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 addition of a load compensator on 

the yaw channel on helicopters which are POST modification 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 control 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 with 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 equipped with an Arriel 2D engine but not embodying 

modification 075606 (subject of this Service Bulletin). 

NOTE 1 

Refer to the aircraft individual inspection record (MOD 

record) and the aircraft log book to identify the actual 

configuration of the helicopter. 

1.A.2. Non-installed equipment 

Not applicable. 

1.B. ASSOCIATED REQUIREMENTS 

Previous embodiment of modification 076604 (Modification 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 the 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 the 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 embodying modification 075606. To do so, the following 

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 rotating pitch-change spider and the rotating pitch-change

spider assembly. 

- Modification of the tail rotor flight control linkage in order to be able to install a load compensator. 
 

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- Modification of the electrical installation: 

NOTE 2 

The modification of the electrical installation depends on the 

helicopter configuration. 

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

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

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

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

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

helicopter documents and on the components concerned. 

- 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 subsidiaries 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, issued 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 modification 075606 which was approved on January 21, 2013 by 

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 Design Organization Approval No. 21J.056 for helicopters 

of civil versions subject to an Airworthiness Certificate. 

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

on February 15, 2013 under the authority of EASA Design Organization Approval No. 21J.056 for helicopters 

of civil versions subject to an Airworthiness Certificate. 

1.G. MANPOWER 

For compliance with this Service Bulletin, EUROCOPTER recommends the following personnel 

qualifications: 

Qualification: - 2 Mechanical Engineering Technicians 

 - 1 Electrical Engineering Technician 

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

Time for the operations: - approximately 176 hours for the Mechanical Engineering Technicians 

 - approximately 24 hours for the Electrical Engineering 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 an 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 - Molykote product usage procedure 

MTC: 20.02.01.410: General - Installation of crimped terminal lugs on cables 

MTC: 20.02.01.411: General - Cable binding methods 

MTC: 20.02.01.415: General - Installation of electrical cable bundles 

MTC: 20.02.01.418: General - Protection of electrical wiring during maintenance operations 

MTC: 20.02.05.404: Joining - Joining by bolts and nuts 

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 procedure 

MTC: 20.02.07.403: Electrical Bonding - Use of Vernelec 43022 varnish 

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

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

MTC: 20.05.01.211: General sealing procedures - Sealing 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 - Instructions applicable during maintenance operations on 

hydraulic systems 

MTC: 20.07.03.406: Technical instructions - Instructions applicable when working on an aircraft electrical 

circuit and power generating systems 

MTC: 20.07.03.408: Technical instructions - Appearance checks on an aircraft after an inspection or repair 

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

MTC: 20.08.05.103: General rules applicable to aircraft - 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: preparation of EC2216 or CN EC2216 adhesive 

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

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

AMM: 29-00-00, 3-1: Hydraulic Power - General Safety 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 / Draining - Hydraulic System (Single power system) or (Twin 

power system) 

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

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

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

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

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

AMM: 64-10-00, 8-22: Tail Rotor Blade - Removal / Installation - 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 - TGB 

AMM: 65-21-00, 4-12b: Tail Gearbox - Removal/Installation - 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 - Rigging - Tail Rotor Flight Controls (Version without 

Auto-Pilot) 

AMM: 67-21-01, 5-1: Tail Rotor Flight Controls - Rigging - Tail Rotor Flight Controls (Version with Auto-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 future revision. 

Documents already updated 

The modifications have been integrated by EUROCOPTER 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 not interchangeable. 

 Mixability: 

Mixability of pre- and post-modification parts is prohibited. 
 

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2. MATERIAL INFORMATION 

2.A. MATERIAL: PRICE - AVAILABILITY - PROCUREMENT 

For any information concerning the kits and/or components, 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 mode of 

transport, the destination and the serial numbers of the 

helicopters to be modified. 

2.B. INFORMATION CONCERNING INDUSTRIAL SUPPORT 

The work will be performed by EUROCOPTER specialists. 

