# Airbus Service Bulletin A310-53-2141

Copy: Revision 01 ("FAA-2016-5596_A310-53-2141_R1"), 155 pages: PDF https://openairdocs.org/files/sha256/5c/55/5c55f1a7dcf7b718088f239c12a6221cec20bd8e510ace5bda19eae817d31c8a; text https://openairdocs.org/service-documents/airbus/a310-53-2141/file/5c55f1a7dcf7.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2016-5596; AD 2016-20-11 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md)
- Type: Service bulletin (Service Bulletin)
- Number: A310-53-2141
- Latest revision known: A310-53-2141, Revision 01, dated July 2, 2015 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/airbus/a310-53-2141

## ADs that cite it (3) (OpenAirDocs)

Newest first, with the revision each names, as OpenAirDocs read it from the AD's text.

- [AD 2017-24-09](https://openairdocs.org/ad/2017-24-09.md), effective Jan 5, 2018: Revision 01
- [AD 2017-21-02](https://openairdocs.org/ad/2017-21-02.md), effective Nov 27, 2017: No revision named
- [AD 2016-20-11](https://openairdocs.org/ad/2016-20-11.md), effective Jan 3, 2017: Revision 01

Also cited in [2 proposed ADs](https://openairdocs.org/service-documents/airbus/a310-53-2141/proposed.md).

## Text (155 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2016-5596; AD 2016-20-11 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

@A310
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
MANDATORY
 MANDATORY
 MANDATORY
ATA SYSTEM: 53
TITLE: FUSELAGE - REAR FUSELAG E - REINFORCEMENT OF AFT CARGO
DOOR SILL BEAM AREA BETWEEN FRAME 60 AND FRAME 63
MODIFICATION No.: 13745D23357
This page transmits Revision No.01 of Service Bulletin No.A310-53-2141
ADDITIONAL WORK
**CONF ALL
No additional work is required by this revision for aircraft modified by any previous issue.
REASON
Revision 01 issued to change the standard tools to special AIRBUS tools.
CHANGES
SUMMARY
MATERIAL PRICE INFORMATION
 MATERIAL PRICE INFORMATION TABLE
UPDATED
R
MATERIAL PRICE INFORMATION TABLE
UPDATED
R
PLANNING INFORMATION
EFFECTIVITY
Material Effectivity
 MATERIAL EFFECTIVITY UPDATED
MATERIAL SET UPDATED
R
MATERIAL EFFECTIVITY UPDATED
MATERIAL SET UPDATED
R
MATERIAL INFORMATION
TOOLING
Tooling - Price and Availability
Procurement Addresses
 PROCUREMENT ADDRESSES UPDATED
MATERIAL SET UPDATED
R
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 1
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 2

@A310
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
Price and Availability
 PRICE AND AVAILABILITY UPDATED
MATERIAL AVAILABILITY UPDATED
MATERIAL PRICE UPDATED
MATERIAL SET UPDATED
R
Tools
 TOOLS UPDATED
 R
Standard tool TOOLD01
 TOOL MATERIAL SET DELETED
 D
Standard tool TOOLD02
 TOOL MATERIAL SET DELETED
 D
Standard tool TOOLD03
 TOOL MATERIAL SET DELETED
 D
Special Tools
 SPECIAL TOOLS UPDATED
 R
Kit tool 532141T01R00
 TOOL MATERIAL SET ADDED
 N
Kit tool 532141T02R00
 TOOL MATERIAL SET ADDED
 N
Kit tool 532141T03R00
 TOOL MATERIAL SET ADDED
 N
ACCOMPLISHMENT INSTRUCTIONS
TASK 532141- 831-848-001-Modification
Subtask 532141-420-201-001
 SUBTASK SOLUTION UPDATED
TOOL UPDATED
SPECIAL TOOL UPDATED
NOTE UPDATED
KEYWORD UPDATED
QUANTITY UPDATED
MATERIAL LIST UPDATED
R
Subtask 532141-420-201-002
 SUBTASK SOLUTION UPDATED
TOOL UPDATED
SPECIAL TOOL UPDATED
NOTE UPDATED
KEYWORD UPDATED
QUANTITY UPDATED
MATERIAL LIST UPDATED
R
FILLING INSTRUCTIONS
This Service Bulletin has been generated electronically and is reissued as a complete document.
Replace the complete document.
Put this Revision Transmittal Sheet in front of the Service Bulletin.
HISTORY OF PREVIOUS REVISIONS
No previous revision
REVISION SEQUENCE
ORIGINAL: Jun 26/15
REVISION No. : 01 - Jul 02/15
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 2
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 3

@A310
SERVICE BULLETIN
SUMMARY
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
This summary is for information only and is not approved for modification of the aircraft.
MANDATORY
 MANDATORY
 MANDATORY
ATA SYSTEM: 53
TITLE: FUSELAGE - REAR FUSELAG E - REINFORCEMENT OF AFT CARGO
DOOR SILL BEAM AREA BETWEEN FRAME 60 AND FRAME 63
**CONF ALL
MODIFICATIONS
MODIFICATION CLASSIFICATION
MAJOR
 13745D23357
MINOR
 None
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
In the frame of the FAR26 - Widespread Fatigue Damage compliance study and a dedicated in service
occurrence, the area of the AFT Cargo-Door Sill-Beam and adjacent structure needs to be reinforced.
This Service Bulletin details the reinforcement of the AFT Cargo Door Lock fitting/torsion plates and Sill
Beam Flag/Sill Beam Web interfaces.
For Configuration 001 the modification is composed of:
- Installation of doublers from FWD and AFT side of the lock fitting/torsion plate interface.
- Installation of angles from FWD and AFT side of the sill-beam flag/sill-beam web interface.
For Configuration 002 the modification is composed of:
- Installation of doublers from FWD and AFT side of the lock fitting/torsion plate interface.
- Installation of angles from FWD and AFT side of the sill-beam flag/sill-beam web interface.
- Replacement of lock fittings.
NOTE
: Some aircraft have been repaired prior to the instruction of this modification at single sill
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 1
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 4

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SERVICE BULLETIN
SUMMARY
beam flag position by Repair and Design Approval Sheets (RDAS). In this case the
sill beam flag/sill beam web interface reinforcement as per this modification is not
applicable. The repair by RDAS solution is considered sufficient to achieve from the
structural integrity.
The accomplishment of this Service Bulletin will improve the reliability of the lower Cargo-Door Sill
Beam Area structure.
The accomplishment of this Service Bulletin cancels the Inspection Service Bulletin A310-53-2139.
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). Prior to Service
Bulletin embodiment, specific attention must be paid to structural damage which may exist and to
repairs which were performed on the aircraft because they may be affected by the Service Bulletin. It
must be verified that all allowable damage limits and repairs performed (both in accordance with the
SRM and outside of 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 not covered by the SRM
and for repairs outside of the SRM covered by an RAS issued by AIRBUS, AIRBUS Customer Services
Repair Engineering Support (SEOE) should be contacted. Repair review will be done by AIRBUS at
conditions of the Customer Services Catalogue.
GENERAL EVALUATION
EVALUATION TABLE
COMPLIANCE
 MANDATORY (1)
 CANCELS INSPECTION SB
 YES
POTENTIAL AD
 YES
 A/C OPERATION AFFECTED
 NO
RELIABILITY AFFECTED
 NO
 PAX COMFORT AFFECTED
 NO
COST SAVING
 NO
 ETOPS AFFECTED
 NO
STRUCTURAL LIFE EXTN
 NO
 VENDOR SB INVOLVED
 NO
NOTE
 (1)
: Service Bulletin must be accomplished.
MATERIAL PRICE INFORMATION
**CONF 001
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
 QTY PER
A/C
PRICE PER
A/C (USD)
MAIN PARTS
Kit 532141D01R00
 1
 11,500.00
 Doubler, Angles, Fastener
Kit tool
 532141T01R00
 1
 12,670.00
 Cold Working Capital Tooling
Kit tool
 532141T02R00
 1
 2,150.00
 Cold Working Durable Tooling
Kit tool
 532141T03R00
 1
 70.00
 Cold Working Expendable Tooling
TOTAL
 26,390.00
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 2
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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SERVICE BULLETIN
SUMMARY
**CONF 002
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
 QTY PER
A/C
PRICE PER
A/C (USD)
MAIN PARTS
Kit 532141D02R00
 1
 82,000.00
 Doubler, Angles, Fittings, Fastener
Kit tool
 532141T01R00
 1
 12,670.00
 Cold Working Capital Tooling
Kit tool
 532141T02R00
 1
 2,150.00
 Cold Working Durable Tooling
Kit tool
 532141T03R00
 1
 70.00
 Cold Working Expendable Tooling
TOTAL
 96,890.00
EFFECTIVITY
**CONF ALL
This Service Bulletin is applicable to this (these) operator(s) :
18T 50W 58X 82Z 98W 99Y AFG BBC CFC DGA F2I FDX GAF
I2L IRA IRM IYE K1P KAC KZU PCA PIA QAF R1T RJA ROT
RZO SGX SUD THY TSC TXP UBD UZB WHT
CONCURRENT REQUIREMENTS
Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of the
following Service Bulletin:
Service Bulletin No. A310-53-2139
NOTE
: Service Bulletin No. A310-53-2139 (FU SELAGE-REAR FUSEL AGE-INSPECTION OF
AFT CARGO DOOR LOWER TORSION BOX AREA)
REFERENCES / REPERCUSSIONS
TFU
 53.17.00.006
OEB
 None
AOT
 A53W005-14
SIL
 None
ISI
 None
LINE MAINTENANCE AFFECTED
 No
LIFE LIMIT
 None
OTHER
 None
NATURE OF THE WORK
AIRCRAFT
 YES
EQUIPMENT
 NO
HARD
 NO
SOFT
 NO
OBRM
 NO
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 3
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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SERVICE BULLETIN
SUMMARY
MANPOWER
**CONF 001
Task 532141-831-848-001: Modification
TOTAL MANHOURS
 47.00
ELAPSED TIME (HOURS)
 27.00
**CONF 002
Task 532141-831-848-001: Modification
TOTAL MANHOURS
 68.00
ELAPSED TIME (HOURS)
 40.00
APPENDICES
**CONF ALL
APPENDIX 01: GANTT CHART
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 4
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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SERVICE BULLETIN
SUMMARY
**CONF 001
FR62
FR61
FR60
FR63
FR59A
FR60A
FR61A
FR62A
FR63A
STGR46RH
STGR43RH
A
FR63A
FR59A
B
B
AFT CARGO 
DOOR
REINFORCED TORSION
BOX PLATE
A
Z150
B_SB_532141_6_SAAA_01_00
Figure A-GSAAA - Sheet 01
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 5
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 8

@A310
SERVICE BULLETIN
SUMMARY
**CONF 002
AFR63A
FR59A
AFT CARGO 
DOOR
FR59A
FR60
FR60A
FR61
FR61A
FR62
FR62A
FR63
DOOR SILL BEAM WEB
LOCK FITTING
LOCK FITTING
C
B
C
B
FR62
FR61
FR60
FR63
FR59A
FR60A
FR61A
FR62A
FR63A
STGR46RH
STGR43RH
REINFORCED TORSION
BOX PLATE
A
Z150
B_SB_532141_6_SAAB_01_00
Figure A-GSAAB - Sheet 01
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 6
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 9

