@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: WING - CENTER WING - INSPECTION OF THE LOWER RIBS AT FR36

JUNCTION

MODIFICATION No.: None

This page transmits Revision No.01 of Service Bulletin No.A320-57-1175

ADDITIONAL WORK

**CONF ALL

Additional work is required by this revision for aircraft modified by any previous issue and on which:

- the removal of the shims and fasteners in inspected area has not been done,

- the HFEC inspection of the radius of the rib flanges has not been done,

- the rototest inspection has not been done.

The additional work consist in:

- the removal of the shims and fasteners in inspected area,

- the HFEC inspection of the radius of the rib flanges,

- the rototest inspection.

REASON

Revision No. 01 issued to incorporate changes found necessary and carried out during the

accomplishment of this Service Bulletin on aircraft with Manufacturer Serial Number (MSN) 0078.

This Service Bulletin has been validated at original issue on A320 aircraft with Manufacturer Serial

Number (MSN) 0078.

Aircraft with Manufacturer Serial Number (MSN) 0078 complies fully with the requirements of the

current issue of the Service Bulletin.

CHANGES

The main changes of this revision are:

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 1

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REVISION TRANSMITTAL SHEET

- add the removal of the shim for the special detailed inspection,

- create supplementary tasks ADDITIONAL WORK.

SUMMARY

GENERAL EVALUATION GENERAL EVALUATION TABLE UPDATED R

MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE

UPDATED

R

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

EFFECTIVITY OPERATOR LIST UPDATED R

MANPOWER MANPOWER UPDATED R

MANPOWER UPDATED R

APPENDICES APPENDICES UPDATED R

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

Configuration definition

CONF 001 CONFIGURATION DEFINITION UPDATED R

Material Effectivity MATERIAL EFFECTIVITY UPDATED

MATERIAL SET UPDATED

MATERIAL SET QUANTITY UPDATED

R

MATERIAL EFFECTIVITY UPDATED

MATERIAL SET UPDATED

MATERIAL SET QUANTITY UPDATED

R

COMPLIANCE

Classification CLASSIFICATION UPDATED R

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED

CONFIGURATION UPDATED

R

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED

CONFIGURATION UPDATED

R

MANPOWER MANPOWER UPDATED

CONFIGURATION UPDATED

R

MANPOWER UPDATED

CONFIGURATION UPDATED

R

REFERENCES REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

PUBLICATION AFFECTED PUBLICATIONS AFFECTED UPDATED R

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY

Procurement Addresses PROCUREMENT ADDRESSES UPDATED

MATERIAL SET UPDATED

R

Price and Availability PRICE AND AVAILABILITY UPDATED

MATERIAL AVAILABILITY UPDATED

MATERIAL PRICE UPDATED

MATERIAL SET UPDATED

R

LIST OF COMPONENTS LIST OF COMPONENTS UPDATED R

Kit 571175A01R00 PART MATERIAL SET ADDED N

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 2

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REVISION TRANSMITTAL SHEET

Kit 571175A02R00 PART MATERIAL SET ADDED N

LIST OF MATERIALS - OPERATOR

SUPPLIED

Consumable Materials

Consumable CMLA01 CONSUMABLE MATERIAL SET UPDATED

QUANTITY UPDATED

CONSUMABLE UPDATED

R

Components COMPONENTS UPDATED R

Component COMPA01 PART MATERIAL SET DELETED D

Component COMPA02 PART MATERIAL SET DELETED D

TOOLING TOOLING UPDATED R

Tooling - Price and Availability TOOLING - PRICE AND AVAILABILITY

PARAGRAPH ADDED

N

Tools TOOLS PARAGRAPH ADDED N

Special Tools SPECIAL TOOLS PARAGRAPH ADDED N

Kit tool 571175T01R00 TOOL MATERIAL SET ADDED N

ACCOMPLISHMENT INSTRUCTIONS

TASK 571175- 832-801-001-Special

Detailed Inspection of the Radius and

Holes of the Rib Flanges and Vertical

Stiffener at FR36

TASK SOLUTION UPDATED

TASK TITLE UPDATED

CAUTION UPDATED

NOTE UPDATED

R

Task associated data - 001 ZONE UPDATED

PANEL UPDATED

MAN HOURS UPDATED

ELAPSED TIME UPDATED

R

Task associated data - 002 ZONE UPDATED

PANEL UPDATED

MAN HOURS UPDATED

ELAPSED TIME UPDATED

R

Subtask 571175-910-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 571175-910-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 571175-941-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

NOTE UPDATED

REFERENCES UPDATED

R

Subtask 571175-010-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 571175-941-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

NOTE UPDATED

REFERENCES UPDATED

R

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 3

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REVISION TRANSMITTAL SHEET

Subtask 571175-010-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 571175-000-003-001 SUBTASK SOLUTION ADDED N

Subtask 571175-832-001-001 SUBTASK SOLUTION UPDATED

PANEL UPDATED

ZONE UPDATED

REFERENCED DOCUMENTATION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

CONSUMABLE UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER DESCRIPTION UPDATED

NOTE UPDATED

LOCATION UPDATED

MANPOWER RESSOURCE UPDATED

REFERENCES UPDATED

R

Subtask 571175-831-005-001 SUBTASK SOLUTION ADDED N

Subtask 571175-831-006-001 SUBTASK SOLUTION ADDED N

Subtask 571175-400-003-001 SUBTASK SOLUTION ADDED N

Subtask 571175-000-003-002 SUBTASK SOLUTION ADDED N

Subtask 571175-832-001-002 SUBTASK SOLUTION UPDATED

PANEL UPDATED

ZONE UPDATED

QUANTITY UPDATED

REFERENCED DOCUMENTATION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

CONSUMABLE UPDATED

ITEM NUMBER UPDATED

PART NUMBER DESCRIPTION UPDATED

NOTE UPDATED

LOCATION UPDATED

MANPOWER RESSOURCE UPDATED

MATERIAL LIST UPDATED

REFERENCES UPDATED

R

Subtask 571175-831-005-002 SUBTASK SOLUTION ADDED N

Subtask 571175-831-006-002 SUBTASK SOLUTION ADDED N

Subtask 571175-400-003-002 SUBTASK SOLUTION ADDED N

Subtask 571175-700-001-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

NOTE UPDATED

R

Subtask 571175-700-001-001 SUBTASK SOLUTION UPDATED

CONFIGURATION UPDATED

NOTE UPDATED

R

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 4

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REVISION TRANSMITTAL SHEET

Subtask 571175-942-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

NOTE UPDATED

CONFIGURATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 571175-942-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

NOTE UPDATED

CONFIGURATION UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

TASK 571175- 832-802-001-Special

Detailed Inspection of the Radius and

Holes of the Rib Flanges and Vertical

Stiffener at FR36 for ADDITIONAL WORK

TASK SOLUTION ADDED N

Task associated data - 001 TASK ASSOCIATED DATA ADDED N

Task associated data - 002 TASK ASSOCIATED DATA ADDED N

Subtask 571175-910-003-001 SUBTASK SOLUTION ADDED N

Subtask 571175-839-003-001 SUBTASK SOLUTION ADDED N

Subtask 571175-910-003-001 SUBTASK SOLUTION ADDED N

Subtask 571175-839-003-001 SUBTASK SOLUTION ADDED N

Subtask 571175-941-003-001 SUBTASK SOLUTION ADDED N

Subtask 571175-010-003-001 SUBTASK SOLUTION ADDED N

Subtask 571175-941-003-001 SUBTASK SOLUTION ADDED N

Subtask 571175-010-003-001 SUBTASK SOLUTION ADDED N

Subtask 571175-000-004-001 SUBTASK SOLUTION ADDED N

Subtask 571175-832-003-001 SUBTASK SOLUTION ADDED N

Subtask 571175-831-007-001 SUBTASK SOLUTION ADDED N

Subtask 571175-831-008-001 SUBTASK SOLUTION ADDED N

Subtask 571175-400-004-001 SUBTASK SOLUTION ADDED N

Subtask 571175-000-004-002 SUBTASK SOLUTION ADDED N

Subtask 571175-832-003-002 SUBTASK SOLUTION ADDED N

Subtask 571175-831-007-002 SUBTASK SOLUTION ADDED N

Subtask 571175-831-008-002 SUBTASK SOLUTION ADDED N

Subtask 571175-400-004-002 SUBTASK SOLUTION ADDED N

Subtask 571175-700-003-001 SUBTASK SOLUTION ADDED N

Subtask 571175-700-003-001 SUBTASK SOLUTION ADDED N

Subtask 571175-942-003-001 SUBTASK SOLUTION ADDED N

Subtask 571175-942-003-001 SUBTASK SOLUTION ADDED N

TASK 571175-831-801 TASK DELETED FOR APPLICABLE MSN D

Fig. A-FBAAA FIGURE SOLUTION UPDATED R

Fig. A-FBAAA Sheet 01 SHEET UPDATED R

Fig. A-FBAAA Sheet 02 SHEET UPDATED R

Fig. A-FBAAA Sheet 03 SHEET ADDED N

Fig. A-FBBAA FIGURE SOLUTION UPDATED R

Fig. A-FBBAA Sheet 01 SHEET UPDATED R

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 5

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REVISION TRANSMITTAL SHEET

Fig. A-FBBAA Sheet 02 SHEET UPDATED R

Fig. A-FBBAB FIGURE SOLUTION ADDED N

Fig. A-FBBAB Sheet 01 SHEET ADDED N

Fig. A-FBBAB Sheet 02 SHEET ADDED N

Fig. A-FBDAA FIGURE SOLUTION ADDED N

Fig. A-FBDAA Sheet 01 SHEET ADDED N

Fig. A-FBEAA FIGURE SOLUTION ADDED N

Fig. A-FBEAA Sheet 01 SHEET ADDED N

Fig. A-FBEAA Sheet 02 SHEET ADDED N

Fig. A-FBEAB FIGURE SOLUTION ADDED N

Fig. A-FBEAB Sheet 01 SHEET ADDED N

Fig. A-FBEAB Sheet 02 SHEET ADDED N

Fig. A-FBFAA FIGURE SOLUTION ADDED N

Fig. A-FBFAA Sheet 01 SHEET ADDED N

Fig. A-FBFAB FIGURE SOLUTION ADDED N

Fig. A-FBFAB Sheet 01 SHEET ADDED N

Fig. A-FBGAA FIGURE SOLUTION ADDED N

Fig. A-FBGAA Sheet 01 SHEET ADDED N

Fig. A-FBGAA Sheet 02 SHEET ADDED N

Fig. A-FBGAB FIGURE SOLUTION ADDED N

Fig. A-FBGAB Sheet 01 SHEET ADDED N

Fig. A-FBGAB Sheet 02 SHEET ADDED N

Fig. A-FBHAA FIGURE SOLUTION ADDED N

Fig. A-FBHAA Sheet 01 SHEET ADDED N

Fig. A-FBHAA Sheet 02 SHEET ADDED N

Fig. A-FBHAB FIGURE SOLUTION ADDED N

Fig. A-FBHAB Sheet 01 SHEET ADDED N

Fig. A-FBHAB Sheet 02 SHEET ADDED N

Fig. A-FBJAA FIGURE SOLUTION ADDED N

Fig. A-FBJAA Sheet 01 SHEET ADDED N

Fig. A-FBJAB FIGURE SOLUTION ADDED N

Fig. A-FBJAB Sheet 01 SHEET ADDED N

Fig. A-FBC FIGURE DELETED FOR APPLICABLE MSN D

Fig. A-FFAAA

Fig. A-FFAAA Sheet 01 SHEET UPDATED R

Fig. A-FFBAA FIGURE SOLUTION ADDED N

Fig. A-FFBAA Sheet 01 SHEET ADDED N

Fig. A-FRAAA FIGURE SOLUTION UPDATED R

Fig. A-FRAAA Sheet 01 SHEET UPDATED R

Fig. A-FRAAA Sheet 02 SHEET UPDATED R

Fig. A-FRAAA Sheet 03 SHEET ADDED N

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 6

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Appendix 01 - Non-Destructive Test Requirements

APPENDIX CONTENT APPENDIX CONTENT ADDED N

Fig. A-FAAAA FIGURE SOLUTION ADDED N

Fig. A-FAAAA Sheet 01 SHEET ADDED N

Appendix 02 - Elapsed Time Assumption

APPENDIX CONTENT APPENDIX CONTENT ADDED N

Fig. A-FABAA FIGURE SOLUTION ADDED N

Fig. A-FABAA Sheet 01 SHEET ADDED N

FILLING INSTRUCTIONS

This Service Bulletin has been generated electronically and is reissued as a complete document.

Replace the complete document.

Put this Revision Transmittal Sheet in front of the Service Bulletin.

HISTORY OF PREVIOUS REVISIONS

No previous revision

REVISION SEQUENCE

ORIGINAL: Oct 24/13

REVISION No. : 01 - May 28/14

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 7

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 8

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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: WING - CENTER WING - INSPECTION OF THE LOWER RIBS AT FR36

JUNCTION

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During Full Scale Fatigue Tests, cracks were found in the Center Wing Box internal lower ribs flange at

front spar level. Cracks initiated from vertical fillets of the lower rib flange.

To prevent such damages, Modification No. 20908P1283 was embodied on the aircraft in production

(Serial modification) from MSN 0085.

It consists in installing reinforced lower rib flanges at front spar level (thickness increase). Note that

Mod. No. 20976P1355 was embodied on several aircraft in production prior to MSN 0085.

It consists in installing shims to reduce unfolding effects of the lower rib flange to avoid crack initiation.

For A/C already in service prior to Mod. No. 20908P1283, accomplishment of Service Bulletin

A320-57-1013 (Mod. No. 20976P1355) was rendered mandatory.

In the frame of the Extended Service Goal exercise based on new fatigue tests, analyses of finding on

MSN 0004 dismantling and following fleet utilization evolution, it has been assessed that an additional

inspection is necessary for A/C PostMod No. 20976P1355.

This Service Bulletin requires the inspection of the lower ribs flange at front spar level.

Accomplishment of this Service Bulletin will contribute to maintain the structural integrity of the lower

ribs at front spar level junction.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 1

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SUMMARY

EVALUATION TABLE

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO

BOOKLET AVAILABLE YES VALIDATION ON AIRCRAFT YES

NOTE (1): Service Bulletin must be accomplished.

NOTE: This Service Bulletin has been validated at original issue on A320 aircraft with

Manufacturer Serial Number (MSN) 0078.

Aircraft with Manufacturer Serial Number (MSN) 0078 complies fully with the

requirements of the current issue of the Service Bulletin.

NOTE: A booklet including photographs taken during the validation of this Service Bulletin is

available on AIRBUS|World - Maintenance and Engineering - AirN@v engineering (in

the concerned SB file).

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 571175A01R00 1 1,600.00 Pin, Nut

Kit tool 571175T01R00 1 See SB Extractor

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 571175A02R00 1 2,010.00 Pin, Nut

Kit tool 571175T01R00 1 See SB Extractor

EFFECTIVITY

**CONF ALL

This Service Bulletin is applicable to this (these) operator(s) :

ACA AIC DLH GBB JAV USA

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 2

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SUMMARY

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 571175-832-801-001: Special Detailed Inspection of the Radius and Holes of the Rib

Flanges and Vertical Stiffener at FR36

TOTAL MANHOURS 45.00

ELAPSED TIME (HOURS) 31.00

Task 571175-832-802-001: Special Detailed Inspection of the Radius and Holes of the Rib

Flanges and Vertical Stiffener at FR36 for ADDITIONAL WORK

TOTAL MANHOURS 45.00

ELAPSED TIME (HOURS) 31.00

**CONF 002

Task 571175-832-801-001: Special Detailed Inspection of the Radius and Holes of the Rib

Flanges and Vertical Stiffener at FR36

TOTAL MANHOURS 45.00

ELAPSED TIME (HOURS) 31.00

Task 571175-832-802-001: Special Detailed Inspection of the Radius and Holes of the Rib

Flanges and Vertical Stiffener at FR36 for ADDITIONAL WORK

TOTAL MANHOURS 45.00

ELAPSED TIME (HOURS) 31.00

APPENDICES

**CONF ALL

Appendix 01 - Non-Destructive Test Requirements

Appendix 02 - Elapsed Time Assumption

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 3

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SUMMARY

**CONF ALL

A

FR36

FR42

A

B

B

AREA TO BE INSPECTED

N_SB_571175_5_SAAA_01_00

Figure A-FSAAA - Sheet 01

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 4

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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: WING - CENTER WING - INSPECTION OF THE LOWER RIBS AT FR36

JUNCTION

MODIFICATION No.: None

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the

property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with

any information contained in it. It is delivered on the express condition that said document and the

information contained in it shall be treated as confidential, shall not be used for any purpose other than

that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall

not be duplicated in any manner (except for the purposes of performing the tasks described hereunder

and provided that any recipient of such document shall comply with the conditions herein), without

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

NOTE: This Service Bulletin is only applicable to aircraft on which Mod. No.

