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3. En route
3.1 All power-units operating
At each point along the route and planned diversion therefrom,
the all power-units operating performance ceiling appropriate
to the aeroplane mass at that point, taking into account the
amount of fuel and oil expected to be consumed, is not less
than the minimum altitude (see Chapter 4, 4.2.6) or, if greater,
the planned altitude which it is intended to maintain with all
power-units operating, in order to ensure compliance with 3.2
and 3.3.
3.2 One power-unit inoperative
From each point along the route and planned diversions
therefrom, it is possible in the event of one power-unit
becoming inoperative to continue the flight to an en-route
alternate aerodrome where a landing can be made in
accordance with 4.2 and, on anival at the aerodrome, the net
gradient of climb is not less than zero at a height of 450 m
(1 500 ft) above the elevation of the aerodrome.
3.3 Two power-units inoperative
(applicable only to aeroplanes with four power-units)
For each point along the route or planned diversions
therefrom, at which the aeroplane is more than 90 minutes'
flying time at all power-units operating cruising speed from an
en-route alternate aerodrome, the two power-units inoperative
net flight path is such that a height of at least 300 m (1 000 ft)
above terrain can be maintained until arrival at such an
aerodrome.
Note.- The net flight path is that attainable from the
expected gradient of climb or descent diminished by 0.2 per
cent.
3.4 Conditions
The ability to comply with 3.1, 3.2 and 3.3 is assessed:
a) either on the basis of forecast temperatures, or on the
basis of declared temperatures giving an equivalent
average level of performance;
b) on the forecast data on wind velocity versus altitude and
locality assumed for the flight plan as a whole;
C) in the case of 3.2 and 3.3, on the scheduled gradient of
climb or gradient of descent after power failure
appropriate to the mass and altitude at each point
considered;
ATT C-11 1/11/01
Antler 6 - Operation of Aircraft
d) on the basis that, if the aeroplane is expected to gain
altitude at some point in the flight after power failure
has occurred, a satisfactory positive net gradient of
climb is available;
e) in the case of 3.2 on the basis that the minimum altitude
(see Chapter 4,4.2.6), appropriate to each point between
the place at which power failure is assumed to occur and
the aerodrome at which it is intended to alight, is
exceeded;
f) in the case of 3.2, making reasonable allowance for
indecision and navigational error in the event of powerunit
failure at any point.
4. Landing
4.1 Mass
The calculated mass for the expected time of-landing at the
aerodrome of intended landing or any destination alternate
aerodrome is not to exceed the maximum specified in the
flight manual for the altitude and temperature at which the
landing is to be made.
4.2 Landing distance required
The landing distance required at the aerodrome of the intended
landing or at any alternate aerodrome, as determined from the
flight manual, is not to exceed the landing distance available on:
a) the most suitable landing surface for a landing in still
air; and, if more severe,
b) any other landing surface that may be required for
landing because of expected wind conditions at the time
of arrival.
4.3 Conditions
For the purpose of 4.2, the landing distance required is that
corresponding to:
a) the calculated mass of the aeroplane for the expected
time of landing;
b) an altitude equal to the elevation of the aerodrome;
c) the expected temperature at which landing is to be made
or a declared temperature giving an equivalent average
level of performance;
d) the surface slope in the direction of landing;
e) for the purpose of 4.2 a), still air;
f) for the purpose of 4.2 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 2 ON AEROPLANE PERFORMANCE OPERATING LIMITATIONS -
PROCEDURES USED IN DETERMINING TAKE-OFF AND LANDING PERFORMANCE
1. General
1.1 Unless otherwise stated, reference humidity and still
air conditions are applied.
1.2 The performance of the aeroplane is determined in
such a manner that the approved airworthiness limitations for
the aeroplane and its systems are not exceeded.
1.3 The wing flap positions for showing compliance with
　
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