AS 350
B3
Chapter 04
AIRWORTHINESS LIMITATIONS SECTION (ALS)
Airbus Helicopters
Direction Technique Support
Aéroport International Marseille Provence 13725 Marignane Cedex FRANCE
Contact: contact.msm.ah@airbus.com
Issue date
:
2014.05.29
Revision 015
:
2023.05.22
ALS
RECORD OF REVISIONS
ALS
APPROVAL
1
EASA - Approval
The Airworthiness Limitations section is approved and variations must also be approved by EASA.
These ALS revisions are the compilation of the EASA approved changes listed in the table, with non further
technical changes:
Revision
LOEDU Identification
Approval Date
No EASA
REV 000
2001.04.26
DGAC : 2001.08.21
–
REV 001
2002.03.13
DGAC: 2002.10.14
–
REV 002
2003.04.24
DGAC: 2003.09.25
–
REV 003
2004.02.05
EASA: 2004.05.19
2004-5289
REV 004
2005.01.21
EASA: 2005.04.20
2005-3655
REV 005
2005.10.10
EASA: 2006.02.13
R.C.01521
REV 006
2006.06.19
EASA: 2006.12.21
R.C.01956
REV 007
2006.12.20
EASA: 2007.01.10
R.C.01605
REV 008
2007.01.18
EASA: 2007.02.08
R.C.01513 / R.C.02014 / R.C.02098
REV 009
2007.04.05
EASA: 2007.07.05
R.C.02455
REV 010
2007.06.29
EASA: 2007.11.27
R.C.02705
REV 011
2007.12.24
EASA: 2008.03.20
R.C.02819
REV 012
2008.09.26
EASA: 2008.12.19
R.C.03268
REV 013
2009.07.17
EASA: 2009.09.03
10027071
REV 014
2009.10.15
EASA: 2009.11.16
10027905
New REV 000
2010.09.29
EASA: 2010.12.20
10033145
REV 001
2011.05.26
EASA: 2011.09.05
10036377
REV 002
2011.10.20
EASA: 2012.08.30
10041214
REV 003
2012.09.06
EASA: 2012.10.10
10041719
REV 004
2012.12.06
EASA : 2013.01.28
10043432
REV 005
2014.05.29
EASA : 2014.08.27
10050323
AS 350 B3
2023.05.22 EASA Approved
APPROVAL
Page 1
ALS
Revision
REV 006
REV 007
REV 008
LOEDU
Identification
2015.06.11
2015.11.19
2016.07.11
AS 350 B3
2023.05.22 EASA Approved
TFSAC number
Change Approval Date
No. EASA
12.350.0013.a
24/06/2014
10049615
13.350.0006.a
27/06/2014
10049671
13.350.0009.b
27/06/2014
10049669
13.350.0011.a
13/03/2014
10048479
14.350.0009.a
18/12/2014
10051696
14.350.0012.a
19/01/2015
10051936
14.350.0013.a
22/05/2015
10053408
13.350.0014.a
04/05/2015
10053177
14.350.0002.a
04/05/2015
10053199
14.350.0007.a
27/07/2015
10054218
14.350.0008.a
04/05/2015
10053179
14.350.0010.a
09/06/2015
10053588
14.350.0011.a
04/05/2015
10053197
15.350.0002.a
27/05/2015
10053416
15.350.0003.a
27/05/2015
10053417
15.350.0006.a
29/10/2015
10055300
12.350.0015.a
21/02/2013
10043742
14.350.0003.a
01/02/2016
10056556
15.350.0008.a
02/11/2015
10055333
15.350.0009.a
19/11/2015
DOA N°EASA.21J.700
16.350.0002.a
30/06/2016
10058603
APPROVAL
Page 2
ALS
Revision
REV 009
REV 010
LOEDU
Identification
TFSAC number
Change Approval Date
APPROVAL No
15.350.0004.a
07/06/2016
LH/2015/103 (EASA
100058334)
15.350.0007.a
05/02/2016
LH/2015/096 (EASA
10056628)
16.350.0003.a
17/02/2017
LH/2016/133 (EASA
10061065)
17.350.0001.a
03/08/2017
17.350.0003.a
15/06/2017
2016.11.03
2017.12.04
LH/2016/126 (EASA
10062808)
LH/2017/011 (EASA 21J.700)
REV 011
REV 012
REV 013
2018.04.16
2020.10.12
17.350.0002a
03/05/2017
LH/2017/082 (EASA 21J.700)
17.350.0005.a
03/10/2017
LH/2017/132 (EASA 21J.700)
17.350.0008.a
07/11/2017
LH/2017/142 (EASA 21J.700)
16.350.0006.a
20/11/2016
LH/2015/102 (EASA
10060185)
20.350.0004.a
22/01/2021
20.350.0005.a
22/10/2020
LH/2020/148 (EASA
10075446)
2021.04.05
AS 350 B3
2023.05.22 EASA Approved
LH/2019/108 (EASA
10074634)
APPROVAL
Page 3
ALS
Revision
REV 014
LOEDU
Identification
TFSAC number
Change Approval Date
22.350.0002.a
16/02/2022
22.350.0010.a
02/11/2022
APPROVAL No
LH/2022/027 (EASA 21J.700)
2022.12.05
LH/2021/171 (EASA
10080491)
LH/2022/111 (EASA
10081459)
REV 015
2023.05.22
22.350.0011.a
14/03/2023
22.350.0012.a
14/03/2023
22.350.0013.a
11/01/2023
23.350.0003.a
10/03/2023
LH/2022/111 (EASA
10081459)
LH/2022/059 (EASA
10081033)
LH/2022/099 (EASA
10081403)
23.350.0005.a
25/04/2023
LH/2023/063 (EASA 21J.700)
The technical content of these revisions are approved under DOA N°EASA.21J.700 authority. This approval
means that the revisions have been prepared with already EASA approved data and minor changes approved
under DOA N°EASA.21J.700. The revisions are issued under DOA procedure.
The list of chapter 04 effective pages given in the "LOEDU" which is identified by 2023.05.22.
The "LOEDU" identification does not correspond to the approval date, it is a documentation handling code
provided at the bottom of all pages.
End of the Document Unit
AS 350 B3
2023.05.22 EASA Approved
APPROVAL
Page 4
ALS
LOEDU
1 Update
Refer to the "Update of the ALS" Document Unit
2 "Type" Column Code
N-New, to be inserted
R-Revised, to be replaced
D-To be removed from the manual
- (No code) Unchanged with respect to the previous issue
D.U.
Type Date
D.U.
