# Airbus Service Bulletin A350-53-P067

Copy: No revision named ("SB_53-P067_r00"), 89 pages: PDF https://openairdocs.org/files/sha256/82/c6/82c64d5735ae0cb81e21531c0714434c1f20b5a74b512daff647c2a3e27f3620; text https://openairdocs.org/service-documents/airbus/a350-53-p067/file/82c64d5735ae.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2021-1006, the docket of AD 2022-03-22. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md)
- Type: Service bulletin (Service Bulletin)
- Number: A350-53-P067
- Page: https://openairdocs.org/service-documents/airbus/a350-53-p067

## Text (89 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2021-1006, the docket of AD 2022-03-22. 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 Apr 09/21 A350-53-P067
Page 1
CONF ALL
AIRBUS
2, ROND POINT EMILE DEWOITINE
31700 BLAGNAC
FRANCE
 
The content of this document is the property of Airbus. All rights including copyrights are reserved.
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: 53
TITLE: FUSELAGE - CONE/REAR FUSELAGE - INSPECTION OF THS UPPER
AND LOWER ATTACHMENT FITTING BEARING ASSY ROTATION
MODIFICATION No.:
None

### Page 2

A350
SERVICE BULLETIN
SUMMARY
REV 00 Apr 09/21 A350-53-P067
Page 2
ATA SYSTEM: 53
TITLE: FUSELAGE - CONE/REAR FUSELAGE - INSPECTION OF THS UPPER
AND LOWER ATTACHMENT FITTING BEARING ASSY ROTATION
SUMMARY
This summary is for information only and is not approved for modification of the aircraft.
A. MODIFICATIONS
MODIFICATION CLASSIFICATION
MAJOR None
MINOR None
NOTE: As per EASA IR 21, a minor change is one that has no appreciable effect on the
mass, balance, structural strength, reliability, operational characteristics affecting
the airworthiness of the product. All other changes are major changes.
B. REASON
(1) History
When performing the new MPD lubrication task MPD 535000-00M05-01 every 18
months (MP A350-A-53-51-XX-00ZZZ-240Z-A) for A/C post-mod 113102 with new
grease concept (without sealant), one aircraft was found with PREMOD configuration,
sealant was installed in the interface of THS Upper and Lower Corner Fittings with
Bearing Assy at FR 102 and not the CPC and grease according MOD 113102.
This evidence shows that MOD 113102 has not been correctly applied. As a result,
production quality check has been conducted to conclude that the batch of aircraft
included in the applicability list of this Service Bulletin has a pre-mod configuration
with sealant instead of CPC and grease in the junction.
In case of damaged sealant, water tightness cannot be guaranteed, hence there is a
risk of corrosion in the aluminum corner fitting.
(2) Objective/Action
The objective of this Inspection Service Bulletin is to check the presence of the sealant
bead in the interface of THS Upper and Lower Corner Fittings with Bearing Assy at FR
102.
If sealant bead is present and undamaged, it is necessary to remove sealant beads,
apply re-torque and apply CPC and grease.
If sealant bead is present and broken, it is necessary to remove sealant beads,
remove nut and lock washer and perform detailed inspection to check for any trace of
corrosion on aluminum, cracks or paint degradation on accessible area of corner fitting
and bushing. Afterward, it is necessary to apply re-torque and apply CPC and grease.
If no sealant bead is present around the bearing shoulders and nut but grease is
installed as requested for POST MOD 113102, no further action to perform.
(3) Advantages
The accomplishment of this Inspection Service Bulletin will allow the detection of
possible corrosion issues on affected area, reducing the risk of potential structural
degradation due to corrosion. This service bulletin also ensures the correct
embodiment of MOD 113102.

### Page 3

A350
SERVICE BULLETIN
SUMMARY
REV 00 Apr 09/21 A350-53-P067
Page 3
(4) Operational/Maintenance Consequences
The Operational/Maintenance Consequences of this Service Bulletin are covered by
the update of the affected publications detailed in “PLANNING INFORMATION”.
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
No specific aircraft maintenance configuration required.
E. MATERIAL PRICE INFORMATION
(1) Inspection of the FR102 Bearing Fitting Assemblies
(a) T ask set A350-A-53-XX-P067-01000-93BA-A Inspection of the FR102 Bearing
Fitting Assemblies
MATERIAL PRICE INFORMATION TABLE
MATERIAL SET QTYPER A/C PRICE PER A/C MAIN PARTS
Aircraft standard tools See SB See Note Bearing, Prot Floor Panel,
Platform
NOTE: Price information to be obtained from the given supplier.
F. APPLICABILITY
This Service Bulletin is applicable to this (these) operator(s):
AAR AIB CCA CES CHH CPA CRK CSC DAL ETD ETH FIN FWI HVN IBE PAL QTR SIA TAM VIR
G. CONCURRENT REQUIREMENTS
None
H. NATURE OF THE WORK
(1) Inspection of the FR102 Bearing Fitting Assemblies
(a) T ask set A350-A-53-XX-P067-01000-93BA-A Inspection of the FR102 Bearing
Fitting Assemblies
AIRCRAFT YES
EQUIPMENT NO
I. MANPOWER

### Page 4

A350
SERVICE BULLETIN
SUMMARY
REV 00 Apr 09/21 A350-53-P067
Page 4
(1) Inspection of the FR102 Bearing Fitting Assemblies
(a) T ask set A350-A-53-XX-P067-01000-93BA-A Inspection of the FR102 Bearing
Fitting Assemblies
MANPOWER
TOTAL MAN-HOURS 31.50 h
ELAPSED TIME (HOURS) 7.75 h

### Page 5

A350
SERVICE BULLETIN
SUMMARY
Figure ICN-A350-A-53XXP067-A-FAPE3-05UZU-A-001-01 SHEET 1/1
REV 00 Apr 09/21 A350-53-P067General overview
Page 5
J. GENERAL OVERVIEW
CONF ALL
INSPECTION AREA
B
FR102
FR93
A
B
A
Z311
Z312
LH
RH
INSPECTION AREA
VIEW LOOKING FWD
ICN-A350-A-53XXP067-A-FAPE3-05UZU-A-001-01

### Page 6

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 6
ATA SYSTEM: 53
TITLE: FUSELAGE - CONE/REAR FUSELAGE - INSPECTION OF THS UPPER
AND LOWER ATTACHMENT FITTING BEARING ASSY ROTATION
1. PLANNING INFORMATION
A. APPLICABILITY
(1) Models
ON A/C 0065, 0071, 0252, 0258, 0262, 0266, 0274, 0286, 0290, 0296
350-1041
ON A/C 0224, 0232, 0234, 0238, 0244, 0246-0248, 0251, 0254, 0256, 0257, 0259-0261,
0263-0265, 0267-0273, 0276-0284
350-941
CONF ALL
(2) Applicability by MSN
0065 0071 0224 0232 0234 0238 0244 0246-0248 0251 0252 0254 0256-0274 0276-
0284 0286 0290 0296
(3) MSN by configuration
MSN CONFIGURATION
0065 0071 0224 0232 0234 0238 0244 0246 0247 0248 0251
0252 0254 0256 0257 0258 0259 0260 0261 0262 0263 0264
0265 0266 0267 0268 0269 0270 0271 0272 0273 0274 0276
0277 0278 0279 0280 0281 0282 0283 0284 0286 0290 0296
001
(4) Configuration definition
Configuration 001
CONF 001 is applicable for all the aircraft affected by this Service Bulletin as a
standard configuration.
B. CONCURRENT REQUIREMENTS
None
C. REASON
(1) History
When performing the new MPD lubrication task MPD 535000-00M05-01 every 18
months (MP A350-A-53-51-XX-00ZZZ-240Z-A) for A/C post-mod 113102 with new
grease concept (without sealant), one aircraft was found with PREMOD configuration,
sealant was installed in the interface of THS Upper and Lower Corner Fittings with
Bearing Assy at FR 102 and not the CPC and grease according MOD 113102.
This evidence shows that MOD 113102 has not been correctly applied. As a result,
production quality check has been conducted to conclude that the batch of aircraft
included in the applicability list of this Service Bulletin has a pre-mod configuration
with sealant instead of CPC and grease in the junction.
In case of damaged sealant, water tightness cannot be guaranteed, hence there is a
risk of corrosion in the aluminum corner fitting.

