Fuji FA-200 Aero Subaru

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

FA-200 Aero Subaru
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

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.[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
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.

Accidents and incidents
  • On May 13, 2017, a Fuji FM 200-160 with tail number E7-AAS, crashed in Jasenica, near Mostar in Bosnia and Herzegovina, killing all 5 on board. Among them were 3 children.[3]

Specifications (FA-200-180 [Normal])
Fuji FA-200

Data from Jane's all the world's aircraft, 1975–76,[4] 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)
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See also

References
  1. 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.CS1 maint: extra text: authors list (link)
  3. "Light plane crash in Bosnia leaves five dead". Business Insider. 13 May 2017.
  4. 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.
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