Type Date
2014.05.29
2017.12.04
TITLE
N
2023.05.22
UPDATE OF THE ALS
APPROVAL
N
2023.05.22
LOEDU
N
2023.05.22
BREAKDOWN OF THE
ALS
TABLE OF CONTENTS
N
2023.05.22
USE OF THE ALS
-
2015.11.19
HIGHLIGHTS OF THE
REVISION
N
2023.05.22
SB INCORPORATED
R
2023.05.22
04-10-00
R
2023.05.22
GLOSSARY
-
2015.11.19
04-20-00
R
2023.05.22
STRUCTURE OF THE
ALS
-
2014.05.29
End of the Document Unit
AS 350 B3
2023.05.22 EASA Approved
LOEDU
Page 1
ALS
TABLE OF CONTENTS
TITLE
HIGHLIGHTS OF THE REVISION
1 GENERAL
2 OUTLINE OF THE REVISION
3 DETAILED DESCRIPTION
3.1 SB INCORPORATED
3.2 Section 04.10.00
3.3 Section 04.20.00
GLOSSARY
STRUCTURE OF THE ALS
1 GENERAL STRUCTURE OF THE ALS
2 BREAKDOWN OF THE ALS
2.1 Identification of the DUs
2.2 Task codes
2.3 List Of Effective Document Units (LOEDU)
3 CLASSIFICATION OF INFORMATION
UPDATE OF THE ALS
1 REVISION OF THE ALS
2 UPDATE OF THE ALS
2.1 Update procedure
2.2 Identification of the modifications
3 EFFECTIVITY
BREAKDOWN OF THE ALS
1 PURPOSE OF THE ALS
2 CHANGES TO THE ALS
3 AIRWORTHINESS LIMITATIONS SPECIFICATION
3.1 Components subject to a Service Life Limit (SLL)
3.2 Components subject to an airworthiness inspection
4 EFFECTIVITY - RESPONSIBILITY
USE OF THE ALS
1 COMPLIANCE WITH THE AIRWORTHINESS LIMITATIONS SECTION
2 OCCURRENCE REPORTING
AS 350 B3
2023.05.22 EASA Approved
TABLE OF CONTENTS
Page 1
ALS
TITLE
2.1 Reporting to the airworthiness authorities
2.2 Reporting to the helicopter manufacturer
3 IN-SERVICE MONITORING OF COMPONENTS
4 COMPONENT PART NUMBERS
4.1 Definition
4.2 Part Number followed by a suffix
4.3 Applicability of the limits
4.4 Effectivity
5 EXPRESSION OF THE LIMITS
5.1 Flight Hours
5.2 Calendar time
5.2.1 Initial aging date for a component
5.3 Cycles
5.3.1 Cycles with large centrifugal load variation
5.3.2 Cycle with large torque variation
5.4 Number of operations for certain components
5.5 Infinite limit
5.6 Airworthiness limitation units – Description and counting
5.6.1 Airworthiness limitation expressed in Flight Hours
5.6.2 Airworthiness limitation expressed in Torque Cycles
5.6.3 Airworthiness limitations expressed in Flight Hours and Torque Cycles
5.7 Removal of life-limited components
5.8 Provisional limitations
5.9 Version identification of components
5.9.1 Principle
5.9.2 Marking the version
5.10 Periodic and perform once airworthiness inspections
5.11 Performance interval
5.12 Specific and severe atmospheric operating conditions
5.13 Airworthiness limitations value
5.13.1 Definition of the margin
5.13.2 Application of the margin
AS 350 B3
2023.05.22 EASA Approved
TABLE OF CONTENTS
Page 2
ALS
TITLE
5.13.3 Specification of the margin
5.13.4 Example of how the margin is used
6 TRANSFER OF A LIFE-LIMITED COMPONENT INCLUDED IN SECTION 04-10-00 FROM ONE
HELICOPTER VERSION TO ANOTHER HELICOPTER VERSION
6.1 Ecureuil family helicopter versions concerned by the transfer:
6.2 Authorization to transfer
6.3 Application rules
6.4 Calculation rules
6.4.1 Information required for the calculations
6.4.2 Calculating ty
6.4.3 Calculating T
6.5 Counting
6.6 Recording
7 TRANSFER OF A COMPONENT SUBJECT TO AN AIRWORTHINESS INSPECTION INCLUDED IN
SECTION 04-20-00 FROM ONE HELICOPTER VERSION TO ANOTHER HELICOPTER VERSION
7.1 Ecureuil family helicopter versions concerned by the transfer:
7.2 Authorization to transfer
7.3 Transfer rules for components subject to an airworthiness inspection
8 MAINTENANCE CODE (MC)
9 CONTENT OF A TASK
SB INCORPORATED
End of the Document Unit
AS 350 B3
2023.05.22 EASA Approved
TABLE OF CONTENTS
Page 3
ALS
HIGHLIGHTS OF THE REVISION
1
GENERAL
-
Check that the content of the sections is in accordance with the List Of Effective Document Units
(LOEDU).
Return the acknowledgment card.
2
OUTLINE OF THE REVISION
The revision is codified as follows:
3
Revision 015 : 2023.05.22
DETAILED DESCRIPTION
3.1
-
3.2
SB INCORPORATED
SB 05.01.03 R0
Check for absence of rotation of the bearing spacer of the
Tail-Rotor-Head (TRH) pitch-change-unit
Added
Section 04.10.00
25-63 HOISTS ELECTRICAL
25/63/00/100/000/000
Hoist operator safety harness
New task integrated
25/63/00/100/000/005
60 M
60 M
Adjustable lanyard
New task integrated
-
3.3
25/63/00/100/000/010
Lanyard connector
New task integrated
60 M
Section 04.20.00
63-30 MGB MOUNT AND ATTACHMENT
63/30/00/000/000/030
Forward suspension bars
MP/N modified
65-10 TAIL ROTOR DRIVE SHAFT
65/10/00/000/000/019
Tail rotor drive shaft - Greasable bearing
Task deleted
65/10/00/000/000/021
Tail rotor drive shaft - Greasable bearing
New task integrated
AS 350 B3
600 FH
750 FH
HIGHLIGHTS OF THE REVISION
2023.05.22 EASA Approved
Page 1
ALS
-
65/10/00/000/000/022
Tail rotor drive shaft - Greasable bearing
New task integrated
65-20 TAIL GEARBOX
65/20/00/000/000/001
TRH pitch change unit
New task integrated
300 FH
10 FH
67-10 MAIN ROTOR CONTROL
67/10/00/000/000/020
Collective lever lock and "low pitch" locking tab
Task deleted
67/10/00/000/000/025
Collective lever lock and "low pitch" locking tab
New task integrated
600 FH // 24 M
750 FH // 24 M
End of the Document Unit
AS 350 B3
HIGHLIGHTS OF THE REVISION
2023.05.22 EASA Approved
Page 2
ALS
SB INCORPORATED
Airbus Helicopters is required to issue Service Bulletins (ASB/SB) subsequent to new events (incidents, etc).