@A310
SERVICE BULLETIN
AIRBUS
CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
FRANCE
T e l:( 3 3 )56 19 33 33 3
Telex : AIRBU 530526F
F a x:( 3 3 )56 19 34 25 1
MANDATORY
 MANDATORY
 MANDATORY
ATA SYSTEM: 53
TITLE: FUSELAGE - REAR FUSELAG E - REINFORCEMENT OF AFT CARGO
DOOR SILL BEAM AREA BETWEEN FRAME 60 AND FRAME 63
MODIFICATION No.: 13745D23357
This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the
property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with
any information contained in it. It is delivered on the express condition that said document and the
information contained in it shall be treated as confidential, shall not be used for any purpose other than
that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall
not be duplicated in any manner (except for the purposes of performing the tasks described hereunder
and provided that any recipient of such document shall comply with the conditions herein), without
AIRBUS prior written consent.
1. PLANNING INFORMATION
**CONF ALL
A. EFFECTIVITY
NOTE
: This Service Bulletin is applicable to aircraft with MOD 05438 embodied
(A310-A300/600-FUSELAGE SKIN AND FRAME WORK: CARGO DOOR
FRAMES AND SILLS-TO CHANGE THE MATERIAL FROM 2024 TO 7075).
(1) Models
310-222 310-304 310-308 310-322 310-324 310-325
(2) Effectivity by MSN
0418-0419 0421-0422 0425 0431 0434 0436-0437 0439 0441 0444-0447 0449 0452
0456-0458 0467 0472-0473 0478 0480 0482-0484 0488-0492 0494-0500 0503
0519-0520 0522-0524 0526 0537 0539 0545 0547 0549-0552 0562 0564-0565
0567-0568 0571 0574 0576 0585-0588 0590-0595 0597 0599-0600 0620 0622 0624
0636 0644 0646-0649 0651 0653 0656 0658 0660-0661 0663 0667 0671-0672 0674
0676 0678 0682 0687 0689 0691 0700 0702 0704 0706
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 1
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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@A310
SERVICE BULLETIN
(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
18T
 0473
50W
 0498
58X
 0431
82Z
 0550 0551
98W
 0495
99Y
 0489
AFG
 0496 0497
BBC
 0594 0700
CFC
 0425 0441 0444 0446 0482
DGA
 0418 0421 0422
F2I
 0491 0520
FDX
 0439 0449 0452 0456 0457 0458 0467 0492 0500 0539 0549 0552
0593
GAF
 0434 0484 0503 0522 0523
I2L
 0661
IRA
 0436 0671
IRM
 0488 0499 0524 0526 0537 0547 0564 0567 0586 0595 0620
IYE
 0568 0702 0704
K1P
 0648
KAC
 0647 0649 0663
KZU
 0592 0622 0646
PCA
 0419
PIA
 0585 0587 0590 0653 0656 0660 0676 0678 0682 0687 0689 0691
QAF
 0667
R1T
 0591
RJA
 0445 0490
ROT
 0636 0644
RZO
 0571 0624 0651
SGX
 0519 0562
SUD
 0437
THY
 0478 0480
TSC
 0447 0472 0483 0545 0588 0597 0599 0600 0658
TXP
 0565
UBD
 0672 0674
UZB
 0574 0576 0706
WHT
 0494
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 2
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 11

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SERVICE BULLETIN
(4) Configuration by MSN
MSN
 CONFIGURATION
0418 0419 0421 0422 0425 0431 0434 0436 0437 0439 0441
0444 0445 0446 0447 0449 0452 0456 0457 0458 0467 0472
0473 0478 0480 0482 0483 0484 0488 0489 0490 0491 0492
0494 0495 0496 0497 0498 0499 0500 0503 0519 0520 0522
0523 0524 0526 0537 0539 0545 0547 0549 0550 0551 0552
0562 0564 0565 0567 0568 0571 0574 0576 0585 0586 0587
0588 0590 0591 0592 0593 0594 0595 0597 0599 0600 0620
0622 0624 0636 0644 0646 0647 0648 0649 0651 0653 0656
0658 0660 0661 0663 0667 0671 0672 0674 0676 0678 0682
0687 0689 0691
001
0700 0702 0704 0706
 002
(5) Configuration definition
**CONF 001
Config. 001 is valid for all the aircraft which have not embodied Mod 10319D20472.
**CONF 002
Config. 002 is valid for all the aircraft which have embodied Mod 10319D20472.
(6) Material Effectivity
**CONF 001
MATERIAL
 QTY PER A/C
 SEE NOTES
Kit 532141D01R00
 1
Consumable CMLD01
Kit tool
 532141T01R00
 1
Kit tool
 532141T02R00
 1
Kit tool
 532141T03R00
 1
**CONF 002
MATERIAL
 QTY PER A/C
 SEE NOTES
Kit 532141D02R00
 1
Consumable CMLD01
Kit tool
 532141T01R00
 1
Kit tool
 532141T02R00
 1
Kit tool
 532141T03R00
 1
**CONF ALL
B. CONCURRENT REQUIREMENTS
Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of
the following Service Bulletin:
Service Bulletin No. A310-53-2139
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 3
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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SERVICE BULLETIN
NOTE
: Service Bulletin No. A310-53-2139 (FUSELAGE-REAR FUSELAGE-
INSPECTION OF AFT CARGO DOOR LOWER TORSION BOX AREA)
C. REASON
(1) History
In the frame of the FAR26 - Widespread Fatigue Damage compliance study and a
dedicated in service occurrence, the area of the AFT Cargo-Door Sill-Beam and adjacent
structure needs to be reinforced.
(2) Objective/Action
This Service Bulletin details the reinforcement of the AFT Cargo Door Lock fitting/torsion
plates and Sill Beam Flag/Sill Beam Web interfaces.
For Configuration 001 the modification is composed of:
- Installation of doublers from FWD and AFT side of the lock fitting/torsion plate
interface.
- Installation of angles from FWD and AFT side of the sill-beam flag/sill-beam web
interface.
For Configuration 002 the modification is composed of:
- Installation of doublers from FWD and AFT side of the lock fitting/torsion plate
interface.
- Installation of angles from FWD and AFT side of the sill-beam flag/sill-beam web
interface.
- Replacement of lock fittings.
NOTE
: Some aircraft have been repaired prior to the instruction of this
modification at single sill beam flag position by Repair and Design
Approval Sheets (RDAS). In this case the sill beam flag/sill beam web
interface reinforcement as per this modification is not applicable. The
repair by RDAS solution is considered sufficient to achieve from the
structural integrity.
(3) Advantages
The accomplishment of this Service Bulletin will improve the reliability of the lower
Cargo-Door Sill Beam Area structure.
The accomplishment of this Service Bulletin cancels the Inspection Service Bulletin
A310-53-2139.
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 4
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 13

