# SB N° AS350-01.00.66

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### Civil version(s): B3



# SERVICE BULLETIN

SUBJECT: LIMITATIONS

Removal of the additional chin weights and additio n of a load compensator on

the yaw channel on helicopters which are POST modif ication 075601 and

equipped with an Arriel 2D engine

Corresponds to modification 075606

ATA: 24, 25, 29, 31, 39, 64, 65, 67, 88



### Revision No. Date of issue

Revision 0 2013-01-30

Revision 1 2013-02-15



### Summary:

To reduce the dynamic loads on the tail rotor contr ol channel by removing the additional chin weights, and to install

a load compensator.



### Reason for last Revision:

The purpose of Revision 1 of this Service Bulletin is to add the wire batch for helicopters equipped w ith the SMS

units and to update the associated procedures.



### Compliance:

EUROCOPTER recommends compliance with this Service Bulletin. For the attention of

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### 1. PLANNING INFORMATION

1.A. EFFECTIVITY

1.A.1. Helicopters/installed equipment

Helicopters embodying modification 075601 and equip ped with an Arriel 2D engine but not embodying

modification 075606 (subject of this Service Bullet in).



### NOTE 1

Refer to the aircraft individual inspection record (MOD

record) and the aircraft log book to identify the a ctual

configuration of the helicopter.

1.A.2. Non-installed equipment

Not applicable.



### 1.B. ASSOCIATED REQUIREMENTS

Previous embodiment of modification 076604 (Modific ation of Chin Weights and increase in the clearance

with the laminated half-bearing), available through Service Bulletin No. 64.00.11.



### 1.C. REASON

The purpose of this Service Bulletin is to reduce t he dynamic loads on the tail rotor control channel.

Reason for Revision 1:

The purpose of Revision 1 of this Service Bulletin is to add the wire batch for the embodiment of

modification 075606 on helicopters equipped with th e SMS units and to update the associated procedures

. Revision 1 of this Service Bulletin does not affect compliance with Revision 0.



### 1.D. DESCRIPTION

Compliance with this Service Bulletin consists in e mbodying modification 075606. To do so, the followi ng

operations must be carried out:

- Modification of the tail rotor:

a. removal of the additional chin weights.

b. modification of the part numbers for the rotatin g pitch-change spider and the rotating pitch-change

spider assembly.

- Modification of the tail rotor flight control lin kage in order to be able to install a load compensa tor.

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### NOTE 2

The modification of the electrical installation dep ends on the

helicopter configuration.

a. Helicopters equipped with the single hydraulic s ystem with a multi-unit type control unit.

b. Helicopters equipped with the single hydraulic s ystem with an SMS type control unit.

c. Helicopters equipped with the dual hydraulic sys tem with a multi-unit type control unit..

d. Helicopters equipped with the dual hydraulic sys tem with an SMS type control unit..

- Identification of compliance with this Service Bu lletin and embodiment of modification 075606 in the

helicopter documents and on the components concerne d.

- Operating and maintenance instructions following embodiment of the modification.

MODIFICATION 075606 (PARAGRAPHS 3.A. TO 3.C.) IS

TO BE EMBODIED BY EUROCOPTER SPECIALISTS OR

EUROCOPTER SUBSIDIARIES.

THE MAINTENANCE TO BE APPLIED FOLLOWING

EMBODIMENT OF MODIFICATION 075606 (PARAGRAPH

3.D.) IS TO BE PERFORMED BY THE OPERATOR.



### 1.E. COMPLIANCE

1.E.1. Compliance at the works

Not applicable.

1.E.2. Compliance in service

The work must be performed on the helicopter:

- by EUROCOPTER specialists or EUROCOPTER subsidiar ies for embodiment of the modification, and

- by the operator for maintenance.

Helicopters/installed equipment:

Comply with paragraph 3. within 12 months following receipt of Revision 0 of this Service Bulletin, is sued on

the date indicated at the bottom of the page.

Non-installed equipment:

Not applicable. 

### CAUTION

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### 1.F. APPROVAL

Approval of modifications:

The information or instructions relate to modificat ion 075606 which was approved on January 21, 2013 b y the EASA for helicopters of civil versions subject to an Airworthiness Certificate.

Approval of this document:

The technical information contained in this Service Bulletin Revision 0 was approved

on January 30, 2013 under the authority of EASA Des ign Organization Approval No. 21J.056 for helicopte rs

of civil versions subject to an Airworthiness Certi ficate.

The technical information contained in this Service Bulletin Revision 1 was approved

on February 15, 2013 under the authority of EASA De sign Organization Approval No. 21J.056 for helicopt ers

of civil versions subject to an Airworthiness Certi ficate.



### 1.G. MANPOWER

For compliance with this Service Bulletin, EUROCOPT ER recommends the following personnel

qualifications:

Qualification: - 2 Mechanical Engineering Technici ans

- 1 Electrical Engineering Technician

The time for the operations is given for informati on purposes, for a standard configuration.

Time for the operations: - approximately 176 hour s for the Mechanical Engineering Technicians

- approximately 24 hours for the Electrical Engin eering Technician

The estimated helicopter downtime is 2 weeks.



### 1.H. WEIGHT AND BALANCE

Weight: + 2.73 kg

Longitudinal moment: + 11.65 m.kg

Lateral moment: - 0.21 m.kg

Vertical moment: - 4.75 m.kg



### 1.I. EFFECT ON ELECTRICAL LOADS

The installation of the load compensator leads to a n increase in the rated current consumption from 1A

to 1.4A maximum

.



### 1.J. SOFTWARE MODIFICATION EMBODIMENT RECORD

Not applicable.

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### 1.K. REFERENCES

The following documents are required for compliance with this Service Bulletin:

MTC: 20.01.01.312: Use of dry lubricating films - M olykote product usage procedure

MTC: 20.02.01.410: General - Installation of crimpe d terminal lugs on cables

MTC: 20.02.01.411: General - Cable binding methods

MTC: 20.02.01.415: General - Installation of electr ical cable bundles

MTC: 20.02.01.418: General - Protection of electric al wiring during maintenance operations

MTC: 20.02.05.404: Joining - Joining by bolts and n uts

MTC: 20.02.06.402: Safetying and locking assemblies - Safetying with lockwire

MTC: 20.02.06.404: Safetying and locking assemblies - Safetying with cotter pins

MTC: 20.02.07.101: Electrical bonding: General

MTC: 20.02.07.401: Electrical Bonding - Bonding pro cedure

MTC: 20.02.07.403: Electrical Bonding - Use of Vern elec 43022 varnish

MTC: 20.02.07.407: Electrical Bonding - Use of AD-L UB 117 conducting paste

MTC: 20.04.05.402: Paint and primer application pro cedure - Use of EPOXY primer P05-P20 and P50

MTC: 20.05.01.211: General sealing procedures - Sea ling compound Mastinox 6856 K and 6856 H

MTC: 20.07.02.201: Safety Instructions - Helicopter parked in a repair shop

MTC: 20.07.03.404: Technical instructions - Instruc tions applicable during maintenance operations on

hydraulic systems

MTC: 20.07.03.406: Technical instructions - Instruc tions applicable when working on an aircraft electr ical

circuit and power generating systems

MTC: 20.07.03.408: Technical instructions - Appeara nce checks on an aircraft after an inspection or re pair

MTC: 20.08.05.101: General rules applicable to airc raft - Drafting and updating the log card (F.M)

MTC: 20.08.05.103: General rules applicable to airc raft - Monitoring of parts in operation - marking - service

life customization

MTC: 20.09.02.901: Preservation - Preservation and packing methods of airborne equipment

MTC: 20.60.00.166: Standard practices - Blades: pre paration of EC2216 or CN EC2216 adhesive

AMM: 21-51-10, 4-2: Air Conditioning - Removal / In stallation - Air Conditioning System Condenser

AMM: 24-00-00, 3-1: Electrical Power - General Safe ty Instructions - Electrical Power Supply System

AMM: 29-00-00, 3-1: Hydraulic Power - General Safet y Instructions - Hydraulic Power System

AMM: 29-00-00, 3-5: Hydraulic Power - Verification / Charging / Discharging - Load compensator

accumulator pressure

AMM: 29-00-00, 3-3: Hydraulic Power - Filling / Dra ining - Hydraulic System (Single power system) or ( Twin

power system)

AMM: 53-51-00, 4-2: Cowlings - Removal / Installat ion

AMM: 56-11-00, 4-6: Windows and windshield - Remov al / Installation

AMM: 60-00-00, 3-1: General - Mechanics system - Ge neral Safety Instructions - Mechanical Assemblies

AMM: 60-00-00, 3-2: General Safety Instructions - C ritical Parts

AMM: 64-10-00, 5-1a: Tail rotor blades - Tail rotor balancing

AMM: 64-10-00, 8-22: Tail Rotor Blade - Removal / I nstallation - Additional Weights on Chinese Weights

POST MOD 075601

AMM: 64-10-00, 8-10: Tail Rotor Blade - Minor paint touch-up

AMM: 65-21-00, 4-1: Tail Gearbox - Removal - TGB

AMM: 65-21-00, 4-2: Tail Gearbox - Installation - T GB

AMM: 65-21-00, 4-12b: Tail Gearbox - Removal/Instal lation - Pitch-change links POST MOD 075601 or

POST MOD 076602

AMM: 67-00-00, 3-1: Rotor Flight Controls - General Safety Instructions - Flight Controls

AMM: 67-00-00, 6-1: Rotor Flight Controls - Checks after maintenance - Flight Controls

AMM: 67-21-00, 5-1: Tail Rotor Flight Controls - Ri gging - Tail Rotor Flight Controls (Version without

Auto-Pilot)

AMM: 67-21-01, 5-1: Tail Rotor Flight Controls - Ri gging - Tail Rotor Flight Controls (Version with Au to-Pilot)

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### 1.L. DOCUMENTS AFFECTED

CAUTION

THE OPERATOR USING THIS SERVICE

BULLETIN MUST MAKE SURE THAT ALL THE

MAINTENANCE DOCUMENTS REQUIRED FOR

THE MAINTENANCE OF THIS INSTALLATION

ARE AVAILABLE. OTHERWISE, IT IS THE

RESPONSIBILITY OF THE OPERATOR TO

OBTAIN THE DOCUMENTS FROM HIS/HER

USUAL EUROCOPTER CONTACT.