The information contained in the SBs is incorporated in the ALS if, and only if:
The SB contains new periodic checks, or modifies the existing ALS limitations and its incorporation is approved by
EASA.
The table below specifies for each SB incorporated:
-
the
the
the
the
the
number of the SB and its revision number,
subject of the SB,
ATA chapter/section concerned,
number of the associated EASA Airworthiness Directive (AD),
date on which the SB is incorporated in the ALS.
SB N°
Subject
05.00.11 R5 Inspection of blade spars on the tail rotor
ATA
AD number
Incorporation date
64-10
84.064.037 (B) R3 23.12.93
01.00.17 A Behaviour of the helicopter on the ground with 05-53
rotorturning
86.125.48 (B) R1 86.39
05.00.08
R5
Bearings of plain bearings at the aft section
of tail rotor transmission– Inspections and
operating limit
65-10
98.173.073 (A)
05.00.29
R1
T.R.H. pitch change unit-bearing – Check
65-20
99.085.076 (A) R1 18.05.99
05.00.35
53-50
Check of the attachment areas of the heat
shield of the tail rotor drive shaft forward fairing
05.00.37
Checking tail servocontrol eye end fitting for
correct locking
67-30
2001-580-085 R1 14.05.02
05.00.40
Tail rotor blade skin check
64-10
2001-640-089 (A) 16.07.02
01.00.48
Tail rotor hub pitch change plate bearing
65-20
2001-074-081 (A) 03.02.2003
—
Safety belts and restraint systems type 343-1
25-00
2002-104 (AB) R2 30.04.03
05.00.43
Check of the rear frame
53-10
2004-035 (A)
05.00.33
Check for absence of rotation of the bearing
spacer of the tail rotor rotating plate
65-20
2000-222-079 (A) 15.03.04
AS 350 B3
2023.05.22 EASA Approved
02.02.98
2000-340-080 (A) 02.05
R2
04.02.04
SB INCORPORATED
Page 1
ALS
AD number
Incorporation date
Replacement of hydraulic fluid in cold weather 29-00
2004-055 (A)
22.10.04
Tail rotor drive - Tail rotor drive shaft
65-10
2005-158 (A)
10.10.05
05.00.41
R2
Check of the sliding door aft guide roller and
middle rail
52-90
2006-0249
01.09.06
25.00.73
BREEZE 450 Lbs Electric Hoist
25-63
2002-027-088 (A) 27.07.05
R1
05.00.58
Collective pitch lever locking stud
67-10
2009-0019
26.05.11
05.00.60
Check for no play in the tail rotor pitch-change 65-20
links
2010-0006
20.10.11
05.00.84
R0
Periodic inspection of bi-directional suspension 63-30
cross-bar P/Nos. 350A381040.20 and
350A381040.00
2015-0094
03.11.16
01.00.70
R1
Tail rotor drive - Tail rotor drive shaft bearings
65-10
2015-0195
04.12.17
05.00.71
R2
Check of the Tail Rotor laminated half bearings 64-10
2012-0257-E
16.04.18
05.01.03
R0
Check for absence of rotation of the
bearing spacer of the Tail-Rotor-Head (TRH)
pitch-change-unit
2021-0282
22.05.23
SB N°
Subject
05.00.45
R1
–
ATA
65-20
End of the Document Unit
AS 350 B3
2023.05.22 EASA Approved
SB INCORPORATED
Page 2
ALS
04-10-00
D.U.
TITLE
ATA 25
EQUIPMENTS AND FURNISHINGS
ATA 62
ROTOR (S)
ATA 63
ROTOR DRIVE (S)
ATA 64
TAIL ROTOR
ATA 65
TAIL ROTOR DRIVE
ATA 67
ROTOR FLIGHT CONTROLS
AS 350 B3
2023.05.22 EASA Approved
04-10-00
Page 1
ALS
Task Number
Description/Remarks
MP/N (PN)
Type of limit: SLL
Margin
25 - EQUIPMENTS AND FURNISHINGS
25-00 EQUIPMENT AND FURNISHING
25/00/00/000/000/010
Belt and harness
ALL MP/N
(-)
A
60 M
X TSM
0A
Service life applicable to belts and harnesses equipped with type 343 or 343-1 buckles manufactured
by ANJOU (previously TRW Repa SA or AIGLON).
25-63 HOISTS ELECTRICAL
25/63/00/100/000/000
Hoist operator safety harness
60081491E
60081492E
60081493E
(704A41816102)
(704A41816104)
(704A41816103)
A
60 M
X TSM
0A
60081627
(704A41816098)
A
60 M
X TSM
0A
60081629
(704A41816097)
A
60 M
X TSM
0A
A
INF A
X A
0A
12000 FH X A
0A
25/63/00/100/000/005
Adjustable lanyard
25/63/00/100/000/010
Lanyard connector
62 - ROTOR (S)
62-10 MAIN ROTOR BLADE
62/10/00/401/000/025
Unequipped blade pin
350A31-1771-21
(-)
Not to be monitored in service.
Fitted to the assemblies: MP/N 350A31-1770-01, 350A31-1772-02, 350A31-1773-01.
This MP/N must not be mixed with MP/N 350A31-3020-20.
62/10/00/401/000/027
Unequipped blade pin
350A31-3020-20
(-)
A
Optionnal installation: OP6305.
Fitted to the assemblies: MP/N 350A31-1770-02, 350A31-1772-03, 350A31-1773-02.
This MP/N must not be mixed with MP/N 350A31-1771-21.
AS 350 B3
2023.05.22 EASA Approved
04-10-00
Page 2
ALS
Task Number
Description/Remarks
MP/N (PN)
Type of limit: SLL
Margin
62/10/00/401/000/060
Main rotor blade
(-)
(-)
(-)
A
20000 FH X A
0A
350A31-1877-03
(-)
A
80000 FH X A
0A
LB4-1231-1
(704A33633208)
A
6400 FH X A
0A
(704A33633211)
A
6400 FH X A
0A
(-)
A
2200 FH X A
0A
355A11-0030-00
355A11-0030-02
355A11-0030-04
62-20 MAIN ROTOR HEAD
62/20/00/000/000/123
Blade horn
62/20/00/000/000/185
Spherical thrust bearing
Service life limit for metal reinforcements only.
Must not be mixed with any other part numbers.
62/20/00/000/000/188
Spherical thrust bearing
57910700
Service life limit for metal reinforcements only.
