Design began at Kazan in 1993, with design subcontracts to Kazan State Technical University for structural strength and aerodynamic calculations; Aviacon Scientific and Production Centre for rotor; and Aeromekhanica for transmission.
A fuselage mockup was exhibited at the 1995 Paris Air Show, followed by a considerably revised engineering mockup (001) at Paris '97. By August 1998, now marked '01', this had accumulated 10 hours of ground running with engines and rotors, and totalled 800 hours by February 2003.
The design features a traditional metal structure and meets FAR Pt 29 Category A and Russian AP-29 requirements. A hingeless main rotor hub with glass fibre torsion bar, has four main blades; two-blade tail rotor. A two-stage, VR-23 main rotor reduction gear in magnesium case ahead of engines has ratio 16.4; rotation speed 365.4 rpm; blade tip speed 220m/s, and transmission rating 769kW. Tail rotor speed 2,000 rpm via single stage conical geabox. Rotor brake. Manual blade folding. Main rotor aerofoil section NACA 23012.
The aluminium alloy fuselage has sparing use of composites, layered glass fibre main rotor blades, window frames and nosecone. The landing gear has twin skids with Kazan transverse shock-absorbers, tail bumper to protect anti-torque rotor, and wheels optional in tricycle configuration, with Yaroslav tyres and Gidroagregat (Balashikha) brakes.
Power is from two P&W Rus XRK206S turboshafts, each rated at 477kW for T-O, 418kW max continuous, in prototypes. Production version with PW207Ks, rated at 470kW for T-O, 410kW max continuous, 529kW for 30 s, 470kW continuous OEI and 491kW 2 minutes OEI. FADEC standard. Fuel capacity 700 litres in either external panniers or underfloor. Optional internal ferry fuel. Alternatively, two Salyut TV-500A turboshafts, each 478kW.
Seating is for up to 11 persons, including one or two pilots, on energy-absorbing seats; or two stretcher patients and three attendants; or internal or externally slung freight. Two forward-hinged doors each side of flight deck; two horizontally split doors each side of cabin, forward; baggage bay behind cabin, with rear-facing door. Baggage door also used for loading stretchers of medical variant. Accommodation ventilated and heated; optional air conditioning.
Avionika FBW controls comprise quadruples electronic system and duplex hydraulic system. Automatic flight control is standard on all piloting functions and optional on navigation functions. Current FBW system to be replaced by KSU-A digital control system. Main transmission drives two alternators (each 200V, 400Hz), two generators (each 27V), two fans and two hydraulic fuel pumps for separate systems. Electrical system 27V, with battery; optional AC system, with second battery. Electric de-icing optional.
First flight was scheduled for late 1997, but initial designated flight trials aircraft (02) exhibited at Farnborough in September 1998, still unflown. First flight (02) was 12 minute hover on 17 August 1999, with an initial forward flight on 6 October 1999. Trials halted in November 1999, after 4 hours, due to gearbox problems, but resumed in the second quarter of 2000 with a strengthened and redesigned main transmission, scarfed engine exhausts and new identity '902'. Total 120 hours up to February 2003.
The third (second flying) prototype (03) was to have joined the programme in late 1999, but was not completed until August 2001. First flown 27 December 2001, this is to preproduction standard with small, detachable, pannier tanks, increased fin area, PW207 engines, additional side window and flatter windscreen combined with revised nose shape; will add 400 hours to trials programme. Certification flight resting began in October 2002, for completion before end of 2003; by early 2003 had been renumbered '904'.
On 14 September 2001, Ansat declared winner of competition to supply 100 training helicopters to Russian armed forces by 2015.
Aircraft No.5 was to Ansat-U standard, including dual controls and wheel landing gear. Optimised for training (uchebni).
Russian Federal Border Service (Federalnaya Pogranichnaya Sluzhba) requirement for 100 notified in 1997. Total 12 civil sales reported by late 2002, including one for export.
The price was US$2.0 million for utility version (2003). Kazan's development expenditure had reached Rb200 million by mid-2000.
Engine: 2 x Klimov / Pratt & Whitney Canada PW 206 C, 631 shp
Main rotor diameter: 11.5m
Fuselage Length: 37.861 ft / 11.54 m
Length with rotors turning: 13.77m
Height: 11.286 ft / 3.44 m
Rotor diameter: 37.73 ft / 11.5 m
Max take off weight: 7276.5 lb / 3300.0 kg
Cruising speed: 129 kts / 238 km/h
Max speed: 280km/h
Economic cruising speed: 140km/h
Service ceiling: 19685 ft / 6000 m
Hovering ceiling, OGE: 1800-2700m
Maximum range: 335 nm / 620 km
Range: 281 nm / 520 km
Endurance: 3 h
Payload: 8 pax / 1300 kg int. max. / 1650 kg ext. max.