[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: 14CFR25.145]
[Page 358-359]
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. 25.145 Longitudinal control.
(a) It must be possible, at any point between the trim speed
prescribed in Sec. 25.103(b)(6) and stall identification (as defined in
Sec. 25.201(d)), to pitch the nose downward so that the acceleration to
this selected trim speed is prompt with
(1) The airplane trimmed at the trim speed prescribed in Sec.
25.103(b)(6);
(2) The landing gear extended;
(3) The wing flaps (i) retracted and (ii) extended; and
(4) Power (i) off and (ii) at maximum continuous power on the
engines.
(b) With the landing gear extended, no change in trim control, or
exertion of more than 50 pounds control force (representative of the
maximum short term force that can be applied readily by one hand) may be
required for the following maneuvers:
(1) With power off, flaps retracted, and the airplane trimmed at 1.3
VSR1, extend the flaps as rapidly as possible while
maintaining the airspeed at approximately 30 percent above the reference
stall speed existing at each instant throughout the maneuver.
(2) Repeat paragraph (b)(1) except initially extend the flaps and
then retract them as rapidly as possible.
(3) Repeat paragraph (b)(2), except at the go-around power or thrust
setting.
(4) With power off, flaps retracted, and the airplane trimmed at 1.3
VSR1, rapidly set go-around power or thrust while maintaining
the same airspeed.
(5) Repeat paragraph (b)(4) except with flaps extended.
[[Page 359]]
(6) With power off, flaps extended, and the airplane trimmed at 1.3
VSR1, obtain and maintain airspeeds between VSW and either 1.6 VSR1 or
VFE, whichever is lower.
(c) It must be possible, without exceptional piloting skill, to
prevent loss of altitude when complete retraction of the high lift
devices from any position is begun during steady, straight, level flight
at 1.08 VSR1 for propeller powered airplanes, or 1.13 VSR1 for turbojet
powered airplanes, with--
(1) Simultaneous movement of the power or thrust controls to the go-
around power or thrust setting;
(2) The landing gear extended; and
(3) The critical combinations of landing weights and altitudes.
(d) If gated high-lift device control positions are provided,
paragraph (c) of this section applies to retractions of the high-lift
devices from any position from the maximum landing position to the first
gated position, between gated positions, and from the last gated
position to the fully retracted position. The requirements of paragraph
(c) of this section also apply to retractions from each approved landing
position to the control position(s) associated with the high-lift device
configuration(s) used to establish the go-around procedure(s) from that
landing position. In addition, the first gated control position from the
maximum landing position must correspond with a configuration of the
high-lift devices used to establish a go-around procedure from a landing
configuration. Each gated control position must require a separate and
distinct motion of the control to pass through the gated position and
must have features to prevent inadvertent movement of the control
through the gated position. It must only be possible to make this
separate and distinct motion once the control has reached the gated
position.
[Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as amended by Amdt. 25-23,
35 FR 5671, Apr. 8, 1970; Amdt. 25-72, 55 FR 29774, July 20, 1990; Amdt.
25-84, 60 FR 30749, June 9, 1995; Amdt. 25-98, 64 FR 6164, Feb. 8, 1999;
64 FR 10740, Mar. 5, 1999; Amdt. 25-108, 67 FR 70827, Nov. 26, 2002]