The aircraft preceded the US FAR 103 Ultralight Vehicles rules, but fits into the category, including FAR 103's maximum empty weight of 2540NaN0. The aircraft has a standard empty weight of 2000NaN0. It features a cantilever high-wing, a single-seat, partially enclosed cockpit, tricycle landing gear and twin 11.50NaN0 Soarmaster engines powering a single propeller in pusher configuration. Twin go-cart engines have also been employed.
The aircraft is made from aluminum tubing, foam, fiberglass, with the wings finished in doped aircraft fabric covering. Its 321NaN1 span wing features a laminar-flow airfoil, 50%-span elevons and wing tip rudders that can both be deployed simultaneously for use as air brakes. The aircraft has a 22:1 glide ratio. The FLAC has laminated fiberglass main landing gear legs and a nose wheel that is steerable. The aircraft was also designed to be at least nominally foot-launchable to comply with the informal US requirements for ultralights of that period that they be able to do so. Foot launching was carried out by opening a hinged door in the fuselage floor.
In flight the aircraft has been described as unstable, particularly in pitch and at least one accident was attributed to its instability.
