@A318/A319/A320/A321

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 57

TITLE: WINGS - INSPECTION OF FRONT SPAR VERTICAL STRINGERS

MODIFICATION No.: None

This page transmits Revision No.01 of Service Bulletin No.A320-57-1178

ADDITIONAL WORK

**CONF ALL

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

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

- the HFEC inspection of the vertical stiffener radius has not been done,

- the rototest inspection has not been done.

Additional work consists in:

- The removal of the shims and fasteners in inspected area on which it has not been done,

- Addition of the HFEC Inspection of the vertical stiffener and horizontal Floor Beam Radius,

- Addition of the rototest inspection of the upper fasteners holes.

REASON

Revision No. 01 issued to:

- Remove and install the fasteners for the Inspection of front spar vertical stringers radius

- Add HFEC Inspection of the horizontal floor beam radius

- Add the rototest inspection of the fasteners holes of front spar vertical stringers radius

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

Number (MSN) 0078.

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

current issue of the Service Bulletin.

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

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

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

CHANGES

The main changes of this revision are:

- Removal and installation of the fasteners for the Inspection of front spar vertical stringers radius for

conf 001

- Removal, oversizing and installation of the shims for the Inspection of front spar vertical stringers

radius, only for the configurations 002

- Removal and installation of the shims for the Inspection of front spar vertical stringers radius, only

for the configurations 003

- Modification of job set-up and close-up procedures of the Inspection Task

- Creation of the Additional work Task

- Addition of the HFEC Inspection of the horizontal floor beam radius

- Addition of the rototest inspection of the fasteners holes of front spar vertical stringers radius

- Modification of the NTM reference to perform HFEC Inspection

SUMMARY

REASON/DESCRIPTION/OPERATIONAL

CONSEQUENCES

REASON UPDATED R

GENERAL EVALUATION GENERAL EVALUATION TABLE UPDATED R

MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE

UPDATED

R

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

MATERIAL PRICE INFORMATION TABLE

UPDATED

R

EFFECTIVITY OPERATOR LIST UPDATED R

MANPOWER MANPOWER UPDATED R

MANPOWER UPDATED R

MANPOWER UPDATED R

APPENDICES APPENDICES UPDATED R

Fig. A-FSAAA FIGURE SOLUTION UPDATED R

Fig. A-FSAAA Sheet 01 SHEET UPDATED R

Fig. A-FSAAA Sheet 02 SHEET ADDED N

Fig. A-FSAAB FIGURE SOLUTION UPDATED R

Fig. A-FSAAB Sheet 01 SHEET UPDATED R

Fig. A-FSAAB Sheet 02 SHEET ADDED N

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

Configuration definition

CONF 001 CONFIGURATION DEFINITION UPDATED R

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

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

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REVISION TRANSMITTAL SHEET

CONF 002 CONFIGURATION DEFINITION UPDATED R

CONF 003 CONFIGURATION DEFINITION UPDATED R

Material Effectivity MATERIAL EFFECTIVITY UPDATED

MATERIAL SET QUANTITY UPDATED

CONFIGURATION UPDATED

MATERIAL SET UPDATED

R

MATERIAL EFFECTIVITY ADDED N

MATERIAL EFFECTIVITY ADDED N

REASON

History HISTORY UPDATED R

Objective/Action OBJECTIVE/ACTION UPDATED R

Operational/Maintenance

Consequences

OPERATIONAL/MAINTENANCE CONSEQUENCES

UPDATED

R

COMPLIANCE

Classification CLASSIFICATION UPDATED R

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED

CONFIGURATION UPDATED

R

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED

CONFIGURATION UPDATED

R

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED

CONFIGURATION UPDATED

R

MANPOWER MANPOWER UPDATED

CONFIGURATION UPDATED

R

MANPOWER UPDATED

CONFIGURATION UPDATED

R

MANPOWER UPDATED

CONFIGURATION UPDATED

R

REFERENCES REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

PUBLICATION AFFECTED PUBLICATIONS AFFECTED UPDATED R

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY

Procurement Addresses PROCUREMENT ADDRESSES UPDATED

MATERIAL SET UPDATED

R

Price and Availability PRICE AND AVAILABILITY UPDATED

MATERIAL AVAILABILITY UPDATED

MATERIAL PRICE UPDATED

MATERIAL SET UPDATED

R

LIST OF COMPONENTS LIST OF COMPONENTS UPDATED R

Kit 571178A01R01 PART MATERIAL SET ADDED N

Kit 571178A02R01 PART MATERIAL SET ADDED N

Kit 571178A03R01 PART MATERIAL SET ADDED N

LIST OF MATERIALS - OPERATOR

SUPPLIED

Consumable Materials CONSUMABLE MATERIALS UPDATED R

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

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

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REVISION TRANSMITTAL SHEET

Consumable CMLA01 CONSUMABLE MATERIAL SET UPDATED

QUANTITY UPDATED

CONSUMABLE UPDATED

R

Components COMPONENTS UPDATED R

ACCOMPLISHMENT INSTRUCTIONS

TASK 571178- 832-801-001-Special

Detailed Inspection of the spar vertical

Stringers Radius, the horizontal Floor

Beam Radius and the Fasteners Holes on

FR36

TASK SOLUTION UPDATED

TASK TITLE UPDATED

CAUTION UPDATED

NOTE UPDATED

R

Task associated data - 001 MAN HOURS UPDATED

ELAPSED TIME UPDATED

R

Task associated data - 002 MAN HOURS UPDATED

ELAPSED TIME UPDATED

R

Task associated data - 003 MAN HOURS UPDATED

ELAPSED TIME UPDATED

R

Subtask 571178-910-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 571178-910-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 571178-910-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 571178-941-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

NOTE UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 571178-941-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

NOTE UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 571178-941-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

NOTE UPDATED

PANEL UPDATED

REFERENCES UPDATED

R

Subtask 571178-831-001-001 SUBTASK SOLUTION ADDED N

Subtask 571178-832-001-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

CONSUMABLE UPDATED

REFERENCED DOCUMENTATION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

REFERENCES UPDATED

R

Subtask 571178-831-003-001 SUBTASK SOLUTION ADDED N

Subtask 571178-831-001-003 SUBTASK SOLUTION ADDED N

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

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

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Subtask 571178-832-001-002 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

CONSUMABLE UPDATED

REFERENCED DOCUMENTATION UPDATED

CONFIGURATION UPDATED

FIGURE REFERENCE UPDATED

NOTE UPDATED

REFERENCES UPDATED

R

Subtask 571178-831-002-003 SUBTASK SOLUTION ADDED N

Subtask 571178-831-003-003 SUBTASK SOLUTION ADDED N

Subtask 571178-831-001-002 SUBTASK SOLUTION ADDED N

Subtask 571178-832-001-003 SUBTASK SOLUTION ADDED N

Subtask 571178-831-003-002 SUBTASK SOLUTION ADDED N

Subtask 571178-832-001-002 SUBTASK SOLUTION DELETED FOR

APPLICABLE MSN

D

Subtask 571178-700-001-001 SUBTASK SOLUTION UPDATED

NOTE UPDATED

R

Subtask 571178-700-001-001 SUBTASK SOLUTION UPDATED

NOTE UPDATED

R

Subtask 571178-700-001-001 SUBTASK SOLUTION UPDATED

NOTE UPDATED

R

Subtask 571178-942-001-001 SUBTASK SOLUTION UPDATED R

Subtask 571178-942-001-001 SUBTASK SOLUTION UPDATED R

Subtask 571178-942-001-001 SUBTASK SOLUTION UPDATED R

TASK 571178- 832-802-001-Special

Detailed Inspection of the spar vertical

Stringers Radius, the horizontal Floor

Beam Radius and the Fasteners Holes on

FR36 - ADDITIONAL WORK

TASK SOLUTION ADDED N

Task associated data - 001 TASK ASSOCIATED DATA ADDED N

Task associated data - 002 TASK ASSOCIATED DATA ADDED N

Task associated data - 003 TASK ASSOCIATED DATA ADDED N

Subtask 571178-910-002-001 SUBTASK SOLUTION ADDED N

Subtask 571178-839-002-001 SUBTASK SOLUTION ADDED N

Subtask 571178-910-002-001 SUBTASK SOLUTION ADDED N

Subtask 571178-839-002-001 SUBTASK SOLUTION ADDED N

Subtask 571178-910-002-001 SUBTASK SOLUTION ADDED N

Subtask 571178-839-002-001 SUBTASK SOLUTION ADDED N

Subtask 571178-941-002-001 SUBTASK SOLUTION ADDED N

Subtask 571178-941-002-001 SUBTASK SOLUTION ADDED N

Subtask 571178-941-002-001 SUBTASK SOLUTION ADDED N

Subtask 571178-831-004-001 SUBTASK SOLUTION ADDED N

Subtask 571178-832-002-001 SUBTASK SOLUTION ADDED N

Subtask 571178-831-006-001 SUBTASK SOLUTION ADDED N

Subtask 571178-831-004-003 SUBTASK SOLUTION ADDED N

Subtask 571178-832-002-002 SUBTASK SOLUTION ADDED N

Subtask 571178-831-005-003 SUBTASK SOLUTION ADDED N

Subtask 571178-831-006-003 SUBTASK SOLUTION ADDED N

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

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

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REVISION TRANSMITTAL SHEET

Subtask 571178-831-004-002 SUBTASK SOLUTION ADDED N

Subtask 571178-832-002-003 SUBTASK SOLUTION ADDED N

Subtask 571178-831-006-002 SUBTASK SOLUTION ADDED N

Subtask 571178-700-002-001 SUBTASK SOLUTION ADDED N

Subtask 571178-700-002-001 SUBTASK SOLUTION ADDED N

Subtask 571178-700-002-001 SUBTASK SOLUTION ADDED N

Subtask 571178-942-002-001 SUBTASK SOLUTION ADDED N

Subtask 571178-942-002-001 SUBTASK SOLUTION ADDED N

Subtask 571178-942-002-001 SUBTASK SOLUTION ADDED N

Fig. A-FBAAA FIGURE SOLUTION UPDATED R

Fig. A-FBAAA Sheet 01 SHEET UPDATED R

Fig. A-FBAAA Sheet 02 SHEET ADDED N

Fig. A-FBAAB FIGURE SOLUTION UPDATED R

Fig. A-FBAAB Sheet 01 SHEET UPDATED R

Fig. A-FBAAB Sheet 02 SHEET ADDED N

Fig. A-FBBAA FIGURE SOLUTION ADDED N

Fig. A-FBBAA Sheet 01 SHEET ADDED N

Fig. A-FBCAA FIGURE SOLUTION ADDED N

Fig. A-FBCAA Sheet 01 SHEET ADDED N

Fig. A-FBCAA Sheet 02 SHEET ADDED N

Fig. A-FBCAB FIGURE SOLUTION ADDED N

Fig. A-FBCAB Sheet 01 SHEET ADDED N

Fig. A-FBCAB Sheet 02 SHEET ADDED N

Fig. A-FBCAC FIGURE SOLUTION ADDED N

Fig. A-FBCAC Sheet 01 SHEET ADDED N

Fig. A-FBCAC Sheet 02 SHEET ADDED N

Fig. A-FFAAA

Fig. A-FFAAA Sheet 01 SHEET UPDATED R

Fig. A-FFAAB

Fig. A-FFAAB Sheet 01 SHEET UPDATED R

Fig. A-FFBAA FIGURE SOLUTION ADDED N

Fig. A-FFBAA Sheet 01 SHEET ADDED N

Fig. A-FFBAB FIGURE SOLUTION ADDED N

Fig. A-FFBAB Sheet 01 SHEET ADDED N

Fig. A-FRAAA FIGURE SOLUTION UPDATED R

Fig. A-FRAAA Sheet 01 SHEET UPDATED R

Fig. A-FRAAA Sheet 02 SHEET UPDATED R

Fig. A-FRAAA Sheet 03 SHEET ADDED N

Fig. A-FRAAA Sheet 04 SHEET ADDED N

Appendix 01 - Elapsed Time Assumption

APPENDIX CONTENT APPENDIX CONTENT ADDED N

Fig. A-FAAAA FIGURE SOLUTION ADDED N

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

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

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REVISION TRANSMITTAL SHEET

Fig. A-FAAAA Sheet 01 SHEET ADDED N

Fig. A-FAAAC FIGURE SOLUTION ADDED N

Fig. A-FAAAC Sheet 01 SHEET ADDED N

Fig. A-FAAAB FIGURE SOLUTION ADDED N

Fig. A-FAAAB Sheet 01 SHEET ADDED N

FILLING INSTRUCTIONS

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

Replace the complete document.

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

HISTORY OF PREVIOUS REVISIONS

No previous revision

REVISION SEQUENCE

ORIGINAL: Oct 29/13

REVISION No. : 01 - May 28/14

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

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

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

This Page Intentionally Left Blank

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

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

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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: WINGS - INSPECTION OF FRONT SPAR VERTICAL STRINGERS

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During Full Scale Fatigue Tests, cracks were found in the Centre Wing Box front spar external vertical

stiffeners at floor beam level. Cracks initiated from vertical fillets of the vertical stiffeners flange. To

prevent such damages, modification No. 21290P1547 was embodied on the aircraft in production

(Serial modification) from MSN 0156. It consists in installing reinforced vertical stiffener at floor beam

level (thickness increase).

Note that modification No. 21290P1546 was embodied on Aicraft in production from MSN 0080 to 0155.

It consists in installing shims to reduce unfolding effects of the vertical stiffener flange to avoid crack

initiation.

ISB No. A320-57-1016 was issued for Aircraft already delivered. It consists in a repetitive High

Frequency Eddy Current inspection of front spar vertical stiffeners at floor beam level. This inspection

was rendered mandatory by EASA AD 97-311-105 (B). Note that accomplishment of Service Bulletin

No. A320-57-1017 (similar to modification No. 21290P1546) was proposed to cancel the repetitive

inspection.

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

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

inspection is necessary for aircraft POST modification No. 21290P1546. This ISB No. A320-57-1178

cancels and supersedes ISB No. A320-57-1016.

This Service Bulletin requires at the front external upper spar the inspection of vertical stiffeners radius

with floor beams radius and fasteners holes.

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

spar external vertical stiffeners at floor beam level.

ISB No. A320-57-1178 cancels and supersedes ISB No. A320-57-1016.

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

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

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SERVICE BULLETIN

SUMMARY

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO

BOOKLET AVAILABLE YES VALIDATION ON AIRCRAFT YES

NOTE (1): Service Bulletin must be accomplished.

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

Manufacturer Serial Number (MSN) 0078.

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

requirements of the current issue of the Service Bulletin.

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

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

the concerned SB file).

