JAR 23

maximum weight)) or 66·8 N (15 lb), whichever is greater, except that it need not be greater than 156 N (35
lb).
(b) The requirement of sub-paragraph (a) of this paragraph must be met with wing flaps and landing gear
retracted under each of the following conditions -
(1) At 75% of maximum continuous power for reciprocating engines or maximum continuous power
for turbine engines.
(2) In a turn, after the aeroplane is trimmed with wings level, at the minimum speed at which the
required normal acceleration can be achieved without stalling, and at the maximum level flight trim speed
except that the speed may not exceed VNE or VMO/MMO, whichever is appropriate.
(c) There must be no excessive decrease in the gradient of the curve of stick force versus manoeuvring load
factor with increasing load factor.
JAR 23.157 Rate of roll
(a) Take-off. It must be possible, using a favourable combination of controls, to roll the aeroplane from a
steady 30° banked turn through an angle of 60°, so as to reverse the direction of the turn within -
and
(1) For an aeroplane of 2730 kg (6000 lb) or less maximum weight, 5 seconds from initiation of roll;
(2) For aeroplanes of over 2730 kg (6000 lb) maximum weight,
W+200
590
but not more than 10 seconds, where W is the weigh in kg,
⎛ W + 500
⎜
⎝ 1300 but not more than 10 seconds, where W is the weight in lb.)
(b) The requirement of sub-paragraph (a) must be met when rolling the aeroplane in each direction in the
following conditions -
(1) Flaps in the take-off position;
(2) Landing gear retracted;
(3) For a single-engined aeroplane, at maximum take-off power and for a twin-engined aeroplane,
with the critical engine inoperative, the propeller in the minimum drag position and the remaining engine at