# Airbus Service Bulletin A350-55-P002

## Copies (2)

Copies the FAA filed in AD dockets on regulations.gov, newest revision first. A newer revision may exist.

- Revision 1 ("SB A350-55-P002 R1"), 79 pages: PDF https://openairdocs.org/files/sha256/8c/7c/8c7c0452a5cdb9713f0ec95a40621160ee09816f4f60e729e321a67fb5e45e69; text https://openairdocs.org/service-documents/airbus/a350-55-p002/file/8c7c0452a5cd.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2019-0405, the docket of AD 2019-11-01. Not covered by OpenAirDocs’ CC0 dedication.
- No revision named ("SB A350-55-P002"), 65 pages: PDF https://openairdocs.org/files/sha256/c3/d0/c3d0bc3be11b82ab3ee89372e3c0c6d341255befb56fd6bb9d4f9b4d42148658; text https://openairdocs.org/service-documents/airbus/a350-55-p002/file/c3d0bc3be11b.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2018-0791, the docket of AD 2018-25-12. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md)
- Type: Service bulletin (Service Bulletin)
- Number: A350-55-P002
- Latest revision known: A350-55-P002, Revision 1 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/airbus/a350-55-p002

## Text (79 pages)

Revision 1, the newest copy. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2019-0405, the docket of AD 2019-11-01. 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
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 1
CONF ALL
AIRBUS S.A.S.
Customer Services
T echnical Data Support and Services
31703 Blagnac Cedex
FRANCE
 
The content of this document is the property of Airbus.
It is supplied in confidence and commercial security on its contents must be maintained.
It must not be used for any purpose other than that for which it is supplied, nor may information
contained in it be disclosed to unauthorized persons.
It must not be reproduced in whole or in part without permission in writing from the owners of the
copyright. Requests for reproduction of any data in this document and the media authorized for it must
be addressed to Airbus.
MANDATORY MANDATORY MANDATORY
ATA SYSTEM: 55
TITLE: STABILIZERS - VERTICAL STABILIZER - PROTECT VTP TENSION BOLTS
SECTION 19 HOLES AGAINST CORROSION
MODIFICATION No.:
110898L80658

### Page 2

A350
SERVICE BULLETIN
REVISION TRANSMITTAL SHEET
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 2
ATA SYSTEM: 55
TITLE: STABILIZERS - VERTICAL STABILIZER - PROTECT VTP TENSION BOLTS
SECTION 19 HOLES AGAINST CORROSION
REVISION TRANSMITTAL SHEET
This page transmits Revision No. 01 of Service Bulletin No. A350-55-P002.
A. ADDITIONAL WORK
No additional work is required by this revision.
B. REASON
Revision No. 01 is issued to:
- Consider the MOD No. 108307L80457 in the configuration definition of CONF 002
- Simplify the instructions inside the CONF 002
- Transform the Service Bulletin data from ATA iSpec 2200 norm to ASD S1000D norm.
C. CHANGES
CONF 001
SERVICE BULLETIN
General Revised text and layout changes of this revision are
not identified with revision bars.
ACCOMPLISHMENT INSTRUCTIONS
T ask set A350-A-55-XX-
P002-01000-93AA-A MODIFICATION
Reference MP A350-A-20-51-50-01ZZZ-025ZA
replaced by MP A350-A-20-51-50-01ZZZ-02BZA.
CONF 002
SERVICE BULLETIN
General Revised text and layout changes of this revision are
not identified with revision bars.
ACCOMPLISHMENT INSTRUCTIONS
T ask set A350-A-55-XX-
P002-01000-93AA-A MODIFICATION
Reference MP A350-A-20-51-50-01ZZZ-025ZA
replaced by MP A350-A-20-51-50-01ZZZ-02BZA.
CONF ALL
D. FILING INSTRUCTIONS
This Service Bulletin has been generated electronically and is reissued as a complete
document. Replace the complete document.
Put this Revision Transmittal Sheet in front of the Service Bulletin.
E. HISTORY OF PREVIOUS REVISIONS
No previous revision
F. REVISION SEQUENCE
ORIGINAL: Dec 21/17
REVISION No. : 01 - Nov 13/18

### Page 3

A350
SERVICE BULLETIN
SUMMARY
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 3
ATA SYSTEM: 55
TITLE: STABILIZERS - VERTICAL STABILIZER - PROTECT VTP TENSION BOLTS
SECTION 19 HOLES AGAINST CORROSION
SUMMARY
This summary is for information only and is not approved for modification of the aircraft.
A. MODIFICATIONS
CONF 001
MODIFICATION CLASSIFICATION
MAJOR None
MINOR 110898L80658
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.
NOTE: This modification related to an Airworthiness issue has been classified by Airbus
and confirmed by EASA as minor in accordance with EU Part 21.A.91. As such, this
minor change is handled by Airbus under its Design Organisation Approval No.
EASA.21J.031.
CONF 002
MODIFICATION CLASSIFICATION
MAJOR None
MINOR 110898L80658
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.
NOTE: This modification related to an Airworthiness issue has been classified by Airbus
and confirmed by EASA as minor in accordance with EU Part 21.A.91. As such, this
minor change is handled by Airbus under its Design Organisation Approval No.
EASA.21J.031.
CONF ALL
B. REASON
(1) History
The section 19 holes for the Vertical T ail Plane (VTP) tension bolts connection are
not properly protected against corrosion. This modification consists in implementing
means to protect the section 19-VTP frames connections. Those protections are:
- Apply overlapping sealant to the shouldered cap
- Barrel nut hole to be filled with sealant
- Install shouldered caps in inner hole of root joint fittings
- Apply bead sealant around washer and tension bolt-head
- Apply corrosion preventive compound minimum 25 mm (0.984 in.) around the
head and on top of barrel nut.

### Page 4

A350
SERVICE BULLETIN
SUMMARY
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 4
(2) Objective/Action
This Service Bulletin consists in adding barriers and protections in the surrounding of
the tension bolt hole in order to improve the section 19 corrosion protection.
(3) Advantages
Accomplishment of this Service Bulletin will mitigate the risk of corrosion avoiding
further unscheduled maintenance in the area.
(4) Operational/Maintenance Consequences
AIRBUS recommends to carry out the MPD 553000-00S02-01 before this Service
Bulletin.
C. GENERAL EVALUATION
EVALUATION TABLE
COMPLIANCE MANDATORY COST SAVING NO
A/C OPERATION
AFFECTED
NO VENDOR SB NO
CANCELS INSPECTION SB NO ETOPS AFFECTED NO
PAX COMFORT AFFECTED NO POTENTIAL AD YES
RELIABILITY AFFECTED NO STRUCTURAL LIFE EXTENSION NO
LIFE LIMIT NO LINE MAINTENANCE AFFECTED NO
NOTE: Service Bulletin must be accomplished.
D. MAINTENANCE CONFIGURATION
CONF 001
No specific aircraft maintenance configuration required.
CONF 002
No specific aircraft maintenance configuration required.
CONF ALL
E. MATERIAL PRICE INFORMATION
CONF 001
(1) MODIFICATION
(a) T ask set A350-A-55-XX-P002-01000-93AA-A MODIFICATION
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET QTYPER A/C PRICE PER A/C MAIN PARTS
Part kit 55P002D01R02 1 9200.00 USD Shouldered caps
Aircraft standard tools See SB See Note Bulkhead inspection platform -
sect 19, VTP ladder - sect 19
NOTE: Price information to be acquired by the given supplier.
CONF 002
(1) MODIFICATION

### Page 5

A350
SERVICE BULLETIN
SUMMARY
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 5
(a) T ask set A350-A-55-XX-P002-01000-93AA-A MODIFICATION
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET QTYPER A/C PRICE PER A/C MAIN PARTS
Aircraft standard tools See SB See Note Bulkhead inspection platform -
sect 19, VTP ladder - sect 19
NOTE: Price information to be acquired by the given supplier.
CONF ALL
F. APPLICABILITY
This Service Bulletin is applicable to this (these) operator(s):
AAR CAL CPA DLH ETH FIN FWI HVN QTR SIA TAM THA
G. CONCURRENT REQUIREMENTS
None
H. NATURE OF THE WORK
CONF 001
(1) MODIFICATION
(a) T ask set A350-A-55-XX-P002-01000-93AA-A MODIFICATION
AIRCRAFT YES
EQUIPMENT NO
CONF 002
(1) MODIFICATION
(a) T ask set A350-A-55-XX-P002-01000-93AA-A MODIFICATION
AIRCRAFT YES
EQUIPMENT NO
CONF ALL
I. MANPOWER
CONF 001
(1) MODIFICATION
(a) T ask set A350-A-55-XX-P002-01000-93AA-A MODIFICATION
MANPOWER
TOTAL MAN-HOURS 50.00 h
ELAPSED TIME (HOURS) 46.00 h
CONF 002
(1) MODIFICATION
(a) T ask set A350-A-55-XX-P002-01000-93AA-A MODIFICATION
MANPOWER
TOTAL MAN-HOURS 48.00 h

### Page 6

A350
SERVICE BULLETIN
SUMMARY
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 6
MANPOWER
ELAPSED TIME (HOURS) 44.00 h

### Page 7

A350
SERVICE BULLETIN
SUMMARY
Figure ICN-A350-A-55XXP002-A-FAPE3-03C9N-A-002-01 SHEET 1/1
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18
General Overview
Page 7
CONF ALL
J. GENERAL OVERVIEW
CONF 001
A
Z311
Z312
LH
RH
Z323
Z324
LH
RH
A
FR98
FR94
FR95
FR96
FR97
PROTECTION OF TENSION BOLTS AND BARREL
NUT HOLES AGAINST CORROSION AND
MODIFICATION AREA
NOTE:
REPLACEMENT OF THE SHOULDERED CAPS
ICN-A350-A-55XXP002-A-FAPE3-03C9N-A-002-01

### Page 8

A350
SERVICE BULLETIN
SUMMARY
Figure ICN-A350-A-55XXP002-A-FAPE3-03C9P-A-002-01 SHEET 1/1
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18
General Overview
Page 8
CONF 002
A
Z311
Z312
LH
RH
Z323
Z324
LH
RH
A
FR98
FR94
FR95
FR96
FR97
MODIFICATION AREA
NOTE:
PROTECTION OF TENSION BOLTS AND BARREL
NUT HOLES AGAINST CORROSION AND
INSTALLATION OF THE SHOULDERED CAPS
ICN-A350-A-55XXP002-A-FAPE3-03C9P-A-002-01