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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). Prior to Service Bulletin embodiment, specific attention must be paid
to structural damage which may exist and to repairs which were performed on the
aircraft because they may be affected by the Service Bulletin. It must be verified that
all allowable damage limits and repairs performed (both in accordance with the SRM
and outside of 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 not covered by the SRM and for repairs
outside of the SRM covered by an RAS issued by AIRBUS, AIRBUS Customer Services
Repair Engineering Support (SEOE) should be contacted. 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 532141-831-848-001: Modification
(1) Install Reinforcement Doublers and Angles to the Sill Beam and Main Frames/Cargo
Floor Supports
(2) Apply the Surface Protection to the Installation Area
**CONF 002
Task 532141-831-848-001: Modification
(1) Remove the Eccentric Bolts from the Lock Fittings of the AFT Cargo Compartment
Door Frame
(2) Install the new Lock Fitting, the Reinforcement Doublers and Angles to the Sill Beam
and Main Frames/Cargo Floor Supports
(3) Apply the Surface Protection to the Installation Area
(4) Install the Eccentric Bolts in the Lock Fittings of the AFT Cargo Compartment Door
Frame
**CONF ALL
E. COMPLIANCE
(1) Classification
MANDATORY: Service Bulletin must be accomplished.
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 5
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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SERVICE BULLETIN
(2) Accomplishment Timescale
This Service Bulletin has been classified Mandatory. It is expected that an Airworthiness
Directive (AD) published by the European Av iation Safety Agenc y (EASA) will be issued
to confirm this classification. It is anticipated that the AD will confirm the given thresholds
of 19600FC and the grace periods shown in the table 1 below for aircraft which have
missed the Structure Modification Point (SMP), but reference should be made to the AD
for confirmation of the mandated accomplishment timescale.
Table 1
APPLIED INSPECTION METHODS
in accordance with ISB A310-53-2139 or AOT
A53W005-14
GRACE PERIODS
to implement the MSB A310-53-2141
High Frequency Eddy Current (HFEC)
 Latest 2300FC after the last HFEC inspection
performed before release of the MSB
A310-53-2141 or 12 months after release of the
MSB A310-53-2141, whichever comes later.
Detailed Visual Inspection (DET)
 Latest 2300FC after the last DET inspection
performed before release of the MSB
A310-53-2141 or 12 months after release of the
MSB A310-53-2141, whichever comes later.
Ultrasonic (US)
 Latest 12 months after release of the MSB
A310-53-2141
F. APPROVAL
The technical content of this document is approved under the authority of Design
Organisation Approval No. EASA.21J.031.
If an aircraft listed in the effectivity has a modification or repair embodied that is not of
AIRBUS origin, and which affects the content of this Service Bulletin, the operator is
responsible for obtaining approval by its airworthiness authority for any adaptation necessary
before incorporation of the Service Bulletin.
G. MANPOWER
The manpower estimates given in this Service Bulletin are based on the direct labor cost to
do the work. These estimates assume that the work will be done by experienced personnel,
and may need to be revised upwards to suit operator’s circumstances. The estimates do not
include the time to prepare, plan or inspect the work. Manufacture and procurement of parts
and tools, drying times for paints, sealants, etc., and general administration work are also not
included.
**CONF 001
Task 532141-831-848-001: Modification
Get Access
 2.00
On Aircraft
Install Reinforcement Doublers and Angles to the Sill
Beam and Main Frames/Cargo Floor Supports
40.00
Apply the Surface Protection to the Installation Area
 3.00
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 6
6
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SERVICE BULLETIN
Task 532141-831-848-001: Modification
Close-Up
 2.00
TOTAL MANHOURS
 47.00
ELAPSED TIME (HOURS)
 27.00
NOTE
: For an explanation of the manhours and elapsed time, refer to the Gantt
Chart,Fig. A-GAAAA
 given in Appendix 01.
**CONF 002
Task 532141-831-848-001: Modification
Get Access
 2.00
On Aircraft
Remove the Eccentric Bolts from the Lock Fittings of
the AFT Cargo Compartment Door Frame
2.00
Install the new Lock Fitting, the Reinforcement
Doublers and Angles to the Sill Beam and Main
Frames/Cargo Floor Supports
56.00
Apply the Surface Protection to the Installation Area
 3.00
Install the Eccentric Bolts in the Lock Fittings of the
AFT Cargo Compartment Door Frame
2.00
Tests
 1.00
Close-Up
 2.00
TOTAL MANHOURS
 68.00
ELAPSED TIME (HOURS)
 40.00
NOTE
: For an explanation of the manhours and elapsed time, refer to the Gantt
Chart,Fig. A-GAAAB
 given in Appendix 01.
**CONF ALL
H. WEIGHT AND BALANCE
**CONF 001
The weight and balance estimates given in this Service Bulletin are based on the
Manufacturer’s Empty Weight (MEW) and do not include operator’s items. For the definition of
MEW and operator’s items, refer to the Weight and Balance Manual (WBM) Chapter 1-00-07.
Manufacturers Empty Weight 0.756 KG (+1.6666 LB)
Effect on Balance 25.165 KGM (+182.018 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’s items. For the definition of
MEW and operator’s items, refer to the Weight and Balance Manual (WBM) Chapter 1-00-07.
Manufacturers Empty Weight 0.116 KG (+0.2557 LB)
Effect on Balance 3.868 KGM (+27.977 LB.FT )
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 7
6
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SERVICE BULLETIN
**CONF ALL
I. ELECTRICAL LOAD DATA
Not Applicable
J. REFERENCES
**CONF 001
Aircraft Maintenance Manual (AMM)
 06-21-00 06-31-53 06-41-00
20-21-12 24-00-00 25-50-21
25-52-22 25-55-10 52-30-00
Consumable Material List (CML)
Elec. Std. Practices Manual (ESPM)
 20-55-00
In Service Information (ISI)
 ISI 51.48.00001
Non Destructive Test Manual (NTM)
 51-10-01 53-17-33
Standards Manual (SM)
Structural Repair Manual (SRM)
 51-10-00 51-23-20 51-24-00
51-40-20 51-40-21 51-40-30
51-40-40 51-40-41 51-40-44
51-40-50 51-75-10 51-76-10
53-17-18
**CONF 002
Aircraft Maintenance Manual (AMM)
 06-21-00 06-31-53 06-41-00
20-21-12 24-00-00 25-50-21
25-52-22 25-55-10 52-30-00
52-30-31 52-32-11
Consumable Material List (CML)
Elec. Std. Practices Manual (ESPM)
 20-55-00
In Service Information (ISI)
 ISI 51.48.00001
Non Destructive Test Manual (NTM)
 51-10-01 53-17-33
Standards Manual (SM)
Structural Repair Manual (SRM)
 51-10-00 51-23-20 51-24-00
51-40-20 51-40-21 51-40-30
51-40-40 51-40-41 51-40-44
51-40-50 51-75-10 51-76-10
53-17-18
**CONF ALL
K. PUBLICATION AFFECTED
Maintenance Planning Document (MPD)
 531725-01-1
Structural Repair Manual (SRM)
 53-17-18
L. INTERCHANGEABILITY/MIXABILITY
Not Applicable
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 8
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SERVICE BULLETIN
M. SPARES
Fitting Assy-Lock A5397823600200
Fitting Assy-Lock A5397823700200
Fitting Assy-Lock A5397823800200
Fitting Assy-Lock A5397823900200
Fitting Assy-Lock A5397824000200
Fitting Assy-Lock A5397824100200
Fitting Assy-Lock A5397824200200
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 9
6
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This Page Intentionally Left Blank
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 10
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SERVICE BULLETIN
2. MATERIAL INFORMATION
**CONF ALL
A. MATERIAL - PRICE AND AVAILABILITY
(1) Procurement Addresses
This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign.
Customers with aircraft shown in the effectivity of this Service Bulletin should send a
purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is:
Kit 532141D01R00
Kit 532141D02R00
AIRBUS Material, Logistics and Suppliers
Weg beim Jaeger 150
D-22335 HAMBURG
GERMANY
For ordering by internet:
http://spares.airbus.com
For ordering by fax: +49 40 50 76 2590
For ordering by E-mail: airbus.kit@airbus.com
(2) Price and Availability
Kit 532141D01R00
Cost
 11,500.00 USD
Availability
 120 calendar days from receipt of order
The availability given above is the standard lead time from the date of your purchase
order. If items are required before this time, please include a retrofit planning schedule
with your order so that we can try to comply with your requirements.
The sales terms (costs and availability) are estimated in relation to economic conditions.
The latest valid price and lead time for ordering purposes shall be obtained through the
AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.
Kit 532141D02R00
Cost
 82,000.00 USD
Availability
 220 calendar days from receipt of order
The availability given above is the standard lead time from the date of your purchase
order. If items are required before this time, please include a retrofit planning schedule
with your order so that we can try to comply with your requirements.
The sales terms (costs and availability) are estimated in relation to economic conditions.
The latest valid price and lead time for ordering purposes shall be obtained through the
AirbusSpares portal or through a request for quotation to airbus.kit@airbus.com.
B. INDUSTRY SUPPORT INFORMATION
AIRBUS will not provide industry support for accomplishment of this Service Bulletin.
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 11
6
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SERVICE BULLETIN
For the organisation of this retrofit, you are kindly requested to contact AIRBUS retrofit
management department.
AIRBUS CUSTOMER SERVICES DIRECTORATE
1 Rond Point Maurice Bellonte
31707 BLAGNAC CEDEX
France
T e l:( 3 3 )56 71 90 62 2
E-mail : monitored.retrofit@airbus.com
F a x:( 3 3 )56 19 32 74 5
C. LIST OF COMPONENTS
Kit 532141D01R00
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
1
 A5398104820000
 1
 ANGLE
2
 A5398104820100
 1
 ANGLE
3
 A5398104821600
 3
 DOUBLER
4
 A5398104821400
 3
 DOUBLER
5
 A5398104822000
 2
 DOUBLER
6
 A5398104821800
 2
 DOUBLER
7
 A5398104820200
 1
 ANGLE
8
 A5398104820300
 1
 ANGLE
9
 A5398104820400
 1
 ANGLE
10
 A5398104820500
 1
 ANGLE
11
 A5398104820600
 1
 ANGLE
12
 A5398104820700
 1
 ANGLE
13
 A5398104820800
 1
 ANGLE
14
 A5398104820900
 1
 ANGLE
15
 A5398104822400
 1
 DOUBLER
16
 A5398104822200
 1
 DOUBLER
17
 A5398104821000
 1
 ANGLE
18
 A5398104821100
 1
 ANGLE
19
 A5398104822800
 1
 DOUBLER
20
 A5398104822600
 1
 DOUBLER
21
 A5398104821200
 1
 ANGLE
22
 A5398104821300
 1
 ANGLE
23
 DAN5-6-6X
 14
 PIN
24
 DAN5-6-7X
 12
 PIN
25
 DAN5-6-4
 12
 PIN
26
 DAN5-6-6
 51
 PIN
27
 DAN5-6-7
 8
 PIN
28
 DAN7-6-9
 28
 PIN
29
 DAN12-6X
 26
 COLLAR
30
 DAN12-6
 28
 COLLAR
31
 EN6115K3-5
 14
 BOLT
32
 NSA5075-6
 71
 COLLAR
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 12
6
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SERVICE BULLETIN
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
33
 ASNA2528-3
 14
 NUT
NOTE
: If you find part numbers of hardware components in the related kit(s) which
you cannot identify in the LIST OF COMPONENTS of this Service Bulletin,
refer to Standards Manual (SM). The SM will give you the correct part number
to part number relationship.
Kit 532141D02R00
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
1
 A5398104820000
 1
 ANGLE
2
 A5398104820100
 1
 ANGLE
3
 A5398104821600
 3
 DOUBLER
4
 A5398104821400
 3
 DOUBLER
5
 A5398104822000
 2
 DOUBLER
6
 A5398104821800
 2
 DOUBLER
7
 A5398104820200
 1
 ANGLE
8
 A5398104820300
 1
 ANGLE
9
 A5398104820400
 1
 ANGLE
10
 A5398104820500
 1
 ANGLE
11
 A5398104820600
 1
 ANGLE
12
 A5398104820700
 1
 ANGLE
13
 A5398104820800
 1
 ANGLE
14
 A5398104820900
 1
 ANGLE
15
 A5398104822400
 1
 DOUBLER
16
 A5398104822200
 1
 DOUBLER
17
 A5398104821000
 1
 ANGLE
18
 A5398104821100
 1
 ANGLE
19
 A5398104822800
 1
 DOUBLER
20
 A5398104822600
 1
 DOUBLER
21
 A5398104821200
 1
 ANGLE
22
 A5398104821300
 1
 ANGLE
23
 DAN5-6-6X
 14
 PIN
24
 DAN5-6-7X
 12
 PIN
25
 DAN5-6-4
 12
 PIN
26
 DAN5-6-6
 51
 PIN
27
 DAN5-6-7
 8
 PIN
28
 DAN7-6-9
 28
 PIN
29
 DAN12-6X
 120
 COLLAR
30
 DAN12-6
 84
 COLLAR
31
 EN6115K3-5
 14
 BOLT
32
 NSA5075-6
 88
 COLLAR
33
 ASNA2528-3
 14
 NUT
34
 DAN12-8X
 28
 COLLAR
35
 DAN8-6-7X
 66
 PIN
36
 DAN5-6-3
 17
 PIN
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 13
6
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SERVICE BULLETIN
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
37
 DAN8-6-7
 2
 PIN
38
 DAN8-6-8X
 28
 PIN
39
 DAN8-8-13X
 28
 PIN
40
 DAN7-6-7
 54
 PIN
41
 A5397823600295
 1
 FITTING
42
 A5397823700295
 1
 FITTING
43
 A5397823800295
 1
 FITTING
44
 A5397823900295
 1
 FITTING
45
 A5397824000295
 1
 FITTING
46
 A5397824100295
 1
 FITTING
47
 A5397824200295
 1
 FITTING
48
 A5397821320000
 7
 SHIM
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
Wash Primer - Structure
 04CMA2
 As required
Primer Polyurethane Paint -
Corrosion Inhibiting
04EAC2
 As required
Top Coat Polyurethane - External
Structure
04JAA3
 As required
Top Coat Polyurethane - Grey
Internal Structure
04JME4
 As required
Polysulfide Sealant - General
Purpose Interfay
06AAC1
 As required
Adhesion Promoter - For Polysulfide
Sealant
06PAG1
 As required
Non Aqueous Cleaner - General
 08BAA9
 As required
Corrosion Preventive Compound -
Water Displacing
12ABC1
 As required
Corrosion Preventive Compound-
Heavy Duty Soft Fil
12ACC1
 As required
 (1)
Textile - Lint Free Cotton
 14SBA1
 As required
NOTE
 (1)
: For Material No. 12ACC1 you can use Material No. 12ADB1 as an
alternative.
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 14
6
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SERVICE BULLETIN
(2) Components
None
(3) Equipment
None
E. PARTS TO BE RE-IDENTIFIED BY OPERATOR
None
F. TOOLING
(1) Tooling - Price and Availability
(a) Procurement Addresses
Operators interested in obtaining the Cold Working Tool Kits should contact:
Kit tool
 532141T01R00
Kit tool
 532141T02R00
Kit tool
 532141T03R00
AIRBUS Material, Logistics and Suppliers IFD
- In Flight Desk
Weg beim Jaeger 150
D-22335 HAMBURG
GERMANY
For ordering by internet:
http://spares.airbus.com
For ordering by fax: +49 40 50 76 4012
For ordering by E-mail:
ifd.spares@airbus.com
(b) Price and Availability
Kit tool
 532141T01R00
Cost
 12,670.00
 USD
Availability
 85 calendar days from receipt of order
Procurement to be negotiated directly with AIRBUS.
Kit tool
 532141T02R00
Cost
 2,150.00
 USD
Availability
 100 calendar days from receipt of order
Procurement to be negotiated directly with AIRBUS.
Kit tool
 532141T03R00
Cost
 70.00
 USD
Availability
 50 calendar days from receipt of order
Procurement to be negotiated directly with AIRBUS.
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 15
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(2) Tools
None
(3) Special Tools
AIRBUS has allocated the following tool numbers for cold expansion: For the definition
of capital, durable and expendable tools refer to ISI 51.48.00001.
NOTE
: The listed tools can be ordered as complete kits or as single parts to the
customer needs.
Kit tool 532141T01R00
ITEM
 PART N˚
 KEYWORD
 QTY
 SEE
NOTES
FT20
 POWERPAK
 1
FTBXA9
 BOX
 1
LB20
 PULLUNIT
 1
LBRA7
 PULLADAP
 1
NOTE
: Capital tooling: Kit Tool 532141T01R00
The capital tools provided in this kit are not specific to this Service
Bulletin and are normally already available in operators’ stock as a long-
term investment or can be loaned from AIRBUS. If the right angle
adapter extension in not available in the operators stock it can be
ordered separately.
Kit tool 532141T02R00
ITEM
 PART N˚
 KEYWORD
 QTY
 SEE
NOTES
CBCE73-044F
 CAPNOSE
 1
CBG4-4N1
 COMBIGAG
 1
CBM4-4N7-243V1
 MANDREL
 1
CBMG4-4N
 GAGEMAN
 1
CBR4-4NRA1860
 GAGEFINI
 1
CBSD4-4NRA
 DRILL
 1
CBSR4-4NRA
 REAMER
 1
FTBXC1
 BOX
 1
NOTE
: Durable tooling: Kit Tool 532141T02R00
The durable tool kit contains the minimum quantity of durable tools
necessary to accomplish the Service Bulletin on one aircraft. If the
Service Bulletin is to be accomplished on more than one aircraft, the
number of durable kits required can be established by reference to ISI
51.48.00001.
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 16
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Kit tool 532141T03R00
ITEM
 PART N˚
 KEYWORD
 QTY
 SEE
NOTES
CBS4-4N8F
 SLEEVE
 14
NOTE
: Expendable tooling: Kit Tool 532141T03R00
The expendable tool kit contains the quantity of expendable tools
required to accomplish the Service Bulletin on one aircraft. Order one
expendable tool kit for every aircraft on which this Service Bulletin is to
be accomplished.
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 17
6
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This Page Intentionally Left Blank
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 18
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3. ACCOMPLISHMENT INSTRUCTIONS
Task 532141-831-848-001 - Modification
WARNING
: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS
INCLUDED IN THE REFERENCED PROCEDURES.
CAUTION
: WHEN YOU OPEN AND CLOSE THE CARGO DOORS, MAKE SURE THAT
THE ACCESS PLATFORM IS AT THE CORRECT HEIGHT. IF IT IS TOO HIGH,
IT WILL PREVENT FREE MOVEMENT OF THE DOORS.
CAUTION
: MAKE SURE THAT THE AUTOMATIC ANTI-ROLL-OUT LATCHES ARE IN THE
FULLY UP POSITION BEFORE YOU CLOSE THE CARGO DOOR(S). IF THEY
ARE NOT, DAMAGE TO THE DOOR(S) CAN OCCUR.
CAUTION
: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP
ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY
AND MECHANICALLY SERVICEABLE) . WHEN YOU DO MAINTENANCE
WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,
COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO
THIS:
- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS
NECESSARY ON WIRING AND COMPONENTS.
- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND
OTHER CONTAMINATION.
- THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION
AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.
- IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.
NOTE
: The accomplishment instructions of this Service Bulletin refer to procedures
included in other AIRBUS documents. When the words ’refer to’ are used and the
operator has a procedure accepted by the local procedure he belongs to, the
accepted alternative procedure can be used. When the words ’in accordance with’
are used the given procedure must be followed.
NOTE
: The access and close-up instructions, not comprising return to service tests, in this
Service Bulletin do not constitute or affect the technical intent of the Service
Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or
close-up steps to add flexibility to their maintenance operations as long as the
technical intent of the Service Bulletin is met within the set parameters.
NOTE
: Manual titles given in the accomplishment instructions are referred to by acronyms.
Refer to paragraph 1.J., References, for the definition of acronyms.
NOTE
: This Service Bulletin is classified mandatory or expected to be classified mandatory
by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these
accomplishment instructions are Required for Compliance (RC) and must be done
to comply with the AD. Other paragraphs are recommended and may be deviated
from, done as part of other actions or done with accepted methods different from
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 19
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SERVICE BULLETIN
those given in the Service Bulletin, as long as the RC paragraphs can be done and
the aircraft can be put back into a serviceable condition.
Task Associated Data
**CONF 001
Zone
153
Access
Door
 811 812
Manpower
TOTAL MANHOURS
 47.00
ELAPSED TIME (HOURS)
 27.00
**CONF 002
Zone
153
Access
Door
 811 812
Manpower
TOTAL MANHOURS
 68.00
ELAPSED TIME (HOURS)
 40.00
**CONF ALL
A. GENERAL
**CONF 001
(1) Subtask 532141-910-201-001 - Standard Practices
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Maintenance Manual (AMM)
 06-21-00, Page Block 001
06-31-53, Page Block 001
06-41-00, Page Block 001
20-21-12, Page Block 001
Consumable Material List (CML)
Non Destructive Test Manual (NTM)
 51-10-01
Standards Manual (SM)
Structural Repair Manual (SRM)
 51-24-00
51-40-20
51-40-30
51-40-40
51-75-10
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 20
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SERVICE BULLETIN
(a) For the frame (FR) identification, refer to AMM 06-31-53, Page Block 001.
(b) For the identification of zones, refer to AMM 06-21-00, Page Block 001.
(c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001.
(d) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page
Block 001.
(e) Remove and install fasteners in accordance with SRM 51-40-20.
(f) Apply sealant in accordance with SRM 51-24-00.
(g) Renew the protective finish in accordance with SRM 51-75-10.
(h) Obtain fastener hole diameter and drill data in accordance with SRM 51-40-40.
(i) Obtain alternative and substitute fastener data in accordance with SRM 51-40-30.
(j) If alternative and substitute fasteners have to be used, you must make sure that the
associated nut/collar are compatible in accordance with SRM 51-40-00 ’Mating Part’
column.
(k) For the specification of materials (Mat. No.) given in this Service Bulletin refer to
Consumable Materials List (CML).
(l) Do the eddy current rotating probe test in accordance with NTM 51-10-01.
(m) Refer to the AIRBUS Standards Manual (SM) if you find numbers for the hardware
components which you cannot identify in the LIST OF COMPONENTS of this
Service Bulletin. The SM will give you the correct part number to part number
relation.
(n) 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.
(2) Subtask 532141-839-201-001 - 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 002
(1) Subtask 532141-910-201-001 - Standard Practices
Manpower Resources
Skills
 NON SPECIFIC
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 21
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References
Aircraft Maintenance Manual (AMM)
 06-21-00, Page Block 001
06-31-53, Page Block 001
06-41-00, Page Block 001
20-21-12, Page Block 001
Consumable Material List (CML)
Non Destructive Test Manual (NTM)
 51-10-01
Standards Manual (SM)
Structural Repair Manual (SRM)
 51-24-00
51-40-20
51-40-30
51-40-40
51-75-10
(a) For the frame (FR) identification, refer to AMM 06-31-53, Page Block 001.
(b) For the identification of zones, refer to AMM 06-21-00, Page Block 001.
(c) For the identification of access panels, refer to AMM 06-41-00, Page Block 001.
(d) To torque tighten the standard threaded fasteners, refer to AMM 20-21-12, Page
Block 001.
(e) Remove and install fasteners in accordance with SRM 51-40-20.
(f) Apply sealant in accordance with SRM 51-24-00.
(g) Renew the protective finish in accordance with SRM 51-75-10.
(h) Obtain fastener hole diameter and drill data in accordance with SRM 51-40-40.
(i) Obtain alternative and substitute fastener data in accordance with SRM 51-40-30.
(j) If alternative and substitute fasteners have to be used, you must make sure that the
associated nut/collar are compatible in accordance with SRM 51-40-00 ’Mating Part’
column.
(k) For the specification of materials (Mat. No.) given in this Service Bulletin refer to
Consumable Materials List (CML).
(l) Do the eddy current rotating probe test in accordance with NTM 51-10-01.
(m) Refer to the AIRBUS Standards Manual (SM) if you find numbers for the hardware
components which you cannot identify in the LIST OF COMPONENTS of this
Service Bulletin. The SM will give you the correct part number to part number
relation.
(n) 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.
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 22
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SERVICE BULLETIN
(2) Subtask 532141-839-201-001 - 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 532141-941-201-001 - Job Set-up
Manpower Resources
Skills
 AIRFRAME
References
Aircraft Maintenance Manual (AMM)
 24-00-00, Page Block 301
25-50-21, Page Block 401
25-52-22, Page Block 401
25-55-10, Page Block 201
52-30-00, Page Block 001
52-30-00, Page Block 501
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 system s 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 24-00-00, Page
Block 301.
(b) Open the Aft Cargo Compartment Door, refer to AMM 52-30-00, Page Block 001.
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 23
6
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SERVICE BULLETIN
(c) Put an access platform in position at the AFT cargo Compartment Door.
(d) Install the door actuator lock on the AFT Cargo Compartment Door actuator, refer
to AMM 52-30-00, Page Block 001 and refer to AMM 52-30-00, Page Block 501.
(e) Remove the linings 154CR, 154BR and 154AR of the AFT Cargo Compartment
Door frame, refer to AMM 25-55-10, Page Block 201.
(f) Remove the Ball Mats in the entrance area of the AFT Cargo Compartment, refer
to AMM 25-52-22, Page Block 401.
(g) Remove the insulation mats in the entrance area of the AFT Cargo Compartment,
refer to AMM 25-50-21, Page Block 401.
**CONF 002
(1) Subtask 532141-941-201-001 - Job Set-up
Manpower Resources
Skills
 AIRFRAME
References
Aircraft Maintenance Manual (AMM)
 24-00-00, Page Block 301
25-50-21, Page Block 401
25-52-22, Page Block 401
25-55-10, Page Block 201
52-30-00, Page Block 001
52-30-00, Page Block 501
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 system s 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 24-00-00, Page
Block 301.
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 24
6
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SERVICE BULLETIN
(b) Open the Aft Cargo Compartment Door, refer to AMM 52-30-00, Page Block 001.
(c) Put an access platform in position at the AFT cargo Compartment Door.
(d) Install the door actuator lock on the AFT Cargo Compartment Door actuator, refer
to AMM 52-30-00, Page Block 001 and refer to AMM 52-30-00, Page Block 501.
(e) Remove the linings 154CR, 154BR and 154AR of the AFT Cargo Compartment
Door frame, refer to AMM 25-55-10, Page Block 201.
(f) Remove the Ball Mats in the entrance area of the AFT Cargo Compartment, refer
to AMM 25-52-22, Page Block 401.
(g) Remove the insulation mats in the entrance area of the AFT Cargo Compartment,
refer to AMM 25-50-21, Page Block 401.
**CONF ALL
C. PROCEDURE
**CONF 001
(1) Subtask 532141-420-201-001 - Ins tall Reinforcement Doublers and Angles to the
Sill Beam and Main Frames/Cargo Floor Supports
Work Zones and Access Panels
Zone
 Access/Work location
153
 Access
 Door 812
Work location
 from Frame 60 to Frame 63
Stringer 45RH
Manpower Resources
Manhours
 40.00
Minimum number of person
 2
Subtask elapsed time
 20.00
Skills
 AIRFRAME
Material necessary to do the job
Kit 532141D01R00
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
1
 A5398104820000
 1
 ANGLE
2
 A5398104820100
 1
 ANGLE
3
 A5398104821600
 3
 DOUBLER
4
 A5398104821400
 3
 DOUBLER
5
 A5398104822000
 2
 DOUBLER
6
 A5398104821800
 2
 DOUBLER
7
 A5398104820200
 1
 ANGLE
8
 A5398104820300
 1
 ANGLE
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 25
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### Page 34