### Page 7

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 7
(2) Objective/Action
The objective of this Inspection Service Bulletin is to check the presence of the sealant
bead in the interface of THS Upper and Lower Corner Fittings with Bearing Assy at FR
102.
If sealant bead is present and undamaged, it is necessary to remove sealant beads,
apply re-torque and apply CPC and grease.
If sealant bead is present and broken, it is necessary to remove sealant beads,
remove nut and lock washer and perform detailed inspection to check for any trace of
corrosion on aluminum, cracks or paint degradation on accessible area of corner fitting
and bushing. Afterward, it is necessary to apply re-torque and apply CPC and grease.
If no sealant bead is present around the bearing shoulders and nut but grease is
installed as requested for POST MOD 113102, no further action to perform.
(3) Advantages
The accomplishment of this Inspection Service Bulletin will allow the detection of
possible corrosion issues on affected area, reducing the risk of potential structural
degradation due to corrosion. This service bulletin also ensures the correct
embodiment of MOD 113102.
(4) Operational/Maintenance Consequences
The Operational/Maintenance Consequences of this Service Bulletin are covered by
the update of the affected publications detailed in “PLANNING INFORMATION”.
D. DESCRIPTION
T o accomplish this Service Bulletin it is necessary to:
(1) Inspection of the FR102 Bearing Fitting Assemblies
(a) T ask set A350-A-53-XX-P067-01000-93BA-A Inspection of the FR102 Bearing
Fitting Assemblies
1 Do a DVI of the Sealant Bead around the Upper Frame Attachment at
Frame 102 - LH
2 Do a DET of Accessible Area all around the Upper Frame Attachment Fitting
at Frame 102 - LH, Depending on the Inspection Result
3 Do a DVI of the Sealant Bead Around the Upper Frame Attachment Fittings
at FR102 - RH
4 Do a DET of Accessible Area all around the Upper Frame Attachment Fitting
at Frame 102 - RH, Depending on the Inspection Result
5 Do a DVI of the Sealant Bead around the Lower Frame Attachment Fitting
at Frame 102 - LH
6 Do a DET of Accessible Area all around the Lower Frame Attachment Fitting
at Frame 102 - LH, Depending on Inspection Result
7 Do a DVI of the Sealant Bead Around the Lower Frame Attachment Fittings
at FR102 - RH
8 Do a DET of Accessible Area all around the Lower Frame Attachment Fitting
at Frame 102 - RH, Depending on the Inspection Result
E. COMPLIANCE
(1) Classification
MANDATORY: Service Bulletin must be accomplished.

### Page 8

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 8
(2) Accomplishment Timescale
Accomplishment of this Service Bulletin must be done in accordance with the table
below.
This Service Bulletin has been classified Mandatory. It is expected that an
Airworthiness Directive (AD) published by the European Union Aviation Safety Agency
(EASA) will be issued to confirm this classification. It is anticipated that the AD will
confirm the thresholds given but reference should be made to the AD for confirmation
of the mandated accomplishment timescale.
T able 01, CONF 001 — Do a visual inspection of the sealant bead around the upper
and lower frame attachment fittings at FR102.
COMPLIANCE TIME
CONDITIONS ACTION
THRESHOLD GRACE PERIOD
REPETITIVE
INTERVAL
All Aircraft Do a visual
inspection of the
sealant bead
around the upper
and lower frame
attachment
fittings at FR102
in accordance
with Ref. T ask
A350-A-53-XX-
P067-01ZZZ-
300Z-A, Ref. T ask
A350-A-53-XX-
P067-01ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-03ZZZ-
300Z-A and Ref.
T ask A350-A-
53-XX-P067-
02ZZZ-311Z-A.
Within 36
month(s) from
first delivery of
the aircraft (first
Transfer of Title)
None None
There is NOT
a sealant
bead around
the bearing
shoulder and nut
Do a check
for grease at
the bearing
shoulder and nut
in accordance
with Ref. T ask
A350-A-53-XX-
P067-01ZZZ-
300Z-A, Ref. T ask
A350-A-53-XX-
P067-01ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-03ZZZ-
300Z-A and Ref.
T ask A350-A-53-
XX-P067-02ZZZ-
311Z-A. Continue
to T able 02.
Before next flight None None

### Page 9

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 9
COMPLIANCE TIME
CONDITIONS ACTION
THRESHOLD GRACE PERIOD
REPETITIVE
INTERVAL
There is a sealant
bead around
the bearing
shoulder and nut
Do a check for
cracks in the
sealant bead in
accordance with
Ref. T ask A350-
A-53-XX-P067-
01ZZZ-300Z-A,
Ref. T ask A350-
A-53-XX-P067-
01ZZZ-311Z-A,
Ref. T ask A350-
A-53-XX-P067-
03ZZZ-300Z-
A and Ref. T ask
A350-A-53-XX-
P067-02ZZZ-
311Z-A. Continue
to T able 03.
Before next flight None None
T able 02, CONF 001 — Do a check for grease at the bearing shoulder and nut.
COMPLIANCE TIME
CONDITIONS ACTION
THRESHOLD GRACE PERIOD
REPETITIVE
INTERVAL
There is NOT
a sealant
bead around
the bearing
shoulder and nut.
Do a check
for grease at
the bearing
shoulder and nut
in accordance
with Ref. T ask
A350-A-53-XX-
P067-01ZZZ-
300Z-A, Ref. T ask
A350-A-53-XX-
P067-01ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-03ZZZ-
300Z-A and Ref.
T ask A350-A-
53-XX-P067-
02ZZZ-311Z-A.
Before next flight None None
There is
NOT Grease
Contact Airbus Before next flight None None
There is grease No further action None None None
T able 03, CONF 001 — Do a check for cracks in the sealant.
COMPLIANCE TIME
CONDITIONS ACTION
THRESHOLD GRACE PERIOD
REPETITIVE
INTERVAL
There is a sealant
bead around
Do a check if
the sealant
bead is cracked
Before next flight None None

### Page 10

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 10
COMPLIANCE TIME
CONDITIONS ACTION
THRESHOLD GRACE PERIOD
REPETITIVE
INTERVAL
the bearing
shoulder and nut.
in accordance
with Ref. T ask
A350-A-53-XX-
P067-01ZZZ-
300Z-A, Ref. T ask
A350-A-53-XX-
P067-01ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-03ZZZ-
300Z-A and Ref.
T ask A350-A-
53-XX-P067-
02ZZZ-311Z-A.
There are
cracks in the
sealant bead.
Remove the
sealant in
accordance
with Ref. T ask
A350-A-53-XX-
P067-01ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-02ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-01ZZZ-
300Z-A and Ref.
T ask A350-A-
53-XX-P067-
03ZZZ-300Z-A.
Before next flight None None
AND
  Unbend the
tab washer in
accordance
with Ref. T ask
A350-A-53-XX-
P067-04ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-05ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-06ZZZ-
311Z-A and Ref.
T ask A350-A-
53-XX-P067-
07ZZZ-311Z-A.
Before next flight None None
AND
Loosen the tab
washer and
bearing nut
in accordance
Before next flight None None

### Page 11

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 11
COMPLIANCE TIME
CONDITIONS ACTION
THRESHOLD GRACE PERIOD
REPETITIVE
INTERVAL
with Ref. T ask
A350-A-53-XX-
P067-01ZZZ-
300Z-A, Ref. T ask
A350-A-53-XX-
P067-01ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-03ZZZ-
300Z-A and Ref.
T ask A350-A-
53-XX-P067-
02ZZZ-311Z-A.
AND
  Clean the
inspection area
in accordance
with Ref. T ask
A350-A-53-XX-
P067-01ZZZ-
300Z-A, Ref. T ask
A350-A-53-XX-
P067-01ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-03ZZZ-
300Z-Aand Ref.
T ask A350-A-
53-XX-P067-
02ZZZ-311Z-A.
AND
Do a detailed
inspection of
the affected
bearing zone in
accordance with
Ref. T ask A350-
A-53-XX-P067-
04ZZZ-311Z-A,
Ref. T ask A350-
A-53-XX-P067-
05ZZZ-311Z-A,
Ref. T ask A350-
A-53-XX-P067-
06ZZZ-311Z-
A and Ref. T ask
A350-A-53-XX-
P067-07ZZZ-
311Z-A. Continue
to T able 04.
Before next flight None None

### Page 12

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 12
COMPLIANCE TIME
CONDITIONS ACTION
THRESHOLD GRACE PERIOD
REPETITIVE
INTERVAL
There are NOT
cracks in the
sealant bead
Remove the
sealant in
accordance
with Ref. T ask
A350-A-53-XX-
P067-01ZZZ-
300Z-A, Ref. T ask
A350-A-53-XX-
P067-01ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-03ZZZ-
300Z-A and Ref.
T ask A350-A-
53-XX-P067-
02ZZZ-311Z-A.
Before next flight None None
AND
  Unbend the
tab washer in
accordance
with Ref. T ask
A350-A-53-XX-
P067-01ZZZ-
300Z-A, Ref. T ask
A350-A-53-XX-
P067-01ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-03ZZZ-
300Z-A and Ref.
T ask A350-A-
53-XX-P067-
02ZZZ-311Z-A.
Before next flight None None
AND
T orque the
bearing nut
and bend the
tab washer in
accordance
with Ref. T ask
A350-A-53-XX-
P067-01ZZZ-
300Z-A, Ref. T ask
A350-A-53-XX-
P067-01ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-03ZZZ-
300Z-A and Ref.
T ask A350-A-
53-XX-P067-
02ZZZ-311Z-A.
Before next flight None None

### Page 13

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 13
COMPLIANCE TIME
CONDITIONS ACTION
THRESHOLD GRACE PERIOD
REPETITIVE
INTERVAL
AND
Apply CPC
around the
bearing and
fitting interfaces
in accordance
with Ref. T ask
A350-A-53-XX-
P067-01ZZZ-
300Z-A, Ref. T ask
A350-A-53-XX-
P067-01ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-03ZZZ-
300Z-A and Ref.
T ask A350-A-
53-XX-P067-
02ZZZ-311Z-A.
Before next flight None None
AND
Apply grease
around the
bearing contour
in accordance
with Ref. T ask
A350-A-53-XX-
P067-01ZZZ-
300Z-A, Ref. T ask
A350-A-53-XX-
P067-01ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-03ZZZ-
300Z-A and Ref.
T ask A350-A-
53-XX-P067-
02ZZZ-311Z-A.
Before next flight None None
AND
No further action. None None None
T able 04, CONF 001 — Do a check for corrosion on the affected bearing zone.
COMPLIANCE TIME
CONDITIONS ACTION
THRESHOLD GRACE PERIOD
REPETITIVE
INTERVAL
There are
cracks in the
sealant bead.
Do a detailed
inspection of
the affected
bearing zone
in accordance
with Ref. T ask
A350-A-53-XX-
Before next flight None None