### Page 9

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 9
ATA SYSTEM: 55
TITLE: STABILIZERS - VERTICAL STABILIZER - PROTECT VTP TENSION BOLTS
SECTION 19 HOLES AGAINST CORROSION
CONF ALL
1. PLANNING INFORMATION
A. APPLICABILITY
NOTE: This modification is embodied on aircraft with Manufacturer Serial Number (MSN)
0006 by T echnical Adaptation (TA) Reference (REF): 80386684/003/2017, MSN 0018
by TA REF: 80357778/003/2017, MSN 0019 by TA REF: 80381128/003/2017 and
MSN 0020 by TA REF: 80386674/003/2017.
NOTE: This Service Bulletin is not applicable to aircraft on which MOD No. 110696
(STABILIZERS-VERTICAL STABILIZER-PROTECT VTP TENSION BOLTS S19 HOLES
AGAINST CORROSION AND REMOVE PRE-TENSION) is embodied.
(1) Models
ON A/C 0006-0051, 0053, 0054, 0056-0058, 0061, 0062, 0064, 0066-0070, 0072-0077,
0079-0087, 0089, 0091-0097
350-941
CONF ALL
(2) Applicability by MSN
0006-0051 0053 0054 0056-0058 0061 0062 0064 0066-0070 0072-0077 0079-0087
0089 0091-0097
(3) MSN by configuration
CONF 001
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
CONF 002
MSN CONFIGURATION
0040 0041 0042 0043 0044 0045 0046 0047 0048 0049 0050
0051 0053 0054 0056 0057 0058 0061 0062 0064 0066 0067
0068 0069 0070 0072 0073 0074 0075 0076 0077 0079 0080
0081 0082 0083 0084 0085 0086 0087 0089 0091 0092 0093
0094 0095 0096 0097
002
CONF ALL
(4) Configuration definition
CONF 001
Configuration 001
CONF 001 is applicable for all the aircraft on which MOD No. 107716L80409 is
not embodied.
CONF 002

### Page 10

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 10
Configuration 002
CONF 002 is applicable for all the aircraft on which MOD No. 107716L80409 and
MOD No. 108307L80457 are embodied.
CONF ALL
B. CONCURRENT REQUIREMENTS
None
C. REASON
(1) History
The section 19 holes for the Vertical T ail Plane (VTP) tension bolts connection are
not properly protected against corrosion. This modification consists in implementing
means to protect the section 19-VTP frames connections. Those protections are:
- Apply overlapping sealant to the shouldered cap
- Barrel nut hole to be filled with sealant
- Install shouldered caps in inner hole of root joint fittings
- Apply bead sealant around washer and tension bolt-head
- Apply corrosion preventive compound minimum 25 mm (0.984 in.) around the
head and on top of barrel nut.
(2) Objective/Action
This Service Bulletin consists in adding barriers and protections in the surrounding of
the tension bolt hole in order to improve the section 19 corrosion protection.
(3) Advantages
Accomplishment of this Service Bulletin will mitigate the risk of corrosion avoiding
further unscheduled maintenance in the area.
(4) Operational/Maintenance Consequences
AIRBUS recommends to carry out the MPD 553000-00S02-01 before this Service
Bulletin.
D. DESCRIPTION
T o accomplish this Service Bulletin it is necessary to:
(1) MODIFICATION
(a) T ask set A350-A-55-XX-P002-01000-93AA-A MODIFICATION
CONF 001
1 Apply Sealant and Protective Treatment on T ension Bolts, Left Hand (LH)
and Right Hand (RH) side
CONF 002
1 Apply Sealant and Protective Treatment on T ension Bolts, Left Hand (LH)
and Right Hand (RH) side
CONF 001
2 Replace the Barrel Nut Plate(s) with Shouldered Cap(s) in the Inner Hole of
the Root Joint Fitting and Apply Overlapping Sealant, LH and RH side
CONF 002
2 Install Shouldered Cap(s) in the Inner Hole of the Root Joint Fitting and
Apply Overlapping Sealant, LH and RH side

### Page 11

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 11
CONF 001
3 Apply Sealant and Protective Treatment on Barrel Nut Holes, LH and RH
side
CONF 002
3 Apply Sealant and Protective Treatment on Barrel Nut Holes, LH and RH
side
CONF ALL
E. COMPLIANCE
(1) Classification
MANDATORY: Service Bulletin must be accomplished.
(2) Accomplishment Timescale
Accomplishment of this Service Bulletin is must be done 3 years from first delivery of
the aircraft (first transfer of the title).
For aircraft which have exceeded the above thresholds, accomplishment of this
Service Bulletin must be done within 6 months from the issuance of this initial Service
Bulletin date.
This Service Bulletin has been classified Mandatory. It is expected that an
Airworthiness Directive (AD) published by the European Aviation Safety Agency (EASA)
will be issued to confirm this classification. The accomplishment timescale, which has
not yet been defined, will be given in the AD.
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 applicability 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
CONF 001
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.
(1) MODIFICATION
(a) T ask set A350-A-55-XX-P002-01000-93AA-A MODIFICATION
PREPARATION
Job Set-up 4.00 h
PROCEDURE
Apply Sealant and Protective Treatment on T ension Bolts,
Left Hand (LH) and Right Hand (RH) side
14.00 h
Replace the Barrel Nut Plate(s) with Shouldered Cap(s)
in the Inner Hole of the Root Joint Fitting and Apply
Overlapping Sealant, LH and RH side
14.00 h

### Page 12

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 12
Apply Sealant and Protective Treatment on Barrel Nut
Holes, LH and RH side
14.00 h
PREPARATION FOR TEST
None
TEST
None
CLOSE-UP
Close-up 4.00 h
TOTAL MAN-HOURS 50.00 h
ELAPSED TIME (HOURS) 46.00 h
NOTE: For an explanation of the man-hours and elapsed time, refer to the
Gantt Chart given in Appendix Manpower Gantt Chart.
CONF 002
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.
(1) MODIFICATION
(a) T ask set A350-A-55-XX-P002-01000-93AA-A MODIFICATION
PREPARATION
Job Set-up 4.00 h
PROCEDURE
Apply Sealant and Protective Treatment on T ension Bolts,
Left Hand (LH) and Right Hand (RH) side
14.00 h
Install Shouldered Cap(s) in the Inner Hole of the Root Joint
Fitting and Apply Overlapping Sealant, LH and RH side
12.00 h
Apply Sealant and Protective Treatment on Barrel Nut
Holes, LH and RH side
14.00 h
PREPARATION FOR TEST
None
TEST
None
CLOSE-UP
Close-up 4.00 h
TOTAL MAN-HOURS 48.00 h
ELAPSED TIME (HOURS) 44.00 h
NOTE: For an explanation of the man-hours and elapsed time, refer to the
Gantt Chart given in Appendix Manpower Gantt Chart.
CONF ALL
H. WEIGHT AND BALANCE
CONF 001

### Page 13

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 13
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 Ref. WBM.
Manufacturer's Empty Weight +0.660 kg (+1.455 lb)
Effect on Balance +41.498 kg.m (+300.155 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 Ref. WBM.
Manufacturer's Empty Weight +0.889 kg (+1.960 lb)
Effect on Balance +56.499 kg.m (+408.657 lb.ft)
CONF ALL
I. ELECTRICAL LOAD DATA
Not changed
J. REFERENCES
CONF 001
(1) MODIFICATION
(a) T ask set A350-A-55-XX-P002-01000-93AA-A MODIFICATION
AIRCRAFT STRUCTURAL REPAIR (ASR)
A350-A-51-24-XX-01ZZZ-667Z-A A350-A-51-42-XX-01ZZZ-667Z-A
A350-A-51-75-12-00ZZZ-660Z-A
ELECTRICAL STANDARD PRACTICES (ESP)
A350-A-20-55-XX-01ZZZ-042Z-A
INTRODUCTION (INTRO)
A350-A-00-61-04-11ZZZ-018Z-D
IN SERVICE INFORMATION (ISI)
00.00.00161 00.00.00198
MAINTENANCE PROCEDURE (MP)
A350-A-20-51-50-01ZZZ-25BZ-A A350-A-24-41-XX-00ZZZ-170Z-A
A350-A-53-51-62-00ZZZ-520Z-A
A350-A-53-51-62-00ZZZ-720Z-A
A350-A-55-32-73-00ZZZ-520Z-A
A350-A-55-32-73-00ZZZ-720Z-A
A350-A-55-33-71-00ZZZ-720Z-A
A350-A-55-33-71-01ZZZ-520Z-A
SYSTEM DESCRIPTION (SD)
A350-A-06-2X-XX-01ZZZ-04CZ-A A350-A-06-3X-XX-01ZZZ-04CZ-A
A350-A-06-4X-XX-01ZZZ-04CZ-A
TECHNICAL FOLLOW UP (TFU)
55.30.00.001

### Page 14

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 14
WEIGHT AND BALANCE MANUAL (WBM)
CONSUMABLE MATERIAL LIST (CML)
CONF 002
(1) MODIFICATION
(a) T ask set A350-A-55-XX-P002-01000-93AA-A MODIFICATION
AIRCRAFT STRUCTURAL REPAIR (ASR)
A350-A-51-24-XX-01ZZZ-667Z-A A350-A-51-42-XX-01ZZZ-667Z-A
A350-A-51-75-12-00ZZZ-660Z-A
ELECTRICAL STANDARD PRACTICES (ESP)
A350-A-20-55-XX-01ZZZ-042Z-A
INTRODUCTION (INTRO)
A350-A-00-61-04-11ZZZ-018Z-D
IN SERVICE INFORMATION (ISI)
00.00.00161 00.00.00198
MAINTENANCE PROCEDURE (MP)
A350-A-20-51-50-01ZZZ-25BZ-A A350-A-24-41-XX-00ZZZ-170Z-A
A350-A-53-51-62-00ZZZ-520Z-A
A350-A-53-51-62-00ZZZ-720Z-A
A350-A-55-32-73-00ZZZ-520Z-A
A350-A-55-32-73-00ZZZ-720Z-A
A350-A-55-33-71-00ZZZ-720Z-A
A350-A-55-33-71-01ZZZ-520Z-A
SYSTEM DESCRIPTION (SD)
A350-A-06-2X-XX-01ZZZ-04CZ-A A350-A-06-3X-XX-01ZZZ-04CZ-A
A350-A-06-4X-XX-01ZZZ-04CZ-A
TECHNICAL FOLLOW UP (TFU)
55.30.00.001
WEIGHT AND BALANCE MANUAL (WBM)
CONSUMABLE MATERIAL LIST (CML)
CONF ALL
K. PUBLICATION AFFECTED
MAINTENANCE ILLUSTRATED PART DATA (MIPD)
MAINTENANCE PROCEDURE (MP)
L. 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 Oct 31/20 or within 36 months after the issue date of
the 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

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A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 15
affected aircraft of your fleet, for the accomplishment of this Service Bulletin before Oct
31/20 or within 36 months after the issue date of the Service Bulletin.
This Service Bulletin is the subject of an AIRBUS monitored retrofit campaign.
For the organization of this retrofit, you are kindly requested to contact AIRBUS retrofit
management department: monitored.retrofit@airbus.com.