 

Inform EUROCOPTER of the configuration of the helicopters to be modified by specifying the following 

information: 

- Helicopter type and version, 

- S/N of the helicopter, 

- Single/dual hydraulic system (pre or post modification 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/COMPONENT 

 Kits or components to be ordered for one helicopter 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 kit 350A07-

5606-0171. 

For helicopters equipped with the single hydraulic system 

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

5006-0271. 

For helicopters equipped with the dual hydraulic system with 

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

5606-0371. 

For helicopters equipped with the dual hydraulic system with 

SMS unit: order kit 350A-5606-0071 and kit 350A07-5006-

0471. 

NOTE 3 

As the kits are the same for versions B3 and C3, items 

(100), (101), (102), (103), (104) and (105) will not 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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Material to be ordered separately for compliance with Revision 1: 

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 INTERTURBINE AVIATION LOGISTICS company. 

 

Website: http://www.interturbine.com

 Telephone: +49.41.91.809.300 

AOG: +49.41.91.809.444 
 

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 Special tools: 

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 concerning electrical power as per AMM Task 24-00-00, 3-1. 

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

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

Read and comply with the general instructions concerning 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 safetying with lockwire as per MTC Work 

Card 20.02.06.402. 

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

Card 20.02.06.404. 

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

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

Read and comply with the instructions concerning the installation of crimped terminal lugs on cables as per 

MTC Work Card 20.02.01.410. 

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

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

Card 20.02.01.415. 

Read and comply with the instructions concerning the protection of electrical wiring during maintenance as 

per MTC Work Card 20.02.01.418. 

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

Card 20.02.07.101. 

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

Card 20.02.07.401. 

Read and comply with the instructions for use of VERNELEC 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 inspection 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 compartment. 

- Remove and/or open all cowlings, panels, doors and equipment required to gain access to the different 

work areas. 
 

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- For helicopters equipped with air conditioning: 

NOTE 1 

It is not necessary to disconnect the freon pipes. 

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

. Move the condenser forward in the baggage compartment. 

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

- 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 per 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 AMM Task 64-10-00,8-22. 

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

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

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

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

. Install the blank (5) using the washer (7), the nut (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 blanks (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 the 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 which have already been touched up using primer (54) and 

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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3.B.3. Modification of the tail rotor flight control linkage (Figures 3 to 6) 

 

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 rotor 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 servo-control (c): 

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

- Remove and discard the screws (m) and the upper washers (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 removed. 

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 order to increase the lateral travel. 

CAUTION

s 

t 
 

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. When extracting the long rod (k), protect the structural 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 compensator 

- On a workbench: 

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

. Position the ball-joint of the long rod (26) so that 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 reamer (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 is 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) on the tail rotor servo-control (c): 

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

. Install the manifold (f). 

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

. Tighten the banjo bolts (g). 

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

CAUTION

y 
 

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- Install the plastic rivets (40) (Figure 4) with the washers (41). 

- Install teflon tapes (47) on either side of the support (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 retractable part of the long rod (26) and the smooth 

part of the screws (24). 

. Engage the front tip of the long rod (26) into the 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 front 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 smooth 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 front 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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Installation of the load compensator 

- Install the load compensator: 

NOTE 5 

The load compensator comprises the hydraulic actuator 

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 groove 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 actuator 

end (21). 

. Lubricate the smooth part of the bolt (35) with grease (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 structure support (u) (Section H-H, Figure 6): 

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

- Install the bolt (37), the washer (36) and the nut (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 lever (39) and the sleeve (27). 

- Install the spacers (43). 

- Lubricate the smooth part of the bolt (44) with grease (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 freely. 

- 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 of the lever (39) in order to center it in the opening 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 nut (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 screw heads and attachment nuts as per MTC Work 

Card 20.01.01.312. 
 

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- Remove the blanks (zz) (not shown). 

- Connect pipes (14) and (15) to Tee unions (12) and (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) and (15) (Detail F, Figure 6). 

