The unit is intended for fuel supply and automatic control of the engine TV3-117. It ensures:

• fuel metering during starting, acceleration and deceleration;
• maintenance of preset operation modes according to the turbo-compressor rotor speed and free turbine speed;
• synchronized air pressure behind compressor during the simultaneous operation of two engine; change in fuel feed as provide by the electronic -regulator signals;
• fuel distribution among the nozzles;
• engine shut down;
• control of compressor inlet guide vanes.

Gear box /

Gear box / Вертолетный редуктор

Designed to transmit power from two engines to two coaxial rotors and helicopter units, as well as aerodynamic forces from the rotors through the shafts and gearbox housing to the helicopter fuselage.

Installed: VR-252 gearbox - on Ka-27/28, Ka-29, Ka-31

Reducer schemes - stepped with a planetary stage (VR-252)

Rotor Mast / Колонка несущего винта

Designed to control the main rotors, transmit them torque from the engine and transfer lifting force to the fuselage through the center section.

number of blades - 3 x 2;
rotor speed, rpm - 273;
Overall dimensions, mm. - 2040 x 2040 x 3200;
weight, kg. - no more than 740.

Rechargeable battery / Аккумуляторная батарея

Rechargeable batteries provide:

• autonomous launch of auxiliary power units and engines of aircraft, helicopters and unmanned aerial vehicles;
• smoothing of voltage ripples in the on-board DC power supply system with a nominal voltage of 27 V;
• in-flight power supply to first category electricity receivers (necessary to complete the flight and safe landing) in the event of failure or disconnection of primary sources (in case of emergency operation of the power supply system).

PLUNGER PUMP / Насос плунжерный

Auxiliary gas turbine engine designed to start the main engines of the Ka-32, Mi-8 helicopters; Yak-40 and An-140 aircraft, ship and power plants.

Basic information
The AI-9 starting engine consists of the following main structural units:

housings for drive units and oil tank;
centrifugal single-stage compressor;
combustion chambers;
single-stage axial turbine;
exhaust nozzle;
units that ensure engine starting and operation.
The engine oil system is autonomous,
circulation, under pressure, consists of an oil tank, an oil unit and pipelines. Gear-type oil pump, with injection and pump-out stages.

The engine fuel system consists of a starting pump, a control pump with a solenoid valve, a starting injector and working fuel injectors.
The engine electrical system includes an electric starter, ignition coil, spark plug and starting fuel valve installed on the engine, as well as an automatic starting panel, starting resistance, switching, protective and signaling equipment (relays, contactors, circuit breakers, switches and warning lamps) installed by plane
.

Characteristics
Equivalent air power - 214 kW
Rated speed: 38500 ± 500 rpm
Bleed air quantity: 0.4±0.02 kg/s
Total pressure of bleed air, not less than: 0.24 MPa
Bleed air temperature: 403 K
Fuel consumption, no more: 80 kg/h
Dry weight: 65 kg
This APU uses a starter-generator STG-3 ser.2

Designed to determine the spatial position of an airplane or helicopter relative to the horizon and are sensors of roll and pitch angles, which are issued to consumers in the form of electrical signals.

Small-sized gyroverticals MGV-1SK gray. 01, MGV-1SU ser. 01, MGV-1SU8 ser. 01 are used on aircraft TU-154, An-72, An-74, Yak-42, helicopters Mi-26, Ka-32.

The Steering system type РС-60 is designed for longitudinal, lateral and directional control as well as for collective pitch control of an aircraft in manual control mode and in combined guidance mode. РС-60 for Ка-32 type helicopter is operated from two independent hydraulic systems.