# Airbus Service Bulletin A350-53-P012

Copy: No revision named ("SB A350-53-P012"), 76 pages: PDF https://openairdocs.org/files/sha256/49/59/4959d43f7f4acb33a71ebc11b78c0db3bdc21a9558c10fe81949c9006c518036; text https://openairdocs.org/service-documents/airbus/a350-53-p012/file/4959d43f7f4a.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2019-0724, the docket of AD 2019-21-07. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md)
- Type: Service bulletin (Service Bulletin)
- Number: A350-53-P012
- Page: https://openairdocs.org/service-documents/airbus/a350-53-p012

## Text (76 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2019-0724, the docket of AD 2019-21-07. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

@A350
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.
ATA SYSTEM: 53
TITLE: FUSELAGE - REAR FUSELAGE - INRODUCE IMPROVED CARGO
DOOR SURROUND ALU LATCH FITTINGS IN SECTION 16/18 -
**CONF ALL
MODIFICATIONS
MODIFICATION CLASSIFICATION
MAJOR
 None
MINOR
 109223L35723
 110667L35837
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 inspection on an AIRBUS test aircraft, cracks have been detected on parts made of forging
aluminum 7037 due to an unexpected behavior of this material. AIRBUS decided to redesign the AFT
door latch fittings with material change to aluminum 7010T7652. This design change has been applied
in production from Manufacturer Serial Number (MSN) 0040.
For aircraft with MSN 0006 thru MSN 0039 the AFT cargo door latch fittings must be replaced due to
the material improvement from aluminum 7037 to aluminum 7010T7652.
This Service Bulletin details the installation of new AFT cargo-door latch fittings at FR79, FR79A, FR80
and FR80A in the lower part of the cargo door surround.
Accomplishment of this Service Bulletin cancels the requirements of Service Bulletin No. A350-53-P045.
The accomplishment of this Service Bulletin will ensure the 6 years threshold for the first General Visual
Inspection (GVI) in these affected areas.
GENERAL EVALUATION
EVALUATION TABLE
COMPLIANCE
 RECOMMENDED (1)
 CANCELS INSPECTION SB
 YES
POTENTIAL AD
 NO
 A/C OPERATION AFFECTED
 NO
RELIABILITY AFFECTED
 NO
 PAX COMFORT AFFECTED
 NO
COST SAVING
 NO
 ETOPS AFFECTED
 NO
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 1
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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@A350
SERVICE BULLETIN
SUMMARY
EVALUATION TABLE
STRUCTURAL LIFE EXTN
 NO
 VENDOR SB INVOLVED
 NO
NOTE
 (1)
: Service Bulletin recommended to be accomplished to prevent significant operational
disruptions.
MATERIAL PRICE INFORMATION
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET
 QTY PER
A/C
PRICE PER
A/C (USD)
MAIN PARTS
Kit 53P012D01R00
 1
 78,400.00
 Latch fitting assembly, edge protection
Kit 53P012D02R00
 1
 5,200.00
 Angle, bolts, nuts, cotter pins, washers
TOTAL
 83,600.00
Standard tool TOOLD01
 1
 See SB
EFFECTIVITY
This Service Bulletin is applicable to this (these) operator(s) :
CPA FIN HVN QTR SIA TAM
CONCURRENT REQUIREMENTS
Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of the
following Service Bulletin(s):
Service Bulletin No. A350-53-P045.
NOTE
: Service Bulletin No. A350-53-P045 (FUSELAGE - REAR FUSELAGE - INSPECT
EXTERNAL LUGS OF THE CARGO DOOR SURROUND ALU LATCH FITTINGS IN
SECTION 16/18).
REFERENCES / REPERCUSSIONS
TFU
 53.40.00.008
OEB
 None
AOT
 None
SIL
 None
ISI
 None
LINE MAINTENANCE AFFECTED
 No
LIFE LIMIT
 None
OTHER
 None
NATURE OF THE WORK
AIRCRAFT
 YES
EQUIPMENT
 NO
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 2
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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SERVICE BULLETIN
SUMMARY
MANPOWER
Task 53P012-831-848-001: Modification
TOTAL MANHOURS
 48.50
ELAPSED TIME (HOURS)
 36.75
APPENDICES
Appendix 01 - Manpower Gantt Chart
Appendix 02 - Check of the Latch Fitting Alignment
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 3
6
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SERVICE BULLETIN
SUMMARY
**CONF ALL
A
REPLACEMENT OF CARGO
DOOR LATCH FITTINGS
DOOR IN OPEN CONDITION
Z822
A
P_SB_53P012_6_SAAA_01_01
Figure A-GSAAA - Sheet 01
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 4
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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@A350
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
ATA SYSTEM: 53
TITLE: FUSELAGE - REAR FUSELAGE - INRODUCE IMPROVED CARGO
DOOR SURROUND ALU LATCH FITTINGS IN SECTION 16/18 -
MODIFICATION No.: 109223L35723 110667L35837
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 modification is applicable by Service Bulletin only.
(1) Models
350-941
(2) Effectivity by MSN
0006-0039
(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
CPA
 0029 0032 0034 0038 0039
FIN
 0018 0019 0020 0022 0023 0028
HVN
 0014 0015 0016 0017
QTR
 0006 0007 0008 0009 0010 0011 0012 0013 0021 0025 0033 0036
SIA
 0026 0030 0031 0037
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 1
6
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SERVICE BULLETIN
OPERATOR
 MSN
TAM
 0024 0027 0035
(4) Configuration by MSN
MSN
 CONFIGURATION
0006 0007 0008 0009 0010 0011 0012 0013 0014 0015 0016
0017 0018 0019 0020 0021 0022 0023 0024 0025 0026 0027
0028 0029 0030 0031 0032 0033 0034 0035 0036 0037 0038
0039
001
(5) Configuration definition
**CONF 001
Config. 001 is valid for all the aircraft given in the effectivity of this Service Bulletin as a
standard configuration.
(6) Material Effectivity
MATERIAL
 QTY PER A/C
 SEE NOTES
Kit 53P012D01R00
 1
Kit 53P012D02R00
 1
Consumable CMLD01
 1
Standard tool TOOLD01
 1
B. CONCURRENT REQUIREMENTS
Accomplishment of this Service Bulletin requires the prior or simultaneous accomplishment of
the following Service Bulletin(s):
Service Bulletin No. A350-53-P045.
NOTE
: Service Bulletin No. A350-53-P045 (FUSELAGE - REAR FUSELAGE -
INSPECT EXTERNAL LUGS OF THE CARGO DOOR SURROUND ALU
LATCH FITTINGS IN SECTION 16/18).
C. REASON
(1) History
During inspection on an AIRBUS test aircraft, cracks have been detected on parts made
of forging aluminum 7037 due to an unexpected behavior of this material. AIRBUS
decided to redesign the AFT door latch fittings with material change to aluminum
7010T7652. This design change has been applied in production from Manufacturer
Serial Number (MSN) 0040.
For aircraft with MSN 0006 thru MSN 0039 the AFT cargo door latch fittings must be
replaced due to the material improvement from aluminum 7037 to aluminum 7010T7652.
(2) Objective/Action
This Service Bulletin details the installation of new AFT cargo-door latch fittings at FR79,
FR79A, FR80 and FR80A in the lower part of the cargo door surround.
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 2
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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SERVICE BULLETIN
(3) Advantages
Accomplishment of this Service Bulletin cancels the requirements of Service Bulletin No.
A350-53-P045.
The accomplishment of this Service Bulletin will ensure the 6 years threshold for the first
General Visual Inspection (GVI) in these affected areas.
(4) Operational/Maintenance Consequences
None
D. DESCRIPTION
To accomplish this Service Bulletin it is necessary to :
Task 53P012-831-848-001: Modification
(1) Remove Latch Fitting at Frame 80A
(2) Install Latch Fitting at Frame 80A
(3) Remove Latch Fitting at Frame 80
(4) Install Latch Fitting at Frame 80
(5) Remove Latch Fitting at Frame 79A
(6) Install Latch Fitting at Frame 79A
(7) Remove Latch Fitting at Frame 79
(8) Install Latch Fitting at Frame 79
(9) Apply the Surface Protection to the Fasteners and Latch Fittings
E. COMPLIANCE
(1) Classification
RECOMMENDED: Service Bulletin recommended to be accomplished to prevent
significant operational disruptions.
(2) Accomplishment Timescale
Accomplishment of this Service Bulletin is recommended at the earliest opportunity
where manpower and facilities are available.
F. APPROVAL
The technical content of this document is approved under the authority of Design
Organisation Approval No. EASA.21J.031.
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 3
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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@A350
SERVICE BULLETIN
If an aircraft listed in the effectivity has a modification or repair embodied that is not of
AIRBUS origin, and which affects the content of this Service Bulletin, the operator is
responsible for obtaining approval by its airworthiness authority for any adaptation necessary
before incorporation of the Service Bulletin.
G. MANPOWER
The manpower estimates given in this Service Bulletin are based on the direct labor cost to
do the work. These estimates assume that the work will be done by experienced personnel,
and may need to be revised upwards to suit operator’s circumstances. The estimates do not
include the time to prepare, plan or inspect the work. Manufacture and procurement of parts
and tools, drying times for paints, sealants, etc., and general administration work are also not
included.
Task 53P012-831-848-001: Modification
Get Access
 11.00
On Aircraft
Remove Latch Fitting at Frame 80A
 2.00
Install Latch Fitting at Frame 80A
 3.00
Remove Latch Fitting at Frame 80
 2.00
Install Latch Fitting at Frame 80
 3.00
Remove Latch Fitting at Frame 79A
 2.00
Install Latch Fitting at Frame 79A
 3.00
Remove Latch Fitting at Frame 79
 2.00
Install Latch Fitting at Frame 79
 3.00
Apply the Surface Protection to the Fasteners and
Latch Fittings
0.50
Tests
 4.50
Close-Up
 12.50
TOTAL MANHOURS
 48.50
ELAPSED TIME (HOURS)
 36.75
NOTE
: For an explanation of the man-hours and elapsed time, refer to the Gantt
Chart, Fig. A-GAAAA
 given in Appendix 01 - Manpower Gantt Chart .
H. WEIGHT AND BALANCE
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).
Manufacturers Empty Weight -0.1 KG (-0.2 LB)
Effect on Balance -9.9 KGM (-71.6 LB.FT )
I. ELECTRICAL LOAD DATA
Not Changed
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 4
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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@A350
SERVICE BULLETIN
J. REFERENCES
Aircraft Structural Repair (ASR)
 51-24-XX 51-42-XX 51-43-XX
51-44-21 51-4X-XX
Consumable Material List (CML)
Electrical Standard Practices (ESP)
 20-51-20 20-55-XX
Maintenance Procedure (MP)
 20-46-XX 20-51-20 20-51-50
24-41-XX 25-81-74 25-84-74
50-18-61 50-1X-XX 50-23-XX
52-33-XX 52-3X-XX
Process and Material Specification (PMS)
System Description (SD)
 06-3X-XX
Standards Manual (SM)
Weight and Balance Manual (WBM)
K. PUBLICATION AFFECTED
Aircraft Structural Repair (ASR)
 53-41-63 53-45-74
Maintenance Illustrated Part Data (MIPD)
 53-45-74
Structural Repair IPD (SRIPD)
 53-41-63 53-45-74
L. INTERCHANGEABILITY/MIXABILITY
Not Applicable
M. SPARES
Latch Assy C79 V5347391500200
Latch Assy C79A V5347391700200
Latch Assy C80 V5347391900200
Latch Assy C80A V5347392100200
The parts listed here must not be installed anymore on aircraft which have accomplished this
Service Bulletin or which have the equivalent production modification embodied.
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 5
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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@A350
SERVICE BULLETIN
This Page Intentionally Left Blank
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 6
6
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@A350
SERVICE BULLETIN
2. MATERIAL INFORMATION
**CONF ALL
A. MATERIAL - PRICE AND AVAILABILITY
(1) Procurement Addresses
Customers with aircraft shown in the effectivity of this Service Bulletin should send a
purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is:
Kit 53P012D01R00
Kit 53P012D02R00
AIRBUS Material, Logistics and Suppliers
ATP II B,
Hein-Sass-Weg 24
21129 HAMBURG
GERMANY
For ordering by internet:
http://spares.airbus.com
For ordering by E-mail: airbus.kit@airbus.com
Telephone Hotline: +49 40 743 51775
(2) Price and Availability
Kit 53P012D01R00
Cost
 78,400.00 USD
Availability
 99 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
AIRBUS Spares portal or through a request for quotation to airbus.kit@airbus.com.
Kit 53P012D02R00
Cost
 5,200.00 USD
Availability
 99 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
AIRBUS Spares portal or through a request for quotation to airbus.kit@airbus.com.
B. INDUSTRY SUPPORT INFORMATION
AIRBUS will share the costs of accomplishment of this Service Bulletin by providing the kits at
no charge for orders placed before Dec 31/21.
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 7
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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SERVICE BULLETIN
AIRBUS will credit the man hours indicated in this Service Bulletin at the agreed in-house
warranty labor rate for claims received no later than 90 days after completion of the last
affected aircraft of your fleet, for the accomplishment of this Service Bulletin before Dec
31/21.
For the organization of this retrofit, you are kindly requested to contact AIRBUS retrofit
management department: monitored.retrofit@airbus.com.
C. LIST OF COMPONENTS
Kit 53P012D01R00
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
1
 V5347394700000
 1
 PLATE
28
 V5347391500800
 1
 LATCH
29
 V5347391700800
 1
 LATCH
30
 V5347391900800
 1
 LATCH
31
 V5347392100800
 1
 LATCH
Kit 53P012D02R00
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
2
 DAN169E3-8
 7
 SCREW
8
 NAS1149D0316K
 14
 WASHER
9
 ASNA2069N3
 18
 WASHER
10
 NAS1726C3E
 6
 NUT
17
 NSA5191-3V8
 12
 BOLT
18
 MS24665-86
 2
 PIN
19
 NSA5059E3
 2
 NUT
23
 MS21042L3
 2
 NUT
26
 MS24665-372
 1
 PIN
27
 NSA5059E10
 1
 NUT
32
 V5349014420051
 2
 ANGLE
33
 V5347404620051
 2
 ANGLE
34
 EN6114B4E8
 12
 BOLT
35
 EN6114B4E9
 8
 BOLT
36
 EN6114B4E10
 12
 BOLT
37
 EN6114B4E12
 20
 BOLT
38
 EN6114B4E13
 26
 BOLT
39
 EN6114B4E14
 2
 BOLT
40
 EN6115B4E5
 12
 BOLT
41
 EN6115B4E6
 4
 BOLT
42
 EN6115B4E7
 26
 BOLT
43
 EN6115B5-6
 46
 BOLT
44
 EN6115B5-7
 10
 BOLT
45
 EN6115B5-8
 10
 BOLT
46
 ABS1738K4
 128
 NUT
47
 ABS1738K5
 66
 NUT
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 8
6
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SERVICE BULLETIN
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 ITEM
 OLD PART N˚
 INT
 SEE
NOTES
49
 EN6115B4E4
 6
 BOLT
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
Mineral Oil Base Grease - Vaseline
Or Petrolatum
03FAB1
 As required
Synthetic Oil Base Grease -
General Purpose Lithium
03GBC1
 As required
Coating - Flexible Structure
 04QAB2
 As required
Varnish - Electrical Bonding
Structure
04TMB2
 As required
Double Side Adhesive Tape - Foam
Base
05PAC1
 As required
Polysulfide Sealant - General
Purpose Interfay
06AAC1
 As required
Polysulfide Sealant - Low Density
Multi Purpose Bru
06ACA1
 As required
Polysulfide Sealant - Low Density
Multi Purpose Fil
06ACB1
 0
Polysulfide Sealant - Low Adhesion
Brushable
06AEA1
 As required
Polysulfide Sealant - Low Adhesion
Fillet Structure
06AEB2
 As required
Non Hardening Jointing Putty -
Medium Temp. Area
06LCG9
 As required
Aqueous Cleaner - Aircraft Exterior
Pressure Sprayi
08ABC1
 As required
Non Aqueous Cleaner - General
 08BAA9
 As required
Non Aqueous Cleaner - Wax And
Grease Remover
08BDA1
 As required
Corrosion Preventive Compound -
Heavy Duty Long Dur
12AEB1
 As required
Paste Adhesive - Liquid Shim
 13FGC1
 0
Release Agent - Liquid Wax
 14DBB1
 As required
Sealing Profile - Vaccum Bag
Sealant
14JEA1
 As required
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 9
6
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SERVICE BULLETIN
ITEM
 DESCRIPTION
 REFERENCE TO CML
MAT. No.
QTY PER A/C
 SEE
NOTES
Textile - Lint Free Cotton
 14SBA1
 As required
(2) Components
None
(3) Equipment
None
E. PARTS TO BE RE-IDENTIFIED BY OPERATOR
None
F. TOOLING
(1) Tooling - Price and Availability
None
(2) Tools
To accomplish this Service Bulletin it is necessary to use the tools listed in the
subsequent referenced tasks:
- MP Task A350-A-52-3X-XX-05ZZZ-132Z-A.
Standard tool TOOLD01
ITEM
 TOOL N˚
 TOOL NAME
 QTY
 SEE
NOTES
98V52308822000
 Strut-Support, Compartment
Door
1
98V53008001000
 Ground support equipment
 1
(3) Special Tools
None
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 10
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SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS
Task 53P012-831-848-001 - Modification
WARNING
: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS
INCLUDED IN THE REFERENCED PROCEDURES.
WARNING
: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES ARE
IN POSITION BEFORE YOU START A TASK ON OR NEAR:
- THE LANDING GEAR AND RELATED DOORS
MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS
AND CAN CAUSE DAMAGE.
CAUTION
: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP
ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY
AND MECHANICALLY SERVICEABLE) . WHEN YOU DO MAINTENANCE
WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,
COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO
THIS:
- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC., AS
NECESSARY ON WIRING AND COMPONENTS.
- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND
OTHER CONTAMINATION.
THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION
AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.
IF THERE IS CONTAMINATION, REFER TO ESP Task A350-A-20-55-
XX-01ZZZ-042Z-A.
NOTE
: The accomplishment instructions of this Service Bulletin include procedures given
in other documents or in other sections of the Service Bulletin. When the words
’refer to’ are used and the operator has a procedure accepted by the local authority
he belongs to, the accepted alternative procedure can be used. When the words ’in
accordance with’ are used then the given procedure must be followed.
NOTE
: The access and close-up instructions, not comprising return to service tests, in this
Service Bulletin do not constitute or affect the technical intent of the Service
Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or
close-up steps to add flexibility to their maintenance operations as long as the
technical intent of the Service Bulletin is met within the set parameters.
NOTE
: Manual titles given in the accomplishment instructions are referred to by acronyms.
Refer to paragraph 1.J., References, for the definition of acronyms.
NOTE
: This Service Bulletin is classified mandatory or expected to be classified mandatory
by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these
accomplishment instructions are Required for Compliance (RC) and must be done
to comply with the AD. To allow more flexibility, the rule "refer to" and "in
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 11
6
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SERVICE BULLETIN
accordance with" will apply to these paragraphs 3.C. and 3.D. 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
: This Service Bulletin contains the instructions for the on-aircraft maintenance
necessary to ensure the continued airworthiness of the aircraft.
For any deviations to the instructions, including RC paragraph contained herein,
contact AIRBUS for further instructions and approval.
NOTE
: Discarded parts must be managed at the operator’s discretion.
Task Associated Data
Zone
822
Access
Door
 822
Manpower
TOTAL MANHOURS
 48.50
ELAPSED TIME (HOURS)
 36.75
A. GENERAL
(1) Subtask 53P012-910-201-001 - Standard Practices
Manpower Resources
Skills
 NON SPECIFIC
References
Aircraft Structural Repair (ASR)
 Task A350-A-51-24-XX-01ZZZ-667Z-A
Task A350-A-51-42-XX-01ZZZ-667Z-A
Task A350-A-51-43-XX-01ZZZ-667Z-A
Task A350-A-51-4X-XX-01ZZZ-667Z-A
Consumable Material List (CML)
Electrical Standard Practices (ESP)
 Task A350-A-20-51-20-01ZZZ-042Z-A
Maintenance Procedure (MP)
 Task A350-A-20-46-XX-00ZZZ-25BZ-A
Task A350-A-20-51-20-00ZZZ-250Z-A
Task A350-A-20-51-50-01ZZZ-25BZ-A
Process and Material Specification
(PMS)
System Description (SD)
 Task A350-A-06-3X-XX-01ZZZ-04CZ-A
(a) For the identification of zones, refer to SD Task A350-A-06-3X-XX-01ZZZ-04CZ-A.
(b) If alternative and substitute fasteners have to be used, you must make sure that the
associated nut/collar are compatible in accordance with ASR Task A350-A-51-4X-
XX-01ZZZ-667Z-A.
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 12
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SERVICE BULLETIN
(c) For the specification of Material Numbers (Mat. No.) given in this Service Bulletin,
refer to the Consumable Materials List (CML).
(d) Tag all the parts you must remove and retain to make the subsequent installation
easier.
(e) Put all the retained hardware in identified plastic bags and attach the bags to the
related unit.
(f) For Standard Mechanical Torques, refer to MP Task A350-
A-20-51-50-01ZZZ-25BZ-A.
(g) For the electrical bonding, refer t o ESP Task A350-A-20- 51-20-01ZZZ-042Z-A and
MP Task A350-A-20-51-20-00ZZZ-250Z-A.
(h) Remove and install fasteners in accordance with ASR Task A350-A-51-42-
XX-01ZZZ-667Z-A.
(i) Apply sealant in accordance with ASR Task A350-A-51-24-XX-01ZZZ-667Z-A.
(j) Get alternative and substitute fastener data in accordance with ASR Task A350-
A-51-43-XX-01ZZZ-667Z-A.
(k) If the length of any fastener specified in this Service Bulletin does not meet
installation standards given in ASR Data Module 51-4, then a fastener of the same
specification, or an approved substitute, with a length which meets the installation
standards given in ASR Data Module 51-4 may be used. In addition, washers may
be installed for fastener grip length in accordance with ASR Data Module 51-4.
(l) For circuit breaker safety practices, refer to MP Task A350-A-20-46-
XX-00ZZZ-25BZ-A.
(m) If you find process and material specifications that you do not know in the design
drawings, refer to the cross-reference list in the Process and Material Specification
(PMS).
(n) If a fastener hole is damaged and outside the tolerance of the original fastener
nominal diameter, an oversize fastener must be installed in accordance with ASR
Task A350-A-51-43-XX-01ZZZ-667Z-A.
