title-14-part-29-sec29-1433

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

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14 CFR Ch. I (1–1–24 Edition)

§ 29.1435

pump that might contain flammable
vapors or fluids must meet the require-
ments of § 29.1183 if they are in a des-
ignated fire zone.

nents in designated fire zones must be
at least fire resistant.

§ 29.1435

Hydraulic systems.

(a)

Design. Each hydraulic system

must be designed as follows:

(1) Each element of the hydraulic

system must be designed to withstand,
without detrimental, permanent defor-
mation, any structural loads that may
be imposed simultaneously with the
maximum operating hydraulic loads.

(2) Each element of the hydraulic

system must be designed to withstand
pressures sufficiently greater than
those prescribed in paragraph (b) of
this section to show that the system
will not rupture under service condi-
tions.

(3) There must be means to indicate

the pressure in each main hydraulic
power system.

(4) There must be means to ensure

that no pressure in any part of the sys-
tem will exceed a safe limit above the
maximum operating pressure of the
system, and to prevent excessive pres-
sures resulting from any fluid volu-
metric change in lines likely to remain
closed long enough for such a change to
take place. The possibility of detri-
mental transient (surge) pressures dur-
ing operation must be considered.

(5) Each hydraulic line, fitting, and

component must be installed and sup-
ported to prevent excessive vibration
and to withstand inertia loads. Each
element of the installation must be
protected from abrasion, corrosion, and
mechanical damage.

(6) Means for providing flexibility

must be used to connect points, in a
hydraulic fluid line, between which rel-
ative motion or differential vibration
exists.

(b)

Tests. Each element of the system

must be tested to a proof pressure of 1.5
times the maximum pressure to which
that element will be subjected in nor-
mal operation, without failure, mal-
function, or detrimental deformation
of any part of the system.

(c)

Fire protection. Each hydraulic

system using flammable hydraulic

fluid must meet the applicable require-
ments of §§ 29.861, 29.1183, 29.1185, and
29.1189.

§ 29.1439

Protective breathing equip-

ment.

(a) If one or more cargo or baggage

compartments are to be accessible in
flight, protective breathing equipment
must be available for an appropriate
crewmember.

(b) For protective breathing equip-

ment required by paragraph (a) of this
section or by any operating rule of this
chapter—

(1) That equipment must be designed

to protect the crew from smoke, carbon
dioxide, and other harmful gases while
on flight deck duty;

(2) That equipment must include—
(i) Masks covering the eyes, nose, and

mouth; or

(ii) Masks covering the nose and

mouth, plus accessory equipment to
protect the eyes; and

(3) That equipment must supply pro-

tective oxygen of 10 minutes duration
per crewmember at a pressure altitude
of 8,000 feet with a respiratory minute
volume of 30 liters per minute BTPD.

§ 29.1457

Cockpit voice recorders.

(a) Each cockpit voice recorder re-

quired by the operating rules of this
chapter must be approved, and must be
installed so that it will record the fol-
lowing:

(1) Voice communications trans-

mitted from or received in the rotor-
craft by radio.

(2) Voice communications of flight

crewmembers on the flight deck.

(3) Voice communications of flight

crewmembers on the flight deck, using
the rotorcraft’s interphone system.

(4) Voice or audio signals identifying

navigation or approach aids introduced
into a headset or speaker.

(5) Voice communications of flight

crewmembers using the passenger loud-
speaker system, if there is such a sys-
tem, and if the fourth channel is avail-
able in accordance with the require-
ments of paragraph (c)(4)(ii) of this sec-
tion.

(6) If datalink communication equip-

ment is installed, all datalink commu-
nications, using an approved data mes-
sage set. Datalink messages must be