### Page 16

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SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 16
2. MATERIAL INFORMATION
A. MATERIAL APPLICABILITY
CONF 001
Material for task set A350-A-55-XX-P002-01000-93AA-A MODIFICATION
MATERIAL QTY SEE NOTES
Aircraft standard tools See SB
Referenced tools See SB
Consumables See SB
Part kit 55P002D01R02 1
Interchangeable parts See SB
CONF 002
Material for task set A350-A-55-XX-P002-01000-93AA-A MODIFICATION
MATERIAL QTY SEE NOTES
Aircraft standard tools See SB
Referenced tools See SB
Consumables See SB
CONF ALL
B. TOOLING
CONF 001
Aircraft standard tools for task set A350-A-55-XX-P002-01000-93AA-A
MODIFICATION
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
98V53509001000 1 PLATFORM (1)
98V53509004000 1 LADDER (1)
NOTE(S)
(1): The components listed above are not an AIRBUS Kit, the required parts must be
ordered as necessary through the given channel.
CONF 002
Aircraft standard tools for task set A350-A-55-XX-P002-01000-93AA-A
MODIFICATION
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
98V53509001000 1 PLATFORM (1)
98V53509004000 1 LADDER (1)
NOTE(S)
(1): The components listed above are not an AIRBUS Kit, the required parts must be
ordered as necessary through the given channel.
CONF 001
Referenced tools for task set A350-A-55-XX-P002-01000-93AA-A MODIFICATION
NOTE: The tools specified are not specific to this Service Bulletin and are normally already
available in operators stock as a long-term investment.

### Page 17

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 17
CONF 002
Referenced tools for task set A350-A-55-XX-P002-01000-93AA-A MODIFICATION
NOTE: The tools specified are not specific to this Service Bulletin and are normally already
available in operators stock as a long-term investment.
CONF ALL
C. CONSUMABLES
CONF 001
Consumables for task set A350-A-55-XX-P002-01000-93AA-A MODIFICATION
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
03FDB1 Mineral Oil base Grease -Anti-FrettingPaste
04QAB2 Coating - - FlexibleStructure
04QAC5
Coating - - Corrosion
Inhibiting Fastener Head
Protection
06AAC1 Polysulfide Sealant -General Purpose Interfay
06ACA1
Polysulfide Sealant - Low
Density MultiPurpose
Brushable
06ACB1 Polysulfide Sealant - LowDensity MultiPurpose Fillet
06AEA1 Polysulfide Sealant - LowAdhesion Brushable
08BAA9 Non Aqueous Cleaner -General
12AEB1
Corrosion Preventive
Compound - Heavy Duty
Long Durability Hard Film
14DCB1 Release Agent - - SolvantBase
14SBA1 T extile - Lint free Cotton
CONF 002
Consumables for task set A350-A-55-XX-P002-01000-93AA-A MODIFICATION
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
03FDB1 Mineral Oil base Grease -Anti-FrettingPaste
04QAB2 Coating - - FlexibleStructure
04QAC5
Coating - - Corrosion
Inhibiting Fastener Head
Protection
06AAC1 Polysulfide Sealant -General Purpose Interfay

### Page 18

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 18
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
06ACA1
Polysulfide Sealant - Low
Density MultiPurpose
Brushable
06ACB1 Polysulfide Sealant - LowDensity MultiPurpose Fillet
06AEA1 Polysulfide Sealant - LowAdhesion Brushable
08BAA9 Non Aqueous Cleaner -General
12AEB1
Corrosion Preventive
Compound - Heavy Duty
Long Durability Hard Film
14DCB1 Release Agent - - SolvantBase
14SBA1 T extile - Lint free Cotton
CONF ALL
D. LIST OF NEW PARTS
CONF 001
Part kit 55P002D01R02
Cost 9200.00 USD
Availability 090 d (calendar days from receipt of order)
NOTE(S)
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.
Procurement address D4296
AIRBUS Material, Logistics and Suppliers
ATP II B,
Hein-Sass-Weg 24
21129 HAMBURG
GERMANY
Phone: +49 40 743 51775
E-mail: airbus.kit@airbus.com
Internet: http://spares.airbus.com
NOTE(S)
Customers with aircraft shown in the applicability of this Service Bulletin should send
a purchase order to AIRBUS at the address given above and quote the number of this
Service Bulletin.
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
1 V5537150620000 4 CAP
2 V5537150620200 4 CAP
3 V5537150620400 4 CAP
4 V5537150620600 8 CAP

### Page 19

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 19
CONF 002
No parts
CONF ALL
E. LIST OF EXISTING PARTS
CONF 001
Interchangeable parts for task set A350-A-55-XX-P002-01000-93AA-A
MODIFICATION
DESCRIPTION OLD PART No. NEW PART No. INT SEE NOTES
PLATE V5537135220000 V5537150620000 01 (1)
CAP V5537135220200 V5537150620200 01 (1)
CAP V5537135220400 V5537150620400 01 (1)
CAP V5537135220600 V5537150620600 01 (1)
NOTE(S)
For definitions of interchangeability codes in column INT. refer to ATA (CSDD Chapter
2).
(1): The interchangeability possibilities are for new or modified parts introduced by the
accomplishment of this Service Bulletin.
CONF 002
No parts

### Page 20

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 20
CONF ALL
3. ACCOMPLISHMENT INSTRUCTIONS
Task set A350-A-55-XX-P002-01000-93AA-A
MODIFICATION
WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS
INCLUDED IN THE REFERENCED PROCEDURES.
CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL
WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY
SERVICEABLE). WHEN YOU DO MAINTENANCE WORK, REPAIRS OR
MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING, COMPONENTS AND
THE WORK AREA AS CLEAN AS POSSIBLE. TO DO THIS:
- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC., AS
NECESSARY ON WIRING AND COMPONENTS.
- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND
OTHER CONTAMINATION.
THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION AND
DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.
IF THERE IS CONTAMINATION, REFER TO Ref. ESP 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 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: This Service Bulletin is classified mandatory or expected to be classified mandatory by
an Airworthiness Directive (AD). The paragraphs 3.C. and 3.E. in these accomplishment
instructions are Required for Compliance (RC) and must be done to comply with the AD.
T o allow more flexibility, the rule "refer to" and "in accordance with" will apply to these
paragraphs 3.C. and 3.E. 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.
A. TASK SET ASSOCIATED INFORMATION
Task Manpower
CONF 001
TOTAL MAN-HOURS 50.00 h

### Page 21

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 21
CONF 002
TOTAL MAN-HOURS 48.00 h
CONF 001
ELAPSED TIME (HOURS) 46.00 h
CONF 002
ELAPSED TIME (HOURS) 44.00 h
CONF ALL
B. PREPARATION
(1) Task A350-A-55-XX-P002-01001-540A-A - Job Set-up
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
Access Door 311AB, Door 311BB311
Work location From Frame 94 to Frame 98
Manpower/Resources/Skills
Man-hours 4.00 h
Minimum Number of person 2
Elapsed Time 2.00 h
Material necessary to do the job
Aircraft standard tools
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
98V53509001000 1 PLATFORM
98V53509004000 1 LADDER
Referenced Information
Manuals/Drawings References/Sheets
INTRO A350-A-00-61-04-11ZZZ-018Z-D
MP
A350-A-24-41-XX-00ZZZ-170Z-A
A350-A-53-51-62-00ZZZ-520Z-A
A350-A-55-32-73-00ZZZ-520Z-A
A350-A-55-33-71-01ZZZ-520Z-A
Procedure
NOTE: For the basic Aircraft configuration, refer to Ref. INTRO A350-
A-00-61-04-11ZZZ-018Z-D "Maintenance Procedure - Introduction".
(a) Make sure that the aircraft is electrically grounded, refer to Ref. MP A350-
A-24-41-XX-00ZZZ-170Z-A.
(b) Put a warning notice(s) in the cockpit to tell persons not to operate any hydraulic
and flight commands.
(c) Put an access platform (5.00 m (16 ft)) in position below access Door 311AB and
Door 311BB.
(d) Open the access Door 311AB and Door 311BB.
(e) In the rear fuselage, set service light switch 3LJ2 to on.
NOTE: If necessary, use a white light source when you do the work.

### Page 22

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 22
(f) Remove the lower part of the Frame 96, refer to Ref. MP A350-
A-53-51-62-00ZZZ-520Z-A.
(g) Put the access platforms in position to get access to the inspection area shown
on Ref. Fig. Application of Sealant and Protective Treatment on T ension Bolts, LH
and RH side, use:
1 BH PLATFORM S19 98V53509001000  
1 VTP LADDER - S19 98V53509004000  
(h) If necessary, remove clamps from wires and push wires outside the work area
without disconnection to get access to the work area.
(i) Put the cherry picker and/or platform in position to access barrel nut hole.
(j) Remove the dorsal FIN (321AL), refer to Ref. MP A350-A-55-32-73-00ZZZ-520Z-A.
(k) Remove the Trailing Edge (TE) access ( Panel 325AL and Panel 325AR), refer to
Ref. MP A350-A-55-33-71-01ZZZ-520Z-A.

### Page 23

A350
SERVICE BULLETIN
Figure ICN-A350-A-55XXP002-A-FAPE3-03C9I-A-003-01 SHEET 1/4
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18
Application of Sealant and Protective Treatment on T ension Bolts, LH and RH side
Page 23
CONF 001
Z311
Z312
LH
RH
A
A
FWD
CL
STGR1LH
STGR2LH
STGR1RH
STGR2RH
FR94 FR95 FR96 FR97 FR98
A A
B B C C D D E E
EEDDCCBBAA
ICN-A350-A-55XXP002-A-FAPE3-03C9I-A-003-01

### Page 24

A350
SERVICE BULLETIN
Figure ICN-A350-A-55XXP002-A-FAPE3-03C9J-A-007-01 SHEET 2/4
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18
Application of Sealant and Protective Treatment on T ension Bolts, LH and RH side
Page 24
CONF 001
APPLY BEAD SEALANT FLEXIBLE STRUCTURE COATING MATERIAL No 04QAB2.
APPLY CORROSION PREVENTIVE COMPOUND MATERIAL No 12AEB1.
APPLY POLYSULFIDE SEALANT MATERIAL No 06ACB1 ON BOLT, WASHER, FRAME
AND AROUND THE BOLT HEAD.
03
02
01
NOTE:
WASHER
BOLT
FRAME
04
05
06
(32) (31)
APPLY CORROSION INHIBITING FASTENER HEAD PROTECTION COATING MATERIAL No 04QAC5.
WET INSTALL THE FASTENERS WITH POLYSULFIDE SEALANT No 06ACA1.
01
13.00 mm
(0.512 in)
A A B B
(21)
FWD FWD
(22)
LH
RH
(23)
(24)
LH
RH (34)
LH SHOWN
RH SYMMETRICAL
LH SHOWN
RH SYMMETRICAL
07
TOP OF THE BOLT HEAD HAS TO REMAIN CLEAN AND PROVIDE 4.00 mm (0.157 in) CLEARANCE FROM PROTECTION TO BOLT HEAD.
25.00 mm
(0.985 in)
13.00 mm
(0.512 in)
25.00 mm
(0.985 in)
BOLT
USE A SELF-ADHESIVE ROUND TAPE TO PROTECT THE BOLT HEAD TOP SURFACE.
03 03
MIN MIN
WASHER
BOLT
FRAME
(32) (31)
01
(17)
(18)
LH
RH
(19)
(20)
LH
RH (34)
25.00 mm
(0.985 in)
25.00 mm
(0.985 in)
BOLT
03
MIN MIN
14.00 mm
(0.551 in)
14.00 mm
(0.551 in)
01
02 02
01
0404 0404
05
05 0506
06
06
06
05 0505
03
07
07
07
07
ICN-A350-A-55XXP002-A-FAPE3-03C9J-A-007-01

