190 

14 CFR Ch. I (1–1–24 Edition) 

§ 23.2440 

(b) The exhaust system, including ex-

haust heat exchangers for each power-
plant or auxiliary power unit, must— 

(1) Provide a means to safely dis-

charge potential harmful material; and 

(2) Be designed to prevent likely haz-

ards from heat, corrosion, or blockage. 

§ 23.2440

Powerplant fire protection. 

(a) A powerplant, auxiliary power 

unit, or combustion heater that in-
cludes a flammable fluid and an igni-
tion source for that fluid must be in-
stalled in a designated fire zone. 

(b) Each designated fire zone must 

provide a means to isolate and miti-
gate hazards to the airplane in the 
event of fire or overheat within the 
zone. 

(c) Each component, line, fitting, and 

control subject to fire conditions 
must— 

(1) Be designed and located to pre-

vent hazards resulting from a fire, in-
cluding any located adjacent to a des-
ignated fire zone that may be affected 
by fire within that zone; 

(2) Be fire-resistant if carrying flam-

mable fluid, gas or air, or is required to 
operate in the event of a fire; and 

(3) Be fireproof or enclosed by a fire 

proof shield if storing concentrated 
flammable fluids. 

(d) The applicant must provide a 

means to prevent hazardous quantities 
of flammable fluids from flowing into, 
within or through each designated fire 
zone. This means must— 

(1) Not restrict flow or limit oper-

ation of any remaining powerplant or 
auxiliary power unit, or equipment 
necessary for safety; 

(2) Prevent inadvertent operation; 

and 

(3) Be located outside the fire zone 

unless an equal degree of safety is pro-
vided with a means inside the fire zone. 

(e) A means to ensure the prompt de-

tection of fire must be provided for 
each designated fire zone— 

(1) On a multiengine airplane where 

detection will mitigate likely hazards 
to the airplane; or 

(2) That contains a fire extinguisher. 
(f) A means to extinguish fire within 

a fire zone, except a combustion heater 
fire zone, must be provided for— 

(1) Any fire zone located outside the 

pilot’s view; 

(2) Any fire zone embedded within the 

fuselage, which must also include a re-
dundant means to extinguish fire; and 

(3) Any fire zone on a level 4 airplane. 

[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] 

Subpart F—Equipment 

§ 23.2500

Airplane level systems re-

quirements. 

This section applies generally to in-

stalled equipment and systems unless a 
section of this part imposes require-
ments for a specific piece of equipment, 
system, or systems. 

(a) The equipment and systems re-

quired for an airplane to operate safely 
in the kinds of operations for which 
certification is requested (Day VFR, 
Night VFR, IFR) must be designed and 
installed to— 

(1) Meet the level of safety applicable 

to the certification and performance 
level of the airplane; and 

(2) Perform their intended function 

throughout the operating and environ-
mental limits for which the airplane is 
certificated. 

(b) The systems and equipment not 

covered by paragraph (a) of this sec-
tion—considered separately and in re-
lation to other systems—must be de-
signed and installed so their operation 
does not have an adverse effect on the 
airplane or its occupants. 

[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] 

§ 23.2505

Function and installation. 

When installed, each item of equip-

ment must function as intended. 

§ 23.2510

Equipment, systems, and in-

stallations. 

For any airplane system or equip-

ment whose failure or abnormal oper-
ation has not been specifically ad-
dressed by another requirement in this 
part, the applicant must design and in-
stall each system and equipment, such 
that there is a logical and acceptable 
inverse relationship between the aver-
age probability and the severity of fail-
ure conditions to the extent that: 

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Federal Aviation Administration, DOT 

§ 23.2530 

(a) Each catastrophic failure condi-

tion is extremely improbable; 

(b) Each hazardous failure condition 

is extremely remote; and 

(c) Each major failure condition is 

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 

(c) Have enough capacity, if the pri-

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. 

(c) Any position lights, if required by 

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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