20976P1355 (Service Bulletin No. A320-57-1013) is embodied and on which

Mod. No. 20908P1283 is not embodied.

(1) Models

320-211 320-231

(2) Effectivity by MSN

0029 0045-0047 0049-0057 0059 0064-0078 0080-0084

(3) Effectivity by Operator

The Operator/MSN relationship is provided for information only and is correct at the time

of issue in accordance with the information available to AIRBUS. Any future changes

resulting from transfer of an aircraft from one operator to another will not be reflected in

this list unless the Service Bulletin is revised for another reason.

OPERATOR MSN

ACA 0059 0068 0073 0084

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 1

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OPERATOR MSN

AIC 0045 0046 0047 0049 0050 0051 0056 0057 0074 0075 0080

DLH 0069 0070 0071 0072 0078 0083

GBB 0067

JAV 0029

USA 0052 0053 0054 0055 0064 0065 0066 0076 0077 0081 0082

(4) Configuration by MSN

MSN CONFIGURATION

0029 002

0045 0046 0047 0049 0050 0051 0052 0053 0054 0055 0056

0057 0059 0064 0065 0066 0067 0068 0069 0070 0071 0072

0073 0074 0075 0076 0077 0078 0080 0081 0082 0083 0084

001

(5) Configuration definition

**CONF 001

Config. 001 is valid for A320 aircraft on which Mod. No. 20976P1355 is embodied and

Service Bulletin No. A320-57-1013 is not accomplished.

**CONF 002

Config. 002 is valid for A320 aircraft on which Mod. No. 20976P1355 is not embodied

and Service Bulletin No. A320-57-1013 is accomplished.

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Kit 571175A01R00 1

Consumable CMLA01 1

Kit tool 571175T01R00 1

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Kit 571175A02R00 1

Consumable CMLA01 1

Kit tool 571175T01R00 1

**CONF ALL

B. CONCURRENT REQUIREMENTS

None

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 2

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C. REASON

(1) History

During Full Scale Fatigue Tests, cracks were found in the Center Wing Box internal

lower ribs flange at front spar level. Cracks initiated from vertical fillets of the lower rib

flange.

To prevent such damages, Modification No. 20908P1283 was embodied on the aircraft

in production (Serial modification) from MSN 0085.

It consists in installing reinforced lower rib flanges at front spar level (thickness

increase). Note that Mod. No. 20976P1355 was embodied on several aircraft in

production prior to MSN 0085.

It consists in installing shims to reduce unfolding effects of the lower rib flange to

avoid crack initiation. For A/C already in service prior to Mod. No. 20908P1283,

accomplishment of Service Bulletin A320-57-1013 (Mod. No. 20976P1355) was rendered

mandatory.

In the frame of the Extended Service Goal exercise based on new fatigue tests,

analyses of finding on MSN 0004 dismantling and following fleet utilization evolution, it

has been assessed that an additional inspection is necessary for A/C PostMod No.

20976P1355.

(2) Objective/Action

This Service Bulletin requires the inspection of the lower ribs flange at front spar level.

(3) Advantages

Accomplishment of this Service Bulletin will contribute to maintain the structural integrity

of the lower ribs at front spar level junction.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 571175-832-801-001: Special Detailed Inspection of the Radius and Holes of the Rib

Flanges and Vertical Stiffener at FR36

(1) Remove the Fasteners and the Shims

(2) Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and

Vertical Stiffener at FR36

(3) Oversize the Holes of the Shims, on Bench

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 3

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(4) Oversize the Holes of the Rib Flanges, on Aircraft

(5) Install the Shims with the New Fasteners

Task 571175-832-802-001: Special Detailed Inspection of the Radius and Holes of the Rib

Flanges and Vertical Stiffener at FR36 for ADDITIONAL WORK

(1) Remove the Fasteners and the Shims

(2) Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and

Vertical Stiffener at FR36

(3) Oversize the Holes of the Shims, on Bench

(4) Oversize the Holes of the Rib Flanges, on Aircraft

(5) Install the Shims with the New Fasteners

**CONF 002

Task 571175-832-801-001: Special Detailed Inspection of the Radius and Holes of the Rib

Flanges and Vertical Stiffener at FR36

(1) Remove the Fasteners and the Shims

(2) Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and

Vertical Stiffener at FR36

(3) Oversize the Holes of the Shims, on Bench

(4) Oversize the Holes of the Rib Flanges, on Aircraft

(5) Install the Shims with the New Fasteners

Task 571175-832-802-001: Special Detailed Inspection of the Radius and Holes of the Rib

Flanges and Vertical Stiffener at FR36 for ADDITIONAL WORK

(1) Remove the Fasteners and the Shims

(2) Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and

Vertical Stiffener at FR36

(3) Oversize the Holes of the Shims, on Bench

(4) Oversize the Holes of the Rib Flanges, on Aircraft

(5) Install the Shims with the New Fasteners

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 4

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SERVICE BULLETIN

**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

**CONF 001

This Service Bulletin has been classified Mandatory by the issue of an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must

be used as the reference document for the mandated accomplishment timescale.

Table 1, Config. 001 - Special detailed inspection of the radius and holes of the rib flanges and HFEC

Inspection of the Vertical Stiffener at FR36

Condition Action Compliance Time (whichever occurs later)

Threshold (whichever

occurs first)

Grace Period

(whichever occurs

first)

Repetitive interval

(whichever occurs

first)

All Aircraft Do a special detailed

inspection of the radius

and holes of the rib

flanges and vertical

stiffener at FR36, in

accordance with TASK

571175-832-801 001

Special Detailed

Inspection of the

Radius and Holes of

the Rib Flanges and

Vertical Stiffener at

FR36

47800FC /

95600FH from first

flight

850FC /

1700FH from SB

rev00 issue date

None

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 5

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Table 1, Config. 001 - Special detailed inspection of the radius and holes of the rib flanges and HFEC

Inspection of the Vertical Stiffener at FR36

Condition Action Compliance Time (whichever occurs later)

Threshold (whichever

occurs first)

Grace Period

(whichever occurs

first)

Repetitive interval

(whichever occurs

first)

Oversize holes and

install new fasteners,

refer to in accordance

with SUBTASK

571175-831-005 001

Oversize the Holes of

the Shims, on Bench

and SUBTASK

571175-831-006 001

Oversize the Holes of

the Rib Flanges, on

Aircraft and SUBTASK

571175-400-003 001

Install the Shims with

the New Fasteners

and

No crack Before next flight None None

found

Repeat the special

detailed inspection of

the radius and holes of

the rib flanges and

vertical stiffener at

FR36, in accordance

with TASK

571175-832-801 001

Special Detailed

Inspection of the

Radius and Holes of

the Rib Flanges and

Vertical Stiffener at

FR36 (See NOTE*)

None None 32500FC /

65000FH

Crack

found

Contact AIRBUS and

follow their instructions

Before next flight None None

NOTE*: For the repetitive inspections it is not necessary to oversize the holes as the holes are in

transition fit.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 6

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Table 2, Config. 001 - Special detailed inspection of the radius and holes of the rib flanges and HFEC

Inspection of the Vertical Stiffener at FR36 for ADDITIONAL WORK

Condition Action Compliance Time (whichever occurs later)

Threshold (whichever

occurs first)

Grace Period

(whichever occurs

first)

Repetitive interval

(whichever occurs

first)

All Aircraft Do a special

detailed inspection

of the radius and

holes of the rib

flanges and vertical

stiffener at FR36, in

accordance with

TASK

571175-832-802

001 Special

Detailed Inspection

of the Radius and

Holes of the Rib

Flanges and Vertical

Stiffener at FR36 for

ADDITIONAL

WORK

47800FC /

95600FH from first

flight

850FC /

1700FH from SB

rev00 issue date

None

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 7

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Table 2, Config. 001 - Special detailed inspection of the radius and holes of the rib flanges and HFEC

Inspection of the Vertical Stiffener at FR36 for ADDITIONAL WORK

Condition Action Compliance Time (whichever occurs later)

Threshold (whichever

occurs first)

Grace Period

(whichever occurs

first)

Repetitive interval

(whichever occurs

first)

Oversize holes and

install new

fasteners, in

accordance with

SUBTASK

571175-831-005

001 Oversize the

Holes of the Shims,

on Bench and

SUBTASK

571175-831-006

001 Oversize the

Holes of the Rib

Flanges, on Aircraft

and SUBTASK

571175-400-003

001 Install the

Shims with the New

Fasteners

and

No crack Before next flight None None

found

Repeat the special

detailed inspection

of the radius and

holes of the rib

flanges and vertical

stiffener at FR36, in

accordance with

TASK

571175-832-801

001 Special

Detailed Inspection

of the Radius and

Holes of the Rib

Flanges and Vertical

Stiffener at FR36

(See NOTE*)

None None 32500FC /

65000FH

Crack

found

Contact AIRBUS

and follow their

instructions

Before next flight None None

NOTE*: For the repetitive inspections it is not necessary to oversize the holes as the holes are in

transition fit.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 8

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**CONF 002

This Service Bulletin has been classified Mandatory by the issue of an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must

be used as the reference document for the mandated accomplishment timescale.

Table 1, Config. 002 - Special detailed inspection of the radius and holes of the rib flanges and HFEC

Inspection of the Vertical Stiffener at FR36

Condition Action Compliance Time (whichever occurs later)

Threshold (whichever

occurs first)

Grace Period

(whichever occurs

first)

Repetitive interval

(whichever occurs

first)

All Aircraft Do a special detailed

inspection of the radius

and holes of the rib

flanges and vertical

stiffener at FR36, in

accordance with TASK

571175-832-801 001

Special Detailed

Inspection of the

Radius and Holes of

the Rib Flanges and

Vertical Stiffener at

FR36

10700FC /

21500FH from MSB

A320-57-1013

embodiment

850FC /

1700FH from SB

rev00 issue date

None

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 9

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Table 1, Config. 002 - Special detailed inspection of the radius and holes of the rib flanges and HFEC

Inspection of the Vertical Stiffener at FR36

Condition Action Compliance Time (whichever occurs later)

Threshold (whichever

occurs first)

Grace Period

(whichever occurs

first)

Repetitive interval

(whichever occurs

first)

Oversize holes and

install new fasteners,

in accordance with

SUBTASK

571175-831-007 002

Oversize the Holes of

the Shims, on Bench

and SUBTASK

571175-831-008 002

Oversize the Holes of

the Rib Flanges, on

Aircraft and

SUBTASK

571175-400-004 002

Install the Shims with

the New Fasteners

and

No crack Before next flight None None

found

Repeat the special

detailed inspection of

the radius and holes of

the rib flanges and

vertical stiffener at

FR36, in accordance

with TASK

571175-832-801 001

Special Detailed

Inspection of the

Radius and Holes of

the Rib Flanges and

Vertical Stiffener at

FR36 (See NOTE*)

None None 32500FC /

65000FH

Crack

found

Contact AIRBUS and

follow their instructions

Before next flight None None

NOTE*: For the repetitive inspections it is not necessary to oversize the holes as the holes are in

transition fit.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 10

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Table 2, Config. 002 - Special detailed inspection of the radius and holes of the rib flanges and HFEC

Inspection of the Vertical Stiffener at FR36 for ADDITIONAL WORK

Condition Action Compliance Time (whichever occurs later)

Threshold (whichever

occurs first)

Grace Period

(whichever occurs

first)

Repetitive interval

(whichever occurs

first)

All Aircraft Do a special detailed

inspection of the radius

and holes of the rib

flanges and vertical

stiffener at FR36, in

accordance with TASK

571175-832-802 001

Special Detailed

Inspection of the

Radius and Holes of

the Rib Flanges and

Vertical Stiffener at

FR36 for ADDITIONAL

WORK

10700FC /

21500FH from MSB

A320-57-1013

embodiment

850FC /

1700FH from SB

rev00 issue date

None

Oversize holes and

install new fasteners,

in accordance with

SUBTASK

571175-831-007 002

Oversize the Holes of

the Shims, on Bench

and SUBTASK

571175-831-008 002

Oversize the Holes of

the Rib Flanges, on

Aircraft and

SUBTASK

571175-400-004 002

Install the Shims with

the New Fasteners

and

No crack Before next flight None None

found

Repeat special

detailed inspection of

the radius and holes of

the rib flanges and

vertical stiffener at

FR36, in accordance

with TASK

571175-832-801 001

Special Detailed

Inspection of the

Radius and Holes of

the Rib Flanges and

Vertical Stiffener at

FR36 (See NOTE*)

None None 32500FC /

65000FH

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 11

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SERVICE BULLETIN

Table 2, Config. 002 - Special detailed inspection of the radius and holes of the rib flanges and HFEC

Inspection of the Vertical Stiffener at FR36 for ADDITIONAL WORK

Condition Action Compliance Time (whichever occurs later)

Threshold (whichever

occurs first)

Grace Period

(whichever occurs

first)

Repetitive interval

(whichever occurs

first)

Crack

found

Contact AIRBUS and

follow their instructions

Before next flight None None

NOTE*: For the repetitive inspections it is not necessary to oversize the holes as the holes are in

transition fit.

**CONF ALL

F. APPROVAL

The technical content of this document is approved under the authority of Design

Organisation Approval No. EASA.21J.031.

If an aircraft listed in the effectivity has a modification or repair embodied that is not of

AIRBUS origin, and which affects the content of this Service Bulletin, the operator is

responsible for obtaining approval by its airworthiness authority for any adaptation necessary

before incorporation of the Service Bulletin.

G. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labor cost to

do the work. These estimates assume that the work will be done by experienced personnel,

and may need to be revised upwards to suit operator’s circumstances. The estimates do not

include the time to prepare, plan or inspect the work. Manufacture and procurement of parts

and tools, drying times for paints, sealants, etc., and general administration work are also not

included.

**CONF 001

Task 571175-832-801-001: Special Detailed Inspection of the Radius and Holes of the Rib

Flanges and Vertical Stiffener at FR36

Get Access 6.00

On Aircraft

Remove the Fasteners and the Shims 4.00

Do a Special Detailed Inspection of the Radius and

Holes of the Rib Flanges and Vertical Stiffener at FR36

13.00

Oversize the Holes of the Rib Flanges, on Aircraft 2.00

Install the Shims with the New Fasteners 10.00

On Bench

Oversize the Holes of the Shims, on Bench 2.00

Tests 1.00

Close-Up 7.00

TOTAL MANHOURS 45.00

ELAPSED TIME (HOURS) 31.00

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 12

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NOTE: For an explanation of the manhours and elapsed time, refer to the Gantt

Chart Fig. A-FABAA given in Appendix 02 - Elapsed Time Assumption .

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

Task 571175-832-802-001: Special Detailed Inspection of the Radius and Holes of the Rib

Flanges and Vertical Stiffener at FR36 for ADDITIONAL WORK

Get Access 6.00

On Aircraft

Remove the Fasteners and the Shims 4.00

Do a Special Detailed Inspection of the Radius and

Holes of the Rib Flanges and Vertical Stiffener at FR36

13.00

Oversize the Holes of the Rib Flanges, on Aircraft 2.00

Install the Shims with the New Fasteners 10.00

On Bench

Oversize the Holes of the Shims, on Bench 2.00

Tests 1.00

Close-Up 7.00

TOTAL MANHOURS 45.00

ELAPSED TIME (HOURS) 31.00

NOTE: For an explanation of the manhours and elapsed time, refer to the Gantt

Chart Fig. A-FABAA given in Appendix 02 - Elapsed Time Assumption .

