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14 CFR Ch. I (1–1–19 Edition) 

§ 27.1361 

(1) The main circuits of starter mo-

tors; and 

(2) Circuits in which no hazard is pre-

sented 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 over-
ridden 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 ex-

ists, the device will open the circuit re-
gardless of the position of the oper-
ating 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 Fed-
eral 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] 

§ 27.1361

Master switch. 

(a) There must be a master switch ar-

rangement to allow ready disconnec-
tion of each electric power source from 
the main bus. The point of disconnec-
tion 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. 

§ 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 ac-
cordance 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] 

§ 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. 

L

IGHTS

 

§ 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. 

§ 27.1383

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. 

(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. 

§ 27.1385

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 

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