The Mil Mi-54 is Twin turbine commercial utility helicopter first announced in 1992, intended to replace the Mi-2 and the Mi-8 helicopters. It was planned to use two 574 kW Saturn/Lyulka AL-32 turboshaft engines, four-bladed main and tail rotors, and fixed tricycle-type landing gear with one nosewheel and two rear wheels on sponsons.[1]

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Mi-54
Mil Mi-54 mock up at MAKS 2007 Airshow
Role	Civil Utility helicopter Type of aircraft
National origin	Russia
Manufacturer	Mil

Specifications

Data from ^{[citation needed]}

General characteristics

• Crew: 1-2
• Capacity: 10-12 passengers
• Length: 13.113 m (43 ft 0 in)
• Height: 4.8 m (15 ft 9 in)
• Empty weight: 3,000 kg (6,614 lb)
• Gross weight: 4,500 kg (9,921 lb)
• Max takeoff weight: 4,700 kg (10,362 lb)
• Powerplant: 2 × Saturn/Lyulka AL-32 turboshaft engines, 575 kW (771 shp) each
• Main rotor diameter: 13.5 m (44 ft 3 in)
• Main rotor area: 143.16 m² (1,541.0 sq ft)

Performance

• Maximum speed: 280 km/h (170 mph, 150 kn)
• Cruise speed: 260 km/h (160 mph, 140 kn)
• Service ceiling: 6,000 m (20,000 ft)

References

External links

Wikimedia Commons has media related to Mil Mi-54.

На других языках

[ru] Ми-54