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

**CONF 002

Task 571175-832-801-001: Special Detailed Inspection of the Radius and Holes of the Rib

Flanges and Vertical Stiffener at FR36

Get Access 6.00

On Aircraft

Remove the Fasteners and the Shims 4.00

Do a Special Detailed Inspection of the Radius and

Holes of the Rib Flanges and Vertical Stiffener at FR36

13.00

Oversize the Holes of the Rib Flanges, on Aircraft 2.00

Install the Shims with the New Fasteners 10.00

On Bench

Oversize the Holes of the Shims, on Bench 2.00

Tests 1.00

Close-Up 7.00

TOTAL MANHOURS 45.00

ELAPSED TIME (HOURS) 31.00

NOTE: For an explanation of the manhours and elapsed time, refer to the Gantt

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 13

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Chart Fig. A-FABAA given in Appendix 02 - Elapsed Time Assumption .

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

Task 571175-832-802-001: Special Detailed Inspection of the Radius and Holes of the Rib

Flanges and Vertical Stiffener at FR36 for ADDITIONAL WORK

Get Access 6.00

On Aircraft

Remove the Fasteners and the Shims 4.00

Do a Special Detailed Inspection of the Radius and

Holes of the Rib Flanges and Vertical Stiffener at FR36

13.00

Oversize the Holes of the Rib Flanges, on Aircraft 2.00

Install the Shims with the New Fasteners 10.00

On Bench

Oversize the Holes of the Shims, on Bench 2.00

Tests 1.00

Close-Up 7.00

TOTAL MANHOURS 45.00

ELAPSED TIME (HOURS) 31.00

NOTE: For an explanation of the manhours and elapsed time, refer to the Gantt

Chart Fig. A-FABAA given in Appendix 02 - Elapsed Time Assumption .

NOTE: The minimum manhours necessary to accomplish this Service Bulletin are

those for the Inspection. Depending on the inspection result, additional

manhours can apply.

**CONF ALL

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-52

06-41-53 12-34-24 20-28-00

21-20-00 21-21-41 25-54-12

25-80-00 28-25-00 32-12-00

38-11-41 52-30-00 57-17-11

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-55-00

Non Destructive Test Manual (NTM) 51-10-01 51-10-08

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 14

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SERVICE BULLETIN

Service Bulletin (SB) A320-57-1013

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-12 51-24-00 51-40-00

51-42-00 51-43-00 51-44-00

51-75-12 51-76-11

**CONF 002

Aircraft Maintenance Manual (AMM) 06-20-00 06-31-53 06-41-52

06-41-53 12-34-24 20-28-00

21-20-00 21-21-41 25-54-12

25-80-00 28-25-00 32-12-00

38-11-41 52-30-00 57-17-11

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-55-00

Non Destructive Test Manual (NTM) 51-10-01 51-10-08

Service Bulletin (SB) A320-57-1013

Standards Manual (SM)

Structural Repair Manual (SRM) 51-23-12 51-24-00 51-40-00

51-42-00 51-43-00 51-44-00

51-75-12 51-76-11

**CONF ALL

K. PUBLICATION AFFECTED

Maintenance Planning Document (MPD) 571197-01-1

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 15

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This Page Intentionally Left Blank

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 16

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SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Customers with aircraft shown in the effectivity of this Service Bulletin should send a

purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is:

Kit 571175A01R00

Kit 571175A02R00

AIRBUS Material, Logistics and Suppliers

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

For ordering by internet:

http://spares.airbus.com

For ordering by fax: +49 40 50 76 2590

For ordering by E-mail: airbus.kit@airbus.com

(2) Price and Availability

Kit 571175A01R00

Cost 1,600.00 USD

Availability 180 calendar days from receipt of order

The availability given above is the standard lead time from the date of your purchase

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions.

The latest valid price and lead time for ordering purposes shall be obtained through the

AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.

Kit 571175A02R00

Cost 2,010.00 USD

Availability 180 calendar days from receipt of order

The availability given above is the standard lead time from the date of your purchase

order. If items are required before this time, please include a retrofit planning schedule

with your order so that we can try to comply with your requirements.

The sales terms (costs and availability) are estimated in relation to economic conditions.

The latest valid price and lead time for ordering purposes shall be obtained through the

AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will not provide industry support for accomplishment of this Service Bulletin.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 17

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C. LIST OF COMPONENTS

Kit 571175A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

3 EN6115V5X15 24 BOLT

4 ASNA2536-5 24 NUT

9 MS24665-153 6 PIN

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

Kit 571175A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

4 ASNA2536-5 24 NUT

5 EN6115V5Y15 24 BOLT

9 MS24665-153 6 PIN

NOTE: If you find part numbers of hardware components in the related kit(s) which

you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,

refer to Standards Manual (SM). The SM will give you the correct part number

to part number relationship.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Epoxy Primer 04DAB2 As required

Anti-Vapor Paint 04PAF8 As required

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

Polysulfide Sealant-Fuel Tank

Brushable

06ABA1 As required

Polysulfide Sealant-Fuel Tank Fillet 06ABB1 As required

Non Aqueous Cleaner-General 08BAA9 As required

(2) Components

None

(3) Equipment

None

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 18

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E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

(1) Tooling - Price and Availability

None

(2) Tools

None

(3) Special Tools

Kit tool 571175T01R00

ITEM PART N ̊ KEYWORD QTY SEE

NOTES

98D57103003000 TOOL 1

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 19

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DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 20

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 571175-832-801-001 - Special Detailed Inspection of the Radius and Holes of the Rib

Flanges and Vertical Stiffener at FR36

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

WARNING: MAKE SURE THAT THE FORWARD CARGO DOOR IS OPEN BEFORE YOU

REMOVE A PARTITION PANEL IN THE FORWARD CARGO COMPARTMENT.

AIR FROM THE FUEL TANK INERTING SYSTEM CAN COLLECT IN THE

AREA BEHIND THE PANEL. AIR FROM THIS SYSTEM HAS A LOW OXYGEN

CONTENT AND CAN CAUSE INJURY OR DEATH.

WARNING: MAKE SURE THAT YOU DO THE REFUEL PANEL TEST BEFORE OR DURING

THE REFUEL PROCEDURE. DEFECTIVE HIGH-LEVEL SENSORS CAN CAUSE

FUEL TO SPILL OVERBOARD. MAKE SURE THAT YOU COMPLETE THE

REFUEL PANEL TEST BEFORE THE FUEL TANK IS 70 PERCENT FULL.

WARNING: YOU MUST WEAR SAFETY BREATHING EQUIPMENT WHEN YOU DO WORK

IN A FUEL TANK. THE TANKS CAN CONTAIN AIR FROM THE TANK INERTING

SYSTEM. AIR FROM THIS SYSTEM HAS A LOW-OXYGEN CONTENT AND CAN

CAUSE INJURY AND DEATH.

WARNING: BEFORE YOU DO WORK IN OR NEAR A FUEL TANK, MAKE SURE THAT YOU

OBEY ALL THE SAFETY PROCEDURES. THIS WILL PREVENT INJURY TO

PERSONS AND/OR DAMAGE TO THE AIRCRAFT.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS:

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IF THERE IS CONTAMINATION REFER TO ESPM 20-55-00.

NOTE: The accomplishment instructions of this Service Bulletin include procedures given

in other documents or in other sections of the Service Bulletin. When the words

"refer to" are used and the operator has a procedure accepted by the local

authority he belongs to, the accepted alternative procedure can be used. When the

words "in accordance with" are used then the given procedure must be followed.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 21

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Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

NOTE: The purpose of flow charts is to supplement the information given in the Procedure

and Compliance paragraphs and not to serve as the primary source for tasks or

compliance times given in this Service Bulletin.

NOTE: This Service Bulletin is mandated or expected to be mandated by an Airworthiness

Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions

are Required for Compliance (RC) and must be done to comply with the AD. Other

paragraphs are recommended and may be deviated from, done as part of other

actions or done with accepted methods different from those given in the Service

Bulletin, as long as the RC paragraphs can be done and the aircraft can be put

back into a serviceable condition.

Task Associated Data

**CONF 001

Zone

130 140

Access

Panel 131NW 131PW 132PW 147AZ 148AZ

Manpower

TOTAL MANHOURS 45.00

ELAPSED TIME (HOURS) 31.00

**CONF 002

Zone

130 140

Access

Panel 131NW 131PW 132PW 147AZ 148AZ

Manpower

TOTAL MANHOURS 45.00

ELAPSED TIME (HOURS) 31.00

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

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**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 571175-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-31-53, Page Block 001

06-41-52, Page Block 001

06-41-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-42-00

51-43-00

51-44-00

51-75-12

51-76-11

(a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to

the Consumable Material List (CML).

(b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(c) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(d) For the identification of access panels, refer to AMM 06-41-52, Page Block 001 and

AMM 06-41-53, Page Block 001.

(e) Remove and install fasteners in accordance with SRM 51-42-00.

(f) Apply sealant in accordance with SRM 51-24-00.

(g) Renew the protective finish in accordance with SRM 51-75-12.

(h) If alternative and substitute fasteners have to be used, you must make sure that the

associated nut/collar are compatible in accordance with SRM 51-40-00 "Mating

Part" column.

(i) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(j) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

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(k) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00.

(l) Do the repair of fuel tank sealing in accordance with SRM 51-76-11.

(2) Subtask 571175-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in the

Service Bulletin.

**CONF 002

(1) Subtask 571175-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-31-53, Page Block 001

06-41-52, Page Block 001

06-41-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-42-00

51-43-00

51-44-00

51-75-12

51-76-11

(a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to

the Consumable Material List (CML).

(b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(c) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(d) For the identification of access panels, refer to AMM 06-41-52, Page Block 001 and

AMM 06-41-53, Page Block 001.

(e) Remove and install fasteners in accordance with SRM 51-42-00.

(f) Apply sealant in accordance with SRM 51-24-00.

(g) Renew the protective finish in accordance with SRM 51-75-12.

(h) If alternative and substitute fasteners have to be used, you must make sure that the

associated nut/collar are compatible in accordance with SRM 51-40-00 "Mating

Part" column.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 24

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(i) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(j) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00.

(k) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00.

(l) Do the repair of fuel tank sealing in accordance with SRM 51-76-11.

(2) Subtask 571175-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in the

Service Bulletin.

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 571175-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002

Task 21-20-00-010-001

Task 25-54-12-000-001

Task 32-12-00-010-001

Task 52-30-00-860-001

Task 57-17-11-000-001

NOTE: The items given in this note shall be considered as the basic Aircraft

configuration before you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety

locks and the wheel chocks are in position on the landing gear)

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

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- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position

(a) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-869-002.

(b) Put an access platform in position at door 825.

(c) Open the FWD cargo compartment door 825, refer to AMM Task

52-30-00-860-001.

(d) Open the main landing gear doors, refer to AMM Task 32-12-00-010-001.

(e) Put an access platform in position at zones 147 and 148.

(f) Do the preparation procedure as specified in the Removal of the Access Covers

147AZ and 148AZ, refer to AMM Task 57-17-11-000-001.

(g) Do the preparation procedure as specified in the Removal of the Air-Conditioning

Distribution Ducts, refer to AMM Task 21-20-00-010-001.

(h) Do the preparation procedure as specified in the Removal of the Forward CargoCompartment Partition panels at Frame 34, refer to AMM Task 25-54-12-000-001.

(2) Subtask 571175-010-001-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-001

Task 21-21-41-000-001

Task 25-54-12-000-001

Task 25-80-00-000-001

Task 28-25-00-650-001

Task 28-25-00-869-001

Task 38-11-41-000-001

Task 57-17-11-000-001

(a) Defuel the center tank, refer to AMM Task 28-25-00-650-001 or move the fuel into

a different tank, refer to AMM Task 28-25-00-869-001.

(b) Open access covers 147AZ and 148AZ, refer to AMM Task 57-17-11-000-001.

(c) Remove the Forward Cargo-Compartment Partition panels 131PW, 132PW and

131NW at Frame 34, refer to AMM Task 25-54-12-000-001.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

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(d) If necessary remove the recirculation filters LH and RH sides, refer to AMM Task

21-21-41-000-001.

(e) If necessary, remove the Air-Conditioning Distribution Ducts to get access to the

working area, refer to AMM Task 21-20-00-010-001.

(f) If necessary remove the potable water tank 3000MM, refer to AMM Task

38-11-41-000-001.

(g) Remove insulation blankets around working areas between Frame 35 and Frame

36 LH and RH sides for access, refer to AMM Task 25-80-00-000-001.

(h) If necessary, remove electrical bundle clamps and push the bundles aside without

disconnection in order to be able to get them out of the working area.

**CONF 002

(1) Subtask 571175-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002

Task 21-20-00-010-001

Task 25-54-12-000-001

Task 32-12-00-010-001

Task 52-30-00-860-001

Task 57-17-11-000-001

NOTE: The items given in this note shall be considered as the basic Aircraft

configuration before you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety

locks and the wheel chocks are in position on the landing gear)

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 27

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(a) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-869-002.

(b) Put an access platform in position at door 825.

(c) Open the FWD cargo compartment door 825, refer to AMM Task

52-30-00-860-001.

(d) Open the main landing gear doors, refer to AMM Task 32-12-00-010-001.

(e) Put an access platform in position at zones 147 and 148.

(f) Do the preparation procedure as specified in the Removal of the Access Covers

147AZ and 148AZ, refer to AMM Task 57-17-11-000-001.

(g) Do the preparation procedure as specified in the Removal of the Air-Conditioning

Distribution Ducts, refer to AMM Task 21-20-00-010-001.

(h) Do the preparation procedure as specified in the Removal of the Forward CargoCompartment Partition panels at Frame 34, refer to AMM Task 25-54-12-000-001.

(2) Subtask 571175-010-001-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-001

Task 21-21-41-000-001

Task 25-54-12-000-001

Task 25-80-00-000-001

Task 28-25-00-650-001

Task 28-25-00-869-001

Task 38-11-41-000-001

Task 57-17-11-000-001

(a) Defuel the center tank, refer to AMM Task 28-25-00-650-001 or move the fuel into

a different tank, refer to AMM Task 28-25-00-869-001.

(b) Open access covers 147AZ and 148AZ, refer to AMM Task 57-17-11-000-001.

(c) Remove the Forward Cargo-Compartment Partition panels 131PW, 132PW and

131NW at Frame 34, refer to AMM Task 25-54-12-000-001.

(d) If necessary remove the recirculation filters LH and RH sides, refer to AMM Task

21-21-41-000-001.

(e) If necessary, remove the Air-Conditioning Distribution Ducts to get access to the

working area, refer to AMM Task 21-20-00-010-001.

(f) If necessary remove the potable water tank 3000MM, refer to AMM Task

38-11-41-000-001.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 28

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(g) Remove insulation blankets around working areas between Frame 35 and Frame

36 LH and RH sides for access, refer to AMM Task 25-80-00-000-001.

(h) If necessary, remove electrical bundle clamps and push the bundles aside without

disconnection in order to be able to get them out of the working area.

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 571175-000-003-001 - Remove the Fasteners and the Shims

Work Zones and Access Panels

Zone Access/Work location

130 Access Panel 131PW, Panel 132PW, Panel 131NW

140 Access Panel 147AZ, Panel 148AZ

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9

Kit tool 571175T01R00

ITEM PART N ̊ KEYWORD QTY SEE

NOTES

98D57103003000 TOOL 1

References

Structural Repair Manual (SRM) 51-42-00

51-44-00

Fig. A-FBBAA

Removal/Installation of the Shims

Sheet 01

Sheet 02

Fig. A-FBDAA

Removal/Installation of the Rods

Sheet 01

Refer to Fig. A-FBBAA

Refer to Fig. A-FBDAA

In accordance with SRM 51-42-00, SRM 51-44-00

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

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(a) Remove the sealant around the nuts:

1 If necessary, use a non-metallic spatula to remove the sealant and clean the

areas with solvent:

Non Aqueous

Cleaner-General

08BAA9 As required

(b) Remove the nuts:

Refer to Fig. A-FBBAA Sheet 01 and Fig. A-FBBAA Sheet 02

24 Nut Item (2) Discard

(c) Remove the bottom attachment bolt of the rod:

Refer to Fig. A-FBDAA Sheet 01

NOTE: The quantities are given as a maximum for all ribs, it is not allowed

to have 2 rods removed at the same time.

