The aircraft was first flown before the US FAR 103 Ultralight Vehicles rules were introduced and the early versions of the Goldwing did not meet the category's maximum empty weight of 2540NaN0 or its maximum speed requirement of 630NaN0. Later models were made lighter and slower to fit FAR 103. The Goldwing UL model has a standard empty weight of 2520NaN0. It features a cantilever mid-wing, canard, a single-seat, open cockpit, tricycle landing gear and a single engine in pusher configuration.
The aircraft is made from molded fiberglass epoxy composites, including Kevlar, carbon-fiber-reinforced polymer and high-density foam. Its 301NaN1 span wing is built with a carbon epoxy spar, with the rest of the wing built from foam and covered with doped aircraft fabric covering. The wing features tip rudders and ailerons combined with spoilers for roll control. Pitch is controlled by the canard surface. The landing gear includes laminated fiberglass main gear legs and a steerable nosewheel. The aft-mounted powerplant was a 300NaN0 Kawasaki 440, 300NaN0 Cuyuna 430R or a 280NaN0 Rotax 277. The Goldwing has a 16:1 glide ratio.
In flight the aircraft is reported to be very pitch-sensitive.
