Section 27.1413

14 CFR Ch. I (1-1-19 Edition)

Section 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 Federal 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]

Section 27.1415 Ditching equipment.
(a) Emergency flotation and signaling equipment required by any operating 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 provisions for life preservers must accommodate one life preserver for each occupant 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 location.

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[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27-11, 41 FR 55470, Dec. 20,
1976]

Section 27.1419 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 Part 29 of this
chapter within the rotorcraft altitude
envelope. An analysis must be performed to establish, on the basis of the
rotorcraft-s operational needs, the adequacy of the ice protection system for
the various components of the rotorcraft.
(c) In addition to the analysis and
physical evaluation prescribed in paragraph (b) of this section, the effectiveness of the ice protection system and

its components must be shown by
flight tests of the rotorcraft or its components in measured natural atmospheric 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 components.
(2) Flight dry air tests of the ice protection system as a whole, or its individual 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 applicable primarily to the airframe. Powerplant installation requirements are
contained in Subpart E of this part.
(e) A means must be indentified or
provided for determining the formation
of ice on critical parts of the rotorcraft. 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 formation and must contain information necessary for safe operation of the rotorcraft in icing conditions.
[Amdt. 27-19, 48 FR 4389, Jan. 31, 1983]

Section 27.1435

Hydraulic systems.

(a) Design. Each hydraulic system
and its elements must withstand, without yielding, any structural loads expected in addition to hydraulic loads.
(b) Tests. Each system must be substantiated by proof pressure tests.
When proof tested, no part of any system may fail, malfunction, or experience a permanent set. The proof load of
each system must be at least 1.5 times
the maximum operating pressure of
that system.
(c) Accumulators. No hydraulic accumulator or pressurized reservoir may
be installed on the engine side of any
firewall unless it is an integral part of
an engine.
Section 27.1457

Cockpit voice recorders.

(a) Each cockpit voice recorder required by the operating rules of this
chapter must be approved, and must be

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