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

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

NOTE 7 

The position of bearing No. 1 must be adjusted so as 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 support (s). 

- Install the TGB as per AMM Task 65-21-00, 4-2 without connecting the pitch-change links. 
 

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Figure 1 

a 

1 

50 

51

5

4 3 

7 2 6 

a 

9 - 11

79 - 97 

COUPE A-A
 

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b

PRE MOD 

Zone B Zone C 

Zone D 

Figure 2 

PRE MOD 

POST MOD 

POST MOD 

ZONE B 

ZONE C 
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7 

r 

32 57 

22 

24 

23 

22 

25 

25 

33 

g 55 

15 

14 

9 

8 

e 

d 

c 

f 

46 

10 

11 

46 

d e 

m n p q i 

j 

h 

h 

f g 

r 

k 

c 

27 

13 

12 

8 

Figure 3 

G355
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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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21 20 19 

w 

39 

x 

Figure 5

Section H - H 

(Figure 7) 
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39 

u 

21 

14 15 

F

Figure 6 

DETAIL F

14 

15 

29 

18 

44 57 

G355

37 

G355 57 

27 

43 

30 36 38 

21 

21 

37 

40 41 

u 
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3.B.4. Modification of the electrical installation 

NOTE 8 

 

For the crimping of crimp contacts (107), (108), (109), (132), 

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

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

refer to paragraph 4.B. 

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

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

For the crimping of contacts (131), refer to paragraph 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 hydraulic 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 "30 ALP". 

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

. Close panel "30 ALP". 

. Fill in the identification plate (116) using a permanent 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 and 16) 

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

. Clean the surface and affix VNE label (117) or (118) 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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3.B.4.a.3 Modification of the wiring (Figures 8, 10, 12, 13 and 17) 

- Addition of electrical grounding module 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 surfaces between the grounding module (106) and the 

structure. 

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

nut (121). 

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

. Clean the surface and affix label 144N (120) close 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), sheath it using the NOMEX sheath (151). 

. Install the grommet (110) on the NOMEX sheath (151) (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 label (x1), its washer (x2) and its nut (x3). 

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

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

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

. Carry out the connections of connector “104DEL-J1D” using the crimp contacts (109) (Figure 8). 
 

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- Wiring of connector "104DEL - P1D" (Figure 8): 

. 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 DR25 (152). 

. Carry out the connections using crimp contacts (107) 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 12 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 modified and added wiring. 
 

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3.B.4.b. Helicopters equipped with the single hydraulic system with SMS unit: Kit 350A07-5606-0271 

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 already 

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 central post or instrument panel. 

. Clean the surface and affix VNE label (117) or (118) or (119) on the canopy's central post as per 

Figure 15. 

3.B.4.b.2. Addition of grounding module 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 surfaces between the grounding module (106) and the 

structure. 

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

nut (121). 

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

. Clean the surface and affix label 144N (120) close 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 and 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 (151). 

. 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 label (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 “47D” 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 modified 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 central post or instrument panel. 

. Clean the surface and affix VNE label (117) or (118) 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 (according 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 modified 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 label (x1), its washer (x2) and its nut (x3). 

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

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3.B.4.c. Helicopters equipped with the dual hydraulic system with multi-unit: Kit 350A07-5606-0371 

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

 . Open panel "31ALP32" and remove the blank from the plate in order to position the new circuit breaker 

(136) (Figure 18). 

 . Install the circuit breaker (136) on panel "31ALP32". 

 . 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 paragraph 

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 place of the previously removed circuit breaker (aa). 

. Close panel "30ALP". 

. Fill in the identification plate (116) using a permanent 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 filter (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 versions 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 modified wiring.

- Helicopters equipped with the dual hydraulic system 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 contacts (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 the marker batch (138). 

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

. Clean the surface and affix VNE label (117) or (118) or (119) on the canopy's central post as per 

Figure 15. 

3.B.4.c.3. Modification of the wiring (Figures 7, 10, 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 surfaces between the grounding module (106) and the 

structure. 

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

nut (121). 