Must not be mixed with any other part numbers.
62/20/00/000/000/255
Starflex star
350A31-1916-00
Stars must be paired with frequency adapters fitted with AMPEP swivel bearings MP/N 11-7775P.
Stars must not be installed on helicopters fitted with ARRIEL 2D engine.
62/20/00/000/000/280
Starflex star
350A31-1918-00
(-)
A
3000 FH X A
0A
Stars must be paired with frequency adapters fitted with AMPEP swivel bearings MP/N 11-7775P.
62/20/00/000/000/300
Starflex star
350A31-1907-03
350A31-1908-02
(-)
(-)
A
2200 FH X A
0A
Stars must be paired with frequency adapters fitted with AMPEP swivel bearings MP/N 11-7775P.
Stars must not be installed on helicopters fitted with ARRIEL 2D engine.
62/20/00/000/000/301
Starflex star
350A31-1917-00
350A31-1917-01
(-)
(-)
A
2400 FH X A
0A
Stars must be paired with frequency adapters fitted with AMPEP swivel bearings MP/N 11-7775P.
Stars must not be installed on helicopters fitted with ARRIEL 2D engine.
AS 350 B3
2023.05.22 EASA Approved
04-10-00
Page 3
ALS
Task Number
Description/Remarks
MP/N (PN)
Type of limit: SLL
Margin
62/20/00/402/000/025
Lower sleeve flange (Straight)
350A31-1850-02
(-)
A
6600 FH X A
0A
In the event of a sudden or repetitive severe tracking error, check: frequency adapters, spherical thrust
bearings, main blades, rigging of flying controls. If there is no improvement, before the next flight, remove
the blades and visually check the sleeve bushes for bonding separation.
If bushes have separated, replace the sleeve flanges.
62/20/00/402/000/070
Upper sleeve flange (Straight)
350A31-1850-03
(-)
A
6600 FH X A
0A
In the event of a sudden or repetitive severe tracking error, check: frequency adapters, spherical thrust
bearings, main blades, rigging of flying controls. If there is no improvement, before the next flight, remove
the blades and visualy check the sleeve bushes for bonding separation.
If bushes have separated, replace the sleeve flanges.
62/20/00/402/000/120
Spherical thrust bearing bolts
(-)
A
3000 FH X A
0A
350A37-1290-02
350A37-1290-03
350A37-1290-04
350A37-1290-05
(-)
(-)
(-)
(-)
A
90000 TC X A
0A
350A37-1291-00
(-)
A
INF A
X A
0A
(-)
A
INF A
X A
0A
(-)
(-)
(-)
(-)
(-)
A
INF A
X A
0A
350A31-1854-21
62-30 MAIN ROTOR MAST
62/30/00/000/000/143
Main rotor shaft
62/30/00/000/000/154
Rotor shaft upper casing
Not to be monitored in service.
62/30/00/000/000/155
Rotor shaft lower casing
350A37-1292-00
Not to be monitored in service.
62/30/00/000/000/162
Non-rotating and rotating swashplates
350A37-1002-06
350A37-1002-07
350A37-1003-06
350A37-1003-07
350A37-1003-08
Not to be monitored in service.
AS 350 B3
2023.05.22 EASA Approved
04-10-00
Page 4
ALS
Task Number
Description/Remarks
MP/N (PN)
Type of limit: SLL
Margin
62/30/00/000/000/170
Rotating swashplate
350A37-1018-00
(-)
A
20000 FH X A
0A
350A37-1126-01
350A37-1126-02
350A37-1126-03
350A37-1127-01
350A37-1127-02
(-)
(-)
(-)
(-)
(-)
A
INF A
X A
0A
(-)
(-)
(-)
A
INF A
X A
0A
(-)
(-)
A
20000 FH X A
0A
62/30/00/000/000/290
Scissor link
Not to be monitored in service.
62/30/00/000/000/300
Scissor drive adapter
350A37-1119-21
350A37-1119-23
350A37-1119-25
Not to be monitored in service.
62/30/00/000/000/305
Scissor drive adapter
355A37-1235-27
355A37-1235-29
POST OP 3082 // OP 3346: Installation of a twin hydraulic power system.
62/30/00/000/000/365
Fixed scissor screw
350A37-1146-22
(-)
A
20000 FH X A
0A
350A37-1242-22
350A37-1243-22
(-)
(-)
A
2200 FH X A
0A
350A37-1244-20
350A37-1245-20
(-)
(-)
A
3000 FH X A
0A
62/30/00/401/000/028
MRH attachment bolts
62/30/00/401/000/040
MRH attachment bolts
63 - ROTOR DRIVE (S)
63-20 MAIN GEARBOX
63/20/00/000/000/285
Sun gear
350A32-1075-20
350A32-1075-21
350A32-1075-22
(-)
(-)
(-)
A
INF A
X A
0A
Not to be monitored in service.
AS 350 B3
2023.05.22 EASA Approved
04-10-00
Page 5
ALS
Task Number
Description/Remarks
MP/N (PN)
Type of limit: SLL
Margin
63/20/00/000/000/383
Planet gear cage
350A32-1089-21
(-)
A
49000 TC X A
0A
350A32-1082-20
350A32-1082-21
(-)
(-)
A
20000 FH X A
0A
(-)
(-)
A
20000 FH X A
0A
(-)
A
89800 TC X A
0A
(-)
A
89800 TC X A
0A
350A32-3119-06
(-)
A
79200 TC X A
0A
350A32-3156-21
350A32-3156-22
(-)
(-)
A
//
20000 FH X A
120000 TC X A
0A
0A
63/20/00/000/000/405
Planet gear
Fitted to the assemblies: MP/N 350A32-1082-03, 350A32-1082-04.
63/20/00/000/000/415
Planet gear
350A32-1114-20
350A32-1114-21
Fitted to the assembly: MP/N 350A32-1114-00.
63/20/00/000/000/421
Equipped main housing
350A32-3191-00
Unequipped housing MP/N 350A32-3191-20.
63/20/00/000/000/423
Equipped main housing
350A32-3191-01
Unequipped housing MP/N 350A32-3191-21.
63/20/00/000/000/425
Lower housing equipped
63/20/00/000/000/451
Main casing
Fitted to the assemblies: MP/N 350A32-3156-01, 350A32-3156-02.
