Fuji FA-200 Aero Subaru

FA-200 Aero Subaru
FA-200 Aero Subaru
	Fuji FA-200-160
General information
Type	Civil light aircraft
Manufacturer	Fuji
Number built	275
History
Manufactured	1968–1986
Introduction date	1968
First flight	12 August 1965

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]

Variants

F-200-II: Prototype with a 120 kW (160 hp) Lycoming O-320 engine
FA-200-160: Initial version, powered by 120 kW Lycoming O-320 engine and fixed-pitch propeller.
FA-200-180: More powerful development - 130 kW (180 hp) Lycoming IO-360 engine and constant speed propeller.
FA-200-180AO: Powered by 130 kW 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)

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

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 (5,000 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

References

^ ^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.
^ Donald, David, ed. (1997). The Encyclopedia of World Aircraft. Aerospace Publishing. ISBN 1-85605-375-X.
^ "Light plane crash in Bosnia leaves five dead". Business Insider. 13 May 2017. Archived from the original on 12 April 2019. Retrieved 3 January 2019.

External links

FUJI/FA-200 AERO SUBARU Archived 2014-07-17 at the Wayback Machine

[Janes_76-77-1] 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, ed. (1997). The Encyclopedia of World Aircraft. Aerospace Publishing. ISBN 1-85605-375-X.

[3] "Light plane crash in Bosnia leaves five dead". Business Insider. 13 May 2017. Archived from the original on 12 April 2019. Retrieved 3 January 2019.

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