Single seat single engined high wing monoplane with conventional three axis control. Wing has unswept leading and trailing edges, and constant chord; cruciform tail. Pitch control by elevator on tail; yaw control by fin mounted rudder; roll control by half span ailerons; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from below by struts; wing profile; double surface. Undercarriage has three wheels in tricycle formation; suspension on all wheels. Push right go right nose-wheel steering connected to yaw control. Aluminium tube/steel tube framework, with optional pod. Engine mounted at wing height driving tractor propeller.

Phantom Aircraft Firecracker Article

This prototype was undergoing an intensive test flying programme in 1983.

Engine: Zenoah G25B, 22 hp at 6500 rpm
Power per unit area 0.14 hp/sq.ft, 1.6hp/sq.m
Fuel capacity 5.0 US gal, 4.2 Imp gal, 18.9 litre
Length overall 17.0 ft, 5.18 m
Height overall 7.0ft, 2.13m
Wing span 32.0ft, 9.75m
Constant chord 4.8 ft, 1.43 m
Sweepback 0 deg
Total wing area 150 sq.ft, 13.9 sq.m
Wing aspect ratio 6.8/1
Empty weight 216 lb, 98kg
Max take off weight 450 lb, 204kg
Payload 234 lb, 106kg
Max wing loading 3.0 lb/sq.ft, 14.6kg/sq.m
Max power loading 20.5 lb/hp, 9.3kg/hp
Load factors; +4.5, 3.0 ultimate
Max level speed 65 mph, 105 kph
Max cruising speed 55 mph, 88 kph
Stalling speed 25 mph, 40 kph
Max climb rate at sea level 600 ft/min, 3.0 m/s
Min sink rate 290 ft/min, 1. 5 m/s
Best glide ratio with power off 10/1
Take off distance 100ft, 30m
Landing distance 125ft, 38m
Service ceiling 10,000ft, 3050m
Range at average cruising speed 165 mile, 265 km

The 1983 PGO Aviation AJS 2000 is a two-seater tandem multiaxis ultralight. It was fitted with dual controls, hydraulic disc brake, and Fournalès shock absorbers.

Engine: Rotax 532, 65 hp
Wingspan: 10.60 m
Wing area: 16 sq.m
Fuel capacity: 40 lt
VNE: 145 km / h
Cruise: 110 km / h
VSo: 55km / h
Fuel consumption: 13 lt/hr