Photograph:
Aero Design Pulsar VH-BTS3 (c/n N353) at Narromine, NSW (David C Eyre)
Country of origin:
United States of America
Description:
Two-seat light sport monoplane
Power Plant:
One 60 kw (80 hp) Rotax 912 four-cylinder, four-stroke, horizontally-opposed liquid-and-air-cooled engine
Specifications:
- Wingspan:7.62 m (25 ft)
- Length: 5.94 m (19 ft 6 in)
- Height: 1.92 m (6 ft 4 in)
- Wing area: 7.43 m² (80 sq ft)
- Max speed: 258 km/h (160 mph)
- Max cruising speed: 241 km/h (150 mph)
- Stalling speed full flap: 74 km/h (46 mph)
- Rate of climb: 366 m/min (1,200 ft/min)
- Service ceiling: 4,572 m (15,000 ft)
- Max range: 966 km (600 miles)
- Take-off run: 244 m (800 ft)
- Landing run: 244 m (800 ft)
- Fuel capacity: 105 litres ((23 Imp gals)
- Empty weight: 231 kg (510 lb)
- Loaded weight: 481 kg (1,060 lb)
History:
The Pulsar was produced by Aero Design Inc of San Antonio, Texas, USA and was a derivative of the Company’s Star-lite which won the Experimental Aircraft Association Outstanding New Design Award in 1983. In later times the type has been marketed by SkyStar Aircraft Corporation of Caldwell, Indiana as the Pulsar III.
Since its introduction to the light aircraft market the design has been developed and has basically been available in two models, mainly varying in the engine available, the 49 kw (66 hp) Rotax 582 two-stroke, or the 60 kw (80 hp) Rotax 912 four-stroke, with which it is known as the Pulsar XP. In Pulsar III form it could be fitted with the 86 kw (115 hp) Rotax 914 Turbocharged engine, or the 90 kw (120 hp) six-cylinder Jabiru 3300.
The Pulsar fuselage was made of epoxy sandwich, and the wing was fitted with a composite spar with plywood skinning. It was available in kit form as a homebuilt and could be fitted with either a tricycle or tailwheel undercarriage. Quite a number have been built around the world, including more than 30 in Great Britain where it became popular because the wing could be quickly removed, the aircraft placed on a trailer and taken to the owner’s home for storage. Design limits were +6 and –4G. The fuel capacity was 72 litres (15.8 Imp gals).
First of the type registered in New Zealand was ZK-RUS (c/n 325/MAANZ/510) and first in Australia was VH-JPA (c/n 153/W162) in mid 1995. Other examples have been completed and registered under ultralight RAA Regulations.