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 571178A01R01 1 620.00 Screws, Nuts

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 571178A03R01 1 1,210.00 Screws, Nuts

**CONF 003

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 571178A02R01 1 620.00 Screws, Nuts

EFFECTIVITY

**CONF ALL

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

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

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

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SUMMARY

35U 73W ACA AFR AIB AIC ART DAL DLH F2I FPY GBB GWI

JAV MMA SVR TAR USA

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 571178-832-801-001: Special Detailed Inspection of the spar vertical Stringers Radius, the

horizontal Floor Beam Radius and the Fasteners Holes on FR36

TOTAL MANHOURS 23.25

ELAPSED TIME (HOURS) 12.75

Task 571178-832-802-001: Special Detailed Inspection of the spar vertical Stringers Radius, the

horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK

TOTAL MANHOURS 23.25

ELAPSED TIME (HOURS) 12.75

**CONF 002

Task 571178-832-801-001: Special Detailed Inspection of the spar vertical Stringers Radius, the

horizontal Floor Beam Radius and the Fasteners Holes on FR36

TOTAL MANHOURS 24.25

ELAPSED TIME (HOURS) 13.75

Task 571178-832-802-001: Special Detailed Inspection of the spar vertical Stringers Radius, the

horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK

TOTAL MANHOURS 24.25

ELAPSED TIME (HOURS) 13.75

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

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

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SUMMARY

**CONF 003

Task 571178-832-801-001: Special Detailed Inspection of the spar vertical Stringers Radius, the

horizontal Floor Beam Radius and the Fasteners Holes on FR36

TOTAL MANHOURS 23.25

ELAPSED TIME (HOURS) 12.75

Task 571178-832-802-001: Special Detailed Inspection of the spar vertical Stringers Radius, the

horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK

TOTAL MANHOURS 23.25

ELAPSED TIME (HOURS) 12.75

APPENDICES

**CONF ALL

Appendix 01 - Elapsed Time Assumption

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

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

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SUMMARY

**CONF 001

INSPECTION AREA

NOTE:

A

A

B

FR36

FR42

A

VIEW LOOKING AFT

B

B

B

B

B

B

A

Z240

FASTENERS HOLES TO BE INSPECTED

N_SB_571178_5_SAAA_01_04

Figure A-FSAAA - Sheet 01

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

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

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SUMMARY

**CONF 001

DATUM

FWD

FR36

A A

VIEW LOOKING FWD

FLOOR BEAM

B B

B

B

INSPECTION AREA

NOTE:

FASTENERS HOLES TO BE INSPECTED

N_SB_571178_5_SAAA_02_00

Figure A-FSAAA - Sheet 02

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

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

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SERVICE BULLETIN

SUMMARY

**CONF 002 thru 003

INSPECTION AREA

NOTE:

A

A

B

FR36

FR42

A

VIEW LOOKING AFT

B

B

B

B

B

B

A

Z240

FASTENERS HOLES TO BE INSPECTED

N_SB_571178_5_SAAB_01_04

Figure A-FSAAB - Sheet 01

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

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

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SERVICE BULLETIN

SUMMARY

**CONF 002 thru 003

DATUM

FWD

FR36

A A

VIEW LOOKING FWD

FLOOR BEAM

B B

B

B

INSPECTION AREA

NOTE:

FASTENERS HOLES TO BE INSPECTED 

N_SB_571178_5_SAAB_02_00

Figure A-FSAAB - Sheet 02

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

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

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
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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: WINGS - INSPECTION OF FRONT SPAR VERTICAL STRINGERS

MODIFICATION No.: None

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

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

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

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

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

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

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

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

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

21290P1547 is not embodied.

(1) Models

320-211 320-212 320-231

(2) Effectivity by MSN

0029 0045-0047 0049-0057 0059 0064-0078 0080-0088 0090 0093-0096 0099 0104

0110-0119 0121-0127 0135 0137-0138 0140-0142 0147-0150 0152-0154

(3) Effectivity by Operator

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

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

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

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

OPERATOR MSN

35U 0088

73W 0087

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

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

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SERVICE BULLETIN

OPERATOR MSN

ACA 0059 0068 0073 0084 0122 0126 0127 0141 0149 0150 0154

AFR 0115

AIB 0138

AIC 0045 0046 0047 0049 0050 0051 0056 0057 0074 0075 0080 0090

0095 0096

ART 0142

DAL 0118 0121 0125 0152 0153

DLH 0069 0070 0071 0072 0078 0083 0086 0093 0094 0104 0110 0111

0116 0117 0135 0137

F2I 0085 0148

FPY 0112

GBB 0067

GWI 0147

JAV 0029

MMA 0113 0114

SVR 0140

TAR 0119 0123 0124

USA 0052 0053 0054 0055 0064 0065 0066 0076 0077 0081 0082 0099

(4) Configuration by MSN

MSN CONFIGURATION

0029 0045 0046 0047 0049 0050 0051 0052 0053 0054 0055

0056 0057 0059 0064 0065 0066 0067 0068 0069 0070 0071

0072 0073 0074 0075 0076 0077 0078

001 002

0080 0081 0082 0083 0084 0085 0086 0087 0088 0090 0093

0094 0095 0096 0099 0104 0110 0111 0112 0113 0114 0115

0116 0117 0118 0119 0121 0122 0123 0124 0125 0126 0127

0135 0137 0138 0140 0141 0142 0147 0148 0149 0150 0152

0153 0154

003

(5) Configuration definition

**CONF 001

Config. 001 is valid for aircraft on which modification No. 21290P1546 is not embodied

and on which Service Bulletin No. A320-57-1017 is not accomplished.

**CONF 002

Config. 002 is valid for aircraft on which modification No. 21290P1546 is not embodied

and on which Service Bulletin No. A320-57-1017 is accomplished.

**CONF 003

Config. 003 is valid for aircraft on which modification No. 21290P1546 is embodied.

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Kit 571178A01R01 1

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

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

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SERVICE BULLETIN

MATERIAL QTY PER A/C SEE NOTES

Consumable CMLA01 1

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Kit 571178A03R01 1

Consumable CMLA01 1

**CONF 003

MATERIAL QTY PER A/C SEE NOTES

Kit 571178A02R01 1

Consumable CMLA01 1

**CONF ALL

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During Full Scale Fatigue Tests, cracks were found in the Centre Wing Box front spar

external vertical stiffeners at floor beam level. Cracks initiated from vertical fillets of the

vertical stiffeners flange. To prevent such damages, modification No. 21290P1547 was

embodied on the aircraft in production (Serial modification) from MSN 0156. It consists in

installing reinforced vertical stiffener at floor beam level (thickness increase).

Note that modification No. 21290P1546 was embodied on Aicraft in production from

MSN 0080 to 0155. It consists in installing shims to reduce unfolding effects of the

vertical stiffener flange to avoid crack initiation.

ISB No. A320-57-1016 was issued for Aircraft already delivered. It consists in a

repetitive High Frequency Eddy Current inspection of front spar vertical stiffeners at floor

beam level. This inspection was rendered mandatory by EASA AD 97-311-105 (B). Note

that accomplishment of Service Bulletin No. A320-57-1017 (similar to modification No.

21290P1546) was proposed to cancel the repetitive inspection.

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

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

has been assessed that an additional inspection is necessary for aircraft POST

modification No. 21290P1546. This ISB No. A320-57-1178 cancels and supersedes ISB

No. A320-57-1016.

(2) Objective/Action

This Service Bulletin requires at the front external upper spar the inspection of vertical

stiffeners radius with floor beams radius and fasteners holes.

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

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

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SERVICE BULLETIN

(3) Advantages

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

of the front spar external vertical stiffeners at floor beam level.

(4) Operational/Maintenance Consequences

ISB No. A320-57-1178 cancels and supersedes ISB No. A320-57-1016.

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 571178-832-801-001: Special Detailed Inspection of the spar vertical Stringers Radius,

the horizontal Floor Beam Radius and the Fasteners Holes on FR36

(1) Remove the fasteners of the spar vertical Stringers on FR36

(2) Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers

Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the

Fasteners Holes on FR36

(3) Install the new fasteners of the spar vertical Stringers on FR36

Task 571178-832-802-001: Special Detailed Inspection of the spar vertical Stringers Radius,

the horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK

(1) Remove the fasteners of the spar vertical Stringers on FR36

(2) Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers

Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the

Fasteners Holes on FR36

(3) Install the new fasteners of the spar vertical Stringers on FR36

**CONF 002

Task 571178-832-801-001: Special Detailed Inspection of the spar vertical Stringers Radius,

the horizontal Floor Beam Radius and the Fasteners Holes on FR36

(1) Remove the fasteners and the shims of the spar vertical Stringers on FR36

(2) Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers

Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the

Fasteners Holes on FR36

(3) Oversize the holes of the spar vertical Stringers, the horizontal floor Beam and the

holes of the shims on FR36

(4) Install the new fasteners and the shims of the spar vertical Stringers on FR36

Task 571178-832-802-001: Special Detailed Inspection of the spar vertical Stringers Radius,

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

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

5

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SERVICE BULLETIN

the horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK

(1) Remove the fasteners and the shims of the spar vertical Stringers on FR36

(2) Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers

Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the

Fasteners Holes on FR36

(3) Oversize the holes of the spar vertical Stringers radius, the horizontal floor Beam and

the holes of the shims on FR36

(4) Install the new fasteners and the shims of the spar vertical Stringers on FR36

**CONF 003

Task 571178-832-801-001: Special Detailed Inspection of the spar vertical Stringers Radius,

the horizontal Floor Beam Radius and the Fasteners Holes on FR36

(1) Remove the fasteners and the shims of the spar vertical Stringers on FR36

(2) Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers

Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the

Fasteners Holes on FR36

(3) Install the new fasteners and the shims of the spar vertical Stringers on FR36

Task 571178-832-802-001: Special Detailed Inspection of the spar vertical Stringers Radius,

the horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK

(1) Remove the fasteners and the shims of the spar vertical Stringers on FR36

(2) Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers

Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the

Fasteners Holes on FR36

(3) Install the new fasteners and the shims of the spar vertical Stringers on FR36

**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

**CONF 001

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

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

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

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

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

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SERVICE BULLETIN

Table 1, Config. 001 - Do a Special Detailed Inspection of the spar vertical Stringers Radius, the

horizontal Floor Beam Radius and the Fasteners Holes on Frame 36

Compliance Time (whichever occurs

later)

Condition Action

Threshold from

first flight

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

All Aircraft Do a Special Detailed

Inspection of the spar

vertical Stringers

Radius, the horizontal

Floor Beam Radius

and the Fasteners

Holes on Frame 36 in

accordance with

TASK

571178-832-801 001

Special Detailed

Inspection of the spar

vertical Stringers

Radius, the horizontal

Floor Beam Radius

and the Fasteners

Holes on FR36

24000FC/

48000FH from

first flight

8800FC/ 17700FH

from last

Inspection SB No.

A320-57-1016

or

850FC/ 1700FH

from SB original

issuance date

without exceeding

14000FC from last

inspection

None

Crack found Contact Airbus and

apply further

instructions

Before next flight None None

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

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

5

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SERVICE BULLETIN

Table 1, Config. 001 - Do a Special Detailed Inspection of the spar vertical Stringers Radius, the

horizontal Floor Beam Radius and the Fasteners Holes on Frame 36

Compliance Time (whichever occurs

later)

Condition Action

Threshold from

first flight

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

Apply Service Bulletin

No. A320-57-1017

and

None None None

Repeat the HFEC

and rototest

inspections in

accordance with

TASK

571178-832-801 001

Special Detailed

Inspection of the spar

vertical Stringers

Radius, the horizontal

Floor Beam Radius

and the Fasteners

Holes on FR36

None None 24900FC/

49800FH

OR

No crack found

Repeat the HFEC

and rototest

Inspections in

accordance TASK

571178-832-801 001

Special Detailed

Inspection of the spar

vertical Stringers

Radius, the horizontal

Floor Beam Radius

and the Fasteners

Holes on FR36

None None 8800FC/ 17700FH

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

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

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SERVICE BULLETIN

Table 2, Config. 001 - ADDITIONAL WORK - Do a Special Detailed Inspection of the spar vertical

Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on Frame 36

Compliance Time (whichever occurs

later)

Condition Action

Threshold from

first flight

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

All Aircraft Do a Special Detailed

Inspection of the spar

vertical Stringers

Radius, the horizontal

Floor Beam Radius

and the Fasteners

Holes on Frame 36 in

accordance with

TASK

571178-832-802 001

Special Detailed

Inspection of the spar

vertical Stringers

Radius, the horizontal

Floor Beam Radius

and the Fasteners

Holes on FR36 -

ADDITIONAL WORK

24000FC/

48000FH from

first flight

8 800FC/

17700FH from last

Inspection SB No.

A320-57-1016

or

850FC/ 1700FH

from SB original

issuance date

without exceeding

14000FC from last

inspection

None

Crack found Contact Airbus and

apply further

instructions

Before next flight None None

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

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

5

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SERVICE BULLETIN

Table 2, Config. 001 - ADDITIONAL WORK - Do a Special Detailed Inspection of the spar vertical

Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on Frame 36

Compliance Time (whichever occurs

later)

Condition Action

Threshold from

first flight

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

Apply Service Bulletin

No. A320-57-1017

and

None None None

Repeat the HFEC and

rototest inspections in

accordance with

TASK

571178-832-801 001

Special Detailed

Inspection of the spar

vertical Stringers

Radius, the horizontal

Floor Beam Radius

and the Fasteners

Holes on FR36

None None 24900FC/

49800FH

OR

No crack found

Repeat the HFEC and

rototest Inspections in

accordance with

TASK

571178-832-801 001

Special Detailed

Inspection of the spar

vertical Stringers

Radius, the horizontal

Floor Beam Radius

and the Fasteners

Holes on FR36

None None 8800FC/ 17700FH

**CONF 002

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

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

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

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

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

5

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SERVICE BULLETIN

Table 1, Config. 002 - Do a Special Detailed Inspection of the spar vertical Stringers Radius, the

horizontal Floor Beam Radius and the Fasteners Holes on Frame 36

Compliance Time (whichever

occurs later)

Condition Action

Threshold

from first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

All Aircraft Service Bulletin

No.

A320-57-1016

not

accomplished

as a prerequisite of

Service Bulletin

No.

A320-57-1017

accomplishment

Do a Special

Detailed Inspection

of the spar vertical

Stringers Radius,

the horizontal Floor

Beam Radius and

the Fasteners

Holes on Frame 36

in accordance with

TASK

571178-832-801

001 Special

Detailed Inspection

of the spar vertical

Stringers Radius,

the horizontal Floor

Beam Radius and

the Fasteners

Holes on FR36

8800FC/

17700FH from

Service

Bulletin

A320-57-1017

embodiement

850FC/

1700FH from

SB original

issuance date

None

All Aircraft Service Bulletin

No.

A320-57-1016

accomplished

as a prerequisite of

Service Bulletin

No.

