# Airbus Service Bulletin A350-57-P076

Copy: No revision named ("SB_57-P076_r00"), 73 pages: PDF https://openairdocs.org/files/sha256/26/a3/26a313d31718d062728c13c2a86f24a44c602f2b29ffed4c69e176a4818943dd; text https://openairdocs.org/service-documents/airbus/a350-57-p076/file/26a313d31718.md. Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2022-1567, the docket of AD 2022-25-09. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Airbus](https://openairdocs.org/service-documents/airbus.md)
- Type: Service bulletin (Service Bulletin)
- Number: A350-57-P076
- Page: https://openairdocs.org/service-documents/airbus/a350-57-p076

## Text (73 pages)

Rights: © Airbus S.A.S. Filed by the FAA in regulations.gov docket FAA-2022-1567, the docket of AD 2022-25-09. 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 Nov 05/21 A350-57-P076
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: 57
TITLE: WINGS - OUTER WING - INSPECTION OF WING UPPER AND LOWER
COVERS FOR MISSING HEAVY EXPANDED COPPER FOIL PATCHES
MODIFICATION No.:
None

### Page 2

A350
SERVICE BULLETIN
SUMMARY
REV 00 Nov 05/21 A350-57-P076
Page 2
ATA SYSTEM: 57
TITLE: WINGS - OUTER WING - INSPECTION OF WING UPPER AND LOWER
COVERS FOR MISSING HEAVY EXPANDED COPPER FOIL PATCHES
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 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.
CONF 002
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.
CONF ALL
B. REASON
(1) History
It has been identified that, due to a production quality issue, Heavy Expanded Copper
Foil (HECF) patches may not have been installed at all required locations of the A350
Wing Lower Cover (WLC) and Wing Upper Cover (WUC).
Non-Destructive T est (NDT) data available from the production line for all the affected
aircraft has been reviewed to confirm the specific location of missing patches. For
a determined set of aircraft, the missing patches are confirmed and they require
corrective action by repair. For those aircraft for which the review of production NDT
data available has not been possible to determine if the HECF patches are missing or
not, a one-time Special Detailed Inspection (SDI) is required to confirm the presence of
the required HECF patches.
(2) Objective/Action
This Service Bulletin provides the necessary instructions to:
- Apply the correction of the already confirmed missing patches by repair
instructions
- Perform an Ultrasonic (US) inspection to confirm the presence of the required
HECF on those aircraft for which the assessment with NDT data available was
inconclusive.

### Page 3

A350
SERVICE BULLETIN
SUMMARY
REV 00 Nov 05/21 A350-57-P076
Page 3
(3) Advantages
Accomplishment of this Service Bulletin will restore the missing layer of lightning strike
protection in accordance with the certification requirements.
(4) Operational/Maintenance Consequences
None
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) Repair Instruction to put missing HECF Patches
(a) T ask set A350-A-57-XX-P076-01000-93CA-A Repair Instruction to put missing
HECF Patches
No material
CONF 002
(1) Inspection of WUC and WLC for missing HECF Patches
(a) T ask set A350-A-57-XX-P076-01000-93BA-A Inspection of WUC and WLC for
missing HECF Patches
No material
CONF ALL
F. APPLICABILITY
This Service Bulletin is applicable to this (these) operator(s):
AAR AFR AZU CHH CPA CSC DLH QTR SIA THA THY VIR
G. CONCURRENT REQUIREMENTS
None
H. NATURE OF THE WORK

### Page 4

A350
SERVICE BULLETIN
SUMMARY
REV 00 Nov 05/21 A350-57-P076
Page 4
CONF 001
(1) Repair Instruction to put missing HECF Patches
(a) T ask set A350-A-57-XX-P076-01000-93CA-A Repair Instruction to put missing
HECF Patches
AIRCRAFT YES
EQUIPMENT NO
CONF 002
(1) Inspection of WUC and WLC for missing HECF Patches
(a) T ask set A350-A-57-XX-P076-01000-93BA-A Inspection of WUC and WLC for
missing HECF Patches
AIRCRAFT YES
EQUIPMENT NO
CONF ALL
I. MANPOWER
CONF 001
(1) Repair Instruction to put missing HECF Patches
(a) T ask set A350-A-57-XX-P076-01000-93CA-A Repair Instruction to put missing
HECF Patches
MANPOWER
TOTAL MAN-HOURS 3.50 h
ELAPSED TIME (HOURS) 3.50 h
CONF 002
(1) Inspection of WUC and WLC for missing HECF Patches
(a) T ask set A350-A-57-XX-P076-01000-93BA-A Inspection of WUC and WLC for
missing HECF Patches
MANPOWER
TOTAL MAN-HOURS 10.50 h
ELAPSED TIME (HOURS) 10.50 h

### Page 5

A350
SERVICE BULLETIN
SUMMARY
Figure ICN-A350-A-57XXP076-A-FAPE3-067J7-A-002-01 Fig.SA Sol.AB SHEET 1/3
REV 00 Nov 05/21 A350-57-P076General Overview
Page 5
CONF ALL
J. GENERAL OVERVIEW
CONF 001
A
B
Z500
Z600
C
VIEW LOOKING UP
F
W
D A RIB22
RIB23
REPAIR OF WLC FOR HECF PATCHES
FRONT SPAR
ICN-A350-A-57XXP076-A-FAPE3-067J7-A-002-01

### Page 6

A350
SERVICE BULLETIN
SUMMARY
Figure ICN-A350-A-57XXP076-A-FAPE3-067J8-A-001-01 Fig.SA Sol.AB SHEET 2/3
REV 00 Nov 05/21 A350-57-P076General Overview
Page 6
CONF 001
RIB7
RIB15
VIEW LOOKING DOWN
F
W
D
REPAIR OF WUC FOR HECF PATCHES
B
STGR14
STGR1
ICN-A350-A-57XXP076-A-FAPE3-067J8-A-001-01

### Page 7

A350
SERVICE BULLETIN
SUMMARY
Figure ICN-A350-A-57XXP076-A-FAPE3-067J9-A-001-01 Fig.SA Sol.AB SHEET 3/3
REV 00 Nov 05/21 A350-57-P076General Overview
Page 7
CONF 001
STGR17
STGR18
RIB1
RIB2
RIB3
RIB4
RIB2A
VIEW LOOKING UP
F
W
D C
REPAIR OF WLC FOR HECF PATCHES
REAR SPAR
ICN-A350-A-57XXP076-A-FAPE3-067J9-A-001-01

### Page 8

A350
SERVICE BULLETIN
SUMMARY
Figure ICN-A350-A-57XXP076-A-FAPE3-067A9-A-001-01 Fig.SA Sol.AA SHEET 1/4
REV 00 Nov 05/21 A350-57-P076General Overview
Page 8
CONF 002
C
STGR5
STGR4
STGR2
STGR6
STGR7
STGR8
STGR9
STGR10
STGR11
STGR13
STGR14
STGR16
STGR17
STGR12
STGR15
STGR18
STGR3
RIB22
RIB16
RIB2
RIB1
RIB3
RIB4
RIB5
RIB6
RIB7
RIB8
RIB9
RIB10
RIB11
RIB12
RIB13
RIB14
RIB15
RIB17
RIB18
RIB19 RIB20
RIB21 RIB23
RIB24
RIB25
RIB26
RIB27
RIB28
STGR1
VIEW LOOKING DOWN
A
F
W
D
UC1
UC2
UC3
UC4
UC5
UC6
UC7
UC8
UC9
UC10
UC11
UC12
UC13
UC14
UC15
UC16
INSPECTION AREA
NOTE:
B
A
Z500
Z600
INSPECTION OF WUC FOR HECF PATCHES
D
ICN-A350-A-57XXP076-A-FAPE3-067A9-A-001-01

