• meet the Transport Canada eligibility requirements for registration as a basic ultra-light aeroplane;
• apply to Transport Canada, Civil Aviation for registration marks to be assigned to your aeroplane;
• apply to Transport Canada, Civil Aviation to register your aeroplane;
• provide aeroplane-specific documentation with the application;
• pay the applicable fee(s).

• meet the basic ultra-light definition set out below.

• apply to the appropriate Transport Canada, Civil Aviation office for registration marks to be issued to the aeroplane. Registration marks will be issued in the C-I series.

• complete the form entitled Application for registration of ultra-light or advanced ultra-light aeroplane (form 26-0521). Forms may also be obtained from any Transport Canada, Civil Aviation office;
• attach the proof of ownership document (e.g. bill of sale, statement of construction from plans or raw materials);
• include a photo of the aeroplane ID plate, clearly showing the name of the manufacturer, model and serial number;
• include fee payment;
• provide the form, attachments and fee to the appropriate Transport Canada, Civil Aviation office.

• contact any office at:  http://www.tc.gc.ca/
  Civilaviation/general/ccarcs/RegionalOffices.htm;
• view the Ultra-Light Aeroplane Transition Strategy at:  http://www.tc.gc.ca/civilaviation/general/
  recavi/Ultralight/ULTransitionStrategy/menu.htm;
• view Part II of the Canadian Aviation Regulations (CARs) and associated standard on aircraft registration at:  http://www.tc.gc.ca/
  civilaviation/RegServ/Affairs/cars/menu.htm;
• call the Transport Canada, Civil Aviation Communications Centre at 1-800-305-2059.

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