A320-57-1017

accomplishment

Do a Special

Detailed Inspection

of the spar vertical

Stringers Radius,

the horizontal Floor

Beam Radius and

the Fasteners

Holes on Frame 36

in accordance with

TASK

571178-832-801

001 Special

Detailed Inspection

of the spar vertical

Stringers Radius,

the horizontal Floor

Beam Radius and

the Fasteners

Holes on FR36

24900FC/

49800FH from

Service

Bulletin

A320-57-1017

embodiement

850FC/

1700FH from

SB original

issuance date

None

Crack found Contact Airbus and

apply further

instructions

Before next

flight

None None

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

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

5

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SERVICE BULLETIN

Table 1, Config. 002 - Do a Special Detailed Inspection of the spar vertical Stringers Radius, the

horizontal Floor Beam Radius and the Fasteners Holes on Frame 36

Compliance Time (whichever

occurs later)

Condition Action

Threshold

from first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

No crack found Repeat the HFEC

and rototest

inspections in

accordance with

TASK

571178-832-801

001 Special

Detailed Inspection

of the spar vertical

Stringers Radius,

the horizontal Floor

Beam Radius and

the Fasteners

Holes on FR36

None None 24900FC/

49800FH

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

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

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SERVICE BULLETIN

Table 2, Config. 002 - ADDITIONAL WORK - Do a Special Detailed Inspection of the spar vertical

Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on Frame 36

Compliance Time (whichever

occurs later)

Condition Action

Threshold

from first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

Service Bulletin

No.

A320-57-1016

not

accomplished

as a prerequisite of

Service Bulletin

No.

A320-57-1017

accomplishment

Do a Special

Detailed Inspection

of the spar vertical

Stringers Radius,

the horizontal Floor

Beam Radius and

the Fasteners

Holes on Frame 36

in accordance with

TASK

571178-832-802

001 Special

Detailed Inspection

of the spar vertical

Stringers Radius,

the horizontal Floor

Beam Radius and

the Fasteners

Holes on FR36 -

ADDITIONAL

WORK

8800FC/

17700FH from

Service

Bulletin

A320-57-1017

embodiement

850FC/

1700FH from

SB original

issuance date

All Aircraft None

Service Bulletin

No.

A320-57-1016

accomplished

as a prerequisite of

Service Bulletin

No.

A320-57-1017

accomplishment

Do a Special

Detailed Inspection

of the spar vertical

Stringers Radius,

the horizontal Floor

Beam Radius and

the Fasteners

Holes on Frame 36

in accordance with

TASK

571178-832-802

001 Special

Detailed Inspection

of the spar vertical

Stringers Radius,

the horizontal Floor

Beam Radius and

the Fasteners

Holes on FR36 -

ADDITIONAL

WORK

24900FC/

49800FH from

Service

Bulletin

A320-57-1017

embodiement

850FC/

1700FH from

SB original

issuance date

None

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

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

5

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SERVICE BULLETIN

Table 2, Config. 002 - ADDITIONAL WORK - Do a Special Detailed Inspection of the spar vertical

Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on Frame 36

Compliance Time (whichever

occurs later)

Condition Action

Threshold

from first flight

(whichever

occurs first)

Grace period

(whichever

occurs first)

Repetitive

Interval

(whichever

occurs first)

Crack found Contact Airbus and

apply further

instructions

Before next

flight

None None

No crack found Repeat the HFEC

and rototest

inspections in

accordance with

TASK

571178-832-801

001 Special

Detailed Inspection

of the spar vertical

Stringers Radius,

the horizontal Floor

Beam Radius and

the Fasteners

Holes on FR36

None None 24900FC/

49800FH

**CONF 003

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

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

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

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

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

5

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SERVICE BULLETIN

Table 1, Config. 003 - Do a Special Detailed Inspection of the spar vertical Stringers Radius, the

horizontal Floor Beam Radius and the Fasteners Holes on Frame 36

Compliance Time (whichever occurs

later)

Condition Action

Threshold from

first flight

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

All Aircraft Do a Special

Detailed Inspection of

the spar vertical

Stringers Radius, the

horizontal Floor

Beam Radius and

the Fasteners Holes

on Frame 36 in

accordance with

TASK

571178-832-801 001

Special Detailed

Inspection of the spar

vertical Stringers

Radius, the

horizontal Floor

Beam Radius and

the Fasteners Holes

on FR36

54300FC/

108600FH from

first flight

None None

Crack found Contact Airbus and

apply further

instructions

Before next flight None None

No crack found Repeat the HFEC

and rototest

inspections in

accordance with

TASK

571178-832-801 001

Special Detailed

Inspection of the spar

vertical Stringers

Radius, the

horizontal Floor

Beam Radius and

the Fasteners Holes

on FR36

None None 24900FC/

49800FH

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

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

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SERVICE BULLETIN

Table 2, Config. 003 - ADDITIONAL WORK - Do a Special Detailed Inspection of the spar vertical

Stringers Radius, the horizontal Floor Beam Radius and the Fasteners Holes on Frame 36

Compliance Time (whichever occurs

later)

Condition Action

Threshold from

first flight

(whichever occurs

first)

Grace period

(whichever occurs

first)

Repetitive Interval

(whichever occurs

first)

All Aircraft Do a Special Detailed

Inspection of the spar

vertical Stringers

Radius, the horizontal

Floor Beam Radius

and the Fasteners

Holes on Frame 36 in

accordance with

TASK

571178-832-802 001

Special Detailed

Inspection of the spar

vertical Stringers

Radius, the horizontal

Floor Beam Radius

and the Fasteners

Holes on FR36 -

ADDITIONAL WORK

54300FC/

108600FH from

first flight

None None

Crack found Contact Airbus and

apply further

instructions

Before next flight None None

No crack found Repeat the HFEC

and rototest

inspections in

accordance with

TASK

571178-832-801 001

Special Detailed

Inspection of the spar

vertical Stringers

Radius, the horizontal

Floor Beam Radius

and the Fasteners

Holes on FR36

None None 24900FC/

49800FH

**CONF ALL

F. APPROVAL

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

Organisation Approval No. EASA.21J.031.

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

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

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SERVICE BULLETIN

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

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

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

before incorporation of the Service Bulletin.

G. MANPOWER

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

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

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

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

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

included.

**CONF 001

Task 571178-832-801-001: Special Detailed Inspection of the spar vertical Stringers Radius, the

horizontal Floor Beam Radius and the Fasteners Holes on FR36

Get Access 6.00

On Aircraft

Remove the fasteners of the spar vertical Stringers on

FR36

3.00

Do High Frequency Eddy Current (HFEC) Inspections

of the spar vertical Stringers Radius and the horizontal

Floor Beam Radius and do a Rototest Inspection of the

Fasteners Holes on FR36

2.00

Install the new fasteners of the spar vertical Stringers

on FR36

5.00

Tests 0.25

Close-Up 7.00

TOTAL MANHOURS 23.25

ELAPSED TIME (HOURS) 12.75

Task 571178-832-802-001: Special Detailed Inspection of the spar vertical Stringers Radius, the

horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK

Get Access 6.00

On Aircraft

Remove the fasteners of the spar vertical Stringers on

FR36

3.00

Do High Frequency Eddy Current (HFEC) Inspections

of the spar vertical Stringers Radius and the horizontal

Floor Beam Radius and do a Rototest Inspection of the

Fasteners Holes on FR36

2.00

Install the new fasteners of the spar vertical Stringers

on FR36

5.00

Tests 0.25

Close-Up 7.00

TOTAL MANHOURS 23.25

ELAPSED TIME (HOURS) 12.75

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

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

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SERVICE BULLETIN

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

Chart,Fig. A-FAAAB given in Appendix 01 - Elapsed Time Assumption .

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

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

manhours can apply.

**CONF 002

Task 571178-832-801-001: Special Detailed Inspection of the spar vertical Stringers Radius, the

horizontal Floor Beam Radius and the Fasteners Holes on FR36

Get Access 6.00

On Aircraft

Remove the fasteners and the shims of the spar

vertical Stringers on FR36

3.00

Do High Frequency Eddy Current (HFEC) Inspections

of the spar vertical Stringers Radius and the horizontal

Floor Beam Radius and do a Rototest Inspection of the

Fasteners Holes on FR36

2.00

Oversize the holes of the spar vertical Stringers, the

horizontal floor Beam and the holes of the shims on

FR36

1.00

Install the new fasteners and the shims of the spar

vertical Stringers on FR36

5.00

Tests 0.25

Close-Up 7.00

TOTAL MANHOURS 24.25

ELAPSED TIME (HOURS) 13.75

Task 571178-832-802-001: Special Detailed Inspection of the spar vertical Stringers Radius, the

horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK

Get Access 6.00

On Aircraft

Remove the fasteners and the shims of the spar

vertical Stringers on FR36

3.00

Do High Frequency Eddy Current (HFEC) Inspections

of the spar vertical Stringers Radius and the horizontal

Floor Beam Radius and do a Rototest Inspection of the

Fasteners Holes on FR36

2.00

Oversize the holes of the spar vertical Stringers radius,

the horizontal floor Beam and the holes of the shims

on FR36

1.00

Install the new fasteners and the shims of the spar

vertical Stringers on FR36

5.00

Tests 0.25

Close-Up 7.00

TOTAL MANHOURS 24.25

ELAPSED TIME (HOURS) 13.75

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

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

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

Chart,Fig. A-FAAAA given in Appendix 01 - Elapsed Time Assumption .

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

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

manhours can apply.

**CONF 003

Task 571178-832-801-001: Special Detailed Inspection of the spar vertical Stringers Radius, the

horizontal Floor Beam Radius and the Fasteners Holes on FR36

Get Access 6.00

On Aircraft

Remove the fasteners and the shims of the spar

vertical Stringers on FR36

3.00

Do High Frequency Eddy Current (HFEC) Inspections

of the spar vertical Stringers Radius and the horizontal

Floor Beam Radius and do a Rototest Inspection of the

Fasteners Holes on FR36

2.00

Install the new fasteners and the shims of the spar

vertical Stringers on FR36

5.00

Tests 0.25

Close-Up 7.00

TOTAL MANHOURS 23.25

ELAPSED TIME (HOURS) 12.75

Task 571178-832-802-001: Special Detailed Inspection of the spar vertical Stringers Radius, the

horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK

Get Access 6.00

On Aircraft

Remove the fasteners and the shims of the spar

vertical Stringers on FR36

3.00

Do High Frequency Eddy Current (HFEC) Inspections

of the spar vertical Stringers Radius and the horizontal

Floor Beam Radius and do a Rototest Inspection of the

Fasteners Holes on FR36

2.00

Install the new fasteners and the shims of the spar

vertical Stringers on FR36

5.00

Tests 0.25

Close-Up 7.00

TOTAL MANHOURS 23.25

ELAPSED TIME (HOURS) 12.75

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

Chart,Fig. A-FAAAC given in Appendix 01 - Elapsed Time Assumption .

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

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

manhours can apply.

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

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

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**CONF ALL

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

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

12-34-24 20-21-11 25-21-41

25-28-41 52-10-00 53-32-12

Consumable Material List (CML)

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

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

Service Bulletin (SB) A320-57-1017

Standards Manual (SM)

Structural Repair Manual (SRM) 51-40-00 51-42-00 51-43-00

51-44-00 51-75-12

**CONF 002

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

12-34-24 20-21-11 25-21-41

25-28-41 52-10-00 53-32-12

Consumable Material List (CML)

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

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

Service Bulletin (SB) A320-57-1017

Standards Manual (SM)

Structural Repair Manual (SRM) 51-40-00 51-42-00 51-43-00

51-44-00 51-75-12

**CONF 003

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

12-34-24 20-21-11 25-21-41

25-28-41 52-10-00 53-32-12

Consumable Material List (CML)

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

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

Standards Manual (SM)

Structural Repair Manual (SRM) 51-40-00 51-42-00 51-43-00

51-44-00 51-75-12

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

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

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**CONF ALL

K. PUBLICATION AFFECTED

Maintenance Planning Document (MPD) 571196-01-1

571196-02-1

NOTE: Refer to old MPD 571196-01-1 if the Inspection Service Bulletin No.

A320-57-1016 is accomplished.

NOTE: Refer to new MPD 571196-02-1 if the Inspection Service Bulletin No.

A320-57-1178 is accomplished.

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

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

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

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2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

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

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

Kit 571178A01R01

Kit 571178A02R01

Kit 571178A03R01

AIRBUS Material, Logistics and Suppliers

Weg beim Jaeger 150

D-22335 HAMBOURG

GERMANY

For ordering by internet:

http://spares.airbus.com

For ordering by fax: +49 40 50 76 2590

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

(2) Price and Availability

Kit 571178A01R01

Cost 620.00 USD

Availability 90 calendar days from receipt of order

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

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

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

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

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

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

Kit 571178A02R01

Cost 620.00 USD

Availability 90 calendar days from receipt of order

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

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

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

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

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

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

Kit 571178A03R01

Cost 1,210.00 USD

Availability 180 calendar days from receipt of order

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

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

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

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

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

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

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

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

B. INDUSTRY SUPPORT INFORMATION

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

C. LIST OF COMPONENTS

Kit 571178A01R01

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

NOTES

1 EN6115V4-6 12 SCREW

2 ASNA2536-4 12 NUT

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

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

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

to part number relationship.

Kit 571178A02R01

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

NOTES

2 ASNA2536-4 12 NUT

6 EN6115V4-9 12 SCREW

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

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

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

to part number relationship.

Kit 571178A03R01

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

NOTES

2 ASNA2536-4 12 NUT

3 EN6115V4Y9 12 SCREW

4 EN6115V5-9 12 SCREW

5 ASNA2536-5 12 NUT

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

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

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

to part number relationship.

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

REVISION No.: 01 - May 28/14 Page: 22

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D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Primer Epoxy Paint-- Corrosion

Inhibiting Structure

04DAB2 As required

Top Coat Polyurethane-- Grey

Internal Structure

04JME4 As required

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

Non Aqueous Cleaner-General 08BAA9 As required

Paste Adhesive - Liquid Shim 13FGC1 As required

(2) Components

To accomplish this Service Bulletin it is necessary to use the expendable parts listed in

the subsequent referenced AMM task:

- AMM Task 53-32-12-400-002.

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

None

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

REVISION No.: 01 - May 28/14 Page: 23

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This Page Intentionally Left Blank

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

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

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 571178-832-801-001 - Special Detailed Inspection of the spar vertical Stringers Radius,

the horizontal Floor Beam Radius and the Fasteners Holes on FR36

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

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

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

THIS:

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

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

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

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

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

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

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

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

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

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

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

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

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

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

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

NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory

by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these

accomplishment instructions are Required for Compliance (RC) and must be done

to comply with the AD. Other paragraphs are recommended and may be deviated

from, done as part of other actions or done with accepted methods different from

those given in the Service Bulletin, as long as the RC paragraphs can be done and

the aircraft can be put back into a serviceable condition.

