Pt. 135, App. A

14 CFR Ch. I (1-1-19 Edition)

engine windmilling with the propeller controls in the normal position except that, if
an approved automatic feathering system is
installed, the propellers may be in the feathered position:
(1) Takeoff: landing gear extended. The minimum steady gradient of climb must be
measurably positive at the speed V1.
(2) Takeoff: landing gear retracted. The minimum steady gradient of climb may not be
less than 2 percent at speed V2. For airplanes
with fixed landing gear this requirement
must be met with the landing gear extended.
(c) En route climb: one-engine-inoperative.
The maximum weight must be determined
for each altitude and ambient temperature
within the operational limits established for
the airplane, at which the steady gradient of
climb is not less 1.2 percent at an altitude
1,000 feet above the takeoff surface, with the
airplane in the en route configuration, the
critical engine inoperative, the remaining
engine at the maximum continuous power or
thrust, and the most unfavorable center of
gravity.
7. Landing. (a) The landing field length described in paragraph (b) of this section must
be determined for standard atmosphere at
each weight and altitude within the operational limits established by the applicant.
(b) The landing field length is equal to the
landing distance determined under FAR
23.75(a) divided by a factor of 0.6 for the destination airport and 0.7 for the alternate airport. Instead of the gliding approach specified in FAR 23.75(a)(1), the landing may be
preceded by a steady approach down to the
50-foot height at a gradient of descent not
greater than 5.2 percent (3Section) at a calibrated
airspeed not less than 1.3VS1.

Stability
9. Static longitudinal stability. (a) In showing
compliance with FAR 23.175(b) and with
paragraph (b) of this section, the airspeed
must return to within Section71-2 percent of the
trim speed.
(b) Cruise stability. The stick force curve
must have a stable slope for a speed range of
Section50 knots from the trim speed except that
the speeds need not exceed VFC/MFC or be less
than 1.4VS1. This speed range will be considered to begin at the outer extremes of the
friction band and the stick force may not exceed 50 pounds with - 
(1) Landing gear retracted;
(2) Wing flaps retracted;
(3) The maximum cruising power as selected by the applicant as an operating limitation for turbine engines or 75 percent of
maximum continuous power for reciprocating engines except that the power need
not exceed that required at VMO/MMO;
(4) Maximum takeoff weight; and
(5) The airplane trimmed for level flight
with the power specified in paragraph (3) of
this paragraph.
VFC/MFC may not be less than a speed midway between VMO/MMO and VDF/MDF, except
that, for altitudes where Mach number is the
limiting factor, MFC need not exceed the
Mach number at which effective speed warning occurs.
(c) Climb stability (turbopropeller powered
airplanes only). In showing compliance with
FAR 23.175(a), an applicant must, instead of
the power specified in FAR 23.175(a)(4), use
the maximum power or thrust selected by
the applicant as an operating limitation for
use during climb at the best rate of climb
speed, except that the speed need not be less
than 1.4VS1.

Trim

Stalls

8. Trim. (a) Lateral and directional trim. The
airplane must maintain lateral and directional trim in level flight at a speed of VH or
VMO/MMO, whichever is lower, with landing
gear and wing flaps retracted.
(b) Longitudinal trim. The airplane must
maintain longitudinal trim during the following conditions, except that it need not
maintain trim at a speed greater than VMO/
MMO:
(1) In the approach conditions specified in
FAR 23.161(c) (3) through (5), except that instead of the speeds specified in those paragraphs, trim must be maintained with a
stick force of not more than 10 pounds down
to a speed used in showing compliance with
section 7 or 1.4VS1 whichever is lower.
(2) In level flight at any speed from VH or
VMO/MMO, whichever is lower, to either Vx or
1.4VS1, with the landing gear and wing flaps
retracted.

10. Stall warning. If artificial stall warning
is required to comply with FAR 23.207, the
warning device must give clearly distinguishable indications under expected conditions of flight. The use of a visual warning
device that requires the attention of the
crew within the cockpit is not acceptable by
itself.
Control Systems
11. Electric trim tabs. The airplane must
meet FAR 23.677 and in addition it must be
shown that the airplane is safely controllable and that a pilot can perform all the
maneuvers and operations necessary to effect a safe landing following any probable
electric trim tab runaway which might be
reasonably expected in service allowing for
appropriate time delay after pilot recognition of the runaway. This demonstration
must be conducted at the critical airplane
weights and center of gravity positions.

516

VerDate Sep<11>2014

08:20 May 17, 2019

Jkt 247048

PO 00000

Frm 00526

Fmt 8010

Sfmt 8002

Y:\SGML\247048.XXX

247048