Federal Aviation Administration, DOT

Section 25.145

activated and is performing its intended function, it must be demonstrated in flight with the most critical of the ice accretion(s) defined in
Appendix C, part II, paragraph (e) of
this part and Appendix O, part II, paragraph (d) of this part, as applicable, in
accordance with Section 25.21(g), that:
(1) The airplane is controllable in a
pull-up maneuver up to 1.5 g load factor; and
(2) There is no pitch control force reversal during a pushover maneuver
down to 0.5 g load factor.
[Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as
amended by Amdt. 25-42, 43 FR 2321, Jan. 16,
1978; Amdt. 25-84, 60 FR 30749, June 9, 1995;
Amdt. 25-108, 67 FR 70826, Nov. 26, 2002;
Amdt. 25-121, 72 FR 44667, Aug. 8, 2007; Amdt.
25-129, 74 FR 38339, Aug. 3, 2009; Amdt. 25-140,
79 FR 65525, Nov. 4, 2014]

spaschal on DSK3GDR082PROD with CFR

Section 25.145

Longitudinal control.

(a) It must be possible, at any point
between the trim speed prescribed in
Section 25.103(b)(6) and stall identification (as
defined in Section 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 Section 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.
(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 goaround 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]

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