Fuji FA-200 Aero Subaru
# 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.

## 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. 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.

Production started in March 1968, continuing until 1986, with a total of 275 built.

## 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.

## Specifications (FA-200-180)

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

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 $m^2$ (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
