title-14-part-23-sec23-2330

187

Federal Aviation Administration, DOT

§ 23.2330

(b) Airplanes approved for aerobatics

must have a means to egress the air-
plane in flight.

[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]

§ 23.2320

Occupant physical environ-

ment.

(a) The applicant must design the

airplane to—

(1) Allow clear communication be-

tween the flightcrew and passengers;

(2) Protect the pilot and flight con-

trols from propellers; and

(3) Protect the occupants from seri-

ous injury due to damage to wind-
shields, windows, and canopies.

(b) For level 4 airplanes, each wind-

shield and its supporting structure di-
rectly in front of the pilot must with-
stand, without penetration, the impact
equivalent to a two-pound bird when
the velocity of the airplane is equal to
the airplane’s maximum approach flap
speed.

occupant with air at a breathable pres-
sure, free of hazardous concentrations
of gases, vapors, and smoke during nor-
mal operations and likely failures.

(d) If a pressurization system is in-

stalled in the airplane, it must be de-
signed to protect against—

(1) Decompression to an unsafe level;

and

(2) Excessive differential pressure.
(e) If an oxygen system is installed in

the airplane, it must—

(1) Effectively provide oxygen to each

user to prevent the effects of hypoxia;
and

(2) Be free from hazards in itself, in

its method of operation, and its effect
upon other components.

IRE AND

IGH

NERGY

ROTECTION

§ 23.2325

Fire protection.

(a) The following materials must be

self-extinguishing—

(1) Insulation on electrical wire and

electrical cable;

(2) For levels 1, 2, and 3 airplanes,

materials in the baggage and cargo
compartments inaccessible in flight;
and

(3) For level 4 airplanes, materials in

the cockpit, cabin, baggage, and cargo
compartments.

(b) The following materials must be

flame resistant—

(1) For levels 1, 2 and 3 airplanes, ma-

terials in each compartment accessible
in flight; and

(2) Any equipment associated with

any electrical cable installation and
that would overheat in the event of cir-
cuit overload or fault.

fuselage, if installed, must not be a
flame propagation hazard.

(d) Sources of heat within each bag-

gage and cargo compartment that are
capable of igniting adjacent objects
must be shielded and insulated to pre-
vent such ignition.

(e) For level 4 airplanes, each bag-

gage and cargo compartment must—

(1) Be located where a fire would be

visible to the pilots, or equipped with a
fire detection system and warning sys-
tem; and

(2) Be accessible for the manual ex-

tinguishing of a fire, have a built-in
fire extinguishing system, or be con-
structed and sealed to contain any fire
within the compartment.

(f) There must be a means to extin-

guish any fire in the cabin such that—

(1) The pilot, while seated, can easily

access the fire extinguishing means;
and

(2) For levels 3 and 4 airplanes, pas-

sengers have a fire extinguishing
means available within the passenger
compartment.

(g) Each area where flammable fluids

or vapors might escape by leakage of a
fluid system must—

(1) Be defined; and
(2) Have a means to minimize the

probability of fluid and vapor ignition,
and the resultant hazard, if ignition oc-
curs.

(h) Combustion heater installations

must be protected from uncontained
fire.

§ 23.2330

Fire protection in designated

fire zones and adjacent areas.

(a) Flight controls, engine mounts,

and other flight structures within or
adjacent to designated fire zones must
be capable of withstanding the effects
of a fire.

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188

14 CFR Ch. I (1–1–24 Edition)

§ 23.2335

(b) Engines in a designated fire zone

must remain attached to the airplane
in the event of a fire.

nals, equipment, and electrical cables
used during emergency procedures
must be fire-resistant.

§ 23.2335

Lightning protection.

The airplane must be protected

against catastrophic effects from light-
ning.

Subpart E—Powerplant

§ 23.2400

Powerplant installation.

(a) For the purpose of this subpart,

the airplane powerplant installation
must include each component nec-
essary for propulsion, which affects
propulsion safety, or provides auxiliary
power to the airplane.

(b) Each airplane engine and pro-

peller must be type certificated, except
for engines and propellers installed on
level 1 low-speed airplanes, which may
be approved under the airplane type
certificate in accordance with a stand-
ard accepted by the Administrator that
contains airworthiness criteria the Ad-
ministrator has found appropriate and
applicable to the specific design and in-
tended use of the engine or propeller
and provides a level of safety accept-
able to the Administrator.

arrange each powerplant installation
to account for—

(1) Likely operating conditions, in-

cluding foreign object threats;

(2) Sufficient clearance of moving

parts to other airplane parts and their
surroundings;

(3) Likely hazards in operation in-

cluding hazards to ground personnel;
and

(4) Vibration and fatigue.
(d) Hazardous accumulations of

fluids, vapors, or gases must be iso-
lated from the airplane and personnel
compartments, and be safely contained
or discharged.

(e) Powerplant components must

comply with their component limita-

tions and installation instructions or
be shown not to create a hazard.

[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]

§ 23.2405

Automatic power or thrust

control systems.

(a) An automatic power or thrust

control system intended for in-flight
use must be designed so no unsafe con-
dition will result during normal oper-
ation of the system.

(b) Any single failure or likely com-

bination of failures of an automatic
power or thrust control system must
not prevent continued safe flight and
landing of the airplane.

matic power or thrust control system
by the flightcrew must be prevented, or
if not prevented, must not result in an
unsafe condition.

(d) Unless the failure of an automatic

power or thrust control system is ex-
tremely remote, the system must—

(1) Provide a means for the flightcrew

to verify the system is in an operating
condition;

(2) Provide a means for the flightcrew

to override the automatic function;
and

(3) Prevent inadvertent deactivation

of the system.

§ 23.2410

Powerplant installation haz-

ard assessment.

The applicant must assess each pow-

erplant separately and in relation to
other airplane systems and installa-
tions to show that any hazard resulting
from the likely failure of any power-
plant system, component, or accessory
will not—

(a) Prevent continued safe flight and

landing or, if continued safe flight and
landing cannot be ensured, the hazard
has been minimized;

(b) Cause serious injury that may be

avoided; and

crewmember for continued operation of
any remaining powerplant system.

§ 23.2415

Powerplant ice protection.

(a) The airplane design, including the

induction and inlet system, must pre-
vent foreseeable accumulation of ice or