Code of Federal Regulations - Title 14

201

Federal Aviation Administration, DOT

§ 23.161

(1) For an airplane of 6,000 pounds or

less maximum weight, 4 seconds from
initiation of roll; and

(2) For an airplane of over 6,000

pounds maximum weight,

(W+2,800)/2,200

seconds, but not more than 7 seconds,
where W is the weight in pounds.

(d) The requirement of paragraph (c)

of this section must be met when roll-
ing the airplane in each direction in
the following conditions—

(1) Flaps in the landing position(s);
(2) Landing gear extended;
(3) All engines operating at the power

for a 3 degree approach; and

(4) The airplane trimmed at V

REF

[Amdt. 23–14, 38 FR 31819, Nov. 19, 1973, as
amended by Amdt. 23–45, 58 FR 42158, Aug. 6,
1993; Amdt. 23–50, 61 FR 5189, Feb. 9, 1996]

RIM

§ 23.161

Trim.

(a)

General. Each airplane must meet

the trim requirements of this section
after being trimmed and without fur-
ther pressure upon, or movement of,
the primary controls or their cor-
responding trim controls by the pilot
or the automatic pilot. In addition, it
must be possible, in other conditions of
loading, configuration, speed and power
to ensure that the pilot will not be un-
duly fatigued or distracted by the need
to apply residual control forces exceed-
ing those for prolonged application of
§ 23.143(c). This applies in normal oper-
ation of the airplane and, if applicable,
to those conditions associated with the
failure of one engine for which per-
formance characteristics are estab-
lished.

(b)

Lateral and directional trim. The

airplane must maintain lateral and di-
rectional trim in level flight with the
landing gear and wing flaps retracted
as follows:

(1) For normal, utility, and acrobatic

category airplanes, at a speed of 0.9 V

, or V

, whichever is lowest; and

(2) For commuter category airplanes,

at all speeds from 1.4 V

to the lesser

of V

or V

(c)

Longitudinal trim. The airplane

must maintain longitudinal trim under
each of the following conditions:

(1) A climb with—

(i) Takeoff power, landing gear re-

tracted, wing flaps in the takeoff posi-
tion(s), at the speeds used in deter-
mining the climb performance required
by § 23.65; and

(ii) Maximum continuous power at

the speeds and in the configuration
used in determining the climb perform-
ance required by § 23.69(a).

(2) Level flight at all speeds from the

lesser of V

and either V

or V

(as appropriate), to 1.4 V

, with the

landing gear and flaps retracted.

(3) A descent at V

or V

whichever is applicable, with power off
and with the landing gear and flaps re-
tracted.

(4) Approach with landing gear ex-

tended and with—

(i) A 3 degree angle of descent, with

flaps retracted and at a speed of 1.4 V

;

(ii) A 3 degree angle of descent, flaps

in the landing position(s) at V

REF

; and

(iii) An approach gradient equal to

the steepest used in the landing dis-
tance demonstrations of § 23.75, flaps in
the landing position(s) at V

REF

(d) In addition, each multiple air-

plane must maintain longitudinal and
directional trim, and the lateral con-
trol force must not exceed 5 pounds at
the speed used in complying with
§ 23.67(a), (b)(2), or (c)(3), as appro-
priate, with—

(1) The critical engine inoperative,

and if applicable, its propeller in the
minimum drag position;

(2) The remaining engines at max-

imum continuous power;

(3) The landing gear retracted;
(4) Wing flaps retracted; and
(5) An angle of bank of not more than

five degrees.

(e) In addition, each commuter cat-

egory airplane for which, in the deter-
mination of the takeoff path in accord-
ance with § 23.57, the climb in the take-
off configuration at V

extends beyond

400 feet above the takeoff surface, it
must be possible to reduce the longitu-
dinal and lateral control forces to 10
pounds and 5 pounds, respectively, and
the directional control force must not
exceed 50 pounds at V

with—

(1) The critical engine inoperative

and its propeller in the minimum drag
position;

(2) The remaining engine(s) at take-

off power;

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