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. 

(c) Approved survival equipment 

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. 

(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 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] 

M

ISCELLANEOUS

E

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 

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