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

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

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

- Wiring of electrovalve "9D" (x) (Figures 17 and 22): 

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

. Install the grommet (110) on the NOMEX sheath (151). 

. 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 label (x1), its washer (x2) and its nut (x3). 

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

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

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

. Carry out the connections of connector “104DEL-J1D” using the crimp contacts (109) (Figure 22). 
 

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- 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 DR25 (152) (Not shown in Figure 22). 

. Carry out the connections using crimp contacts (107) and (108). 

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

- Modification of the wiring of panel “30ALP” (Figures 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 22 

using crimp contacts (107), (108), (131), (132), (134) and the bushes (129). 

NOTE 14 

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

socket extracted during disconnection of push-button "50D". 

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

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

per Figure 19. 

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

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

removed. 

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

- Electrical continuity check: 

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

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3.B.4.d. Helicopters equipped with the dual hydraulic system with SMS unit: Kit 350A07-5606-0471 

NOTE 15 

For helicopters equipped with the dual hydraulic system with 

SMS unit on which the power supply wires of electrovalve 

“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 system with 

SMS unit on which the power supply wires of electrovalve 

“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 panels (Figures 18 and 20) 

. Open panel "31ALP32" and remove the blank from the plate in order to position the new circuit breaker 

(136) (Figure 18). 

 . Install the circuit breaker (136) on panel "31ALP32". 

 . 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 paragraph 

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 place 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 central post or the instrument panel. 

. Clean the surface and affix VNE label (117) or (118) or (119) on the canopy's central post as per 

Figure 15. 

3.B.4.d.3. Addition of grounding module 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 surfaces between the grounding module (106) and the 

structure. 

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

nut (121). 

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

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

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

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3.B.4.d.4. Wiring of electrovalve “9D” (Figures 17 and 25) 

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 (151). 

. Carry out the connections using the crimp contacts (107), (108), (109), (144) and (159), the pre-insulated 

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 label (x1), its washer (x2) and its nut (x3). 

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

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

3.B.4.d.5. Wiring modification of panel “30ALP” (Figure 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 modified and added wiring. 
 

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3.B.4.d.7. Modification of the circuit breaker panels (Figures 18 and 20) 

. Open panel "31ALP32" and remove the blank from the plate in order to position the new circuit breaker 

(136) (Figure 18). 

 . Install the circuit breaker (136) on panel "31ALP32". 

 . 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 paragraph 

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 place 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 central post or the instrument panel. 

. Clean the surface and affix VNE label (117) or (118) 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 contacts (130), (144), the pre-insulated round terminal 

lugs (112), the cap (113) and the extension lead (123). 

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

. Carry out an electrical continuity check of the modified 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 label (x1), its washer (x2) and its nut (x3). 

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

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

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3.B.5. Tests 

- 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 67-21-00, 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 stop, 

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 pedal in the forward position so that the primary stop, 

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, connect the tail rotor pitch-change links as per AMM 

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

- If the measurements are not within tolerances, adjust 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-tightness. 

- Check the level of the hydraulic fluid and, if necessary, 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 per 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 ducts of the condenser as per AMM Task 21-51-10, 4-2.

- Install the rear closing panel in the baggage compartment. 

- Close the load compensator inspection door. 

- Install the tail rotor drive fairings. 

- Install and/or close all cowlings, panels and doors 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-site crew. 

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

CAUTION
 

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3.C. IDENTIFICATION 

 Identification of this document: 

Record compliance with this document, with the revision 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 documentation: 

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

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

rotating pitch-change spider assembly as per MTC Work 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 and 

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 + on the 

Log Card 

Tail rotor blade 

assembly 

355A12-0055-03 355A12-0060-01 075606 Yellow ink + on 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 PHILLIPS ink 

No. 7 

 

3.D. OPERATING AND MAINTENANCE INSTRUCTIONS 

 Operating instructions: 

Refer to the Flight Manual (FLM). 

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

Insert the pages applicable post modification 075606 in place of the pages applicable pre 

modification 075606. 

