In March 1981 Romuald Drlik began the design work for a new lightweight canard-type aircraft, tentativly named Falcon and in May 1981 Romuald and helpers began construction on the first Falcon prototype (model "A"). After first trying a single-wheel gear and side-stick (neither successful) the #1 Falcon flies in late July 1981 using tricycle gear, a double-surface variable camber Dacron wing, centre hinged-stick, and a Robin 240 cc single-cylinder engine. In August 1983 three pre-production ultralight-legal Falcons were flown at Oshkosh, utilizing Kevlar-and-graphite fuselages and numerous refinements. Two of the planes were delivered to Falcon dealers. One craft won Reserve Grand Champion, then was flown home in one afternoon to Minneapolis (over 260 miles), averaging 57 mph ground speed. In August 1983, load tests to destruction were performed on the other Oshkosh plane (prototype #9, which was weighed by the EAA at 240 lbs), documenting a load-carrying strength of 7 g's positive, three negative for the main wing and over 10 g positive 5 negative for the forward wing. January 1984 - Deliveries of production Falcons begin. Wing has swept back leading and trailing edges, and tapering chord; no tail, canard wing. Pitch control by elevator on canard; yaw control by tip-rudders, roll control by full-span ailerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from below by struts; wing profile; double-surface. Undercarriage has three wheels in tricycle formation; steel-spring suspension on nosewheel and axle-flex suspension on main wheels. Push-right go-right nosewheel steering connected to yaw control. Brake on nosewheel. Glass-fibre fuselage, partially enclosed. Engine mounted below wing driving pusher propeller. The Falcon XP two seat tandem verson became available in early 1984. For more history of the development of the Falcon, click here.
