The Cadet was designed to comply with the US FAR 103 Ultralight Vehicles rules, including the category's maximum empty weight of 2540NaN0. The aircraft has a standard empty weight of 2480NaN0. It features a strut-braced high-wing, single-seat, open cockpit, single tractor engine configuration, and is equipped with tricycle landing gear.
The aircraft is made from bolted together aluminum alloy tubing, with the wings and tail covered in Dacron sailcloth. Its 301NaN1 span wing employs "V" lift struts and jury struts. The aircraft keel is an aluminum tube that runs from the tail, mounts the wings and the engine at its forward end. The standard factory-supplied engine is the 280NaN0 Rotax 277, driving a 600NaN0 diameter fixed-pitch propeller with a 280NaN0 pitch. The pilot sits on an open seat without a windshield. The control system is conventional three-axis, with half-span ailerons. The main landing gear is sprung steel and the nosewheel incorporates steering. There is a small tail caster to protect the tail. Brakes are optionally available.
Reviewer Andre Cliche describes the Cadet as "a clean and simple design that is inexpensive to maintain."
