title-14-part-23-sec23-2530

191

Federal Aviation Administration, DOT

§ 23.2530

(a) Each catastrophic failure condi-

tion is extremely improbable;

(b) Each hazardous failure condition

is extremely remote; and

remote.

§ 23.2515

Electrical and electronic sys-

tem lightning protection.

An airplane approved for IFR oper-

ations must meet the following re-
quirements, unless an applicant shows
that exposure to lightning is unlikely:

(a) Each electrical or electronic sys-

tem that performs a function, the fail-
ure of which would prevent the contin-
ued safe flight and landing of the air-
plane, must be designed and installed
such that—

(1) The function at the airplane level

is not adversely affected during and
after the time the airplane is exposed
to lightning; and

(2) The system recovers normal oper-

ation of that function in a timely man-
ner after the airplane is exposed to
lightning unless the system’s recovery
conflicts with other operational or
functional requirements of the system.

(b) Each electrical and electronic

system that performs a function, the
failure of which would significantly re-
duce the capability of the airplane or
the ability of the flightcrew to respond
to an adverse operating condition,
must be designed and installed such
that the system recovers normal oper-
ation of that function in a timely man-
ner after the airplane is exposed to
lightning.

§ 23.2520

High-intensity Radiated

Fields (HIRF) protection.

(a) Each electrical and electronic

system that performs a function, the
failure of which would prevent the con-
tinued safe flight and landing of the
airplane, must be designed and in-
stalled such that—

(1) The function at the airplane level

is not adversely affected during and
after the time the airplane is exposed
to the HIRF environment; and

(2) The system recovers normal oper-

ation of that function in a timely man-
ner after the airplane is exposed to the
HIRF environment, unless the system’s
recovery conflicts with other oper-

ational or functional requirements of
the system.

(b) For airplanes approved for IFR

operations, each electrical and elec-
tronic system that performs a func-
tion, the failure of which would signifi-
cantly reduce the capability of the air-
plane or the ability of the flightcrew to
respond to an adverse operating condi-
tion, must be designed and installed
such that the system recovers normal
operation of that function in a timely
manner after the airplane is exposed to
the HIRF environment.

[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]

§ 23.2525

System power generation,

storage, and distribution.

The power generation, storage, and

distribution for any system must be de-
signed and installed to—

(a) Supply the power required for op-

eration of connected loads during all
intended operating conditions;

(b) Ensure no single failure or mal-

function of any one power supply, dis-
tribution system, or other utilization
system will prevent the system from
supplying the essential loads required
for continued safe flight and landing;
and

mary source fails, to supply essential
loads, including non-continuous essen-
tial loads for the time needed to com-
plete the function required for contin-
ued safe flight and landing.

§ 23.2530

External and cockpit light-

ing.

(a) The applicant must design and in-

stall all lights to minimize any adverse
effects on the performance of
flightcrew duties.

(b) Any position and anti-collision

lights, if required by part 91 of this
chapter, must have the intensities,
flash rate, colors, fields of coverage,
and other characteristics to provide
sufficient time for another aircraft to
avoid a collision.

part 91 of this chapter, must include a
red light on the left side of the air-
plane, a green light on the right side of
the airplane, spaced laterally as far

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14 CFR Ch. I (1–1–24 Edition)

§ 23.2535

apart as practicable, and a white light
facing aft, located on an aft portion of
the airplane or on the wing tips.

(d) Any taxi and landing lights must

be designed and installed so they pro-
vide sufficient light for night oper-
ations.

(e) For seaplanes or amphibian air-

planes, riding lights must provide a
white light visible in clear atmospheric
conditions.

§ 23.2535

Safety equipment.

Safety and survival equipment, re-

quired by the operating rules of this
chapter, must be reliable, readily ac-
cessible, easily identifiable, and clearly
marked to identify its method of oper-
ation.

§ 23.2540

Flight in icing conditions.

An applicant who requests certifi-

cation for flight in icing conditions de-
fined in part 1 of appendix C to part 25
of this chapter, or an applicant who re-
quests certification for flight in these
icing conditions and any additional at-
mospheric icing conditions, must show
the following in the icing conditions
for which certification is requested:

(a) The ice protection system pro-

vides for safe operation.

(b) The airplane design must provide

protection from stalling when the
autopilot is operating.

§ 23.2545

Pressurized systems ele-

ments.

Pressurized systems must withstand

appropriate proof and burst pressures.

§ 23.2550

Equipment containing high-

energy rotors.

Equipment containing high-energy

rotors must be designed or installed to
protect the occupants and airplane
from uncontained fragments.

Subpart G—Flightcrew Interface

and Other Information

§ 23.2600

Flightcrew interface.

(a) The pilot compartment, its equip-

ment, and its arrangement to include
pilot view, must allow each pilot to
perform his or her duties, including
taxi, takeoff, climb, cruise, descent,
approach, landing, and perform any
maneuvers within the operating enve-

lope of the airplane, without excessive
concentration, skill, alertness, or fa-
tigue.

(b) The applicant must install flight,

navigation, surveillance, and power-
plant controls and displays so
flightcrew members can monitor and
perform defined tasks associated with
the intended functions of systems and
equipment. The system and equipment
design must minimize flightcrew er-
rors, which could result in additional
hazards.

flightcrew interface design must allow
for continued safe flight and landing
after the loss of vision through any one
of the windshield panels.

[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]

§ 23.2605

Installation and operation.

(a) Each item of installed equipment

related to the flightcrew interface
must be labelled, if applicable, as to it
identification, function, or operating
limitations, or any combination of
these factors.

(b) There must be a discernible

means of providing system operating
parameters required to operate the air-
plane, including warnings, cautions,
and normal indications to the respon-
sible crewmember.

system operating condition must be
provided in a timely manner to the
crewmember responsible for taking
corrective action. The information
must be clear enough to avoid likely
crewmember errors.

§ 23.2610

Instrument markings, control

markings, and placards.

(a) Each airplane must display in a

conspicuous manner any placard and
instrument marking necessary for op-
eration.

(b) The design must clearly indicate

the function of each cockpit control,
other than primary flight controls.

strument marking and placard infor-
mation in the Airplane Flight Manual.