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2) the aeroplane remains on or close to the ground;
3) the landing gear remains extended.
b) The horizontal distance traversed and the height attained
by the aeroplane operating at the take-off safety speed
during the time required to retract the landing gear,
retraction being initiated at the end of 2.6.2.1 a) with:
1) the critical power-unit inoperative, its propeller
windmilling, and the propeller pitch control in the
position recommended for normal use during takeoff,
except that, if the completion of the retraction of
the landing gear occurs later than the completion of
the stopping of the propeller initiated in accordance
with 2.6.2.1 c) I), the propeller may be assumed to
be stopped throughout the remainder of the time
required to retract the landing gear;
2) the landing gear extended
c) When the completion of the retraction of the landing
gear occurs earlier than the completion of the stopping
of the propeller, the horizontal distance traversed and
the height attained by the aeroplane in the time elapsed
from the end of 2.6.2.1 b) until the rotation of the
inoperative propeller has been stopped, when:
1) the operation of stopping the propeller is initiated not
earlier than the instant the aeroplane has attained a
total height of 15.2 m (50 ft) above the take-off
surface:
2) the aeroplane speed is equal to the take-off safety
speed;
3) the landing gear is retracted;
4) the inoperative propeller is windmilling with the
propeller pitch control in the position recommended
for normal use during take-off.
d) The horizontal distance traversed and the height attained
by the aeroplane in the time elapsed from the end of
2.6.2.1 c) until the time limit on the use of take-off
power is reached, while operating at the take-off safety
speed, with:
1) the inoperative propeller stopped;
2) the landing gear retracted.
The elapsed time from the start of the take-off need not extend
beyond a total of 5 minutes.
e) The slope of the flight path with the aeroplane in the
configuration prescribed in 2.6.2.1 d) and with the
remaining power-unit(s) operating within the maximum
continuous power limitations, where the time limit on
the use of take-off power is less than 5 minutes.
2.6.2.2 If satisfactory data are available, the variations in
drag of the propeller during feathering and of the landing gear
throughout the period of retraction are permitted to be taken into
account in determining the appropriate portions of the elements.
2.6.2.3 During the take-off and subsequent climb
represented by the elements, the wing flap control setting is
not changed, except that changes made before the critical point
has been reached, and not earlier than 1 minute after the
critical point has been passed, are permitted; in this case, it is
demonstrated that such changes can be accomplished without
undue skill, concentration, or effort on the part of the pilot.
2.6.3 Continuous method
2.6.3.1 The take-off path is determined from an actual
take-off during which:
a) the critical power-unit is made inoperative at the critical
point;
b) the climb-away is not initiated until the take-off safety
speed has been reached and the airspeed does not fall
below this value in the subsequent climb;
c) retraction of the landing gear is not initiated before the
aeroplane reaches the take-off safety speed;
d) the wing flap control setting is not changed, except that
changes made before the critical point has been reached,
and not earlier than 1 minute after the critical point has
been passed, are permitted; in this case, it is
demonstrated that such changes can be accomplished
without undue skill, concentration, or effort on the part
of the pilot;
ATT C-7
Annex 6 - Operation of Aircraft
e) the operation of stopping the propeller is not initiated
until the aeroplane has cleared a point 15.2 m (50 ft)
above the take-off surface.
2.6.3.2 Suitable methods are provided and employed to
take into account, and to correct for, any vertical gradient of
wind velocity which may exist during the take-off.
1) sea level;
2) aeroplane mass equal to the maximum landing mass
at sea level;
3) level, smooth, dry and hard landing surfaces (landplanes);
4) smooth water of declared density (seaplanes);
2.7 Take-off distance required
b) over selected ranges of the following variables:
The take-off distance required is the horizontal distance along
the take-off flight path from the start of the take-off to a point
where the aeroplane attains a height of 15.2 m (50 ft) above
　
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