### Page 14

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 14
COMPLIANCE TIME
CONDITIONS ACTION
THRESHOLD GRACE PERIOD
REPETITIVE
INTERVAL
P067-04ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-05ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-06ZZZ-
311Z-A and Ref.
T ask A350-A-
53-XX-P067-
07ZZZ-311Z-A.
There is corrosion
on the affected
bearing zone
Contact Airbus. Before next flight None None
There is NOT
Corrosion on
the affected
bearing zone
Apply sealant
in accordance
with Ref. T ask
A350-A-53-XX-
P067-04ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-05ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-07ZZZ-
311Z-A and Ref.
T ask A350-A-
53-XX-P067-
01ZZZ-920Z-A
Before next flight None None
AND
T orque the
bearing nut
and bend the
tab washer in
accordance
with Ref. T ask
A350-A-53-XX-
P067-04ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-05ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-06ZZZ-
311Z-A and Ref.
T ask A350-A-
53-XX-P067-
07ZZZ-311Z-A.
Before next flight None None
AND
Apply CPC
around the
Before next flight None None

### Page 15

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 15
COMPLIANCE TIME
CONDITIONS ACTION
THRESHOLD GRACE PERIOD
REPETITIVE
INTERVAL
bearing and
fitting interfaces
in accordance
with Ref. T ask
A350-A-53-XX-
P067-04ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-05ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-06ZZZ-
311Z-A and Ref.
T ask A350-A-
53-XX-P067-
07ZZZ-311Z-A.
AND
Apply grease
around the
bearing contour
in accordance
with Ref. T ask
A350-A-53-XX-
P067-04ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-05ZZZ-
311Z-A, Ref. T ask
A350-A-53-XX-
P067-06ZZZ-
311Z-A and Ref.
T ask A350-A-
53-XX-P067-
07ZZZ-311Z-A.
Before next flight None None
AND
No further action. None None None
F. APPROVAL
The technical content of this document is approved under the authority of the Design
Organisation Approval ref. 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
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.

### Page 16

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 16
(1) Inspection of the FR102 Bearing Fitting Assemblies
(a) T ask set A350-A-53-XX-P067-01000-93BA-A Inspection of the FR102 Bearing
Fitting Assemblies
PREPARATION
Job Set-up 1.50 h
PROCEDURE
Do a DVI of the Sealant Bead around the Upper Frame
Attachment at Frame 102 - LH
0.75 h
Do a DET of Accessible Area all around the Upper Frame
Attachment Fitting at Frame 102 - LH, Depending on the
Inspection Result
6.00 h
Do a DVI of the Sealant Bead Around the Upper Frame
Attachment Fittings at FR102 - RH
0.75 h
Do a DET of Accessible Area all around the Upper Frame
Attachment Fitting at Frame 102 - RH, Depending on the
Inspection Result
6.00 h
Do a DVI of the Sealant Bead around the Lower Frame
Attachment Fitting at Frame 102 - LH
0.75 h
Do a DET of Accessible Area all around the Lower Frame
Attachment Fitting at Frame 102 - LH, Depending on
Inspection Result
6.00 h
Do a DVI of the Sealant Bead Around the Lower Frame
Attachment Fittings at FR102 - RH
0.75 h
Do a DET of Accessible Area all around the Lower Frame
Attachment Fitting at Frame 102 - RH, Depending on the
Inspection Result
6.00 h
PREPARATION FOR TEST
Install APU Fire Extinguisher Bottle 1.00 h
TEST
T est 0.50 h
CLOSE-UP
Close-up 1.50 h
TOTAL MAN-HOURS 31.50 h
ELAPSED TIME (HOURS) 7.75 h
NOTE: For an explanation of the man-hours and elapsed time, refer to the
Gantt Chart given in Appendix A.
NOTE: The minimum man-hours necessary to accomplish this Service Bulletin
are those for the Inspection. Depending on the inspection result,
additional man-hours can apply.
H. WEIGHT AND BALANCE
Not changed
I. ELECTRICAL LOAD DATA
Not changed
J. REFERENCES

### Page 17

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 17
(1) Inspection of the FR102 Bearing Fitting Assemblies
(a) T ask set A350-A-53-XX-P067-01000-93BA-A Inspection of the FR102 Bearing
Fitting Assemblies
AIRCRAFT STRUCTURAL REPAIR (ASR)
A350-A-51-21-11-00ZZZ-660Z-A A350-A-51-24-XX-01ZZZ-667Z-A
ELECTRICAL STANDARD PRACTICES (ESP)
A350-A-20-55-XX-01ZZZ-042Z-A
INTRODUCTION (INTRO)
A350-A-00-61-04-11ZZZ-018Z-D
MAINTENANCE PROCEDURE (MP)
A350-A-20-46-XX-00ZZZ-25BZ-A A350-A-24-41-XX-00ZZZ-170Z-A
A350-A-26-22-55-00ZZZ-520Z-A
A350-A-26-22-55-00ZZZ-720Z-A
A350-A-27-44-XX-00ZZZ-240Z-A
NON DESTRUCTIVE TEST (NDT)
A350-A-51-99-XX-01ZZZ-040Z-A A350-A-51-99-12-00ZZZ-311Z-A
PROCESS AND MATERIAL SPECIFICATION (PMS)
01-05-03 01-02-106
SYSTEM DESCRIPTION (SD)
A350-A-06-2X-XX-01ZZZ-04CZ-A A350-A-06-3X-XX-01ZZZ-04CZ-A
TECHNICAL FOLLOW UP (TFU)
53.56.00.004
K. PUBLICATION AFFECTED
None
L. INDUSTRY SUPPORT INFORMATION
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 01/
26.

### Page 18

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 18
2. MATERIAL INFORMATION
A. MATERIAL APPLICABILITY
Material for task set A350-A-53-XX-P067-01000-93BA-A Inspection of the FR102
Bearing Fitting Assemblies
MATERIAL QTY SEE NOTES
Aircraft standard tools See SB
Referenced tools See SB
Consumables See SB
Referenced consumables See SB
B. TOOLING
Aircraft standard tools for task set A350-A-53-XX-P067-01000-93BA-A Inspection
of the FR102 Bearing Fitting Assemblies
Procurement address
D4296
AIRBUS Material, Logistics and Suppliers
Customer Order Fulfilment
Weg beim Jaeger 150
22335 HAMBURG
GERMANY
Phone: +49 (0) 40 50 76 40 02
E-mail: Please contact your Single Point Of Contact
(SPOC)
Internet: http://spares.airbus.com
D4296
AIRBUS Material, Logistics and Suppliers
Weg beim Jaeger 150
22335 HAMBURG
GERMANY
Fax: +49 40 50 76 3225
E-mail: T ool.LEASE@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.
Operators interested in the lease of standard tools should contact AIRBUS at the
address given above.
AIRBUS tool kits cannot be ordered as a complete set. For the necessary tools, send
an order for each single item through the given channel.
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
98V53509013000
(D4296) (D4296) 1 PLATFORM
98V55109011000
(D4296) (D4296) 1 BEARING
98V55109012000
(D4296) (D4296) 1 PROT
Referenced tools for task set A350-A-53-XX-P067-01000-93BA-A Inspection of the
FR102 Bearing Fitting Assemblies
T o accomplish this Service Bulletin it is necessary to use the tools listed in:
Ref. MP A350-A-26-22-55-00ZZZ-720Z-A

### Page 19

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 19
C. CONSUMABLES
Consumables for task set A350-A-53-XX-P067-01000-93BA-A Inspection of the
FR102 Bearing Fitting Assemblies
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
03GBC1
Synthetic Oil base Grease
- General Purpose Lithium
Thickened Low T emp
04DAB2
Primer Epoxy Paint -
- Corrosion Inhibiting
Structure
04JME4 T op Coat Polyurethane - -Grey InternalStructure
06AAC1 Polysulfide Sealant -General Purpose Interfay
08BAA9 Non Aqueous Cleaner -General
10ABC1
Surface Pretreatment
- Light Alloys Chemical
Conversion Yellow
12ABC1
Corrosion Preventive
Compound - Water
Displacing Soft Film
14SBA1 T extile - Lint free Cotton
Referenced consumables for task set A350-A-53-XX-P067-01000-93BA-A
Inspection of the FR102 Bearing Fitting Assemblies
T o accomplish this Service Bulletin it is necessary to use the consumable materials listed in:
Ref. MP A350-A-26-22-55-00ZZZ-720Z-A
D. LIST OF NEW PARTS
No parts
E. LIST OF EXISTING PARTS
No parts

### Page 20

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 20
3. ACCOMPLISHMENT INSTRUCTIONS
Task set A350-A-53-XX-P067-01000-93BA-A (A350-A-53-XX-P067-01ZZZ-93BZ-A)
Inspection of the FR102 Bearing Fitting Assemblies
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 FLIGHT CONTROLS
- THE FLIGHT CONTROL SURFACES
- THE LANDING GEAR AND RELATED DOORS
- THE CARGO DOOR
- THE ENGINES
- OTHER COMPONENTS THAT MOVE.
MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS
AND/OR DAMAGE TO EQUIPMENT.
CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP ELECTRICAL
WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY AND MECHANICALLY
SERVICEABLE). WHEN YOU DO A 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: The purpose of flowcharts is to supplement the information given in the Procedure and
Compliance paragraphs and not to serve as the primary source for tasks or compliance
times given in this Service Bulletin.

