Development of the Russian Mi-38 medium multipurpose helicopter began in 1981; and there was a presentation at the 1992 Moscow Aeroshow.  Prodcution of the series was facilitated by Kazan Helicopters JSC, as of the year 2000.  Initial versions of the twin-engined aircraft wielded either the BK-2500 or PW-127T/V engines.  Maximum internal and slung loads are 6000 kg and 7000 kg, repectively; passenger capacity is 32 or 16 stretchers.  The helicopter is equipped with GPS and PNKB-38 navigation systems; the main rotor may also be folded.

Data is based on the year 2017 data points of the fourth protoype and 2000 Russia's Helicopter World catalog data points of the Mi-38.

Overview

Data on design, manufacture and status

Design authority: MVZ Mil

Primary manufacturer: MVZ Mil

Parent type: Mil Mi-38

Aircraft status: Operational

Configuration

Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift configuration: Single main rotor

Dedicated control device: Tail rotor

Crew required: 1-3

Crew seating: Side-by-side

Landing gear: Wheels (non-retractable)

Overall Dimensions

Data on aircraft size

Overall Width: 21.10 m (69.2 ft)

Engine Details

Aircraft powerplant (lift and/or propulsion)

Total number of engines: 2

Engine designation: Klimov TV7-117V turbine

Engine manufacturer: JSC Klimov United Engine Corporation

Take-off / rated power: 2088 kW (2799 hp)

Weights and Performance

Data on aircraft weight and flight characteristics

Max Gross Weight (ground): 15600 kg (34392 lb)

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