63/20/00/000/000/452
Main casing
350A32-3121-04
350A32-3121-06
(-)
(-)
A
//
20000 FH X A
120000 TC X A
0A
0A
350A32-3119-05
(-)
A
20000 FH X A
0A
350A32-3122-21
350A32-3150-21
(-)
(-)
A
20000 FH X A
0A
63/20/00/000/000/465
MGB bottom casing
63/20/00/000/000/471
Bevel gear
AS 350 B3
2023.05.22 EASA Approved
04-10-00
Page 6
ALS
Task Number
Description/Remarks
MP/N (PN)
Type of limit: SLL
Margin
63/20/00/000/000/477
Bevel gear
350A32-3163-20
350A32-3164-20
350A32-3172-20
350A32-3173-20
(-)
(-)
(-)
(-)
A
20000 FH X A
0A
350A32-3123-21
350A32-3151-22
(-)
(-)
A
20000 FH X A
0A
350A32-3165-20
350A32-3166-20
(-)
(-)
A
20000 FH X A
0A
350A32-1086-23
350A32-1118-20
350A32-1119-20
(-)
(-)
(-)
A
20000 FH X A
0A
350A35-1200-00
(-)
A
72000 TC X A
0A
(-)
A
72000 TC X A
0A
(-)
A
120000 TC X A
0A
90000 TC (P) A
0A
63/20/00/000/000/481
Bevel wheel
63/20/00/000/000/487
Bevel wheel
63/20/00/000/000/490
Fixed ring gear
63/20/00/000/000/510
Free wheel shaft
TURBOMECA part number: 0.292.90.003.0
ARRIEL 2B/2B1 Free wheel.
63/20/00/000/000/520
Splined sleeve
350A35-1210-20
TURBOMECA part number: 0.292.90.016.0
ARRIEL 2B/2B1 Free wheel.
63/20/00/000/000/620
Free wheel shaft
0.292.90.023.0
ARRIEL 2D free wheel.
Fitted to the free wheel assembly MP/N 0.292.90.020.0 (P/N 704A43622004).
63/20/00/000/000/630
Free wheel flange
0.292.90.025.0
(-)
A
ARRIEL 2D free wheel.
Fitted to the free wheel assembly MP/N 0.292.90.020.0 (P/N 704A43622004).
AS 350 B3
2023.05.22 EASA Approved
04-10-00
Page 7
ALS
Task Number
Description/Remarks
Type of limit: SLL
Margin
INF A
X A
0A
A
4000 FH X A
0A
MP/N (PN)
63-30 MGB MOUNT AND ATTACHMENT
63/30/00/000/000/095
MGB suspension cross bar
350A38-1040-00
350A38-1040-20
(-)
(-)
A
64 - TAIL ROTOR
64-10 TAIL ROTOR BLADE
64/10/00/000/000/130
Tail rotor blade
355A12-0050-04
355A12-0050-10
355A12-0050-12
355A12-0050-14
355A12-0051-04
355A12-0051-10
355A12-0051-12
355A12-0051-14
(-)
(-)
(-)
(-)
(-)
(-)
(-)
(-)
Blades must not be installed on helicopters fitted with ARRIEL 2D engine.
64/10/00/000/000/140
Tail rotor blade
355A12-0060-00
355A12-0060-02
355A12-0060-04
355A12-0060-06
(-)
(-)
(-)
(-)
A
4000 FH X A
0A
355A12-5103-00
(-)
A
20000 FH X A
0A
64/10/00/000/000/200
Tail rotor blade horn
Blade horn must not be installed on helicopters fitted with ARRIEL 2D engine.
64/10/00/000/000/211
Tail rotor blade horn
350A12-1368-03
350A12-1368-04
(-)
(-)
A
INF A
X A
0A
Blade horns must not be installed on helicopters fitted with ARRIEL 2D engine.
64/10/00/000/000/240
Tail rotor blade horn
355A12-5102-00
(-)
A
1000 FH X A
0A
355A12-5102-01
(-)
A
20000 FH X A
0A
64/10/00/000/000/245
Tail rotor blade horn
AS 350 B3
2023.05.22 EASA Approved
04-10-00
Page 8
ALS
Task Number
Description/Remarks
MP/N (PN)
Type of limit: SLL
Margin
64/10/00/000/000/250
Pitch rod
A
20000 FH X A
0A
(-)
(-)
A
9000 FH X A
0A
350A33-1090-02
(-)
A
20000 FH X A
0A
350A33-1000-20
(-)
A
3700 FH X A
0A
LB6-1231-3-1
LB6-1231-3-2
(704A47137035)
(704A47137036)
65 - TAIL ROTOR DRIVE
65-10 TAIL ROTOR DRIVE SHAFT
65/10/00/000/000/135
Aft shaft
350A34-1012-05
350A34-1012-06
MP/N 350A34-1012-05 on assy 350A34-0210-06.
MP/N 350A34-1012-06 on assy 350A34-0210-07.
65-20 TAIL GEARBOX
65/20/00/000/000/160
Casing
65/20/00/000/000/195
Bevel gear
Must not be installed on helicopters with optional all-up weight extension installation: OP 3369.
65/20/00/000/000/199
Bevel gear
350A33-1000-21
350A33-1000-22
350A33-1000-23
350A33-1000-24
(-)
(-)
(-)
(-)
A
5500 FH X A
0A
Gears MP/N 350A33-1000-21 and wheels MP/N 350A33-1001-21 or -22 must be paired.
Gears MP/N 350A33-1000-22/-24 and wheels MP/N 350A33-1001-23 must be paired.
Gears MP/N 350A33-1000-23 and wheels MP/N 350A33-1001-24 must be paired.
65/20/00/000/000/235
Bevel wheel
350A33-1001-20
(-)
A
10900 FH X A
0A
Must not be installed on helicopters with optional all-up weight extension installation: OP 3369.
AS 350 B3
2023.05.22 EASA Approved
04-10-00
Page 9
ALS
Task Number
Description/Remarks
MP/N (PN)
Type of limit: SLL
Margin
65/20/00/000/000/239
Bevel wheel
350A33-1001-21
350A33-1001-22
350A33-1001-23
350A33-1001-24
(-)
(-)
(-)
(-)
A
16500 FH X A
0A
Gears MP/N 350A33-1000-21 and wheels MP/N 350A33-1001-21 or -22 must be paired.
Gears MP/N 350A33-1000-22/-24 and wheels MP/N 350A33-1001-23 must be paired.
Gears MP/N 350A33-1000-23 and wheels MP/N 350A33-1001-24 must be paired.