### Page 21

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 21
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.
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 Required for Compliance paragraph
contained herein, contact AIRBUS for further instructions and approval.
A. TASK SET ASSOCIATED INFORMATION
Task Manpower
TOTAL MAN-HOURS 31.50 h
ELAPSED TIME (HOURS) 7.75 h
B. PREPARATION
(1) Task A350-A-53-XX-P067-01001-540A-A (A350-A-53-XX-P067-01ZZZ-540Z-A)
Job Set-up
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
310
Manpower/Resources/Skills
Man-hours 1.50 h
Minimum Number of person 2
Elapsed Time 1.00 h
Skills Airframe
Material necessary to do the job
Aircraft standard tools
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
98V53509013000 1 PLATFORM
98V55109012000 1 PROT
Referenced Information
Manuals/Drawings References/Sheets
INTRO A350-A-00-61-04-11ZZZ-018Z-D
MP A350-A-24-41-XX-00ZZZ-170Z-AA350-A-27-44-XX-00ZZZ-240Z-A
Procedure
NOTE: For the basic Aircraft configuration, refer to Ref. INTRO A350-A-00-61-04-
11ZZZ-018Z-D “Maintenance Procedure - Introduction”.

### Page 22

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 22
(a) Make sure that the aircraft is electrically grounded, refer to Ref. MP A350-A-24-
41-XX-00ZZZ-170Z-A.
(b) Do the Job Set-up procedure as specified in the lubrication of the THS hinge line
bearings and upper and lower frame attachment-bearings, refer to Ref. MP A350-
A-27-44-XX-00ZZZ-240Z-A.
(c) Put an access platform in position below access doors Panel 311AB and Panel
311BB.
(d) Open the access doors Panel 311AB and Panel 311BB.
(e) Install:
1 PROT FLOOR PANEL-HTP 98V55109012000  
1 PLATFORM FR102 - S19 98V53509013000  
C. PROCEDURE
(1) Task A350-A-53-XX-P067-01001-311A-A (A350-A-53-XX-P067-01ZZZ-311Z-A)
Do a DVI of the Sealant Bead around the Upper Frame Attachment at Frame
102 - LH
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
311 Access Panel 311AB, Panel 314AR
Manpower/Resources/Skills
Man-hours 0.75 h
Minimum Number of person 1
Elapsed Time 0.75 h
Skills Airframe
Material necessary to do the job
Aircraft standard tools
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
98V55109011000 1 BEARING
Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
03GBC1
Synthetic Oil base Grease
- General Purpose Lithium
Thickened Low T emp
04DAB2
Primer Epoxy Paint -
- Corrosion Inhibiting
Structure
08BAA9 Non Aqueous Cleaner -General
10ABC1
Surface Pretreatment
- Light Alloys Chemical
Conversion Yellow

### Page 23

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 23
Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
12ABC1
Corrosion Preventive
Compound - Water
Displacing Soft Film
14SBA1 T extile - Lint free Cotton
Referenced Information
Manuals/Drawings References/Sheets
ASR A350-A-51-21-11-00ZZZ-660Z-AA350-A-51-24-XX-01ZZZ-667Z-A
MP A350-A-26-22-55-00ZZZ-520Z-A
NDT A350-A-51-99-XX-01ZZZ-040Z-A
SD A350-A-06-2X-XX-01ZZZ-04CZ-AA350-A-06-3X-XX-01ZZZ-04CZ-A
PMS 01-02-10601-05-03
Procedure
(a) Standard Practices given in this procedure:
1 For identification of zones, refer to Ref. SD A350-A-06-3X-XX-01ZZZ-04CZ-A.
2 For the Frame (FR) identification, refer to Ref. SD A350-A-06-2X-XX-01ZZZ-
04CZ-A.
3 Repair the protective treatment of metal parts in accordance with Ref. ASR
A350-A-51-21-11-00ZZZ-660Z-A.
4 For removing the Auxiliary Power Unit (APU) fire-extinguisher bottle
assembly, refer to Ref. MP A350-A-26-22-55-00ZZZ-520Z-A.
5 Apply sealant in accordance with Ref. ASR A350-A-51-24-XX-01ZZZ-667Z-A.
6 Clean the inspection area, refer to Ref. PMS 01-02-106.
(b) Do a visual inspection of the sealant bead around the Upper frame attachment
at Frame 102 in accordance with Ref. NDT A350-A-51-99-XX-01ZZZ-040Z-A,
refer to Ref. Fig. Flow Chart and Ref. Fig. Visual Inspection of Sealant Bead of the
Upper Attachment Fittings within the threshold given in PLANNING INFORMATION
paragraph E.(2).
1 If a sealant bead is not found around the bearing shoulder and nut:
a Do a check for grease.
<1> If grease is found around the bearing shoulder and nut, no
further action.
<2> If NO grease is found around the bearing shoulder and nut,
contact AIRBUS before the next flight.
2 If a sealant bead is found around the bearing shoulder and nut, continue to
the next step.
(c) Do a check for cracks in the sealant bead.
1 If the sealant bead is cracked:

### Page 24

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 24
a Remove the Auxiliary Power Unit (APU) fire-extinguisher bottle
assembly, refer to Ref. MP A350-A-26-22-55-00ZZZ-520Z-A.
b Remove the fillet sealant from the contour of the bearing to corner
fitting assembly.
NOTE: Use a plastic spatula to remove the sealant.
NOTE: Remove all the sealant in order to allow the tabs are visible.
NOTE: It is important to remove the sealant between the nut and
the washer. It should be removed in order to avoid that the
lock washer would be stuck to the nut due to the sealant.
c Clean the working area, refer to Ref. PMS 01-02-106 and with:
  T extile - Lint free Cotton14SBA1  
made moist with:
  Non Aqueous Cleaner -
General
08BAA9  
d Using a suitable punch, bend the tab flush with the structure using
masking to prevent damage to the component surface treatment. Un-
bend the tab to unlock the lock washer, refer to Ref. PMS 01-05-03.
NOTE: Mark the un-bent tab. It is not allowed to re-use the un-bent
tab.
NOTE: Ensure that bending the tab does not result in any cracking,
thinning or damage to the tab.
e Loosen the bearing nut with:
1 BEARING TOOL SET -
HTP
98V55109011000  
f Loosen the washer.
g Clean the working area, refer to Ref. PMS 01-02-106 and with:
  T extile - Lint free Cotton14SBA1  
made moist with:
  Non Aqueous Cleaner -
General
08BAA9  
h If necessary, remove interfay sealant with a plastic spatula.
i Remove any traces of debris from the nut, lock washer and corner
fitting.
j Do a detailed inspection of the affected bearing zone, refer to Ref.
T ask A350-A-53-XX-P067-05ZZZ-311Z-A.
2 If the sealant bead is NOT cracked:
a If necessary remove the Auxiliary Power Unit (APU) fire-extinguisher
bottle assembly, refer to Ref. MP A350-A-26-22-55-00ZZZ-520Z-A.
b Remove the fillet sealant from the contour of the bearing to corner
fitting assembly.
NOTE: Use a plastic spatula to remove the sealant.

### Page 25

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 25
NOTE: Remove all the sealant in order to allow the tabs are visible.
NOTE: It is important to remove the sealant between the nut and
the washer. It should be removed in order to avoid that the
lock washer would be stuck to the nut due to the sealant.
c Clean the working area, refer to Ref. PMS 01-02-106 and with:
  T extile - Lint free Cotton14SBA1  
made moist with:
  Non Aqueous Cleaner -
General
08BAA9  
d If paint is damaged during the sealant removal, apply protection with:
  Surface Pretreatment
- Light Alloys Chemical
Conversion Yellow
10ABC1  
  Primer Epoxy Paint -
- Corrosion Inhibiting
Structure
04DAB2  
e Using a suitable punch, bend the tab flush with the structure using
masking to prevent damage to the component surface treatment. Un-
bend the tab to unlock the lock washer, refer to Ref. PMS 01-05-03.
NOTE: Mark the un-bent tab. It is not allowed to re-use the un-bent
tab.
NOTE: Ensure that bending the tab does not result in any cracking,
thinning or damage to the tab.
f T orque the bearing nut to between 125 Nm (1106.35 lbf.in) and 130
Nm (1150.59 lbf.in), using:
1 BEARING TOOL SET -
HTP
98V55109011000  
g Bend a new tab on the washer, refer to Ref. PMS 01-05-03.
NOTE: Make sure that the tab washer has been correctly assembled
and bent over to effect a positive locking, without any
damage and that any sharp edges are deburred.
h Apply CPC around the bearing and fitting interfaces, refer to Ref.
Fig. Application of Protection at the Upper Attachment Fittings, if the
Sealant Bead is not Cracked.
  Corrosion Preventive
Compound - Water
Displacing Soft Film
12ABC1  
i Apply grease 30 minutes after the application of CPC, around the
bearing contour.
  Synthetic Oil base
Grease - General
Purpose Lithium
Thickened Low T emp
03GBC1

### Page 26

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 26
j No further action.