Documents to be updated

EUROCOPTER will modify the following documents with respect to this Service Bulletin:

- Wiring Diagram Manual (WDM)

- Illustrated Parts Catalog (IPC)

The documents affected will be updated during a fut ure revision.

Documents already updated

The modifications have been integrated by EUROCOPTE R in the following documents:

- Aircraft Maintenance Manual (AMM)

- Flight Manual (FLM)

- Master Servicing Manual (MSM)



### 1.M. INTERCHANGEABILITY OR MIXABILITY OF PARTS

Interchangeability:

Pre-modification and post-modification parts are no t interchangeable.

Mixability:

Mixability of pre- and post-modification parts is p rohibited.

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### 2. MATERIAL INFORMATION

2.A. MATERIAL: PRICE - AVAILABILITY - PROCUREMENT

For any information concerning the kits and/or comp onents, contact the EUROCOPTER Network Sales &

Customer Relations Department.

EUROCOPTER

Etablissement de Marignane

Direction Ventes et Relations Client (ECR)

13725 MARIGNANE CEDEX

FRANCE



### NOTE 1

On the purchase order, please always specify the mo de of

transport, the destination and the serial numbers o f the

helicopters to be modified.



### 2.B. INFORMATION CONCERNING INDUSTRIAL SUPPORT

The work will be performed by EUROCOPTER specialist s.

Inform EUROCOPTER of the configuration of the helic opters to be modified by specifying the following

information:

- Helicopter type and version,

- S/N of the helicopter,

- Single/dual hydraulic system (pre or post modific ation OP3082 or OP3346),

- Type of control unit (SMS unit: pre modification 074280 or multi-unit: post modification 074280),

- Language required for the VNE label.

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### 2.C. MATERIAL REQUIRED FOR EACH HELICOPTER/COMPONEN T

Kits or components to be ordered for one helicopte r or one assembly:

Key Word Qty New

P/N Item Former

P/N → Instruction

Mechanical retrofit kit

350A07-5606-0071 comprising:

pin 4 355A12-5109-20 1 / /

castellated

hexagonal nut 4 6PHCR135M 2 / /

flat washer 4 23112AG060LE 3 / /

hexagonal head

screw 4 22129BC060040L 4 / /

blank 4 355A12-5110-20 5 / /

cotter pin 4 EN2367-18020 6 / /

flat washer 7 23111AG060LE 7 / /

Special union 1 355A75-1375-20 8 / /

Special union 1 355A75-1376-20 9 / /

O-ring 1 DHS621-100.02 10 / /

O-ring 1 DHS621-100.03 11 / /

Tee union 1 702A30-5500-01 12 / /

Tee union 1 702A30-5500-59 13 / /

flexible pipe 1 9SN40141

(704A34412260) 14 / /

flexible pipe 1 9SN40151

(704A34412261) 15 / /

clamp block 1 E0688-01 18 / /

diaphragm union 1 355A75-1377-20 19 / /

static seal ring 1 81811-100 20 / /

hydraulic actuator

assembly 1 355A75-1370-04 21 / /

washer 8 350A27-1142-20 22 / /

hexagonal head

screw 1 22125BC060046L 23 / /

hexagonal head

screw 3 22201BC060029L 24 / /

self-locking

hexagonal nut 4 ASN52320BH060N 25 / /

rod assembly 1 350A27-1910-0401 26 350A27-1910-05 /

sleeve 1 355A27-0060-20 27 / /

flight control rod 1 ED-RLGRSA-1 28 / /

cotter pin 5 23310CA015020 30 / /

castellated

hexagonal nut 3 ASNA0045-060BCL 31 / /

threaded pin 1 22731BC060022M 32 / /

washer 2 355A27-0073-21 33 / /

piston thrust

washer 2 355A75-1387-20 34 / /

threaded pin 1 22731BC060019M 35 / /

flat washer 2 23111AG080LE 36 / /

threaded pin 2 22731BC100057M 37 / /

castellated

hexagonal nut 2 ASNA0045-080BCL 38 / /

fitted lever

assembly 1 355A27-0082-01 39 / /

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plastic rivet 2 52607NOIR 40 / /

flat washer 2 23119AG060LE 41 / /

washer 8 984427CA10 42 / /

spacer 2 355A27-0065-20 43 / /

threaded pin 1 22731BC060043M 44 / /

washer 2 355A27-0073-22 45 / /

o-ring 2 81810-110-24B7 46 / /

Key Word Qty New

P/N Item Former

P/N → Instruction

ELEC. retrofit kit, Single hydraulic system,

multi-unit:

50A07-5606-0171

Connector 1 ECS0727R04A 100 / /

Tab 1 ECS0727WM04P 101 / /

Connector 1 ECS0727P04B 102 / /

Tab 1 ECS0727WM04S 103 / /

Crimp contact 3 EN3155-019F2020 104 / /

Crimp contact 3 EN3155-018M2020 105 / /

Grounding module 1 E0656A01N1S0 106 / /

Crimp contact 1 EN3155-016M2018 107 / /

Crimp contact 2 EN3155-008M2020 108 / /

Crimp contact 2 EN3155-003F2020 109 / /

Grommet 1 15-201 110 / /

Wire batch 1 350A08-4535-0098 111 / /

Wire batch and

marker 1 350A08-4535-0099 124 / /

Pre-insulated round

terminal lug 4 NSA936501TA2006 112 / /

Cap 1 E0737B0816 113 /

Extension lead 1 E0541-12 114 /

Circuit breaker 1 4120-V110-7,5A 115 / /

Identification plate 1 ECS2033.32 116 / /

Label 144N 1 350A61-2969-60 120 / /

Self-locking

hexagonal nut 1 ASN52320BH050N 121 / /

Washer 1 23111AG050LE 122 / /

ELEC. retrofit kit, Single hydraulic system,

SMS unit:

350A07-5606-0271

Pre-insulated round

terminal lug 4 NSA936501TA2006 112 / /

Extension lead 1 E0541-12 114 / /

ELEC. retrofit kit, Dual Hydraulic System,

multi-unit:

350A07-5606-0371

Pre-insulated round

terminal lug 4 NSA936501TA2006 112 / /

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Extension lead 1 E0541-11 123 / /

Crimp contact 3 EN3155-008M2020 108 / /

Crimp contact 2 EN3155-003F2020 109 / /

Grommet 1 15-201 110 / /

Grounding module 1 E0656A01N1S0 106 / /

Crimp contact 6 EN3155-016M2018 107 / /

Bush 3 130743-1 129 / /

Crimp contact 1 350689-3 130 / /

Crimp contact 2 001704-120-02 131 / /

Crimp contact 10 EN3155-003F2222 132 / /

Connector 1 ECS0780-01 133 / /

Crimp contact 4 EN3155-016M2222 134 / /

Wire batch 1 350A08-4543-0098 135 / /

Wire batch 1 350A08-4535-0099 124 / /

Connector 1 ECS0727R04A 100 / /

Tab 1 ECS0727WM04P 101 / /

Connector 1 ECS0727P04B 102 / /

Tab 1 ECS0727WM04S 103 / /

Crimp contact 3 EN3155-019F2020 104 / /

Crimp contact 3 EN3155-018M2020 105 / /

144N label 1 350A61-2969-60 120 / /

Self-locking

hexagonal nut 1 ASN52320BH050N 121 / /

Washer 1 23111AG050LE 122 / /

Circuit breaker 1 4120-V110-7,5A 115 / /

Identification plate 1 ECS2033.32 116 / /

Circuit breaker 1 ECS0744A02A5 136 / /

HYD label 1 350A61-2637-84 137 / /

Batch of markers 1 350A67-4283-0099 138 / /

Indicator light 1 ECS0763F2007N 139 / /

Single sleeve 1 29709-001 140 / /

Protective cover 1 35860-104 141 / /

ELEC. retrofit kit, Dual hydraulic system, SMS

unit:

350A07-5606-0471 / /

/ /

Circuit breaker 1 ECS0744A02A5 136 / /

HYD label 1 350A61-2637-84 137 / /

Pushbutton 1 304-2493-00 145 / /

Protective flap 1 040101A105A 146 / /

Circuit breaker 1 ECS0744A06A0 147 / /

Pre-insulated round

terminal lug 4 NSA936501TA2006 112 / /

Extension lead 1 E0541-11 123 / /

Crimp contact 1 350689-3 130 / /

Crimp contact 1 EN3155-003F1614 144 / /

Cap 1 E0737B0816 113 / /

/ /

/ /

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### NOTE 2

For helicopters equipped with the single hydraulic system

with multi-unit: order kit 350A07-5606-0071 and ki t 350A07-

5606-0171.

For helicopters equipped with the single hydraulic system

with SMS unit: order kit 350A-5606-0071 and kit 35 0A07-

5006-0271.

For helicopters equipped with the dual hydraulic sy stem with

multi-unit: order kit 350A07-5606-0071 and kit 350 A07-

5606-0371.

For helicopters equipped with the dual hydraulic sy stem with

SMS unit: order kit 350A-5606-0071 and kit 350A07-5 006-

0471.



### NOTE 3

As the kits are the same for versions B3 and C3, it ems

(100), (101), (102), (103), (104) and (105) will no t be used in

this Service Bulletin.

