fasteners holes. Accomplishment of this Service Bulletin will contribute to maintain the structural integrity of the front spar external vertical stiffeners at floor beam level. ISB No. A320-57-1178 cancels and supersedes ISB No. A320-57-1016.
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 GENERAL EVALUATION EVALUATION TABLE COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO POTENTIAL AD YES A/C OPERATION AFFECTED NO RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO COST SAVING NO ETOPS AFFECTED NO STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO 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 571178A01R01 1 620.00 Screws, Nuts **CONF 002 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 571178A03R01 1 1,210.00 Screws, Nuts **CONF 003 MATERIAL PRICE INFORMATION TABLE MATERIAL SET QTY PER A/C PRICE PER A/C (USD) MAIN PARTS Kit 571178A02R01 1 620.00 Screws, Nuts EFFECTIVITY **CONF ALL This Service Bulletin is applicable to this (these) operator(s) :

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 35U 73W ACA AFR AIB AIC ART DAL DLH F2I FPY GBB GWI JAV MMA SVR TAR USA CONCURRENT REQUIREMENTS None REFERENCES / REPERCUSSIONS TFU None OEB None AOT None SIL None LINE MAINTENANCE AFFECTED No LIFE LIMIT None OTHER None NATURE OF THE WORK AIRCRAFT YES EQUIPMENT NO HARD NO SOFT NO OBRM NO MANPOWER **CONF 001 Task 571178-832-801-001: Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 TOTAL MANHOURS 23.25 ELAPSED TIME (HOURS) 12.75 Task 571178-832-802-001: Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK TOTAL MANHOURS 23.25 ELAPSED TIME (HOURS) 12.75 **CONF 002 Task 571178-832-801-001: Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 TOTAL MANHOURS 24.25 ELAPSED TIME (HOURS) 13.75 Task 571178-832-802-001: Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK TOTAL MANHOURS 24.25 ELAPSED TIME (HOURS) 13.75
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 003 Task 571178-832-801-001: Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 TOTAL MANHOURS 23.25 ELAPSED TIME (HOURS) 12.75 Task 571178-832-802-001: Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK TOTAL MANHOURS 23.25 ELAPSED TIME (HOURS) 12.75 APPENDICES **CONF ALL Appendix 01 - Elapsed Time Assumption

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 SUMMARY

**CONF 001

INSPECTION AREA **NOTE:** 

### A **A**



## B FR36 FR42



## A

VIEW LOOKING AFT 

### B **B B** 
**B B**  **B A**  Z240

FASTENERS HOLES TO BE INSPECTED N_SB_571178_5_SAAA_01_04 Figure A-FSAAA - Sheet 01

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 SUMMARY

**CONF 001

DATUM

**FWD** FR36



## A **A**

VIEW LOOKING FWD FLOOR BEAM



## B **B B** 

**B**

INSPECTION AREA **NOTE:**

FASTENERS HOLES TO BE INSPECTED N_SB_571178_5_SAAA_02_00 Figure A-FSAAA - Sheet 02

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 SUMMARY

**CONF 002 thru 003

INSPECTION AREA **NOTE:** 

### A **A**



## B FR36 FR42



## A

VIEW LOOKING AFT 

### B **B B** 
**B B**  **B A**  Z240

FASTENERS HOLES TO BE INSPECTED N_SB_571178_5_SAAB_01_04 Figure A-FSAAB - Sheet 01

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 SUMMARY

**CONF 002 thru 003

DATUM

**FWD** FR36



## A **A**

VIEW LOOKING FWD FLOOR BEAM



## B **B B** 

**B**

INSPECTION AREA **NOTE:**

FASTENERS HOLES TO BE INSPECTED N_SB_571178_5_SAAB_02_00 Figure A-FSAAB - Sheet 02

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
AIRBUS CUSTOMER SERVICES DIRECTORATE 1 Rond Point Maurice Bellonte 31707 BLAGNAC CEDEX FRANCE Tel : (33) 5 61 93 33 33 Telex : AIRBU 530526F Fax : (33) 5 61 93 42 51



# MANDATORY MANDATORY MANDATORY
ATA SYSTEM: 57 

### TITLE: WINGS - INSPECTION OF FRONT SPAR VERTICAL STRINGERS 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. 21290P1547 is not embodied. (1) Models 320-211 320-212 320-231 (2) Effectivity by MSN 0029 0045-0047 0049-0057 0059 0064-0078 0080-0088 0090 0093-0096 0099 0104 0110-0119 0121-0127 0135 0137-0138 0140-0142 0147-0150 0152-0154 (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 35U 0088 73W 0087 DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 ACA 0059 0068 0073 0084 0122 0126 0127 0141 0149 0150 0154 AFR 0115 AIB 0138 AIC 0045 0046 0047 0049 0050 0051 0056 0057 0074 0075 0080 0090 0095 0096 ART 0142 DAL 0118 0121 0125 0152 0153 DLH 0069 0070 0071 0072 0078 0083 0086 0093 0094 0104 0110 0111 0116 0117 0135 0137 F2I 0085 0148 FPY 0112 GBB 0067 GWI 0147 JAV 0029 MMA 0113 0114 SVR 0140 TAR 0119 0123 0124 USA 0052 0053 0054 0055 0064 0065 0066 0076 0077 0081 0082 0099 (4) Configuration by MSN MSN CONFIGURATION 0029 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 001 002
0080 0081 0082 0083 0084 0085 0086 0087 0088 0090 0093 0094 0095 0096 0099 0104 0110 0111 0112 0113 0114 0115 0116 0117 0118 0119 0121 0122 0123 0124 0125 0126 0127 0135 0137 0138 0140 0141 0142 0147 0148 0149 0150 0152 0153 0154 003

(5) Configuration definition **CONF 001 Config. 001 is valid for aircraft on which modification No. 21290P1546 is not embodied and on which Service Bulletin No. A320-57-1017 is not accomplished. **CONF 002 Config. 002 is valid for aircraft on which modification No. 21290P1546 is not embodied and on which Service Bulletin No. A320-57-1017 is accomplished. **CONF 003 Config. 003 is valid for aircraft on which modification No. 21290P1546 is embodied. (6) Material Effectivity **CONF 001 MATERIAL QTY PER A/C SEE NOTES Kit 571178A01R01 1 DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

MATERIAL QTY PER A/C SEE NOTES Consumable CMLA01 1 **CONF 002 MATERIAL QTY PER A/C SEE NOTES Kit 571178A03R01 1 Consumable CMLA01 1 **CONF 003 MATERIAL QTY PER A/C SEE NOTES Kit 571178A02R01 1 Consumable CMLA01 1 **CONF ALL B. CONCURRENT REQUIREMENTS None C. REASON (1) History During Full Scale Fatigue Tests, cracks were found in the Centre Wing Box front spar external vertical stiffeners at floor beam level. Cracks initiated from vertical fillets of the vertical stiffeners flange. To prevent such damages, modification No. 21290P1547 was embodied on the aircraft in production (Serial modification) from MSN 0156. It consists in installing reinforced vertical stiffener at floor beam level (thickness increase). Note that modification No. 21290P1546 was embodied on Aicraft in production from MSN 0080 to 0155. It consists in installing shims to reduce unfolding effects of the vertical stiffener flange to avoid crack initiation. ISB No. A320-57-1016 was issued for Aircraft already delivered. It consists in a repetitive High Frequency Eddy Current inspection of front spar vertical stiffeners at floor beam level. This inspection was rendered mandatory by EASA AD 97-311-105 (B). Note that accomplishment of Service Bulletin No. A320-57-1017 (similar to modification No. 21290P1546) was proposed to cancel the repetitive inspection. 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 aircraft POST modification No. 21290P1546. This ISB No. A320-57-1178 cancels and supersedes ISB No. A320-57-1016. (2) Objective/Action This Service Bulletin requires at the front external upper spar the inspection of vertical stiffeners radius with floor beams radius and fasteners holes.

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 (3) Advantages Accomplishment of this Service Bulletin will contribute to maintain the structural integrity of the front spar external vertical stiffeners at floor beam level. (4) Operational/Maintenance Consequences ISB No. A320-57-1178 cancels and supersedes ISB No. A320-57-1016. D. DESCRIPTION To accomplish this Service Bulletin it is necessary to : **CONF 001 Task 571178-832-801-001: Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 (1) Remove the fasteners of the spar vertical Stringers on FR36 (2) Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the Fasteners Holes on FR36 (3) Install the new fasteners of the spar vertical Stringers on FR36 Task 571178-832-802-001: Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK (1) Remove the fasteners of the spar vertical Stringers on FR36 (2) Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the Fasteners Holes on FR36 (3) Install the new fasteners of the spar vertical Stringers on FR36 **CONF 002 Task 571178-832-801-001: Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 (1) Remove the fasteners and the shims of the spar vertical Stringers on FR36 (2) Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the Fasteners Holes on FR36 (3) Oversize the holes of the spar vertical Stringers, the horizontal floor Beam and the holes of the shims on FR36 (4) Install the new fasteners and the shims of the spar vertical Stringers on FR36 Task 571178-832-802-001: Special Detailed Inspection of the spar vertical Stringers Radius, DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
the horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK (1) Remove the fasteners and the shims of the spar vertical Stringers on FR36 (2) Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the Fasteners Holes on FR36 (3) Oversize the holes of the spar vertical Stringers radius, the horizontal floor Beam and the holes of the shims on FR36 (4) Install the new fasteners and the shims of the spar vertical Stringers on FR36 **CONF 003 Task 571178-832-801-001: Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 (1) Remove the fasteners and the shims of the spar vertical Stringers on FR36 (2) Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the Fasteners Holes on FR36 (3) Install the new fasteners and the shims of the spar vertical Stringers on FR36 Task 571178-832-802-001: Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK (1) Remove the fasteners and the shims of the spar vertical Stringers on FR36 (2) Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the Fasteners Holes on FR36 (3) Install the new fasteners and the shims of the spar vertical Stringers on FR36 **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.

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 - Do a Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on Frame 36 Compliance Time (whichever occurs later) Condition Action Threshold from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval (whichever occurs first)

All Aircraft Do a Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on Frame 36 in accordance with TASK 571178-832-801 001 Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 24000FC/ 48000FH from first flight 8800FC/ 17700FH from last Inspection SB No. A320-57-1016 or 850FC/ 1700FH from SB original issuance date without exceeding 14000FC from last inspection None

Crack found Contact Airbus and apply further instructions Before next flight None None

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 1, Config. 001 - Do a Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on Frame 36 Compliance Time (whichever occurs later) Condition Action Threshold from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval (whichever occurs first)

Apply Service Bulletin No. A320-57-1017 and None None None Repeat the HFEC and rototest inspections in accordance with TASK 571178-832-801 001 Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 None None 24900FC/ 49800FH

OR No crack found

Repeat the HFEC and rototest Inspections in accordance TASK 571178-832-801 001 Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 None None 8800FC/ 17700FH

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 - ADDITIONAL WORK - Do a Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on Frame 36 Compliance Time (whichever occurs later) Condition Action Threshold from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval (whichever occurs first)

All Aircraft Do a Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on Frame 36 in accordance with TASK 571178-832-802 001 Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK 24000FC/ 48000FH from first flight 8 800FC/ 17700FH from last Inspection SB No. A320-57-1016 or 850FC/ 1700FH from SB original issuance date without exceeding 14000FC from last inspection None

Crack found Contact Airbus and apply further instructions Before next flight None None

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
Table 2, Config. 001 - ADDITIONAL WORK - Do a Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on Frame 36 Compliance Time (whichever occurs later) Condition Action Threshold from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval (whichever occurs first)

Apply Service Bulletin No. A320-57-1017 and None None None Repeat the HFEC and rototest inspections in accordance with TASK 571178-832-801 001 Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 None None 24900FC/ 49800FH

OR No crack found

Repeat the HFEC and rototest Inspections in accordance with TASK 571178-832-801 001 Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 None None 8800FC/ 17700FH

**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.

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 - Do a Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on Frame 36 Compliance Time (whichever occurs later) Condition Action Threshold from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval (whichever occurs first)