6 Bolt Item (6) Retain

6 Washer Item (7) Retain

6 Nut Item (8) Retain

6 Cotter Pin Item (9) Discard

(d) Push the rod out of the working area:

6 Rod Item (10) Retain

(e) From inside the tank push back the fasteners until they are flush.

NOTE: Do not remove the fasteners by pushing them through the stack up,

there is a risk of damaging the hole and contaminating it with steel

particles.

(f) Install temporarily the rod in initial position before to do the next rod:

Refer to Fig. A-FBDAA Sheet 01

6 Rod Item (10) Retained at

removal

6 Bolt Item (6) Retained at

removal

6 Washer Item (7) Retained at

removal

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6 Nut Item (8) Retained at

removal

(g) When all bolts are pushed back, use the special extraction tool, from the forward

cargo area, to remove these fasteners:

98D57103003000 Extractor 1

(h) From the tank, remove the shims with non-metallic spatula and identify their

position:

Refer to Fig. A-FBBAA Sheet 02

12 Shim Item (11) Retain

attached with:

24 Bolt Item (1) Discard

(2) Subtask 571175-832-001-001 - Do a Special Detailed Inspection of the Radius and

Holes of the Rib Flanges and Vertical Stiffener at FR36

Work Zones and Access Panels

Zone Access/Work location

130 Access Panel 131PW, Panel 132PW, Panel 131NW

140 Access Panel 147AZ, Panel 148AZ

Manpower Resources

Manhours 13.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

References

Non Destructive Test Manual (NTM) 51-10-01

51-10-08

Structural Repair Manual (SRM) 51-42-00

51-44-00

Fig. A-FBAAA

Inspection of the Radius and Holes of

the Rib Flanges and Vertical Stiffener at

FR36

Sheet 01

Sheet 02

Sheet 03

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References

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Fig. A-FFAAA

Flow Chart

Sheet 01

(a) At threshold given in the table 1 of the PLANNING INFORMATION Paragraph

E.(2):

Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and

Vertical Stiffener at FR36.

Refer to Fig. A-FFAAA

Refer to Fig. A-FBAAA

1 Remove the fasteners from the holes to be inspected as described in

SUBTASK 571175-000-003 001 Remove the Fasteners and the Shims .

2 Do a High Frequency Eddy Current (HFEC) inspection of the radius of the rib

flanges and vertical stiffener and a rototest Inspection of the holes at FR36.

Refer to Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 02

a If necessary, use a non-metallic spatula to remove the sealant and clean

the areas with solvent:

Non Aqueous

Cleaner-General

08BAA9 As required

b Deburr all the holes before inspection.

c Do a High Frequency Eddy Current (HFEC) inspection of the radius of

the rib flanges and vertical stiffener and a rototest inspection of the holes

as specified in NTM 51-10-08 and NTM 51-10-01.

NOTE: For additional information of procedure NTM 51-10-01

refer to Appendix 01 - Non-Destructive Test

Requirements.

<1> If no crack is found:

<a> Oversize the holes of the rib flanges and the shims, refer

to SUBTASK 571175-831-005 001 Oversize the Holes of

the Shims, on Bench and SUBTASK 571175-831-006 001

Oversize the Holes of the Rib Flanges, on Aircraft .

and

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

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Repeat the inspection of the radius and holes in the rib flanges

on front spar side at the interval given in the table 1 of the

PLANNING INFORMATION Paragraph E.(2), refer to TASK

571175-832-801 001 Special Detailed Inspection of the Radius

and Holes of the Rib Flanges and Vertical Stiffener at FR36 .

NOTE: For the repetitive inspections it is not necessary

to oversize the holes as the holes are in

transition fit.

<2> If crack is found:

<a> Contact Airbus before next flight and follow their instructions.

3 For the inspection report, refer to Fig. A-FRAAA.

(3) Subtask 571175-831-005-001 - Oversize the Holes of the Shims, on Bench

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

References

Structural Repair Manual (SRM) 51-44-00

Fig. A-FBFAA

Oversizing of the Holes of the Shims, on

Bench

Sheet 01

Refer to Fig. A-FBFAA

In accordance with SRM 51-44-00

(a) Oversize the holes of the shims to the diameter given in Fig. A-FBFAA Sheet 01.

(b) Deburr and clean the holes with:

Non Aqueous

Cleaner-General

08BAA9 As required

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

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(4) Subtask 571175-831-006-001 - Oversize the Holes of the Rib Flanges, on Aircraft

Work Zones and Access Panels

Zone Access/Work location

140 Access Panel 147AZ, Panel 148AZ

Work location Frame 42

130 Access Panel 131PW, Panel 132PW, Panel 131NW

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

References

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

Fig. A-FBEAA

Oversizing of the Holes of the Rib

Flanges, on Aircraft

Sheet 01

Sheet 02

Refer to Fig. A-FBEAA

In accordance with SRM 51-24-00, SRM 51-42-00, SRM 51-43-00, SRM 51-44-00

NOTE: This procedure must be applied to one rib at a time.

(a) Disengage the rod.

(b) Oversize the holes of the rib flanges to the diameter given in Fig. A-FBEAA Sheet

02.

(c) Deburr and clean the drilled area with:

Non Aqueous

Cleaner-General

08BAA9 As required

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

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(5) Subtask 571175-400-003-001 - Install the Shims with the New Fasteners

Work Zones and Access Panels

Zone Access/Work location

140 Access Panel 147AZ, Panel 148AZ

Work location Frame 42

130 Access Panel 131PW, Panel 132PW, Panel 131NW

Manpower Resources

Manhours 10.00

Minimum number of person 2

Subtask elapsed time 5.00

Skills AIRFRAME

Material necessary to do the job

Kit 571175A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 EN6115V5X15 24 BOLT

4 ASNA2536-5 24 NUT

9 MS24665-153 6 PIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Epoxy Primer 04DAB2 As required

Anti-Vapor Paint 04PAF8 As required

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

Polysulfide Sealant-Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant-Fuel

Tank Fillet

06ABB1 As required

References

Structural Repair Manual (SRM) 51-23-12

51-24-00

51-42-00

51-43-00

51-75-12

Fig. A-FBBAA

Removal/Installation of the Shims

Sheet 01

Sheet 02

Fig. A-FBDAA

Removal/Installation of the Rods

Sheet 01

Refer to Fig. A-FBBAA

Refer to Fig. A-FBDAA

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 35

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In accordance with SRM 51-24-00, SRM 51-42-00, SRM 51-43-00, SRM 51-75-12

(a) Install the shims:

Refer to Fig. A-FBBAA Sheet 02

12 Shim Item (11) Retained at

removal

with:

24 Bolt EN6115V5X15 Item 3

24 Nut ASNA2536-5 Item 4

NOTE: Apply sealant on all contact surface between the shims Item (11)

and front spar:

Polysulfide SealantFuel Tank Fillet06ABB1 As required

NOTE: Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(b) After installation:

1 Over coat the fastener tails and nuts in the tank and perform sealing of the

shims and inspection area with:

Polysulfide SealantFuel Tank

Brushable

06ABA1 As required

(c) In the cargo area:

1 Apply epoxy primer and anti-vapor paint:

Epoxy Primer 04DAB2 As required

and

Anti-Vapor Paint 04PAF8 As required

2 Renew the special protection around the fastener heads in accordance with

SRM 51-23-12.

(d) Install the rod in initial position and install the attachment fastener.

Refer to Fig. A-FBDAA Sheet 01

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 36

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1 Install:

6 Rod Item (10) Retained at

removal

Attached with:

6 Bolt Item (6) Retained at

removal

6 Washer Item (7) Retained at

removal

6 Nut Item (8) Retained at

removal

6 Cotter Pin MS24665-153 Item 9

NOTE: The quantities are given as a maximum for all ribs, it is not

allowed to have 2 rods removed at the same time.

2 Perform over coating of nuts and bolts head with:

Polysulfide SealantFuel Tank

Brushable

06ABA1 As required

**CONF 002

(1) Subtask 571175-000-003-002 - Remove the Fasteners and the Shims

Work Zones and Access Panels

Zone Access/Work location

130 Access Panel 131PW, Panel 132PW, Panel 131NW

140 Access Panel 147AZ, Panel 148AZ

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 37

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Kit tool 571175T01R00

ITEM PART N ̊ KEYWORD QTY SEE

NOTES

98D57103003000 TOOL 1

References

Structural Repair Manual (SRM) 51-42-00

51-44-00

Fig. A-FBBAB

Removal/Installation of the Shims

Sheet 01

Sheet 02

Fig. A-FBDAA

Removal/Installation of the Rods

Sheet 01

Refer to Fig. A-FBBAB

Refer to Fig. A-FBDAA

In accordance with SRM 51-42-00, SRM 51-44-00

(a) Remove the sealant around the nuts:

1 If necessary, use a non-metallic spatula to remove the sealant and clean the

areas with solvent:

Non Aqueous

Cleaner-General

08BAA9 As required

(b) Remove the nuts:

Refer to Fig. A-FBBAB Sheet 01 and Fig. A-FBBAB Sheet 02

24 Nut Item (2) Discard

(c) Remove the bottom attachment bolt of the rod:

Refer to Fig. A-FBDAA Sheet 01

NOTE: The quantities are given as a maximum for all ribs, it is not allowed

to have 2 rods removed at the same time.

6 Bolt Item (6) Retain

6 Washer Item (7) Retain

6 Nut Item (8) Retain

6 Cotter Pin Item (9) Discard

(d) Push the rod out of the working area:

6 Rod Item (10) Retain

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

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(e) From inside the tank push back the fasteners until they are flush.

NOTE: Do not remove the fasteners by pushing them through the stack up,

there is a risk of damaging the hole and contaminating it with steel

particles.

(f) Install temporarily the rod in initial position before to do the next rod:

Refer to Fig. A-FBDAA Sheet 01

6 Rod Item (10) Retained at

removal

6 Bolt Item (6) Retained at

removal

6 Washer Item (7) Retained at

removal

6 Nut Item (8) Retained at

removal

(g) When all bolts are pushed back, use the special extraction tool, from the forward

cargo area, to remove these fasteners:

98D57103003000 Extractor 1

(h) From the tank, remove shims with non-metallic spatula and identify their position:

Refer to Fig. A-FBBAB Sheet 02

12 Shim Item (11) Retain

attached with:

24 Bolt Item (1) Discard

(2) Subtask 571175-832-001-002 - Do a Special Detailed Inspection of the Radius and

Holes of the Rib Flanges and Vertical Stiffener at FR36

Work Zones and Access Panels

Zone Access/Work location

130 Access Panel 131PW, Panel 132PW, Panel 131NW

140 Access Panel 147AZ, Panel 148AZ

Manpower Resources

Manhours 13.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 39

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Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9

References

Non Destructive Test Manual (NTM) 51-10-01

51-10-08

Structural Repair Manual (SRM) 51-42-00

51-44-00

Fig. A-FBAAA

Inspection of the Radius and Holes of

the Rib Flanges and Vertical Stiffener at

FR36

Sheet 01

Sheet 02

Sheet 03

Fig. A-FFAAA

Flow Chart

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

(a) At threshold given in the table 1 of the PLANNING INFORMATION Paragraph

E.(2):

Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and

Vertical Stiffener at FR36.

Refer to Fig. A-FFAAA

Refer to Fig. A-FBAAA

1 Remove the fasteners from the holes to be inspected as described in

SUBTASK 571175-000-003 002 Remove the Fasteners and the Shims .

2 Do a High Frequency Eddy Current (HFEC) inspection of the radius of the rib

flanges and vertical stiffener and a rototest Inspection of the holes at FR36.

Refer to Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 02

a If necessary, use a non-metallic spatula to remove the sealant and clean

the areas with solvent:

Non Aqueous

Cleaner-General

08BAA9 As required

b Deburr all the holes before inspection.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 40

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c Do a High Frequency Eddy Current (HFEC) inspection of the radius of

the rib flanges and vertical stiffener and a rototest inspection of the holes

as specified in NTM 51-10-08 and NTM 51-10-01.

NOTE: For additional information of procedure NTM 51-10-01

refer to Appendix 01 - Non-Destructive Test

Requirements.

<1> If no crack is found:

<a> Oversize the holes of the rib flanges and shims, refer

to SUBTASK 571175-831-005 002 Oversize the Holes of

the Shims, on Bench and SUBTASK 571175-831-006 002

Oversize the Holes of the Rib Flanges, on Aircraft .

and

Repeat the inspection of the radius and holes in the rib flanges

on front spar side at the interval given in the table 1 of the

PLANNING INFORMATION Paragraph E.(2), refer to TASK

571175-832-801 001 Special Detailed Inspection of the Radius

and Holes of the Rib Flanges and Vertical Stiffener at FR36 .

NOTE: For the repetitive inspections it is not necessary

to oversize the holes as the holes are in

transition fit.

<2> If crack is found:

<a> Contact Airbus before next flight and follow their instructions.

3 For the inspection report, refer to Fig. A-FRAAA.

(3) Subtask 571175-831-005-002 - Oversize the Holes of the Shims, on Bench

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

References

Structural Repair Manual (SRM) 51-44-00

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 41

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References

Fig. A-FBFAB

Oversizing of the Holes of the Shims, on

Bench

Sheet 01

Refer to Fig. A-FBFAB

In accordance with SRM 51-44-00

(a) Oversize the holes of the shims to the diameter given in Fig. A-FBFAB Sheet 01.

(b) Deburr and clean the holes with:

Non Aqueous

Cleaner-General

08BAA9 As required

(4) Subtask 571175-831-006-002 - Oversize the Holes of the Rib Flanges, on Aircraft

Work Zones and Access Panels

Zone Access/Work location

140 Access Panel 147AZ, Panel 148AZ

Work location Frame 42

130 Access Panel 131PW, Panel 132PW, Panel 131NW

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

References

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

Fig. A-FBEAB

Oversizing of the Holes of the Rib

Flanges, on Aircraft

Sheet 01

Sheet 02

Refer to Fig. A-FBEAB

In accordance with SRM 51-24-00, SRM 51-42-00, SRM 51-43-00, SRM 51-44-00

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 42

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NOTE: This procedure must be applied to one rib at a time.

(a) Disengage the rod.

(b) Oversize the holes of the rib flanges to the diameter given in Fig. A-FBEAB Sheet

02.

(c) Deburr and clean the drilled area with:

Non Aqueous

Cleaner-General

08BAA9 As required

(5) Subtask 571175-400-003-002 - Install the Shims with the New Fasteners

Work Zones and Access Panels

Zone Access/Work location

140 Access Panel 147AZ, Panel 148AZ

Work location Frame 42

130 Access Panel 131PW, Panel 132PW, Panel 131NW

Manpower Resources

Manhours 10.00

Minimum number of person 2

Subtask elapsed time 5.00

Skills AIRFRAME

Material necessary to do the job

Kit 571175A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

4 ASNA2536-5 24 NUT

5 EN6115V5Y15 24 BOLT

9 MS24665-153 6 PIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Epoxy Primer 04DAB2 As required

Anti-Vapor Paint 04PAF8 As required

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

Polysulfide Sealant-Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant-Fuel

Tank Fillet

06ABB1 As required

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 43

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References

Structural Repair Manual (SRM) 51-23-12

51-24-00

51-42-00

51-43-00

51-75-12

Fig. A-FBBAB

Removal/Installation of the Shims

Sheet 01

Sheet 02

Fig. A-FBDAA

Removal/Installation of the Rods

Sheet 01

Refer to Fig. A-FBBAB

Refer to Fig. A-FBDAA

In accordance with SRM 51-24-00, SRM 51-42-00, SRM 51-43-00, SRM 51-75-12

(a) Install the shims:

Refer to Fig. A-FBBAB Sheet 02

12 Shim Item (11) Retained at

removal

with:

24 Bolt EN6115V5Y15 Item 5

24 Nut ASNA2536-5 Item 4

NOTE: Apply sealant on all contact surface between the shims Item (11)

and front spar:

Polysulfide SealantFuel Tank Fillet06ABB1 As required

NOTE: Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(b) After installation:

1 Over coat the fastener tails and nuts in the tank and perform sealing of the

shims and inspection area with:

Polysulfide SealantFuel Tank

Brushable

06ABA1 As required

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 44

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(c) In the cargo area:

1 Apply epoxy primer and anti-vapor paint:

Epoxy Primer 04DAB2 As required

and

Anti-Vapor Paint 04PAF8 As required

2 Renew the special protection around the fastener heads in accordance with

SRM 51-23-12.

