Code of Federal Regulations - Title 14

190

14 CFR Ch. I (1–1–14 Edition)

§ 23.53

landing, if applicable) under all reason-
ably expected conditions, including
turbulence and complete failure of the
critical engine;

(ii) 1.10 V

; or

(iii) 1.20 V

(2) For single-engine airplanes, the

higher of—

(i) A speed that is shown to be safe

under all reasonably expected condi-
tions, including turbulence and com-
plete engine failure; or

(ii) 1.20 V

category multiengine jets of more than
6,000 pounds maximum weight and
commuter category airplanes, the fol-
lowing apply:

(l) V

must be established in relation

to V

as follows:

(i) V

is the calibrated airspeed at

which the critical engine is assumed to
fail. V

must be selected by the appli-

cant but must not be less than 1.05 V

determined under § 23.149(b) or, at the
option of the applicant, not less than
V

MCG

determined under § 23.149(f).

(ii) The takeoff decision speed, V

, is

the calibrated airspeed on the ground
at which, as a result of engine failure
or other reasons, the pilot is assumed
to have made a decision to continue or
discontinue the takeoff. The takeoff
decision speed, V

, must be selected by

the applicant but must not be less than
V

plus the speed gained with the crit-

ical engine inoperative during the time
interval between the instant at which
the critical engine is failed and the in-
stant at which the pilot recognizes and
reacts to the engine failure, as indi-
cated by the pilot’s application of the
first retarding means during the accel-
erate-stop determination of § 23.55.

(2) The rotation speed, V

, in terms

of calibrated airspeed, must be selected
by the applicant and must not be less
than the greatest of the following:

(i) V

;

(ii) 1.05 V

determined under

§ 23.149(b);

(iii) 1.10 V

; or

(iv) The speed that allows attaining

the initial climb-out speed, V

, before

reaching a height of 35 feet above the
takeoff surface in accordance with
§ 23.57(c)(2).

(3) For any given set of conditions,

such as weight, altitude, temperature,

and configuration, a single value of V

must be used to show compliance with
both the one-engine-inoperative take-
off and all-engines-operating takeoff
requirements.

(4) The takeoff safety speed, V

, in

terms of calibrated airspeed, must be
selected by the applicant so as to allow
the gradient of climb required in § 23.67
(c)(1) and (c)(2) but mut not be less
than 1.10 V

or less than 1.20 V

(5) The one-engine-inoperative take-

off distance, using a normal rotation
rate at a speed 5 knots less than V

, es-

tablished in accordance with paragraph
(c)(2) of this section, must be shown
not to exceed the corresponding one-
engine-inoperative takeoff distance,
determined in accordance with § 23.57
and § 23.59(a)(1), using the established
V

. The takeoff, otherwise performed

in accordance with § 23.57, must be con-
tinued safely from the point at which
the airplane is 35 feet above the takeoff
surface and at a speed not less than the
established V

minus 5 knots.

(6) The applicant must show, with all

engines operating, that marked in-
creases in the scheduled takeoff dis-
tances, determined in accordance with
§ 23.59(a)(2), do not result from over-ro-
tation of the airplane or out-of-trim
conditions.

[Doc. No. 27807, 61 FR 5184, Feb. 9, 1996, as
amended by Amdt. 23–62, 76 FR 75753, Dec. 2,
2011]

§ 23.53

Takeoff performance.

(a) For normal, utility, and acrobatic

category airplanes, the takeoff dis-
tance must be determined in accord-
ance with paragraph (b) of this section,
using speeds determined in accordance
with § 23.51 (a) and (b).

(b) For normal, utility, and acrobatic

category airplanes, the distance re-
quired to takeoff and climb to a height
of 50 feet above the takeoff surface
must be determined for each weight,
altitude, and temperature within the
operational limits established for take-
off with—

(1) Takeoff power on each engine;
(2) Wing flaps in the takeoff posi-

tion(s); and

(3) Landing gear extended.
(c) For normal, utility, and acrobatic

category multiengine jets of more than
6,000 pounds maximum weight and

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