TYPE: Four-seat kitbuilt.

PROGRAMME: Based on Zenith STOL CH 701 design; work started in 1988 for an undisclosed customer, but was suspended when order cancelled. Subsequently revived; prototype built by Flypass Ltd in Ontario, Canada, and first flown March 1998. Launched at Oshkosh, July 1998, with kit deliveries following.
In 2003, Jordan Aerospace Industries of Amman announced the Hawk-I CH801, a locally marketed and assembled CH 801.

CUSTOMERS: 150 kits sold and 20 flying by end 2002. Marketing by CZAW (Czech Republic), which offers builder's assistance programme.

COSTS: Kit excluding engine US$20,950 (2003).

DESIGN FEATURES: High-wing, strut-braced monoplane. Although visually similar to the CH 701, no commonality of parts. Quoted build time 700 hours.
Wing aerofoil NACA65015.

FLYING CONTROLS: Manual. Full-span Junkers flaperons with outboard section offset 2° higher; deflection to 35° elevator; all-moving, horn-balanced fin. Fixed full-span leading-edge wing slats.

STRUCTURE: All-metal semi-monocoque construction, making extensive use of blind rivets. Single-spar 6061-T6 aluminium wing. Fuselage welded 4130 tubular steel frame.

LANDING GEAR: Tricycle type; cantilever mainwheel legs optimised for rough-field operations with Matco or Cleveland wheels and brakes. Nosewheel steerable ±15°. Tundra tyres on all wheels. Optional flotation gear.

POWER PLANT: One 134 kW (180 hp) Textron Lycoming O-360-A driving two-blade, fixed-pitch Sensenich 76-EMB-O-54 metal propeller in production prototype; engines in the range 112 to 179 kW (150 to 240 hp) can be fitted, including four-stroke LOM M337B of 173 kW (232 hp). Standard fuel capacity 151 litres (40.0 US gallons; 33.3 Imp gallons); optional fuel capacity 303 litres (80.0 US gallons; 66.6 Imp gallons).

ACCOMMODATION: Pilot and three passengers in enclosed cabin. Single door on port side. Underfuselage cargo pod optional.