TYPE: Two-seat training aircraft.
PROGRAMME: First flight of prototype 31 May 1989; displayed at 1989 Paris Air Show after 15 h North Atlantic ferry flight.
DESIGN FEATURES: Based on Ed Swearingen's SX300 light aircraft described and illustrated in 1987-88 Jane's; skin thickness increased by 50 per cent to cater for higher performance, new canopy with miniature detonating cord and either rocket extraction system or Martin-Baker lightweight ejection seats; larger wheels, tyres and brakes; NASA NLF 0416 laminar flow aerofoil section claimed to produce handling characteristics of jet aircraft.
FLYING CONTROLS: Ailerons have electric trim; electrically operated trim tab in elevator, hydraulically actuated trailing-edge flaps.
STRUCTURE: Mainly all-metal structure; single spar wings, composites used in wingtips and fuselage fairings; stressed skin fuselage, composites tailcone and engine cowling panels; composites in fin and tailplane tips.
LANDING GEAR: Hydraulically retractable tricycle type, with single wheel and oleo-pneumatic shock absorber on each unit. Manual hydraulic pump for emergency extension, and gas-spring powered secondary emergency extension. Steerable nose unit, with shimmy damper. Mainwheel tyres size 6.00-6, nosewheel tyre size 5.00-5 (all three 6-ply). Hydraulic disc brakes and parking brake.
POWER PLANT: One 313 kW (420 shp) Allison 250-B17D turboprop, driving a three-blade constant-speed propeller. Inlet anti-iced by engine bleed air. Fuel in two integral wing tanks (each 128.5 litres; 34 US gallons; 28 Imp gallons usable) and a 72 litre (19 US gallon; 16 Imp gallon) fuselage header tank, giving total usable capacity of 329 litres (87 US gallons; 72 Imp gallons).
ACCOMMODATION: Side by side seats for instructor and pupil, with full-shoulder inertia reel safety harness each occupant. Dual controls standard. Hydraulically actuated 'omnivision' canopy, with windscreen demisting.
Baggage space aft of seats. Accommodation heated (by engine bleed air) and ventilated.
SYSTEMS: Hydraulic system for actuation of flaps, landing gear and mainwheel brakes. Electrical system (28V DC), with lead-acid battery and 70A alternator, provides power for engine start, aileron and elevator trim, hydraulic pumps, navigation, strobe, landing and cockpit lights.