@A318/A319/A320/A321

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 53

TITLE: FUSELAGE - CONE/REAR FUSELAGE - REPLACE CLIPS,

SHEARWEBS AND ANGLES IN SECTION 19 AT FR 72 AND FR 74

MODIFICATION No.: 153833K16120

This page transmits Revision No.03 of Service Bulletin No.A320-53-1266

ADDITIONAL WORK

**CONF ALL

No additional work is required by this revision for aircraft modified by any previous issue.

REASON

Revision No. 03 issued to:

- update the Accomplishment Timescale in the COMPLIANCE paragraph

- add Kit D11 for new Config 004

- add aircraft with the Manufacturer Serial Number (MSN) 0202, 0209, 0216, 0267-0269, 0346 and

0382 to the effectivity of this Service Bulletin

- remove aircraft with the MSN 0147 from the effectivity of this Service Bulletin

- add ALS in PUBLICATION AFFECTED paragraph.

CHANGES

FRONT MATTER

FUSELAGE - CONE/REAR FUSELAGE -

REPLACE CLIPS, SHEARWEBS AND

ANGLES IN SECTION 19 AT FR 72 AND

FR 74

CONFIGURATION UPDATED R

SUMMARY

MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE ADDED N

MANPOWER MANPOWER ADDED N

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 1

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

Configuration definition CONFIGURATION LIST UPDATED R

CONF 002 CONFIGURATION DEFINITION UPDATED

CONFIGURATION DESCRIPTION UPDATED

R

CONF 003 CONFIGURATION DEFINITION UPDATED

CONFIGURATION DESCRIPTION UPDATED

R

CONF 004 CONFIGURATION ADDED N

Material Effectivity MATERIAL EFFECTIVITY ADDED N

DESCRIPTION DESCRIPTION UPDATED R

COMPLIANCE

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED R

MANPOWER MANPOWER ADDED N

WEIGHT AND BALANCE CONFIGURATION UPDATED R

Minor editorial or document structure change R

Minor editorial or document structure change R

REFERENCES REFERENCED DOCUMENTATION ADDED N

PUBLICATION AFFECTED PUBLICATIONS AFFECTED UPDATED R

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY

Procurement Addresses PROCUREMENT ADDRESSES UPDATED

MATERIAL SET UPDATED

R

LIST OF COMPONENTS LIST OF COMPONENTS UPDATED R

Kit 531266D11R02 PART MATERIAL SET ADDED N

Kit 531266D14R00 PART MATERIAL SET UPDATED

QUANTITY UPDATED

R

ACCOMPLISHMENT INSTRUCTIONS

TASK 531266- 831-848-001-Modification TASK SOLUTION UPDATED

NOTE UPDATED

R

Task associated data - 004 TASK ASSOCIATED DATA ADDED N

Subtask 531266-910-201-001 SUBTASK SOLUTION ADDED N

Subtask 531266-839-201-001 SUBTASK SOLUTION ADDED N

Subtask 531266-941-201-001 SUBTASK SOLUTION ADDED N

Subtask 531266-020-203-003 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

R

Subtask 531266-420-203-003 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

MATERIAL LIST UPDATED

R

Subtask 531266-020-204-003 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

R

Subtask 531266-020-201-004 SUBTASK SOLUTION ADDED N

Subtask 531266-420-201-004 SUBTASK SOLUTION ADDED N

Subtask 531266-020-208-004 SUBTASK SOLUTION ADDED N

Subtask 531266-420-202-004 SUBTASK SOLUTION ADDED N

Subtask 531266-020-203-004 SUBTASK SOLUTION ADDED N

Subtask 531266-420-203-004 SUBTASK SOLUTION ADDED N

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 2

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SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 531266-020-204-004 SUBTASK SOLUTION ADDED N

Subtask 531266-420-204-004 SUBTASK SOLUTION ADDED N

Subtask 531266-700-201-001 SUBTASK SOLUTION ADDED N

Subtask 531266-942-201-001 SUBTASK SOLUTION UPDATED R

Subtask 531266-942-201-001 SUBTASK SOLUTION UPDATED R

Subtask 531266-942-201-001 SUBTASK SOLUTION UPDATED R

Subtask 531266-942-201-001 SUBTASK SOLUTION ADDED N

Fig. A-GBBAE FIGURE SOLUTION ADDED N

Fig. A-GBBAE Sheet 01 SHEET ADDED N

Fig. A-GBBAE Sheet 02 SHEET ADDED N

Fig. A-GBBAE Sheet 03 SHEET ADDED N

Fig. A-GBBAE Sheet 04 SHEET ADDED N

Fig. A-GBCAE FIGURE SOLUTION ADDED N

Fig. A-GBCAE Sheet 01 SHEET ADDED N

Fig. A-GBCAE Sheet 02 SHEET ADDED N

Fig. A-GBCAE Sheet 03 SHEET ADDED N

Fig. A-GBCAE Sheet 04 SHEET ADDED N

Fig. A-GBDAA

Fig. A-GBDAA Sheet 01 SHEET UPDATED R

Fig. A-GBDAB

Fig. A-GBDAB Sheet 01 SHEET UPDATED R

Fig. A-GBDAD

Fig. A-GBDAD Sheet 01 SHEET UPDATED R

Fig. A-GBDAE FIGURE SOLUTION ADDED N

Fig. A-GBDAE Sheet 01 SHEET ADDED N

FILING INSTRUCTIONS

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

Replace the complete document.

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

HISTORY OF PREVIOUS REVISIONS

Revision No.01 is issued to incorporate the results from the Service Bulletin validation and to extend the

effectivity. The defect reports as described in TA-SEMBN-2013-867945 have been integrated.

This Service Bulletin has been validated on A320 aircraft with Manufacturer Serial Number (MSN) 0401.

Revision No. 02 issued to:

change the compliance of this Service Bulletin to Mandatory

remove UAL aircraft from the SB applicability due to the Extended Service Goal (ESG) flexibility which

postpones the structure reinforcement requirement from 60000 Flight Hours (FH) up to 96000 FH,

without exceeding 48000 Flight Cycles (FC).

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 3

6

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@A318/A319/A320/A321

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Kit D13 cancelled and kit D14 added

update the aircraft effectivity.

REVISION SEQUENCE

ORIGINAL: Jan 11/13

REVISION No. : 01 - Jun 20/13

REVISION No. : 02 - Aug 13/14

REVISION No. : 03 - May 07/15

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 4

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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: 53

TITLE: FUSELAGE - CONE/REAR FUSELAGE - REPLACE CLIPS,

SHEARWEBS AND ANGLES IN SECTION 19 AT FR 72 AND FR 74

**CONF ALL

MODIFICATIONS

MODIFICATION CLASSIFICATION

MAJOR None

MINOR 153833K16120

NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the

mass, balance, structural strength, reliability, operational characteristics affecting the

airworthiness of the product. All other changes are major changes.

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During damage finding tests on A320 aircraft, a full scale fatigue test specimen was carried out. This

was done to enable the Extended Service Goal (ESG) to be effective after reaching an accumulated

Flight Cycle/Flight Hours.

The analysis identified in the Cone/Rear Fuselage area (Section19, FR72 and FR74) - Clips,

Shearwebs and Angles resulted in a non-serviceable condition and needed to be replaced.

This Service Bulletin details the instructions to modify the Clips, Shearwebs and Angles in the

Cone/Rear Fuselage area (Section19, FR72 and FR74). These parts are supplied with pilot holes.

The accomplishment of this Service Bulletin will remove the risk of fatigue failure (identified during the

ESG tests), reinforce the Cone/Rear Fuselage area and contribute to ensure that ESG is achieved.

This Service Bulletin has been validated at revision No.00 on A320 aircraft with Manufacturer Serial

Number (MSN) 0401. Aircraft with Manufacturer Serial Number (MSN) 0401 complies fully with the

requirements of the current issue of the Service Bulletin.

This Service Bulletin is based on the aircraft configuration as known by AIRBUS (first aircraft delivery

configuration and modified by the reported incorporation of AIRBUS Service Bulletins).

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 1

6

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

SERVICE BULLETIN

SUMMARY

Prior to Service Bulletin embodiment, the operator is reminded to pay specific attention to structural

damage which may exist and to repairs which were performed on the aircraft because they may be

affected by the Service Bulletin. Operators must verify that all allowable damage limits and repairs

performed (both in accordance with the SRM and outside the SRM) are still applicable and effective to

the new Service Bulletin configuration. There may be additional or modified maintenance requirements,

such as temporary limits or additional inspections, that apply with respect to the Service Bulletin

configuration.

AIRBUS disclaims any liability for the effect which the Service Bulletin may have on repairs performed

on the aircraft before embodiment of the Service Bulletin. If the post Service Bulletin repair status is no

more covered by the SRM and for repairs outside of the SRM covered by a RAS issued by AIRBUS,

the operator should contact AIRBUS Customer Services Repair Engineering Support (SER1). Repair

review will be done by AIRBUS at conditions of the Customer Services Catalogue.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO ETOPS AFFECTED NO

STRUCTURAL LIFE EXTN YES VENDOR SB INVOLVED NO

SB VALIDATION YES BOOKLET YES

NOTE (1): Service Bulletin must be accomplished.

NOTE: This Service Bulletin has been validated at revision No.00 on A320 aircraft with

Manufacturer Serial Number (MSN) 0401.

Aircraft with Manufacturer Serial Number (MSN) 0401 complies fully with the

requirements of the current issue of the Service Bulletin.

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

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

the concerned SB file).

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 531266D01R04 1 See SB Webs, Clips, Angles and Hardware

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 531266D12R02 1 See SB Webs, Clips, Angles and Hardware

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 2

6

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@A318/A319/A320/A321

SERVICE BULLETIN

SUMMARY

**CONF 003

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 531266D14R00 1 See SB Webs, Clips, Angles and Hardware

**CONF 004

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Kit 531266D11R02 1 See SB Webs, Clips, Angles and Hardware

EFFECTIVITY

**CONF ALL

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

DLH GWI

NOTE: This Service Bulletin is written for the operators listed above. The modification in this

Service Bulletin can be done by other operators. If other operators want to do this

modification, use the RFC/RMO procedure and write to :

AIRBUS

CUSTOMER SERVICES DIRECTORATE

SC Department

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 3

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@A318/A319/A320/A321

SERVICE BULLETIN

SUMMARY

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 531266-831-848-001: Modification

TOTAL MANHOURS 110.00

ELAPSED TIME (HOURS) 106.0

**CONF 002

Task 531266-831-848-001: Modification

TOTAL MANHOURS 110.00

ELAPSED TIME (HOURS) 106.0

**CONF 003

Task 531266-831-848-001: Modification

TOTAL MANHOURS 110.00

ELAPSED TIME (HOURS) 106.0

**CONF 004

Task 531266-831-848-001: Modification

TOTAL MANHOURS 110.00

ELAPSED TIME (HOURS) 106.0

APPENDICES

**CONF ALL

Appendix 01: Elapsed Time Assumption

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 4

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@A318/A319/A320/A321

SERVICE BULLETIN

SUMMARY

**CONF ALL

A

N_SB_531266_6_SAAA_01_00

Z310

FR72

FR74

ACCESS

DOORS

SKIN PLATES

VERTICAL STABILIZER

ATTACHMENT FITTING

A

FR77

FR70

Figure A-GSAAA - Sheet 01

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 5

6

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

SERVICE BULLETIN

SUMMARY

This Page Intentionally Left Blank

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 6

6

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

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 53

TITLE: FUSELAGE - CONE/REAR FUSELAGE - REPLACE CLIPS,

SHEARWEBS AND ANGLES IN SECTION 19 AT FR 72 AND FR 74

MODIFICATION No.: 153833K16120

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

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

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

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

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

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

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

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

This modification is applicable by Service Bulletin only.

(1) Models

320-211

(2) Effectivity by MSN

0069-0072 0078 0083 0086 0093-0094 0104 0110-0111 0116-0117 0135 0137

0161-0162 0172 0200-0202 0209 0216-0218 0267-0269 0346 0382 0401

(3) Effectivity by Operator

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

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

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

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

OPERATOR MSN

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

0116 0172 0346

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 1

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@A318/A319/A320/A321

SERVICE BULLETIN

OPERATOR MSN

GWI 0117 0135 0137 0161 0162 0200 0201 0202 0209 0216 0217 0218

0267 0268 0269 0382 0401

(4) Configuration by MSN

MSN CONFIGURATION

0069 0070 0071 0072 0078 0083 0086 0093 0094 0104 0110

0111 0116 0117 0135 0137

002

0161 0162 0172 0200 0201 0202 0209 0216 0217 0218 0267

0268 0269

003

0346 0382 004

0401 001

(5) Configuration definition

**CONF 001

Config. 001 is valid for aircraft MSN 0401.

**CONF 002

Config. 002 is valid for aircraft MSN 0069 , 0070 , 0071 , 0072 , 0078 , 0083 , 0086 ,

0093 , 0094 , 0104 , 0110 , 0111 , 0116 , 0117 , 0135 and 0137.

**CONF 003

Config. 003 is valid for aircraft MSN 0161 , 0162 , 0172 , 0200 , 0201 , 0202 , 0209 ,

0216 , 0217 , 0218 , 0267 , 0268 and 0269.

**CONF 004

Config. 004 is valid for aircraft MSN 0346 and 0382.

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Kit 531266D01R04 1

Consumable CMLD01 1

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Kit 531266D12R02 1

Consumable CMLD01 1

**CONF 003

MATERIAL QTY PER A/C SEE NOTES

Kit 531266D14R00 1

Consumable CMLD01 1

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 2

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@A318/A319/A320/A321

SERVICE BULLETIN

**CONF 004

MATERIAL QTY PER A/C SEE NOTES

Kit 531266D11R02 1

Consumable CMLD01 1

**CONF ALL

B. CONCURRENT REQUIREMENTS

None

C. REASON

(1) History

During damage finding tests on A320 aircraft, a full scale fatigue test specimen was

carried out. This was done to enable the Extended Service Goal (ESG) to be effective

after reaching an accumulated Flight Cycle/Flight Hours.

The analysis identified in the Cone/Rear Fuselage area (Section19, FR72 and FR74) -

Clips, Shearwebs and Angles resulted in a non-serviceable condition and needed to be

replaced.

(2) Objective/Action

This Service Bulletin details the instructions to modify the Clips, Shearwebs and Angles

in the Cone/Rear Fuselage area (Section19, FR72 and FR74). These parts are supplied

with pilot holes.

(3) Advantages

The accomplishment of this Service Bulletin will remove the risk of fatigue failure

(identified during the ESG tests), reinforce the Cone/Rear Fuselage area and contribute

to ensure that ESG is achieved.

This Service Bulletin has been validated at revision No.00 on A320 aircraft with

Manufacturer Serial Number (MSN) 0401. Aircraft with Manufacturer Serial Number

(MSN) 0401 complies fully with the requirements of the current issue of the Service

Bulletin.

(4) Operational/Maintenance Consequences

This Service Bulletin is based on the aircraft configuration as known by AIRBUS (first

aircraft delivery configuration and modified by the reported incorporation of AIRBUS

Service Bulletins).

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 3

6

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

SERVICE BULLETIN

Prior to Service Bulletin embodiment, the operator is reminded to pay specific attention

to structural damage which may exist and to repairs which were performed on the

aircraft because they may be affected by the Service Bulletin. Operators must verify that

all allowable damage limits and repairs performed (both in accordance with the SRM

and outside the SRM) are still applicable and effective to the new Service Bulletin

configuration. There may be additional or modified maintenance requirements, such as

temporary limits or additional inspections, that apply with respect to the Service Bulletin

configuration.

AIRBUS disclaims any liability for the effect which the Service Bulletin may have on

repairs performed on the aircraft before embodiment of the Service Bulletin. If the post

Service Bulletin repair status is no more covered by the SRM and for repairs outside of

the SRM covered by a RAS issued by AIRBUS, the operator should contact AIRBUS

Customer Services Repair Engineering Support (SER1). Repair review will be done by

AIRBUS at conditions of the Customer Services Catalogue.

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 531266-831-848-001: Modification

(1) Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, LH

and STGR1, RH

(2) Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR1, RH and

STGR13, LH

(3) Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, RH

and STGR3, RH

(4) Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR3, RH to

STGR13, RH

(5) Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, LH

and STGR1, RH

(6) Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR1, RH and

STGR12, LH

(7) Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, RH

and STGR3, RH

(8) Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR3, RH and

STGR12, RH

**CONF 002

Task 531266-831-848-001: Modification

(1) Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, LH

and STGR1, RH

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 4

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SERVICE BULLETIN

(2) Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR1, RH and

STGR13, LH

(3) Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, RH

and STGR3, RH

(4) Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR3, RH to

STGR13, RH

(5) Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, LH

and STGR1, RH

(6) Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR1, RH and

STGR12, LH

(7) Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, RH

and STGR3, RH

(8) Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR3, RH and

STGR12, RH

**CONF 003

Task 531266-831-848-001: Modification

(1) Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, LH

and STGR1, RH

(2) Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR1, RH and

STGR13, LH

(3) Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, RH

and STGR3, RH

(4) Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR3, RH to

STGR13, RH

(5) Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, LH

and STGR1, RH

(6) Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR1, RH and

STGR12, LH

(7) Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, RH

and STGR3, RH

(8) Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR3, RH and

STGR12, RH

**CONF 004

Task 531266-831-848-001: Modification

(1) Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, LH

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 5

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SERVICE BULLETIN

and STGR1, RH

(2) Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR1, RH and

STGR13, LH

(3) Remove the Angles, Webs, Brackets and Clips at Frame 72, between STGR13, RH

and STGR3, RH

(4) Install the Angles, Webs, Brackets and Clips at Frame 72, between STGR3, RH to

STGR13, RH

(5) Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, LH

and STGR1, RH

(6) Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR1, RH and

STGR12, LH

(7) Remove the Angles, Webs, Brackets and Clips at Frame 74, between STGR12, RH

and STGR3, RH

(8) Install the Angles, Webs, Brackets and Clips at Frame 74, between STGR3, RH and

STGR12, RH

**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

This Service Bulletin is mandatory for ESG operation above 48000 FC or 96000 FH from

aeroplane first flight whichever occurs first.

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

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

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

F. APPROVAL

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

Organisation Approval No. EASA.21J.031.

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

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

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

before incorporation of the Service Bulletin.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 6

6

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

SERVICE BULLETIN

G. MANPOWER

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

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

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

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

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

included.

**CONF 001

Task 531266-831-848-001: Modification

Get Access 3.00

On Aircraft

Remove the Angles, Webs, Brackets and Clips at

Frame 72, between STGR13, LH and STGR1, RH

13.00

Install the Angles, Webs, Brackets and Clips at Frame

72, between STGR1, RH and STGR13, LH

16.00

Remove the Angles, Webs, Brackets and Clips at

Frame 72, between STGR13, RH and STGR3, RH

11.00

Install the Angles, Webs, Brackets and Clips at Frame

72, between STGR3, RH to STGR13, RH

14.00

Remove the Angles, Webs, Brackets and Clips at

Frame 74, between STGR12, LH and STGR1, RH

11.00

Install the Angles, Webs, Brackets and Clips at Frame

74, between STGR1, RH and STGR12, LH

14.00

Remove the Angles, Webs, Brackets and Clips at

Frame 74, between STGR12, RH and STGR3, RH

11.00

Install the Angles, Webs, Brackets and Clips at Frame

74, between STGR3, RH and STGR12, RH

12.00

Tests 1.00

Close-Up 4.00

TOTAL MANHOURS 110.00

ELAPSED TIME (HOURS) 106.0

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

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

**CONF 002

Task 531266-831-848-001: Modification

Get Access 3.00

On Aircraft

Remove the Angles, Webs, Brackets and Clips at

Frame 72, between STGR13, LH and STGR1, RH

13.00

Install the Angles, Webs, Brackets and Clips at Frame

72, between STGR1, RH and STGR13, LH

16.00

Remove the Angles, Webs, Brackets and Clips at

Frame 72, between STGR13, RH and STGR3, RH

11.00

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 7

6

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

SERVICE BULLETIN

Task 531266-831-848-001: Modification

Install the Angles, Webs, Brackets and Clips at Frame

72, between STGR3, RH to STGR13, RH

14.00

Remove the Angles, Webs, Brackets and Clips at

Frame 74, between STGR12, LH and STGR1, RH

11.00

Install the Angles, Webs, Brackets and Clips at Frame

74, between STGR1, RH and STGR12, LH

14.00

Remove the Angles, Webs, Brackets and Clips at

Frame 74, between STGR12, RH and STGR3, RH

11.00

Install the Angles, Webs, Brackets and Clips at Frame

74, between STGR3, RH and STGR12, RH

12.00

Tests 1.00

Close-Up 4.00

TOTAL MANHOURS 110.00

ELAPSED TIME (HOURS) 106.0

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

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

**CONF 003

Task 531266-831-848-001: Modification

Get Access 3.00

On Aircraft

Remove the Angles, Webs, Brackets and Clips at

Frame 72, between STGR13, LH and STGR1, RH

13.00

Install the Angles, Webs, Brackets and Clips at Frame

72, between STGR1, RH and STGR13, LH

16.00

Remove the Angles, Webs, Brackets and Clips at

Frame 72, between STGR13, RH and STGR3, RH

11.00

Install the Angles, Webs, Brackets and Clips at Frame

72, between STGR3, RH to STGR13, RH

14.00

Remove the Angles, Webs, Brackets and Clips at

Frame 74, between STGR12, LH and STGR1, RH

11.00

Install the Angles, Webs, Brackets and Clips at Frame

74, between STGR1, RH and STGR12, LH

14.00

Remove the Angles, Webs, Brackets and Clips at

Frame 74, between STGR12, RH and STGR3, RH

11.00

Install the Angles, Webs, Brackets and Clips at Frame

74, between STGR3, RH and STGR12, RH

12.00

Tests 1.00

Close-Up 4.00

TOTAL MANHOURS 110.00

ELAPSED TIME (HOURS) 106.0

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

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

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 8

6

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

SERVICE BULLETIN

**CONF 004

Task 531266-831-848-001: Modification

Get Access 3.00

On Aircraft

Remove the Angles, Webs, Brackets and Clips at

Frame 72, between STGR13, LH and STGR1, RH

13.00

Install the Angles, Webs, Brackets and Clips at Frame

72, between STGR1, RH and STGR13, LH

16.00

Remove the Angles, Webs, Brackets and Clips at

Frame 72, between STGR13, RH and STGR3, RH

11.00

Install the Angles, Webs, Brackets and Clips at Frame

72, between STGR3, RH to STGR13, RH

14.00

Remove the Angles, Webs, Brackets and Clips at

Frame 74, between STGR12, LH and STGR1, RH

11.00

Install the Angles, Webs, Brackets and Clips at Frame

74, between STGR1, RH and STGR12, LH

14.00

Remove the Angles, Webs, Brackets and Clips at

Frame 74, between STGR12, RH and STGR3, RH

11.00

Install the Angles, Webs, Brackets and Clips at Frame

74, between STGR3, RH and STGR12, RH

12.00

Tests 1.00

Close-Up 4.00

TOTAL MANHOURS 110.00

ELAPSED TIME (HOURS) 106.0

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

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

**CONF ALL

H. WEIGHT AND BALANCE

**CONF 001, 004

The weight and balance estimates given in this Service Bulletin are based on the

Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition of

MEW and operator’s items, refer to Weight and Balance Manual (WBM) Chapter 1-00-07.

A320:

Manufacturers Empty Weight +0.117 KG (+0.2579 LB)

Effect on Balance +4.087 KGM (+29.561 LB.FT )

**CONF 002

The weight and balance estimates given in this Service Bulletin are based on the

Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition of

MEW and operator’s items, refer to Weight and Balance Manual (WBM) Chapter 1-00-07.

A320:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 9

6

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

SERVICE BULLETIN

Manufacturers Empty Weight +0.145 KG (+0.3196 LB

Effect on Balance +5.068 KGM (+36.656 LB.FT )

**CONF 003

The weight and balance estimates given in this Service Bulletin are based on the

Manufacturer’s Empty Weight (MEW) and do not include operator item’s. For the definition of

MEW and operator’s items, refer to Weight and Balance Manual (WBM) Chapter 1-00-07.

A320:

Manufacturers Empty Weight +0.115 KG (+0.2535 LB)

Effect on Balance +4.014 KGM (+29.033 LB.FT )

**CONF ALL

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

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

12-34-24 20-16-00 20-21-11

29-00-00 29-11-00 29-13-00

36-12-00 36-12-41 52-10-00

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-11 20-55-00

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

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-40-11 51-42-00

51-43-00 51-44-00 51-75-12

Weight and Balance Manual (WBM) Weight and Balance Manual

(WBM) Chapter 1-00-07

**CONF 002

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

12-34-24 20-16-00 20-21-11

29-00-00 29-11-00 29-13-00

36-12-00 36-12-41 52-10-00

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-11 20-55-00

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

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-40-11 51-42-00

51-43-00 51-44-00 51-75-12

Weight and Balance Manual (WBM) Weight and Balance Manual

(WBM) Chapter 1-00-07

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 10

6

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

SERVICE BULLETIN

**CONF 003

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

12-34-24 20-16-00 20-21-11

29-00-00 29-11-00 29-13-00

36-12-00 36-12-41 52-10-00

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-11 20-55-00

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

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-40-11 51-42-00

51-43-00 51-44-00 51-75-12

Weight and Balance Manual (WBM) Weight and Balance Manual

(WBM) Chapter 1-00-07

**CONF 004

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

12-34-24 20-16-00 20-21-11

29-00-00 29-11-00 29-13-00

36-12-00 36-12-41 52-10-00

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-11 20-55-00

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

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-40-11 51-42-00

51-43-00 51-44-00 51-75-12

Weight and Balance Manual (WBM) Weight and Balance Manual

(WBM) Chapter 1-00-07

**CONF ALL

K. PUBLICATION AFFECTED

Airworthiness Limitation Section (ALS) Part 2

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 11

6

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

SERVICE BULLETIN

This Page Intentionally Left Blank

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 12

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

SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

The AIRBUS material is included in the commercial offer of the Letter Agreement,

and as such will be supplied by AIRBUS Upgrade Services. To facilitate the material

reception, Airline Customers are requested to send a Customer Purchase Order to:

Kit 531266D01R04

Kit 531266D12R02

Kit 531266D14R00

Kit 531266D11R02

AIRBUS Upgrade Services

Attn. Key Account Manager (KAM)

(2) Price and Availability

Sales terms must be agreed between the Customer and AIRBUS in accordance with the

RFC (or RFC/RMO) procedure.

B. INDUSTRY SUPPORT INFORMATION

Industry Support terms must be agreed between the Customer and AIRBUS in accordance

with the RFC (or RFC/RMO) procedure.

C. LIST OF COMPONENTS

Kit 531266D01R04

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

NOTES

1 D5357113140000 1 ANGLE (1) D5357113140000

2 D5357113140100 1 ANGLE (2) D5357113140100

3 D5357113146800 1 WEB (3) D5357113146800

4 D5357113146900 1 WEB (4) D5357113146900

5 D5357113143800 1 WEB (5) D5357113143800

6 D5357113143900 1 WEB (6) D5357113143900

7 D5357113144000 1 CLIP (7) D5357113144000

8 D5357113144100 1 CLIP (8) D5357113144100

9 D5357113146600 1 CLIP (9) D5357113146600

10 D5357113146700 1 CLIP (10) D5357113146700

11 D5357113143600 1 WEB (11) D5357113143600

12 D5357113143700 1 WEB (12) D5357113143700

13 D5357113145600 1 ANGLE (13) D5357113145600

14 D5357113145700 1 ANGLE (14) D5357113145700

15 D5357113145000 1 CLIP (15) D5357113145000

16 D5357113145100 1 CLIP (16) D5357113145100

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 13

6

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

SERVICE BULLETIN

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

NOTES

17 D5357113145400 1 ANGLE (17) D5357113145400

18 D5357113145500 1 ANGLE (18) D5357113145500

19 D5357113144800 1 CLIP (19) D5357113144800

20 D5357113144900 1 CLIP (20) D5357113144900

21 D5357113144600 1 WEB (21) D5357113144600

22 D5357113144700 1 WEB (22) D5357113144700

23 D5357113145200 1 ANGLE (23) D5357113145200

24 D5357113145300 1 ANGLE (24) D5357113145300

25 D5357113145800 1 ANGLE (25) D5357113145800

26 D5357113145900 1 ANGLE (26) D5357113145900

27 D5357113144400 1 CLIP (27) D5357113144400

28 D5357113144500 1 CLIP (28) D5357113144500

29 D5357072225600 1 ANGLE (29) D5357072225600

30 D5357072225700 1 ANGLE (30) D5357072225700

31 D5357072224400 1 CLIP (31) D5357072224400

32 D5357072224500 1 CLIP (32) D5357072224500

33 D5357072226000 1 ANGLE (33) D5357072226000

34 D5357072226100 1 ANGLE (34) D5357072226100

35 D5357113144200 1 WEB (35) D5357113144200

36 D5357072225400 1 ANGLE (36) D5357072225400

37 D5357072225500 1 ANGLE (37) D5357072225500

38 D5357072225800 1 ANGLE (38) D5357072225800

39 D5357072225900 1 ANGLE (39) D5357072225900

40 D5357072224600 1 CLIP (40) D5357072224600

41 D5357072224700 1 CLIP (41) D5357072224700

42 D5357072225200 1 ANGLE (42) D5357072225200

43 D5357072225300 1 ANGLE (43) D5357072225300

44 D5357072224800 1 WEB (44) D5357072224800

45 D5357072224900 1 WEB (45) D5357072224900

46 D5357072225000 1 CLIP (46) D5357072225000

47 D5357072225100 1 CLIP (47) D5357072225100

48 D5357072224200 2 CLIP (48) D5357072224200

49 D5357072224000 1 WEB (49) D5357072224000

50 D5357116122000 1 WEB (50) D5357116122000

51 D5357113339600 1 ANGLE (51) D5357113339600

52 D5357113339700 1 ANGLE (52) D5357113339700

53 D5357113339800 2 FILLER (53) D5357113339800

54 D5357113321400 1 ANGLE (54) D5357113321400

55 D5357113321500 1 ANGLE (55) D5357113321500

56 D5357113337200 1 ANGLE (56) D5357113337200

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 14

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

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

NOTES

57 D5357113337300 1 ANGLE (57) D5357113337300

58 D5357113337000 1 ANGLE (58) D5357113337000

59 D5357113337100 1 ANGLE (59) D5357113337100

60 D5357113340000 1 WEB (60) D5357113340000

61 D5357113340100 1 WEB (61) D5357113340100

62 D5357113339400 1 WEB (62) D5357113339400

63 D5357113339500 1 WEB (63) D5357113339500

64 D5357113339000 1 ANGLE (64) D5357113339000

65 D5357113339100 1 ANGLE (65) D5357113339100

66 D5357113338400 1 CLIP (66) D5357113338400

67 D5357113338500 1 CLIP (67) D5357113338500

68 D5357113337800 1 WEB (68) D5357113337800

69 D5357113337900 1 WEB (69) D5357113337900

70 D5357113338800 1 ANGLE (70) D5357113338800

71 D5357113338900 1 ANGLE (71) D5357113338900

72 D5357113338200 1 CLIP (72) D5357113338200

73 D5357113338300 1 CLIP (73) D5357113338300

74 D5357113338600 1 ANGLE (74) D5357113338600

75 D5357113338700 1 ANGLE (75) D5357113338700

76 D5357113338000 1 CLIP (76) D5357113338000

77 D5357113338100 1 CLIP (77) D5357113338100

78 D5357113339200 1 ANGLE (78) D5357113339200

79 D5357113339300 1 ANGLE (79) D5357113339300

80 D5357072425400 1 ANGLE (80) D5357072425400

81 D5357072425500 1 ANGLE (81) D5357072425500

82 D5357072424200 1 CLIP (82) D5357072424200

83 D5357072424300 1 CLIP (83) D5357072424300

84 D5357113337600 1 WEB (84) D5357113337600

85 D5357113337700 1 WEB (85) D5357113337700

86 D5357072425800 1 ANGLE (86) D5357072425800

87 D5357072425900 1 ANGLE (87) D5357072425900

88 D5357072425200 1 ANGLE (88) D5357072425200

89 D5357072425300 1 ANGLE (89) D5357072425300

90 D5357072425600 1 ANGLE (90) D5357072425600

91 D5357072425700 1 ANGLE (91) D5357072425700

92 D5357072424400 1 CLIP (92) D5357072424400

93 D5357072424500 1 CLIP (93) D5357072424500

94 D5357072425000 1 ANGLE (94) D5357072425000

95 D5357072425100 1 ANGLE (95) D5357072425100

96 D5357072424800 1 WEB (96) D5357072424800

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 15

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SERVICE BULLETIN

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

NOTES

97 D5357072424900 1 WEB (97) D5357072424900

98 D5357072424600 1 CLIP (98) D5357072424600

99 D5357072424700 1 CLIP (99) D5357072424700

100 D5357072424000 1 WEB (100) D5357072424000

102 DAN5-6-4X 104 PIN DAN5-6-4

103 DAN11-6X 485 COLLAR NSA5075-6

104 DAN5-6-5X 88 PIN DAN5-6-6

105 DAN5-6-6X 10 PIN DAN5-6-6

106 EN6081D5-06 116 RIVET LN91984000CF

107 DAN5-6-5 32 PIN DAN5-5-5

108 NSA5075-6 214 COLLAR NSA5075-6

109 DAN5-5-6 60 PIN DAN5-5-6

110 NSA5075-5 106 COLLAR NSA5075-5

111 DAN5-5-5 44 PIN DAN5-5-5

112 DAN5-6-6 52 PIN DAN5-5-6

113 DAN5-6-3X 6 PIN DAN5-6-3

114 DAN5-8-5X 70 PIN DAN5-8-5

115 DAN11-8X 133 COLLAR NSA5057-8

116 DAN5-8-4X 8 PIN DAN5-8-4

117 DAN5-8-7X 18 PIN DAN5-8-7

118 DAN5-8-8X 4 PIN DAN5-8-8

119 DAN6-6-3X 16 PIN DAN6-6-3

120 DAN6-6-4X 112 PIN DAN6-6-4

121 DAN6-6-5X 62 PIN DAN6-6-5

122 EN6069D5-06 30 RIVET NAS1097KE5-00

123 DAN6-8-6X 15 PIN DAN6-8-6

124 DAN6-6-7X 46 PIN DAN6-6-7

125 DAN6-6-7 78 PIN DAN6-5-7

126 DAN6-6-6 20 PIN DAN6-5-6

127 DAN6-6-5 12 PIN DAN6-5-5

128 DAN6-6-3 16 PIN DAN6-5-3

129 DAN5-6-3 6 PIN DAN5-5-3

130 DAN5-6-7X 8 PIN DAN5-6-7

131 DAN5-8-6X 18 PIN DAN5-8-6

132 DAN6-6-6X 24 PIN DAN6-6-6

133 DAN6-5-7 2 PIN DAN6-5-7

135 EN6081D5-08 4 RIVET LN91984000CF

136 EN6069D5-07 134 RIVET NAS1097KE5-00

137 EN6069D5-08 64 RIVET NAS1097KE5-00

144 DAN7-6-11X 2 PIN DAN7-6-11

145 DAN12-6X 2 COLLAR DAN12-6

146 DAN5-6-10X 4 PIN DAN5-6-10

148 DAN5-6-8X 4 PIN DAN5-6-8

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 16

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SERVICE BULLETIN

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

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

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

to part number relationship.

Kit 531266D11R02

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

NOTES

1 D5357113140090 1 ANGLE (1) D5357113140000

2 D5357113140190 1 ANGLE (2) D5357113140100

3 D5357113146890 1 WEB (3) D5357113146800

4 D5357113146990 1 WEB (4) D5357113146900

5 D5357113143890 1 WEB (5) D5357113143800

6 D5357113143990 1 WEB (6) D5357113143900

7 D5357113144090 1 CLIP (7) D5357113144000

8 D5357113144190 1 CLIP (8) D5357113144100

9 D5357113146690 1 CLIP (9) D5357113146600

10 D5357113146790 1 CLIP (10) D5357113146700

11 D5357113143690 1 WEB (11) D5357113143600

12 D5357113143790 1 WEB (12) D5357113143700

13 D5357113145690 1 ANGLE (13) D5357113145600

14 D5357113145790 1 ANGLE (14) D5357113145700

15 D5357113145090 1 CLIP (15) D5357113145000

16 D5357113145190 1 CLIP (16) D5357113145100

17 D5357113145490 1 ANGLE (17) D5357113145400

18 D5357113145590 1 ANGLE (18) D5357113145500

19 D5357113144890 1 CLIP (19) D5357113144800

20 D5357113144990 1 CLIP (20) D5357113144900

21 D5357113144690 1 WEB (21) D5357113144600

22 D5357113144790 1 WEB (22) D5357113144700

23 D5357113145290 1 ANGLE (23) D5357113145200

24 D5357113145390 1 ANGLE (24) D5357113145300

25 D5357113145890 1 ANGLE (25) D5357113145800

26 D5357113145990 1 ANGLE (26) D5357113145900

27 D5357113144490 1 CLIP (27) D5357113144400

28 D5357113144590 1 CLIP (28) D5357113144500

29 D5357072225690 1 ANGLE (29) D5357072225600

30 D5357072225790 1 ANGLE (30) D5357072225700

31 D5357072224490 1 CLIP (31) D5357072224400

32 D5357072224590 1 CLIP (32) D5357072224500

33 D5357072226090 1 ANGLE (33) D5357072226000

34 D5357072226190 1 ANGLE (34) D5357072226100

35 D5357113144290 1 WEB (35) D5357113144200

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 17

6

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

SERVICE BULLETIN

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

NOTES

36 D5357072225490 1 ANGLE (36) D5357072225400

37 D5357072225590 1 ANGLE (37) D5357072225500

38 D5357072225890 1 ANGLE (38) D5357072225800

39 D5357072225990 1 ANGLE (39) D5357072225900

40 D5357072224690 1 CLIP (40) D5357072224600

41 D5357072224790 1 CLIP (41) D5357072224700

42 D5357072225290 1 ANGLE (42) D5357072225200

43 D5357072225390 1 ANGLE (43) D5357072225300

44 D5357072224890 1 WEB (44) D5357072224800

45 D5357072224990 1 WEB (45) D5357072224900

46 D5357072225090 1 CLIP (46) D5357072225000

47 D5357072225190 1 CLIP (47) D5357072225100

48 D5357072224290 2 CLIP (48) D5357072224200

49 D5357072224090 1 WEB (49) D5357072224000

50 D5357116122090 1 WEB (50) D5357116122000

51 D5357113339690 1 ANGLE (51) D5357113339600

52 D5357113339790 1 ANGLE (52) D5357113339700

53 D5357113339800 2 FILLER (53) D5357113339800

54 D5357113321490 1 ANGLE (54) D5357113321400

55 D5357113321590 1 ANGLE (55) D5357113321500

56 D5357113337290 1 ANGLE (56) D5357113337200

57 D5357113337390 1 ANGLE (57) D5357113337300

58 D5357113337090 1 ANGLE (58) D5357113337000

59 D5357113337190 1 ANGLE (59) D5357113337100

60 D5357113340090 1 WEB (60) D5357113340000

61 D5357113340190 1 WEB (61) D5357113340100

62 D5357113339490 1 WEB (62) D5357113339400

63 D5357113339590 1 WEB (63) D5357113339500

64 D5357113339090 1 ANGLE (64) D5357113339000

65 D5357113339190 1 ANGLE (65) D5357113339100

66 D5357113338490 1 CLIP (66) D5357113338400

67 D5357113338590 1 CLIP (67) D5357113338500

68 D5357113337890 1 WEB (68) D5357113337800

69 D5357113337990 1 WEB (69) D5357113337900

70 D5357113338890 1 ANGLE (70) D5357113338800

71 D5357113338990 1 ANGLE (71) D5357113338900

72 D5357113338290 1 CLIP (72) D5357113338200

73 D5357113338390 1 CLIP (73) D5357113338300

74 D5357113338690 1 ANGLE (74) D5357113338600

75 D5357113338790 1 ANGLE (75) D5357113338700

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 18

6

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

SERVICE BULLETIN

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

NOTES

76 D5357113338090 1 CLIP (76) D5357113338000

77 D5357113338190 1 CLIP (77) D5357113338100

78 D5357113339290 1 ANGLE (78) D5357113339200

79 D5357113339390 1 ANGLE (79) D5357113339300

80 D5357072425490 1 ANGLE (80) D5357072425400

81 D5357072425590 1 ANGLE (81) D5357072425500

82 D5357072424290 1 CLIP (82) D5357072424200

83 D5357072424390 1 CLIP (83) D5357072424300

84 D5357113337690 1 WEB (84) D5357113337600

85 D5357113337790 1 WEB (85) D5357113337700

86 D5357072425890 1 ANGLE (86) D5357072425800

87 D5357072425990 1 ANGLE (87) D5357072425900

88 D5357072425290 1 ANGLE (88) D5357072425200

89 D5357072425390 1 ANGLE (89) D5357072425300

90 D5357072425690 1 ANGLE (90) D5357072425600

91 D5357072425790 1 ANGLE (91) D5357072425700

92 D5357072424490 1 CLIP (92) D5357072424400

93 D5357072424590 1 CLIP (93) D5357072424500

94 D5357072425090 1 ANGLE (94) D5357072425000

95 D5357072425190 1 ANGLE (95) D5357072425100

96 D5357072424890 1 WEB (96) D5357072424800

97 D5357072424990 1 WEB (97) D5357072424900

98 D5357072424690 1 CLIP (98) D5357072424600

99 D5357072424790 1 CLIP (99) D5357072424700

100 D5357072424090 1 WEB (100) D5357072424000

102 DAN5-6-4X 104 PIN DAN5-6-4

103 DAN11-6X 492 COLLAR NSA5075-6

104 DAN5-6-5X 88 PIN DAN5-6-5

105 DAN5-6-6X 14 PIN DAN5-6-6

106 EN6081D5-06 116 RIVET LN91984000CF

107 DAN5-6-5 32 PIN DAN5-5-5

108 NSA5075-6 214 COLLAR NSA5075-6

109 DAN5-5-6 70 PIN DAN5-5-6

110 NSA5075-5 104 COLLAR NSA5075-5

111 DAN5-5-5 34 PIN DAN5-5-5

112 DAN5-6-6 52 PIN DAN5-5-6

113 DAN5-6-3X 6 PIN DAN5-6-3

114 DAN5-8-5X 70 PIN DAN5-8-5

115 DAN11-8X 133 COLLAR NSA5075-8

116 DAN5-8-4X 8 PIN DAN5-8-4

117 DAN5-8-7X 18 PIN DAN5-8-7

118 DAN5-8-8X 4 PIN DAN5-8-8

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 19

6

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

SERVICE BULLETIN

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

NOTES

119 DAN6-6-3X 16 PIN DAN6-6-3

120 DAN6-6-4X 112 PIN DAN6-6-4

121 DAN6-6-5X 56 PIN DAN6-6-5

122 EN6069D5-06 30 RIVET NAS1097KE5-00

123 DAN6-8-6X 15 PIN DAN6-8-6

124 DAN6-6-7X 46 PIN DAN6-6-7

125 DAN6-6-7 76 PIN DAN6-5-7

126 DAN6-6-6 20 PIN DAN6-5-6

127 DAN6-6-5 12 PIN DAN6-5-5

128 DAN6-6-3 16 PIN DAN6-5-3

129 DAN5-6-3 6 PIN DAN5-5-3

130 DAN5-6-7X 8 PIN DAN5-6-7

131 DAN5-8-6X 18 PIN DAN5-8-6

132 DAN6-6-6X 34 PIN DAN6-6-6

135 EN6081D5-08 4 RIVET LN91984000CF

136 EN6069D5-07 134 RIVET NAS1097KE5-00

137 EN6069D5-08 64 RIVET NAS1097KE5-00

144 DAN7-6-11X 2 PIN DAN7-6-11

145 DAN12-6X 2 COLLAR DAN12-6

146 DAN5-6-10X 4 PIN DAN5-6-10

148 DAN5-6-8X 4 PIN DAN5-6-8

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

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

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

to part number relationship.

