(b)
With the airplanein trim, or as nearly aspossiblein trim and without the trimming control being moved throughout the maneuver;
(c)
At an approachgradientequal tothe steepest usedinthelanding distancedemons-tration of Sec. 23.75; and
(d)
With only those power changes, if any, that would be made when landing normally
from an approach at VREF.] Amdt. 23-50, E.. 03/11/96
FAR 23.155 : Elevator control force in maneuvers.
(a) The elevator control force needed to achieve the positive limit maneuvering load factor may not be less than–
(1) For wheel controls, W (where W is the maximum weight) or 20 pounds,
100
whicheverisgreater, exceptthatit need notbegreaterthan50pounds; or
W
(2) For stick controls, (whereW is the maximum weight) or 15 pounds, whi-
140
chever is greater, except that it need not be greater than 35 pounds.
(b)
[The requirement of paragraph (a) of this section must be met at 75 percent of maximumcontinuouspowerfor reciprocating engines,orthe maximumcontinuous power for turbine engines, and with the wing .aps and landing gear retracted–
(1)
In a turn, with the trim setting used for wings level .ight at VO ; and]
(2)
In a turn with the trim setting used for the maximum wings level .ight speed, except that the speed may not exceed VNE or VMO/MMO, whichever is ap-propriate.
(c)
[There mustbe no excessivedecreasein thegradientof the curve of stickforce versus maneuvering loadfactor withincreasing loadfactor.]
Amdt. 23-50, E.. 03/11/96
FAR 23.157 : Rate of roll.
(a) Takeo.. It must be possible, using a favorable combination of controls, to roll the airplane from a steady 30'banked turn through an angle of 60', so as to reverse the direction of the turn within–
(1)
For an airplane of 6,000 pounds or less maximum weight, 5 seconds from ini-tiation of roll; and
(2)
For an airplane of over 6,000 pounds maximum weight, W+500 seconds, but
1300
not more than 10 seconds, where W is the weight in pounds.
(b)
The requirement of paragraph (a) of this section must be met when rolling the airplane in each direction with–
(1)
Flaps in the takeo. position;
(2)
Landing gear retracted;
(3)
For a single-engine airplane, at maximum takeo.power; andfor a multiengine airplane with the critical engineinoperative and thepropellerin the minimum dragposition, andthe other engines at maximumtakeo.power; and
(4)
The airplane trimmed at a speed equal to the greater of 1.2 VS1 or 1.1 VMC, or as nearly as possible in trim for straight .ight.
(c)
Approach. It must be possible, using a favorable combination of controls, to roll the
''
airplane from a steady 30banked turn through an angle of 60, so as to reverse the direction of the turn within :
(1)
For an airplane of 6,000 pounds or less maximum weight, 4 seconds from ini-tiation of roll; and
(2)
For an airplane of over 6,000 pounds maximum weight, W+2800 seconds, but
2200
not more than 7 seconds, where W is the weight in pounds.
(d)
[The requirement of paragraph (c) of this section must be met when rolling the airplane in each direction in the following conditions–
(1)
Flaps in the landing position(s);
(2)
Landinggear extended;
(3)
All engines operating at the power for a 3 degree approach; and
(4) 中國(guó)航空網(wǎng) m.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：FAA規(guī)章 美國(guó)聯(lián)邦航空規(guī)章 Federal Aviation Regulations 1(133)
