title-14-part-29-sec29-1357

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.

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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§ 29.1385

designed to de-energize and disconnect
faulty power sources and power trans-
mission equipment from their associ-
ated buses with sufficient rapidity to
provide protection from hazardous
overvoltage and other malfunctioning.

device must be designed so that, when
an overload or circuit fault exists, it
will open the circuit regardless of the
position of the operating control.

(d) If the ability to reset a circuit

breaker or replace a fuse is essential to
safety in flight, that circuit breaker or
fuse must be located and identified so
that it can be readily reset or replaced
in flight.

(e) Each essential load must have in-

dividual circuit protection. However,
individual protection for each circuit
in an essential load system (such as
each position light circuit in a system)
is not required.

(f) If fuses are used, there must be

spare fuses for use in flight equal to at
least 50 percent of the number of fuses
of each rating required for complete
circuit protection.

(g) Automatic reset circuit breakers

may be used as integral protectors for
electrical equipment provided there is
circuit protection for the cable sup-
plying power to the equipment.

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–24, 49 FR 44440, Nov. 6,
1984]

§ 29.1359

Electrical system fire and

smoke protection.

(a) Components of the electrical sys-

tem must meet the applicable fire and
smoke protection provisions of §§ 29.831
and 29.863.

(b) Electrical cables, terminals, and

equipment, in designated fire zones,
and that are used in emergency proce-
dures, must be at least fire resistant.

cable installed in the rotorcraft must
be self-extinguishing when tested in ac-
cordance with Appendix F, Part I(a)(3),
of part 25 of this chapter.

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–42, 63 FR 43285, Aug. 12,
1998]

§ 29.1363

Electrical system tests.

(a) When laboratory tests of the elec-

trical system are conducted—

(1) The tests must be performed on a

mock-up using the same generating
equipment used in the rotorcraft;

(2) The equipment must simulate the

electrical characteristics of the dis-
tribution wiring and connected loads to
the extent necessary for valid test re-
sults; and

(3) Laboratory generator drives must

simulate the prime movers on the
rotorcraft with respect to their reac-
tion to generator loading, including
loading due to faults.

(b) For each flight condition that

cannot be simulated adequately in the
laboratory or by ground tests on the
rotorcraft, flight tests must be made.

IGHTS

§ 29.1381

Instrument lights.

The instrument lights must—
(a) Make each instrument, switch,

and other device for which they are
provided easily readable; and

(b) Be installed so that—
(1) Their direct rays are shielded

from the pilot’s eyes; and

(2) No objectionable reflections are

visible to the pilot.

§ 29.1383

Landing lights.

(a) Each required landing or hovering

light must be approved.

(b) Each landing light must be in-

stalled so that—

(1) No objectionable glare is visible

to the pilot;

(2) The pilot is not adversely affected

by halation; and

(3) It provides enough light for night

operation, including hovering and land-
ing.

be provided, as applicable—

(1) For each separately installed

landing light; and

(2) For each group of landing lights

installed at a common location.

§ 29.1385

Position light system installa-

tion.

(a)

General. Each part of each posi-

tion light system must meet the appli-
cable requirements of this section and
each system as a whole must meet the
requirements of §§ 29.1387 through
29.1397.