(2) Subtask 53P012-839-201-001 - 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: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 13
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SERVICE BULLETIN
B. PREPARATION
(1) Subtask 53P012-941-201-001 - Job Set-up
Manpower Resources
Skills
 NON SPECIFIC
References
Maintenance Procedure (MP)
 Task A350-A-24-41-XX-00ZZZ-170Z-A
Task A350-A-50-23-XX-00ZZZ-561Z-A
WARNING
: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING
NOTICES ARE 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
MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS.
WARNING
: BE CAREFUL WHEN YOU DO WORK WITH COMPOSITE
MATERIALS:
- IMMEDIATELY REMOVE THE DUST WITH A VACUUM CLEANER.
CARBON DUST IS ELECTRICALLY CONDUCTIVE AND CAN
CAUSE AN EXPLOSION
- DO NOT USE THESE MATERIALS NEAR A FLAME, SPARKS OR
SOURCES OF HEAT
- USE PROTECTIVE GLOVES, GOGGLES AND A FILTER MASK
WHEN YOU CUT, ABRADE OR DRILL
- MAKE SURE THAT THERE IS A GOOD FLOW OF AIR THROUGH
THE WORK AREA
- IF YOU GET THE DUST ON YOUR SKIN, REMOVE IT WITH
SOAP AND A FLOW OF CLEAN WATER
- IF YOU GET THE DUST IN YOUR EYES, FLUSH IT AWAY WITH
A FLOW OF CLEAN WATER. GET MEDICAL AID
- IF YOU GET THE DUST IN YOUR LUNGS, GO OUTDOORS
IMMEDIATELY AND BREATHE FRESH AIR. GET MEDICAL AID
- OBEY THE MATERIAL MANUFACTURER INSTRUCTIONS AND
THE LOCAL REGULATIONS.
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 14
6
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SERVICE BULLETIN
CAUTION
: MAKE SURE THAT YOU DO NOT CAUSE DAMAGE TO THE
SURFACES. THESE COMPONENTS ARE MADE OF CARBON FIBER
REINFORCED PLASTIC.
NOTE
: For the basic Aircraft configuration, refer to AMM Chapter "Introduction -
Aircraft status for maintenance" in Manual Front Matter section.
(a) Make sure that the aircraft is electrically grounded, refer to MP Task A350-A-24-41-
XX-00ZZZ-170Z-A.
(b) Make sure that the car go loading system is de-energized , refer to MP Task A350-
A-50-23-XX-00ZZZ-561Z-A.
(2) Subtask 53P012-010-201-001 - Remove/Open for Access to the Work Area
Manpower Resources
Skills
 NON SPECIFIC
Material necessary to do the job
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Non Aqueous Cleaner -
Wax And Grease Remover
08BDA1
Textile - Lint Free Cotton
 14SBA1
 As required
Standard tool TOOLD01
ITEM
 TOOL N˚
 TOOL NAME
 QTY
 SEE
NOTES
98V52308822000
 Strut-Support,
Compartment Door
1
References
Maintenance Procedure (MP)
 Task A350-A-25-81-74-31ZZZ-94ZZ-A
Task A350-A-25-84-74-34ZZZ-94ZZ-A
Task A350-A-50-18-61-01ZZZ-520Z-A
Task A350-A-50-1X-XX-02ZZZ-170Z-A
Task A350-A-52-3X-XX-05ZZZ-132Z-A
Fig. A-GBAAA
Removal/Installation of the Plate-Scuff
Edge Protection Sill Assy
Sheet 01
Fig. A-GBBAA
Removal/Installation of the Ball Mat
Assemblies
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Fig. A-GBCAA
Removal/Installation of the Lock Fitting
Bolts
Sheet 01
Sheet 02
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 15
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SERVICE BULLETIN
WARNING
: USE GOGGLES EACH TIME YOU CUT A COTTER PIN. REMOVE AND
DISCARD THE COTTER PIN IMMEDIATELY.
(a) Put an access platform in position below aft cargo-compartment door.
(b) Get access to the AFT cargo compartment, refer to MP Task A350-A-50-1X-
XX-02ZZZ-170Z-A.
(c) To keep door 822 in fully open, put in position, refer to MP Task A350-A-52-3X-
XX-05ZZZ-132Z-A.
98V52308822000 Strut-Support,
Compartment Door
1
(d) Remove plate-scuff edge protection sill assy of the bottom edge of cargo
compartment door area as shown on Fig. A-GBAAA Sheet 01
 .
1
 Remove:
7 Screw Item (2) Discard
attached with
1 Plate-Scuff Edge
Protection Sill Assy
Item (1) Discard
2
 Remove the old sealant with non-metallic spatula.
3
 Use the hot air blower to apply heat to the edge protection sill assy (1), make
sure that temperature is not more than 100 degree celsius.
4
 Carefully put the non-metallic scrapper between the fuselage skin and edge
protection sill assy to lower adhesion of the sealant underneath.
5
 Clean the work area with non-metallic scrapper:
Textile - Lint Free
Cotton
14SBA1 As required
moistened with
Non Aqueous
Cleaner - Wax And
Grease Remover
08BDA1 As required
(e) Remove the ball mat assemblies between Frame 78 and Frame 81, as shown on
Fig. A-GBBAA Sheet 01
 thru Fig. A-GBBAA Sheet 04
 .
1
 Loosen the captive screws (7).
116 Screw Item (7) Retain
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 16
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SERVICE BULLETIN
2
 Lift the ball mats assemblies:
1 Ball Mat Assy Item (3) Retain
1 Ball Mat Assy Item (4) Retain
1 Ball Mat Assy Item (5) Retain
1 Ball Mat Assy Item (6) Retain
3
 Disconnect the electrical connectors (11) and (12) from the drain pan.
4
 Remove the bonding straps item (50):
6 Nut Item (10) Discard
6 Washer Item (9) Discard
2 Washer Item (8) Discard
1 Bonding straps Item (50) Retain
(f) Remove the drain pans between Frame 78 and Frame 81, refer to MP Task A350-
A-50-18-61-01ZZZ-520Z-A.
6 Drain Pan Retain
attached with
12 Bolt Discard
12 Washer Discard
12 Washer Discard
(g) Remove the insulation blankets on the modification area, refer to MP Task A350-
A-25-81-74-31ZZZ-94ZZ-A and MP Task A350-A- 25-84-74-34ZZZ-94ZZ-A.
(h) Remove the latch fitting bolts from latches at Frame 79, Frame 79A, Frame 80 and
Frame 80A as shown on Fig. A-GBCAA Sheet 01
 and Fig. A-GBCAA Sheet 02
 .
1
 Remove:
2 Pin-Cotter Item (13) Discard
2 Nut Item (14) Discard
2 Washer Item (15) Retain
1 Plate-Serration Item (16) Retain
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 17
6
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SERVICE BULLETIN
1 Plate-Serration Item (17) Retain
2 Nut Item (18) Discard
2 Washer Item (19) Retain
2 Bolt Item (20) Retain
1 Pin-Cotter Item (21) Discard
1 Nut Item (22) Discard
1 Washer Item (23) Retain
1 Bolt-Eccentric Item (24) Retain
1 Bush-Adjustment Item (25) Retain
1 Spool Item (26) Retain
1 Bush-Eccentric Item (27) Retain
C. PROCEDURE
(1) Subtask 53P012-020-201-001 - Remove Latch Fitting at Frame 80A
Work Zones and Access Panels
Zone
 Access/Work location
822
 Access
 Door 822
Work location
 Frame 80A
Manpower Resources
Manhours
 2.00
Minimum number of person
 1
Subtask elapsed time
 2.00
Skills
 AIRFRAME
References
Fig. A-GBDAA
Removal of the Latch Fittings
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
(a) Remove the latch fitting as shown on Fig. A-GBDAA Sheet 01
 thru Fig. A-GBDAA
Sheet 06
:
1 Latch Assy C80A Item (31) Discard
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 18
6
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SERVICE BULLETIN
attached with
88 Fasteners Discard
(2) Subtask 53P012-420-201-001 - Install Latch Fitting at Frame 80A
Work Zones and Access Panels
Zone
 Access/Work location
822
 Access
 Door 822
Work location
 Frame 80A
Manpower Resources
Manhours
 3.00
Minimum number of person
 1
Subtask elapsed time
 3.00
Skills
 AIRFRAME
Material necessary to do the job
Kit 53P012D01R00
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
31
 V5347392100800
 1
 LATCH
Kit 53P012D02R00
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
32
 V5349014420051
 1
 ANGLE
33
 V5347404620051
 1
 ANGLE
34
 EN6114B4E8
 4
 BOLT
36
 EN6114B4E10
 4
 BOLT
37
 EN6114B4E12
 4
 BOLT
38
 EN6114B4E13
 8
 BOLT
42
 EN6115B4E7
 9
 BOLT
43
 EN6115B5-6
 10
 BOLT
45
 EN6115B5-8
 5
 BOLT
46
 ABS1738K4
 32
 NUT
47
 ABS1738K5
 15
 NUT
49
 EN6115B4E4
 3
 BOLT
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Mineral Oil Base Grease -
Vaseline Or Petrolatum
03FAB1
 As required
Coating - Flexible Structure
 04QAB2
 As required
Polysulfide Sealant -
General Purpose Interfay
06AAC1
 As required
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 19
6
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SERVICE BULLETIN
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Non Aqueous Cleaner -
General
08BAA9
 As required
Textile - Lint Free Cotton
 14SBA1
 As required
Standard tool TOOLD01
ITEM
 TOOL N˚
 TOOL NAME
 QTY
 SEE
NOTES
98V53008001000
 Ground support
equipment
1
References
Aircraft Structural Repair (ASR)
 Task A350-A-51-44-21-01ZZZ-667Z-A
Fig. A-GBEAA
Installation of the Latch Fittings
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
Sheet 07
(a) Clean the area with:
Textile - Lint Free
Cotton
14SBA1 As required
made moist with
Non Aqueous
Cleaner - General
08BAA9 As required
and a non metallic scrapper.
(b) Put in position as shown on Fig. A-GBEAA Sheet 01
 , Fig. A-GBEAA Sheet 02
 and
Fig. A-GBEAA Sheet 03
 with the use of the Ground Support Equipment (GSE) Tool
98V53008001000, refer to Appendix 02 - Check of the Latch Fitting Alignment .
1
 Apply, inside the latch fitting bushes and on the positioning tool to avoid a
stacking between both due to the close manufacturing tolerances:
Mineral Oil Base
Grease - Vaseline
Or Petrolatum
03FAB1 As required
1 Latch V5347392100800 Item 31
98V53008001000 Ground support
equipment
1
NOTE
: Tool Part Number (PN) 98V53008001000 is a full box
containing 2 Bolt Assy PN 98V53008001040.
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 20
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SERVICE BULLETIN
WARNING
: PROTECT YOUR EYES WITH GOGGLES, MOUTH WITH
RESPIRATOR AND SKIN WITH A PROTECTIVE SUIT WITH
GLOVES TO AVOID ANY CONTACT WITH CFRP PARTICLES
WHILE GRINDING, MILLING, DRILLING OR CLEANING OF CFRP
STRUCTURE PARTS.
(c) Transfer drill the fastener holes from the fuselage structure to the new latch fitting
with a drill diameter of 2.5mm (0.1 in.) with the use of drill bush.
(d) Final drill the fasteners holes to the diameter as shown on Fig. A-GBEAA Sheet 07
 .
(e) Remove the new latch fitting and the positioning tool.
(f) Deburr and clean the fastener holes with:
Textile - Lint Free
Cotton
14SBA1 As required
made moist with
Non Aqueous
Cleaner - General
08BAA9 As required
(g) Apply:
Polysulfide Sealant
- General Purpose
Interfay
06AAC1 As required
to the faying surface of the new latch fitting.
(h) Put the new latch in position without the positioning tool.
(i) Wet install the fasteners to the latch fitting on the sill beam as shown on Fig. A-
GBEAA Sheet 01
 thru Fig. A-GBEAA Sheet 07
 :
5 Bolt EN6115B5-8 Item 45
10 Bolt EN6115B5-6 Item 43
15 Nut ABS1738K5 Item 47
with
Polysulfide Sealant
- General Purpose
Interfay
06AAC1 As required
CAUTION
: OBEY CAREFULLY THE INSTRUCTIONS GIVEN IN THE ASR
Task A350-A-51-44- 21-01ZZZ-667Z-A TO AVOID DAMAGE TO THE
FASTENER HOLES DURING DRILLING THROUGH THE CFRP AND
ALUMINUM MATERIAL.
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 21
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(j) Put the new angles item 32 and 33 in position and transfer drill the pilot
holes from the angles to the new fitting in accordance with ASR Task A350-
A-51-44-21-01ZZZ-667Z-A.
(k) Transfer drill the fastener holes to the final diameter from the shear web to the new
angles in accordance with ASR Task A 350-A-51-44-21-01ZZZ-667Z-A as shown on
Fig. A-GBEAA Sheet 06
 and Fig. A-GBEAA Sheet 07
 .
(l) Drill the fastener holes from the new angles to the new latch fitting to the final
diameter in accordance with ASR Task A350-A-51-44-21-01ZZZ-667Z-A as shown
on Fig. A-GBEAA Sheet 06
 and Fig. A-GBEAA Sheet 07
 .
(m) Deburr and clean the fastener holes with:
Textile - Lint Free
Cotton
14SBA1 As required
made moist with
Non Aqueous
Cleaner - General
08BAA9 As required
(n) Wet install the angles with fasteners as shown on Fig. A-GBEAA Sheet 01
 thru Fig.
A-GBEAA Sheet 07
.
1 Angle V5349014420051 Item 32
1 Angle V5347404620051 Item 33
9 Bolt EN6115B4E7 Item 42
3 Bolt EN6115B4E4 Item 49
12 Nut ABS1738K4 Item 46
with
Polysulfide Sealant
- General Purpose
Interfay
06AAC1 As required
Coating - Flexible
Structure
04QAB2 As required
(o) Wet install the fasteners in the Carbon Fibre Reinforced Plastic (CFRP) fuselage
skin and inside the torsion box as shown on Fig. A-GBEAA Sheet 01
 thru Fig. A-
GBEAA Sheet 07
:
4 Bolt EN6114B4E8 Item 34
4 Bolt EN6114B4E10 Item 36
4 Bolt EN6114B4E12 Item 37
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 22
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SERVICE BULLETIN
8 Bolt EN6114B4E13 Item 38
20 Nut ABS1738K4 Item 46
with
Polysulfide Sealant
- General Purpose
Interfay
06AAC1 As required
(3) Subtask 53P012-020-202-001 - Remove Latch Fitting at Frame 80
Work Zones and Access Panels
Zone
 Access/Work location
822
 Access
 Door 822
Work location
 Frame 80
Manpower Resources
Manhours
 2.00
Minimum number of person
 1
Subtask elapsed time
 2.00
Skills
 AIRFRAME
References
Fig. A-GBDAA
Removal of the Latch Fittings
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
(a) Remove the latch fitting as shown on Fig. A-GBDAA Sheet 01
 thru Fig. A-GBDAA
Sheet 06
:
1 Latch Assy C80 Item (30) Discard
attached with
98 Fasteners Discard
(4) Subtask 53P012-420-202-001 - Install Latch Fitting at Frame 80
Work Zones and Access Panels
Zone
 Access/Work location
822
 Access
 Door 822
Work location
 Frame 80
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 23
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SERVICE BULLETIN
Manpower Resources
Manhours
 3.00
Minimum number of person
 1
Subtask elapsed time
 3.00
Skills
 AIRFRAME
Material necessary to do the job
Kit 53P012D01R00
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
30
 V5347391900800
 1
 LATCH
Kit 53P012D02R00
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
34
 EN6114B4E8
 4
 BOLT
35
 EN6114B4E9
 4
 BOLT
37
 EN6114B4E12
 12
 BOLT
40
 EN6115B4E5
 6
 BOLT
42
 EN6115B4E7
 6
 BOLT
43
 EN6115B5-6
 12
 BOLT
44
 EN6115B5-7
 5
 BOLT
46
 ABS1738K4
 32
 NUT
47
 ABS1738K5
 17
 NUT
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Mineral Oil Base Grease -
Vaseline Or Petrolatum
03FAB1
 As required
Polysulfide Sealant -
General Purpose Interfay
06AAC1
 As required
Polysulfide Sealant - Low
Density Multi Purpose Bru
06ACA1
 As required
Non Aqueous Cleaner -
General
08BAA9
 As required
Textile - Lint Free Cotton
 14SBA1
 As required
Standard tool TOOLD01
ITEM
 TOOL N˚
 TOOL NAME
 QTY
 SEE
NOTES
98V53008001000
 Ground support
equipment
1
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 24
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SERVICE BULLETIN
References
Fig. A-GBEAA
Installation of the Latch Fittings
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
Sheet 07
(a) Clean the area with:
Textile - Lint Free
Cotton
14SBA1 As required
made moist with
Non Aqueous
Cleaner - General
08BAA9 As required
and non a metallic scrapper.
(b) Put in position as shown in Fig. A-GBEAA Sheet 01
 , Fig. A-GBEAA Sheet 02
 and
Fig. A-GBEAA Sheet 03
 with the use of the GSE tool 98V5300800100, refer to
Appendix 02 - Check of the Latch Fitting Alignment .
1
 Apply, inside the latch fitting bushes and on the positioning tool to avoid a
stacking between both due to the close manufacturing tolerances:
Mineral Oil Base
Grease - Vaseline
Or Petrolatum
03FAB1 As required
1 Latch V5347391900800 Item 30
98V53008001000 Ground support
equipment
1
NOTE
: Tool PN 98V53008001000 is a full box containing 2 Bolt Assy
PN 98V53008001040.
WARNING
: PROTECT YOUR EYES WITH GOGGLES, MOUTH WITH
RESPIRATOR AND SKIN WITH A PROTECTIVE SUIT WITH
GLOVES TO AVOID ANY CONTACT WITH CFRP PARTICLES
WHILE GRINDING, MILLING, DRILLING OR CLEANING OF CFRP
STRUCTURE PARTS.
(c) Transfer drill the fastener holes from the fuselage structure to the new latch fitting
with a drill diameter of 2.5mm (0.1 in.) with the use of drill bush.
(d) Final drill the fasteners holes to the diameter as shown on Fig. A-GBEAA Sheet 07
 .
(e) Remove the new latch fitting and the positioning tool.
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 25
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SERVICE BULLETIN
(f) Deburr and clean the fastener holes with:
Textile - Lint Free
Cotton
14SBA1 As required
made moist with
Non Aqueous
Cleaner - General
08BAA9 As required
(g) Apply:
Polysulfide Sealant
- General Purpose
Interfay
06AAC1 As required
to the faying surface of the new latch fitting.
(h) Put the new latch in position without the positioning tool.
(i) Wet install the fasteners to latch the fitting on the sill beam as shown on Fig. A-
GBEAA Sheet 01
 thru Fig. A-GBEAA Sheet 07
 :
5 Bolt EN6115B5-7 Item 44
12 Bolt EN6115B5-6 Item 43
17 Nut ABS1738K5 Item 47
with
Polysulfide Sealant
- General Purpose
Interfay
06AAC1 As required
(j) Wet install the fasteners in the CFRP fuselage skin and inside the torsion box as
shown on Fig. A-GBEAA Sheet 01
 thru Fig. A-GBEAA Sheet 07
 :
4 Bolt EN6114B4E8 Item 34
4 Bolt EN6114B4E9 Item 35
12 Bolt EN6114B4E12 Item 37
6 Bolt EN6115B4E5 Item 40
6 Bolt EN6115B4E7 Item 42
32 Nut ABS1738K4 Item 46
with
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 26
6
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SERVICE BULLETIN
Polysulfide Sealant
- Low Density Multi
Purpose Bru
06ACA1 As required
(5) Subtask 53P012-020-204-001 - Remove Latch Fitting at Frame 79A
Work Zones and Access Panels
Zone
 Access/Work location
822
 Access
 Door 822
Work location
 Frame 79A
Manpower Resources
Manhours
 2.00
Minimum number of person
 1
Subtask elapsed time
 2.00
Skills
 AIRFRAME
References
Fig. A-GBDAA
Removal of the Latch Fittings
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
(a) Remove the latch fitting as shown on Fig. A-GBDAA Sheet 01
 thru Fig. A-GBDAA
Sheet 05
:
1 Latch Assy C79A Item (29) Discard
attached with
92 Fasteners Discard
(6) Subtask 53P012-420-203-001 - Install Latch Fitting at Frame 79A
Work Zones and Access Panels
Zone
 Access/Work location
822
 Access
 Door 822
Work location
 Frame 79A
Manpower Resources
Manhours
 3.00
Minimum number of person
 1
Subtask elapsed time
 3.00
Skills
 NON SPECIFIC
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 27
6
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SERVICE BULLETIN
Material necessary to do the job
Kit 53P012D01R00
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
29
 V5347391700800
 1
 LATCH
Kit 53P012D02R00
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
32
 V5349014420051
 1
 ANGLE
33
 V5347404620051
 1
 ANGLE
34
 EN6114B4E8
 4
 BOLT
36
 EN6114B4E10
 4
 BOLT
37
 EN6114B4E12
 4
 BOLT
38
 EN6114B4E13
 8
 BOLT
42
 EN6115B4E7
 9
 BOLT
43
 EN6115B5-6
 12
 BOLT
45
 EN6115B5-8
 5
 BOLT
46
 ABS1738K4
 32
 NUT
47
 ABS1738K5
 17
 NUT
49
 EN6115B4E4
 3
 BOLT
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Mineral Oil Base Grease -
Vaseline Or Petrolatum
03FAB1
 As required
Coating - Flexible Structure
 04QAB2
 As required
Polysulfide Sealant -
General Purpose Interfay
06AAC1
 As required
Polysulfide Sealant - Low
Density Multi Purpose Bru
06ACA1
 As required
Non Aqueous Cleaner -
General
08BAA9
 As required
Textile - Lint Free Cotton
 14SBA1
 As required
Standard tool TOOLD01
ITEM
 TOOL N˚
 TOOL NAME
 QTY
 SEE
NOTES
98V53008001000
 Ground support
equipment
1
References
Aircraft Structural Repair (ASR)
 Task A350-A-51-44-21-01ZZZ-667Z-A
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 28
6
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SERVICE BULLETIN
References
Fig. A-GBEAA
Installation of the Latch Fittings
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
Sheet 07
(a) Clean the area with:
Textile - Lint Free
Cotton
14SBA1 As required
made moist with
Non Aqueous
Cleaner - General
08BAA9 As required
and a non metallic scrapper.
(b) Put in position as shown in Fig. A-GBEAA Sheet 01
 , Fig. A-GBEAA Sheet 02
 and
Fig. A-GBEAA Sheet 03
 with the use of the GSE tool 98V53008001000, refer to
Appendix 02 - Check of the Latch Fitting Alignment .
1
 Apply, inside the latch fitting bushes and on the positioning tool to avoid a
stacking between both due to the close manufacturing tolerances:
Mineral Oil Base
Grease - Vaseline
Or Petrolatum
03FAB1 As required
1 Latch V5347391700800 Item 29
98V53008001000 Ground support
equipment
1
NOTE
: Tool PN 98V53008001000 is a full box containing 2 Bolt Assy
PN 98V53008001040.
WARNING
: PROTECT YOUR EYES WITH GOGGLES, MOUTH WITH
RESPIRATOR AND SKIN WITH A PROTECTIVE SUIT WITH
GLOVES TO AVOID ANY CONTACT WITH CFRP PARTICLES
WHILE GRINDING, MILLING, DRILLING OR CLEANING OF CFRP
STRUCTURE PARTS.
(c) Transfer drill the fastener holes from the fuselage structure to the new latch fitting
with a drill diameter of 2.5mm (0.1 in.) with the use of drill bush.
(d) Final drill the fasteners holes to the diameter as shown on Fig. A-GBEAA Sheet 07
 .
(e) Remove the new latch fitting and the positioning tool.
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 29
6
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SERVICE BULLETIN
(f) Deburr and clean the fastener holes with:
Textile - Lint Free
Cotton
14SBA1 As required
made moist with
Non Aqueous
Cleaner - General
08BAA9 As required
(g) Apply:
Polysulfide Sealant
- General Purpose
Interfay
06AAC1 As required
to the faying surface of the new latch fitting.
(h) Put the new latch in position without the positioning tool.
(i) Wet install the fasteners to the latch fitting on the sill beam as shown on Fig. A-
GBEAA Sheet 01
 thru Fig. A-GBEAA Sheet 07
 :
5 Bolt EN6115B5-8 Item 45
12 Bolt EN6115B5-6 Item 43
17 Nut ABS1738K5 Item 47
with
Polysulfide Sealant
- General Purpose
Interfay
06AAC1 As required
CAUTION
: OBEY CAREFULLY THE INSTRUCTIONS GIVEN IN THE ASR
Task A350-A-51-44- 21-01ZZZ-667Z-A TO AVOID DAMAGE TO THE
FASTENER HOLES DURING DRILLING THROUGH THE CFRP AND
ALUMINUM MATERIAL.
(j) Put the new angles item 32 and 33 in position and transfer drill the pilot
holes from the angles to the new fitting in accordance with ASR Task A350-
A-51-44-21-01ZZZ-667Z-A.
(k) Transfer drill the fastener holes to the final diameter from the shear web to the new
angles in accordance with ASR Task A 350-A-51-44-21-01ZZZ-667Z-A as shown on
Fig. A-GBEAA Sheet 06
 and Fig. A-GBEAA Sheet 07
 .
(l) Drill the fastener holes from the new angles to the new latch fitting to the final
diameter in accordance with ASR Task A350-A-51-44-21-01ZZZ-667Z-A as shown
on Fig. A-GBEAA Sheet 06
 and Fig. A-GBEAA Sheet 07
 .
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 30
6
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### Page 35