Material to be ordered separately:

Key Word Qty New

P/N Item Former

P/N → Instruction

Binding clamp 2 E0043-2C0 29 / /

Teflon adhesive

tape A/R A2007LARGEUR40 47 / /

Laminated

half-bearing A/R 704A33-633-261 48 704A33-633-261 To be scrapped

if more than

5 FH logged

since new

Washer 2 355A75-1387-21 49 / /

VNE label in

French 1 350A00-0120-FJ 117 / /

VNE label in

English 1 350A00-0120-FK 118 / /

Russian VNE label

in English 1 350A00-0161-54 119 / /

DR20 wire 1m EN2267-010A006S 148 / /

DR22 wire 0.5

m EN2267-010A004S 149 / /

NOMEX sheath 25m EN6049-003-04-5 151 / /

DR25 sheath 10m DHS271-611.05 152 / /

Binding clamp 100 E0043-4C0 154 / /

Binding clamp 200 E0043-5C0 155 / /

Binding clamp 100 E0043-7C0 156 / /

/ /

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Key Word Qty New

P/N Item Former

P/N → Instruction

All helicopters equipped with SMS units:

Grounding module 1 E0656A01N1S0 106 / /

Crimp contact 1 EN3155-016M2018 107 / /

Crimp contact 2 EN3155-008M2020 108 / /

Crimp contact 2 EN3155-003F2020 109 / /

Grommet 1 15-201 110 / /

144N label 1 350A61-2969-60 120

Self-locking

hexagonal nut 1 ASN52320BH050N 121

Washer 1 23111AG050LE 122

Specifically for helicopters with single

hydraulic system equipped with SMS unit:

Wire batch and

marker 1 350A08-4546-0099 157 / /

Cap 1 E0737B0816 113

Specifically for helicopters with dual hydraulic

system equipped with SMS unit:

Bush 1 130743-1 129 / /

Crimp contact 3 EN3155-015F2018 159 / /

Wire batch and

marker 1 350A08-4547-0098 158 / /

Products to be ordered separately:

Refer to the Work Cards and Tasks specified in this Service Bulletin and the list below:

Key Word Qty Product P/N CM Item

Adhesive A/R EC2216 CM672 50

Mastinox sealing compound A/R Mastinox 6856H CM518 51

Finish paint A/R DHN1-028P81M / 52

Sand paper A/R Off the shelf / 53

Primer A/R P05 / 54

0.8 lockwire A/R EN3628-0,8 CM776 55

spray varnish A/R Molykote CM5002 56

Grease A/R AIR4206 CM116 57

0.6 lockwire A/R EN 3628-0.63 CM775 58

Varnish A/R Vernelec 43022 CM514 59

Conductive paste A/R AD-LUB 117 / 60

Hardener A/R 2-K-HS-STANDARD / 61

Polyurethane paint A/R ECS2018.30-3624 / 62

The products can be ordered separately from the INT ERTURBINE AVIATION LOGISTICS company.

Website: http://www.interturbine.com

Telephone: +49.41.91.809.300

AOG: +49.41.91.809.444

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Key Word Qty P/N of the tool or equivalent Item

Blanks A/R Off the shelf zz

6H8 reamer 1 Reamer Paris No. 2 yy

5.5 mm diam. drill 1 Off the shelf ww

Plug removal tool 1 29082-001 xx



### 2.D. MATERIAL TO BE RETURNED

Not applicable.

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### 3. ACCOMPLISHMENT INSTRUCTIONS

3.A. GENERAL

Read and comply with the general instructions conce rning electrical power as per AMM Task 24-00-00, 3- 1.

Read and comply with the general instructions conce rning hydraulic power as per AMM Task 29-00-00, 3-1

. Read and comply with the general instructions conce rning flight controls as per AMM Task 67-00-00, 3-1

. Read and comply with the general instructions conce rning mechanical assemblies as per

AMM Task 60-00-00, 3-1.

Read and comply with the assembly instructions for joining by bolts and nuts as per MTC Work

Card 20.02.05.404.

Read and comply with the general instructions for s afetying with lockwire as per MTC Work

Card 20.02.06.402.

Read and comply with the general instructions for s afetying with cotter pins as per MTC Work

Card 20.02.06.404.

Read and comply with the general instructions appli cable to critical parts as per AMM Task 60-00-00,3- 2.

Read and comply with the Mastinox preparation metho d as per MTC Work Card 20.05.01.211.

Read and comply with the instructions concerning th e installation of crimped terminal lugs on cables a s per

MTC Work Card 20.02.01.410.

Read and comply with the cable binding methods as p er MTC Work Card 20.02.01.411.

Read and comply with the instructions for installat ion of electrical harnesses as per MTC Work

Card 20.02.01.415.

Read and comply with the instructions concerning th e protection of electrical wiring during maintenanc e as

per MTC Work Card 20.02.01.418.

Read and comply with the general instructions conce rning electrical bonding as per MTC Work

Card 20.02.07.101.

Read and comply with the instructions concerning th e electrical bonding procedure as per MTC Work

Card 20.02.07.401.

Read and comply with the instructions for use of VE RNELEC 43022 varnish as per MTC Work

Card 20.02.07.403.

Read and comply with the instructions for use of AD -LUB 117 conductive paste as per MTC Work

Card 20.02.07.407.

Read and comply with the instructions for aircraft parked in a repair shop as per MTC Work

Card 20.07.02.201.

Perform the appearance checks on aircraft after ins pection or repair as per MTC Work Card 20.07.03.408

.



### 3.B. OPERATIONAL PROCEDURE

3.B.1. Preliminary steps

- Install the access equipment.

- Remove the tail rotor drive fairings.

- Open the load compensator inspection door.

- Open the baggage compartment door.

- Remove the rear closing panel in the baggage comp artment.

- Remove and/or open all cowlings, panels, doors an d equipment required to gain access to the differen t

work areas.

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### NOTE 1

It is not necessary to disconnect the freon pipes.

. Remove the air ducts and the four screws attachin g the condenser as per AMM Task 21-51-10, 4-2.

. Move the condenser forward in the baggage compart ment.

- Remove the TGB as per AMM Task 65-21-00, 4-1 whil st leaving the flexible coupling installed on the T GB.

- Protect the flux valve.

- Remove the lower cowlings as per AMM Task 53-51- 00, 4-2.

- Remove the nose-fairing hatch.

- Remove the enlarged field-of-vision windows as p er AMM Task 56-11-00, 4-6.

3.B.2. Modification of the tail rotor

3.B.2.a. Removal of additional chin weights (Figure 1)

- Remove the four additional chin weights as per AM M Task 64-10-00,8-22.

- Install blanks (5) on the chin weights (a) (Secti on A-A, Figure 1):

. Install a centering pin (1) using adhesive (50) a s per MTC Work Card 20.60.00.166.

. Apply Mastinox sealing compound (51) to the cente ring pins (1) and the smooth part of the screw (4).

. Fit the washer (3) on the screw (4) (on the mille d side toward the screw head).

. Install the blank (5) using the washer (7), the n ut (2) and the screw (4) (fitted with washer (3)).

. Torque-tighten the nut (2) as per Figure 1.

. Lock the nut (2) using the cotter pin (6).

. Apply the same procedure to the three other blank s (5).

. Touch up the paint on the chin weights (a), using finish paint (62) + hardener (61) as per AMM

Task 64-10-00, 8-10.

. Re-identify the blade assembly as per paragraph 3 .C.

- As a precaution, replace the four laminated half- bearings (48) (not shown) only if they have logged

more than 5 hours since new.

- Scrap the replaced laminated half-bearings.

3.B.2.b. Modification of the rotating pitch-change spider assembly (Figure 2)

WHEN DELETING THE MARKING, DO NOT TOUCH THE

BASE METAL.

- On the rotating pitch-change spider (b), delete t he two stamp-markings "DO NOT INSTALL WITH YAW

LOAD COMPENSATOR", using sand paper (53) (Detail C, Figure 2).

- Carry out a protective touch-up on the zones whic h have already been touched up using primer (54) an d

finish paint (52).

- Re-identify the rotating pitch-change spider and the rotating pitch-change spider assembly as per

paragraph 3.C. (Details B and D, Figure 2).

- Carry out a protective touch-up using primer (54) and finish paint (52). 

### CAUTION

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AS THE WORK AREA IS LOCATED BENEATH THE TAIL

ROTOR DRIVE SHAFT, YOU MUST TAKE ALL THE

NECESSARY PRECAUTIONS TO PREVENT DAMAGE TO

THE TAIL ROTOR DRIVE SHAFT.

3.B.3.a. Removal

- Disconnect the "pressure" pipe (d) (Figure 3) and the "return" pipe (e) from the manifold assembly ( f) of

the tail rotor servo-control (c).

- If necessary, remove the manifold (f) as follows:

. Remove the lockwire from the banjo bolts (g).

. Remove the banjo bolts (g).

. Remove the manifold (f).

. Remove and discard the seals (h).

- Remove and discard the plug-in unions (i) and the seals (j).

- Install the blanks (zz) (not shown) on pipes (d) and (e).

- Install the blanks (zz) (not shown) on the tail r otor servo-control (c) or on the manifold (f).

- In order to remove the long rod (k):

. Uncouple the long rod (k) from the tail rotor ser vo-control (c):

- Remove and discard the nuts (q) and the lower was hers (p).

- Remove and discard the screws (m) and the upper w ashers (n).

- Remove and retain the friction pad (r).

- Release the long rod (k).

. If necessary, and in order to facilitate removal of the long rod (k), remove the TGB front support ( s) (see

photo below).



### NOTE 2

Exceptionally, the TGB front support (s) may be rem oved.

If the TGB front support (s) attachment screws are removed

too frequently, there is a risk that the elliptical deformation

nut plates may need replacing.

. Separate the bearing (t) from support No.1, in or der to increase the lateral travel. 

### CAUTION

s t

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. When extracting the long rod (k), protect the str uctural passages.