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SERVICE BULLETIN
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
9
 A5398104820400
 1
 ANGLE
10
 A5398104820500
 1
 ANGLE
11
 A5398104820600
 1
 ANGLE
12
 A5398104820700
 1
 ANGLE
13
 A5398104820800
 1
 ANGLE
14
 A5398104820900
 1
 ANGLE
15
 A5398104822400
 1
 DOUBLER
16
 A5398104822200
 1
 DOUBLER
17
 A5398104821000
 1
 ANGLE
18
 A5398104821100
 1
 ANGLE
19
 A5398104822800
 1
 DOUBLER
20
 A5398104822600
 1
 DOUBLER
21
 A5398104821200
 1
 ANGLE
22
 A5398104821300
 1
 ANGLE
23
 DAN5-6-6X
 14
 PIN
24
 DAN5-6-7X
 12
 PIN
25
 DAN5-6-4
 12
 PIN
26
 DAN5-6-6
 51
 PIN
27
 DAN5-6-7
 8
 PIN
28
 DAN7-6-9
 28
 PIN
29
 DAN12-6X
 26
 COLLAR
30
 DAN12-6
 28
 COLLAR
31
 EN6115K3-5
 14
 BOLT
32
 NSA5075-6
 71
 COLLAR
33
 ASNA2528-3
 14
 NUT
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Polysulfide Sealant -
General Purpose Interfay
06AAC1
 As required
Non Aqueous Cleaner -
General
08BAA9
 As required
Textile - Lint Free Cotton
 14SBA1
 As required
Kit tool 532141T01R00
ITEM
 PART N˚
 KEYWORD
 QTY
 SEE
NOTES
FT20
 POWERPAK
 1
FTBXA9
 BOX
 1
LB20
 PULLUNIT
 1
LBRA7
 PULLADAP
 1
NOTE
: Capital tooling: Kit Tool 532141T01R00
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 26
6
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SERVICE BULLETIN
The capital tools provided in this kit are not specific to this Service
Bulletin and are normally already available in operators’ stock as a long-
term investment or can be loaned from AIRBUS. If the right angle
adapter extension in not available in the operators stock it can be
ordered separately.
Kit tool 532141T02R00
ITEM
 PART N˚
 KEYWORD
 QTY
 SEE
NOTES
CBCE73-044F
 CAPNOSE
 1
CBG4-4N1
 COMBIGAG
 1
CBM4-4N7-243V1
 MANDREL
 1
CBMG4-4N
 GAGEMAN
 1
CBR4-4NRA1860
 GAGEFINI
 1
CBSD4-4NRA
 DRILL
 1
CBSR4-4NRA
 REAMER
 1
FTBXC1
 BOX
 1
NOTE
: Durable tooling: Kit Tool 532141T02R00
The durable tool kit contains the minimum quantity of durable tools
necessary to accomplish the Service Bulletin on one aircraft. If the
Service Bulletin is to be accomplished on more than one aircraft, the
number of durable kits required can be established by reference to ISI
51.48.00001.
Kit tool 532141T03R00
ITEM
 PART N˚
 KEYWORD
 QTY
 SEE
NOTES
CBS4-4N8F
 SLEEVE
 14
NOTE
: Expendable tooling: Kit Tool 532141T03R00
The expendable tool kit contains the quantity of expendable tools
required to accomplish the Service Bulletin on one aircraft. Order one
expendable tool kit for every aircraft on which this Service Bulletin is to
be accomplished.
References
Non Destructive Test Manual (NTM)
 51-10-01
53-17-33
Structural Repair Manual (SRM)
 51-10-00
51-24-00
51-40-21
51-40-40
51-40-41
51-40-44
51-40-50
53-17-18
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 27
6
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SERVICE BULLETIN
References
Fig. A-GBAAA
Reinforcement of the Lower AFT Cargo
Door Frame Structure
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
Sheet 07
Sheet 08
Sheet 09
Sheet 10
Sheet 11
Sheet 12
Sheet 13
Sheet 14
(a) Clean the installation area with:
Non Aqueous
Cleaner - General
08BAA9 As required
and
Textile - Lint Free
Cotton
14SBA1 As required
(b) Check the affected aircraft struct ure for cracks, other damages and applied repairs
in accordance with SRM 51-10-00, in accordance with SRM 53-17-18 and in
accordance with NTM 53-17-33.
NOTE
: Some aircraft have been repaired prior to the instruction of this
modification at single sill beam flag position by Repair and Design
Approval Sheets (RDAS). In these case the sill beam flag/sill
beam web interface reinforcement as per this modification is not
applicable. The repair by RDAS solution is considered sufficient
from the structural integrity point of view.
(c) Install the reinforcement doublers and angles to the sill beam and main
frames/cargo door support at FR60 as shown on Fig. A-GBAAA Sheet 01
 , Fig. A-
GBAAA Sheet 02
 , Fig. A-GBAAA Sheet 05
 , Fig. A-GBAAA Sheet 07
 and Fig. A-
GBAAA Sheet 14
.
1
 Remove from the sill beam and main frames/cargo door support in accordance
with SRM 51-40-21 and as shown on Fig. A-GBAAA Sheet 05
 :
4 Pin-Rivet DAN7-5A7 Item (9) Discard
7 Collar DAN12-5 Item (10) Discard
3 Pin-Rivet DAN7-5A4 Item (16) Discard
4 Rivet NSA5411-40-000 Item (17) Discard
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 28
6
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SERVICE BULLETIN
9 Rivet LN9198-4000CF Item (18) Discard
2 Pin-Rivet HL1012VF6-2 Item (19) Discard
2 Collar DAN12-6 Item (15) Discard
2
 Clean the work area with a none-metallic spatula and with:
Non Aqueous
Cleaner - General
08BAA9 As required
and
Textile - Lint Free
Cotton
14SBA1 As required
3
 Temporary put in position the doublers, item 3 and item 4 and angles, item 1
and item 2, on the sill beam and main frames/cargo floor supports as shown
on Fig. A-GBAAA Sheet 07
 .
4
 Check the edge margin of the fastener holes in accordance with SRM
51-40-50
5
 Transfer drill the existing fastener holes with a drill bush to a diameter
of 2.5mm (0.098in) from the main frames/cargo door supports to the
reinforcement doublers, item 3 and item 4.
6
 Transfer drill the existing fastener holes with a drill bush to a diameter of
2.5mm (0.098in) from the sill beam and main frames/cargo door supports to
the reinforcement angles, item 1 and item 2.
7
 Drill the two holes for the cold working to the diameter of between 4.29mm
(0.169in) and 4.34mm (0.171in) as shown on Fig. A-GBAAA Sheet 07
 and Fig.
A-GBAAA Sheet 14
.
8
 Remove the reinforcement doublers, item 3 and item 4.
9
 Deburr the two fastener holes for cold working.
10
 Remove the drill chippings from the installation area.
11
 Clean the installation areas with:
Non Aqueous
Cleaner - General
08BAA9 As required
and
Textile - Lint Free
Cotton
14SBA1 As required
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 29
6
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### Page 38