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SERVICE BULLETIN
(m) Deburr and clean the fastener holes with:
Textile - Lint Free
Cotton
14SBA1 As required
made moist with
Non Aqueous
Cleaner - General
08BAA9 As required
(n) Wet install the angles with fasteners as shown on Fig. A-GBEAA Sheet 01
 thru Fig.
A-GBEAA Sheet 07
:
1 Angle V5349014420051 Item 32
1 Angle V5347404620051 Item 33
9 Bolt EN6115B4E7 Item 42
3 Bolt EN6115B4E4 Item 49
12 Nut ABS1738K4 Item 46
with
Polysulfide Sealant
- General Purpose
Interfay
06AAC1 As required
Coating - Flexible
Structure
04QAB2 As required
(o) Wet install the fasteners in the CFRP fuselage skin and inside the torsion box as
shown on Fig. A-GBEAA Sheet 01
 thru Fig. A-GBEAA Sheet 07
 :
4 Bolt EN6114B4E8 Item 34
4 Bolt EN6114B4E10 Item 36
4 Bolt EN6114B4E12 Item 37
8 Bolt EN6114B4E13 Item 38
20 Nut ABS1738K4 Item 46
with
Polysulfide Sealant
- Low Density Multi
Purpose Bru
06ACA1 As required
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 31
6
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SERVICE BULLETIN
(7) Subtask 53P012-020-205-001 - Remove Latch Fitting at Frame 79
Work Zones and Access Panels
Zone
 Access/Work location
822
 Access
 Door 822
Work location
 Frame 79
Manpower Resources
Manhours
 2.00
Minimum number of person
 1
Subtask elapsed time
 2.00
Skills
 AIRFRAME
References
Fig. A-GBDAA
Removal of the Latch Fittings
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
(a) Remove the latch fitting as shown on Fig. A-GBDAA Sheet 01
 thru Fig. A-GBDAA
Sheet 05
:
1 Latch Assy C79 Item (28) Discard
attached with
98 Fasteners Discard
(8) Subtask 53P012-420-204-001 - Install Latch Fitting at Frame 79
Work Zones and Access Panels
Zone
 Access/Work location
822
 Access
 Door 822
Work location
 Frame 79
Manpower Resources
Manhours
 3.00
Minimum number of person
 1
Subtask elapsed time
 3.00
Skills
 AIRFRAME
Material necessary to do the job
Kit 53P012D01R00
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
28
 V5347391500800
 1
 LATCH
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 32
6
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### Page 37

