Single seat single engined high wing mono¬plane with hybrid control. Wing has constant chord; cruciform tail. Pitch control by weight¬shift; yaw control by fully flying rudder; no separate roll control; control inputs through weight shift for pitch/yaw/roll. Wing braced from above by kingpost and cables, from below by cables; single ¬surface. Undercarriage has three wheels in tricycle formation; torsion bar suspension on all wheels. Nosewheel steering. No brakes. Aluminium tube framework, without pod. Engine mounted above wing driving pusher propeller. Framework from 6061T6 and 2024T3 aluminium, 4130 aircraft steel; coated stainless steel rigging, Dacron wing surface.
The Canadian Skyrider is a hybrid control ultra¬light, the pilot using his swing seat as the principal means of control, with his weight shift aided in yaw by a rudder.
Standard power unit is a twin cylinder Cuyuna 430R with dual ignition and in flight recoil restart facility. Alternatively, the sing¬le cylinder Cuyuna 215 cc engine may be fitted. Construction time is estimated at 30 h; a trailer is needed for transportation.
After producing between 150 and 200 aircraft, the future of the company seemed in some doubt in 1983.

Engine: Cuyuna 430R, 30 hp
Propeller: 48 x 23 inch, 1.22 x 0.58 m
Reduction ratio: 2.0/1
Power per unit area: 0.19 hp/sq.ft, 2.0 hp/sq.m
Wing span: 32.0ft, 9.75m
Fuel capac¬ity: 3.8 USG, 3.2 ImpG, 14.4 lt
Contant chord: 5.0 ft, 1.52 m
Total wing area: 160 sq.ft, 14.9 sq.m
Aspect ratio: 6.4/1
Nosewheel dia. Overall: 11 inch, 28cm
Empty weight: 155 lb, 70 kg
Main wheels dia overall: 11 inch, 28cm
MTOW: 420 lb, 191 kg
Payload: 265 lb, 120 kg
Vne: 55 mph, 88 kph
Wing loading: 2.62 lb/sq.ft, 12.8 kg/sq.m
Power loading: 14.0 lb/hp, 6.4 kg/hp

Engine: Cuyuna 215R, 20 hp
Power per unit area: 0.13 hp/ sq.ft, 1.3 hp/ sq.m
Wing span 32.0ft, 9.75m.
Fuel capac¬ity: 3.8 USG, 3.2 ImpG, 14.4 lt
Contant chord: 5.0 ft, 1.52 m
Total wing area: 160 sq.ft, 14.9 sq.m
Aspect ratio: 6.4/1
Nosewheel dia overall: 11 inch, 28cm
Vne: 55 mph, 88 kph
Main wheels dia overall: 11 inch, 28cm

Single seat single engined mid wing mono¬plane with conventional three axis control. Wing has swept forward leading and trailing edges, and tapering chord; T tail. Pitch control by elevator on tail; yaw control by fin mounted rudder; roll control by one third span ailerons; control inputs through stick for pitch/roll and pedals for yaw. Cantilever wing; wing profile Worthmann FX 66SA96 V1; dou¬ble surface. Undercarriage has two wheels in tandem with wing tip skids and tailskid; no suspension on any wheels. Push right go right tailwheel steering connected to yaw control. Brake on main wheel. Glass fibre fuselage, totally enclosed. Engine mounted above wing driving pusher propeller.
The designation PLM80 clearly shows that this aircraft is what the French call a planeur leger motorise, which translates as motor glider rather than micro¬light. As we write, this prototype has hardly completed its first flights and at present exceeds most countries’ definition of a micro¬light. In 1982, this latest product from Aerostruc¬ture is being test flown with a view to conventional certification.
Its structure is made entirely of glass fibre laminates, as with all modern conventional gliders, and the PLM80 has a Worthmann FX66S-196V1 profile, set at 1½O incidence and with the maximum coefficient of lift of 1.5. The drag coefficient 0.45. The wing is also fitted with air brakes, totalling 1.79sq.ft (0.166sq.m) in surface area and which can travel from + 16 to 21%. The T tail uses Worthmann FK71L 150/42.5 profiles vertical fin and 150/30 for the horizontal, with the latter installed at 2.5% incidence.
The engine is also a prototype, the three ¬cylinder French PAL640 from JPX, which was on static show at the end of July 1982 at Brienne le Chateau, the annual convention for European homebuilders. At that time it had just completed its bench testing. It drives a three bladed propeller directly, of fixed pitch and 37 inch (0.93 m) diameter.

Engine: JPX PAL640, 32 hp at 4600 rpm.
Propeller diameter: 37 inch, 0.93 m.
Power per unit area: 0.46 hp/sq.ft, 5.0 hp/sq.m.
Empty weight: 353 lb, 160kg.
Max take off weight: 618 lb, 280kg.
Payload: 265 lb, 120kg.
Max wing loading: 8.95 lb/ sq.ft, 43.8 kg/sq.m.
Max power loading: 19.3 lb/hp, 8.8kg/hp.
Load factors: +8.0, 4.0 ultimate.
Length overall: 16.7 ft, 5.1 m.
Height overall: 3.5ft, 1.04m.
Wing span: 36.1ft, 11.0m.
Chord at root: 2.7ft, 0.8m.
Chord at tip: 1.2ft, 0.35m.
Dihedral: 4 degs
Sweep forward: 3.5degs
Tailplane span: 5.9 ft, 1.8 m.
Fin height: 3.4ft, 1.0 m.
Total win area: 69 sq.ft, 6.4 sq.m.
Total aileron area: 9.1 sq.ft, 0.85 sq.m.
Fin area: 6.5 sq.ft, 0.6 sq.m.
Rudder area: 2.7 sq.ft, 0.25 sq.m.
Tailplane area: 7.8 sq.ft, 0.72 sq.m.
Total elevator area: 2.3 sq.ft, 0.22 sq.m.
Wing aspect ratio: 18.9/1.
Tailwheel diar overall: 8 inch, 20 cm.
Main wheel dia overall: 12 inch, 30 cm.