Successor to the Nakajima Aircraft Company, Fuji Heavy Industries was
formed in July 1953 and, just over a year later, delivered the first of
161 license-built Beech Mentor which were supplied to Japan Self-Defence
Forces, to the Philippine air force, and the Indonesian air force. The
company evolved a number a number of derivatives which were built in small
numbers, and design of an entirely new four-seat light aircraft, the
FA-200 Aero Subaru.
Of all-metal construction,
the FA-200 prototype was flown for the first time on 12 August 1965, and
subsequently went into production at Fujiís Utsunomiya factory, initially
as the FA-200-160 powered by a 160-hp (119-kW) Avco Lycoming O-320-D2A
engine. In its basic four-seat configuration, the FA-200 was awarded a
Normal category type certificate by the Japan Civil Aviation Bureau on 1
March 1966; certification as a three-seater in the Utility category, and
as a two-seater in the Aerobatic category fallowed on 6 July 1966 and 29
July 1967, respectively. United States FAA Type Approval in all three
categories was awarded on 26 September 1967.
The installation of the
180-hp (134-kW) Avco Lycoming IO-360-B1B engine, driving a constant-speed
propeller, resulted in the introduction of the FA-200-180, which received
Japanese Type Approval in the Normal, Aerobatic and Utility categories on
28 February 1968. In the latter case, approval was for full four-seat
use. With a fixed-pitch propeller, the aircraft became the FA-200-180 AO,
certificated in Japan on 27 September 1973 US certification for the
FA-200-180 and -180 AO was received on 25 April 1968 and 1 February 1974,
During 1980, after 294 had
been competed, Fuji temporarily suspended production to concentrate on
joint development with Rockwell of the Fuji 300 light twin. Deliveries of
the FA-200 recommenced early in 1981, initially from a stock of
single-engined four-seater aerobatic, touring and training monoplane.
(FA-200-160) one 160-hp (119-kW) Avco Lycoming O-320-D2A flat-four piston
maximum speed 138 mph (222 km/h) as sea level; economic cruising speed 102
mph (164 km/h) at 5,000 ft (1525 m); service ceiling 11,400 ft (3475 m)
range with maximum fuel 755 miles (1215 km).
empty 1,366 lb (620 kg); maximum take-off 2,333 lb (1059 kg).
span 30 ft 11 in (9.42 m); length 26 ft 9 Ĺ in (8.17 m); height 8 ft 6 in
(2.59 m); wing area 150.7 sq ft (14.00 m2)