65/20/00/000/000/242
Tail rotor shaft
350A33-1092-01
(-)
A
20000 FH X A
0A
350A33-1525-01
(-)
A
1000 FH X A
0A
350A33-1524-00
350A33-1526-00
(-)
(-)
A
20000 FH X A
0A
350A33-1535-00
(-)
A
20000 FH X A
0A
(704A33651190)
A
300 FH X A
0A
65/20/00/000/000/251
Control lever
65/20/00/000/000/252
Control lever
65/20/00/000/000/257
Control lever
65/20/00/000/000/320
TRH pitch change unit - Bearing
6010F234M16
67 - ROTOR FLIGHT CONTROLS
67-00 ROTORS FLIGHT CONTROLS
67/00/00/000/000/000
Roll control actuator
418-00478-204
418-00625-114
(704A47135033)
(704A47135033)
A
INF A
X A
0A
418-00478-304
418-00625-174
(704A47135052)
(704A47135052)
A
INF A
X A
0A
418-00478-554
418-00625-134
(704A47135031)
(704A47135031)
A
INF A
X A
0A
67/00/00/000/000/030
Pitch control actuator
67/00/00/000/000/050
Yaw control actuator
AS 350 B3
2023.05.22 EASA Approved
04-10-00
Page 10
ALS
Task Number
Description/Remarks
MP/N (PN)
Type of limit: SLL
Margin
67-30 SERVOCONTROL
67/30/00/402/000/020
Main servocontrol
SC5081
SC5081-1
SC5082
SC5082-1
SC5083
SC5084
(704A44831123)
(704A44831137)
(704A44831124)
(704A44831136)
(704A44831141)
(704A44831140)
A
INF A
X A
0A
SC5081-2
SC5083-1
(704A44831159)
(704A44831161)
A
INF A
X A
0A
INF A
X A
0A
INF A
X A
0A
20000 FH X A
0A
67/30/00/402/000/021
Main (roll) servocontrol
Must be installed with main (pitch) servocontrol, MP/N SC5082-2 or SC5084-1.
Cannot be mixed with any other part number.
67/30/00/402/000/022
Main (pitch) servocontrol
SC5082-2
SC5084-1
(704A44831160)
(704A44831162)
A
Must be installed with main (roll) servocontrol, MP/N SC5081-2 or SC5083-1.
67/30/00/402/000/035
Main servocontrol
SC8042
SC8043
(704A44831102)
(704A44831103)
A
POST OP 3082 // OP 3346: Installation of a twin hydraulic power system.
67/30/00/402/000/500
Main servocontrol
SA7450-100
SA7650-100
(704A44831170)
(704A44831171)
A
POST OP 3082 // OP 3346: Installation of a twin hydraulic power system.
67/30/00/403/000/010
Tail servocontrol
AC66436
AC67032MOD2
AC67032MOD6
SC5071
SC5071-1
SC5072
(704A44831063)
(704A44831094)
(704A44831115)
(704A44831125)
(704A44831138)
(704A44831142)
A
INF A
X A
0A
End of the Document Unit
AS 350 B3
2023.05.22 EASA Approved
04-10-00
Page 11
ALS
04-20-00
D.U.
TITLE
ATA 05
TIME LIMITS/MAINTENANCE CHECKS
ATA 25
EQUIPMENTS AND FURNISHINGS
ATA 29
HYDRAULIC POWER
ATA 52
DOORS
ATA 53
FUSELAGE
ATA 62
ROTOR (S)
ATA 63
ROTOR DRIVE (S)
ATA 64
TAIL ROTOR
ATA 65
TAIL ROTOR DRIVE
ATA 67
ROTOR FLIGHT CONTROLS
AS 350 B3
2023.05.22 EASA Approved
04-20-00
Page 1
ALS
Task Number
Description/
Remarks
MP/N (PN)
Type of limit: CHK
Margin
Documentation
05 - TIME LIMITS/MAINTENANCE CHECKS
05-53 INSPECTION FOLLOWING OPERATING INCIDENTS
05/53/00/000/000/020
Abnormal behaviour of the helicopter on the ground - Rotor spinning
AMM
AMM
AMM
AMM
AMM
AMM
AMM
AMM
AMM
AMM
AMM
AMM
AMM
AMM
AMM
AMM
AMM
AMM
AMM
AMM
AMM
32-11-00, 4-1
32-11-00, 4-2
32-11-00, 4-3
32-11-00, 6-1
32-11-00, 6-3
32-11-00, 6-4
62-21-00, 6-1
62-21-00, 6-2
62-21-00, 6-3
62-21-00, 6-4
62-21-00, 6-5
62-21-00, 6-6
62-21-00, 6-7
62-21-00, 6-8
62-21-00, 6-9
62-21-00, 6-10
63-31-00, 6-1
63-31-00, 6-3
63-31-00, 6-4
63-32-00, 6-1
63-32-00, 6-2
Check the following components on all helicopters on which incipient divergent dynamic excitation
has been noted (in flight or on the ground, rotor spinning):
- condition of MGB suspension bars,
- MRH,
- laminated pads without removing the MGB,
- landing gear.
DI|GR
25 - EQUIPMENTS AND FURNISHINGS
25-63 HOISTS ELECTRICAL
25/63/00/000/000/000
Electric hoist 450 lbs
BL2970023
(704A41815056)
A
//
3M X
50 HC X
0A
0A
AMM 25-63-11, 6-3
Dimensional check of the damper assembly buffer.
DI
AS 350 B3
2023.05.22 EASA Approved
04-20-00
Page 2
ALS
Task Number
Description/
Remarks
MP/N (PN)
Type of limit: CHK
Margin
Documentation
29 - HYDRAULIC POWER
29-00 HYDRAULIC POWER
29/00/00/000/000/005
Hydraulic system
AMM 29-00-00, 3-3
For flights at outside air temperatures equal to or below -15°C (5°F).
Before each flight, check that the hydraulic fluid was last replaced less than 110 FH // 1 M ago.
If this is not the case, replace the hydraulic fluid.
VC
52 - DOORS
52-90 SLIDING DOOR
52/90/00/000/000/015
Sliding door
A
100 FH X
0A
AMM 52-12-00, 6-3
PRE MOD 073287 (LH door), PRE MOD 073290 (RH door).
Checking the roller diameter and the front end opening dimension of the middle rail.
DI
53 - FUSELAGE
53-10 PRIMARY STRUCTURE
53/10/02/000/000/010
Rear frame
PO A
2600 FH X
100 FH
AMM 53-31-00, 6-5
Each time after the component is installed :
- PRE MOD 073215 and not equipped with the 2 reinforcement angles on the RH side (task 53-31-00, 8-5 AMM).
- PRE MOD 074766.
Visual check.
- If there is/are cracks of length less than or equal to 30 mm, this check must be carried out every 110 FH.
- If there is at least one crack of length more than 30 mm, comply with task 53-31-00, 8-5 (AMM).