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SERVICE BULLETIN
12
 Do the cold working on the two fastener holes as shown on Fig. A-GBAAA
Sheet 07
 and Fig. A-GBAAA Sheet 14
 .
a
 Do a eddy current rotating probe inspection in the two fastener holes to
avoid crack propagation in accordance with NTM 51-10-01.
b
 Oversize the holes to the starting diameter in accordance with SRM
51-40-41.
Use tool list No.
FTBXC1
 BOX
 1
with
CBSD4-4NRA
 DRILL - STARTING
 1
CBSR4-4NRA
 REAMER -
STARTING
1
c
 Clean the installation area with:
Non Aqueous
Cleaner - General
08BAA9 As required
and
Textile - Lint Free
Cotton
14SBA1 As required
d
 Install the sleeves in accordance with SRM 51-40-41.
Use tool list No.
CBS4-4N8F
 SLEEVE
 2
NOTE
: The split within the installed split sleeve shall be aligned
inside the hole in accordance with Fig. A-GBAAA Sheet
07
. The permissible angular tolerance for the alignment of
the split is 10 degrees.
NOTE
: Ensure that the split sleeve length is at least 0.8 mm
(1/32 in) longer than the combined stack thickness to be
cold expanded.
Only one sleeve is allowed, it is not acceptable to
combine sleeves to achieve the length required.
e
 Do the cold expansion of the fastener holes in accordance with SRM
51-40-41
Use tool list No.
FTBXA9
 BOX
 1
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 30
6
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### Page 39

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SERVICE BULLETIN
with
FT20
 POWERPAK
 1
LB20
 PULLER UNIT
 1
LBRA7
 PULLER - 90 DEG
ADAPTER
1
and
FTBXC1
 BOX
 1
with
CBMG4-4N
 GAGE - MANDREL,
WEAR
1
CBM4-4N7-243V1
 MANDREL
 1
CBCE73-044F
 CAP - NOSE
 1
f
 Remove the sleeves.
g
 Ream the holes to the final diameter between 4.723mm (0.186in) and
4.745mm (0.187in) in accordance with SRM 51-40-40 and Fig. A-GBAAA
Sheet 07
 and Fig. A-GBAAA Sheet 14
 .
Use tool list No.
FTBXC1
 BOX
 1
with
CBG4-4N1
 GAGE -
COMBINATION
1
CBR4-4NRA1860
 GAGE - FINISH
REAMER
1
NOTE
: Holes shall be free of damage, spiral ridges, cuts and
reamer removal markings. A last reaming pass will be 0.2
mm as maximum.
NOTE
: It is permissible for a post reamed hole to exhibit a region
at hole entry, exit or interface that does not clean up
(partial ridge remains in hole). A hole in this condition is
considered to be acceptable providing the total length of
the ridge does not exceed 0.5 mm (0.197 in).
13
 Install the reinforcement doublers, item 3 and item 4.
14
 Drill all the fastener holes to the final diameter as shown on Fig. A-GBAAA
Sheet 07
 and Fig. A-GBAAA Sheet 14
 and in accordance with SRM 51-40-44.
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 31
6
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### Page 40

