The CAVOK project began in the middle of 2000. The primary development model was the CAVOK 10, with a wingspan of , extendable to with
wing tip extensions. The design goals for the aircraft included maximizing performance for the price, compliance with JAR 22 rules for standard class sailplanes and also European ultralight category rules, including French ULM regulations. Certification was also intended to JAR-VLA standards for countries that lack an ultralight category. The aircraft is built from
fibreglass and features a fixed, fuselage-mounted, single-cylinder,
two-stroke Gas Gas motorcycle engine, driving a retractable two-bladed fixed-pitch
tractor propeller. The engine can be started and run before extending and engaging the propeller. The wing features
flaperons and, unlike most other aircraft in this category, lacks wing-mounted
air brakes, the brake being fuselage mounted. The
landing gear consists of fixed nose, centre and tail wheels along with auxiliary wheels out on the wing from the
fuselage. The aircraft is finished in white
polyurethane paint. The aircraft was designed for quick assembly and disassembly by one person without assistance, as no part weighs over . The aircraft is normally transported by towed trailer. The last news release the company put out, on 14 December 2002, indicated that development work had been delayed, but was underway at that time. The company website had been removed by 2005 and it is likely that only prototypes were completed and flown. ==Specifications (CAVOK 10) ==