TYPE: Side-by-side ultralight.

PROGRAMME: Development began early 1998; prototype (D-MVFK), then unflown, exhibited at Aero '99 at Friedrichshafen in April 1999 and first flown May 1999. In production by 2000.

CURRENT VERSIONS: FK 14: Baseline version; as described.
FK 14B: New tailwheel variant first shown at Aero '03, Friedrichshafen, at which time prototype (D-MVFK upgraded) not then flown. New carbon wing and 78 litre (20.6 US gallons; 17.2 Imp gallon) fuel tank. Mainwheels as baseline version, with solid tailwheel.

CUSTOMERS: 30 flying by January 2003.

COSTS: With Rotax 912, €72,000; with Rotax 912 ULS, €74,200; both including tax (2003).

DESIGN FEATURES: Low wing with upturned wingtips incorporating navigation lights; wing section designed with assistance of Stuttgart University wind tunnel.

FLYING CONTROLS: Conventional and manual; electrically operated Fowler flaps extend on rails to 20°; spring trim system; horn-balanced rudder.

STRUCTURE: Mainly composites, with metal ailerons, tailplane and flaps; elevators and rudder fabric-covered.

LANDING GEAR: Non-retractable tricycle type; composites cantilever main legs; steerable nosewheel; drum brakes; speed fairing on all wheels. Mainwheels 6.00-6.

POWER PLANT: One 59.6 kW (79.9 hp) Rotax 912 UL or 73.5 kW (98.6 hp) Rotax 912 ULS driving a Junkers three-blade, ground-adjustable pitch, carbon fibre propeller. Fuel contained in single tank behind cockpit, capacity 65 litres (17.2 US gallons; 14.3 Imp gallons).

EQUIPMENT: BRS 5 emergency parachute recovery system.