. Pull the long rod (k) toward the rear, on the LH side of the upper fin.

. Store the long rod as per MTC Work Card 20.09.02. 901.

3.B.3.b. Installation

Prerequisites for the installation of the load comp ensator

- On a workbench:

. Assemble the long rod (26) with the sleeve (27).

. Position the ball-joint of the long rod (26) so t hat the side with the thickest crimp points upward.

. Mark the sleeve (27) and the long rod (26).

. Install a screw (24) and a washer (22).

. Check the bore of the second hole using a 6H8 rea mer (yy) (not shown).

. Disassemble the long rod (26) from the sleeve (27 ).

. Deburr sharp edges.

- Make sure that the bearing (y) of support No. 5 i s installed in compliance with the photo below:

- Position the long rod (26):

. Slide the long rod (26) into the bearings.

. Position the long rod (26) so that the side with the thickest crimp points upward.

- On the manifold (f): (Figure 3)

. Install Tee union (12) on special union (8).

. Install Tee union (13) on special union (9).

. Install special unions (8) with seal (10).

. Install special union (9) with seal (11).

TAKE CARE NOT TO PINCH THE SEALS (46) DURING

THEIR INSTALLATION.

- If previously removed, install the manifold (f) o n the tail rotor servo-control (c):

. Install seals (46) between the tail rotor servo-c ontrol (c) and the manifold (f).

. Install the manifold (f).

. Install seals (46) between the manifold (f) and t he banjo bolts (g).

. Tighten the banjo bolts (g).

. Safety the banjo bolts (g) using lockwire (55). 

### CAUTION y

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- Install teflon tapes (47) on either side of the s upport (u) as per Figure 4.

- Install the load compensator control: (Figure 3):

. Install the sleeve (27):

- Couple the sleeve (27) with the long rod (26):

. Apply Mastinox sealing compound (51) to the retra ctable part of the long rod (26) and the smooth

part of the screws (24).

. Engage the front tip of the long rod (26) into th e sleeve (27) as marked during assembly of the long

rod (26) and sleeve (27) on the workbench.

TAKE CARE TO COMPLY WITH THE SCREW

INSTALLATION DIRECTION AS PER THE DETAIL IN

FIGURE 3.

. Install the screws (24), the washers (22) and the nuts (25).



### NOTE 3

The curved part of the washers (22) must be in fron t of the

sleeve (27).

. Tighten the nuts (25) to standard torque.

- Couple the sleeve (27) with the tail rotor servo- control (c):

. Install the friction pad (r) in the slide (v).

. Install the upper washers (22) on screws (23) and (24).

. Apply Mastinox sealing compound (51) to the smoot h part of screws (23) and (24).

. Install screws (23) and (24), the lower washers ( 22) and the nuts (25).



### NOTE 4

The curved part of the washers (22) must be in fron t of the

sleeve (27).

. Make sure that the friction pad (r) is flush with the bottom of the slide (v).

. Tighten the nuts (25) to standard torque.

- Install the compensation rod (28):

. Position the compensation rod (28) in the sleeve (27).

. Install a washer (33) on either side of the ball- joint of the compensation rod (28).

. Lubricate the smooth part of the bolt with grease (57).

. Install the bolt (32), the washer (7) and the nut (31).

. Tighten the nut (31) to standard torque.

. Lock the nut (31) with a cotter pin (30). 

### CAUTION

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- Install the load compensator:



### NOTE 5

The load compensator comprises the hydraulic actuat or

assembly (21) and the lever (39).

. On a workbench:

- Install the sealing ring (20) (Figure 6) and the diaphragm union (19) on the hydraulic actuator

assembly (21).



### NOTE 6

The sealing ring (20) must be inserted in the groov e of the

diaphragm union (19).

- Couple the hydraulic actuator assembly (21) with the lever (39) (Section H-H, Figure 6):

. Ensure the position of the hydraulic actuator end in the yoke:

- Install a thrust washer (34) or (49) (Section H-H , Figure 6) on either side of the hydraulic actuato r

end (21).

. Lubricate the smooth part of the bolt (35) with g rease (57).

. Install the bolt (35), the washer (7) and the nut (31).

. Tighten the nut (31) to standard torque.

. Lock the nut (31) with a cotter pin (30).

. Install the hydraulic actuator assembly on the st ructure support (u) (Section H-H, Figure 6):

- lubricate the smooth part of the bolt (37) with g rease (57).

- Install the bolt (37), the washer (36) and the nu t (38).

- Tighten the nut (38) to standard torque.

- Lock the nut (38) with a cotter pin (30).

. Position the lever (39) on the structure support (u) and on the compensation rod (28).

. Install the lever (39) on the sleeve (27) and the compensation rod (28) (Section G-G, Figure 6):

- Install the friction washers (45) between the lev er (39) and the sleeve (27).

- Install the spacers (43).

- Lubricate the smooth part of the bolt (44) with g rease (57).

- Install the bolt (44), the washer (7) and the nut (31).

- Tighten the nut (31) to standard torque.

- Make sure that the friction washers (45) rotate f reely.

- Lock the nut (31) with a cotter pin (30).

. Install the lever (39) on the structure support ( u) (Section H-H, Figure 6):

- Install as required washers (42) on either side o f the lever (39) in order to center it in the openi ng of

the sleeve (27).

- Ensure a lateral play "J" less than or equal to 0 .5 mm (.02 in.) before tightening the bolt (37).

- Lubricate the smooth part of the bolt (37).

- Install the bolt (37), the washer (36) and the nu t (38).

- Tighten the nut (38) to standard torque.

- Lock the nut (38) with a cotter pin (30).

. Apply a spray varnish (56) protection to the scre w heads and attachment nuts as per MTC Work

Card 20.01.01.312.

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- Connect pipes (14) and (15) to Tee unions (12) an d (13) (Figure 3) as well as to the hydraulic

actuator (21) (Figure 6).

- Connect pipes (d) and (e) to Tee unions (12) and (13).

- Install the clamp block (18) between pipes (14) a nd (15) (Detail F, Figure 6).

- Attach the pipes to the clamp block (18) using th e binding clamps (29).

- Attach the bearing (t) to support No. 1.



### NOTE 7

The position of bearing No. 1 must be adjusted so a s to

have as little friction as possible on the long rod in the event

of extreme ranges of travel.

- If previously removed, install the TGB front supp ort (s).

- Install the TGB as per AMM Task 65-21-00, 4-2 wit hout connecting the pitch-change links.

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1

50

51

5 3 4

6 2 7 a



### 9

- 11

79 - 97 

## COUPE A

- A

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## PAGE LEFT BLANK INTENTIONALLYSBNo. AS350-01.00.66Revision 0 2013-01-30Page 23/80Revision 1 2013-02-15This document is available on the internet:www.eurocopter.com/techpubbPRE MODPRE MODPOST MODZone BZone CZone DFigure 2PRE MODPOST MODPOST MODZONE BZONE CZONE DSBNo. AS350-01.00.66Revision 0 2013-01-30Page 24/80Revision 1 2013-02-15This document is available on the internet:www.eurocopter.com/techpubPAGE LEFT BLANK INTENTIONALLYSBNo. AS350-01.00.66Revision 0 2013-01-30Page 25/80Revision 1 2013-02-15This document is available on the internet:www.eurocopter.com/techpub7vr245126513257222423222524512225313033g55151498edcf46101146demnpqijhhfgrkc272813128Figure 3G355SBNo. AS350-01.00.66Revision 0 2013-01-30Page 26/80Revision 1 2013-02-15This document is available on the internet:www.eurocopter.com/techpubPAGE LEFT BLANK INTENTIONALLY

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47

40

41

40

41 47

u u

Figure 4 

## DETAIL E E

5 x 30 mm

.2 x 1.18 in.

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w 39

x

Figure 5 

## Section H - H

(Figure 7)SBNo. AS350-01.00.66Revision 0 2013-01-30Page 29/80Revision 1 2013-02-15This document is available on the internet:www.eurocopter.com/techpub39u211415FFigure 6DETAIL F14152918COUPEG-G4228JJ445739G3553757G355277303130363843434530363873031COUPEH-H21G355392137355740414041u34ou/or49SBNo. AS350-01.00.66Revision 0 2013-01-30Page 30/80Revision 1 2013-02-15This document is available on the internet:www.eurocopter.com/techpubPAGE LEFT BLANK INTENTIONALLY

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### NOTE 8

For the crimping of crimp contacts (107), (108), (1 09), (132),

(134), (144) and (159), refer to paragraph 4.A.

For the crimping of pre-insulated round terminal lu gs (112),

refer to paragraph 4.B.

For the crimping of bushes (129), refer to paragrap h 4.C.

For the crimping of contacts (130), refer to paragr aph 4.D.

For the crimping of contacts (131), refer to paragr aph 4.E.

For the installation of extension leads (114) and ( 123), refer

to paragraph 4.F.

3.B.4.a. Helicopters equipped with the single hydra ulic system with multi-unit: Kit 350A07-5606-0171

3.B.4.a.1 Modification of the circuit breaker panel (Figure 14)

. Open panel "30 ALP".

. Remove the 5 A circuit breaker (aa) from panel "3 0 ALP".

. Install the new 7.5 A circuit breaker (115) in pl ace of the previously removed circuit breaker (aa).

. Close panel "30 ALP".

. Fill in the identification plate (116) using a pe rmanent marker as follows:

- in the "MODEL DESCR." space, write "350A",

- in the "ASSY.N°" space, write "08456500",

- in the "SERIAL N°" space, write the serial number of the "30ALP",

- in the "MFRG DATE" space, write the modification embodiment date.

. Affix the identification plate (116) close to the connection.

. Apply VERNELEC varnish (59) to the identification plate (116) once the ink is dry.

3.B.4.a.2 Modification of the console (Figures 15 a nd 16)

. Remove all the VNE labels (ab) or (ac) from the c entral post or the instrument panel.