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

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

compliance times given in this Service Bulletin.

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

REVISION No.: 01 - May 28/14 Page: 25

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Task Associated Data

**CONF 001

Zone

From 241 to 242

Access

Panel 241AF 241BF 241CF 241DF 242BF 242CF 242DF

Manpower

TOTAL MANHOURS 23.25

ELAPSED TIME (HOURS) 12.75

**CONF 002

Zone

From 241 to 242

Access

Panel 241AF 241BF 241CF 241DF 242BF 242CF 242DF

Manpower

TOTAL MANHOURS 24.25

ELAPSED TIME (HOURS) 13.75

**CONF 003

Zone

From 241 to 242

Access

Panel 241AF 241BF 241CF 241DF 242BF 242CF 242DF

Manpower

TOTAL MANHOURS 23.25

ELAPSED TIME (HOURS) 12.75

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 571178-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-21-11-911-001

Consumable Material List (CML)

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

REVISION No.: 01 - May 28/14 Page: 26

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References

Structural Repair Manual (SRM) 51-40-00

51-42-00

51-43-00

51-44-00

51-75-12

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

Consumable Materials List (CML).

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

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

(d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001.

(e) To torque tighten the standard threaded fasteners, refer to AMM Task

20-21-11-911-001.

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

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

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

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

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

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

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

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

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

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

Part" column.

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

(2) Subtask 571178-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 002

(1) Subtask 571178-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

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

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

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References

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

06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-21-11-911-001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-40-00

51-42-00

51-43-00

51-44-00

51-75-12

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

Consumable Materials List (CML).

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

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

(d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001.

(e) To torque tighten the standard threaded fasteners, refer to AMM Task

20-21-11-911-001.

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

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

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

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

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

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

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

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

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

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

Part" column.

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

(2) Subtask 571178-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

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

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

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**CONF 003

(1) Subtask 571178-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-21-11-911-001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-40-00

51-42-00

51-43-00

51-44-00

51-75-12

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

Consumable Materials List (CML).

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

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

(d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001.

(e) To torque tighten the standard threaded fasteners, refer to AMM Task

20-21-11-911-001.

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

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

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

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

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

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

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

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

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

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

Part" column.

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

(2) Subtask 571178-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

REVISION No.: 01 - May 28/14 Page: 29

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

Service Bulletin.

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 571178-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-21-41-000-001

Task 25-28-41-000-001

Task 52-10-00-010-001

Task 53-32-12-000-002

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

configuration before you start a maintenance task:

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

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

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position

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

12-34-24-869-002.

(b) Put an access platform in position at 831.

(c) Open the FWD passenger/crew door 831, refer to AMM Task 52-10-00-010-001.

(d) Remove the passengers Seats between Frame 35 and Frame 36, refer to AMM

Task 25-21-41-000-001.

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

REVISION No.: 01 - May 28/14 Page: 30

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(e) Remove the textile floor covering between Frame 35 and Frame 36, refer to AMM

Task 25-28-41-000-001.

(f) Remove the floor Panels 242DF, 242CF, 242BF, 241DF, 241CF, 241BF and

241AF, refer to AMM Task 53-32-12-000-002.

(g) If necessary, remove the hydraulic pipes clamps and push the pipes without to

disconnect them in order to facilitate access of the working area .

**CONF 002

(1) Subtask 571178-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-21-41-000-001

Task 25-28-41-000-001

Task 52-10-00-010-001

Task 53-32-12-000-002

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

configuration before you start a maintenance task:

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

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

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position

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

12-34-24-869-002.

(b) Put an access platform in position at 831.

(c) Open the FWD passenger/crew door 831, refer to AMM Task 52-10-00-010-001.

(d) Remove the passengers Seats between Frame 35 and Frame 36, refer to AMM

Task 25-21-41-000-001.

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

REVISION No.: 01 - May 28/14 Page: 31

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(e) Remove the textile floor covering between Frame 35 and Frame 36, refer to AMM

Task 25-28-41-000-001.

(f) Remove the floor Panels 242DF, 242CF, 242BF, 241DF, 241CF, 241BF and

241AF, refer to AMM Task 53-32-12-000-002.

(g) If necessary, remove the hydraulic pipes clamps and push the pipes without to

disconnect them in order to facilitate access of the working area .

**CONF 003

(1) Subtask 571178-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-21-41-000-001

Task 25-28-41-000-001

Task 52-10-00-010-001

Task 53-32-12-000-002

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

configuration before you start a maintenance task:

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

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

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position

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

12-34-24-869-002.

(b) Put an access platform in position at 831.

(c) Open the FWD passenger/crew door 831, refer to AMM Task 52-10-00-010-001.

(d) Remove the passengers Seats between Frame 35 and Frame 36, refer to AMM

Task 25-21-41-000-001.

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

REVISION No.: 01 - May 28/14 Page: 32

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(e) Remove the textile floor covering between Frame 35 and Frame 36, refer to AMM

Task 25-28-41-000-001.

(f) Remove the floor Panels 242DF, 242CF, 242BF, 241DF, 241CF, 241BF and

241AF, refer to AMM Task 53-32-12-000-002.

(g) If necessary, remove the hydraulic pipes clamps and push the pipes without to

disconnect them in order to facilitate access of the working area .

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 571178-831-001-001 - Remove the fasteners of the spar vertical Stringers

on FR36

Work Zones and Access Panels

Zone Access/Work location

From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel

241DF

Work location Frame 36

To 242 Access Panel 242BF, Panel 242CF, Panel 242DF

Work location Frame 36

Manpower Resources

Manhours 3.00

Minimum number of person 2

Subtask elapsed time 1.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

References

Structural Repair Manual (SRM) 51-42-00

Fig. A-FBCAA

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

(a) Remove the fasteners of the spar vertical Stringers and the horizontal floor beam.

Refer to Fig. A-FBCAA

In accordance with SRM 51-42-00

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

REVISION No.: 01 - May 28/14 Page: 33

5

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SERVICE BULLETIN

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

areas with solvent:

Non Aqueous

Cleaner-General

08BAA9 As required

2 Remove:

12 Screw Item (1) Discard

12 Nut Item (2) Discard

(2) Subtask 571178-832-001-001 - Do High Frequency Eddy Current (HFEC)

Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam

Radius and do a Rototest Inspection of the Fasteners Holes on FR36

Work Zones and Access Panels

Zone Access/Work location

From 241 Access Panel 241AF, Panel 241DF, Panel 241CF, Panel

241BF

Work location Frame 36

To 242 Access Panel 242DF, Panel 242CF, Panel 242BF

Work location Frame 36

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

References

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

51-10-08

Service Bulletin (SB) A320-57-1017

Fig. A-FBAAA

Inspection Area

Sheet 01

Sheet 02

Fig. A-FFAAA

Flow Chart

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

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

REVISION No.: 01 - May 28/14 Page: 34

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SERVICE BULLETIN

References

Fig. A-FBBAA

Inspection of the Fasteners Holes

Sheet 01

At the threshold given in PLANNING INFORMATION paragraph E.(2):

Do Special Detailed Inspection of the spar vertical Stringers Radius on Frame 36.

Refer to Fig. A-FBAAA.

Refer to Fig. A-FBBAA.

Refer to Fig. A-FFAAA.

(a) Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers

Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the

Fasteners Holes on Frame 36:

1 Remove the protective finish from areas to be inspected with:

Non Aqueous

Cleaner-General

08BAA9 As required

2 Do a Rototest Inspection of the fasteners holes of spar vertical Stringers

Radius in center fuselage on Frame 36:

Refer to Fig. A-FBBAA Sheet 01

Refer to NTM 51-10-01

3 Do a High Frequency Eddy Current (HFEC) inspection at the horizontal floor

beam radius of the backside of the spar vertical Stringers radius and do a

HFEC inspection of the front spar vertical Stringers radius in center fuselage

on Frame 36.

Refer to Fig. A-FBAAA Sheet 01

Refer to NTM 51-10-08

a If crack is found in one of inspections:

<1> Contact Airbus and apply further instructions before next flight.

b If no crack is found in any inspections:

<1> Apply Service Bulletin No. A320-57-1017.

And

Repeat the inspections at the interval given in PLANNING

INFORMATION paragraph E.(2) in accordance with TASK

571178-832-801 001 Special Detailed Inspection of the spar vertical

Stringers Radius, the horizontal Floor Beam Radius and the

Fasteners Holes on FR36 .

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

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

5

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SERVICE BULLETIN

OR

<2> Install the fasteners on the holes to be inspected as described in

SUBTASK 571178-831-003 001 Install the new fasteners of the spar

vertical Stringers on FR36 .

And

Repeat the inspections at the interval given in PLANNING

INFORMATION paragraph E.(2) in accordance with TASK

571178-832-801 001 Special Detailed Inspection of the spar vertical

Stringers Radius, the horizontal Floor Beam Radius and the

Fasteners Holes on FR36 .

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

(3) Subtask 571178-831-003-001 - Install the new fasteners of the spar vertical

Stringers on FR36

Work Zones and Access Panels

Zone Access/Work location

From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel

241DF

Work location Frame 36

To 242 Access Panel 242BF, Panel 242CF, Panel 242DF

Work location Frame 36

Manpower Resources

Manhours 5.00

Minimum number of person 2

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 571178A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V4-6 12 SCREW

2 ASNA2536-4 12 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Primer Epoxy Paint

Corrosion Inhibiting

Structure

04DAB2 As required

Top Coat Polyurethane

Grey Internal Structure

04JME4 As required

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

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

5

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SERVICE BULLETIN

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Structural Repair Manual (SRM) 51-42-00

51-43-00

51-75-12

Fig. A-FBCAA

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

(a) Install the new fasteners of the spar vertical Stringers and the horizontal floor

beam.

Refer to Fig. A-FBCAA

In accordance with SRM 51-42-00

In accordance with SRM 51-43-00

In accordance with SRM 51-75-12

Refer to AMM Task 20-21-11-911-001

1 Install:

12 Screw EN6115V4-6 Item 1

12 Nut ASNA2536-4 Item 2

NOTE: Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

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

Top Coat

Polyurethane Grey

Internal Structure

04JME4 As required

And

Primer Epoxy Paint

Corrosion Inhibiting

Structure

04DAB2 As required

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

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

5

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SERVICE BULLETIN

**CONF 002

(1) Subtask 571178-831-001-003 - Remove the fasteners and the shims of the spar

vertical Stringers on FR36

Work Zones and Access Panels

Zone Access/Work location

From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel

241DF

Work location Frame 36

To 242 Access Panel 242BF, Panel 242CF, Panel 242DF

Work location Frame 36

Manpower Resources

Manhours 3.00

Minimum number of person 2

Subtask elapsed time 1.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

References

Structural Repair Manual (SRM) 51-42-00

Fig. A-FBCAC

Removal/Installation of the Shims and

the Fasteners

Sheet 01

Sheet 02

(a) Remove the fasteners of the spar vertical Stringers, the shims and the horizontal

floor beam.

Refer to Fig. A-FBCAC

In accordance with SRM 51-42-00

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

areas with solvent:

Non Aqueous

Cleaner-General

08BAA9 As required

2 Remove the shims:

Refer to figure Fig. A-FBCAC Sheet 01

6 Shim Item (7) Retain

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

REVISION No.: 01 - May 28/14 Page: 38

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SERVICE BULLETIN

6 Shim Item (8) Retain

Attached with, depending on aircraft configuration:

12 Screw Item (3) Discard

12 Nut Item (2) Discard

Or

12 Screw Item (4) Discard

12 Nut Item (5) Discard

(2) Subtask 571178-832-001-002 - Do High Frequency Eddy Current (HFEC)

Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam

Radius and do a Rototest Inspection of the Fasteners Holes on FR36

Work Zones and Access Panels

Zone Access/Work location

From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel

241DF

Work location Frame 36

To 242 Access Panel 242BF, Panel 242CF, Panel 242DF

Work location Frame 36

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

References

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

51-10-08

Fig. A-FBAAB

Inspection Area

Sheet 01

Sheet 02

Fig. A-FFAAB

Flow Chart

Sheet 01

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

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

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SERVICE BULLETIN

References

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FBBAA

Inspection of the Fasteners Holes

Sheet 01

At the threshold given in PLANNING INFORMATION paragraph E.(2):

Do Special Detailed Inspection of the spar vertical Stringers Radius on Frame 36.

Refer to Fig. A-FBAAB.

Refer to Fig. A-FBBAA.

Refer to Fig. A-FFAAB.

(a) Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers

Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the

Fasteners Holes on Frame 36:

1 Remove the protective finish from areas to be inspected with:

Non Aqueous

Cleaner-General

08BAA9 As required

2 Do a Rototest Inspection of the fasteners holes of spar vertical Stringers

Radius in center fuselage on Frame 36:

Refer to Fig. A-FBBAA Sheet 01

Refer to NTM 51-10-01

3 Do a High Frequency Eddy Current (HFEC) inspection at the horizontal floor

beam radius of the backside of the spar vertical Stringers radius and do a

HFEC inspection of the front spar vertical Stringers radius in center fuselage

on Frame 36.

Refer to Fig. A-FBAAB Sheet 01

Refer to NTM 51-10-08

a If crack is found in one of inspections:

<1> Contact Airbus and apply further instructions before next flight.

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

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

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b If no crack is found in any inspections:

<1> Oversize the holes of the spar vertical Stringers radius, the shims

and the horizontal floor beam radius as described in SUBTASK

571178-831-002 003 Oversize the holes of the spar vertical

Stringers, the horizontal floor Beam and the holes of the shims on

FR36 .

And

Install the fasteners and the shims on the holes to be inspected

as described in SUBTASK 571178-831-003 003 Install the new

fasteners and the shims of the spar vertical Stringers on FR36 .

And

Repeat the inspections at the interval given in PLANNING

INFORMATION paragraph E.(2) in accordance with TASK

571178-832-801 001 Special Detailed Inspection of the spar vertical

Stringers Radius, the horizontal Floor Beam Radius and the

Fasteners Holes on FR36 .

NOTE: For the repetitive inspections it is not necessary to

oversize the holes as the holes are in transition fit.

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

(3) Subtask 571178-831-002-003 - Oversize the holes of the spar vertical Stringers, the

horizontal floor Beam and the holes of the shims on FR36

Work Zones and Access Panels

Zone Access/Work location

From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel

241DF

Work location Frame 36

To 242 Access Panel 242BF, Panel 242CF, Panel 242DF

Work location Frame 36

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-44-00

Fig. A-FBCAC

Removal/Installation of the Shims and

the Fasteners

Sheet 01

Sheet 02

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

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

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SERVICE BULLETIN

(a) Oversize the holes of the spar vertical Stringers, the holes of the shims and the

horizontal floor beam.

Refer to Fig. A-FBCAC

In accordance with SRM 51-44-00

1 Depending on aircraft configuration:

a If the holes are in the first oversize diameter:

Drill to the second oversize diameter the holes to the dimensions given in

Fig. A-FBCAC.

