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Fuji FA-200 Aero Subaru

From Wikipedia, the free encyclopedia

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
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

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]


Prototype with a 160 hp Lycoming O-320 engine
Initial version, powered by 160 hp Lycoming O-320 engine and fixed-pitch propeller.
More powerful development - 180 hp Lycoming IO-360 engine and constant speed propeller.
Powered by 180 hp Lycoming IO-320 engine and fitted with fixed-pitch propeller.
Experimental short takeoff and landing (STOL) version, developed by Japan's National Aerospace Laboratory fitted with Boundary layer control system.
Proposed three-seat variant, not built.
Proposed two-seat aerobatic variant, not built.
Proposed STOL variant.
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)

Fuji FA-200
Fuji FA-200

Data from Jane's All the World's Aircraft, 1976-1977 [1]

General characteristics

  • Crew: 1/2
  • Capacity: 2/3 passengers
  • 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: 14.0 m2 (151 sq ft)
  • Aspect ratio: 6.34:1
  • 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 metal constant-speed propeller, 1.88 m (6 ft 2 in) diameter


  • Maximum speed: 233 km/h (145 mph, 126 kn)
  • Cruise speed: 167 km/h (104 mph, 90 kn) 55% power at 1,525 m (5,000 ft)
  • Stall speed: 97 km/h (60 mph, 52 kn) flaps down
  • Range: 1,343 km (834 mi, 725 nmi) ; 55% power at 2,300 m (7,500 ft) with no reserve (max fuel)
  • Service ceiling: 4,200 m (13,700 ft)
  • Rate of climb: 3.9 m/s (760 ft/min) at sea level

See also


  1. ^ a b c Taylor, John W. R., ed. (1976). Jane's all the World's Aircraft 1976-77. London: Jane's Yearbooks. pp. 120–121. ISBN 0-354-00538-3.
  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.

External links

This page was last edited on 28 December 2020, at 16:16
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