[Code of Federal Regulations]
[Title 14, Volume 1]
[Revised as of January 1, 2004]
From the U.S. Government Printing Office via GPO Access
[CITE: 14CFR23.67]

[Page 183-184]
 
                     TITLE 14--AERONAUTICS AND SPACE
 
CHAPTER I--FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION
 
PART 23--AIRWORTHINESS STANDARDS: NORMAL, UTILITY, ACROBATIC, AND COMMUTER 
CATEGORY AIRPLANES--Table of Contents
 
                            Subpart B--Flight
 
Sec. 23.67  Climb: One engine inoperative.

    (a) For normal, utility, and acrobatic category reciprocating 
engine-powered airplanes of 6,000 pounds or less maximum weight, the 
following apply:
    (1) Except for those airplanes that meet the requirements prescribed 
in Sec. 23.562(d), each airplane with a VSO of more than 61 
knots must be able to maintain a steady climb gradient of at least 1.5 
percent at a pressure altitude of 5,000 feet with the--
    (i) Critical engine inoperative and its propeller in the minimum 
drag position;
    (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 VS1.
    (2) For each airplane that meets the requirements prescribed in 
Sec. 23.562(d), or that has a VSO 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 position;
    (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 1.2VS1.
    (b) For normal, utility, and acrobatic category reciprocating 
engine-powered airplanes of more than 6,000 pounds maximum weight, and 
turbine engine-powered airplanes in the normal, utility, and acrobatic 
category--
    (1) The steady gradient of climb at an altitude of 400 feet above 
the takeoff must be measurably positive with the--
    (i) Critical engine inoperative and its propeller in the minimum 
drag position;
    (ii) Remaining engine(s) at takeoff power;
    (iii) Landing gear retracted;
    (iv) Wing flaps in the takeoff position(s); and
    (v) Climb speed equal to that achieved at 50 feet in the 
demonstration of Sec. 23.53.
    (2) The steady gradient of climb must not be less than 0.75 percent 
at an altitude of 1,500 feet above the takeoff surface, or landing 
surface, as appropriate, with the--
    (i) Critical engine inoperative and its propeller in the minimum 
drag position;
    (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 VS1.
    (c) For commuter category airplanes, the following apply:
    (1) Takeoff; landing gear extended. The steady gradient of climb at 
the altitude

[[Page 184]]

of the takeoff surface must be measurably positive for two-engine 
airplanes, not less than 0.3 percent for three-engine airplanes, or 0.5 
percent for four-engine airplanes with--
    (i) The critical engine inoperative and its propeller in the 
position it rapidly and automatically assumes;
    (ii) The remaining engine(s) at takeoff power;
    (iii) The landing gear extended, and all landing gear doors open;
    (iv) The wing flaps in the takeoff position(s);
    (v) The wings level; and
    (vi) A climb speed equal to V2.
    (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 rapidly and automatically assumes;
    (ii) The remaining engine(s) at takeoff power;
    (iii) The landing gear retracted;
    (iv) The wing flaps in the takeoff position(s);
    (v) A climb speed equal to V2.
    (3) Enroute. The steady gradient of climb at an altitude of 1,500 
feet above the takeoff or landing surface, as appropriate, must be not 
less than 1.2 percent for two-engine airplanes, 1.5 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 VS1.
    (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-engine airplanes, with--
    (i) The critical engine inoperative and its propeller in the minimum 
drag position;
    (ii) The remaining engine(s) at takeoff power;
    (iii) Landing gear retracted;
    (iv) Wing flaps in the approach position(s) in which VS1 
for these position(s) does not exceed 110 percent of the VS1 
for the related all-engines-operated landing position(s); and
    (v) A climb speed established in connection with normal landing 
procedures but not exceeding 1.5 VS1.

[Doc. No. 27807, 61 FR 5186, Feb. 9, 1996]