A modification of the Mi-1, the Mi-2 was the first Russian light helicopter (NATO Designation: 'Hoplite') powered with two turboshaft engines.  Although initially built and test flown in the USSR all subsequent development and production was carried  out by WSK in Swidnik, Poland. (now PZL-Świdnik). Development began in 1960 and the Mi-2 became widely used in both the armed forces and civil aviation after it began production in 1965.  The aircraft may be fitted with a sling system with a load capacity of 800 kg and a load hoist with a lifting capacity of 260 kg.  The cabin can carry eight passengers in addition to the pilot.

Overview

Data on design, manufacture and status

Design authority: OKB Mil

Latest or last primary manufacturer: WSK-Świdnik
Originally manufactured by OKB Mil

Parent type: Mil Mi-2

Aircraft status: Operational

Configuration

Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift configuration: Single main rotor

Dedicated control device: Tail rotor

Crew required: 1-2

Crew seating: Side-by-side

Landing gear: Wheels (non-retractable)

Overall Dimensions

Data on aircraft size

Overall Width: 14.50 m (47.6 ft)

Engine Details

Aircraft powerplant (lift and/or propulsion)

Total number of engines: 2

Engine designation: Klimov GTD-350 turbine

Engine manufacturer: JSC Klimov United Engine Corporation

Take-off / rated power: 298 kW (400 hp)

Weights and Performance

Data on aircraft weight and flight characteristics

Max Gross Weight (ground): 3700 kg (8157 lb)

Max Range: 350 km (189 nm)

Max Endurance: 3.5 hrs (3.5 hrs)

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