555
Federal Aviation Administration, DOT
§ 27.1401
Dihedral angle (light in-
cluded)
Angle from right or left
of longitudinal axis,
measured from dead
ahead
Intensity
(candles)
L and R (forward red
and green).
10
°
to 10
°
...................
10
°
to 20
°
...................
20
°
to 110
°
.................
40
30
5
A (rear white) ..............
110
°
to 180
°
...............
20
§ 27.1393
Minimum intensities in any
vertical plane of forward and rear
position lights.
Each position light intensity must
equal or exceed the applicable values in
the following table:
Angle above or below the horizontal plane
Intensity, l
0
°
.........................................................................
1.00
0
°
to 5
°
................................................................
0.90
5
°
to 10
°
..............................................................
0.80
10
°
to 15
°
............................................................
0.70
15
°
to 20
°
............................................................
0.50
20
°
to 30
°
............................................................
0.30
30
°
to 40
°
............................................................
0.10
40
°
to 90
°
............................................................
0.05
§ 27.1395
Maximum intensities in over-
lapping beams of forward and rear
position lights.
No position light intensity may ex-
ceed the applicable values in the fol-
lowing table, except as provided in
§ 27.1389(b)(3).
Overlaps
Maximum Intensity
Area A
(candles)
Area B
(candles)
Green in dihedral angle L .............
10 1
Red in dihedral angle R ................
10 1
Green in dihedral angle A .............
5 1
Red in dihedral angle A ................
5 1
Rear white in dihedral angle L ......
5 1
Rear white in dihedral angle R .....
5 1
Where—
(a) Area A includes all directions in
the adjacent dihedral angle that pass
through the light source and intersect
the common boundary plane at more
than 10 degrees but less than 20 de-
grees, and
(b) Area B includes all directions in
the adjacent dihedral angle that pass
through the light source and intersect
the common boundary plane at more
than 20 degrees.
§ 27.1397
Color specifications.
Each position light color must have
the applicable International Commis-
sion on Illumination chromaticity co-
ordinates as follows:
(a)
Aviation red—
y is not greater than 0.335; and
z is not greater than 0.002.
(b)
Aviation green—
x is not greater than 0.440
¥
0.320
y;
x is not greater than y
¥
0.170; and
y is not less than 0.390
¥
0.170
x.
(c)
Aviation white—
x is not less than 0.300 and not greater than
0.540;
y is not less than x
¥
0.040’’ or
y
c
¥
0.010,
whichever is the smaller; and
y is not greater than x + 0.020 nor
0.636
¥
0.400
x;
Where
y
c
is the
y coordinate of the Planck-
ian radiator for the value of
x considered.
[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27–6, 36 FR 12972, July 10,
1971]
§ 27.1399
Riding light.
(a) Each riding light required for
water operation must be installed so
that it can—
(1) Show a white light for at least
two nautical miles at night under clear
atmospheric conditions; and
(2) Show a maximum practicable un-
broken light with the rotorcraft on the
water.
(b) Externally hung lights may be
used.
[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27–2, 33 FR 964, Jan. 26,
1968]
§ 27.1401
Anticollision light system.
(a)
General. If certification for night
operation is requested, the rotorcraft
must have an anticollision light sys-
tem that—
(1) Consists of one or more approved
anticollision lights located so that
their emitted light will not impair the
crew’s vision or detract from the con-
spicuity of the position lights; and
(2) Meets the requirements of para-
graphs (b) through (f) of this section.
(b)
Field of coverage. The system must
consist of enough lights to illuminate
the vital areas around the rotorcraft,
considering the physical configuration
and flight characteristics of the rotor-
craft. The field of coverage must ex-
tend in each direction within at least
30 degrees below the horizontal plane of
the rotorcraft, except that there may
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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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