Kit 531266D12R02

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

NOTES

1 D5357113120490 1 ANGLE (1) D5357113120400

2 D5357113120590 1 ANGLE (2) D5357113120500

3 D5357113133090 1 WEB (3) D5357113133000

4 D5357113133190 1 WEB (4) D5357113133100

5 D5357113134690 1 WEB (5) D5357113134600

6 D5357113134790 1 WEB (6) D5357113134700

7 D5357113136690 1 CLIP (7) D5357113136600

8 D5357113136790 1 CLIP (8) D5357113136700

9 D5357113122690 1 CLIP (9) D5357113122600

10 D5357113122790 1 CLIP (10) D5357113122700

11 D5357113134490 1 WEB (11) D5357113134400

12 D5357113134590 1 WEB (12) D5357113134500

13 D5357114726090 1 ANGLE (23) D5357114725600

14 D5357114726190 1 ANGLE (14) D5357114726100

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 20

6

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

SERVICE BULLETIN

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

NOTES

15 D5357113122490 1 CLIP (15) D5357113122400

16 D5357113122590 1 CLIP (16) D5357113122500

17 D5357114725890 1 ANGLE (17) D5357114725800

18 D5357114725990 1 ANGLE (18) D5357114725900

19 D5357113132290 1 CLIP (19) D5357113132200

20 D5357113132390 1 CLIP (20) D5357113132300

21 D5357113134290 1 WEB (21) D5357113134200

22 D5357113134390 1 WEB (22) D5357113134300

23 D5357114725690 1 ANGLE (23) D5357114725600

24 D5357114725790 1 ANGLE (24) D5357114725700

25 D5357114727890 1 ANGLE (25) D5357114727800

26 D5357114727990 1 ANGLE (26) D5357114727900

27 D5357113136490 1 CLIP (27) D5357113136400

28 D5357113136590 1 CLIP (28) D5357113136500

29 D5357114725490 1 ANGLE (29) D5357114725400

30 D5357114725590 1 ANGLE (30) D5357114725500

31 D5357072231090 1 CLIP (32) D5357072231000

32 D5357072231190 1 CLIP (32) D5357072231100

33 D5357114727690 1 ANGLE (33) D5357114727600

34 D5357114727790 1 ANGLE (34) D5357114727700

35 D5357113134090 1 WEB (35) D5357113134000

36 D5357114725290 1 ANGLE (36) D5357114725200

37 D5357114725390 1 ANGLE (37) D5357114725300

38 D5357114727490 1 ANGLE (38) D5357114727400

39 D5357114727590 1 ANGLE (39) D5357114727500

40 D5357072221290 1 CLIP (40) D5357072221200

41 D5357072221390 1 CLIP (41) D5357072221300

42 D5357114725090 1 ANGLE (42) D5357114725000

43 D5357114725190 1 ANGLE (43) D5357114725100

44 D5357072222090 1 WEB (44) D5357072222000

45 D5357072222190 1 WEB (45) D5357072222100

46 D5357072221490 1 CLIP (46) D5357072221400

47 D5357072221590 1 CLIP (47) D5357072221500

48 D5357072221890 2 CLIP (48) D5357072221800

49 D5357072221690 1 WEB (49) D5357072221600

50 D5357116135090 1 WEB (50) D5357116135000

51 D5357113331290 1 ANGLE (51) D5357113331200

52 D5357113331390 1 ANGLE (52) D5357113331300

53 D5357113335400 2 FILLER (53) D5357113335400

54 D5357113321490 1 ANGLE (54) D5357113321400

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 21

6

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

SERVICE BULLETIN

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

NOTES

55 D5357113321590 1 ANGLE (55) D5357113321500

56 D5357113321090 1 ANGLE (56) D5357113321000

57 D5357113321190 1 ANGLE (57) D5357113321100

58 D5357113320890 1 ANGLE (58) D5357113320800

59 D5357113320990 1 ANGLE (59) D5357113320900

60 D5357113336090 1 WEB (60) D5357113336000

61 D5357113336190 1 WEB (61) D5357113336100

62 D5357113330690 1 WEB (62) D5357113330600

63 D5357113330790 1 WEB (63) D5357113330700

64 D5357114727290 1 ANGLE (64) D5357114727200

65 D5357114727390 1 ANGLE (65) D5357114727300

66 D5357113330490 1 CLIP (66) D5357113330400

67 D5357113330590 1 CLIP (67) D5357113330500

68 D5357113336290 1 WEB (68) D5357113336200

69 D5357113336390 1 WEB (69) D5357113336300

70 D5357114727090 1 ANGLE (70) D5357114727000

71 D5357114727190 1 ANGLE (71) D5357114727100

72 D5357113330290 1 CLIP (72) D5357113330200

73 D5357113330390 1 CLIP (73) D5357113330300

74 D5357114726890 1 ANGLE (74) D5357114726800

75 D5357114726990 1 ANGLE (75) D5357114726900

76 D5357113330090 1 CLIP (76) D5357113330000

77 D5357113330190 1 CLIP (77) D5357113330100

78 D5357114728490 1 ANGLE (78) D5357114728400

79 D5357114728590 1 ANGLE (79) D5357114728500

80 D5357114726690 1 ANGLE (80) D5357114726600

81 D5357114726790 1 ANGLE (81) D5357114726700

82 D5357072431090 1 CLIP (82) D5357072431000

83 D5357072431190 1 CLIP (83) D5357072431100

84 D5357113336490 1 WEB (84) D5357113336400

85 D5357113336590 1 WEB (85) D5357113336500

86 D5357114728290 1 ANGLE (64) D5357114727200

87 D5357114728390 1 ANGLE (87) D5357114728300

88 D5357114726490 1 ANGLE (88) D5357114726400

89 D5357114726590 1 ANGLE (89) D5357114726500

90 D5357114728090 1 ANGLE (90) D5357114728000

91 D5357114728190 1 ANGLE (91) D5357114728100

92 D5357072421290 1 CLIP (92) D5357072421200

93 D5357072421390 1 CLIP (93) D5357072421300

94 D5357114726290 1 ANGLE (94) D5357114726200

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 22

6

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

SERVICE BULLETIN

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

NOTES

95 D5357114726390 1 ANGLE (95) D5357114726300

96 D5357072421690 1 WEB (96) D5357072421600

97 D5357072421790 1 WEB (97) D5357072421700

98 D5357072421490 1 CLIP (98) D5357072421400

99 D5357072421590 1 CLIP (99) D5357072421500

100 D5357072421890 1 WEB (100) D5357072421800

102 DAN5-6-4X 104 PIN DAN5-6-4

103 DAN11-6X 474 COLLAR NSA5075-6

104 DAN5-6-5X 88 PIN DAN5-6-5

105 DAN5-6-6X 14 PIN DAN5-6-6

106 EN6081D5-06 116 RIVET LN91984000CF

108 NSA5330-6 104 COLLAR NSA5075-6

109 DAN5-6-6 108 PIN DAN5-5-6

110 NSA5075-6 228 COLLAR NSA5075-6

111 DAN5-6-5 74 PIN DAN5-5-5

112 DAN6-6-5 2 PIN DAN6-5-5

113 DAN5-6-3X 6 PIN DAN5-6-3

114 DAN5-8-5X 70 PIN DAN5-8-5

115 DAN11-8X 133 COLLAR NSA5057-8

116 DAN5-8-4X 8 PIN DAN5-8-4

117 DAN5-8-7X 18 PIN DAN5-8-7

118 DAN5-8-8X 4 PIN DAN5-8-8

119 DAN6-6-3X 16 PIN DAN6-6-3

120 DAN6-6-4X 112 PIN DAN6-6-4

121 DAN6-6-5Y 50 PIN DAN6-6-5

122 EN6069D5-06 30 RIVET NAS1097KE5-00

123 DAN6-8-6X 15 PIN DAN6-8-6

124 DAN6-6-6Y 54 PIN DAN5-8-4

125 DAN6-6-7X 84 PIN DAN6-6-7

126 DAN6-6-6 20 PIN DAN6-5-6

127 DAN6-6-5X 26 PIN DAN6-6-5

128 DAN6-6-3 16 PIN DAN6-5-3

129 DAN5-6-3 6 PIN DAN5-5-3

130 DAN5-6-7X 8 PIN DAN5-6-7

131 DAN5-8-6X 18 PIN DAN5-8-6

132 DAN6-6-6X 8 PIN DAN6-6-6

133 DAN6-5-7 2 PIN DAN6-5-7

134 DAN6-6-7 2 PIN DAN6-6-7

135 EN6081D5-07 4 RIVET LN91984000CF

136 EN6069D5-07 134 RIVET NAS1097KE5-00

137 EN6069D5-08 64 RIVET NAS1097KE5-00

144 DAN7-6-11X 2 PIN DAN7-6-11

145 DAN12-6X 2 COLLAR DAN12-6

146 DAN5-6-10X 4 PIN DAN5-6-10

148 DAN5-6-8X 4 PIN DAN5-6-8

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 23

6

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

SERVICE BULLETIN

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

NOTES

160 NSA5075-5 2 COLLAR NSA5075-5

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

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

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

to part number relationship.

Kit 531266D14R00

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

NOTES

1 D5357113120490 1 ANGLE (1) D5357113120400

2 D5357113120590 1 ANGLE (2) D5357113120500

3 D5357113133090 1 WEB (3) D5357113133000

4 D5357113133190 1 WEB (4) D5357113133100

5 D5357113134690 1 WEB (5) D5357113134600

6 D5357113134790 1 WEB (6) D5357113134700

7 D5357113136690 1 CLIP (7) D5357113136600

8 D5357113136790 1 CLIP (8) D5357113136700

9 D5357113122690 1 CLIP (9) D5357113122600

10 D5357113122790 1 CLIP (10) D5357113122700

11 D5357113134490 1 WEB (11) D5357113134400

12 D5357113134590 1 WEB (12) D5357113134500

13 D5357113138290 1 ANGLE (13) D5357113138200

14 D5357113138390 1 ANGLE (14) D5357113138300

15 D5357113137690 1 CLIP (15) D5357113137600

16 D5357113137790 1 CLIP (16) D5357113137700

17 D5357113138090 1 ANGLE (17) D5357113138000

18 D5357113138190 1 ANGLE (18) D5357113138100

19 D5357113137490 1 CLIP (19) D5357113137400

20 D5357113137590 1 CLIP (20) D5357113137500

21 D5357113137290 1 WEB (21) D5357113137200

22 D5357113137390 1 WEB (22) D5357113137300

23 D5357113137890 1 ANGLE (23) D5357113137800

24 D5357113137990 1 ANGLE (24) D5357113137900

25 D5357113138490 1 ANGLE (25) D5357113138400

26 D5357113138590 1 ANGLE (26) D5357113138500

27 D5357113137090 1 CLIP (27) D5357113137000

28 D5357113137190 1 CLIP (28) D5357113137100

29 D5357072223490 1 ANGLE (29) D5357072223400

30 D5357072223590 1 ANGLE (30) D5357072223500

31 D5357072222290 1 CLIP (31) D5357072222200

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 24

6

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

SERVICE BULLETIN

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

NOTES

32 D5357072222390 1 CLIP (32) D5357072222300

33 D5357072223890 1 ANGLE (33) D5357072223800

34 D5357072223990 1 ANGLE (34) D5357072223900

35 D5357113136890 1 WEB (35) D5357113136800

36 D5357072223290 1 ANGLE (36) D5357072223200

37 D5357072223390 1 ANGLE (37) D5357072223300

38 D5357072223690 1 ANGLE (38) D5357072223600

39 D5357072223790 1 ANGLE (39) D5357072223700

40 D5357072222490 1 CLIP (40) D5357072222400

41 D5357072222590 1 CLIP (41) D5357072222500

42 D5357072223090 1 ANGLE (42) D5357072223000

43 D5357072223190 1 ANGLE (43) D5357072223100

44 D5357072222690 1 WEB (44) D5357072222600

45 D5357072222790 1 WEB (45) D5357072222700

46 D5357072222890 1 CLIP (46) D5357072222800

47 D5357072222990 1 CLIP (47) D5357072222900

48 D5357072221890 2 CLIP (48) D5357072221800

49 D5357072221690 1 WEB (49) D5357072221600

50 D5357116135490 1 WEB (50) D5357116135400

51 D5357113331290 1 ANGLE (51) D5357113331200

52 D5357113331390 1 ANGLE (52) D5357113331300

53 D5357113335400 2 FILLER (53) D5357113335400

54 D5357113321490 1 ANGLE (54) D5357113321400

55 D5357113321590 1 ANGLE (55) D5357113321500

56 D5357113321090 1 ANGLE (56) D5357113321000

57 D5357113321190 1 ANGLE (57) D5357113321100

58 D5357113320890 1 ANGLE (58) D5357113320800

59 D5357113320990 1 ANGLE (59) D5357113320900

60 D5357113336090 1 WEB (60) D5357113336000

61 D5357113336190 1 WEB (61) D5357113336100

62 D5357113330690 1 WEB (62) D5357113330600

63 D5357113330790 1 WEB (63) D5357113330700

64 D5357113327090 1 ANGLE (64) D5357113327000

65 D5357113327190 1 ANGLE (65) D5357113327100

66 D5357113326490 1 CLIP (66) D5357113326400

67 D5357113326590 1 CLIP (67) D5357113326500

68 D5357113325890 1 WEB (68) D5357113325800

69 D5357113325990 1 WEB (69) D5357113325900

70 D5357113326890 1 ANGLE (70) D5357113326800

71 D5357113326990 1 ANGLE (71) D5357113326900

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 25

6

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

NOTES

72 D5357113326290 1 CLIP (72) D5357113326200

73 D5357113326390 1 CLIP (73) D5357113326300

74 D5357113326690 1 ANGLE (74) D5357113326600

75 D5357113326790 1 ANGLE (75) D5357113326700

76 D5357113326090 1 CLIP (76) D5357113326000

77 D5357113326190 1 CLIP (77) D5357113326100

78 D5357113327290 1 ANGLE (78) D5357113327200

79 D5357113327390 1 ANGLE (79) D5357113327300

80 D5357072423490 1 ANGLE (80) D5357072423400

81 D5357072423590 1 ANGLE (81) D5357072423500

82 D5357072422090 1 CLIP (82) D5357072422000

83 D5357072422190 1 CLIP (83) D5357072422100

84 D5357113325690 1 WEB (84) D5357113325600

85 D5357113325790 1 WEB (85) D5357113325700

86 D5357072423890 1 ANGLE (86) D5357072423800

87 D5357072423990 1 ANGLE (87) D5357072423900

88 D5357072423290 1 ANGLE (88) D5357072423200

89 D5357072423390 1 ANGLE (89) D5357072423300

90 D5357072423690 1 ANGLE (90) D5357072423600

91 D5357072423790 1 ANGLE (91) D5357072423700

92 D5357072422290 1 CLIP (92) D5357072422200

93 D5357072422390 1 CLIP (93) D5357072422300

94 D5357072423090 1 ANGLE (94) D5357072423000

95 D5357072423190 1 ANGLE (95) D5357072423100

96 D5357072422690 1 WEB (96) D5357072422600

97 D5357072422790 1 WEB (97) D5357072422700

98 D5357072422490 1 CLIP (98) D5357072422400

99 D5357072422590 1 CLIP (99) D5357072422500

100 D5357072421890 1 WEB (100) D5357072421800

102 DAN5-6-4X 104 PIN DAN5-6-4

103 DAN11-6X 488 COLLAR NSA5075-6

104 DAN5-6-5X 88 PIN DAN5-6-5

105 DAN5-6-6X 10 PIN DAN5-6-6

107 DAN5-6-5 32 PIN DAN5-5-5

108 NSA5075-6 214 COLLAR NSA5075-6

109 DAN5-5-6 70 PIN DAN5-5-6

111 DAN5-5-5 34 PIN DAN5-5-5

112 DAN5-6-6 52 PIN DAN5-5-6

113 DAN5-6-3X 6 PIN DAN5-6-3

114 DAN5-8-5X 70 PIN DAN5-8-5

115 DAN11-8X 133 COLLAR NSA5057-8

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

NOTES

116 DAN5-8-4X 8 PIN DAN5-8-4

117 DAN5-8-7X 18 PIN DAN5-8-7

118 DAN5-8-8X 4 PIN DAN5-8-8

119 DAN6-6-3X 16 PIN DAN6-6-3

120 DAN6-6-4X 112 PIN DAN6-6-4

121 DAN6-6-5X 56 PIN DAN6-6-5

123 DAN6-8-6X 15 PIN DAN6-8-6

125 DAN6-6-7X 46 PIN DAN6-6-7

126 DAN6-6-6 20 PIN DAN6-5-6

127 DAN6-6-5 12 PIN DAN6-5-5

128 DAN6-6-3 16 PIN DAN6-5-3

129 DAN5-6-3 6 PIN DAN5-5-3

130 DAN5-6-7X 8 PIN DAN5-6-7

131 DAN5-8-6X 18 PIN DAN5-8-6

132 DAN6-6-6X 34 PIN DAN6-6-6

134 DAN6-6-7 76 PIN DAN6-6-7

135 EN6081D5-07 116 RIVET LN91984000CF

137 EN6069D5-08 228 RIVET NAS1097KE5-00

144 DAN7-6-11X 2 PIN DAN7-6-11

145 DAN12-6X 2 COLLAR DAN12-6

146 DAN5-6-10X 4 PIN DAN5-6-10

148 DAN5-6-8X 4 PIN DAN5-6-8

160 NSA5075-5 104 COLLAR NSA5075-5

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

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

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

to part number relationship.

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Sealant, Brush Consistency 09-013 As required

Corrosion Preventative Compound,

Temporary

15-009 As required

Anti-Corrosion Primer Polyurethane 16-001 As required

Polyurethane Finish Paint 16-018 As required

(2) Components

None

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(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

None

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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3. ACCOMPLISHMENT INSTRUCTIONS

Task 531266-831-848-001 - Modification

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

INCLUDED IN THE REFERENCED PROCEDURES.

WARNING: PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION

BEFORE YOU START A TASK ON OR NEAR:

- THE FLIGHT CONTROLS

- THE FLIGHT CONTROL SURFACES

- THE LANDING GEAR AND THE RELATED DOORS

- COMPONENTS THAT MOVE.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL

WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND

MECHANICALLY SERVICEABLE).

WHEN YOU DO MAINTENANCE WORK, REPAIRS OR MODIFICATIONS,

ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND THE WORK AREA

AS CLEAN AS POSSIBLE. TO DO THIS:

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

NECESSARY ON ELECTRICAL WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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

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

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

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

the aircraft can be put back into a serviceable condition.

NOTE: Discarded parts must be managed at the operator’s discretion.

Task Associated Data

**CONF 001

Zone

310

Manpower

TOTAL MANHOURS 110.00

ELAPSED TIME (HOURS) 106.0

**CONF 002

Zone

310

Manpower

TOTAL MANHOURS 110.00

ELAPSED TIME (HOURS) 106.0

**CONF 003

Zone

310

Manpower

TOTAL MANHOURS 110.00

ELAPSED TIME (HOURS) 106.0

**CONF 004

Zone

310

Manpower

TOTAL MANHOURS 110.00

ELAPSED TIME (HOURS) 106.0

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 531266-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-16-00-912-001

Task 20-21-11-911-801

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-11

Non Destructive Test Manual (NTM) Task 51-10-01-250-801

Task 51-10-01-250-802

Structural Repair Manual (SRM) 51-24-00

51-40-11

51-42-00

51-43-00

51-44-00

51-75-12

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

to the Consumable Materials List (CML).

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

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

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

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

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

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

51-40-11.

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

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

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

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

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

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

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

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

20-21-11-911-801.

(l) For the drilling of rivet holes:

- Use a soft lead pencil and make marks to show the position of the rivet holes

- Make sure that you have the correct edge clearance before you drill the

fastener holes

- If not shown otherwise the tolerance for rivet holes is +0.1 mm (+0.004 in.)

- Transfer-drill the existing holes with a pilot hole drill and a drill bush

- Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in.) diameter.

Increase the hole diameter to the correct size for the fastener which you must

install

- Deburr the holes after you have drilled them.

(m) Cut the rivets to the necessary length.

(n) Install rivets immediately after you position the components with sealant. If not,

tacking pins must be installed temporarily in every third hole.

(o) Tag the parts that you must remove and retain to make the subsequent installation

easier.

(p) Put all the retained hardware in identified plastic bags and attach the bags to the

related unit.

(q) For the installation of the wiring, refer to ESPM 20-33-11.

(r) For rotating probe inspection of the holes, refer to NTM Task 51-10-01-250-801. If

the access is difficult use the manual probe, refer to NTM Task 51-10-01-250-802.

(2) Subtask 531266-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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**CONF 002

(1) Subtask 531266-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-16-00-912-001

Task 20-21-11-911-801

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-11

Non Destructive Test Manual (NTM) Task 51-10-01-250-801

Task 51-10-01-250-802

Structural Repair Manual (SRM) 51-24-00

51-40-11

51-42-00

51-43-00

51-44-00

51-75-12

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

to the Consumable Materials List (CML).

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

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

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

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

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

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

51-40-11.

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

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

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

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

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

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

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

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

20-21-11-911-801.

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(l) For the drilling of rivet holes:

- Use a soft lead pencil and make marks to show the position of the rivet holes

- Make sure that you have the correct edge clearance before you drill the

fastener holes

- If not shown otherwise the tolerance for rivet holes is +0.1 mm (+0.004 in.)

- Transfer-drill the existing holes with a pilot hole drill and a drill bush

- Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in.) diameter.

Increase the hole diameter to the correct size for the fastener which you must

install

- Deburr the holes after you have drilled them.

(m) Cut the rivets to the necessary length.

(n) Install rivets immediately after you position the components with sealant. If not,

tacking pins must be installed temporarily in every third hole.

(o) Tag the parts that you must remove and retain to make the subsequent installation

easier.

(p) Put all the retained hardware in identified plastic bags and attach the bags to the

related unit.

(q) For the installation of the wiring, refer to ESPM 20-33-11.

(r) For rotating probe inspection of the holes, refer to NTM Task 51-10-01-250-801. If

the access is difficult use the manual probe, refer to NTM Task 51-10-01-250-802.

(2) Subtask 531266-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 003

(1) Subtask 531266-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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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 20-16-00-912-001

Task 20-21-11-911-801

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-11

Non Destructive Test Manual (NTM) Task 51-10-01-250-801

Task 51-10-01-250-802

Structural Repair Manual (SRM) 51-24-00

51-40-11

51-42-00

51-43-00

51-44-00

51-75-12

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

to the Consumable Materials List (CML).

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

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

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

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

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

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

51-40-11.

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

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

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

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

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

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

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

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

20-21-11-911-801.

(l) For the drilling of rivet holes:

- Use a soft lead pencil and make marks to show the position of the rivet holes

- Make sure that you have the correct edge clearance before you drill the

fastener holes

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- If not shown otherwise the tolerance for rivet holes is +0.1 mm (+0.004 in.)

- Transfer-drill the existing holes with a pilot hole drill and a drill bush

- Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in.) diameter.

Increase the hole diameter to the correct size for the fastener which you must

install

- Deburr the holes after you have drilled them.

(m) Cut the rivets to the necessary length.

(n) Install rivets immediately after you position the components with sealant. If not,

tacking pins must be installed temporarily in every third hole.

(o) Tag the parts that you must remove and retain to make the subsequent installation

easier.

(p) Put all the retained hardware in identified plastic bags and attach the bags to the

related unit.

(q) For the installation of the wiring, refer to ESPM 20-33-11.

(r) For rotating probe inspection of the holes, refer to NTM Task 51-10-01-250-801. If

the access is difficult use the manual probe, refer to NTM Task 51-10-01-250-802.

(2) Subtask 531266-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF 004

(1) Subtask 531266-910-201-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

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

06-31-53, Page Block 001

06-41-53, Page Block 001

Task 20-16-00-912-001

Task 20-21-11-911-801

Consumable Material List (CML)

Elec. Std. Practices Manual (ESPM) 20-33-11

Non Destructive Test Manual (NTM) Task 51-10-01-250-801

Task 51-10-01-250-802

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References

Structural Repair Manual (SRM) 51-24-00

51-40-11

51-42-00

51-43-00

51-44-00

51-75-12

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

to the Consumable Materials List (CML).

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

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

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

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

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

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

51-40-11.

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

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

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

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

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

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

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

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

20-21-11-911-801.

(l) For the drilling of rivet holes:

- Use a soft lead pencil and make marks to show the position of the rivet holes

- Make sure that you have the correct edge clearance before you drill the

fastener holes

- If not shown otherwise the tolerance for rivet holes is +0.1 mm (+0.004 in.)

- Transfer-drill the existing holes with a pilot hole drill and a drill bush

- Drill new fastener holes with a pilot drill of 2.5 mm (0.098 in.) diameter.

Increase the hole diameter to the correct size for the fastener which you must

install

- Deburr the holes after you have drilled them.

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(m) Cut the rivets to the necessary length.

(n) Install rivets immediately after you position the components with sealant. If not,

tacking pins must be installed temporarily in every third hole.

(o) Tag the parts that you must remove and retain to make the subsequent installation

easier.

(p) Put all the retained hardware in identified plastic bags and attach the bags to the

related unit.

(q) For the installation of the wiring, refer to ESPM 20-33-11.

(r) For rotating probe inspection of the holes, refer to NTM Task 51-10-01-250-801. If

the access is difficult use the manual probe, refer to NTM Task 51-10-01-250-802.

(2) Subtask 531266-839-201-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

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

Service Bulletin.

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 531266-941-201-001 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 70 to Frame 77

from Stringer 1 to Stringer 13

Manpower Resources

Skills NON SPECIFIC

References

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

Task 29-00-00-864-001

Task 36-12-41-000-001

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

configuration before you start a maintenance task:

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

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

- Engine shut down, thrust reversers closed and locked

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- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position.

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

12-34-24-869-002.

(b) Open, safety/lock and tag this (these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

49VU AIR BLEED/X

FEED/VALVE/BAT

2HV D13

49VU AIR BLEED/ENG 1/CTL 3HA1 D12

49VU AIR BLEED/ENG 1/MONG 2HA1 D11

122VU AIR BLEED/ENG 2/CTL 3HA2 Z23

122VU AIR BLEED/ENG 2/MONG 2HA2 Z22

122VU AIR BLEED/X FEED

VALVE/NORM

1HV Z20

(c) Put the access platform in position below the access doors 312AR and 314AR.

(d) Open the access doors 312AR and 314AR.

(e) Put access platform(s) in the location Frame 70 thru Frame 77.

(f) Make sure that the pressure is released from the green and yellow hydraulic

systems, refer to AMM Task 29-00-00-864-001.

(g) Put warning notices in position to tell persons not to operate the hydraulic systems.

(h) Carefully loosen the hydraulic lines at Frame 72 to gain access to the modified

areas.

(i) Carefully loosen the wire and remove all wire clamps to gain access to the modified

areas.

(j) Carefully loosen the light 4LJ to gain access to the modified areas.

(k) Remove the APU bleed air duct between frame 71 and frame 77 to get access to

the modified areas, refer to AMM Task 36-12-41-000-001.

(l) Protect the THS upper panel to avoid unwanted delamination caused by tools.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 39

6

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**CONF 002

(1) Subtask 531266-941-201-001 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 70 to Frame 77

from Stringer 1 to Stringer 13

Manpower Resources

Skills NON SPECIFIC

References

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

Task 29-00-00-864-001

Task 36-12-41-000-001

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

configuration before you start a maintenance task:

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

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

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position.

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

12-34-24-869-002.

(b) Open, safety/lock and tag this (these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

49VU AIR BLEED/X

FEED/VALVE/BAT

2HV D13

49VU AIR BLEED/ENG 1/CTL 3HA1 D12

49VU AIR BLEED/ENG 1/MONG 2HA1 D11

122VU AIR BLEED/ENG 2/CTL 3HA2 Z23

122VU AIR BLEED/ENG 2/MONG 2HA2 Z22

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 40

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PANEL DESIGNATION FIN LOCATION SEE

NOTES

122VU AIR BLEED/X FEED

VALVE/NORM

1HV Z20

(c) Put the access platform in position below the access doors 312AR and 314AR.

(d) Open the access doors 312AR and 314AR.

(e) Put access platform(s) in the location Frame 70 thru Frame 77.

(f) Make sure that the pressure is released from the green and yellow hydraulic

systems, refer to AMM Task 29-00-00-864-001.

(g) Put warning notices in position to tell persons not to operate the hydraulic systems.

(h) Carefully loosen the hydraulic lines at Frame 72 to gain access to the modified

areas.

(i) Carefully loosen the wire and remove all wire clamps to gain access to the modified

areas.

(j) Carefully loosen the light 4LJ to gain access to the modified areas.

(k) Remove the APU bleed air duct between frame 71 and frame 77 to get access to

the modified areas, refer to AMM Task 36-12-41-000-001.

(l) Protect the THS upper panel to avoid unwanted delamination caused by tools.

**CONF 003

(1) Subtask 531266-941-201-001 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 70 to Frame 77

from Stringer 1 to Stringer 13

Manpower Resources

Skills NON SPECIFIC

References

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

Task 29-00-00-864-001

Task 36-12-41-000-001

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

configuration before you start a maintenance task:

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

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

- Engine shut down, thrust reversers closed and locked

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 41

6

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- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position.

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

12-34-24-869-002.

(b) Open, safety/lock and tag this (these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

49VU AIR BLEED/X

FEED/VALVE/BAT

2HV D13

49VU AIR BLEED/ENG 1/CTL 3HA1 D12

49VU AIR BLEED/ENG 1/MONG 2HA1 D11

122VU AIR BLEED/ENG 2/CTL 3HA2 Z23

122VU AIR BLEED/ENG 2/MONG 2HA2 Z22

122VU AIR BLEED/X FEED

VALVE/NORM

1HV Z20

(c) Put the access platform in position below the access doors 312AR and 314AR.

(d) Open the access doors 312AR and 314AR.

(e) Put access platform(s) in the location Frame 70 thru Frame 77.

(f) Make sure that the pressure is released from the green and yellow hydraulic

systems, refer to AMM Task 29-00-00-864-001.

(g) Put warning notices in position to tell persons not to operate the hydraulic systems.

(h) Carefully loosen the hydraulic lines at Frame 72 to gain access to the modified

areas.

(i) Carefully loosen the wire and remove all wire clamps to gain access to the modified

areas.

(j) Carefully loosen the light 4LJ to gain access to the modified areas.

(k) Remove the APU bleed air duct between frame 71 and frame 77 to get access to

the modified areas, refer to AMM Task 36-12-41-000-001.

(l) Protect the THS upper panel to avoid unwanted delamination caused by tools.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 42

6

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SERVICE BULLETIN

**CONF 004

(1) Subtask 531266-941-201-001 - Job Set-up

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 70 to Frame 77

from Stringer 1 to Stringer 13

Manpower Resources

Skills NON SPECIFIC

References

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

Task 29-00-00-864-001

Task 36-12-41-000-001

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

configuration before you start a maintenance task:

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

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

- Engine shut down, thrust reversers closed and locked

- Aircraft in clean configuration

- Parking brake applied

- Aircraft electrical network de-energized

- Hydraulic systems depressurized

- Access to the cockpit and cabin is available

- All circuit breakers are in closed position

- All controls in NORM, AUTO or OFF position.

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

12-34-24-869-002.

(b) Open, safety/lock and tag this (these) circuit breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

49VU AIR BLEED/X

FEED/VALVE/BAT

2HV D13

49VU AIR BLEED/ENG 1/CTL 3HA1 D12

49VU AIR BLEED/ENG 1/MONG 2HA1 D11

122VU AIR BLEED/ENG 2/CTL 3HA2 Z23

122VU AIR BLEED/ENG 2/MONG 2HA2 Z22

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 43

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PANEL DESIGNATION FIN LOCATION SEE

NOTES

122VU AIR BLEED/X FEED

VALVE/NORM

1HV Z20

(c) Put the access platform in position below the access doors 312AR and 314AR.

(d) Open the access doors 312AR and 314AR.

(e) Put access platform(s) in the location Frame 70 thru Frame 77.

(f) Make sure that the pressure is released from the green and yellow hydraulic

systems, refer to AMM Task 29-00-00-864-001.

(g) Put warning notices in position to tell persons not to operate the hydraulic systems.

(h) Carefully loosen the hydraulic lines at Frame 72 to gain access to the modified

areas.

(i) Carefully loosen the wire and remove all wire clamps to gain access to the modified

areas.

(j) Carefully loosen the light 4LJ to gain access to the modified areas.

(k) Remove the APU bleed air duct between frame 71 and frame 77 to get access to

the modified areas, refer to AMM Task 36-12-41-000-001.

(l) Protect the THS upper panel to avoid unwanted delamination caused by tools.

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 531266-020-201-001 - Remove the Angles, Webs, Brackets and Clips at

Frame 72, between STGR13, LH and STGR1, RH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 72

from Stringer 13 LH to Stringer 1 RH

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 44

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Manpower Resources

Manhours 13.00

Minimum number of person 1

Subtask elapsed time 13.00

Skills AIRFRAME

NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) Task 51-10-01-250-801

51-10-08

Fig. A-GBAAA

Location of Inspection Area for Clips at

FR72/FR74

Sheet 01

Fig. A-GBBAA

Removal/Installation of Angles, Webs,

Brackets and Clips at FR72

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the items between STGR13 and STGR11 LH, refer to Fig. A-GBBAA

Sheet 01 and Fig. A-GBBAA Sheet 02.

1 As shown in View B, remove:

26 Pin-Rivet Discard

26 Collar Discard

6 Rivet Discard

2 As shown in Section B-B, remove:

2 Pin-Rivet Discard

2 Collar Discard

3 As shown in View D, remove:

16 Pin-Rivet Discard

16 Collar Discard

4 Remove:

1 Angle D5357113140000 Item (1) Discard

1 Web D5357113146800 Item (3) Discard

1 Web D5357113143800 Item (5) Discard

1 Bracket-Z D9357073720000 Item (133) Retain

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 45

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5 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(b) Remove the items between STGR11 and STGR9 LH, refer to Fig. A-GBBAA Sheet

01 and Fig. A-GBBAA Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STRG11 (Section A-A) and

2 Rivet Discard

from the angle at STGR10 (Section A-A).

Remove:

23 Pin-Rivet Discard

23 Collar Discard

11 Rivet Discard

from View B.

2 As shown in View F, remove:

19 Pin-Rivet Discard

19 Collar Discard

16 Rivet Discard

3 Remove:

1 Clip D5357113144000 Item (7) Discard

1 Clip D5357113146600 Item (9) Discard

1 Web D5357113143600 Item (11) Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 46

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1 Bracket-Z D9357073720000 Item (133) Retain

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(c) Remove the items between STGR9 and STGR7 LH, refer to Fig. A-GBBAA Sheet

01 and Fig. A-GBBAA Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR9 (Section A-A) and

2 Rivet Discard

from the angle at STGR8 (Section A-A).

Remove:

31 Pin-Rivet Discard

31 Collar Discard

from View B.

2 As shown in View F, remove:

21 Pin-Rivet Discard

21 Collar Discard

14 Rivet Discard

3 Remove:

1 Angle D5357113145600 Item (13) Discard

1 Clip D5357113145000 Item (15) Discard

1 Angle D5357113145400 Item (17) Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 47

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1 Clip D5357113144800 Item (19) Discard

1 Web D5357113144600 Item (21) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(d) Remove the items between STGR7 and STGR5 LH, refer to Fig. A-GBBAA Sheet

01 and Fig. A-GBBAA Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR7 (Section A-A) and

2 Rivet Discard

from the angle at STGR6 (Section A-A).

Remove:

33 Pin-Rivet Discard

33 Collar Discard

2 Rivet Discard

from View B.

2 As shown in View F, remove:

28 Pin-Rivet Discard

28 Collar Discard

10 Rivet Discard

3 Remove:

1 Angle D5357113145200 Item (23) Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 48

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1 Angle D5357113145800 Item (25) Discard

1 Clip D5357113144400 Item (27) Discard

1 Angle D5357072225600 Item (29) Discard

1 Clip D5357072224400 Item (31) Discard

1 Angle D5357072226000 Item (33) Discard

1 Web D5357113144200 Item (35) Discard

1 Bracket-Z D9357073720000 Item (133) Retain

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(e) Remove the items between STGR5 and STGR3 LH, refer to Fig. A-GBBAA Sheet

01 and Fig. A-GBBAA Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR5 (Section A-A) and

2 Rivet Discard

from the angle at STGR4 (Section A-A).

Remove:

20 Pin-Rivet Discard

8 Collar Discard

12 Nut Discard

from View B.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 49

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2 As shown in View F, remove:

19 Pin-Rivet Discard

19 Collar Discard

14 Rivet Discard

3 Remove:

1 Angle D5357072225400 Item (36) Discard

1 Angle D5357072225800 Item (38) Discard

1 Clip D5357072224600 Item (40) Discard

1 Angle D5357072225200 Item (42) Discard

1 Web D5357072224800 Item (44) Discard

1 Clip D5357072225000 Item (46) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(f) Remove the items at STGR1 RH and LH, refer to Fig. A-GBBAA Sheet 01 and Fig.

A-GBBAA Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR1 (Section A-A).

10 Pin-Rivet Discard

10 Nut Discard

from View B.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 50

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2 As shown in View E, remove:

7 Pin-Rivet Discard

7 Nut Discard

8 Rivet Discard

3 Remove:

1 Clip D5357072224200 Item (48) Discard

1 Web D5357072224000 Item (49) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(2) Subtask 531266-420-201-001 - Install the Angles, Webs, Brackets and Clips at

Frame 72, between STGR1, RH and STGR13, LH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 72

from Stringer 1 RH to Stringer 13 LH

Manpower Resources

Manhours 16.00

Minimum number of person 1

Subtask elapsed time 16.00

Skills AIRFRAME

Material necessary to do the job

Kit 531266D01R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 D5357113140000 1 ANGLE

3 D5357113146800 1 WEB

5 D5357113143800 1 WEB

7 D5357113144000 1 CLIP

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 51

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 D5357113146600 1 CLIP

11 D5357113143600 1 WEB

13 D5357113145600 1 ANGLE

15 D5357113145000 1 CLIP

17 D5357113145400 1 ANGLE

19 D5357113144800 1 CLIP

21 D5357113144600 1 WEB

23 D5357113145200 1 ANGLE

25 D5357113145800 1 ANGLE

27 D5357113144400 1 CLIP

29 D5357072225600 1 ANGLE

31 D5357072224400 1 CLIP

33 D5357072226000 1 ANGLE

35 D5357113144200 1 WEB

36 D5357072225400 1 ANGLE

38 D5357072225800 1 ANGLE

40 D5357072224600 1 CLIP

42 D5357072225200 1 ANGLE

44 D5357072224800 1 WEB

46 D5357072225000 1 CLIP

48 D5357072224200 1 CLIP

49 D5357072224000 1 WEB

102 DAN5-6-4X 31 PIN

103 DAN11-6X 143 COLLAR

104 DAN5-6-5X 40 PIN

106 EN6081D5-06 33 RIVET

107 DAN5-6-5 16 PIN

108 NSA5075-6 55 COLLAR

109 DAN5-5-6 15 PIN

110 NSA5075-5 27 COLLAR

111 DAN5-5-5 12 PIN

112 DAN5-6-6 2 PIN

113 DAN5-6-3X 3 PIN

114 DAN5-8-5X 10 PIN

115 DAN11-8X 29 COLLAR

116 DAN5-8-4X 2 PIN

117 DAN5-8-7X 8 PIN

118 DAN5-8-8X 2 PIN

119 DAN6-6-3X 8 PIN

120 DAN6-6-4X 29 PIN

121 DAN6-6-5X 16 PIN

122 EN6069D5-06 12 RIVET

123 DAN6-8-6X 7 PIN

124 DAN6-6-7X 10 PIN

125 DAN6-6-7 19 PIN

126 DAN6-6-6 4 PIN

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 52

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

127 DAN6-6-5 3 PIN

128 DAN6-6-3 8 PIN

129 DAN5-6-3 4 PIN

132 DAN6-6-6X 6 PIN

135 EN6081D5-08 2 RIVET

136 EN6069D5-07 33 RIVET

137 EN6069D5-08 17 RIVET

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant, Brush Consistency 09-013 As required

Corrosion Preventative

Compound, Temporary

15-009 As required

Anti-Corrosion Primer

Polyurethane

16-001 As required

Polyurethane Finish Paint 16-018 As required

References

Consumable Material List (CML)

Fig. A-GBBAA

Removal/Installation of Angles, Webs,

Brackets and Clips at FR72

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-GBDAA

Fastener Symbol Identification

Sheet 01

NOTE: The structural parts listed in the above kit are defined with suffix 00 and

include pilot holes. Alternatively, the equivalent parts may be supplied

without holes for ease of installation. The alternative parts will have suffix

90 and are fully interchangeable.

(a) Install the items between STGR1 LH and RH, refer to Fig. A-GBBAA Sheet 03 and

Fig. A-GBDAA Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Web D5357072224000 Item 49

with:

8 Pin DAN5-8-7X Item 117

8 Collar DAN11-8X Item 115

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 53

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and then install:

1 Clip D5357072224200 Item 48

with:

2 PIN DAN5-8-8X Item 118

2 Collar DAN11-8X Item 115

2 As shown in Section E-E, install:

2 Pin DAN5-6-3 Item 129

2 Collar NSA5075-6 Item 108

3 As shown in View K, install:

7 Pin DAN6-8-6X Item 123

7 Collar DAN11-8X Item 115

5 Rivet EN6069D5-07 Item 136

3 Rivet EN6069D5-08 Item 137

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 115,117, 118 and 123.

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 106, 115, 117, 118, 123, 136 and 137.

(b) Install the items between STGR3 and STGR4 on the LH Side, refer to Fig. AGBBAA Sheet 03, Fig. A-GBBAA Sheet 04 and Fig. A-GBDAA Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 54

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to wet install on Frame 72, as shown in View G:

1 Angle D5357072225200 Item 42

1 Clip D5357072225000 Item 46

with:

4 Pin DAN5-8-5X Item 114

4 Collar DAN11-8X Item 115

3 Pin DAN5-5-5 Item 111

3 Collar NSA5075-5 Item 110

2 As shown in Section C-C, STGR4 install:

2 Rivet EN6081D5-06 Item 106

3 As shown in View L, install between STGR3 and STGR4:

3 Pin DAN6-6-5X Item 121

4 Pin DAN6-6-7X Item 124

7 Collar DAN11-6X Item 103

7 Rivet EN6069D5-08 Item 137

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

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

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

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

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 55

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SERVICE BULLETIN

(c) Install the items between STGR4 and STGR5 on the LH Side, refer to Fig. AGBBAA Sheet 03, Fig. A-GBBAA Sheet 04 and Fig. A-GBDAA Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357072225400 Item 36

1 Web D5357072224800 Item 44

with:

2 Pin DAN5-8-4X Item 116

2 Collar DAN11-8X Item 115

and then install:

1 Clip D5357072224600 Item 40

with:

6 Pin DAN5-8-5X Item 114

6 Collar DAN11-8X Item 115

and then install:

1 Angle D5357072225800 Item 38

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 110

2 As shown in Section, C-C at STGR5, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in View L, between STGR4 and STGR5, install:

6 Pin DAN6-6-6X Item 132

6 Pin DAN6-6-7X Item 124

12 Collar DAN11-6X Item 103

7 Rivet EN6069D5-08 Item 137

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 56

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SERVICE BULLETIN

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

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

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

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

137.

(d) Install the items between STGR5 and STGR7 on the LH Side, refer to Fig. AGBBAA Sheet 03, Fig. A-GBBAA Sheet 04 and Fig. A-GBDAA Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357072225600 Item 29

1 Angle D5357113145200 Item 23

1 Web D5357113144200 Item 35

with:

9 Pin DAN5-6-4X Item 102

9 Collar DAN11-6X Item 103

2 Rivet EN6081D5-08 Item 135

and then between STGR5 and STGR6 install:

1 Clip D5357072224400 Item 31

with:

7 Pin DAN5-6-5X Item 104

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 57

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SERVICE BULLETIN

7 Collar DAN11-6X Item 103

and then between STGR5 and STGR6 install:

1 Angle D5357072226000 Item 33

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 110

and then between STGR6 and STGR7 install:

1 Clip D5357113144400 Item 27

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

and then between STGR6 and STGR7 install:

1 Angle D5357113145800 Item 25

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 110

2 As shown in Section C-C, at STGR6, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section C-C, at STGR7, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View L, between STGR5 and STGR7, install:

19 Pin DAN6-6-7 Item 125

23 Collar NSA5075-6 Item 108

9 Rivet EN6069D5-07 Item 136

4 Pin DAN6-6-6 Item 126

4 Pin DAN6-6-5X Item 121

4 Collar DAN11-6X Item 103

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 58

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SERVICE BULLETIN

1 Pin DAN6-6-5 Item 127

1 Rivet EN6069D5-06 Item 122

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

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

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

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

127 and 136.

(e) Install the items between STGR7 and STGR9 on the LH Side, refer to Fig. AGBBAA Sheet 03, Fig. A-GBBAA Sheet 04 and Fig. A-GBDAA Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357113145600 Item 13

1 Angle D5357113145400 Item 17

NOTE: Item 13 and Item 17 are temporally held in place.

Then between STGR7 and STGR9 install:

1 Web D5357113144600 Item 21

with:

10 Pin DAN5-6-4X Item 102

10 Collar DAN11-6X Item 103

and then between STGR7 and STGR8 install:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 59

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SERVICE BULLETIN

1 Clip D5357113144800 Item 19

with:

5 Pin DAN5-6-5X Item 104

5 Collar DAN11-6X Item 103

4 Pin DAN5-5-5 Item 111

4 Collar NSA5075-5 Item 110

and then between Stringer STGR8 and STGR9 install:

1 Clip D5357113145000 Item 15

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

5 Pin DAN5-5-5 Item 111

5 Collar NSA5075-5 Item 110

2 As shown in Section C-C, at STGR8, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section C-C, at STGR9, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View L, between STGR7 and STGR9, install:

10 Pin DAN6-6-4X Item 120

19 Collar DAN11-6X Item 103

12 Rivet EN6069D5-07 Item 136

2 Rivet EN6069D5-06 Item 122

2 Pin DAN6-6-5 Item 127

9 Pin DAN6-6-5X Item 121

2 Collar NSA5075-6 Item 108

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 60

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SERVICE BULLETIN

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 108, 110, 111, 120, 122, and 127.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 110, 111, 120, 121, 122, 127

and 136.

(f) Install the items between STGR9 and STGR11 on the LH Side, refer to Fig. AGBBAA Sheet 03, Fig. A-GBBAA Sheet 04 and Fig. A-GBDAA Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Bracket-Z D9357073720000 Item (133) Retained at

removal

1 Web D5357113143600 Item 11

with:

2 Rivet EN6081D5-06 Item 106

9 Pin DAN5-6-4X Item 102

9 Collar DAN11-6X Item 103

and then STGR9 and STGR10, install:

1 Clip D5357113146600 Item 9

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 61

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SERVICE BULLETIN

5 Rivet EN6081D5-06 Item 106

and then between STGR10 and STGR11, install:

1 Clip D5357113144000 Item 7

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

4 Rivet EN6081D5-06 Item 106

2 As shown in Section C-C, at STGR10 install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section C-C, at STGR11 install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View L, between STGR9 and STGR11, install:

10 Pin DAN6-6-4X Item 120

19 Collar DAN11-6X Item 103

7 Rivet EN6069D5-07 Item 136

9 Rivet EN6069D5-06 Item 122

9 Pin DAN6-6-4X Item 120

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 120.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 106, 120, 122 and 136.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 62

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SERVICE BULLETIN

(g) Install the items between STGR11 and STGR13 on the LH Side, refer to Fig. AGBBAA Sheet 03 and Fig. A-GBDAA Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Bracket-Z D9357073720000 Item (133) Retained at

removal

1 Web D5357113143800 Item 5

with:

2 Rivet EN6081D5-06 Item 106

3 Pin DAN5-6-3X Item 113

3 Collar DAN11-6X Item 103

and then install:

1 Web D5357113146800 Item 3

with:

3 Pin DAN5-6-4X Item 102

3 Collar DAN11-6X Item 103

4 Rivet EN6081D5-06 Item 106

and then install:

1 Angle D5357113140000 Item 1

with:

16 Pin DAN5-6-5 Item 107

18 Collar NSA5075-6 Item 108

2 Pin DAN5-6-6 Item 112

2 As shown in Section D-D, at STGR12, install:

2 Pin DAN5-6-3 Item 129

2 Collar NSA5075-6 Item 108

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 63

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SERVICE BULLETIN

3 As shown in View J, install:

8 Pin DAN6-6-3X Item 119

8 Collar DAN11-6X Item 103

8 Pin DAN6-6-3 Item 128

8 Collar NSA5075-6 Item 108

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 107, 108, 113, 119, 112 and 128.

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 106, 107, 108, 113, 119, 112 and 128.

(3) Subtask 531266-020-208-001 - Remove the Angles, Webs, Brackets and Clips at

Frame 72, between STGR13, RH and STGR3, RH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 72

from Stringer 13 RH to Stringer 3 RH

Manpower Resources

Manhours 11.00

Minimum number of person 1

Subtask elapsed time 11.00

Skills AIRFRAME

NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) Task 51-10-01-250-801

51-10-08

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 64

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References

Fig. A-GBAAA

Location of Inspection Area for Clips at

FR72/FR74

Sheet 01

Fig. A-GBBAA

Removal/Installation of Angles, Webs,

Brackets and Clips at FR72

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the items between STGR13 and STGR11 RH, refer to Fig. A-GBBAA

Sheet 01 and Fig. A-GBBAA Sheet 02.

1 As shown in View B, remove:

26 Pin-Rivet Discard

26 Collar Discard

6 Rivet Discard

2 As shown in Section B-B, remove:

2 Pin-Rivet Discard

2 Collar Discard

3 As shown in View D, remove:

16 Pin-Rivet Discard

16 Collar Discard

4 Remove:

1 Angle D5357113140100 Item (2) Discard

1 Web D5357113146900 Item (4) Discard

1 Web D5357113143900 Item (6) Discard

1 Bracket-Z D9357073720000 Item (133) Retain

5 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 65

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SERVICE BULLETIN

- If no cracks are found, do the worksteps that follow.

(b) Remove the items between STGR11 and STGR9 RH, refer to Fig. A-GBBAA Sheet

01 and Fig. A-GBBAA Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STRG11 (Section A-A) and

2 Rivet Discard

from the angle at STGR10 (Section A-A).

Remove:

23 Pin-Rivet Discard

23 Collar Discard

11 Rivet Discard

from View B.

2 As shown in View F, remove:

19 Pin-Rivet Discard

19 Collar Discard

16 Rivet Discard

3 Remove:

1 Clip D5357113144100 Item (8) Discard

1 Clip D5357113146700 Item (10) Discard

1 Web D5357113143700 Item (12) Discard

1 Bracket-Z D9357073720000 Item (133) Retain

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 66

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SERVICE BULLETIN

- If no cracks are found, do the worksteps that follow.

(c) Remove the items between STGR9 and STGR7 RH, refer to Fig. A-GBBAA Sheet

01 and Fig. A-GBBAA Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR9 (Section A-A) and

2 Rivet Discard

from the angle at STGR8 (Section A-A).

Remove:

31 Pin-Rivet Discard

31 Collar Discard

from View B.