### Page 25

A350
SERVICE BULLETIN
Figure ICN-A350-A-55XXP002-A-FAPE3-03MKW-A-004-01 SHEET 3/4
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18
Application of Sealant and Protective Treatment on T ension Bolts, LH and RH side
Page 25
CONF 001
FWD D D
LH SHOWN
RH SYMMETRICAL
C CFWD
LH SHOWN
RH SYMMETRICAL
APPLY BEAD SEALANT FLEXIBLE STRUCTURE COATING MATERIAL No 04QAB2.
APPLY CORROSION PREVENTIVE COMPOUND MATERIAL No 12AEB1.
APPLY POLYSULFIDE SEALANT MATERIAL No 06ACB1 ON BOLT, WASHER, FRAME
AND AROUND THE BOLT HEAD.
03
02
01
NOTE:
04
05
06
APPLY CORROSION INHIBITING FASTENER HEAD PROTECTION COATING MATERIAL No 04QAC5.
WET INSTALL THE FASTENERS WITH POLYSULFIDE SEALANT No 06ACA1.
07
TOP OF THE BOLT HEAD HAS TO REMAIN CLEAN AND PROVIDE 4.00 mm (0.157 in) CLEARANCE FROM PROTECTION TO BOLT HEAD.
USE A SELF-ADHESIVE ROUND TAPE TO PROTECT THE BOLT HEAD TOP SURFACE.
WASHER
BOLT
FRAME
(32) (31)
01
(13)
(14)
LH
RH
(15)
(16)
LH
RH (33)
25.00 mm
(0.985 in)
25.00 mm
(0.985 in)
BOLT
03
MIN MIN
16.00 mm
(0.630 in)
15.00 mm
(0.591 in)
WASHER
BOLT
FRAME
(32) (31)
01
(9)
(10)
LH
RH
(11)
(12)
LH
RH (30)
25.00 mm
(0.985 in)
25.00 mm
(0.985 in)
BOLT
03
MIN MIN
17.00 mm
(0.669 in)
17.00 mm
(0.669 in)
02 02
0101
03
0404
05
0506
06
05
07
07
03
0404
05
0506
06
05
07
07
ICN-A350-A-55XXP002-A-FAPE3-03MKW-A-004-01

### Page 26

A350
SERVICE BULLETIN
Figure ICN-A350-A-55XXP002-A-FAPE3-03ONC-A-003-01 SHEET 4/4
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18
Application of Sealant and Protective
Treatment on T ension Bolts, LH and RH side Page 26
CONF 001
FWD E E
LH SHOWN
RH SYMMETRICAL
APPLY BEAD SEALANT FLEXIBLE STRUCTURE COATING MATERIAL No 04QAB2.
APPLY CORROSION PREVENTIVE COMPOUND MATERIAL No 12AEB1.
APPLY POLYSULFIDE SEALANT MATERIAL No 06ACB1 ON BOLT, WASHER, FRAME
AND AROUND THE BOLT HEAD.
03
02
01
NOTE:
WET INSTALL THE FASTENERS WITH POLYSULFIDE SEALANT No 06ACA1.04
05
06
APPLY CORROSION INHIBITING FASTENER HEAD PROTECTION COATING MATERIAL No 04QAC5.
USE A SELF-ADHESIVE ROUND TAPE TO PROTECT THE BOLT HEAD TOP SURFACE.
WASHER
BOLT
FRAME
(32) (31)
01
(5)
(6)
LH
RH
(7)
(8)
LH
RH (30)
25.00 mm
(0.985 in)
25.00 mm
(0.985 in)
BOLT
03
MIN MIN
17.00 mm
(0.669 in)
16.00 mm
(0.630 in)
02
01
03
0404
05
0506
06
05
07
07
TOP OF THE BOLT HEAD HAS TO REMAIN CLEAN AND PROVIDE 4.00 mm (0.157 in)
CLEARANCE FROM PROTECTION TO BOLT HEAD.
07
ICN-A350-A-55XXP002-A-FAPE3-03ONC-A-003-01

### Page 27

A350
SERVICE BULLETIN
Figure ICN-A350-A-55XXP002-A-FAPE3-03C9K-A-002-01 SHEET 1/4
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18
Application of Sealant and Protective Treatment on T ension Bolts, LH and RH side
Page 27
CONF 002
Z311
Z312
LH
RH
A
A
FWD
CL
STGR1LH
STGR2LH
STGR1RH
STGR2RH
FR94 FR95 FR96 FR97 FR98
A A
B B C C D D E E
EEDDCCBBAA
ICN-A350-A-55XXP002-A-FAPE3-03C9K-A-002-01

### Page 28

A350
SERVICE BULLETIN
Figure ICN-A350-A-55XXP002-A-FAPE3-03C9L-A-004-01 SHEET 2/4
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18
Application of Sealant and Protective Treatment on T ension Bolts, LH and RH side
Page 28
CONF 002
APPLY CORROSION PREVENTIVE COMPOUND MATERIAL No 12AEB1.
WASHER
BOLT
FRAME
(32) (31)
APPLY CORROSION INHIBITING FASTENER HEAD PROTECTION COATING MATERIAL No 04QAC5.
WET INSTALL THE FASTENERS WITH POLYSULFIDE SEALANT No 06ACA1.
13.00 mm
(0.512 in)
A A B B
(21)
FWD FWD
(22)
LH
RH
(23)
(24)
LH
RH (34)
LH SHOWN
RH SYMMETRICAL
LH SHOWN
RH SYMMETRICAL
TOP OF THE BOLT HEAD HAS TO REMAIN CLEAN AND PROVIDE 4.00 mm (0.157 in) CLEARANCE FROM PROTECTION TO BOLT HEAD.
25.00 mm
(0.985 in)
13.00 mm
(0.512 in)
25.00 mm
(0.985 in)
BOLT
USE A SELF-ADHESIVE ROUND TAPE TO PROTECT THE BOLT HEAD TOP SURFACE.
MIN MIN
WASHER
BOLT
FRAME
(32) (31) (17)(18) LHRH
(19)
(20)
LH
RH (34)
25.00 mm
(0.985 in)
25.00 mm
(0.985 in)
BOLT
MIN MIN
14.00 mm
(0.551 in)
14.00 mm
(0.551 in)
03
02
04
05
06
01
NOTE:
01 01
01
01
EXISTING SEALANT LAYER.
02
0303
0303
020202
0303
04
04
04
04
05
05
05
05
06 06
ICN-A350-A-55XXP002-A-FAPE3-03C9L-A-004-01

### Page 29

A350
SERVICE BULLETIN
Figure ICN-A350-A-55XXP002-A-FAPE3-044Q9-A-002-01 SHEET 3/4
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18
Application of Sealant and Protective Treatment on T ension Bolts, LH and RH side
Page 29
CONF 002
FWD D D
LH SHOWN
RH SYMMETRICAL
C CFWD
LH SHOWN
RH SYMMETRICAL
WASHER
BOLT
FRAME
(32) (31) (13)(14) LHRH
(15)
(16)
LH
RH (33)
25.00 mm
(0.985 in)
25.00 mm
(0.985 in)
BOLT
MIN MIN
16.00 mm
(0.630 in)
15.00 mm
(0.591 in)
WASHER
BOLT
FRAME
(32) (31) (9)(10) LHRH
(11)
(12)
LH
RH (30)
25.00 mm
(0.985 in)
25.00 mm
(0.985 in)
BOLT
MIN MIN
17.00 mm
(0.669 in)
17.00 mm
(0.669 in)
APPLY CORROSION PREVENTIVE COMPOUND MATERIAL No 12AEB1.
APPLY CORROSION INHIBITING FASTENER HEAD PROTECTION COATING MATERIAL No 04QAC5.
WET INSTALL THE FASTENERS WITH POLYSULFIDE SEALANT No 06ACA1.
TOP OF THE BOLT HEAD HAS TO REMAIN CLEAN AND PROVIDE 4.00 mm (0.157 in) CLEARANCE FROM PROTECTION TO BOLT HEAD.
USE A SELF-ADHESIVE ROUND TAPE TO PROTECT THE BOLT HEAD TOP SURFACE.
03
02
04
05
06
01
NOTE:
EXISTING SEALANT LAYER.
01 01
02
03
02
0303
04
04
05
05
06 01 01
02
03
02
0303
04
04
05
05
06
ICN-A350-A-55XXP002-A-FAPE3-044Q9-A-002-01

### Page 30

A350
SERVICE BULLETIN
Figure ICN-A350-A-55XXP002-A-FAPE3-044QA-A-002-01 SHEET 4/4
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18
Application of Sealant and Protective
Treatment on T ension Bolts, LH and RH side Page 30
CONF 002
FWD E E
LH SHOWN
RH SYMMETRICAL
WASHER
BOLT
FRAME
(32) (31) (5)(6) LHRH
(7)
(8)
LH
RH (30)
25.00 mm
(0.985 in)
25.00 mm
(0.985 in)
BOLT
MIN MIN
17.00 mm
(0.669 in)
16.00 mm
(0.630 in)
APPLY CORROSION PREVENTIVE COMPOUND MATERIAL No 12AEB1.
APPLY CORROSION INHIBITING FASTENER HEAD PROTECTION COATING MATERIAL No 04QAC5.
WET INSTALL THE FASTENERS WITH POLYSULFIDE SEALANT No 06ACA1.
TOP OF THE BOLT HEAD HAS TO REMAIN CLEAN AND PROVIDE 4.00 mm (0.157 in) CLEARANCE
USE A SELF-ADHESIVE ROUND TAPE TO PROTECT THE BOLT HEAD TOP SURFACE.
03
02
04
01
NOTE:
FROM PROTECTION TO BOLT HEAD.
EXISTING SEALANT LAYER.
01 01
02
03
02
0303
04
04
05
05
06
06
05
ICN-A350-A-55XXP002-A-FAPE3-044QA-A-002-01

