662 

14 CFR Ch. I (1–1–24 Edition) 

§ 29.1353 

(i) A single malfunction, including a 

wire bundle or junction box fire, can-
not result in loss of the part turned off 
and the part turned on; 

(ii) The parts turned on are elec-

trically and mechanically isolated 
from the parts turned off; and 

(2) Additional requirements for Cat-

egory A Rotorcraft. 

(i) Unless it can be shown that the 

loss of the normal electrical power gen-
erating system is extremely improb-
able, an emergency electrical power 
system, independent of the normal 
electrical power generating system, 
must be provided, with sufficient ca-
pacity to power all systems necessary 
for continued safe flight and landing. 

(ii) Failures, including junction box, 

control panel, or wire bundle fires, 
which would result in the loss of the 
normal and emergency systems, must 
be shown to be extremely improbable. 

(iii) Systems necessary for imme-

diate safety must continue to operate 
following the loss of the normal elec-
trical power generating system, with-
out the need for flight crew action. 

(e) Electrical equipment, controls, 

and wiring must be installed so that 
operation of any one unit or system of 
units will not adversely affect the si-
multaneous operation of any other 
electrical unit or system essential to 
safe operation. 

(f) Cables must be grouped, routed, 

and spaced so that damage to essential 
circuits will be minimized if there are 
faults in heavy current-carrying ca-
bles. 

(Secs. 313(a), 601, 603, 604, and 605 of the Fed-
eral Aviation Act of 1958 (49 U.S.C. 1354(a), 
1421, 1423, 1424, and 1425); and sec. 6(c), Dept. 
of Transportation Act (49 U.S.C. 1655(c))) 

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as 
amended by Amdt. 29–14, 42 FR 36973, July 18, 
1977; Amdt. 29–40, 61 FR 21908, May 10, 1996; 
Amdt. 29–42, 63 FR 43285, Aug. 12, 1998; Amdt. 
29–59, 88 FR 8740, Feb. 10, 2023] 

§ 29.1353

Energy storage systems. 

Energy storage systems must be de-

signed and installed as follows: 

(a) Energy storage systems must pro-

vide automatic protective features for 
any conditions that could prevent con-
tinued safe flight and landing. 

(b) Energy storage systems must not 

emit any flammable, explosive, or 

toxic gases, smoke, or fluids that could 
accumulate in hazardous quantities 
within the rotorcraft. 

(c) Corrosive fluids or gases that es-

cape from the system must not damage 
surrounding structures, adjacent equip-
ment, or systems necessary for contin-
ued safe flight and landing. 

(d) The maximum amount of heat 

and pressure that can be generated dur-
ing any operation or under any failure 
condition of the energy storage system 
or its individual components must not 
result in any hazardous effect on rotor-
craft structure, equipment, or systems 
necessary for continued safe flight and 
landing. 

(e) Energy storage system installa-

tions required for continued safe flight 
and landing of the rotorcraft must 
have monitoring features and a means 
to indicate to the pilot the status of all 
critical system parameters. 

[Amdt. 29–59, 88 FR 8740, Feb. 10, 2023] 

§ 29.1355

Distribution system. 

(a) The distribution system includes 

the distribution busses, their associ-
ated feeders, and each control and pro-
tective device. 

(b) If two independent sources of 

electrical power for particular equip-
ment or systems are required by this 
chapter, in the event of the failure of 
one power source for such equipment or 
system, another power source (includ-
ing its separate feeder) must be pro-
vided automatically or be manually se-
lectable to maintain equipment or sys-
tem operation. 

(Secs. 313(a), 601, 603, 604, and 605 of the Fed-
eral Aviation Act of 1958 (49 U.S.C. 1354(a), 
1421, 1423, 1424, and 1425); and sec. 6(c), Dept. 
of Transportation Act (49 U.S.C. 1655(c))) 

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as 
amended by Amdt. 29–14, 42 FR 36973, July 18, 
1977; Amdt. 29–24, 49 FR 44439, Nov. 6, 1984] 

§ 29.1357

Circuit protective devices. 

(a) Automatic protective devices 

must be used to minimize distress to 
the electrical system and hazard to the 
rotorcraft system and hazard to the 
rotorcraft in the event of wiring faults 
or serious malfunction of the system or 
connected equipment. 

(b) The protective and control de-

vices in the generating system must be 

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