Canadian Aviation Regulations

704.46 (1) Subject to section 704.51, no air operator shall authorize a flight — and no person shall conduct a take-off — in an aeroplane unless the following conditions are met:

• (a) the weight of the aeroplane does not exceed the maximum take-off weight specified in the aircraft flight manual for the pressure-altitude and the ambient temperature at the departure aerodrome; and

• (b) after allowing for planned fuel consumption during the flight to the destination aerodrome or alternate aerodrome, the weight of the aeroplane does not exceed the maximum landing weight specified in the aircraft flight manual for the pressure-altitude and the ambient temperature at the destination aerodrome or alternate aerodrome.

(2) In the determination of the maximum take-off weight referred to in paragraph (1)(a) for a propeller-driven aeroplane having an MCTOW of not more than 5 700 kg (12,566 pounds),

• (a) the required accelerate-stop distance specified in the aircraft flight manual shall not exceed the accelerate-stop distance available (ASDA) unless

  • (i) the maximum take-off weight is not limited by the accelerate-stop distance requirements set out in the aircraft flight manual, and

  • (ii) the aeroplane has fewer than 10 passengers on board or is operated in a non-scheduled air service; and

• (b) the all-engines-operating take-off distance specified in the aircraft flight manual shall not exceed the take-off distance available (TODA).

(3) In the determination of the maximum take-off weight referred to in paragraph (1)(a) for a turbo-jet-powered aeroplane or a large aeroplane that is propeller-driven,

• (a) the required accelerate-stop distance specified in the aircraft flight manual shall not exceed the accelerate-stop distance available (ASDA) unless, in the case of a large aeroplane that is propeller-driven,

  • (i) the maximum take-off weight is not limited by the required accelerate-stop distance requirements set out in the aircraft flight manual, and

  • (ii) the aeroplane has fewer than 10 passengers on board;

• (b) the required take-off run specified in the aircraft flight manual shall not exceed the take-off run available (TORA); and

• (c) the required take-off distance specified in the aircraft flight manual shall not exceed the take-off distance available (TODA) unless, in the case of a large aeroplane that is propeller-driven,

  • (i) the maximum take-off weight is not limited by the take-off distance requirements set out in the aircraft flight manual, and

  • (ii) the aeroplane has fewer than 10 passengers on board.

(4) In the determination of the maximum take-off weights referred to in subsections (2) and (3), the following factors shall be taken into account:

• (a) the pressure-altitude at the aerodrome;

• (b) the ambient temperature at the aerodrome;

• (c) the runway slope in the direction of take-off; and

• (d) a wind component that is not more than 50% of the reported headwind or not less than 150% of the reported tailwind.

(5) In the case of a take-off or landing on a gravel runway, the maximum weights referred to in paragraphs (1)(a) and (b) shall be determined in accordance with the gravel runway information specified in the aircraft flight manual.

(6) In the absence of the information referred to in subsection (5) for a propeller-driven aeroplane, the maximum weights referred to in paragraphs (1)(a) and (b) shall be determined on the basis of the information specified in the aircraft flight manual for a dry, paved hard-surface runway that does not exceed 1 524 m (5,000 feet) in length, except that

• (a) no credit shall be allowed for reverse thrust;

• (b) in determining the maximum take-off weight, no credit shall be allowed for any clearway; and

• (c) the corresponding length of dry, paved hard-surface runway used to determine the take-off distance required, the accelerate-stop distance required and the landing distance required shall be obtained by dividing the length of the gravel runway by a factor of

  • (i) 1.10, in the case of an aeroplane with an MCTOW of not more than 5 700 kg (12,566 pounds), or

  • (ii) 1.15, in the case of a large aeroplane.