 Maintenance instructions: 

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

compensator : 

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

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

chapter 05-25. 

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

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Figure 7
 

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Figure 8 

PRE MOD 

POST MOD 

112 

112 

109 108 

114 

110 

113 

107 

148 
 

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PAGE LAISSEE INTENTIONNELLEMENT BLANCHE 
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Figure 9 

PRE MOD 

109 

112 

112 

110 14
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Figure 10 

106 

121 122 

120 

59 

60 
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Figure 12 

PRE MOD
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Figure 13 

POST MOD 
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Figure 14 

aa 115 

POST MOD: 7,5APRE MOD: 5A
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Figure 15 

ab 

ac 

VNE

POWER O

Hp (ft) IAS 

0 1

2000 14000 16000 18000 1

10000 112000 114000 116000 118000 120000 922000 8

POWER OF

- 30 kts
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Figure 16 

PRE MOD 

POST MOD 

ad 

ad 
 

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Figure 17 

112 

110 

124 

x 

151 

x1 x2 x3 

55 
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Figure 18 

137 136 
 

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Figure 19 

PRE MOD 

POST MOD 

139 

140 

141 

50D 

49D 

50D 

ae 

ae 

138 
 

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Figure 20

af 

147 

146 

145 
 

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Figure 21 

PRE MOD 

POST MOD 

130 

151 

123 
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Figure 22 

148 
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Figure 23 

PRE MOD 

POST MOD

50D

50D-P1

134ALP-P1

50D
 

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To 22ALP (See Wiring 

Diagrams manual) 

1DH178F .REP2298 

1DH78E 

1DH141E .REP2298 

1DH78E 

1DH94E 

1DH93NE 

1DH50E 1DH50F 1DH96NE 1DH96NF 

PRE MOD 

POST MOD 

.REP2298 

1DH178E 

1DH96NE 1DH96NF 

1DH50E 1DH50F 

1DH93NE 1DH94E 

1DH141E 

.REP2

1DH178E 

1DH78F 

.REP2298 

112 

144 113 

130 123 

149 

To 22ALP (See Wiring 

Figure 24 Diagrams manual) 
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Figure 25 

PRE MOD 

POST MOD 

130 

123 

107 

109 112 

112 

129 

159 

144 

108 

110 

DR20 
 

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Figure 26 

PRE MOD 

POST MOD 

114 

112 148 
 

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Figure 27 

114 

112 148 

PRE MOD 

POST 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 hydraulic system with multi-unit 

The check for voltage at the hydraulic valves can be 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 order to prevent residual magnetization. 

** Ground the attachment screws of each solenoid in order 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 flashes 

+ 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 stops 

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) 

8 - Disconnect the 29 D pressure switch 

connector 

- The "HYDR" caption light on the warning panel goes 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 test 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 internet: 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 "SERVO" and "HYDR" caption lights on the 

warning panel are on 

2 - On panel 134α, press pushbutton "SERVO 

TST" 

- The "SERVO" caption light on the warning panel 

goes out 

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

comes on 

4 - Disconnect the RH servo-control (1D3) - The “LIMIT” 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 31α32, remove circuit-breaker "HYD" 

(2.5A) 

- The "LIMIT" caption light on the warning panel goes 

out 

8 - On 31α32, reinstall circuit-breaker "HYD" - The “LIMIT” caption 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 30α, remove circuit-breaker HYD (7.5A) - The voltage disappears 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 electrovalve 

(2D) is magnetized 

17 - Open circuit breaker HYD 2.5A on 31α32 - The electrovalve is no longer magnetized 

18 - Close circuit breaker HYD 2.5A on 31α32 - 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 internet: www.eurocopter.com/techpub

4.G.3. Helicopters equipped with the SMS unit 

The check for voltage at the hydraulic valves can be 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 order to prevent residual magnetization. 

** Ground the attachment screws of each solenoid in order 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 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-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 flashes 

- 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 stops 

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 test with the copilot's collective pitch stick.