Section 27.1361

14 CFR Ch. I (1-1-19 Edition)

(1) The main circuits of starter motors; and
(2) Circuits in which no hazard is presented by their omission.
(b) A protective device for a circuit
essential to flight safety may not be
used to protect any other circuit.
(c) Each resettable circuit protective
device ( - trip free -  device in which the
tripping mechanism cannot be overridden by the operating control) must
be designed so that - 
(1) A manual operation is required to
restore service after trippling; and
(2) If an overload or circuit fault exists, the device 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) If fuses are used, there must be
one spare of each rating, or 50 percent
spare fuses of each rating, whichever is
greater.
(Secs. 313(a), 601, 603, 604, and 605 of the Federal Aviation Act of 1958 (49 U.S.C. 1354(a),
1421, 1423, 1424, and 1425); and sec. 6(c) of the
Dept. of Transportation Act (49 U.S.C.
1655(c)))
[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964; 29
FR 17885, Dec. 17, 1964, as amended by Amdt.
27-13, 42 FR 36972, July 18, 1977]

Section 27.1361

Master switch.

spaschal on DSK3GDR082PROD with CFR

(a) There must be a master switch arrangement to allow ready disconnection of each electric power source from
the main bus. The point of disconnection must be adjacent to the sources
controlled by the switch.
(b) Load circuits may be connected so
that they remain energized after the
switch is opened, if they are protected
by circuit protective devices, rated at
five amperes or less, adjacent to the
electric power source.
(c) The master switch or its controls
must be installed so that the switch is
easily discernible and accessible to a
crewmember in flight.
Section 27.1365

Electric cables.

(a) Each electric connecting cable
must be of adequate capacity.

(b) Each cable that would overheat in
the event of circuit overload or fault
must be at least flame resistant and
may not emit dangerous quantities of
toxic fumes.
(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. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27-35, 63 FR 43285, Aug. 12,
1998]

Section 27.1367 Switches.
Each switch must be - 
(a) Able to carry its rated current;
(b) Accessible to the crew; and
(c) Labeled as to operation and the
circuit controlled.
LIGHTS
Section 27.1381 Instrument lights.
The instrument lights must - 
(a) Make each instrument, switch,
and other devices 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.
Section 27.1383 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 27.1385 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

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