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  • Fuji FA-200 Aero Subaru

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    Description

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

    General Information

    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 160 hp Lycoming O-320 engine

    FA-200-160

    Initial version, powered by 160 hp Lycoming O-320 engine and fixed-pitch propeller.

    FA-200-180

    More powerful development - 180 hp Lycoming IO-360 engine and constant speed propeller.

    FA-200-180AO

    Powered by 180 hp 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.

     

    Specifications below are for the FA-200-180 variuant

    FujiFA-200D-EAMA.jpg_thumb.2d615cf53136bc56fc3c05fa411191fc.jpg

    FujiFA-200D-EKBB.jpg_thumb.f8ab6c9c616549ce8c5242d950d5c435.jpg

    FujiFA-200G-BDFR.jpg_thumb.c002722659216b683cdf9852d5606544.jpg

    FujiFA200PH-MBK.jpg_thumb.106bfd10120731db8d0ef2f654cf4a8e.jpg

    FujiFA-200-180AeroSubaruKynetonVH-FJY.jpg_thumb.59abd98aed922f2630869f29a4ac3480.jpg

    Specifications

    Seats:
    Four
    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 sq m (150 sq ft)
    Wing Loading:
    82.1 kg/sq m (16.8 lb/sq ft)
    Empty Weight:
    650 kg (1,433 lb)
    MTOW:
    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)
    Vne:
    Maximum speed: 233 km/h (145 mph, 126 kn)
    Cruise Speed:
    Maximum speed: 233 km/h (145 mph, 126 kn)
    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
    Rate of Climb:
    3.866 m/s (761.0 ft/min) at sea level
    Service Ceiling:
    4,175 m (13,698 ft)

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