@A350
SERVICE BULLETIN
Kit 53P012D02R00
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
35
 EN6114B4E9
 4
 BOLT
36
 EN6114B4E10
 4
 BOLT
38
 EN6114B4E13
 10
 BOLT
39
 EN6114B4E14
 2
 BOLT
40
 EN6115B4E5
 6
 BOLT
41
 EN6115B4E6
 4
 BOLT
42
 EN6115B4E7
 2
 BOLT
43
 EN6115B5-6
 12
 BOLT
44
 EN6115B5-7
 5
 BOLT
46
 ABS1738K4
 32
 NUT
47
 ABS1738K5
 17
 NUT
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Mineral Oil Base Grease -
Vaseline Or Petrolatum
03FAB1
 As required
Polysulfide Sealant -
General Purpose Interfay
06AAC1
 As required
Non Aqueous Cleaner -
General
08BAA9
 As required
Textile - Lint Free Cotton
 14SBA1
 As required
Standard tool TOOLD01
ITEM
 TOOL N˚
 TOOL NAME
 QTY
 SEE
NOTES
98V53008001000
 Ground support
equipment
1
References
Fig. A-GBEAA
Installation of the Latch Fittings
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
Sheet 07
(a) Clean the area with:
Textile - Lint Free
Cotton
14SBA1 As required
made moist with
Non Aqueous
Cleaner - General
08BAA9 As required
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 33
6
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### Page 38