### Page 27

A350
SERVICE BULLETIN
Figure ICN-A350-A-53XXP067-A-FAPE3-05UZT-A-007-01 SHEET 1/1
REV 00 Apr 09/21 A350-53-P067Flow Chart
Page 27
CONF ALL
NOTE:
THE PURPOSE OF FLOWCHARTS IS TO SUPPLEMENT
THE INFORMATION GIVEN IN THE PROCEDURE AND 
COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS
THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE
TIMES GIVEN IN THE SERVICE BULLETIN.
AROUND THE UPPER AND LOWER FRAME
ATTACHMENT FITTINGS AT FR102
DO A VISUAL INSPECTION OF THE SEALANT BEAD
IS THERE
A SEALANT BEAD
AROUND THE BEARING
SHOULDER AND
NO FOR GREASEDO A CHECK
IS
THERE
GREASE? NO
BEFORE NEXT FLIGHT
CONTACT AIRBUS
YES
SEALANT BEAD
CRACKED?
YES
NO
WASHER AND THE
LOOSEN THE TAB
BEARING NUT
BEARING CONTOUR
APPLY GREASE AROUND THE
IS THE
INSPECTION OF THE 
AFFECTED BEARING ZONE
DO A DETAILED
THE BEARING CONTOUR
APPLY CPC AROUND
NO FURTHER ACTION
NUT?
YES
SEALANT BEAD
REMOVE THE
CRACKS IN THE
SEALANT BEAD
DO A CHECK FOR
IS THERE
CORROSION ON
THE AFFECTED
BEARING
YES
BEFORE NEXT FLIGHT
CONTACT AIRBUS
SEALANT BEAD
REMOVE THE
NO
APPLY TORQUE ON THE 
BEARING NUT AND BEND
THE TAB WASHER
APPLY SEALANT
NO FURTHER ACTION
INSPECTION AREA
CLEAN THE
ZONE?
TAB WASHER
UNBEND THE
TAB WASHER
UNBEND THE
ICN-A350-A-53XXP067-A-FAPE3-05UZT-A-007-01

### Page 28

A350
SERVICE BULLETIN
Figure ICN-A350-A-53XXP067-A-FAPE3-05UZL-A-001-01 SHEET 1/2
REV 00 Apr 09/21 A350-53-P067Visual Inspection of Sealant Bead
of the Upper Attachment Fittings Page 28
CONF ALL
B
FR102
FR93
A
B
A
Z311
Z312
LH
RH
C
C
ICN-A350-A-53XXP067-A-FAPE3-05UZL-A-001-01

### Page 29

A350
SERVICE BULLETIN
Figure ICN-A350-A-53XXP067-A-FAPE3-05UZM-A-001-01 SHEET 2/2
REV 00 Apr 09/21 A350-53-P067Visual Inspection of Sealant Bead
of the Upper Attachment Fittings Page 29
CONF ALL
C
A
A
LH SHOWN
RH SYMMETRICAL
A A INBD
NOTE:
INSPECTION AREA
NUT
LOCK
WASHER
CORNER
FITTING
BEARING
ASSEMBLY
BUSHING
PAD PLATE
CORNER
FITTING
LH SHOWN
RH SYMMETRICAL
ICN-A350-A-53XXP067-A-FAPE3-05UZM-A-001-01

### Page 30

A350
SERVICE BULLETIN
Figure ICN-A350-A-53XXP067-A-FAPE3-05YWR-A-001-01 SHEET 1/2
REV 00 Apr 09/21 A350-53-P067Application of Protection at the Upper Attachment
Fittings, if the Sealant Bead is not Cracked Page 30
CONF ALL
B
FR102
FR93
A
B
A
Z311
Z312
LH
RH
C
C
ICN-A350-A-53XXP067-A-FAPE3-05YWR-A-001-01

### Page 31

A350
SERVICE BULLETIN
Figure ICN-A350-A-53XXP067-A-FAPE3-05YWS-A-001-01 SHEET 2/2
REV 00 Apr 09/21 A350-53-P067Application of Protection at the Upper Attachment
Fittings, if the Sealant Bead is not Cracked Page 31
CONF ALL
C
A
A
LH SHOWN
RH SYMMETRICAL
A A INBD01NOTE:APPLY MATERIAL No 12ABC1
02
TORQUE TIGHTEN THE NUTS BETWEEN 125 Nm (1106.35 lbf.in)
CORNER
FITTING
BEARING
ASSEMBLY
BUSHING
03
PAD PLATE
CORNER
FITTING
LH SHOWN
RH SYMMETRICAL
0202
LOCK
WASHER
NUT
02
01
02
APPLY MATERIAL No 03GBC1
03
01
01
01
AND 130 Nm (1150.59 lbf.in) ICN-A350-A-53XXP067-A-FAPE3-05YWS-A-001-01

### Page 32

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 32
(2) Task A350-A-53-XX-P067-05001-311A-A (A350-A-53-XX-P067-05ZZZ-311Z-A)
Do a DET of Accessible Area all around the Upper Frame Attachment Fitting
at Frame 102 - LH, Depending on the Inspection Result
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
311 Access Panel 311AB, Panel 314AR
Manpower/Resources/Skills
Man-hours 6.00 h
Minimum Number of person 2
Elapsed Time 6.00 h
Skills Non-Destructive T esting
Material necessary to do the job
Aircraft standard tools
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
98V55109011000 1 BEARING
Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
03GBC1
Synthetic Oil base Grease
- General Purpose Lithium
Thickened Low T emp
04DAB2
Primer Epoxy Paint -
- Corrosion Inhibiting
Structure
06AAC1 Polysulfide Sealant -General Purpose Interfay
10ABC1
Surface Pretreatment
- Light Alloys Chemical
Conversion Yellow
12ABC1
Corrosion Preventive
Compound - Water
Displacing Soft Film
Referenced Information
Manuals/Drawings References/Sheets
NDT A350-A-51-99-12-00ZZZ-311Z-A
SD A350-A-06-2X-XX-01ZZZ-04CZ-AA350-A-06-3X-XX-01ZZZ-04CZ-A
PMS 01-05-03
Procedure
(a) Standard Practices given in this procedure:
1 For identification of zones, refer to Ref. SD A350-A-06-3X-XX-01ZZZ-04CZ-A.

### Page 33

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 33
2 For the Frame (FR) identification, refer to Ref. SD A350-A-06-2X-XX-01ZZZ-
04CZ-A.
(b) Do a detailed inspection all around accessible area at corner fitting, bushing and
bearing interface to find any traces of corrosion on aluminium, cracks or paint
degradation (flaking and/or blisters) in accordance with Ref. NDT A350-A-51-99-
12-00ZZZ-311Z-A, refer to Ref. Fig. Detailed Inspection for Corrosion of the Upper
Attachment Fittings.
1 If corrosion, cracks or paint degradation are found on the bearing zone,
contact AIRBUS.
2 If corrosion is NOT found on the affected bearing zone, continue to the next
step.
a Apply interfay sealant in the contact surface between the lock washer
and fitting, refer to Ref. Fig. Application of Protection at the Upper
Attachment Fittings, if Sealant Bead is Cracked, Section A-A.
  Polysulfide Sealant
- General Purpose
Interfay
06AAC1  
b If paint is damaged during the sealant removal, apply protection with:
  Surface Pretreatment
- Light Alloys Chemical
Conversion Yellow
10ABC1  
  Primer Epoxy Paint -
- Corrosion Inhibiting
Structure
04DAB2  
c T orque the bearing nut to between 125 Nm (1106.35 lbf.in) and 130
Nm (1150.59 lbf.in), using:
1 BEARING TOOL SET -
HTP
98V55109011000  
d Bend a new tab on the washer, refer to Ref. PMS 01-05-03.
NOTE: Make sure that the tab washer has been correctly assembled
and bent over to effect a positive locking, without any
damage and that any sharp edges are deburred.
e Apply CPC the bearing and fitting interfaces.
  Corrosion Preventive
Compound - Water
Displacing Soft Film
12ABC1  
f Apply grease 30 minutes after the application of CPC, around the
bearing contour.
  Synthetic Oil base
Grease - General
Purpose Lithium
Thickened Low T emp
03GBC1  
g No further action.

### Page 34

A350
SERVICE BULLETIN
Figure ICN-A350-A-53XXP067-A-FAPE3-05UZH-A-001-01 SHEET 1/2
REV 00 Apr 09/21 A350-53-P067Detailed Inspection for Corrosion
of the Upper Attachment Fittings Page 34
CONF ALL
B
FR102
FR93
A
B
A
Z311
Z312
LH
RH
C D
C D
ICN-A350-A-53XXP067-A-FAPE3-05UZH-A-001-01

### Page 35

A350
SERVICE BULLETIN
Figure ICN-A350-A-53XXP067-A-FAPE3-05UZI-A-001-01 SHEET 2/2
REV 00 Apr 09/21 A350-53-P067Detailed Inspection for Corrosion
of the Upper Attachment Fittings Page 35
CONF ALL
VIEW LOOKING INBD
VIEW LOOKING OUTBD
NOTE:
INSPECTION AREA
C
D
FWD
FWD
RH SHOWN
LH SYMMETRICAL
RH SHOWN
LH SYMMETRICAL
ICN-A350-A-53XXP067-A-FAPE3-05UZI-A-001-01

### Page 36

A350
SERVICE BULLETIN
Figure ICN-A350-A-53XXP067-A-FAPE3-05UZN-A-001-01 SHEET 1/2
REV 00 Apr 09/21 A350-53-P067Application of Protection at the Upper Attachment
Fittings, if the Sealant Bead is Cracked Page 36
CONF ALL
B
FR102
FR93
A
B
A
Z311
Z312
LH
RH
C
C
ICN-A350-A-53XXP067-A-FAPE3-05UZN-A-001-01

