Code of Federal Regulations - Title 14

815

Federal Aviation Administration, DOT

§ 29.1419

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.

(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]

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