### Page 9

A350
SERVICE BULLETIN
SUMMARY
Figure ICN-A350-A-57XXP076-A-FAPE3-067AA-A-001-01 Fig.SA Sol.AA SHEET 2/4
REV 00 Nov 05/21 A350-57-P076General Overview
Page 9
CONF 002
STGR3
STGR4
STGR5
STGR6
STGR7
STGR8
STGR9
STGR10
STGR11
STGR13
STGR14
STGR16
STGR17
STGR12
STGR15
STGR18
RIB9
RIB10 RIB11
RIB12
RIB13
RIB14
RIB15
RIB1
RIB2
RIB3
RIB4 RIB5
RIB6
RIB7
RIB8
RIB2A
RIB16
RIB17
RIB18
RIB20 RIB21
RIB22
RIB23
RIB24
RIB25
RIB26
RIB27
RIB28
RIB19
STGR2
B
VIEW LOOKING UP
F
W
D
LC1
LC4 LC2
LC3
INSPECTION AREA
NOTE:
INSPECTION OF WLC FOR HECF PATCHES
ICN-A350-A-57XXP076-A-FAPE3-067AA-A-001-01

### Page 10

A350
SERVICE BULLETIN
SUMMARY
Figure ICN-A350-A-57XXP076-A-FAPE3-067I4-A-001-01 Fig.SA Sol.AA SHEET 3/4
REV 00 Nov 05/21 A350-57-P076General Overview
Page 10
CONF 002
STGR5
STGR4
STGR2
STGR6
STGR7
STGR8
STGR9
STGR10
STGR11
STGR13
STGR14
STGR16
STGR17
STGR12
STGR15
STGR18
STGR3
RIB22
RIB16
RIB2
RIB1
RIB3
RIB4
RIB5
RIB6
RIB7
RIB8
RIB9
RIB10
RIB11
RIB12
RIB13
RIB14
RIB15
RIB17
RIB18
RIB19RIB20
RIB21RIB23
RIB24
RIB25
RIB26
RIB27
RIB28
STGR1
VIEW LOOKING DOWN
UC1
UC2
UC3
UC4
UC5
UC6
UC7
UC8
F
W
D
INSPECTION AREA
NOTE:
INSPECTION OF WUC FOR HECF PATCHES
C
ICN-A350-A-57XXP076-A-FAPE3-067I4-A-001-01

### Page 11

A350
SERVICE BULLETIN
SUMMARY
Figure ICN-A350-A-57XXP076-A-FAPE3-067I5-A-001-01 Fig.SA Sol.AA SHEET 4/4
REV 00 Nov 05/21 A350-57-P076General Overview
Page 11
CONF 002
STGR3
STGR4
STGR5
STGR6
STGR7
STGR8
STGR9
STGR10
STGR11
STGR13
STGR14
STGR16
STGR17
STGR12
STGR15
STGR18
RIB9
RIB10RIB11
RIB12
RIB13
RIB14
RIB15
RIB1
RIB2
RIB3
RIB4RIB5
RIB6
RIB7
RIB8
RIB2A
RIB16
RIB17
RIB18
RIB20RIB21
RIB22
RIB23
RIB24
RIB25
RIB26
RIB27
RIB28
RIB19
STGR2
VIEW LOOKING UP
LC1
LC2
LC3
F
W
D
INSPECTION AREA
NOTE:
INSPECTION OF WLC FOR HECF PATCHES
D
ICN-A350-A-57XXP076-A-FAPE3-067I5-A-001-01

### Page 12

A350
SERVICE BULLETIN
REV 00 Nov 05/21 A350-57-P076
Page 12
ATA SYSTEM: 57
TITLE: WINGS - OUTER WING - INSPECTION OF WING UPPER AND LOWER
COVERS FOR MISSING HEAVY EXPANDED COPPER FOIL PATCHES
CONF ALL
1. PLANNING INFORMATION
A. APPLICABILITY
(1) Models
ON A/C 0298
350-1041
ON A/C 0044, 0060, 0061, 0124, 0211, 0224, 0237, 0251, 0292, 0385, 0407, 0421
350-941
CONF ALL
(2) Applicability by MSN
0044 0060 0061 0124 0211 0224 0237 0251 0292 0298 0385 0407 0421
(3) MSN by configuration
CONF 001
MSN CONFIGURATION
0044 0060 0061 0292 0298 001
CONF 002
MSN CONFIGURATION
0124 0211 0224 0237 0251 0385 0407 0421 002
CONF ALL
(4) Configuration definition
CONF 001
Configuration 001
CONF 001 is applicable for all the aircraft which have known location of missing
HECF patches.
CONF 002
Configuration 002
CONF 002 is applicable for all the aircraft which have possible missing HECF
patches and need to be inspected.
CONF ALL
B. CONCURRENT REQUIREMENTS
None
C. REASON
(1) History
It has been identified that, due to a production quality issue, Heavy Expanded Copper
Foil (HECF) patches may not have been installed at all required locations of the A350
Wing Lower Cover (WLC) and Wing Upper Cover (WUC).

### Page 13

A350
SERVICE BULLETIN
REV 00 Nov 05/21 A350-57-P076
Page 13
Non-Destructive T est (NDT) data available from the production line for all the affected
aircraft has been reviewed to confirm the specific location of missing patches. For
a determined set of aircraft, the missing patches are confirmed and they require
corrective action by repair. For those aircraft for which the review of production NDT
data available has not been possible to determine if the HECF patches are missing or
not, a one-time Special Detailed Inspection (SDI) is required to confirm the presence of
the required HECF patches.
(2) Objective/Action
This Service Bulletin provides the necessary instructions to:
- Apply the correction of the already confirmed missing patches by repair
instructions
- Perform an Ultrasonic (US) inspection to confirm the presence of the required
HECF on those aircraft for which the assessment with NDT data available was
inconclusive.
(3) Advantages
Accomplishment of this Service Bulletin will restore the missing layer of lightning strike
protection in accordance with the certification requirements.
(4) Operational/Maintenance Consequences
None
D. DESCRIPTION
T o accomplish this Service Bulletin it is necessary to:
CONF 001
(1) Repair Instruction to put missing HECF Patches
(a) T ask set A350-A-57-XX-P076-01000-93CA-A Repair Instruction to put missing
HECF Patches
1 Repair the WUC and WLC for HECF Patches, LH side
2 Repair the WUC and WLC for HECF Patches, RH side
CONF 002
(2) Inspection of WUC and WLC for missing HECF Patches
(a) T ask set A350-A-57-XX-P076-01000-93BA-A Inspection of WUC and WLC for
missing HECF Patches
1 Do a SDI of the WUC and WLC for HECF Patches, LH side
2 Do a SDI of the WUC and WLC for HECF Patches, RH side
3 Complete and Send the Inspection Report Sheet
CONF ALL
E. COMPLIANCE
CONF 001
(1) Classification
MANDATORY: Service Bulletin must be accomplished.
(2) Accomplishment Timescale
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

### Page 14

A350
SERVICE BULLETIN
REV 00 Nov 05/21 A350-57-P076
Page 14
confirm the thresholds given but reference should be made to the AD for confirmation
of the mandated accomplishment timescale.
Accomplishment of this Service Bulletin must be done within 6 years from Entry Into
Service (EIS).
CONF 002
(1) Classification
MANDATORY: Service Bulletin must be accomplished.
(2) Accomplishment Timescale
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.
COMPLIANCE TIME
CONDITIONS ACTION
THRESHOLD GRACE PERIOD
REPETITIVE
INTERVAL
For the aircraft
MSN0124
RH wing and
MSN0211
LH wing
Do the SDI of the
WUC for missing
HECF patch
in accordance
with Ref. T ask
set A350-A-
57-XX-P076-
01ZZZ-93BZ-A
Within 1 year(s)
from the first
issue of this
Service Bulletin
None None
All other aircraft Do the SDI of
the WUC and
WLC for missing
HECF patch
in accordance
with Ref. T ask
set A350-A-
57-XX-P076-
01ZZZ-93BZ-A
Within 6 year(s)
from EIS
None None
If HECF is missing
or the fasteners
(stringer runout
bolts) are not
fully surrounded
by HECF patch
Contact Airbus
for repair
instructions
Before next
flight — findings
should be
repaired before
next flight for
ALL aircraft(s)
None None
If HECF is present
and the fasteners
(stringer runout
bolts) are fully
surrounded by
HECF patch
No further
action with this
Service Bulletin
None None None
All inspections
completed
Complete
and send the
inspection
report sheet in
accordance with
Ref. T ask A350-
None None None