### Page 37

A350
SERVICE BULLETIN
Figure ICN-A350-A-53XXP067-A-FAPE3-05UZO-A-003-01 SHEET 2/2
REV 00 Apr 09/21 A350-53-P067Application of Protection at the Upper Attachment
Fittings, if the Sealant Bead is Cracked Page 37
CONF ALL
C
A
A
LH SHOWN
RH SYMMETRICAL
A A INBDAPPLY MATERIAL No 06AAC101
NOTE:
APPLY MATERIAL No 12ABC102
TORQUE TIGHTEN THE NUTS BETWEEN 125 Nm (1106.35 lbf.in) AND 130 Nm (1150.59 lbf.in)04
CORNER
FITTING
BEARING
ASSEMBLY
BUSHING
04
PAD PLATE
CORNER
FITTING
LH SHOWN
RH SYMMETRICAL
0303
LOCK
WASHER
NUT
01
03
01
02
03
APPLY MATERIAL No 03GBC103
02
02
02
ICN-A350-A-53XXP067-A-FAPE3-05UZO-A-003-01

### Page 38

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 38
(3) Task A350-A-53-XX-P067-01001-300A-A (A350-A-53-XX-P067-01ZZZ-300Z-A)
Do a DVI of the Sealant Bead Around the Upper Frame Attachment Fittings
at FR102 - RH
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
311 Access Panel 311AB, Panel 314AR
Manpower/Resources/Skills
Man-hours 0.75 h
Minimum Number of person 1
Elapsed Time 0.75 h
Skills Airframe
Material necessary to do the job
Aircraft standard tools
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
98V55109011000 1 BEARING
Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
03GBC1
Synthetic Oil base Grease
- General Purpose Lithium
Thickened Low T emp
04DAB2
Primer Epoxy Paint -
- Corrosion Inhibiting
Structure
08BAA9 Non Aqueous Cleaner -General
10ABC1
Surface Pretreatment
- Light Alloys Chemical
Conversion Yellow
12ABC1
Corrosion Preventive
Compound - Water
Displacing Soft Film
14SBA1 T extile - Lint free Cotton
Referenced Information
Manuals/Drawings References/Sheets
ASR A350-A-51-21-11-00ZZZ-660Z-AA350-A-51-24-XX-01ZZZ-667Z-A
NDT A350-A-51-99-XX-01ZZZ-040Z-A
SD A350-A-06-2X-XX-01ZZZ-04CZ-AA350-A-06-3X-XX-01ZZZ-04CZ-A
PMS 01-02-10601-05-03
Procedure

### Page 39

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 39
(a) Standard Practices given in this procedure:
1 For identification of zones, refer to Ref. SD A350-A-06-3X-XX-01ZZZ-04CZ-A.
2 For the Frame (FR) identification, refer to Ref. SD A350-A-06-2X-XX-01ZZZ-
04CZ-A.
3 Repair the protective treatment of metal parts in accordance with Ref. ASR
A350-A-51-21-11-00ZZZ-660Z-A.
4 Apply sealant in accordance with Ref. ASR A350-A-51-24-XX-01ZZZ-667Z-A.
5 Clean the inspection area, refer to Ref. PMS 01-02-106.
(b) Do a visual inspection of the sealant bead around the Upper frame attachment
at Frame 102 in accordance with Ref. NDT A350-A-51-99-XX-01ZZZ-040Z-A,
refer to Ref. Fig. Flow Chart and Ref. Fig. Visual Inspection of Sealant Bead of the
Upper Attachment Fittings within the threshold given in PLANNING INFORMATION
paragraph E.(2).
1 If a sealant bead is not found around the bearing shoulder and nut:
a Do a check for grease.
<1> If grease is found around the bearing shoulder and nut, no
further action.
<2> If NO grease is found around the bearing shoulder and nut,
contact AIRBUS before the next flight.
2 If a sealant bead is found around the bearing shoulder and nut, continue to
the next step.
(c) Do a check for cracks in the sealant bead.
1 If the sealant bead is cracked:
a Remove the fillet sealant from the contour of the bearing to corner
fitting assembly.
NOTE: Use a plastic spatula to remove the sealant.
NOTE: Remove all the sealant in order to allow the tabs are visible.
NOTE: It is important to remove the sealant between the nut and
the washer. It should be removed in order to avoid that the
lock washer would be stuck to the nut due to the sealant.
b Clean the working area, refer to Ref. PMS 01-02-106 and with:
  T extile - Lint free Cotton14SBA1  
made moist with:
  Non Aqueous Cleaner -
General
08BAA9  
c Using a suitable punch, bend the tab flush with the structure using
masking to prevent damage to the component surface treatment. Un-
bend the tab to unlock the lock washer, refer to Ref. PMS 01-05-03.
NOTE: Mark the un-bent tab. It is not allowed to re-use the un-bent
tab.
NOTE: Ensure that bending the tab does not result in any cracking,
thinning or damage to the tab.

### Page 40

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 40
d Loosen the bearing nut with:
1 BEARING TOOL SET -
HTP
98V55109011000  
e Loosen the washer.
f Clean the working area, refer to Ref. PMS 01-02-106 and with:
  T extile - Lint free Cotton14SBA1  
made moist with:
  Non Aqueous Cleaner -
General
08BAA9  
g If necessary, remove interfay sealant with a plastic spatula.
h Remove any traces of debris from the nut, lock washer and corner
fitting.
i Do a detailed inspection of the affected bearing zone , refer to Ref.
T ask A350-A-53-XX-P067-04ZZZ-311Z-A.
2 If the sealant bead is NOT cracked:
a Remove the fillet sealant from the contour of the bearing to corner
fitting assembly.
NOTE: Use a plastic spatula to remove the sealant.
NOTE: Remove all the sealant in order to allow the tabs are visible.
NOTE: It is important to remove the sealant between the nut and
the washer. It should be removed in order to avoid that the
lock washer would be stuck to the nut due to the sealant.
b Clean the working area, refer to Ref. PMS 01-02-106 and with:
  T extile - Lint free Cotton14SBA1  
made moist with:
  Non Aqueous Cleaner -
General
08BAA9  
c If paint is damaged during the sealant removal, apply protection with:
  Surface Pretreatment
- Light Alloys Chemical
Conversion Yellow
10ABC1  
  Primer Epoxy Paint -
- Corrosion Inhibiting
Structure
04DAB2  
d Using a suitable punch, bend the tab flush with the structure using
masking to prevent damage to the component surface treatment. Un-
bend the tab to unlock the lock washer, refer to Ref. PMS 01-05-03.
NOTE: Mark the un-bent tab. It is not allowed to re-use the un-bent
tab.
NOTE: Ensure that bending the tab does not result in any cracking,
thinning or damage to the tab.

### Page 41

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 41
e T orque the bearing nut to between 125 Nm (1106.35 lbf.in) and 130
Nm (1150.59 lbf.in), using:
1 BEARING TOOL SET -
HTP
98V55109011000  
f Bend a new tab on the washer, refer to Ref. PMS 01-05-03.
NOTE: Make sure that the tab washer has been correctly assembled
and bent over to effect a positive locking, without any
damage and that any sharp edges are deburred.
g Apply CPC around the bearing and fitting interfaces, refer to Ref.
Fig. Application of Protection at the Upper Attachment Fittings, if the
Sealant Bead is not Cracked.
  Corrosion Preventive
Compound - Water
Displacing Soft Film
12ABC1  
h Apply grease 30 minutes after the application of CPC, around the
bearing contour.
  Synthetic Oil base
Grease - General
Purpose Lithium
Thickened Low T emp
03GBC1  
i No further action.

### Page 42

A350
SERVICE BULLETIN
Figure ICN-A350-A-53XXP067-A-FAPE3-05UZT-A-007-01 SHEET 1/1
REV 00 Apr 09/21 A350-53-P067Flow Chart
Page 42
CONF ALL
NOTE:
THE PURPOSE OF FLOWCHARTS IS TO SUPPLEMENT
THE INFORMATION GIVEN IN THE PROCEDURE AND 
COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS
THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE
TIMES GIVEN IN THE SERVICE BULLETIN.
AROUND THE UPPER AND LOWER FRAME
ATTACHMENT FITTINGS AT FR102
DO A VISUAL INSPECTION OF THE SEALANT BEAD
IS THERE
A SEALANT BEAD
AROUND THE BEARING
SHOULDER AND
NO FOR GREASEDO A CHECK
IS
THERE
GREASE? NO
BEFORE NEXT FLIGHT
CONTACT AIRBUS
YES
SEALANT BEAD
CRACKED?
YES
NO
WASHER AND THE
LOOSEN THE TAB
BEARING NUT
BEARING CONTOUR
APPLY GREASE AROUND THE
IS THE
INSPECTION OF THE 
AFFECTED BEARING ZONE
DO A DETAILED
THE BEARING CONTOUR
APPLY CPC AROUND
NO FURTHER ACTION
NUT?
YES
SEALANT BEAD
REMOVE THE
CRACKS IN THE
SEALANT BEAD
DO A CHECK FOR
IS THERE
CORROSION ON
THE AFFECTED
BEARING
YES
BEFORE NEXT FLIGHT
CONTACT AIRBUS
SEALANT BEAD
REMOVE THE
NO
APPLY TORQUE ON THE 
BEARING NUT AND BEND
THE TAB WASHER
APPLY SEALANT
NO FURTHER ACTION
INSPECTION AREA
CLEAN THE
ZONE?
TAB WASHER
UNBEND THE
TAB WASHER
UNBEND THE
ICN-A350-A-53XXP067-A-FAPE3-05UZT-A-007-01

### Page 43

A350
SERVICE BULLETIN
Figure ICN-A350-A-53XXP067-A-FAPE3-05UZL-A-001-01 SHEET 1/2
REV 00 Apr 09/21 A350-53-P067Visual Inspection of Sealant Bead
of the Upper Attachment Fittings Page 43
CONF ALL
B
FR102
FR93
A
B
A
Z311
Z312
LH
RH
C
C
ICN-A350-A-53XXP067-A-FAPE3-05UZL-A-001-01