2 As shown in View F, remove:

21 Pin-Rivet Discard

21 Collar Discard

14 Rivet Discard

3 Remove:

1 Angle D5357113145700 Item (14) Discard

1 Clip D5357113145100 Item (16) Discard

1 Angle D5357113145500 Item (18) Discard

1 Clip D5357113144900 Item (20) Discard

1 Web D5357113144700 Item (22) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 67

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c Findings:

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

- If no cracks are found, do the worksteps that follow.

(d) Remove the items between STGR7 and STGR5 RH, refer to Fig. A-GBBAA Sheet

01 and Fig. A-GBBAA Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR7 (Section A-A) and

2 Rivet Discard

from the angle at STGR6 (Section A-A).

Remove:

33 Pin-Rivet Discard

33 Collar Discard

2 Rivet Discard

from View B.

2 As shown in View F, remove:

28 Pin-Rivet Discard

28 Collar Discard

10 Rivet Discard

3 As shown in View C, remove:

1 Angle D5357113145300 Item (24) Discard

1 Angle D5357113145900 Item (26) Discard

1 Clip D5357113144500 Item (28) Discard

1 Angle D5357072225700 Item (30) Discard

1 Clip D5357072224500 Item (32) Discard

1 Angle D5357072226100 Item (34) Discard

1 Web D5357116122000 Item (50) Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 68

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SERVICE BULLETIN

1 Bracket-Z D9357073720000 Item (133) Retain

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(e) Remove the items between STGR5 and STGR3 RH, refer to Fig. A-GBBAA Sheet

01 and Fig. A-GBBAA Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR5 (Section A-A) and

2 Rivet Discard

from the angle at STGR4 (Section A-A).

Remove:

20 Pin-Rivet Discard

8 Collar Discard

12 Nut Discard

from View B.

2 As shown in View F, remove:

19 Pin-Rivet Discard

19 Collar Discard

14 Rivet Discard

3 Remove:

1 Angle D5357072225500 Item (37) Discard

1 Angle D5357072225900 Item (39) Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 69

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SERVICE BULLETIN

1 Clip D5357072224700 Item (41) Discard

1 Angle D5357072225300 Item (43) Discard

1 Web D5357072224900 Item (45) Discard

1 Clip D5357072225100 Item (47) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(4) Subtask 531266-420-202-001 - Install the Angles, Webs, Brackets and Clips at

Frame 72, between STGR3, RH to STGR13, RH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 72

from Stringer 3 RH to Stringer 13 RH

Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills AIRFRAME

Material necessary to do the job

Kit 531266D01R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 D5357113140100 1 ANGLE

4 D5357113146900 1 WEB

6 D5357113143900 1 WEB

8 D5357113144100 1 CLIP

10 D5357113146700 1 CLIP

12 D5357113143700 1 WEB

14 D5357113145700 1 ANGLE

16 D5357113145100 1 CLIP

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 70

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

18 D5357113145500 1 ANGLE

20 D5357113144900 1 CLIP

22 D5357113144700 1 WEB

24 D5357113145300 1 ANGLE

26 D5357113145900 1 ANGLE

28 D5357113144500 1 CLIP

30 D5357072225700 1 ANGLE

32 D5357072224500 1 CLIP

34 D5357072226100 1 ANGLE

37 D5357072225500 1 ANGLE

39 D5357072225900 1 ANGLE

41 D5357072224700 1 CLIP

43 D5357072225300 1 ANGLE

45 D5357072224900 1 WEB

47 D5357072225100 1 CLIP

50 D5357116122000 1 WEB

102 DAN5-6-4X 31 PIN

103 DAN11-6X 140 COLLAR

104 DAN5-6-5X 40 PIN

106 EN6081D5-06 33 RIVET

107 DAN5-6-5 16 PIN

108 NSA5075-6 53 COLLAR

109 DAN5-5-6 15 PIN

110 NSA5075-5 27 COLLAR

111 DAN5-5-5 12 PIN

112 DAN5-6-6 2 PIN

113 DAN5-6-3X 3 PIN

114 DAN5-8-5X 10 PIN

115 DAN11-8X 12 COLLAR

116 DAN5-8-4X 2 PIN

119 DAN6-6-3X 8 PIN

120 DAN6-6-4X 29 PIN

121 DAN6-6-5X 12 PIN

122 EN6069D5-06 12 RIVET

124 DAN6-6-7X 10 PIN

125 DAN6-6-7 19 PIN

126 DAN6-6-6 4 PIN

127 DAN6-6-5 3 PIN

128 DAN6-6-3 8 PIN

129 DAN5-6-3 2 PIN

132 DAN6-6-6X 6 PIN

135 EN6081D5-08 2 RIVET

136 EN6069D5-07 28 RIVET

137 EN6069D5-08 14 RIVET

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 71

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SERVICE BULLETIN

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant, Brush Consistency 09-013 As required

Corrosion Preventative

Compound, Temporary

15-009 As required

Anti-Corrosion Primer

Polyurethane

16-001 As required

Polyurethane Finish Paint 16-018 As required

References

Consumable Material List (CML)

Fig. A-GBBAA

Removal/Installation of Angles, Webs,

Brackets and Clips at FR72

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-GBDAA

Fastener Symbol Identification

Sheet 01

NOTE: The structural parts listed in the above kit are defined with suffix 00 and

include pilot holes. Alternatively, the equivalent parts may be supplied

without holes for ease of installation. The alternative parts will have suffix

90 and are fully interchangeable.

(a) Install the items between STGR3 and STGR4 on the RH Side, refer to Fig. AGBBAA Sheet 03,Fig. A-GBBAA Sheet 04 and Fig. A-GBDAA Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357072225300 Item 43

1 Clip D5357072225100 Item 47

with:

4 Pin DAN5-8-5X Item 114

4 Collar DAN11-8X Item 115

3 Pin DAN5-5-5 Item 111

3 Collar NSA5075-5 Item 110

2 As shown in Section C-C at STGR4, install:

2 Rivet EN6081D5-06 Item 106

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 72

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3 As shown in View L, at STGR3 and STGR4, install:

3 Pin DAN6-6-5X Item 121

7 Collar DAN11-6X Item 103

4 Pin DAN6-6-7X Item 124

7 Rivet EN6069D5-08 Item 137

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

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

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

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

(b) Install the items between STGR4 and STGR5 on the RH Side, refer to Fig. AGBBAA Sheet 03,Fig. A-GBBAA Sheet 04 and Fig. A-GBDAA Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357072225500 Item 37

1 Web D5357072224900 Item 45

with:

2 Pin DAN5-8-4X Item 116

2 Collar DAN11-8X Item 115

and then install:

1 Clip D5357072224700 Item 41

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 73

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SERVICE BULLETIN

with:

6 Pin DAN5-8-5X Item 114

6 Collar DAN11-8X Item 115

and then install:

1 Angle D5357072225900 Item 39

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 110

2 As shown in Section C-C at STGR5, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in View L, at STGR4 and STGR5, install:

6 Pin DAN6-6-6X Item 132

12 Collar DAN11-6X Item 103

6 Pin DAN6-6-7X Item 124

7 Rivet EN6069D5-08 Item 137

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

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

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

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

137.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 74

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SERVICE BULLETIN

(c) Install the items between STGR5 and STGR7 on the RH Side, refer to Fig. AGBBAA Sheet 03,Fig. A-GBBAA Sheet 04 and Fig. A-GBDAA Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357072225700 Item 30

1 Angle D5357113145300 Item 24

1 Bracket-Z D9357073720000 Item (133) Retained at

removal

1 Web D5357116122000 Item 50

with:

9 Pin DAN5-6-4X Item 102

9 Collar DAN11-6X Item 103

2 Rivet EN6081D5-08 Item 135

and between STGR5 and STGR7, as shown in View H, install:

1 Clip D5357072224500 Item 32

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

and between STGR5 and STGR7, install:

1 Angle D5357072226100 Item 34

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 110

and between STGR6 and STGR7, install:

1 Clip D5357113144500 Item 28

with:

7 Pin DAN5-6-5X Item 104

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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7 Collar DAN11-6X Item 103

and between STGR6 and STGR7 install:

1 Angle D5357113145900 Item 26

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 110

2 As shown in Section C-C at STGR6, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section C-C at STGR7, install:

2 Rivet EN6081D5-06 Item 106

4 Install to the fuselage skin between STGR5 and STGR7, refer to Fig. AGBBAA Sheet 04, View L:

19 Pin DAN6-6-7 Item 125

24 Collar NSA5075-6 Item 108

9 Rivet EN6069D5-07 Item 136

4 Pin DAN6-6-6 Item 126

4 Pin DAN6-6-5X Item 121

4 Collar DAN11-6X Item 103

1 Pin DAN6-6-5 Item 127

1 Rivet EN6069D5-06 Item 122

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

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

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 76

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6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

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

127 and 136.

(d) Install the items between STGR7 and STGR9 on the RH Side, refer to Fig. AGBBAA Sheet 03, Fig. A-GBBAA Sheet 04 and Fig. A-GBDAA Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357113145700 Item 14

1 Angle D5357113145500 Item 18

NOTE: Item 14 and Item 18 are temporally held in place.

Then between STGR7 and STGR9 install:

1 Web D5357113144700 Item 22

with:

10 Pin DAN5-6-4X Item 102

10 Collar DAN11-6X Item 103

and then between STGR7 and STGR8 install:

1 Clip D5357113144900 Item 20

with:

5 Pin DAN5-6-5X Item 104

5 Collar DAN11-6X Item 103

4 Pin DAN5-5-5 Item 111

4 Collar NSA5075-5 Item 110

and then between Stringer STGR8 and STGR9 install:

1 Clip D5357113145100 Item 16

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 77

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with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

5 Pin DAN5-5-5 Item 111

5 Collar NSA5075-5 Item 110

2 As shown in Section C-C at STGR8, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section C-C at STGR9, install:

2 Rivet EN6081D5-06 Item 106

4 Install to the fuselage skin between STGR7 and STGR9, refer to Fig. AGBBAA Sheet 04, View L:

10 Pin DAN6-6-4X Item 120

16 Collar DAN11-6X Item 103

12 Rivet EN6069D5-07 Item 136

2 Rivet EN6069D5-06 Item 122

2 Pin DAN6-6-5 Item 127

5 Pin DAN6-6-5X Item 121

1 Collar NSA5075-6 Item 108

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 108, 110, 111, 120 and 127.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 78

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SERVICE BULLETIN

to the fasteners, Items 102, 103, 104, 106, 108, 110, 111, 120, 122, 127 and

136.

(e) Install the items between STGR9 and STGR11 on the RH Side, refer to Fig. AGBBAA Sheet 03, Fig. A-GBBAA Sheet 04 and Fig. A-GBDAA Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Bracket-Z D9357073720000 Item (133) Retained at

removal

1 Web D5357113143700 Item 12

with:

2 Rivet EN6081D5-06 Item 106

9 Pin DAN5-6-4X Item 102

9 Collar DAN11-6X Item 103

and then STGR9 and STGR10, install:

1 Clip D5357113146700 Item 10

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

5 Rivet EN6081D5-06 Item 106

and then between STGR10 and STGR11, install:

1 Clip D5357113144100 Item 8

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

4 Rivet EN6081D5-06 Item 106

2 As shown in Section C-C, at STGR 10, install:

2 Rivet EN6081D5-06 Item 106

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 79

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3 As shown in Section C-C, at STGR 11, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View L, between STGR9 and STGR11, install:

19 Pin DAN6-6-4X Item 120

19 Collar DAN11-6X Item 103

7 Rivet EN6069D5-07 Item 136

9 Rivet EN6069D5-06 Item 122

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104 and 120.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 106, 120, 122 and 136.

(f) Install the items between STGR11 and STGR13 on the RH Side, refer to Fig. AGBBAA Sheet 03 and Fig. A-GBDAA Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Bracket-Z D9357073720000 Item (133) Retained at

removal

1 Web D5357113143900 Item 6

with:

2 Rivet EN6081D5-06 Item 106

3 Pin DAN5-6-3X Item 113

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 80

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3 Collar DAN11-6X Item 103

and then install:

1 Web D5357113146900 Item 4

with:

3 Pin DAN5-6-4X Item 102

3 Collar DAN11-6X Item 103

4 Rivet EN6081D5-06 Item 106

and then install:

1 Angle D5357113140100 Item 2

with:

16 Pin DAN5-6-5 Item 107

18 Collar NSA5075-6 Item 108

2 Pin DAN5-6-6 Item 112

2 As shown in Section D-D, at STGR12, install:

2 Pin DAN5-6-3 Item 129

2 Collar NSA5075-6 Item 108

3 As shown in View J, install:

8 Pin DAN6-6-3X Item 119

8 Collar DAN11-6X Item 103

8 Pin DAN6-6-3 Item 128

8 Collar NSA5075-6 Item 108

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 107, 108, 113, 119, 112 and 128.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 81

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5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 106, 107, 108, 113, 119, 112 and 128.

(5) Subtask 531266-020-203-001 - Remove the Angles, Webs, Brackets and Clips at

Frame 74, between STGR12, LH and STGR1, RH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 74

from Stringer 12 LH to Stringer 1 RH

Manpower Resources

Manhours 11.00

Minimum number of person 1

Subtask elapsed time 11.00

Skills AIRFRAME

NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) Task 51-10-01-250-801

51-10-08

Fig. A-GBAAA

Location of Inspection Area for Clips at

FR72/FR74

Sheet 01

Fig. A-GBCAA

Removal/Installation of Angles, Webs,

Brackets and Clips at FR74

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the items between STGR12 and STGR9 LH, refer to Fig. A-GBCAA Sheet

01 and Fig. A-GBCAA Sheet 02.

1 As shown in Section A-A, remove:

2 Rivet Discard

from the angle at STGR11 (Section A-A) and

2 Rivet Discard

from the angle at STGR10 (Section A-A).

Remove:

42 Pin-Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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42 Collar Discard

8 Rivet Discard

from View B.

2 As shown in View E, remove:

27 Pin-Rivet Discard

27 Collar Discard

16 Rivet Discard

3 Remove:

1 Angle D5357113339600 Item (51) Discard

1 Filler D5357113339800 Item (53) Discard

1 Angle D5357113321400 Item (54) Discard

1 Angle D5357113337200 Item (56) Discard

1 Angle D5357113337000 Item (58) Discard

1 Web D5357113340000 Item (60) Discard

1 Web D5357113339400 Item (62) Discard

4 As shown in View F, remove:

5 Pin-Rivet Discard

5 Collar Discard

5 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 83

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(b) Remove the items between STGR9 and STGR7 LH, refer to Fig. A-GBCAA Sheet

01 and Fig. A-GBCAA Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STRG9 (Section A-A) and

2 Rivet Discard

from the angle at STRG8 (Section A-A).

Remove:

27 Pin-Rivet Discard

27 Collar Discard

from View B.

2 As shown in View E, remove:

19 Pin-Rivet Discard

19 Collar Discard

14 Rivet Discard

3 Remove:

1 Angle D5357113339000 Item (64) Discard

1 Clip D5357113338400 Item (66) Discard

1 Web D5357113337800 Item (68) Discard

1 Angle D5357113338800 Item (70) Discard

1 Clip D5357113338200 Item (72) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 84

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- If no cracks are found, do the worksteps that follow.

(c) Remove the items between STGR7 and STGR5 LH, refer to Fig. A-GBCAA Sheet

01.

1 Remove:

2 Rivet Discard

from the angle at STRG7 (Section A-A) and

2 Rivet Discard

from the angle at STRG6 (Section A-A).

Remove:

32 Pin-Rivet Discard

32 Collar Discard

from View B.

2 As shown in View C, remove:

30 Pin-Rivet Discard

30 Collar Discard

8 Rivet Discard

3 Remove:

1 Angle D5357113338600 Item (74) Discard

1 Clip D5357113338000 Item (76) Discard

1 Angle D5357113339200 Item (78) Discard

1 Angle D5357072425400 Item (80) Discard

1 Clip D5357072424200 Item (82) Discard

1 Web D5357113337600 Item (84) Discard

1 Angle D5357072425800 Item (86) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(d) Remove the items between STGR5 and STGR3, refer to Fig. A-GBCAA Sheet 01.

1 Remove:

2 Rivet Discard

from the angle at STRG5 (Section A-A) and

2 Rivet Discard

from the angle at STRG4 (Section A-A).

Remove:

18 Pin-Rivet Discard

18 Collar Discard

from View B.

2 As shown in View C, remove:

17 Pin-Rivet Discard

17 Collar Discard

14 Rivet Discard

3 Remove:

1 Angle D5357072425200 Item (88) Discard

1 Angle D5357072425600 Item (90) Discard

1 Clip D5357072424400 Item (92) Discard

1 Angle D5357072425000 Item (94) Discard

1 Web D5357072424800 Item (96) Discard

1 Clip D5357072424600 Item (98) Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 86

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4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(e) Remove the items between STGR2 LH and STGR1 RH, refer to Fig. A-GBCAA

Sheet 01 and Fig. A-GBCAA Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STRG1 (Section A-A).

Remove:

12 Pin-Rivet Discard

12 Collar Discard

from View B.

2 As shown in View D, remove:

8 Pin-Rivet Discard

8 Collar Discard

8 Pin-Rivet Discard

3 Remove:

1 Clip D5357072224200 Item (48) Discard

1 Web D5357072424000 Item (100) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 87

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c Findings:

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

- If no cracks are found, do the worksteps that follow.

(6) Subtask 531266-420-203-001 - Install the Angles, Webs, Brackets and Clips at

Frame 74, between STGR1, RH and STGR12, LH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 74

from Stringer 1 RH to Stringer 12 LH

Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills AIRFRAME

Material necessary to do the job

Kit 531266D01R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

48 D5357072224200 1 CLIP

51 D5357113339600 1 ANGLE

53 D5357113339800 1 FILLER

54 D5357113321400 1 ANGLE

56 D5357113337200 1 ANGLE

58 D5357113337000 1 ANGLE

60 D5357113340000 1 WEB

62 D5357113339400 1 WEB

64 D5357113339000 1 ANGLE

66 D5357113338400 1 CLIP

68 D5357113337800 1 WEB

70 D5357113338800 1 ANGLE

72 D5357113338200 1 CLIP

74 D5357113338600 1 ANGLE

76 D5357113338000 1 CLIP

78 D5357113339200 1 ANGLE

80 D5357072425400 1 ANGLE

82 D5357072424200 1 CLIP

84 D5357113337600 1 WEB

86 D5357072425800 1 ANGLE

88 D5357072425200 1 ANGLE

90 D5357072425600 1 ANGLE

92 D5357072424400 1 CLIP

94 D5357072425000 1 ANGLE

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 88

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

96 D5357072424800 1 WEB

98 D5357072424600 1 CLIP

100 D5357072424000 1 WEB

102 DAN5-6-4X 21 PIN

103 DAN11-6X 101 COLLAR

104 DAN5-6-5X 4 PIN

105 DAN5-6-6X 5 PIN

106 EN6081D5-06 26 RIVET

108 NSA5075-6 53 COLLAR

109 DAN5-5-6 15 PIN

110 NSA5075-5 26 COLLAR

111 DAN5-5-5 10 PIN

112 DAN5-6-6 24 PIN

114 DAN5-8-5X 25 PIN

115 DAN11-8X 56 COLLAR

116 DAN5-8-4X 2 PIN

117 DAN5-8-7X 10 PIN

118 DAN5-8-8X 2 PIN

120 DAN6-6-4X 27 PIN

121 DAN6-6-5X 17 PIN

122 EN6069D5-06 3 RIVET

123 DAN6-8-6X 8 PIN

124 DAN6-6-7X 13 PIN

125 DAN6-6-7 20 PIN

126 DAN6-6-6 6 PIN

127 DAN6-6-5 3 PIN

130 DAN5-6-7X 4 PIN

131 DAN5-8-6X 9 PIN

132 DAN6-6-6X 6 PIN

133 DAN6-5-7 1 PIN

136 EN6069D5-07 38 RIVET

137 EN6069D5-08 19 RIVET

144 DAN7-6-11X 1 PIN

145 DAN12-6X 1 COLLAR

146 DAN5-6-10X 2 PIN

148 DAN5-6-8X 2 PIN

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant, Brush Consistency 09-013 As required

Corrosion Preventative

Compound, Temporary

15-009 As required

Anti-Corrosion Primer

Polyurethane

16-001 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 89

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ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Polyurethane Finish Paint 16-018 As required

References

Consumable Material List (CML)

Fig. A-GBCAA

Removal/Installation of Angles, Webs,

Brackets and Clips at FR74

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-GBDAA

Fastener Symbol Identification

Sheet 01

NOTE: The structural parts listed in the above kit are defined with suffix 00 and

include pilot holes. Alternatively, the equivalent parts may be supplied

without holes for ease of installation. The alternative parts will have suffix

90 and are fully interchangeable.

(a) Install the items between STGR2 on the RH Side and STGR2 on the LH Side, refer

to Fig. A-GBCAA Sheet 03, Fig. A-GBCAA Sheet 04 and Fig. A-GBDAA Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Web D5357072424000 Item 100

with:

10 Pin DAN5-8-7X Item 117

10 Collar DAN11-8X Item 115

and then install:

1 Clip D5357072224200 Item 48

with:

2 PIN DAN5-8-8X Item 118

2 Collar DAN11-8X Item 115

2 As shown in Section B-B, at STGR1, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in View J, install:

8 Pin DAN6-8-6X Item 123

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 90

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8 Collar DAN11-8X Item 115

3 Rivet EN6069D5-07 Item 136

5 Rivet EN6069D5-08 Item 137

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 117, 115, 123, 118 and 122.

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 117, 115, 123, 118 and 122.

(b) Install the items between STGR3 and STGR5 on the LH Side, refer to Fig. AGBCAA Sheet 03, Fig. A-GBCAA Sheet 04 and Fig. A-GBDAA Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Angle D5357072425000 Item 94

1 Angle D5357072425200 Item 88

1 Clip D5357072424600 Item 98

1 Web D5357072424800 Item 96

with:

3 Pin DAN5-8-6X Item 131

5 Collar DAN11-8X Item 115

2 Pin DAN5-5-5 Item 111

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 91

6

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SERVICE BULLETIN

2 Collar NSA5075-5 Item 110

2 Pin DAN5-8-4X Item 116

and install:

1 Clip D5357072424400 Item 92

with:

6 Pin DAN5-8-5X Item 114

6 Collar DAN11-8X Item 115

and install:

1 Angle D5357072425600 Item 90

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 110

2 As shown in Section B-B, at STGR4, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section B-B, at STGR5, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View H, install:

2 Pin DAN6-6-5X Item 121

6 Pin DAN6-6-6X Item 132

17 Collar DAN11-6X Item 103

9 Pin DAN6-6-7X Item 124

14 Rivet EN6069D5-08 Item 137

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 131, 115, 109, 110, 132, 124, 122, 116, 114 and 103.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 92

6

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SERVICE BULLETIN

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 131, 115, 109, 110, 132, 124, 122, 116, 114 and 103.

(c) Install the items between STGR5 and STGR7 on the LH Side, refer to Fig. AGBCAA Sheet 03, Fig. A-GBCAA Sheet 04 and Fig. A-GBDAA Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Angle D5357072425400 Item 80

1 Angle D5357113338600 Item 74

NOTE: Item 80 and Item 74 are temporally held in place.

Then between STGR5 and STGR7 install:

1 Web D5357113337600 Item 84

with:

10 Pin DAN5-6-4X Item 102

10 Collar DAN11-6X Item 103

and then between Stringer STGR5 and STGR6 install:

1 Clip D5357072424200 Item 82

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

5 Pin DAN5-8-5X Item 114

5 Collar DAN11-8X Item 115

and then between Stringer STGR5 and STGR6 install:

1 Angle D5357072425800 Item 86

with:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 93

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SERVICE BULLETIN

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 110

and then between Stringer STGR6 and STGR7 install:

1 Clip D5357113338000 Item 76

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

5 Pin DAN5-8-5X Item 114

5 Collar DAN11-8X Item 115

and then between Stringer STGR6 and STGR7 install:

1 Angle D5357113339200 Item 78

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 110

2 As shown in Section B-B at STGR6, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section B-B, at STGR7, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View H, install:

19 Pin DAN6-6-7 Item 125

26 Collar NSA5075-6 Item 108

6 Pin DAN6-6-6 Item 126

7 Rivet EN6069D5-07 Item 136

4 Pin DAN6-6-5X Item 121

4 Collar DAN11-6X Item 103

1 Pin DAN6-6-5 Item 127

1 Rivet EN6069D5-06 Item 122

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 94

6

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SERVICE BULLETIN

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

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

and 127.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

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

and 127.

(d) Install the items between Stringer STGR7 and STGR9 on the LH Side, refer to Fig.

A-GBCAA Sheet 03, Fig. A-GBCAA Sheet 04 and Fig. A-GBDAA Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Angle D5357113338800 Item 70

1 Angle D5357113339000 Item 64

NOTE: Item 70 and Item 64 are temporally held in place.

Then between STGR7 and STGR9 install:

1 Web D5357113337800 Item 68

with:

8 Pin DAN5-6-4X Item 102

8 Collar DAN11-6X Item 103

and install:

1 Clip D5357113338200 Item 72

with:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 95

6

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SERVICE BULLETIN

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

4 Pin DAN5-8-5X Item 114

4 Collar DAN11-8X Item 115

4 Pin DAN5-5-5 Item 111

4 Collar NSA5075-5 Item 110

and install:

1 Clip D5357113338400 Item 66

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

5 Pin DAN5-8-5X Item 114

5 Collar DAN11-8X Item 115

4 Pin DAN5-5-5 Item 111

4 Collar NSA5075-5 Item 110

2 As shown in Section B-B, at STGR8, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section B-B, at STGR9, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View K, install:

8 Pin DAN6-6-5X Item 121

17 Collar DAN11-6X Item 103

9 Pin DAN6-6-4X Item 120

2 Pin DAN6-6-5 Item 127

2 Collar NSA5075-6 Item 108

2 Rivet EN6069D5-06 Item 122

12 Rivet EN6069D5-07 Item 136

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 96

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SERVICE BULLETIN

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 114, 115, 111, 110, 121, 127, 108, 122

and 120.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 114, 115, 111, 110, 121, 127, 108, 122

and 120.

(e) Install the items between Stringer STGR9 and STGR12 on the LH Side, refer to

Fig. A-GBCAA Sheet 03, Fig. A-GBCAA Sheet 04 and Fig. A-GBDAA Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Web D5357113339400 Item 62

with:

3 Pin DAN5-6-4X Item 102

3 Collar DAN11-6X Item 103

and install:

1 Angle D5357113339600 Item 51

1 Filler D5357113339800 Item 53

1 Angle D5357113321400 Item 54

with:

24 Pin DAN5-6-6 Item 112

24 Collar NSA5075-6 Item 108

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 97

6

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SERVICE BULLETIN

and install:

1 Web D5357113340000 Item 60

with:

6 Pin DAN5-8-6X Item 131

6 Collar DAN11-8X Item 115

8 Rivet EN6081D5-06 Item 106

5 Pin DAN5-6-6X Item 105

5 Collar DAN11-6X Item 103

and install:

1 Angle D5357113337000 Item 58

1 Angle D5357113337200 Item 56

with:

4 Pin DAN5-6-7X Item 130

4 Collar DAN11-6X Item 103

2 As shown in Section B-B, at STGR10, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section B-B, at STGR11, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View K, install:

18 Pin DAN6-6-4X Item 120

25 Collar DAN11-6X Item 103

16 Rivet EN6069D5-07 Item 136

3 Pin DAN6-6-5X Item 121

4 Pin DAN6-6-7X Item 124

1 Pin DAN6-6-7 Item 125

1 Collar NSA5075-6 Item 108

1 Pin DAN6-5-7 Item 133

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 98

6

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SERVICE BULLETIN

1 Collar NSA5075-5 Item 110

5 As shown in View L, install:

1 Pin DAN7-6-11X Item 144

1 Collar DAN12-6X Item 145

2 Pin DAN5-6-10X Item 146

2 Pin DAN5-6-8X Item 148

4 Collar DAN11-6X Item 103

6 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 112, 108, 121, 124, 131, 115, 106, 105, 120,

130 and 122.

7 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 112, 108, 121, 124, 131, 115, 106, 105, 120,

130 and 122.

(7) Subtask 531266-020-204-001 - Remove the Angles, Webs, Brackets and Clips at

Frame 74, between STGR12, RH and STGR3, RH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 74

from Stringer 12RH to Stringer 3RH

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 99

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SERVICE BULLETIN

Manpower Resources

Manhours 11.00

Minimum number of person 1

Subtask elapsed time 11.00

Skills AIRFRAME

NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) Task 51-10-01-250-801

51-10-08

Fig. A-GBAAA

Location of Inspection Area for Clips at

FR72/FR74

Sheet 01

Fig. A-GBCAA

Removal/Installation of Angles, Webs,

Brackets and Clips at FR74

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the items between STGR12 and STGR9 RH, refer to Fig. A-GBCAA Sheet

01 and Fig. A-GBCAA Sheet 02.

1 As shown in Section A-A, remove:

2 Rivet Discard

from the angle at STGR11 (Section A-A) and

2 Rivet Discard

from the angle at STGR10 (Section A-A).

Remove:

42 Pin-Rivet Discard

42 Collar Discard

8 Rivet Discard

from View B.

2 As shown in View E, remove:

27 Pin-Rivet Discard

27 Collar Discard

16 Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 100

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SERVICE BULLETIN

3 Remove:

1 Angle D5357113339700 Item (52) Discard

1 Filler D5357113339800 Item (53) Discard

1 Angle D5357113321500 Item (55) Discard

1 Angle D5357113337300 Item (57) Discard

1 Angle D5357113337100 Item (59) Discard

1 Web D5357113340100 Item (61) Discard

1 Web D5357113339500 Item (63) Discard

4 As shown in View F, remove:

5 Pin-Rivet Discard

5 Collar Discard

5 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(b) Remove the items between STGR9 and STGR7 RH, refer to Fig. A-GBCAA Sheet

01 and Fig. A-GBCAA Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STRG9 (Section A-A) and

2 Rivet Discard

from the angle at STRG8 (Section A-A).

Remove:

27 Pin-Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 101

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SERVICE BULLETIN

27 Collar Discard

from View B.

2 As shown in View E, remove:

19 Pin-Rivet Discard

19 Collar Discard

14 Rivet Discard

3 Remove:

1 Angle D5357113339100 Item (65) Discard

1 Clip D5357113338500 Item (67)

1 Web D5357113337900 Item (69) Discard

1 Angle D5357113338900 Item (71) Discard

1 Clip D5357113338300 Item (73) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(c) Remove the items between STGR7 and STGR5, refer to Fig. A-GBCAA Sheet 01.

1 Remove:

2 Rivet Discard

from the angle at STRG7 (Section A-A) and

2 Rivet Discard

from the angle at STRG6 (Section A-A).

Remove:

32 Pin-Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 102

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SERVICE BULLETIN

32 Collar Discard

from View B.

2 As shown in View C, remove:

30 Pin-Rivet Discard

30 Collar Discard

8 Rivet Discard

3 Remove:

1 Angle D5357113338700 Item (75) Discard

1 Clip D5357113338100 Item (77) Discard

1 Angle D5357113339300 Item (79) Discard

1 Angle D5357072425500 Item (81) Discard

1 Clip D5357072424300 Item (83) Discard

1 Web D5357113337700 Item (85) Discard

1 Angle D5357072425900 Item (87) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(d) Remove the items between STGR5 and STGR3, refer to Fig. A-GBCAA Sheet 01.

1 Remove:

2 Rivet Discard

from the angle at STRG5 (Section A-A) and

2 Rivet Discard

from the angle at STRG4 (Section A-A).

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 103

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SERVICE BULLETIN

Remove:

18 Pin-Rivet Discard

18 Collar Discard

from View B.

2 As shown in View C, remove:

17 Pin-Rivet Discard

17 Collar Discard

14 Rivet Discard

3 Remove:

1 Angle D5357072425300 Item (89) Discard

1 Angle D5357072425700 Item (91) Discard

1 Clip D5357072424500 Item (93) Discard

1 Angle D5357072425100 Item (95) Discard

1 Web D5357072424900 Item (97) Discard

1 Clip D5357072424700 Item (99) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(8) Subtask 531266-420-204-001 - Install the Angles, Webs, Brackets and Clips at

Frame 74, between STGR3, RH and STGR12, RH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 74

from Stringer 3 RH to Stringer 12 RH

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 104

6

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SERVICE BULLETIN

Manpower Resources

Manhours 12.00

Minimum number of person 1

Subtask elapsed time 12.00

Skills AIRFRAME

Material necessary to do the job

Kit 531266D01R04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

52 D5357113339700 1 ANGLE

53 D5357113339800 1 FILLER

55 D5357113321500 1 ANGLE

57 D5357113337300 1 ANGLE

59 D5357113337100 1 ANGLE

61 D5357113340100 1 WEB

63 D5357113339500 1 WEB

65 D5357113339100 1 ANGLE

67 D5357113338500 1 CLIP

69 D5357113337900 1 WEB

71 D5357113338900 1 ANGLE

73 D5357113338300 1 CLIP

75 D5357113338700 1 ANGLE

77 D5357113338100 1 CLIP

79 D5357113339300 1 ANGLE

81 D5357072425500 1 ANGLE

83 D5357072424300 1 CLIP

85 D5357113337700 1 WEB

87 D5357072425900 1 ANGLE

89 D5357072425300 1 ANGLE

91 D5357072425700 1 ANGLE

93 D5357072424500 1 CLIP

95 D5357072425100 1 ANGLE

97 D5357072424900 1 WEB

99 D5357072424700 1 CLIP

102 DAN5-6-4X 21 PIN

103 DAN11-6X 101 COLLAR

104 DAN5-6-5X 4 PIN

105 DAN5-6-6X 5 PIN

106 EN6081D5-06 24 RIVET

108 NSA5075-6 53 COLLAR

109 DAN5-5-6 15 PIN

110 NSA5075-5 26 COLLAR

111 DAN5-5-5 10 PIN

112 DAN5-6-6 24 PIN

114 DAN5-8-5X 25 PIN

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 105

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

115 DAN11-8X 36 COLLAR

116 DAN5-8-4X 2 PIN

120 DAN6-6-4X 27 PIN

121 DAN6-6-5X 17 PIN

122 EN6069D5-06 3 RIVET

124 DAN6-6-7X 13 PIN

125 DAN6-6-7 20 PIN

126 DAN6-6-6 6 PIN

127 DAN6-6-5 3 PIN

130 DAN5-6-7X 4 PIN

131 DAN5-8-6X 9 PIN

132 DAN6-6-6X 6 PIN

133 DAN6-5-7 1 PIN

136 EN6069D5-07 35 RIVET

137 EN6069D5-08 14 RIVET

144 DAN7-6-11X 1 PIN

145 DAN12-6X 1 COLLAR

146 DAN5-6-10X 2 PIN

148 DAN5-6-8X 2 PIN

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant, Brush Consistency 09-013 As required

Corrosion Preventative

Compound, Temporary

15-009 As required

Anti-Corrosion Primer

Polyurethane

16-001 As required

Polyurethane Finish Paint 16-018 As required

References

Consumable Material List (CML)

Fig. A-GBCAA

Removal/Installation of Angles, Webs,

Brackets and Clips at FR74

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-GBDAA

Fastener Symbol Identification

Sheet 01

NOTE: The structural parts listed in the above kit are defined with suffix 00 and

include pilot holes. Alternatively, the equivalent parts may be supplied

without holes for ease of installation. The alternative parts will have suffix

90 and are fully interchangeable.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 106

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SERVICE BULLETIN

(a) Install the items between STGR3 and STGR5 on the RH Side, refer to Fig. AGBCAA Sheet 03, Fig. A-GBCAA Sheet 04 and Fig. A-GBDAA Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Angle D5357072425100 Item 95

1 Angle D5357072425300 Item 89

1 Clip D5357072424700 Item 99

1 Web D5357072424900 Item 97

with:

3 Pin DAN5-8-6X Item 131

5 Collar DAN11-8X Item 115

2 Pin DAN5-5-5 Item 111

2 Collar NSA5075-5 Item 110

2 Pin DAN5-8-4X Item 116

and install:

1 Clip D5357072424500 Item 93

with:

6 Pin DAN5-8-5X Item 114

6 Collar DAN11-8X Item 115

and install:

1 Angle D5357072425700 Item 91

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 110

2 As shown in Section B-B, at STGR4, install:

2 Rivet EN6081D5-06 Item 106

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 107

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SERVICE BULLETIN

3 As shown in Section B-B, at STGR5, install:

2 Rivet EN6081D5-06 Item 106

4 Install:

2 Pin DAN6-6-5X Item 121

6 Pin DAN6-6-6X Item 132

17 Collar DAN11-6X Item 103

9 Pin DAN6-6-7X Item 124

14 Rivet EN6069D5-08 Item 137

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 131, 115, 109, 110, 132, 124, 122, 116, 114 and 103.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 131, 115, 109, 110, 132, 124, 122, 116, 114 and 103.

(b) Install the items between STGR5 and STGR7 on the RH Side, refer to Fig. AGBCAA Sheet 03, Fig. A-GBCAA Sheet 04 and Fig. A-GBDAA Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Angle D5357072425500 Item 81

1 Angle D5357113338700 Item 75

NOTE: Item 81 and Item 75 are temporally held in place.

Then between STGR5 and STGR7 install:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 108

6

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SERVICE BULLETIN

1 Web D5357113337700 Item 85

with:

10 Pin DAN5-6-4X Item 102

10 Collar DAN11-6X Item 103

and between Stringer STGR5 and STGR6 install:

1 Clip D5357072424300 Item 83

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

5 Pin DAN5-8-5X Item 114

5 Collar DAN11-8X Item 115

and between Stringer STGR5 and STGR6 install:

1 Angle D5357072425900 Item 87

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 110

and between Stringer STGR6 and STGR7 install:

1 Clip D5357113338100 Item 77

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

5 Pin DAN5-8-5X Item 114

5 Collar DAN11-8X Item 115

and between Stringer STGR6 and STGR7 install:

1 Angle D5357113339300 Item 79

with:

5 Pin DAN5-5-6 Item 109

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 109

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SERVICE BULLETIN

5 Collar NSA5075-5 Item 110

2 As shown in Section B-B, at STGR6, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section B-B, at STGR7, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View H, install:

19 Pin DAN6-6-7 Item 125

26 Collar NSA5075-6 Item 108

6 Pin DAN6-6-6 Item 126

7 Rivet EN6069D5-07 Item 136

4 Pin DAN6-6-5X Item 121

4 Collar DAN11-6X Item 103

1 Pin DAN6-6-5 Item 127

1 Rivet EN6069D5-06 Item 122

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

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

and 127.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

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

and 127.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 110

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SERVICE BULLETIN

(c) Install the items between Stringer STGR7 and STGR9 on the RH Side, refer to Fig.

A-GBCAA Sheet 03, Fig. A-GBCAA Sheet 04 and Fig. A-GBDAA Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Angle D5357113338900 Item 71

1 Angle D5357113339100 Item 65

NOTE: Item 71 and Item 64 are temporally held in place.

Then between STGR7 and STGR9 install:

1 Web D5357113337900 Item 69

with:

8 Pin DAN5-6-4X Item 102

8 Collar DAN11-6X Item 103

and install:

1 Clip D5357113338300 Item 73

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

4 Pin DAN5-8-5X Item 114

4 Collar DAN11-8X Item 115

4 Pin DAN5-5-5 Item 111

4 Collar NSA5075-5 Item 110

and install:

1 Clip D5357113338500 Item 67

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 111

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SERVICE BULLETIN

5 Pin DAN5-8-5X Item 114

5 Collar DAN11-8X Item 115

4 Pin DAN5-5-5 Item 111

4 Collar NSA5075-5 Item 110

2 As shown in Section B-B, at STGR8, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section B-B, at STGR9, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View K, install:

8 Pin DAN6-6-5X Item 121

17 Collar DAN11-6X Item 103

9 Pin DAN6-6-4X Item 120

2 Pin DAN6-6-5 Item 127

2 Collar NSA5075-6 Item 108

2 Rivet EN6069D5-06 Item 122

12 Rivet EN6069D5-07 Item 136

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 114, 115, 111, 110, 121, 127, 108, 122

and 120.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 114, 115, 111, 110, 121, 127, 108, 122

and 120.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 112

6

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SERVICE BULLETIN

(d) Install the items between STGR9 and STGR12 on the RH Side, refer to Fig. AGBCAA Sheet 03, Fig. A-GBCAA Sheet 04 and Fig. A-GBDAA Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Web D5357113339500 Item 63

with:

3 Pin DAN5-6-4X Item 102

3 Collar DAN11-6X Item 103

and install:

1 Angle D5357113339700 Item 52

1 Filler D5357113339800 Item 53

1 Angle D5357113321500 Item 55

with:

24 Pin DAN5-6-6 Item 112

24 Collar NSA5075-6 Item 108

and install:

1 Web D5357113340100 Item 61

with:

6 Pin DAN5-8-6X Item 131

6 Collar DAN11-8X Item 115

8 Rivet EN6081D5-06 Item 106

5 Pin DAN5-6-6X Item 105

5 Collar DAN11-6X Item 103

and install:

1 Angle D5357113337100 Item 59

1 Angle D5357113337300 Item 57

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 113

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SERVICE BULLETIN

with:

4 Pin DAN5-6-7X Item 130

4 Collar DAN11-6X Item 103

2 As shown in Section B-B, at STGR10, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section B-B, at STGR11, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View K, install:

18 Pin DAN6-6-4X Item 120

25 Collar DAN11-6X Item 103

16 Rivet EN6069D5-07 Item 136

3 Pin DAN6-6-5X Item 121

4 Pin DAN6-6-7X Item 124

1 Pin DAN6-6-7 Item 125

1 Collar NSA5075-6 Item 108

1 Pin DAN6-5-7 Item 133

1 Collar NSA5075-5 Item 110

5 As shown in View L, install:

1 Pin DAN7-6-11X Item 144

1 Collar DAN12-6X Item 145

2 Pin DAN5-6-10X Item 146

2 Pin DAN5-6-8X Item 148

4 Collar DAN11-6X Item 103

6 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 114

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SERVICE BULLETIN

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 112, 108, 121, 124, 131, 115, 106, 105, 120,

130 and 122.

7 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 112, 108, 121, 124, 131, 115, 106, 105, 120,

130 and 122.

**CONF 002

(1) Subtask 531266-020-201-002 - Remove the Angles, Webs, Brackets and Clips at

Frame 72, between STGR13, LH and STGR1, RH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 72

from Stringer 13 LH to Stringer 1 RH

Manpower Resources

Manhours 13.00

Minimum number of person 1

Subtask elapsed time 13.00

Skills AIRFRAME

NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) Task 51-10-01-250-801

51-10-08

Fig. A-GBAAA

Location of Inspection Area for Clips at

FR72/FR74

Sheet 01

Fig. A-GBBAB

Removal/Installation of Angles, Webs,

Brackets and Clips at FR72

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the items between STGR13 and STGR11 LH, refer to Fig. A-GBBAB

Sheet 01 and Fig. A-GBBAB Sheet 02.

1 As shown in View B, remove:

26 Pin-Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 115

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26 Collar Discard

6 Rivet Discard

2 As shown in Section B-B, remove:

2 Pin-Rivet Discard

2 Collar Discard

3 As shown in View D, remove:

16 Pin-Rivet Discard

16 Collar Discard

4 Remove:

1 Angle D5357113120400 Item (1) Discard

1 Web D5357113133000 Item (3) Discard

1 Web D5357113134600 Item (5) Discard

1 Bracket-Z D9357073720000 Item (133) Retain

5 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(b) Remove the items between STGR11 and STGR9 LH, refer to Fig. A-GBBAB Sheet

01 and Fig. A-GBBAB Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STRG11 (Section A-A) and

2 Rivet Discard

from the angle at STGR10 (Section A-A).

Remove:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 116

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SERVICE BULLETIN

23 Pin-Rivet Discard

23 Collar Discard

11 Rivet Discard

from View B.

2 As shown in View F, remove:

19 Pin-Rivet Discard

19 Collar Discard

16 Rivet Discard

3 Remove:

1 Clip D5357113136600 Item (7) Discard

1 Clip D5357113122600 Item (9) Discard

1 Web D5357113134400 Item (11) Discard

1 Bracket-Z D9357073720000 Item (133) Retain

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(c) Remove the items between STGR9 and STGR7 LH, refer to Fig. A-GBBAB Sheet

01 and Fig. A-GBBAB Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR9 (Section A-A) and

2 Rivet Discard

from the angle at STGR8 (Section A-A).

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 117

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SERVICE BULLETIN

Remove:

31 Pin-Rivet Discard

31 Collar Discard

from View B.

2 As shown in View F, remove:

21 Pin-Rivet Discard

21 Collar Discard

14 Rivet Discard

3 Remove:

1 Angle D5357114726000 Item (13) Discard

1 Clip D5357113122400 Item (15) Discard

1 Angle D5357114725800 Item (17) Discard

1 Clip D5357113132200 Item (19) Discard

1 Web D5357113134200 Item (21) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(d) Remove the items between STGR7 and STGR5 LH, refer to Fig. A-GBBAB Sheet

01 and Fig. A-GBBAB Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR7 (Section A-A) and

2 Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 118

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SERVICE BULLETIN

from the angle at STGR6 (Section A-A).

Remove:

33 Pin-Rivet Discard

33 Collar Discard

2 Rivet Discard

from View B.

2 As shown in View F, remove:

28 Pin-Rivet Discard

28 Collar Discard

10 Rivet Discard

3 Remove:

1 Angle D5357114725600 Item (23) Discard

1 Angle D5357114727800 Item (25) Discard

1 Clip D5357113136400 Item (27) Discard

1 Angle D5357114725400 Item (29) Discard

1 Clip D5357072231000 Item (32) Discard

1 Angle D5357114727600 Item (33) Discard

1 Web D5357113134000 Item (35) Discard

1 Bracket-Z D9357073720000 Item (133) Retain

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 119

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SERVICE BULLETIN

(e) Remove the items between STGR5 and STGR3 LH, refer to Fig. A-GBBAB Sheet

01 and Fig. A-GBBAB Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR5 (Section A-A) and

2 Rivet Discard

from the angle at STGR4 (Section A-A).

Remove:

17 Pin-Rivet Discard

17 Collar Discard

from View B.

2 As shown in View F, remove:

19 Pin-Rivet Discard

19 Collar Discard

14 Rivet Discard

3 Remove:

1 Angle D5357114725200 Item (36) Discard

1 Angle D5357114727400 Item (38) Discard

1 Clip D5357072221200 Item (40) Discard

1 Angle D5357114725000 Item (42) Discard

1 Web D5357072222000 Item (44) Discard

1 Clip D5357072221400 Item (46) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 120

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c Findings:

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

- If no cracks are found, do the worksteps that follow.

(f) Remove the items at STGR1 RH and LH, refer to Fig. A-GBBAB Sheet 01 and Fig.

A-GBBAB Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR1 (Section A-A).

10 Pin-Rivet Discard

10 Nut Discard

from View B.