All Aircraft Service Bulletin No. A320-57-1016 not accomplishedas a prerequisite of Service Bulletin No. A320-57-1017 accomplishment Do a Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on Frame 36 in accordance with TASK 571178-832-801 001 Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 8800FC/ 17700FH from Service Bulletin A320-57-1017 embodiement 850FC/ 1700FH from SB original issuance date None

All Aircraft Service Bulletin No. A320-57-1016 accomplishedas a prerequisite of Service Bulletin No. A320-57-1017 accomplishment Do a Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on Frame 36 in accordance with TASK 571178-832-801 001 Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 24900FC/ 49800FH from Service Bulletin A320-57-1017 embodiement 850FC/ 1700FH from SB original issuance date None

Crack found Contact Airbus and apply further instructions Before next flight None None

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 1, Config. 002 - Do a Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on Frame 36 Compliance Time (whichever occurs later) Condition Action Threshold from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval (whichever occurs first)

No crack found Repeat the HFEC and rototest inspections in accordance with TASK 571178-832-801 001 Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 None None 24900FC/ 49800FH

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 - ADDITIONAL WORK - Do a Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on Frame 36 Compliance Time (whichever occurs later) Condition Action Threshold from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval (whichever occurs first)

Service Bulletin No. A320-57-1016 not accomplishedas a prerequisite of Service Bulletin No. A320-57-1017 accomplishment Do a Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on Frame 36 in accordance with TASK 571178-832-802 001 Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK 8800FC/ 17700FH from Service Bulletin A320-57-1017 embodiement 850FC/ 1700FH from SB original issuance date None All Aircraft

Service Bulletin No. A320-57-1016 accomplishedas a prerequisite of Service Bulletin No. A320-57-1017 accomplishment Do a Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on Frame 36 in accordance with TASK 571178-832-802 001 Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK 24900FC/ 49800FH from Service Bulletin A320-57-1017 embodiement 850FC/ 1700FH from SB original issuance date None

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
Table 2, Config. 002 - ADDITIONAL WORK - Do a Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on Frame 36 Compliance Time (whichever occurs later) Condition Action Threshold from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval (whichever occurs first)

Crack found Contact Airbus and apply further instructions Before next flight None None
No crack found Repeat the HFEC and rototest inspections in accordance with TASK 571178-832-801 001 Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 None None 24900FC/ 49800FH

**CONF 003 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.

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
Table 1, Config. 003 - Do a Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on Frame 36 Compliance Time (whichever occurs later) Condition Action Threshold from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval (whichever occurs first)

All Aircraft Do a Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on Frame 36 in accordance with TASK 571178-832-801 001 Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 54300FC/ 108600FH from first flight None None

Crack found Contact Airbus and apply further instructions Before next flight None None
No crack found Repeat the HFEC and rototest inspections in accordance with TASK 571178-832-801 001 Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 None None 24900FC/ 49800FH

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
Table 2, Config. 003 - ADDITIONAL WORK - Do a Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on Frame 36 Compliance Time (whichever occurs later) Condition Action Threshold from first flight (whichever occurs first) Grace period (whichever occurs first) Repetitive Interval (whichever occurs first)

All Aircraft Do a Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on Frame 36 in accordance with TASK 571178-832-802 001 Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK 54300FC/ 108600FH from first flight None None

Crack found Contact Airbus and apply further instructions Before next flight None None
No crack found Repeat the HFEC and rototest inspections in accordance with TASK 571178-832-801 001 Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 None None 24900FC/ 49800FH

**CONF ALL F. APPROVAL The technical content of this document is approved under the authority of Design Organisation Approval No. EASA.21J.031.

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 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 571178-832-801-001: Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 Get Access 6.00 On Aircraft Remove the fasteners of the spar vertical Stringers on FR36 3.00 Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the Fasteners Holes on FR36 2.00
Install the new fasteners of the spar vertical Stringers on FR36 5.00 Tests 0.25 Close-Up 7.00 TOTAL MANHOURS 23.25 ELAPSED TIME (HOURS) 12.75 Task 571178-832-802-001: Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK Get Access 6.00 On Aircraft Remove the fasteners of the spar vertical Stringers on FR36 3.00 Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the Fasteners Holes on FR36 2.00
Install the new fasteners of the spar vertical Stringers on FR36 5.00 Tests 0.25 Close-Up 7.00 TOTAL MANHOURS 23.25 ELAPSED TIME (HOURS) 12.75

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
NOTE: For an explanation of the manhours and elapsed time, refer to the Gantt Chart, Fig. A-FAAAB given in Appendix 01 - 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 571178-832-801-001: Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 Get Access 6.00 On Aircraft Remove the fasteners and the shims of the spar vertical Stringers on FR36 3.00 Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the Fasteners Holes on FR36 2.00
Oversize the holes of the spar vertical Stringers, the horizontal floor Beam and the holes of the shims on FR36 1.00 Install the new fasteners and the shims of the spar vertical Stringers on FR36 5.00 Tests 0.25 Close-Up 7.00 TOTAL MANHOURS 24.25 ELAPSED TIME (HOURS) 13.75 Task 571178-832-802-001: Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK Get Access 6.00 On Aircraft Remove the fasteners and the shims of the spar vertical Stringers on FR36 3.00 Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the Fasteners Holes on FR36 2.00
Oversize the holes of the spar vertical Stringers radius, the horizontal floor Beam and the holes of the shims on FR36 1.00 Install the new fasteners and the shims of the spar vertical Stringers on FR36 5.00 Tests 0.25 Close-Up 7.00 TOTAL MANHOURS 24.25 ELAPSED TIME (HOURS) 13.75

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
NOTE: For an explanation of the manhours and elapsed time, refer to the Gantt Chart, Fig. A-FAAAA given in Appendix 01 - 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 003 Task 571178-832-801-001: Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 Get Access 6.00 On Aircraft Remove the fasteners and the shims of the spar vertical Stringers on FR36 3.00 Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the Fasteners Holes on FR36 2.00
Install the new fasteners and the shims of the spar vertical Stringers on FR36 5.00 Tests 0.25 Close-Up 7.00 TOTAL MANHOURS 23.25 ELAPSED TIME (HOURS) 12.75 Task 571178-832-802-001: Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK Get Access 6.00 On Aircraft Remove the fasteners and the shims of the spar vertical Stringers on FR36 3.00 Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the Fasteners Holes on FR36 2.00
Install the new fasteners and the shims of the spar vertical Stringers on FR36 5.00 Tests 0.25 Close-Up 7.00 TOTAL MANHOURS 23.25 ELAPSED TIME (HOURS) 12.75 NOTE: For an explanation of the manhours and elapsed time, refer to the Gantt Chart, Fig. A-FAAAC given in Appendix 01 - 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.
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
**CONF ALL H. WEIGHT AND BALANCE Not Changed I. ELECTRICAL LOAD DATA Not Changed J. REFERENCES **CONF 001 Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-53 12-34-24 20-21-11 25-21-41 25-28-41 52-10-00 53-32-12 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) A320-57-1017 Standards Manual (SM) Structural Repair Manual (SRM) 51-40-00 51-42-00 51-43-00 51-44-00 51-75-12 **CONF 002 Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-53 12-34-24 20-21-11 25-21-41 25-28-41 52-10-00 53-32-12 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) A320-57-1017 Standards Manual (SM) Structural Repair Manual (SRM) 51-40-00 51-42-00 51-43-00 51-44-00 51-75-12 **CONF 003 Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-53 12-34-24 20-21-11 25-21-41 25-28-41 52-10-00 53-32-12 Consumable Material List (CML) Elec. Std. Practices Manual (ESPM) 20-55-00 Non Destructive Test Manual (NTM) 51-10-01 51-10-08 Standards Manual (SM) Structural Repair Manual (SRM) 51-40-00 51-42-00 51-43-00 51-44-00 51-75-12

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
**CONF ALL K. PUBLICATION AFFECTED

Maintenance Planning Document (MPD) 571196-01-1 571196-02-1 NOTE: Refer to old MPD 571196-01-1 if the Inspection Service Bulletin No. A320-57-1016 is accomplished. NOTE: Refer to new MPD 571196-02-1 if the Inspection Service Bulletin No. A320-57-1178 is accomplished. L. INTERCHANGEABILITY/MIXABILITY Not Applicable M. SPARES None

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
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 571178A01R01 Kit 571178A02R01 Kit 571178A03R01 AIRBUS Material, Logistics and Suppliers Weg beim Jaeger 150 D-22335 HAMBOURG 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 571178A01R01 Cost 620.00 USD Availability 90 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 571178A02R01 Cost 620.00 USD Availability 90 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 571178A03R01 Cost 1,210.00 USD Availability 180 calendar days from receipt of order

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 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. C. LIST OF COMPONENTS Kit 571178A01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 1 EN6115V4-6 12 SCREW 2 ASNA2536-4 12 NUT NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship. Kit 571178A02R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 2 ASNA2536-4 12 NUT 6 EN6115V4-9 12 SCREW 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 571178A03R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE NOTES 2 ASNA2536-4 12 NUT 3 EN6115V4Y9 12 SCREW 4 EN6115V5-9 12 SCREW 5 ASNA2536-5 12 NUT NOTE: If you find part numbers of hardware components in the related kit(s) which you cannot identify in the LIST OF COMPONENTS of this Service Bulletin, refer to Standards Manual (SM). The SM will give you the correct part number to part number relationship.

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Primer Epoxy Paint-- Corrosion Inhibiting Structure 04DAB2 As required Top Coat Polyurethane-- Grey Internal Structure 04JME4 As required Polysulfide Sealant-General Purpose Brushable 06AAA1 As required Non Aqueous Cleaner-General 08BAA9 As required Paste Adhesive - Liquid Shim 13FGC1 As required (2) Components To accomplish this Service Bulletin it is necessary to use the expendable parts listed in the subsequent referenced AMM task:
- AMM Task 53-32-12-400-002. (3) Equipment None E. PARTS TO BE RE-IDENTIFIED BY OPERATOR None F. TOOLING None

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

This Page Intentionally Left Blank

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
3. ACCOMPLISHMENT INSTRUCTIONS Task 571178-832-801-001 - Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS. - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00. NOTE: The accomplishment instructions of this Service Bulletin include procedures given in other documents or in other sections of the Service Bulletin. When the words "refer to" are used and the operator has a procedure accepted by the local authority he belongs to, the accepted alternative procedure can be used. When the words "in accordance with" are used then the given procedure must be followed. NOTE: The access and close-up instructions, not comprising return to service tests, in this Service Bulletin do not constitute or affect the technical intent of the Service Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or close-up steps to add flexibility to their maintenance operations as long as the technical intent of the Service Bulletin is met within the set parameters. NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms. Refer to paragraph 1.J., References, for the definition of acronyms. NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions are Required for Compliance (RC) and must be done to comply with the AD. Other paragraphs are recommended and may be deviated from, done as part of other actions or done with accepted methods different from those given in the Service Bulletin, as long as the RC paragraphs can be done and the aircraft can be put back into a serviceable condition. 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.

