663 

Federal Aviation Administration, DOT 

§ 29.1387 

§ 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. 

(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 po-
sition, 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 posi-

tion light must be a white light mount-
ed 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 ap-
preciable light transmission during 
normal use. 

§ 29.1387

Position light system dihe-

dral 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 dihe-
dral 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 de-
grees to the left of the first, as viewed 
when looking forward along the longi-
tudinal axis. 

VerDate Sep<11>2014 

12:50 Apr 30, 2019

Jkt 247046

PO 00000

Frm 00673

Fmt 8010

Sfmt 8010

Y:\SGML\247046.XXX

247046

spaschal on DSK3GDR082PROD with CFR