### Page 15

A350
SERVICE BULLETIN
REV 00 Nov 05/21 A350-57-P076
Page 15
COMPLIANCE TIME
CONDITIONS ACTION
THRESHOLD GRACE PERIOD
REPETITIVE
INTERVAL
A-57-XX-P076-
03ZZZ-90AZ-A
CONF ALL
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
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) Repair Instruction to put missing HECF Patches
(a) T ask set A350-A-57-XX-P076-01000-93CA-A Repair Instruction to put missing
HECF Patches
PREPARATION
Job Set-up 0.50 h
PROCEDURE
Repair the WUC and WLC for HECF Patches, LH side 0.50 h
Repair the WUC and WLC for HECF Patches, RH side 2.00 h
PREPARATION FOR TEST
None
TEST
None
CLOSE-UP
Close-up 0.50 h
TOTAL MAN-HOURS 3.50 h
ELAPSED TIME (HOURS) 3.50 h
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) Inspection of WUC and WLC for missing HECF Patches

### Page 16

A350
SERVICE BULLETIN
REV 00 Nov 05/21 A350-57-P076
Page 16
(a) T ask set A350-A-57-XX-P076-01000-93BA-A Inspection of WUC and WLC for
missing HECF Patches
PREPARATION
Job Set-up 0.50 h
PROCEDURE
Do a SDI of the WUC and WLC for HECF Patches, LH side 6.25 h
Do a SDI of the WUC and WLC for HECF Patches, RH side 3.00 h
Complete and Send the Inspection Report Sheet 0.25 h
PREPARATION FOR TEST
None
TEST
None
CLOSE-UP
Close-up 0.50 h
TOTAL MAN-HOURS 10.50 h
ELAPSED TIME (HOURS) 10.50 h
CONF ALL
H. WEIGHT AND BALANCE
Not changed
I. ELECTRICAL LOAD DATA
Not changed
J. REFERENCES
CONF 001
(1) Repair Instruction to put missing HECF Patches
(a) T ask set A350-A-57-XX-P076-01000-93CA-A Repair Instruction to put missing
HECF Patches
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-24-41-XX-00ZZZ-170Z-A
SYSTEM DESCRIPTION (SD)
A350-A-06-2X-XX-01ZZZ-04CZ-A A350-A-06-3X-XX-01ZZZ-04CZ-A
TOP DRAWINGS SHEET(S)
R57V40124 all sheets
R57V40125 all sheets
R57V40126 all sheets
R57V40127 all sheets

### Page 17

A350
SERVICE BULLETIN
REV 00 Nov 05/21 A350-57-P076
Page 17
TOP DRAWINGS SHEET(S)
R57V40128 all sheets
CONF 002
(1) Inspection of WUC and WLC for missing HECF Patches
(a) T ask set A350-A-57-XX-P076-01000-93BA-A Inspection of WUC and WLC for
missing HECF Patches
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)
00.00.00179
MAINTENANCE PROCEDURE (MP)
A350-A-24-41-XX-00ZZZ-170Z-A
NON DESTRUCTIVE TEST (NDT)
A350-A-51-94-43-00ZZZ-355Z-A
SYSTEM DESCRIPTION (SD)
A350-A-06-2X-XX-01ZZZ-04CZ-A A350-A-06-3X-XX-01ZZZ-04CZ-A
CONSUMABLE MATERIAL LIST (CML)
CONF ALL
K. PUBLICATION AFFECTED
None
L. INDUSTRY SUPPORT INFORMATION
CONF 001
For the accomplishment of this Service Bulletin within one year after the initial 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. Claims for this allowance shall be received no
later than 90 days after completion of the last affected aircraft of your fleet fulfilling above
timeframe conditions.
CONF 002
For the accomplishment of this Service Bulletin within 6 years after the initial 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. Claims for this allowance shall be received no
later than 90 days after completion of the last affected aircraft of your fleet fulfilling above
timeframe conditions.
In case of findings, AIRBUS will share the costs of accomplishment of this Service Bulletin by
crediting the operator supplied AIRBUS parts for orders placed within 6 years after the initial
issue date of the Service Bulletin. Claims for this allowance should be received no later than
90 days after completion of the last affected aircraft of your fleet fulfilling above timeframe
conditions.

### Page 18

A350
SERVICE BULLETIN
REV 00 Nov 05/21 A350-57-P076
Page 18
CONF ALL
2. MATERIAL INFORMATION
A. MATERIAL APPLICABILITY
CONF 001
No material for task set A350-A-57-XX-P076-01000-93CA-A Repair Instruction to
put missing HECF Patches
CONF 002
Material for task set A350-A-57-XX-P076-01000-93BA-A Inspection of WUC and
WLC for missing HECF Patches
MATERIAL QTY SEE NOTES
Consumables See SB
CONF ALL
B. TOOLING
No tools
C. CONSUMABLES
CONF 002
Consumables for task set A350-A-57-XX-P076-01000-93BA-A Inspection of WUC
and WLC for missing HECF Patches
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
08BAA9 Non Aqueous Cleaner -General
14SBA1 T extile - Lint free Cotton
CONF 001
No consumables
CONF ALL
D. LIST OF NEW PARTS
No parts
E. LIST OF EXISTING PARTS
No parts

### Page 19

A350
SERVICE BULLETIN
REV 00 Nov 05/21 A350-57-P076
Page 19
3. ACCOMPLISHMENT INSTRUCTIONS
CONF 001
Task set A350-A-57-XX-P076-01000-93CA-A (A350-A-57-XX-P076-01ZZZ-93CZ-A)
Repair Instruction to put missing HECF Patches
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 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: 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.
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.
A. TASK SET ASSOCIATED INFORMATION
Task Manpower

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A350
SERVICE BULLETIN
REV 00 Nov 05/21 A350-57-P076
Page 20
TOTAL MAN-HOURS 3.50 h
ELAPSED TIME (HOURS) 3.50 h
B. PREPARATION
(1) Task A350-A-57-XX-P076-02001-540A-A (A350-A-57-XX-P076-02ZZZ-540Z-A)
Job Set-up
Job Set-Up Information
Manpower/Resources/Skills
Man-hours 0.50 h
Minimum Number of person 1
Elapsed Time 0.50 h
Referenced Information
Manuals/Drawings References/Sheets
INTRO A350-A-00-61-04-11ZZZ-018Z-D
MP A350-A-24-41-XX-00ZZZ-170Z-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 an access platform in position below the applicable zone (Zone 500 or Zone
600).
(c) On the overhead panel, on the ELEC section of panel (Electrical Panel 225VM),
put the warning notices in position to tell persons not to energize the aircraft
electrical circuits.
(d) Put an access platform in position below access door (Door 122AR).
(e) Open access door (Door 122AR).
(f) Put the warning notices in position on EXT PWR panel (Electrical Panel 925VU), to
tell persons not to energize the aircraft electrical circuits.
C. PROCEDURE
(1) Task A350-A-57-XX-P076-01001-600A-A (A350-A-57-XX-P076-01ZZZ-600Z-A)
Repair the WUC and WLC for HECF Patches, LH side
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
500 Work location From Rib 22 to Rib 23
Manpower/Resources/Skills
Man-hours 0.50 h
Minimum Number of person 1
Elapsed Time 0.50 h
Skills Airframe

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A350
SERVICE BULLETIN
REV 00 Nov 05/21 A350-57-P076
Page 21
Referenced Information
Manuals/Drawings References/Sheets
SD A350-A-06-2X-XX-01ZZZ-04CZ-AA350-A-06-3X-XX-01ZZZ-04CZ-A
R57V40124 all sheets
Procedure
Ref. Fig.FA Flow Chart
(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 identification of ribs, refer to Ref. SD A350-A-06-2X-XX-01ZZZ-04CZ-
A.
(b) Identify possible impacted locations:
1 For MSN 0044, WLC - Rib 22 to Rib 23, Front Spar (FS):
a Repair in accordance with repair drawing Ref. R57V40124 all sheets.