2 As shown in View E, remove:

7 Pin-Rivet Discard

7 Nut Discard

8 Rivet Discard

3 Remove:

1 Clip D5357072221800 Item (48) Discard

1 Web D5357072221600 Item (49) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 121

6

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SERVICE BULLETIN

(2) Subtask 531266-420-201-002 - Install the Angles, Webs, Brackets and Clips at

Frame 72, between STGR1, RH and STGR13, LH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 72

from Stringer 1 RH to Stringer 13 LH

Manpower Resources

Manhours 16.00

Minimum number of person 1

Subtask elapsed time 16.00

Skills AIRFRAME

Material necessary to do the job

Kit 531266D12R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 D5357113120490 1 ANGLE

3 D5357113133090 1 WEB

5 D5357113134690 1 WEB

7 D5357113136690 1 CLIP

9 D5357113122690 1 CLIP

11 D5357113134490 1 WEB

13 D5357114726090 1 ANGLE

15 D5357113122490 1 CLIP

17 D5357114725890 1 ANGLE

19 D5357113132290 1 CLIP

21 D5357113134290 1 WEB

23 D5357114725690 1 ANGLE

25 D5357114727890 1 ANGLE

27 D5357113136490 1 CLIP

29 D5357114725490 1 ANGLE

31 D5357072231090 1 CLIP

33 D5357114727690 1 ANGLE

35 D5357113134090 1 WEB

36 D5357114725290 1 ANGLE

38 D5357114727490 1 ANGLE

40 D5357072221290 1 CLIP

42 D5357114725090 1 ANGLE

44 D5357072222090 1 WEB

46 D5357072221490 1 CLIP

48 D5357072221890 1 CLIP

49 D5357072221690 1 WEB

102 DAN5-6-4X 31 PIN

103 DAN11-6X 140 COLLAR

104 DAN5-6-5X 40 PIN

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 122

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

105 DAN5-6-6X 2 PIN

106 EN6081D5-06 33 RIVET

108 NSA5330-6 27 COLLAR

109 DAN5-6-6 16 PIN

110 NSA5075-6 59 COLLAR

111 DAN5-6-5 27 PIN

113 DAN5-6-3X 3 PIN

114 DAN5-8-5X 10 PIN

115 DAN11-8X 29 COLLAR

116 DAN5-8-4X 2 PIN

117 DAN5-8-7X 8 PIN

118 DAN5-8-8X 2 PIN

119 DAN6-6-3X 8 PIN

120 DAN6-6-4X 29 PIN

121 DAN6-6-5Y 13 PIN

122 EN6069D5-06 12 RIVET

123 DAN6-8-6X 7 PIN

124 DAN6-6-6Y 14 PIN

125 DAN6-6-7X 19 PIN

126 DAN6-6-6 4 PIN

127 DAN6-6-5X 4 PIN

128 DAN6-6-3 8 PIN

129 DAN5-6-3 4 PIN

132 DAN6-6-6X 2 PIN

135 EN6081D5-07 2 RIVET

136 EN6069D5-07 33 RIVET

137 EN6069D5-08 17 RIVET

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant, Brush Consistency 09-013 As required

Corrosion Preventative

Compound, Temporary

15-009 As required

Anti-Corrosion Primer

Polyurethane

16-001 As required

Polyurethane Finish Paint 16-018 As required

References

Consumable Material List (CML)

Fig. A-GBBAB

Removal/Installation of Angles, Webs,

Brackets and Clips at FR72

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-GBDAB

Fastener Symbol Identification

Sheet 01

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 123

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SERVICE BULLETIN

(a) Install the items between STGR1 LH and RH, refer to Fig. A-GBBAB Sheet 03 and

Fig. A-GBDAB Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Web D5357072221690 Item 49

with:

8 Pin DAN5-8-7X Item 117

8 Collar DAN11-8X Item 115

and then install:

1 Clip D5357072221890 Item 48

with:

2 PIN DAN5-8-8X Item 118

2 Collar DAN11-8X Item 115

2 As shown in Section E-E, install:

2 Pin DAN5-6-3 Item 129

2 Collar NSA5075-6 Item 110

3 As shown in View K, install:

7 Pin DAN6-8-6X Item 123

7 Collar DAN11-8X Item 115

5 Rivet EN6069D5-07 Item 136

3 Rivet EN6069D5-08 Item 137

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 115,117, 118 and 123.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 124

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5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 106, 115, 117, 118, 123, 136 and 137.

(b) Install the items between STGR3 and STGR4 on the LH Side, refer to Fig. AGBBAB Sheet 03, Fig. A-GBBAB Sheet 04 and Fig. A-GBDAB Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357114725090 Item 42

1 Clip D5357072221490 Item 46

with:

4 Pin DAN5-8-5X Item 114

4 Collar DAN11-8X Item 115

2 Pin DAN5-6-5 Item 111

2 Collar NSA5075-6 Item 110

2 As shown in Section C-C, STGR4 install:

2 Rivet EN6081D5-06 Item 106

3 As shown in View L, install between STGR3 and STGR4:

3 Pin DAN6-6-5X Item 127

3 Collar DAN11-6X Item 103

3 Pin DAN6-6-6Y Item 124

3 Collar NSA5330-6 Item 108

1 Pin DAN6-6-6X Item 132

1 Collar DAN11-6X Item 103

7 Rivet EN6069D5-08 Item 137

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 125

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4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

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

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

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

(c) Install the items between STGR4 and STGR5 on the LH Side, refer to Fig. AGBBAB Sheet 03, Fig. A-GBBAB Sheet 04 and Fig. A-GBDAB Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357114725290 Item 36

1 Web D5357072222090 Item 44

with:

2 Pin DAN5-8-4X Item 116

2 Collar DAN11-8X Item 115

and then install:

1 Clip D5357072221290 Item 40

with:

6 Pin DAN5-8-5X Item 114

6 Collar DAN11-8X Item 115

and then install:

1 Angle D5357114727490 Item 38

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 126

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SERVICE BULLETIN

with:

4 Pin DAN5-6-6 Item 109

4 Collar NSA5075-6 Item 110

2 As shown in Section, C-C at STGR5, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in View L, between STGR4 and STGR5, install:

11 Pin DAN6-6-6Y Item 124

11 Collar NSA5330-6 Item 108

1 Pin DAN6-6-6X Item 132

1 Collar DAN11-6X Item 103

7 Rivet EN6069D5-08 Item 137

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

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

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

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

137.

(d) Install the items between STGR5 and STGR7 on the LH Side, refer to Fig. AGBBAB Sheet 03, Fig. A-GBBAB Sheet 04 and Fig. A-GBDAB Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 127

6

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SERVICE BULLETIN

1 Angle D5357114725490 Item 29

1 Angle D5357114725690 Item 23

1 Web D5357113134090 Item 35

with:

9 Pin DAN5-6-4X Item 102

9 Collar DAN11-6X Item 103

2 Rivet EN6081D5-07 Item 135

and then between STGR5 and STGR6 install:

1 Clip D5357072231090 Item 31

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

and then between STGR5 and STGR6 install:

1 Angle D5357114727690 Item 33

with:

5 Pin DAN5-6-6 Item 109

5 Collar NSA5075-6 Item 110

and then between STGR6 and STGR7 install:

1 Clip D5357113136490 Item 27

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

and then between STGR6 and STGR7 install:

1 Angle D5357114727890 Item 25

with:

5 Pin DAN5-6-6 Item 109

5 Collar NSA5075-6 Item 110

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 128

6

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SERVICE BULLETIN

2 As shown in Section C-C, at STGR6, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section C-C, at STGR7, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View L, between STGR5 and STGR7, install:

19 Pin DAN6-6-7X Item 125

20 Collar DAN11-6X Item 103

9 Rivet EN6069D5-07 Item 136

4 Pin DAN6-6-6 Item 126

4 Collar NSA5075-6 Item 110

4 Pin DAN6-6-5Y Item 121

4 Collar NSA5330-6 Item 108

1 Pin DAN6-6-5X Item 127

1 Rivet EN6069D5-06 Item 122

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

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

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

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

127 and 136.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 129

6

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SERVICE BULLETIN

(e) Install the items between STGR7 and STGR9 on the LH Side, refer to Fig. AGBBAB Sheet 03, Fig. A-GBBAB Sheet 04 and Fig. A-GBDAB Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357114725890 Item 17

1 Angle D5357114726090 Item 13

NOTE: Item 17 and Item 13 are temporally held in place.

Then between STGR7 and STGR9 install:

1 Web D5357113134290 Item 21

with:

10 Pin DAN5-6-4X Item 102

10 Collar DAN11-6X Item 103

and then between STGR7 and STGR8 install:

1 Clip D5357113132290 Item 19

with:

5 Pin DAN5-6-5X Item 104

5 Collar DAN11-6X Item 103

4 Pin DAN5-6-5 Item 111

4 Collar NSA5075-6 Item 110

and then between Stringer STGR8 and STGR9 install:

1 Clip D5357113122490 Item 15

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

5 Pin DAN5-6-5 Item 111

5 Collar NSA5075-6 Item 110

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 130

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SERVICE BULLETIN

2 As shown in Section C-C, at STGR8, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section C-C, at STGR9, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View L, between STGR7 and STGR9, install:

10 Pin DAN6-6-4X Item 120

2 Pin DAN6-6-5X Item 127

12 Collar DAN11-6X Item 103

9 Pin DAN6-6-5Y Item 121

9 Collar NSA5330-6 Item 108

12 Rivet EN6069D5-07 Item 136

2 Rivet EN6069D5-06 Item 122

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 108, 110, 111, 120, 122, and 127.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 110, 111, 120, 121, 122, 127

and 136.

(f) Install the items between STGR9 and STGR11 on the LH Side, refer to Fig. AGBBAB Sheet 03, Fig. A-GBBAB Sheet 04 and Fig. A-GBDAB Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 131

6

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SERVICE BULLETIN

to wet install on Frame 72, as shown in View G:

1 Bracket-Z D9357073720000 Item (133) Retained at

removal

1 Web D5357113134490 Item 11

with:

2 Rivet EN6081D5-06 Item 106

9 Pin DAN5-6-4X Item 102

9 Collar DAN11-6X Item 103

and then STGR9 and STGR10, install:

1 Clip D5357113122690 Item 9

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

5 Rivet EN6081D5-06 Item 106

and then between STGR10 and STGR11, install:

1 Clip D5357113136690 Item 7

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

4 Rivet EN6081D5-06 Item 106

2 As shown in Section C-C, at STGR10 install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section C-C, at STGR11 install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View L, between STGR9 and STGR11, install:

19 Pin DAN6-6-4X Item 120

19 Collar DAN11-6X Item 103

7 Rivet EN6069D5-07 Item 136

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 132

6

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SERVICE BULLETIN

9 Rivet EN6069D5-06 Item 122

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 120.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 106, 120, 122 and 136.

(g) Install the items between STGR11 and STGR13 on the LH Side, refer to Fig. AGBBAB Sheet 03 and Fig. A-GBDAB Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Bracket-Z D9357073720000 Item (133) Retained at

removal

1 Web D5357113134690 Item 5

with:

2 Rivet EN6081D5-06 Item 106

3 Pin DAN5-6-3X Item 113

3 Collar DAN11-6X Item 103

and then install:

1 Web D5357113133090 Item 3

with:

3 Pin DAN5-6-4X Item 102

3 Collar DAN11-6X Item 103

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 133

6

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SERVICE BULLETIN

4 Rivet EN6081D5-06 Item 106

and then install:

1 Angle D5357113120490 Item 1

with:

16 Pin DAN5-6-5 Item 111

18 Collar NSA5075-6 Item 110

2 Pin DAN5-6-6 Item 109

2 Pin DAN5-6-6X Item 105

2 Collar DAN11-6X Item 103

2 As shown in Section D-D, at STGR12, install:

2 Pin DAN5-6-3 Item 129

2 Collar NSA5075-6 Item 110

3 As shown in View J, install:

8 Pin DAN6-6-3X Item 119

8 Collar DAN11-6X Item 103

8 Pin DAN6-6-3 Item 128

8 Collar NSA5075-6 Item 110

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 107, 108, 113, 119, 112 and 128.

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 106, 107, 108, 113, 119, 112 and 128.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 134

6

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SERVICE BULLETIN

(3) Subtask 531266-020-208-002 - Remove the Angles, Webs, Brackets and Clips at

Frame 72, between STGR13, RH and STGR3, RH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 72

from Stringer 13 RH to Stringer 3 RH

Manpower Resources

Manhours 11.00

Minimum number of person 1

Subtask elapsed time 11.00

Skills AIRFRAME

NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) Task 51-10-01-250-801

51-10-08

Fig. A-GBAAA

Location of Inspection Area for Clips at

FR72/FR74

Sheet 01

Fig. A-GBBAB

Removal/Installation of Angles, Webs,

Brackets and Clips at FR72

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the items between STGR13 and STGR11 RH, refer to Fig. A-GBBAB

Sheet 01 and Fig. A-GBBAB Sheet 02.

1 As shown in View B, remove:

26 Pin-Rivet Discard

26 Collar Discard

6 Rivet Discard

2 As shown in Section B-B, remove:

2 Pin-Rivet Discard

2 Collar Discard

3 As shown in View D, remove:

16 Pin-Rivet Discard

16 Collar Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 135

6

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SERVICE BULLETIN

4 Remove:

1 Angle D5357113120500 Item (2) Discard

1 Web D5357113133100 Item (4) Discard

1 Web D5357113134700 Item (6) Discard

1 Bracket-Z D9357073720000 Item (133) Retain

5 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(b) Remove the items between STGR11 and STGR9 RH, refer to Fig. A-GBBAB Sheet

01 and Fig. A-GBBAB Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STRG11 (Section A-A) and

2 Rivet Discard

from the angle at STGR10 (Section A-A).

Remove:

23 Pin-Rivet Discard

23 Collar Discard

11 Rivet Discard

from View B.

2 As shown in View F, remove:

19 Pin-Rivet Discard

19 Collar Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 136

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SERVICE BULLETIN

16 Rivet Discard

3 Remove:

1 Clip D5357113136700 Item (8) Discard

1 Clip D5357113122700 Item (10) Discard

1 Web D5357113134500 Item (12) Discard

1 Bracket-Z D9357073720000 Item (133) Retain

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(c) Remove the items between STGR9 and STGR7 RH, refer to Fig. A-GBBAB Sheet

01 and Fig. A-GBBAB Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR9 (Section A-A) and

2 Rivet Discard

from the angle at STGR8 (Section A-A).

Remove:

31 Pin-Rivet Discard

31 Collar Discard

from View B.

2 As shown in View F, remove:

21 Pin-Rivet Discard

21 Collar Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 137

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SERVICE BULLETIN

14 Rivet Discard

3 Remove:

1 Angle D5357114726100 Item (14) Discard

1 Clip D5357113122500 Item (16) Discard

1 Angle D5357114725900 Item (18) Discard

1 Clip D5357113132300 Item (20) Discard

1 Web D5357113134300 Item (22) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(d) Remove the items between STGR7 and STGR5 RH, refer to Fig. A-GBBAB Sheet

01 and Fig. A-GBBAB Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR7 (Section A-A) and

2 Rivet Discard

from the angle at STGR6 (Section A-A).

Remove:

33 Pin-Rivet Discard

33 Collar Discard

2 Rivet Discard

from View B.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 138

6

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SERVICE BULLETIN

2 As shown in View F, remove:

28 Pin-Rivet Discard

28 Collar Discard

10 Rivet Discard

3 As shown in View C, remove:

1 Angle D5357114725700 Item (24) Discard

1 Angle D5357114727900 Item (26) Discard

1 Clip D5357113136500 Item (28) Discard

1 Angle D5357114725500 Item (30) Discard

1 Clip D5357072231000 Item (32) Discard

1 Angle D5357114727700 Item (34) Discard

1 Web-Shear D5357116135000 Item (50) Discard

1 Bracket-Z D9357073720000 Item (133) Retain

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(e) Remove the items between STGR5 and STGR3 RH, refer to Fig. A-GBBAB Sheet

01 and Fig. A-GBBAB Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR5 (Section A-A) and

2 Rivet Discard

from the angle at STGR4 (Section A-A).

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 139

6

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SERVICE BULLETIN

Remove:

14 Pin-Rivet Discard

14 Collar Discard

3 Rivet Discard

from View B.

2 As shown in View F, remove:

19 Pin-Rivet Discard

19 Collar Discard

14 Rivet Discard

3 Remove:

1 Angle D5357114725300 Item (37) Discard

1 Angle D5357114727500 Item (39) Discard

1 Clip D5357072221300 Item (41) Discard

1 Angle D5357114725100 Item (43) Discard

1 Web D5357072222100 Item (45) Discard

1 Clip D5357072221500 Item (47) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 140

6

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SERVICE BULLETIN

(4) Subtask 531266-420-202-002 - Install the Angles, Webs, Brackets and Clips at

Frame 72, between STGR3, RH to STGR13, RH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 72

from Stringer 3 RH to Stringer 13 RH

Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills AIRFRAME

Material necessary to do the job

Kit 531266D12R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 D5357113120590 1 ANGLE

4 D5357113133190 1 WEB

6 D5357113134790 1 WEB

8 D5357113136790 1 CLIP

10 D5357113122790 1 CLIP

12 D5357113134590 1 WEB

14 D5357114726190 1 ANGLE

16 D5357113122590 1 CLIP

18 D5357114725990 1 ANGLE

20 D5357113132390 1 CLIP

22 D5357113134390 1 WEB

24 D5357114725790 1 ANGLE

26 D5357114727990 1 ANGLE

28 D5357113136590 1 CLIP

30 D5357114725590 1 ANGLE

32 D5357072231190 1 CLIP

34 D5357114727790 1 ANGLE

37 D5357114725390 1 ANGLE

39 D5357114727590 1 ANGLE

41 D5357072221390 1 CLIP

43 D5357114725190 1 ANGLE

45 D5357072222190 1 WEB

47 D5357072221590 1 CLIP

50 D5357116135090 1 WEB

102 DAN5-6-4X 31 PIN

103 DAN11-6X 140 COLLAR

104 DAN5-6-5X 40 PIN

105 DAN5-6-6X 2 PIN

106 EN6081D5-06 33 RIVET

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 141

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

108 NSA5330-6 27 COLLAR

109 DAN5-6-6 16 PIN

110 NSA5075-6 57 COLLAR

111 DAN5-6-5 27 PIN

113 DAN5-6-3X 3 PIN

114 DAN5-8-5X 10 PIN

115 DAN11-8X 12 COLLAR

116 DAN5-8-4X 2 PIN

119 DAN6-6-3X 8 PIN

120 DAN6-6-4X 29 PIN

121 DAN6-6-5Y 13 PIN

122 EN6069D5-06 12 RIVET

124 DAN6-6-6Y 14 PIN

125 DAN6-6-7X 19 PIN

126 DAN6-6-6 4 PIN

127 DAN6-6-5X 6 PIN

128 DAN6-6-3 8 PIN

129 DAN5-6-3 2 PIN

132 DAN6-6-6X 2 PIN

135 EN6081D5-07 2 RIVET

136 EN6069D5-07 28 RIVET

137 EN6069D5-08 14 RIVET

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant, Brush Consistency 09-013 As required

Corrosion Preventative

Compound, Temporary

15-009 As required

Anti-Corrosion Primer

Polyurethane

16-001 As required

Polyurethane Finish Paint 16-018 As required

References

Consumable Material List (CML)

Fig. A-GBBAB

Removal/Installation of Angles, Webs,

Brackets and Clips at FR72

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-GBDAB

Fastener Symbol Identification

Sheet 01

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 142

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SERVICE BULLETIN

(a) Install the items between STGR3 and STGR4 on the RH Side, refer to Fig. AGBBAB Sheet 03, Fig. A-GBBAB Sheet 04 and Fig. A-GBDAB Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357114725190 Item 43

1 Clip D5357072221590 Item 47

with:

4 Pin DAN5-8-5X Item 114

4 Collar DAN11-8X Item 115

2 Pin DAN5-6-5 Item 111

2 Collar NSA5075-6 Item 110

2 As shown in Section C-C at STGR4, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in View L, at STGR3 and STGR4, install:

3 Pin DAN6-6-6Y Item 124

3 Collar NSA5330-6 Item 108

3 Pin DAN6-6-5X Item 127

4 Collar DAN11-6X Item 103

1 Pin DAN6-6-6X Item 132

7 Rivet EN6069D5-08 Item 137

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 103, 108, 110, 111, 114, 115, 124, 127 and 132.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 143

6

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SERVICE BULLETIN

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 103, 106, 108, 110, 111, 114, 115, 124, 127, 132 and

137.

(b) Install the items between STGR4 and STGR5 on the RH Side, refer to Fig. AGBBAB Sheet 03, Fig. A-GBBAB Sheet 04 and Fig. A-GBDAB Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357114725390 Item 37

1 Web D5357072222190 Item 45

with:

2 Pin DAN5-8-4X Item 116

2 Collar DAN11-8X Item 115

and then install:

1 Clip D5357072221390 Item 41

with:

6 Pin DAN5-8-5X Item 114

6 Collar DAN11-8X Item 115

and then install:

1 Angle D5357114727590 Item 39

with:

4 Pin DAN5-6-6 Item 109

4 Collar NSA5075-6 Item 110

2 As shown in Section C-C at STGR5, install:

2 Rivet EN6081D5-06 Item 106

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 144

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@A318/A319/A320/A321

SERVICE BULLETIN

3 As shown in View L, at STGR4 and STGR5, install:

11 Pin DAN6-6-6Y Item 124

11 Collar NSA5330-6 Item 108

1 Pin DAN6-6-6X Item 132

1 Collar DAN11-6X Item 103

7 Rivet EN6069D5-08 Item 137

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 103, 108, 109, 110, 114, 115, 116, 124 and 132.

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 103, 106, 108, 109, 110, 114, 115, 116, 124, 132 and

137.

(c) Install the items between STGR5 and STGR7 on the RH Side, refer to Fig. AGBBAB Sheet 03, Fig. A-GBBAB Sheet 04 and Fig. A-GBDAB Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View H:

1 Angle D5357114725590 Item 30

1 Angle D5357114725790 Item 24

1 Bracket-Z D9357073720000 Item (133) Retained at

removal

1 Web D5357116135090 Item 50

with:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 145

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SERVICE BULLETIN

9 Pin DAN5-6-4X Item 102

9 Collar DAN11-6X Item 103

2 Rivet EN6081D5-07 Item 135

and between STGR5 and STGR7, as shown in View H, install:

1 Clip D5357072231190 Item 32

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

and between STGR5 and STGR7, install:

1 Angle D5357114727790 Item 34

with:

5 Pin DAN5-6-6 Item 109

5 Collar NSA5075-6 Item 110

and between STGR6 and STGR7, install:

1 Clip D5357113136590 Item 28

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

and between STGR6 and STGR7 install:

1 Angle D5357114727990 Item 26

with:

5 Pin DAN5-6-6 Item 109

5 Collar NSA5075-6 Item 110

2 As shown in Section C-C at STGR6, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section C-C at STGR7, install:

2 Rivet EN6081D5-06 Item 106

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 146

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SERVICE BULLETIN

4 Install to the fuselage skin between STGR5 and STGR7, refer to Fig. AGBBAB Sheet 04, View L:

19 Pin DAN6-6-7X Item 125

1 Pin DAN6-6-5X Item 127

20 Collar DAN11-6X Item 103

4 Pin DAN6-6-6 Item 126

4 Collar NSA5075-6 Item 110

9 Rivet EN6069D5-07 Item 136

4 Pin DAN6-6-5Y Item 121

4 Collar NSA5330-6 Item 108

1 Rivet EN6069D5-06 Item 122

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

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

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

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

127, 135 and 136.

(d) Install the items between STGR7 and STGR9 on the RH Side, refer to Fig. AGBBAB Sheet 03, Fig. A-GBBAB Sheet 04 and Fig. A-GBDAB Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357114725990 Item 18

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 147

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SERVICE BULLETIN

1 Angle D5357114726190 Item 14

NOTE: Item 18 and Item 14 are temporally held in place.

Then between STGR7 and STGR9 install:

1 Web D5357113134390 Item 22

with:

10 Pin DAN5-6-4X Item 102

10 Collar DAN11-6X Item 103

and then between STGR7 and STGR8 install:

1 Clip D5357113132390 Item 20

with:

5 Pin DAN5-6-5X Item 104

5 Collar DAN11-6X Item 103

4 Pin DAN5-6-5 Item 111

4 Collar NSA5075-6 Item 110

and then between Stringer STGR8 and STGR9 install:

1 Clip D5357113122590 Item 16

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

5 Pin DAN5-6-5 Item 111

5 Collar NSA5075-6 Item 110

2 As shown in Section C-C at STGR8, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section C-C at STGR9, install:

2 Rivet EN6081D5-06 Item 106

4 Install to the fuselage skin between STGR7 and STGR9, refer to Fig. AGBBAB Sheet 04, View L:

10 Pin DAN6-6-4X Item 120

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 148

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SERVICE BULLETIN

2 Pin DAN6-6-5X Item 127

12 Collar DAN11-6X Item 103

9 Pin DAN6-6-5Y Item 121

9 Collar NSA5330-6 Item 108

12 Rivet EN6069D5-07 Item 136

2 Rivet EN6069D5-06 Item 122

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 108, 110, 111, 120, 121 and 127.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 108, 110, 111, 120, 121, 122, 127 and

136.

(e) Install the items between STGR9 and STGR11 on the RH Side, refer to Fig. AGBBAB Sheet 03, Fig. A-GBBAB Sheet 04 and Fig. A-GBDAB Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Bracket-Z D9357073720000 Item (133) Retained at

removal

1 Web D5357113134590 Item 12

with:

2 Rivet EN6081D5-06 Item 106

9 Pin DAN5-6-4X Item 102

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 149

6

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SERVICE BULLETIN

9 Collar DAN11-6X Item 103

and then STGR9 and STGR10, install:

1 Clip D5357113122790 Item 10

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

5 Rivet EN6081D5-06 Item 106

and then between STGR10 and STGR11, install:

1 Clip D5357113136790 Item 8

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

4 Rivet EN6081D5-06 Item 106

2 As shown in Section C-C, at STGR 10, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section C-C, at STGR 11, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View L, between STGR9 and STGR11, install:

19 Pin DAN6-6-4X Item 120

19 Collar DAN11-6X Item 103

7 Rivet EN6069D5-07 Item 136

9 Rivet EN6069D5-06 Item 122

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, and 120.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 150

6

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SERVICE BULLETIN

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 106, 120, 122 and 136.

(f) Install the items between STGR11 and STGR13 on the RH Side, refer to Fig. AGBBAB Sheet 03 and Fig. A-GBDAB Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Bracket-Z D9357073720000 Item (133) Retained at

removal

1 Web D5357113134790 Item 6

with:

2 Rivet EN6081D5-06 Item 106

3 Pin DAN5-6-3X Item 113

3 Collar DAN11-6X Item 103

and then install:

1 Web D5357113133190 Item 4

with:

3 Pin DAN5-6-4X Item 102

3 Collar DAN11-6X Item 103

4 Rivet EN6081D5-06 Item 106

and then install:

1 Angle D5357113120590 Item 2

with:

16 Pin DAN5-6-5 Item 111

2 Pin DAN5-6-6 Item 109

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 151

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SERVICE BULLETIN

18 Collar NSA5075-6 Item 110

2 Pin DAN5-6-6X Item 105

2 Collar DAN11-6X Item 103

2 As shown in Section D-D, at STGR12, install:

2 Pin DAN5-6-3 Item 129

2 Collar NSA5075-6 Item 110

3 As shown in View J, install:

8 Pin DAN6-6-3X Item 119

8 Collar DAN11-6X Item 103

8 Pin DAN6-6-3 Item 128

8 Collar NSA5075-6 Item 110

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 105, 107, 108, 110, 111, 112, 113, 119, 128

and 129.

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 105, 106, 107, 108, 110, 111, 112, 113, 119,

128 and 129.

(5) Subtask 531266-020-203-002 - Remove the Angles, Webs, Brackets and Clips at

Frame 74, between STGR12, LH and STGR1, RH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 74

from Stringer 12 LH to Stringer 1 RH

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 152

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SERVICE BULLETIN

Manpower Resources

Manhours 11.00

Minimum number of person 1

Subtask elapsed time 11.00

Skills AIRFRAME

NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) Task 51-10-01-250-801

51-10-08

Fig. A-GBAAA

Location of Inspection Area for Clips at

FR72/FR74

Sheet 01

Fig. A-GBCAB

Removal/Installation of Angles, Webs,

Brackets and Clips at FR74

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the items between STGR12 and STGR9 LH, refer to Fig. A-GBCAB Sheet

01 and Fig. A-GBCAB Sheet 02.

1 As shown in Section A-A, remove:

2 Rivet Discard

from the angle at STGR11 (Section A-A) and

2 Rivet Discard

from the angle at STGR10 (Section A-A).

Remove:

42 Pin-Rivet Discard

42 Collar Discard

8 Rivet Discard

from View B.

2 As shown in View E, remove:

27 Pin-Rivet Discard

27 Collar Discard

16 Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 153

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SERVICE BULLETIN

3 Remove:

1 Angle D5357113331200 Item (51) Discard

1 Filler D5357113335400 Item (53) Discard

1 Angle D5357113321400 Item (54) Discard

1 Angle D5357113321000 Item (56) Discard

1 Angle D5357113320800 Item (58) Discard

1 Web D5357113336000 Item (60) Discard

1 Web D5357113330600 Item (62) Discard

4 As shown in View F, remove:

5 Pin-Rivet Discard

5 Collar Discard

5 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(b) Remove the items between STGR9 and STGR7 LH, refer to Fig. A-GBCAB Sheet

01 and Fig. A-GBCAB Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STRG9 (Section A-A) and

2 Rivet Discard

from the angle at STRG8 (Section A-A).

Remove:

27 Pin-Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 154

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SERVICE BULLETIN

27 Collar Discard

from View B.

2 As shown in View E, remove:

19 Pin-Rivet Discard

19 Collar Discard

14 Rivet Discard

3 Remove:

1 Angle D5357114727200 Item (64) Discard

1 Clip D5357113330400 Item (66) Discard

1 Web D5357113336200 Item (68) Discard

1 Angle D5357114727000 Item (70) Discard

1 Clip D5357113330200 Item (72) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(c) Remove the items between STGR7 and STGR5 LH, refer to Fig. A-GBCAB Sheet

01.

1 Remove:

2 Rivet Discard

from the angle at STRG7 (Section A-A) and

2 Rivet Discard

from the angle at STRG6 (Section A-A).

Remove:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 155

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SERVICE BULLETIN

32 Pin-Rivet Discard

32 Collar Discard

from View B.

2 As shown in View C, remove:

30 Pin-Rivet Discard

30 Collar Discard

8 Rivet Discard

3 Remove:

1 Angle D5357114726800 Item (74) Discard

1 Clip D5357113330000 Item (76) Discard

1 Angle D5357114728400 Item (78) Discard

1 Angle D5357114726600 Item (80) Discard

1 Clip D5357072431000 Item (82) Discard

1 Web D5357113336400 Item (84) Discard

1 Angle D5357114728200 Item (86) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(d) Remove the items between STGR5 and STGR3, refer to Fig. A-GBCAB Sheet 01.

1 Remove:

2 Rivet Discard

from the angle at STRG5 (Section A-A) and

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 156

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SERVICE BULLETIN

2 Rivet Discard

from the angle at STRG4 (Section A-A).

Remove:

16 Pin-Rivet Discard

16 Collar Discard

from View B.

2 As shown in View C, remove:

17 Pin-Rivet Discard

17 Collar Discard

14 Rivet Discard

3 Remove:

1 Angle D5357114726400 Item (88) Discard

1 Angle D5357114728000 Item (90) Discard

1 Clip D5357072421200 Item (92) Discard

1 Angle D5357114726200 Item (94) Discard

1 Web D5357072421600 Item (96) Discard

1 Clip D5357072421400 Item (98) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 157

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SERVICE BULLETIN

(e) Remove the items between STGR2 LH and STGR1 RH, refer to Fig. A-GBCAB

Sheet 01 and Fig. A-GBCAB Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STRG1 (Section A-A) and

12 Pin-Rivet Discard

12 Collar Discard

from View B.

2 As shown in View D, remove:

8 Pin-Rivet Discard

8 Collar Discard

8 Rivet Discard

3 Remove:

1 Clip D5357072221800 Item (48) Discard

1 Web D5357072421800 Item (100) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(6) Subtask 531266-420-203-002 - Install the Angles, Webs, Brackets and Clips at

Frame 74, between STGR1, RH and STGR12, LH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 74

from Stringer 1 RH to Stringer 12 LH

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 158

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SERVICE BULLETIN

Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills AIRFRAME

Material necessary to do the job

Kit 531266D12R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

48 D5357072221890 1 CLIP

51 D5357113331290 1 ANGLE

53 D5357113335400 1 FILLER

54 D5357113321490 1 ANGLE

56 D5357113321090 1 ANGLE

58 D5357113320890 1 ANGLE

60 D5357113336090 1 WEB

62 D5357113330690 1 WEB

64 D5357114727290 1 ANGLE

66 D5357113330490 1 CLIP

68 D5357113336290 1 WEB

70 D5357114727090 1 ANGLE

72 D5357113330290 1 CLIP

74 D5357114726890 1 ANGLE

76 D5357113330090 1 CLIP

78 D5357114728490 1 ANGLE

80 D5357114726690 1 ANGLE

82 D5357072431090 1 CLIP

84 D5357113336490 1 WEB

86 D5357114728290 1 ANGLE

88 D5357114726490 1 ANGLE

90 D5357114728090 1 ANGLE

92 D5357072421290 1 CLIP

94 D5357114726290 1 ANGLE

96 D5357072421690 1 WEB

98 D5357072421490 1 CLIP

100 D5357072421890 1 WEB

102 DAN5-6-4X 21 PIN

103 DAN11-6X 97 COLLAR

104 DAN5-6-5X 4 PIN

105 DAN5-6-6X 5 PIN

106 EN6081D5-06 26 RIVET

108 NSA5330-6 25 COLLAR

109 DAN5-6-6 38 PIN

110 NSA5075-6 56 COLLAR

111 DAN5-6-5 10 PIN

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 159

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

112 DAN6-6-5 1 PIN

114 DAN5-8-5X 25 PIN

115 DAN11-8X 56 COLLAR

116 DAN5-8-4X 2 PIN

117 DAN5-8-7X 10 PIN

118 DAN5-8-8X 2 PIN

120 DAN6-6-4X 27 PIN

121 DAN6-6-5Y 12 PIN

122 EN6069D5-06 3 RIVET

123 DAN6-8-6X 8 PIN

124 DAN6-6-6Y 13 PIN

125 DAN6-6-7X 23 PIN

126 DAN6-6-6 6 PIN

127 DAN6-6-5X 7 PIN

130 DAN5-6-7X 4 PIN

131 DAN5-8-6X 9 PIN

132 DAN6-6-6X 2 PIN

133 DAN6-5-7 1 PIN

134 DAN6-6-7 1 PIN

136 EN6069D5-07 38 RIVET

137 EN6069D5-08 19 RIVET

144 DAN7-6-11X 1 PIN

145 DAN12-6X 1 COLLAR

146 DAN5-6-10X 2 PIN

148 DAN5-6-8X 2 PIN

160 NSA5075-5 1 COLLAR

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant, Brush Consistency 09-013 As required

Corrosion Preventative

Compound, Temporary

15-009 As required

Anti-Corrosion Primer

Polyurethane

16-001 As required

Polyurethane Finish Paint 16-018 As required

References

Consumable Material List (CML)

Fig. A-GBCAB

Removal/Installation of Angles, Webs,

Brackets and Clips at FR74

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-GBDAB

Fastener Symbol Identification

Sheet 01

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 160

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SERVICE BULLETIN

(a) Install the items between STGR2 on the RH Side and STGR2 on the LH Side, refer

to Fig. A-GBCAB Sheet 03, Fig. A-GBCAB Sheet 04 and Fig. A-GBDAB Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Web D5357072421890 Item 100

with:

10 Pin DAN5-8-7X Item 117

10 Collar DAN11-8X Item 115

and then install:

1 Clip D5357072221890 Item 48

with:

2 PIN DAN5-8-8X Item 118

2 Collar DAN11-8X Item 115

2 As shown in Section B-B, at STGR1, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in View J, install:

8 Pin DAN6-8-6X Item 123

8 Collar DAN11-8X Item 115

3 Rivet EN6069D5-07 Item 136

5 Rivet EN6069D5-08 Item 137

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 115, 117, 118 and 123.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 161

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SERVICE BULLETIN

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 106, 115, 117, 118, 122, 123, 136 and 137.

(b) Install the items between STGR3 and STGR5 on the LH Side, refer to Fig. AGBCAB Sheet 03, Fig. A-GBCAB Sheet 04 and Fig. A-GBDAB Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Angle D5357114726290 Item 94

1 Angle D5357114726490 Item 88

1 Clip D5357072421490 Item 98

1 Web D5357072421690 Item 96

with:

3 Pin DAN5-8-6X Item 131

2 Pin DAN5-8-4X Item 116

5 Collar DAN11-8X Item 115

2 Pin DAN5-6-5 Item 111

2 Collar NSA5075-6 Item 110

and install:

1 Clip D5357072421290 Item 92

with:

6 Pin DAN5-8-5X Item 114

6 Collar DAN11-8X Item 115

and install:

1 Angle D5357114728090 Item 90

with:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 162

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SERVICE BULLETIN

4 Pin DAN5-6-6 Item 109

4 Collar NSA5075-6 Item 110

2 As shown in Section B-B, at STGR4, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section B-B, at STGR5, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View H, install:

13 Pin DAN6-6-6Y Item 124

13 Collar NSA5330-6 Item 108

2 Pin DAN6-6-6X Item 132

2 Pin DAN6-6-5X Item 127

4 Collar DAN11-6X Item 103

14 Rivet EN6069D5-08 Item 137

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 103, 108, 109, 110, 111, 114, 115, 116, 124, 127, 131,

and 132

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 103, 106, 108, 109, 110, 111, 114, 115, 116, 122, 124,

127, 131, 132 and 137

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 163

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SERVICE BULLETIN

(c) Install the items between STGR5 and STGR7 on the LH Side, refer to Fig. AGBCAB Sheet 03, Fig. A-GBCAB Sheet 04 and Fig. A-GBDAB Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Angle D5357114726690 Item 80

1 Angle D5357114726890 Item 74

NOTE: Item 80 and Item 74 are temporally held in place.

Then between STGR5 and STGR7 install:

1 Web D5357113336490 Item 84

with:

10 Pin DAN5-6-4X Item 102

10 Collar DAN11-6X Item 103

and then between Stringer STGR5 and STGR6 install:

1 Clip D5357072431090 Item 82

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

5 Pin DAN5-8-5X Item 114

5 Collar DAN11-8X Item 115

and then between Stringer STGR5 and STGR6 install:

1 Angle D5357114728290 Item 86

with:

5 Pin DAN5-6-6 Item 109

5 Collar NSA5075-6 Item 110

and then between Stringer STGR6 and STGR7 install:

1 Clip D5357113330090 Item 76

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 164

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SERVICE BULLETIN

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

5 Pin DAN5-8-5X Item 114

5 Collar DAN11-8X Item 115

and then between Stringer STGR6 and STGR7 install:

1 Angle D5357114728490 Item 78

with:

5 Pin DAN5-6-6 Item 109

5 Collar NSA5075-6 Item 110

2 As shown in Section B-B at STGR6, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section B-B, at STGR7, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View H, install:

19 Pin DAN6-6-7X Item 125

1 Pin DAN6-6-5X Item 127

20 Collar DAN11-6X Item 103

6 Pin DAN6-6-6 Item 126

6 Collar NSA5075-6 Item 110

4 Pin DAN6-6-5Y Item 121

4 Collar NSA5330-6 Item 108

7 Rivet EN6069D5-07 Item 136

1 Rivet EN6069D5-06 Item 122

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 165

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SERVICE BULLETIN

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 108, 109, 110, 114, 115, 121, 125, 126,

and 127.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 109, 110, 114, 115, 121, 125,

126, 127 and 136.

(d) Install the items between Stringer STGR7 and STGR9 on the LH Side, refer to Fig.

A-GBCAB Sheet 03, Fig. A-GBCAB Sheet 04 and Fig. A-GBDAB Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Angle D5357114727090 Item 70

1 Angle D5357114727290 Item 64

NOTE: Item 70 and Item 64 are temporally held in place.

Then between STGR7 and STGR9 install:

1 Web D5357113336290 Item 68

with:

8 Pin DAN5-6-4X Item 102

8 Collar DAN11-6X Item 103

and install:

1 Clip D5357113330290 Item 72

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

4 Pin DAN5-8-5X Item 114

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 166

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SERVICE BULLETIN

4 Collar DAN11-8X Item 115

4 Pin DAN5-6-5 Item 111

4 Collar NSA5075-6 Item 110

and install:

1 Clip D5357113330490 Item 66

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

5 Pin DAN5-8-5X Item 114

5 Collar DAN11-8X Item 115

4 Pin DAN5-6-5 Item 111

4 Collar NSA5075-6 Item 110

2 As shown in Section B-B, at STGR8, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section B-B, at STGR9, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View K, install:

8 Pin DAN6-6-5Y Item 121

8 Collar NSA5330-6 Item 108

9 Pin DAN6-6-4X Item 120

1 Pin DAN6-6-5X Item 127

10 Collar DAN11-6X Item 103

1 Pin DAN6-6-5 Item 112

1 Collar NSA5075-6 Item 110

2 Rivet EN6069D5-06 Item 122

12 Rivet EN6069D5-07 Item 136

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 167

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5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 108, 110, 111, 112, 114, 115, 120, 121

and 127

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 110, 111, 112, 114, 115, 120,

121, 122, 127 and 136.

(e) Install the items between Stringer STGR9 and STGR12 on the LH Side, refer to

Fig. A-GBCAB Sheet 03, Fig. A-GBCAB Sheet 04 and Fig. A-GBDAB Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Web D5357113330690 Item 62

with:

3 Pin DAN5-6-4X Item 102

3 Collar DAN11-6X Item 103

and install:

1 Angle D5357113331290 Item 51

1 Filler D5357113335400 Item 53

1 Angle D5357113321490 Item 54

with:

24 Pin DAN5-6-6 Item 109

24 Collar NSA5075-6 Item 110

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 168

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SERVICE BULLETIN

and install:

1 Web D5357113336090 Item 60

with:

6 Pin DAN5-8-6X Item 131

6 Collar DAN11-8X Item 115

8 Rivet EN6081D5-06 Item 106

5 Pin DAN5-6-6X Item 105

5 Collar DAN11-6X Item 103

and install:

1 Angle D5357113320890 Item 58

1 Angle D5357113321090 Item 56

with:

4 Pin DAN5-6-7X Item 130

4 Collar DAN11-6X Item 103

2 As shown in Section B-B, at STGR10, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section B-B, at STGR11, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View K, install:

18 Pin DAN6-6-4X Item 120

3 Pin DAN6-6-5X Item 127

4 Pin DAN6-6-7X Item 125

25 Collar DAN11-6X Item 103

16 Rivet EN6069D5-07 Item 136

1 Pin DAN6-6-7 Item 134

1 Collar NSA5075-6 Item 110

1 Pin DAN6-5-7 Item 133

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 169

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SERVICE BULLETIN

1 Collar NSA5075-5 Item 160

5 As shown in View L, install:

1 Pin DAN7-6-11X Item 144

1 Collar DAN12-6X Item 145

2 Pin DAN5-6-10X Item 146

2 Pin DAN5-6-8X Item 148

4 Collar DAN11-6X Item 103

6 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 105, 108, 110, 112, 115, 120, 121, 124, 130

and 131

7 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 105, 106, 108, 110, 112, 115, 120, 121, 124,

130, 131 and 136

(7) Subtask 531266-020-204-002 - Remove the Angles, Webs, Brackets and Clips at

Frame 74, between STGR12, RH and STGR3, RH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 74

from Stringer 12 RH to Stringer 3 RH

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 170

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SERVICE BULLETIN

Manpower Resources

Manhours 11.00

Minimum number of person 1

Subtask elapsed time 11.00

Skills AIRFRAME

NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) Task 51-10-01-250-801

51-10-08

Fig. A-GBAAA

Location of Inspection Area for Clips at

FR72/FR74

Sheet 01

Fig. A-GBCAB

Removal/Installation of Angles, Webs,

Brackets and Clips at FR74

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the items between STGR12 and STGR9 RH, refer to Fig. A-GBCAB Sheet

01 and Fig. A-GBCAB Sheet 02.

1 As shown in Section A-A, remove:

2 Rivet Discard

from the angle at STGR11 (Section A-A) and

2 Rivet Discard

from the angle at STGR10 (Section A-A).

Remove:

42 Pin-Rivet Discard

42 Collar Discard

8 Rivet Discard

from View B.

2 As shown in View E, remove:

27 Pin-Rivet Discard

27 Collar Discard

16 Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 171

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3 Remove:

1 Angle D5357113331300 Item (52) Discard

1 Filler D5357113335400 Item (53) Discard

1 Angle D5357113321500 Item (55) Discard

1 Angle D5357113321100 Item (57) Discard

1 Angle D5357113320900 Item (59) Discard

1 Web D5357113336100 Item (61) Discard

1 Web D5357113330700 Item (63) Discard

4 As shown in View F, remove:

5 Pin-Rivet Discard

5 Collar Discard

5 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(b) Remove the items between STGR9 and STGR7 RH, refer to Fig. A-GBCAB Sheet

01 and Fig. A-GBCAB Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STRG9 (Section A-A) and

2 Rivet Discard

from the angle at STRG8 (Section A-A).

Remove:

27 Pin-Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 172

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27 Collar Discard

from View B.

2 As shown in View E, remove:

19 Pin-Rivet Discard

19 Collar Discard

14 Rivet Discard

3 Remove:

1 Angle D5357114727300 Item (65) Discard

1 Clip D5357113330500 Item (67) Discard

1 Web D5357113336300 Item (69) Discard

1 Angle D5357114727100 Item (71) Discard

1 Clip D5357113330300 Item (73) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(c) Remove the items between STGR7 and STGR5, refer to Fig. A-GBCAB Sheet 01.

1 Remove:

2 Rivet Discard

from the angle at STRG7 (Section A-A) and

2 Rivet Discard

from the angle at STRG6 (Section A-A).

Remove:

32 Pin-Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 173

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32 Collar Discard

from View B.

2 As shown in View C, remove:

30 Pin-Rivet Discard

30 Collar Discard

8 Rivet Discard

3 Remove:

1 Angle D5357114726900 Item (75) Discard

1 Clip D5357113330100 Item (77) Discard

1 Angle D5357114728500 Item (79) Discard

1 Angle D5357114726700 Item (81) Discard

1 Clip D5357072431100 Item (83) Discard

1 Web D5357113336500 Item (85) Discard

1 Angle D5357114728300 Item (87) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(d) Remove the items between STGR5 and STGR3, refer to Fig. A-GBCAB Sheet 01.

1 Remove:

2 Rivet Discard

from the angle at STRG5 (Section A-A) and

2 Rivet Discard

from the angle at STRG4 (Section A-A).

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 174

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Remove:

16 Pin-Rivet Discard

16 Collar Discard

from View B.

