556 

14 CFR Ch. I (1–1–19 Edition) 

§ 27.1413 

§ 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] 

§ 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 per-
formed to establish, on the basis of the 
rotorcraft’s operational needs, the ade-
quacy of the ice protection system for 
the various components of the rotor-
craft. 

(c) In addition to the analysis and 

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 indentified 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. 27–19, 48 FR 4389, Jan. 31, 1983] 

§ 27.1435

Hydraulic systems. 

(a) 

Design. 

Each hydraulic system 

and its elements must withstand, with-
out yielding, any structural loads ex-
pected in addition to hydraulic loads. 

(b) 

Tests. 

Each system must be sub-

stantiated by proof pressure tests. 
When proof tested, no part of any sys-
tem may fail, malfunction, or experi-
ence 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 accu-

mulator or pressurized reservoir may 
be installed on the engine side of any 
firewall unless it is an integral part of 
an engine. 

§ 27.1457

Cockpit voice recorders. 

(a) Each cockpit voice recorder re-

quired by the operating rules of this 
chapter must be approved, and must be 

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