OR

b If the holes are in the second oversize diameter:

Drill to the next nominal diameter the holes to the dimensions given in

Fig. A-FBCAC.

(4) Subtask 571178-831-003-003 - Install the new fasteners and the shims of the spar

vertical Stringers on FR36

Work Zones and Access Panels

Zone Access/Work location

From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel

241DF

Work location Frame 36

To 242 Access Panel 242BF, Panel 242CF, Panel 242DF

Work location Frame 36

Manpower Resources

Manhours 5.00

Minimum number of person 2

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 571178A03R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2536-4 12 NUT

3 EN6115V4Y9 12 SCREW

4 EN6115V5-9 12 SCREW

5 ASNA2536-5 12 NUT

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

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

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@A318/A319/A320/A321

SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Primer Epoxy Paint

Corrosion Inhibiting

Structure

04DAB2 As required

Top Coat Polyurethane

Grey Internal Structure

04JME4 As required

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

Paste Adhesive - Liquid

Shim

13FGC1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Structural Repair Manual (SRM) 51-42-00

51-43-00

51-75-12

Fig. A-FBCAC

Removal/Installation of the Shims and

the Fasteners

Sheet 01

Sheet 02

(a) Install the new fasteners of the spar vertical Stringers and the horizontal floor

beam.

Refer to Fig. A-FBCAC

In accordance with SRM 51-42-00

In accordance with SRM 51-43-00

In accordance with SRM 51-75-12

Refer to AMM Task 20-21-11-911-001

1 Install the shims:

6 Shim Item (7) Retained at

removal

6 Shim Item (8) Retained at

removal

NOTE: Install the shims with:

Paste Adhesive -

Liquid Shim

13FGC1 As required

With, depending on aircraft configuration:

12 Screw EN6115V4Y9 Item 3

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

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

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SERVICE BULLETIN

12 Nut ASNA2536-4 Item 2

Or

12 Screw EN6115V5-9 Item 4

12 Nut ASNA2536-5 Item 5

NOTE: Install the shims with:

Paste Adhesive -

Liquid Shim

13FGC1 As required

NOTE: Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

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

Top Coat

Polyurethane Grey

Internal Structure

04JME4 As required

And

Primer Epoxy Paint

Corrosion Inhibiting

Structure

04DAB2 As required

**CONF 003

(1) Subtask 571178-831-001-002 - Remove the fasteners and the shims of the spar

vertical Stringers on FR36

Work Zones and Access Panels

Zone Access/Work location

From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel

241DF

Work location Frame 36

To 242 Access Panel 242BF, Panel 242CF, Panel 242DF

Work location Frame 36

Manpower Resources

Manhours 3.00

Minimum number of person 2

Subtask elapsed time 1.50

Skills AIRFRAME

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

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

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

References

Structural Repair Manual (SRM) 51-42-00

Fig. A-FBCAB

Removal/Installation of the Shims and

the Fasteners

Sheet 01

Sheet 02

(a) Remove the fasteners of the spar vertical Stringers, the shims and the horizontal

floor beam.

Refer to Fig. A-FBCAB

In accordance with SRM 51-42-00

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

areas with solvent:

Non Aqueous

Cleaner-General

08BAA9 As required

2 Remove the shims:

Refer to figure Fig. A-FBCAB Sheet 01

6 Shim Item (7) Retain

6 Shim Item (8) Retain

Attached with:

12 Screw Item (6) Discard

12 Nut Item (2) Discard

(2) Subtask 571178-832-001-003 - Do High Frequency Eddy Current (HFEC)

Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam

Radius and do a Rototest Inspection of the Fasteners Holes on FR36

Work Zones and Access Panels

Zone Access/Work location

From 241 Access Panel 241AF, Panel 241DF, Panel 241CF, Panel

241BF

Work location Frame 36

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

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

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To 242 Access Panel 242DF, Panel 242CF, Panel 242BF

Work location Frame 36

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

References

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

51-10-08

Fig. A-FBAAB

Inspection Area

Sheet 01

Sheet 02

Fig. A-FFAAB

Flow Chart

Sheet 01

Fig. A-FBBAA

Inspection of the Fasteners Holes

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

At the threshold given in PLANNING INFORMATION paragraph E.(2):

Do Special Detailed Inspection of the spar vertical Stringers Radius on Frame 36.

Refer to Fig. A-FBAAB.

Refer to Fig. A-FBBAA.

Refer to Fig. A-FFAAB.

(a) Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers

Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the

Fasteners Holes on Frame 36:

1 Remove the protective finish from areas to be inspected with:

Non Aqueous

Cleaner-General

08BAA9 As required

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

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

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2 Do a Rototest Inspection of the fasteners holes of spar vertical Stringers

Radius in center fuselage on Frame 36:

Refer to Fig. A-FBBAA Sheet 01

Refer to NTM 51-10-01

3 Do a High Frequency Eddy Current (HFEC) inspection at the horizontal floor

beam radius of the backside of the spar vertical Stringers radius and do a

HFEC inspection of the front spar vertical Stringers radius in center fuselage

on Frame 36.

Refer to Fig. A-FBAAB Sheet 01

Refer to NTM 51-10-08

a If crack is found in one of inspections:

<1> Contact Airbus and apply further instructions before next flight.

b If no crack is found in any inspections:

<1> Install the fasteners and the shims on the holes to be inspected

as described in SUBTASK 571178-831-003 002 Install the new

fasteners and the shims of the spar vertical Stringers on FR36 .

And

Repeat the inspections at the interval given in PLANNING

INFORMATION paragraph E.(2) in accordance with TASK

571178-832-801 001 Special Detailed Inspection of the spar vertical

Stringers Radius, the horizontal Floor Beam Radius and the

Fasteners Holes on FR36 .

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

(3) Subtask 571178-831-003-002 - Install the new fasteners and the shims of the spar

vertical Stringers on FR36

Work Zones and Access Panels

Zone Access/Work location

From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel

241DF

Work location Frame 36

To 242 Access Panel 242BF, Panel 242CF, Panel 242DF

Work location Frame 36

Manpower Resources

Manhours 5.00

Minimum number of person 2

Subtask elapsed time 2.50

Skills AIRFRAME

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

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

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

Material necessary to do the job

Kit 571178A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2536-4 12 NUT

6 EN6115V4-9 12 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Primer Epoxy Paint

Corrosion Inhibiting

Structure

04DAB2 As required

Top Coat Polyurethane

Grey Internal Structure

04JME4 As required

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

Paste Adhesive - Liquid

Shim

13FGC1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Structural Repair Manual (SRM) 51-42-00

51-43-00

51-75-12

Fig. A-FBCAB

Removal/Installation of the Shims and

the Fasteners

Sheet 01

Sheet 02

(a) Install the new fasteners and the shims of the spar vertical Stringers and the

horizontal floor beam.

Refer to Fig. A-FBCAB

In accordance with SRM 51-42-00

In accordance with SRM 51-43-00

In accordance with SRM 51-75-12

Refer to AMM Task 20-21-11-911-001

1 Install the shims:

6 Shim Item (7) Retained at

removal

6 Shim Item (8) Retained at

removal

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

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

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With:

12 Screw EN6115V4-9 Item 6

12 Nut ASNA2536-4 Item 2

NOTE: Install the shims with:

Paste Adhesive -

Liquid Shim

13FGC1 As required

NOTE: Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

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

Top Coat

Polyurethane Grey

Internal Structure

04JME4 As required

And

Primer Epoxy Paint

Corrosion Inhibiting

Structure

04DAB2 As required

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 571178-700-001-001 - Testing

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 25-21-41-400-001

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

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

manhours for the tests are included in the referenced Service Bulletin

subtasks.

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

the installation of the Passenger Seats, refer to AMM Task 25-21-41-400-001.

- Do the test procedure as specified after the installation of the Passenger Seats,

refer to AMM Task 25-21-41-400-001.

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

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

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**CONF 002

(1) Subtask 571178-700-001-001 - Testing

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 25-21-41-400-001

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

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

manhours for the tests are included in the referenced Service Bulletin

subtasks.

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

the installation of the Passenger Seats, refer to AMM Task 25-21-41-400-001.

- Do the test procedure as specified after the installation of the Passenger Seats,

refer to AMM Task 25-21-41-400-001.

**CONF 003

(1) Subtask 571178-700-001-001 - Testing

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 25-21-41-400-001

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

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

manhours for the tests are included in the referenced Service Bulletin

subtasks.

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

the installation of the Passenger Seats, refer to AMM Task 25-21-41-400-001.

- Do the test procedure as specified after the installation of the Passenger Seats,

refer to AMM Task 25-21-41-400-001.

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 571178-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

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

REVISION No.: 01 - May 28/14 Page: 50

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References

Aircraft Maintenance Manual (AMM) Task 25-21-41-400-001

Task 25-28-41-400-001

Task 52-10-00-410-001

Task 53-32-12-400-002

(a) If removed, install hydraulic pipes clamps and them back in initial position.

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

equipment.

(c) Install the floor Panels 242DF, 242CF, 242BF, 241DF, 241CF, 241BF and 241AF,

refer to AMM Task 53-32-12-400-002.

(d) Install the textile floor covering between FR35 and FR36, refer to AMM Task

25-28-41-400-001.

(e) Install the passengers Seats between FR35 and FR36, refer to AMM Task

25-21-41-400-001.

(f) Close the FWD passenger/crew door 831, refer to AMM Task 52-10-00-410-001.

(g) Remove the access platform(s).

(h) Disconnect the aircraft electrical ground-connection.

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

**CONF 002

(1) Subtask 571178-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-21-41-400-001

Task 25-28-41-400-001

Task 52-10-00-410-001

Task 53-32-12-400-002

(a) If removed, install hydraulic pipes clamps and them back in initial position.

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

equipment.

(c) Install the floor Panels 242DF, 242CF, 242BF, 241DF, 241CF, 241BF and 241AF,

refer to AMM Task 53-32-12-400-002.

(d) Install the textile floor covering between FR35 and FR36, refer to AMM Task

25-28-41-400-001.

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

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

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(e) Install the passengers Seats between FR35 and FR36, refer to AMM Task

25-21-41-400-001.

(f) Close the FWD passenger/crew door 831, refer to AMM Task 52-10-00-410-001.

(g) Remove the access platform(s).

(h) Disconnect the aircraft electrical ground-connection.

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

**CONF 003

(1) Subtask 571178-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-21-41-400-001

Task 25-28-41-400-001

Task 52-10-00-410-001

Task 53-32-12-400-002

(a) If removed, install hydraulic pipes clamps and them back in initial position.

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

equipment.

(c) Install the floor Panels 242DF, 242CF, 242BF, 241DF, 241CF, 241BF and 241AF,

refer to AMM Task 53-32-12-400-002.

(d) Install the textile floor covering between FR35 and FR36, refer to AMM Task

25-28-41-400-001.

(e) Install the passengers Seats between FR35 and FR36, refer to AMM Task

25-21-41-400-001.

(f) Close the FWD passenger/crew door 831, refer to AMM Task 52-10-00-410-001.

(g) Remove the access platform(s).

(h) Disconnect the aircraft electrical ground-connection.

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

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

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

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Task 571178-832-802-001 - Special Detailed Inspection of the spar vertical Stringers Radius,

the horizontal Floor Beam Radius and the Fasteners Holes on FR36 - ADDITIONAL WORK

**CONF ALL

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

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

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

THIS:

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

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

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

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

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

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

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

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

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

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

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

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

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

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

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

NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory

by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these

accomplishment instructions are Required for Compliance (RC) and must be done

to comply with the AD. Other paragraphs are recommended and may be deviated

from, done as part of other actions or done with accepted methods different from

those given in the Service Bulletin, as long as the RC paragraphs can be done and

the aircraft can be put back into a serviceable condition.

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

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

compliance times given in this Service Bulletin.

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

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Task Associated Data

**CONF 001

Zone

From 241 to 242

Access

Panel 241AF 241BF 241CF 241DF 242BF 242CF 242DF

Manpower

TOTAL MANHOURS 23.25

ELAPSED TIME (HOURS) 12.75

**CONF 002

Zone

From 241 to 242

Access

Panel 241AF 241BF 241CF 241DF 242BF 242CF 242DF

Manpower

TOTAL MANHOURS 24.25

ELAPSED TIME (HOURS) 13.75

**CONF 003

Zone

From 241 to 242

Access

Panel 241AF 241BF 241CF 241DF 242BF 242CF 242DF

Manpower

TOTAL MANHOURS 23.25

ELAPSED TIME (HOURS) 12.75

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 571178-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-21-11-911-001

Consumable Material List (CML)

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

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

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References

Structural Repair Manual (SRM) 51-40-00

51-42-00

51-43-00

51-44-00

51-75-12

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

Consumable Materials List (CML).

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

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

(d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001.

(e) To torque tighten the standard threaded fasteners, refer to AMM Task

20-21-11-911-001.

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

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

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

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

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

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

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

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

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

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

Part" column.

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

(2) Subtask 571178-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 002

(1) Subtask 571178-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

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

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

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References

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

06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-21-11-911-001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-40-00

51-42-00

51-43-00

51-44-00

51-75-12

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

Consumable Materials List (CML).

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

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

(d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001.

(e) To torque tighten the standard threaded fasteners, refer to AMM Task

20-21-11-911-001.

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

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

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

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

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

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

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

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

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

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

Part" column.

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

(2) Subtask 571178-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

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

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

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**CONF 003

(1) Subtask 571178-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-21-11-911-001

Consumable Material List (CML)

Structural Repair Manual (SRM) 51-40-00

51-42-00

51-43-00

51-44-00

51-75-12

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

Consumable Materials List (CML).

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

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

(d) For the identification of access panels, refer to AMM 06-41-53, Page Block 001.

(e) To torque tighten the standard threaded fasteners, refer to AMM Task

20-21-11-911-001.

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

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

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

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

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

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

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

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

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

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

Part" column.

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

(2) Subtask 571178-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

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

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

Service Bulletin.

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 571178-941-002-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-21-41-000-001

Task 25-28-41-000-001

Task 52-10-00-010-001

Task 53-32-12-000-002

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

configuration before you start a maintenance task:

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

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

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position

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

12-34-24-869-002.

(b) Put an access platform in position at door 831.

(c) Open the FWD passenger/crew door 831, refer to AMM Task 52-10-00-010-001.

(d) Remove the passengers Seats between Frame 35 and Frame 36, refer to AMM

Task 25-21-41-000-001.

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

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

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(e) Remove the textile floor covering between Frame 35 and Frame 36, refer to AMM

Task 25-28-41-000-001.

(f) Remove the floor Panels 242DF, 242CF, 242BF, 241DF, 241CF, 241BF and

241AF, refer to AMM Task 53-32-12-000-002.

