663 

Federal Aviation Administration, DOT 

§ 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. 

(c) Each resettable circuit protective 

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. 

(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. 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. 

L

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. 

(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. 

§ 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. 

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