[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: 14CFR25.175]



[Page 363-364]

 

                     TITLE 14--AERONAUTICS AND SPACE

 

CHAPTER I--FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION

 

PART 25_AIRWORTHINESS STANDARDS: TRANSPORT CATEGORY AIRPLANES--Table 

of Contents

 

                            Subpart B_Flight

 

Sec. 25.175  Demonstration of static longitudinal stability.



    Static longitudinal stability must be shown as follows:

    (a) Climb. The stick force curve must have a stable slope at speeds 

between 85 and 115 percent of the speed at which the airplane--

    (1) Is trimmed, with--

    (i) Wing flaps retracted;

    (ii) Landing gear retracted;

    (iii) Maximum takeoff weight; and

    (iv) 75 percent of maximum continuous power for reciprocating 

engines or the maximum power or thrust selected by the applicant as an 

operating limitation for use during climb for turbine engines; and

    (2) Is trimmed at the speed for best rate-of-climb except that the 

speed need not be less than 1.3 VSR1.

    (b) Cruise. Static longitudinal stability must be shown in the 

cruise condition as follows:

    (1) With the landing gear retracted at high speed, the stick force 

curve must have a stable slope at all speeds within a range which is the 

greater of 15 percent of the trim speed plus the resulting free return 

speed range, or 50 knots plus the resulting free return speed range, 

above and below the trim speed (except that the speed range need not 

include speeds less than 1.3 VSR1, nor speeds greater than 

VFC/MFC, nor speeds that require a stick force of more than 50 pounds), 

with--

    (i) The wing flaps retracted;

    (ii) The center of gravity in the most adverse position (see Sec. 

25.27);

    (iii) The most critical weight between the maximum takeoff and 

maximum landing weights;

    (iv) 75 percent of maximum continuous power for reciprocating 

engines or for turbine engines, the maximum cruising power selected by 

the applicant as an operating limitation (see Sec. 25.1521), except 

that the power need not exceed that required at VMO/MMO; and

    (v) The airplane trimmed for level flight with the power required in 

paragraph (b)(1)(iv) of this section.

    (2) With the landing gear retracted at low speed, the stick force 

curve must have a stable slope at all speeds within a range which is the 

greater of 15 percent of the trim speed plus the resulting free return 

speed range, or 50 knots plus the resulting free return speed range, 

above and below the trim speed (except that the speed range need not 

include speeds less than 1.3 VSR1, nor speeds greater than 

the minimum speed of the applicable speed range prescribed in paragraph 

(b)(1), nor speeds that require a stick force of more than 50 pounds), 

with--

    (i) Wing flaps, center of gravity position, and weight as specified 

in paragraph (b)(1) of this section;

    (ii) Power required for level flight at a speed equal to (VMO + 1.3 

VSR1)/2; and

    (iii) The airplane trimmed for level flight with the power required 

in paragraph (b)(2)(ii) of this section.

    (3) With the landing gear extended, the stick force curve must have 

a stable slope at all speeds within a range which is the greater of 15 

percent of the trim speed plus the resulting free return speed range, or 

50 knots plus the resulting free return speed range, above and below the 

trim speed (except that the speed range need not include speeds less 

than 1.3 VSR1, nor speeds greater than VLE, nor speeds that 

require a stick force of more than 50 pounds), with--

    (i) Wing flap, center of gravity position, and weight as specified 

in paragraph (b)(1) of this section;

    (ii) 75 percent of maximum continuous power for reciprocating 

engines or, for turbine engines, the maximum cruising power selected by 

the applicant as an operating limitation, except that the power need not 

exceed that required for level flight at VLE; and

    (iii) The aircraft trimmed for level flight with the power required 

in paragraph (b)(3)(ii) of this section.

    (c) Approach. The stick force curve must have a stable slope at 

speeds between VSW and 1.7 VSR1, with--

    (1) Wing flaps in the approach position;

    (2) Landing gear retracted;

    (3) Maximum landing weight; and



[[Page 364]]



    (4) The airplane trimmed at 1.3 VSR1 with enough power to 

maintain level flight at this speed.

    (d) Landing. The stick force curve must have a stable slope, and the 

stick force may not exceed 80 pounds, at speeds between VSW and 1.7 

VSR0 with--

    (1) Wing flaps in the landing position;

    (2) Landing gear extended;

    (3) Maximum landing weight;

    (4) The airplane trimmed at 1.3 VSR0 with--

    (i) Power or thrust off, and

    (ii) Power or thrust for level flight.

    (5) The airplane trimmed at 1.3 VSR0 with power or thrust 

off.



[Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as amended by Amdt. 25-7, 30 

FR 13117, Oct. 15, 1965; Amdt. 25-108, 67 FR 70827, Nov. 26, 2002; Amdt. 

25-115, 69 FR 40527, July 2, 2004]