Sundog One-Seater
# Sundog One-Seater

The Sundog One-Seater (also called the Pup) is a Canadian powered parachute that was designed and produced by Sundog Powerchutes of Sparwood, British Columbia and later Pierceland, Saskatchewan. Now out of production, when it was available the aircraft was supplied as a complete ready-to-fly-aircraft.

The aircraft was introduced in 2002 and production ended when the company went out of business in 2014.

## Design and development

The One-Seater was designed to comply with the Canadian Basic Ultra-Light Aeroplane rules, but also fit the Fédération Aéronautique Internationale microlight category, including the category's maximum gross weight of 450 kg (992 lb). The aircraft has a maximum gross weight of 308 kg (679 lb). It features a 500 sq ft (46 $m^2)$ Apco 500 parachute-style wing, single seat accommodation, tricycle landing gear and a single 50 hp (37 kW) Rotax 503 two-stroke engine in pusher configuration. The prototype was equipped with a Hirth engine.

The aircraft carriage is built from bolted 6061-T6 aluminium, stainless steel fittings and aircraft bolts. In flight steering is accomplished via foot pedals that actuate the canopy brakes, creating roll and yaw. On the ground the aircraft has lever-controlled nosewheel steering. The main landing gear incorporates spring rod suspension. The pilot is protected by a series of circular aluminium tubes in the event of a roll-over. Fuel capacity is 5 U.S. gallons (19 L; 4.2 imp gal) or optionally 10 U.S. gallons (38 L; 8.3 imp gal).

The aircraft has an empty weight of 302 lb (137 kg) and a gross weight of 679 lb (308 kg), giving a useful load of 377 lb (171 kg). With full fuel of 10 U.S. gallons (38 L; 8.3 imp gal) the payload for crew and baggage is 317 lb (144 kg).

The company also supplied custom trailers for towing the aircraft behind an automobile.

## Operational history

In September 2015 there was one example, the prototype, on the Transport Canada registry, although its registration had been cancelled in May 2004. There were none registered in the United States with the Federal Aviation Administration.

## Specifications (One-Seater)

Data from Bertrand and manufacturer

General characteristics

* Crew: one
* Length: 8.41 ft (2.56 m)
* Width: 6.33 ft (1.93 m) carriage only
* Height: 7.0 ft (2.1 m) carriage only
* Wing area: 500 sq ft (46 $m^2)$
* Empty weight: 302 lb (137 kg)
* Gross weight: 679 lb (308 kg)
* Fuel capacity: 5 U.S. gallons (19 L; 4.2 imp gal) or optionally 10 U.S. gallons (38 L; 8.3 imp gal)
* Powerplant: 1 × Rotax 503 twin cylinder, two-stroke, air-cooled aircraft engine, 50 hp (37 kW)
* Propellers: 3-bladed ground adjustable composite Powerfin or GSC Systems

Performance

* Maximum speed: 33 mph (53 km/h, 29 kn)
* Cruise speed: 28 mph (45 km/h, 24 kn)
* Maximum glide ratio: 5:1
* Rate of climb: 800 ft/min (4.1 m/s)
* Rate of sink: 700 ft/min (3.6 m/s)
* Wing loading: 1.4 lb/sq ft (6.8 $kg/m^2)$