### Page 31

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 31
CONF ALL
C. PROCEDURE
CONF 001
(1) Task A350-A-55-XX-P002-01001-920A-A - Apply Sealant and Protective
Treatment on Tension Bolts, Left Hand (LH) and Right Hand (RH) side
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
Access Door 311AB, Door 311BB311
Work location From Frame 94 to Frame 98
312
Manpower/Resources/Skills
Man-hours 14.00 h
Minimum Number of person 1
Elapsed Time 14.00 h
Skills Airframe
Material necessary to do the job
Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
04QAB2 Coating - - FlexibleStructure
04QAC5
Coating - - Corrosion
Inhibiting Fastener Head
Protection
06ACA1
Polysulfide Sealant - Low
Density MultiPurpose
Brushable
06ACB1 Polysulfide Sealant - LowDensity MultiPurpose Fillet
08BAA9 Non Aqueous Cleaner -General
12AEB1
Corrosion Preventive
Compound - Heavy Duty
Long Durability Hard Film
14SBA1 T extile - Lint free Cotton
Referenced Information
Manuals/Drawings References/Sheets
ASR
A350-A-51-24-XX-01ZZZ-667Z-A
A350-A-51-42-XX-01ZZZ-667Z-A
A350-A-51-75-12-00ZZZ-660Z-A
MP A350-A-20-51-50-01ZZZ-25BZ-A
SD
A350-A-06-2X-XX-01ZZZ-04CZ-A
A350-A-06-3X-XX-01ZZZ-04CZ-A
A350-A-06-4X-XX-01ZZZ-04CZ-A

### Page 32

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 32
Manuals/Drawings References/Sheets
CML CONSUMABLE MATERIAL LIST (CML)
Procedure
(a) Standard Practices:
1 For the specification of Material application codes given in this Service
Bulletin, refer to the Ref. CML.
2 For the Frame (FR) identification, refer to Ref. SD A350-A-06-2X-
XX-01ZZZ-04CZ-A.
3 For the Zone identification, refer to Ref. SD A350-A-06-3X-XX-01ZZZ-04CZ-
A.
4 For the identification of access panels, refer to Ref. SD A350-A-06-4X-
XX-01ZZZ-04CZ-A.
5 Apply sealant in accordance with Ref. ASR A350-A-51-24-XX-01ZZZ-667Z-A.
6 Renew the protective finish in accordance with Ref. ASR A350-
A-51-75-12-00ZZZ-660Z-A.
7 T ag all the parts you must remove and retain to make the subsequent
installation easier.
8 Put all the retained hardware in identified plastic bags and attach the bags
to the related unit.
9 For standard mechanical torques, refer to Ref. MP A350-
A-20-51-50-01ZZZ-25BZ-A.
(b) Remove the existing sealant and flexible structure coating by using non metallic
scrapper.
(c) Remove, refer to Ref. Fig. Application of Sealant and Protective Treatment on
T ension Bolts, LH and RH side:
1 Bracket   Item (5) Retain
1 Bracket   Item (6) Retain
1 Bracket   Item (7) Retain
1 Bracket   Item (8) Retain
1 Bracket   Item (9) Retain
1 Bracket   Item (10) Retain
1 Bracket   Item (11) Retain
1 Bracket   Item (12) Retain
1 Bracket   Item (13) Retain
1 Bracket   Item (14) Retain
1 Bracket   Item (15) Retain
1 Bracket   Item (16) Retain
1 Bracket   Item (17) Retain
1 Bracket   Item (18) Retain

### Page 33

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 33
1 Bracket   Item (19) Retain
1 Bracket   Item (20) Retain
1 Bracket   Item (21) Retain
1 Bracket   Item (22) Retain
1 Bracket   Item (23) Retain
1 Bracket   Item (24) Retain
8 Bolt   Item (30) Retain
20 Washer   Item (31) Retain
20 Nut   Item (32) Retain
4 Bolt   Item (33) Retain
8 Bolt   Item (34) Retain
(d) Clean the work area with:
  T extile - Lint free Cotton14SBA1  
and
  Non Aqueous Cleaner -
General
08BAA9  
(e) Apply a self-adhesive round tape on the bolt head top surface.
(f) Apply as shown on Ref. Fig. Application of Sealant and Protective Treatment
on T ension Bolts, LH and RH side SHEET 2, Ref. Fig. Application of Sealant
and Protective Treatment on T ension Bolts, LH and RH side SHEET 3, Ref. Fig.
Application of Sealant and Protective Treatment on T ension Bolts, LH and RH side
SHEET 4 and in accordance with Ref. ASR A350-A-51-24-XX-01ZZZ-667Z-A:
  Polysulfide Sealant
- Low Density
MultiPurpose Fillet
06ACB1  
 
After the drying process, apply:
  Coating - - Flexible
Structure
04QAB2  
 
After the drying process, apply:
  Corrosion Preventive
Compound - Heavy
Duty Long Durability
Hard Film
12AEB1  
(g) Remove the self-adhesive round tape.
(h) Install, refer to Ref. Fig. Application of Sealant and Protective Treatment on
T ension Bolts, LH and RH side and in accordance with Ref. ASR A350-A-51-42-
XX-01ZZZ-667Z-A:
1 Bracket   Item (5) Retained
1 Bracket   Item (6) Retained

### Page 34

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 34
1 Bracket   Item (7) Retained
1 Bracket   Item (8) Retained
1 Bracket   Item (9) Retained
1 Bracket   Item (10) Retained
1 Bracket   Item (11) Retained
1 Bracket   Item (12) Retained
1 Bracket   Item (13) Retained
1 Bracket   Item (14) Retained
1 Bracket   Item (15) Retained
1 Bracket   Item (16) Retained
1 Bracket   Item (17) Retained
1 Bracket   Item (18) Retained
1 Bracket   Item (19) Retained
1 Bracket   Item (20) Retained
1 Bracket   Item (21) Retained
1 Bracket   Item (22) Retained
1 Bracket   Item (23) Retained
1 Bracket   Item (24) Retained
8 Bolt   Item (30) Retained
20 Washer   Item (31) Retained
20 Nut   Item (32) Retained
4 Bolt   Item (33) Retained
8 Bolt   Item (34) Retained
with
  Polysulfide Sealant
- Low Density
MultiPurpose Brushable
06ACA1  
(i) Apply as shown on Ref. Fig. Application of Sealant and Protective Treatment
on T ension Bolts, LH and RH side SHEET 2, Ref. Fig. Application of Sealant
and Protective Treatment on T ension Bolts, LH and RH side SHEET 3, Ref. Fig.
Application of Sealant and Protective Treatment on T ension Bolts, LH and RH side
SHEET 4 and in accordance with Ref. ASR A350-A-51-24-XX-01ZZZ-667Z-A:
  Coating - - Corrosion
Inhibiting Fastener Head
Protection
04QAC5

### Page 35

A350
SERVICE BULLETIN
Figure ICN-A350-A-55XXP002-A-FAPE3-03C9I-A-003-01 SHEET 1/4
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18
Application of Sealant and Protective Treatment on T ension Bolts, LH and RH side
Page 35
CONF 001
Z311
Z312
LH
RH
A
A
FWD
CL
STGR1LH
STGR2LH
STGR1RH
STGR2RH
FR94 FR95 FR96 FR97 FR98
A A
B B C C D D E E
EEDDCCBBAA
ICN-A350-A-55XXP002-A-FAPE3-03C9I-A-003-01

### Page 36

A350
SERVICE BULLETIN
Figure ICN-A350-A-55XXP002-A-FAPE3-03C9J-A-007-01 SHEET 2/4
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18
Application of Sealant and Protective Treatment on T ension Bolts, LH and RH side
Page 36
CONF 001
APPLY BEAD SEALANT FLEXIBLE STRUCTURE COATING MATERIAL No 04QAB2.
APPLY CORROSION PREVENTIVE COMPOUND MATERIAL No 12AEB1.
APPLY POLYSULFIDE SEALANT MATERIAL No 06ACB1 ON BOLT, WASHER, FRAME
AND AROUND THE BOLT HEAD.
03
02
01
NOTE:
WASHER
BOLT
FRAME
04
05
06
(32) (31)
APPLY CORROSION INHIBITING FASTENER HEAD PROTECTION COATING MATERIAL No 04QAC5.
WET INSTALL THE FASTENERS WITH POLYSULFIDE SEALANT No 06ACA1.
01
13.00 mm
(0.512 in)
A A B B
(21)
FWD FWD
(22)
LH
RH
(23)
(24)
LH
RH (34)
LH SHOWN
RH SYMMETRICAL
LH SHOWN
RH SYMMETRICAL
07
TOP OF THE BOLT HEAD HAS TO REMAIN CLEAN AND PROVIDE 4.00 mm (0.157 in) CLEARANCE FROM PROTECTION TO BOLT HEAD.
25.00 mm
(0.985 in)
13.00 mm
(0.512 in)
25.00 mm
(0.985 in)
BOLT
USE A SELF-ADHESIVE ROUND TAPE TO PROTECT THE BOLT HEAD TOP SURFACE.
03 03
MIN MIN
WASHER
BOLT
FRAME
(32) (31)
01
(17)
(18)
LH
RH
(19)
(20)
LH
RH (34)
25.00 mm
(0.985 in)
25.00 mm
(0.985 in)
BOLT
03
MIN MIN
14.00 mm
(0.551 in)
14.00 mm
(0.551 in)
01
02 02
01
0404 0404
05
05 0506
06
06
06
05 0505
03
07
07
07
07
ICN-A350-A-55XXP002-A-FAPE3-03C9J-A-007-01

### Page 37

A350
SERVICE BULLETIN
Figure ICN-A350-A-55XXP002-A-FAPE3-03MKW-A-004-01 SHEET 3/4
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18
Application of Sealant and Protective Treatment on T ension Bolts, LH and RH side
Page 37
CONF 001
FWD D D
LH SHOWN
RH SYMMETRICAL
C CFWD
LH SHOWN
RH SYMMETRICAL
APPLY BEAD SEALANT FLEXIBLE STRUCTURE COATING MATERIAL No 04QAB2.
APPLY CORROSION PREVENTIVE COMPOUND MATERIAL No 12AEB1.
APPLY POLYSULFIDE SEALANT MATERIAL No 06ACB1 ON BOLT, WASHER, FRAME
AND AROUND THE BOLT HEAD.
03
02
01
NOTE:
04
05
06
APPLY CORROSION INHIBITING FASTENER HEAD PROTECTION COATING MATERIAL No 04QAC5.
WET INSTALL THE FASTENERS WITH POLYSULFIDE SEALANT No 06ACA1.
07
TOP OF THE BOLT HEAD HAS TO REMAIN CLEAN AND PROVIDE 4.00 mm (0.157 in) CLEARANCE FROM PROTECTION TO BOLT HEAD.
USE A SELF-ADHESIVE ROUND TAPE TO PROTECT THE BOLT HEAD TOP SURFACE.
WASHER
BOLT
FRAME
(32) (31)
01
(13)
(14)
LH
RH
(15)
(16)
LH
RH (33)
25.00 mm
(0.985 in)
25.00 mm
(0.985 in)
BOLT
03
MIN MIN
16.00 mm
(0.630 in)
15.00 mm
(0.591 in)
WASHER
BOLT
FRAME
(32) (31)
01
(9)
(10)
LH
RH
(11)
(12)
LH
RH (30)
25.00 mm
(0.985 in)
25.00 mm
(0.985 in)
BOLT
03
MIN MIN
17.00 mm
(0.669 in)
17.00 mm
(0.669 in)
02 02
0101
03
0404
05
0506
06
05
07
07
03
0404
05
0506
06
05
07
07
ICN-A350-A-55XXP002-A-FAPE3-03MKW-A-004-01