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
Task Associated Data **CONF 001 Zone From 241 to 242 Access Panel 241AF 241BF 241CF 241DF 242BF 242CF 242DF Manpower TOTAL MANHOURS 23.25 ELAPSED TIME (HOURS) 12.75 **CONF 002 Zone From 241 to 242 Access Panel 241AF 241BF 241CF 241DF 242BF 242CF 242DF Manpower TOTAL MANHOURS 24.25 ELAPSED TIME (HOURS) 13.75 **CONF 003 Zone From 241 to 242 Access Panel 241AF 241BF 241CF 241DF 242BF 242CF 242DF Manpower TOTAL MANHOURS 23.25 ELAPSED TIME (HOURS) 12.75 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 571178-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 Task 20-21-11-911-001 Consumable Material List (CML)
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

References Structural Repair Manual (SRM) 51-40-00 51-42-00 51-43-00 51-44-00 51-75-12 (a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to Consumable Materials List (CML). (b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (c) For the identification of zones, refer to AMM 06-20-00, Page Block 001. (d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001. (e) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-001. (f) Remove and install fasteners in accordance with SRM 51-42-00. (g) 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. (h) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00. (i) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00. (j) 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. (k) Renew the protective finish in accordance with SRM 51-75-12. (2) Subtask 571178-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 002 (1) Subtask 571178-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 Task 20-21-11-911-001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-40-00 51-42-00 51-43-00 51-44-00 51-75-12 (a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to Consumable Materials List (CML). (b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (c) For the identification of zones, refer to AMM 06-20-00, Page Block 001. (d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001. (e) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-001. (f) Remove and install fasteners in accordance with SRM 51-42-00. (g) 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. (h) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00. (i) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00. (j) 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. (k) Renew the protective finish in accordance with SRM 51-75-12. (2) Subtask 571178-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
**CONF 003 (1) Subtask 571178-910-001-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 Task 20-21-11-911-001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-40-00 51-42-00 51-43-00 51-44-00 51-75-12 (a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to Consumable Materials List (CML). (b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (c) For the identification of zones, refer to AMM 06-20-00, Page Block 001. (d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001. (e) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-001. (f) Remove and install fasteners in accordance with SRM 51-42-00. (g) 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. (h) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00. (i) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00. (j) 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. (k) Renew the protective finish in accordance with SRM 51-75-12. (2) Subtask 571178-839-001-001 - Administrative Manpower Resources Skills NON SPECIFIC DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 571178-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002 Task 25-21-41-000-001 Task 25-28-41-000-001 Task 52-10-00-010-001 Task 53-32-12-000-002 NOTE: The items given in this note shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear) - Engine shut down, thrust reversers closed and locked - Aircraft in clean configuration - Parking brake applied - Aircraft electrical network de-energized - Hydraulic systems depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position (a) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-869-002

. (b) Put an access platform in position at 831. (c) Open the FWD passenger/crew door 831, refer to AMM Task 52-10-00-010-001. (d) Remove the passengers Seats between Frame 35 and Frame 36, refer to AMM Task 25-21-41-000-001.

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 (e) Remove the textile floor covering between Frame 35 and Frame 36, refer to AMM Task 25-28-41-000-001. (f) Remove the floor Panels 242DF, 242CF, 242BF, 241DF, 241CF, 241BF and 241AF, refer to AMM Task 53-32-12-000-002. (g) If necessary, remove the hydraulic pipes clamps and push the pipes without to disconnect them in order to facilitate access of the working area . **CONF 002 (1) Subtask 571178-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002 Task 25-21-41-000-001 Task 25-28-41-000-001 Task 52-10-00-010-001 Task 53-32-12-000-002 NOTE: The items given in this note shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear) - Engine shut down, thrust reversers closed and locked - Aircraft in clean configuration - Parking brake applied - Aircraft electrical network de-energized - Hydraulic systems depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position (a) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-869-002

. (b) Put an access platform in position at 831. (c) Open the FWD passenger/crew door 831, refer to AMM Task 52-10-00-010-001. (d) Remove the passengers Seats between Frame 35 and Frame 36, refer to AMM Task 25-21-41-000-001. DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 (e) Remove the textile floor covering between Frame 35 and Frame 36, refer to AMM Task 25-28-41-000-001. (f) Remove the floor Panels 242DF, 242CF, 242BF, 241DF, 241CF, 241BF and 241AF, refer to AMM Task 53-32-12-000-002. (g) If necessary, remove the hydraulic pipes clamps and push the pipes without to disconnect them in order to facilitate access of the working area . **CONF 003 (1) Subtask 571178-941-001-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002 Task 25-21-41-000-001 Task 25-28-41-000-001 Task 52-10-00-010-001 Task 53-32-12-000-002 NOTE: The items given in this note shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear) - Engine shut down, thrust reversers closed and locked - Aircraft in clean configuration - Parking brake applied - Aircraft electrical network de-energized - Hydraulic systems depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position (a) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-869-002

. (b) Put an access platform in position at 831. (c) Open the FWD passenger/crew door 831, refer to AMM Task 52-10-00-010-001. (d) Remove the passengers Seats between Frame 35 and Frame 36, refer to AMM Task 25-21-41-000-001. DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 (e) Remove the textile floor covering between Frame 35 and Frame 36, refer to AMM Task 25-28-41-000-001. (f) Remove the floor Panels 242DF, 242CF, 242BF, 241DF, 241CF, 241BF and 241AF, refer to AMM Task 53-32-12-000-002. (g) If necessary, remove the hydraulic pipes clamps and push the pipes without to disconnect them in order to facilitate access of the working area . **CONF ALL C. PROCEDURE **CONF 001 (1) Subtask 571178-831-001-001 - Remove the fasteners of the spar vertical Stringers on FR36 Work Zones and Access Panels Zone Access/Work location From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel 241DF Work location Frame 36 To 242 Access Panel 242BF, Panel 242CF, Panel 242DF Work location Frame 36 Manpower Resources Manhours 3.00 Minimum number of person 2 Subtask elapsed time 1.50 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) 51-42-00 Fig. A-FBCAA Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Remove the fasteners of the spar vertical Stringers and the horizontal floor beam. Refer to Fig. A-FBCAA In accordance with SRM 51-42-00

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

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

2 Remove: 12 Screw Item (1 ) Discard 12 Nut Item (2) Discard

(2) Subtask 571178-832-001-001 - Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the Fasteners Holes on FR36 Work Zones and Access Panels Zone Access/Work location From 241 Access Panel 241AF, Panel 241DF, Panel 241CF, Panel 241BF Work location Frame 36 To 242 Access Panel 242DF, Panel 242CF, Panel 242BF Work location Frame 36 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9 As required
References Non Destructive Test Manual (NTM) 51-10-01 51-10-08 Service Bulletin (SB) A320-57-1017 Fig. A-FBAAA Inspection Area Sheet 01 Sheet 02 Fig. A-FFAAA Flow Chart Sheet 01 Fig. A-FRAAA Inspection Report Sheet 01 Sheet 02 Sheet 03 Sheet 04 DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

References Fig. A-FBBAA Inspection of the Fasteners Holes Sheet 01 At the threshold given in PLANNING INFORMATION paragraph E.(2): Do Special Detailed Inspection of the spar vertical Stringers Radius on Frame 36. Refer to Fig. A-FBAAA

. Refer to Fig. A-FBBAA

. Refer to Fig. A-FFAAA

. (a) Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the Fasteners Holes on Frame 36: 1 Remove the protective finish from areas to be inspected with: Non Aqueous Cleaner-General 08BAA9 As required

2 Do a Rototest Inspection of the fasteners holes of spar vertical Stringers Radius in center fuselage on Frame 36: Refer to Fig. A-FBBAA Sheet 01 Refer to NTM 51-10-01 3 Do a High Frequency Eddy Current (HFEC) inspection at the horizontal floor beam radius of the backside of the spar vertical Stringers radius and do a HFEC inspection of the front spar vertical Stringers radius in center fuselage on Frame 36. Refer to Fig. A-FBAAA Sheet 01 Refer to NTM 51-10-08
a If crack is found in one of inspections: <1> Contact Airbus and apply further instructions before next flight. b If no crack is found in any inspections: <1> Apply Service Bulletin No. A320-57-1017. And Repeat the inspections at the interval given in PLANNING INFORMATION paragraph E.(2) in accordance with TASK 571178-832-801 001 Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36

. DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
OR <2> Install the fasteners on the holes to be inspected as described in SUBTASK 571178-831-003 001 Install the new fasteners of the spar vertical Stringers on FR36

. And Repeat the inspections at the interval given in PLANNING INFORMATION paragraph E.(2) in accordance with TASK 571178-832-801 001 Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36

. (b) For the inspection report, refer to figure Fig. A-FRAAA

. (3) Subtask 571178-831-003-001 - Install the new fasteners of the spar vertical Stringers on FR36 Work Zones and Access Panels Zone Access/Work location From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel 241DF Work location Frame 36 To 242 Access Panel 242BF, Panel 242CF, Panel 242DF Work location Frame 36 Manpower Resources Manhours 5.00 Minimum number of person 2 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 571178A01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V4-6 12 SCREW 2 ASNA2536-4 12 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Primer Epoxy Paint Corrosion Inhibiting Structure 04DAB2 As required Top Coat Polyurethane Grey Internal Structure 04JME4 As required

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Polysulfide Sealant-General Purpose Brushable 06AAA1 As required
References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001 Structural Repair Manual (SRM) 51-42-00 51-43-00 51-75-12 Fig. A-FBCAA Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Install the new fasteners of the spar vertical Stringers and the horizontal floor beam. Refer to Fig. A-FBCAA In accordance with SRM 51-42-00 In accordance with SRM 51-43-00 In accordance with SRM 51-75-12 Refer to AMM Task 20-21-11-911-001 1 Install: 12 Screw EN6115V4-6 Item 1 12 Nut ASNA2536-4 Item 2 NOTE: Wet install the fasteners with:Polysulfide SealantGeneral Purpose Brushable 06AAA1 As required

NOTE: After the installation of the new fasteners, apply: Top Coat Polyurethane Grey Internal Structure 04JME4 As required

And Primer Epoxy Paint Corrosion Inhibiting Structure 04DAB2 As required

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
**CONF 002 (1) Subtask 571178-831-001-003 - Remove the fasteners and the shims of the spar vertical Stringers on FR36 Work Zones and Access Panels Zone Access/Work location From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel 241DF Work location Frame 36 To 242 Access Panel 242BF, Panel 242CF, Panel 242DF Work location Frame 36 Manpower Resources Manhours 3.00 Minimum number of person 2 Subtask elapsed time 1.50 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) 51-42-00 Fig. A-FBCAC Removal/Installation of the Shims and the Fasteners Sheet 01 Sheet 02 (a) Remove the fasteners of the spar vertical Stringers, the shims and the horizontal floor beam. Refer to Fig. A-FBCAC In accordance with SRM 51-42-00 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

2 Remove the shims: Refer to figure Fig. A-FBCAC Sheet 01 6 Shim Item (7) Retain DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

6 Shim Item (8) Retain Attached with, depending on aircraft configuration: 12 Screw Item (3) Discard 12 Nut Item (2) Discard Or 12 Screw Item (4) Discard 12 Nut Item (5) Discard

(2) Subtask 571178-832-001-002 - Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the Fasteners Holes on FR36 Work Zones and Access Panels Zone Access/Work location From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel 241DF Work location Frame 36 To 242 Access Panel 242BF, Panel 242CF, Panel 242DF Work location Frame 36 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9 As required
References Non Destructive Test Manual (NTM) 51-10-01 51-10-08 Fig. A-FBAAB Inspection Area Sheet 01 Sheet 02 Fig. A-FFAAB Flow Chart Sheet 01

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

References Fig. A-FRAAA Inspection Report Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FBBAA Inspection of the Fasteners Holes Sheet 01 At the threshold given in PLANNING INFORMATION paragraph E.(2): Do Special Detailed Inspection of the spar vertical Stringers Radius on Frame 36. Refer to Fig. A-FBAAB

. Refer to Fig. A-FBBAA

. Refer to Fig. A-FFAAB

. (a) Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the Fasteners Holes on Frame 36: 1 Remove the protective finish from areas to be inspected with: Non Aqueous Cleaner-General 08BAA9 As required

2 Do a Rototest Inspection of the fasteners holes of spar vertical Stringers Radius in center fuselage on Frame 36: Refer to Fig. A-FBBAA Sheet 01 Refer to NTM 51-10-01 3 Do a High Frequency Eddy Current (HFEC) inspection at the horizontal floor beam radius of the backside of the spar vertical Stringers radius and do a HFEC inspection of the front spar vertical Stringers radius in center fuselage on Frame 36. Refer to Fig. A-FBAAB Sheet 01 Refer to NTM 51-10-08
a If crack is found in one of inspections: <1> Contact Airbus and apply further instructions before next flight.