2 As shown in View C, remove:

17 Pin-Rivet Discard

17 Collar Discard

14 Rivet Discard

3 Remove:

1 Angle D5357114726500 Item (89) Discard

1 Angle D5357114728100 Item (91) Discard

1 Clip D5357072421300 Item (93) Discard

1 Angle D5357114726300 Item (95) Discard

1 Web D5357072421700 Item (97) Discard

1 Clip D5357072421500 Item (99) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(8) Subtask 531266-420-204-002 - Install the Angles, Webs, Brackets and Clips at

Frame 74, between STGR3, RH and STGR12, RH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 74

from Stringer 3 RH to Stringer 12 RH

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 175

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SERVICE BULLETIN

Manpower Resources

Manhours 12.00

Minimum number of person 1

Subtask elapsed time 12.00

Skills AIRFRAME

Material necessary to do the job

Kit 531266D12R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

52 D5357113331390 1 ANGLE

53 D5357113335400 1 FILLER

55 D5357113321590 1 ANGLE

57 D5357113321190 1 ANGLE

59 D5357113320990 1 ANGLE

61 D5357113336190 1 WEB

63 D5357113330790 1 WEB

65 D5357114727390 1 ANGLE

67 D5357113330590 1 CLIP

69 D5357113336390 1 WEB

71 D5357114727190 1 ANGLE

73 D5357113330390 1 CLIP

75 D5357114726990 1 ANGLE

77 D5357113330190 1 CLIP

79 D5357114728590 1 ANGLE

81 D5357114726790 1 ANGLE

83 D5357072431190 1 CLIP

85 D5357113336590 1 WEB

87 D5357114728390 1 ANGLE

89 D5357114726590 1 ANGLE

91 D5357114728190 1 ANGLE

93 D5357072421390 1 CLIP

95 D5357114726390 1 ANGLE

97 D5357072421790 1 WEB

99 D5357072421590 1 CLIP

102 DAN5-6-4X 21 PIN

103 DAN11-6X 97 COLLAR

104 DAN5-6-5X 4 PIN

105 DAN5-6-6X 5 PIN

106 EN6081D5-06 24 RIVET

108 NSA5330-6 25 COLLAR

109 DAN5-6-6 38 PIN

110 NSA5075-6 56 COLLAR

111 DAN5-6-5 10 PIN

112 DAN6-6-5 1 PIN

114 DAN5-8-5X 25 PIN

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 176

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

115 DAN11-8X 36 COLLAR

116 DAN5-8-4X 2 PIN

120 DAN6-6-4X 27 PIN

121 DAN6-6-5Y 12 PIN

122 EN6069D5-06 3 RIVET

124 DAN6-6-6Y 13 PIN

125 DAN6-6-7X 23 PIN

126 DAN6-6-6 6 PIN

127 DAN6-6-5X 7 PIN

130 DAN5-6-7X 4 PIN

131 DAN5-8-6X 9 PIN

132 DAN6-6-6X 2 PIN

133 DAN6-5-7 1 PIN

134 DAN6-6-7 1 PIN

136 EN6069D5-07 35 RIVET

137 EN6069D5-08 14 RIVET

144 DAN7-6-11X 1 PIN

145 DAN12-6X 1 COLLAR

146 DAN5-6-10X 2 PIN

148 DAN5-6-8X 2 PIN

160 NSA5075-5 1 COLLAR

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant, Brush Consistency 09-013 As required

Corrosion Preventative

Compound, Temporary

15-009 As required

Anti-Corrosion Primer

Polyurethane

16-001 As required

Polyurethane Finish Paint 16-018 As required

References

Consumable Material List (CML)

Fig. A-GBCAB

Removal/Installation of Angles, Webs,

Brackets and Clips at FR74

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-GBDAB

Fastener Symbol Identification

Sheet 01

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 177

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(a) Install the items between STGR3 and STGR5 on the RH Side, refer to Fig. AGBCAB Sheet 03, Fig. A-GBCAB Sheet 04 and Fig. A-GBDAB Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Angle D5357114726390 Item 95

1 Angle D5357114726590 Item 89

1 Clip D5357072421590 Item 99

1 Web D5357072421790 Item 97

with:

3 Pin DAN5-8-6X Item 131

2 Pin DAN5-8-4X Item 116

5 Collar DAN11-8X Item 115

2 Pin DAN5-6-5 Item 111

2 Collar NSA5075-6 Item 110

and install:

1 Clip D5357072421390 Item 93

with:

6 Pin DAN5-8-5X Item 114

6 Collar DAN11-8X Item 115

and install:

1 Angle D5357114728190 Item 91

with:

4 Pin DAN5-6-6 Item 109

4 Collar NSA5075-6 Item 110

2 As shown in Section B-B, at STGR4, install:

2 Rivet EN6081D5-06 Item 106

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 178

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SERVICE BULLETIN

3 As shown in Section B-B, at STGR5, install:

2 Rivet EN6081D5-06 Item 106

4 Install, as shown in view H:

13 Pin DAN6-6-6Y Item 124

13 Collar NSA5330-6 Item 108

2 Pin DAN6-6-6X Item 132

2 Pin DAN6-6-5X Item 127

4 Collar DAN11-6X Item 103

14 Rivet EN6069D5-08 Item 137

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 103, 109, 110, 111 114, 115, 116, 124, 131 and 132.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 103, 106, 109, 110, 111, 114, 115, 116, 122, 124, 131,

132 and 137.

(b) Install the items between STGR5 and STGR7 on the RH Side, refer to Fig. AGBCAB Sheet 03, Fig. A-GBCAB Sheet 04 and Fig. A-GBDAB Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Angle D5357114726790 Item 81

1 Angle D5357114726990 Item 75

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 179

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SERVICE BULLETIN

NOTE: Item 81 and Item 75 are temporally held in place.

Then between STGR5 and STGR7 install:

1 Web D5357113336590 Item 85

with:

10 Pin DAN5-6-4X Item 102

10 Collar DAN11-6X Item 103

and between Stringer STGR5 and STGR6 install:

1 Clip D5357072431190 Item 83

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

5 Pin DAN5-8-5X Item 114

5 Collar DAN11-8X Item 115

and between Stringer STGR5 and STGR6 install:

1 Angle D5357114728390 Item 87

with:

5 Pin DAN5-6-6 Item 109

5 Collar NSA5075-6 Item 110

and between Stringer STGR6 and STGR7 install:

1 Clip D5357113330190 Item 77

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

5 Pin DAN5-8-5X Item 114

5 Collar DAN11-8X Item 115

and between Stringer STGR6 and STGR7 install:

1 Angle D5357114728590 Item 79

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 180

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with:

5 Pin DAN5-6-6 Item 109

5 Collar NSA5075-6 Item 110

2 As shown in Section B-B, at STGR6, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section B-B, at STGR7, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View H, install:

19 Pin DAN6-6-7X Item 125

1 Pin DAN6-6-5X Item 127

20 Collar DAN11-6X Item 103

6 Pin DAN6-6-6 Item 126

6 Collar NSA5075-6 Item 110

4 Pin DAN6-6-5Y Item 121

4 Collar NSA5330-6 Item 108

7 Rivet EN6069D5-07 Item 136

1 Rivet EN6069D5-06 Item 122

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 108, 109, 110, 114, 115, 121, 125, 126

and 127.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 181

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SERVICE BULLETIN

to the fasteners, Items 102, 103, 104, 106, 108, 109, 110, 114, 115, 121, 122,

125, 126, 127 and 136.

(c) Install the items between Stringer STGR7 and STGR9 on the RH Side, refer to Fig.

A-GBCAB Sheet 03, Fig. A-GBCAB Sheet 04 and Fig. A-GBDAB Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Angle D5357114727190 Item 71

1 Angle D5357114727390 Item 65

NOTE: Item 71 and Item 65 re temporally held in place.

Then between STGR7 and STGR9 install:

1 Web D5357113336390 Item 69

with:

8 Pin DAN5-6-4X Item 102

8 Collar DAN11-6X Item 103

and install:

1 Clip D5357113330390 Item 73

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

4 Pin DAN5-8-5X Item 114

4 Collar DAN11-8X Item 115

4 Pin DAN5-6-5 Item 111

4 Collar NSA5075-6 Item 110

and install:

1 Clip D5357113330590 Item 67

with:

1 Pin DAN5-6-5X Item 104

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 182

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1 Collar DAN11-6X Item 103

5 Pin DAN5-8-5X Item 114

5 Collar DAN11-8X Item 115

4 Pin DAN5-6-5 Item 111

4 Collar NSA5075-6 Item 110

2 As shown in Section B-B, at STGR8, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section B-B, at STGR9, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View K, install:

9 Pin DAN6-6-4X Item 120

1 Pin DAN6-6-5X Item 127

10 Collar DAN11-6X Item 103

8 Pin DAN6-6-5Y Item 121

8 Collar NSA5330-6 Item 108

1 Pin DAN6-6-5 Item 112

1 Collar NSA5075-6 Item 110

2 Rivet EN6069D5-06 Item 122

12 Rivet EN6069D5-07 Item 136

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 108, 110, 111, 112, 114, 115, 120, 121

and 127.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 183

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6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 110, 111, 112, 114, 115, 120,

121, 122, 127 and 136.

(d) Install the items between STGR9 and STGR12 on the RH Side, refer to Fig. AGBCAB Sheet 03, Fig. A-GBCAB Sheet 04 and Fig. A-GBDAB Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Web D5357113330790 Item 63

with:

3 Pin DAN5-6-4X Item 102

3 Collar DAN11-6X Item 103

and install:

1 Angle D5357113331390 Item 52

1 Filler D5357113335400 Item 53

1 Angle D5357113321590 Item 55

with:

24 Pin DAN5-6-6 Item 109

24 Collar NSA5075-6 Item 110

and install:

1 Web D5357113336190 Item 61

with:

6 Pin DAN5-8-6X Item 131

6 Collar DAN11-8X Item 115

8 Rivet EN6081D5-06 Item 106

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 184

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SERVICE BULLETIN

5 Pin DAN5-6-6X Item 105

5 Collar DAN11-6X Item 103

and install:

1 Angle D5357113320990 Item 59

1 Angle D5357113321190 Item 57

with:

4 Pin DAN5-6-7X Item 130

4 Collar DAN11-6X Item 103

2 As shown in Section B-B, at STGR10, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section B-B, at STGR11, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View K, install:

18 Pin DAN6-6-4X Item 120

3 Pin DAN6-6-5X Item 127

4 Pin DAN6-6-7X Item 125

25 Collar DAN11-6X Item 103

16 Rivet EN6069D5-07 Item 136

1 Pin DAN6-6-7 Item 134

1 Collar NSA5075-6 Item 110

1 Pin DAN6-5-7 Item 133

1 Collar NSA5075-5 Item 160

5 As shown in View L, install:

1 Pin DAN7-6-11X Item 144

1 Collar DAN12-6X Item 145

2 Pin DAN5-6-10X Item 146

2 Pin DAN5-6-8X Item 148

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 185

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4 Collar DAN11-6X Item 103

6 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 105, 108, 110, 112, 115, 120, 121, 124, 125,

130 and 131

7 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 105, 106, 108, 110, 112, 115, 120, 121, 124,

125, 130, 131 and 136

**CONF 003

(1) Subtask 531266-020-201-003 - Remove the Angles, Webs, Brackets and Clips at

Frame 72, between STGR13, LH and STGR1, RH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 72

from Stringer 13 LH to Stringer 1 RH

Manpower Resources

Manhours 13.00

Minimum number of person 1

Subtask elapsed time 13.00

Skills AIRFRAME

NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) Task 51-10-01-250-801

51-10-08

Fig. A-GBBAD

Removal/Installation of Angles, Webs,

Brackets and Clips at FR72

Sheet 01

Sheet 02

Sheet 03

Sheet 04

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 186

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References

Fig. A-GBAAA

Location of Inspection Area for Clips at

FR72/FR74

Sheet 01

(a) Remove the items between STGR13 and STGR11 LH, refer to Fig. A-GBBAD

Sheet 01 and Fig. A-GBBAD Sheet 02.

1 As shown in View B, remove:

26 Pin-Rivet Discard

26 Collar Discard

6 Rivet Discard

2 As shown in Section B-B, remove:

2 Pin-Rivet Discard

2 Collar Discard

3 As shown in View D, remove:

16 Pin-Rivet Discard

16 Collar Discard

4 Remove:

1 Angle D5357113120400 Item (1) Discard

1 Web D5357113133000 Item (3) Discard

1 Web D5357113134600 Item (5) Discard

1 Bracket-Z D9357073720000 Item (133) Retain

5 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01

c Findings:

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

- If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 187

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(b) Remove the items between STGR11 and STGR9 LH, refer to Fig. A-GBBAD Sheet

01 and Fig. A-GBBAD Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STRG11 (Section A-A) and

2 Rivet Discard

from the angle at STGR10 (Section A-A).

Remove:

23 Pin-Rivet Discard

23 Collar Discard

11 Rivet Discard

from View B.

2 As shown in View F, remove:

19 Pin-Rivet Discard

19 Collar Discard

16 Rivet Discard

3 Remove:

1 Clip D5357113136600 Item (7) Discard

1 Clip D5357113122600 Item (9) Discard

1 Web D5357113134400 Item (11) Discard

1 Bracket-Z D9357073720000 Item (133) Retain

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 188

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(c) Remove the items between STGR9 and STGR7 LH, refer to Fig. A-GBBAD Sheet

01 and Fig. A-GBBAD Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR9 (Section A-A) and

2 Rivet Discard

from the angle at STGR8 (Section A-A).

Remove:

31 Pin-Rivet Discard

31 Collar Discard

from View B.

2 As shown in View F, remove:

21 Pin-Rivet Discard

21 Collar Discard

14 Rivet Discard

3 Remove:

1 Angle D5357113138200 Item (13) Discard

1 Clip D5357113137600 Item (15) Discard

1 Angle D5357113138000 Item (17) Discard

1 Clip D5357113137400 Item (19) Discard

1 Web D5357113137200 Item (21) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 189

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- If no cracks are found, do the worksteps that follow.

(d) Remove the items between STGR7 and STGR5 LH, refer to Fig. A-GBBAD Sheet

01 and Fig. A-GBBAD Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR7 (Section A-A) and

2 Rivet Discard

from the angle at STGR6 (Section A-A).

Remove:

33 Pin-Rivet Discard

33 Collar Discard

2 Rivet Discard

from View B.

2 As shown in View F, remove:

28 Pin-Rivet Discard

28 Collar Discard

10 Rivet Discard

3 Remove:

1 Angle D5357113137800 Item (23) Discard

1 Angle D5357113138400 Item (25) Discard

1 Clip D5357113137000 Item (27) Discard

1 Angle D5357072223400 Item (29) Discard

1 Clip D5357072222200 Item (31) Discard

1 Angle D5357072223800 Item (33) Discard

1 Web D5357113136800 Item (35) Discard

1 Bracket-Z D9357073720000 Item (133) Retain

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 190

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4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(e) Remove the items between STGR5 and STGR3 LH, refer to Fig. A-GBBAD Sheet

01 and Fig. A-GBBAD Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR5 (Section A-A) and

2 Rivet Discard

from the angle at STGR4 (Section A-A).

Remove:

20 Pin-Rivet Discard

8 Collar Discard

12 Nut Discard

from View B.

2 As shown in View F, remove:

19 Pin-Rivet Discard

19 Collar Discard

14 Rivet Discard

3 Remove:

1 Angle D5357072223200 Item (36) Discard

1 Angle D5357072223600 Item (38) Discard

1 Clip D5357072222400 Item (40) Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 191

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1 Angle D5357072223000 Item (42) Discard

1 Web D5357072222600 Item (44) Discard

1 Clip D5357072222800 Item (46) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(f) Remove the items at STGR1 RH and LH, refer to Fig. A-GBBAD Sheet 01 and Fig.

A-GBBAD Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR1 (Section A-A).

10 Pin-Rivet Discard

10 Nut Discard

from View B.

2 As shown in View E, remove:

7 Pin-Rivet Discard

7 Nut Discard

8 Rivet Discard

3 Remove:

1 Clip D5357072221800 Item (48) Discard

1 Web D5357072221600 Item (49) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 192

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b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(2) Subtask 531266-420-201-003 - Install the Angles, Webs, Brackets and Clips at

Frame 72, between STGR1, RH and STGR13, LH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 72

from Stringer 1 RH to Stringer 13 LH

Manpower Resources

Manhours 16.00

Minimum number of person 1

Subtask elapsed time 16.00

Skills AIRFRAME

Material necessary to do the job

Kit 531266D14R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 D5357113120490 1 ANGLE

3 D5357113133090 1 WEB

5 D5357113134690 1 WEB

7 D5357113136690 1 CLIP

9 D5357113122690 1 CLIP

11 D5357113134490 1 WEB

13 D5357113138290 1 ANGLE

15 D5357113137690 1 CLIP

17 D5357113138090 1 ANGLE

19 D5357113137490 1 CLIP

21 D5357113137290 1 WEB

23 D5357113137890 1 ANGLE

25 D5357113138490 1 ANGLE

27 D5357113137090 1 CLIP

29 D5357072223490 1 ANGLE

31 D5357072222290 1 CLIP

33 D5357072223890 1 ANGLE

35 D5357113136890 1 WEB

36 D5357072223290 1 ANGLE

38 D5357072223690 1 ANGLE

40 D5357072222490 1 CLIP

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 193

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

42 D5357072223090 1 ANGLE

44 D5357072222690 1 WEB

46 D5357072222890 1 CLIP

48 D5357072221890 1 CLIP

49 D5357072221690 1 WEB

102 DAN5-6-4X 31 PIN

103 DAN11-6X 143 COLLAR

104 DAN5-6-5X 40 PIN

107 DAN5-6-5 16 PIN

108 NSA5075-6 56 COLLAR

109 DAN5-5-6 18 PIN

111 DAN5-5-5 9 PIN

112 DAN5-6-6 2 PIN

113 DAN5-6-3X 3 PIN

114 DAN5-8-5X 10 PIN

115 DAN11-8X 29 COLLAR

116 DAN5-8-4X 2 PIN

117 DAN5-8-7X 8 PIN

118 DAN5-8-8X 2 PIN

119 DAN6-6-3X 8 PIN

120 DAN6-6-4X 29 PIN

121 DAN6-6-5X 13 PIN

123 DAN6-8-6X 7 PIN

125 DAN6-6-7X 10 PIN

126 DAN6-6-6 4 PIN

127 DAN6-6-5 3 PIN

128 DAN6-6-3 8 PIN

129 DAN5-6-3 4 PIN

132 DAN6-6-6X 9 PIN

134 DAN6-6-7 19 PIN

135 EN6081D5-07 35 RIVET

137 EN6069D5-08 62 RIVET

160 NSA5075-5 27 COLLAR

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant, Brush Consistency 09-013 As required

Corrosion Preventative

Compound, Temporary

15-009 As required

Anti-Corrosion Primer

Polyurethane

16-001 As required

Polyurethane Finish Paint 16-018 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 194

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References

Consumable Material List (CML)

Fig. A-GBBAD

Removal/Installation of Angles, Webs,

Brackets and Clips at FR72

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-GBDAD

Fastener Symbol Identification

Sheet 01

(a) Install the items between STGR1 LH and RH, refer to Fig. A-GBBAD Sheet 03 and

Fig. A-GBDAD Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Web D5357072221690 Item 49

with:

8 Pin DAN5-8-7X Item 117

8 Collar DAN11-8X Item 115

and then install:

1 Clip D5357072221890 Item 48

with:

2 PIN DAN5-8-8X Item 118

2 Collar DAN11-8X Item 115

2 As shown in Section E-E, install:

2 Pin DAN5-6-3 Item 129

2 Collar NSA5075-6 Item 108

3 As shown in View K, install:

7 Pin DAN6-8-6X Item 123

7 Collar DAN11-8X Item 115

8 Rivet EN6069D5-08 Item 137

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 195

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4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 115, 117, 118 and 123.

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 106, 115, 117, 118, 123 and 137.

(b) Install the items between STGR3 and STGR4 on the LH Side, refer to Fig. AGBBAD Sheet 03,Fig. A-GBBAD Sheet 04 and Fig. A-GBDAD Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357072223090 Item 42

1 Clip D5357072222890 Item 46

with:

4 Pin DAN5-8-5X Item 114

4 Collar DAN11-8X Item 115

3 Pin DAN5-5-6 Item 109

3 Collar NSA5075-5 Item 160

2 As shown in Section C-C, STGR4 install:

2 Rivet EN6081D5-07 Item 135

3 As shown in View L, install between STGR3 and STGR4:

3 Pin DAN6-6-6X Item 132

4 Pin DAN6-6-7X Item 125

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 196

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7 Collar DAN11-6X Item 103

7 Rivet EN6069D5-08 Item 137

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 103, 109, 114, 115, 125, 132 and 160.

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 103, 109, 114, 115, 125, 132, 135, 137 and 160.

(c) Install the items between STGR4 and STGR5 on the LH Side, refer to Fig. AGBBAD Sheet 03,Fig. A-GBBAD Sheet 04 and Fig. A-GBDAD Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357072223290 Item 36

1 Web D5357072222690 Item 44

with:

2 Pin DAN5-8-4X Item 116

2 Collar DAN11-8X Item 115

and then install:

1 Clip D5357072222490 Item 40

with:

6 Pin DAN5-8-5X Item 114

6 Collar DAN11-8X Item 115

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 197

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and then install:

1 Angle D5357072223690 Item 38

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 160

2 As shown in Section, C-C at STGR5, install:

2 Rivet EN6081D5-07 Item 135

3 As shown in View L, between STGR4 and STGR5, install:

6 Pin DAN6-6-6X Item 132

6 Pin DAN6-6-7X Item 125

12 Collar DAN11-6X Item 103

7 Rivet EN6069D5-08 Item 137

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 103, 109, 114, 115, 116, 124, 132 and 160.

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 103, 109, 114, 115, 116, 124, 122, 132, 135, 137 and

160.

(d) Install the items between STGR5 and STGR7 on the LH Side, refer to Fig. AGBBAD Sheet 03,Fig. A-GBBAD Sheet 04 and Fig. A-GBDAD Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 198

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1 Angle D5357072223490 Item 29

1 Angle D5357113137890 Item 23

1 Web D5357113136890 Item 35

with:

9 Pin DAN5-6-4X Item 102

9 Collar DAN11-6X Item 103

2 Rivet EN6081D5-07 Item 135

and then between STGR5 and STGR6 install:

1 Clip D5357072222290 Item 31

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

and then between STGR5 and STGR6 install:

1 Angle D5357072223890 Item 33

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 160

and then between STGR6 and STGR7 install:

1 Clip D5357113137090 Item 27

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

and then between STGR6 and STGR7 install:

1 Angle D5357113138490 Item 25

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 160

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 199

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SERVICE BULLETIN

2 As shown in Section C-C, at STGR6, install:

2 Rivet EN6081D5-07 Item 135

3 As shown in Section C-C, at STGR7, install:

2 Rivet EN6081D5-07 Item 135

4 As shown in View L, between STGR5 and STGR7, install:

19 Pin DAN6-6-7 Item 134

24 Collar NSA5075-6 Item 108

10 Rivet EN6069D5-08 Item 137

4 Pin DAN6-6-6 Item 126

4 Pin DAN6-6-5X Item 121

4 Collar DAN11-6X Item 103

1 Pin DAN6-6-5 Item 127

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 109, 110, 121, 126, 127 and 134.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 109, 110, 121, 126, 127, 134, 135 and

137.

(e) Install the items between STGR7 and STGR9 on the LH Side, refer to Fig. AGBBAD Sheet 03, Fig. A-GBBAD Sheet 04 and Fig. A-GBDAD Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 200

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SERVICE BULLETIN

to wet install on Frame 72, as shown in View G:

1 Angle D5357113138290 Item 13

1 Angle D5357113138090 Item 17

NOTE: Item 13 and Item 17 are temporally held in place.

Then between STGR7 and STGR9 install:

1 Web D5357113137290 Item 21

with:

10 Pin DAN5-6-4X Item 102

10 Collar DAN11-6X Item 103

and then between STGR7 and STGR8 install:

1 Clip D5357113137490 Item 19

with:

5 Pin DAN5-6-5X Item 104

5 Collar DAN11-6X Item 103

4 Pin DAN5-5-5 Item 111

4 Collar NSA5075-5 Item 160

and then between Stringer STGR8 and STGR9 install:

1 Clip D5357113137690 Item 15

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

5 Pin DAN5-5-5 Item 111

5 Collar NSA5075-5 Item 160

2 As shown in Section C-C, at STGR8, install:

2 Rivet EN6081D5-07 Item 135

3 As shown in Section C-C, at STGR9, install:

2 Rivet EN6081D5-07 Item 135

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 201

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SERVICE BULLETIN

4 As shown in View L, between STGR7 and STGR9, install:

10 Pin DAN6-6-4X Item 120

19 Collar DAN11-6X Item 103

14 Rivet EN6069D5-08 Item 137

9 Pin DAN6-6-5X Item 121

2 Collar NSA5075-6 Item 108

2 Pin DAN6-6-5 Item 127

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 108, 110, 111, 120 and 127.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 108, 110, 111, 120, 121, 127, 135 and

137.

(f) Install the items between STGR9 and STGR11 on the LH Side, refer to Fig. AGBBAD Sheet 03, Fig. A-GBBAD Sheet 04 and Fig. A-GBDAD Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Bracket-Z D9357073720000 Item (133) Retained at

removal

1 Web D5357113134490 Item 11

with:

2 Rivet EN6081D5-07 Item 135

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 202

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SERVICE BULLETIN

9 Pin DAN5-6-4X Item 102

9 Collar DAN11-6X Item 103

and then STGR9 and STGR10, install:

1 Clip D5357113122690 Item 9

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

5 Rivet EN6081D5-07 Item 135

and then between STGR10 and STGR11, install:

1 Clip D5357113136690 Item 7

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

4 Rivet EN6081D5-07 Item 135

2 As shown in Section C-C, at STGR10 install:

2 Rivet EN6081D5-07 Item 135

3 As shown in Section C-C, at STGR11 install:

2 Rivet EN6081D5-07 Item 135

4 As shown in View L, between STGR9 and STGR11, install:

10 Pin DAN6-6-4X Item 120

19 Collar DAN11-6X Item 103

16 Rivet EN6069D5-08 Item 137

9 Pin DAN6-6-4X Item 120

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 203

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SERVICE BULLETIN

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104 and 120.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners Items 102, 103, 104, 120, 135 and 137.

(g) Install the items between STGR11 and STGR13 on the LH Side, refer to Fig. AGBBAD Sheet 03 and Fig. A-GBDAD Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Bracket-Z D9357073720000 Item (133) Retained at

removal

1 Web D5357113134690 Item 5

with:

2 Rivet EN6081D5-07 Item 135

3 Pin DAN5-6-3X Item 113

3 Collar DAN11-6X Item 103

and then install:

1 Web D5357113133090 Item 3

with:

3 Pin DAN5-6-4X Item 102

3 Collar DAN11-6X Item 103

4 Rivet EN6081D5-07 Item 135

and then install:

1 Angle D5357113120490 Item 1

with:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 204

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SERVICE BULLETIN

16 Pin DAN5-6-5 Item 107

18 Collar NSA5075-6 Item 108

2 Pin DAN5-6-6 Item 112

2 As shown in Section D-D, at STGR12, install:

2 Pin DAN5-6-3 Item 129

2 Collar NSA5075-6 Item 108

3 As shown in View J, install:

8 Pin DAN6-6-3X Item 119

8 Collar DAN11-6X Item 103

8 Pin DAN6-6-3 Item 128

8 Collar NSA5075-6 Item 108

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 107, 108, 112, 113, 119 and 128.

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 107, 108, 112, 113, 119, 128 and 135.

(3) Subtask 531266-020-208-003 - Remove the Angles, Webs, Brackets and Clips at

Frame 72, between STGR13, RH and STGR3, RH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 72

from Stringer 13 RH to Stringer 3 RH

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 205

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SERVICE BULLETIN

Manpower Resources

Manhours 11.00

Minimum number of person 1

Subtask elapsed time 11.00

Skills AIRFRAME

NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) Task 51-10-01-250-801

51-10-08

Fig. A-GBAAA

Location of Inspection Area for Clips at

FR72/FR74

Sheet 01

Fig. A-GBBAD

Removal/Installation of Angles, Webs,

Brackets and Clips at FR72

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the items between STGR13 and STGR11 RH, refer to Fig. A-GBBAD

Sheet 01 and Fig. A-GBBAD Sheet 02.

1 As shown in View B, remove:

26 Pin-Rivet Discard

26 Collar Discard

6 Rivet Discard

2 As shown in Section B-B, remove:

2 Pin-Rivet Discard

2 Collar Discard

3 As shown in View D, remove:

16 Pin-Rivet Discard

16 Collar Discard

4 Remove:

1 Angle D5357113120500 Item (2) Discard

1 Web D5357113133100 Item (4) Discard

1 Web D5357113134700 Item (6) Discard

1 Bracket-Z D9357073720000 Item (133) Retain

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 206

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5 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(b) Remove the items between STGR11 and STGR9 RH, refer to Fig. A-GBBAD Sheet

01 and Fig. A-GBBAD Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STRG11 (Section A-A) and

2 Rivet Discard

from the angle at STGR10 (Section A-A).

Remove:

23 Pin-Rivet Discard

23 Collar Discard

11 Rivet Discard

from View B.

2 As shown in View F, remove:

19 Pin-Rivet Discard

19 Collar Discard

16 Rivet Discard

3 Remove:

1 Clip D5357113136700 Item (8) Discard

1 Clip D5357113122700 Item (10) Discard

1 Web D5357113134500 Item (12) Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 207

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SERVICE BULLETIN

1 Bracket-Z D9357073720000 Item (133) Retain

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(c) Remove the items between STGR9 and STGR7 RH, refer to Fig. A-GBBAD Sheet

01 and Fig. A-GBBAD Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR9 (Section A-A) and

2 Rivet Discard

from the angle at STGR8 (Section A-A).

Remove:

31 Pin-Rivet Discard

31 Collar Discard

from View B.

2 As shown in View F, remove:

21 Pin-Rivet Discard

21 Collar Discard

14 Rivet Discard

3 Remove:

1 Angle D5357113138300 Item (14) Discard

1 Clip D5357113137700 Item (16) Discard

1 Angle D5357113138100 Item (18) Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 208

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SERVICE BULLETIN

1 Clip D5357113137500 Item (20) Discard

1 Web D5357113137300 Item (22) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(d) Remove the items between STGR7 and STGR5 RH, refer to Fig. A-GBBAD Sheet

01 and Fig. A-GBBAD Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR7 (Section A-A) and

2 Rivet Discard

from the angle at STGR6 (Section A-A).

Remove:

33 Pin-Rivet Discard

33 Collar Discard

2 Rivet Discard

from View B.

2 As shown in View F, remove:

28 Pin-Rivet Discard

28 Collar Discard

10 Rivet Discard

3 As shown in View C, remove:

1 Angle D5357113137900 Item (24) Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 209

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SERVICE BULLETIN

1 Angle D5357113138500 Item (26) Discard

1 Clip D5357113137100 Item (28) Discard

1 Angle D5357072223500 Item (30) Discard

1 Clip D5357072222300 Item (32) Discard

1 Angle D5357072223900 Item (34) Discard

1 Web-Shear D5357116135400 Item (50) Discard

1 Bracket-Z D9357073720000 Item (133) Retain

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(e) Remove the items between STGR5 and STGR3 RH, refer to Fig. A-GBBAD Sheet

01 and Fig. A-GBBAD Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR5 (Section A-A) and

2 Rivet Discard

from the angle at STGR4 (Section A-A).

Remove:

20 Pin-Rivet Discard

8 Collar Discard

12 Nut Discard

from View B.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 210

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2 As shown in View F, remove:

19 Pin-Rivet Discard

19 Collar Discard

14 Rivet Discard

3 Remove:

1 Angle D5357072223300 Item (37) Discard

1 Angle D5357072223700 Item (39) Discard

1 Clip D5357072222500 Item (41) Discard

1 Angle D5357072223100 Item (43) Discard

1 Web D5357072222700 Item (45) Discard

1 Clip D5357072222900 Item (47) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(4) Subtask 531266-420-202-003 - Install the Angles, Webs, Brackets and Clips at

Frame 72, between STGR3, RH to STGR13, RH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 72

from Stringer 3 RH to Stringer 13 RH

Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills AIRFRAME

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 211

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SERVICE BULLETIN

Material necessary to do the job

Kit 531266D14R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 D5357113120590 1 ANGLE

4 D5357113133190 1 WEB

6 D5357113134790 1 WEB

8 D5357113136790 1 CLIP

10 D5357113122790 1 CLIP

12 D5357113134590 1 WEB

14 D5357113138390 1 ANGLE

16 D5357113137790 1 CLIP

18 D5357113138190 1 ANGLE

20 D5357113137590 1 CLIP

22 D5357113137390 1 WEB

24 D5357113137990 1 ANGLE

26 D5357113138590 1 ANGLE

28 D5357113137190 1 CLIP

30 D5357072223590 1 ANGLE

32 D5357072222390 1 CLIP

34 D5357072223990 1 ANGLE

37 D5357072223390 1 ANGLE

39 D5357072223790 1 ANGLE

41 D5357072222590 1 CLIP

43 D5357072223190 1 ANGLE

45 D5357072222790 1 WEB

47 D5357072222990 1 CLIP

50 D5357116135490 1 WEB

102 DAN5-6-4X 31 PIN

103 DAN11-6X 143 COLLAR

104 DAN5-6-5X 40 PIN

107 DAN5-6-5 16 PIN

108 NSA5075-6 54 COLLAR

109 DAN5-5-6 18 PIN

111 DAN5-5-5 9 PIN

112 DAN5-6-6 2 PIN

113 DAN5-6-3X 3 PIN

114 DAN5-8-5X 10 PIN

115 DAN11-8X 12 COLLAR

116 DAN5-8-4X 2 PIN

119 DAN6-6-3X 8 PIN

120 DAN6-6-4X 29 PIN

121 DAN6-6-5X 13 PIN

125 DAN6-6-7X 10 PIN

126 DAN6-6-6 4 PIN

127 DAN6-6-5 3 PIN

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 212

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

128 DAN6-6-3 8 PIN

129 DAN5-6-3 2 PIN

132 DAN6-6-6X 9 PIN

134 DAN6-6-7 19 PIN

135 EN6081D5-07 35 RIVET

137 EN6069D5-08 54 RIVET

160 NSA5075-5 27 COLLAR

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant, Brush Consistency 09-013 As required

Corrosion Preventative

Compound, Temporary

15-009 As required

Anti-Corrosion Primer

Polyurethane

16-001 As required

Polyurethane Finish Paint 16-018 As required

References

Consumable Material List (CML)

Fig. A-GBBAD

Removal/Installation of Angles, Webs,

Brackets and Clips at FR72

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-GBDAD

Fastener Symbol Identification

Sheet 01

(a) Install the items between STGR3 and STGR4 on the RH Side, refer to Fig. AGBBAD Sheet 03,Fig. A-GBBAD Sheet 04 and Fig. A-GBDAD Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357072223190 Item 43

1 Clip D5357072222990 Item 47

with:

4 Pin DAN5-8-5X Item 114

4 Collar DAN11-8X Item 115

3 Pin DAN5-5-6 Item 109

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 213

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3 Collar NSA5075-5 Item 160

2 As shown in Section C-C at STGR4, install:

2 Rivet EN6081D5-07 Item 135

3 As shown in View L, at STGR3 and STGR4, install:

3 Pin DAN6-6-6X Item 132

7 Collar DAN11-6X Item 103

4 Pin DAN6-6-7X Item 125

7 Rivet EN6069D5-08 Item 137

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 109, 114, 115, 125, 132 and 160.

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 111, 114, 115, 121, 125, 135, 137 and 160.

(b) Install the items between STGR4 and STGR5 on the RH Side, refer to Fig. AGBBAD Sheet 03,Fig. A-GBBAD Sheet 04 and Fig. A-GBDAD Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357072223390 Item 37

1 Web D5357072222790 Item 45

with:

2 Pin DAN5-8-4X Item 116

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 214

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2 Collar DAN11-8X Item 115

and then install:

1 Clip D5357072222590 Item 41

with:

6 Pin DAN5-8-5X Item 114

6 Collar DAN11-8X Item 115

and then install:

1 Angle D5357072223790 Item 39

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 160

2 As shown in Section C-C at STGR5, install:

2 Rivet EN6081D5-07 Item 135

3 As shown in View L, at STGR4 and STGR5, install:

6 Pin DAN6-6-6X Item 132

12 Collar DAN11-6X Item 103

6 Pin DAN6-6-7X Item 125

7 Rivet EN6069D5-08 Item 137

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fastener, Items 103, 109, 114, 115, 116, 125, 132 and 160.

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 215

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SERVICE BULLETIN

to the fasteners, 103, 109, 114, 115, 116, 125, 132, 135, 137 and 160.

(c) Install the items between STGR5 and STGR7 on the RH Side, refer to Fig. AGBBAD Sheet 03,Fig. A-GBBAD Sheet 04 and Fig. A-GBDAD Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357072223590 Item 30

1 Angle D5357113137990 Item 24

1 Bracket-Z D9357073720000 Item (133) Retained at

removal

1 Web D5357116135490 Item 50

with:

9 Pin DAN5-6-4X Item 102

9 Collar DAN11-6X Item 103

2 Rivet EN6081D5-07 Item 135

and between STGR5 and STGR7, as shown in View H, install:

1 Clip D5357072222390 Item 32

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

and between STGR5 and STGR7, install:

1 Angle D5357072223990 Item 34

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 160

and between STGR6 and STGR7, install:

1 Clip D5357113137190 Item 28

with:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

and between STGR6 and STGR7 install:

1 Angle D5357113138590 Item 26

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 160

2 As shown in Section C-C at STGR6, install:

2 Rivet EN6081D5-07 Item 135

3 As shown in Section C-C at STGR7, install:

2 Rivet EN6081D5-07 Item 135

4 Install to the fuselage skin between STGR5 and STGR7, refer to Fig. AGBBAD Sheet 04, View L:

19 Pin DAN6-6-7 Item 134

24 Collar NSA5075-6 Item 108

10 Rivet EN6069D5-08 Item 137

4 Pin DAN6-6-6 Item 126

4 Pin DAN6-6-5X Item 121

4 Collar DAN11-6X Item 103

1 Pin DAN6-6-5 Item 127

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 108, 109, 121, 125, 126, 127 and 160.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 217

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SERVICE BULLETIN

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, 102, 103, 104, 108, 109, 121, 126, 127, 134, 135, 137 and

160.

(d) Install the items between STGR7 and STGR9 on the RH Side, refer to Fig. AGBBAD Sheet 03, Fig. A-GBBAD Sheet 04 and Fig. A-GBDAD Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357113138390 Item 14

1 Angle D5357113138190 Item 18

NOTE: Item 14 and Item 18 are temporally held in place.

Then between STGR7 and STGR9 install:

1 Web D5357113137390 Item 22

with:

10 Pin DAN5-6-4X Item 102

10 Collar DAN11-6X Item 103

and then between STGR7 and STGR8 install:

1 Clip D5357113137590 Item 20

with:

5 Pin DAN5-6-5X Item 104

5 Collar DAN11-6X Item 103

4 Pin DAN5-5-5 Item 111

4 Collar NSA5075-5 Item 160

and then between Stringer STGR8 and STGR9 install:

1 Clip D5357113137790 Item 16

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 218

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SERVICE BULLETIN

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

5 Pin DAN5-5-5 Item 111

5 Collar NSA5075-5 Item 160

2 As shown in Section C-C at STGR8, install:

2 Rivet EN6081D5-07 Item 135

3 As shown in Section C-C at STGR9, install:

2 Rivet EN6081D5-07 Item 135

4 Install to the fuselage skin between STGR7 and STGR9, refer to Fig. AGBBAD Sheet 04, View L:

10 Pin DAN6-6-4X Item 120

19 Collar DAN11-6X Item 103

14 Rivet EN6069D5-08 Item 137

9 Pin DAN6-6-5X Item 121

2 Collar NSA5075-6 Item 108

2 Pin DAN6-6-5 Item 127

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 108, 110, 111, 120 and 127.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

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

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 219

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SERVICE BULLETIN

(e) Install the items between STGR9 and STGR11 on the RH Side, refer to Fig. AGBBAD Sheet 03, Fig. A-GBBAD Sheet 04 and Fig. A-GBDAD Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Bracket-Z D9357073720000 Item (133) Retained at

removal

1 Web D5357113134590 Item 12

with:

2 Rivet EN6081D5-07 Item 135

9 Pin DAN5-6-4X Item 102

9 Collar DAN11-6X Item 103

and then STGR9 and STGR10, install:

1 Clip D5357113122790 Item 10

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

5 Rivet EN6081D5-07 Item 135

and then between STGR10 and STGR11, install:

1 Clip D5357113136790 Item 8

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

4 Rivet EN6081D5-07 Item 135

2 As shown in Section C-C, at STGR 10, install:

2 Rivet EN6081D5-07 Item 135

3 As shown in Section C-C, at STGR 11, install:

2 Rivet EN6081D5-07 Item 135

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 220

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SERVICE BULLETIN

4 As shown in View L, between STGR9 and STGR11, install:

19 Pin DAN6-6-4X Item 120

19 Collar DAN11-6X Item 103

16 Rivet EN6069D5-08 Item 137

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104 and 120.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 120, 135, 136 and 137.

(f) Install the items between STGR11 and STGR13 on the RH Side, refer to Fig. AGBBAD Sheet 03 and Fig. A-GBDAD Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Bracket-Z D9357073720000 Item (133) Retained at

removal

1 Web D5357113134790 Item 6

with:

2 Rivet EN6081D5-07 Item 135

3 Pin DAN5-6-3X Item 113

3 Collar DAN11-6X Item 103

and then install:

1 Web D5357113133190 Item 4

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 221

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SERVICE BULLETIN

with:

3 Pin DAN5-6-4X Item 102

3 Collar DAN11-6X Item 103

4 Rivet EN6081D5-07 Item 135

and then install:

1 Angle D5357113120590 Item 2

with:

16 Pin DAN5-6-5 Item 107

18 Collar NSA5075-6 Item 108

2 Pin DAN5-6-6 Item 112

2 As shown in Section D-D, at STGR12, install:

2 Pin DAN5-6-3 Item 129

2 Collar NSA5075-6 Item 108

3 As shown in View J, install:

8 Pin DAN6-6-3X Item 119

8 Collar DAN11-6X Item 103

8 Pin DAN6-6-3 Item 128

8 Collar NSA5075-6 Item 108

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fastener, Items 102, 103, 107, 108, 112, 113, 119 and 128.

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 222

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SERVICE BULLETIN

to the fasteners, Items 102, 103, 107, 108, 112, 113, 119, 128 and 135.

(5) Subtask 531266-020-203-003 - Remove the Angles, Webs, Brackets and Clips at

Frame 74, between STGR12, LH and STGR1, RH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 74

from Stringer 12 LH to Stringer 1 RH

Manpower Resources

Manhours 11.00

Minimum number of person 1

Subtask elapsed time 11.00

Skills AIRFRAME

NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) Task 51-10-01-250-801

51-10-08

Fig. A-GBAAA

Location of Inspection Area for Clips at

FR72/FR74

Sheet 01

Fig. A-GBCAD

Removal/Installation of Angles, Webs,

Brackets and Clips at FR74

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the items between STGR12 and STGR9 LH, refer to Fig. A-GBCAD Sheet

01 and Fig. A-GBCAD Sheet 02.

1 As shown in Section A-A, remove:

2 Rivet Discard

from the angle at STGR11 (Section A-A) and

2 Rivet Discard

from the angle at STGR10 (Section A-A).

Remove:

42 Pin-Rivet Discard

42 Collar Discard

8 Rivet Discard

from View B.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 223

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2 As shown in View E, remove:

25 Pin-Rivet Discard

25 Collar Discard

16 Rivet Discard

3 Remove:

1 Angle D5357113331200 Item (51) Discard

1 Filler D5357113335400 Item (53) Discard

1 Angle D5357113321400 Item (54) Discard

1 Angle D5357113321000 Item (56) Discard

1 Angle D5357113320800 Item (58) Discard

1 Web D5357113336000 Item (60) Discard

1 Web D5357113330600 Item (62) Discard

4 As shown in View F, remove:

5 Pin-Rivet Discard

5 Collar Discard

5 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(b) Remove the items between STGR9 and STGR7 LH, refer to Fig. A-GBCAD Sheet

01 and Fig. A-GBCAD Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STRG9 (Section A-A) and

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 224

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2 Rivet Discard

from the angle at STRG8 (Section A-A).

Remove:

27 Pin-Rivet Discard

27 Collar Discard

from View B.

2 As shown in View E, remove:

19 Pin-Rivet Discard

19 Collar Discard

14 Rivet Discard

3 Remove:

1 Angle D5357113327000 Item (64) Discard

1 Clip D5357113326400 Item (66) Discard

1 Web D5357113325800 Item (68) Discard

1 Angle D5357113326800 Item (70) Discard

1 Clip D5357113326200 Item (72) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(c) Remove the items between STGR7 and STGR5 LH, refer to Fig. A-GBCAD Sheet

01.

1 Remove:

2 Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 225

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SERVICE BULLETIN

from the angle at STRG7 (Section A-A) and

2 Rivet Discard

from the angle at STRG6 (Section A-A).

Remove:

32 Pin-Rivet Discard

32 Collar Discard

from View B.

2 As shown in View C, remove:

30 Pin-Rivet Discard

30 Collar Discard

8 Rivet Discard

3 Remove:

1 Angle D5357113326600 Item (74) Discard

1 Clip D5357113326000 Item (76) Discard

1 Angle D5357113327200 Item (78) Discard

1 Angle D5357072423400 Item (80) Discard

1 Clip D5357072422000 Item (82) Discard

1 Web D5357113325600 Item (84) Discard

1 Angle D5357072423800 Item (86) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 226

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(d) Remove the items between STGR5 and STGR3, refer to Fig. A-GBCAD Sheet 01.

1 Remove:

2 Rivet Discard

from the angle at STRG5 (Section A-A) and

2 Rivet Discard

from the angle at STRG4 (Section A-A).

Remove:

18 Pin-Rivet Discard

18 Collar Discard

from View B.

2 As shown in View C, remove:

17 Pin-Rivet Discard

17 Collar Discard

14 Rivet Discard

3 Remove:

1 Angle D5357072423200 Item (88) Discard

1 Angle D5357072423600 Item (90) Discard

1 Clip D5357072422200 Item (92) Discard

1 Angle D5357072423000 Item (94) Discard

1 Web D5357072422600 Item (96) Discard

1 Clip D5357072422400 Item (98) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 227

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- If no cracks are found, do the worksteps that follow.

(e) Remove the items between STGR2 LH and STGR1 RH, refer to Fig. A-GBCAD

Sheet 01 and Fig. A-GBCAD Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STRG1 (Section A-A).

Remove:

12 Pin-Rivet Discard

12 Collar Discard

from View B.

2 As shown in View D, remove:

8 Pin-Rivet Discard

8 Collar Discard

8 Pin-Rivet Discard

3 Remove:

1 Clip D5357072221800 Item (48) Discard

1 Web D5357072421800 Item (100) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(6) Subtask 531266-420-203-003 - Install the Angles, Webs, Brackets and Clips at

Frame 74, between STGR1, RH and STGR12, LH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 74

from Stringer 1 RH to Stringer 12 LH

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 228

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SERVICE BULLETIN

Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills AIRFRAME

Material necessary to do the job

Kit 531266D14R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

48 D5357072221890 1 CLIP

51 D5357113331290 1 ANGLE

53 D5357113335400 1 FILLER

54 D5357113321490 1 ANGLE

56 D5357113321090 1 ANGLE

58 D5357113320890 1 ANGLE

60 D5357113336090 1 WEB

62 D5357113330690 1 WEB

64 D5357113327090 1 ANGLE

66 D5357113326490 1 CLIP

68 D5357113325890 1 WEB

70 D5357113326890 1 ANGLE

72 D5357113326290 1 CLIP

74 D5357113326690 1 ANGLE

76 D5357113326090 1 CLIP

78 D5357113327290 1 ANGLE

80 D5357072423490 1 ANGLE

82 D5357072422090 1 CLIP

84 D5357113325690 1 WEB

86 D5357072423890 1 ANGLE

88 D5357072423290 1 ANGLE

90 D5357072423690 1 ANGLE

92 D5357072422290 1 CLIP

94 D5357072423090 1 ANGLE

96 D5357072422690 1 WEB

98 D5357072422490 1 CLIP

100 D5357072421890 1 WEB

102 DAN5-6-4X 21 PIN

103 DAN11-6X 101 COLLAR

104 DAN5-6-5X 4 PIN

105 DAN5-6-6X 5 PIN

108 NSA5075-6 52 COLLAR

109 DAN5-5-6 17 PIN

111 DAN5-5-5 8 PIN

112 DAN5-6-6 24 PIN

114 DAN5-8-5X 25 PIN

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

115 DAN11-8X 56 COLLAR

116 DAN5-8-4X 2 PIN

117 DAN5-8-7X 10 PIN

118 DAN5-8-8X 2 PIN

120 DAN6-6-4X 27 PIN

121 DAN6-6-5X 15 PIN

123 DAN6-8-6X 8 PIN

125 DAN6-6-7X 13 PIN

126 DAN6-6-6 6 PIN

127 DAN6-6-5 3 PIN

130 DAN5-6-7X 4 PIN

131 DAN5-8-6X 9 PIN

132 DAN6-6-6X 8 PIN

134 DAN6-6-7 19 PIN

135 EN6081D5-07 26 RIVET

137 EN6069D5-08 60 RIVET

144 DAN7-6-11X 1 PIN

145 DAN12-6X 1 COLLAR

146 DAN5-6-10X 2 PIN

148 DAN5-6-8X 2 PIN

160 NSA5075-5 25 COLLAR

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant, Brush Consistency 09-013 As required

Corrosion Preventative

Compound, Temporary

15-009 As required

Anti-Corrosion Primer

Polyurethane

16-001 As required

Polyurethane Finish Paint 16-018 As required

References

Consumable Material List (CML)

Fig. A-GBCAD

Removal/Installation of Angles, Webs,

Brackets and Clips at FR74

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-GBDAD

Fastener Symbol Identification

Sheet 01

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 230

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SERVICE BULLETIN

(a) Install the items between STGR2 on the RH Side and STGR2 on the LH Side, refer

to Fig. A-GBCAD Sheet 03,Fig. A-GBCAD Sheet 04 and Fig. A-GBDAD Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Web D5357072421890 Item 100

with:

10 Pin DAN5-8-7X Item 117

10 Collar DAN11-8X Item 115

and then install:

1 Clip D5357072221890 Item 48

with:

2 PIN DAN5-8-8X Item 118

2 Collar DAN11-8X Item 115

2 As shown in Section B-B, at STGR1, install:

2 Rivet EN6081D5-07 Item 135

3 As shown in View J, install:

8 Pin DAN6-8-6X Item 123

8 Collar DAN11-8X Item 115

8 Rivet EN6069D5-08 Item 137

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 115,, 117, 118, 123, 135 and 137.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 231

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5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 115, 117, 118, 123, 135 and 137.