### Page 38

A350
SERVICE BULLETIN
Figure ICN-A350-A-55XXP002-A-FAPE3-03ONC-A-003-01 SHEET 4/4
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18
Application of Sealant and Protective
Treatment on T ension Bolts, LH and RH side Page 38
CONF 001
FWD E E
LH SHOWN
RH SYMMETRICAL
APPLY BEAD SEALANT FLEXIBLE STRUCTURE COATING MATERIAL No 04QAB2.
APPLY CORROSION PREVENTIVE COMPOUND MATERIAL No 12AEB1.
APPLY POLYSULFIDE SEALANT MATERIAL No 06ACB1 ON BOLT, WASHER, FRAME
AND AROUND THE BOLT HEAD.
03
02
01
NOTE:
WET INSTALL THE FASTENERS WITH POLYSULFIDE SEALANT No 06ACA1.04
05
06
APPLY CORROSION INHIBITING FASTENER HEAD PROTECTION COATING MATERIAL No 04QAC5.
USE A SELF-ADHESIVE ROUND TAPE TO PROTECT THE BOLT HEAD TOP SURFACE.
WASHER
BOLT
FRAME
(32) (31)
01
(5)
(6)
LH
RH
(7)
(8)
LH
RH (30)
25.00 mm
(0.985 in)
25.00 mm
(0.985 in)
BOLT
03
MIN MIN
17.00 mm
(0.669 in)
16.00 mm
(0.630 in)
02
01
03
0404
05
0506
06
05
07
07
TOP OF THE BOLT HEAD HAS TO REMAIN CLEAN AND PROVIDE 4.00 mm (0.157 in)
CLEARANCE FROM PROTECTION TO BOLT HEAD.
07
ICN-A350-A-55XXP002-A-FAPE3-03ONC-A-003-01

### Page 39

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 39
CONF 002
(1) Task A350-A-55-XX-P002-01002-920A-A - Apply Sealant and Protective
Treatment on Tension Bolts, Left Hand (LH) and Right Hand (RH) side
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
Access Door 311AB, Door 311BB311
Work location From Frame 94 to Frame 98
312
Manpower/Resources/Skills
Man-hours 14.00 h
Minimum Number of person 1
Elapsed Time 14.00 h
Skills Airframe
Material necessary to do the job
Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
04QAC5
Coating - - Corrosion
Inhibiting Fastener Head
Protection
06ACA1
Polysulfide Sealant - Low
Density MultiPurpose
Brushable
08BAA9 Non Aqueous Cleaner -General
12AEB1
Corrosion Preventive
Compound - Heavy Duty
Long Durability Hard Film
14SBA1 T extile - Lint free Cotton
Referenced Information
Manuals/Drawings References/Sheets
ASR
A350-A-51-24-XX-01ZZZ-667Z-A
A350-A-51-42-XX-01ZZZ-667Z-A
A350-A-51-75-12-00ZZZ-660Z-A
MP A350-A-20-51-50-01ZZZ-25BZ-A
SD
A350-A-06-2X-XX-01ZZZ-04CZ-A
A350-A-06-3X-XX-01ZZZ-04CZ-A
A350-A-06-4X-XX-01ZZZ-04CZ-A
CML CONSUMABLE MATERIAL LIST (CML)
Procedure
(a) Standard Practices:
1 For the specification of Material application codes given in this Service
Bulletin, refer to the Ref. CML.

### Page 40

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 40
2 For the FR identification, refer to Ref. SD A350-A-06-2X-XX-01ZZZ-04CZ-A.
3 For the Zone identification, refer to Ref. SD A350-A-06-3X-XX-01ZZZ-04CZ-
A.
4 For the identification of access panels, refer to Ref. SD A350-A-06-4X-
XX-01ZZZ-04CZ-A.
5 Apply sealant in accordance with Ref. ASR A350-A-51-24-XX-01ZZZ-667Z-A.
6 Renew the protective finish in accordance with Ref. ASR A350-
A-51-75-12-00ZZZ-660Z-A.
7 T ag all the parts you must remove and retain to make the subsequent
installation easier.
8 Put all the retained hardware in identified plastic bags and attach the bags
to the related unit.
9 For standard mechanical torques, refer to Ref. MP A350-
A-20-51-50-01ZZZ-25BZ-A.
(b) Remove, refer to Ref. Fig. Application of Sealant and Protective Treatment on
T ension Bolts, LH and RH side:
1 Bracket   Item (5) Retain
1 Bracket   Item (6) Retain
1 Bracket   Item (7) Retain
1 Bracket   Item (8) Retain
1 Bracket   Item (9) Retain
1 Bracket   Item (10) Retain
1 Bracket   Item (11) Retain
1 Bracket   Item (12) Retain
1 Bracket   Item (13) Retain
1 Bracket   Item (14) Retain
1 Bracket   Item (15) Retain
1 Bracket   Item (16) Retain
1 Bracket   Item (17) Retain
1 Bracket   Item (18) Retain
1 Bracket   Item (19) Retain
1 Bracket   Item (20) Retain
1 Bracket   Item (21) Retain
1 Bracket   Item (22) Retain
1 Bracket   Item (23) Retain
1 Bracket   Item (24) Retain
8 Bolt   Item (30) Retain

### Page 41

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 41
20 Washer   Item (31) Retain
20 Nut   Item (32) Retain
4 Bolt   Item (33) Retain
8 Bolt   Item (34) Retain
(c) Clean the work area with:
  T extile - Lint free Cotton14SBA1  
and
  Non Aqueous Cleaner -
General
08BAA9  
(d) Apply a self-adhesive round tape on the bolt head top surface.
(e) Apply as shown on Ref. Fig. Application of Sealant and Protective Treatment
on T ension Bolts, LH and RH side SHEET 2, Ref. Fig. Application of Sealant
and Protective Treatment on T ension Bolts, LH and RH side SHEET 3, Ref. Fig.
Application of Sealant and Protective Treatment on T ension Bolts, LH and RH side
SHEET 4 and in accordance with Ref. ASR A350-A-51-24-XX-01ZZZ-667Z-A:
  Corrosion Preventive
Compound - Heavy
Duty Long Durability
Hard Film
12AEB1  
(f) Remove the self-adhesive round tape.
(g) Install, refer to Ref. Fig. Application of Sealant and Protective Treatment on
T ension Bolts, LH and RH side and in accordance with Ref. ASR A350-A-51-42-
XX-01ZZZ-667Z-A:
1 Bracket   Item (5) Retained
1 Bracket   Item (6) Retained
1 Bracket   Item (7) Retained
1 Bracket   Item (8) Retained
1 Bracket   Item (9) Retained
1 Bracket   Item (10) Retained
1 Bracket   Item (11) Retained
1 Bracket   Item (12) Retained
1 Bracket   Item (13) Retained
1 Bracket   Item (14) Retained
1 Bracket   Item (15) Retained
1 Bracket   Item (16) Retained
1 Bracket   Item (17) Retained
1 Bracket   Item (18) Retained
1 Bracket   Item (19) Retained

### Page 42

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 42
1 Bracket   Item (20) Retained
1 Bracket   Item (21) Retained
1 Bracket   Item (22) Retained
1 Bracket   Item (23) Retained
1 Bracket   Item (24) Retained
8 Bolt   Item (30) Retained
20 Washer   Item (31) Retained
20 Nut   Item (32) Retained
4 Bolt   Item (33) Retained
8 Bolt   Item (34) Retained
with
  Polysulfide Sealant
- Low Density
MultiPurpose Brushable
06ACA1  
(h) Apply as shown on Ref. Fig. Application of Sealant and Protective Treatment
on T ension Bolts, LH and RH side SHEET 2, Ref. Fig. Application of Sealant
and Protective Treatment on T ension Bolts, LH and RH side SHEET 3, Ref. Fig.
Application of Sealant and Protective Treatment on T ension Bolts, LH and RH side
SHEET 4 and in accordance with Ref. ASR A350-A-51-24-XX-01ZZZ-667Z-A:
  Coating - - Corrosion
Inhibiting Fastener Head
Protection
04QAC5

### Page 43

A350
SERVICE BULLETIN
Figure ICN-A350-A-55XXP002-A-FAPE3-03C9K-A-002-01 SHEET 1/4
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18
Application of Sealant and Protective Treatment on T ension Bolts, LH and RH side
Page 43
CONF 002
Z311
Z312
LH
RH
A
A
FWD
CL
STGR1LH
STGR2LH
STGR1RH
STGR2RH
FR94 FR95 FR96 FR97 FR98
A A
B B C C D D E E
EEDDCCBBAA
ICN-A350-A-55XXP002-A-FAPE3-03C9K-A-002-01

### Page 44

A350
SERVICE BULLETIN
Figure ICN-A350-A-55XXP002-A-FAPE3-03C9L-A-004-01 SHEET 2/4
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18
Application of Sealant and Protective Treatment on T ension Bolts, LH and RH side
Page 44
CONF 002
APPLY CORROSION PREVENTIVE COMPOUND MATERIAL No 12AEB1.
WASHER
BOLT
FRAME
(32) (31)
APPLY CORROSION INHIBITING FASTENER HEAD PROTECTION COATING MATERIAL No 04QAC5.
WET INSTALL THE FASTENERS WITH POLYSULFIDE SEALANT No 06ACA1.
13.00 mm
(0.512 in)
A A B B
(21)
FWD FWD
(22)
LH
RH
(23)
(24)
LH
RH (34)
LH SHOWN
RH SYMMETRICAL
LH SHOWN
RH SYMMETRICAL
TOP OF THE BOLT HEAD HAS TO REMAIN CLEAN AND PROVIDE 4.00 mm (0.157 in) CLEARANCE FROM PROTECTION TO BOLT HEAD.
25.00 mm
(0.985 in)
13.00 mm
(0.512 in)
25.00 mm
(0.985 in)
BOLT
USE A SELF-ADHESIVE ROUND TAPE TO PROTECT THE BOLT HEAD TOP SURFACE.
MIN MIN
WASHER
BOLT
FRAME
(32) (31) (17)(18) LHRH
(19)
(20)
LH
RH (34)
25.00 mm
(0.985 in)
25.00 mm
(0.985 in)
BOLT
MIN MIN
14.00 mm
(0.551 in)
14.00 mm
(0.551 in)
03
02
04
05
06
01
NOTE:
01 01
01
01
EXISTING SEALANT LAYER.
02
0303
0303
020202
0303
04
04
04
04
05
05
05
05
06 06
ICN-A350-A-55XXP002-A-FAPE3-03C9L-A-004-01