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
b If no crack is found in any inspections: <1> Oversize the holes of the spar vertical Stringers radius, the shims and the horizontal floor beam radius as described in SUBTASK 571178-831-002 003 Oversize the holes of the spar vertical Stringers, the horizontal floor Beam and the holes of the shims on FR36

. And Install the fasteners and the shims on the holes to be inspected as described in SUBTASK 571178-831-003 003 Install the new fasteners and the shims of the spar vertical Stringers on FR36

. And Repeat the inspections at the interval given in PLANNING INFORMATION paragraph E.(2) in accordance with TASK 571178-832-801 001 Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36

. NOTE: For the repetitive inspections it is not necessary to oversize the holes as the holes are in transition fit. (b) For the inspection report, refer to figure Fig. A-FRAAA

. (3) Subtask 571178-831-002-003 - Oversize the holes of the spar vertical Stringers, the horizontal floor Beam and the holes of the shims on FR36 Work Zones and Access Panels Zone Access/Work location From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel 241DF Work location Frame 36 To 242 Access Panel 242BF, Panel 242CF, Panel 242DF Work location Frame 36 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-44-00 Fig. A-FBCAC Removal/Installation of the Shims and the Fasteners Sheet 01 Sheet 02

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 (a) Oversize the holes of the spar vertical Stringers, the holes of the shims and the horizontal floor beam. Refer to Fig. A-FBCAC In accordance with SRM 51-44-00 1 Depending on aircraft configuration:
a If the holes are in the first oversize diameter: Drill to the second oversize diameter the holes to the dimensions given in Fig. A-FBCAC

. OR b If the holes are in the second oversize diameter: Drill to the next nominal diameter the holes to the dimensions given in Fig. A-FBCAC

. (4) Subtask 571178-831-003-003 - Install the new fasteners and the shims of the spar vertical Stringers on FR36 Work Zones and Access Panels Zone Access/Work location From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel 241DF Work location Frame 36 To 242 Access Panel 242BF, Panel 242CF, Panel 242DF Work location Frame 36 Manpower Resources Manhours 5.00 Minimum number of person 2 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 571178A03R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2536-4 12 NUT 3 EN6115V4Y9 12 SCREW 4 EN6115V5-9 12 SCREW 5 ASNA2536-5 12 NUT

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Primer Epoxy Paint Corrosion Inhibiting Structure 04DAB2 As required Top Coat Polyurethane Grey Internal Structure 04JME4 As required Polysulfide Sealant-General Purpose Brushable 06AAA1 As required Paste Adhesive - Liquid Shim 13FGC1 As required
References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001 Structural Repair Manual (SRM) 51-42-00 51-43-00 51-75-12 Fig. A-FBCAC Removal/Installation of the Shims and the Fasteners Sheet 01 Sheet 02 (a) Install the new fasteners of the spar vertical Stringers and the horizontal floor beam. Refer to Fig. A-FBCAC In accordance with SRM 51-42-00 In accordance with SRM 51-43-00 In accordance with SRM 51-75-12 Refer to AMM Task 20-21-11-911-001 1 Install the shims: 6 Shim Item (7) Retained at removal 6 Shim Item (8) Retained at removal NOTE: Install the shims with: Paste Adhesive - Liquid Shim 13FGC1 As required With, depending on aircraft configuration: 12 Screw EN6115V4Y9 Item 3

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

12 Nut ASNA2536-4 Item 2 Or 12 Screw EN6115V5-9 Item 4 12 Nut ASNA2536-5 Item 5 NOTE: Install the shims with: Paste Adhesive - Liquid Shim 13FGC1 As required
NOTE: Wet install the fasteners with:Polysulfide SealantGeneral Purpose Brushable 06AAA1 As required

NOTE: After the installation of the new fasteners, apply: Top Coat Polyurethane Grey Internal Structure 04JME4 As required

And Primer Epoxy Paint Corrosion Inhibiting Structure 04DAB2 As required

**CONF 003 (1) Subtask 571178-831-001-002 - Remove the fasteners and the shims of the spar vertical Stringers on FR36 Work Zones and Access Panels Zone Access/Work location From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel 241DF Work location Frame 36 To 242 Access Panel 242BF, Panel 242CF, Panel 242DF Work location Frame 36 Manpower Resources Manhours 3.00 Minimum number of person 2 Subtask elapsed time 1.50 Skills AIRFRAME

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
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) 51-42-00 Fig. A-FBCAB Removal/Installation of the Shims and the Fasteners Sheet 01 Sheet 02 (a) Remove the fasteners of the spar vertical Stringers, the shims and the horizontal floor beam. Refer to Fig. A-FBCAB In accordance with SRM 51-42-00 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

2 Remove the shims: Refer to figure Fig. A-FBCAB Sheet 01 6 Shim Item (7) Retain 6 Shim Item (8) Retain Attached with: 12 Screw Item (6) Discard 12 Nut Item (2) Discard

(2) Subtask 571178-832-001-003 - Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the Fasteners Holes on FR36 Work Zones and Access Panels Zone Access/Work location From 241 Access Panel 241AF, Panel 241DF, Panel 241CF, Panel 241BF Work location Frame 36

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

To 242 Access Panel 242DF, Panel 242CF, Panel 242BF Work location Frame 36 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9 As required
References Non Destructive Test Manual (NTM) 51-10-01 51-10-08 Fig. A-FBAAB Inspection Area Sheet 01 Sheet 02 Fig. A-FFAAB Flow Chart Sheet 01 Fig. A-FBBAA Inspection of the Fasteners Holes Sheet 01 Fig. A-FRAAA Inspection Report Sheet 01 Sheet 02 Sheet 03 Sheet 04 At the threshold given in PLANNING INFORMATION paragraph E.(2): Do Special Detailed Inspection of the spar vertical Stringers Radius on Frame 36. Refer to Fig. A-FBAAB

. Refer to Fig. A-FBBAA

. Refer to Fig. A-FFAAB

. (a) Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the Fasteners Holes on Frame 36: 1 Remove the protective finish from areas to be inspected with: Non Aqueous Cleaner-General 08BAA9 As required

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

2 Do a Rototest Inspection of the fasteners holes of spar vertical Stringers Radius in center fuselage on Frame 36: Refer to Fig. A-FBBAA Sheet 01 Refer to NTM 51-10-01 3 Do a High Frequency Eddy Current (HFEC) inspection at the horizontal floor beam radius of the backside of the spar vertical Stringers radius and do a HFEC inspection of the front spar vertical Stringers radius in center fuselage on Frame 36. Refer to Fig. A-FBAAB Sheet 01 Refer to NTM 51-10-08
a If crack is found in one of inspections: <1> Contact Airbus and apply further instructions before next flight. b If no crack is found in any inspections: <1> Install the fasteners and the shims on the holes to be inspected as described in SUBTASK 571178-831-003 002 Install the new fasteners and the shims of the spar vertical Stringers on FR36

. And Repeat the inspections at the interval given in PLANNING INFORMATION paragraph E.(2) in accordance with TASK 571178-832-801 001 Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36

. (b) For the inspection report, refer to figure Fig. A-FRAAA

. (3) Subtask 571178-831-003-002 - Install the new fasteners and the shims of the spar vertical Stringers on FR36 Work Zones and Access Panels Zone Access/Work location From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel 241DF Work location Frame 36 To 242 Access Panel 242BF, Panel 242CF, Panel 242DF Work location Frame 36 Manpower Resources Manhours 5.00 Minimum number of person 2 Subtask elapsed time 2.50 Skills AIRFRAME DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
Material necessary to do the job Kit 571178A02R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2536-4 12 NUT 6 EN6115V4-9 12 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Primer Epoxy Paint Corrosion Inhibiting Structure 04DAB2 As required Top Coat Polyurethane Grey Internal Structure 04JME4 As required Polysulfide Sealant-General Purpose Brushable 06AAA1 As required Paste Adhesive - Liquid Shim 13FGC1 As required
References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001 Structural Repair Manual (SRM) 51-42-00 51-43-00 51-75-12 Fig. A-FBCAB Removal/Installation of the Shims and the Fasteners Sheet 01 Sheet 02 (a) Install the new fasteners and the shims of the spar vertical Stringers and the horizontal floor beam. Refer to Fig. A-FBCAB In accordance with SRM 51-42-00 In accordance with SRM 51-43-00 In accordance with SRM 51-75-12 Refer to AMM Task 20-21-11-911-001 1 Install the shims: 6 Shim Item (7) Retained at removal 6 Shim Item (8) Retained at removal

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
With: 12 Screw EN6115V4-9 Item 6 12 Nut ASNA2536-4 Item 2 NOTE: Install the shims with: Paste Adhesive - Liquid Shim 13FGC1 As required
NOTE: Wet install the fasteners with:Polysulfide SealantGeneral Purpose Brushable 06AAA1 As required

NOTE: After the installation of the new fasteners, apply: Top Coat Polyurethane Grey Internal Structure 04JME4 As required

And Primer Epoxy Paint Corrosion Inhibiting Structure 04DAB2 As required

**CONF ALL D. TEST **CONF 001 (1) Subtask 571178-700-001-001 - Testing Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) Task 25-21-41-400-001 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 subtasks. - Remove the Safety clips and tags and close the circuit breakers as specified after the installation of the Passenger Seats, refer to AMM Task 25-21-41-400-001. - Do the test procedure as specified after the installation of the Passenger Seats, refer to AMM Task 25-21-41-400-001.

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
**CONF 002 (1) Subtask 571178-700-001-001 - Testing Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) Task 25-21-41-400-001 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 subtasks. - Remove the Safety clips and tags and close the circuit breakers as specified after the installation of the Passenger Seats, refer to AMM Task 25-21-41-400-001. - Do the test procedure as specified after the installation of the Passenger Seats, refer to AMM Task 25-21-41-400-001. **CONF 003 (1) Subtask 571178-700-001-001 - Testing Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) Task 25-21-41-400-001 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 subtasks. - Remove the Safety clips and tags and close the circuit breakers as specified after the installation of the Passenger Seats, refer to AMM Task 25-21-41-400-001. - Do the test procedure as specified after the installation of the Passenger Seats, refer to AMM Task 25-21-41-400-001. **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 571178-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

References Aircraft Maintenance Manual (AMM) Task 25-21-41-400-001 Task 25-28-41-400-001 Task 52-10-00-410-001 Task 53-32-12-400-002 (a) If removed, install hydraulic pipes clamps and them back in initial position. (b) Make sure that the work areas are clean and clear of tools and other items of equipment. (c) Install the floor Panels 242DF, 242CF, 242BF, 241DF, 241CF, 241BF and 241AF, refer to AMM Task 53-32-12-400-002. (d) Install the textile floor covering between FR35 and FR36, refer to AMM Task 25-28-41-400-001. (e) Install the passengers Seats between FR35 and FR36, refer to AMM Task 25-21-41-400-001. (f) Close the FWD passenger/crew door 831, refer to AMM Task 52-10-00-410-001. (g) Remove the access platform(s). (h) Disconnect the aircraft electrical ground-connection. (i) Restore the systems and the aircraft to normal operating condition. **CONF 002 (1) Subtask 571178-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 25-21-41-400-001 Task 25-28-41-400-001 Task 52-10-00-410-001 Task 53-32-12-400-002 (a) If removed, install hydraulic pipes clamps and them back in initial position. (b) Make sure that the work areas are clean and clear of tools and other items of equipment. (c) Install the floor Panels 242DF, 242CF, 242BF, 241DF, 241CF, 241BF and 241AF, refer to AMM Task 53-32-12-400-002. (d) Install the textile floor covering between FR35 and FR36, refer to AMM Task 25-28-41-400-001.

