title-14-part-29-sec29-1413

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 t dt

−

∫

( )

(

)

0 2

where:

= effective intensity (candles).

I(t) = instantaneous intensity as a function

of time.

= flash time interval (seconds).

Normally, the maximum value of effective
intensity is obtained when

and

are cho-

sen so that the effective intensity is equal to
the instantaneous intensity at

and

(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)

to 5

................................................................

150

to 10

..............................................................

to 20

............................................................

to 30

............................................................

[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]

AFETY

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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667

Federal Aviation Administration, DOT

§ 29.1433

(b) 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. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–16 43 FR 46233, Oct. 5,
1978]

§ 29.1415

Ditching equipment.

(a) Emergency flotation and sig-

naling equipment required by any oper-
ating rule of this chapter must meet
the requirements of this section.

(b) Each liferaft and each life pre-

server must be approved. In addition—

(1) Provide not less than two rafts, of

an approximately equal rated capacity
and buoyancy to accommodate the oc-
cupants of the rotorcraft; and

(2) Each raft must have a trailing

line, and must have a static line de-
signed to hold the raft near the rotor-
craft but to release it if the rotorcraft
becomes totally submerged.

must be attached to each liferaft.

(d) There must be an approved sur-

vival type emergency locator trans-
mitter for use in one life raft.

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–8, 36 FR 18722, Sept. 21,
1971; Amdt. 29–19, 45 FR 38348, June 9, 1980;
Amdt. 27–26, 55 FR 8005, Mar. 6, 1990; Amdt.
29–33, 59 FR 32057, June 21, 1994]

§ 29.1419

Ice protection.

(a) To obtain certification for flight

into icing conditions, compliance with
this section must be shown.

(b) It must be demonstrated that the

rotorcraft can be safely operated in the
continuous maximum and intermittent
maximum icing conditions determined
under appendix C of this part within
the rotorcraft altitude envelope. An
analysis must be performed to estab-
lish, on the basis of the rotorcraft’s
operational needs, the adequacy of the
ice protection system for the various
components of the rotorcraft.

physical evaluation prescribed in para-
graph (b) of this section, the effective-
ness of the ice protection system and
its components must be shown by
flight tests of the rotorcraft or its com-
ponents in measured natural atmos-

pheric icing conditions and by one or
more of the following tests as found
necessary to determine the adequacy of
the ice protection system:

(1) Laboratory dry air or simulated

icing tests, or a combination of both, of
the components or models of the com-
ponents.

(2) Flight dry air tests of the ice pro-

tection system as a whole, or its indi-
vidual components.

(3) Flight tests of the rotorcraft or

its components in measured simulated
icing conditions.

(d) The ice protection provisions of

this section are considered to be appli-
cable primarily to the airframe. Power-
plant installation requirements are
contained in Subpart E of this part.

(e) A means must be identified or

provided for determining the formation
of ice on critical parts of the rotor-
craft. Unless otherwise restricted, the
means must be available for nighttime
as well as daytime operation. The
rotorcraft flight manual must describe
the means of determining ice forma-
tion and must contain information nec-
essary for safe operation of the rotor-
craft in icing conditions.

[Amdt. 29–21, 48 FR 4391, Jan. 31, 1983]

ISCELLANEOUS

QUIPMENT

§ 29.1431

Electronic equipment.

(a) Radio communication and naviga-

tion equipment installations must be
free from hazards in themselves, in
their method of operation, and in their
effects on other components, under any
critical environmental conditions.

(b) Radio communication and naviga-

tion equipment, controls, and wiring
must be installed so that operation of
any one unit or system of units will
not adversely affect the simultaneous
operation of any other radio or elec-
tronic unit, or system of units, re-
quired by this chapter.

§ 29.1433

Vacuum systems.

(a) There must be means, in addition

to the normal pressure relief, to auto-
matically relieve the pressure in the
discharge lines from the vacuum air
pump when the delivery temperature of
the air becomes unsafe.

(b) Each vacuum air system line and

fitting on the discharge side of the