Federal Aviation Administration, DOT
Section 29.1359 Electrical system
smoke protection.

fire

Section 29.1387

and

(a) Components of the electrical system must meet the applicable fire and
smoke protection provisions of SectionSection 29.831
and 29.863.
(b) Electrical cables, terminals, and
equipment, in designated fire zones,
and that are used in emergency procedures, must be at least fire resistant.
(c) Insulation on electrical wire and
cable installed in the rotorcraft must
be self-extinguishing when tested in accordance 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]

Section 29.1363

Electrical system tests.

(a) When laboratory tests of the electrical 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 distribution wiring and connected loads to
the extent necessary for valid test results; and
(3) Laboratory generator drives must
simulate the prime movers on the
rotorcraft with respect to their reaction 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.
LIGHTS
Section 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.

spaschal on DSK3GDR082PROD with CFR

Section 29.1383

Landing lights.

(a) Each required landing or hovering
light must be approved.
(b) Each landing light must be installed 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 landing.
(c) At least one separate switch must
be provided, as applicable - 
(1) For each separately installed
landing light; and
(2) For each group of landing lights
installed at a common location.
Section 29.1385 Position light system installation.
(a) General. Each part of each position light system must meet the applicable requirements of this section and
each system as a whole must meet the
requirements of SectionSection 29.1387 through
29.1397.
(b) Forward position lights. Forward
position lights must consist of a red
and a green light spaced laterally as
far apart as practicable and installed
forward on the rotorcraft so that, with
the rotorcraft in the normal flying position, the red light is on the left side,
and the green light is on the right side.
Each light must be approved.
(c) Rear position light. The rear position light must be a white light mounted as far aft as practicable, and must
be approved.
(d) Circuit. The two forward position
lights and the rear position light must
make a single circuit.
(e) Light covers and color filters. Each
light cover or color filter must be at
least flame resistant and may not
change color or shape or lose any appreciable light transmission during
normal use.
Section 29.1387 Position light system dihedral angles.
(a) Except as provided in paragraph
(e) of this section, each forward and
rear position light must, as installed,
show unbroken light within the dihedral angles described in this section.
(b) Dihedral angle L (left) is formed
by two intersecting vertical planes, the
first parallel to the longitudinal axis of
the rotorcraft, and the other at 110 degrees to the left of the first, as viewed
when looking forward along the longitudinal axis.

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