Code of Federal Regulations - Title 14

194

14 CFR Ch. I (1–1–14 Edition)

§ 23.67

(2) For each airplane that meets the

requirements prescribed in § 23.562(d),
or that has a V

of 61 knots or less,

the steady gradient of climb or descent
at a pressure altitude of 5,000 feet must
be determined with the—

(i) Critical engine inoperative and its

propeller in the minimum drag posi-
tion;

(ii) Remaining engine(s) at not more

than maximum continuous power;

(iii) Landing gear retracted;
(iv) Wing flaps retracted; and
(v) Climb speed not less than 1.2V

(b) For normal, utility, and acrobatic

category reciprocating engine-powered
airplanes of more than 6,000 pounds
maximum weight, and turbopropeller-
powered airplanes in the normal, util-
ity, and acrobatic category—

(1) The steady gradient of climb at an

altitude of 400 feet above the takeoff
must be no less than 1 percent with
the—

(i) Critical engine inoperative and its

propeller in the minimum drag posi-
tion;

(ii) Remaining engine(s) at takeoff

power;

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

tion(s); and

(v) Climb speed equal to that

achieved at 50 feet in the demonstra-
tion of § 23.53.

(2) The steady gradient of climb must

not be less than 0.75 percent at an alti-
tude of 1,500 feet above the takeoff sur-
face, or landing surface, as appropriate,
with the—

(i) Critical engine inoperative and its

propeller in the minimum drag posi-
tion;

(ii) Remaining engine(s) at not more

than maximum continuous power;

(iii) Landing gear retracted;
(iv) Wing flaps retracted; and
(v) Climb speed not less than 1.2 V

category jets of 6,000 pounds or less
maximum weight—

(1) The steady gradient of climb at an

altitude of 400 feet above the takeoff
must be no less than 1.2 percent with
the—

(i) Critical engine inoperative;
(ii) Remaining engine(s) at takeoff

power;

(iii) Landing gear retracted;

(iv) Wing flaps in the takeoff posi-

tion(s); and

(v) Climb speed equal to that

achieved at 50 feet in the demonstra-
tion of § 23.53.

(2) The steady gradient of climb may

not be less than 0.75 percent at an alti-
tude of 1,500 feet above the takeoff sur-
face, or landing surface, as appropriate,
with the—

(i) Critical engine inoperative;
(ii) Remaining engine(s) at not more

than maximum continuous power;

(iii) Landing gear retracted;
(iv) Wing flaps retracted; and
(v) Climb speed not less than 1.2 V

(d) For jets over 6,000 pounds max-

imum weight in the normal, utility and
acrobatic category and commuter cat-
egory airplanes, the following apply:

(1)

Takeoff; landing gear extended. The

steady gradient of climb at the altitude
of the takeoff surface must be measur-
ably positive for two-engine airplanes,
not less than 0.3 percent for three-en-
gine airplanes, or 0.5 percent for four-
engine airplanes with—

(i) The critical engine inoperative

and its propeller in the position it rap-
idly and automatically assumes;

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

off power;

(iii) The landing gear extended, and

all landing gear doors open;

(iv) The wing flaps in the takeoff po-

sition(s);

(v) The wings level; and
(vi) A climb speed equal to V

(2)

Takeoff; landing gear retracted. The

steady gradient of climb at an altitude
of 400 feet above the takeoff surface
must be not less than 2.0 percent of
two-engine airplanes, 2.3 percent for
three-engine airplanes, and 2.6 percent
for four-engine airplanes with—

(i) The critical engine inoperative

and its propeller in the position it rap-
idly and automatically assumes;

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

off power;

(iii) The landing gear retracted;
(iv) The wing flaps in the takeoff po-

sition(s);

(v) A climb speed equal to V

(3)

Enroute. The steady gradient of

climb at an altitude of 1,500 feet above
the takeoff or landing surface, as ap-
propriate, must be not less than 1.2
percent for two-engine airplanes, 1.5

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