(d) Install the rod in initial position and install the attachment fastener.

Refer to Fig. A-FBDAA Sheet 01

1 Install:

6 Rod Item (10) Retained at

removal

Attached with:

6 Bolt Item (6) Retained at

removal

6 Washer Item (7) Retained at

removal

6 Nut Item (8) Retained at

removal

6 Cotter Pin MS24665-153 Item 9

NOTE: The quantities are given as a maximum for all ribs, it is not

allowed to have 2 rods removed at the same time.

2 Perform over coating of nuts and bolts head with:

Polysulfide SealantFuel Tank

Brushable

06ABA1 As required

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 571175-700-001-001 - Testing

Manpower Resources

Skills NON SPECIFIC

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 45

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References

Aircraft Maintenance Manual (AMM) 20-28-00, Page Block 501

Task 21-20-00-410-001

Task 25-54-12-400-001

Task 52-30-00-860-002

Task 57-17-11-400-001

NOTE: This Service Bulletin requires the accomplishment of the following Tests

which are given in subtasks included in the topic Close-up. The

manhours for the tests are included in the referenced Service Bulletin

subtask.

- Remove the Safety clips and tags and close the circuit breakers as specified after

the Installation of the Air-Conditioning Distribution Ducts, refer to AMM Task

21-20-00-410-001.

- Remove the Safety clips and tags and close the circuit breakers as specified after

the Installation of the Access Covers 147AZ and 148AZ, refer to AMM Task

57-17-11-400-001.

- Remove the Safety clips and tags and close the circuit breakers as specified after

Closing the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump,

refer to AMM Task 52-30-00-860-002.

- Remove the Safety clips and tags and close the circuit breakers as specified after

the Installation of Forward Cargo-Compartment Partition panels at Frame 34, refer

to AMM Task 25-54-12-400-001.

- Do the test procedure as specified after the installation of the access covers 147AZ

and 148AZ, refer to AMM Task 57-17-11-400-001.

- Do the test procedure as specified after the installation of the Air-Conditioning

Distribution Ducts, refer to AMM Task 21-20-00-410-001.

**CONF 002

(1) Subtask 571175-700-001-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 20-28-00, Page Block 501

Task 21-20-00-410-001

Task 25-54-12-400-001

Task 52-30-00-860-002

Task 57-17-11-400-001

NOTE: This Service Bulletin requires the accomplishment of the following Tests

which are given in subtasks included in the topic Close-up. The

manhours for the tests are included in the referenced Service Bulletin

subtask.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 46

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- Remove the Safety clips and tags and close the circuit breakers as specified after

the Installation of the Air-Conditioning Distribution Ducts, refer to AMM Task

21-20-00-410-001.

- Remove the Safety clips and tags and close the circuit breakers as specified after

the Installation of the Access Covers 147AZ and 148AZ, refer to AMM Task

57-17-11-400-001.

- Remove the Safety clips and tags and close the circuit breakers as specified after

Closing the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump,

refer to AMM Task 52-30-00-860-002.

- Remove the Safety clips and tags and close the circuit breakers as specified after

the Installation of Forward Cargo-Compartment Partition panels at Frame 34, refer

to AMM Task 25-54-12-400-001.

- Do the test procedure as specified after the installation of the access covers 147AZ

and 148AZ, refer to AMM Task 57-17-11-400-001.

- Do the test procedure as specified after the installation of the Air-Conditioning

Distribution Ducts, refer to AMM Task 21-20-00-410-001.

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 571175-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-001

Task 21-21-41-400-001

Task 25-54-12-400-001

Task 25-80-00-400-001

28-25-00, Page Block 301

Task 32-12-00-410-001

Task 38-11-41-400-001

Task 52-30-00-860-002

Task 57-17-11-400-801

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Install the access cover 147AZ and 148AZ, refer to AMM Task 57-17-11-400-801.

(c) Install the Air-Conditioning Distribution Ducts removed for access to the working

area, AMM Task 21-20-00-410-001.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 47

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(d) If removed, install the recirculation filters LH and RH sides , refer to AMM Task

21-21-41-400-001.

(e) If removed, install the potable water tank 3000MM, refer to AMM Task

38-11-41-400-001.

(f) Install the removed insulation blankets around working areas, refer to AMM Task

25-80-00-400-001.

1 Install the heat and sound insulation in the area between Frame 35 and Frame

36 LH and RH sides removed for access

2 If removed, install electrical bundle clamps removed for access.

(g) Install the removed Forward Cargo-Compartment Partition 131PW, 132PW and

131NW at Frame 34, refer to AMM Task 25-54-12-400-001.

(h) Refuel the center tank, refer to AMM 28-25-00, Page Block 301.

(i) Close the FWD cargo compartment door 825, refer to AMM Task

52-30-00-860-002.

(j) Close the main landing gear doors, refer to AMM Task 32-12-00-410-001.

(k) Restore the systems and the aircraft to normal operating condition.

(l) Remove the access platform(s).

**CONF 002

(1) Subtask 571175-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-001

Task 21-21-41-400-001

Task 25-54-12-400-001

Task 25-80-00-400-001

28-25-00, Page Block 301

Task 32-12-00-410-001

Task 38-11-41-400-001

Task 52-30-00-860-002

Task 57-17-11-400-801

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Install the access cover 147AZ and 148AZ, refer to AMM Task 57-17-11-400-801.

(c) Install the Air-Conditioning Distribution Ducts removed for access to the working

area, AMM Task 21-20-00-410-001.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 48

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(d) If removed, install the recirculation filters LH and RH sides , refer to AMM Task

21-21-41-400-001.

(e) If removed, install the potable water tank 3000MM, refer to AMM Task

38-11-41-400-001.

(f) Install the removed insulation blankets around working areas, refer to AMM Task

25-80-00-400-001.

1 Install the heat and sound insulation in the area between Frame 35 and Frame

36 LH and RH sides removed for access

2 If removed, install electrical bundle clamps removed for access.

(g) Install the removed Forward Cargo-Compartment Partition 131PW, 132PW and

131NW at Frame 34, refer to AMM Task 25-54-12-400-001.

(h) Refuel the center tank, refer to AMM 28-25-00, Page Block 301.

(i) Close the FWD cargo compartment door 825, refer to AMM Task

52-30-00-860-002.

(j) Close the main landing gear doors, refer to AMM Task 32-12-00-410-001.

(k) Restore the systems and the aircraft to normal operating condition.

(l) Remove the access platform(s).

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 49

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DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

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Task 571175-832-802-001 - Special Detailed Inspection of the Radius and Holes of the Rib

Flanges and Vertical Stiffener at FR36 for ADDITIONAL WORK

**CONF ALL

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

WARNING: MAKE SURE THAT THE FORWARD CARGO DOOR IS OPEN BEFORE YOU

REMOVE A PARTITION PANEL IN THE FORWARD CARGO COMPARTMENT.

AIR FROM THE FUEL TANK INERTING SYSTEM CAN COLLECT IN THE

AREA BEHIND THE PANEL. AIR FROM THIS SYSTEM HAS A LOW OXYGEN

CONTENT AND CAN CAUSE INJURY OR DEATH.

WARNING: MAKE SURE THAT YOU DO THE REFUEL PANEL TEST BEFORE OR DURING

THE REFUEL PROCEDURE. DEFECTIVE HIGH-LEVEL SENSORS CAN CAUSE

FUEL TO SPILL OVERBOARD. MAKE SURE THAT YOU COMPLETE THE

REFUEL PANEL TEST BEFORE THE FUEL TANK IS 70 PERCENT FULL.

WARNING: YOU MUST WEAR SAFETY BREATHING EQUIPMENT WHEN YOU DO WORK

IN A FUEL TANK. THE TANKS CAN CONTAIN AIR FROM THE TANK INERTING

SYSTEM. AIR FROM THIS SYSTEM HAS A LOW-OXYGEN CONTENT AND CAN

CAUSE INJURY AND DEATH.

WARNING: BEFORE YOU DO WORK IN OR NEAR A FUEL TANK, MAKE SURE THAT YOU

OBEY ALL THE SAFETY PROCEDURES. THIS WILL PREVENT INJURY TO

PERSONS AND/OR DAMAGE TO THE AIRCRAFT.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS:

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IF THERE IS CONTAMINATION REFER TO ESPM 20-55-00.

NOTE: The accomplishment instructions of this Service Bulletin refer to procedures

included in other AIRBUS documents. When the words "refer to" are used and the

operator has an accepted alternative procedure, the accepted alternative procedure

can be used. When the words "in accordance with" are included in the instruction,

the procedure in the AIRBUS document must be used.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 51

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Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

NOTE: The purpose of flow charts is to supplement the information given in the Procedure

and Compliance paragraphs and not to serve as the primary source for tasks or

compliance times given in this Service Bulletin.

NOTE: This Service Bulletin is mandated or expected to be mandated by an Airworthiness

Directive (AD). The paragraphs 3.C. and 3.D. in these accomplishment instructions

are Required for Compliance (RC) and must be done to comply with the AD. Other

paragraphs are recommended and may be deviated from, done as part of other

actions or done with accepted methods different from those given in the Service

Bulletin, as long as the RC paragraphs can be done and the aircraft can be put

back into a serviceable condition.

Task Associated Data

**CONF 001

Zone

130 140

Access

Door 131NW 131PW 132PW

Panel 131NW 131PW 132PW 147AZ 148AZ

Manpower

TOTAL MANHOURS 45.00

ELAPSED TIME (HOURS) 31.00

**CONF 002

Zone

130 140

Access

Panel 131NW 131PW 132PW 147AZ 148AZ

Manpower

TOTAL MANHOURS 45.00

ELAPSED TIME (HOURS) 31.00

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 52

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**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 571175-910-003-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-31-53, Page Block 001

06-41-52, Page Block 001

06-41-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-42-00

51-43-00

51-44-00

51-75-12

51-76-11

(a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to

the Consumable Material List (CML).

(b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(c) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(d) For the identification of access panels, refer to AMM 06-41-52, Page Block 001 and

AMM 06-41-53, Page Block 001.

(e) Remove and install fasteners in accordance with SRM 51-42-00.

(f) Apply sealant in accordance with SRM 51-24-00.

(g) Renew the protective finish in accordance with

(h) If alternative and substitute fasteners have to be used, you must make sure that the

associated nut/collar are compatible in accordance with SRM 51-40-00 "Mating

Part" column.

(i) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(j) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 53

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(k) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00.

(l) Do the repair of fuel tank sealing in accordance with SRM 51-76-11.

(2) Subtask 571175-839-003-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in the

Service Bulletin.

**CONF 002

(1) Subtask 571175-910-003-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-31-53, Page Block 001

06-41-52, Page Block 001

06-41-53, Page Block 001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-24-00

51-40-00

51-42-00

51-43-00

51-44-00

51-75-12

51-76-11

(a) For the specification of materials (Mat. No.) given in this Service Bulletin, refer to

the Consumable Material List (CML).

(b) For the Frame (FR) identification, refer to AMM 06-31-53, Page Block 001.

(c) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(d) For the identification of access panels, refer to AMM 06-41-52, Page Block 001 and

AMM 06-41-53, Page Block 001.

(e) Remove and install fasteners in accordance with SRM 51-42-00.

(f) Apply sealant in accordance with SRM 51-24-00.

(g) Renew the protective finish in accordance with

(h) If alternative and substitute fasteners have to be used, you must make sure that the

associated nut/collar are compatible in accordance with SRM 51-40-00 "Mating

Part" column.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 54

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(i) If the length of any fastener specified in this Service Bulletin does not meet

installation standards given in SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards given in SRM Chapter 51 may be used. In addition, washers may be

installed for fastener grip length in accordance with SRM Chapter 51.

(j) Obtain fastener hole diameters and drill data in accordance with SRM 51-44-00.

(k) Obtain alternative and substitute fastener data in accordance with SRM 51-43-00.

(l) Do the repair of fuel tank sealing in accordance with SRM 51-76-11.

(2) Subtask 571175-839-003-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in the

Service Bulletin.

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 571175-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002

Task 21-20-00-010-001

Task 25-54-12-000-001

Task 32-12-00-010-001

Task 52-30-00-860-001

Task 57-17-11-000-001

NOTE: The items given in this note shall be considered as the basic Aircraft

configuration before you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety

locks and the wheel chocks are in position on the landing gear)

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 55

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- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position

(a) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-869-002.

(b) Put an access platform in position at door 825.

(c) Open the FWD cargo compartment door 825, refer to AMM Task

52-30-00-860-001.

(d) Open the main landing gear doors, refer to AMM Task 32-12-00-010-001.

(e) Put an access platform in position at zones 147 and 148.

(f) Do the preparation procedure as specified in the Removal of the Access Covers

147AZ and 148AZ, refer to AMM Task 57-17-11-000-001.

(g) Do the preparation procedure as specified in the Removal of the Air-Conditioning

Distribution Ducts, refer to AMM Task 21-20-00-010-001.

(h) Do the preparation procedure as specified in the Removal of the Forward CargoCompartment Partition panels at Frame 34, refer to AMM Task 25-54-12-000-001.

(2) Subtask 571175-010-003-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-001

Task 21-21-41-000-001

Task 25-54-12-000-001

Task 25-80-00-000-001

Task 28-25-00-650-001

Task 28-25-00-869-001

Task 38-11-41-000-001

Task 57-17-11-000-001

(a) Defuel the center tank, refer to AMM Task 28-25-00-650-001 or move the fuel into

a different tank, refer to AMM Task 28-25-00-869-001.

(b) Open access covers 147AZ and 148AZ, refer to AMM Task 57-17-11-000-001.

(c) Remove the Forward Cargo-Compartment Partition panels 131PW, 132PW and

131NW at Frame 34, refer to AMM Task 25-54-12-000-001.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 56

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(d) If necessary remove the recirculation filters LH and RH sides, refer to AMM Task

21-21-41-000-001.

(e) If necessary, remove the Air-Conditioning Distribution Ducts to get access to the

working area, refer to AMM Task 21-20-00-010-001.

(f) If necessary remove the potable water tank 3000MM, refer to AMM Task

38-11-41-000-001.

(g) Remove insulation blankets around working areas between Frame 35 and Frame

36 LH and RH sides for access, refer to AMM Task 25-80-00-000-001.

(h) If necessary, remove electrical bundle clamps and push the bundles aside without

disconnection in order to be able to get them out of the working area.

**CONF 002

(1) Subtask 571175-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-869-002

Task 21-20-00-010-001

Task 25-54-12-000-001

Task 32-12-00-010-001

Task 52-30-00-860-001

Task 57-17-11-000-001

NOTE: The items given in this note shall be considered as the basic Aircraft

configuration before you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety

locks and the wheel chocks are in position on the landing gear)

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 57

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(a) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-869-002.

(b) Put an access platform in position at door 825.

(c) Open the FWD cargo compartment door 825, refer to AMM Task

52-30-00-860-001.

(d) Open the main landing gear doors, refer to AMM Task 32-12-00-010-001.

(e) Put an access platform in position at zones 147 and 148.

(f) Do the preparation procedure as specified in the Removal of the Access Covers

147AZ and 148AZ, refer to AMM Task 57-17-11-000-001.

