556
14 CFR Ch. I (1–1–24 Edition)
§ 27.1411
be solid angles of obstructed visibility
totaling not more than 0.5 steradians.
(c)
Flashing characteristics. The ar-
rangement of the system, that is, the
number of light sources, beam width,
speed of rotation, and other character-
istics, must give an effective flash fre-
quency of not less than 40, nor more
than 100, cycles per minute. The effec-
tive flash frequency is the frequency at
which the rotorcraft’s complete anti-
collision light system is observed from
a distance, and applies to each sector
of light including any overlaps that
exist when the system consists of more
than one light source. In overlaps,
flash frequencies may exceed 100, but
not 180, cycles per minute.
(d)
Color. Each anticollision light
must be aviation red and must meet
the applicable requirements of § 27.1397.
(e)
Light intensity. The minimum
light intensities in any vertical plane,
measured with the red filter (if used)
and expressed in terms of ‘‘effective’’
intensities, must meet the require-
ments of paragraph (f) of this section.
The following relation must be as-
sumed:
I
I t dt
t
t
e
t
t
=
+
−
(
)
∫
( )
.
1
2
0 2
2
1
where:
I
e
= effective intensity (candles).
I(t) = instantaneous intensity as a function
of time.
t
2
¥
t
1
= flash time interval (seconds).
Normally, the maximum value of effective
intensity is obtained when
t
2
and
t
1
are cho-
sen so that the effective intensity is equal to
the instantaneous intensity at
t
2
and
t
1
.
(f)
Minimum effective intensities for
anticollision light. Each anticollision
light effective intensity must equal or
exceed the applicable values in the fol-
lowing table:
Angle above or below the horizontal plane
Effective
intensity
(candles)
0
°
to 5
°
................................................................
150
5
°
to 10
°
..............................................................
90
10
°
to 20
°
............................................................
30
20
°
to 30
°
............................................................
15
[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27–6, 36 FR 12972, July 10,
1971; Amdt. 27–10, 41 FR 5290, Feb. 5, 1976]
S
AFETY
E
QUIPMENT
§ 27.1411
General.
(a) Required safety equipment to be
used by the crew in an emergency, such
as flares and automatic liferaft re-
leases, must be readily accessible.
(b) Stowage provisions for required
safety equipment must be furnished
and must—
(1) Be arranged so that the equip-
ment is directly accessible and its loca-
tion is obvious; and
(2) Protect the safety equipment
from damage caused by being subjected
to the inertia loads specified in § 27.561.
[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27–11, 41 FR 55470, Dec. 20,
1976]
§ 27.1413
Safety belts.
Each safety belt must be equipped
with a metal to metal latching device.
(Secs. 313, 314, and 601 through 610 of the Fed-
eral Aviation Act of 1958 (49 U.S.C. 1354, 1355,
and 1421 through 1430) and sec. 6(c), Dept. of
Transportation Act (49 U.S.C. 1655(c)))
[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27–15, 43 FR 46233, Oct. 5,
1978; Amdt. 27–21, 49 FR 44435, Nov. 6, 1984]
§ 27.1415
Ditching equipment.
(a) Emergency flotation and sig-
naling equipment required by any oper-
ating rule in this chapter must meet
the requirements of this section.
(b) Each raft and each life preserver
must be approved and must be installed
so that it is readily available to the
crew and passengers. The storage pro-
visions for life preservers must accom-
modate one life preserver for each oc-
cupant for which certification for
ditching is requested.
(c) Each raft released automatically
or by the pilot must be attached to the
rotorcraft by a line to keep it alongside
the rotorcraft. This line must be weak
enough to break before submerging the
empty raft to which it is attached.
(d) Each signaling device must be
free from hazard in its operation and
must be installed in an accessible loca-
tion.
[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27–11, 41 FR 55470, Dec. 20,
1976]
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