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 (e) Install the passengers Seats between FR35 and FR36, refer to AMM Task 25-21-41-400-001. (f) Close the FWD passenger/crew door 831, refer to AMM Task 52-10-00-410-001. (g) Remove the access platform(s). (h) Disconnect the aircraft electrical ground-connection. (i) Restore the systems and the aircraft to normal operating condition. **CONF 003 (1) Subtask 571178-942-001-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 25-21-41-400-001 Task 25-28-41-400-001 Task 52-10-00-410-001 Task 53-32-12-400-002 (a) If removed, install hydraulic pipes clamps and them back in initial position. (b) Make sure that the work areas are clean and clear of tools and other items of equipment. (c) Install the floor Panels 242DF, 242CF, 242BF, 241DF, 241CF, 241BF and 241AF, refer to AMM Task 53-32-12-400-002. (d) Install the textile floor covering between FR35 and FR36, refer to AMM Task 25-28-41-400-001. (e) Install the passengers Seats between FR35 and FR36, refer to AMM Task 25-21-41-400-001. (f) Close the FWD passenger/crew door 831, refer to AMM Task 52-10-00-410-001. (g) Remove the access platform(s). (h) Disconnect the aircraft electrical ground-connection. (i) Restore the systems and the aircraft to normal operating condition.

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 Task 571178-832-802-001 - Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK **CONF ALL WARNING : MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS INCLUDED IN THE REFERENCED PROCEDURES. CAUTION : ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS: - PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS NECESSARY ON WIRING AND COMPONENTS. - REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND OTHER CONTAMINATION. THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION. IF THERE IS CONTAMINATION, REFER TO ESPM 20-55-00. NOTE: The accomplishment instructions of this Service Bulletin include procedures given in other documents or in other sections of the Service Bulletin. When the words "refer to" are used and the operator has a procedure accepted by the local authority he belongs to, the accepted alternative procedure can be used. When the words "in accordance with" are used then the given procedure must be followed. NOTE: The access and close-up instructions, not comprising return to service tests, in this Service Bulletin do not constitute or affect the technical intent of the Service Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or close-up steps to add flexibility to their maintenance operations as long as the technical intent of the Service Bulletin is met within the set parameters. NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms. Refer to paragraph 1.J., References, for the definition of acronyms. NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions are Required for Compliance (RC) and must be done to comply with the AD. Other paragraphs are recommended and may be deviated from, done as part of other actions or done with accepted methods different from those given in the Service Bulletin, as long as the RC paragraphs can be done and the aircraft can be put back into a serviceable condition. 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.

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
Task Associated Data **CONF 001 Zone From 241 to 242 Access Panel 241AF 241BF 241CF 241DF 242BF 242CF 242DF Manpower TOTAL MANHOURS 23.25 ELAPSED TIME (HOURS) 12.75 **CONF 002 Zone From 241 to 242 Access Panel 241AF 241BF 241CF 241DF 242BF 242CF 242DF Manpower TOTAL MANHOURS 24.25 ELAPSED TIME (HOURS) 13.75 **CONF 003 Zone From 241 to 242 Access Panel 241AF 241BF 241CF 241DF 242BF 242CF 242DF Manpower TOTAL MANHOURS 23.25 ELAPSED TIME (HOURS) 12.75 **CONF ALL A. GENERAL **CONF 001 (1) Subtask 571178-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 Task 20-21-11-911-001 Consumable Material List (CML)
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

References Structural Repair Manual (SRM) 51-40-00 51-42-00 51-43-00 51-44-00 51-75-12 (a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to Consumable Materials List (CML). (b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (c) For the identification of zones, refer to AMM 06-20-00, Page Block 001. (d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001. (e) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-001. (f) Remove and install fasteners in accordance with SRM 51-42-00. (g) 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. (h) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00. (i) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00. (j) 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. (k) Renew the protective finish in accordance with SRM 51-75-12. (2) Subtask 571178-839-002-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF 002 (1) Subtask 571178-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 Task 20-21-11-911-001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-40-00 51-42-00 51-43-00 51-44-00 51-75-12 (a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to Consumable Materials List (CML). (b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (c) For the identification of zones, refer to AMM 06-20-00, Page Block 001. (d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001. (e) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-001. (f) Remove and install fasteners in accordance with SRM 51-42-00. (g) 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. (h) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00. (i) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00. (j) 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. (k) Renew the protective finish in accordance with SRM 51-75-12. (2) Subtask 571178-839-002-001 - Administrative Manpower Resources Skills NON SPECIFIC Write in the applicable aircraft records that you have done all the work given in this Service Bulletin.

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
**CONF 003 (1) Subtask 571178-910-002-001 - Standard Practices Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001 06-31-53, Page Block 001 06-41-53, Page Block 001 Task 20-21-11-911-001 Consumable Material List (CML) Structural Repair Manual (SRM) 51-40-00 51-42-00 51-43-00 51-44-00 51-75-12 (a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to Consumable Materials List (CML). (b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001. (c) For the identification of zones, refer to AMM 06-20-00, Page Block 001. (d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001. (e) To torque tighten the standard threaded fasteners, refer to AMM Task 20-21-11-911-001. (f) Remove and install fasteners in accordance with SRM 51-42-00. (g) 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. (h) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00. (i) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00. (j) 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. (k) Renew the protective finish in accordance with SRM 51-75-12. (2) Subtask 571178-839-002-001 - Administrative Manpower Resources Skills NON SPECIFIC DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 Write in the applicable aircraft records that you have done all the work given in this Service Bulletin. **CONF ALL B. PREPARATION **CONF 001 (1) Subtask 571178-941-002-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002 Task 25-21-41-000-001 Task 25-28-41-000-001 Task 52-10-00-010-001 Task 53-32-12-000-002 NOTE: The items given in this note shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear). - Engine shut down, thrust reversers closed and locked - Aircraft in clean configuration - Parking brake applied - Aircraft electrical network de-energized - Hydraulic systems depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position (a) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-869-002. (b) Put an access platform in position at door 831. (c) Open the FWD passenger/crew door 831, refer to AMM Task 52-10-00-010-001. (d) Remove the passengers Seats between Frame 35 and Frame 36, refer to AMM Task 25-21-41-000-001.

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 (e) Remove the textile floor covering between Frame 35 and Frame 36, refer to AMM Task 25-28-41-000-001. (f) Remove the floor Panels 242DF, 242CF, 242BF, 241DF, 241CF, 241BF and 241AF, refer to AMM Task 53-32-12-000-002. (g) If necessary, remove the hydraulic pipes clamps and push the pipes without to disconnect them in order to facilitate access of the working area . **CONF 002 (1) Subtask 571178-941-002-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002 Task 25-21-41-000-001 Task 25-28-41-000-001 Task 52-10-00-010-001 Task 53-32-12-000-002 NOTE: The items given in this note shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear). - Engine shut down, thrust reversers closed and locked - Aircraft in clean configuration - Parking brake applied - Aircraft electrical network de-energized - Hydraulic systems depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position (a) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-869-002. (b) Put an access platform in position at door 831. (c) Open the FWD passenger/crew door 831, refer to AMM Task 52-10-00-010-001. (d) Remove the passengers Seats between Frame 35 and Frame 36, refer to AMM Task 25-21-41-000-001. DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 (e) Remove the textile floor covering between Frame 35 and Frame 36, refer to AMM Task 25-28-41-000-001. (f) Remove the floor Panels 242DF, 242CF, 242BF, 241DF, 241CF, 241BF and 241AF, refer to AMM Task 53-32-12-000-002. (g) If necessary, remove the hydraulic pipes clamps and push the pipes without to disconnect them in order to facilitate access of the working area . **CONF 003 (1) Subtask 571178-941-002-001 - Job Set-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002 Task 25-21-41-000-001 Task 25-28-41-000-001 Task 52-10-00-010-001 Task 53-32-12-000-002 NOTE: The items given in this note shall be considered as the basic Aircraft configuration before you start a maintenance task: - Aircraft on the ground resting on landing gear (the ground safety locks and the wheel chocks are in position on the landing gear). - Engine shut down, thrust reversers closed and locked - Aircraft in clean configuration - Parking brake applied - Aircraft electrical network de-energized - Hydraulic systems depressurized - Access to the cockpit and cabin is available - All circuit breakers are in closed position - All controls in NORM, AUTO or OFF position (a) Make sure that the aircraft is electrically grounded, refer to AMM Task 12-34-24-869-002. (b) Put an access platform in position at door 831. (c) Open the FWD passenger/crew door 831, refer to AMM Task 52-10-00-010-001. (d) Remove the passengers Seats between Frame 35 and Frame 36, refer to AMM Task 25-21-41-000-001. DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 (e) Remove the textile floor covering between Frame 35 and Frame 36, refer to AMM Task 25-28-41-000-001. (f) Remove the floor Panels 242DF, 242CF, 242BF, 241DF, 241CF, 241BF and 241AF, refer to AMM Task 53-32-12-000-002. (g) If necessary, remove the hydraulic pipes clamps and push the pipes without to disconnect them in order to facilitate access of the working area . **CONF ALL C. PROCEDURE NOTE: This Additional Work is necessary in case of the fasteners and/or shims have not been removed the HFEC inspection of the vertical stiffener radius and the rototest inspection of the holes has not been done during accomplishment instruction of Service Bulletin No. A320-57-1178 at original issue. **CONF 001 (1) Subtask 571178-831-004-001 - Remove the fasteners of the spar vertical Stringers on FR36 Work Zones and Access Panels Zone Access/Work location From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel 241DF Work location Frame 36 To 242 Access Panel 242BF, Panel 242CF, Panel 242DF Work location Frame 36 Manpower Resources Manhours 3.00 Minimum number of person 2 Subtask elapsed time 1.50 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) 51-42-00 Fig. A-FBCAA Removal/Installation of the Fasteners Sheet 01 Sheet 02

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 Fig. A-FBBAA Inspection of the Fasteners Holes Sheet 01 (a) Remove the fasteners of the spar vertical Stringers and the horizontal floor beam. Refer to Fig. A-FBCAA In accordance with SRM 51-42-00 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

2 Remove: 12 Screw Item (1 ) Discard 12 Nut Item (2) Discard

(2) Subtask 571178-832-002-001 - Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the Fasteners Holes on FR36 Work Zones and Access Panels Zone Access/Work location From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel 241DF Work location Frame 36 To 242 Access Panel 242BF, Panel 242CF, Panel 242DF Work location Frame 36 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9 As required
References Non Destructive Test Manual (NTM) 51-10-01 51-10-08 DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

References Service Bulletin (SB) A320-57-1017 Fig. A-FBAAA Inspection Area Sheet 01 Sheet 02 Fig. A-FBBAA Inspection of the Fasteners Holes Sheet 01 Fig. A-FRAAA Inspection Report Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FFBAA Flow Chart - ADDITIONAL WORK Sheet 01 At the threshold given in PLANNING INFORMATION paragraph E.(2): Do Special Detailed Inspection of the spar vertical Stringers Radius on Frame 36. Refer to Fig. A-FBAAA

. Refer to Fig. A-FBBAA

. Refer to Fig. A-FFBAA

. (a) Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the Fasteners Holes on Frame 36: 1 Remove the protective finish from areas to be inspected with: Non Aqueous Cleaner-General 08BAA9 As required

2 Do a Rototest Inspection of the fasteners holes of spar vertical Stringers Radius in center fuselage on Frame 36: Refer to Fig. A-FBBAA Sheet 01 Refer to NTM 51-10-01 3 Do a High Frequency Eddy Current (HFEC) inspection at the horizontal floor beam radius of the backside of the spar vertical Stringers radius and do a HFEC inspection of the front spar vertical Stringers radius in center fuselage on Frame 36. Refer to Fig. A-FBAAA Sheet 01 Refer to NTM 51-10-08
a If crack is found in one of inspections: <1> Contact Airbus and apply further instructions before next flight.