(g) Do the preparation procedure as specified in the Removal of the Air-Conditioning

Distribution Ducts, refer to AMM Task 21-20-00-010-001.

(h) Do the preparation procedure as specified in the Removal of the Forward CargoCompartment Partition panels at Frame 34, refer to AMM Task 25-54-12-000-001.

(2) Subtask 571175-010-003-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-20-00-010-001

Task 21-21-41-000-001

Task 25-54-12-000-001

Task 25-80-00-000-001

Task 28-25-00-650-001

Task 28-25-00-869-001

Task 38-11-41-000-001

Task 57-17-11-000-001

(a) Defuel the center tank, refer to AMM Task 28-25-00-650-001 or move the fuel into

a different tank, refer to AMM Task 28-25-00-869-001.

(b) Open access covers 147AZ and 148AZ, refer to AMM Task 57-17-11-000-001.

(c) Remove the Forward Cargo-Compartment Partition panels 131PW, 132PW and

131NW at Frame 34, refer to AMM Task 25-54-12-000-001.

(d) If necessary remove the recirculation filters LH and RH sides, refer to AMM Task

21-21-41-000-001.

(e) If necessary, remove the Air-Conditioning Distribution Ducts to get access to the

working area, refer to AMM Task 21-20-00-010-001.

(f) If necessary remove the potable water tank 3000MM, refer to AMM Task

38-11-41-000-001.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 58

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(g) Remove insulation blankets around working areas between Frame 35 and Frame

36 LH and RH sides for access, refer to AMM Task 25-80-00-000-001.

(h) If necessary, remove electrical bundle clamps and push the bundles aside without

disconnection in order to be able to get them out of the working area.

**CONF ALL

C. PROCEDURE

NOTE: This Additional Work is necessary in case of the fasteners and the shims

have not been removed to perform the rototest inspection of the holes and

inspection of the radius of the rib flange during accomplishment of Service

Bulletin No. A320-57-1175 at original issue.

**CONF 001

(1) Subtask 571175-000-004-001 - Remove the Fasteners and the Shims

Work Zones and Access Panels

Zone Access/Work location

130 Access Door 131PW, Door 132PW, Door 131NW

140 Access Panel 147AZ, Panel 148AZ

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9

Kit tool 571175T01R00

ITEM PART N ̊ KEYWORD QTY SEE

NOTES

98D57103003000 TOOL 1

References

Structural Repair Manual (SRM) 51-42-00

51-44-00

Fig. A-FBGAA

Removal/Installation of the Shims for

ADDITIONAL WORK

Sheet 01

Sheet 02

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 59

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References

Fig. A-FBDAA

Removal/Installation of the Rods

Sheet 01

Refer to Fig. A-FBDAA

Refer to Fig. A-FBGAA

In accordance with SRM 51-42-00, SRM 51-44-00

(a) Remove the sealant around the nuts:

1 If necessary, use a non-metallic spatula to remove the sealant and clean the

areas with solvent:

Non Aqueous

Cleaner-General

08BAA9 As required

(b) Remove the nuts:

Refer to Fig. A-FBGAA Sheet 01 and Fig. A-FBGAA Sheet 02

24 Nut Item (4) Discard

(c) Remove the bottom attachment bolt of the rod:

Refer to Fig. A-FBDAA Sheet 01

NOTE: The quantities are given as a maximum for all ribs, it is not allowed

to have 2 rods removed at the same time.

6 Bolt Item (6) Retain

6 Washer Item (7) Retain

6 Nut Item (8) Retain

6 Cotter Pin Item (9) Discard

(d) Push the rod out of the working area:

6 Rod Item (10) Retain

(e) From inside the tank push back the fasteners until they are flush.

NOTE: Do not remove the fasteners by pushing them through the stack up,

there is a risk of damaging the hole and contaminating it with steel

particles.

(f) Install temporarily the rod in initial position before to do the next rod:

Refer to Fig. A-FBDAA Sheet 01

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

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6 Rod Item (10) Retained at

removal

6 Bolt Item (6) Retained at

removal

6 Washer Item (7) Retained at

removal

6 Nut Item (8) Retained at

removal

(g) When all bolts are pushed back, use the special extraction tool, from the forward

cargo area, to remove these fasteners:

98D57103003000 Extractor 1

(h) From the tank, remove the shims with non-metallic spatula and identify their

position:

Refer to Fig. A-FBGAA Sheet 02

12 Shim Item (11) Retain

attached with:

24 Bolt Item (3) Discard

(2) Subtask 571175-832-003-001 - Do a Special Detailed Inspection of the Radius and

Holes of the Rib Flanges and Vertical Stiffener at FR36

Work Zones and Access Panels

Zone Access/Work location

130 Access Panel 131PW, Panel 132PW, Panel 131NW

140 Access Panel 147AZ, Panel 148AZ

Manpower Resources

Manhours 13.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 61

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References

Non Destructive Test Manual (NTM) 51-10-01

51-10-08

Structural Repair Manual (SRM) 51-42-00

51-44-00

Fig. A-FBAAA

Inspection of the Radius and Holes of

the Rib Flanges and Vertical Stiffener at

FR36

Sheet 01

Sheet 02

Sheet 03

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Fig. A-FFBAA

Flow Chart for ADDITIONAL WORK

Sheet 01

(a) At threshold given in the table 2 of the PLANNING INFORMATION Paragraph

E.(2):

Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and

Vertical Stiffener at FR36.

Refer to Fig. A-FFBAA

Refer to Fig. A-FBAAA

1 Remove the fasteners from the holes to be inspected as described in

SUBTASK 571175-000-004 001 Remove the Fasteners and the Shims .

2 Do a High Frequency Eddy Current (HFEC) inspection of the radius of the rib

flanges and vertical stiffener and a rototest Inspection of the holes at FR36.

Refer to Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 02

a If necessary, use a non-metallic spatula to remove the sealant and clean

the areas with solvent:

Non Aqueous

Cleaner-General

08BAA9 As required

b Deburr all the holes before inspection.

c Do a High Frequency Eddy Current (HFEC) inspection of the radius of

the rib flanges and vertical stiffener and a rototest inspection of the holes

as specified in NTM 51-10-08 and NTM 51-10-01.

NOTE: For additional information of procedure NTM 51-10-01

refer to Appendix 01 - Non-Destructive Test

Requirements.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

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<1> If no crack is found:

<a> Oversize the holes of the rib flanges and the shims, refer

to SUBTASK 571175-831-007 001 Oversize the Holes of

the Shims, on Bench and SUBTASK 571175-831-008 001

Oversize the Holes of the Rib Flanges, on Aircraft .

and

Repeat the inspection of the radius and holes in the rib flanges

on front spar side at the interval given in the table 2 of the

PLANNING INFORMATION Paragraph E.(2), refer to TASK

571175-832-801 001 Special Detailed Inspection of the Radius

and Holes of the Rib Flanges and Vertical Stiffener at FR36 .

NOTE: For the repetitive inspections it is not necessary

to oversize the holes as the holes are in

transition fit.

<2> If crack is found:

<a> Contact Airbus before next flight and follow their instructions.

3 For the inspection report, refer to Fig. A-FRAAA.

(3) Subtask 571175-831-007-001 - Oversize the Holes of the Shims, on Bench

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

References

Structural Repair Manual (SRM) 51-44-00

Fig. A-FBJAA

Oversizing of the Holes of the Shims for

ADDITIONAL WORK, on Bench

Sheet 01

Refer to Fig. A-FBJAA

In accordance with SRM 51-44-00

(a) Oversize the holes of the shims to the diameter given in Fig. A-FBJAA Sheet 01.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 63

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(b) Deburr and clean the holes with:

Non Aqueous

Cleaner-General

08BAA9 As required

(4) Subtask 571175-831-008-001 - Oversize the Holes of the Rib Flanges, on Aircraft

Work Zones and Access Panels

Zone Access/Work location

140 Access Panel 147AZ, Panel 148AZ

Work location Frame 42

130 Access Panel 131PW, Panel 132PW, Panel 131NW

Work location Frame 36

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

References

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

Fig. A-FBHAA

Oversizing of the Holes of the Rib

Flanges for ADDITIONAL WORK, on

Aircraft

Sheet 01

Sheet 02

Refer to Fig. A-FBHAA

In accordance with SRM 51-24-00, SRM 51-42-00, SRM 51-43-00, SRM 51-44-00

NOTE: This procedure must be applied to one rib at a time.

(a) Disengage the rod.

(b) Oversize the holes of the rib flanges to the diameter given in Fig. A-FBHAA Sheet

02.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

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(c) Deburr and clean the holes with:

Non Aqueous

Cleaner-General

08BAA9 As required

(5) Subtask 571175-400-004-001 - Install the Shims with the New Fasteners

Work Zones and Access Panels

Zone Access/Work location

140 Access Panel 147AZ, Panel 148AZ

Work location Frame 42

130 Access Panel 131PW, Panel 132PW, Panel 131NW

Work location Frame 36

Manpower Resources

Manhours 10.00

Minimum number of person 2

Subtask elapsed time 5.00

Skills AIRFRAME

Material necessary to do the job

Kit 571175A01R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

3 EN6115V5X15 24 BOLT

4 ASNA2536-5 24 NUT

9 MS24665-153 6 PIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Epoxy Primer 04DAB2 As required

Anti-Vapor Paint 04PAF8 As required

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

Polysulfide Sealant-Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant-Fuel

Tank Fillet

06ABB1 As required

References

Structural Repair Manual (SRM) 51-23-12

51-24-00

51-42-00

51-43-00

51-75-12

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 65

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References

Fig. A-FBGAA

Removal/Installation of the Shims for

ADDITIONAL WORK

Sheet 01

Sheet 02

Fig. A-FBDAA

Removal/Installation of the Rods

Sheet 01

Refer to Fig. A-FBDAA

Refer to Fig. A-FBGAA

In accordance with SRM 51-24-00, SRM 51-42-00, SRM 51-43-00, SRM 51-75-12

(a) Install the shims:

Refer to Fig. A-FBGAA Sheet 02

12 Shim Item (11) Retained at

removal

with:

24 Bolt EN6115V5X15 Item 3

24 Nut ASNA2536-5 Item 4

NOTE: Apply sealant on all contact surface between the shims Item (11)

and front spar:

Polysulfide SealantFuel Tank Fillet06ABB1 As required

NOTE: Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(b) After installation:

1 Over coat the fastener tails and nuts in the tank and perform sealing of the

shims and inspection area with:

Polysulfide SealantFuel Tank

Brushable

06ABA1 As required

(c) In the cargo area:

1 Apply epoxy primer and anti-vapor paint:

Epoxy Primer 04DAB2 As required

and

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 66

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Anti-Vapor Paint 04PAF8 As required

2 Renew the special protection around the fastener heads in accordance with

SRM 51-23-12.

(d) Install the rod in initial position and install the attachment fastener.

Refer to Fig. A-FBDAA Sheet 01

1 Install:

6 Rod Item (10) Retained at

removal

Attached with:

6 Bolt Item (6) Retained at

removal

6 Washer Item (7) Retained at

removal

6 Nut Item (8) Retained at

removal

6 Cotter Pin MS24665-153 Item 9

NOTE: The quantities are given as a maximum for all ribs, it is not

allowed to have 2 rods removed at the same time.

2 Perform over coating of nuts and bolts head with:

Polysulfide SealantFuel Tank

Brushable

06ABA1 As required

**CONF 002

(1) Subtask 571175-000-004-002 - Remove the Fasteners and the Shims

Work Zones and Access Panels

Zone Access/Work location

130 Access Panel 131PW, Panel 132PW, Panel 131NW

140 Access Panel 147AZ, Panel 148AZ

Manpower Resources

Manhours 4.00

Minimum number of person 2

Subtask elapsed time 2.00

Skills NON SPECIFIC

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 67

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Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9

Kit tool 571175T01R00

ITEM PART N ̊ KEYWORD QTY SEE

NOTES

98D57103003000 TOOL 1

References

Structural Repair Manual (SRM) 51-42-00

51-44-00

Fig. A-FBGAB

Removal/Installation of the Shims for

ADDITIONAL WORK

Sheet 01

Sheet 02

Fig. A-FBDAA

Removal/Installation of the Rods

Sheet 01

Refer to Fig. A-FBDAA

Refer to Fig. A-FBGAB

In accordance with SRM 51-42-00, SRM 51-44-00

(a) Remove the sealant around the nuts:

1 If necessary, use a non-metallic spatula to remove the sealant and clean the

areas with solvent:

Non Aqueous

Cleaner-General

08BAA9 As required

(b) Remove the nuts:

Refer to Fig. A-FBGAB Sheet 01 and Fig. A-FBGAB Sheet 02

24 Nut Item (4) Discard

(c) Remove the bottom attachment bolt of the rod:

Refer to Fig. A-FBDAA Sheet 01

NOTE: The quantities are given as a maximum for all ribs, it is not allowed

to have 2 rods removed at the same time.

6 Bolt Item (6) Retain

6 Washer Item (7) Retain

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 68

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6 Nut Item (8) Retain

6 Cotter Pin Item (9) Discard

(d) Push the rod out of the working area:

6 Rod Item (10) Retain

(e) From inside the tank push back the fasteners until they are flush.

NOTE: Do not remove the fasteners by pushing them through the stack up,

there is a risk of damaging the hole and contaminating it with steel

particles.

(f) Install temporarily the rod in initial position before to do the next rod:

Refer to Fig. A-FBDAA Sheet 01

6 Rod Item (10) Retained at

removal

6 Bolt Item (6) Retained at

removal

6 Washer Item (7) Retained at

removal

6 Nut Item (8) Retained at

removal

(g) When all bolts are pushed back, use the special extraction tool, from the forward

cargo area, to remove these fasteners:

98D57103003000 Extractor 1

(h) From the tank, remove shims with non-metallic spatula and identify their position:

Refer to Fig. A-FBGAB Sheet 02

12 Shim Item (11) Retain

attached with:

24 Bolt Item (5) Discard

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 69

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(2) Subtask 571175-832-003-002 - Do a Special Detailed Inspection of the Radius and

Holes of the Rib Flanges and Vertical Stiffener at FR36

Manpower Resources

Manhours 13.00

Minimum number of person 2

Subtask elapsed time 8.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9

References

Non Destructive Test Manual (NTM) 51-10-01

51-10-08

Structural Repair Manual (SRM) 51-42-00

51-44-00

Fig. A-FBAAA

Inspection of the Radius and Holes of

the Rib Flanges and Vertical Stiffener at

FR36

Sheet 01

Sheet 02

Sheet 03

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Fig. A-FFBAA

Flow Chart for ADDITIONAL WORK

Sheet 01

(a) At threshold given in the table 2 of the PLANNING INFORMATION Paragraph

E.(2):

Do a Special Detailed Inspection of the Radius and Holes of the Rib Flanges and

Vertical Stiffener at FR36.

Refer to Fig. A-FFBAA

Refer to Fig. A-FBAAA

NOTE: The following part of the SUBTASK 571175-832-003 002 Do a

Special Detailed Inspection of the Radius and Holes of the Rib

Flanges and Vertical Stiffener at FR36 must be applied to one rib at

a time. It is not allowed to have 2 rods removed at the same time.

1 Remove the fasteners from the holes to be inspected as described in

SUBTASK 571175-000-004 002 Remove the Fasteners and the Shims .

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 70

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2 Do a High Frequency Eddy Current (HFEC) inspection of the radius of the rib

flanges and vertical stiffener and a rototest Inspection of the holes at FR36.

Refer to Fig. A-FBAAA Sheet 01 and Fig. A-FBAAA Sheet 02

a If necessary, use a non-metallic spatula to remove the sealant and clean

the areas with solvent:

Non Aqueous

Cleaner-General

08BAA9 As required

b Deburr all the holes before inspection.

c Do a High Frequency Eddy Current (HFEC) inspection of the radius of

the rib flanges and vertical stiffener and a rototest inspection of the holes

as specified in NTM 51-10-08 and NTM 51-10-01.

NOTE: For additional information of procedure NTM 51-10-01

refer to Appendix 01 - Non-Destructive Test

Requirements.

