Fuji FA-200 Aero Subaru

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FA-200 Aero Subaru
Fuji FA-200-180.JPG
Fuji FA-200-160
Role Civil light aircraft
Manufacturer Fuji
First flight 12 August 1965
Introduction 1968
Produced 1968 - 1986
Number built 275
Fuji FA-200-180

The Fuji FA-200 Aero Subaru is a single-engine piston-powered monoplane built by Fuji Heavy Industries of Japan.

Design and development[edit]

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.[1] 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.[1]

Production started in March 1968, continuing until 1986, with a total of 275 built.[2]

Variants[edit]

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 [Normal])[edit]

Data from Jane's all the world's aircraft, 1975-76,[3] Jane's All the World's Aircraft, 1976-1977 [1]

General characteristics

  • Crew: 1/2
  • Capacity: 2/3 pax
  • Length: 8.17 m (26 ft 10 in)
  • Wingspan: 9.42 m (30 ft 11 in)
  • Height: 2.59 m (8 ft 6 in)
  • Wing area: 14 m2 (150 sq ft)
  • Aspect ratio: 6.34
  • Empty weight: 650 kg (1,433 lb)
  • Max takeoff weight: 1,150 kg (2,535 lb)
  • Fuel capacity: 204.5 l (54.0 US gal; 45.0 imp gal)
  • Powerplant: 1 × Lycoming IO-360B1B four cylinder air-cooled horizontally-opposed piston engine, 130 kW (180 hp)
  • Propellers: 2-bladed McCauley B2D34C53/74E-0, 1.88 m (6 ft 2 in) diameter constant-speed metal propeller

Performance

  • Maximum speed: 233 km/h (145 mph; 126 kn)
  • Cruise speed: 167 km/h (104 mph; 90 kn) 55% power at 1,525 m (5,003 ft)
  • Stall speed: 97 km/h (60 mph; 52 kn) flaps down
  • Range: 1,343 km (835 mi; 725 nmi) max fuel 55% power at 2,290 m (7,510 ft) with no reserve
  • Service ceiling: 4,175 m (13,698 ft)
  • Rate of climb: 3.866 m/s (761.0 ft/min) at sea level
  • Wing loading: 82.1 kg/m2 (16.8 lb/sq ft)
  • Power/mass: 0.117 kW/kg (0.071 hp/lb)

See also[edit]

References[edit]

  1. ^ a b c Taylor, John W. R., ed. (1973). Jane's all the World's Aircraft 1976-77. London: Jane's Yearbooks. ISBN 0 3540 0538 3. 
  2. ^ Donald, David (Editor) (1997). The Encyclopedia of World Aircraft. Aerospace Publishing. ISBN 1-85605-375-X. 
  3. ^ Taylor, John W.R., ed. (1975). Jane's all the world's aircraft, 1975-76 (66th annual ed.). New York: Franklin Watts Inc. pp. 142–143. ISBN 978-0531032503. 

External links[edit]