title-14-part-23-sec23-2115

179

Federal Aviation Administration, DOT

§ 23.2115

(2) Level 2—for airplanes with a max-

imum seating configuration of 2 to 6
passengers.

(3) Level 3—for airplanes with a max-

imum seating configuration of 7 to 9
passengers.

(4) Level 4—for airplanes with a max-

imum seating configuration of 10 to 19
passengers.

and V

≤

250 Knots Calibrated

Airspeed (KCAS) and a M

≤

0.6.

(2) High speed—for airplanes with a

or V

> 250 KCAS or a M

> 0.6.

(d) Airplanes not certified for aero-

batics may be used to perform any ma-
neuver incident to normal flying, in-
cluding—

(1) Stalls (except whip stalls); and
(2) Lazy eights, chandelles, and steep

turns, in which the angle of bank is not
more than 60 degrees.

(e) Airplanes certified for aerobatics

may be used to perform maneuvers
without limitations, other than those
limitations established under subpart
G of this part.

§ 23.2010

Accepted means of compli-

ance.

(a) An applicant must comply with

this part using a means of compliance,
which may include consensus stand-
ards, accepted by the Administrator.

(b) An applicant requesting accept-

ance of a means of compliance must
provide the means of compliance to the
FAA in a form and manner acceptable
to the Administrator.

Subpart B—Flight

ERFORMANCE

§ 23.2100

Weight and center of gravity.

(a) The applicant must determine

limits for weights and centers of grav-
ity that provide for the safe operation
of the airplane.

(b) The applicant must comply with

each requirement of this subpart at
critical combinations of weight and
center of gravity within the airplane’s
range of loading conditions using toler-
ances acceptable to the Administrator.

the time of determining its empty

weight and center of gravity must be
well defined and easily repeatable.

§ 23.2105

Performance data.

(a) Unless otherwise prescribed, an

airplane must meet the performance
requirements of this subpart in—

(1) Still air and standard atmospheric

conditions at sea level for all airplanes;
and

(2) Ambient atmospheric conditions

within the operating envelope for lev-
els 1 and 2 high-speed and levels 3 and
4 airplanes.

(b) Unless otherwise prescribed, the

applicant must develop the perform-
ance data required by this subpart for
the following conditions:

(1) Airport altitudes from sea level to

10,000 feet (3,048 meters); and

(2) Temperatures above and below

standard day temperature that are
within the range of operating limita-
tions, if those temperatures could have
a negative effect on performance.

mining takeoff and landing distances
must be executable consistently by pi-
lots of average skill in atmospheric
conditions expected to be encountered
in service.

(d) Performance data determined in

accordance with paragraph (b) of this
section must account for losses due to
atmospheric conditions, cooling needs,
and other demands on power sources.

§ 23.2110

Stall speed.

The applicant must determine the

airplane stall speed or the minimum
steady flight speed for each flight con-
figuration used in normal operations,
including takeoff, climb, cruise, de-
scent, approach, and landing. The stall
speed or minimum steady flight speed
determination must account for the
most adverse conditions for each flight
configuration with power set at—

(a) Idle or zero thrust for propulsion

systems that are used primarily for
thrust; and

(b) A nominal thrust for propulsion

systems that are used for thrust, flight
control, and/or high-lift systems.

§ 23.2115

Takeoff performance.

(a) The applicant must determine air-

plane takeoff performance accounting
for—

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14 CFR Ch. I (1–1–24 Edition)

§ 23.2120

(1) Stall speed safety margins;
(2) Minimum control speeds; and
(3) Climb gradients.
(b) For single engine airplanes and

levels 1, 2, and 3 low-speed multiengine
airplanes, takeoff performance includes
the determination of ground roll and
initial climb distance to 50 feet (15 me-
ters) above the takeoff surface.

multiengine airplanes, and level 4 mul-
tiengine airplanes, takeoff performance
includes a determination of the fol-
lowing distances after a sudden critical
loss of thrust—

(1) An aborted takeoff at critical

speed;

(2) Ground roll and initial climb to 35

feet (11 meters) above the takeoff sur-
face; and

(3) Net takeoff flight path.

[Doc. No. FAA–2015–1621, Amdt. 23–64, 81 FR
96689, Dec. 30, 2016, as amended by Doc. No.
FAA–2022–1355, Amdt. 23–65, 87 FR 75710, Dec.
9, 2022]

§ 23.2120

Climb requirements.

The design must comply with the fol-

lowing minimum climb performance
out of ground effect:

(a) With all engines operating and in

the initial climb configuration(s)—

(1) For levels 1 and 2 low-speed air-

planes, a climb gradient of 8.3 percent
for landplanes and 6.7 percent for sea-
planes and amphibians; and

(2) For levels 1 and 2 high-speed air-

planes, all level 3 airplanes, and level 4
single-engines a climb gradient after
takeoff of 4 percent.

(b) After a critical loss of thrust on

multiengine airplanes—

(1) For levels 1 and 2 low-speed air-

planes that do not meet single-engine
crashworthiness requirements, a climb
gradient of 1.5 percent at a pressure al-
titude of 5,000 feet (1,524 meters) in the
cruise configuration(s);

(2) For levels 1 and 2 high-speed air-

planes, and level 3 low-speed airplanes,
a 1 percent climb gradient at 400 feet
(122 meters) above the takeoff surface
with the landing gear retracted and
flaps in the takeoff configuration(s);
and

(3) For level 3 high-speed airplanes

and all level 4 airplanes, a 2 percent
climb gradient at 400 feet (122 meters)
above the takeoff surface with the

landing gear retracted and flaps in the
approach configuration(s).

dient of 3 percent without creating
undue pilot workload with the landing
gear extended and flaps in the landing
configuration(s).

[Doc. No. FAA–2015–1621, Amdt. 23–64, 81 FR
96689, Dec. 30, 2016, as amended by Doc. No.
FAA–2022–1355, Amdt. 23–65, 87 FR 75710, Dec.
9, 2022]

§ 23.2125

Climb information.

(a) The applicant must determine

climb performance at each weight, alti-
tude, and ambient temperature within
the operating limitations—

(1) For all single-engine airplanes;
(2) For levels 1 and 2 high-speed mul-

tiengine airplanes and level 3 multien-
gine airplanes, following a critical loss
of thrust on takeoff in the initial climb
configuration; and

(3) For all multiengine airplanes,

during the enroute phase of flight with
all engines operating and after a crit-
ical loss of thrust in the cruise configu-
ration.

(b) The applicant must determine the

glide performance for single-engine air-
planes after a complete loss of thrust.

§ 23.2130

Landing.

The applicant must determine the

following, for standard temperatures at
critical combinations of weight and al-
titude within the operational limits:

(a) The distance, starting from a

height of 50 feet (15 meters) above the
landing surface, required to land and
come to a stop.

(b) The approach and landing speeds,

configurations, and procedures, which
allow a pilot of average skill to land
within the published landing distance
consistently and without causing dam-
age or injury, and which allow for a
safe transition to the balked landing
conditions of this part accounting for:

(1) Stall speed safety margin; and
(2) Minimum control speeds.

LIGHT

HARACTERISTICS

§ 23.2135

Controllability.

(a) The airplane must be controllable

and maneuverable, without requiring
exceptional piloting skill, alertness, or