@A310
SERVICE BULLETIN
15
 Remove the reinforcement doublers, item 3 and item 4 and the angles, item 1
and item 2.
16
 Deburr the fastener holes.
17
 Clean the installation area and the reinforcement doublers, item 3 and item 4
and angles, item 1 and item 2 with:
Non Aqueous
Cleaner - General
08BAA9 As required
and
Textile - Lint Free
Cotton
14SBA1 As required
18
 Apply to the faying surfaces of the structure parts in accordance with SRM
51-24-00.
Polysulfide Sealant
- General Purpose
Interfay
06AAC1 As required
19
 Install to the sill beam and main frames/cargo door supports at FR60 as
shown on Fig. A-GBAAA Sheet 07
 and Fig. A-GBAAA Sheet 14
 and in
accordance with SRM 51-40-21:
1 Angle A5398104820000 Item 1
1 Angle A5398104820100 Item 2
1 Doubler A5398104821600 Item 3
1 Doubler A5398104821400 Item 4
with
3 Pin DAN5-6-4 Item 25
6 Pin DAN5-6-6 Item 26
2 Pin DAN5-6-7 Item 27
11 Collar NSA5075-6 Item 32
3 Pin DAN5-6-7X Item 24
2 Pin DAN5-6-6X Item 23
5 Collar DAN12-6X Item 29
2 Bolt EN6115K3-5 Item 31
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 32
6
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### Page 41

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SERVICE BULLETIN
2 Nut ASNA2528-3 Item 33
4 Pin DAN7-6-9 Item 28
4 Collar DAN12-6 Item 30
20
 Remove unwanted sealant from the installation area.
(d) Install the reinforcement doublers and angles to the sill beam and main
frames/cargo door supports at FR60A as shown on Fig. A-GBAAA Sheet 01
 , Fig.
A-GBAAA Sheet 02
 , Fig. A-GBAAA Sheet 06
 , Fig. A-GBAAA Sheet 08
 and Fig. A-
GBAAA Sheet 14
.
1
 Remove from the sill beam and main frames/cargo door support in accordance
with SRM 51-40-21 and as shown on Fig. A-GBAAA Sheet 06
 :
4 Pin-Rivet DAN7-5A7 Item (9) Discard
4 Collar DAN12-5 Item (10) Discard
7 Rivet NSA5411-40-000 Item (17) Discard
2 Pin-Rivet HL1012VF6-2 Item (19) Discard
2 Collar DAN12-6 Item (15) Discard
2
 Clean the work area with a none-metallic spatula and with:
Non Aqueous
Cleaner - General
08BAA9 As required
and
Textile - Lint Free
Cotton
14SBA1 As required
3
 Temporary put in position the doublers, item 5 and item 6 and angles, item 7
and item 8 on the sill beam and main frames/cargo floor supports as shown
on Fig. A-GBAAA Sheet 08
 .
4
 Check the edge margin of the fastener holes in accordance with SRM
51-40-50
5
 Transfer drill the pilot holes to a diameter of 2.5mm (0.098in) from the
reinforcement doublers, item 5 and item 6 to the main frames/cargo door
supports.
6
 Transfer drill the existing fastener holes with a drill bush to a diameter
of 2.5mm (0.098in) from the main frames/cargo door supports to the
reinforcement doublers, item 5 and item 6.
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 33
6
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### Page 42

@A310
SERVICE BULLETIN
7
 Transfer drill the existing fastener holes with a drill bush to a diameter of
2.5mm (0.098in) from the sill beam and main frames/cargo door supports to
the reinforcement angles, item 7 and item 8.
8
 Drill the two holes for the cold working to the diameter between 4.29mm
(0.169in) and 4.34mm (0.171in) as shown on Fig. A-GBAAA Sheet 08
 and Fig.
A-GBAAA Sheet 14
.
9
 Remove the reinforcement doublers, item 5 and item 6.
10
 Deburr the two fastener holes for cold working.
11
 Remove the drill chippings from the installation area.
12
 Clean the installation areas with:
Non Aqueous
Cleaner - General
08BAA9 As required
and
Textile - Lint Free
Cotton
14SBA1 As required
13
 Do the cold working on the two fastener holes as shown on Fig. A-GBAAA
Sheet 08
 and Fig. A-GBAAA Sheet 14
 .
a
 Do a eddy current rotating probe inspection in the two fastener holes to
avoid crack propagation in accordance with NTM 51-10-01.
b
 Oversize the holes to the starting diameter in accordance with SRM
51-40-41.
Use tool list No.
FTBXC1
 BOX
 1
with
CBSD4-4NRA
 DRILL - STARTING
 1
CBSR4-4NRA
 REAMER -
STARTING
1
c
 Clean the installation areas with:
Non Aqueous
Cleaner - General
08BAA9 As required
and
Textile - Lint Free
Cotton
14SBA1 As required
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 34
6
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### Page 43

@A310
SERVICE BULLETIN
d
 Install the sleeves in accordance with SRM 51-40-41
Use tool list No.
CBS4-4N8F
 SLEEVE
 2
NOTE
: The split within the installed split sleeve shall be aligned
inside the hole in accordance with Fig. A-GBAAA Sheet
08
. The permissible angular tolerance for the alignment of
the split is 10 degrees.
NOTE
: Ensure that the split sleeve length is at least 0.8 mm
(1/32 in) longer than the combined stack thickness to be
cold expanded.
Only one sleeve is allowed, it is not acceptable to
combine sleeves to achieve the length required.
e
 Do the cold expansion of the fastener holes in accordance with SRM
51-40-41
Use tool list No.
FTBXA9
 BOX
 1
with
FT20
 POWERPAK
 1
LB20
 PULLER UNIT
 1
LBRA7
 PULLER - 90 DEG
ADAPTER
1
and
FTBXC1
 BOX
 1
with
CBMG4-4N
 GAGE - MANDREL,
WEAR
1
CBM4-4N7-243V1
 MANDREL
 1
CBCE73-044F
 CAP - NOSE
 1
f
 Remove the sleeves.
g
 Ream the to holes to the final diameter between 4.723mm (0.186in) and
4.745mm (0.187in) in accordance with SRM 51-40-40.
Use tool list No.
FTBXC1
 BOX
 1
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 35
6
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### Page 44

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SERVICE BULLETIN
with
CBG4-4N1
 GAGE -
COMBINATION
1
CBR4-4NRA1860
 GAGE - FINISH
REAMER
1
NOTE
: Holes shall be free of damage, spiral ridges, cuts and
reamer removal markings. A last reaming pass will be 0.2
mm as maximum.
NOTE
: It is permissible for a post reamed hole to exhibit a region
at hole entry, exit or interface that does not clean up
(partial ridge remains in hole). A hole in this condition is
considered to be acceptable providing the total length of
the ridge does not exceed 0.5 mm (0.197 in).
14
 Install the reinforcement doublers, item 5 and item 6 as shown on Fig. A-
GBAAA Sheet 08
 and Fig. A-GBAAA Sheet 14
 .
15
 Drill the fastener holes to the final diameter and in accordance with SRM
51-40-44.
16
 Remove the reinforcement doublers, item 5 and item 6 and angles, item 7 and
item 8.
17
 Deburr the fastener holes.
18
 Clean the installation area and the reinforcement doublers, item 5 and item 6
and angles, item 7 and item 8 with:
Non Aqueous
Cleaner - General
08BAA9 As required
and
Textile - Lint Free
Cotton
14SBA1 As required
19
 Apply to the faying surfaces of the structure parts in accordance with SRM
51-24-00.
Polysulfide Sealant
- General Purpose
Interfay
06AAC1 As required
20
 Install to the sill beam and main frames/cargo door supports at FR60A as
shown in Fig. A-GBAAA Sheet 08
 and Fig. A-GBAAA Sheet 14
 and in
accordance with SRM 51-40-21:
1 Angle A5398104820200 Item 7
1 Angle A5398104820300 Item 8
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 36
6
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### Page 45

@A310
SERVICE BULLETIN
1 Doubler A5398104822000 Item 5
1 Doubler A5398104821800 Item 6
with
9 Pin DAN5-6-6 Item 26
9 Collar NSA5075-6 Item 32
2 Bolt EN6115K3-5 Item 31
2 Nut ASNA2528-3 Item 33
2 Pin DAN5-6-6X Item 23
2 Collar DAN12-6X Item 29
4 Pin DAN7-6-9 Item 28
4 Collar DAN12-6 Item 30
21
 Remove unwanted sealant from the installation area.
(e) Install the reinforcement doublers and angles to the sill beam and main
frames/cargo door supports at FR61 as shown on Fig. A-GBAAA Sheet 01
 , Fig. A-
GBAAA Sheet 03
 , Fig. A-GBAAA Sheet 05
 , Fig. A-GBAAA Sheet 09
 and Fig. A-
GBAAA Sheet 14
.
1
 Remove from the sill beam and main frames/cargo door support in accordance
with SRM 51-40-21 and as shown on Fig. A-GBAAA Sheet 05
 :
4 Pin-Rivet DAN7-5A7 Item (9) Discard
7 Collar DAN12-5 Item (10) Discard
3 Pin-Rivet DAN7-5A4 Item (16) Discard
4 Rivet NSA5411-40-000 Item (17) Discard
9 Rivet LN9198-4000CF Item (18) Discard
2 Pin-Rivet HL1012VF6-2 Item (19) Discard
2 Collar DAN12-6 Item (15) Discard
2
 Clean the working area with a none-metallic spatula and with:
Non Aqueous
Cleaner - General
08BAA9 As required
and
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 37
6
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### Page 46

@A310
SERVICE BULLETIN
Textile - Lint Free
Cotton
14SBA1 As required
3
 Temporary put in position the doublers and angles on the sill beam and main
frames/cargo floor supports as shown on Fig. A-GBAAA Sheet 09
 and Fig. A-
GBAAA Sheet 14
.
4
 Check the edge margin of the fastener holes in accordance with SRM
51-40-50
5
 Transfer drill the existing fastener holes with a drill bush to a diameter
of 2.5mm (0.098in) from the main frames/cargo door supports to the
reinforcement doublers, item 3 and item 4.
6
 Transfer drill the existing fastener holes with a drill bush to a diameter of
2.5mm (0.098in) from the sill beam and main frames/cargo door supports to
the reinforcement angles, item 9 and item 10.
7
 Drill the two holes for the cold working to the diameter between 4.29mm
(0.169in) and 4.34mm (0.171in) as shown on Fig. A-GBAAA Sheet 09
 and Fig.
A-GBAAA Sheet 14
.
8
 Remove the reinforcement doublers, item 3 and item 4.
9
 Deburr the two fastener holes for cold working.
10
 Remove the drill chippings from the installation area.
11
 Clean the installation areas with:
Non Aqueous
Cleaner - General
08BAA9 As required
and
Textile - Lint Free
Cotton
14SBA1 As required
12
 Do the cold working on the two fastener holes as shown on Fig. A-GBAAA
Sheet 09
 and Fig. A-GBAAA Sheet 14
 .
a
 Do a eddy current rotating probe inspection in the two fastener holes to
avoid crack propagation in accordance with NTM 51-10-01.
b
 Oversize the holes to the starting diameter in accordance with SRM
51-40-41.
Use tool list No.
FTBXC1
 BOX
 1
with
CBSD4-4NRA
 DRILL - STARTING
 1
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 38
6
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### Page 47