<1> If no crack is found:

<a> Oversize the holes of the rib flanges and the shims, refer

to SUBTASK 571175-831-007 002 Oversize the Holes of

the Shims, on Bench and SUBTASK 571175-831-008 002

Oversize the Holes of the Rib Flanges, on Aircraft .

and

Repeat the inspection of the radius and holes in the rib flanges

on front spar side at the interval given in the table 2 of the

PLANNING INFORMATION Paragraph E.(2), refer to TASK

571175-832-801 001 Special Detailed Inspection of the Radius

and Holes of the Rib Flanges and Vertical Stiffener at FR36 .

NOTE: For the repetitive inspections it is not necessary

to oversize the holes as the holes are in

transition fit.

<2> If crack is found:

<a> Contact Airbus before next flight and follow their instructions.

3 For the inspection report, refer to Fig. A-FRAAA.

(3) Subtask 571175-831-007-002 - Oversize the Holes of the Shims, on Bench

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 71

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Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

References

Structural Repair Manual (SRM) 51-44-00

Fig. A-FBJAB

Oversizing of the Holes of the Shims for

ADDITIONAL WORK, on Bench

Sheet 01

Refer to Fig. A-FBJAB

In accordance with SRM 51-44-00

(a) Oversize the holes of the shims to the diameter given in Fig. A-FBJAB Sheet 01.

(b) Deburr and clean the holes with:

Non Aqueous

Cleaner-General

08BAA9 As required

(4) Subtask 571175-831-008-002 - Oversize the Holes of the Rib Flanges, on Aircraft

Work Zones and Access Panels

Zone Access/Work location

140 Access Panel 147AZ, Panel 148AZ

Work location Frame 42

130 Access Panel 131PW, Panel 132PW, Panel 131NW

Work location Frame 36

Manpower Resources

Manhours 2.00

Minimum number of person 2

Subtask elapsed time 1.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 72

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References

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

Fig. A-FBHAB

Oversizing of the Holes of the Rib

Flanges for ADDITIONAL WORK, on

Aircraft

Sheet 01

Sheet 02

Refer to Fig. A-FBHAB

In accordance with SRM 51-24-00, SRM 51-42-00, SRM 51-43-00, SRM 51-44-00

NOTE: This procedure must be applied to one rib at a time.

(a) Disengage the rod.

(b) Oversize the holes of the rib flanges to the diameter given in Fig. A-FBHAB Sheet

02.

(c) Deburr and clean the holes with:

Non Aqueous

Cleaner-General

08BAA9 As required

(5) Subtask 571175-400-004-002 - Install the Shims with the New Fasteners

Work Zones and Access Panels

Zone Access/Work location

140 Access Panel 147AZ

Work location Frame 42

130 Access Panel 131PW, Panel 132PW, Panel 131NW

Work location Frame 36

Manpower Resources

Manhours 10.00

Minimum number of person 2

Subtask elapsed time 5.00

Skills AIRFRAME

Material necessary to do the job

Kit 571175A02R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

4 ASNA2536-5 24 NUT

5 EN6115V5Y15 24 BOLT

9 MS24665-153 6 PIN

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 73

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Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Epoxy Primer 04DAB2 As required

Anti-Vapor Paint 04PAF8 As required

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

Polysulfide Sealant-Fuel

Tank Brushable

06ABA1 As required

Polysulfide Sealant-Fuel

Tank Fillet

06ABB1 As required

References

Structural Repair Manual (SRM) 51-23-12

51-24-00

51-42-00

51-43-00

51-75-12

Fig. A-FBGAB

Removal/Installation of the Shims for

ADDITIONAL WORK

Sheet 01

Sheet 02

Fig. A-FBDAA

Removal/Installation of the Rods

Sheet 01

Refer to Fig. A-FBDAA

Refer to Fig. A-FBGAB

In accordance with SRM 51-24-00, SRM 51-42-00, SRM 51-43-00, SRM 51-75-12

(a) Install the shims:

Refer to Fig. A-FBGAB Sheet 02

12 Shim Item (11) Retained at

removal

with:

24 Bolt EN6115V5Y15 Item 5

24 Nut ASNA2536-5 Item 4

NOTE: Apply sealant on all contact surface between the shims Item (11)

and front spar:

Polysulfide SealantFuel Tank Fillet06ABB1 As required

NOTE: Wet install the fasteners with:

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 74

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Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

(b) After installation:

1 Over coat the fastener tails and nuts in the tank and perform sealing of the

shims and inspection area with:

Polysulfide SealantFuel Tank

Brushable

06ABA1 As required

(c) In the cargo area:

1 Apply epoxy primer and anti-vapor paint:

Epoxy Primer 04DAB2 As required

and

Anti-Vapor Paint 04PAF8 As required

2 Renew the special protection around the fastener heads in accordance with

SRM 51-23-12.

(d) Install the rod in initial position and install the attachment fastener.

Refer to Fig. A-FBDAA Sheet 01

1 Install:

6 Rod Item (10) Retained at

removal

Attached with:

6 Bolt Item (6) Retained at

removal

6 Washer Item (7) Retained at

removal

6 Nut Item (8) Retained at

removal

6 Cotter Pin MS24665-153 Item 9

NOTE: The quantities are given as a maximum for all ribs, it is not

allowed to have 2 rods removed at the same time.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 75

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2 Perform over coating of nuts and bolts head with:

Polysulfide SealantFuel Tank

Brushable

06ABA1 As required

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 571175-700-003-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 20-28-00, Page Block 501

Task 21-20-00-410-001

Task 25-54-12-400-001

Task 52-30-00-860-002

Task 57-17-11-400-001

NOTE: This Service Bulletin requires the accomplishment of the following Tests

which are given in subtasks included in the topic Close-up. The

manhours for the tests are included in the referenced Service Bulletin

subtask.

- Remove the Safety clips and tags and close the circuit breakers as specified after

the Installation of the Air-Conditioning Distribution Ducts, refer to AMM Task

21-20-00-410-001.

- Remove the Safety clips and tags and close the circuit breakers as specified after

the Installation of the Access Covers 147AZ and 148AZ, refer to AMM Task

57-17-11-400-001.

- Remove the Safety clips and tags and close the circuit breakers as specified after

Closing the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump,

refer to AMM Task 52-30-00-860-002.

- Remove the Safety clips and tags and close the circuit breakers as specified after

the Installation of Forward Cargo-Compartment Partition panels at Frame 34, refer

to AMM Task 25-54-12-400-001.

- Do the test procedure as specified after the installation of the access covers 147AZ

and 148AZ, refer to AMM Task 57-17-11-400-001.

- Do the test procedure as specified after the installation of the Air-Conditioning

Distribution Ducts, refer to AMM Task 21-20-00-410-001.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 76

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**CONF 002

(1) Subtask 571175-700-003-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 20-28-00, Page Block 501

Task 21-20-00-410-001

Task 25-54-12-400-001

Task 52-30-00-860-002

Task 57-17-11-400-001

NOTE: This Service Bulletin requires the accomplishment of the following Tests

which are given in subtasks included in the topic Close-up. The

manhours for the tests are included in the referenced Service Bulletin

subtask.

- Remove the Safety clips and tags and close the circuit breakers as specified after

the Installation of the Air-Conditioning Distribution Ducts, refer to AMM Task

21-20-00-410-001.

- Remove the Safety clips and tags and close the circuit breakers as specified after

the Installation of the Access Covers 147AZ and 148AZ, refer to AMM Task

57-17-11-400-001.

- Remove the Safety clips and tags and close the circuit breakers as specified after

Closing the FWD or AFT Cargo-Compartment Door with the Yellow Electric Pump,

refer to AMM Task 52-30-00-860-002.

- Remove the Safety clips and tags and close the circuit breakers as specified after

the Installation of Forward Cargo-Compartment Partition panels at Frame 34, refer

to AMM Task 25-54-12-400-001.

- Do the test procedure as specified after the installation of the access covers 147AZ

and 148AZ, refer to AMM Task 57-17-11-400-001.

- Do the test procedure as specified after the installation of the Air-Conditioning

Distribution Ducts, refer to AMM Task 21-20-00-410-001.

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 571175-942-003-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 77

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References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-001

Task 21-21-41-400-001

Task 25-54-12-400-001

Task 25-80-00-400-001

28-25-00, Page Block 301

Task 32-12-00-410-001

Task 38-11-41-400-001

Task 52-30-00-860-002

Task 57-17-11-400-801

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Install the access cover 147AZ and 148AZ, refer to AMM Task 57-17-11-400-801.

(c) Install the Air-Conditioning Distribution Ducts removed for access to the working

area, AMM Task 21-20-00-410-001.

(d) If removed, install the recirculation filters LH and RH sides, refer to AMM Task

21-21-41-400-001.

(e) If removed, install the potable water tank 3000MM, refer to AMM Task

38-11-41-400-001.

(f) Install the removed insulation blankets around working areas, refer to AMM Task

25-80-00-400-001.

1 Install the heat and sound insulation in the area between Frame 35 and Frame

36 LH and RH sides removed for acces.

2 If removed, install electrical bundle clamps removed for access.

(g) Install the removed Forward Cargo-Compartment Partition 131PW, 132PW and

131NW at Frame 34, refer to AMM Task 25-54-12-400-001.

(h) Refuel the center tank, refer to AMM 28-25-00, Page Block 301.

(i) Close the FWD cargo compartment door 825, refer to AMM Task

52-30-00-860-002.

(j) Close the main landing gear doors, refer to AMM Task 32-12-00-410-001.

(k) Restore the systems and the aircraft to normal operating condition.

(l) Remove the access platform(s).

**CONF 002

(1) Subtask 571175-942-003-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 78

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References

Aircraft Maintenance Manual (AMM) Task 21-20-00-410-001

Task 21-21-41-400-001

Task 25-54-12-400-001

Task 25-80-00-400-001

28-25-00, Page Block 301

Task 32-12-00-410-001

Task 38-11-41-400-001

Task 52-30-00-860-002

Task 57-17-11-400-801

(a) Make sure that the work areas are clean and clear of tools and other items of

equipment.

(b) Install the access cover 147AZ and 148AZ, refer to AMM Task 57-17-11-400-801.

(c) Install the Air-Conditioning Distribution Ducts removed for access to the working

area, AMM Task 21-20-00-410-001.

(d) If removed, install the recirculation filters LH and RH sides, refer to AMM Task

21-21-41-400-001.

(e) If removed, install the potable water tank 3000MM, refer to AMM Task

38-11-41-400-001.

(f) Install the removed insulation blankets around working areas, refer to AMM Task

25-80-00-400-001.

1 Install the heat and sound insulation in the area between Frame 35 and Frame

36 LH and RH sides removed for acces.

2 If removed, install electrical bundle clamps removed for access.

(g) Install the removed Forward Cargo-Compartment Partition 131PW, 132PW and

131NW at Frame 34, refer to AMM Task 25-54-12-400-001.

(h) Refuel the center tank, refer to AMM 28-25-00, Page Block 301.

(i) Close the FWD cargo compartment door 825, refer to AMM Task

52-30-00-860-002.

(j) Close the main landing gear doors, refer to AMM Task 32-12-00-410-001.

(k) Restore the systems and the aircraft to normal operating condition.

(l) Remove the access platform(s).

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 79

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This Page Intentionally Left Blank

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 80

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**CONF ALL

FR36

FR42

A

B

C

C

C

C

C

C

Y−1292

Y−765

Y−254

Y 254

Y 765

Y 1292

D

D

D

D

D

D

E

E

E

E

E

E

B

A

N_SB_571175_5_BAAA_01_03

Figure A-FBAAA - Sheet 01

Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 81

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**CONF ALL

HOLES TO BE INSPECTED

VIEW LOOKING FORWARD

LH SHOWN

INSPECTION AREA RH SYMMETRICAL

NOTE:

C

D

N_SB_571175_5_BAAA_02_02

Figure A-FBAAA - Sheet 02

Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 82

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**CONF ALL

E

VIEW LOOKING BACK

INSPECTION AREA

NOTE:

N_SB_571175_5_BAAA_03_00

Figure A-FBAAA - Sheet 03

Inspection of the Radius and Holes of the Rib Flanges and Vertical Stiffener at FR36

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 83

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**CONF 001

A

FR36

FR42

A

B

B

C

C

C

C

C

C

Y−1292

Y−765

Y−254

Y 254

Y 765

Y 1292

N_SB_571175_5_BBAA_01_02

Figure A-FBBAA - Sheet 01

Removal/Installation of the Shims

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 84

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**CONF 001

HOLE

SYMBOLE ITEM PN DESCRIPTION

EN6115V5X15 BOLT

ASNA2536−5 NUT

NOTE:

01 WET INSTALL WITH MAT. No 06AAA1

03

03 AFTER INSTALLATION, APPLY:

− ON THE FASTENER HEAD MAT. No 04DAB2 AND MAT. No 04PAF8

− ON THE NUT MAT. No 06ABA1

01

F

HEAD ON HIDDEN SIDE F

REMARKS

C

VIEW LOOKING FORWARD

02 (11) 02 (11)

(1)

(2)

3

4

02 SEALANT MUST BE APPLIED ON ALL CONTACT SURFACE BETWEEN SHIM

AND FRONT SPAR WITH MAT. No 06ABB1

FIRST OVERSIZE DIAMETER IN TRANSITION FIT

N_SB_571175_5_BBAA_02_05

Figure A-FBBAA - Sheet 02

Removal/Installation of the Shims

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 85

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**CONF 002

A

FR36

FR42

A

B

B

C

C

C

C

C

C

Y−1292

Y−765

Y−254

Y 254

Y 765

Y 1292

N_SB_571175_5_BBAB_01_01

Figure A-FBBAB - Sheet 01

Removal/Installation of the Shims

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 86

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**CONF 002

HOLE

SYMBOLE ITEM PN DESCRIPTION

EN6115V5Y15 BOLT

ASNA2536−5 NUT

NOTE:

01 WET INSTALL WITH MAT. No 06AAA1

03

03 AFTER INSTALLATION, APPLY:

− ON THE FASTENER HEAD MAT. No 04DAB2 AND MAT. No 04PAF8

− ON THE NUT MAT. No 06ABA1

01

F

HEAD ON HIDDEN SIDE F

REMARKS

C

VIEW LOOKING FORWARD

02 (11) 02 (11)

(1)

(2)

5

4

02 SEALANT MUST BE APPLIED ON ALL CONTACT SURFACE BETWEEN SHIM

AND FRONT SPAR WITH MAT. No 06ABB1

SECOND OVERSIZE DIAMETER IN

TRANSITION FIT

N_SB_571175_5_BBAB_02_00

Figure A-FBBAB - Sheet 02

Removal/Installation of the Shims

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 87

5

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**CONF ALL

(10)

TYPICAL VIEW

(6)

(7)

(8)

9

(9)

A A

FWD

A

A

FR36

FR42

B

A

B

01

NOTE:

01 AFTER INSTALATION OF THE FASTENER APPLY:

− ON THE FASTENER HEAD MAT. No 04EAC2

− ON THE NUT MAT. No 06ABA1

0/+ 0.2 mm

(0/+0.0079 in)

A

N_SB_571175_5_BDAA_01_01

Figure A-FBDAA - Sheet 01

Removal/Installation of the Rods

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 88

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**CONF 001

FR36

FR42

A

B

C

C

C

C

C

C

Y−1292

Y−765

Y−254

Y 254

Y 765

Y 1292

A

B

N_SB_571175_5_BEAA_01_01

Figure A-FBEAA - Sheet 01

Oversizing of the Holes of the Rib Flanges, on Aircraft

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 89

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**CONF 001

C

VIEW LOOKING FORWARD

HOLE HOLE DIAMETER

MIN MAX

8.296 mm

(0.327 in)

8.335 mm

(0.328 in)