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A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-066HB-A-003-01 Fig.FA Sol.AA SHEET 1/1
REV 00 Nov 05/21 A350-57-P076Flow Chart
Page 22
CONF 001
PERFORM CORRESPONDING
REPAIR INSTRUCTION
IDENTIFY ALL THE IMPACTED
LOCATIONS
NOTE:
01 FOR THE COMPLIANCE TIMES, REFER TO THE
ACCOMPLISHMENT TIMESCALE PARA 1.E.(2)
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
01
ICN-A350-A-57XXP076-A-FAPE3-066HB-A-003-01

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A350
SERVICE BULLETIN
REV 00 Nov 05/21 A350-57-P076
Page 23
(2) Task A350-A-57-XX-P076-02001-600A-A (A350-A-57-XX-P076-02ZZZ-600Z-A)
Repair the WUC and WLC for HECF Patches, RH side
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
600 Work location From Rib 1 to Rib 15
Manpower/Resources/Skills
Man-hours 2.00 h
Minimum Number of person 1
Elapsed Time 2.00 h
Skills Airframe
Referenced Information
Manuals/Drawings References/Sheets
SD A350-A-06-2X-XX-01ZZZ-04CZ-AA350-A-06-3X-XX-01ZZZ-04CZ-A
R57V40125 all sheets
R57V40126 all sheets
R57V40127 all sheets
R57V40128 all sheets
Procedure
Ref. Fig.FA Flow Chart
(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 identification of ribs, refer to Ref. SD A350-A-06-2X-XX-01ZZZ-04CZ-
A.
(b) Identify possible impacted locations:
1 For MSN 0060, WUC - Rib 15, Stringer 14:
a Repair in accordance with repair drawing Ref. R57V40125 all sheets.
2 For MSN 0061, WLC - Rib 1 to Rib 3, Rear Spar (RS):
a Repair in accordance with repair drawing Ref. R57V40126 all sheets.
3 For MSN 0292, WLC - Rib 3, Stringer 18:
a Repair in accordance with repair drawing Ref. R57V40127 all sheets.
4 For MSN 0298, WUC - Rib 7, Stringer 1:
a Repair in accordance with repair drawing Ref. R57V40128 all sheets.

### Page 24

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-066HB-A-003-01 Fig.FA Sol.AA SHEET 1/1
REV 00 Nov 05/21 A350-57-P076Flow Chart
Page 24
CONF 001
PERFORM CORRESPONDING
REPAIR INSTRUCTION
IDENTIFY ALL THE IMPACTED
LOCATIONS
NOTE:
01 FOR THE COMPLIANCE TIMES, REFER TO THE
ACCOMPLISHMENT TIMESCALE PARA 1.E.(2)
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
01
ICN-A350-A-57XXP076-A-FAPE3-066HB-A-003-01

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A350
SERVICE BULLETIN
REV 00 Nov 05/21 A350-57-P076
Page 25
D. PREPARATION FOR TEST
None
E. TEST
None
F. CLOSE-UP
(1) Task A350-A-57-XX-P076-02001-740A-A (A350-A-57-XX-P076-02ZZZ-740Z-A)
Close-up
Job Set-Up Information
Manpower/Resources/Skills
Man-hours 0.50 h
Minimum Number of person 1
Elapsed Time 0.50 h
Procedure
(a) Make sure that the work areas are clean and clear of tools and other items of
equipment.
(b) Remove the warning notice(s).
(c) Remove the access platform(s).
(d) Put the aircraft back to its initial configuration.
G. ADMINISTRATIVE
(1) Task A350-A-57-XX-P076-01001-90AA-A (A350-A-57-XX-P076-01ZZZ-90AZ-A)
Administrative
Procedure
Confirm in the applicable aircraft records that you have completed all the work defined
in this Service Bulletin task set as required.

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A350
SERVICE BULLETIN
REV 00 Nov 05/21 A350-57-P076
Page 26
CONF 002
Task set A350-A-57-XX-P076-01000-93BA-A (A350-A-57-XX-P076-01ZZZ-93BZ-A)
Inspection of WUC and WLC for missing HECF Patches
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 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: 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.
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.
A. TASK SET ASSOCIATED INFORMATION
Task Manpower
TOTAL MAN-HOURS 10.50 h

### Page 27

A350
SERVICE BULLETIN
REV 00 Nov 05/21 A350-57-P076
Page 27
ELAPSED TIME (HOURS) 10.50 h
B. PREPARATION
(1) Task A350-A-57-XX-P076-01001-540A-A (A350-A-57-XX-P076-01ZZZ-540Z-A)
Job Set-up
Job Set-Up Information
Manpower/Resources/Skills
Man-hours 0.50 h
Minimum Number of person 1
Elapsed Time 0.50 h
Referenced Information
Manuals/Drawings References/Sheets
INTRO A350-A-00-61-04-11ZZZ-018Z-D
MP A350-A-24-41-XX-00ZZZ-170Z-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 an access platform in position below the applicable zone (Zone 500 or Zone
600).
(c) On the overhead panel, on the ELEC section of panel (Electrical Panel 225VM),
put the warning notices in position to tell persons not to energize the aircraft
electrical circuits.
(d) Put an access platform in position below access door (Door 122AR).
(e) Open access door (Door 122AR).
(f) Put the warning notices in position on EXT PWR panel (Electrical Panel 925VU), to
tell persons not to energize the aircraft electrical circuits.
C. PROCEDURE
(1) Task A350-A-57-XX-P076-01001-346A-A (A350-A-57-XX-P076-01ZZZ-346Z-A)
Do a SDI of the WUC and WLC for HECF Patches, LH side
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
500 Work location From Rib 2 to Rib 27
Manpower/Resources/Skills
Man-hours 6.25 h
Minimum Number of person 1
Elapsed Time 6.25 h
AirframeSkills
Non-Destructive T esting

### Page 28

A350
SERVICE BULLETIN
REV 00 Nov 05/21 A350-57-P076
Page 28
Material necessary to do the job
Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
08BAA9 Non Aqueous Cleaner -General
14SBA1 T extile - Lint free Cotton
Referenced Information
Manuals/Drawings References/Sheets
NDT A350-A-51-94-43-00ZZZ-355Z-A
SD A350-A-06-2X-XX-01ZZZ-04CZ-AA350-A-06-3X-XX-01ZZZ-04CZ-A
CML CONSUMABLE MATERIAL LIST (CML)
Procedure
Ref. Fig.BA Inspection of WUC and WLC for HECF Patches, LH side
Ref. Fig.FA Flow Chart
(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 identification of ribs, refer to Ref. SD A350-A-06-2X-XX-01ZZZ-04CZ-
A.
3 For the specification of Material application codes given in this Service
Bulletin, refer to Ref. CML.
(b) Identify possible impacted locations:
1 For MSN 0211, WUC - UC1, UC2, UC3, UC4, UC5, UC6, UC7, UC8, UC9,
UC10, UC11, UC12, UC13, UC14, UC15 and UC16.
a For the detailed geometrical definition of HECF patch, refer to view C
thru V.
2 For MSNs 0224 and 00251, WLC - LC1.
a For the detailed geometrical definition of HECF patch, refer to view X.
3 For MSN 0407, WLC - LC1, LC2 and LC3.
a For the detailed geometrical definition of HECF patch, refer to view X
thru Z.
4 For MSN 0421, WLC - LC1, LC2, LC3 and LC4.
a For the detailed geometrical definition of HECF patch, refer to view X
thru AA.
(c) Make sure that the inspection area is sufficiently clean to do a satisfactory
inspection of the area.
1 If necessary, clean the inspection area with:
  T extile - Lint free Cotton14SBA1  
made moist with:
  Non Aqueous Cleaner -
General
08BAA9

