The Mil Mi-2 is a twin-engined light utility helicopter developed by the Soviet manufacturer Mil OKB, today MIL Moscow helicopter plant, JSC (Russia).
The Mil Mi-2 was produced by WSK PZL-Swidnik in Poland only.
Total 5,450 built for civil and military operators by January 1999, majority exported.
Three-blade main rotor with hydraulic blade vibration dampers; flapping, drag and pitch hinges on each blade; anti-flutter weights on leading-edges, balancing plates on trailing-edges. Coil spring counterbalance in main and tail rotor systems; pitch change centrifugal loads on tail rotor carried by ribbon-type steel torsion elements. Blades do not fold; rotor brake fitted. Main rotor blade section NACA 230-12M. Main rotor shaft driven via gearbox on each engine; three-stage WR-2 main gearbox, intermediate gearbox and tail rotor gearbox; main rotor/engine rpm ratio 1:24.6, tail rotor/engine rpm ratio 1:4.16; main gearbox provides drive for auxiliary systems and take-off for rotor brake; freewheel units permit disengagement of failed engine and autorotation.
Hydraulic system for cyclic and collective pitch control boosters; variable incidence horizontal stabiliser, controlled by collective pitch lever.
Main and tail rotor blades have extruded duralumin spar with bonded honeycomb trailing-edge pockets; pod and boom fuselage of sheet duralumin, bonded and spot welded or riveted or longerons and frames, in three main assemblies (nose including cockpit, central section and tailboom); steel alloy main load-bearing joints.
Non-retractable tricycle type, plus tailskid. Twin-wheel nose unit. Single wheel on each main unit. Oleo-pneumatic shock-absorbers in all units, including tailskid. Main shock-absorbers designed to cope with both normal operating loads and possible ground resonance. Mainwheel tyres size 600 x 180, pressure 4.41 bars. Nosewheel tyres size 400 x 125, pressure 3.45 bars. Pneumatic brakes on mainwheels. Metal ski landing gear optional.
Two 313kW Polish-built Isotov GTD-350 turboshafts, mounted side by side above cabin. Fuel in single rubber tank, capacity 600 litres, under cabin floor. Provision for carrying 238 litre external tank on each side of cabin. Refuelling point in starboard side of fuselage. Oil capacity 25 litres.
Normal accommodation for one pilot on flight deck (port side). Seats for up to eight passengers in air conditioned cabin, comprising back to back bench seats for three persons each, with two optional extra starboard side seats at rear, one behind the other. All passenger seats removable for carrying up to 700kg of internal freight. Access to cabin via forward-hinged doors on each side at front of cabin and aft on port side. Pilot’s sliding window jettisonable in emergency. Ambulance version has accommodation for four stretchers and medical attendant, or two stretchers and two sitting casualties. Side by side seats and dual controls in pilot training version. Cabin heating, ventilation and air conditioning standard.
Cabin heating, by engine bleed air, and ventilation; heat exchangers warm atmospheric air for ventilation system during cold weather. Hydraulic system, pressure 65 bars, for cyclic and collective pitch control boosters. Hydraulic fluid flow rate 7.5 litres/min. Vented reservoir, with gravity feed. Pneumatic system, pressure 49 bars, for mainwheel brakes. AC electrical system, with two STG-3 3kW engine-driven starter/generators and 208V 16kVA three-phase alternator. 24V DC system, with two 28Ah lead-acid batteries. Main and tail rotor blades de-iced electrically; engine air intake de-icing by engine bleed air. Electric de-icing of windscreen.
Standard items include two transceivers (MF/HF), gyrocompass, radio compass, radio altimeter, intercom system and blind-flying panel. Nose and tail warning radar fitted to some military versions.
Agricultural version carries hopper on each side of fuselage (total capacity 1,000 litres of liquid or 750kg of dry chemical) and either a spraybar to rear of cabin on each side or distributor for dry chemicals under each hopper. Swath width covered by spraying version is 40 to 45m. For search and rescue, electric hoist, capacity 120kg, is fitted. In freight role an underfuselage hook can be fitted for suspended loads of up to 800kg. Polish press has illustrated version equipped for laying smokescreens. Electrically operated wiper for pilot’s windscreen. Freon fire extinguishing system, for engine bays and main gearbox compartment, can be actuated automatically or manually.
Capacity: 8 passengers or 700 kg (1,543 lb) internal, 800 kg (1,764 lb) external cargo
Length: 11.40 m (37 ft 4¾ in)
Rotor diameter: 14.50 m (47 ft 6⅞ in)
Height: 3.75 m (12 ft 3½ in)
Disc area: 165.13 m² (1,777.44 ft²)
Empty weight: 2,372 kg (5,218 lb)
Loaded weight: 3,550 kg (7,826 lb)
Max. takeoff weight: 3,700 kg (8,157 lb)
Powerplant: 2 × PZL GTD-350P turboshafts, 298 kW (400 shp) each
Maximum speed: 200 km/h (108 knots, 124 mph)
Range: 440 km (237 nmi, 273 mi) (max internatal fuel, no reserves)
Service ceiling: 4,000 m (13,125 ft)
Rate of climb: 4.5 m/s (885 ft/min)
Disc loading: 22.41 kg/m² (4.59 lb/ft²)
Power/mass: 12.4 kg/kW (20.4 lb/hp)