Code of Federal Regulations - Title 14

188

14 CFR Ch. I (1–1–14 Edition)

§ 23.45

(1) The lowest possible pitch allows

compliance with paragraph (b)(1) of
this section; and

(2) The highest possible pitch allows

compliance with paragraph (b)(2) of
this section.

(d)

Controllable pitch propellers with

constant speed controls. Each control-
lable pitch propeller with constant
speed controls must have—

(1) With the governor in operation, a

means at the governor to limit the
maximum engine speed to the max-
imum allowable takeoff r.p.m.; and

(2) With the governor inoperative,

the propeller blades at the lowest pos-
sible pitch, with takeoff power, the air-
plane stationary, and no wind, either—

(i) A means to limit the maximum

engine speed to 103 percent of the max-
imum allowable takeoff r.p.m., or

(ii) For an engine with an approved

overspeed, a means to limit the max-
imum engine and propeller speed to not
more than the maximum approved
overspeed.

[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as
amended by Amdt. 23–45, 58 FR 42156, Aug. 6,
1993; Amdt. 23–50, 61 FR 5183, Feb. 9, 1996]

ERFORMANCE

§ 23.45

General.

(a) Unless otherwise prescribed, the

performance requirements of this part
must be met for—

(1) Still air and standard atmosphere;

and

(2) Ambient atmospheric conditions,

for commuter category airplanes, for
reciprocating engine-powered airplanes
of more than 6,000 pounds maximum
weight, and for turbine engine-powered
airplanes.

(b) Performance data must be deter-

mined over not less than the following
ranges of conditions—

(1) Airport altitudes from sea level to

10,000 feet; and

(2) For reciprocating engine-powered

airplanes of 6,000 pounds, or less, max-
imum weight, temperature from stand-
ard to 30

C above standard; or

(3) For reciprocating engine-powered

airplanes of more than 6,000 pounds
maximum weight and turbine engine-
powered airplanes, temperature from
standard to 30

C above standard, or

the maximum ambient atmospheric

temperature at which compliance with
the cooling provisions of § 23.1041 to
§ 23.1047 is shown, if lower.

mined with the cowl flaps or other
means for controlling the engine cool-
ing air supply in the position used in
the cooling tests required by §§ 23.1041
to 23.1047.

(d) The available propulsive thrust

must correspond to engine power, not
exceeding the approved power, less—

(1) Installation losses; and
(2) The power absorbed by the acces-

sories and services appropriate to the
particular ambient atmospheric condi-
tions and the particular flight condi-
tion.

(e) The performance, as affected by

engine power or thrust, must be based
on a relative humidity:

(1) Of 80 percent at and below stand-

ard temperature; and

(2) From 80 percent, at the standard

temperature, varying linearly down to
34 percent at the standard temperature
plus 50

(f) Unless otherwise prescribed, in de-

termining the takeoff and landing dis-
tances, changes in the airplane’s con-
figuration, speed, and power must be
made in accordance with procedures es-
tablished by the applicant for oper-
ation in service. These procedures must
be able to be executed consistently by
pilots of average skill in atmospheric
conditions reasonably expected to be
encountered in service.

(g) The following, as applicable, must

be determined on a smooth, dry, hard-
surfaced runway—

(1) Takeoff distance of § 23.53(b);
(2) Accelerate-stop distance of § 23.55;
(3) Takeoff distance and takeoff run

of § 23.59; and

(4) Landing distance of § 23.75.

OTE

: The effect on these distances of op-

eration on other types of surfaces (for exam-
ple, grass, gravel) when dry, may be deter-
mined or derived and these surfaces listed in
the Airplane Flight Manual in accordance
with § 23.1583(p).

(h) For multiengine jets weighing

over 6,000 pounds in the normal, util-
ity, and acrobatic category and com-
muter category airplanes, the fol-
lowing also apply:

(1) Unless otherwise prescribed, the

applicant must select the takeoff,

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