TYPE: Four-seat kitbuilt.

PROGRAMME: Design began 15 April 1997 and construction of first prototype (N202KT) on 2 June 1998. Formally announced at AirVenture '99; mockup displayed at Sun 'n' Fun 2000. Part-completed prototype displayed at Sun 'n' Fun 2001 and again at AirVenture 01, with first flight then expected before end 2001; this later slipped to June 2002 but had not taken place by November 2002, when it was said to be expected in the following month; achieved 29 March 2003 and by August 2003 had completed 60 hours of flying. Kit deliveries planned to begin December 2003.

COSTS: Development costs estimated at US$500,000 in 1997. Kit US$49,000, excluding engine, propeller, avionics, instrument, interior or paint; four sub-kits are available (2003 prices).

DESIGN FEATURES: Cantilever high-wing monoplane of rectangular fuselage cross-section. Constant-chord wings and tailplane; sweptback fin with fillet. High-performance kitbuilt meeting FAR Pt 23 certification and 51 per cent homebuilt rule. Many parts supplied pre-formed, pre-drilled or pre-assembled. Quoted build time 1,200 to 1,600 hours.
Aerofoil section NACA 642A215, dihedral 1° 30'; incidence 1°; no twist.

FLYING CONTROLS: Conventional and manual. Horn-balanced elevator and rudder, both with electric trim. Single-slotted Fowler flaps. Dorsal fillet and drooped outboard cuff assists spin resistance.

STRUCTURE: All-metal wing with square tips. Fuselage of 4130 steel tube covered with aluminium sheet.

LANDING GEAR: Tricycle type; fixed, Wittmann sprung steel main legs. Cleveland wheels; disc brakes on mainwheels. Nosewheel 5.00-5, steerable ±60°. Mainwheels 6.00-6, all with 2.07 bar (30.0 lb/sq in) tyre pressure. Pressure Recovery wheel fairings.

POWER PLANT: Prototype has one 224 kW (300 hp) Teledvne Continental IO-550-L driving a three-blade Hartzell constant-speed propeller; engine mount also compatible with IO-520-L. Mounts and cowlings for 194 kW (260 hp) Textron Lycoming IO-540 and 224 kW (300 hp) Zehrbach engines under consideration. Fuel in two integral wing leading-edge tanks, combined capacity 277 litres (73.0 US gallons; 60.8 Imp gallons); or alternative long-range tanks combined capacity 390 litres (103 US gallons; 85.8 Imp gallons), of which 386 litres (101 US gallons; 84.9 Imp gallons) are usable. Gravity refuelling point on wing. Oil capacity 7.6 litres (2.0 US gallons; 1.7 Imp gallons).

ACCOMMODATION: Pilot and three passengers in two pairs of seats. Split doors on each side of fuselage; single baggage door at rear of cabin.

SYSTEMS: 12 V 24 Ah Concorde RG-25XC battery. Electric fuel pump.

AVIONICS: Prototype has two Bendix/King KX 155A com radios, Bendix/King KLN 94 VOR/DME and GPS.