DI
AS 350 B3
2023.05.22 EASA Approved
04-20-00
Page 3
ALS
Task Number
Description/
Remarks
MP/N (PN)
Type of limit: CHK
Margin
Documentation
100 FH
AMM 53-31-00, 6-7
53/10/02/000/000/030
Rear frame
PO A
2600 FH X
Each time after the component is installed:
Visual check to be carried out on aircraft:
- PRE MOD 073215,
- PRE MOD 074766,
- equipped with the 2 reinforcement angles on the RH side (task 53-31-00, 8-5 AMM),
- not equipped with the 4 reinforcement angles (task 53-31-00, 8-5 AMM).
DI
53/10/02/000/000/000
Rear frame
A
500 FH X
50 FH
AMM 53-31-00, 6-6
- PRE MOD 073215 and not equipped with the 2 reinforcement angles on the RH side (task 53-31-00, 8-5 AMM).
- PRE MOD 074766.
Visual check.
Operation to be done from 3250 FH.
- If there is/are cracks of length less than or equal to 30 mm, this check must be carried out every 110 FH.
- If there is at least one crack of length more than 30 mm, comply with task 53-31-00, 8-5 (AMM).
DI
53/10/02/000/000/005
Rear frame
A
500 FH X
50 FH
AMM 53-31-00, 6-7
Visual check to be carried out from 3250 FH on aircraft:
- PRE MOD 073215,
- PRE MOD 074766,
- equipped with the 2 reinforcement angles on the RH side (task 53-31-00, 8-5 AMM),
- not equipped with the 4 reinforcement angles (task 53-31-00, 8-5 AMM).
DI
53-50 COWLING AND FAIRING
53/50/00/000/000/000
Forward cowling - Tail rotor drive shaft
A
A ALF X
0A
AMM 05-40-00, 6-6
PRE MOD 073385
Check.
GVI
AS 350 B3
2023.05.22 EASA Approved
04-20-00
Page 4
ALS
Task Number
Description/
Remarks
MP/N (PN)
Type of limit: CHK
Margin
Documentation
53/50/00/000/000/010
Forward cowling - Tail rotor drive shaft
A
50 FH X
0A
AMM 53-31-00, 6-3
(PRE MOD 073097 and before embodiment of overhaul and AMM 53-31-00, 8-6) or (PRE
MOD 073097 and before repair sheet 350-53-42-00).
Check.
GVI
53/50/00/000/000/020
Forward cowling - Tail rotor drive shaft
A
100 FH X
0A
AMM 53-31-00, 6-3
[(POST MOD 073097 or (after embodiment of overhaul and AMM 53-31-00, 8-6) or after
repair sheet 350-53-42-00)] and PRE MOD 073385.
Check.
GVI
62 - ROTOR (S)
62-20 MAIN ROTOR HEAD
62/20/00/000/000/100
MRH
355A31-0002-00
355A31-0002-01
(-)
(-)
When removing the upper or lower sleeve flanges check the bushes at the star arm ends.
When removing the rotor hub, check the bushings in the center of the star.
All hubs MUST be fitted with droop restrainers.
GVI
62/20/00/000/000/139
Spherical thrust bearing
57910700
LB4-1231-1
(704A33633211)
(704A33633208)
A
10 FH X
0A
AMM 05-40-00, 6-7
(-)
(-)
(-)
(-)
(-)
A
10 FH X
0A
AMM 05-40-00, 6-7
Check of the elastomer part.
GVI
62/20/00/000/000/200
Starflex star
350A31-1907-03
350A31-1908-02
350A31-1916-00
350A31-1917-00
350A31-1917-01
Check.
GVI
AS 350 B3
2023.05.22 EASA Approved
04-20-00
Page 5
ALS
Task Number
Description/
Remarks
MP/N (PN)
Type of limit: CHK
Margin
Documentation
62/20/00/000/000/320
Starflex star
350A31-1918-00
(-)
A
50 FH X
10 FH
AMM 05-40-00, 6-7
(-)
(704A33640031)
A
10 FH X
0A
AMM 05-40-00, 6-7
Check.
GVI
62/20/00/402/000/175
Frequency adapter
365A31-1019-22
E1T2624-01A
Check of the elastomer part.
MP/N E1T2624-01A delivered in sets of three under MP/N 350A31-1827-01.
Must not be mixed together, nor with the other part numbers.
MP/N E1T2624-01A must not be installed on helicopters fitted with ARRIEL 2D engine.
GVI
62/20/00/402/000/185
Frequency adapter
365A31-1019-23
E1T3023-01
(-)
(704A33640046)
A
10 FH X
0A
AMM 05-40-00, 6-7
Check of the elastomer part.
MP/N E1T3023-01 delivered in sets of three under MP/N 350A31-1827-02.
Must not be mixed together, nor with the other part numbers.
MP/N E1T3023-01 must not be installed on helicopters fitted with ARRIEL 2D engine.
GVI
62/20/00/402/000/205
Frequency adapter
365A31-1019-25
E-4165F01
E-4165F11
(-)
(704A33640088)
(704A33640100)
A
10 FH X
0A
AMM 05-40-00, 6-7
Check of the elastomer part.
MP/N E-4165F01/11 delivered in sets of three under MP/N 350A31-1827-03/-04.
Must not be mixed together, nor with the other part numbers.
MP/N E-4165F01 must not be installed on helicopters fitted with ARRIEL 2D engine.
GVI
AS 350 B3
2023.05.22 EASA Approved
04-20-00
Page 6
ALS
Task Number
Description/
Remarks
MP/N (PN)
Type of limit: CHK
Margin
Documentation
63 - ROTOR DRIVE (S)
63-10 ENGINE-TO-M.G.B. COUPLING
63/10/00/000/000/090
Hydraulic pump on MGB
AP6VSC-PI0080
APV6SC-PA0080
(704A44320017)
(-)
A
//
500 FH X
24 M X
0A
0A
AMM 63-21-00, 4-8
ABEX type AP6VSC46.
Remove and check the pump and its drive.
CAUTION: the connection of any equipment to the power take-off must be approved by an
airworthiness approval (by competent airworthiness authorities).
Operating limitation: max permissible power = 32 kW.
DI
63-30 MGB MOUNT AND ATTACHMENT
63/30/00/000/000/030
Forward suspension bars
704A33-633-036
B211000-074
FDT14193
AMM 63-32-00, 6-1
AMM 63-32-00, 6-2
(704A33633036)
(704A33633262)
(704A33633074)
Check the condition of the MGB suspension bars:
a) During a MGB removal or whenever an operation requires suspension bar removal.
b) After a hard landing.
c) After incipient divergent dynamic excitation (in flight or on the ground, rotor spinning).