@A350
SERVICE BULLETIN
and a non metallic scrapper.
(b) Put in position as shown in Fig. A-GBEAA Sheet 01
 , Fig. A-GBEAA Sheet 02
 and
Fig. A-GBEAA Sheet 03
 with the use of the GSE tool 98V53008001000, refer to
Appendix 02 - Check of the Latch Fitting Alignment .
1
 Apply, inside the latch fitting bushes and on the positioning tool to avoid a
stacking between both due to the close manufacturing tolerances:
Mineral Oil Base
Grease - Vaseline
Or Petrolatum
03FAB1 As required
1 Latch V5347391500800 Item 28
98V53008001000 Ground support
equipment
1
NOTE
: Tool PN 98V53008001000 is a full box containing 2 Bolt Assy
PN 98V53008001040.
WARNING
: PROTECT YOUR EYES WITH GOGGLES, MOUTH WITH
RESPIRATOR AND SKIN WITH A PROTECTIVE SUIT WITH
GLOVES TO AVOID ANY CONTACT WITH CFRP PARTICLES
WHILE GRINDING, MILLING, DRILLING OR CLEANING OF CFRP
STRUCTURE PARTS.
(c) Transfer drill the fastener holes from the fuselage structure to the new latch fitting
with a drill diameter of 2.5mm (0.1 in.) with the use of drill bush.
(d) Final drill the fasteners holes to the diameter as shown on Fig. A-GBEAA Sheet 07
 .
(e) Remove the new latch fitting and the positioning tool.
(f) Deburr and clean the fastener holes with:
Textile - Lint Free
Cotton
14SBA1 As required
made moist with
Non Aqueous
Cleaner - General
08BAA9 As required
(g) Apply:
Polysulfide Sealant
- General Purpose
Interfay
06AAC1 As required
to the faying surface of the new latch fitting.
(h) Put the new latch in position without the positioning tool.
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 34
6
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### Page 39