(b) Install the items between STGR3 and STGR5 on the LH Side, refer to Fig. AGBCAD Sheet 03,Fig. A-GBCAD Sheet 04 and Fig. A-GBDAD Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Angle D5357072423090 Item 94

1 Angle D5357072423290 Item 88

1 Clip D5357072422490 Item 98

1 Web D5357072422690 Item 96

with:

3 Pin DAN5-8-6X Item 131

5 Collar DAN11-8X Item 115

2 Pin DAN5-5-6 Item 109

2 Collar NSA5075-5 Item 160

2 Pin DAN5-8-4X Item 116

and install:

1 Clip D5357072422290 Item 92

with:

6 Pin DAN5-8-5X Item 114

6 Collar DAN11-8X Item 115

and install:

1 Angle D5357072423690 Item 90

with:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 232

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5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 160

2 As shown in Section B-B, at STGR4, install:

2 Rivet EN6081D5-07 Item 135

3 As shown in Section B-B, at STGR5, install:

2 Rivet EN6081D5-07 Item 135

4 As shown in View H, install:

8 Pin DAN6-6-6X Item 132

17 Collar DAN11-6X Item 103

9 Pin DAN6-6-7X Item 125

14 Rivet EN6069D5-08 Item 137

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 103, 109, 110, 114, 115, 116, 125, 131 and 132.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 103, 109, 110, 114, 115, 116, 125, 131, 132, 135 and

137.

(c) Install the items between STGR5 and STGR7 on the LH Side, refer to Fig. AGBCAD Sheet 03,Fig. A-GBCAD Sheet 04 and Fig. A-GBDAD Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 233

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SERVICE BULLETIN

1 Angle D5357072423490 Item 80

1 Angle D5357113326690 Item 74

NOTE: Item 80 and Item 74 are temporally held in place.

Then between STGR5 and STGR7 install:

1 Web D5357113325690 Item 84

with:

10 Pin DAN5-6-4X Item 102

10 Collar DAN11-6X Item 103

and then between Stringer STGR5 and STGR6 install:

1 Clip D5357072422090 Item 82

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

5 Pin DAN5-8-5X Item 114

5 Collar DAN11-8X Item 115

and then between Stringer STGR5 and STGR6 install:

1 Angle D5357072423890 Item 86

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 160

and then between Stringer STGR6 and STGR7 install:

1 Clip D5357113326090 Item 76

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

5 Pin DAN5-8-5X Item 114

5 Collar DAN11-8X Item 115

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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SERVICE BULLETIN

and then between Stringer STGR6 and STGR7 install:

1 Angle D5357113327290 Item 78

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 160

2 As shown in Section B-B at STGR6, install:

2 Rivet EN6081D5-07 Item 135

3 As shown in Section B-B, at STGR7, install:

2 Rivet EN6081D5-07 Item 135

4 As shown in View H, install between STGR5 and STGR7

19 Pin DAN6-6-7 Item 134

26 Collar NSA5075-6 Item 108

6 Pin DAN6-6-6 Item 126

8 Rivet EN6069D5-08 Item 137

4 Pin DAN6-6-5X Item 121

4 Collar DAN11-6X Item 103

1 Pin DAN6-6-5 Item 127

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 108, 109, 114, 115, 121, 126, 127, 132,

134 and 160.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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SERVICE BULLETIN

to the fasteners, Items 102, 103, 104, 109, 114, 115, 121, 125, 126, 127, 132,

134, 135, 137 and 160.

(d) Install the items between Stringer STGR7 and STGR9 on the LH Side, refer to Fig.

A-GBCAD Sheet 03, Fig. A-GBCAD Sheet 04 and Fig. A-GBDAD Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Angle D5357113326890 Item 70

1 Angle D5357113327090 Item 64

NOTE: Item 70 and Item 64 are temporally held in place.

Then between STGR7 and STGR9 install:

1 Web D5357113325890 Item 68

with:

8 Pin DAN5-6-4X Item 102

8 Collar DAN11-6X Item 103

and install:

1 Clip D5357113326290 Item 72

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

4 Pin DAN5-8-5X Item 114

4 Collar DAN11-8X Item 115

4 Pin DAN5-5-5 Item 111

4 Collar NSA5075-5 Item 160

and install:

1 Clip D5357113326490 Item 66

with:

1 Pin DAN5-6-5X Item 104

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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1 Collar DAN11-6X Item 103

5 Pin DAN5-8-5X Item 114

5 Collar DAN11-8X Item 115

4 Pin DAN5-5-5 Item 111

4 Collar NSA5075-5 Item 160

2 As shown in Section B-B, at STGR8, install:

2 Rivet EN6081D5-07 Item 135

3 As shown in Section B-B, at STGR9, install:

2 Rivet EN6081D5-07 Item 135

4 As shown in View K, install:

8 Pin DAN6-6-5X Item 121

17 Collar DAN11-6X Item 103

9 Pin DAN6-6-4X Item 120

14 Rivet EN6069D5-08 Item 137

2 Pin DAN6-6-5 Item 127

2 Collar NSA5075-6 Item 108

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 108, 111, 114, 115, 120, 121, 127 and

160.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 108, 111, 114, 115, 120, 121, 127, 135,

137 and 160.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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(e) Install the items between Stringer STGR9 and STGR12 on the LH Side, refer to

Fig. A-GBCAD Sheet 03, Fig. A-GBCAD Sheet 04 and Fig. A-GBDAD Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Web D5357113330690 Item 62

with:

3 Pin DAN5-6-4X Item 102

3 Collar DAN11-6X Item 103

and install:

1 Angle D5357113331290 Item 51

1 Filler D5357113335400 Item 53

1 Angle D5357113321490 Item 54

with:

24 Pin DAN5-6-6 Item 112

24 Collar NSA5075-6 Item 108

and install:

1 Web D5357113336090 Item 60

with:

6 Pin DAN5-8-6X Item 131

6 Collar DAN11-8X Item 115

8 Rivet EN6081D5-07 Item 135

5 Pin DAN5-6-6X Item 105

5 Collar DAN11-6X Item 103

and install:

1 Angle D5357113320890 Item 58

1 Angle D5357113321090 Item 56

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with:

4 Pin DAN5-6-7X Item 130

4 Collar DAN11-6X Item 103

2 As shown in Section B-B, at STGR10, install:

2 Rivet EN6081D5-07 Item 135

3 As shown in Section B-B, at STGR11, install:

2 Rivet EN6081D5-07 Item 135

4 As shown in View K, install:

18 Pin DAN6-6-4X Item 120

25 Collar DAN11-6X Item 103

16 Rivet EN6069D5-08 Item 137

3 Pin DAN6-6-5X Item 121

4 Pin DAN6-6-7X Item 125

5 As shown in View L, install:

1 Pin DAN7-6-11X Item 144

1 Collar DAN12-6X Item 145

2 Pin DAN5-6-10X Item 146

2 Pin DAN5-6-8X Item 148

4 Collar DAN11-6X Item 103

6 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 105, 108, 112, 115, 120, 121, 122, 125, 130

and 131.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 239

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7 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 105, 108, 112, 115, 120, 121, 122, 124, 125,

130, 131, 135 and 137.

(7) Subtask 531266-020-204-003 - Remove the Angles, Webs, Brackets and Clips at

Frame 74, between STGR12, RH and STGR3, RH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 74

from Stringer 12 RH to Stringer 3 RH

Manpower Resources

Manhours 11.00

Minimum number of person 1

Subtask elapsed time 11.00

Skills AIRFRAME

NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) Task 51-10-01-250-801

51-10-08

Fig. A-GBAAA

Location of Inspection Area for Clips at

FR72/FR74

Sheet 01

Fig. A-GBCAD

Removal/Installation of Angles, Webs,

Brackets and Clips at FR74

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the items between STGR12 and STGR9 RH, refer to Fig. A-GBCAD Sheet

01 and Fig. A-GBCAD Sheet 02.

1 As shown in Section A-A, remove:

2 Rivet Discard

from the angle at STGR11 (Section A-A) and

2 Rivet Discard

from the angle at STGR10 (Section A-A).

Remove:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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42 Pin-Rivet Discard

42 Collar Discard

8 Rivet Discard

from View B.

2 As shown in View E, remove:

25 Pin-Rivet Discard

25 Collar Discard

16 Rivet Discard

3 Remove:

1 Angle D5357113331300 Item (52) Discard

1 Filler D5357113335400 Item (53) Discard

1 Angle D5357113321500 Item (55) Discard

1 Angle D5357113321100 Item (57) Discard

1 Angle D5357113320900 Item (59) Discard

1 Web D5357113336100 Item (61) Discard

1 Web D5357113330700 Item (63) Discard

4 As shown in View F, remove:

5 Pin-Rivet Discard

5 Collar Discard

5 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

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(b) Remove the items between STGR9 and STGR7 RH, refer to Fig. A-GBCAD Sheet

01 and Fig. A-GBCAD Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STRG9 (Section A-A) and

2 Rivet Discard

from the angle at STRG8 (Section A-A).

Remove:

27 Pin-Rivet Discard

27 Collar Discard

from View B.

2 As shown in View E, remove:

19 Pin-Rivet Discard

19 Collar Discard

14 Rivet Discard

3 Remove:

1 Angle D5357113327100 Item (65) Discard

1 Clip D5357113326500 Item (67) Discard

1 Web D5357113325900 Item (69) Discard

1 Angle D5357113326900 Item (71) Discard

1 Clip D5357113326300 Item (73) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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- If no cracks are found, do the worksteps that follow.

(c) Remove the items between STGR7 and STGR5, refer to Fig. A-GBCAD Sheet 01.

1 Remove:

2 Rivet Discard

from the angle at STRG7 (Section A-A) and

2 Rivet Discard

from the angle at STRG6 (Section A-A).

Remove:

32 Pin-Rivet Discard

32 Collar Discard

from View B.

2 As shown in View C, remove:

30 Pin-Rivet Discard

30 Collar Discard

8 Rivet Discard

3 Remove:

1 Angle D5357113326700 Item (75) Discard

1 Clip D5357113326100 Item (77) Discard

1 Angle D5357113327300 Item (79) Discard

1 Angle D5357072423500 Item (81) Discard

1 Clip D5357072422100 Item (83) Discard

1 Web D5357113325700 Item (85) Discard

1 Angle D5357072423900 Item (87) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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c Findings:

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

- If no cracks are found, do the worksteps that follow.

(d) Remove the items between STGR5 and STGR3, refer to Fig. A-GBCAD Sheet 01.

1 Remove:

2 Rivet Discard

from the angle at STRG5 (Section A-A) and

2 Rivet Discard

from the angle at STRG4 (Section A-A).

Remove:

18 Pin-Rivet Discard

18 Collar Discard

from View B.

2 As shown in View C, remove:

17 Pin-Rivet Discard

17 Collar Discard

14 Rivet Discard

3 Remove:

1 Angle D5357072423300 Item (89) Discard

1 Angle D5357072423700 Item (91) Discard

1 Clip D5357072422300 Item (93) Discard

1 Angle D5357072423100 Item (95) Discard

1 Web D5357072422700 Item (97) Discard

1 Clip D5357072422500 Item (99) Discard

4 Inspection:

a Do a rotating probe testing of the fastener holes, refer to NTM Task

51-10-01-250-801.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

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

- If no cracks are found, do the worksteps that follow.

(8) Subtask 531266-420-204-003 - Install the Angles, Webs, Brackets and Clips at

Frame 74, between STGR3, RH and STGR12, RH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 74

from Stringer 3 RH to Stringer 12 RH

Manpower Resources

Manhours 12.00

Minimum number of person 1

Subtask elapsed time 12.00

Skills AIRFRAME

Material necessary to do the job

Kit 531266D14R00

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

52 D5357113331390 1 ANGLE

53 D5357113335400 1 FILLER

55 D5357113321590 1 ANGLE

57 D5357113321190 1 ANGLE

59 D5357113320990 1 ANGLE

61 D5357113336190 1 WEB

63 D5357113330790 1 WEB

65 D5357113327190 1 ANGLE

67 D5357113326590 1 CLIP

69 D5357113325990 1 WEB

71 D5357113326990 1 ANGLE

73 D5357113326390 1 CLIP

75 D5357113326790 1 ANGLE

77 D5357113326190 1 CLIP

79 D5357113327390 1 ANGLE

81 D5357072423590 1 ANGLE

83 D5357072422190 1 CLIP

85 D5357113325790 1 WEB

87 D5357072423990 1 ANGLE

89 D5357072423390 1 ANGLE

91 D5357072423790 1 ANGLE

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

93 D5357072422390 1 CLIP

95 D5357072423190 1 ANGLE

97 D5357072422790 1 WEB

99 D5357072422590 1 CLIP

102 DAN5-6-4X 21 PIN

103 DAN11-6X 101 COLLAR

104 DAN5-6-5X 4 PIN

105 DAN5-6-6X 5 PIN

108 NSA5075-6 52 COLLAR

109 DAN5-5-6 17 PIN

111 DAN5-5-5 8 PIN

112 DAN5-6-6 24 PIN

114 DAN5-8-5X 25 PIN

115 DAN11-8X 36 COLLAR

116 DAN5-8-4X 2 PIN

120 DAN6-6-4X 27 PIN

121 DAN6-6-5X 15 PIN

125 DAN6-6-7X 13 PIN

126 DAN6-6-6 6 PIN

127 DAN6-6-5 3 PIN

130 DAN5-6-7X 4 PIN

131 DAN5-8-6X 9 PIN

132 DAN6-6-6X 8 PIN

134 DAN6-6-7 19 PIN

135 EN6081D5-07 20 RIVET

137 EN6069D5-08 52 RIVET

144 DAN7-6-11X 1 PIN

145 DAN12-6X 1 COLLAR

146 DAN5-6-10X 2 PIN

148 DAN5-6-8X 2 PIN

160 NSA5075-5 25 COLLAR

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant, Brush Consistency 09-013 As required

Corrosion Preventative

Compound, Temporary

15-009 As required

Anti-Corrosion Primer

Polyurethane

16-001 As required

Polyurethane Finish Paint 16-018 As required

References

Consumable Material List (CML)

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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References

Fig. A-GBCAD

Removal/Installation of Angles, Webs,

Brackets and Clips at FR74

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-GBDAD

Fastener Symbol Identification

Sheet 01

(a) Install the items between STGR3 and STGR5 on the RH Side, refer to Fig. AGBCAD Sheet 03,Fig. A-GBCAD Sheet 04 and Fig. A-GBDAD Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Angle D5357072423190 Item 95

1 Angle D5357072423390 Item 89

1 Clip D5357072422590 Item 99

1 Web D5357072422790 Item 97

with:

3 Pin DAN5-8-6X Item 131

5 Collar DAN11-8X Item 115

2 Pin DAN5-5-6 Item 109

2 Collar NSA5075-5 Item 160

2 Pin DAN5-8-4X Item 116

and install:

1 Clip D5357072422390 Item 93

with:

6 Pin DAN5-8-5X Item 114

6 Collar DAN11-8X Item 115

and install:

1 Angle D5357072423790 Item 91

with:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 160

2 As shown in Section B-B, at STGR4, install:

2 Rivet EN6081D5-07 Item 135

3 As shown in Section B-B, at STGR5, install:

2 Rivet EN6081D5-07 Item 135

4 As shown in View H, install:

8 Pin DAN6-6-6X Item 132

17 Collar DAN11-6X Item 103

9 Pin DAN6-6-7X Item 125

14 Rivet EN6069D5-08 Item 137

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 103, 109, 114, 115, 116, 122, 124, 131, 132 and 160.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 103, 109, 114, 115, 116, 122, 124, 131, 132 and 160.

(b) Install the items between STGR5 and STGR7 on the RH Side, refer to Fig. AGBCAD Sheet 03,Fig. A-GBCAD Sheet 04 and Fig. A-GBDAD Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Angle D5357072423590 Item 81

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 248

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1 Angle D5357113326790 Item 75

NOTE: Item 81 and Item 75 are temporally held in place.

Then between STGR5 and STGR7 install:

1 Web D5357113325790 Item 85

with:

10 Pin DAN5-6-4X Item 102

10 Collar DAN11-6X Item 103

and between Stringer STGR5 and STGR6 install:

1 Clip D5357072422190 Item 83

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

5 Pin DAN5-8-5X Item 114

5 Collar DAN11-8X Item 115

and between Stringer STGR5 and STGR6 install:

1 Angle D5357072423990 Item 87

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 160

and between Stringer STGR6 and STGR7 install:

1 Clip D5357113326190 Item 77

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

5 Pin DAN5-8-5X Item 114

5 Collar DAN11-8X Item 115

and between Stringer STGR6 and STGR7 install:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 249

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1 Angle D5357113327390 Item 79

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 160

2 As shown in Section B-B, at STGR6, install:

2 Rivet EN6081D5-07 Item 135

3 As shown in Section B-B, at STGR7, install:

2 Rivet EN6081D5-07 Item 135

4 As shown in View H, install between STGR5 and STGR7

19 Pin DAN6-6-7 Item 134

26 Collar NSA5075-6 Item 108

6 Pin DAN6-6-6 Item 126

8 Rivet EN6069D5-08 Item 137

4 Pin DAN6-6-5X Item 121

4 Collar DAN11-6X Item 103

1 Pin DAN6-6-5 Item 127

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 108, 109, 114, 115, 122, 134, 126, 127

and 160.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 108, 109, 114, 115, 134, 126, 127 and

160.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 250

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(c) Install the items between Stringer STGR7 and STGR9 on the RH Side, refer to Fig.

A-GBCAD Sheet 03, Fig. A-GBCAD Sheet 04 and Fig. A-GBDAD Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Angle D5357113326990 Item 71

1 Angle D5357113327190 Item 65

NOTE: Item 71 and Item 64 are temporally held in place.

Then between STGR7 and STGR9 install:

1 Web D5357113325990 Item 69

with:

8 Pin DAN5-6-4X Item 102

8 Collar DAN11-6X Item 103

and install:

1 Clip D5357113326390 Item 73

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

4 Pin DAN5-8-5X Item 114

4 Collar DAN11-8X Item 115

4 Pin DAN5-5-5 Item 111

4 Collar NSA5075-5 Item 160

and install:

1 Clip D5357113326590 Item 67

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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5 Pin DAN5-8-5X Item 114

5 Collar DAN11-8X Item 115

4 Pin DAN5-5-5 Item 111

4 Collar NSA5075-5 Item 160

2 As shown in Section B-B, at STGR8, install:

1 Rivet EN6081D5-07 Item 135

3 As shown in Section B-B, at STGR9, install:

1 Rivet EN6081D5-07 Item 135

4 As shown in View K, install:

8 Pin DAN6-6-5X Item 121

17 Collar DAN11-6X Item 103

9 Pin DAN6-6-4X Item 120

2 Collar NSA5075-6 Item 108

14 Rivet EN6069D5-08 Item 137

2 Pin DAN6-6-5 Item 127

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 108, 111, 114, 115, 120, 121, 127 and

160.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 108, 111, 114, 115, 120, 121, 122, 127,

135, 137 and 160.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 252

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SERVICE BULLETIN

(d) Install the items between STGR9 and STGR12 on the RH Side, refer to Fig. AGBCAD Sheet 03, Fig. A-GBCAD Sheet 04 and Fig. A-GBDAD Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Web D5357113330790 Item 63

with:

3 Pin DAN5-6-4X Item 102

3 Collar DAN11-6X Item 103

and install:

1 Angle D5357113331390 Item 52

1 Filler D5357113335400 Item 53

1 Angle D5357113321590 Item 55

with:

24 Pin DAN5-6-6 Item 112

24 Collar NSA5075-6 Item 108

and install:

1 Web D5357113336190 Item 61

with:

6 Pin DAN5-8-6X Item 131

6 Collar DAN11-8X Item 115

8 Rivet EN6081D5-07 Item 135

5 Pin DAN5-6-6X Item 105

5 Collar DAN11-6X Item 103

and install:

1 Angle D5357113320990 Item 59

1 Angle D5357113321190 Item 57

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 253

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SERVICE BULLETIN

with:

4 Pin DAN5-6-7X Item 130

4 Collar DAN11-6X Item 103

2 As shown in Section B-B, at STGR10, install:

1 Rivet EN6081D5-07 Item 135

3 As shown in Section B-B, at STGR11, install:

1 Rivet EN6081D5-07 Item 135

4 As shown in View K, install:

18 Pin DAN6-6-4X Item 120

25 Collar DAN11-6X Item 103

16 Rivet EN6069D5-08 Item 137

3 Pin DAN6-6-5X Item 121

4 Pin DAN6-6-7X Item 125

5 As shown in View L, install:

1 Pin DAN7-6-11X Item 144

1 Collar DAN12-6X Item 145

2 Pin DAN5-6-10X Item 146

2 Pin DAN5-6-8X Item 148

4 Collar DAN11-6X Item 103

6 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 105, 108, 112, 115, 120, 121, 124, 130 and

131.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 254

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SERVICE BULLETIN

7 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 105, 108, 112, 115, 120, 121, 122, 125, 130,

131 and 135.

**CONF 004

(1) Subtask 531266-020-201-004 - Remove the Angles, Webs, Brackets and Clips at

Frame 72, between STGR13, LH and STGR1, RH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 72

from Stringer 13 LH to Stringer 1 RH

Manpower Resources

Manhours 13.00

Minimum number of person 1

Subtask elapsed time 13.00

Skills AIRFRAME

NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) Task 51-10-01-250-801

51-10-08

Fig. A-GBAAA

Location of Inspection Area for Clips at

FR72/FR74

Sheet 01

Fig. A-GBBAE

Removal/Installation of Angles, Webs,

Brackets and Clips at FR72

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the items between STGR13 and STGR11 LH, refer to Fig. A-GBBAE

Sheet 01 and Fig. A-GBBAE Sheet 02.

1 As shown in View B, remove:

26 Pin-Rivet Discard

26 Collar Discard

6 Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 255

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2 As shown in Section B-B, remove:

2 Pin-Rivet Discard

2 Collar Discard

3 As shown in View D, remove:

16 Pin-Rivet Discard

16 Collar Discard

4 Remove:

1 Angle D5357113140000 Item (1) Discard

1 Web D5357113146800 Item (3) Discard

1 Web D5357113143800 Item (5) Discard

1 Bracket-Z D9357073720000 Item (133) Retain

5 Inspection:

a Do a rotating probe test of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

- If cracks are found, contact AIRBUS and apply the repair

instructions.

- If no cracks are found, do the worksteps that follow.

(b) Remove the items between STGR11 and STGR9 LH, refer to Fig. A-GBBAE Sheet

01 and Fig. A-GBBAE Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR11 (Section A-A) and

2 Rivet Discard

from the angle at STGR10 (Section A-A).

2 Remove:

23 Pin-Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 256

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23 Collar Discard

11 Rivet Discard

from View B.

3 As shown in View F, remove:

19 Pin-Rivet Discard

19 Collar Discard

16 Rivet Discard

4 Remove:

1 Clip D5357113144000 Item (7) Discard

1 Clip D5357113146600 Item (9) Discard

1 Web D5357113143600 Item (11) Discard

1 Bracket-Z D9357073720000 Item (133) Retain

5 Inspection:

a Do a rotating probe test of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

- If cracks are found, contact AIRBUS and apply the repair

instructions.

- If no cracks are found, do the worksteps that follow.

(c) Remove the items between STGR9 and STGR7 LH, refer to Fig. A-GBBAE Sheet

01 and Fig. A-GBBAE Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR9 (Section A-A) and

2 Rivet Discard

from the angle at STGR8 (Section A-A).

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 257

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SERVICE BULLETIN

2 Remove:

31 Pin-Rivet Discard

31 Collar Discard

from View B.

3 As shown in View F, remove:

21 Pin-Rivet Discard

21 Collar Discard

14 Rivet Discard

4 Remove:

1 Angle D5357113145600 Item (13) Discard

1 Clip D5357113145000 Item (15) Discard

1 Angle D5357113145400 Item (17) Discard

1 Clip D5357113144800 Item (19) Discard

1 Web D5357113144600 Item (21) Discard

5 Inspection:

a Do a rotating probe test of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

- If cracks are found, contact AIRBUS and apply the repair

instructions.

- If no cracks are found, do the worksteps that follow.

(d) Remove the items between STGR7 and STGR5 LH, refer to Fig. A-GBBAE Sheet

01 and Fig. A-GBBAE Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR7 (Section A-A) and

2 Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 258

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SERVICE BULLETIN

from the angle at STGR6 (Section A-A).

2 Remove:

33 Pin-Rivet Discard

33 Collar Discard

2 Rivet Discard

from View B.

3 As shown in View F, remove:

28 Pin-Rivet Discard

28 Collar Discard

10 Rivet Discard

4 Remove:

1 Angle D5357113145200 Item (23) Discard

1 Angle D5357113145800 Item (25) Discard

1 Clip D5357113144400 Item (27) Discard

1 Angle D5357072225600 Item (29) Discard

1 Clip D5357072224400 Item (31) Discard

1 Angle D5357072226000 Item (33) Discard

1 Web D5357113144200 Item (35) Discard

1 Bracket-Z D9357073720000 Item (133) Retain

5 Inspection:

a Do a rotating probe test of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

- If cracks are found, contact AIRBUS and apply the repair

instructions.

- If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 259

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SERVICE BULLETIN

(e) Remove the items between STGR5 and STGR3 LH, refer to Fig. A-GBBAE Sheet

01 and Fig. A-GBBAE Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR5 (Section A-A) and

2 Rivet Discard

from the angle at STGR4 (Section A-A).

2 Remove:

20 Pin-Rivet Discard

20 Collar Discard

from View B.

3 As shown in View F, remove:

19 Pin-Rivet Discard

19 Collar Discard

14 Rivet Discard

4 Remove:

1 Angle D5357072225400 Item (36) Discard

1 Angle D5357072225800 Item (38) Discard

1 Clip D5357072224600 Item (40) Discard

1 Angle D5357072225200 Item (42) Discard

1 Web D5357072224800 Item (44) Discard

1 Clip D5357072225000 Item (46) Discard

5 Inspection:

a Do a rotating probe test of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 260

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c Findings:

- If cracks are found, contact AIRBUS and apply the repair

instructions.

- If no cracks are found, do the worksteps that follow.

(f) Remove the items at STGR1 RH and LH, refer to Fig. A-GBBAE Sheet 01 and Fig.

A-GBBAE Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR1 (Section A-A).

2 Remove:

10 Pin-Rivet Discard

10 Nut Discard

3 As shown in View E, remove:

7 Pin-Rivet Discard

7 Collar Discard

8 Rivet Discard

4 Remove:

1 Clip D5357072224200 Item (48) Discard

1 Web D5357072224000 Item (49) Discard

5 Inspection:

a Do a rotating probe test of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

- If cracks are found, contact AIRBUS and apply the repair

instructions.

- If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 261

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SERVICE BULLETIN

(2) Subtask 531266-420-201-004 - Install the Angles, Webs, Brackets and Clips at

Frame 72, between STGR1, RH and STGR13, LH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 72

from Stringer 1 RH to Stringer 13 LH

Manpower Resources

Manhours 16.00

Minimum number of person 1

Subtask elapsed time 16.00

Skills AIRFRAME

Material necessary to do the job

Kit 531266D11R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

1 D5357113140090 1 ANGLE

3 D5357113146890 1 WEB

5 D5357113143890 1 WEB

7 D5357113144090 1 CLIP

9 D5357113146690 1 CLIP

11 D5357113143690 1 WEB

13 D5357113145690 1 ANGLE

15 D5357113145090 1 CLIP

17 D5357113145490 1 ANGLE

19 D5357113144890 1 CLIP

21 D5357113144690 1 WEB

23 D5357113145290 1 ANGLE

25 D5357113145890 1 ANGLE

27 D5357113144490 1 CLIP

29 D5357072225690 1 ANGLE

31 D5357072224490 1 CLIP

33 D5357072226090 1 ANGLE

35 D5357113144290 1 WEB

36 D5357072225490 1 ANGLE

38 D5357072225890 1 ANGLE

40 D5357072224690 1 CLIP

42 D5357072225290 1 ANGLE

44 D5357072224890 1 WEB

46 D5357072225090 1 CLIP

48 D5357072224290 1 CLIP

49 D5357072224090 1 WEB

102 DAN5-6-4X 31 PIN

103 DAN11-6X 145 COLLAR

104 DAN5-6-5X 40 PIN

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 262

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

105 DAN5-6-6X 2 PIN

106 EN6081D5-06 33 RIVET

107 DAN5-6-5 16 PIN

108 NSA5075-6 56 COLLAR

109 DAN5-5-6 18 PIN

110 NSA5075-5 27 COLLAR

111 DAN5-5-5 9 PIN

112 DAN5-6-6 2 PIN

113 DAN5-6-3X 3 PIN

114 DAN5-8-5X 10 PIN

115 DAN11-8X 29 COLLAR

116 DAN5-8-4X 2 PIN

117 DAN5-8-7X 8 PIN

118 DAN5-8-8X 2 PIN

119 DAN6-6-3X 8 PIN

120 DAN6-6-4X 29 PIN

121 DAN6-6-5X 13 PIN

122 EN6069D5-06 12 RIVET

123 DAN6-8-6X 7 PIN

124 DAN6-6-7X 10 PIN

125 DAN6-6-7 19 PIN

126 DAN6-6-6 4 PIN

127 DAN6-6-5 3 PIN

128 DAN6-6-3 8 PIN

129 DAN5-6-3 4 PIN

132 DAN6-6-6X 9 PIN

135 EN6081D5-08 2 RIVET

136 EN6069D5-07 33 RIVET

137 EN6069D5-08 17 RIVET

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant, Brush Consistency 09-013 As required

Corrosion Preventative

Compound, Temporary

15-009 As required

Anti-Corrosion Primer

Polyurethane

16-001 As required

Polyurethane Finish Paint 16-018 As required

References

Consumable Material List (CML)

Fig. A-GBBAE

Removal/Installation of Angles, Webs,

Brackets and Clips at FR72

Sheet 01

Sheet 02

Sheet 03

Sheet 04

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 263

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SERVICE BULLETIN

References

Fig. A-GBDAE

Fastener Symbol Identification

Sheet 01

(a) Install the items between STGR1 LH and RH, refer to Fig. A-GBBAE Sheet 01,

View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04 and Fig. A-GBDAE

Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Web D5357072224090 Item 49

with:

8 Pin DAN5-8-7X Item 117

8 Collar DAN11-8X Item 115

and then install:

1 Clip D5357072224290 Item 48

with:

2 PIN DAN5-8-8X Item 118

2 Collar DAN11-8X Item 115

2 As shown in Section E-E, install:

2 Pin DAN5-6-3 Item 129

2 Collar NSA5075-6 Item 108

3 As shown in View K, install:

7 Pin DAN6-8-6X Item 123

7 Collar DAN11-8X Item 115

5 Rivet EN6069D5-07 Item 136

3 Rivet EN6069D5-08 Item 137

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 264

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SERVICE BULLETIN

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 108, 115, 117, 118, 123 and 129.

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 108, 115, 117, 118, 123, 129, 136 and 137.

(b) Install the items between STGR3 and STGR4 on the LH side, refer to Fig. AGBBAE Sheet 01, View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04 and

Fig. A-GBDAE Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357072225290 Item 42

1 Clip D5357072225090 Item 46

with:

4 Pin DAN5-8-5X Item 114

4 Collar DAN11-8X Item 115

3 Pin DAN5-5-6 Item 109

3 Collar NSA5075-5 Item 110

2 As shown in Section C-C, at STGR4, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in View L, install between STGR3 and STGR4:

3 Pin DAN6-6-6X Item 132

4 Pin DAN6-6-7X Item 124

7 Collar DAN11-6X Item 103

7 Rivet EN6069D5-08 Item 137

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 265

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4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

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

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

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

(c) Install the items between STGR4 and STGR5 on the LH side, refer to Fig. AGBBAE Sheet 01, View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04 and

Fig. A-GBDAE Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357072225490 Item 36

1 Web D5357072224890 Item 44

with:

2 Pin DAN5-8-4X Item 116

2 Collar DAN11-8X Item 115

and then install:

1 Clip D5357072224690 Item 40

with:

6 Pin DAN5-8-5X Item 114

6 Collar DAN11-8X Item 115

and then install:

1 Angle D5357072225890 Item 38

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 266

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with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 110

2 As shown in Section C-C, at STGR5, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in View L, between STGR4 and STGR5, install:

6 Pin DAN6-6-6X Item 132

6 Pin DAN6-6-7X Item 124

12 Collar DAN11-6X Item 103

7 Rivet EN6069D5-08 Item 137

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

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

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

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

(d) Install the items between STGR5 and STGR7 on the LH side, refer to Fig. AGBBAE Sheet 01, View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04 and

Fig. A-GBDAE Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357072225690 Item 29

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 267

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SERVICE BULLETIN

1 Angle D5357113145290 Item 23

1 Bracket-Z D9357073720000 Item (133) Retained at

removal

1 Web D5357113144290 Item 35

with:

9 Pin DAN5-6-4X Item 102

9 Collar DAN11-6X Item 103

2 Rivet EN6081D5-08 Item 135

and then between STGR5 and STGR6, install:

1 Clip D5357072224490 Item 31

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

and then between STGR5 and STGR6, install:

1 Angle D5357072226090 Item 33

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 110

and then between STGR6 and STGR7, install:

1 Clip D5357113144490 Item 27

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

and then between STGR6 and STGR7, install:

1 Angle D5357113145890 Item 25

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 110

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 268

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2 As shown in Section C-C, at STGR6, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section C-C, at STGR7, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View L, between STGR5 and STGR7, install:

19 Pin DAN6-6-7 Item 125

4 Pin DAN6-6-6 Item 126

1 Pin DAN6-6-5 Item 127

24 Collar NSA5075-6 Item 108

4 Pin DAN6-6-5X Item 121

4 Collar DAN11-6X Item 103

9 Rivet EN6069D5-07 Item 136

1 Rivet EN6069D5-06 Item 122

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

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

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

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

127, 135 and 136.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 269

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SERVICE BULLETIN

(e) Install the items between STGR7 and STGR9 on the LH side, refer to Fig. AGBBAE Sheet 01, View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04 and

Fig. A-GBDAE Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357113145690 Item 13

1 Angle D5357113145490 Item 17

NOTE: Items 13 and 17 are temporarily held in place.

Then between STGR7 and STGR9, install:

1 Web D5357113144690 Item 21

with:

10 Pin DAN5-6-4X Item 102

10 Collar DAN11-6X Item 103

and then between STGR7 and STGR8, install:

1 Clip D5357113144890 Item 19

with:

5 Pin DAN5-6-5X Item 104

5 Collar DAN11-6X Item 103

4 Pin DAN5-5-5 Item 111

4 Collar NSA5075-5 Item 110

and then between STGR8 and STGR9, install:

1 Clip D5357113145090 Item 15

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

5 Pin DAN5-5-5 Item 111

5 Collar NSA5075-5 Item 110

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 270

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2 As shown in Section C-C, at STGR8, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section C-C, at STGR9, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View L, between STGR7 and STGR9, install:

10 Pin DAN6-6-4X Item 120

9 Pin DAN6-6-5X Item 121

19 Collar DAN11-6X Item 103

12 Rivet EN6069D5-07 Item 136

2 Rivet EN6069D5-06 Item 122

2 Pin DAN6-6-5 Item 127

2 Collar NSA5075-6 Item 108

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 108, 110, 111, 120, 121 and 127.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 110, 111, 120, 121, 122, 127

and 136.

(f) Install the items between STGR9 and STGR11 on the LH side, refer to Fig. AGBBAE Sheet 01, View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04 and

Fig. A-GBDAE Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 271

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SERVICE BULLETIN

to wet install on Frame 72, as shown in View G:

1 Bracket-Z D9357073720000 Item (133) Retained at

removal

1 Web D5357113143690 Item 11

with:

2 Rivet EN6081D5-06 Item 106

9 Pin DAN5-6-4X Item 102

9 Collar DAN11-6X Item 103

and then between STGR9 and STGR10, install:

1 Clip D5357113146690 Item 9

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

5 Rivet EN6081D5-06 Item 106

and then between STGR10 and STGR11, install:

1 Clip D5357113144090 Item 7

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

4 Rivet EN6081D5-06 Item 106

2 As shown in Section C-C, at STGR10, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section C-C, at STGR11, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View L, between STGR9 and STGR11, install:

19 Pin DAN6-6-4X Item 120

19 Collar DAN11-6X Item 103

7 Rivet EN6069D5-07 Item 136

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 272

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9 Rivet EN6069D5-06 Item 122

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104 and 120.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 106, 120, 122 and 136.

(g) Install the items between STGR11 and STGR13 on the LH side, refer to Fig. AGBBAE Sheet 01, View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04 and

Fig. A-GBDAE Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Bracket-Z D9357073720000 Item (133) Retained at

removal

1 Web D5357113143890 Item 5

with:

2 Rivet EN6081D5-06 Item 106

3 Pin DAN5-6-3X Item 113

3 Collar DAN11-6X Item 103

and then between STGR11 and STGR12, install:

1 Web D5357113146890 Item 3

with:

3 Pin DAN5-6-4X Item 102

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 273

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SERVICE BULLETIN

3 Collar DAN11-6X Item 103

4 Rivet EN6081D5-06 Item 106

and then install:

1 Angle D5357113140090 Item 1

with:

16 Pin DAN5-6-5 Item 107

2 Pin DAN5-6-6 Item 112

18 Collar NSA5075-6 Item 108

2 Pin DAN5-6-6X Item 105

2 Collar DAN11-6X Item 103

2 As shown in Section D-D, at STGR12, install:

2 Pin DAN5-6-3 Item 129

2 Collar NSA5075-6 Item 108

3 As shown in View J, install:

8 Pin DAN6-6-3X Item 119

8 Collar DAN11-6X Item 103

8 Pin DAN6-6-3 Item 128

8 Collar NSA5075-6 Item 108

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 105, 107, 108, 112, 113, 119, 128 and 129.

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 274

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SERVICE BULLETIN

to the fasteners, Items 102, 103, 105, 106, 107, 108, 112, 113, 119, 128 and

129.

(3) Subtask 531266-020-208-004 - Remove the Angles, Webs, Brackets and Clips at

Frame 72, between STGR13, RH and STGR3, RH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 72

from Stringer 13 LH to Stringer 1 RH

Manpower Resources

Manhours 11.00

Minimum number of person 1

Subtask elapsed time 11.00

Skills AIRFRAME

NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) Task 51-10-01-250-801

51-10-08

Fig. A-GBAAA

Location of Inspection Area for Clips at

FR72/FR74

Sheet 01

Fig. A-GBBAE

Removal/Installation of Angles, Webs,

Brackets and Clips at FR72

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the items between STGR13 and STGR11 RH, refer to Fig. A-GBBAE

Sheet 01 and Fig. A-GBBAE Sheet 02.

1 As shown in View B, remove:

26 Pin-Rivet Discard

26 Collar Discard

6 Rivet Discard

2 As shown in Section B-B, remove:

2 Pin-Rivet Discard

2 Collar Discard

3 As shown in View D, remove:

16 Pin-Rivet Discard

16 Collar Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 275

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SERVICE BULLETIN

4 Remove:

1 Angle D5357113140100 Item (2) Discard

1 Web D5357113146900 Item (4) Discard

1 Web D5357113143900 Item (6) Discard

1 Bracket-Z D9357073720000 Item (133) Retain

5 Inspection:

a Do a rotating probe test of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

- If cracks are found, contact AIRBUS and apply the repair

instructions.

- If no cracks are found, do the worksteps that follow.

(b) Remove the items between STGR11 and STGR9 RH, refer to Fig. A-GBBAE Sheet

01 and Fig. A-GBBAE Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR11 (Section A-A) and

2 Rivet Discard

from the angle at STGR10 (Section A-A).

2 Remove:

23 Pin-Rivet Discard

23 Collar Discard

11 Rivet Discard

from View B.

3 As shown in View F, remove:

19 Pin-Rivet Discard

19 Collar Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 276

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16 Rivet Discard

4 Remove:

1 Clip D5357113144100 Item (8) Discard

1 Clip D5357113146700 Item (10) Discard

1 Web D5357113143700 Item (12) Discard

1 Bracket-Z D9357073720000 Item (133) Retain

5 Inspection:

a Do a rotating probe test of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection of the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

- If cracks are found, contact AIRBUS and apply the repair

instructions.

- If no cracks are found, do the worksteps that follow.

(c) Remove the items between STGR9 and STGR7 RH, refer to Fig. A-GBBAE Sheet

01 and Fig. A-GBBAE Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR9 (Section A-A) and

2 Rivet Discard

from the angle at STGR8 (Section A-A).

2 Remove:

31 Pin-Rivet Discard

31 Collar Discard

from View B.

3 As shown in View F, remove:

21 Pin-Rivet Discard

21 Collar Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 277

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SERVICE BULLETIN

14 Rivet Discard

4 Remove:

1 Angle D5357113145700 Item (14) Discard

1 Clip D5357113145100 Item (16) Discard

1 Angle D5357113145500 Item (18) Discard

1 Clip D5357113144900 Item (20) Discard

1 Web D5357113144700 Item (22) Discard

5 Inspection:

a Do a rotating probe test of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

- If cracks are found, contact AIRBUS and apply the repair

instructions.

- If no cracks are found, do the worksteps that follow.

(d) Remove the items between STGR7 and STGR5 RH, refer to Fig. A-GBBAE Sheet

01 and Fig. A-GBBAE Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR7 (Section A-A) and

2 Rivet Discard

from the angle at STGR6 (Section A-A).

2 Remove:

33 Pin-Rivet Discard

33 Collar Discard

2 Rivet Discard

from View B.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 278

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SERVICE BULLETIN

3 As shown in View F, remove:

28 Pin-Rivet Discard

28 Collar Discard

10 Rivet Discard

4 As shown in View C, remove:

1 Angle D5357113145300 Item (24) Discard

1 Angle D5357113145900 Item (26) Discard

1 Clip D5357113144500 Item (28) Discard

1 Angle D5357072225700 Item (30) Discard

1 Clip D5357072224500 Item (32) Discard

1 Angle D5357072226100 Item (34) Discard

1 Web D5357116122000 Item (50) Discard

1 Bracket-Z D9357073720000 Item (133) Retain

5 Inspection:

a Do a rotating probe test of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection of the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

- If cracks are found, contact AIRBUS and apply the repair

instructions.

- If no cracks are found, do the worksteps that follow.

(e) Remove the items between STGR5 and STGR3 RH, refer to Fig. A-GBBAE Sheet

01 and Fig. A-GBBAE Sheet 02.

1 Remove:

2 Rivet Discard

from the angle at STGR5 (Section A-A) and

2 Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 279

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SERVICE BULLETIN

from the angle at STGR4 (Section A-A).

2 Remove:

20 Pin-Rivet Discard

20 Collar Discard

from View B.

3 As shown in View F, remove:

19 Pin-Rivet Discard

19 Collar Discard

14 Rivet Discard

4 Remove:

1 Angle D5357072225500 Item (37) Discard

1 Angle D5357072225900 Item (39) Discard

1 Clip D5357072224700 Item (41) Discard

1 Angle D5357072225300 Item (43) Discard

1 Web D5357072224900 Item (45) Discard

1 Clip D5357072225100 Item (47) Discard

5 Inspection:

a Do a rotating probe test of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

- If cracks are found, contact AIRBUS and apply the repair

instructions.

