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as determined from the flight manual, is not to exceed 60 per
cent of the landing distance available on:
a) the most suitable landing surface for a landing in still
air; and, if more severe,
where N is the number of power-units installed; b) any other landing surface that may be required for
landing because of expected wind conditions at the time
of arrival.
b) the aeroplane complies with 4.1.1 at 300 m (1 000 ft)
above the aerodrome used as an alternate in this
procedure; 5.2.2 Alternate aerodromes
c) after the power-unit failure considered, account is taken The landing distance at any alternate aerodrome, as
of the effect of winds and temperatures on the flight determined from the flight manual, is not to exceed 70 per cent
path; of the landing distance available on:
d) it is assumed that the mass of the aeroplane as it a) the most suitable landing surface for a landing in still
proceeds along its intended track is progressively air; and, if more severe,
reduced by normal consumption of fuel and oil;
b) any other landing surface that may be required for
e) it is customary to assume such fuel jettisoning as is landing because of expected wind conditions at the time
consistent with reaching the aerodrome in question. of arrival.
1/11/01 ATT C-4
Attachment C Annex 6 - Operation of Aircraft
Note.- The procedure used in determining the landing
distance is described in the Appendix to this example.
b) an altitude equal to the elevation of the aerodrome;
c) for the purpose of 5.2.1 a) and 5.2.2 a), still air;
5.3 Conditions
For the purpose of 5.2, the landing distances are not to exceed
those corresponding to:
a) the calculated mass of the aeroplane for the expected
time of landing;
d) for the purpose of 5.2.1 b) and 5.2.2 b), not more than
50 per cent of the expected wind component along the
landing path and opposite to the direction of landing and
not less than 150 per cent of the expected wind
component in the direction of landing.
APPENDIX TO EXAMPLE 1 ON AEROPLANE PERFORMANCE OPERATING LIMITATIONS -
PROCEDURES USED IN DETERMINING TAKE-OFF AND LANDING PERFORMANCE
1. General 2. Take-off
1.1 Unless otherwise specified, Standard Atmosphere and
still air conditions are applied.
1.2 Engine powers are based on a water vapour pressure
corresponding to 80 per cent relative humidity in standard
conditions. When performance is established for temperature
above standard, the water vapour pressure for a given altitude
is assumed to remain at the value stated above for standard
atmospheric conditions.
1.3 Each set of performance data required for a particular
flight condition is determined with the powerplant accessories
absorbing the normal amount of power appropriate to that
flight condition.
1.4 Various wing flap positions are selected. These
positions are permitted to be made variable with mass, altitude
and temperature in so far as this is considered consistent with
acceptable operating practices.
1.5 The position of the centre of gravity is selected within
the permissible range so that the performance achieved in the
configuration and power indicated in the specification under
consideration is a minimum.
1.6 The performance of the aeroplane is determined in
such a manner that under all conditions the approved
limitations for the powerplant are not exceeded.
2.1 General
2.1.1 The take-off performance data are determined:
a) for the following conditions:
1) sea level;
2) aeroplane mass equal to the maximum take-off mass
at sea level;
3) level, smooth, dry and hard take-off surfaces
(landplanes);
4) smooth water of declared density (seaplanes);
b) over selected ranges of the following variables:
1) atmospheric conditions, namely: altitude and also
pressure-altitude and temperature;
2) aeroplane mass;
3) steady wind velocity parallel to the direction of takeoff;
4) steady wind velocity normal to the direction of takeoff
(seaplanes);
5) uniform take-off surface slope (landplanes);
1.7 The determined performance is so scheduled that it 6) type of take-off surface (landplanes);
can serve directly in showing compliance with the aeroplane
performance operating limitations. 7) water surface condition (seaplanes);
ATT C-5
Annex 6 - Operation of Aircraft
8) density of water (seaplanes);
9) strength of current (seaplanes).
2.1.2 The methods of correcting the performance data to
obtain data for adverse atmospheric conditions include
appropriate allowance for any increased airspeeds and cowl
flap or radiator shutter openings necessary under such
　
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