668
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.
(c) Other vacuum air system compo-
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
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§ 29.1457
recorded as the output signal from the
communications unit that translates
the signal into usable data.
(b) The recording requirements of
paragraph (a)(2) of this section may be
met—
(1) By installing a cockpit-mounted
area microphone, located in the best
position for recording voice commu-
nications originating at the first and
second pilot stations and voice commu-
nications of other crewmembers on the
flight deck when directed to those sta-
tions; or
(2) By installing a continually ener-
gized or voice-actuated lip microphone
at the first and second pilot stations.
The microphone specified in this para-
graph must be so located and, if nec-
essary, the preamplifiers and filters of
the recorder must be so adjusted or
supplemented, that the recorded com-
munications are intelligible when re-
corded under flight cockpit noise con-
ditions and played back. The level of
intelligibility must be approved by the
Administrator. Repeated aural or vis-
ual playback of the record may be used
in evaluating intelligibility.
(c) Each cockpit voice recorder must
be installed so that the part of the
communication or audio signals speci-
fied in paragraph (a) of this section ob-
tained from each of the following
sources is recorded on a separate chan-
nel:
(1) For the first channel, from each
microphone, headset, or speaker used
at the first pilot station.
(2) For the second channel, from each
microphone, headset, or speaker used
at the second pilot station.
(3) For the third channel, from the
cockpit-mounted area microphone, or
the continually energized or voice-ac-
tuated lip microphones at the first and
second pilot stations.
(4) For the fourth channel, from—
(i) Each microphone, headset, or
speaker used at the stations for the
third and fourth crewmembers; or
(ii) If the stations specified in para-
graph (c)(4)(i) of this section are not re-
quired or if the signal at such a station
is picked up by another channel, each
microphone on the flight deck that is
used with the passenger loudspeaker
system if its signals are not picked up
by another channel.
(iii) Each microphone on the flight
deck that is used with the rotorcraft’s
loudspeaker system if its signals are
not picked up by another channel.
(d) Each cockpit voice recorder must
be installed so that—
(1)(i) It receives its electrical power
from the bus that provides the max-
imum reliability for operation of the
cockpit voice recorder without jeopard-
izing service to essential or emergency
loads.
(ii) It remains powered for as long as
possible without jeopardizing emer-
gency operation of the rotorcraft.
(2) There is an automatic means to
simultaneously stop the recorder and
prevent each erasure feature from func-
tioning, within 10 minutes after crash
impact;
(3) There is an aural or visual means
for preflight checking of the recorder
for proper operation;
(4) Whether the cockpit voice re-
corder and digital flight data recorder
are installed in separate boxes or in a
combination unit, no single electrical
failure external to the recorder may
disable both the cockpit voice recorder
and the digital flight data recorder;
and
(5) It has an independent power
source—
(i) That provides 10
±
1 minutes of
electrical power to operate both the
cockpit voice recorder and cockpit-
mounted area microphone;
(ii) That is located as close as prac-
ticable to the cockpit voice recorder;
and
(iii) To which the cockpit voice re-
corder and cockpit-mounted area
microphone are switched automati-
cally in the event that all other power
to the cockpit voice recorder is inter-
rupted either by normal shutdown or
by any other loss of power to the elec-
trical power bus.
(e) The record container must be lo-
cated and mounted to minimize the
probability of rupture of the container
as a result of crash impact and con-
sequent heat damage to the record
from fire.
(f) If the cockpit voice recorder has a
bulk erasure device, the installation
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14 CFR Ch. I (1–1–24 Edition)
§ 29.1459
must be designed to minimize the prob-
ability of inadvertent operation and ac-
tuation of the device during crash im-
pact.
(g) Each recorder container must be
either bright orange or bright yellow.
(h) When both a cockpit voice re-
corder and a flight data recorder are
required by the operating rules, one
combination unit may be installed,
provided that all other requirements of
this section and the requirements for
flight data recorders under this part
are met.
[Amdt. 29–6, 35 FR 7293, May 9, 1970, as
amended by Amdt. 29–50, 73 FR 12564, Mar. 7,
2008; 74 FR 32800, July 9, 2009; Amdt. 29–52, 75
FR 17045, Apr. 5, 2010]
§ 29.1459
Flight data recorders.
(a) Each flight recorder required by
the operating rules of Subchapter G of
this chapter must be installed so that:
(1) It is supplied with airspeed, alti-
tude, and directional data obtained
from sources that meet the accuracy
requirements of §§ 29.1323, 29.1325, and
29.1327 of this part, as applicable;
(2) The vertical acceleration sensor is
rigidly attached, and located longitu-
dinally within the approved center of
gravity limits of the rotorcraft;
(3)(i) It receives its electrical power
from the bus that provides the max-
imum reliability for operation of the
flight data recorder without jeopard-
izing service to essential or emergency
loads.
(ii) It remains powered for as long as
possible without jeopardizing emer-
gency operation of the rotorcraft.
(4) There is an aural or visual means
for perflight checking of the recorder
for proper recording of data in the stor-
age medium;
(5) Except for recorders powered sole-
ly by the engine-drive electrical gener-
ator system, there is an automatic
means to simultaneously stop a re-
corder that has a data erasure feature
and prevent each erasure feature from
functioning, within 10 minutes after
any crash impact; and
(6) Whether the cockpit voice re-
corder and digital flight data recorder
are installed in separate boxes or in a
combination unit, no single electrical
failure external to the recorder may
disable both the cockpit voice recorder
and the digital flight data recorder.
(b) Each nonejectable recorder con-
tainer must be located and mounted so
as to minimize the probability of con-
tainer rupture resulting from crash im-
pact and subsequent damage to the
record from fire.
(c) A correlation must be established
between the flight recorder readings of
airspeed, altitude, and heading and the
corresponding readings (taking into ac-
count correction factors) of the first pi-
lot’s instruments. This correlation
must cover the airspeed range over
which the aircraft is to be operated,
the range of altitude to which the air-
craft is limited, and 360 degrees of
heading. Correlation may be estab-
lished on the ground as appropriate.
(d) Each recorder container must:
(1) Be either bright orange or bright
yellow;
(2) Have a reflective tape affixed to
its external surface to facilitate its lo-
cation under water; and
(3) Have an underwater locating de-
vice, when required by the operating
rules of this chapter, on or adjacent to
the container which is secured in such
a manner that it is not likely to be sep-
arated during crash impact.
(e) When both a cockpit voice re-
corder and a flight data recorder are
required by the operating rules, one
combination unit may be installed,
provided that all other requirements of
this section and the requirements for
cockpit voice recorders under this part
are met.
[Amdt. 29–25, 53 FR 26145, July 11, 1988; 53 FR
26144, July 11, 1988, as amended by Amdt. 29–
50, 73 FR 12564, Mar. 7, 2008; 74 FR 32800, July
9, 2009; Amdt. 29–52, 75 FR 17045, Apr. 5, 2010]
§ 29.1461
Equipment containing high
energy rotors.
(a) Equipment containing high en-
ergy rotors must meet paragraph (b),
(c), or (d) of this section.
(b) High energy rotors contained in
equipment must be able to withstand
damage caused by malfunctions, vibra-
tion, abnormal speeds, and abnormal
temperatures. In addition—
(1) Auxiliary rotor cases must be able
to contain damage caused by the fail-
ure of high energy rotor blades; and
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