Fuji FA 200 Aero Subaru

Design and development

Fuji Heavy Industries began development of a four-seat light aeroplane, the Fuji FA-200 Aero Subaru in 1964, the first prototype flying on 12 August 1965. It is a low-wing all-metal aircraft, fitted with a fixed nosewheel undercarriage and a sliding canopy. It was first certified in Japan on 6 July 1966, with certification in the United States occurring on 26 September 1967.

Production started in March 1968, continuing until 1986, with a total of 275 built.

Variants

F-200-II

Prototype with a 160 hp Lycoming O-320 engine

FA-200-160

Initial version, powered by 160 hp Lycoming O-320 engine and fixed-pitch propeller.

FA-200-180

More powerful development - 180 hp Lycoming IO-360 engine and constant speed propeller.

FA-200-180AO

Powered by 180 hp Lycoming IO-320 engine and fitted with fixed-pitch propeller.

FA-203-S

Experimental short takeoff and landing (STOL) version, developed by Japan's National Aerospace Laboratory fitted with Boundary layer control system.

F-201

Proposed three-seat variant, not built.

F-202

Proposed two-seat aerobatic variant, not built.

F-203

Proposed STOL variant.

F-204

Proposed crop spraying variant, not built.

Specifications (FA-200-180)

Data from Jane's All the World's Aircraft, 1976-1977

General characteristics

Crew: one

Capacity: three

Length: 8.17 m (26 ft 9½ in)

Wingspan: 9.42 m (30 ft 11 in)

Height: 2.59 m (8 ft 6 in)

Wing area: 14.0 m² (151 ft²)

Empty weight: 650 kg (1,433 lb)

Max. takeoff weight: 1,150 kg (2,535 lb)

Powerplant: 1 × Avco Lycoming IO-360 four cylinder horizontally opposed piston engine, 134 kW (180 hp)

Performance

Maximum speed: 237 km/h (128 knots, 147 mph)

Cruise speed: 185 km/h (100 knots, 115 mph) (economy cruise - 55% power)

Stall speed: 87 km/h (47 knots, 54 mph) (flaps down)

Range: 1,400 km (755 nm, 870 mi)

Service ceiling: 5,790 m (19,000 ft)

Rate of climb: 5.7 m/s (1,129 ft/min)

Wing loading: 82.1 kg/m² (16.8 lb/ft²)

Power/mass: 0.12 kW/kg (0.071 hp/lb)