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Fuji FA-200 Aero Subaru (9560 views - Transportation - Air Water Earth)

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

Fuji FA-200 Aero Subaru

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

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.

Specifications (FA-200-180 [Normal])

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


  • 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

This article uses material from the Wikipedia article "Fuji FA-200 Aero Subaru", which is released under the Creative Commons Attribution-Share-Alike License 3.0. There is a list of all authors in Wikipedia

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