TYPE: Six-seat kitbuilt.

PROGRAMME: Prototype (N83W) was due to fly late 1999, but delayed by hangar construction; new completion target was late 2000 but this slipped into 2003; wing and tail mating undertaken in September 2001; final assembly took place from September 2002. Engine test runs began in March 2003, followed by taxi tests in July 2003; first flight expected in September 2003, but had not taken place by November 2003.

CUSTOMERS: Launch orders being sought once prototype is flying.

COSTS: US$89,900 (2003).

DESIGN FEATURES: Designed to meet FAR Pt 23 and 51 per cent kitplane rules; extensive use of composites results in lightweight design. High wing with single bracing strut each side. Quoted build time 2,500 hours.
Dihedral 1° 44'; incidence 1° 30' at wing root; -1° 30' at tip.

FLYING CONTROLS: Conventional and manual. Frise-type ailerons travel +21°/-14°30'; NACA single-slotted three-position (10, 20, 40°) flaps; horn-balanced rudder (travel ±27°13') and elevators (travel +21°/-17°).

STRUCTURE: Primary structure is 7781 pre-preg 36-38 per cent resin with Nomex core and graphite rod packs. Fuselage has central keel fitted with load-bearing rods.

LANDING GEAR: Fixed tricycle type; speed fairings optional. Skis, floats and tailwheel layout optional.

POWER PLANT: One 298 kW (400 hp) Textron Lycoming IO-720-A1B flat-eight driving a Hartzell HC-E3YR-1RF/F8468A-6R constant-speed propeller. Fuel capacity 341 litres (90.0 US gallons; 74.9 Imp gallons), optionally increased to 526 litres (140 US gallons; 116 Imp gallons). Oil capacity 19.9 litres (5.25 US gallons; 4.4 Imp gallons).

ACCOMMODATION: Pilot and up to five passengers; club seating for four in rear cabin. Passenger/cargo double door on starboard side; optional door in port side for pilot. Dual controls.

AVIONICS: Onboard computer will provide aeronautical charts and e-mail services.