@A310
SERVICE BULLETIN
CBSR4-4NRA
 REAMER -
STARTING
1
c
 Clean the installation areas with:
Non Aqueous
Cleaner - General
08BAA9 As required
and
Textile - Lint Free
Cotton
14SBA1 As required
d
 Install the sleeves in accordance with SRM 51-40-41.
Use tool list No.
CBS4-4N8F
 SLEEVE
 2
NOTE
: The split within the installed split sleeve shall be aligned
inside the hole in accordance with Fig. A-GBAAA Sheet
09
. The permissible angular tolerance for the alignment of
the split is 10 degrees.
NOTE
: Ensure that the split sleeve length is at least 0.8 mm
(1/32 in) longer than the combined stack thickness to be
cold expanded.
Only one sleeve is allowed, it is not acceptable to
combine sleeves to achieve the length required.
e
 Do the cold expansion of the fastener holes in accordance with SRM
51-40-41.
Use tool list No.
FTBXA9
 BOX
 1
with
FT20
 POWERPAK
 1
LB20
 PULLER UNIT
 1
LBRA7
 PULLER - 90 DEG
ADAPTER
1
and
FTBXC1
 BOX
 1
with
CBMG4-4N
 GAGE - MANDREL,
WEAR
1
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 39
6
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### Page 48

@A310
SERVICE BULLETIN
CBM4-4N7-243V1
 MANDREL
 1
CBCE73-044F
 CAP - NOSE
 1
f
 Remove the sleeves.
g
 Ream the to holes to the final hole diameter between 4.723mm (0.186in)
and 4.745mm (0.187in) in accordance with SRM 51-40-40 and as shown
on Fig. A-GBAAA Sheet 09
 and Fig. A-GBAAA Sheet 14
 .
Use tool list No.
FTBXC1
 BOX
 1
with
CBG4-4N1
 GAGE -
COMBINATION
1
CBR4-4NRA1860
 GAGE - FINISH
REAMER
1
NOTE
: Holes shall be free of damage, spiral ridges, cuts and
reamer removal markings. A last reaming pass will be 0.2
mm as maximum.
NOTE
: It is permissible for a post reamed hole to exhibit a region
at hole entry, exit or interface that does not clean up
(partial ridge remains in hole). A hole in this condition is
considered to be acceptable providing the total length of
the ridge does not exceed 0.5 mm (0.197 in).
13
 Install the reinforcement doublers, item 3 and item 4.
14
 Drill all the fastener holes to the final diameter and in accordance with SRM
51-40-44.
15
 Remove the reinforcement doublers, item 3 and item 4 and angles, item 9 and
item 10.
16
 Deburr the fastener holes.
17
 Clean the installation area and the reinforcement doublers, item 3 and item 4
and angles, item 9 and item 10 with:
Non Aqueous
Cleaner - General
08BAA9 As required
and
Textile - Lint Free
Cotton
14SBA1 As required
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 40
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 49

@A310
SERVICE BULLETIN
18
 Apply to the faying surfaces of the structure parts in accordance with SRM
51-24-00.
Polysulfide Sealant
- General Purpose
Interfay
06AAC1 As required
19
 Install to the sill beam and main frames/cargo door supports at FR61 as
shown on Fig. A-GBAAA Sheet 09
 and Fig. A-GBAAA Sheet 14
 and in
accordance with SRM 51-40-21:
1 Angle A5398104820400 Item 9
1 Angle A5398104820500 Item 10
1 Doubler A5398104821600 Item 3
1 Doubler A5398104821400 Item 4
with
3 Pin DAN5-6-4 Item 25
6 Pin DAN5-6-6 Item 26
2 Pin DAN5-6-7 Item 27
11 Collar NSA5075-6 Item 32
3 Pin DAN5-6-7X Item 24
2 Pin DAN5-6-6X Item 23
5 Collar DAN12-6X Item 29
2 Bolt EN6115K3-5 Item 31
2 Nut ASNA2528-3 Item 33
4 Pin DAN7-6-9 Item 28
4 Collar DAN12-6 Item 30
20
 Remove unwanted sealant from the installation area.
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 41
6
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### Page 50

@A310
SERVICE BULLETIN
(f) Install the reinforcement doublers and angles to the sill beam and main
frames/cargo door supports at FR61A as shown on Fig. A-GBAAA Sheet 01
 , Fig.
A-GBAAA Sheet 03
 , Fig. A-GBAAA Sheet 06
 . Fig. A-GBAAA Sheet 10
 and Fig. A-
GBAAA Sheet 14
.
1
 Remove from the sill beam and main frames/cargo door support in accordance
with SRM 51-40-21 and as shown on Fig. A-GBAAA Sheet 06
 :
4 Pin-Rivet DAN7-5A7 Item (9) Discard
4 Collar DAN12-5 Item (10) Discard
7 Rivet NSA5411-40-000 Item (17) Discard
2 Pin-Rivet HL1012VF6-2 Item (19) Discard
2 Collar DAN12-6 Item (15) Discard
2
 Clean the working area with a none-metallic spatula and with:
Non Aqueous
Cleaner - General
08BAA9 As required
and
Textile - Lint Free
Cotton
14SBA1 As required
3
 Temporary put in position the doublers, item 5 and item 6 and angles, item 11
and item 12 on the sill beam and main frames/cargo floor supports as shown
on Fig. A-GBAAA Sheet 10
 and Fig. A-GBAAA Sheet 14
 .
4
 Check the edge margin of the fastener holes in accordance with SRM
51-40-50
5
 Transfer drill the existing faster holes with a drill bush to a diameter of 2.5mm
(0.098in) from the main frames/cargo door supports to the reinforcement
doublers, item 5 and item 6.
6
 Transfer drill the pilot holes to a diameter of 2.5mm (0.098in) from the
reinforcement doublers, item 5 and item 6 to the main frames/cargo door
supports.
7
 Transfer drill the existing faster holes with a drill bush to a diameter of 2.5mm
(0.098in) from the sill beam and main frames/cargo door supports to the
reinforcement angles, item 11 and item 12.
8
 Drill the two holes for the cold working to the diameter between 4.29mm
(0.169in) and 4.34mm (0.171in) as shown on Fig. A-GBAAA Sheet 10
 and Fig.
A-GBAAA Sheet 14
.
9
 Remove the reinforcement doublers, item 5 and item 6.
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 42
6
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### Page 51

@A310
SERVICE BULLETIN
10
 Deburr the two fastener holes for cold working.
11
 Remove the drill chippings from the installation area.
12
 Clean the installation areas with:
Non Aqueous
Cleaner - General
08BAA9 As required
and
Textile - Lint Free
Cotton
14SBA1 As required
13
 Do the cold working on the two fastener holes.
a
 Do a eddy current rotating probe inspection in the two fastener holes to
avoid crack propagation in accordance with NTM 51-10-01.
b
 Oversize the holes to the starting diameter in accordance with SRM
51-40-41 an refer to Fig. A-GBAAA Sheet 10
 and Fig. A-GBAAA Sheet
14
.
Use tool list No.
FTBXC1
 BOX
 1
with
CBSD4-4NRA
 DRILL - STARTING
 1
CBSR4-4NRA
 REAMER -
STARTING
1
c
 Clean the installation areas with:
Non Aqueous
Cleaner - General
08BAA9 As required
and
Textile - Lint Free
Cotton
14SBA1 As required
d
 Install the sleeves in accordance with SRM 51-40-41
Use tool list No.
CBS4-4N8F
 SLEEVE
 2
NOTE
: The split within the installed split sleeve shall be aligned
inside the hole in accordance with Fig. A-GBAAA Sheet
10
. The permissible angular tolerance for the alignment of
the split is 10 degrees.
NOTE
: Ensure that the split sleeve length is at least 0.8 mm
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 43
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 52

@A310
SERVICE BULLETIN
(1/32 in) longer than the combined stack thickness to be
cold expanded.
Only one sleeve is allowed, it is not acceptable to
combine sleeves to achieve the length required.
e
 Do the cold expansion of the fastener holes in accordance with SRM
51-40-41
Use tool list No.
FTBXA9
 BOX
 1
with
FT20
 POWERPAK
 1
LB20
 PULLER UNIT
 1
LBRA7
 PULLER - 90 DEG
ADAPTER
1
and
FTBXC1
 BOX
 1
with
CBMG4-4N
 GAGE - MANDREL,
WEAR
1
CBM4-4N7-243V1
 MANDREL
 1
CBCE73-044F
 CAP - NOSE
 1
f
 Remove the sleeves.
g
 Ream the to holes to the final hole diameter between 4.723mm (0.186in)
and 4.745mm (0.187in) in accordance with SRM 51-40-40.
Use tool list No.
FTBXC1
 BOX
 1
with
CBG4-4N1
 GAGE -
COMBINATION
1
CBR4-4NRA1860
 GAGE - FINISH
REAMER
1
NOTE
: Holes shall be free of damage, spiral ridges, cuts and
reamer removal markings. A last reaming pass will be 0.2
mm as maximum.
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 44
6
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### Page 53

@A310
SERVICE BULLETIN
NOTE
: It is permissible for a post reamed hole to exhibit a region
at hole entry, exit or interface that does not clean up
(partial ridge remains in hole). A hole in this condition is
considered to be acceptable providing the total length of
the ridge does not exceed 0.5 mm (0.197 in).
14
 Install the reinforcement doublers, item 5 and item 6 as shown on Fig. A-
GBAAA Sheet 10
 and Fig. A-GBAAA Sheet 14
 .
15
 Drill the fastener holes to the final diameter and in accordance with SRM
51-40-44.
16
 Remove the reinforcement doublers, item 5 and item 6 and angles, item 11
and item 12.
17
 Deburr the fastener holes.
18
 Clean the installation area and the reinforcement doublers, item 5 and item 6
and angles, item 11 and item 12 with:
Non Aqueous
Cleaner - General
08BAA9 As required
and
Textile - Lint Free
Cotton
14SBA1 As required
19
 Apply to the faying surfaces of the structure parts in accordance with SRM
51-24-00.
Polysulfide Sealant
- General Purpose
Interfay
06AAC1 As required
20
 Install to the sill beam and main frames/cargo door supports at FR61A as
shown on Fig. A-GBAAA Sheet 10
 and Fig. A-GBAAA Sheet 14
 and in
accordance with SRM 51-40-21:
1 Angle A5398104820600 Item 11
1 Angle A5398104820700 Item 12
1 Doubler A5398104822000 Item 5
1 Doubler A5398104821800 Item 6
with
9 Pin DAN5-6-6 Item 26
9 Collar NSA5075-6 Item 32
2 Bolt EN6115K3-5 Item 31
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 45
6
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### Page 54

