Code of Federal Regulations - Title 14

811

Federal Aviation Administration, DOT

§ 29.1383

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
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—

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