- If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 280

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SERVICE BULLETIN

(4) Subtask 531266-420-202-004 - Install the Angles, Webs, Brackets and Clips at

Frame 72, between STGR3, RH to STGR13, RH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 72

from Stringer 3 RH to Stringer 13 RH

Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills AIRFRAME

Material necessary to do the job

Kit 531266D11R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

2 D5357113140190 1 ANGLE

4 D5357113146990 1 WEB

6 D5357113143990 1 WEB

8 D5357113144190 1 CLIP

10 D5357113146790 1 CLIP

12 D5357113143790 1 WEB

14 D5357113145790 1 ANGLE

16 D5357113145190 1 CLIP

18 D5357113145590 1 ANGLE

20 D5357113144990 1 CLIP

22 D5357113144790 1 WEB

24 D5357113145390 1 ANGLE

26 D5357113145990 1 ANGLE

28 D5357113144590 1 CLIP

30 D5357072225790 1 ANGLE

32 D5357072224590 1 CLIP

34 D5357072226190 1 ANGLE

37 D5357072225590 1 ANGLE

39 D5357072225990 1 ANGLE

41 D5357072224790 1 CLIP

43 D5357072225390 1 ANGLE

45 D5357072224990 1 WEB

47 D5357072225190 1 CLIP

50 D5357116122090 1 WEB

102 DAN5-6-4X 31 PIN

103 DAN11-6X 145 COLLAR

104 DAN5-6-5X 40 PIN

105 DAN5-6-6X 2 PIN

106 EN6081D5-06 33 RIVET

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 281

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

107 DAN5-6-5 16 PIN

108 NSA5075-6 54 COLLAR

109 DAN5-5-6 18 PIN

110 NSA5075-5 27 COLLAR

111 DAN5-5-5 9 PIN

112 DAN5-6-6 2 PIN

113 DAN5-6-3X 3 PIN

114 DAN5-8-5X 10 PIN

115 DAN11-8X 12 COLLAR

116 DAN5-8-4X 2 PIN

119 DAN6-6-3X 8 PIN

120 DAN6-6-4X 29 PIN

121 DAN6-6-5X 13 PIN

122 EN6069D5-06 12 RIVET

124 DAN6-6-7X 10 PIN

125 DAN6-6-7 19 PIN

126 DAN6-6-6 4 PIN

127 DAN6-6-5 3 PIN

128 DAN6-6-3 8 PIN

129 DAN5-6-3 2 PIN

132 DAN6-6-6X 9 PIN

135 EN6081D5-08 2 RIVET

136 EN6069D5-07 28 RIVET

137 EN6069D5-08 14 RIVET

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant, Brush Consistency 09-013 As required

Corrosion Preventative

Compound, Temporary

15-009 As required

Anti-Corrosion Primer

Polyurethane

16-001 As required

Polyurethane Finish Paint 16-018 As required

References

Consumable Material List (CML)

Fig. A-GBBAE

Removal/Installation of Angles, Webs,

Brackets and Clips at FR72

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-GBDAE

Fastener Symbol Identification

Sheet 01

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 282

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SERVICE BULLETIN

(a) Install the items between STGR3 and STGR4 on the RH side, refer to Fig. AGBBAE Sheet 01, View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04 and

Fig. A-GBDAE Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357072225390 Item 43

1 Clip D5357072225190 Item 47

with:

4 Pin DAN5-8-5X Item 114

4 Collar DAN11-8X Item 115

3 Pin DAN5-5-6 Item 109

3 Collar NSA5075-5 Item 110

2 As shown in Section C-C, at STGR4, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in View L, between STGR3 and STGR4, install:

4 Pin DAN6-6-7X Item 124

3 Pin DAN6-6-6X Item 132

7 Collar DAN11-6X Item 103

7 Rivet EN6069D5-08 Item 137

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

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

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 283

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5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

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

(b) Install the items between STGR4 and STGR5 on the RH side, refer to Fig. AGBBAE Sheet 01, View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04and

Fig. A-GBDAE Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357072225590 Item 37

1 Web D5357072224990 Item 45

with:

2 Pin DAN5-8-4X Item 116

2 Collar DAN11-8X Item 115

and then install:

1 Clip D5357072224790 Item 41

with:

6 Pin DAN5-8-5X Item 114

6 Collar DAN11-8X Item 115

and then install:

1 Angle D5357072225990 Item 39

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 110

2 As shown in Section C-C, at STGR5, install:

2 Rivet EN6081D5-06 Item 106

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 284

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3 As shown in View L, between STGR4 and STGR5, install:

6 Pin DAN6-6-7X Item 124

6 Pin DAN6-6-6X Item 132

12 Collar DAN11-6X Item 103

7 Rivet EN6069D5-08 Item 137

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

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

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

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

(c) Install the items between STGR5 and STGR7 on the RH side, refer to Fig. AGBBAE Sheet 01, View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04 and

Fig. A-GBDAE Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357113145390 Item 24

1 Angle D5357072225790 Item 30

1 Bracket-Z D9357073720000 Item (133) Retained at

removal

1 Web D5357116122090 Item 50

with:

9 Pin DAN5-6-4X Item 102

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 285

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9 Collar DAN11-6X Item 103

2 Rivet EN6081D5-08 Item 135

and between STGR5 and STGR6, as shown in View H, install:

1 Clip D5357072224590 Item 32

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

and between STGR5 and STGR6, install:

1 Angle D5357072226190 Item 34

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 110

and between STGR6 and STGR7, install:

1 Clip D5357113144590 Item 28

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

and between STGR6 and STGR7, install:

1 Angle D5357113145990 Item 26

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 110

2 As shown in Section C-C, at STGR6, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section C-C, at STGR7, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View L, between STGR5 and STGR7, install:

19 Pin DAN6-6-7 Item 125

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 286

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4 Pin DAN6-6-6 Item 126

1 Pin DAN6-6-5 Item 127

24 Collar NSA5075-6 Item 108

4 Pin DAN6-6-5X Item 121

4 Collar DAN11-6X Item 103

9 Rivet EN6069D5-07 Item 136

1 Rivet EN6069D5-06 Item 122

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

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

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

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

127, 135 and 136.

(d) Install the items between STGR7 and STGR9 on the RH side, refer to Fig. AGBBAE Sheet 01, View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04 and

Fig. A-GBDAE Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Angle D5357113145790 Item 14

1 Angle D5357113145590 Item 18

NOTE: Items 14 and 18 are temporarily held in place.

Then between STGR7 and STGR9, install:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 287

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SERVICE BULLETIN

1 Web D5357113144790 Item 22

with:

10 Pin DAN5-6-4X Item 102

10 Collar DAN11-6X Item 103

and then between STGR7 and STGR8, install:

1 Clip D5357113144990 Item 20

with:

5 Pin DAN5-6-5X Item 104

5 Collar DAN11-6X Item 103

4 Pin DAN5-5-5 Item 111

4 Collar NSA5075-5 Item 110

and then between STGR8 and STGR9, install:

1 Clip D5357113145190 Item 16

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

5 Pin DAN5-5-5 Item 111

5 Collar NSA5075-5 Item 110

2 As shown in Section C-C, at STGR8, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section C-C, at STGR9, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View L, between STGR7 and STGR9, install:

10 Pin DAN6-6-4X Item 120

9 Pin DAN6-6-5X Item 121

19 Collar DAN11-6X Item 103

2 Pin DAN6-6-5 Item 127

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 288

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SERVICE BULLETIN

2 Collar NSA5075-6 Item 108

12 Rivet EN6069D5-07 Item 136

2 Rivet EN6069D5-06 Item 122

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 108, 110, 111, 120, 121 and 127.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 110, 111, 120, 121, 122, 127

and 136.

(e) Install the items between STGR9 and STGR11 on the RH side, refer to Fig. AGBBAE Sheet 01, View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04 and

Fig. A-GBDAE Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Bracket-Z D9357073720000 Item (133) Retained at

removal

1 Web D5357113143790 Item 12

with:

2 Rivet EN6081D5-06 Item 106

9 Pin DAN5-6-4X Item 102

9 Collar DAN11-6X Item 103

and then between STGR9 and STGR10, install:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 289

6

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SERVICE BULLETIN

1 Clip D5357113146790 Item 10

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

5 Rivet EN6081D5-06 Item 106

and then between STGR10 and STGR11, install:

1 Clip D5357113144190 Item 8

with:

7 Pin DAN5-6-5X Item 104

7 Collar DAN11-6X Item 103

4 Rivet EN6081D5-06 Item 106

2 As shown in Section C-C, at STGR10, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section C-C, at STGR11, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View L, between STGR9 and STGR11, install:

19 Pin DAN6-6-4X Item 120

19 Collar DAN11-6X Item 103

7 Rivet EN6069D5-07 Item 136

9 Rivet EN6069D5-06 Item 122

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104 and 120.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 290

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SERVICE BULLETIN

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 106, 120, 122 and 136.

(f) Install the items between STGR11 and STGR13 on the RH side, refer to Fig. AGBBAE Sheet 01, View A, Fig. A-GBBAE Sheet 03, Fig. A-GBBAE Sheet 04 and

Fig. A-GBDAE Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 72, as shown in View G:

1 Bracket-Z D9357073720000 Item (133) Retained at

removal

1 Web D5357113143990 Item 6

with

2 Rivet EN6081D5-06 Item 106

3 Pin DAN5-6-3X Item 113

3 Collar DAN11-6X Item 103

and then install:

1 Web D5357113146990 Item 4

with:

3 Pin DAN5-6-4X Item 102

3 Collar DAN11-6X Item 103

4 Rivet EN6081D5-06 Item 106

and then install:

1 Angle D5357113140190 Item 2

with:

2 Pin DAN5-6-6X Item 105

2 Collar DAN11-6X Item 103

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 291

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SERVICE BULLETIN

16 Pin DAN5-6-5 Item 107

2 Pin DAN5-6-6 Item 112

18 Collar NSA5075-6 Item 108

2 As shown in Section D-D, at STGR12, install:

2 Pin DAN5-6-3 Item 129

2 Collar NSA5075-6 Item 108

3 As show in View J, install:

8 Pin DAN6-6-3X Item 119

8 Collar DAN11-6X Item 103

8 Pin DAN6-6-3 Item 128

8 Collar NSA5075-6 Item 108

4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 105, 107, 108, 112, 113, 119, 128 and 129.

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 105, 106, 107, 108, 112, 113, 119, 128 and

129.

(5) Subtask 531266-020-203-004 - Remove the Angles, Webs, Brackets and Clips at

Frame 74, between STGR12, LH and STGR1, RH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 74

from Stringer 12 LH to Stringer 1 RH

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 292

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SERVICE BULLETIN

Manpower Resources

Manhours 11.00

Minimum number of person 1

Subtask elapsed time 11.00

Skills AIRFRAME

NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) Task 51-10-01-250-801

51-10-08

Fig. A-GBAAA

Location of Inspection Area for Clips at

FR72/FR74

Sheet 01

Fig. A-GBCAE

Removal/Installation of Angles, Webs,

Brackets and Clips at FR74

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the items between STGR12 and STGR9 LH, refer to Fig. A-GBCAE Sheet

01 and Fig. A-GBCAE Sheet 02.

1 As shown in Section A-A, remove:

2 Rivet Discard

from the angle at STGR11 and

2 Rivet Discard

from the angle at STGR10.

2 Remove:

42 Pin-Rivet Discard

42 Collar Discard

8 Rivet Discard

from View B.

3 As shown in View E, remove:

25 Pin-Rivet Discard

25 Collar Discard

16 Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 293

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4 Remove:

1 Angle D5357113339600 Item (51) Discard

1 Filler D5357113339800 Item (53) Discard

1 Angle D5357113321400 Item (54) Discard

1 Angle D5357113337200 Item (56) Discard

1 Angle D5357113337000 Item (58) Discard

1 Web D5357113340000 Item (60) Discard

1 Web D5357113339400 Item (62) Discard

5 As shown in View F, remove:

5 Pin-Rivet Discard

5 Collar Discard

6 Inspection:

a Do a rotating probe test of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

- If cracks are found, contact AIRBUS and apply the repair

instructions.

- If no cracks are found, do the worksteps that follow.

(b) Remove the items between STGR9 and STGR7 LH, refer to Fig. A-GBCAE Sheet

01 and Fig. A-GBCAE Sheet 02.

1 As shown in Section A-A, remove:

2 Rivet Discard

from the angle at STGR9 and

2 Rivet Discard

from the angle at STGR8.

2 Remove:

27 Pin-Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 294

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27 Collar Discard

from View B.

3 As shown in View E, remove:

19 Pin-Rivet Discard

19 Collar Discard

14 Rivet Discard

4 Remove:

1 Angle D5357113339000 Item (64) Discard

1 Clip D5357113338400 Item (66) Discard

1 Web D5357113337800 Item (68) Discard

1 Angle D5357113338800 Item (70) Discard

1 Clip D5357113338200 Item (72) Discard

5 Inspection:

a Do a rotating probe test of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

- If cracks are found, contact AIRBUS and apply the repair

instructions.

- If no cracks are found, do the worksteps that follow.

(c) Remove the items between STGR7 and STGR5 LH, refer to Fig. A-GBCAE Sheet

01 and Fig. A-GBCAE Sheet 02.

1 As shown in Section A-A, remove:

2 Rivet Discard

from the angle at STGR7 and

2 Rivet Discard

from the angle at STGR6.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 295

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2 Remove:

32 Pin-Rivet Discard

32 Collar Discard

from View B.

3 As shown in View C, remove:

30 Pin-Rivet Discard

30 Collar Discard

8 Rivet Discard

4 Remove:

1 Angle D5357113338600 Item (74) Discard

1 Clip D5357113338000 Item (76) Discard

1 Angle D5357113339200 Item (78) Discard

1 Angle D5357072425400 Item (80) Discard

1 Clip D5357072424200 Item (82) Discard

1 Web D5357113337600 Item (84) Discard

1 Angle D5357072425800 Item (86) Discard

5 Inspection:

a Do a rotating probe test of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

- If cracks are found, contact AIRBUS and apply the repair

instructions.

- If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 296

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(d) Remove the items between STGR5 and STGR3 LH, refer to Fig. A-GBCAE Sheet

01 and Fig. A-GBCAE Sheet 02.

1 As shown in Section A-A, remove:

2 Rivet Discard

from the angle at STGR5 and

2 Rivet Discard

from the angle at STGR4.

2 Remove:

18 Pin-Rivet Discard

18 Collar Discard

from View B.

3 As shown in View C, remove:

17 Pin-Rivet Discard

17 Collar Discard

14 Rivet Discard

4 Remove:

1 Angle D5357072425200 Item (88) Discard

1 Angle D5357072425600 Item (90) Discard

1 Clip D5357072424400 Item (92) Discard

1 Angle D5357072425000 Item (94) Discard

1 Web D5357072424800 Item (96) Discard

1 Clip D5357072424600 Item (98) Discard

5 Inspection:

a Do a rotating probe test of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 297

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c Findings:

- If cracks are found, contact AIRBUS and apply the repair

instructions.

- If no cracks are found, do the worksteps that follow.

(e) Remove the items between STGR2 LH and STGR1 RH, refer to Fig. A-GBCAE

Sheet 01 and Fig. A-GBCAE Sheet 02.

1 As shown in Section A-A, remove:

2 Rivet Discard

from the angle at STGR1.

2 Remove:

12 Pin-Rivet Discard

12 Collar Discard

from View B.

3 As shown in View D, remove:

8 Pin-Rivet Discard

8 Collar Discard

8 Rivet Discard

4 Remove:

1 Clip D5357072224200 Item (48) Discard

1 Web D5357072424000 Item (100) Discard

5 Inspection:

a Do a rotating probe test of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

- If cracks are found, contact AIRBUS and apply the repair

instructions.

- If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 298

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SERVICE BULLETIN

(6) Subtask 531266-420-203-004 - Install the Angles, Webs, Brackets and Clips at

Frame 74, between STGR1, RH and STGR12, LH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 74

from Stringer 1 RH to Stringer 12 LH

Manpower Resources

Manhours 14.00

Minimum number of person 1

Subtask elapsed time 14.00

Skills AIRFRAME

Material necessary to do the job

Kit 531266D11R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

48 D5357072224290 1 CLIP

51 D5357113339690 1 ANGLE

53 D5357113339800 1 FILLER

54 D5357113321490 1 ANGLE

56 D5357113337290 1 ANGLE

58 D5357113337090 1 ANGLE

60 D5357113340090 1 WEB

62 D5357113339490 1 WEB

64 D5357113339090 1 ANGLE

66 D5357113338490 1 CLIP

68 D5357113337890 1 WEB

70 D5357113338890 1 ANGLE

72 D5357113338290 1 CLIP

74 D5357113338690 1 ANGLE

76 D5357113338090 1 CLIP

78 D5357113339290 1 ANGLE

80 D5357072425490 1 ANGLE

82 D5357072424290 1 CLIP

84 D5357113337690 1 WEB

86 D5357072425890 1 ANGLE

88 D5357072425290 1 ANGLE

90 D5357072425690 1 ANGLE

92 D5357072424490 1 CLIP

94 D5357072425090 1 ANGLE

96 D5357072424890 1 WEB

98 D5357072424690 1 CLIP

100 D5357072424090 1 WEB

102 DAN5-6-4X 21 PIN

103 DAN11-6X 101 COLLAR

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 299

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ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

104 DAN5-6-5X 4 PIN

105 DAN5-6-6X 5 PIN

106 EN6081D5-06 26 RIVET

108 NSA5075-6 52 COLLAR

109 DAN5-5-6 17 PIN

110 NSA5075-5 25 COLLAR

111 DAN5-5-5 8 PIN

112 DAN5-6-6 24 PIN

114 DAN5-8-5X 25 PIN

115 DAN11-8X 56 COLLAR

116 DAN5-8-4X 2 PIN

117 DAN5-8-7X 10 PIN

118 DAN5-8-8X 2 PIN

120 DAN6-6-4X 27 PIN

121 DAN6-6-5X 15 PIN

122 EN6069D5-06 3 RIVET

123 DAN6-8-6X 8 PIN

124 DAN6-6-7X 13 PIN

125 DAN6-6-7 19 PIN

126 DAN6-6-6 6 PIN

127 DAN6-6-5 3 PIN

130 DAN5-6-7X 4 PIN

131 DAN5-8-6X 9 PIN

132 DAN6-6-6X 8 PIN

136 EN6069D5-07 38 RIVET

137 EN6069D5-08 19 RIVET

144 DAN7-6-11X 1 PIN

145 DAN12-6X 1 COLLAR

146 DAN5-6-10X 2 PIN

148 DAN5-6-8X 2 PIN

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant, Brush Consistency 09-013 As required

Corrosion Preventative

Compound, Temporary

15-009 As required

Anti-Corrosion Primer

Polyurethane

16-001 As required

Polyurethane Finish Paint 16-018 As required

References

Consumable Material List (CML)

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 300

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References

Fig. A-GBCAE

Removal/Installation of Angles, Webs,

Brackets and Clips at FR74

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-GBDAE

Fastener Symbol Identification

Sheet 01

(a) Install the items between STGR2 on the RH side and STGR2 on the LH side, refer

to Fig. A-GBCAE Sheet 01, View A, Fig. A-GBCAE Sheet 03, Fig. A-GBCAE Sheet

04 and Fig. A-GBDAE Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Web D5357072424090 Item 100

with:

10 Pin DAN5-8-7X Item 117

10 Collar DAN11-8X Item 115

and then install:

1 Clip D5357072224290 Item 48

with:

2 PIN DAN5-8-8X Item 118

2 Collar DAN11-8X Item 115

2 As shown in Section B-B, at STGR1, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in View J, install:

8 Pin DAN6-8-6X Item 123

8 Collar DAN11-8X Item 115

3 Rivet EN6069D5-07 Item 136

5 Rivet EN6069D5-08 Item 137

XXXX

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 301

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4 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 115, 117, 118 and 123.

5 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 106, 115, 117, 118, 123, 136 and 137.

(b) Install the items between STGR3 and STGR5 on the LH side, refer to Fig. AGBCAE Sheet 01, View A, Fig. A-GBCAE Sheet 03, Fig. A-GBCAE Sheet 04 and

Fig. A-GBDAE Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Angle D5357072425090 Item 94

1 Angle D5357072425290 Item 88

1 Clip D5357072424690 Item 98

1 Web D5357072424890 Item 96

with:

2 Pin DAN5-5-6 Item 109

2 Collar NSA5075-5 Item 110

3 Pin DAN5-8-6X Item 131

2 Pin DAN5-8-4X Item 116

5 Collar DAN11-8X Item 115

and then install:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 302

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SERVICE BULLETIN

1 Clip D5357072424490 Item 92

with:

6 Pin DAN5-8-5X Item 114

6 Collar DAN11-8X Item 115

and then install:

1 Angle D5357072425690 Item 90

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 110

2 As shown in Section B-B, at STGR4, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section B-B, at STGR5, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View H, install:

9 Pin DAN6-6-7X Item 124

8 Pin DAN6-6-6X Item 132

17 Collar DAN11-6X Item 103

14 Rivet EN6069D5-08 Item 137

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 103, 109, 110, 114, 115, 116, 124, 131 and 132.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 303

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to the fasteners, Items 103, 106, 109, 110, 114, 115, 116, 124, 131, 132 and

137.

(c) Install the items between STGR5 and STGR7 on the LH side, refer to Fig. AGBCAE Sheet 01, View A, Fig. A-GBCAE Sheet 03, Fig. A-GBCAE Sheet 04 and

Fig. A-GBDAE Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Angle D5357072425490 Item 80

1 Angle D5357113338690 Item 74

NOTE: Items 74 and 80 are temporarily held in place.

Then between STGR5 and STGR7, install:

1 Web D5357113337690 Item 84

with:

10 Pin DAN5-6-4X Item 102

10 Collar DAN11-6X Item 103

and then between STGR5 and STGR6, install:

1 Clip D5357072424290 Item 82

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

5 Pin DAN5-8-5X Item 114

5 Collar DAN11-8X Item 115

and then between STGR5 and STGR6, install:

1 Angle D5357072425890 Item 86

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 110

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 304

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and then between STGR6 and STGR7, install:

1 Clip D5357113338090 Item 76

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

5 Pin DAN5-8-5X Item 114

5 Collar DAN11-8X Item 115

and then between STGR6 and STGR7, install:

1 Angle D5357113339290 Item 78

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 110

2 As shown in Section B-B, at STGR6, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section B-B, at STGR7, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View H, install:

19 Pin DAN6-6-7 Item 125

6 Pin DAN6-6-6 Item 126

1 Pin DAN6-6-5 Item 127

26 Collar NSA5075-6 Item 108

4 Pin DAN6-6-5X Item 121

4 Collar DAN11-6X Item 103

7 Rivet EN6069D5-07 Item 136

1 Rivet EN6069D5-06 Item 122

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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SERVICE BULLETIN

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 108, 109, 110, 114, 115, 121, 125, 126

and 127.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 109, 110, 114, 115, 121, 122,

125, 126, 127 and 136.

(d) Install the items between STGR7 and STGR9 on the LH side, refer to Fig. AGBCAE Sheet 01, View A, Fig. A-GBCAE Sheet 03, Fig. A-GBCAE Sheet 04 and

Fig. A-GBDAE Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Angle D5357113338890 Item 70

1 Angle D5357113339090 Item 64

NOTE: Items 64 and 70 are temporarily held in place.

Then between STGR7 and STGR9, install:

1 Web D5357113337890 Item 68

with:

8 Pin DAN5-6-4X Item 102

8 Collar DAN11-6X Item 103

and then between STGR7 and STGR8, install:

1 Clip D5357113338290 Item 72

with:

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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SERVICE BULLETIN

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

4 Pin DAN5-8-5X Item 114

4 Collar DAN11-8X Item 115

4 Pin DAN5-5-5 Item 111

4 Collar NSA5075-5 Item 110

and then between STGR8 and STGR9, install:

1 Clip D5357113338490 Item 66

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

5 Pin DAN5-8-5X Item 114

5 Collar DAN11-8X Item 115

4 Pin DAN5-5-5 Item 111

4 Collar NSA5075-5 Item 110

2 As shown in Section B-B, at STGR8, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section B-B, at STGR9, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View K, install:

9 Pin DAN6-6-4X Item 120

8 Pin DAN6-6-5X Item 121

17 Collar DAN11-6X Item 103

2 Pin DAN6-6-5 Item 127

2 Collar NSA5075-6 Item 108

2 Rivet EN6069D5-06 Item 122

12 Rivet EN6069D5-07 Item 136

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 307

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SERVICE BULLETIN

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 108, 110, 111, 114, 115, 120, 121 and

127.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 110, 111, 114, 115, 120, 121,

122, 127 and 136.

(e) Install the items between STGR9 and STGR12 on the LH side, refer to Fig. AGBCAE Sheet 01, View A, Fig. A-GBCAE Sheet 03, Fig. A-GBCAE Sheet 04 and

Fig. A-GBDAE Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Web D5357113339490 Item 62

with:

3 Pin DAN5-6-4X Item 102

3 Collar DAN11-6X Item 103

and then install:

1 Angle D5357113339690 Item 51

1 Filler D5357113339800 Item 53

1 Angle D5357113321490 Item 54

with:

24 Pin DAN5-6-6 Item 112

24 Collar NSA5075-6 Item 108

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 308

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SERVICE BULLETIN

and then install:

1 Web D5357113340090 Item 60

with:

5 Pin DAN5-6-6X Item 105

5 Collar DAN11-6X Item 103

6 Pin DAN5-8-6X Item 131

6 Collar DAN11-8X Item 115

8 Rivet EN6081D5-06 Item 106

and then install:

1 Angle D5357113337290 Item 56

1 Angle D5357113337090 Item 58

with:

4 Pin DAN5-6-7X Item 130

4 Collar DAN11-6X Item 103

2 As shown in Section B-B, at STGR10, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section B-B, at STGR11, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View K, install:

18 Pin DAN6-6-4X Item 120

18 Collar DAN11-6X Item 103

3 Pin DAN6-6-5X Item 121

3 Collar DAN11-6X Item 103

4 Pin DAN6-6-7X Item 124

4 Collar DAN11-6X Item 103

16 Rivet EN6069D5-07 Item 136

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 309

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SERVICE BULLETIN

5 As shown in View L, install:

1 Pin DAN7-6-11X Item 144

1 Collar DAN12-6X Item 145

2 Pin DAN5-6-10X Item 146

2 Collar DAN11-6X Item 103

2 Pin DAN5-6-8X Item 148

2 Collar DAN11-6X Item 103

6 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 105, 108, 112, 115, 120, 121, 124, 130, 131,

144, 145, 146 and 148.

7 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 105, 106, 108, 112, 115, 120, 121, 124, 130,

131, 136, 144, 145, 146 and 148.

(7) Subtask 531266-020-204-004 - Remove the Angles, Webs, Brackets and Clips at

Frame 74, between STGR12, RH and STGR3, RH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 74

from Stringer 3RH to Stringer 12RH

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 310

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SERVICE BULLETIN

Manpower Resources

Manhours 11.00

Minimum number of person 1

Subtask elapsed time 11.00

Skills AIRFRAME

NON DESTRUCTIVE

TESTING

References

Non Destructive Test Manual (NTM) Task 51-10-01-250-801

51-10-08

Fig. A-GBAAA

Location of Inspection Area for Clips at

FR72/FR74

Sheet 01

Fig. A-GBCAE

Removal/Installation of Angles, Webs,

Brackets and Clips at FR74

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the items between STGR12 and STGR9 RH, refer to Fig. A-GBCAE Sheet

01 and Fig. A-GBCAE Sheet 02.

1 As shown in Section A-A, remove:

2 Rivet Discard

from the angle at STGR11 and

2 Rivet Discard

from the angle at STGR10.

2 Remove:

42 Pin-Rivet Discard

42 Collar Discard

8 Rivet Discard

from View B.

3 As shown in View E, remove:

25 Pin-Rivet Discard

25 Collar Discard

16 Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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SERVICE BULLETIN

4 Remove:

1 Angle D5357113339700 Item (52) Discard

1 Filler D5357113339800 Item (53) Discard

1 Angle D5357113321500 Item (55) Discard

1 Angle D5357113337300 Item (57) Discard

1 Angle D5357113337100 Item (59) Discard

1 Web D5357113340100 Item (61) Discard

1 Web D5357113339500 Item (63) Discard

5 As shown in View F, remove:

5 Pin-Rivet Discard

5 Collar Discard

6 Inspection:

a Do a rotating probe test of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

- If cracks are found, contact AIRBUS and apply the repair

instructions.

- If no cracks are found, do the worksteps that follow.

(b) Remove the items between STGR9 and STGR7 RH, refer to Fig. A-GBCAE Sheet

01 and Fig. A-GBCAE Sheet 02.

1 As shown in Section A-A, remove:

2 Rivet Discard

from the angle at STGR9 and

2 Rivet Discard

from the angle at STGR8.

2 Remove:

27 Pin-Rivet Discard

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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SERVICE BULLETIN

27 Collar Discard

from View B.

3 As shown in View E, remove:

19 Pin-Rivet Discard

19 Collar Discard

14 Rivet Discard

4 Remove:

1 Angle D5357113339100 Item (65) Discard

1 Clip D5357113338500 Item (67) Discard

1 Web D5357113337900 Item (69) Discard

1 Angle D5357113338900 Item (71) Discard

1 Clip D5357113338300 Item (73) Discard

5 Inspection:

a Do a rotating probe test of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

- If cracks are found, contact AIRBUS and apply the repair

instructions.

- If no cracks are found, do the worksteps that follow.

(c) Remove the items between STGR7 and STGR5 RH, refer to Fig. A-GBCAE Sheet

01 and Fig. A-GBCAE Sheet 02.

1 As shown in Section A-A, remove:

2 Rivet Discard

from the angle at STGR7 and

2 Rivet Discard

from the angle at STGR6.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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SERVICE BULLETIN

2 Remove:

32 Pin-Rivet Discard

32 Collar Discard

from View B.

3 As shown in View C, remove:

30 Pin-Rivet Discard

30 Collar Discard

8 Rivet Discard

4 Remove:

1 Angle D5357113338700 Item (75) Discard

1 Clip D5357113338100 Item (77) Discard

1 Angle D5357113339300 Item (79) Discard

1 Angle D5357072425500 Item (81) Discard

1 Clip D5357072424300 Item (83) Discard

1 Web D5357113337700 Item (85) Discard

1 Angle D5357072425900 Item (87) Discard

5 Inspection:

a Do a rotating probe test of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Fequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

c Findings:

- If cracks are found, contact AIRBUS and apply the repair

instructions.

- If no cracks are found, do the worksteps that follow.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 314

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SERVICE BULLETIN

(d) Remove the items between STGR5 and STGR3 RH, refer to Fig. A-GBCAE Sheet

01 and Fig. A-GBCAE Sheet 02.

1 As shown in Section A-A, remove:

2 Rivet Discard

from the angle at STGR5 and

2 Rivet Discard

from the angle at STGR4.

2 Remove:

18 Pin-Rivet Discard

18 Collar Discard

from View B.

3 As shown in View C, remove:

17 Pin-Rivet Discard

17 Collar Discard

14 Rivet Discard

4 Remove:

1 Angle D5357072425300 Item (89) Discard

1 Angle D5357072425700 Item (91) Discard

1 Clip D5357072424500 Item (93) Discard

1 Angle D5357072425100 Item (95) Discard

1 Web D5357072424900 Item (97) Discard

1 Clip D5357072424700 Item (99) Discard

5 Inspection:

a Do a rotating probe test of the fastener holes, refer to NTM Task

51-10-01-250-801.

b Do a High Frequency Eddy Current (HFEC) crack inspection on the

stringers, refer to NTM 51-10-08 and Fig. A-GBAAA Sheet 01.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 315

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c Findings:

- If cracks are found, contact AIRBUS and apply the repair

instructions.

- If no cracks are found, do the worksteps that follow.

(8) Subtask 531266-420-204-004 - Install the Angles, Webs, Brackets and Clips at

Frame 74, between STGR3, RH and STGR12, RH

Work Zones and Access Panels

Zone Access/Work location

310 Work location Frame 74

from Stringer 3 RH to Stringer 12 RH

Manpower Resources

Manhours 12.00

Minimum number of person 1

Subtask elapsed time 12.00

Skills AIRFRAME

Material necessary to do the job

Kit 531266D11R02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

52 D5357113339790 1 ANGLE

53 D5357113339800 1 FILLER

55 D5357113321590 1 ANGLE

57 D5357113337390 1 ANGLE

59 D5357113337190 1 ANGLE

61 D5357113340190 1 WEB

63 D5357113339590 1 WEB

65 D5357113339190 1 ANGLE

67 D5357113338590 1 CLIP

69 D5357113337990 1 WEB

71 D5357113338990 1 ANGLE

73 D5357113338390 1 CLIP

75 D5357113338790 1 ANGLE

77 D5357113338190 1 CLIP

79 D5357113339390 1 ANGLE

81 D5357072425590 1 ANGLE

83 D5357072424390 1 CLIP

85 D5357113337790 1 WEB

87 D5357072425990 1 ANGLE

89 D5357072425390 1 ANGLE

91 D5357072425790 1 ANGLE

93 D5357072424590 1 CLIP

95 D5357072425190 1 ANGLE

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

97 D5357072424990 1 WEB

99 D5357072424790 1 CLIP

102 DAN5-6-4X 21 PIN

103 DAN11-6X 101 COLLAR

104 DAN5-6-5X 4 PIN

105 DAN5-6-6X 5 PIN

106 EN6081D5-06 24 RIVET

108 NSA5075-6 52 COLLAR

109 DAN5-5-6 17 PIN

110 NSA5075-5 25 COLLAR

111 DAN5-5-5 8 PIN

112 DAN5-6-6 24 PIN

114 DAN5-8-5X 25 PIN

115 DAN11-8X 36 COLLAR

116 DAN5-8-4X 2 PIN

120 DAN6-6-4X 27 PIN

121 DAN6-6-5X 15 PIN

122 EN6069D5-06 3 RIVET

124 DAN6-6-7X 13 PIN

125 DAN6-6-7 19 PIN

126 DAN6-6-6 6 PIN

127 DAN6-6-5 3 PIN

130 DAN5-6-7X 4 PIN

131 DAN5-8-6X 9 PIN

132 DAN6-6-6X 8 PIN

136 EN6069D5-07 35 RIVET

137 EN6069D5-08 14 RIVET

144 DAN7-6-11X 1 PIN

145 DAN12-6X 1 COLLAR

146 DAN5-6-10X 2 PIN

148 DAN5-6-8X 2 PIN

Consumable CMLD01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Sealant, Brush Consistency 09-013 As required

Corrosion Preventative

Compound, Temporary

15-009 As required

Anti-Corrosion Primer

Polyurethane

16-001 As required

Polyurethane Finish Paint 16-018 As required

References

Consumable Material List (CML)

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 317

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References

Fig. A-GBCAE

Removal/Installation of Angles, Webs,

Brackets and Clips at FR74

Sheet 01

Sheet 02

Sheet 03

Sheet 04

Fig. A-GBDAE

Fastener Symbol Identification

Sheet 01

(a) Install the items between STGR3 and STGR5 on the RH side, refer to Fig. AGBCAE Sheet 01, View A, Fig. A-GBCAE Sheet 03, Fig. A-GBCAE Sheet 04 and

Fig. A-GBDAE Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Angle D5357072425190 Item 95

1 Angle D5357072425390 Item 89

1 Clip D5357072424790 Item 99

1 Web D5357072424990 Item 97

with:

2 Pin DAN5-5-6 Item 109

2 Collar NSA5075-5 Item 110

3 Pin DAN5-8-6X Item 131

2 Pin DAN5-8-4X Item 116

5 Collar DAN11-8X Item 115

and then install:

1 Clip D5357072424590 Item 93

with:

6 Pin DAN5-8-5X Item 114

6 Collar DAN11-8X Item 115

and then install:

1 Angle D5357072425790 Item 91

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 318

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SERVICE BULLETIN

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 110

2 As shown in Section B-B, at STGR4, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section B-B, at STGR5, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View H, install:

9 Pin DAN6-6-7X Item 124

8 Pin DAN6-6-6X Item 132

17 Collar DAN11-6X Item 103

14 Rivet EN6069D5-08 Item 137

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 103, 109, 110, 114, 115, 116, 124, 131 and 132.

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 103, 106, 109, 110, 114, 115, 116, 124, 131, 132 and

137.

(b) Install the items between STGR5 and STGR7 on the RH side, refer to Fig. AGBCAE Sheet 01, View A, Fig. A-GBCAE Sheet 03, Fig. A-GBCAE Sheet 04 and

Fig. A-GBDAE Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 319

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SERVICE BULLETIN

to wet install on Frame 74, as shown in View G:

1 Angle D5357113338790 Item 75

1 Angle D5357072425590 Item 81

NOTE: Items 75 and 81 are temporarily held in place.

Then between STGR5 and STGR7, install:

1 Web D5357113337790 Item 85

with:

10 Pin DAN5-6-4X Item 102

10 Collar DAN11-6X Item 103

and between STGR5 and STGR6, install:

1 Clip D5357072424390 Item 83

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

5 Pin DAN5-8-5X Item 114

5 Collar DAN11-8X Item 115

and between STGR5 and STGR6, install:

1 Angle D5357072425990 Item 87

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 110

and between STGR6 and STGR7, install:

1 Clip D5357113338190 Item 77

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

5 Pin DAN5-8-5X Item 114

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 320

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5 Collar DAN11-8X Item 115

and between STGR6 and STGR7, install:

1 Angle D5357113339390 Item 79

with:

5 Pin DAN5-5-6 Item 109

5 Collar NSA5075-5 Item 110

2 As shown in Section B-B, at STGR6, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section B-B, at STGR7, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View H, install:

19 Pin DAN6-6-7 Item 125

6 Pin DAN6-6-6 Item 126

1 Pin DAN6-6-5 Item 127

26 Collar NSA5075-6 Item 108

4 Pin DAN6-6-5X Item 121

4 Collar DAN11-6X Item 103

7 Rivet EN6069D5-07 Item 136

1 Rivet EN6069D5-06 Item 122

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 108, 109, 110, 114, 115, 121, 125, 126

and 127.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 321

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SERVICE BULLETIN

6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 109, 110, 114, 115, 121, 122,

125, 126, 127 and 136.

(c) Install the items between STGR7 and STGR9 on the RH side, refer to Fig. AGBCAE Sheet 01, View A, Fig. A-GBCAE Sheet 03, Fig. A-GBCAE Sheet 04 and

Fig. A-GBDAE Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74 as shown in View G:

1 Angle D5357113338990 Item 71

1 Angle D5357113339190 Item 65

NOTE: Items 65 and 71 are temporarily held in place.

Then between STGR7 and STGR9, install:

1 Web D5357113337990 Item 69

with:

8 Pin DAN5-6-4X Item 102

8 Collar DAN11-6X Item 103

and then install:

1 Clip D5357113338390 Item 73

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

4 Pin DAN5-8-5X Item 114

4 Collar DAN11-8X Item 115

4 Pin DAN5-5-5 Item 111

4 Collar NSA5075-5 Item 110

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 322

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and then install:

1 Clip D5357113338590 Item 67

with:

1 Pin DAN5-6-5X Item 104

1 Collar DAN11-6X Item 103

5 Pin DAN5-8-5X Item 114

5 Collar DAN11-8X Item 115

4 Pin DAN5-5-5 Item 111

4 Collar NSA5075-5 Item 110

2 As shown in Section B-B, at STGR8, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section B-B, at STGR9, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View K, install:

9 Pin DAN6-6-4X Item 120

8 Pin DAN6-6-5X Item 121

17 Collar DAN11-6X Item 103

2 Pin DAN6-6-5 Item 127

2 Collar NSA5075-6 Item 108

2 Rivet EN6069D5-06 Item 122

12 Rivet EN6069D5-07 Item 136

5 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 104, 108, 110, 111, 114, 115, 120, 121 and

127.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 323

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6 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 104, 106, 108, 110, 111, 114, 115, 120, 121,

122, 127 and 136.

(d) Install the items between STGR9 and STGR12 on the RH side, refer to Fig. AGBCAE Sheet 01, View A, Fig. A-GBCAE Sheet 03, Fig. A-GBCAE Sheet 04 and

Fig. A-GBDAE Sheet 01.

1 Use

Sealant, Brush

Consistency

09-013 As required

to wet install on Frame 74, as shown in View G:

1 Web D5357113339590 Item 63

with:

3 Pin DAN5-6-4X Item 102

3 Collar DAN11-6X Item 103

and then install:

1 Angle D5357113339790 Item 52

1 Filler D5357113339800 Item 53

1 Angle D5357113321590 Item 55

with:

24 Pin DAN5-6-6 Item 112

24 Collar NSA5075-6 Item 108

and then install:

1 Web D5357113340190 Item 61

with:

5 Pin DAN5-6-6X Item 105

5 Collar DAN11-6X Item 103

6 Pin DAN5-8-6X Item 131

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 324

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6 Collar DAN11-8X Item 115

8 Rivet EN6081D5-06 Item 106

and then install:

1 Angle D5357113337390 Item 57

1 Angle D5357113337190 Item 59

with:

4 Pin DAN5-6-7X Item 130

4 Collar DAN11-6X Item 103

2 As shown in Section B-B, at STGR10, install:

2 Rivet EN6081D5-06 Item 106

3 As shown in Section B-B, at STGR11, install:

2 Rivet EN6081D5-06 Item 106

4 As shown in View K, install:

18 Pin DAN6-6-4X Item 120

3 Pin DAN6-6-5X Item 121

4 Pin DAN6-6-7X Item 124

25 Collar DAN11-6X Item 103

16 Rivet EN6069D5-07 Item 136

5 As shown in View L, install:

1 Pin DAN7-6-11X Item 144

1 Collar DAN12-6X Item 145

2 Pin DAN5-6-10X Item 146

2 Pin DAN5-6-8X Item 148

4 Collar DAN11-6X Item 103

6 Apply:

Anti-Corrosion

Primer

Polyurethane

16-001 As required

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 325

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Polyurethane Finish

Paint

16-018 As required

to the fasteners, Items 102, 103, 105, 108, 112, 115, 120, 121, 124, 130, 131,

144, 145, 146 and 148.

7 Apply:

Corrosion

Preventative

Compound,

Temporary

15-009 As required

to the fasteners, Items 102, 103, 105, 106, 108, 112, 115, 120, 121, 124, 130,

131, 136, 144, 145, 146 and 148.

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 531266-700-201-001 - Test

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-12-00-790-001

Task 36-12-41-400-001

(a) Preparation:

1 Install the APU bleed air duct between frame 71 and frame 77, refer to AMM

Task 36-12-41-400-001.

(b) Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit

breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

49VU AIR BLEED/X

FEED/VALVE/BAT

2HV D13

49VU AIR BLEED/ENG 1/CTL 3HA1 D12

49VU AIR BLEED/ENG 1/MONG 2HA1 D11

122VU AIR BLEED/ENG 2/CTL 3HA2 Z23

122VU AIR BLEED/ENG 2/MONG 2HA2 Z22

122VU AIR BLEED/X FEED

VALVE/NORM

1HV Z20

(c) Do the leak test of the APU bleed air supply system, refer to AMM Task

36-12-00-790-001.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 326

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**CONF 002

(1) Subtask 531266-700-201-001 - Test

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-12-00-790-001

Task 36-12-41-400-001

(a) Preparation:

1 Install the APU bleed air duct between frame 71 and frame 77, refer to AMM

Task 36-12-41-400-001.

(b) Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit

breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

49VU AIR BLEED/X

FEED/VALVE/BAT

2HV D13

49VU AIR BLEED/ENG 1/CTL 3HA1 D12

49VU AIR BLEED/ENG 1/MONG 2HA1 D11

122VU AIR BLEED/ENG 2/CTL 3HA2 Z23

122VU AIR BLEED/ENG 2/MONG 2HA2 Z22

122VU AIR BLEED/X FEED

VALVE/NORM

1HV Z20

(c) Do the leak test of the APU bleed air supply system, refer to AMM Task

36-12-00-790-001.

**CONF 003

(1) Subtask 531266-700-201-001 - Test

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-12-00-790-001

Task 36-12-41-400-001

(a) Preparation:

1 Install the APU bleed air duct between frame 71 and frame 77, refer to AMM

Task 36-12-41-400-001.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 327

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(b) Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit

breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

49VU AIR BLEED/X

FEED/VALVE/BAT

2HV D13

49VU AIR BLEED/ENG 1/CTL 3HA1 D12

49VU AIR BLEED/ENG 1/MONG 2HA1 D11

122VU AIR BLEED/ENG 2/CTL 3HA2 Z23

122VU AIR BLEED/ENG 2/MONG 2HA2 Z22

122VU AIR BLEED/X FEED

VALVE/NORM

1HV Z20

(c) Do the leak test of the APU bleed air supply system, refer to AMM Task

36-12-00-790-001.

**CONF 004

(1) Subtask 531266-700-201-001 - Test

Manpower Resources

Skills AIRFRAME

References

Aircraft Maintenance Manual (AMM) Task 36-12-00-790-001

Task 36-12-41-400-001

(a) Preparation:

1 Install the APU bleed air duct between frame 71 and frame 77, refer to AMM

Task 36-12-41-400-001.

(b) Remove the safety clip(s) and/or tag(s) and close/unlock this (these) circuit

breaker(s):

PANEL DESIGNATION FIN LOCATION SEE

NOTES

49VU AIR BLEED/X

FEED/VALVE/BAT

2HV D13

49VU AIR BLEED/ENG 1/CTL 3HA1 D12

49VU AIR BLEED/ENG 1/MONG 2HA1 D11

122VU AIR BLEED/ENG 2/CTL 3HA2 Z23

122VU AIR BLEED/ENG 2/MONG 2HA2 Z22

122VU AIR BLEED/X FEED

VALVE/NORM

1HV Z20

(c) Do the leak test of the APU bleed air supply system, refer to AMM Task

36-12-00-790-001.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 328

6

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**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 531266-942-201-001 - Close-up

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 70 to Frame 77

from Stringer 1 to Stringer 13

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 29-11-00, Page Block 001

29-13-00, Page Block 001

Task 52-10-00-410-001

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

equipment.

(b) Put the affected hydraulic lines which were loosened for access back in position at

Frame 72.

(c) Install the loosened wire and wire clamps.

(d) Install the light 4LJ.

(e) Pressurize the green and yellow hydraulic systems, refer to AMM 29-11-00, Page

Block 001 and AMM 29-13-00, Page Block 001.

(f) Close the access doors 312AR and 314AR.

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

(h) Remove the access platform(s).

(i) Put the aircraft back to its initial configuration.

**CONF 002

(1) Subtask 531266-942-201-001 - Close-up

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 70 to Frame 77

from Stringer 1 to Stringer 13

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 329

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Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 29-11-00, Page Block 001

29-13-00, Page Block 001

Task 52-10-00-410-001

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

equipment.

(b) Put the affected hydraulic lines which were loosened for access back in position at

Frame 72.

(c) Install the loosened wire and wire clamps.

(d) Install the light 4LJ.

(e) Pressurize the green and yellow hydraulic systems, refer to AMM 29-11-00, Page

Block 001 and AMM 29-13-00, Page Block 001.

(f) Close the access doors 312AR and 314AR.

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

(h) Remove the access platform(s).

(i) Put the aircraft back to its initial configuration.

**CONF 003

(1) Subtask 531266-942-201-001 - Close-up

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 70 to Frame 77

from Stringer 1 to Stringer 13

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 29-11-00, Page Block 001

29-13-00, Page Block 001

Task 52-10-00-410-001

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

equipment.

(b) Put the affected hydraulic lines which were loosened for access back in position at

Frame 72.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 330

6

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(c) Install the loosened wire and wire clamps.

(d) Install the light 4LJ.

(e) Pressurize the green and yellow hydraulic systems, refer to AMM 29-11-00, Page

Block 001 and AMM 29-13-00, Page Block 001.

(f) Close the access doors 312AR and 314AR.

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

(h) Remove the access platform(s).

(i) Put the aircraft back to its initial configuration.

**CONF 004

(1) Subtask 531266-942-201-001 - Close-up

Work Zones and Access Panels

Zone Access/Work location

310 Work location from Frame 70 to Frame 77

from Stringer 1 to Stringer 13

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 29-11-00, Page Block 001

29-13-00, Page Block 001

Task 52-10-00-410-001

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

equipment.

(b) Put the affected hydraulic lines which were loosened for access back in position at

Frame 72.

(c) Install the loosened wire and wire clamps.

(d) Install the light 4LJ.

(e) Pressurize the green and yellow hydraulic systems, refer to AMM 29-11-00, Page

Block 001 and AMM 29-13-00, Page Block 001.

(f) Close the access doors 312AR and 314AR.

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

(h) Remove the access platform(s).

(i) Put the aircraft back to its initial configuration.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 331

6

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SERVICE BULLETIN

**CONF ALL

A

Z310

FR72

FR74

FR77

FR70

A

A

A

A

A

FWD

FR72

FR74

90.0 mm

(3.54 in)

90.0 mm

(3.54 in)

TYPICAL FOR

STGR11LH − STGR11RH

PERFORM CRACK DETECTION ON STRINGER USING

NOTE:

01

DYNAMIC EDDY CURRENT ACC. TO NTM 51−10−08.