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 If no crack is found in any inspections: <1> Apply Service Bulletin No. A320-57-1017. And Repeat the inspections at the interval given in PLANNING INFORMATION paragraph E.(2) in accordance with TASK 571178-832-801 001 Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36

. OR <2> Install the fasteners on the holes to be inspected as described in SUBTASK 571178-831-006 001 Install the new fasteners of the spar vertical Stringers on FR36

. And Repeat the inspections at the interval given in PLANNING INFORMATION paragraph E.(2)in accordance with TASK 571178-832-801 001 Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36

. (b) For the inspection report, refer to figure Fig. A-FRAAA

. (3) Subtask 571178-831-006-001 - Install the new fasteners of the spar vertical Stringers on FR36 Work Zones and Access Panels Zone Access/Work location From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel 241DF Work location Frame 36 To 242 Access Panel 242BF, Panel 242CF, Panel 242DF Work location Frame 36 Manpower Resources Manhours 5.00 Minimum number of person 2 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 571178A01R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 1 EN6115V4-6 12 SCREW DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2536-4 12 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Primer Epoxy Paint Corrosion Inhibiting Structure 04DAB2 As required Top Coat Polyurethane Grey Internal Structure 04JME4 As required Polysulfide Sealant-General Purpose Brushable 06AAA1 As required
References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001 Structural Repair Manual (SRM) 51-42-00 51-43-00 51-75-12 Fig. A-FBCAA Removal/Installation of the Fasteners Sheet 01 Sheet 02 (a) Install the new fasteners of the spar vertical Stringers and the horizontal floor beam. Refer to Fig. A-FBCAA In accordance with SRM 51-42-00 In accordance with SRM 51-75-12 In accordance with SRM 51-43-00 Refer to AMM Task 20-21-11-911-001 1 Install: 12 Screw EN6115V4-6 Item 1 12 Nut ASNA2536-4 Item 2 NOTE: Wet install the fasteners with:Polysulfide SealantGeneral Purpose Brushable 06AAA1 As required

NOTE: After the installation of the new fasteners, apply:

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
Top Coat Polyurethane Grey Internal Structure 04JME4 As required

And Primer Epoxy Paint Corrosion Inhibiting Structure 04DAB2 As required

**CONF 002 (1) Subtask 571178-831-004-003 - Remove the fasteners and the shims of the spar vertical Stringers on FR36 Work Zones and Access Panels Zone Access/Work location From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel 241DF Work location Frame 36 To 242 Access Panel 242BF, Panel 242CF, Panel 242DF Work location Frame 36 Manpower Resources Manhours 3.00 Minimum number of person 2 Subtask elapsed time 1.50 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) 51-42-00 Fig. A-FBCAC Removal/Installation of the Shims and the Fasteners Sheet 01 Sheet 02 Fig. A-FBBAA Inspection of the Fasteners Holes Sheet 01 (a) Remove the fasteners of the spar vertical Stringers, the shims and the horizontal floor beam. Refer to Fig. A-FBCAC In accordance with SRM 51-42-00 DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

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

2 Remove the shims: Refer to figure Fig. A-FBCAC Sheet 01 6 Shim Item (7) Retain 6 Shim Item (8) Retain Attached with, depending on aircraft configuration: 12 Screw Item (3) Discard 12 Nut Item (2) Discard Or 12 Screw Item (4) Discard 12 Nut Item (5) Discard

(2) Subtask 571178-832-002-002 - Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the Fasteners Holes on FR36 Work Zones and Access Panels Zone Access/Work location From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel 241DF Work location Frame 36 To 242 Access Panel 242BF, Panel 242CF, Panel 242DF Work location Frame 36 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9 As required
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

References Non Destructive Test Manual (NTM) 51-10-01 51-10-08 Service Bulletin (SB) A320-57-1017 Fig. A-FBAAB Inspection Area Sheet 01 Sheet 02 Fig. A-FBBAA Inspection of the Fasteners Holes Sheet 01 Fig. A-FRAAA Inspection Report Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FFBAB Flow Chart - ADDITIONAL WORK Sheet 01 At the threshold given in PLANNING INFORMATION paragraph E.(2): Do Special Detailed Inspection of the spar vertical Stringers Radius on Frame 36. Refer to Fig. A-FBAAB

. Refer to Fig. A-FBBAA

. Refer to Fig. A-FFBAB

. (a) Do High Frequency Eddy Current (HFEC) Inspection of the spar vertical Stringers Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the Fasteners Holes on Frame 36: 1 Remove the protective finish from areas to be inspected with: Non Aqueous Cleaner-General 08BAA9 As required

2 Do a Rototest Inspection of the fasteners holes of spar vertical Stringers Radius in center fuselage on Frame 36: Refer to Fig. A-FBBAA Sheet 01 Refer to NTM 51-10-01 3 Do a High Frequency Eddy Current (HFEC) inspection at the horizontal floor beam radius of the backside of the spar vertical Stringers radius and do a HFEC inspection of the front spar vertical Stringers radius in center fuselage on Frame 36. Refer to Fig. A-FBAAB Sheet 01 Refer to NTM 51-10-08

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

a If crack is found in one of inspections: <1> Contact Airbus and apply further instructions before next flight. b If no crack is found in any inspections: <1> Oversize the holes of the spar vertical Stringers radius, the shims and the horizontal floor beam radius as described in SUBTASK 571178-831-005 003 Oversize the holes of the spar vertical Stringers radius, the horizontal floor Beam and the holes of the shims on FR36

. And Install the fasteners and the shims on the holes to be inspected as described in SUBTASK 571178-831-006 003 Install the new fasteners and the shims of the spar vertical Stringers on FR36

. And Repeat the inspections at the interval given in PLANNING INFORMATION paragraph E.(2) in accordance with TASK 571178-832-801 001 Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36

. NOTE: For the repetitive Inspections is not necessary to oversize the holes as the holes are in transition fit. (b) For the inspection report, refer to figure Fig. A-FRAAA

. (3) Subtask 571178-831-005-003 - Oversize the holes of the spar vertical Stringers radius, the horizontal floor Beam and the holes of the shims on FR36 Work Zones and Access Panels Zone Access/Work location From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel 241DF Work location Frame 36 To 242 Access Panel 242BF, Panel 242CF, Panel 242DF Work location Frame 36 Manpower Resources Manhours 1.00 Minimum number of person 1 Subtask elapsed time 1.00 Skills AIRFRAME References Structural Repair Manual (SRM) 51-44-00

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

References Fig. A-FBCAC Removal/Installation of the Shims and the Fasteners Sheet 01 Sheet 02 (a) Oversize the holes of the spar vertical Stringers radius, the holes of the shims and the horizontal floor beam radius. Refer to Fig. A-FBCAC In accordance with SRM 51-44-00 1 Depending on aircraft configuration:
a If the holes are in the first oversize diameter: Drill to the second oversize diameter the holes to the dimensions given in Fig. A-FBCAC

. OR b If the holes are in the second oversize diameter: Drill to the next nominal diameter the holes to the dimensions given in Fig. A-FBCAC

. (4) Subtask 571178-831-006-003 - Install the new fasteners and the shims of the spar vertical Stringers on FR36 Work Zones and Access Panels Zone Access/Work location From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel 241DF Work location Frame 36 To 242 Access Panel 242BF, Panel 242CF, Panel 242DF Work location Frame 36 Manpower Resources Manhours 5.00 Minimum number of person 2 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 571178A03R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2536-4 12 NUT 3 EN6115V4Y9 12 SCREW 4 EN6115V5-9 12 SCREW DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 5 ASNA2536-5 12 NUT Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Primer Epoxy Paint Corrosion Inhibiting Structure 04DAB2 As required Top Coat Polyurethane Grey Internal Structure 04JME4 As required Polysulfide Sealant-General Purpose Brushable 06AAA1 As required Paste Adhesive - Liquid Shim 13FGC1 As required
References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001 Structural Repair Manual (SRM) 51-42-00 51-43-00 51-75-12 Fig. A-FBCAC Removal/Installation of the Shims and the Fasteners Sheet 01 Sheet 02 (a) Install the new fasteners of the spar vertical Stringers, the shims and the horizontal floor beam. Refer to Fig. A-FBCAC In accordance with SRM 51-42-00 In accordance with SRM 51-43-00 In accordance with SRM 51-75-12 Refer to AMM Task 20-21-11-911-001 1 Install the shims: 6 Shim Item (7) Retained at removal 6 Shim Item (8) Retained at removal NOTE: Install the shims with: Paste Adhesive - Liquid Shim 13FGC1 As required

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 With, depending on aircraft configuration: 12 Screw EN6115V4Y9 Item 3 12 Nut ASNA2536-4 Item 2 Or 12 Screw EN6115V5-9 Item 4 12 Nut ASNA2536-5 Item 5 NOTE: Install the shims with: Paste Adhesive - Liquid Shim 13FGC1 As required
NOTE: Wet install the fasteners with:Polysulfide SealantGeneral Purpose Brushable 06AAA1 As required

NOTE: After the installation of the new fasteners, apply: Top Coat Polyurethane Grey Internal Structure 04JME4 As required

And Primer Epoxy Paint Corrosion Inhibiting Structure 04DAB2 As required

**CONF 003 (1) Subtask 571178-831-004-002 - Remove the fasteners and the shims of the spar vertical Stringers on FR36 Work Zones and Access Panels Zone Access/Work location From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel 241DF Work location Frame 36 To 242 Access Panel 242BF, Panel 242CF, Panel 242DF Work location Frame 36 Manpower Resources Manhours 3.00 Minimum number of person 2 Subtask elapsed time 1.50 Skills AIRFRAME DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
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) 51-42-00 Fig. A-FBCAB Removal/Installation of the Shims and the Fasteners Sheet 01 Sheet 02 Fig. A-FBBAA Inspection of the Fasteners Holes Sheet 01 (a) Remove the fasteners of the spar vertical Stringers, the shims and the horizontal floor beam. Refer to Fig. A-FBCAB In accordance with SRM 51-42-00 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

2 Remove the shims: Refer to figure Fig. A-FBCAB Sheet 01 6 Shim Item (7) Retain 6 Shim Item (8) Retain Attached with: 12 Screw Item (6) Discard 12 Nut Item (2) Discard

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 (2) Subtask 571178-832-002-003 - Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the Fasteners Holes on FR36 Work Zones and Access Panels Zone Access/Work location From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel 241DF Work location Frame 36 To 242 Access Panel 242BF, Panel 242CF, Panel 242DF Work location Frame 36 Manpower Resources Manhours 2.00 Minimum number of person 1 Subtask elapsed time 2.00 Skills AIRFRAME Material necessary to do the job Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTESNon Aqueous CleanerGeneral 08BAA9 As required
References Non Destructive Test Manual (NTM) 51-10-01 51-10-08 Fig. A-FRAAA Inspection Report Sheet 01 Sheet 02 Sheet 03 Sheet 04 Fig. A-FBBAA Inspection of the Fasteners Holes Sheet 01 Fig. A-FBAAB Inspection Area Sheet 01 Sheet 02 Fig. A-FFBAB Flow Chart - ADDITIONAL WORK Sheet 01 At the threshold given in PLANNING INFORMATION paragraph E.(2): Do Special Detailed Inspection of the spar vertical Stringers Radius on Frame 36. Refer to Fig. A-FBAAB

. Refer to Fig. A-FBBAA

. Refer to Fig. A-FFBAB

.
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 BULLETIN (a) Do High Frequency Eddy Current (HFEC) Inspection of the spar vertical Stringers Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the Fasteners Holes on Frame 36: 1 Remove the protective finish from areas to be inspected with: Non Aqueous Cleaner-General 08BAA9 As required

2 Do a Rototest Inspection of the fasteners holes of spar vertical Stringers Radius in center fuselage on Frame 36: Refer to Fig. A-FBBAA Sheet 01 Refer to NTM 51-10-01 3 Do a High Frequency Eddy Current (HFEC) inspection at the horizontal floor beam radius of the backside of the spar vertical Stringers radius and do a HFEC inspection of the front spar vertical Stringers radius in center fuselage on Frame 36. Refer to Fig. A-FBAAB Sheet 01 Refer to NTM 51-10-08
a If crack is found in one of inspections: <1> Contact Airbus and apply further instructions before next flight. b If no crack is found in any inspections: <1> Install the fasteners and the shims on the holes to be inspected as described in SUBTASK 571178-831-006 002 Install the new fasteners and the shims of the spar vertical Stringers on FR36

