Development of the Russian-made Mi-8 (NATO Designation: 'Hip') medium multipurpose helicopter began in 1958 with the prototype, V-8.  The airframe is of semimonocoque type with wings.

Maximum internal and external payloads are 4000 kg and 3000 kg, respectively.  The aircraft can carry 26 passengers in addition to the crew. 

Overview

Data on design, manufacture and status

Design authority: MVZ Mil

Primary manufacturer: MVZ Mil

Parent type: Mil Mi-8/Mi-14/Mi-17

Aircraft status: Operational

Configuration

Primary flight and mechanical characteristics

VTOL type: Helicopter

Lift configuration: Single main rotor

Dedicated control device: Tail rotor

Crew required: 3

Crew seating: Other

Landing gear: Wheels (non-retractable)

Overall Dimensions

Data on aircraft size

Overall Height: 5.65 m (18.5 ft)

Overall Length: 25.24 m (82.8 ft)

Overall Width: 21.29 m (69.8 ft)

Engine Details

Aircraft powerplant (lift and/or propulsion)

Total number of engines: 2

Engine designation: Motor Sich TV3-117VM turbine

Engine manufacturer: Motor Sich

Weights and Performance

Data on aircraft weight and flight characteristics

Max Gross Weight (ground): 13000 kg (28660 lb)

Max Range: 480 km (259 nm)

Max Endurance: 3.5 hrs (3.5 hrs)

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