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Mi-10

The Mil Mi-10 was a Soviet military transport helicopter of flying crane configuration, developed in 1962 from the Mi-6.  It entered service in 1963.

Also known as "Product 60" by Rostov-upon-Don helicopter facility.

It was built as the short-legged ("Mi-10K") version, and the long-legged ("Mi-10R") version.  It is powered by two 5,500 shp (4,100 kW) Soloviev D-25 turboshafts.  The Mi-10 uses a closed circuit camera system that scans forward from under the rear fuselage and downward through the sling hatch to watch the payload and landing gear and for touchdown.

 

General characteristics

Crew: 3 (pilot, copilot, flight engineer)

Capacity:

 28 passengers or

 up to 15,000 kg (33,070 lb) payload on platform or

 8,000 kg (17,635 lb) max slung payload

Length: 32.86 m (107 ft 9 in)

Rotor diameter: 35.00 m (114 ft 10 in)

Height: 9.80 m (32 ft 2 in)

Disc area: 962 m² (10,350 ft²)

Empty weight : 27,300 kg (60,185 lb)

Loaded weight: 38,000 kg (83,775 lb)

Max. takeoff weight : 43,700 kg (96,340 lb)

Powerplant : 2 × Soloviev D-25 V turboshafts , 4,100 kW (5,500 shp) each

Ground clearance under fuselage: 3.75 m (12 ft 3 in)

 

Performance

Maximum speed : 235 km/h

Cruise speed : 200 km/h

Range : 250 km (155 mi)

Service ceiling : 3,000 m (9,850 ft)