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A350
SERVICE BULLETIN
REV 00 Nov 05/21 A350-57-P076
Page 29
(d) Do a SDI for the presence of HECF at each identified location within the threshold
given in the PLANNING INFORMATION paragraph E.(2).
Refer to Ref. NDT A350-A-51-94-43-00ZZZ-355Z-A
1 If HECF patch is present and the fasteners (stringer runout bolts) are
fully surrounded by the HECF patch in accordance with the geometrical
definition as shown in view C thru AA:
a No further action in accordance with this Service Bulletin.
2 If HECF is not detected within the defined inspection area or the fasteners
(stringer runout bolts) are not fully surrounded by the HECF patch in
accordance with the geometrical definition as shown in view C thru AA:
a Contact AIRBUS before next flight and follow their instructions.
(e) After completion of all inspections, complete and send the inspection report
sheet in accordance with Ref. T ask A350-A-57-XX-P076-03ZZZ-90AZ-A.

### Page 30

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067AC-A-001-01 Fig.BA Sol.AA SHEET 1/22
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, LH side
Page 30
CONF 002
STGR5
STGR4
STGR2
STGR6
STGR7
STGR8
STGR9
STGR10
STGR11
STGR13
STGR14
STGR16
STGR17
STGR12
STGR15
STGR18
STGR3
RIB22
RIB16
RIB2
RIB1
RIB3
RIB4
RIB5
RIB6
RIB7
RIB8
RIB9
RIB10
RIB11
RIB12
RIB13
RIB14
RIB15
RIB17
RIB18
RIB19 RIB20
RIB21 RIB23
RIB24
RIB25
RIB26
RIB27
RIB28
STGR1
VIEW LOOKING DOWN
B
A
A
F
W
D
Z500
C
D
E
F
G
H
J
K
L
M
P
Q
R
S
T
V
UC1
UC2
UC3
UC4
UC5
UC6
UC7
UC8
UC9
UC10
UC11
UC12
UC13
UC14
UC15
UC16
ICN-A350-A-57XXP076-A-FAPE3-067AC-A-001-01

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A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067AD-A-001-01 Fig.BA Sol.AA SHEET 2/22
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, LH side
Page 31
CONF 002
STGR3
STGR4
STGR5
STGR6
STGR7
STGR8
STGR9
STGR10
STGR11
STGR13
STGR14
STGR16
STGR17
STGR12
STGR15
STGR18
RIB9
RIB10 RIB11
RIB12
RIB13
RIB14
RIB15
RIB1
RIB2
RIB3
RIB4 RIB5
RIB6
RIB7
RIB8
RIB2A
RIB16
RIB17
RIB18
RIB20 RIB21
RIB22
RIB23
RIB24
RIB25
RIB26
RIB27
RIB28
RIB19
STGR2
B
VIEW LOOKING UP
F
W
D
X
Y
Z
A A
LC1
LC4 LC2
LC3
ICN-A350-A-57XXP076-A-FAPE3-067AD-A-001-01

### Page 32

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067AE-A-001-01 Fig.BA Sol.AA SHEET 3/22
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, LH side
Page 32
CONF 002
NOTE:
2 x KEY STRINGER RUN OUT BOLTS SHOWN01
SKIN THICKNESS VALUE02
F
W
D INBDC
°
RIB2
STGR2
LEADING EDGE
PANEL UPPER AFTLEADING EDGE
PANEL 1 INBOARD
67 °
177 mm
(6.968 in)
192 mm
(7.559 in)
192 mm
(7.559 in)
80 mm
(3.149 in)
200 mm
(7.873 in)
EDGE OF
LEADING EDGE
PANEL
VIEW LOOKING DOWN
01
326 mm
(12.835 in)
336 mm
(13.228 in)
113°
10 mm
(0.393 in) 02
ICN-A350-A-57XXP076-A-FAPE3-067AE-A-001-01

### Page 33

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067AF-A-001-01 Fig.BA Sol.AA SHEET 4/22
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, LH side
Page 33
CONF 002
NOTE:
2 x KEY STRINGER RUN OUT BOLTS SHOWN01
SKIN THICKNESS VALUE02
RIB5
STGR1
100°
80°
VIEW LOOKING DOWN
162 mm
(6.377 in)258 mm
(10.157 in)
193 mm
(7.598 in)
12 mm
(0.472 in)
1119 mm
(44.054 in)
178 mm
(7.007 in)
254 mm
(10.000 in)
193 mm
(7.598 in)
02
LEADING EDGE
PANEL 1 OUTBOARD LEADING EDGEPANEL 1 INBOARD
EDGE OF
LEADING EDGE
PANEL
F
W
D INBDD
01
ICN-A350-A-57XXP076-A-FAPE3-067AF-A-001-01

### Page 34

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067AG-A-001-01 Fig.BA Sol.AA SHEET 5/22
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, LH side
Page 34
CONF 002
NOTE:
2 x KEY STRINGER RUN OUT BOLTS SHOWN01
SKIN THICKNESS VALUE02
RIB7
STGR1
101°
79°
200 mm
(7.873 in)
354 mm
(13.936 in)
134 mm
(5.275 in)
305 mm
(12.007 in)
354 mm
(13.936 in)
302 mm
(11.889 in)
14 mm
(0.551 in)
178 mm
(7.007 in)
F
W
D INBD
VIEW LOOKING DOWN
E
EDGE OF
LEADING EDGE
PANEL
LEADING EDGE
PANEL 1 OUTBOARD
01
02
ICN-A350-A-57XXP076-A-FAPE3-067AG-A-001-01

### Page 35

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067AH-A-001-01 Fig.BA Sol.AA SHEET 6/22
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, LH side
Page 35
CONF 002
NOTE:
2 x KEY STRINGER RUN OUT BOLTS SHOWN01
SKIN THICKNESS VALUE02
STGR2
94°
RIB12
86°
1077 mm
(42.401 in)
193 mm
(7.598 in)
15 mm
(0.560 in)
200 mm
(7.873 in)
187 mm
(7.362 in)
193 mm
(7.598 in)
173 mm
(6.811 in)
201 mm
(7.913 in)
F
W
D INBD
VIEW LOOKING DOWN
F
02
01
LEADING EDGE
PANEL 2 UPPER
EDGE OF
LEADING EDGE
PANEL
ICN-A350-A-57XXP076-A-FAPE3-067AH-A-001-01

### Page 36

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067AI-A-001-01 Fig.BA Sol.AA SHEET 7/22
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, LH side
Page 36
CONF 002
NOTE:
SKIN THICKNESS VALUE02
8 x KEY STRINGER RUN OUT BOLTS SHOWN03
STGR3
RIB15
RIB16
94°
86°
193 mm
(7.598 in)
1373 mm
(54.054 in)
132 mm
(5.196 in)
14 mm
(0.551 in)
761 mm
(29.960 in)
763 mm
(30.039 in)
F
W
D INBD
VIEW LOOKING DOWN
G
LEADING EDGE
PANEL 3 UPPER
EDGE OF
LEADING EDGE
PANEL
03
02
187 mm
(7.362 in)
193 mm
(7.598 in)
ICN-A350-A-57XXP076-A-FAPE3-067AI-A-001-01