(g) If necessary, remove the hydraulic pipes clamps and push the pipes without to

disconnect them in order to facilitate access of the working area .

**CONF 002

(1) Subtask 571178-941-002-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-21-41-000-001

Task 25-28-41-000-001

Task 52-10-00-010-001

Task 53-32-12-000-002

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

configuration before you start a maintenance task:

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

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

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position

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

12-34-24-869-002.

(b) Put an access platform in position at door 831.

(c) Open the FWD passenger/crew door 831, refer to AMM Task 52-10-00-010-001.

(d) Remove the passengers Seats between Frame 35 and Frame 36, refer to AMM

Task 25-21-41-000-001.

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

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

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(e) Remove the textile floor covering between Frame 35 and Frame 36, refer to AMM

Task 25-28-41-000-001.

(f) Remove the floor Panels 242DF, 242CF, 242BF, 241DF, 241CF, 241BF and

241AF, refer to AMM Task 53-32-12-000-002.

(g) If necessary, remove the hydraulic pipes clamps and push the pipes without to

disconnect them in order to facilitate access of the working area .

**CONF 003

(1) Subtask 571178-941-002-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

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

Task 25-21-41-000-001

Task 25-28-41-000-001

Task 52-10-00-010-001

Task 53-32-12-000-002

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

configuration before you start a maintenance task:

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

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

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position

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

12-34-24-869-002.

(b) Put an access platform in position at door 831.

(c) Open the FWD passenger/crew door 831, refer to AMM Task 52-10-00-010-001.

(d) Remove the passengers Seats between Frame 35 and Frame 36, refer to AMM

Task 25-21-41-000-001.

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

REVISION No.: 01 - May 28/14 Page: 60

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(e) Remove the textile floor covering between Frame 35 and Frame 36, refer to AMM

Task 25-28-41-000-001.

(f) Remove the floor Panels 242DF, 242CF, 242BF, 241DF, 241CF, 241BF and

241AF, refer to AMM Task 53-32-12-000-002.

(g) If necessary, remove the hydraulic pipes clamps and push the pipes without to

disconnect them in order to facilitate access of the working area .

**CONF ALL

C. PROCEDURE

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

not been removed the HFEC inspection of the vertical stiffener radius and the

rototest inspection of the holes has not been done during accomplishment

instruction of Service Bulletin No. A320-57-1178 at original issue.

**CONF 001

(1) Subtask 571178-831-004-001 - Remove the fasteners of the spar vertical Stringers

on FR36

Work Zones and Access Panels

Zone Access/Work location

From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel

241DF

Work location Frame 36

To 242 Access Panel 242BF, Panel 242CF, Panel 242DF

Work location Frame 36

Manpower Resources

Manhours 3.00

Minimum number of person 2

Subtask elapsed time 1.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

References

Structural Repair Manual (SRM) 51-42-00

Fig. A-FBCAA

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

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REVISION No.: 01 - May 28/14 Page: 61

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References

Fig. A-FBBAA

Inspection of the Fasteners Holes

Sheet 01

(a) Remove the fasteners of the spar vertical Stringers and the horizontal floor beam.

Refer to Fig. A-FBCAA

In accordance with SRM 51-42-00

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

areas with solvent:

Non Aqueous

Cleaner-General

08BAA9 As required

2 Remove:

12 Screw Item (1) Discard

12 Nut Item (2) Discard

(2) Subtask 571178-832-002-001 - Do High Frequency Eddy Current (HFEC)

Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam

Radius and do a Rototest Inspection of the Fasteners Holes on FR36

Work Zones and Access Panels

Zone Access/Work location

From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel

241DF

Work location Frame 36

To 242 Access Panel 242BF, Panel 242CF, Panel 242DF

Work location Frame 36

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

References

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

51-10-08

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

REVISION No.: 01 - May 28/14 Page: 62

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References

Service Bulletin (SB) A320-57-1017

Fig. A-FBAAA

Inspection Area

Sheet 01

Sheet 02

Fig. A-FBBAA

Inspection of the Fasteners Holes

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FFBAA

Flow Chart - ADDITIONAL WORK

Sheet 01

At the threshold given in PLANNING INFORMATION paragraph E.(2):

Do Special Detailed Inspection of the spar vertical Stringers Radius on Frame 36.

Refer to Fig. A-FBAAA.

Refer to Fig. A-FBBAA.

Refer to Fig. A-FFBAA.

(a) Do High Frequency Eddy Current (HFEC) Inspections of the spar vertical Stringers

Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the

Fasteners Holes on Frame 36:

1 Remove the protective finish from areas to be inspected with:

Non Aqueous

Cleaner-General

08BAA9 As required

2 Do a Rototest Inspection of the fasteners holes of spar vertical Stringers

Radius in center fuselage on Frame 36:

Refer to Fig. A-FBBAA Sheet 01

Refer to NTM 51-10-01

3 Do a High Frequency Eddy Current (HFEC) inspection at the horizontal floor

beam radius of the backside of the spar vertical Stringers radius and do a

HFEC inspection of the front spar vertical Stringers radius in center fuselage

on Frame 36.

Refer to Fig. A-FBAAA Sheet 01

Refer to NTM 51-10-08

a If crack is found in one of inspections:

<1> Contact Airbus and apply further instructions before next flight.

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

REVISION No.: 01 - May 28/14 Page: 63

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SERVICE BULLETIN

b If no crack is found in any inspections:

<1> Apply Service Bulletin No. A320-57-1017.

And

Repeat the inspections at the interval given in PLANNING

INFORMATION paragraph E.(2) in accordance with TASK

571178-832-801 001 Special Detailed Inspection of the spar vertical

Stringers Radius, the horizontal Floor Beam Radius and the

Fasteners Holes on FR36 .

OR

<2> Install the fasteners on the holes to be inspected as described in

SUBTASK 571178-831-006 001 Install the new fasteners of the spar

vertical Stringers on FR36 .

And

Repeat the inspections at the interval given in PLANNING

INFORMATION paragraph E.(2)in accordance with TASK

571178-832-801 001 Special Detailed Inspection of the spar vertical

Stringers Radius, the horizontal Floor Beam Radius and the

Fasteners Holes on FR36 .

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

(3) Subtask 571178-831-006-001 - Install the new fasteners of the spar vertical

Stringers on FR36

Work Zones and Access Panels

Zone Access/Work location

From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel

241DF

Work location Frame 36

To 242 Access Panel 242BF, Panel 242CF, Panel 242DF

Work location Frame 36

Manpower Resources

Manhours 5.00

Minimum number of person 2

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 571178A01R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 EN6115V4-6 12 SCREW

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

REVISION No.: 01 - May 28/14 Page: 64

5

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2536-4 12 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Primer Epoxy Paint

Corrosion Inhibiting

Structure

04DAB2 As required

Top Coat Polyurethane

Grey Internal Structure

04JME4 As required

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Structural Repair Manual (SRM) 51-42-00

51-43-00

51-75-12

Fig. A-FBCAA

Removal/Installation of the Fasteners

Sheet 01

Sheet 02

(a) Install the new fasteners of the spar vertical Stringers and the horizontal floor

beam.

Refer to Fig. A-FBCAA

In accordance with SRM 51-42-00

In accordance with SRM 51-75-12

In accordance with SRM 51-43-00

Refer to AMM Task 20-21-11-911-001

1 Install:

12 Screw EN6115V4-6 Item 1

12 Nut ASNA2536-4 Item 2

NOTE: Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

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

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

REVISION No.: 01 - May 28/14 Page: 65

5

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SERVICE BULLETIN

Top Coat

Polyurethane Grey

Internal Structure

04JME4 As required

And

Primer Epoxy Paint

Corrosion Inhibiting

Structure

04DAB2 As required

**CONF 002

(1) Subtask 571178-831-004-003 - Remove the fasteners and the shims of the spar

vertical Stringers on FR36

Work Zones and Access Panels

Zone Access/Work location

From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel

241DF

Work location Frame 36

To 242 Access Panel 242BF, Panel 242CF, Panel 242DF

Work location Frame 36

Manpower Resources

Manhours 3.00

Minimum number of person 2

Subtask elapsed time 1.50

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

References

Structural Repair Manual (SRM) 51-42-00

Fig. A-FBCAC

Removal/Installation of the Shims and

the Fasteners

Sheet 01

Sheet 02

Fig. A-FBBAA

Inspection of the Fasteners Holes

Sheet 01

(a) Remove the fasteners of the spar vertical Stringers, the shims and the horizontal

floor beam.

Refer to Fig. A-FBCAC

In accordance with SRM 51-42-00

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

REVISION No.: 01 - May 28/14 Page: 66

5

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SERVICE BULLETIN

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

areas with solvent:

Non Aqueous

Cleaner-General

08BAA9 As required

2 Remove the shims:

Refer to figure Fig. A-FBCAC Sheet 01

6 Shim Item (7) Retain

6 Shim Item (8) Retain

Attached with, depending on aircraft configuration:

12 Screw Item (3) Discard

12 Nut Item (2) Discard

Or

12 Screw Item (4) Discard

12 Nut Item (5) Discard

(2) Subtask 571178-832-002-002 - Do High Frequency Eddy Current (HFEC)

Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam

Radius and do a Rototest Inspection of the Fasteners Holes on FR36

Work Zones and Access Panels

Zone Access/Work location

From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel

241DF

Work location Frame 36

To 242 Access Panel 242BF, Panel 242CF, Panel 242DF

Work location Frame 36

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

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

REVISION No.: 01 - May 28/14 Page: 67

5

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SERVICE BULLETIN

References

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

51-10-08

Service Bulletin (SB) A320-57-1017

Fig. A-FBAAB

Inspection Area

Sheet 01

Sheet 02

Fig. A-FBBAA

Inspection of the Fasteners Holes

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FFBAB

Flow Chart - ADDITIONAL WORK

Sheet 01

At the threshold given in PLANNING INFORMATION paragraph E.(2):

Do Special Detailed Inspection of the spar vertical Stringers Radius on Frame 36.

Refer to Fig. A-FBAAB.

Refer to Fig. A-FBBAA.

Refer to Fig. A-FFBAB.

(a) Do High Frequency Eddy Current (HFEC) Inspection of the spar vertical Stringers

Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the

Fasteners Holes on Frame 36:

1 Remove the protective finish from areas to be inspected with:

Non Aqueous

Cleaner-General

08BAA9 As required

2 Do a Rototest Inspection of the fasteners holes of spar vertical Stringers

Radius in center fuselage on Frame 36:

Refer to Fig. A-FBBAA Sheet 01

Refer to NTM 51-10-01

3 Do a High Frequency Eddy Current (HFEC) inspection at the horizontal floor

beam radius of the backside of the spar vertical Stringers radius and do a

HFEC inspection of the front spar vertical Stringers radius in center fuselage

on Frame 36.

Refer to Fig. A-FBAAB Sheet 01

Refer to NTM 51-10-08

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

REVISION No.: 01 - May 28/14 Page: 68

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SERVICE BULLETIN

a If crack is found in one of inspections:

<1> Contact Airbus and apply further instructions before next flight.

b If no crack is found in any inspections:

<1> Oversize the holes of the spar vertical Stringers radius, the shims

and the horizontal floor beam radius as described in SUBTASK

571178-831-005 003 Oversize the holes of the spar vertical

Stringers radius, the horizontal floor Beam and the holes of the

shims on FR36 .

And

Install the fasteners and the shims on the holes to be inspected

as described in SUBTASK 571178-831-006 003 Install the new

fasteners and the shims of the spar vertical Stringers on FR36 .

And

Repeat the inspections at the interval given in PLANNING

INFORMATION paragraph E.(2) in accordance with TASK

571178-832-801 001 Special Detailed Inspection of the spar vertical

Stringers Radius, the horizontal Floor Beam Radius and the

Fasteners Holes on FR36 .

NOTE: For the repetitive Inspections is not necessary to

oversize the holes as the holes are in transition fit.

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

(3) Subtask 571178-831-005-003 - Oversize the holes of the spar vertical Stringers

radius, the horizontal floor Beam and the holes of the shims on FR36

Work Zones and Access Panels

Zone Access/Work location

From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel

241DF

Work location Frame 36

To 242 Access Panel 242BF, Panel 242CF, Panel 242DF

Work location Frame 36

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Structural Repair Manual (SRM) 51-44-00

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

REVISION No.: 01 - May 28/14 Page: 69

5

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SERVICE BULLETIN

References

Fig. A-FBCAC

Removal/Installation of the Shims and

the Fasteners

Sheet 01

Sheet 02

(a) Oversize the holes of the spar vertical Stringers radius, the holes of the shims and

the horizontal floor beam radius.

Refer to Fig. A-FBCAC

In accordance with SRM 51-44-00

1 Depending on aircraft configuration:

a If the holes are in the first oversize diameter:

Drill to the second oversize diameter the holes to the dimensions given in

Fig. A-FBCAC.

OR

b If the holes are in the second oversize diameter:

Drill to the next nominal diameter the holes to the dimensions given in

Fig. A-FBCAC.

(4) Subtask 571178-831-006-003 - Install the new fasteners and the shims of the spar

vertical Stringers on FR36

Work Zones and Access Panels

Zone Access/Work location

From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel

241DF

Work location Frame 36

To 242 Access Panel 242BF, Panel 242CF, Panel 242DF

Work location Frame 36

Manpower Resources

Manhours 5.00

Minimum number of person 2

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 571178A03R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2536-4 12 NUT

3 EN6115V4Y9 12 SCREW

4 EN6115V5-9 12 SCREW

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

REVISION No.: 01 - May 28/14 Page: 70

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

5 ASNA2536-5 12 NUT

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Primer Epoxy Paint

Corrosion Inhibiting

Structure

04DAB2 As required

Top Coat Polyurethane

Grey Internal Structure

04JME4 As required

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

Paste Adhesive - Liquid

Shim

13FGC1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Structural Repair Manual (SRM) 51-42-00

51-43-00

51-75-12

Fig. A-FBCAC

Removal/Installation of the Shims and

the Fasteners

Sheet 01

Sheet 02

(a) Install the new fasteners of the spar vertical Stringers, the shims and the horizontal

floor beam.