. Clean the surface and affix VNE label (117) or (1 18) or (119) to the canopy's central post as per

Figure 15.

- Helicopters equipped with the sand filter:

. Move the "SAND FILT" button (ad) as per Figure 16 using an extraction tool (xx).

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Revision 1 2013-02-15 This document is available on the interne t: www.eurocopter.com/techpub 3.B.4.a.3 Modification of the wiring (Figures 8, 10 , 12, 13 and 17)

- Addition of electrical grounding module 144N (Fig ure 10):

. Back drill as per Figure 10.

. Strip the contact surface between frame X4390 and the grounding module (106) over a diameter of

16mm (0.63 in.).

. Apply conductive paste (60) to the contact surfac es between the grounding module (106) and the

structure.

. Install the grounding module (106) and secure it using the washer (122) and the self-locking hexagon al

nut (121).

. Tighten the self-locking hexagonal nut (121) to s tandard torque.

. Clean the surface and affix label 144N (120) clos e to the grounding module (106).

. Apply VERNELEC 43022 varnish (59) to label 144N ( 120).

- Wiring of electrovalve "9D" (x) (Figures 8 and 17 ):

. Make a bundle from the batch of wires (124), shea th it using the NOMEX sheath (151).

. Install the grommet (110) on the NOMEX sheath (15 1) (Figure 17).

. Crimp the pre-insulated round terminal lugs (112)

.



### CAUTION

PAY PARTICULAR ATTENTION WHEN

CONNECTING ELECTROVALVE “9D”: TAKE INTO

ACCOUNT THE POLARITY.

. Carry out the connection of electrovalve "9D" (x) on a workbench as per Figures 8 and 17.

. Install the grommet (110) on electrovalve "9D" (x ).



### CAUTION

WHEN CRIMPING THE ELECTROVALVE "9D"

COWLING CLOSURE NUT (x3), TAKE CARE NOT

TO CRUSH THE CIRCULAR LABEL (x1).

. Install electrovalve "9D" (x) with its circular l abel (x1), its washer (x2) and its nut (x3).

. Lock the nut (x3) using the lockwire (55).

. Route the previously made harness following the e xisting routing and protect the zones subject to

rubbing using sheath DR25 (152) (not shown in Figur e 17).

. Carry out the connections of connector “104DEL-J1 D” using the crimp contacts (109) (Figure 8).

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. Route the wires in the wire batch (111) following the existing routing in the NOMEX sheath (151) and

protect the zones subject to rubbing using sheath D R25 (152).

. Carry out the connections using crimp contacts (1 07) and (108) (Figure 8).

. Install the extension lead (114).

- Wiring of relay "47D" (Figure 8):

. Disconnect the wire from the A3 terminal of relay "47D" and plug it using the cap (113).

. Attach using binding clamps (154), (155) and (156 ).

- Modification of the sand filter wiring (Figures 1 2 and 13):

. Carry out the wiring modifications of connector “ 134ALP – P1” as per Figures 12 and 13.

. Attach using binding clamps (154), (155) and (156 ).

- Electrical continuity check:

. Carry out an electrical continuity check of the m odified and added wiring.

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### NOTE 9

For helicopters equipped with the single hydraulic system

with SMS unit on which the power supply wires of

electrovalve “9D” (“1DH50F” and “1DH51NF”) are not yet

installed: comply with paragraphs 3.B.4.b.1 to 3.B. 4.b.5.

For helicopters equipped with the single hydraulic system

with SMS unit on which the power supply wires of

electrovalve “9D” (“1DH50F” and “1DH51NF”) are alre ady

installed: comply with paragraphs 3.B.4.b.6 to 3.B. 4.b.7.

3.B.4.b.1. Modification of the VNE label (Figure 15 )

. Remove all the VNE labels (ab) or (ac) from the c entral post or instrument panel.

. Clean the surface and affix VNE label (117) or (1 18) or (119) on the canopy's central post as per

Figure 15.

3.B.4.b.2. Addition of grounding module 144N (Figur e 10):

. Back drill as per Figure 10.

. Strip the contact surface between frame X4390 and the grounding module (106) over a diameter of

16mm (0.63 in).

. Apply conductive paste (60) to the contact surfac es between the grounding module (106) and the

structure.

. Install the grounding module (106) and secure it using the washer (122) and the self-locking hexagon al

nut (121).

. Tighten the self-locking hexagonal nut (121) to s tandard torque.

. Clean the surface and affix label 144N (120) clos e to the grounding module (106).

. Apply VERNELEC 43022 varnish (59) to label 144N ( 120).

3.B.4.b.3. Wiring of electrovalve “9D” (Figures 9 a nd 17)



### CAUTION

PAY PARTICULAR ATTENTION WHEN

CONNECTING ELECTROVALVE "9D": TAKE INTO

ACCOUNT THE POLARITY.

. Carry out the wiring with the wire batch (157) as per Figures 9 and 17.

. Sheath using NOMEX sheath (151).

. Install the grommet (110) on the NOMEX sheath (15 1).

. Carry out the connections using the pre-insulated round terminal lugs (112) and the crimp contacts

(107), (108) and (109).

. Install the extension lead (114).

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### CAUTION

WHEN CRIMPING THE ELECTROVALVE "9D"

COWLING CLOSURE NUT (x3), TAKE CARE NOT

TO CRUSH THE CIRCULAR LABEL (x1).

. Install electrovalve "9D" (x) with its circular l abel (x1), its washer (x2) and its nut (x3).

. Lock the nut (x3) using the lockwire (55).

3.B.4.b.4. Wiring of relay “47D” (Figure 9):

. Disconnect the wire from terminal A3 of relay “47 D” and plug it using the cap (113).

. Attach using the binding clamps (154), (155) and (156).

3.B.4.b.5. Electrical continuity check:

. Carry out an electrical continuity check of the m odified and added wiring.

3.B.4.b.6. Modification of the VNE label (Figure 15 )

. Remove all the VNE labels (ab) or (ac) from the c entral post or instrument panel.

. Clean the surface and affix VNE label (117) or (1 18) or (119) on the canopy's central post as per

Figure 15.

3.B.4.b.7. Wiring of electrovalve “9D” (Figures 17, 26 and 27)



### CAUTION

PAY PARTICULAR ATTENTION WHEN

CONNECTING ELECTROVALVE "9D": TAKE INTO

ACCOUNT THE POLARITY.

. Carry out the wiring as per Figures 26 and 27 (ac cording to configuration) and Figure 17.

. Carry out the connections using the pre-insulated round terminal lugs (112).

. Install the extension lead (114).

. Carry out an electrical continuity check of the m odified and added wiring.



### CAUTION

WHEN CRIMPING THE ELECTROVALVE "9D"

COWLING CLOSURE NUT (x3), TAKE CARE NOT

TO CRUSH THE CIRCULAR LABEL (x1).

. Install electrovalve "9D" (x) with its circular l abel (x1), its washer (x2) and its nut (x3).

. Lock the nut (x3) using the lockwire (55).

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3.B.4.c.1. Modification of circuit breaker panels ( Figures 14 and 18)

. Open panel "31ALP32" and remove the blank from t he plate in order to position the new circuit break er

(136) (Figure 18).

. Install the circuit breaker (136) on panel "31AL P32".

. Replace the former label with the label marked " HYD" (137) as per Figure 18.



### NOTE 10

Panel "31ALP32" will be closed at the end of paragr aph

3.B.4.c.3.

. Open panel "30ALP".

. Remove the 5 A circuit breaker (aa) from panel " 30ALP" (Figure 14).

. Install the new 7.5 A circuit breaker (115) in p lace of the previously removed circuit breaker (aa)

. . Close panel "30ALP".

. Fill in the identification plate (116) using a pe rmanent marker as follows:

- in the "MODEL DESCR." space, write "350A",

- in the "ASSY.N°" space, write "08456500",

- in the "SERIAL N°" space, write the serial number of the 30ALP,

- in the "MFRG DATE" space, write the modification embodiment date.

. Affix the identification plate (116) close to the connection.

. Apply VERNELEC varnish (59) to the identification plate (116) once the ink is dry.

3.B.4.c.2. Modification of the console (Figures 12, 13, 15, 16, 19 and 23)

- Helicopters equipped with the optional sand filte r (Figures 12, 13 and 16):

. Move the "SAND FILT" button (ad) as per Figure 16 using an extraction tool (xx).

- Modification of the sand filter wiring (all versi ons concerned):

. Carry out the wiring modifications as per Figures 12 and 13.

. Attach using binding clamps (154), (155) and (156 ).

. Carry out an electrical continuity check on the m odified wiring.

- Helicopters equipped with the dual hydraulic syst em with multi-unit (Figures 15, 19 and 23):

. Remove the "SERVO TST" (“50D”) button (ae) as per Figure 19.



### NOTE 11

The socket of push-button "50D" will be reused when

wiring push-button “49D”.

. Disconnect connector “134ALP – P1”.

. Modify the wiring as per Figure 23 using the cont acts (132).



### NOTE 12

Reroute the wires of indicator light "50D" from the strap so

as to gain in length and connect them to connector

“134ALP-P1”.

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. Clean the surface and affix the “50D” label of th e marker batch (138).

. Remove all the VNE labels (ab) or (ac) from the c entral post or from the instrument panel.

. Clean the surface and affix VNE label (117) or (1 18) or (119) on the canopy's central post as per

Figure 15.

3.B.4.c.3. Modification of the wiring (Figures 7, 1 0, 17, 21 and 22)

- Addition of electrical ground 144N (Figure 10):

. Back drill as per Figure 10.

. Strip the contact surface between frame X4390 and the grounding module (106) over a diameter of

16mm (0.63 in).

. Apply conductive paste (60) to the contact surfac es between the grounding module (106) and the

structure.