### Page 44

A350
SERVICE BULLETIN
Figure ICN-A350-A-53XXP067-A-FAPE3-05UZM-A-001-01 SHEET 2/2
REV 00 Apr 09/21 A350-53-P067Visual Inspection of Sealant Bead
of the Upper Attachment Fittings Page 44
CONF ALL
C
A
A
LH SHOWN
RH SYMMETRICAL
A A INBD
NOTE:
INSPECTION AREA
NUT
LOCK
WASHER
CORNER
FITTING
BEARING
ASSEMBLY
BUSHING
PAD PLATE
CORNER
FITTING
LH SHOWN
RH SYMMETRICAL
ICN-A350-A-53XXP067-A-FAPE3-05UZM-A-001-01

### Page 45

A350
SERVICE BULLETIN
Figure ICN-A350-A-53XXP067-A-FAPE3-05YWR-A-001-01 SHEET 1/2
REV 00 Apr 09/21 A350-53-P067Application of Protection at the Upper Attachment
Fittings, if the Sealant Bead is not Cracked Page 45
CONF ALL
B
FR102
FR93
A
B
A
Z311
Z312
LH
RH
C
C
ICN-A350-A-53XXP067-A-FAPE3-05YWR-A-001-01

### Page 46

A350
SERVICE BULLETIN
Figure ICN-A350-A-53XXP067-A-FAPE3-05YWS-A-001-01 SHEET 2/2
REV 00 Apr 09/21 A350-53-P067Application of Protection at the Upper Attachment
Fittings, if the Sealant Bead is not Cracked Page 46
CONF ALL
C
A
A
LH SHOWN
RH SYMMETRICAL
A A INBD01NOTE:APPLY MATERIAL No 12ABC1
02
TORQUE TIGHTEN THE NUTS BETWEEN 125 Nm (1106.35 lbf.in)
CORNER
FITTING
BEARING
ASSEMBLY
BUSHING
03
PAD PLATE
CORNER
FITTING
LH SHOWN
RH SYMMETRICAL
0202
LOCK
WASHER
NUT
02
01
02
APPLY MATERIAL No 03GBC1
03
01
01
01
AND 130 Nm (1150.59 lbf.in) ICN-A350-A-53XXP067-A-FAPE3-05YWS-A-001-01

### Page 47

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 47
(4) Task A350-A-53-XX-P067-04001-311A-A (A350-A-53-XX-P067-04ZZZ-311Z-A)
Do a DET of Accessible Area all around the Upper Frame Attachment Fitting
at Frame 102 - RH, Depending on the Inspection Result
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
311 Access Panel 311AB, Panel 314AR
Manpower/Resources/Skills
Man-hours 6.00 h
Minimum Number of person 2
Elapsed Time 6.00 h
Skills Non-Destructive T esting
Material necessary to do the job
Aircraft standard tools
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
98V55109011000 1 BEARING
Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
03GBC1
Synthetic Oil base Grease
- General Purpose Lithium
Thickened Low T emp
04DAB2
Primer Epoxy Paint -
- Corrosion Inhibiting
Structure
06AAC1 Polysulfide Sealant -General Purpose Interfay
10ABC1
Surface Pretreatment
- Light Alloys Chemical
Conversion Yellow
12ABC1
Corrosion Preventive
Compound - Water
Displacing Soft Film
Referenced Information
Manuals/Drawings References/Sheets
NDT A350-A-51-99-12-00ZZZ-311Z-A
SD A350-A-06-2X-XX-01ZZZ-04CZ-AA350-A-06-3X-XX-01ZZZ-04CZ-A
PMS 01-05-03
Procedure
(a) Standard Practices given in this procedure:
1 For identification of zones, refer to Ref. SD A350-A-06-3X-XX-01ZZZ-04CZ-A.

### Page 48

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 48
2 For the Frame (FR) identification, refer to Ref. SD A350-A-06-2X-XX-01ZZZ-
04CZ-A.
(b) Do a detailed inspection all around accessible area at corner fitting, bushing and
bearing interface to find any traces of corrosion on aluminium, cracks or paint
degradation (flaking and/or blisters) in accordance with Ref. NDT A350-A-51-99-
12-00ZZZ-311Z-A, refer to Ref. Fig. Detailed Inspection for Corrosion of the Upper
Attachment Fittings.
1 If corrosion, cracks or paint degradation are found on the bearing zone,
contact AIRBUS.
2 If corrosion is NOT found on the affected bearing zone:
a Apply interfay sealant in the contact surface between the lock washer
and fitting, refer to Ref. Fig. Application of Protection at the Upper
Attachment Fittings, if Sealant Bead is Cracked, Section A-A.
  Polysulfide Sealant
- General Purpose
Interfay
06AAC1  
b If paint is damaged during the sealant removal, apply protection with:
  Surface Pretreatment
- Light Alloys Chemical
Conversion Yellow
10ABC1  
  Primer Epoxy Paint -
- Corrosion Inhibiting
Structure
04DAB2  
c T orque the bearing nut to between 125 Nm (1106.35 lbf.in) and 130
Nm (1150.59 lbf.in), using:
1 BEARING TOOL SET -
HTP
98V55109011000  
d Bend a new tab on the washer, refer to Ref. PMS 01-05-03.
NOTE: Make sure that the tab washer has been correctly assembled
and bent over to effect a positive locking, without any
damage and that any sharp edges are deburred.
e Apply CPC around the bearing and fitting interfaces.
  Corrosion Preventive
Compound - Water
Displacing Soft Film
12ABC1  
f Apply grease 30 minutes after the application of CPC, around the
bearing contour.
  Synthetic Oil base
Grease - General
Purpose Lithium
Thickened Low T emp
03GBC1  
g No further action.

### Page 49

A350
SERVICE BULLETIN
Figure ICN-A350-A-53XXP067-A-FAPE3-05UZH-A-001-01 SHEET 1/2
REV 00 Apr 09/21 A350-53-P067Detailed Inspection for Corrosion
of the Upper Attachment Fittings Page 49
CONF ALL
B
FR102
FR93
A
B
A
Z311
Z312
LH
RH
C D
C D
ICN-A350-A-53XXP067-A-FAPE3-05UZH-A-001-01

### Page 50

A350
SERVICE BULLETIN
Figure ICN-A350-A-53XXP067-A-FAPE3-05UZI-A-001-01 SHEET 2/2
REV 00 Apr 09/21 A350-53-P067Detailed Inspection for Corrosion
of the Upper Attachment Fittings Page 50
CONF ALL
VIEW LOOKING INBD
VIEW LOOKING OUTBD
NOTE:
INSPECTION AREA
C
D
FWD
FWD
RH SHOWN
LH SYMMETRICAL
RH SHOWN
LH SYMMETRICAL
ICN-A350-A-53XXP067-A-FAPE3-05UZI-A-001-01

### Page 51

A350
SERVICE BULLETIN
Figure ICN-A350-A-53XXP067-A-FAPE3-05UZN-A-001-01 SHEET 1/2
REV 00 Apr 09/21 A350-53-P067Application of Protection at the Upper Attachment
Fittings, if the Sealant Bead is Cracked Page 51
CONF ALL
B
FR102
FR93
A
B
A
Z311
Z312
LH
RH
C
C
ICN-A350-A-53XXP067-A-FAPE3-05UZN-A-001-01

### Page 52

A350
SERVICE BULLETIN
Figure ICN-A350-A-53XXP067-A-FAPE3-05UZO-A-003-01 SHEET 2/2
REV 00 Apr 09/21 A350-53-P067Application of Protection at the Upper Attachment
Fittings, if the Sealant Bead is Cracked Page 52
CONF ALL
C
A
A
LH SHOWN
RH SYMMETRICAL
A A INBDAPPLY MATERIAL No 06AAC101
NOTE:
APPLY MATERIAL No 12ABC102
TORQUE TIGHTEN THE NUTS BETWEEN 125 Nm (1106.35 lbf.in) AND 130 Nm (1150.59 lbf.in)04
CORNER
FITTING
BEARING
ASSEMBLY
BUSHING
04
PAD PLATE
CORNER
FITTING
LH SHOWN
RH SYMMETRICAL
0303
LOCK
WASHER
NUT
01
03
01
02
03
APPLY MATERIAL No 03GBC103
02
02
02
ICN-A350-A-53XXP067-A-FAPE3-05UZO-A-003-01

### Page 53

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 53
(5) Task A350-A-53-XX-P067-02001-311A-A (A350-A-53-XX-P067-02ZZZ-311Z-A)
Do a DVI of the Sealant Bead around the Lower Frame Attachment Fitting at
Frame 102 - LH
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
312 Access Panel 311AB, Panel 314AR
Manpower/Resources/Skills
Man-hours 0.75 h
Minimum Number of person 1
Elapsed Time 0.75 h
Skills Airframe
Material necessary to do the job
Aircraft standard tools
ITEM PART No. QTY (UM) KEYWORD DRAWING SEE NOTES
98V55109011000 1 BEARING
Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
03GBC1
Synthetic Oil base Grease
- General Purpose Lithium
Thickened Low T emp
04DAB2
Primer Epoxy Paint -
- Corrosion Inhibiting
Structure
04JME4 T op Coat Polyurethane - -Grey InternalStructure
08BAA9 Non Aqueous Cleaner -General
10ABC1
Surface Pretreatment
- Light Alloys Chemical
Conversion Yellow
12ABC1
Corrosion Preventive
Compound - Water
Displacing Soft Film
14SBA1 T extile - Lint free Cotton
Referenced Information
Manuals/Drawings References/Sheets
ASR A350-A-51-21-11-00ZZZ-660Z-AA350-A-51-24-XX-01ZZZ-667Z-A
NDT A350-A-51-99-XX-01ZZZ-040Z-A
SD A350-A-06-2X-XX-01ZZZ-04CZ-AA350-A-06-3X-XX-01ZZZ-04CZ-A
PMS 01-02-10601-05-03