@A350
SERVICE BULLETIN
(i) Wet install the fasteners to the latch fitting on the sill beam as shown on Fig. A-
GBEAA Sheet 01
 thru Fig. A-GBEAA Sheet 07
 :
5 Bolt EN6115B5-7 Item 44
12 Bolt EN6115B5-6 Item 43
17 Nut ABS1738K5 Item 47
with
Polysulfide Sealant
- General Purpose
Interfay
06AAC1 As required
(j) Wet install the fasteners in the CFRP fuselage skin and inside the torsion box as
shown on Fig. A-GBEAA Sheet 01
 thru Fig. A-GBEAA Sheet 07
 :
4 Bolt EN6114B4E9 Item 35
4 Bolt EN6114B4E10 Item 36
10 Bolt EN6114B4E13 Item 38
2 Bolt EN6114B4E14 Item 39
6 Bolt EN6115B4E5 Item 40
4 Bolt EN6115B4E6 Item 41
2 Bolt EN6115B4E7 Item 42
32 Nut ABS1738K4 Item 46
with
Polysulfide Sealant
- General Purpose
Interfay
06AAC1 As required
(9) Subtask 53P012-914-201-001 - Apply the Surface Protection to the Fasteners and
Latch Fittings
Work Zones and Access Panels
Zone
 Access/Work location
822
 Access
 Door 822
Work location
 from Frame 79 to Frame 80A
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 35
6
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### Page 40

@A350
SERVICE BULLETIN
Manpower Resources
Manhours
 0.50
Minimum number of person
 1
Subtask elapsed time
 0.50
Skills
 AIRFRAME
Material necessary to do the job
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Coating - Flexible Structure
 04QAB2
 As required
Polysulfide Sealant - Low
Density Multi Purpose Bru
06ACA1
 As required
Polysulfide Sealant - Low
Density Multi Purpose Fil
06ACB1
 As required
Corrosion Preventive
Compound - Heavy Duty
Long Dur
12AEB1
 As required
References
Fig. A-GBEAA
Installation of the Latch Fittings
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Sheet 05
Sheet 06
Sheet 07
(a) Overcoat the fastener heads and nuts as shown on Fig. A-GBEAA Sheet 03
 thru
Fig. A-GBEAA Sheet 07
 ,w i t h:
Polysulfide Sealant
- Low Density Multi
Purpose Bru
06ACA1 As required
(b) Apply beads of sealant with:
Polysulfide Sealant
- Low Density Multi
Purpose Fil
06ACB1 As required
around the new structure parts.
(c) Overcoat the sealant beads with:
Polysulfide Sealant
- Low Density Multi
Purpose Bru
06ACA1 As required
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 36
6
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### Page 41