### Page 45

A350
SERVICE BULLETIN
Figure ICN-A350-A-55XXP002-A-FAPE3-044Q9-A-002-01 SHEET 3/4
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18
Application of Sealant and Protective Treatment on T ension Bolts, LH and RH side
Page 45
CONF 002
FWD D D
LH SHOWN
RH SYMMETRICAL
C CFWD
LH SHOWN
RH SYMMETRICAL
WASHER
BOLT
FRAME
(32) (31) (13)(14) LHRH
(15)
(16)
LH
RH (33)
25.00 mm
(0.985 in)
25.00 mm
(0.985 in)
BOLT
MIN MIN
16.00 mm
(0.630 in)
15.00 mm
(0.591 in)
WASHER
BOLT
FRAME
(32) (31) (9)(10) LHRH
(11)
(12)
LH
RH (30)
25.00 mm
(0.985 in)
25.00 mm
(0.985 in)
BOLT
MIN MIN
17.00 mm
(0.669 in)
17.00 mm
(0.669 in)
APPLY CORROSION PREVENTIVE COMPOUND MATERIAL No 12AEB1.
APPLY CORROSION INHIBITING FASTENER HEAD PROTECTION COATING MATERIAL No 04QAC5.
WET INSTALL THE FASTENERS WITH POLYSULFIDE SEALANT No 06ACA1.
TOP OF THE BOLT HEAD HAS TO REMAIN CLEAN AND PROVIDE 4.00 mm (0.157 in) CLEARANCE FROM PROTECTION TO BOLT HEAD.
USE A SELF-ADHESIVE ROUND TAPE TO PROTECT THE BOLT HEAD TOP SURFACE.
03
02
04
05
06
01
NOTE:
EXISTING SEALANT LAYER.
01 01
02
03
02
0303
04
04
05
05
06 01 01
02
03
02
0303
04
04
05
05
06
ICN-A350-A-55XXP002-A-FAPE3-044Q9-A-002-01

### Page 46

A350
SERVICE BULLETIN
Figure ICN-A350-A-55XXP002-A-FAPE3-044QA-A-002-01 SHEET 4/4
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18
Application of Sealant and Protective
Treatment on T ension Bolts, LH and RH side Page 46
CONF 002
FWD E E
LH SHOWN
RH SYMMETRICAL
WASHER
BOLT
FRAME
(32) (31) (5)(6) LHRH
(7)
(8)
LH
RH (30)
25.00 mm
(0.985 in)
25.00 mm
(0.985 in)
BOLT
MIN MIN
17.00 mm
(0.669 in)
16.00 mm
(0.630 in)
APPLY CORROSION PREVENTIVE COMPOUND MATERIAL No 12AEB1.
APPLY CORROSION INHIBITING FASTENER HEAD PROTECTION COATING MATERIAL No 04QAC5.
WET INSTALL THE FASTENERS WITH POLYSULFIDE SEALANT No 06ACA1.
TOP OF THE BOLT HEAD HAS TO REMAIN CLEAN AND PROVIDE 4.00 mm (0.157 in) CLEARANCE
USE A SELF-ADHESIVE ROUND TAPE TO PROTECT THE BOLT HEAD TOP SURFACE.
03
02
04
01
NOTE:
FROM PROTECTION TO BOLT HEAD.
EXISTING SEALANT LAYER.
01 01
02
03
02
0303
04
04
05
05
06
06
05
ICN-A350-A-55XXP002-A-FAPE3-044QA-A-002-01

### Page 47

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 47
CONF 001
(2) Task A350-A-55-XX-P002-02001-920A-A - Replace the Barrel Nut Plate(s)
with Shouldered Cap(s) in the Inner Hole of the Root Joint Fitting and Apply
Overlapping Sealant, LH and RH side
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
Access Door 311AB, Door 311AB311
Work location From Frame 94 to Frame 98
312
323 Access
Panel 321AL, Panel 323AL, Panel 323AR, Panel
323BL, Panel 323BR, Panel 323CL, Panel 323CR,
Panel 323DL, Panel 323DR, Panel 323EL, Panel
323ER, Panel 325AL, Panel 325AR
324
Manpower/Resources/Skills
Man-hours 14.00 h
Minimum Number of person 1
Elapsed Time 14.00 h
Skills Airframe
Material necessary to do the job
Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
04QAB2 Coating - - FlexibleStructure
06AAC1 Polysulfide Sealant -General Purpose Interfay
06ACB1 Polysulfide Sealant - LowDensity MultiPurpose Fillet
08BAA9 Non Aqueous Cleaner -General
14SBA1 T extile - Lint free Cotton
Part kit 55P002D01R02
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
1 V5537150620000 4 CAP
2 V5537150620200 4 CAP
3 V5537150620400 4 CAP
4 V5537150620600 8 CAP
Referenced Information
Manuals/Drawings References/Sheets
ASR A350-A-51-24-XX-01ZZZ-667Z-A
MP A350-A-20-51-50-01ZZZ-25BZ-A
SD A350-A-06-2X-XX-01ZZZ-04CZ-A

### Page 48

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 48
Manuals/Drawings References/Sheets
A350-A-06-3X-XX-01ZZZ-04CZ-A
A350-A-06-4X-XX-01ZZZ-04CZ-A
CML CONSUMABLE MATERIAL LIST (CML)
Procedure
(a) Standard Practices:
1 For the specification of Material application codes given in this Service
Bulletin, refer to the Ref. CML.
2 For the FR identification, refer to Ref. SD A350-A-06-2X-XX-01ZZZ-04CZ-A.
3 For the Zone identification, refer to Ref. SD A350-A-06-3X-XX-01ZZZ-04CZ-
A.
4 For the identification of access panels, refer to Ref. SD A350-A-06-4X-
XX-01ZZZ-04CZ-A.
5 Apply sealant in accordance with Ref. ASR A350-A-51-24-XX-01ZZZ-667Z-A.
6 For standard mechanical torques, refer to Ref. MP A350-
A-20-51-50-01ZZZ-25BZ-A.
(b) Remove the existing barrel nut plate(s) and sealant by using non metallic
scrapper as shown on Ref. Fig. Installation of the Shouldered Cap(s) in the Inner
Hole of the Root Joint Fitting, LH and RH side SHEET 2.
1 At Frame 94, remove:
1 PLATE V5537135220000 Item (1) Discard
 
Clean the work area with:
  T extile - Lint free Cotton14SBA1  
and
  Non Aqueous Cleaner -
General
08BAA9  
 
Install:
4 CAP V5537150620000 Item 1
 
At Frame 95, remove:
4 CAP V5537135220200 Item (2) Discard
 
Clean the work area with:
  T extile - Lint free Cotton14SBA1  
and
  Non Aqueous Cleaner -
General
08BAA9  
 
Install:
4 CAP V5537150620200 Item 2
 
At Frame 96, remove:

### Page 49

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 49
4 CAP V5537135220400 Item (3) Discard
 
Clean the work area with:
  T extile - Lint free Cotton14SBA1  
and
  Non Aqueous Cleaner -
General
08BAA9  
 
Install:
4 CAP V5537150620400 Item 3
 
At Frame 97 and Frame 98, remove:
8 CAP V5537135220600 Item (4) Discard
 
Clean the work area with:
  T extile - Lint free Cotton14SBA1  
and
  Non Aqueous Cleaner -
General
08BAA9  
 
Install:
8 CAP V5537150620600 Item 4
 
with
  Polysulfide Sealant
- General Purpose
Interfay
06AAC1  
(c) Apply on all shouldered caps as shown on Ref. Fig. Installation of the Shouldered
Cap(s) in the Inner Hole of the Root Joint Fitting, LH and RH side SHEET 2 view C
and in accordance with Ref. ASR A350-A-51-24-XX-01ZZZ-667Z-A:
  Polysulfide Sealant
- Low Density
MultiPurpose Fillet
06ACB1  
 
After the drying process, apply:
  Coating - - Flexible
Structure
04QAB2

### Page 50

A350
SERVICE BULLETIN
Figure ICN-A350-A-55XXP002-A-FAPE3-03IQ8-A-001-01 SHEET 1/2
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18
Installation of the Shouldered Cap(s) in the Inner
Hole of the Root Joint Fitting, LH and RH side Page 50
CONF 001
A
Z311
Z312
LH
RH
A
Z323
Z324
LH
RH
FR98
FR94
B
B
B
B
B
B
B
FR95
FR96
FR97
ICN-A350-A-55XXP002-A-FAPE3-03IQ8-A-001-01

### Page 51

A350
SERVICE BULLETIN
Figure ICN-A350-A-55XXP002-A-FAPE3-03IQ9-A-005-01 SHEET 2/2
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18
Installation of the Shouldered Cap(s) in the Inner Hole of the Root Joint Fitting, LH and RH side
Page 51
CONF 001
FR94
TYPICAL
VIEW LOOKING OUTBD
FR95
FR96
FR97
FR98
B
A
A
A
A
FR94
FR95
FR96
FR97
FR98
(1)
(2)
(3)
(4)
APPLY POLYSULFIDE FILLET SEALANT MATERIAL No 06ACB1.
APPLY BEAD SEALANT FLEXIBLE STRUCTURE COATING MATERIAL No 04QAB2.
NOTE:
APPLY POLYSULFIDE INTERFAY SEALANT MATERIAL No 06AAC1.
03
02
01
TYPICAL
A A
TYPICAL
CBARREL NUT
FR94
FR95
FR96
FR97
FR98
1
2
3
4
4
BEFORE
AFTER 5.00 mmMIN (0.197 in)
3.00 mm
(0.119 in) MIN
03
02
01
C D
TYPICAL
D
(4)
BARREL NUT
ICN-A350-A-55XXP002-A-FAPE3-03IQ9-A-005-01

### Page 52

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 52
CONF 002
(2) Task A350-A-55-XX-P002-02002-920A-A - Install Shouldered Cap(s) in the
Inner Hole of the Root Joint Fitting and Apply Overlapping Sealant, LH and
RH side
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
Access Door 311AB, Door 311BB311
Work location From Frame 94 to Frame 98
312
323 Access
Panel 321AL, Panel 323AL, Panel 323AR, Panel
323BL, Panel 323BR, Panel 323CL, Panel 323CR,
Panel 323DL, Panel 323DR, Panel 323EL, Panel
323ER, Panel 325AL, Panel 325AR
324
Manpower/Resources/Skills
Man-hours 12.00 h
Minimum Number of person 1
Elapsed Time 12.00 h
Skills Airframe
Material necessary to do the job
Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
04QAB2 Coating - - FlexibleStructure
06AAC1 Polysulfide Sealant -General Purpose Interfay
06ACB1 Polysulfide Sealant - LowDensity MultiPurpose Fillet
08BAA9 Non Aqueous Cleaner -General
14SBA1 T extile - Lint free Cotton
Referenced Information
Manuals/Drawings References/Sheets
ASR A350-A-51-24-XX-01ZZZ-667Z-A
MP A350-A-20-51-50-01ZZZ-25BZ-A
SD
A350-A-06-2X-XX-01ZZZ-04CZ-A
A350-A-06-3X-XX-01ZZZ-04CZ-A
A350-A-06-4X-XX-01ZZZ-04CZ-A
CML CONSUMABLE MATERIAL LIST (CML)
Procedure
(a) Standard Practices:

