TYPE: Side-by-side ultralight twin.

PROGRAMME: Public debut (F-31A) at aviation exhibition in Prague, September 2000.

CURRENT VERSIONS: F-31A: Tailwheel version; as described. Prototype is of this version.
F-31B: Tricycle landing gear; under development.
F-31C: Modified lifting and control surface geometry; under development.
F-31D: Multiseat, non-ultralight version; under development.

COSTS: Provisional cost US$43,365 (2003).

DESIGN FEATURES: Low-wing monoplane with dihedral from roots and upturned wingtips; cruciform tailplane.

FLYING CONTROLS: Conventional and manual; flaps fitted.

STRUCTURE: All-composites (CFRP sandwich shell); single-spar wing.

LANDING GEAR: Tailwheel type; fixed. Cantilever self-sprung main units.

POWER PLANT: Two 33.6 kW (45 hp) Hirth F23 flat-twin engines, each driving a SportProp 1360W two-blade, glass fibre propeller. Fuel capacity 75 litres (19.8 US gallons; 16.5 Imp gallons). Other suitable engines include Rotax 503 UL-2V, 582 DCDI-2V or 618 DCDI-2V.

AVIONICS: VFR instrumentation standard; IFR to customer's requirements, including Bendix/King KY 97 transceiver Garmin GPS.