### Page 37

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067AJ-A-001-01 Fig.BA Sol.AA SHEET 8/22
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, LH side
Page 37
CONF 002
NOTE:
SKIN THICKNESS VALUE02
6 x KEY STRINGER RUN OUT BOLTS SHOWN04
RIB19
83°
STGR4
193 mm
(7.598 in)
1729 mm
(68.070 in)
193 mm
(7.598 in)
97°
478 mm
(18.818 in)
171 mm
(6.732 in)
476 mm
(18.740 in)
136 mm
(5.354 in)
14 mm
(0.551 in)
F
W
D INBD
VIEW LOOKING DOWN
H
02
04
EDGE OF
LEADING EDGE
PANEL
LEADING EDGE
PANEL 4 UPPER
ICN-A350-A-57XXP076-A-FAPE3-067AJ-A-001-01

### Page 38

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067AK-A-001-01 Fig.BA Sol.AA SHEET 9/22
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, LH side
Page 38
CONF 002
NOTE:
SKIN THICKNESS VALUE02
6 x KEY STRINGER RUN OUT BOLTS SHOWN04
STGR5
RIB23
94°
86°
691 mm
(27.204 in)
155 mm
(6.102 in)
193 mm
(7.598 in)
693 mm
(27.283 in)
104 mm
(4.094 in)
1543 mm
(60.747 in)
193 mm
(7.598 in)
14 mm
F
W
D INBD
VIEW LOOKING DOWN
J
02(0.551 in)
04
EDGE OF
LEADING EDGE
PANEL
LEADING EDGE
PANEL 5 UPPER
ICN-A350-A-57XXP076-A-FAPE3-067AK-A-001-01

### Page 39

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067AL-A-001-01 Fig.BA Sol.AA SHEET 10/22
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, LH side
Page 39
CONF 002
NOTE:
SKIN THICKNESS VALUE02
6 x KEY STRINGER RUN OUT BOLTS SHOWN04
STGR6
RIB27
94°
86°
13 mm
498 mm
(19.606 in)
151 mm
(5.944 in)
193 mm
(7.598 in)
500 mm
(19.684 in)
193 mm
(7.598 in)
1730 mm
(68.110 in)
114 mm
(4.488 in) 02 (0.511 in)
04
LEADING EDGE
PANEL 6 UPPER
EDGE OF
LEADING EDGE
PANEL
F
W
D INBD
VIEW LOOKING DOWN
K
ICN-A350-A-57XXP076-A-FAPE3-067AL-A-001-01

### Page 40

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067AM-A-001-01 Fig.BA Sol.AA SHEET 11/22
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, LH side
Page 40
CONF 002
STGR11
F
W
D INBD
VIEW LOOKING DOWN
RIB21
83 °
97 °
04
TRAILING EDGE
PANEL 11 UPPER
TRAILING EDGE
PANEL
L
EDGE OF
330 mm
(12.992 in)
268 mm
(10.551 in)
296 mm
(11.653 in)
294 mm
(11.574 in)
268 mm
(10.551 in)
NOTE:
SKIN THICKNESS VALUE02
6 x KEY STRINGER RUN OUT BOLTS SHOWN04
17 mm
(0.669 in)02
160 mm
(6.299 in)
198 mm
(7.795 in)
ICN-A350-A-57XXP076-A-FAPE3-067AM-A-001-01

### Page 41

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067AN-A-001-01 Fig.BA Sol.AA SHEET 12/22
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, LH side
Page 41
CONF 002
95°
85°
RIB19
TRAILING EDGE
PANEL 10 UPPER
59 mm
(2.322 in)
10 mm
(0.393 in)
49 mm
(1.929 in)
60 mm
(2.362 in)
109 mm
(4.291 in)
RIB19
0220 - 21 mm(0.789 - 0.826 in)
2 mm
(0.079 in)
STGR12
STGR12FW
D INBD
VIEW LOOKING DOWN
M
F
W
D INBD
VIEW LOOKING DOWN
N
N
129 mm
(5.078 in)
TRAILING EDGE
PANEL
EDGE OF
133°
137°
200 mm
(7.874 in) 155 mm
(6.102 in)
201 mm
(7.913 in)
440 mm
(17.323 in)
449 mm
(17.677 in)
01
NOTE:
2 x KEY STRINGER RUN OUT BOLTS SHOWN01
SKIN THICKNESS VALUE02
02 17 - 20 mm(0.669 - 0.787 in)
450 mm
(17.716 in)
ICN-A350-A-57XXP076-A-FAPE3-067AN-A-001-01

### Page 42

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067AO-A-001-01 Fig.BA Sol.AA SHEET 13/22
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, LH side
Page 42
CONF 002
STGR13
RIB17
97°
83°
191 mm
(7.519 in)
01
TRAILING EDGE
PANEL 8 UPPER
F
W
D INBD
VIEW LOOKING DOWN
TRAILING EDGE
PANEL
EDGE OF
278 mm
(10.944 in)193 mm
(7.598 in)
278 mm
(10.944 in)
157 mm
(6.18 in)
182 mm
(7.165 in)
P
115 mm
(4.527 in)
NOTE:
2 x KEY STRINGER RUN OUT BOLTS SHOWN01
SKIN THICKNESS VALUE02
16 mm02 (0.629 in)
ICN-A350-A-57XXP076-A-FAPE3-067AO-A-001-01

### Page 43

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067AP-A-001-01 Fig.BA Sol.AA SHEET 14/22
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, LH side
Page 43
CONF 002
STGR14
RIB15
278 mm
(10.944 in)
97°
83°
143 mm
(5.629 in)
TRAILING EDGE
PANEL 7 UPPER
F
W
D INBD
VIEW LOOKING DOWN
251 mm
(9.881 in)
01
TRAILING EDGE
PANEL 8 UPPER TRAILING EDGEPANEL
EDGE OF
236 mm
(9.291 in)
203 mm
(7.992 in)
253 mm
(9.960 in)
Q
278 mm
(10.944 in)
NOTE:
2 x KEY STRINGER RUN OUT BOLTS SHOWN01
SKIN THICKNESS VALUE02
17 mm02 (0.669 in)
ICN-A350-A-57XXP076-A-FAPE3-067AP-A-001-01

### Page 44

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067AQ-A-001-01 Fig.BA Sol.AA SHEET 15/22
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, LH side
Page 44
CONF 002
97°
83°
201 mm
(7.913 in)
01
RIB13
STGR15
F
W
D INBD
VIEW LOOKING DOWN
TRAILING EDGE
PANEL 7 UPPER
R
203 mm
(7.992 in)
286 mm
(11.259 in)
34 mm
(1.338 in)
206 mm
(8.110 in)
285 mm
(11.220 in)
18 mm02
233 mm
(9.173 in)
TRAILING EDGE
PANEL
EDGE OF
(0.708 in)
NOTE:
2 x KEY STRINGER RUN OUT BOLTS SHOWN01
SKIN THICKNESS VALUE02 ICN-A350-A-57XXP076-A-FAPE3-067AQ-A-001-01

### Page 45

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067AR-A-001-01 Fig.BA Sol.AA SHEET 16/22
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, LH side
Page 45
CONF 002
RIB11
RIB10
STGR16
656 mm
(25.826 in)
158 mm
(6.220 in)
98°
82°
03
TRAILING EDGE
PANEL 5 UPPERF
W
D INBD
VIEW LOOKING DOWN
249 mm
(9.803 in)
663 mm
(26.102 in)
247 mm
(9.724 in)
TRAILING EDGE
PANEL
EDGE OF
S
287 mm
(11.299 in)
NOTE:
SKIN THICKNESS VALUE02
8 x KEY STRINGER RUN OUT BOLTS SHOWN03
287 mm
(11.299 in)
15 mm02 (0.590 in)
ICN-A350-A-57XXP076-A-FAPE3-067AR-A-001-01

