666
14 CFR Ch. I (1–1–24 Edition)
§ 29.1411
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 above and 30 degrees below
the horizontal plane of the rotorcraft,
except that there may 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 § 29.1397.
(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
l
= 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. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–7, 36 FR 12972, July 10,
1971; Amdt. 29–11, 41 FR 5290, Feb. 5, 1976]
S
AFETY
E
QUIPMENT
§ 29.1411
General.
(a)
Accessibility.
Required safety
equipment to be used by the crew in an
emergency, such as automatic liferaft
releases, must be readily accessible.
(b)
Stowage provisions. Stowage provi-
sions for required emergency equip-
ment 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 inadvertent damage.
(c)
Emergency exit descent device. The
stowage provisions for the emergency
exit descent device required by
§ 29.809(f) must be at the exits for which
they are intended.
(d)
Liferafts. Liferafts must be stowed
near exits through which the rafts can
be launched during an unplanned ditch-
ing. Rafts automatically or remotely
released outside the rotorcraft must be
attached to the rotorcraft by the static
line prescribed in § 29.1415.
(e)
Long-range signaling device. The
stowage provisions for the long-range
signaling device required by § 29.1415
must be near an exit available during
an unplanned ditching.
(f)
Life preservers. Each life preserver
must be within easy reach of each oc-
cupant while seated.
§ 29.1413
Safety belts: passenger warn-
ing device.
(a) If there are means to indicate to
the passengers when safety belts
should be fastened, they must be in-
stalled to be operated from either pilot
seat.
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