KAPPA KP-2U SOVA

English name: Owl

TYPE: Side-by-side ultralight/kitbuilt.

PROGRAMME: Designed by Kappa company and Institute of Aerospace Engineering at Brno Technical University and developed over a 22-month period. First of two flying prototypes (OK-BUU 23) first flown 26 May 1996; first public demonstration the following month at Jihlava Aero '96 Czech certification 23 September 1997; German certification, and of kit by FAA, in June 1999, followed by Polish certification in April 2001 and Portuguese certification in June 2002. Australian and Spanish certification under way at end 2002.

CUSTOMERS: Over 100 sold by April 2003; customers in Belgium, Brazil, Czech Republic, Ecuador, France, Germany (known as KPD-2U), Italy, Netherlands, Poland, Portugal, Spain and USA.

COSTS: €45,000 flyaway with Rotax 912 UL (2003).

DESIGN FEATURES: Low-wing monoplane conforming to BFU 95 regulations; JAR-VLA version being developed.
Wing sections NASA GA(W)-1 at root and GA(W)-2 at tip; upturned wingtips, dihedral 6o. Sweptback vertical tail.

FLYING CONTROLS: Conventional and manual. Electrically operated trim tab in port elevator; manually operated Fowler flaps (deflection 10 and 35o).

STRUCTURE: All-metal, except for CFRP cockpit frame.

LANDING GEAR: Electrically retractable tricycle type (all units rearward); rubber shock-absorption; mainwheels semi-exposed when retracted. Steerable nosewheel; mechanically operated brakes (hydraulic optional). Fixed gear optional.

POWER PLANT: One 59.6 kW (79.9 hp) Rotax 912 UL engine, with 4:1 reduction drive to a two- or three-blade, flight-adjustable or three-blade ground-adjustable pitch propeller; can alternatively accommodate Rotax 582 UL, 912 ULS or 914. Fuel capacity (two wing tanks) 64 litres (16.9 US gallons; 14.1 Imp gallons); 94 litres (24.8 US gallons; 20.7 Imp gallons) for Australian market.

ACCOMMODATION: Forward-hinged canopy. Dual controls. Space behind seats for 14 kg (31 lb) of baggage.

 

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