DI
63/30/00/000/000/040
Aft suspension bars
704A33-633-035
FDT14194
AMM 63-32-00, 6-1
AMM 63-32-00, 6-2
(704A33633035)
(704A33633075)
Check the condition of the MGB suspension bars:
a) During a MGB removal or whenever an operation requires suspension bar removal.
b) After a hard landing.
c) After incipient divergent dynamic excitation (in flight or on the ground, rotor spinning).
DI
63/30/00/000/000/065
MGB suspension cross bar
350A38-1040-00
350A38-1040-20
(-)
(-)
A
//
3000 FH X
60000 TC X
300 FH
0A
AMM 63-31-00, 6-4
Check with removal.
DI
AS 350 B3
2023.05.22 EASA Approved
04-20-00
Page 7
ALS
Task Number
Description/
Remarks
MP/N (PN)
Type of limit: CHK
Margin
Documentation
63/30/00/000/000/120
Laminated stops
579065H
579069G
AMM 63-31-00, 6-1
AMM 63-31-00, 6-3
(704A33633151)
(704A33633153)
Check the condition of the laminated stops:
a) During a MGB removal or whenever an operation requires MGB suspension cross bar removal.
b) After a hard landing.
c) After incipient divergent dynamic excitation (in flight or on the ground, rotor spinning).
DI
64 - TAIL ROTOR
64-10 TAIL ROTOR BLADE
64/10/00/000/000/033
Tail rotor blade
355A12-0050-04
355A12-0051-04
(-)
(-)
A
//
A ALF X
10 FH X
0A
0A
AMM 64-10-00, 6-6
A
30 FH X
0A
AMM 64-10-00, 6-2
Check.
GVI
64/10/00/000/000/040
Tail rotor blade
Check.
GVI
64/10/00/000/000/075
Tail rotor blade
AMM 64-10-00, 6-3
Remove and check the blade spar per WC.
Operation to be carried out:
- Each time the incidence laminated bearings are removed,
- If difficulties are encountered when balancing the rotor,
- In the event of abnormal noise.
DI
64/10/00/000/000/150
Tail rotor blade - Laminated pitch half-bearing
579063
579153
(704A33633116)
(704A33633261)
A
10 FH X
0A
AMM 05-40-00, 6-7
Check.
GVI
AS 350 B3
2023.05.22 EASA Approved
04-20-00
Page 8
ALS
Task Number
Description/
Remarks
MP/N (PN)
Type of limit: CHK
Margin
Documentation
64/10/00/000/000/160
Tail rotor blade - Laminated pitch half-bearing
579266
(704A33633303)
A
20 FH X
0A
AMM 05-40-00, 6-7
Check.
GVI
65 - TAIL ROTOR DRIVE
65-10 TAIL ROTOR DRIVE SHAFT
65/10/00/000/000/002
Tail rotor drive shaft - Sleeves
704A33-698-027
(-)
A
100 FH X
10 FH
AMM 65-11-00, 6-13
A
150 FH X
15 FH
AMM 65-11-00, 6-15
A
750 FH X
75 FH
AMM 65-11-00,3-1
AMM 65-11-00,6-5
A
300 FH X
30 FH
AMM 65-11-00,6-25
Check.
GVI
65/10/00/000/000/006
Tail rotor drive shaft – Greasable bearing
593404
(704A33651181)
Check without removal.
GVI
65/10/00/000/000/021
Tail rotor drive shaft - Greasable bearing
593404
(704A33651181)
Check and greasing.
DI|LUB
65/10/00/000/000/022
Tail rotor drive shaft - Greasable bearing
593404
(704A33651181)
Check the free rotation of the shaft without disassembly of the shaft.
DI
AS 350 B3
2023.05.22 EASA Approved
04-20-00
Page 9
ALS
Task Number
Description/
Remarks
MP/N (PN)
Type of limit: CHK
Margin
Documentation
65-20 TAIL GEARBOX
65/20/00/000/000/001
TRH pitch change unit
350A33-2030-00
350A33-2167-00
350A33-2167-01
(-)
(-)
(-)
A
10 FH X
0A
AMM 65-21-00, 6-15
POST MOD 0765002
Check the alignment of the black paint line between the pitch change spider and the bearing spacer.
VC
65/20/00/000/000/375
TRH pitch change unit - Baffle/Spacer
350A33-2004-05
350A33-2004-06
A
A ALF X
0A
AMM 05-40-00, 6-6
A
//
50 FH X
6M X
0A
0A
AMM 65-21-00, 6-8
A
100 FH X
0A
AMM 65-21-00, 6-8
(-)
A
30 FH X
0A
AMM 05-40-00, 6-7
(704A47137035)
(704A47137036)
A
50 FH X
0A
AMM 65-21-00, 6-21
(-)
(-)
PRE MOD 076554
Paint index marks alignment check.
GVI
65/20/00/000/000/387
TRH pitch change unit - Bearing
6010-2RS1
(704A33651003)
PRE MOD 076551
Check.
DI
65/20/00/000/000/390
TRH pitch change unit - Bearing
6010F234M16
(704A33651190)
POST MOD 076551 & PRE MOD 076550
Check.
DI
65/20/00/000/000/520
Pitch change links
350A33-2145-01
Check for absence of play.
DI
65/20/00/000/000/530
Pitch rod
LB6-1231-3-1
LB6-1231-3-2
Check elastomeric bearing.
GVI
AS 350 B3
2023.05.22 EASA Approved
04-20-00
Page 10
ALS
Task Number
Description/
Remarks
MP/N (PN)
Type of limit: CHK
Margin
Documentation
75 FH
0A
AMM 67-12-00, 6-2
67 - ROTOR FLIGHT CONTROLS
67-10 MAIN ROTOR CONTROL
67/10/00/000/000/025
Collective lever lock and "low pitch" locking tab
A
//
750 FH X
24 M X
Measurement of the clearance between the collective lever lock and the "low pitch" locking tab,
GVI
67-30 SERVOCONTROL
67/30/00/402/000/010
Main servocontrol
AC64182
AC66442
AC67030
AC67034
AC67244
AC67246
(704A44831062)
(704A44831065)
(704A44831093)
(704A44831095)
(704A44831112)
(704A44831113)
A
10 FH X
0A
AMM 05-40-00, 6-7
(704A44831063)
(704A44831094)
(704A44831115)
(704A44831125)
(704A44831138)
(704A44831142)
A
500 FH X
50 FH
AMM 67-33-00, 6-1
Visual check.
GVI
67/30/00/403/000/050
Tail servocontrol
AC66436
AC67032MOD2
AC67032MOD6
SC5071
SC5071-1
SC5072
PRE MOD 073139
Check the safeting of the tail servocontrol eye end-fitting.
GVI
End of the Document Unit
AS 350 B3
2023.05.22 EASA Approved
04-20-00
Page 11