. Install the grounding module (106) and secure it using the washer (122) and the self-locking hexagon al

nut (121).

. Tighten the self-locking hexagonal nut (121) to s tandard torque.

. Clean the surface and affix label 144N (120) clos e to the grounding module (106).

. Apply VERNELEC 43022 varnish (59) to label 144N ( 120).

- Wiring of electrovalve "9D" (x) (Figures 17 and 2 2):

. Make a bundle from the batch of wires (124), shea th it in the NOMEX sheath (151).

. Install the grommet (110) on the NOMEX sheath (15 1).

. Crimp the pre-insulated round terminal lugs (112)

.



### CAUTION

PAY PARTICULAR ATTENTION WHEN

CONNECTING ELECTROVALVE “9D”: TAKE

INTO ACCOUNT THE POLARITY.

. Carry out the connection of electrovalve "9D" (x) on a workbench as per Figures 22 and 17.

. Install the grommet (110) on electrovalve "9D" (x ).



### CAUTION

WHEN TIGHTENING THE ELECTROVALVE "9D"

COWLING CLOSURE NUT (x3), TAKE CARE NOT

TO CRUSH THE CIRCULAR LABEL (x1).

. Install electrovalve "9D" (x) with its circular l abel (x1), its washer (x2) and its nut (x3).

. Lock the nut (x3) using the lockwire (55).

. Route the previously made harness following the e xisting routing and protect the zones subject to

rubbing using sheath DR25 (152) (Not shown in Figur e 17).

. Carry out the connections of connector “104DEL-J1 D” using the crimp contacts (109) (Figure 22).

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Revision 1 2013-02-15 This document is available on the interne t: www.eurocopter.com/techpub - Wiring of connector "104DEL - P1D" (Figure 22):

. Route wires "1DH161NE" and "1DH160E" of the wire batch (135) following the existing routing and

protect the zones subject to rubbing using sheath D R25 (152) (Not shown in Figure 22).

. Carry out the connections using crimp contacts (1 07) and (108).

. Attach using binding clamps (154), (155) and (156 ).

- Modification of the wiring of panel “30ALP” (Figu res 7 and 21):

. Modify the wiring of panel “30ALP” as per Figure 21 using the contact (130) and the NOMEX

sheath (151).



### NOTE 13

If wire "1DH78F" installed on the helicopter is too short,

remove and replace it with wire "1DH78F" from wire batch

(135).

If required, replace the extension lead (123).

- Modification of the wiring of push-button “49D” (Figures 7, 19 and 22):

. Using the wire and marker batch (135), route the wires and carry out the connections as per Figure 2 2

using crimp contacts (107), (108), (131), (132), (1 34) and the bushes (129).



### NOTE 14

For the wiring of the socket of push-button “49D”, use the

socket extracted during disconnection of push-butto n "50D".

If necessary, replace the socket of "49D" with sock et (133).

. Position the " ACCU TST" button ("49D") (139), it s single sleeve (140) and its protective cover (141 ) as

per Figure 19.

. Clean the surface and affix the "49D" marker batc h (138) label.

. Attach using binding clamps (154), (155) and (156 ) and reposition the identification sleeves if prev iously

removed.

. Close panel "31ALP32" opened during compliance wi th paragraph 3.B.4.c.1.

- Electrical continuity check:

. Carry out an electrical continuity check of the m odified and added wires.

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### NOTE 15

For helicopters equipped with the dual hydraulic sy stem with

SMS unit on which the power supply wires of electro valve

“9D” (“1DH50F” and “1DH96NF”) are not yet installed :

comply with paragraphs 3.B.4.d.1. to 3.B.4.d.6.

For helicopters equipped with the dual hydraulic sy stem with

SMS unit on which the power supply wires of electro valve

“9D” (“1DH50F” and “1DH96NF”) are already installed :

comply with paragraphs 3.B.4.d.7. to 3.B.4.d.9.

3.B.4.d.1. Modification of the circuit breaker pane ls (Figures 18 and 20)

. Open panel "31ALP32" and remove the blank from th e plate in order to position the new circuit breake r

(136) (Figure 18).

. Install the circuit breaker (136) on panel "31AL P32".

. Replace the former label with the label marked " HYD" (137) according to Figure 18.



### NOTE 16

The panel "31ALP32" will be closed at the end of pa ragraph

3.B.4.d.4.

. Remove the 2.5 A circuit breaker (af) from panel "30ALP" (Figure 20).

. Position the new 6 A circuit breaker (147) in pla ce of the previously removed circuit breaker (af).

3.B.4.d.2. Modification of the console (Figures 15 and 20)

. Position the "ACCU TST" pushbutton (145) and its protective flap (146) as per Figure 20.

. Remove all the VNE labels (ab) or (ac) from the c entral post or the instrument panel.

. Clean the surface and affix VNE label (117) or (1 18) or (119) on the canopy's central post as per

Figure 15.

3.B.4.d.3. Addition of grounding module 144N (Figur e 10):

. Back drill as per Figure 10.

. Strip the contact surface between frame X4390 and the grounding module (106) over a diameter of

16mm (0.63 in).

. Apply conductive paste (60) to the contact surfac es between the grounding module (106) and the

structure.

. Install the grounding module (106) and secure it using the washer (122) and the self-locking hexagon al

nut (121).

. Tighten the self-locking hexagonal nut (121) to s tandard torque.

. Clean the surface and affix label 144N (120) clos e to the grounding module (106).

. Apply VERNELEC 43022 varnish (59) to label 144N ( 120).

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### CAUTION

PAY PARTICULAR ATTENTION WHEN

CONNECTING ELECTROVALVE “9D”: TAKE

INTO ACCOUNT THE POLARITY.

. Carry out the wiring with the wire batch (158) as per Figures 25 and 17.

. Sheath in NOMEX sheath (151).

. Install the grommet (110) on the NOMEX sheath (15 1).

. Carry out the connections using the crimp contact s (107), (108), (109), (144) and (159), the pre-ins ulated

round terminal lugs (112) and the bush (129).



### CAUTION

WHEN CRIMPING THE “9D” ELECTROVALVE

COWLING CLOSURE NUT (x3), TAKE CARE NOT

TO CRUSH THE CIRCULAR LABEL (x1).

. Install electrovalve "9D" (x) with its circular lab el (x1), its washer (x2) and its nut (x3).

. Lock the nut (x3) using the lockwire (55).

. Close panel "31ALP32" opened during compliance wi th paragraph 3.B.4.d.1.

3.B.4.d.5. Wiring modification of panel “30ALP” (Fi gure 25):

. Modify the wiring of panel “30ALP“ as per Figure 25 using the contact (130) and NOMEX sheath (151).



### NOTE 17

If wire “1DH78F” installed on aircraft is too short , remove

and replace it with wire “1DH78F” from wire batch ( 158).

If necessary, replace the extension lead (123).

3.B.4.d.6. Electrical continuity check:

. Carry out an electrical continuity check of the m odified and added wiring.

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. Open panel "31ALP32" and remove the blank from th e plate in order to position the new circuit breake r

(136) (Figure 18).

. Install the circuit breaker (136) on panel "31AL P32".

. Replace the former label with the label marked " HYD" (137) according to Figure 18.



### NOTE 18

The panel "31ALP32" will be closed at the end of pa ragraph

3.B.4.d.3.

. Remove the 2.5 A circuit breaker (af) from panel "30ALP" (Figure 20).

. Position the new 6 A circuit breaker (147) in pla ce of the previously removed circuit breaker (af).

3.B.4.d.8. Modification of the console (Figures 15 and 20)

. Position the "ACCU TST" pushbutton (145) and its protective flap (146) as per Figure 20.

. Remove all the VNE labels (ab) or (ac) from the c entral post or the instrument panel.

. Clean the surface and affix VNE label (117) or (1 18) or (119) on the canopy's central post as per

Figure 15.

3.B.4.d.9. Wiring of electrovalve “9D” (Figures 17 and 24)



### CAUTION

PAY PARTICULAR ATTENTION WHEN

CONNECTING ELECTROVALVE “9D”: TAKE INTO

ACCOUNT THE POLARITY.

. Modify the wiring as per Figures 17 and 24.

. Carry out the connections using the crimp contact s (130), (144), the pre-insulated round terminal

lugs (112), the cap (113) and the extension lead (1 23).

. Plug wire “1DH141E” on the “30ALP-P4” side using the cap (113).

. Carry out an electrical continuity check of the m odified and added wiring.



### CAUTION

WHEN CRIMPING THE “9D” ELECTROVALVE

COWLING CLOSURE NUT (x3), TAKE CARE NOT

TO CRUSH THE CIRCULAR LABEL (x1).

. Install electrovalve "9D" (x) with its circular lab el (x1), its washer (x2) and its nut (x3).

. Lock the nut (x3) using the lockwire (55).

. Close panel "31ALP32" opened during compliance wi th paragraph 3.B.4.d.7.

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- Check the yaw control adjustment at the TGB.

DO NOT MODIFY THE POSITION OF THE TAIL ROTOR

DURING THE COURSE OF THE FOLLOWING STEPS.

. Immobilize the tail rotor as per AMM Task 67-21-0 0, 5-1 (version without AP) or

67-21-01, 5-1 (version with AP).

. Make a temporary mark on the TGB and on the pitch -change spider in order to take measurements in

the same place.

. Measure the dimension in neutral (M) between the pitch-change spider and the TGB using a caliper

gage.

. Check the high pitch dimension by holding the RH pedal in the forward position so that the primary s top,

located in the baggage compartment, is in contact:

M - 19.8 mm +/- 0.5 mm (M - .78 +/- .02 in.)

. Check the low pitch dimension by holding the LH p edal in the forward position so that the primary st op,

located in the baggage compartment, is in contact:

M + 20.3 mm +/- 0.5 mm (M + .80 +/- .02 in.)

