810
14 CFR Ch. I (1–1–14 Edition)
§ 29.1353
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.
(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]
§ 29.1353
Electrical equipment and in-
stallations.
(a) 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.
(b) 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.
(c) Storage batteries must be de-
signed and installed as follows:
(1) Safe cell temperatures and pres-
sures must be maintained during any
probable charging and discharging con-
dition. No uncontrolled increase in cell
temperature may result when the bat-
tery is recharged (after previous com-
plete discharge)—
(i) At maximum regulated voltage or
power;
(ii) During a flight of maximum dura-
tion; and
(iii) Under the most adverse cooling
condition likely in service.
(2) Compliance with paragraph (a)(1)
of this section must be shown by test
unless experience with similar bat-
teries and installations has shown that
maintaining safe cell temperatures and
pressures presents no problem.
(3) No explosive or toxic gases emit-
ted by any battery in normal oper-
ation, or as the result of any probable
malfunction in the charging system or
battery installation, may accumulate
in hazardous quantities within the
rotorcraft.
(4) No corrosive fluids or gases that
may escape from the battery may dam-
age surrounding structures or adjacent
essential equipment.
(5) Each nickel cadmium battery in-
stallation capable of being used to
start an engine or auxiliary power unit
must have provisions to prevent any
hazardous effect on structure or essen-
tial systems that may be caused by the
maximum amount of heat the battery
can generate during a short circuit of
the battery or of its individual cells.
(6) Nickel cadmium battery installa-
tions capable of being used to start an
engine or auxiliary power unit must
have—
(i) A system to control the charging
rate of the battery automatically so as
to prevent battery overheating;
(ii) A battery temperature sensing
and over-temperature warning system
with a means for disconnecting the
battery from its charging source in the
event of an over-temperature condi-
tion; or
(iii) A battery failure sensing and
warning system with a means for dis-
connecting the battery from its charg-
ing source in the event of battery fail-
ure.
(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. 29–15, 43 FR 2327, Jan. 16, 1978]
§ 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
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