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(d) a weight which, allowing for normal consumption of fuel and oil in flight
and taking into account either the forecast temperature and pressure or
approved declared conditions, will permit compliance with the landing
distance limitations specified in subsection 10 related to the longest
available landing length under conditions of zero wind.
5 LANDING WEIGHT LIMITATIONS
5.1 Except in an emergency, an aeroplane must not land at a weight in excess of
the least of the weights determined in accordance with subparagraphs (a) and
(b):
(a) a weight at which the landing distance required in accordance with
subsection 10 for the pressure height, temperature, runway slope (if in
excess of 1%), and wind component along the runway at the time of
landing, is equal to or less than the landing distance available in the
direction of landing. Approved declared conditions may be used instead of
actual pressure height and temperature;
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Amdt No. 212
-3- SECTION 20.7.4
Issue 4
(b) a weight which will permit compliance with the landing climb
requirements specified in subsection 9, taking into account the elevation of
the aerodrome of landing instead of actual pressure height and
temperature.
6 TAKE-OFF DISTANCE REQUIRED
6.1 Subject to paragraph 6.3, the take-off distance required is the distance to
accelerate from a standing start with all engines operating and to achieve takeoff
safety speed at a height of 50 feet above the take-off surface, multiplied by
the following factors:
(a) 1.15 for aeroplanes with maximum take-off weights of 2 000 kg or less;
(b) 1.25 for aeroplanes with maximum take-off weights of 3 500 kg or
greater; or
(c) for aeroplanes with maximum take-off weights between 2 000 kg and
3 500 kg, a factor derived by linear interpolation between 1.15 and 1.25
according to the maximum take-off weight of the aeroplane.
6.2 For aeroplanes operated on land, take-off distances are to be determined for a
level short dry grass surface. For aeroplanes operated on water, take-off
distances are to be determined taking into account the maximum crosswind
component and the most adverse water conditions for the aeroplane type.
6.3 Where there is an approved foreign flight manual or a manufacturer’s data
manual for an aeroplane that sets out the take-off distance required for that
aeroplane, then that aeroplane must be operated so as to comply with either the
requirements set out in paragraphs 6.1 and 6.2 or the requirements relating to
take-off distance set out in either of those manuals.
Note: The data contained in some manufacturers’ data manuals is unfactored and makes no
allowance for degraded aircraft performance. Where there is a considerable difference
between the data in a manufacturer’s data manual and the data in the flight manual for the
aeroplane then the manufacturer’s data should be treated with caution.
7 TAKE-OFF CLIMB PERFORMANCE
7.1 In the take-off configuration with landing gear extended, an aeroplane must
have the ability to achieve a climb gradient of 6% at take-off safety speed,
without ground effect, and with all engines operating at take-off power.
8 EN-ROUTE CLIMB PERFORMANCE
8.1 Multi-engined aeroplanes engaged in charter operations under the Instrument
Flight Rules or aerial work operations under the Instrument Flight Rules must
have the ability to climb with a critical engine inoperative at a gradient of 1%
at all heights up to 5 000 feet in the standard atmosphere in the following
configuration:
(a) propeller of inoperative engine stopped;
(b) undercarriage (if retractable) and flaps retracted;
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Amdt No. 212
SECTION 20.7.4 -4-
Issue 4
(c) remaining engine(s) operating at maximum continuous power;
(d) airspeed not less than 1.2 VS.
8.2 Multi-engined aeroplanes (other than those specified in paragraph 8.1) must
have the ability to maintain height at all heights up to 5 000 feet in the standard
atmosphere in the configuration specified in subparagraphs 8.1 (a), (b), (c) and
(d).
8.3 Single-engined aeroplanes must have the ability to climb at a gradient of 4.5%
at an airspeed not less than 1.2VS at all heights up to 5 000 feet in standard
atmospheric conditions with the engine operating at maximum continuous
power, undercarriage (if retractable) and flaps retracted.
9 LANDING CLIMB PERFORMANCE
9.1 In the landing configuration with all engines operating at take-off power an
aeroplane must have the ability to climb at a gradient of 3.2% in standard
atmospheric conditions at a speed not exceeding 1.3VS.
10 LANDING DISTANCE REQUIRED
　
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