Bushcaddy R80 Spec and information

Flagship of the fleet the R80 boasts outstanding Stol performance, cruise speed and a number of engine choices.

The Bushcaddy R-80 is a Canadian ultralight and light-sport aircraft that was designed by Jean Eudes Potvin of Lac Saint-Jean, Quebec in 1994 and produced by his company Club Aeronautique Delisle  Incorporated (CADI). It was later built by Canadian Light Aircraft Sales and Service (CLASS) of St. Lazare, Quebec and later Les Cedres, Quebec and now Bushcaddy International with head office in China and the North American distributorship through Ottawa Aviation Services / Bushcaddy – North America.

The R-80 designation indicates that the aircraft was originally designed for a Rotax engine of 80 hp (60 kW).  The aircraft is supplied as a kit for amateur construction or as a complete ready-to-fly-aircraft.

The aircraft was designed to comply with the Canadian advanced ultralight rules and is also an approved US light-sport aircraft. It features a strut-braced high-wing, a two-seats-in-side-by-side configuration enclosed cockpit, fixed tricycle landing gear or conventional landing gear and a single engine in tractor configuration.

The aircraft is made from 6061-T6 aluminum sheet over a cage of welded aluminum square 6061-T6 aluminum tube. The tail boom is conventional semi-monocoque construction. The non-tapered planform wings have 6061-T6 ribs and spars and employ a NACA 4413 (mod) airfoil. The airfoil modification removes the undercamber on the bottom of the wing, which makes construction easier, without giving up low speed performance. The aircraft's structure uses 2024-T3 aluminium for critical parts where extra strength is required, such as the spar, float and strut attachments as well as other critical components like the rudder horns. The R-80's structure is covered with 6061-T6 sheet of varying thicknesses; wing bottom skins are 0.016 in (0.41 mm) inches thick while the top is 0.020 in (0.51 mm) inches. The wings are supported by conventional "V" struts. 6061-T6 is predominantly used for its lower cost and also its better corrosion resistance, since many R-80s are flown on floats. Its 32 ft (9.8 m) span wing has an area of 168 sq ft (15.6 m2) and does not fit flaps.

Standard engines used on the R-80 include the 80 hp (60 kW) Rotax 912UL and the 100 hp (75 kW) Rotax 912ULS four-stroke powerplants. The 115 hp (86 kW) turbocharged Rotax 914 has also been fitted. The aircraft is also approved for the new MW Fly Aeropower B22R engine from Italy, producing 130 bhp, normally aspirated. See mwflyna.com for further information. The aircraft can also be mounted on floats and skis. Controls include a central "Y" control stick.

Construction time for the R-80 from the factory kit is 1,200 hours.



General characteristics
Crew: one
Capacity: one passenger
Length: 22 ft 1 in (6.73 m)
Wingspan: 32 ft (9.8 m)
Wing area: 168 sq ft (15.6 m2)
Airfoil: NACA 4413 (mod)
Empty weight: 710 lb (322 kg)
Gross weight: 1,320 lb (599 kg) (1500 lbs with factory approval)
Fuel capacity: 90 litres (20 imp gal; 24 US gal)
Powerplant: 1 × Rotax 912ULS four cylinder, liquid and air-cooled, four stroke aircraft engine, 100 hp (75 kW)