### Page 46

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067AS-A-001-01 Fig.BA Sol.AA SHEET 17/22
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, LH side
Page 46
CONF 002
71 mm
(2.795 in)
21 mm
(0.826 in)
28 mm
(1.102 in)
78 mm
(3.070 in)
138°
RIB8
F
W
D INBD
VIEW LOOKING DOWN
STGR17
RIB8
136 mm
(5.354 in)
95°
85°
F
W
D INBD
VIEW LOOKING DOWN
197 mm
(7.755 in)
DATUM LINE CREATED
THROUGH BOLT LOCATIONS
DATUM LINE
CREATED THROUGH
BOLT LOCATIONS
170 mm
(6.692 in)
60 mm
(2.362 in)
201 mm
(7.913 in)
49 mm
(1.929 in)
STGR17
T
U
U
01
NOTE:
2 x KEY STRINGER RUN OUT BOLTS SHOWN01
SKIN THICKNESS VALUE02
202 mm
(7.952 in)
130 mm
(5.118 in)
02 17 - 19 mm(0.669 - 0.748 in)
134°
18 - 20 mm02 (0.708 - 0.787 in)
2 mm
(0.079 in)
ICN-A350-A-57XXP076-A-FAPE3-067AS-A-001-01

### Page 47

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067AT-A-001-01 Fig.BA Sol.AA SHEET 18/22
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, LH side
Page 47
CONF 002
92°
RIB6 STGR18
01
F
W
D INBD
VIEW LOOKING DOWN
TRAILING EDGE
PANEL 3 UPPER
88°
105 mm
(4.134 in)
255 mm
(10.039 in)
251 mm
(9.881 in)
165 mm
(6.496 in)
DATUM LINE
CREATED THROUGH
BOLT LOCATIONS
139 mm
(5.472 in)
130 mm
(5.118 in)
DATUM LINE
CREATED THROUGH
BOLT LOCATIONS
139 mm
(5.472 in)
RIB6
STGR18
48 mm
(1.890 in)
76 mm
(2.992 in)
26 mm
(1.024 in)
23 mm
(0.906 in)
18 mm
(0.709 in)02
F
W
D INBD
VIEW LOOKING DOWN
2 mm
(0.079 in)
137°
73 mm
(2.874 in)
V
W
W
NOTE:
2 x KEY STRINGER RUN OUT BOLTS SHOWN01
SKIN THICKNESS VALUE02
02 18 mm(0.70 in)
135°
ICN-A350-A-57XXP076-A-FAPE3-067AT-A-001-01

### Page 48

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067AU-A-001-01 Fig.BA Sol.AA SHEET 19/22
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, LH side
Page 48
CONF 002
INBD
VIEW LOOKING UP
LEADING EDGE
PANEL 1 INBD LOWER
STGR2
RIB3
90°
90°
47 mm
(1.850 in)
F
W
D
01
225 mm
(8.858 in)
225 mm
(8.858 in)
150 mm
(5.905 in)
350 mm
(13.779 in)
LEADING EDGE
PANEL
EDGE OF
150 mm
(5.905 in)
X
NOTE:
2 x KEY STRINGER RUN OUT BOLTS SHOWN01
SKIN THICKNESS VALUE02
02 10 mm(0.393 in)
ICN-A350-A-57XXP076-A-FAPE3-067AU-A-001-01

### Page 49

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067AV-A-001-01 Fig.BA Sol.AA SHEET 20/22
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, LH side
Page 49
CONF 002
INBD
VIEW LOOKING UP
STGR3
86°
12 mm
F
W
D
02
LEADING EDGE
PANEL 3 INBD LOWER
94°
RIB15
05
132 mm
(5.196 in)
302 mm
(11.889 in)
200 mm
(7.873 in)
301 mm
(11.850 in)
178 mm
(7.007 in)
LEADING EDGE
PANEL
EDGE OF
223 mm
(8.779 in)
223 mm
(8.779 in)
(0.472 in)
NOTE:
SKIN THICKNESS VALUE02
4 x KEY STRINGER RUN OUT BOLTS SHOWN05
Y
ICN-A350-A-57XXP076-A-FAPE3-067AV-A-001-01

### Page 50

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067AW-A-001-01 Fig.BA Sol.AA SHEET 21/22
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, LH side
Page 50
CONF 002
INBD
VIEW LOOKING UP
F
W
D
LEADING EDGE
PANEL 4 INBD LOWER
83°
12 mm 02
14 mm
(0.551 in)
05
RIB19
STGR4
97°
LEADING EDGE
PANEL
EDGE OF
115 mm
(4.527 in) 300 mm
(11.810 in)
224 mm
(8.818 in)302 mm
(11.889 in)
224 mm
(8.818 in)
(0.472 in)
Z
NOTE:
SKIN THICKNESS VALUE02
4 x KEY STRINGER RUN OUT BOLTS SHOWN05
224 mm
(8.818 in)
ICN-A350-A-57XXP076-A-FAPE3-067AW-A-001-01

### Page 51

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067AX-A-001-01 Fig.BA Sol.AA SHEET 22/22
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, LH side
Page 51
CONF 002
90°
90°
452 mm
(17.795 in)
STGR16
INBD
VIEW LOOKING UP
F
W
D
LEADING EDGE
PANEL 6 LOWER
452 mm
(17.795 in)
DATUM LINE CREATED
THROUGH BOLT LOCATIONS
196 mm
(7.716 in)
230 mm
(9.055 in)
287 mm
(11.299 in)
230 mm
(9.055 in) 323 mm
(12.716 in)
DATUM LINE CREATED
THROUGH BOLT LOCATIONS
RIB8
01
A A
NOTE:
2 x KEY STRINGER RUN OUT BOLTS SHOWN01
SKIN THICKNESS VALUE02
02 11 - 14 mm(0.433 - 0.551 in)
ICN-A350-A-57XXP076-A-FAPE3-067AX-A-001-01

### Page 52

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-066HC-A-001-01 Fig.FA Sol.AB SHEET 1/1
REV 00 Nov 05/21 A350-57-P076Flow Chart
Page 52
CONF 002
IDENTIFY ALL THE POSSIBLE
IMPACTED LOCATIONS
PERFORM A SPECIAL DETAILED
INSPECTION (SDI) AT EACH
CONTACT AIRBUS FOR
REPAIR INSTRUCTIONS
NO
YES
SEND INSPECTION
REPORT TO AIRBUS
NO FURTHER
ACTION WITH THIS
SERVICE BULLETIN
NOTE:
01 FOR THE COMPLIANCE TIMES, REFER TO THE
ACCOMPLISHMENT TIMESCALE PARA 1.E.(2)
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
01
IDENTIFIED LOCATION
EXPANDED  COPPER
FOIL (HECF) MISSING OR THE
FASTERNERS (STRINGER RUNOUT
BOLTS) ARE NOT FULLY 
SURROUNDED BY
IS HEAVY
HECF PATCH?
01
01
01
ICN-A350-A-57XXP076-A-FAPE3-066HC-A-001-01

### Page 53

A350
SERVICE BULLETIN
REV 00 Nov 05/21 A350-57-P076
Page 53
(2) Task A350-A-57-XX-P076-02001-346A-A (A350-A-57-XX-P076-02ZZZ-346Z-A)
Do a SDI of the WUC and WLC for HECF Patches, RH side
Job Set-Up Information
Working Area
Impacted Zone Access / Work Location
600 Work location From Rib 2 to Rib 27
Manpower/Resources/Skills
Man-hours 3.00 h
Minimum Number of person 1
Elapsed Time 3.00 h
AirframeSkills
Non-Destructive T esting
Material necessary to do the job
Consumables
ITEM REFERENCE CML DESCRIPTION DRAWING SEE NOTES
08BAA9 Non Aqueous Cleaner -General
14SBA1 T extile - Lint free Cotton
Referenced Information
Manuals/Drawings References/Sheets
NDT A350-A-51-94-43-00ZZZ-355Z-A
SD A350-A-06-2X-XX-01ZZZ-04CZ-AA350-A-06-3X-XX-01ZZZ-04CZ-A
CML CONSUMABLE MATERIAL LIST (CML)
Procedure
Ref. Fig.BB Inspection of WUC and WLC for HECF Patches, RH side
Ref. Fig.FA Flow Chart
(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 identification of ribs, refer to Ref. SD A350-A-06-2X-XX-01ZZZ-04CZ-
A.
3 For the specification of Material application codes given in this Service
Bulletin, refer to Ref. CML.
(b) Identify possible impacted locations:
1 For MSN 0124, WUC - UC1, UC2, UC3, UC4, UC5, UC6, UC7 and UC8.
a For the detailed geometrical definition of HECF patch, refer to view C
thru K.
2 For MSN 0237, WLC - LC1.
a For the detailed geometrical definition of HECF patch, refer to view L.
3 For MSN 0385, WLC - LC1, LC2 and LC3.