02 SURFACE TO BE CHECKED.

B

A A

02

B

VIEW LOOKING FWD

N_SB_531266_6_BAAA_01_02

01

Figure A-GBAAA - Sheet 01

Location of Inspection Area for Clips at FR72/FR74

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 332

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**CONF 001

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

STGR13

AD

STGR12

STGR3

STGR2

FR72

BEFORE

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING FWD

STGR5RH

STGR6RH

STGR7RH

VIEW LOOKING FWD

(5)

(6)

LH

RH

(1)

(2)

LH

RH

(3)

(4)

LH

RH

(7)

(8)

LH

RH

(9)

(10)

LH

RH

(11)

(12)

LH

RH

(13)

(14)

LH

RH

(17)

(18)

LH

RH

(15)

(16)

LH

RH

(19)

(20)

LH

RH

(23)

(25)

(29)

(33)

(38)

(39)

LH

RH

(36)

(37)

LH

RH

(42)

(43)

LH

RH

RH SIDE ONLY

FR72

(24)

(26)

(30)

(34)

(50)

(28)

(32)

(48) (49)

(46)

(47)

LH

RH

(40)

(41)

LH

RH

(44)

(45)

LH

RH

LH ONLY

(35)

(27)

(31)

B

C

C

A

Z310

FR72

FR74

FR77

FR70

A

B

REMOVE AND DISCARD

EXSISTING FASTENERS

FASTENER TABLE

(133)

(133)

(133)

(133)

STGR12

FR72

B B

F

W

D

FR72

STGR

A A

B B

A

A

(21)

(22)

LH

RH

F

W

D

D

E

F

G

TYPICAL FOR

STGR1 (AD) AND

STGR4 − STGR11

N_SB_531266_6_BBAA_01_01

Figure A-GBBAA - Sheet 01

Removal/Installation of Angles, Webs, Brackets and Clips at FR72

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 333

6

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**CONF 001

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

FWD FR72

N_SB_531266_6_BBAA_02_00

FR72

STGR13

STGR12

STGR11

FWD

F

W

D

AD

FR72

D

E

F

REMOVE AND DISCARD

EXSISTING FASTENERS

FASTENER TABLE

Figure A-GBBAA - Sheet 02

Removal/Installation of Angles, Webs, Brackets and Clips at FR72

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 334

6

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**CONF 001

(133)

(133)

(133)

(133)

FR72

STGR13

STGR12

STGR11

FWD

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

STGR13

AD

STGR12

STGR3

STGR2

FR72

AFTER

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING FWD

STGR5RH

STGR6RH

STGR7RH

VIEW LOOKING FWD

5

6

LH

RH

1

2

LH

RH

3

4

LH

RH

7

8

LH

RH

9

10

LH

RH

11

12

LH

RH

13

14

LH

RH

17

18

LH

RH

15

16

LH

RH

19

20

LH

RH

21

22

LH

RH

23

25

29

33

38

39

LH

RH

36

37

LH

RH

40

41

LH

RH

44

45

LH

RH

46

47

LH

RH

42

43

LH

RH

RH SIDE ONLY

FR72

24

26

30

34

50

28

32

48

LH ONLY

27

35

31

STGR12

FR72

F

W

D

FR72

TYPICAL FOR

F

W

D

AD

FR72

G

H

J C C K D D

F

W

D

C

C

D D

H

J

K

L

STGR4 − STGR11

N_SB_531266_6_BBAA_03_02

E

E 49

FOR FASTENER SYMBOLS, REFER TO FIG. N_SB_531266_6_BDAA SHEET 1

NOTE:

STGR4 − STGR11

STGR1 (AD)

F

W

D

E E

FR72

Figure A-GBBAA - Sheet 03

Removal/Installation of Angles, Webs, Brackets and Clips at FR72

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 335

6

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**CONF 001

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

FWD L FR72

N_SB_531266_6_BBAA_04_01

FOR FASTENER SYMBOLS, REFER 

NOTE:

TO FIG. N_SB_531266_6_BDAA SHEET 1

Figure A-GBBAA - Sheet 04

Removal/Installation of Angles, Webs, Brackets and Clips at FR72

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 336

6

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**CONF 002

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

STGR13

AD

STGR12

STGR3

STGR2

FR72

BEFORE

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING FWD

STGR5RH

STGR6RH

STGR7RH

VIEW LOOKING FWD

(5)

(6)

LH

RH

(1)

(2)

LH

RH

(3)

(4)

LH

RH

(7)

(8)

LH

RH

(9)

(10)

LH

RH

(11)

(12)

LH

RH

(13)

(14)

LH

RH

(17)

(18)

LH

RH

(15)

(16)

LH

RH

(19)

(20)

LH

RH

(23)

(25)

(29)

(33)

(38)

(39)

LH

RH

(36)

(37)

LH

RH

(42)

(43)

LH

RH

RH SIDE ONLY

FR72

(24)

(26)

(30)

(34)

(50)

(28)

(32)

(48) (49)

(46)

(47)

LH

RH

(40)

(41)

LH

RH

(44)

(45)

LH

RH

LH ONLY

(35)

(27)

(31)

B

C

C

A

Z310

FR72

FR74

FR77

FR70

A

B

(133)

(133)

(133)

(133)

STGR12

FR72

B B

F

W

D

FR72

STGR

A A

B B

A

A

(21)

(22)

LH

RH

F

W

D

D

E

F

G

REMOVE AND DISCARD

EXISTING FASTENERS

FASTENER TABLE

TYPICAL FOR

STGR1 (AD) AND

STGR4 − STGR11

N_SB_531266_6_BBAB_01_01

Figure A-GBBAB - Sheet 01

Removal/Installation of Angles, Webs, Brackets and Clips at FR72

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 337

6

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**CONF 002

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

FWD FR72

FR72

STGR13

STGR12

STGR11

FWD

F

W

D

AD

FR72

D

E

F

REMOVE AND DISCARD

EXISTING FASTENERS

FASTENER TABLE

N_SB_531266_6_BBAB_02_00

Figure A-GBBAB - Sheet 02

Removal/Installation of Angles, Webs, Brackets and Clips at FR72

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 338

6

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**CONF 002

FOR FASTENER SYMBOLS, REFER TO FIG. N_SB_531266_6_BDAB SHEET 1

NOTE:

STGR1 (AD)

F

W

D

E E

FR72

(133)

(133)

(133)

(133)

FR72

STGR13

STGR12

STGR11

FWD

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

STGR13

AD

STGR12

STGR3

STGR2

FR72

AFTER

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING FWD

STGR5RH

STGR6RH

STGR7RH

VIEW LOOKING FWD

5

6

LH

RH

1

2

LH

RH

3

4

LH

RH

7

8

LH

RH

9

10

LH

RH

11

12

LH

RH

13

14

LH

RH

17

18

LH

RH

15

16

LH

RH

19

20

LH

RH

21

22

LH

RH

23

25

29

33

38

39

LH

RH

36

37

LH

RH

40

41

LH

RH

44

45

LH

RH

46

47

LH

RH

42

43

LH

RH

RH SIDE ONLY

FR72

24

26

30

34

50

28

32

48

LH ONLY

27

35

31

STGR12

FR72

F

W

D

FR72

TYPICAL FOR

F

W

D

AD

FR72

G

H

J C C K D D

F

W

D

C

C

D D

H

J

K

L

STGR4 − STGR11

N_SB_531266_6_BBAB_03_01

E

E 49

STGR4 − STGR11

Figure A-GBBAB - Sheet 03

Removal/Installation of Angles, Webs, Brackets and Clips at FR72

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 339

6

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

SERVICE BULLETIN

**CONF 002

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

FWD L FR72 FOR FASTENER SYMBOLS, REFER 

NOTE:

TO FIG. N_SB_531266_6_BDAB SHEET 1 N_SB_531266_6_BBAB_04_02

Figure A-GBBAB - Sheet 04

Removal/Installation of Angles, Webs, Brackets and Clips at FR72

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 340

6

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

SERVICE BULLETIN

**CONF 003

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

STGR13

AD

STGR12

STGR3

STGR2

FR72

BEFORE

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING FWD

STGR5RH

STGR6RH

STGR7RH

VIEW LOOKING FWD

(5)

(6)

LH

RH

(1)

(2)

LH

RH

(3)

(4)

LH

RH

(7)

(8)

LH

RH

(9)

(10)

LH

RH

(11)

(12)

LH

RH

(13)

(14)

LH

RH

(17)

(18)

LH

RH

(15)

(16)

LH

RH

(19)

(20)

LH

RH

(23)

(25)

(29)

(33)

(38)

(39)

LH

RH

(36)

(37)

LH

RH

(42)

(43)

LH

RH

RH SIDE ONLY

FR72

(24)

(26)

(30)

(34)

(50)

(28)

(32)

(48) (49)

(46)

(47)

LH

RH

(40)

(41)

LH

RH

(44)

(45)

LH

RH

LH ONLY

(35)

(27)

(31)

B

C

C

A

Z310

FR72

FR74

FR77

FR70

A

B

(133)

(133)

(133)

(133)

STGR12

FR72

B B

F

W

D

FR72

STGR

A A

B B

A

A

(21)

(22)

LH

RH

F

W

D

D

E

F

G

REMOVE AND DISCARD

EXISTING FASTENERS

FASTENER TABLE

TYPICAL FOR

STGR1 (AD) AND

STGR4 − STGR11

N_SB_531266_6_BBAD_01_00

Figure A-GBBAD - Sheet 01

Removal/Installation of Angles, Webs, Brackets and Clips at FR72

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 341

6

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

SERVICE BULLETIN

**CONF 003

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

FWD FR72

FR72

STGR13

STGR12

STGR11

FWD

F

W

D

AD

FR72

D

E

F

REMOVE AND DISCARD

EXISTING FASTENERS

FASTENER TABLE

N_SB_531266_6_BBAD_02_00

Figure A-GBBAD - Sheet 02

Removal/Installation of Angles, Webs, Brackets and Clips at FR72

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 342

6

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

SERVICE BULLETIN

**CONF 003

FOR FASTENER SYMBOLS, REFER TO FIG. N_SB_531266_6_BDAD SHEET 1

NOTE:

STGR1 (AD)

F

W

D

E E

FR72

(133)

(133)

(133)

(133)

FR72

STGR13

STGR12

STGR11

FWD

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

STGR13

AD

STGR12

STGR3

STGR2

FR72

AFTER

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING FWD

STGR5RH

STGR6RH

STGR7RH

VIEW LOOKING FWD

5

6

LH

RH

1

2

LH

RH

3

4

LH

RH

7

8

LH

RH

9

10

LH

RH

11

12

LH

RH

13

14

LH

RH

17

18

LH

RH

15

16

LH

RH

19

20

LH

RH

21

22

LH

RH

23

25

29

33

38

39

LH

RH

36

37

LH

RH

40

41

LH

RH

44

45

LH

RH

46

47

LH

RH

42

43

LH

RH

RH SIDE ONLY

FR72

24

26

30

34

50

28

32

48

LH ONLY

27

35

31

STGR12

FR72

F

W

D

FR72

TYPICAL FOR

G

H

J C C D D

F

W

D

C

C

D D

H

J

K

L

STGR4 − STGR11

E

E 49

STGR4 − STGR11

F

W

D

AD

FR72

K

N_SB_531266_6_BBAD_03_02

Figure A-GBBAD - Sheet 03

Removal/Installation of Angles, Webs, Brackets and Clips at FR72

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 343

6

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

SERVICE BULLETIN

**CONF 003

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

FWD L FR72

FOR FASTENER SYMBOLS, REFER 

NOTE:

TO FIG. N_SB_531266_6_BDAD SHEET 1 N_SB_531266_6_BBAD_04_00

Figure A-GBBAD - Sheet 04

Removal/Installation of Angles, Webs, Brackets and Clips at FR72

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 344

6

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

SERVICE BULLETIN

**CONF 004

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

STGR13

AD

STGR12

STGR3

STGR2

FR72

BEFORE

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING FWD

STGR5RH

STGR6RH

STGR7RH

VIEW LOOKING FWD

(5)

(6)

LH

RH

(1)

(2)

LH

RH

(3)

(4)

LH

RH

(7)

(8)

LH

RH

(9)

(10)

LH

RH

(11)

(12)

LH

RH

(13)

(14)

LH

RH

(17)

(18)

LH

RH

(15)

(16)

LH

RH

(19)

(20)

LH

RH

(23)

(25)

(29)

(33)

(38)

(39)

LH

RH

(36)

(37)

LH

RH

(42)

(43)

LH

RH

RH SIDE ONLY

FR72

(24)

(26)

(30)

(34)

(50)

(28)

(32)

(49)

(46)

(47)

LH

RH

(40)

(41)

LH

RH

(44)

(45)

LH

RH

LH ONLY

(35)

(27)

(31)

B

C

C

A

Z310

FR72

FR74

FR77

FR70

A

REMOVE AND DISCARD

EXSISTING FASTENERS

FASTENER TABLE

(133)

(133)

(133)

(133)

STGR12

FR72

B B

F

W

D

FR72

STGR

A A

B B

A

A

(21)

(22)

LH

RH

F

W

D

D

E

F

TYPICAL FOR

STGR1 (AD) AND

STGR4 − STGR11

B G

(48)

N_SB_531266_6_BBAE_01_00

Figure A-GBBAE - Sheet 01

Removal/Installation of Angles, Webs, Brackets and Clips at FR72

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 345

6

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

SERVICE BULLETIN

**CONF 004

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

FWD FR72

FR72

STGR13

STGR12

STGR11

FWD

F

W

D

AD

FR72

D

E

F

REMOVE AND DISCARD

EXSISTING FASTENERS

FASTENER TABLE

N_SB_531266_6_BBAE_02_00

Figure A-GBBAE - Sheet 02

Removal/Installation of Angles, Webs, Brackets and Clips at FR72

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 346

6

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

SERVICE BULLETIN

**CONF 004

(133)

(133)

(133)

(133)

FR72

STGR13

STGR12

STGR11

FWD

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

STGR13

AD

STGR12

STGR3

STGR2

FR72

AFTER

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING FWD

STGR5RH

STGR6RH

STGR7RH

VIEW LOOKING FWD

5

6

LH

RH

1

2

LH

RH

3

4

LH

RH

7

8

LH

RH

9

10

LH

RH

11

12

LH

RH

13

14

LH

RH

17

18

LH

RH

15

16

LH

RH

19

20

LH

RH

21

22

LH

RH

23

25

29

33

38

39

LH

RH

36

37

LH

RH

40

41

LH

RH

44

45

LH

RH

46

47

LH

RH

42

43

LH

RH

RH SIDE ONLY

FR72

24

26

30

34

50

28

32

48

LH ONLY

27

35

31

STGR12

FR72

F

W

D

FR72

TYPICAL FOR

F

W

D

AD

FR72

G

H

J C C K D D

F

W

D

C

C

D D

H

J

K

L

STGR4 − STGR11

E

E 49

FOR FASTENER SYMBOLS, REFER TO FIG. N_SB_531266_6_BDAE SHEET 1

NOTE:

STGR4 − STGR11

STGR1 (AD)

F

W

D

E E

FR72

N_SB_531266_6_BBAE_03_00

Figure A-GBBAE - Sheet 03

Removal/Installation of Angles, Webs, Brackets and Clips at FR72

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 347

6

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

SERVICE BULLETIN

**CONF 004

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

FWD L FR72 FOR FASTENER SYMBOLS, REFER 

NOTE:

TO FIG. N_SB_531266_6_BDAE SHEET 1 N_SB_531266_6_BBAE_04_00

Figure A-GBBAE - Sheet 04

Removal/Installation of Angles, Webs, Brackets and Clips at FR72

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 348

6

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

SERVICE BULLETIN

**CONF 001

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

AD

STGR12

STGR3

STGR2

FR74

BEFORE

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING FWD

(53) (54)

(55)

LH

RH

(51)

(52)

LH

RH

(56)

(57)

LH

RH

(58)

(59)

LH

RH

(60)

(61)

LH

RH

(62)

(63)

LH

RH

(64)

(65)

LH

RH

(68)

(69)

LH

RH

(66)

(67)

LH

RH

(72)

(73)

LH

RH

(74)

(75)

LH

RH

(78)

(79)

LH

RH

(80)

(81)

LH

RH

(86)

(87)

LH

RH

(88)

(89)

LH

RH

(90)

(91)

LH

RH

(48) (100)

(94)

(95)

LH

RH

(70)

(71)

LH

RH

(76)

(77)

LH

RH

(84)

(85)

LH

RH

(82)

(83)

LH

RH

(98)

(99)

LH

RH

(96)

(97)

LH

RH

(92)

(93)

LH

RH

B

A

Z310

FR72

FR74

FR77

FR70

A

B

REMOVE AND DISCARD

EXSISTING FASTENERS

FASTENER TABLE

F

W

D

STGR7 STGR6 STGR5 STGR4

FR74

F

W

D

FR74

STGR

A A

C

A

A

C

D

E

TYPICAL FOR

STGR1 (AD) AND

STGR4 − STGR11

N_SB_531266_6_BCAA_01_02

F

G

Figure A-GBCAA - Sheet 01

Removal/Installation of Angles, Webs, Brackets and Clips at FR74

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 349

6

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

SERVICE BULLETIN

**CONF 001

FWD

STGR7

STGR8

STGR9

STGR10

STGR11

STGR12

FR74

REMOVE AND DISCARD

EXSISTING FASTENERS

FASTENER TABLE

F

W

D

AD

FR74

D

E

N_SB_531266_6_BCAA_02_01

F

W

D

STGR12

F

FR74

Figure A-GBCAA - Sheet 02

Removal/Installation of Angles, Webs, Brackets and Clips at FR74

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 350

6

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

SERVICE BULLETIN

**CONF 001

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

AD

STGR12

STGR3

STGR2

FR74

AFTER

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING FWD

53 54

55

LH

RH

51

52

LH

RH

56

57

LH

RH

58

59

LH

RH

60

61

LH

RH

62

63

LH

RH

64

65

LH

RH

68

69

LH

RH

66

67

LH

RH

72

73

LH

RH

74

75

LH

RH

78

79

LH

RH

80

81

LH

RH

86

87

LH

RH

88

89

LH

RH

90

91

LH

RH

100

92

93

LH

RH

70

71

LH

RH

76

77

LH

RH

84

85

LH

RH

82

83

LH

RH

94

95

LH

RH

98

99

LH

RH

96

97

LH

RH

F

W

D

AD

FR74

F

W

D

STGR7 STGR6 STGR5 STGR4

FR74

F

W

D

FR74

STGR

B B

B

B

TYPICAL FOR

STGR1 (AD) AND

STGR4 − STGR11

48

FOR FASTENER SYMBOLS, REFER TO FIG. N_SB_531266_6_BDAA SHEET 1

NOTE:

G

H

J

J

H

K

L

N_SB_531266_6_BCAA_03_03

Figure A-GBCAA - Sheet 03

Removal/Installation of Angles, Webs, Brackets and Clips at FR74

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 351

6

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

SERVICE BULLETIN

**CONF 001

FWD

STGR7

STGR8

STGR9

STGR10

STGR11

STGR12

FR74

FOR FASTENER SYMBOLS, REFER TO FIG. N_SB_531266_6_BDAA SHEET 1 N_SB_531266_6_BCAA_04_01

NOTE:

F

W

D

STGR12

FR74

K

L

Figure A-GBCAA - Sheet 04

Removal/Installation of Angles, Webs, Brackets and Clips at FR74

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 352

6

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

SERVICE BULLETIN

**CONF 002

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

AD

STGR12

STGR3

STGR2

FR74

BEFORE

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING FWD

(53) (54)

(55)

LH

RH

(51)

(52)

LH

RH

(56)

(57)

LH

RH

(58)

(59)

LH

RH

(60)

(61)

LH

RH

(62)

(63)

LH

RH

(64)

(65)

LH

RH

(68)

(69)

LH

RH

(66)

(67)

LH

RH

(72)

(73)

LH

RH

(74)

(75)

LH

RH

(78)

(79)

LH

RH

(80)

(81)

LH

RH

(86)

(87)

LH

RH

(88)

(89)

LH

RH

(90)

(91)

LH

RH

(48) (100)

(94)

(95)

LH

RH

(70)

(71)

LH

RH

(76)

(77)

LH

RH

(84)

(85)

LH

RH

(82)

(83)

LH

RH

(98)

(99)

LH

RH

(96)

(97)

LH

RH

(92)

(93)

LH

RH

B

A

Z310

FR72

FR74

FR77

FR70

A

B

F

W

D

STGR7 STGR6 STGR5 STGR4

FR74

F

W

D

FR74

STGR

A A

C

A

A

C

D

E

REMOVE AND DISCARD

EXISTING FASTENERS

FASTENER TABLE

TYPICAL FOR

STGR1 (AD) AND

STGR4 − STGR11

N_SB_531266_6_BCAB_01_02

F

G

Figure A-GBCAB - Sheet 01

Removal/Installation of Angles, Webs, Brackets and Clips at FR74

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 353

6

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

SERVICE BULLETIN

**CONF 002

FWD

STGR7

STGR8

STGR9

STGR10

STGR11

STGR12

FR74

F

W

D

AD

FR74

D

E

REMOVE AND DISCARD

EXISTING FASTENERS

FASTENER TABLE

N_SB_531266_6_BCAB_02_01

F

W

D

STGR12

F

FR74

Figure A-GBCAB - Sheet 02

Removal/Installation of Angles, Webs, Brackets and Clips at FR74

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 354

6

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

SERVICE BULLETIN

**CONF 002

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

AD

STGR12

STGR3

STGR2

FR74

AFTER

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING FWD

53 54

55

LH

RH

51

52

LH

RH

56

57

LH

RH

58

59

LH

RH

60

61

LH

RH

62

63

LH

RH

64

65

LH

RH

68

69

LH

RH

66

67

LH

RH

72

73

LH

RH

74

75

LH

RH

78

79

LH

RH

80

81

LH

RH

86

87

LH

RH

88

89

LH

RH

90

91

LH

RH

100

92

93

LH

RH

70

71

LH

RH

76

77

LH

RH

84

85

LH

RH

82

83

LH

RH

94

95

LH

RH

98

99

LH

RH

96

97

LH

RH

F

W

D

AD

FR74

F

W

D

STGR7 STGR6 STGR5 STGR4

FR74

F

W

D

FR74

STGR

B B

B

B

TYPICAL FOR

STGR1 (AD) AND

STGR4 − STGR11

48

FOR FASTENER SYMBOLS, REFER TO FIG. N_SB_531266_6_BDAB SHEET 1 N_SB_531266_6_BCAB_03_01

NOTE:

G

J

H

K

L H

J

Figure A-GBCAB - Sheet 03

Removal/Installation of Angles, Webs, Brackets and Clips at FR74

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 355

6

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

SERVICE BULLETIN

**CONF 002

FWD

STGR7

STGR8

STGR9

STGR10

STGR11

STGR12

FR74

FOR FASTENER SYMBOLS, REFER TO FIG. N_SB_531266_6_BDAB SHEET 1 N_SB_531266_6_BCAB_04_01

NOTE:

F

W

D

STGR12

FR74

K

L

Figure A-GBCAB - Sheet 04

Removal/Installation of Angles, Webs, Brackets and Clips at FR74

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 356

6

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

SERVICE BULLETIN

**CONF 003

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

AD

STGR12

STGR3

STGR2

FR74

BEFORE

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING FWD

(53) (54)

(55)

LH

RH

(51)

(52)

LH

RH

(56)

(57)

LH

RH

(58)

(59)

LH

RH

(60)

(61)

LH

RH

(62)

(63)

LH

RH

(64)

(65)

LH

RH

(68)

(69)

LH

RH

(66)

(67)

LH

RH

(72)

(73)

LH

RH

(74)

(75)

LH

RH

(78)

(79)

LH

RH

(80)

(81)

LH

RH

(86)

(87)

LH

RH

(88)

(89)

LH

RH

(90)

(91)

LH

RH

(48) (100)

(94)

(95)

LH

RH

(70)

(71)

LH

RH

(76)

(77)

LH

RH

(84)

(85)

LH

RH

(82)

(83)

LH

RH

(98)

(99)

LH

RH

(96)

(97)

LH

RH

(92)

(93)

LH

RH

B

A

Z310

FR72

FR74

FR77

FR70

A

B

F

W

D

STGR7 STGR6 STGR5 STGR4

FR74

F

W

D

FR74

STGR

A A

C

A

A

C

D

E

REMOVE AND DISCARD

EXISTING FASTENERS

FASTENER TABLE

TYPICAL FOR

STGR1 (AD) AND

STGR4 − STGR11

F

G

N_SB_531266_6_BCAD_01_00

Figure A-GBCAD - Sheet 01

Removal/Installation of Angles, Webs, Brackets and Clips at FR74

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 357

6

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

SERVICE BULLETIN

**CONF 003

FWD

STGR7

STGR8

STGR9

STGR10

STGR11

STGR12

FR74

F

W

D

AD

FR74

D

E

REMOVE AND DISCARD

EXISTING FASTENERS

FASTENER TABLE

F

W

D

STGR12

F

FR74

N_SB_531266_6_BCAD_02_00

Figure A-GBCAD - Sheet 02

Removal/Installation of Angles, Webs, Brackets and Clips at FR74

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 358

6

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

SERVICE BULLETIN

**CONF 003

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

AD

STGR12

STGR3

STGR2

FR74

AFTER

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING FWD

53 54

55

LH

RH

51

52

LH

RH

56

57

LH

RH

58

59

LH

RH

60

61

LH

RH

62

63

LH

RH

64

65

LH

RH

68

69

LH

RH

66

67

LH

RH

72

73

LH

RH

74

75

LH

RH

78

79

LH

RH

80

81

LH

RH

86

87

LH

RH

88

89

LH

RH

90

91

LH

RH

100

92

93

LH

RH

70

71

LH

RH

76

77

LH

RH

84

85

LH

RH

82

83

LH

RH

94

95

LH

RH

98

99

LH

RH

96

97

LH

RH

F

W

D

FR74

STGR

B B

B

B

TYPICAL FOR

STGR1 (AD) AND

STGR4 − STGR11

48

FOR FASTENER SYMBOLS, REFER TO FIG. N_SB_531266_6_BDAD SHEET 1

NOTE:

G

J

H

K

L F

W

D

STGR7 STGR6 STGR5 STGR4

FR74

F

W

D

AD

FR74

H

J

N_SB_531266_6_BCAD_03_01

Figure A-GBCAD - Sheet 03

Removal/Installation of Angles, Webs, Brackets and Clips at FR74

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 359

6

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

SERVICE BULLETIN

**CONF 003

FWD

FOR FASTENER SYMBOLS, REFER TO FIG. N_SB_531266_6_BDAD SHEET 1

NOTE:

F

W

D

STGR12

FR74

K

L

STGR7

STGR8

STGR9

STGR10

STGR11

STGR12

FR74

N_SB_531266_6_BCAD_04_00

Figure A-GBCAD - Sheet 04

Removal/Installation of Angles, Webs, Brackets and Clips at FR74

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 360

6

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

SERVICE BULLETIN

**CONF 004

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

AD

STGR12

STGR3

STGR2

FR74

BEFORE

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING FWD

(53) (54)

(55)

LH

RH

(51)

(52)

LH

RH

(56)

(57)

LH

RH

(58)

(59)

LH

RH

(60)

(61)

LH

RH

(62)

(63)

LH

RH

(64)

(65)

LH

RH

(68)

(69)

LH

RH

(66)

(67)

LH

RH

(72)

(73)

LH

RH

(74)

(75)

LH

RH

(78)

(79)

LH

RH

(80)

(81)

LH

RH

(86)

(87)

LH

RH

(88)

(89)

LH

RH

(90)

(91)

LH

RH

(48) (100)

(94)

(95)

LH

RH

(70)

(71)

LH

RH

(76)

(77)

LH

RH

(84)

(85)

LH

RH

(82)

(83)

LH

RH

(98)

(99)

LH

RH

(96)

(97)

LH

RH

(92)

(93)

LH

RH

B

A

Z310

FR72

FR74

FR77

FR70

A

REMOVE AND DISCARD

EXSISTING FASTENERS

FASTENER TABLE

F

W

D

STGR7 STGR6 STGR5 STGR4

FR74

F

W

D

FR74

STGR

A A

C

A

A

C

D

E

TYPICAL FOR

STGR1 (AD) AND

STGR4 − STGR11

F

B G

N_SB_531266_6_BCAE_01_00

Figure A-GBCAE - Sheet 01

Removal/Installation of Angles, Webs, Brackets and Clips at FR74

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 361

6

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

SERVICE BULLETIN

**CONF 004

FWD

STGR7

STGR8

STGR9

STGR10

STGR11

STGR12

FR74

REMOVE AND DISCARD

EXSISTING FASTENERS

FASTENER TABLE

F

W

D

AD

FR74

D

E

F

W

D

STGR12

F

FR74

N_SB_531266_6_BCAE_02_00

Figure A-GBCAE - Sheet 02

Removal/Installation of Angles, Webs, Brackets and Clips at FR74

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 362

6

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

SERVICE BULLETIN

**CONF 004

STGR4

STGR5

STGR6

STGR7

STGR8

STGR9

STGR10

STGR11

AD

STGR12

STGR3

STGR2

FR74

AFTER

LH SHOWN

RH SYMMETRICAL

VIEW LOOKING FWD

53 54

55

LH

RH

51

52

LH

RH

56

57

LH

RH

58

59

LH

RH

60

61

LH

RH

62

63

LH

RH

64

65

LH

RH

68

69

LH

RH

66

67

LH

RH

72

73

LH

RH

74

75

LH

RH

78

79

LH

RH

80

81

LH

RH

86

87

LH

RH

88

89

LH

RH

90

91

LH

RH

100

92

93

LH

RH

70

71

LH

RH

76

77

LH

RH

84

85

LH

RH

82

83

LH

RH

94

95

LH

RH

98

99

LH

RH

96

97

LH

RH

F

W

D

AD

FR74

F

W

D

STGR7 STGR6 STGR5 STGR4

FR74

F

W

D

FR74

STGR

B B

B

B

TYPICAL FOR

STGR1 (AD) AND

STGR4 − STGR11

48

FOR FASTENER SYMBOLS, REFER TO FIG. N_SB_531266_6_BDAE SHEET 1

NOTE:

G

H

J

J

H

K

L

N_SB_531266_6_BCAE_03_00

Figure A-GBCAE - Sheet 03

Removal/Installation of Angles, Webs, Brackets and Clips at FR74

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 363

6

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

SERVICE BULLETIN

**CONF 004

FWD

STGR7

STGR8

STGR9

STGR10

STGR11

STGR12

FR74

FOR FASTENER SYMBOLS, REFER TO FIG. N_SB_531266_6_BDAE SHEET 1

NOTE:

F

W

D

STGR12

FR74

K

L

N_SB_531266_6_BCAE_04_00

Figure A-GBCAE - Sheet 04

Removal/Installation of Angles, Webs, Brackets and Clips at FR74

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 364

6

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

SERVICE BULLETIN

**CONF 001

ITEM PART NUMBER DESCRIPTION

DAN5−6−4X PIN, HI−LOK

DAN11−6X COLLAR, HI−LOK

102

103

DAN5−6−5X

DAN11−6X

104

103

DAN5−6−6X

DAN11−6X

105

103

106 EN6081D5−06 RIVET

DAN5−6−5

NSA5075−6

107

108

DAN5−5−6

NSA5075−5

109

110

DAN5−5−5

NSA5075−5

111

110

DAN5−6−6

NSA5075−6

112

108

DAN5−6−3X

DAN11−6X

113

103

DAN5−8−5X

DAN11−8X

114

115

DAN5−8−4X

DAN11−8X

116

115

DAN5−8−7X

DAN11−8X

117

115

DAN5−8−8X

DAN11−8X

118

115

DAN6−6−3X

DAN11−6X

119

103

DAN6−6−4X

DAN11−6X

120

103

DAN6−6−5X

DAN11−6X

121

103

122 EN6069D5−06 RIVET

DAN6−8−6X

DAN11−8X

123

115

DAN6−6−7X

DAN11−6X

124

103

DAN6−6−7

NSA5075−6

125

108

DAN6−6−6

NSA5075−6

126

108

DAN6−6−5

NSA5075−6

127

108

DAN6−6−3

NSA5075−6

128

108

DAN5−6−3

NSA5075−6

129

108

DAN5−6−7X

DAN11−6X

130

103

DAN5−8−6X

DAN11−8X

131

115

DAN6−6−6X

DAN11−6X

132

103

135 EN6081D5−07 RIVET

136 EN6069D5−07 RIVET

137 EN6069D5−08 RIVET

FINAL HOLE DIAMETER

MIN MAX

HOLE 

SYMBOL

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

4.060 mm

(0.160 in)

4.170 mm

(0.164 in)

4.125 mm

(0.162 in)

4.160 mm

(0.164 in)

4.125 mm

(0.162 in)

4.160 mm

(0.164 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

ITEM PART NUMBER DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

HOLE 

SYMBOL

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

MIN

PITCH

MIN EDGE

MARGIN

MIN

PITCH

MIN EDGE

MARGIN

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

21.800 mm

(0.858 in)

12.800 mm

(0.504 in)

21.800 mm

(0.858 in)

12.800 mm

(0.504 in)

21.800 mm

(0.858 in)

12.800 mm

(0.504 in)

21.800 mm

(0.858 in)

12.800 mm

(0.504 in)

21.800 mm

(0.858 in)

12.800 mm

(0.504 in)

NOTE:

UNLESS OTHERWISE STATED −

MINIMUM EDGE DISTANCE HAVE TO BE ACHIEVED FOR 

INSTALLATION OF CLIPS, SHEAR WEBS AND ANGLES.

4.060 mm

(0.160 in)

4.170 mm

(0.164 in)

4.060 mm

(0.160 in)

4.170 mm

(0.164 in)

4.060 mm

(0.160 in)

4.170 mm

(0.164 in)

4.060 mm

(0.160 in)

4.170 mm

(0.164 in)

DAN6−5−7

NSA5075−5

DAN7−6−11X

DAN12−6X

DAN5−6−10X

DAN11−6X

DAN5−6−8X

DAN11−6X

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

133

110

144

145

146

103

148

103

4.125 mm

(0.162 in)

4.160 mm

(0.164 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

21.800 mm

(0.858 in)

12.800 mm

(0.504 in)

N_SB_531266_6_BDAA_01_05

Figure A-GBDAA - Sheet 01

Fastener Symbol Identification

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 365

6

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

SERVICE BULLETIN

**CONF 002

ITEM PART NUMBER DESCRIPTION

DAN5−6−4X PIN, HI−LOK

DAN11−6X COLLAR, HI−LOK

102

103

DAN5−6−5X

DAN11−6X

104

103

DAN5−6−6X

DAN11−6X

105

103

106 EN6081D5−06 RIVET

DAN5−6−6

NSA5075−6

109

110

DAN5−6−5

NSA5075−6

111

110

DAN6−6−5

NSA5075−6

112

110

DAN5−6−3X

DAN11−6X

113

103

DAN5−8−5X

DAN11−8X

114

115

DAN5−8−4X

DAN11−8X

116

115

DAN5−8−7X

DAN11−8X

117

115

DAN5−8−8X

DAN11−8X

118

115

DAN6−6−3X

DAN11−6X

119

103

DAN6−6−4X

DAN11−6X

120

103

DAN6−6−5Y

NSA5330−6

121

108

122 EN6069D5−06 RIVET

DAN6−8−6X

DAN11−8X

123

115

DAN6−6−6Y

NSA5330−6

124

108

DAN6−6−7X

DAN11−6X

125

103

DAN6−6−6

NSA5075−6

126

110

DAN6−6−5X

DAN11−6X

127

103

DAN6−6−3

NSA5075−6

128

110

DAN5−6−3

NSA5075−6

129

110

DAN5−6−7X

DAN11−6X

130

103

DAN5−8−6X

DAN11−8X

131

115

DAN6−6−6X

DAN11−6X

132

103

135 EN6081D5−07 RIVET

FINAL HOLE DIAMETER

MIN MAX

HOLE 

SYMBOL

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

4.060 mm

(0.160 in)

4.170 mm

(0.164 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.509 mm

(0.217 in)

5.549 mm

(0.219 in)

4.060 mm

(0.160 in)

4.170 mm

(0.164 in)

5.509 mm

(0.217 in)

5.549 mm

(0.219 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

4.060 mm

(0.160 in)

4.170 mm

(0.164 in)

ITEM PART NUMBER DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

HOLE 

SYMBOL

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

MIN

PITCH

MIN EDGE

MARGIN

MIN

PITCH

MIN EDGE

MARGIN

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

17.900 mm

(0.705 in)

10.200 mm

(0.402 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

17.900 mm

(0.705 in)

10.200 mm

(0.402 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

21.800 mm

(0.858 in)

12.800 mm

(0.504 in)

21.800 mm

(0.858 in)

12.800 mm

(0.504 in)

21.800 mm

(0.858 in)

12.800 mm

(0.504 in)

21.800 mm

(0.858 in)

12.800 mm

(0.504 in)

21.800 mm

(0.858 in)

12.800 mm

(0.504 in)

NOTE:

UNLESS OTHERWISE STATED −

MINIMUM EDGE DISTANCE HAVE TO BE ACHIEVED FOR 

INSTALLATION OF CLIPS, SHEAR WEBS AND ANGLES.

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

136 EN6069D5−07 RIVET

137 EN6069D5−08 RIVET

4.060 mm

(0.160 in)

4.170 mm

(0.164 in)

4.060 mm

(0.160 in)

4.170 mm

(0.164 in)

DAN6−5−7

NSA5075−5

DAN7−6−11X

DAN12−6X

DAN5−6−10X

DAN11−6X

DAN5−6−8X

DAN11−6X

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

133

144

145

146

148

4.125 mm

(0.162 in)

4.160 mm

(0.164 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

160

103

103

DAN6−6−7

NSA5075−6

PIN, HI−LOK

COLLAR, HI−LOK

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

134

110

21.800 mm

(0.858 in)

12.800 mm

(0.504 in)

N_SB_531266_6_BDAB_01_02

Figure A-GBDAB - Sheet 01

Fastener Symbol Identification

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 366

6

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

SERVICE BULLETIN

**CONF 003

ITEM PART NUMBER DESCRIPTION

DAN5−6−4X PIN, HI−LOK

DAN11−6X COLLAR, HI−LOK

102

103

DAN5−6−5X

DAN11−6X

104

103

DAN5−6−6X

DAN11−6X

105

103

106 EN6081D5−06 RIVET

DAN5−5−6

NSA5075−5

109

160

DAN5−5−5

NSA5075−5

111

160

DAN6−6−5

NSA5075−6

127

108

DAN5−6−3X

DAN11−6X

113

103

DAN5−8−5X

DAN11−8X

114

115

DAN5−8−4X

DAN11−8X

116

115

DAN5−8−7X

DAN11−8X

117

115

DAN5−8−8X

DAN11−8X

118

115

DAN6−6−3X

DAN11−6X

119

103

DAN6−6−4X

DAN11−6X

120

103

DAN6−8−6X

DAN11−8X

123

115

DAN6−6−7X

DAN11−6X

125

103

DAN6−6−6

NSA5075−6

126

108

DAN6−6−5X

DAN11−6X

121

103

DAN6−6−3

NSA5075−6

128

108

DAN5−6−3

NSA5075−6

129

108

DAN5−6−7X

DAN11−6X

130

103

DAN5−8−6X

DAN11−8X

131

115

DAN6−6−6X

DAN11−6X

132

103

135 EN6081D5−07 RIVET

FINAL HOLE DIAMETER

MIN MAX

HOLE 

SYMBOL

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

4.060 mm

(0.160 in)

4.170 mm

(0.164 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

4.060 mm

(0.160 in)

4.170 mm

(0.164 in)

ITEM PART NUMBER DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

HOLE 

SYMBOL

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

MIN

PITCH

MIN EDGE

MARGIN

MIN

PITCH

MIN EDGE

MARGIN

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

21.800 mm

(0.858 in)

12.800 mm

(0.504 in)

21.800 mm

(0.858 in)

12.800 mm

(0.504 in)

21.800 mm

(0.858 in)

12.800 mm

(0.504 in)

21.800 mm

(0.858 in)

12.800 mm

(0.504 in)

21.800 mm

(0.858 in)

12.800 mm

(0.504 in)

NOTE:

UNLESS OTHERWISE STATED −

MINIMUM EDGE DISTANCE HAVE TO BE ACHIEVED FOR 

INSTALLATION OF CLIPS, SHEAR WEBS AND ANGLES.

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

137 EN6069D5−08 RIVET 4.060 mm

(0.160 in)

4.170 mm

(0.164 in)

DAN7−6−11X

DAN12−6X

DAN5−6−10X

DAN11−6X

DAN5−6−8X

DAN11−6X

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

144

145

146

148

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

4.125 mm

(0.162 in)

4.160 mm

(0.164 in)

103

103

DAN6−6−7

NSA5075−6

PIN, HI−LOK

COLLAR, HI−LOK

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

134

108

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

4.125 mm

(0.162 in)

4.160 mm

(0.164 in)

DAN5−6−5

NSA5075−6

107

108

PIN, HI−LOK

COLLAR, HI−LOK

DAN5−6−6

NSA5075−6

112

108

PIN, HI−LOK

COLLAR, HI−LOK

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

21.800 mm

(0.858 in)

12.800 mm

(0.504 in)

N_SB_531266_6_BDAD_01_02

Figure A-GBDAD - Sheet 01

Fastener Symbol Identification

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 367

6

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

SERVICE BULLETIN

**CONF 004

ITEM PART NUMBER DESCRIPTION

DAN5−6−4X PIN, HI−LOK

DAN11−6X COLLAR, HI−LOK

102

103

DAN5−6−5X

DAN11−6X

104

103

DAN5−6−6X

DAN11−6X

105

103

106 EN6081D5−06 RIVET

DAN5−6−5

NSA5075−6

107

108

DAN5−5−6

NSA5075−5

109

110

DAN5−5−5

NSA5075−5

111

110

DAN5−6−6

NSA5075−6

112

108

DAN5−6−3X

DAN11−6X

113

103

DAN5−8−5X

DAN11−8X

114

115

DAN5−8−4X

DAN11−8X

116

115

DAN5−8−7X

DAN11−8X

117

115

DAN5−8−8X

DAN11−8X

118

115

DAN6−6−3X

DAN11−6X

119

103

DAN6−6−4X

DAN11−6X

120

103

DAN6−6−5X

DAN11−6X

121

103

122 EN6069D5−06 RIVET

DAN6−8−6X

DAN11−8X

123

115

DAN6−6−7X

DAN11−6X

124

103

DAN6−6−7

NSA5075−6

125

108

DAN6−6−6

NSA5075−6

126

108

DAN6−6−5

NSA5075−6

127

108

DAN6−6−3

NSA5075−6

128

108

DAN5−6−3

NSA5075−6

129

108

DAN5−6−7X

DAN11−6X

130

103

DAN5−8−6X

DAN11−8X

131

115

DAN6−6−6X

DAN11−6X

132

103

135 EN6081D5−08 RIVET

136 EN6069D5−07 RIVET

137 EN6069D5−08 RIVET

FINAL HOLE DIAMETER

MIN MAX

HOLE 

SYMBOL

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

4.060 mm

(0.160 in)

4.170 mm

(0.164 in)

4.125 mm

(0.162 in)

4.160 mm

(0.164 in)

4.125 mm

(0.162 in)

4.160 mm

(0.164 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

ITEM PART NUMBER DESCRIPTION

FINAL HOLE DIAMETER

MIN MAX

HOLE 

SYMBOL

6.706 mm

(0.264 in)

6.747 mm

(0.266 in)

MIN

PITCH

MIN EDGE

MARGIN

MIN

PITCH

MIN EDGE

MARGIN

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

15.600 mm

(0.614 in)

8.000 mm

(0.315 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

21.800 mm

(0.858 in)

12.800 mm

(0.504 in)

21.800 mm

(0.858 in)

12.800 mm

(0.504 in)

21.800 mm

(0.858 in)

12.800 mm

(0.504 in)

21.800 mm

(0.858 in)

12.800 mm

(0.504 in)

21.800 mm

(0.858 in)

12.800 mm

(0.504 in)

21.800 mm

(0.858 in)

12.800 mm

(0.504 in)

NOTE:

UNLESS OTHERWISE STATED −

MINIMUM EDGE DISTANCE HAVE TO BE ACHIEVED FOR 

INSTALLATION OF CLIPS, SHEAR WEBS AND ANGLES.

4.060 mm

(0.160 in)

4.170 mm

(0.164 in)

4.060 mm

(0.160 in)

4.170 mm

(0.164 in)

4.060 mm

(0.160 in)

4.170 mm

(0.164 in)

4.060 mm

(0.160 in)

4.170 mm

(0.164 in)

DAN7−6−11X

DAN12−6X

DAN5−6−10X

DAN11−6X

DAN5−6−8X

DAN11−6X

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

PIN, HI−LOK

COLLAR, HI−LOK

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

4.780 mm

(0.188 in)

4.821 mm

(0.190 in)

144

145

146

103

148

103

5.113 mm

(0.201 in)

5.152 mm

(0.203 in)

16.600 mm

(0.653 in)

9.600 mm

(0.378 in)

N_SB_531266_6_BDAE_01_01

Figure A-GBDAE - Sheet 01

Fastener Symbol Identification

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 368

6

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

SERVICE BULLETIN

Appendix 01: Elapsed Time Assumption

**CONF ALL

ELAPSED TIME ASSUMPTION SERVICE BULLETIN No A320−53−1266

GET ACCESS

STEPS MH ET/S

3.00 1.50

13.00 13.00

16.00 16.00

MH

ET/S:

PER

MANHOURS

ELAPSED TIME PER STEP

NUMBER OF PERSONS

01

02

THIS CHART IS ONLY A PROPOSAL.

OPERATORS MAY DETERMINE THAT ANOTHER WAY

TO DO THE WORK IS MORE SUITABLE FOR THEM.

01

02

NOTE:

PER

2

1

1

:

: IF A VSB IS INVOLVED, THE ASSOCIATED MANHOURS

ARE NOT REFLECTED IN THIS GANTT CHART.

SB ELAPSED TIME

(HOURS)

SB ELAPSED TIME

110.00

106.00

10 20 30 40 50 60 70 80 90 100 110

REMOVE THE ANGLES, WEBS, BRACKETS LH AND STGR1, RH 

STGR13, LH AND STGR1, RH

INSTALL THE ANGLES, WEBS, BRACKETS AND CLIPS AT FRAME 72, 

BETWEEN STGR1, RH AND STGR13, LH

REMOVE THE ANGLES, WEBS, BRACKETS AND CLIPS AT FRAME 72, 

BETWEEN STGR13, RH AND STGR3, RH

INSTALL THE ANGLES, WEBS, BRACKETS AND CLIPS AT FRAME 72, 

BETWEEN STGR3, RH TO STGR13, RH

REMOVE THE ANGLES, WEBS, BRACKETS AND CLIPS AT FRAME 74, 

BETWEEN STGR12, LH AND STGR1, RH

TEST

CLOSE−UP

INSTALL THE ANGLES, WEBS, BRACKETS AND CLIPS AT FRAME 74, 

BETWEEN STGR1, RH AND STGR12, LH

REMOVE THE ANGLES, WEBS, BRACKETS AND CLIPS AT FRAME 74, 

BETWEEN STGR12, RH AND STGR3, RH

INSTALL THE ANGLES, WEBS, BRACKETS AND CLIPS AT FRAME 74, 

BETWEEN STGR3, RH AND STGR12, RH 

11.00 11.00 1

14.00 14.00 1

11.00 11.00 1

14.00 14.00 1

11.00 11.00 1

12.00 12.00 1

1.00 0.50 2

4.00 2.00 2

TOTAL MANHOURS

0

N_SB_531266_6_AAAA_01_00

Figure A-GAAAA - Sheet 01

Gantt Chart

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 1

6

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

SERVICE BULLETIN

REPORTING SHEET

TITLE: FUSELAGE - CONE/REAR FUSELAGE - REPLACE CLIPS,

SHEARWEBS AND ANGLES IN SECTION 19 AT FR 72 AND FR 74

MODIFICATION No.: 153833K16120

Please complete the appropriate item (A or B):

A - SB WILL BE embodied YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to

next normal revision or prior to SB embodiment, please indicate required service(s):

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational

documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With

the next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.

- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 1

6

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

SERVICE BULLETIN

QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data

that you provide us will be used to analyse areas of difficulties and to take corrective action to further

improve the quality of our Service Bulletins.

We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

X Reason X List of Materials Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Jan 11/13 SERVICE BULLETIN No.: A320-53-1266

REVISION No.: 03 - May 07/15 Page: 1

6

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