Design work on the Viper began in 2004, with the first flight on 1 November 2006 and market introduction in 2008. It is intended for touring, training and glider towing. The Viper is constructed mostly of metal, with aluminium skinning, using CNC machining. Composite materials are used for the tips of the flying surfaces, the fuselage upper decking, engine cowling and wheel fairings. The wings have constant chord and curved, slightly upswept tips; they are built around one main and one auxiliary spar. The short span ailerons move on piano-type hinges, with slotted flaps on the rest of the trailing edges. The low-mounted horizontal tail is also of constant chord apart from a cut-out for rudder movement; the starboard elevator carries a flight adjustable trim tab. Fin and rudder are straight-edged, but swept. The standard Viper is powered by a 60 kW (81 hp) Rotax 912UL flat four engine but the more powerful 75 kW (100 hp) Rotax 912ULS is an option. The forward fuselage is a monocoque, the rear a tube structure with an aluminium skin. The cockpit seats two in side-by-side configuration under a framed single piece canopy, with further transparencies in the fuselage immediately aft. The main undercarriage legs are cantilever springs. The mainwheels are faired and fitted with hydraulic brakes; the nosewheel is also faired and may, as an option, be steerable. Other options include instrumentation, ballistic parachute and towing gear. The aircraft received its EASA SD4 RTC restricted type certificate in March 2016. In the US it is an accepted light-sport aircraft. Variants UL Ultralight aircraft version with maximum gross weight of 472.5 kg (1,042 lb) with a ballistic parachute, for the European market. LSA Light-sport aircraft version with maximum gross weight of 600 kg (1,323 lb) with a ballistic parachute, for the US market. For specifications of the LSA version, click here. Specifications below are for the UL version.