Refer to Fig. A-FBCAC

In accordance with SRM 51-42-00

In accordance with SRM 51-43-00

In accordance with SRM 51-75-12

Refer to AMM Task 20-21-11-911-001

1 Install the shims:

6 Shim Item (7) Retained at

removal

6 Shim Item (8) Retained at

removal

NOTE: Install the shims with:

Paste Adhesive -

Liquid Shim

13FGC1 As required

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

REVISION No.: 01 - May 28/14 Page: 71

5

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SERVICE BULLETIN

With, depending on aircraft configuration:

12 Screw EN6115V4Y9 Item 3

12 Nut ASNA2536-4 Item 2

Or

12 Screw EN6115V5-9 Item 4

12 Nut ASNA2536-5 Item 5

NOTE: Install the shims with:

Paste Adhesive -

Liquid Shim

13FGC1 As required

NOTE: Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

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

Top Coat

Polyurethane Grey

Internal Structure

04JME4 As required

And

Primer Epoxy Paint

Corrosion Inhibiting

Structure

04DAB2 As required

**CONF 003

(1) Subtask 571178-831-004-002 - Remove the fasteners and the shims of the spar

vertical Stringers on FR36

Work Zones and Access Panels

Zone Access/Work location

From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel

241DF

Work location Frame 36

To 242 Access Panel 242BF, Panel 242CF, Panel 242DF

Work location Frame 36

Manpower Resources

Manhours 3.00

Minimum number of person 2

Subtask elapsed time 1.50

Skills AIRFRAME

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

REVISION No.: 01 - May 28/14 Page: 72

5

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SERVICE BULLETIN

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) 51-42-00

Fig. A-FBCAB

Removal/Installation of the Shims and

the Fasteners

Sheet 01

Sheet 02

Fig. A-FBBAA

Inspection of the Fasteners Holes

Sheet 01

(a) Remove the fasteners of the spar vertical Stringers, the shims and the horizontal

floor beam.

Refer to Fig. A-FBCAB

In accordance with SRM 51-42-00

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

areas with solvent:

Non Aqueous

Cleaner-General

08BAA9 As required

2 Remove the shims:

Refer to figure Fig. A-FBCAB Sheet 01

6 Shim Item (7) Retain

6 Shim Item (8) Retain

Attached with:

12 Screw Item (6) Discard

12 Nut Item (2) Discard

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

REVISION No.: 01 - May 28/14 Page: 73

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SERVICE BULLETIN

(2) Subtask 571178-832-002-003 - Do High Frequency Eddy Current (HFEC)

Inspections of the spar vertical Stringers Radius and the horizontal Floor Beam

Radius and do a Rototest Inspection of the Fasteners Holes on FR36

Work Zones and Access Panels

Zone Access/Work location

From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel

241DF

Work location Frame 36

To 242 Access Panel 242BF, Panel 242CF, Panel 242DF

Work location Frame 36

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Non Aqueous CleanerGeneral08BAA9 As required

References

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

51-10-08

Fig. A-FRAAA

Inspection Report

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-FBBAA

Inspection of the Fasteners Holes

Sheet 01

Fig. A-FBAAB

Inspection Area

Sheet 01

Sheet 02

Fig. A-FFBAB

Flow Chart - ADDITIONAL WORK

Sheet 01

At the threshold given in PLANNING INFORMATION paragraph E.(2):

Do Special Detailed Inspection of the spar vertical Stringers Radius on Frame 36.

Refer to Fig. A-FBAAB.

Refer to Fig. A-FBBAA.

Refer to Fig. A-FFBAB.

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

REVISION No.: 01 - May 28/14 Page: 74

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SERVICE BULLETIN

(a) Do High Frequency Eddy Current (HFEC) Inspection of the spar vertical Stringers

Radius and the horizontal Floor Beam Radius and do a Rototest Inspection of the

Fasteners Holes on Frame 36:

1 Remove the protective finish from areas to be inspected with:

Non Aqueous

Cleaner-General

08BAA9 As required

2 Do a Rototest Inspection of the fasteners holes of spar vertical Stringers

Radius in center fuselage on Frame 36:

Refer to Fig. A-FBBAA Sheet 01

Refer to NTM 51-10-01

3 Do a High Frequency Eddy Current (HFEC) inspection at the horizontal floor

beam radius of the backside of the spar vertical Stringers radius and do a

HFEC inspection of the front spar vertical Stringers radius in center fuselage

on Frame 36.

Refer to Fig. A-FBAAB Sheet 01

Refer to NTM 51-10-08

a If crack is found in one of inspections:

<1> Contact Airbus and apply further instructions before next flight.

b If no crack is found in any inspections:

<1> Install the fasteners and the shims on the holes to be inspected

as described in SUBTASK 571178-831-006 002 Install the new

fasteners and the shims of the spar vertical Stringers on FR36 .

And

Repeat the inspections at the interval given in PLANNING

INFORMATION paragraph E.(2) in accordance with TASK

571178-832-801 001 Special Detailed Inspection of the spar vertical

Stringers Radius, the horizontal Floor Beam Radius and the

Fasteners Holes on FR36 .

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

(3) Subtask 571178-831-006-002 - Install the new fasteners and the shims of the spar

vertical Stringers on FR36

Work Zones and Access Panels

Zone Access/Work location

From 241 Access Panel 241AF, Panel 241BF, Panel 241CF, Panel

241DF

Work location Frame 36

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

REVISION No.: 01 - May 28/14 Page: 75

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To 242 Access Panel 242BF, Panel 242CF, Panel 242DF

Work location Frame 36

Manpower Resources

Manhours 5.00

Minimum number of person 2

Subtask elapsed time 2.50

Skills AIRFRAME

Material necessary to do the job

Kit 571178A02R01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 ASNA2536-4 12 NUT

6 EN6115V4-9 12 SCREW

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Primer Epoxy Paint

Corrosion Inhibiting

Structure

04DAB2 As required

Top Coat Polyurethane

Grey Internal Structure

04JME4 As required

Polysulfide Sealant-General

Purpose Brushable

06AAA1 As required

Paste Adhesive - Liquid

Shim

13FGC1 As required

References

Aircraft Maintenance Manual (AMM) Task 20-21-11-911-001

Structural Repair Manual (SRM) 51-42-00

51-43-00

51-75-12

Fig. A-FBCAB

Removal/Installation of the Shims and

the Fasteners

Sheet 01

Sheet 02

(a) Install the new fasteners of the spar vertical Stringers, the shims and the horizontal

floor beam.

Refer to Fig. A-FBCAB

In accordance with SRM 51-42-00

In accordance with SRM 51-43-00

In accordance with SRM 51-75-12

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

REVISION No.: 01 - May 28/14 Page: 76

5

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SERVICE BULLETIN

Refer to AMM Task 20-21-11-911-001

1 Install the shims:

6 Shim Item (7) Retained at

removal

6 Shim Item (8) Retained at

removal

NOTE: Install the shims with:

Paste Adhesive -

Liquid Shim

13FGC1 As required

With:

12 Screw EN6115V4-9 Item 6

12 Nut ASNA2536-4 Item 2

NOTE: Install the shims with:

Paste Adhesive -

Liquid Shim

13FGC1 As required

NOTE: Wet install the fasteners with:

Polysulfide SealantGeneral Purpose

Brushable

06AAA1 As required

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

Top Coat

Polyurethane Grey

Internal Structure

04JME4 As required

And

Primer Epoxy Paint

Corrosion Inhibiting

Structure

04DAB2 As required

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 571178-700-002-001 - Testing

Manpower Resources

Skills AIRFRAME

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

REVISION No.: 01 - May 28/14 Page: 77

5

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 25-21-41-400-001

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

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

manhours for the tests are included in the referenced Service Bulletin

subtasks.

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

the installation of the Passenger Seats, refer to AMM Task 25-21-41-400-001.

- Do the test procedure as specified after the installation of the Passenger Seats,

refer to AMM Task 25-21-41-400-001.

**CONF 002

(1) Subtask 571178-700-002-001 - Testing

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 25-21-41-400-001

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

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

manhours for the tests are included in the referenced Service Bulletin

subtasks.

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

the installation of the Passenger Seats, refer to AMM Task 25-21-41-400-001.

- Do the test procedure as specified after the installation of the Passenger Seats,

refer to AMM Task 25-21-41-400-001.

**CONF 003

(1) Subtask 571178-700-002-001 - Testing

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 25-21-41-400-001

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

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

manhours for the tests are included in the referenced Service Bulletin

subtasks.

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

the installation of the Passenger Seats, refer to AMM Task 25-21-41-400-001.

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

REVISION No.: 01 - May 28/14 Page: 78

5

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SERVICE BULLETIN

- Do the test procedure as specified after the installation of the Passenger Seats,

refer to AMM Task 25-21-41-400-001.

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 571178-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-21-41-400-001

Task 25-28-41-400-001

Task 52-10-00-410-001

Task 53-32-12-400-002

(a) If removed, install hydraulic pipes clamps and them back in initial position.

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

equipment.

(c) Install the floor Panels 242DF, 242CF, 242BF, 241DF, 241CF, 241BF and 241AF,

refer to AMM Task 53-32-12-400-002.

(d) Install the textile floor covering between Frame 35 and Frame 36, refer to AMM

Task 25-28-41-400-001.

(e) Install the passengers Seats between Frame 35 and Frame 36, refer to AMM Task

25-21-41-400-001.

(f) Close the FWD passenger/crew door 831, refer to AMM Task 52-10-00-410-001.

(g) Remove the access platform(s).

(h) Disconnect the aircraft electrical ground-connection.

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

**CONF 002

(1) Subtask 571178-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

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

REVISION No.: 01 - May 28/14 Page: 79

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References

Aircraft Maintenance Manual (AMM) Task 25-21-41-400-001

Task 25-28-41-400-001

Task 52-10-00-410-001

Task 53-32-12-400-002

(a) If removed, install hydraulic pipes clamps and them back in initial position.

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

equipment.

(c) Install the floor Panels 242DF, 242CF, 242BF, 241DF, 241CF, 241BF and 241AF,

refer to AMM Task 53-32-12-400-002.

(d) Install the textile floor covering between Frame 35 and Frame 36, refer to AMM

Task 25-28-41-400-001.

(e) Install the passengers Seats between Frame 35 and Frame 36, refer to AMM Task

25-21-41-400-001.

(f) Close the FWD passenger/crew door 831, refer to AMM Task 52-10-00-410-001.

(g) Remove the access platform(s).

(h) Disconnect the aircraft electrical ground-connection.

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

**CONF 003

(1) Subtask 571178-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-21-41-400-001

Task 25-28-41-400-001

Task 52-10-00-410-001

Task 53-32-12-400-002

(a) If removed, install hydraulic pipes clamps and them back in initial position.

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

equipment.

(c) Install the floor Panels 242DF, 242CF, 242BF, 241DF, 241CF, 241BF and 241AF,

refer to AMM Task 53-32-12-400-002.

(d) Install the textile floor covering between Frame 35 and Frame 36, refer to AMM

Task 25-28-41-400-001.

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

REVISION No.: 01 - May 28/14 Page: 80

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(e) Install the passengers Seats between Frame 35 and Frame 36, refer to AMM Task

25-21-41-400-001.

(f) Close the FWD passenger/crew door 831, refer to AMM Task 52-10-00-410-001.

(g) Remove the access platform(s).

(h) Disconnect the aircraft electrical ground-connection.

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

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

REVISION No.: 01 - May 28/14 Page: 81

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**CONF 001

DATUM

FWD

FR36

INSPECTION AREA

NOTE:

A

A

A A

B

FR36

FR42

A

VIEW LOOKING AFT

FLOOR BEAM

B

B

B

B

B

B

A

Z240

N_SB_571178_5_BAAA_01_04

Figure A-FBAAA - Sheet 01

Inspection Area

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

REVISION No.: 01 - May 28/14 Page: 82

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**CONF 001

DATUM

FWD

FR36

INSPECTION AREA

NOTE:

A A

VIEW LOOKING FWD

FLOOR BEAM

B B

B

B

N_SB_571178_5_BAAA_02_00

Figure A-FBAAA - Sheet 02

Inspection Area

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

REVISION No.: 01 - May 28/14 Page: 83

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**CONF 002 thru 003

INSPECTION AREA

NOTE:

A

A

B

FR36

FR42

A

VIEW LOOKING AFT

B

B

B

B

B

B

A

Z240

N_SB_571178_5_BAAB_01_04

Figure A-FBAAB - Sheet 01

Inspection Area

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

REVISION No.: 01 - May 28/14 Page: 84

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**CONF 002 thru 003

DATUM

FWD

FR36

INSPECTION AREA

NOTE:

A A

VIEW LOOKING FWD

FLOOR BEAM

B B

B

B

01 REMOVE THE SHIMS AND ASSOCIATED FASTENERS TO PERFORM THE HFEC INSPECTIONS

OF FLOOR BEAM AND VERTICAL STIFFENER RADIUS

01

N_SB_571178_5_BAAB_02_00

Figure A-FBAAB - Sheet 02

Inspection Area

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

REVISION No.: 01 - May 28/14 Page: 85

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**CONF ALL

DATUM

FWD

FR36

NOTE:

A

A

A A

B

FR36

FR42

A

VIEW LOOKING AFT

FLOOR BEAM

B

B

B

B

B

B

A

Z240

FASTENERS HOLES

TO BE INSPECTED

FASTENERS HOLES TO BE INSPECTED

N_SB_571178_5_BBAA_01_00

Figure A-FBBAA - Sheet 01

Inspection of the Fasteners Holes

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

REVISION No.: 01 - May 28/14 Page: 86

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**CONF 001

DATUM

FWD

FR36

A

A

A A B

FR36

FR42

A

VIEW LOOKING AFT

FLOOR BEAM

B

B

B

B

B

B

A

Z240

N_SB_571178_5_BCAA_01_01

Figure A-FBCAA - Sheet 01

Removal/Installation of the Fasteners

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

REVISION No.: 01 - May 28/14 Page: 87

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SERVICE BULLETIN

**CONF 001

HOLE ITEM PN DESCRIPTION REMARKS SYMBOL

1

2

SCREW

ASNA2536−4 NUT

(1) EN6115V4−6

(2)

NOTE:

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

01

02

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

AND APPLY PROTECTIVE FINISH WITH MAT. No 04DAB2 N_SB_571178_5_BCAA_02_01

Figure A-FBCAA - Sheet 02

Removal/Installation of the Fasteners

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

REVISION No.: 01 - May 28/14 Page: 88

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**CONF 003

FR36 DATUM

A

A

A A

B

FR36

FR42

A

VIEW LOOKING AFT

FLOOR BEAM

B

B

B

B

B

B

A

Z240

DATUM FR36

FLOOR BEAM

B B

B

B

(7) 01 01 (8)

01

NOTE:

INSTALL THE SHIMS AND WITH LIQUID SHIM MAT. No 13FGC1 (7) (8)

FWD FWD

N_SB_571178_5_BCAB_01_02

Figure A-FBCAB - Sheet 01

Removal/Installation of the Shims and the Fasteners

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

REVISION No.: 01 - May 28/14 Page: 89

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**CONF 003

HOLE ITEM PN DESCRIPTION REMARKS SYMBOL

6

2

SCREW

ASNA2536−4 NUT

(6) EN6115V4−9

(2)

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

03

02

AND APPLY PROTECTIVE FINISH WITH MAT. No 04DAB2

NOTE:

