[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: 14CFR23.57]



[Page 186-187]

 

                     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. 23.57  Takeoff path.



    For each commuter category airplane, the takeoff path is as follows:

    (a) The takeoff path extends from a standing start to a point in the 

takeoff at which the airplane is 1500 feet above the takeoff surface at 

or below which height the transition from the takeoff to the enroute 

configuration must be completed; and

    (1) The takeoff path must be based on the procedures prescribed in 

Sec. 23.45;

    (2) The airplane must be accelerated on the ground to VEF at which 

point the



[[Page 187]]



critical engine must be made inoperative and remain inoperative for the 

rest of the takeoff; and

    (3) After reaching VEF, the airplane must be accelerated to V2.

    (b) During the acceleration to speed V2, the nose gear 

may be raised off the ground at a speed not less than VR. 

However, landing gear retraction must not be initiated until the 

airplane is airborne.

    (c) During the takeoff path determination, in accordance with 

paragraphs (a) and (b) of this section--

    (1) The slope of the airborne part of the takeoff path must not be 

negative at any point;

    (2) The airplane must reach V2 before it is 35 feet above the 

takeoff surface, and must continue at a speed as close as practical to, 

but not less than V2, until it is 400 feet above the takeoff surface;

    (3) At each point along the takeoff path, starting at the point at 

which the airplane reaches 400 feet above the takeoff surface, the 

available gradient of climb must not be less than--

    (i) 1.2 percent for two-engine airplanes;

    (ii) 1.5 percent for three-engine airplanes;

    (iii) 1.7 percent for four-engine airplanes; and

    (4) Except for gear retraction and automatic propeller feathering, 

the airplane configuration must not be changed, and no change in power 

that requires action by the pilot may be made, until the airplane is 400 

feet above the takeoff surface.

    (d) The takeoff path to 35 feet above the takeoff surface must be 

determined by a continuous demonstrated takeoff.

    (e) The takeoff path to 35 feet above the takeoff surface must be 

determined by synthesis from segments; and

    (1) The segments must be clearly defined and must be related to 

distinct changes in configuration, power, and speed;

    (2) The weight of the airplane, the configuration, and the power 

must be assumed constant throughout each segment and must correspond to 

the most critical condition prevailing in the segment; and

    (3) The takeoff flight path must be based on the airplane's 

performance without utilizing ground effect.



[Amdt. 23-34, 52 FR 1827, Jan. 15, 1987, as amended by Amdt. 23-50, 61 

FR 5185, Feb. 9, 1996]