@A350
SERVICE BULLETIN
(d) Apply beads of sealant and overcoat with:
Coating - Flexible
Structure
04QAB2 As required
to the fastener heads and nuts.
(e) Apply:
Corrosion
Preventive
Compound - Heavy
Duty Long Dur
12AEB1 As required
to the structure inside the torsion box.
D. TEST
(1) Subtask 53P012-700-201-001 - Testing
Manpower Resources
Skills
 NON SPECIFIC
References
Maintenance Procedure (MP)
 Task A350-A-50-23-XX-00ZZZ-343Z-A
Task A350-A-52-33-XX-00ZZZ-360Z-A
NOTE
: To perform testing procedure, it is necessary to accomplish SUBTASK
53P012-410-201 001 Install/Close Items Removed/Opened for Access
before.
(a) Do a functional test of the cargo door latch/lock mechanism, refer to MP Task
A350-A-50-23-XX-00ZZZ-343Z-A.
(b) Do a BITE test of the power drive units, refer to MP Task A350-A-52-33-
XX-00ZZZ-360Z-A.
E. CLOSE-UP
(1) Subtask 53P012-410-201-001 - Install/Close Items Removed/Opened for Access
Manpower Resources
Skills
 NON SPECIFIC
Material necessary to do the job
Kit 53P012D01R00
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
1
 V5347394700000
 1
 PLATE
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 37
6
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### Page 42

@A350
SERVICE BULLETIN
Kit 53P012D02R00
ITEM
 NEW PART N˚
 QTY (UM)
 KEYWORD
 SEE
NOTES
2
 DAN169E3-8
 7
 SCREW
8
 NAS1149D0316K
 14
 WASHER
9
 ASNA2069N3
 18
 WASHER
10
 NAS1726C3E
 6
 NUT
17
 NSA5191-3V8
 12
 BOLT
18
 MS24665-86
 2
 PIN
19
 NSA5059E3
 2
 NUT
23
 MS21042L3
 2
 NUT
26
 MS24665-372
 1
 PIN
27
 NSA5059E10
 1
 NUT
Consumable CMLD01
ITEM
 DESCRIPTION
 REFERENCE TO
CML MAT. No.
QTY PER A/C
 SEE
NOTES
Synthetic Oil Base Grease -
General Purpose Lithium
03GBC1
 As required
Coating - Flexible Structure
 04QAB2
 As required
Varnish - Electrical Bonding
Structure
04TMB2
 As required
Double Side Adhesive Tape
- Foam Base
05PAC1
 As required
Polysulfide Sealant -
General Purpose Interfay
06AAC1
 As required
Polysulfide Sealant - Low
Density Multi Purpose Bru
06ACA1
 As required
Polysulfide Sealant - Low
Adhesion Brushable
06AEA1
 As required
Polysulfide Sealant - Low
Adhesion Fillet Structure
06AEB2
 As required
Non Hardening Jointing
Putty - Medium Temp. Area
06LCG9
 As required
Aqueous Cleaner - Aircraft
Exterior Pressure Sprayi
08ABC1
 As required
Non Aqueous Cleaner -
General
08BAA9
 As required
Corrosion Preventive
Compound - Heavy Duty
Long Dur
12AEB1
 As required
Paste Adhesive - Liquid
Shim
13FGC1
 As required
Release Agent - Liquid Wax
 14DBB1
 As required
Sealing Profile - Vaccum
Bag Sealant
14JEA1
 As required
Textile - Lint Free Cotton
 14SBA1
 As required
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 38
6
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### Page 43

@A350
SERVICE BULLETIN
References
Maintenance Procedure (MP)
 Task A350-A-25-81-74-31ZZZ-94ZZ-A
Task A350-A-25-81-74-34ZZZ-94ZZ-A
Task A350-A-50-18-61-01ZZZ-720Z-A
Fig. A-GBAAA
Removal/Installation of the Plate-Scuff
Edge Protection Sill Assy
Sheet 01
Fig. A-GBBAA
Removal/Installation of the Ball Mat
Assemblies
Sheet 01
Sheet 02
Sheet 03
Sheet 04
Fig. A-GBCAA
Removal/Installation of the Lock Fitting
Bolts
Sheet 01
Sheet 02
(a) Make sure that the work area is clean and clear of tools and other items.
(b) Install the latch fitting bolts to the latches at Frame 79, Frame 79A, Frame 80 and
Frame 80A as shown on Fig. A-GBCAA Sheet 01
 and Fig. A-GBCAA Sheet 02
 .
1
 Install:
1 Bush-Eccentric Item (27) Retained at
removal
1 Spool Item (26) Retained at
removal
1 Bush-Adjustment Item (25) Retained at
removal
1 Bolt-Eccentric Item (24) Retained at
removal
1 Washer Item (23) Retained at
removal
1 Nut NSA5059E10 Item 27
1 Pin MS24665-372 Item 26
2 Bolt Item (20) Retained at
removal
2 Washer Item (19) Retained at
removal
2 Nut MS21042L3 Item 23
1 Plate-Serration Item (17) Retained at
removal
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 39
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SERVICE BULLETIN
1 Plate-Serration Item (16) Retained at
removal
2 Washer Item (15) Retained at
removal
2 Nut NSA5059E3 Item 19
2 Pin MS24665-86 Item 18
with
Synthetic Oil Base
Grease - General
Purpose Lithium
03GBC1 As required
Corrosion
Preventive
Compound - Heavy
Duty Long Dur
12AEB1 As required
(c) Install the insulation blankets in the modification area, refer to MP Task A350-
A-25-81-74-31ZZZ-94ZZ-A and MP Task A350-A- 25-81-74-34ZZZ-94ZZ-A.
(d) Install drain pans between Frame 78 and Frame 81, refer to MP Task A350-
A-50-18-61-01ZZZ-720Z-A.
6 Drain Pan Retained at
removal
12 Bolt NSA5191-3V8 Item 17
12 Washer NAS1149D0316K Item 8
12 Washer ASNA2069N3 Item 9
(e) Install ball mat assemblies between Frame 78 and Frame 81 as shown on Fig. A-
GBBAA Sheet 01
 thru Fig. A-GBBAA Sheet 04
 .
1
 Connect the electrical connectors (11) and (12) to the drain pan.
2
 Install the bonding straps item (50):
1 Bonding straps Item (50) Retained at
removal
6 Nut NAS1726C3E Item 10
6 Washer ASNA2069N3 Item 9
2 Washer NAS1149D0316K Item 8
NOTE
: On the bonding points, ensure that the bonding lug is located
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 40
6
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SERVICE BULLETIN
between items 9 and 10.
NOTE
: Ensure that bonding cables do not lie below the filter element
in the installed position.
3
 Apply:
Polysulfide Sealant
- Low Density Multi
Purpose Bru
06ACA1 As required
Varnish - Electrical
Bonding Structure
04TMB2 As required
4
 Apply:
Corrosion
Preventive
Compound - Heavy
Duty Long Dur
12AEB1 As required
to the electrical connectors.
5
 For the dummy connections, apply:
Polysulfide Sealant
- General Purpose
Interfay
06AAC1 As required
6
 Apply:
Polysulfide Sealant
- Low Adhesion
Brushable
06AEA1 As required
to the faying surface of the ball mats and cargo compartment floor structure.
7
 Install the ball mat assemblies:
1 Ball Mat Assy Item (3) Retained at
removal
1 Ball Mat Assy Item (4) Retained at
removal
1 Ball Mat Assy Item (5) Retained at
removal
1 Ball Mat Assy Item (6) Retained at
removal
116 Screw Item (7) Retained at
removal
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 41
6
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SERVICE BULLETIN
Install the screws with:
Non Hardening
Jointing Putty -
Medium Temp.
Area
06LCG9 As required
8
 Torque tighten the captive screws (7) to between 2.3 and 2.8 Nm (20.35 and
24.78 lbf.in).
(f) Install plate-scuff edge protection sill assy to the bottom edge of cargo
compartment door area, as shown on Fig. A-GBAAA Sheet 01
 .
1
 Put the edge protection sill assembly in its final position.
2
 Check the gap between the edge protection sill assy and the below fuselage
surface, if the gap is between 0.3 mm (0.102 in.) and 1.0 mm (0.02 in.) fill the
gap with:
Paste Adhesive -
Liquid Shim
13FGC1 As required
3
 Clean the work area with:
Textile - Lint Free
Cotton
14SBA1 As required
and
Non Aqueous
Cleaner - General
08BAA9 As required
4
 Apply a thin layer of:
Polysulfide Sealant
- Low Adhesion
Fillet Structure
06AEB2 As required
to the contact surface of fuselage skin and door sill area.
5
 Cover the edges of the edge protection sill assembly with a masking tape in
the width of 15 mm (0.59 in.).
6
 Apply layer of:
Release Agent -
Liquid Wax
14DBB1 As required
to the contact surface of edge protection sill assy.
7
 Remove the masking tape from the edge protection sill assy.
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 42
6
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### Page 47