@A310
SERVICE BULLETIN
2 Nut ASNA2528-3 Item 33
2 Pin DAN5-6-6X Item 23
2 Collar DAN12-6X Item 29
4 Pin DAN7-6-9 Item 28
4 Collar DAN12-6 Item 30
21
 Remove unwanted sealant from the installation area.
(g) Install the reinforcement doublers and angles to the sill beam and main
frames/cargo door supports at FR62 as shown on Fig. A-GBAAA Sheet 01
 , Fig. A-
GBAAA Sheet 03
 , Fig. A-GBAAA Sheet 05
 , Fig. A-GBAAA Sheet 11
 and Fig. A-
GBAAA Sheet 14
.
1
 Remove from the sill beam and main frames/cargo door support in accordance
with SRM 51-40-21 and as shown on Fig. A-GBAAA Sheet 05
 :
4 Pin-Rivet DAN7-5A7 Item (9) Discard
7 Collar DAN12-5 Item (10) Discard
3 Pin-Rivet DAN7-5A4 Item (16) Discard
5 Rivet NSA5411-40-000 Item (17) Discard
9 Rivet LN9198-4000CF Item (18) Discard
2 Pin-Rivet HL1012VF6-2 Item (19) Discard
2 Collar DAN12-6 Item (15) Discard
2
 Clean the working area with a none-metallic spatula and with:
Non Aqueous
Cleaner - General
08BAA9 As required
and
Textile - Lint Free
Cotton
14SBA1 As required
3
 Temporary put in position the doublers, item 3 and item 4 and angles, item 13
and 14 on the sill beam and main frames/cargo floor supports as shown on
Fig. A-GBAAA Sheet 11
 .
4
 Check the edge margin of the fastener holes in accordance with SRM
51-40-50
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 46
6
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### Page 55

@A310
SERVICE BULLETIN
5
 Transfer drill the existing faster holes with a drill bush to a diameter of 2.5mm
(0.098in) from the main frames/cargo door supports to the reinforcement
doublers, item 3 and item 4.
6
 Transfer drill the existing faster holes with a drill bush to a diameter of 2.5mm
(0.098in) from the sill beam and main frames/cargo door supports to the
reinforcement angles, item 13 and item 14.
7
 Drill the two holes for the cold working to the diameter between 4.29mm
(0.169in) and 4.34mm (0.171in) as shown on Fig. A-GBAAA Sheet 11
 and Fig.
A-GBAAA Sheet 14
8
 Remove the reinforcement doublers, item 3 and item 4.
9
 Deburr the two fastener holes for cold working.
10
 Remove the drill chippings from the installation area.
11
 Clean the installation areas with:
Non Aqueous
Cleaner - General
08BAA9 As required
and
Textile - Lint Free
Cotton
14SBA1 As required
12
 Do the cold working on the two fastener holes as shown on Fig. A-GBAAA
Sheet 11
 and Fig. A-GBAAA Sheet 14
 .
a
 Do a eddy current rotating probe inspection in the two fastener holes to
avoid crack propagation in accordance with NTM 51-10-01.
b
 Oversize the holes to the starting diameter in accordance with SRM
51-40-41.
Use tool list No.
FTBXC1
 BOX
 1
with
CBSD4-4NRA
 DRILL - STARTING
 1
CBSR4-4NRA
 REAMER -
STARTING
1
c
 Clean the installation areas with:
Non Aqueous
Cleaner - General
08BAA9 As required
and
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 47
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 56

@A310
SERVICE BULLETIN
Textile - Lint Free
Cotton
14SBA1 As required
d
 Install the sleeves in accordance with SRM 51-40-41
Use tool list No.
CBS4-4N8F
 SLEEVE
 2
NOTE
: The split within the installed split sleeve shall be aligned
inside the hole in accordance with Fig. A-GBAAA Sheet
11
. The permissible angular tolerance for the alignment of
the split is 10 degrees.
NOTE
: Ensure that the split sleeve length is at least 0.8 mm
(1/32 in) longer than the combined stack thickness to be
cold expanded.
Only one sleeve is allowed, it is not acceptable to
combine sleeves to achieve the length required.
e
 Do the cold expansion of the fastener holes in accordance with SRM
51-40-41
Use tool list No.
FTBXA9
 BOX
 1
with
FT20
 POWERPAK
 1
LB20
 PULLER UNIT
 1
LBRA7
 PULLER - 90 DEG
ADAPTER
1
and
FTBXC1
 BOX
 1
with
CBMG4-4N
 GAGE - MANDREL,
WEAR
1
CBM4-4N7-243V1
 MANDREL
 1
CBCE73-044F
 CAP - NOSE
 1
f
 Remove the sleeves.
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 48
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 57

@A310
SERVICE BULLETIN
g
 Ream the to holes to the final diameter between 4.723mm (0.186in) and
4.745mm (0.187in) in accordance with SRM 51-40-40 and as shown on
Fig. A-GBAAA Sheet 11
 and Fig. A-GBAAA Sheet 14
 .
Use tool list No.
FTBXC1
 BOX
 1
with
CBG4-4N1
 GAGE -
COMBINATION
1
CBR4-4NRA1860
 GAGE - FINISH
REAMER
1
NOTE
: Holes shall be free of damage, spiral ridges, cuts and
reamer removal markings. A last reaming pass will be 0.2
mm as maximum.
NOTE
: It is permissible for a post reamed hole to exhibit a region
at hole entry, exit or interface that does not clean up
(partial ridge remains in hole). A hole in this condition is
considered to be acceptable providing the total length of
the ridge does not exceed 0.5 mm (0.197 in).
13
 Install the reinforcement doublers item 3 and item 4 as shown on Fig. A-
GBAAA Sheet 11
 and Fig. A-GBAAA Sheet 14
 .
14
 Drill all the fastener holes to the final diameter in accordance with SRM
51-40-44.
15
 Remove the reinforcement doublers, item 3 and item 4 and angles, item 13
and item 14.
16
 Deburr the fastener holes.
17
 Clean the installation area and the reinforcement doublers, item 3 and item 4
and angles, item 13 and item 14 with:
Non Aqueous
Cleaner - General
08BAA9 As required
and
Textile - Lint Free
Cotton
14SBA1 As required
18
 Apply to the faying surfaces of the structure parts in accordance with SRM
51-24-00.
Polysulfide Sealant
- General Purpose
Interfay
06AAC1 As required
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 49
6
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### Page 58

@A310
SERVICE BULLETIN
19
 Install to the sill beam and main frames/cargo door supports at FR62 as
shown on Fig. A-GBAAA Sheet 11
 and Fig. A-GBAAA Sheet 14
 and in
accordance with SRM 51-40-21:
1 Angle A5398104820800 Item 13
1 Angle A5398104820900 Item 14
1 Doubler A5398104821600 Item 3
1 Doubler A5398104821400 Item 4
with
3 Pin DAN5-6-4 Item 25
6 Pin DAN5-6-6 Item 26
2 Pin DAN5-6-7 Item 27
11 Collar NSA5075-6 Item 32
3 Pin DAN5-6-7X Item 24
2 Pin DAN5-6-6X Item 23
5 Collar DAN12-6X Item 29
2 Bolt EN6115K3-5 Item 31
2 Nut ASNA2528-3 Item 33
4 Pin DAN7-6-9 Item 28
4 Collar DAN12-6 Item 30
20
 Remove unwanted sealant from the installation area.
(h) Install the reinforcement doublers and angles to the sill beam and main
frames/cargo door supports at FR62A as shown on Fig. A-GBAAA Sheet 01
 , Fig.
A-GBAAA Sheet 04
 , Fig. A-GBAAA Sheet 06
 , Fig. A-GBAAA Sheet 12
 and Fig. A-
GBAAA Sheet 14
.
1
 Remove from the sill beam and main frames/cargo door support in accordance
with SRM 51-40-21 and as shown on Fig. A-GBAAA Sheet 06
 :
4 Pin-Rivet DAN7-5A7 Item (9) Discard
4 Collar DAN12-5 Item (10) Discard
7 Rivet NSA5411-40-000 Item (17) Discard
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 50
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 59

@A310
SERVICE BULLETIN
2 Pin-Rivet HL1012VF6-2 Item (19) Discard
2 Collar DAN12-6 Item (15) Discard
2
 Clean the working area with a none-metallic spatula and with:
Non Aqueous
Cleaner - General
08BAA9 As required
and
Textile - Lint Free
Cotton
14SBA1 As required
3
 Temporary put in position the doublers, item 15 and 16 and angles on the sill
beam and main frames/cargo floor supports as shown on Fig. A-GBAAA Sheet
12
.
4
 Check the edge margin of the fastener holes in accordance with SRM
51-40-50
5
 Transfer drill the pilot holes to a diameter of 2.5mm (0.098in) from the
reinforcement doublers, item 15 and item 16 to the main frames/cargo door
supports.
6
 Transfer drill the existing fastener holes with a drill bush to a diameter
of 2.5mm (0.098in) from the main frames/cargo door supports to the
reinforcement doublers, item 15 and item 16.
7
 Transfer drill the existing fastener holes with a drill bush to a diameter of
2.5mm (0.098in) from the sill beam and main frames/cargo door supports the
reinforcement angles, item 17 and item 18.
8
 Drill the two holes for the cold working to the diameter between 4.29mm
(0.169in) and 4.34mm (0.171in) as shown on Fig. A-GBAAA Sheet 12
 and Fig.
A-GBAAA Sheet 14
.
9
 Remove the reinforcement doublers, item 15 and item 16.
10
 Deburr the two fastener holes for cold working.
11
 Remove the drill chippings from the installation area.
12
 Clean the installation areas with:
Non Aqueous
Cleaner - General
08BAA9 As required
and
Textile - Lint Free
Cotton
14SBA1 As required
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 51
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 60

@A310
SERVICE BULLETIN
13
 Do the cold working on the two fastener holes as shown on Fig. A-GBAAA
Sheet 12
 and Fig. A-GBAAA Sheet 14
 .
a
 Do a eddy current rotating probe inspection in the two fastener holes to
avoid crack propagation in accordance with NTM 51-10-01.
b
 Oversize the holes to the starting diameter in accordance with SRM
51-40-41.
Use tool list No.
FTBXC1
 BOX
 1
with
CBSD4-4NRA
 DRILL - STARTING
 1
CBSR4-4NRA
 REAMER -
STARTING
1
c
 Clean the installation areas with:
Non Aqueous
Cleaner - General
08BAA9 As required
and
Textile - Lint Free
Cotton
14SBA1 As required
d
 Install the sleeves in accordance with SRM 51-40-41
Use tool list No.
CBS4-4N8F
 SLEEVE
 2
NOTE
: The split within the installed split sleeve shall be aligned
inside the hole in accordance with Fig. A-GBAAA Sheet
12
. The permissible angular tolerance for the alignment of
the split is 10 degrees.
NOTE
: Ensure that the split sleeve length is at least 0.8 mm
(1/32 in) longer than the combined stack thickness to be
cold expanded.
Only one sleeve is allowed, it is not acceptable to
combine sleeves to achieve the length required.
e
 Do the cold expansion of the fastener holes in accordance with SRM
51-40-41
Use tool list No.
FTBXA9
 BOX
 1
DATE: Jun 26/15 SERVICE BULLETIN No.: A310-53-2141
REVISION No.: 01 - Jul 02/15 Page: 52
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