[Code of Federal Regulations]

[Title 14, Volume 1]

[Revised as of January 1, 2006]

From the U.S. Government Printing Office via GPO Access

[CITE: 14CFR23.67]



[Page 189-190]

 

                     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 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;



[[Page 190]]



    (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]