. And Repeat the inspections at the interval given in PLANNING INFORMATION paragraph E.(2) in accordance with TASK 571178-832-801 001 Special Detailed Inspection of the spar vertical Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on FR36

. (b) For the inspection report, refer to figure Fig. A-FRAAA

. (3) Subtask 571178-831-006-002 - Install the new fasteners and the shims of the spar vertical Stringers on FR36 Work Zones and Access Panels Zone Access/Work location From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel 241DF Work location Frame 36
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

To 242 Access Panel 242BF, Panel 242CF, Panel 242DF Work location Frame 36 Manpower Resources Manhours 5.00 Minimum number of person 2 Subtask elapsed time 2.50 Skills AIRFRAME Material necessary to do the job Kit 571178A02R01 ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE NOTES 2 ASNA2536-4 12 NUT 6 EN6115V4-9 12 SCREW Consumable CMLA01 ITEM DESCRIPTION REFERENCE TO CML MAT. No. QTY PER A/C SEE NOTES Primer Epoxy Paint Corrosion Inhibiting Structure 04DAB2 As required Top Coat Polyurethane Grey Internal Structure 04JME4 As required Polysulfide Sealant-General Purpose Brushable 06AAA1 As required Paste Adhesive - Liquid Shim 13FGC1 As required
References Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001 Structural Repair Manual (SRM) 51-42-00 51-43-00 51-75-12 Fig. A-FBCAB Removal/Installation of the Shims and the Fasteners Sheet 01 Sheet 02 (a) Install the new fasteners of the spar vertical Stringers, the shims and the horizontal floor beam. Refer to Fig. A-FBCAB In accordance with SRM 51-42-00 In accordance with SRM 51-43-00 In accordance with SRM 51-75-12
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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
Refer to AMM Task 20-21-11-911-001 1 Install the shims: 6 Shim Item (7) Retained at removal 6 Shim Item (8) Retained at removal NOTE: Install the shims with: Paste Adhesive - Liquid Shim 13FGC1 As required
With: 12 Screw EN6115V4-9 Item 6 12 Nut ASNA2536-4 Item 2 NOTE: Install the shims with: Paste Adhesive - Liquid Shim 13FGC1 As required
NOTE: Wet install the fasteners with:Polysulfide SealantGeneral Purpose Brushable 06AAA1 As required

NOTE: After the installation of the new fasteners, apply: Top Coat Polyurethane Grey Internal Structure 04JME4 As required

And Primer Epoxy Paint Corrosion Inhibiting Structure 04DAB2 As required

**CONF ALL D. TEST **CONF 001 (1) Subtask 571178-700-002-001 - Testing Manpower Resources Skills AIRFRAME
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 25-21-41-400-001 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 subtasks. - Remove the Safety clips and tags and close the circuit breakers as specified after the installation of the Passenger Seats, refer to AMM Task 25-21-41-400-001. - Do the test procedure as specified after the installation of the Passenger Seats, refer to AMM Task 25-21-41-400-001. **CONF 002 (1) Subtask 571178-700-002-001 - Testing Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) Task 25-21-41-400-001 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 subtasks. - Remove the Safety clips and tags and close the circuit breakers as specified after the installation of the Passenger Seats, refer to AMM Task 25-21-41-400-001. - Do the test procedure as specified after the installation of the Passenger Seats, refer to AMM Task 25-21-41-400-001. **CONF 003 (1) Subtask 571178-700-002-001 - Testing Manpower Resources Skills AIRFRAME References Aircraft Maintenance Manual (AMM) Task 25-21-41-400-001 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 subtasks. - Remove the Safety clips and tags and close the circuit breakers as specified after the installation of the Passenger Seats, refer to AMM Task 25-21-41-400-001. DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 - Do the test procedure as specified after the installation of the Passenger Seats, refer to AMM Task 25-21-41-400-001. **CONF ALL E. CLOSE-UP **CONF 001 (1) Subtask 571178-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 25-21-41-400-001 Task 25-28-41-400-001 Task 52-10-00-410-001 Task 53-32-12-400-002 (a) If removed, install hydraulic pipes clamps and them back in initial position. (b) Make sure that the work areas are clean and clear of tools and other items of equipment. (c) Install the floor Panels 242DF, 242CF, 242BF, 241DF, 241CF, 241BF and 241AF, refer to AMM Task 53-32-12-400-002. (d) Install the textile floor covering between Frame 35 and Frame 36, refer to AMM Task 25-28-41-400-001. (e) Install the passengers Seats between Frame 35 and Frame 36, refer to AMM Task 25-21-41-400-001. (f) Close the FWD passenger/crew door 831, refer to AMM Task 52-10-00-410-001. (g) Remove the access platform(s). (h) Disconnect the aircraft electrical ground-connection. (i) Restore the systems and the aircraft to normal operating condition. **CONF 002 (1) Subtask 571178-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

References Aircraft Maintenance Manual (AMM) Task 25-21-41-400-001 Task 25-28-41-400-001 Task 52-10-00-410-001 Task 53-32-12-400-002 (a) If removed, install hydraulic pipes clamps and them back in initial position. (b) Make sure that the work areas are clean and clear of tools and other items of equipment. (c) Install the floor Panels 242DF, 242CF, 242BF, 241DF, 241CF, 241BF and 241AF, refer to AMM Task 53-32-12-400-002. (d) Install the textile floor covering between Frame 35 and Frame 36, refer to AMM Task 25-28-41-400-001. (e) Install the passengers Seats between Frame 35 and Frame 36, refer to AMM Task 25-21-41-400-001. (f) Close the FWD passenger/crew door 831, refer to AMM Task 52-10-00-410-001. (g) Remove the access platform(s). (h) Disconnect the aircraft electrical ground-connection. (i) Restore the systems and the aircraft to normal operating condition. **CONF 003 (1) Subtask 571178-942-002-001 - Close-up Manpower Resources Skills NON SPECIFIC References Aircraft Maintenance Manual (AMM) Task 25-21-41-400-001 Task 25-28-41-400-001 Task 52-10-00-410-001 Task 53-32-12-400-002 (a) If removed, install hydraulic pipes clamps and them back in initial position. (b) Make sure that the work areas are clean and clear of tools and other items of equipment. (c) Install the floor Panels 242DF, 242CF, 242BF, 241DF, 241CF, 241BF and 241AF, refer to AMM Task 53-32-12-400-002. (d) Install the textile floor covering between Frame 35 and Frame 36, refer to AMM Task 25-28-41-400-001.

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 (e) Install the passengers Seats between Frame 35 and Frame 36, refer to AMM Task 25-21-41-400-001. (f) Close the FWD passenger/crew door 831, refer to AMM Task 52-10-00-410-001. (g) Remove the access platform(s). (h) Disconnect the aircraft electrical ground-connection. (i) Restore the systems and the aircraft to normal operating condition.

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 001

DATUM

**FWD** FR36

INSPECTION AREA **NOTE:** 

### A **A**



## A **A B**  FR36 FR42



## A

VIEW LOOKING AFT FLOOR BEAM 

### B **B B** 
**B B**  **B A**  Z240

N_SB_571178_5_BAAA_01_04 Figure A-FBAAA - Sheet 01 Inspection Area
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 001

DATUM

**FWD** FR36

INSPECTION AREA **NOTE:** 

## A **A**

VIEW LOOKING FWD FLOOR BEAM



## B **B B** 

**B**

N_SB_571178_5_BAAA_02_00 Figure A-FBAAA - Sheet 02 Inspection Area
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 002 thru 003

INSPECTION AREA **NOTE:** 

### A **A**



## B FR36 FR42



## A

VIEW LOOKING AFT 

### B **B B** 
**B B**  **B A**  Z240

N_SB_571178_5_BAAB_01_04 Figure A-FBAAB - Sheet 01 Inspection Area
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 002 thru 003

DATUM

**FWD** FR36

INSPECTION AREA **NOTE:** 

## A **A**

VIEW LOOKING FWD FLOOR BEAM



## B **B B** 

**B**

01 REMOVE THE SHIMS AND ASSOCIATED FASTENERS TO PERFORM THE HFEC INSPECTIONS OF FLOOR BEAM AND VERTICAL STIFFENER RADIUS 01

N_SB_571178_5_BAAB_02_00 Figure A-FBAAB - Sheet 02 Inspection Area
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 ALL

DATUM

**FWD** FR36

**NOTE:** 

### A **A**



## A **A B**  FR36 FR42



## A

VIEW LOOKING AFT FLOOR BEAM 

### B **B B** 
**B B**  **B A**  Z240

FASTENERS HOLES TO BE INSPECTED

FASTENERS HOLES TO BE INSPECTED N_SB_571178_5_BBAA_01_00 Figure A-FBBAA - Sheet 01 Inspection of the Fasteners Holes
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 001

DATUM

**FWD** FR36



### A **A**



## A **A B**  FR36 FR42



## A

VIEW LOOKING AFT FLOOR BEAM 

### B **B B** 
**B B**  **B A**  Z240

N_SB_571178_5_BCAA_01_01 Figure A-FBCAA - Sheet 01 Removal/Installation of the Fasteners
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 001

HOLE PN DESCRIPTION REMARKS ITEM SYMBOL
1

2 SCREW

NUT ASNA2536−4 EN6115V4−6 (1)
(2)

**NOTE:**
PROTECT THE FASTENERS WITH INTERIOR FINISH MAT. No 04JME4 02 01 02

INSTALL THE FASTENERS WITH MAT. No 06AAA1 (WET ASSEMBLY) 01
AND APPLY PROTECTIVE FINISH WITH MAT. No 04DAB2 N_SB_571178_5_BCAA_02_01 Figure A-FBCAA - Sheet 02 Removal/Installation of the Fasteners
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 003

DATUM FR36



### A **A**



## A **A B**  FR36 FR42



## A

VIEW LOOKING AFT FLOOR BEAM 

### B **B B** 
**B B**  **B A**  Z240

FR36 DATUM

FLOOR BEAM



## B **B B** 

**B** (8) (7) 01 01

01 **NOTE:** INSTALL THE SHIMS AND WITH LIQUID SHIM MAT. No 13FGC1 (8) (7) **FWD FWD**  N_SB_571178_5_BCAB_01_02 Figure A-FBCAB - Sheet 01 Removal/Installation of the Shims and the Fasteners
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 003

HOLE PN DESCRIPTION REMARKS ITEM SYMBOL 6
2 SCREW NUT ASNA2536−4 EN6115V4−9 (6) (2)

PROTECT THE FASTENERS WITH INTERIOR FINISH MAT. No 04JME4 03 03 02

AND APPLY PROTECTIVE FINISH WITH MAT. No 04DAB2 **NOTE:**

02 INSTALL THE FASTENERS WITH MAT. No 06AAA1 (WET ASSEMBLY)
N_SB_571178_5_BCAB_02_01 Figure A-FBCAB - Sheet 02 Removal/Installation of the Shims and the Fasteners
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

DATUM

**FWD** FR36



### A **A**



## A **A B**  FR36 FR42



## A

VIEW LOOKING AFT FLOOR BEAM 

### B **B B** 
**B B**  **B A**  Z240

FR36 DATUM

FLOOR BEAM



## B **B**

**FWD** 

### B

**B** (8) (7) 01 01

01 INSTALL THE SHIMS AND WITH LIQUID SHIM MAT. No 13FGC1 (8) (7) **NOTE:** N_SB_571178_5_BCAC_01_02 Figure A-FBCAC - Sheet 01 Removal/Installation of the Shims and the Fasteners
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

HOLE PN DESCRIPTION REMARKS ITEM SYMBOL 3
2 SCREW NUT ASNA2536−4 EN6115V4Y9 (3) (2)

PROTECT THE FASTENERS WITH INTERIOR FINISH MAT. No 04JME4 03 SECOND OVERSIZE FASTENER IN TRANSITION FIT FINAL HOLE DIAMETER