### Page 54

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 54
Procedure
(a) Standard Practices given in this procedure:
1 For identification of zones, refer to Ref. SD A350-A-06-3X-XX-01ZZZ-04CZ-A.
2 For the Frame (FR) identification, refer to Ref. SD A350-A-06-2X-XX-01ZZZ-
04CZ-A.
3 Repair the protective treatment of metal parts in accordance with Ref. ASR
A350-A-51-21-11-00ZZZ-660Z-A.
4 Apply sealant in accordance with Ref. ASR A350-A-51-24-XX-01ZZZ-667Z-A.
5 Clean the inspection area, refer to Ref. PMS 01-02-106.
(b) Do a visual inspection of the sealant bead around the Lower frame attachment
at Frame 102 in accordance with Ref. NDT A350-A-51-99-XX-01ZZZ-040Z-A,
refer to Ref. Fig. Flow Chart and Ref. Fig. Visual Inspection of Sealant Bead of the
Lower Attachment Fittings within the threshold given in PLANNING INFORMATION
paragraph E.(2).
1 If a sealant bead is not found around the bearing shoulder and nut:
a Do a check for grease.
<1> If grease is found around the bearing shoulder and nut, no
further action.
<2> If NO grease is found around the bearing shoulder and nut,
contact AIRBUS before the next flight.
(c) Do a check for cracks in the sealant bead.
1 If the sealant bead is cracked:
a Remove the fillet sealant from the contour of the bearing to corner
fitting assembly.
NOTE: Use a plastic spatula to remove the sealant.
NOTE: Remove all the sealant in order to allow the tabs are visible.
NOTE: It is important to remove the sealant between the nut and
the washer. It should be removed in order to avoid that the
lock washer would be stuck to the nut due to the sealant.
b Clean the working area, refer to Ref. PMS 01-02-106 and with:
  T extile - Lint free Cotton14SBA1  
made moist with:
  Non Aqueous Cleaner -
General
08BAA9  
c Using a suitable punch, bend the tab flush with the structure using
masking to prevent damage to the component surface treatment. Un-
bend the tab to unlock the lock washer, refer to Ref. PMS 01-05-03.
NOTE: Mark the un-bent tab. It is not allowed to re-use the un-bent
tab.
NOTE: Ensure that bending the tab does not result in any cracking,
thinning or damage to the tab.

### Page 55

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 55
d Loosen the bearing nut with:
1 BEARING TOOL SET -
HTP
98V55109011000  
e Loosen the washer.
f Clean the working area, refer to Ref. PMS 01-02-106 and with:
  T extile - Lint free Cotton14SBA1  
made moist with:
  Non Aqueous Cleaner -
General
08BAA9  
g If necessary, remove interfay sealant with a plastic spatula.
h Remove any traces of debris from the nut, lock washer and corner
fitting.
i Do a detailed inspection of the affected bearing zone, refer to Ref.
T ask A350-A-53-XX-P067-07ZZZ-311Z-A.
2 If the sealant bead is NOT cracked:
a Remove the fillet sealant from the contour of the bearing to corner
fitting assembly.
NOTE: Use a plastic spatula to remove the sealant.
NOTE: Remove all the sealant in order to allow the tabs are visible.
NOTE: It is important to remove the sealant between the nut and
the washer. It should be removed in order to avoid that the
lock washer would be stuck to the nut due to the sealant.
b Clean the working area, refer to Ref. PMS 01-02-106 and with:
  T extile - Lint free Cotton14SBA1  
made moist with:
  Non Aqueous Cleaner -
General
08BAA9  
c If paint is damaged during the sealant removal, apply protection with:
  Surface Pretreatment
- Light Alloys Chemical
Conversion Yellow
10ABC1  
  Primer Epoxy Paint -
- Corrosion Inhibiting
Structure
04DAB2  
  T op Coat Polyurethane -
- Grey InternalStructure
04JME4  
d Using a suitable punch, bend the tab flush with the structure using
masking to prevent damage to the component surface treatment. Un-
bend the tab to unlock the lock washer, refer to Ref. PMS 01-05-03.
NOTE: Mark the un-bent tab. It is not allowed to re-use the un-bent
tab.

### Page 56

A350
SERVICE BULLETIN
REV 00 Apr 09/21 A350-53-P067
Page 56
NOTE: Ensure that bending the tab does not result in any cracking,
thinning or damage to the tab.
e T orque the bearing nut to between 125 Nm (1106.35 lbf.in) and 130
Nm (1150.59 lbf.in), using:
1 BEARING TOOL SET -
HTP
98V55109011000  
f Bend a new tab on the washer, refer to Ref. PMS 01-05-03.
NOTE: Make sure that the tab washer has been correctly assembled
and bent over to effect a positive locking, without any
damage and that any sharp edges are deburred.
g Apply CPC around the bearing and fitting interfaces, refer to Ref.
Fig. Application of Protection at the Lower Attachment Fittings, if the
Sealant Bead is not Cracked.
  Corrosion Preventive
Compound - Water
Displacing Soft Film
12ABC1  
h Apply grease 30 minutes after the application of CPC, around the
bearing contour.
  Synthetic Oil base
Grease - General
Purpose Lithium
Thickened Low T emp
03GBC1  
i No further action.

### Page 57

A350
SERVICE BULLETIN
Figure ICN-A350-A-53XXP067-A-FAPE3-05UZT-A-007-01 SHEET 1/1
REV 00 Apr 09/21 A350-53-P067Flow Chart
Page 57
CONF ALL
NOTE:
THE PURPOSE OF FLOWCHARTS IS TO SUPPLEMENT
THE INFORMATION GIVEN IN THE PROCEDURE AND 
COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS
THE PRIMARY SOURCE FOR TASKS OR COMPLIANCE
TIMES GIVEN IN THE SERVICE BULLETIN.
AROUND THE UPPER AND LOWER FRAME
ATTACHMENT FITTINGS AT FR102
DO A VISUAL INSPECTION OF THE SEALANT BEAD
IS THERE
A SEALANT BEAD
AROUND THE BEARING
SHOULDER AND
NO FOR GREASEDO A CHECK
IS
THERE
GREASE? NO
BEFORE NEXT FLIGHT
CONTACT AIRBUS
YES
SEALANT BEAD
CRACKED?
YES
NO
WASHER AND THE
LOOSEN THE TAB
BEARING NUT
BEARING CONTOUR
APPLY GREASE AROUND THE
IS THE
INSPECTION OF THE 
AFFECTED BEARING ZONE
DO A DETAILED
THE BEARING CONTOUR
APPLY CPC AROUND
NO FURTHER ACTION
NUT?
YES
SEALANT BEAD
REMOVE THE
CRACKS IN THE
SEALANT BEAD
DO A CHECK FOR
IS THERE
CORROSION ON
THE AFFECTED
BEARING
YES
BEFORE NEXT FLIGHT
CONTACT AIRBUS
SEALANT BEAD
REMOVE THE
NO
APPLY TORQUE ON THE 
BEARING NUT AND BEND
THE TAB WASHER
APPLY SEALANT
NO FURTHER ACTION
INSPECTION AREA
CLEAN THE
ZONE?
TAB WASHER
UNBEND THE
TAB WASHER
UNBEND THE
ICN-A350-A-53XXP067-A-FAPE3-05UZT-A-007-01

### Page 58

A350
SERVICE BULLETIN
Figure ICN-A350-A-53XXP067-A-FAPE3-05UZV-A-001-01 SHEET 1/2
REV 00 Apr 09/21 A350-53-P067Visual Inspection of Sealant Bead
of the Lower Attachment Fittings Page 58
CONF ALL
B
FR102
FR93
A
B
A
Z311
Z312
LH
RH
C
C
ICN-A350-A-53XXP067-A-FAPE3-05UZV-A-001-01

### Page 59

A350
SERVICE BULLETIN
Figure ICN-A350-A-53XXP067-A-FAPE3-05UZW-A-001-01 SHEET 2/2
REV 00 Apr 09/21 A350-53-P067Visual Inspection of Sealant Bead
of the Lower Attachment Fittings Page 59
CONF ALL
C
LH SHOWN
RH SYMMETRICAL
A
A
A A INBD
NUT
LOCK
WASHER
CORNER
FITTING
BEARING
ASSEMBLY
BUSHING
PAD PLATE
CORNER
FITTING
NOTE:
INSPECTION AREA
LH SHOWN
RH SYMMETRICAL
ICN-A350-A-53XXP067-A-FAPE3-05UZW-A-001-01

### Page 60

A350
SERVICE BULLETIN
Figure ICN-A350-A-53XXP067-A-FAPE3-05YWT-A-001-01 SHEET 1/2
REV 00 Apr 09/21 A350-53-P067Application of Protection at the Lower Attachment
Fittings, if the Sealant Bead is not Cracked Page 60
CONF ALL
B
FR102
FR93
A
B
A
Z311
Z312
LH
RH
C
C
ICN-A350-A-53XXP067-A-FAPE3-05YWT-A-001-01

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