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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. 

(c) In designated fire zones, termi-

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. 

(c) The applicant must construct and 

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. 

(c) Inadvertent operation of an auto-

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 

(c) Require immediate action by any 

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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