Subsequently Aviation Boosters, Inc. was formed to produce the aircraft in quantity and in the August 1945 issue of the magazine 'Flying', the Skyhopper was offered for $ 1,000. The prototype underwent considerable development and refinement, in particular the original open cockpit, within a year it gave way to an enclosed cabin with a removable sliding clear-view canopy, as pictured here.
However, by the flooding of the light aircraft market with surplus military planes within a year after Skyhopper's first flight, it became obvious that financial backing was going to be a difficult proposition. By March 1946, the business venture to produce the aircraft as a certified aircraft was dropped and Salvay and Stark split up. Salvay retained the aircraft and subsequently moved to California where he became a senior engineering executive on the AJ-1 Savage project with North American Aviation at Inglewood.
Flown initially with a 50 hp Continental engine, in 1948 the prototype was fitted with a 65 hp Continental A65 flat-four, this was changed in 1956 for an 85 hp Continental C85 and by 1959 a total of 1,000 hours of flying had been logged by the prototype. The plans were revised in 1957 and incorporated a number of changes, including a raised rear fuselage (turtle deck), and the plans were marketed through Skyhopper Airplanes, Inc.
The original single-seat version was initially marketed as the Skyhopper I (later as the Skyhopper 10) and suited for engines in the 65-125hp range. The Skyhopper II (later Skyhopper 20), was a side-by-side two-seat variant was started by Salvay in 1959, and had a wider fuselage and cabin, and increased wingspan. The type could accept engines in the 85-125hp range such as the Lycoming O-235, O-290, Continental C85, C90, etc.
The Skyhoppers registered varied in many details. Canopy, engine cowling, and landing gear were subject of change to the constructors liking, as seen in photo 10781. As early of June 1958, Dale Stark, a farmer of Angus, Minnesota, flew the first two-seater, adopted from single-seat plans, it was subsequently fitted with a tricycle landing gear.
Until marketing of the Skyhopper ended in the mid-1970s, over 600 sets of plans were sold, the number of eventually completed Skyhoppers is unknown. The pictured prototype was sold to Thomas A. Dawson of Brooksville, Florida on September 12, 1961, four years later, May 22, 1965 the registration was cancelled, the fate of the aircraft is unknown.
WINGS. Cantilever low-wing monoplane. Wing section NACA 23015-23012. Aspect ratio 6.0. All-wood two-spar structure. Leading-edge covered with aluminum sheet; remainder fabric-covered. Statically and dynamically balanced ailerons, fabric-covered. No flaps.
FUSELAGE. Welded steel-tube structure with fabric-covering.
TAIL UNIT. Cantilever tailplane and fin have plywood-covered wooden structure. Statically and dynamically balanced rudder and elevators have welded tube structure, with fabric covering.
LANDING GEAR. Non-retractable tail-wheel type. Oil and spring shock-absorbers. Main wheels, size 5.00 X 5. Wheel spats optional. Steerable tail-wheel.
POWER PLANT. One 65 hp Continental A65 or 85 hp Continental C85 four-cylinder horizontally-opposed air-cooled engine driving two-blade fixed-pitch airscrew. Fuel capacity 15 gal (56.8 l).
ACCOMMODATION. Single seat or two side-by-side seats under rear-ward-sliding canopy. Small baggage space aft of seat.