7.102 mm (0.280 in) 7.141 mm (0.281 in) MIN MAX

AND APPLY PROTECTIVE FINISH WITH MAT. No 04DAB2 4
5 SCREW NUT ASNA2536−5 EN6115V5−9 (4) (5) 7.900 mm (0.311 in) 7.940 mm (0.312 in) NEXT NOMINAL DIAMETER IN TRANSITION FIT

**NOTE:**

02 INSTALL THE FASTENERS WITH MAT. No 06AAA1 (WET ASSEMBLY) 03 02

03 02

N_SB_571178_5_BCAC_02_02 Figure A-FBCAC - Sheet 02 Removal/Installation of the Shims and the Fasteners
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

QUESTION ACTION FINDING CRACK FOUND NO YES REFER TO TASK 571178−832−801−001

CONTACT AIRBUS AND APPLY FURTHER

APPLY SERVICE BULLETIN No A320−57−1017 −OF THE FASTENERS HOLES OF FRONT SPAR VERTICAL STRINGERS ON FRAME 36 −OF THE HORIZONTAL FLOOR BEAM RADIUS ON FRAME 36 DO A SPECIAL DETAILED INSPECTION : −OF FRONT SPAR VERTICAL STRINGERS RADIUS ON FRAME 36

INSTRUCTIONS BEFORE NEXT FLIGHT OR

REPEAT THE INSPECTION AT THE INTERVAL GIVEN IN THE TABLE 1

OF THE PLANNING INFORMATION PARAGRAPH E.(2) REFER TO TASK 571178−832−801−001

REPEAT THE INSPECTION AT THE INTERVAL GIVEN IN THE TABLE 1

OF THE PLANNING INFORMATION PARAGRAPH E.(2) REFER TO TASK 571178−832−801−001

**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 AT THE THRESHOLD GIVEN IN THE TABLE 1 OF THE PLANNING INFORMATION PARAGRAPH E.(2)

N_SB_571178_5_FAAA_01_04 Figure A-FFAAA - Sheet 01 Flow Chart
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 thru 003

CRACK FOUND NO YES

CONTACT AIRBUS AND APPLY FURTHER REPEAT THE INSPECTION AT THE INTERVAL GIVEN IN THE TABLE 1 OF THE PLANNING INFORMATION PARAGRAPH E.(2) REFER TO TASK 571178−832−801−001 INSTRUCTIONS BEFORE NEXT FLIGHT

QUESTION ACTION FINDING **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 REFER TO TASK 571178−832−801−001 −OF THE FASTENERS HOLES OF FRONT SPAR VERTICAL STRINGERS ON FRAME 36 −OF THE HORIZONTAL FLOOR BEAM RADIUS ON FRAME 36 DO A SPECIAL DETAILED INSPECTION :

−OF FRONT SPAR VERTICAL STRINGERS RADIUS ON FRAME 36 AT THE THRESHOLD GIVEN IN THE TABLE 1 OF THE PLANNING INFORMATION PARAGRAPH E.(2)

N_SB_571178_5_FAAB_01_04 Figure A-FFAAB - Sheet 01 Flow Chart
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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

QUESTION ACTION FINDING CRACK FOUND NO YES REFER TO TASK 571178−832−802−001

CONTACT AIRBUS AND APPLY FURTHER

APPLY SERVICE BULLETIN No A320−57−1017 −OF THE FASTENERS HOLES OF FRONT SPAR VERTICAL STRINGERS ON FRAME 36 −OF THE HORIZONTAL FLOOR BEAM RADIUS ON FRAME 36 DO A SPECIAL DETAILED INSPECTION : −OF FRONT SPAR VERTICAL STRINGERS RADIUS ON FRAME 36

INSTRUCTIONS BEFORE NEXT FLIGHT OR

REPEAT THE INSPECTION AT THE INTERVAL GIVEN IN THE TABLE 2

OF THE PLANNING INFORMATION PARAGRAPH E.(2) REFER TO TASK 571178−832−801−001

REPEAT THE INSPECTION AT THE INTERVAL GIVEN IN THE TABLE 2

OF THE PLANNING INFORMATION PARAGRAPH E.(2) REFER TO TASK 571178−832−801−001

**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 AT THE THRESHOLD GIVEN IN THE TABLE 2 OF THE PLANNING INFORMATION PARAGRAPH E.(2)

N_SB_571178_5_FBAA_01_01 Figure A-FFBAA - Sheet 01 Flow Chart - ADDITIONAL WORK
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 002 thru 003

CRACK FOUND NO YES

CONTACT AIRBUS AND APPLY FURTHER REPEAT THE INSPECTION AT THE INTERVAL GIVEN IN THE TABLE 2 OF THE PLANNING INFORMATION PARAGRAPH E.(2) REFER TO TASK 571178−832−801−001 INSTRUCTIONS BEFORE NEXT FLIGHT

QUESTION ACTION FINDING **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 REFER TO TASK 571178−832−802−001 −OF THE FASTENERS HOLES OF FRONT SPAR VERTICAL STRINGERS ON FRAME 36 −OF THE HORIZONTAL FLOOR BEAM RADIUS ON FRAME 36 DO A SPECIAL DETAILED INSPECTION :

−OF FRONT SPAR VERTICAL STRINGERS RADIUS ON FRAME 36 AT THE THRESHOLD GIVEN IN THE TABLE 2 OF THE PLANNING INFORMATION PARAGRAPH E.(2)

N_SB_571178_5_FBAB_01_01 Figure A-FFBAB - Sheet 01 Flow Chart - ADDITIONAL WORK
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 ALL

FR36 FR42 **INSPECTION REPORT** SERVICE BULLETIN No : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A320−57−1178

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)



## A

INSPECTION AREA **NOTE:** 

### A **A**



## B ZONE 1 ZONE 2 6 5 4 3 2 1

VIEW LOOKING AFT 

### B **B B**  **B B**  **B**

FASTENERS HOLES TO BE INSPECTED
N_SB_571178_5_RAAA_01_04 Figure A-FRAAA - Sheet 01 Inspection Report
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 ALL **INSPECTION REPORT** SERVICE BULLETIN No : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A320−57−1178

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)

DATUM

**FWD** FR36



## A **A** VIEW LOOKING FWD FLOOR BEAM



## B **B B** 

**B** ZONE 2 ZONE 1

INSPECTION AREA **NOTE:**

FASTENERS HOLES TO BE INSPECTED FASTENERS HOLES TO BE INSPECTED

N_SB_571178_5_RAAA_02_03 Figure A-FRAAA - Sheet 02 Inspection Report
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 ALL

YES NO NUMBER CRACK
1 2 3 4 5 6 **INSPECTION REPORT** SERVICE BULLETIN No : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A320−57−1178

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

HF EDDY CURRENT INSPECTION

FRONT SPAR

VERTICAL STRINGERS FAX +33 (0)5 61 93 36 14 CENTER WING BOX (SA/LA)

YES NO CRACK VERTICAL STRINGERS SIDE FRONT SPAR BEAM SIDE FLOOR

N_SB_571178_5_RAAA_03_01 Figure A-FRAAA - Sheet 03 Inspection Report
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 ALL

YES NO NUMBER CRACK
1 2 3 4 5 6 **INSPECTION REPORT** SERVICE BULLETIN No : A/C MSN : FLIGHT CYCLES : FLIGHT HOURS : A320−57−1178

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

ROTOTEST INSPECTION

FRONT SPAR

VERTICAL STRINGERS FAX +33 (0)5 61 93 36 14 CENTER WING BOX (SA/LA)

YES NO CRACK ZONE 1 HOLE ZONE 2 HOLE

N_SB_571178_5_RAAA_04_00 Figure A-FRAAA - Sheet 04 Inspection Report
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 Appendix 01 - Elapsed Time Assumption **CONF ALL For an explanation of the manhours and elapsed time, refer to the following Gantt Chart.

DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 - Elapsed Time Assumption

**CONF 002

**ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A320−57−1178**

STEPS

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

: : SB ELAPSED TIME (HOURS) 0 2 5 7 9 GET ACCESS

DO HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTIONS OF THE SPAR VERTICAL STRINGERS RADIUS AND THE HORIZONTAL FLOOR BEAM RADIUS AND DO A ROTOTEST INSPECTION OF

OVERSIZE THE HOLES OF THE SPAR VERTICAL STRINGERS RADIUS,

INSTALL THE NEW FASTENERS AND THE SHIMS OF THE SPAR VERTICAL STRINGERS ON FR36 REMOVE THE FASTENERS AND THE SHIMS OF THE SPAR VERTICAL STRINGERS ON FR36

TEST

CLOSE−UP 12 13 MH ET/S
6.00 3.00 PER

2

5.00 2.50 2 3.00 1.50 2

1.00 1.00 1

7.00 3.50 2

TOTAL MANHOURS SB ELAPSED TIME 24.25 13.75

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

IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS ARE NOT REFLECTED IN THIS GANTT CHART. THE FASTENERS HOLES ON FR36

THE HORIZONTAL FLOOR BEAM AND THE HOLES OF THE SHIMS ON FR36

1 3 4 6 8 10 11 14 2.00 2.00 1

0.25 0.25 1

N_SB_571178_5_AAAA_01_02 Figure A-FAAAA - Sheet 01 Gantt Chart
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 01 - Elapsed Time Assumption

**CONF 003

**ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A320−57−1178**

STEPS

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

: : SB ELAPSED TIME (HOURS) 0 2 5 7 9 GET ACCESS

DO HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTIONS OF THE SPAR VERTICAL STRINGERS RADIUS AND THE HORIZONTAL FLOOR BEAM RADIUS AND DO A ROTOTEST INSPECTION OF

INSTALL THE NEW FASTENERS AND THE SHIMS OF THE SPAR VERTICAL STRINGERS ON FR36 REMOVE THE FASTENERS AND THE SHIMS OF THE SPAR VERTICAL STRINGERS ON FR36

TEST

CLOSE−UP 12 13 MH ET/S
6.00 3.00 PER

2

5.00 2.50 2 3.00 1.50 2

7.00 3.50 2

TOTAL MANHOURS SB ELAPSED TIME 23.25 12.75

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

IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS ARE NOT REFLECTED IN THIS GANTT CHART. THE FASTENERS HOLES ON FR36

1 3 4 6 8 10 11 14 2.00 2.00 1

0.25 0.25 1

N_SB_571178_5_AAAC_01_01 Figure A-FAAAC - Sheet 01 Gantt Chart
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 Appendix 01 - Elapsed Time Assumption

**CONF 001

**ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A320−57−1178**

GET ACCESS MH ET/S

TOTAL MANHOURS SB ELAPSED TIME 23.25 12.75 STEPS

6.00 3.00

0 REMOVE THE FASTENERS OF THE SPAR 3.00 1.50

2.00 2.00

5.00 2.50

TEST 0.25 0.25

CLOSE−UP 7.00 3.50

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

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

2

2

1

2

1

2

: : SB ELAPSED TIME (HOURS) 2 4 6 8

IF A VSB IS INVOLVED THE ASSOCIATED MANHOURS ARE NOT REFLECTED IN THIS GANTT CHART VERTICAL STRINGERS ON FR36
DO HIGH FREQUENSY EDDY CURRENT (HFEC) INSPECTION OF THE SPAR

INSTALL THE NEW FASTENERS OF THE SPAR VERTICAL STRINGERS ON FR36 VERTICAL STRINGERS RADIUS AND THE

10 12 14 DO A ROTOTEST INSPECTION OF THE FASTENERS HOLES ON FR36 HORIZONTAL FLOOR BEAM RADIUS AND

N_SB_571178_5_AAAB_01_01 Figure A-FAAAB - Sheet 01 Gantt Chart
DATE: Oct 29/13 SERVICE BULLETIN No.: A320-57-1178 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 REPORTING SHEET 

### TITLE: WINGS - INSPECTION OF FRONT SPAR VERTICAL STRINGERS 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 29/13 SERVICE BULLETIN No.: A320-57-1178 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 29/13 SERVICE BULLETIN No.: A320-57-1178 REVISION No.: 01 - May 28/14 Page: 1 5

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