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

N_SB_571178_5_BCAB_02_01

Figure A-FBCAB - Sheet 02

Removal/Installation of the Shims and the Fasteners

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

REVISION No.: 01 - May 28/14 Page: 90

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SERVICE BULLETIN

**CONF 002

DATUM

FWD

FR36

A

A

A A

B

FR36

FR42

A

VIEW LOOKING AFT

FLOOR BEAM

B

B

B

B

B

B

A

Z240

DATUM FR36

FLOOR BEAM

B B

FWD

B

B

(7) 01 01 (8)

01 INSTALL THE SHIMS AND WITH LIQUID SHIM MAT. No 13FGC1 (7) (8)

NOTE:

N_SB_571178_5_BCAC_01_02

Figure A-FBCAC - Sheet 01

Removal/Installation of the Shims and the Fasteners

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

REVISION No.: 01 - May 28/14 Page: 91

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SERVICE BULLETIN

**CONF 002

HOLE ITEM PN DESCRIPTION REMARKS SYMBOL

3

2

SCREW

ASNA2536−4 NUT

(3) EN6115V4Y9

(2)

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

SECOND OVERSIZE

FASTENER

IN TRANSITION

FIT

FINAL HOLE DIAMETER

7.102 mm

(0.280 in)

7.141 mm

(0.281 in)

MIN MAX

AND APPLY PROTECTIVE FINISH WITH MAT. No 04DAB2

4

5

SCREW

ASNA2536−5 NUT

(4) EN6115V5−9

(5)

7.900 mm

(0.311 in)

7.940 mm

(0.312 in)

NEXT NOMINAL 

DIAMETER IN

TRANSITION FIT

NOTE:

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

03

02

03

02

N_SB_571178_5_BCAC_02_02

Figure A-FBCAC - Sheet 02

Removal/Installation of the Shims and the Fasteners

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

REVISION No.: 01 - May 28/14 Page: 92

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**CONF 001

QUESTION

ACTION

FINDING

NO CRACK FOUND YES

REFER TO TASK 571178−832−801−001

CONTACT AIRBUS AND

APPLY FURTHER

APPLY SERVICE

BULLETIN No A320−57−1017

−OF THE FASTENERS HOLES OF FRONT SPAR VERTICAL STRINGERS ON FRAME 36

−OF THE HORIZONTAL FLOOR BEAM RADIUS ON FRAME 36

DO A SPECIAL DETAILED INSPECTION :

−OF FRONT SPAR VERTICAL STRINGERS RADIUS ON FRAME 36

INSTRUCTIONS BEFORE

NEXT FLIGHT

OR

REPEAT THE INSPECTION AT

THE INTERVAL GIVEN IN THE TABLE 1

OF THE PLANNING INFORMATION

PARAGRAPH E.(2)

REFER TO TASK 571178−832−801−001

REPEAT THE INSPECTION AT

THE INTERVAL GIVEN IN THE TABLE 1

OF THE PLANNING INFORMATION

PARAGRAPH E.(2)

REFER TO TASK 571178−832−801−001

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

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

N_SB_571178_5_FAAA_01_04

Figure A-FFAAA - Sheet 01

Flow Chart

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

REVISION No.: 01 - May 28/14 Page: 93

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**CONF 002 thru 003

NO CRACK FOUND YES

CONTACT AIRBUS AND

APPLY FURTHER

REPEAT THE INSPECTION AT

THE INTERVAL GIVEN IN THE

TABLE 1 OF THE PLANNING INFORMATION

PARAGRAPH E.(2)

REFER TO TASK 571178−832−801−001

INSTRUCTIONS BEFORE

NEXT FLIGHT

QUESTION

ACTION

FINDING

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

REFER TO TASK 571178−832−801−001

−OF THE FASTENERS HOLES OF FRONT SPAR VERTICAL STRINGERS ON FRAME 36

−OF THE HORIZONTAL FLOOR BEAM RADIUS ON FRAME 36

DO A SPECIAL DETAILED INSPECTION :

−OF FRONT SPAR VERTICAL STRINGERS RADIUS ON FRAME 36

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

N_SB_571178_5_FAAB_01_04

Figure A-FFAAB - Sheet 01

Flow Chart

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

REVISION No.: 01 - May 28/14 Page: 94

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**CONF 001

QUESTION

ACTION

FINDING

NO CRACK FOUND YES

REFER TO TASK 571178−832−802−001

CONTACT AIRBUS AND

APPLY FURTHER

APPLY SERVICE

BULLETIN No A320−57−1017

−OF THE FASTENERS HOLES OF FRONT SPAR VERTICAL STRINGERS ON FRAME 36

−OF THE HORIZONTAL FLOOR BEAM RADIUS ON FRAME 36

DO A SPECIAL DETAILED INSPECTION :

−OF FRONT SPAR VERTICAL STRINGERS RADIUS ON FRAME 36

INSTRUCTIONS BEFORE

NEXT FLIGHT

OR

REPEAT THE INSPECTION AT

THE INTERVAL GIVEN IN THE TABLE 2

OF THE PLANNING INFORMATION

PARAGRAPH E.(2)

REFER TO TASK 571178−832−801−001

REPEAT THE INSPECTION AT

THE INTERVAL GIVEN IN THE TABLE 2

OF THE PLANNING INFORMATION

PARAGRAPH E.(2)

REFER TO TASK 571178−832−801−001

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

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

N_SB_571178_5_FBAA_01_01

Figure A-FFBAA - Sheet 01

Flow Chart - ADDITIONAL WORK

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

REVISION No.: 01 - May 28/14 Page: 95

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**CONF 002 thru 003

NO CRACK FOUND YES

CONTACT AIRBUS AND

APPLY FURTHER

REPEAT THE INSPECTION AT

THE INTERVAL GIVEN IN THE

TABLE 2 OF THE PLANNING INFORMATION

PARAGRAPH E.(2)

REFER TO TASK 571178−832−801−001

INSTRUCTIONS BEFORE

NEXT FLIGHT

QUESTION

ACTION

FINDING

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN

REFER TO TASK 571178−832−802−001

−OF THE FASTENERS HOLES OF FRONT SPAR VERTICAL STRINGERS ON FRAME 36

−OF THE HORIZONTAL FLOOR BEAM RADIUS ON FRAME 36

DO A SPECIAL DETAILED INSPECTION :

−OF FRONT SPAR VERTICAL STRINGERS RADIUS ON FRAME 36

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

N_SB_571178_5_FBAB_01_01

Figure A-FFBAB - Sheet 01

Flow Chart - ADDITIONAL WORK

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

REVISION No.: 01 - May 28/14 Page: 96

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**CONF ALL

FR36

FR42

INSPECTION REPORT

SERVICE BULLETIN No :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−57−1178

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES4

PAX DOORS − FUSELAGE (SA/LA) − WINDOWS −

INSPECTION METHOD :

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

SPECIAL DETAILED E−mail : structure.sbinspectionresult@airbus.com

INSPECTION FAX +33 (0)5 61 93 36 14

CENTER WING BOX (SA/LA)

A

INSPECTION AREA

NOTE:

A

A

B

ZONE 1 ZONE 2

6 5 4

3

2 1

VIEW LOOKING AFT

B

B

B

B

B

B

FASTENERS HOLES TO BE INSPECTED 

N_SB_571178_5_RAAA_01_04

Figure A-FRAAA - Sheet 01

Inspection Report

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

REVISION No.: 01 - May 28/14 Page: 97

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**CONF ALL

INSPECTION REPORT

SERVICE BULLETIN No :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−57−1178

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES4

PAX DOORS − FUSELAGE (SA/LA) − WINDOWS −

INSPECTION METHOD :

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

SPECIAL DETAILED E−mail : structure.sbinspectionresult@airbus.com

INSPECTION FAX +33 (0)5 61 93 36 14

CENTER WING BOX (SA/LA)

DATUM

FWD

FR36

A A VIEW LOOKING FWD

FLOOR BEAM

B B

B

B

ZONE 2 ZONE 1

INSPECTION AREA

NOTE:

FASTENERS HOLES TO BE INSPECTED 

FASTENERS HOLES

TO BE INSPECTED 

N_SB_571178_5_RAAA_02_03

Figure A-FRAAA - Sheet 02

Inspection Report

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

REVISION No.: 01 - May 28/14 Page: 98

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**CONF ALL

YES NO

NUMBER CRACK

1

2

3

4

5

6

INSPECTION REPORT

SERVICE BULLETIN No :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−57−1178

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES4

PAX DOORS − FUSELAGE (SA/LA) − WINDOWS −

INSPECTION METHOD :

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

SPECIAL DETAILED E−mail : structure.sbinspectionresult@airbus.com

INSPECTION

HF EDDY CURRENT

INSPECTION

FRONT SPAR

VERTICAL

STRINGERS

FAX +33 (0)5 61 93 36 14

CENTER WING BOX (SA/LA)

YES NO

CRACK

VERTICAL STRINGERS SIDE

FRONT SPAR

BEAM SIDE

FLOOR

N_SB_571178_5_RAAA_03_01

Figure A-FRAAA - Sheet 03

Inspection Report

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

REVISION No.: 01 - May 28/14 Page: 99

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SERVICE BULLETIN

**CONF ALL

YES NO

NUMBER CRACK

1

2

3

4

5

6

INSPECTION REPORT

SERVICE BULLETIN No :

A/C MSN :

FLIGHT CYCLES :

FLIGHT HOURS :

A320−57−1178

DATE OF INSPECTION :

RETURN TO :

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES4

PAX DOORS − FUSELAGE (SA/LA) − WINDOWS −

INSPECTION METHOD :

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

SPECIAL DETAILED E−mail : structure.sbinspectionresult@airbus.com

INSPECTION

ROTOTEST

INSPECTION

FRONT SPAR

VERTICAL

STRINGERS

FAX +33 (0)5 61 93 36 14

CENTER WING BOX (SA/LA)

YES NO

CRACK

ZONE 1 HOLE ZONE 2 HOLE

N_SB_571178_5_RAAA_04_00

Figure A-FRAAA - Sheet 04

Inspection Report

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

REVISION No.: 01 - May 28/14 Page: 100

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SERVICE BULLETIN

Appendix 01 - Elapsed Time Assumption

**CONF ALL

For an explanation of the manhours and elapsed time, refer to the following Gantt Chart.

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

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

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Appendix 01 - Elapsed Time Assumption

**CONF 002

ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A320−57−1178

STEPS

MH

ET/S:

PER

MANHOURS

ELAPSED TIME PER STEP

NUMBER OF PERSONS

01

02

:

:

SB ELAPSED TIME

(HOURS)

0 2 5 7 9

GET ACCESS

DO HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTIONS OF THE SPAR VERTICAL STRINGERS

RADIUS AND THE HORIZONTAL FLOOR BEAM RADIUS AND DO A ROTOTEST INSPECTION OF 

OVERSIZE THE HOLES OF THE SPAR VERTICAL STRINGERS RADIUS,

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

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

TEST

CLOSE−UP

12 13

MH ET/S

6.00 3.00

PER

2

5.00 2.50 2

3.00 1.50 2

1.00 1 1.00

7.00 3.50 2

TOTAL MANHOURS

SB ELAPSED TIME

24.25

13.75

THIS CHART IS ONLY A PROPOSAL.

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM.

01

02

NOTE:

IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS

ARE NOT REFLECTED IN THIS GANTT CHART.

THE FASTENERS HOLES ON FR36

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

1 3 4 6 8 10 11 14

2.00 2.00 1

0.25 0.25 1

N_SB_571178_5_AAAA_01_02

Figure A-FAAAA - Sheet 01

Gantt Chart

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

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

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SERVICE BULLETIN

Appendix 01 - Elapsed Time Assumption

**CONF 003

ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A320−57−1178

STEPS

MH

ET/S:

PER

MANHOURS

ELAPSED TIME PER STEP

NUMBER OF PERSONS

01

02

:

:

SB ELAPSED TIME

(HOURS)

0 2 5 7 9

GET ACCESS

DO HIGH FREQUENCY EDDY CURRENT (HFEC) INSPECTIONS OF THE SPAR VERTICAL STRINGERS

RADIUS AND THE HORIZONTAL FLOOR BEAM RADIUS AND DO A ROTOTEST INSPECTION OF 

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

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

TEST

CLOSE−UP

12 13

MH ET/S

6.00 3.00

PER

2

5.00 2.50 2

3.00 1.50 2

7.00 3.50 2

TOTAL MANHOURS

SB ELAPSED TIME

23.25

12.75

THIS CHART IS ONLY A PROPOSAL.

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM.

01

02

NOTE:

IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS

ARE NOT REFLECTED IN THIS GANTT CHART.

THE FASTENERS HOLES ON FR36

1 3 4 6 8 10 11 14

2.00 2.00 1

0.25 0.25 1

N_SB_571178_5_AAAC_01_01

Figure A-FAAAC - Sheet 01

Gantt Chart

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

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

5

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@A318/A319/A320/A321

SERVICE BULLETIN

Appendix 01 - Elapsed Time Assumption

**CONF 001

ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A320−57−1178

GET ACCESS

MH ET/S

TOTAL MANHOURS

SB ELAPSED TIME

23.25

12.75

STEPS

6.00 3.00

0

REMOVE THE FASTENERS OF THE SPAR

3.00 1.50

2.00 2.00

5.00 2.50

TEST 0.25 0.25

CLOSE−UP 7.00 3.50

MH

ET/S:

PER

MANHOURS

ELAPSED TIME PER STEP

NUMBER OF PERSONS

01

02

THIS CHART IS ONLY A PROPOSAL

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM

01

02

NOTE:

PER

2

2

1

2

1

2

:

:

SB ELAPSED TIME

(HOURS)

2 4 6 8

IF A VSB IS INVOLVED THE ASSOCIATED MANHOURS

ARE NOT REFLECTED IN THIS GANTT CHART

VERTICAL STRINGERS ON FR36

DO HIGH FREQUENSY EDDY CURRENT

(HFEC) INSPECTION OF THE SPAR

INSTALL THE NEW FASTENERS OF THE

SPAR VERTICAL STRINGERS ON FR36

VERTICAL STRINGERS RADIUS AND THE

10 12 14

DO A ROTOTEST INSPECTION OF THE

FASTENERS HOLES ON FR36

HORIZONTAL FLOOR BEAM RADIUS AND

N_SB_571178_5_AAAB_01_01

Figure A-FAAAB - Sheet 01

Gantt Chart

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

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

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A318/A319/A320/A321

SERVICE BULLETIN

REPORTING SHEET

TITLE: WINGS - INSPECTION OF FRONT SPAR VERTICAL STRINGERS

MODIFICATION No.: None

Please complete the appropriate item (A or B):

A - SB WILL BE embodied YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to

next normal revision or prior to SB embodiment, please indicate required service(s):

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational

documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With

the next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.

- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

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

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

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SERVICE BULLETIN

QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data

that you provide us will be used to analyse areas of difficulties and to take corrective action to further

improve the quality of our Service Bulletins.

We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

X Reason X List of Materials Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

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

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

5

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