TYPE: Single-seat ultralight/motor glider.
PROGRAMME: Design started 1997; first flight of prototype September 1998; construction of first production aircraft began 1999. Marketed as fast-build kit or ready to fly.
CUSTOMERS: Total of seven ordered and five built by December 2001, including one export to Chile.
COSTS: Kit less engine, propeller and instruments, €23,000, plus tax (2003).
DESIGN FEATURES: Pod-and-boom configuration, with T tail. Aimed at meeting FAI ultralight and JAR 22 certification criteria.
FLYING CONTROLS: Conventional and manual; cable-operated elevators, flaperons and rudder; three-position flaps, deflections -5, 0 and +5o. Airbrakes on upper wing surfaces.
STRUCTURE: Fuselage moulded in half-shells of glass fibre/epoxy with plywood bulkheads. Wings have carbon fibre spar caps and glass fibre skins. Fabric-covered rudder. Optional winglets. Quoted build time 300 hours.
LANDING GEAR: Non-retractable monowheel type; tailwheel incorporated in base of rudder for directional control on the ground; small outrigger wheel at each wingtip. Drum brake on mainwheel.
POWER PLANT: One 13.4 kW (18 hp) JPX D-320 two-stroke flat twin with 2.38:1 reduction drive to a carbon fibre two-blade folding pusher propeller (three-blade propeller being tested October 2001). Fuel capacity 19 litres (5.0 US gallons; 4.2 Imp gallons).
EQUIPMENT: Optional ballistic parachute recovery system.