Code of Federal Regulations - Title 14

195

Federal Aviation Administration, DOT

§ 23.75

percent for three-engine airplanes, and
1.7 percent for four-engine airplanes
with—

(i) The critical engine inoperative

and its propeller in the minimum drag
position;

(ii) The remaining engine(s) at not

more than maximum continuous
power;

(iii) The landing gear retracted;
(iv) The wing flaps retracted; and
(v) A climb speed not less than 1.2

(4)

Discontinued approach. The steady

gradient of climb at an altitude of 400
feet above the landing surface must be
not less than 2.1 percent for two-engine
airplanes, 2.4 percent for three-engine
airplanes, and 2.7 percent for four-en-
gine airplanes, with—

(i) The critical engine inoperative

and its propeller in the minimum drag
position;

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

off power;

(iii) Landing gear retracted;
(iv) Wing flaps in the approach posi-

tion(s) in which V

for these posi-

tion(s) does not exceed 110 percent of
the V

for the related all-engines-oper-

ated landing position(s); and

(v) A climb speed established in con-

nection with normal landing proce-
dures but not exceeding 1.5 V

[Doc. No. 27807, 61 FR 5186, Feb. 9, 1996, as
amended by Amdt. 23–62, 76 FR 75754, Dec. 2,
2011]

§ 23.69

Enroute climb/descent.

(a)

All engines operating. The steady

gradient and rate of climb must be de-
termined at each weight, altitude, and
ambient temperature within the oper-
ational limits established by the appli-
cant with—

(1) Not more than maximum contin-

uous power on each engine;

(2) The landing gear retracted;
(3) The wing flaps retracted; and
(4) A climb speed not less than 1.3

(b)

One engine inoperative. The steady

gradient and rate of climb/descent
must be determined at each weight, al-
titude, and ambient temperature with-
in the operational limits established by
the applicant with—

(1) The critical engine inoperative

and its propeller in the minimum drag
position;

(2) The remaining engine(s) at not

more than maximum continuous
power;

(3) The landing gear retracted;
(4) The wing flaps retracted; and
(5) A climb speed not less than 1.2

[Doc. No. 27807, 61 FR 5187, Feb. 9, 1996]

§ 23.71

Glide: Single-engine airplanes.

The maximum horizontal distance

traveled in still air, in nautical miles,
per 1,000 feet of altitude lost in a glide,
and the speed necessary to achieve this
must be determined with the engine in-
operative, its propeller in the min-
imum drag position, and landing gear
and wing flaps in the most favorable
available position.

[Doc. No. 27807, 61 FR 5187, Feb. 9, 1996]

§ 23.73

Reference landing approach

speed.

(a) For normal, utility, and acrobatic

category reciprocating engine-powered
airplanes of 6,000 pounds or less max-
imum weight, the reference landing ap-
proach speed, V

REF

, may not be less

than the greater of V

, determined in

§ 23.149(b) with the wing flaps in the
most extended takeoff position, and 1.3
V

(b) For normal, utility, and acrobatic

category turbine powered airplanes of
6,000 pounds or less maximum weight,
turboprops of more than 6,000 pounds
maximum weight, and reciprocating
engine-powered airplanes of more than
6,000 pounds maximum weight, the ref-
erence landing approach speed, V

REF

may not be less than the greater of
V

, determined in § 23.149(c), and 1.3

category jets of more than 6,000 pounds
maximum weight and commuter cat-
egory airplanes, the reference landing
approach speed, V

REF

, may not be less

than the greater of 1.05 V

, deter-

mined in § 23.149(c), and 1.3 V

[Amdt. 23–62, 76 FR 75754, Dec. 2, 2011]

§ 23.75

Landing distance.

The horizontal distance necessary to

land and come to a complete stop from

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