### Page 54

A350
SERVICE BULLETIN
REV 00 Nov 05/21 A350-57-P076
Page 54
a For the detailed geometrical definition of HECF patch, refer to view L
thru N.
(c) Make sure that the inspection area is sufficiently clean to do a satisfactory
inspection of the area.
1 If necessary, clean the inspection area with:
  T extile - Lint free Cotton14SBA1  
made moist with:
  Non Aqueous Cleaner -
General
08BAA9  
(d) Do a SDI for the presence of HECF at each identified location within the threshold
given in the PLANNING INFORMATION paragraph E.(2).
Refer to Ref. NDT A350-A-51-94-43-00ZZZ-355Z-A
1 If HECF patch is present and the fasteners (stringer runout bolts) are
fully surrounded by the HECF patch in accordance with the geometrical
definition as shown in view C thru N:
a No further action in accordance with this Service Bulletin.
2 If HECF patch is not detected within the defined inspection area or the
fasteners (stringer runout bolts) are not fully surrounded by the HECF
patch in accordance with the geometrical definition as shown in view C
thru N:
a Contact AIRBUS before next flight and follow their instructions.
(e) After completion of all inspections, complete and send the inspection report
sheet in accordance with Ref. T ask A350-A-57-XX-P076-03ZZZ-90AZ-A.

### Page 55

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067E0-A-001-01 Fig.BB Sol.AA SHEET 1/13
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, RH side
Page 55
CONF 002
A
B
Z600
STGR5
STGR4
STGR2
STGR6
STGR7
STGR8
STGR9
STGR10
STGR11
STGR13
STGR14
STGR16
STGR17
STGR12
STGR15
STGR18
STGR3
RIB14
RIB28
RIB27
RIB26
RIB25
RIB24
RIB23
RIB22
RIB21
RIB20 RIB19
RIB18
RIB17
RIB16
RIB15
RIB13
RIB12
RIB11
RIB10
RIB9
RIB8
RIB7
RIB6
RIB5
RIB4
STGR1
RIB3 RIB2
RIB1
VIEW LOOKING DOWN
F
W
D A
K
J
H
G
F
E
D
C
UC1
UC2
UC3
UC4
UC5
UC6
UC7
UC8
ICN-A350-A-57XXP076-A-FAPE3-067E0-A-001-01

### Page 56

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067E1-A-001-01 Fig.BB Sol.AA SHEET 2/13
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, RH side
Page 56
CONF 002
STGR3
STGR4
STGR5
STGR6
STGR7
STGR8
STGR9
STGR10
STGR11
STGR13
STGR14
STGR16
STGR17
STGR12
STGR15
STGR18
RIB9
RIB10RIB11
RIB12
RIB13
RIB14
RIB15
RIB1
RIB2
RIB3
RIB4RIB5
RIB6
RIB7
RIB8
RIB2A
RIB16
RIB17
RIB18
RIB20RIB21
RIB22
RIB23
RIB24
RIB25
RIB26
RIB27
RIB28
RIB19
STGR2
VIEW LOOKING UP
LC1
LC2
LC3
B
F
W
D
N
M
L
ICN-A350-A-57XXP076-A-FAPE3-067E1-A-001-01

### Page 57

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067E2-A-001-01 Fig.BB Sol.AA SHEET 3/13
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, RH side
Page 57
CONF 002
NOTE:
2 x KEY STRINGER RUN OUT BOLTS SHOWN01
SKIN THICKNESS VALUE02
°
RIB2
STGR2
LEADING EDGE
PANEL UPPER AFT LEADING EDGE
PANEL 1 INBOARD
67°
113°
EDGE OF
LEADING EDGE
PANEL
326 mm
(12.835 in)
VIEW LOOKING DOWN
INBD
F
W
D
01
C
80 mm
(3.150 in)
192 mm
(7.559 in)
192 mm
(7.559 in)
02 10 mm(0.394 in)
177 mm
(6.969 in)
336 mm
(13.228 in)
200 mm
(7.874 in)
ICN-A350-A-57XXP076-A-FAPE3-067E2-A-001-01

### Page 58

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067E3-A-001-01 Fig.BB Sol.AA SHEET 4/13
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, RH side
Page 58
CONF 002
NOTE:
2 x KEY STRINGER RUN OUT BOLTS SHOWN01
SKIN THICKNESS VALUE02
RIB5
STGR1
LEADING EDGE
PANEL 1 INBOARD
LEADING EDGE
PANEL 1 OUTBOARD
100°
80°
EDGE OF
LEADING EDGE
PANEL
VIEW LOOKING DOWN
INBD
F
W
DD
162 mm
(6.378 in) 258 mm
(10.158 in)
193 mm
(7.598 in)
12 mm02 (0.472 in)
1119 mm
(44.055 in)
178 mm
(7.008 in)
254 mm
(10.000 in)
193 mm
(7.598 in)
01
ICN-A350-A-57XXP076-A-FAPE3-067E3-A-001-01

### Page 59

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067E4-A-001-01 Fig.BB Sol.AA SHEET 5/13
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, RH side
Page 59
CONF 002
NOTE:
2 x KEY STRINGER RUN OUT BOLTS SHOWN01
SKIN THICKNESS VALUE02
RIB7
STGR1
LEADING EDGE
PANEL 1 OUTBOARD
VIEW LOOKING DOWN
101°
79°
EDGE OF
LEADING EDGE
PANEL
01
INBD
F
W
DE
200 mm
(7.874 in)
354 mm
(13.937 in)
134 mm
(5.276 in)
305 mm
(12.008 in)
354 mm
(13.937 in)
302 mm
(11.890 in)
14 mm 02(0.551 in)
178 mm
(7.008 in)
ICN-A350-A-57XXP076-A-FAPE3-067E4-A-001-01

### Page 60

A350
SERVICE BULLETIN
Figure ICN-A350-A-57XXP076-A-FAPE3-067E5-A-001-01 Fig.BB Sol.AA SHEET 6/13
REV 00 Nov 05/21 A350-57-P076Inspection of WUC and WLC for HECF Patches, RH side
Page 60
CONF 002
NOTE:
2 x KEY STRINGER RUN OUT BOLTS SHOWN01
SKIN THICKNESS VALUE02
STGR2
94°
LEADING EDGE
PANEL 2 UPPER
RIB12
VIEW LOOKING DOWN
EDGE OF
LEADING EDGE
PANEL
86°
01
INBD
F
W
DF
1077 mm
(42.401 in)
193 mm
(7.598 in)
15 mm
(0.591 in)02
200 mm
(7.873 in)
187 mm
(7.362 in)
193 mm
(7.598 in)
173 mm
(6.811 in)
201 mm
(7.913 in)
ICN-A350-A-57XXP076-A-FAPE3-067E5-A-001-01

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