@A350
SERVICE BULLETIN
8
 Apply:
Polysulfide Sealant
- Low Adhesion
Fillet Structure
06AEB2 As required
to the edge of the edge protection sill assy where the masking tape has been
removed.
9
 Put in position:
1 Plate - Scuff Edge
Protection Sill Assy
V5347394700000 Item 1
10
 Apply:
Non Hardening
Jointing Putty -
Medium Temp.
Area
06LCG9 As required
to the screws (2).
11
 Install:
7 Screw DAN169E3-8 Item 2
12
 Tighten the screws (2).
13
 Cover the edge protection sill assy with a sheet of porous felt sheet material
and secure with double side adhesive tape, use:
Double Side
Adhesive Tape -
Foam Base
05PAC1 As required
14
 Apply around the edges of edge protection sill assy with the distance of
approximately 30 mm (1.18 in.):
Sealing Profile -
Vaccum Bag
Sealant
14JEA1 As required
15
 Cover the edge protection sill assy with the vacuum plastic foil with a overlay
of 50mm (1.97 in.).
16
 Stick the plastic foil to sealant bead.
17
 Connect the vacuum pump and the vacuum valve PN 98A52307557000 to the
plastic foil and remove the entrapped air until the sealant has been cured.
18
 Remove the vacuum pump, vacuum valve, and plastic foil.
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 43
6
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### Page 48

@A350
SERVICE BULLETIN
19
 Clean the work area with:
Textile - Lint Free
Cotton
14SBA1 As required
and
Aqueous Cleaner -
Aircraft Exterior
Pressure Sprayi
08ABC1 As required
to remove the remaining sealant from edge protection sill assy.
20
 Overcoat the fastener nuts with:
Polysulfide Sealant
- Low Density Multi
Purpose Bru
06ACA1 As required
21
 Apply:
Coating - Flexible
Structure
04QAB2 As required
to the sealant beads and overcoated fastener nuts.
22
 Apply:
Corrosion
Preventive
Compound - Heavy
Duty Long Dur
12AEB1 As required
to the structure of door sill area.
23
 Apply:
Polysulfide Sealant
- Low Adhesion
Brushable
06AEA1 As required
around the plate-scuff edge protection sill assy.
(2) Subtask 53P012-942-201-001 - Close-up
Manpower Resources
Skills
 NON SPECIFIC
References
Maintenance Procedure (MP)
 Task A350-A-50-1X-XX-03ZZZ-170Z-A
Task A350-A-50-23-XX-01ZZZ-761Z-A
(a) Make sure that the work areas are clean and clear of tools and other items of
equipment.
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 44
6
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### Page 49

@A350
SERVICE BULLETIN
(b) Energize the cargo loading syst em, refer to MP Task A350-A-50-23-
XX-01ZZZ-761Z-A.
(c) Close the access to AFT cargo compartment, refer to MP Task A350-A-50-1X-
XX-03ZZZ-170Z-A.
(d) Remove the access platform(s).
(e) Put the aircraft back to its initial configuration.
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 45
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

### Page 50

@A350
SERVICE BULLETIN
**CONF ALL
Z822
A
OVERCOAT THE FASTENERS WITH POLYSULFIDE SEALANT MATERIAL No 06ACA1.01
APPLY FLEXIBLE COATING MATERIAL No 04QAB2 TO THE FASTENERS.02
APPLY CORROSION PREVENTIVE COMPOUND MATERIAL No 12AEB1 TO THE STRUCTURE AREA.03
04
05
INSTALL THE BOLT, ITEM 2, WITH NON HARDENING JOINING PUTTY MATERIAL No 06LCG9.06
NOTE:
MEASURE THE GAP BETWEEN EDGE PROTECTION SILL ASSY AND FUSELAGE SKIN. IF THE GAP IS
BETWEEN 0.30 mm (0.012 in) AND 1.00 mm (0.039 in), FILL IT WITH LIQUID SHIM MATERIAL No 13FGC1.
RELEASE AGENT MATERIAL No 14DBB1 SHOULD NOT BE APPLIED IN THIS AREA. APPLY POLYSULFIDE SEALANT
MATERIAL No 06AEB2 WITHIN THE DISTANCE OF 15.00 mm (0.591 in) FROM THE EDGE OF THE EDGE PROTECTION SILL ASSY.
A
DOOR IN OPEN CONDITION
(2)
2
B
(1)
1
98V52308822000
98V52308822000
15.00 mm
(0.591 in) 05
B
A A
A
A
(1)
1
(2)
2 06
VIEW LOOKING FWD
15.00 mm
(0.591 in) 0504
04
03
02
01
P_SB_53P012_6_BAAA_01_02
Figure A-GBAAA - Sheet 01
Removal/Installation of the Plate-Scuff Edge Protection Sill Assy
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 46
6
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### Page 51

@A350
SERVICE BULLETIN
**CONF ALL
A
A
Z150
TRACK 7
TRACK 1 FR60
AFT CARGO DOOR
FR77
FR82
B
P_SB_53P012_6_BBAA_01_01
Figure A-GBBAA - Sheet 01
Removal/Installation of the Ball Mat Assemblies
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 47
6
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### Page 52

@A350
SERVICE BULLETIN
**CONF ALL
(3)
(7) x33
B
G
H
01
INSTALL THE SCREWS, ITEM (7), WITH NON HARDENING JOINING PUTTY02
NOTE:
APPLY SEALANT MATERIAL No 06AEA1 TO THE FAYING SURFACE OF THE BALL MATS AND
CARGO COMPARTMENT FLOOR STRUCTURE BEFORE INSTALLATION.
MATERIAL No 06LCG9.
01
02
C
C
D
E
F
P_SB_53P012_6_BBAA_02_01
Figure A-GBBAA - Sheet 02
Removal/Installation of the Ball Mat Assemblies
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 48
6
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### Page 53

@A350
SERVICE BULLETIN
**CONF ALL
(5)
(7)
(4)
x25
(6)
J
(7)
L
K
(7)
L
01
02
NOTE:
APPLY SEALANT MATERIAL No 06AEA1 TO THE FAYING SURFACE OF THE BALL MATS AND
CARGO COMPARTMENT FLOOR STRUCTURE BEFORE INSTALLATION.
MATERIAL No 06LCG9.
01
01
01
02
x3502
x2302
D
E
F
INSTALL THE SCREWS, ITEM (7), WITH NON HARDENING JOINING PUTTY
P_SB_53P012_6_BBAA_03_01
Figure A-GBBAA - Sheet 03
Removal/Installation of the Ball Mat Assemblies
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 49
6
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### Page 54

@A350
SERVICE BULLETIN
**CONF ALL
11
(10)
(9)
(8)
10
9
8
10
9
(10)
(9)
11
10
9 8
(10)
(9) (8)
10
9
(10)
(9)
12
11
12
11
(10)
(9)
TYPICAL10
9
ELECTRICAL BONDING
NOTE:
11
APPLY ELECTRICAL BONDING LACQUER MATERIAL No 04TMB2.
WET INSTALL THE FASTENERS WITH POLYSULFIDE SEALANT MATERIAL No 06ACA1.
APPLY POLYSULFIDE SEALANT INTERFAY MATERIAL No 06AAC1.
(50)
(50)
(50)
03
04
05
05
05
04
04
04
03
03
G
H
J
K
L
03
P_SB_53P012_6_BBAA_04_02
Figure A-GBBAA - Sheet 04
Removal/Installation of the Ball Mat Assemblies
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 50
6
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### Page 55

@A350
SERVICE BULLETIN
**CONF ALL
A
FR77A
FR82
Z822
A
B
P_SB_53P012_6_BCAA_01_01
Figure A-GBCAA - Sheet 01
Removal/Installation of the Lock Fitting Bolts
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 51
6
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### Page 56

@A350
SERVICE BULLETIN
**CONF ALL
(25)
(27)
(26)
(17)
(20)
(20)
(16)
(24) 02 03
(19)(18)
(19)
(13)
(14)
(15)
(15)
(14)
(13)
21
22
(23)
18
(21)
(22)
14
13
14
13
TYPICAL
APPLY CORROSION PREVENTIVE COMPOUND MATERIAL No 12AEB1.01
INSTALL WITH GREASE MATERIAL No 03GBC1.02
INSERT BOLT ITEM (24) AGAINST THE FLIGHT DIRECTION.03
NOTE:
01
01
01
01
01
01
01
01
01
01
01
01
02
02
02
02
02
B
P_SB_53P012_6_BCAA_02_01
Figure A-GBCAA - Sheet 02
Removal/Installation of the Lock Fitting Bolts
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 52
6
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### Page 57

@A350
SERVICE BULLETIN
**CONF ALL
A
DOOR IN OPEN CONDITION
Z822
A
B
98V52308822000
98V52308822000
P_SB_53P012_6_BDAA_01_00
Figure A-GBDAA - Sheet 01
Removal of the Latch Fittings
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 53
6
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### Page 58

@A350
SERVICE BULLETIN
**CONF ALL
B
C
D
E
FR79
FR80
P_SB_53P012_6_BDAA_02_01
Figure A-GBDAA - Sheet 02
Removal of the Latch Fittings
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 54
6
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### Page 59

@A350
SERVICE BULLETIN
**CONF ALL
C
VIEW LOOKING INBOARD
FWD
FR79
FR80A
FR79AFR80
(28)
(29)(30)(31)
NOTE:
REMOVE AND DISCARD.
EXISTING FASTENERS. P_SB_53P012_6_BDAA_03_00
Figure A-GBDAA - Sheet 03
Removal of the Latch Fittings
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 55
6
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### Page 60

@A350
SERVICE BULLETIN
**CONF ALL
FR79 FR79A
D
ENOTE:
REMOVE AND DISCARD.
EXISTING FASTENERS.
VIEW LOOKING OUTBOARD
VIEW LOOKING OUTBOARD
FWD
FWD
FR80 FR80A
(28) (29)
(31)(30)
F
G
J
H
P_SB_53P012_6_BDAA_04_00
Figure A-GBDAA - Sheet 04
Removal of the Latch Fittings
DATE: Dec 17/18 SERVICE BULLETIN No.: A350-53-P012
REVISION No.: 00 - Dec 17/18 Page: 56
6
Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.

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