Ultralight aircraft (Canada)
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The Canadian Aviation Regulations define two types of ultralight aircraft: basic ultra-light aeroplane (BULA), and advanced ultra-light aeroplane (AULA).
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[edit] Canadian definition of ultra-light
Regulation of ultra-light aircraft in Canada is covered by the Canadian Aviation Regulations, Part I, Subpart 1. An earlier definition of "ultra-light aeroplane", effective October 10, 1996, meant
- a single-seat aeroplane that has a launch weight of 165 kg (364 pounds) or less, and a wing area, expressed in square metres, of not less than the launch weight in kilograms minus 15, divided by 10, and in no case less than 10 m²,
- a two-seat instructional aeroplane that has a launch weight of 195 kg (430 pounds) or less, and a wing area, expressed in square metres, of not less than 10 m² and a wing loading of not more than 25 kg/m² (5.12 lb/ft²), the wing loading being calculated using the launch weight plus the occupant weight of 80 kg (176 pounds) per person, or
- an advanced ultra-light aeroplane;
On June 1, 2003, the definition was amended to state that an "ultra-light aeroplane" means either an advanced ultra-light aeroplane or a basic ultra-light aeroplane.
[edit] Basic ultra-light aeroplane
Regulation of ultralight aircraft in Canada is covered by the Canadian Aviation Regulations, which defines a "basic ultra-light aeroplane" as:
an aeroplane having no more than two seats, designed and manufactured to have:
- a maximum take-off weight not exceeding 544 kg (1,200 pounds), and
- a stall speed in the landing configuration (VS0) of 39 knots (45 mph) indicated airspeed, or less, at the maximum take-off weight;
[edit] Advanced ultra-light aeroplane
According to Canadian Aviation Regulations, Part I, Subpart 1, an "advanced ultra-light aeroplane" means an aeroplane that has a type design that is in compliance with the standards specified in the manual entitled Design Standards for Advanced Ultra-light Aeroplanes (DS10141).
An advanced ultra-light aeroplane is an aeroplane which:
- Is propeller driven;
- Is designed to carry a maximum of two persons, including the pilot;
- Has a maximum take-off mass, MTOmax or WTOmax, of:
- 350 kg (770 lb) for a single place aeroplane, or
- 560.0 kg (1232 lb) for a two place aeroplane;
- A maximum stalling speed in the landing configuration, VS0, at manufacturer's recommended maximum take-off mass (weight) not exceeding 72 km/h (20 m/s, 45 mph) (IAS); and
- Is limited to non-aerobatic operations. Non-aerobatic operations include:
- manoeuvres incident to normal flying
- stalls and spins (if approved for type);
- lazy eights, chandelles; and
- steep turns, in which the angle of bank is not more than 60º
[edit] Minimum useful load
Advanced ultra-light aeroplanes shall have a minimum useful load, MU or WU computed as follows:
- For a single place aeroplane:
-
- MU = 80 + 0.3P, in kg; where P is the rated engine(s) power in kilowatts;
- MU = 175 + 0.5P, in lb; where P is the rated engine(s) power in brake horsepower (bhp).
- For a two place aeroplane:
-
- MU = 160 + 0.3P, in kg; where P is the rated engine(s) power in kW;
- MU = 350 + 0.5P, in lb; where P is the rated engine(s) power in bhp).
[edit] Maximum empty mass (weight)
The maximum empty mass, MEmax, (WEmax) includes all operational equipment that is actually installed in the aeroplane. It includes the mass (weight) of the airframe, powerplant, required equipment, optional and specific equipment, fixed ballast, full engine coolant, hydraulic fluid, and the residual fuel and oil. Hence, the maximum empty mass (weight) = maximum take-off mass (weight) - minimum useful load.
The registration marks that will be issued to an advanced ultra-light aeroplane will begin with “C-Ixxx”.