. Interpretation of the data:

- If the measurements are within tolerances, connec t the tail rotor pitch-change links as per AMM

Task 65-21-00,4-12b.

- If the measurements are not within tolerances, ad just the yaw control at the TGB as per AMM

Task 67-21-00, 5-1 (version without AP) or 67-21-01 , 5-1 (version with AP).

- Charge the accumulator (w) as per AMM Task 29-00- 00, 3-5.

- Check the load compensator and unions for leak-ti ghtness.

- Check the level of the hydraulic fluid and, if ne cessary, top it up as per AMM Task 29-00-00, 3-3.

- Balance the tail rotor as per AMM Task 64-10-00, 5-1a.

- Perform the electrical tests as per paragraph 4.G

.

3.B.6. Final steps

- Install the enlarged field-of-vision windows as p er AMM Task 56-11-00, 4-6.

- Install the nose-fairing hatch.

- Install the lower cowlings as per AMM Task 53-51- 00, 4-2.

- Remove the protection installed on the flux valve

. - For helicopters equipped with air conditioning:

. Install the condenser in the tail boom.

. Install the four attachment screws and the air du cts of the condenser as per AMM Task 21-51-10, 4-2.

- Install the rear closing panel in the baggage com partment.

- Close the load compensator inspection door.

- Install the tail rotor drive fairings.

- Install and/or close all cowlings, panels and doo rs and equipment removed and/or opened during the

preliminary steps (paragraph 3.B.1.).

- Remove the access equipment.

- Set helicopter into flight configuration.

3.B.7. Ground run/Flight test

- Carry out a test-run up as per FLM with an on-sit e crew.

- Perform a test flight as per FLM section 8 sheet 7 “VNE with power off” with an on-site crew. 

### C AUT ION

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### 3.C. IDENTIFICATION

Identification of this document:

Record compliance with this document, with the revi sion number, in the helicopter documents and on the

Log Cards of the tail rotor blades and the rotating pitch-change spider assembly.

Identification of modifications on the documentati on:

- Record the embodiment of modification 075606 in t he helicopter documents.

- Identify modification 075606 and the new part num bers on the Log Cards of the tail rotor blades and the

rotating pitch-change spider assembly as per MTC Wo rk Card 20.08.05.101.

Identification of modifications on the equipment:

Identify the parts / assemblies in accordance with the table below and/or MTC Work Card 20.08.05.103 a nd

AMM Task 64-10-00, 8-10:

Key Word Former P/N New P/N MOD Type of marking

Tail rotor blade

assembly 355A12-0055-02 355A12-0060-00 075606 Yellow ink + o n the

Log Card

Tail rotor blade

assembly 355A12-0055-03 355A12-0060-01 075606 Yellow ink + o n the

Log Card

Identify parts / assemblies as per table below and/ or as per MTC Work Card 20.08.05.103.

Key Word Former P/N New P/N MOD Type of marking

Rotating pitch-change

spider 350A33-2166-01 350A33-2166-02 075606 Vibro-engraved + on the Log Card

Tail rotor pitch-change

spider assembly 350A33-2167-00 350A33-2167-01 075606 with PHILLIPS ink

No. 7 + on the Log

Card

Tail Rotor servo-control 350A75-1050-1101 350A75-1050-1001 075606 with PHILL IPS ink

No. 7



### 3.D. OPERATING AND MAINTENANCE INSTRUCTIONS

Operating instructions:

Refer to the Flight Manual (FLM).

Remove the pages inserted during compliance with AL ERT SERVICE BULLETIN No. 01.00.65.

Insert the pages applicable post modification 07560 6 in place of the pages applicable pre

modification 075606.

Maintenance instructions:

Refer to the Master Servicing Manual (MSM) for main tenance of blades, tail rotor assembly and load

compensator :

- Pipes 704A34412260 (14) and 704A34412261 (15) sup plying the load compensator are post

modification 074239 and are therefore not subject t o the periodic replacement recommended by MSM

chapter 05-25.

Refer to ALS Chapter 04-20 for maintenance of the l aminated half-bearings.

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## PRE MOD

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112 109 108

114

110

113 107

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## PAGE LAISSEE INTENTIONNELLEMENT BLANCHESBNo. AS350-01.00.66Revision 0 2013-01-30Page 47/80Revision 1 2013-02-15This document is available on the internet:www.eurocopter.com/techpubFigure 9PRE MODPOST MOD114107108109112112113110 148SBNo. AS350-01.00.66Revision 0 2013-01-30Page 48/80Revision 1 2013-02-15This document is available on the internet:www.eurocopter.com/techpubPAGE LAISSEE INTENTIONNELLEMENT BLANCHESBNo. AS350-01.00.66Revision 0 2013-01-30Page 49/80Revision 1 2013-02-15This document is available on the internet:www.eurocopter.com/techpubFigure 101061211221061205960Ø 5,5 mm(0.22 in.)77P (Optional)SBNo. AS350-01.00.66Revision 0 2013-01-30Page 50/80Revision 1 2013-02-15This document is available on the internet:www.eurocopter.com/techpubPAGE LEFT BLANK INTENTIONALLYSBNo. AS350-01.00.66Revision 0 2013-01-30Page 51/80Revision 1 2013-02-15This document is available on the internet:www.eurocopter.com/techpubFigure 12PRE MODSBNo. AS350-01.00.66Revision 0 2013-01-30Page 52/80Revision 1 2013-02-15This document is available on the internet:www.eurocopter.com/techpubPAGE LEFT BLANK INTENTIONALLYSBNo. AS350-01.00.66Revision 0 2013-01-30Page 53/80Revision 1 2013-02-15This document is available on the internet:www.eurocopter.com/techpubFigure 13POST MODSBNo. AS350-01.00.66Revision 0 2013-01-30Page 54/80Revision 1 2013-02-15This document is available on the internet:www.eurocopter.com/techpubPAGE LEFT BLANK INTENTIONALLYSBNo. AS350-01.00.66Revision 0 2013-01-30Page 55/80Revision 1 2013-02-15This document is available on the internet:www.eurocopter.com/techpubFigure 14aa11511659POST MOD: 7,5APRE MOD: 5ASBNo. AS350-01.00.66Revision 0 2013-01-30Page 56/80Revision 1 2013-02-15This document is available on the internet:www.eurocopter.com/techpubPAGE LEFT BLANK INTENTIONALLYSBNo. AS350-01.00.66Revision 0 2013-01-30Page 57/80Revision 1 2013-02-15This document is available on the internet:www.eurocopter.com/techpubFigure 15117ou/or118ou/or119abacVNEPOWER ONHp (ft)IAS (kts)01552000149400014360001378000131100001251200011914000113160001071800010120000952200089POWER OFF:- 30 ktsSBNo. AS350-01.00.66Revision 0 2013-01-30Page 58/80Revision 1 2013-02-15This document is available on the internet:www.eurocopter.com/techpubPAGE LEFT BLANK INTENTIONALLY

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## PRE MOD

POST MOD ad

ad

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## PAGE LEFT BLANK INTENTIONALLYSBNo. AS350-01.00.66Revision 0 2013-01-30Page 61/80Revision 1 2013-02-15This document is available on the internet:www.eurocopter.com/techpubFigure 17112110124xGROUND9D151x1x2x3POSITIVE55SBNo. AS350-01.00.66Revision 0 2013-01-30Page 62/80Revision 1 2013-02-15This document is available on the internet:www.eurocopter.com/techpubPAGE LEFT BLANK INTENTIONALLY

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### 137 136

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## PRE MOD

POST MOD

139

140

141 50D

49D 50D 

### ae

ae

138

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### af

147

146 145

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## PRE MOD

POST MOD

130

151 123SBNo. AS350-01.00.66Revision 0 2013-01-30Page 67/80Revision 1 2013-02-15This document is available on the internet:www.eurocopter.com/techpubFigure 22148SBNo. AS350-01.00.66Revision 0 2013-01-30Page 68/80Revision 1 2013-02-15This document is available on the internet:www.eurocopter.com/techpubPAGE LEFT BLANK INTENTIONALLY

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## PRE MOD

POST MOD 50D 50D

- P1

134ALP

- P1

50D

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## PAGE LEFT BLANK INTENTIONALLYSBNo. AS350-01.00.66Revision 0 2013-01-30Page 71/80Revision 1 2013-02-15This document is available on the internet:www.eurocopter.com/techpubTo 22ALP (See WiringDiagrams manual)1DH178F.REP22981DH78E1DH141E.REP22981DH78E1DH94E1DH93NE1DH50E1DH50F1DH96NE1DH96NFPRE MODPOST MOD.REP22981DH178E1DH96NE1DH96NF1DH50F1DH50E1DH93NE1DH94E1DH141E.REP28001DH178E1DH78F.REP2298112144 113130 123149To 22ALP (See WiringDiagrams manual)Figure 24SBNo. AS350-01.00.66Revision 0 2013-01-30Page 72/80Revision 1 2013-02-15This document is available on the internet:www.eurocopter.com/techpubPAGE LEFT BLANK INTENTIONALLY

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## PRE MOD

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107

109 112 112

129

159

144 108

110

DR20

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## PRE MOD

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### 114 112 148 

## PRE MOD

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### 4. APPENDIX

4.A. CRIMPING OF CONTACTS P/N EN3155****

P/N Size Pliers M22520/ or equivalent Tool INS/EXT

M81969

Gage 1-01 Adj. 2-01 Adj. 7-01 Adj. P/N Col.(*)

EN3155

- 003F1614 16 20 7.04 7 14.03 Bl/Wh

EN3155

- 003F2020 20 20 2.10 6 7.08 6 14.11 Re/Wh

EN3155

- 003F2222 22 22 2.06 4 7.06 3 14.10 Gr/Wh

EN3155

- 008M2020 20 20 2.10 6 7.08 6 14.10 Re/Or

EN3155

- 015F2018 20 20 2.08 7 86-79 6 39.01 Re/Wh

EN3155

- 016M2018 20 20 2.02 7 7.02 6 14.11 Re/Wh

22 2.02 6 7.02 5 14.11 Re/Wh

EN3155

- 016M2222 22 22 EN4008-007 3 86-325 4 14.01 Gr/Wh

EN3155

- 018M2020 20 20 2.02 7 7.02 6 14.11 Re/Wh

EN3155

- 019F2020 20 20 2.02 7 7.02 6 14.11 Re/Wh

(*) Color: Re (Red), Wh (White), Or (Orange), Bl ( Blue), Gr (Green).



