197
Federal Aviation Administration, DOT
§ 23.145
(3) Wing flaps in the landing position;
and
(4) A climb speed equal to V
REF
, as de-
fined in § 23.73(c).
[Doc. No. 27807, 61 FR 5187, Feb. 9, 1996, as
amended by Amdt. 23–62, 76 FR 75754, Dec. 2,
2011]
F
LIGHT
C
HARACTERISTICS
§ 23.141
General.
The airplane must meet the require-
ments of §§ 23.143 through 23.253 at all
practical loading conditions and oper-
ating altitudes for which certification
has been requested, not exceeding the
maximum operating altitude estab-
lished under § 23.1527, and without re-
quiring exceptional piloting skill,
alertness, or strength.
[Doc. No. 26269, 58 FR 42156, Aug. 6, 1993]
C
ONTROLLABILITY AND
M
ANEUVERABILITY
§ 23.143
General.
(a) The airplane must be safely con-
trollable and maneuverable during all
flight phases including—
(1) Takeoff;
(2) Climb;
(3) Level flight;
(4) Descent;
(5) Go-around; and
(6) Landing (power on and power off)
with the wing flaps extended and re-
tracted.
(b) It must be possible to make a
smooth transition from one flight con-
dition to another (including turns and
slips) without danger of exceeding the
limit load factor, under any probable
operating condition (including, for
multiengine airplanes, those condi-
tions normally encountered in the sud-
den failure of any engine).
(c) If marginal conditions exist with
regard to required pilot strength, the
control forces necessary must be deter-
mined by quantitative tests. In no case
may the control forces under the condi-
tions specified in paragraphs (a) and (b)
of this section exceed those prescribed
in the following table:
Values in pounds force applied
to the relevant control
Pitch Roll Yaw
(a) For temporary application:
Stick ....................................
60 30
............
Wheel (Two hands on rim)
75
50 ............
Values in pounds force applied
to the relevant control
Pitch Roll Yaw
Wheel (One hand on rim) ..
50
25 ............
Rudder Pedal .....................
............
............
150
(b) For prolonged application ....
10
5
20
[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as
amended by Amdt. 23–14, 38 FR 31819, Nov. 19,
1973; Amdt. 23–17, 41 FR 55464, Dec. 20, 1976;
Amdt. 23–45, 58 FR 42156, Aug. 6, 1993; Amdt.
23–50, 61 FR 5188, Feb. 9, 1996]
§ 23.145
Longitudinal control.
(a) With the airplane as nearly as
possible in trim at 1.3 V
S1
, it must be
possible, at speeds below the trim
speed, to pitch the nose downward so
that the rate of increase in airspeed al-
lows prompt acceleration to the trim
speed with—
(1) Maximum continuous power on
each engine;
(2) Power off; and
(3) Wing flap and landing gear—
(i) retracted, and
(ii) extended.
(b) Unless otherwise required, it must
be possible to carry out the following
maneuvers without requiring the appli-
cation of single-handed control forces
exceeding those specified in § 23.143(c).
The trimming controls must not be ad-
justed during the maneuvers:
(1) With the landing gear extended,
the flaps retracted, and the airplanes
as nearly as possible in trim at 1.4 V
S1
,
extend the flaps as rapidly as possible
and allow the airspeed to transition
from 1.4V
S1
to 1.4 V
SO
:
(i) With power off; and
(ii) With the power necessary to
maintain level flight in the initial con-
dition.
(2) With landing gear and flaps ex-
tended, power off, and the airplane as
nearly as possible in trim at 1.3 V
SO
:
quickly apply takeoff power and re-
tract the flaps as rapidly as possible to
the recommended go around setting
and allow the airspeed to transition
from 1.3 V
SO
to 1.3 V
S1
. Retract the gear
when a positive rate of climb is estab-
lished.
(3) With landing gear and flaps ex-
tended, in level flight, power necessary
to attain level flight at 1.1 V
SO
, and the
airplane as nearly as possible in trim,
it must be possible to maintain ap-
proximately level flight while retract-
ing the flaps as rapidly as possible with
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