### Page 53

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 53
1 For the specification of Material application codes given in this Service
Bulletin, refer to the Ref. CML.
2 For the FR identification, refer to Ref. SD A350-A-06-2X-XX-01ZZZ-04CZ-A.
3 For the Zone identification, refer to Ref. SD A350-A-06-3X-XX-01ZZZ-04CZ-
A.
4 For the identification of access panels, refer to Ref. SD A350-A-06-4X-
XX-01ZZZ-04CZ-A.
5 Apply sealant in accordance with Ref. ASR A350-A-51-24-XX-01ZZZ-667Z-A.
6 For standard mechanical torques, refer to Ref. MP A350-
A-20-51-50-01ZZZ-25BZ-A.
(b) Remove as shown on Ref. Fig. Replacement of the Shouldered Cap(s) in the Inner
Hole of the Root Joint Fitting, LH and RH side SHEET 2 view C:
At Frame 94, remove:
4 Cap   Item (1) Retain
 
Clean the work area with:
  T extile - Lint free Cotton14SBA1  
and
  Non Aqueous Cleaner -
General
08BAA9  
 
Install:
4 Cap   Item (1) Retained
 
At Frame 95, remove:
4 Cap   Item (2) Retain
 
Clean the work area with:
  T extile - Lint free Cotton14SBA1  
and
  Non Aqueous Cleaner -
General
08BAA9  
 
Install:
4 Cap   Item (2) Retained
 
At Frame 96, remove:
4 Cap   Item (3) Retain
 
Clean the work area with:
  T extile - Lint free Cotton14SBA1  
and
  Non Aqueous Cleaner -
General
08BAA9

### Page 54

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 54
Install:
4 Cap   Item (3) Retained
 
At Frame 97 and Frame 98, remove:
8 Cap   Item (4) Retain
 
Clean the work area with:
  T extile - Lint free Cotton14SBA1  
and
  Non Aqueous Cleaner -
General
08BAA9  
 
Install:
8 Cap   Item (4) Retained
 
with:
  Polysulfide Sealant
- General Purpose
Interfay
06AAC1  
(c) Apply on all shouldered caps as shown on Ref. Fig. Replacement of the
Shouldered Cap(s) in the Inner Hole of the Root Joint Fitting, LH and RH side
SHEET 2 view C and in accordance with Ref. ASR A350-A-51-24-XX-01ZZZ-667Z-
A:
  Polysulfide Sealant
- Low Density
MultiPurpose Fillet
06ACB1  
 
After the drying process, apply:
  Coating - - Flexible
Structure
04QAB2

### Page 55

A350
SERVICE BULLETIN
Figure ICN-A350-A-55XXP002-A-FAPE3-03IQ6-A-001-01 SHEET 1/2
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18
Replacement of the Shouldered Cap(s) in the
Inner Hole of the Root Joint Fitting, LH and RH side Page 55
CONF 002
A
Z311
Z312
LH
RH
A
Z323
Z324
LH
RH
FR98
FR94
B
B
B
B
B
B
B
FR95
FR96
FR97
ICN-A350-A-55XXP002-A-FAPE3-03IQ6-A-001-01

### Page 56

A350
SERVICE BULLETIN
Figure ICN-A350-A-55XXP002-A-FAPE3-03IQ7-A-003-01 SHEET 2/2
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18
Replacement of the Shouldered Cap(s) in the Inner Hole of the Root Joint Fitting, LH and RH side
Page 56
CONF 002
FR94
TYPICAL
VIEW LOOKING OUTBD
FR95
FR96
FR97
FR98
B TYPICAL
TYPICAL
5.00 mm
3.00 mm
(0.119 in)
MIN (0.197 in)
MIN
APPLY POLYSULFIDE FILLET SEALANT MATERIAL No 06ACB1.
(1)
(2)
(3)
(4)
FR94
FR95
FR96
FR97
(4) FR98
A A
C
C
APPLY BEAD SEALANT FLEXIBLE STRUCTURE COATING MATERIAL No 04QAB2.
BARREL NUT
A
A
A
A
NOTE:
APPLY POLYSULFIDE INTERFAY SEALANT MATERIAL No 06AAC1.
03
02
01
03
02
01
ICN-A350-A-55XXP002-A-FAPE3-03IQ7-A-003-01

### Page 57

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 57
CONF 001
(3) Task A350-A-55-XX-P002-03001-920A-A - Apply Sealant and Protective
Treatment on Barrel Nut Holes, LH and RH side
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
Access Door 311AB, Door 311BB311
Work location From Frame 94 to Frame 98
312
323 Access
Panel 321AL, Panel 323AL, Panel 323AR, Panel
323BL, Panel 323BR, Panel 323CL, Panel 323CR,
Panel 323DL, Panel 323DR, Panel 323EL, Panel
323ER, Panel 325AL, Panel 325AR
324
Manpower/Resources/Skills
Man-hours 14.00 h
Minimum Number of person 1
Elapsed Time 14.00 h
Skills Airframe
Material necessary to do the job
Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
03FDB1 Mineral Oil base Grease -Anti-FrettingPaste
06ACA1
Polysulfide Sealant - Low
Density MultiPurpose
Brushable
06AEA1 Polysulfide Sealant - LowAdhesion Brushable
08BAA9 Non Aqueous Cleaner -General
12AEB1
Corrosion Preventive
Compound - Heavy Duty
Long Durability Hard Film
14DCB1 Release Agent - - SolvantBase
14SBA1 T extile - Lint free Cotton
Referenced Information
Manuals/Drawings References/Sheets
ASR
A350-A-51-24-XX-01ZZZ-667Z-A
A350-A-51-42-XX-01ZZZ-667Z-A
A350-A-51-75-12-00ZZZ-660Z-A
MP A350-A-20-51-50-01ZZZ-25BZ-A
SD A350-A-06-2X-XX-01ZZZ-04CZ-AA350-A-06-3X-XX-01ZZZ-04CZ-A

### Page 58

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 58
Manuals/Drawings References/Sheets
A350-A-06-4X-XX-01ZZZ-04CZ-A
CML CONSUMABLE MATERIAL LIST (CML)
Procedure
(a) Standard Practices:
1 For the specification of Material application codes given in this Service
Bulletin, refer to the Ref. CML.
2 For the FR identification, refer to Ref. SD A350-A-06-2X-XX-01ZZZ-04CZ-A.
3 For the Zone identification, refer to Ref. SD A350-A-06-3X-XX-01ZZZ-04CZ-
A.
4 For the identification of access panels, refer to Ref. SD A350-A-06-4X-
XX-01ZZZ-04CZ-A.
5 Apply sealant in accordance with Ref. ASR A350-A-51-24-XX-01ZZZ-667Z-A.
6 Renew the protective finish in accordance with Ref. ASR A350-
A-51-75-12-00ZZZ-660Z-A.
7 T ag all the parts you must remove and retain to make the subsequent
installation easier.
8 Put all the retained hardware in identified plastic bags and attach the bags
to the related unit.
9 For standard mechanical torques, refer to Ref. MP A350-
A-20-51-50-01ZZZ-25BZ-A.
(b) Remove, as shown on Ref. Fig. Removal and Installation of the Screws and the
Plate Covers, LH and RH side SHEET 1:
1 Plate Cover   Item (35) Retain
1 Plate Cover   Item (36) Retain
1 Plate Cover   Item (37) Retain
1 Plate Cover   Item (38) Retain
1 Plate Cover   Item (39) Retain
1 Plate Cover   Item (40) Retain
1 Plate Cover   Item (41) Retain
1 Plate Cover   Item (42) Retain
1 Plate Cover   Item (43) Retain
1 Plate Cover   Item (44) Retain
10 Screw   Item (45) Retain
NOTE: For MSNs 0006-0020 the screws used are NSA5191-3-5 (Hex Head) and
for MSNs 0021-0097 the screws used are DAN169K3-7 (Counter Sunk).
(c) Clean the work area with:
  T extile - Lint free Cotton14SBA1  
and

### Page 59

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 59
  Non Aqueous Cleaner -
General
08BAA9  
(d) Apply on top of the barrel nut as shown on Ref. Fig. Application of Sealant and
Protective Treatment on Barrel Nut Holes, LH and RH side SHEET 2 view C and in
accordance with Ref. ASR A350-A-51-24-XX-01ZZZ-667Z-A:
  Corrosion Preventive
Compound - Heavy
Duty Long Durability
Hard Film
12AEB1  
After the drying process, fill the barrel nut hole with:
  Polysulfide Sealant -
Low Adhesion Brushable
06AEA1  
(e) Fill the gap as shown on Ref. Fig. Removal and Installation of the Screws and the
Plate Covers, LH and RH side SHEET 2, with:
  Polysulfide Sealant
- Low Density
MultiPurpose Brushable
06ACA1  
(f) Apply release agent between cover plate and the fitting as shown on Ref. Fig.
Removal and Installation of the Screws and the Plate Covers, LH and RH side
SHEET 2 in accordance with Ref. ASR A350-A-51-24-XX-01ZZZ-667Z-A:
  Release Agent - -
Solvant Base
14DCB1  
(g) Install, as shown on Ref. Fig. Removal and Installation of the Screws and the
Plate Covers, LH and RH side and in accordance with Ref. ASR A350-A-51-42-
XX-01ZZZ-667Z-A:
1 Plate Cover   Item (35) Retained
1 Plate Cover   Item (36) Retained
1 Plate Cover   Item (37) Retained
1 Plate Cover   Item (38) Retained
1 Plate Cover   Item (39) Retained
1 Plate Cover   Item (40) Retained
1 Plate Cover   Item (41) Retained
1 Plate Cover   Item (42) Retained
1 Plate Cover   Item (43) Retained
1 Plate Cover   Item (44) Retained
10 Screw   Item (45) Retained
with
  Mineral Oil base Grease
- Anti-FrettingPaste
03FDB1  
NOTE: For MSNs 0006-0020 the screws used are NSA5191-3-5 (Hex Head) and
for MSNs 0021-0097 the screws used are DAN169K3-7 (Counter Sunk).

### Page 60

A350
SERVICE BULLETIN
REV 00 Dec 21/17 A350-55-P002
REV 01 Nov 13/18 Page 60
(h) Apply sealant as shown on Ref. Fig. Removal and Installation of the Screws and
the Plate Covers, LH and RH side SHEET 2 in accordance with Ref. ASR A350-
A-51-24-XX-01ZZZ-667Z-A:
  Polysulfide Sealant
- Low Density
MultiPurpose Brushable
06ACA1

The text continues at https://openairdocs.org/service-documents/airbus/a350-55-p002/file/8c7c0452a5cd.md?from=61

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