spaschal on DSK3GDR082PROD with CFR

Federal Aviation Administration, DOT

Section 25.121

VLOF and at which the landing gear is
fully retracted) and in the configuration used in Section 25.111 but without ground
effect, the steady gradient of climb
must be positive for two-engine airplanes, and not less than 0.3 percent for
three-engine airplanes or 0.5 percent
for four-engine airplanes, at VLOF and
with - 
(1) The critical engine inoperative
and the remaining engines at the power
or thrust available when retraction of
the landing gear is begun in accordance
with Section 25.111 unless there is a more critical power operating condition existing
later along the flight path but before
the point at which the landing gear is
fully retracted; and
(2) The weight equal to the weight
existing when retraction of the landing
gear is begun, determined under
Section 25.111.
(b) Takeoff; landing gear retracted. In
the takeoff configuration existing at
the point of the flight path at which
the landing gear is fully retracted, and
in the configuration used in Section 25.111 but
without ground effect:
(1) The steady gradient of climb may
not be less than 2.4 percent for two-engine airplanes, 2.7 percent for three-engine airplanes, and 3.0 percent for fourengine airplanes, at V2 with:
(i) The critical engine inoperative,
the remaining engines at the takeoff
power or thrust available at the time
the landing gear is fully retracted, determined under Section 25.111, unless there is
a more critical power operating condition existing later along the flight path
but before the point where the airplane
reaches a height of 400 feet above the
takeoff surface; and
(ii) The weight equal to the weight
existing when the airplane-s landing
gear is fully retracted, determined
under Section 25.111.
(2) The requirements of paragraph
(b)(1) of this section must be met:
(i) In non-icing conditions; and
(ii) In icing conditions with the most
critical of the takeoff ice accretion(s)
defined in Appendices C and O of this
part, as applicable, in accordance with
Section 25.21(g), if in the configuration used to
show compliance with Section 25.121(b) with
this takeoff ice accretion:
(A) The stall speed at maximum
takeoff weight exceeds that in non-

icing conditions by more than the
greater of 3 knots CAS or 3 percent of
VSR; or
(B) The degradation of the gradient
of climb determined in accordance with
Section 25.121(b) is greater than one-half of
the applicable actual-to-net takeoff
flight path gradient reduction defined
in Section 25.115(b).
(c) Final takeoff. In the en route configuration at the end of the takeoff
path determined in accordance with
Section 25.111:
(1) The steady gradient of climb may
not be less than 1.2 percent for two-engine airplanes, 1.5 percent for three-engine airplanes, and 1.7 percent for fourengine airplanes, at VFTO with - 
(i) The critical engine inoperative
and the remaining engines at the available maximum continuous power or
thrust; and
(ii) The weight equal to the weight
existing at the end of the takeoff path,
determined under Section 25.111.
(2) The requirements of paragraph
(c)(1) of this section must be met:
(i) In non-icing conditions; and
(ii) In icing conditions with the most
critical of the final takeoff ice accretion(s) defined in Appendices C and O of
this part, as applicable, in accordance
with Section 25.21(g), if in the configuration
used to show compliance with Section 25.121(b)
with the takeoff ice accretion used to
show compliance with Section 25.111(c)(5)(i):
(A) The stall speed at maximum
takeoff weight exceeds that in nonicing conditions by more than the
greater of 3 knots CAS or 3 percent of
VSR; or
(B) The degradation of the gradient
of climb determined in accordance with
Section 25.121(b) is greater than one-half of
the applicable actual-to-net takeoff
flight path gradient reduction defined
in Section 25.115(b).
(d) Approach. In a configuration corresponding to the normal all-enginesoperating procedure in which VSR for
this configuration does not exceed 110
percent of the VSR for the related allengines-operating landing configuration:
(1) The steady gradient of climb may
not be less than 2.1 percent for two-engine airplanes, 2.4 percent for three-engine airplanes, and 2.7 percent for fourengine airplanes, with - 

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