Ultra-light Aeroplane Definitions
(a) a single-seat aeroplane that has a launch weight of 165 kg
(368.8 pounds) or less, and a wing area, expressed in square metres, of
not less than the launch weight minus 15, divided by 10, and in no case less
than 10 m²;
(b) a two-seat instructional aeroplane that has a launch weight of
195 kg (429.9 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 pounds/ft.² ), the wing loading being calculated using
the launch weight plus the occupant weight of 80 kg (176.4 pounds) per
person; or
(c) an aeroplane having no more than two seats, designed and manufactured
to have a maximum take-off weight of 544 kg (1199 pounds) and a stall
speed in the landing configuration (Vso) of 39 knots (45 mph) or less
indicated airspeed at the maximum take-off weight.
If registering a basic ultra-light aeroplane under option (c), the following
minimum useful load (Mu or Wu) calculation shall be carried out:
For a single-place aeroplane
Mu = 80 + 0.3P, in kg; where P is the rated engine power in kilowatts
(Wu) = 175 + 0.5P, in lb.; where P is the rated engine power in Brake Horse
Power
For a two-place aeroplane
Mu = 160 + 0.3P, in kg; where P is the rated engine power in kilowatts
(Wu) = 350 + 0.5P, in lb.; where P is the rated engine power in Brake Horse
Power
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