### 4.B. CRIMPING OF PRE-INSULATED ROUND TERMINAL LUGS P/N NSA936501******

P/N Gage Color AMP P/N

NSA936501TA2006 20 GREY 152659

Tool: Pliers AMP 576779



### 4.C. CRIMPING OF BUSHES P/N 130743-1

P/N Gage Stripped

length Pliers Extraction tool

130743

- 1 22 to 18 6.3 mm 45098 305183

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### 4.D. CRIMPING OF CONTACTS P/N 350689-3

P/N Gage Stripped

length Pliers Extraction tool

350689

- 3 20-24 4 mm 654 148-1 458994-1



### 4.E. CRIMPING OF CONTACTS P/N 001714-120-02

P/N Gage Pliers Positioner INS/EXT

001714

- 120

- 02 22/24 M22520/2-01 M22520/2-06 00111210025



### 4.F. EXTENSION LEADS ASN E0541-XX

P/N Max. number

of wires on

one side Max. number

of wires on

the other

side Stripping length of

the wire (mm) Pliers AD-1377S or GTM

232 (M22520/37-01) imprint

ASN E0541-11 2 2 7 +/- 0.5 Blue

16-20

ASN E0541-12 2 2 7 +/- 0.5 Yellow

12-16

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### 4.G. ELECTRICAL INSTALLATION TESTS

4.G.1. Helicopters equipped with the single hydraul ic system with multi-unit

The check for voltage at the hydraulic valves can b e carried out as follows:

- The solenoid of the valve becomes magnetized when power is applied (a metallic object is magnetized

when placed close to the valve).

- Wait a few seconds between two actuations in orde r to prevent residual magnetization.

** Ground the attachment screws of each solenoid in o rder to prevent any reversal of polarity.

ACTION CHECK

1 - Set the HORN control to ON

- Energize the helicopter. - The "HYDR" caption light on the warning panel is on

2 - On the pilot's collective pitch stick,

set the hydraulic control switch to

the rear position - The following equipment is powered by 28Vdc:

Front Servo-valve (21D1), RH Servo-valve (21D2), LH

Servo-valve (21D3), Regulation valve (21D) **

- The following equipment is not powered by 28Vdc: Rear

Servo-valve (9D)

3 - Open circuit-breaker HYD (7.5A)

30 ALP - The following equipment is not powered by 28Vdc

Front Servo-valve (21D1), RH Servo-valve (21D2), LH

Servo-valve (21D3), Regulation Valve (21D)

4 - Close circuit-breaker HYD (7.5A)

30 ALP - The following equipment is powered by 28Vdc:

Front Servo-valve (21D1), RH Servo-valve (21D2), LH

Servo-valve (21D3), Regulation valve (21D) **

- The following equipment is not powered by 28Vdc: Rear

Servo-valve (9D)

5 - On the pilot's collective pitch stick,

set the hydraulic control switch to

the front position - The following equipment is not powered by 28Vdc:

Front Servo-valve (21D1), RH Servo-valve (21D2), LH

Servo-valve (21D3), Regulation valve (21D) and Rear

Servo-valve (9D)

6 - On the console, press pushbutton

"ACCU TST" (49D), it remains in +

function feedback "ON" comes on - The "HYDR" caption light on the warning panel fla shes

+ audio alarm in the headset

- The following equipment is not powered by 28Vdc:

Front Servo-valve (21D1), RH Servo-valve (21D2), LH

Servo-valve (21D3)

- The following equipment is powered by 28Vdc:

Regulation Valve (21D) and Rear Servo-valve (9D)

7 - On the console (30 α ), press

pushbutton "ACCU TST" (49D), it

remains out - The "HYDR" caption light on the warning panel sto ps

flashing

- The following equipment is not powered by 28Vdc:

Front Servo-valve (21D1), RH Servo-valve (21D2), L H

Servo-valve (21D3), Regulation valve (21D) and Rear

Servo-valve (9D)

8 - Disconnect the 29 D pressure switch

connector - The "HYDR" caption light on the warning panel goe s out

9 - Reconnect the 29D hydraulic

pressure switch connector - The "HYDR" caption light comes on

- Audio alarm (GONG) in the headset

10 - De-energize the helicopter.

- For the version with dual control, repeat the tes t with the copilot's collective pitch stick.

# SB No. AS350-01.00.66

Revision 0 2013-01-30 Page 79/80

Revision 1 2013-02-15 This document is available on the intern et: www.eurocopter.com/techpub 4.G.2. Helicopters equipped with the dual hydraulic system with multi-unit

ACTION CHECK

1 - Set the BATT switch to the ON position - The "SER VO" and "HYDR" caption lights on the

warning panel are on

2 - On panel 134 α , press pushbutton "SERVO

TST" - The "SERVO" caption light on the warning panel

goes out

3 - Release pushbutton "SERVO TST" - The "SERVO" capt ion light on the warning panel

comes on

4 - Disconnect the RH servo-control (1D3) - The “LIM IT” caption light on the instrument panel

comes on

5 - Disconnect the LH (1D2) and front (1D1)

servo-controls and short the following

terminals: 2 and 4 from 1D3, 1 and 4 from

1D2, 1 and 4 from 1D1 - The "SERVO" caption light on the warning panel

goes out

- "LIMIT" stays on

6 - Set the lighting control to NIGHT - The "LIMIT" caption light comes on in the dimming

mode (as well as the warning panel)

7 - On 31 α 32, remove circuit-breaker "HYD"

(2.5A) - The "LIMIT" caption light on the warning panel go es

out

8 - On 31 α 32, reinstall circuit-breaker "HYD" - The “LIMIT” c aption light on the warning panel

comes on

9 - Disconnect the 3D2 hydraulic pressure switch - The "HYDR" caption light on the warning panel

stays on

10 - Disconnect the 3D1 hydraulic pressure switch - The "HYDR" caption light on the warning panel

goes out

11 - Reconnect the 3D2 hydraulic pressure switch - The "HYDR" caption light on the warning panel

comes on

12 - Reconnect the 3D1 hydraulic pressure switch - The "HYDR" caption light on the warning panel

stays on

13 - Remove the shunts and reconnect the

servo-controls.

- On 49D, press the "ACCU" pushbutton - The terminals of the 9D yaw servo-control are

powered by 28V

14 - On 30 α , remove circuit-breaker HYD (7.5A) - The voltage d isappears at the terminals of the 9D

yaw servo-control

15 - On 49D, release "ACCU"

- Reinstall circuit-breaker HYD (7.5A)

16 - Set the HYD switch on the collective pitch

stick to ON - Using a metallic object, check that the electrova lve

(2D) is magnetized

17 - Open circuit breaker HYD 2.5A on 31 α 32 - The electrovalve is no longer magnetized

18 - Close circuit breaker HYD 2.5A on 31 α 32 - The electrovalve is magnetized again

19 - Restore the helicopter's initial configuration

# SB No. AS350-01.00.66

Revision 0 2013-01-30 Page 80/80

Revision 1 2013-02-15 This document is available on the intern et: www.eurocopter.com/techpub 4.G.3. Helicopters equipped with the SMS unit

The check for voltage at the hydraulic valves can b e carried out as follows:

- The solenoid of the valve becomes magnetized when power is applied (a metallic object is magnetized

when placed close to the valve).

- Wait a few seconds between two actuations in orde r to prevent residual magnetization.

** Ground the attachment screws of each solenoid in o rder to prevent any reversal of polarity.

ACTION CHECK

1 - Set the HORN control to ON

- Energize the helicopter. - The "HYD" caption light on the warning panel is o n

2 - On the pilot's collective pitch stick,

set the hydraulic control switch to the

rear position - The following equipment is powered by 28Vdc:

Front Servo-valve (21D1), RH Servo-valve (21D2), LH

Servo-valve (21D3), Regulation valve (21D) **

- The following equipment is not powered by 28Vdc:

Rear Servo-control (9D)

3 - On the pilot's collective pitch stick,

set the hydraulic control switch to the

front position - The following equipment is not powered by 28Vdc:

Front Servo-valve (21D1), RH Servo-valve (21D2), LH

Servo-valve (21D3), Regulation valve (21D) and Rear

Servo-valve (9D)

4 - On the console (30 α ), press

pushbutton "ACCU TST", it remains

in - The "HYD" caption light on the warning panel flas hes

- The following equipment is not powered by 28Vdc:

Front Servo-valve (21D1), RH Servo-valve (21D2), LH

Servo-valve (21D3)

- The following equipment is powered by 28Vdc:

Regulation Valve (21D) and Rear Servo-valve (9D)

5 - On the console (30 α ), press the

"ACCU TST" pushbutton, it remains

out - The "HYD" caption light on the warning panel stop s

flashing

- The following equipment is not powered by 28Vdc:

Front Servo-valve (21D1), RH Servo-valve (21D2), LH

Servo-valve (21D3), Regulation valve (21D) and Rear

Servo-valve (9D)

6 - Disconnect the connector of the 29D

pressure switch - The "HYD" caption light on the warning panel goes out.

7 - Reconnect the connector of the 29D

hydraulic pressure switch - The "HYD" caption light comes on

- Audio alarm (GONG) in the headset

8 - De-energize the helicopter.

- For the version with dual control, repeat the tes t with the copilot's collective pitch stick.