Designed for use as a sustainer propulsion system on twin-engine helicopters of various applications in the class of load capacity up to 20000 kg. It powers Mi-26, Mi-26T helicopters. It meets the effective environmental requirements of ICAO standards. In commercial production since 1978.
|Takeoff (SLS, ISA)|
|Specific fuel consumption, kg/hp/h||0.198|
|Dimensions, mm||3,715 x 1,382 x 1,124|
|Weight, dry, kg||1,077|
|Specified service life, h||3,000|