title-14-part-23-sec23-2415

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

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§ 23.2435

snow that adversely affects powerplant
operation.

(b) The powerplant installation de-

sign must prevent any accumulation of
ice or snow that adversely affects pow-
erplant operation, in those icing condi-
tions for which certification is re-
quested.

§ 23.2420

Reversing systems.

Each reversing system must be de-

signed so that—

(a) No unsafe condition will result

during normal operation of the system;
and

(b) The airplane is capable of contin-

ued safe flight and landing after any
single failure, likely combination of
failures, or malfunction of the revers-
ing system.

§ 23.2425

Powerplant operational char-

acteristics.

(a) The installed powerplant must op-

erate without any hazardous character-
istics during normal and emergency op-
eration within the range of operating
limitations for the airplane and the en-
gine.

(b) The pilot must have the capa-

bility to stop the powerplant in flight
and restart the powerplant within an
established operational envelope.

§ 23.2430

Fuel systems.

(a) Each fuel system must—
(1) Be designed and arranged to pro-

vide independence between multiple
fuel storage and supply systems so that
failure of any one component in one
system will not result in loss of fuel
storage or supply of another system;

(2) Be designed and arranged to pre-

vent ignition of the fuel within the sys-
tem by direct lightning strikes or
swept lightning strokes to areas where
such occurrences are highly probable,
or by corona or streamering at fuel
vent outlets;

(3) Provide the fuel necessary to en-

sure each powerplant and auxiliary
power unit functions properly in all
likely operating conditions;

(4) Provide the flightcrew with a

means to determine the total useable
fuel available and provide uninter-
rupted supply of that fuel when the
system is correctly operated, account-
ing for likely fuel fluctuations;

(5) Provide a means to safely remove

or isolate the fuel stored in the system
from the airplane;

(6) Be designed to retain fuel under

all likely operating conditions and
minimize hazards to the occupants dur-
ing any survivable emergency landing.
For level 4 airplanes, failure due to
overload of the landing system must be
taken into account; and

(7) Prevent hazardous contamination

of the fuel supplied to each powerplant
and auxiliary power unit.

(b) Each fuel storage system must—
(1) Withstand the loads under likely

operating conditions without failure;

(2) Be isolated from personnel com-

partments and protected from hazards
due to unintended temperature influ-
ences;

(3) Be designed to prevent significant

loss of stored fuel from any vent sys-
tem due to fuel transfer between fuel
storage or supply systems, or under
likely operating conditions;

(4) Provide fuel for at least one-half

hour of operation at maximum contin-
uous power or thrust; and

(5) Be capable of jettisoning fuel safe-

ly if required for landing.

charging system must be designed to—

(1) Prevent improper refilling or re-

charging;

(2) Prevent contamination of the fuel

stored during likely operating condi-
tions; and

(3) Prevent the occurrence of any

hazard to the airplane or to persons
during refilling or recharging.

§ 23.2435

Powerplant induction and

exhaust systems.

(a) The air induction system for each

powerplant or auxiliary power unit and
their accessories must—

(1) Supply the air required by that

powerplant or auxiliary power unit and
its accessories under likely operating
conditions;

(2) Be designed to prevent likely haz-

ards in the event of fire or backfire;

(3) Minimize the ingestion of foreign

matter; and

(4) Provide an alternate intake if

blockage of the primary intake is like-
ly.