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the performance specifications are selected.
Note.- Alternative wing flap positions are made available,
if so desired, in such a manner as to be consistent with
acceptably simple operating techniques.
1.4 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.
1.5 The performance of the aeroplane is determined in
such a manner that under all conditions the approved
limitations for the powerplant are not exceeded.
1/11/01 ATT C-12
Attachment C Annex 6 - Operation of Aircrafl
1.6 While certain configurations of cooling gills have
been specified based upon maximum anticipated temperature,
the use of other positions is acceptable provided that an
equivalent level of safety is maintained.
1.7 The determined performance is so scheduled that it
can serve directly in showing compliance with the aeroplane
performance operating limitations.
2.1 General
2.1.1 The following take-off data are determined for sea
f) take-off surface slope over the take-off distance required
(landplanes);
g) water surface condition (seaplanes);
h) density of water (seaplanes);
i) strength of current (seaplanes);
j) power failure point (subject to provisions of 2.4.3).
2.1.3 For seaplanes appropriate interpretations of the term
landing gear, etc., are made to provide for the operation of
retractable floats, if employed.
2.2 Take-off safety speed
level pressure and temperature in the Standard Atmosphere,
2.2.1 The take-off safety speed is an airspeed (CAS) so
and reference humidity conditions, with the aeroplane at the
selected that it is not less than:
corresponding maximum take-off mass for a level, smooth,
dry and hard take-off surface (landplanes) and for smooth
a) 1.20V,, , for aeroplanes with two power-units;
water of declared density (seaplanes):
a) take-off safety speed and any other relevant speed;
b) power failure point; 1 t associated with
c) power failure point criterion,
items d), e), f)
e.g. airspeed indicator reading;
d) accelerate-stop distance required;
e) take-off run required;
f) take-off distance required;
b) 1.15Vs,, for aeroplanes having more than two powerunits;
c) 1.10 times the minimum control speed, VMc, established
as prescribed in 2.3;
d) the minimum speed prescribed in 2.9.7.6;
where Vs, is appropriate to the take-off configuration.
Note.- See Example I for definition of 5, .
g) net take-off flight path; 2.3 Minimum control speed
h) radius of a steady Rate 1 (180 degrees per minute) turn 2.3.1 The minimum control speed is such that, when any
made at the airspeed used in establishing the net take- one power-unit is made inoperative at that speed, it is possible
off flight path, and the corresponding reduction in to recover control of the aeroplane with the one power-unit
gradient of climb in accordance with the conditions still inoperative and to maintain the aeroplane in straight flight
of 2.9. at that speed either with zero yaw or with a bank not in excess
of 5 degrees.
2.1.2 The determination is also made over selected ranges
of the following variables:
a) aeroplane mass;
b) pressure-altitude at the take-off surface;
c) outside air temperature;
d) steady wind velocity parallel to the direction of take-off;
e) steady wind velocity normal to the direction of take-off
(seaplanes);
2.3.2 From the time at which the power-unit is made
inoperative to the time at which recovery is complete,
exceptional skill, alertness, or strength, on the part of the pilot
is not required to prevent any loss of altitude other than that
implicit in the loss of performance or any change of heading
in excess of 20 degrees, nor does the aeroplane assume any
dangerous attitude.
2.3.3 It is demonstrated that to maintain the aeroplane in
steady straight flight at this speed after recovery and before
retrimming does not require a rudder control force exceeding
800 N and does not make it necessary for the flight crew to
reduce the power of the remaining power-units.
ATT C-13 1/11/01
Annex 6 - Operation of Aircraft Part I
2.4 Power failure point 2.7 Take-off distance required
2.4.1 The power failure point is the point at which sudden 2.7.1 The take-off distance required is the distance
complete loss of power from the power-unit, critical from the required to reach a height of:
performance aspect in the case considered, is assumed to
occur. If the airspeed corresponding to this point is less than 10.7 m (35 ft), for aeroplanes with two power-units,
　
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