SYMBOLE

FIRST OVERSIZE DIAMETER IN TRANSITION FIT

REMARKS

N_SB_571175_5_BEAA_02_00

Figure A-FBEAA - Sheet 02

Oversizing of the Holes of the Rib Flanges, on Aircraft

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 90

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**CONF 002

A

FR36

FR42

A

B

B

C

C

C

C

C

C

Y−1292

Y−765

Y−254

Y 254

Y 765

Y 1292

N_SB_571175_5_BEAB_01_01

Figure A-FBEAB - Sheet 01

Oversizing of the Holes of the Rib Flanges, on Aircraft

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 91

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**CONF 002

C

VIEW LOOKING FORWARD

HOLE

SYMBOL

HOLE DIAMETER

MIN MAX

8.692 mm

(0.342 in)

8.732 mm

(0.344 in)

SECOND OVERSIZE DIAMETER IN

TRANSITION FIT

REMARKS

N_SB_571175_5_BEAB_02_00

Figure A-FBEAB - Sheet 02

Oversizing of the Holes of the Rib Flanges, on Aircraft

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 92

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**CONF 001

ON BENCH

HOLE HOLE DIAMETER

MIN MAX

8.321 mm

(0.328 in)

8.345 mm

(0.329 in)

SYMBOLE

(11) (11)

N_SB_571175_5_BFAA_01_00

Figure A-FBFAA - Sheet 01

Oversizing of the Holes of the Shims, on Bench

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 93

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**CONF 002

HOLE

SYMBOL

HOLE DIAMETER

MIN MAX

8.717 mm

(0.343 in)

8.742 mm

(0.344 in)

ON BENCH

(11) (11)

N_SB_571175_5_BFAB_01_00

Figure A-FBFAB - Sheet 01

Oversizing of the Holes of the Shims, on Bench

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 94

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**CONF 001

A

FR36

FR42

A

B

B

C

C

C

C

C

C

Y−1292

Y−765

Y−254

Y 254

Y 765

Y 1292

N_SB_571175_5_BGAA_01_01

Figure A-FBGAA - Sheet 01

Removal/Installation of the Shims for ADDITIONAL WORK

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 95

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**CONF 001

HOLE

SYMBOLE ITEM PN DESCRIPTION

EN6115V5X15 BOLT

ASNA2536−5 NUT

NOTE:

01 WET INSTALL WITH MAT. No 06AAA1

03

03 AFTER INSTALLATION, APPLY:

− ON THE FASTENER HEAD MAT. No 04DAB2 AND MAT. No 04PAF8

− ON THE NUT MAT. No 06ABA1

01

F

HEAD ON HIDDEN SIDE F

REMARKS

C

VIEW LOOKING FORWARD

02 (11) 02 (11)

(3)

(4)

5

4

02 SEALANT MUST BE APPLIED ON ALL CONTACT SURFACE BETWEEN SHIM

AND FRONT SPAR WITH MAT. No 06ABB1

FIRST OVERSIZE DIAMETER IN

TRANSITION FIT

N_SB_571175_5_BGAA_02_01

Figure A-FBGAA - Sheet 02

Removal/Installation of the Shims for ADDITIONAL WORK

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 96

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**CONF 002

A

FR36

FR42

A

B

B

C

C

C

C

C

C

Y−1292

Y−765

Y−254

Y 254

Y 765

Y 1292

N_SB_571175_5_BGAB_01_01

Figure A-FBGAB - Sheet 01

Removal/Installation of the Shims for ADDITIONAL WORK

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 97

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**CONF 002

HOLE

SYMBOLE ITEM PN DESCRIPTION

EN6115V5Y15 BOLT

ASNA2536−5 NUT

NOTE:

01 WET INSTALL WITH MAT. No 06AAA1

03

03 AFTER INSTALLATION, APPLY:

− ON THE FASTENER HEAD MAT. No 04DAB2 AND MAT. No 04PAF8

− ON THE NUT MAT. No 06ABA1

01

F

HEAD ON HIDDEN SIDE F

REMARKS

C

VIEW LOOKING FORWARD

02 (11) 02 (11)

(5)

(4)

6

7

02 SEALANT MUST BE APPLIED ON ALL CONTACT SURFACE BETWEEN SHIM

AND FRONT SPAR WITH MAT. No 06ABB1

SECOND OVERSIZE DIAMETER IN

TRANSITION FIT

N_SB_571175_5_BGAB_02_01

Figure A-FBGAB - Sheet 02

Removal/Installation of the Shims for ADDITIONAL WORK

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 98

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**CONF 001

A

FR36

FR42

A

B

B

C

C

C

C

C

C

Y−1292

Y−765

Y−254

Y 254

Y 765

Y 1292

N_SB_571175_5_BHAA_01_01

Figure A-FBHAA - Sheet 01

Oversizing of the Holes of the Rib Flanges for ADDITIONAL WORK, on Aircraft

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 99

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**CONF 001

C

VIEW LOOKING FORWARD

HOLE

SYMBOL

HOLE DIAMETER

MIN MAX

8.296 mm

(0.327 in)

8.335 mm

(0.328 in)

FIRST OVERSIZE DIAMETER IN

TRANSITION FIT

REMARKS

N_SB_571175_5_BHAA_02_01

Figure A-FBHAA - Sheet 02

Oversizing of the Holes of the Rib Flanges for ADDITIONAL WORK, on Aircraft

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 100

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**CONF 002

A

FR36

FR42

A

B

B

C

C

C

C

C

C

Y−1292

Y−765

Y−254

Y 254

Y 765

Y 1292

N_SB_571175_5_BHAB_01_01

Figure A-FBHAB - Sheet 01

Oversizing of the Holes of the Rib Flanges for ADDITIONAL WORK, on Aircraft

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 101

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**CONF 002

C

VIEW LOOKING FORWARD

HOLE

SYMBOL

HOLE DIAMETER

MIN MAX

8.692 mm

(0.342 in)

8.732 mm

(0.344 in)

SECOND OVERSIZE DIAMETER IN

TRANSITION FIT

REMARKS

N_SB_571175_5_BHAB_02_01

Figure A-FBHAB - Sheet 02

Oversizing of the Holes of the Rib Flanges for ADDITIONAL WORK, on Aircraft

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 102

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**CONF 001

HOLE

SYMBOL

HOLE DIAMETER

MIN MAX

8.321 mm

(0.328 in)

8.345 mm

(0.329 in)

ON BENCH

(11) (11)

N_SB_571175_5_BJAA_01_01

Figure A-FBJAA - Sheet 01

Oversizing of the Holes of the Shims for ADDITIONAL WORK, on Bench

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 103

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**CONF 002

HOLE

SYMBOL

HOLE DIAMETER

MIN MAX

8.717 mm

(0.343 in)

8.742 mm

(0.344 in)

ON BENCH

(11) (11)

N_SB_571175_5_BJAB_01_01

Figure A-FBJAB - Sheet 01

Oversizing of the Holes of the Shims for ADDITIONAL WORK, on Bench

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 104

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**CONF ALL

QUESTION

ACTION

FINDING

AT THE THRESHOLD GIVEN IN THE TABLE 1 OF THE PLANNING

INFORMATION PARAGRAPH E.(2) REFER TO TASK 571175−832−801

YES CRACKS FOUND NO

OVERSIZE AND INSTALL NEW

FASTENERS

DO A SPECIAL DETAILED INSPECTION OF THE RADUIS AND HOLES OF 

THE RIB FLANGES AND VERTICAL STIFFENER AT FR36

BEFORE NEXT FLIGHT

AND FOLLOW

CONTACT AIRBUS

THEIR INSTRUCTIONS

REFER TO SUBTASK 571175−831−005

HOLES OF THE RIB FLANGES AND VERTICAL

REPEAT THE INSPECTION OF THE RADIUS AND

THE TABLE 1 OF THE PLANNING INFORMATION

PARAGRAPH E.(2)

STIFFENER AT FR36 AT THE INTERVAL GIVEN IN

REFER TO TASK 571175−832−801

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

01

01 FOR REPETITIVE INSPECTION IT IS NOT NECESSARY TO OVERSIZE THE HOLES AS THE HOLES ARE

IN TANSITION FIT

AND SUBTASK 571175−831−006

AND SUBTASK 571175−400−003

N_SB_571175_5_FAAA_01_06

Figure A-FFAAA - Sheet 01

Flow Chart

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 105

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**CONF ALL

QUESTION

ACTION

FINDING

AT THE THRESHOLD GIVEN IN THE TABLE 2 OF THE PLANNING

INFORMATION PARAGRAPH E.(2) REFER TO TASK 571175−832−802

YES CRACKS FOUND NO

OVERSIZE AND INSTALL NEW

FASTENERS

DO A SPECIAL DETAILED INSPECTION OF THE RADUIS AND HOLES OF 

THE RIB FLANGES AND VERTICAL STIFFENER AT FR36

BEFORE NEXT FLIGHT

AND FOLLOW

CONTACT AIRBUS

THEIR INSTRUCTIONS

AND HOLES OF THE RIB FLANGES AND VERTICAL

REPEAT THE INSPECTION OF THE RADIUS

THE TABLE 1 OF THE PLANNING INFORMATION

PARAGRAPH E.(2)

STIFFENER AT FR36 AT THE INTERVAL GIVEN IN

REFER TO TASK 571175−832−801

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

01

01 FOR REPETITIVE INSPECTION IT IS NOT NECESSARY TO OVERSIZE THE HOLES AS THE HOLES ARE

IN TANSITION FIT

REFER TO SUBTASK 571175−831−007

AND SUBTASK 571175−831−008

AND SUBTASK 571175−400−004

N_SB_571175_5_FBAA_01_03

Figure A-FFBAA - Sheet 01

Flow Chart for ADDITIONAL WORK

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 106

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**CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−57−1175

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES4

PAX DOORS − FUSELAGE (SA/LA) − WINDOWS −

INSPECTION METHOD :

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

SPECIAL DETAILED E−mail: structure.sbinspectionresult@airbus.com

INSPECTION FAX: +33 (0)5 61 93 36 14

CENTER WING BOX (SA/LA)

LOWER RIB

Y 1292

LOWER RIB

Y 765

LOWER RIB

Y 254

LOWER RIB

Y −254

LOWER RIB

Y −765

LOWER RIB

Y −1292

CRACK FOUND

VIEW LOOKING FORWARD

NOTE:

IN CASE OF CRACK FOUND, GIVE HOLE NUMBER

TYPICAL

NO CRACK

FOUND

H1 H2

H3 H4

N_SB_571175_5_RAAA_01_03

Figure A-FRAAA - Sheet 01

Inspection Report

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 107

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**CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−57−1175

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES4

PAX DOORS − FUSELAGE (SA/LA) − WINDOWS −

INSPECTION METHOD :

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

SPECIAL DETAILED E−mail: structure.sbinspectionresult@airbus.com

INSPECTION FAX: +33 (0)5 61 93 36 14

CENTER WING BOX (SA/LA)

LOWER RIB

Y 1292

LOWER RIB

Y 765

LOWER RIB

Y 254

LOWER RIB

Y −254

LOWER RIB

Y −765

LOWER RIB

Y −1292

CRACK FOUND

NOTE:

TYPICAL

NO CRACK

FOUND

LH SHOWN

RH SYMMETRICAL

INSPECTION AREA

LH RH LH RH LH RH LH RH LH RH LH RH

N_SB_571175_5_RAAA_02_01

Figure A-FRAAA - Sheet 02

Inspection Report

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 108

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**CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−57−1175

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES4

PAX DOORS − FUSELAGE (SA/LA) − WINDOWS −

INSPECTION METHOD :

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

SPECIAL DETAILED E−mail: structure.sbinspectionresult@airbus.com

INSPECTION FAX: +33 (0)5 61 93 36 14

CENTER WING BOX (SA/LA)

INSPECTION AREA

NOTE:

VIEW LOOKING BACK

TYPICAL

CRACK FOUND

NO CRACK 

FOUND

LH

LOWER RIB

Y 1292

TOP BOTTOM

RH

TOP BOTTOM

LH

LOWER RIB

Y 765

TOP BOTTOM

RH

TOP BOTTOM

LH

LOWER RIB

Y 254

TOP BOTTOM

RH

TOP BOTTOM

CRACK FOUND

NO CRACK 

FOUND

LH

LOWER RIB

Y−254

TOP BOTTOM

RH

TOP BOTTOM

LH

LOWER RIB

Y−765

TOP BOTTOM

RH

TOP BOTTOM

LH

LOWER RIB

Y−1292

TOP BOTTOM

RH

TOP BOTTOM

N_SB_571175_5_RAAA_03_00

Figure A-FRAAA - Sheet 03

Inspection Report

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 109

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This Page Intentionally Left Blank

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 110

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Appendix 01 - Non-Destructive Test Requirements

**CONF ALL

For the non-destructive test requirements refer to the following sheet.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 1

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Appendix 01 - Non-Destructive Test Requirements

**CONF ALL

DURING THE ACCOMPLISHMENT OF HFEC ROTO TEST HOLE INSPECTION (NTM 51−10−01), DEFECT 

SIGNALS IDENTIFIED AS COMING FROM THE INTERFACE OF THE RIB FLANGE AND THE ANGLE FITTING 

(SEE FIGURE 1) MAYBE A RESULT OF BURRING. TYPICAL SIGNALS ARE SHOWN IN FIGURES 2 & 3.

CAUTION:

FIGURE 1: STRUCTURAL CONFIGURATION OF INSPECTED HOLES SB 57−1175

THE SIGNAL MAY BE LARGER AND NOISIER WITH THE ADDITIONAL DB’S AS REQUIRED 

NOTE: 

BY NTM 51−10−01 (FIG 2 & 3).

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

FIGURE 3: TYPICAL BURR SIGNAL +6DB 

FIGURE 4: TYPICAL BURR SIGNAL Y/X−T NO DB ADDED 

1. LOCALLY POLISH THE INTERFACE WITH A NON METALLIC 

ABRASIVE TO REDUCE THE AMPLITUDE. 

2. USE NTM 51−10−01 BUT DO NOT ADD THE ADDITIONAL 

TASK: 

DB’S (B. INSTRUMENT ADJUSTMENT (6) (A) 5). 

3. RE−INSPECT. 

4. APPLY ACCEPTANCE CRITERIA (C. INSPECTION (6) (A) & 

(B)) (SEE FIG 4). 

N_SB_571175_5_AAAA_01_00

Figure A-FAAAA - Sheet 01

Non-Destructive Test Requirements

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 2

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Appendix 02 - Elapsed Time Assumption

**CONF ALL

For an explanation of the manhours and elapsed time, refer to the following Gantt Chart.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 1

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Appendix 02 - Elapsed Time Assumption

**CONF ALL

ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A320−57−1175

SB ELAPSED TIME

(HOURS)

GET ACCESS

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

45.00

31.00

STEPS

6.00 6.00

0 5 10 15

MH

ET/S:

PER

MANHOURS

ELAPSED TIME PER STEP

NUMBER OF PERSONS

01

02

THIS CHART IS ONLY A PROPOSAL

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM

01

02

NOTE:

PER

1

:

: IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS

ARE NOT REFLECTED IN THIS GANTT CHART

20 25

REMOVE THE FASTENERS 4.00 2.00 2

DO A SPECIAL DETAILED 13.00 2 8.00

OVERSIZE THE HOLES OF 2.00 1.00 2

OVERSIZE THE HOLES OF THE 2.00 1.00 2

INSTALL THE SHIMS WITH NEW 10.00 2 5.00

TEST 1.00 1.00 1

CLOSED−UP 7.00 7.00 1

INSPECTION

THE SHIMS

RIB FLANGES

FASTENERS

30

AND THE SHIMS

N_SB_571175_5_ABAA_01_01

Figure A-FABAA - Sheet 01

Elapsed Time Assumption

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 2

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REPORTING SHEET

TITLE: WING - CENTER WING - INSPECTION OF THE LOWER RIBS AT FR36

JUNCTION

MODIFICATION No.: None

Please complete the appropriate item (A or B):

A - SB WILL BE embodied YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to

next normal revision or prior to SB embodiment, please indicate required service(s):

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational

documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With

the next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.

- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 1

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data

that you provide us will be used to analyse areas of difficulties and to take corrective action to further

improve the quality of our Service Bulletins.

We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

X Reason X List of Materials Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Oct 24/13 SERVICE BULLETIN No.: A320-57-1175

REVISION No.: 01 - May 28/14 Page: 1

5

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