557
Federal Aviation Administration, DOT
§ 27.1457
§ 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
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
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 po-
sition for recording voice communica-
tions originating at the first and sec-
ond pilot stations and voice commu-
nications of other crewmembers on the
flight deck when directed to those sta-
tions; or
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14 CFR Ch. I (1–1–24 Edition)
§ 27.1457
(2) By installing a continually ener-
gized or voice-actuated lip microphone
at the first and second pilot stations.
The microphone specified in this
paragraph must be so located and, if
necessary, the preamplifiers and filters
of the recorder must be adjusted or
supplemented so that the recorded
communications are intelligible when
recorded under flight cockpit noise
conditions and played back. The level
of intelligibility must be approved by
the Administrator. Repeated aural or
visual 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 microphone 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
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
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Federal Aviation Administration, DOT
§ 27.1461
flight data recorders under this part
are met.
[Amdt. 27–22, 53 FR 26144, July 11, 1988, as
amended by Amdt. 27–43, 73 FR 12563, Mar. 7,
2008; 74 FR 32800, July 9, 2009; Amdt. 27–45, 75
FR 17045, Apr. 5, 2010]
§ 27.1459
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 §§ 27.1323, 27.1325, and
27.1327 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 preflight checking of the recorder
for proper recording of data in the stor-
age medium;
(5) Except for recorders powered sole-
ly by the engine-driven electrical gen-
erator 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 they are not likely to be
separated 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. 27–22, 53 FR 26144, July 11, 1988, as
amended by Amdt. 27–43, 73 FR 12564, Mar. 7,
2008; 74 FR 32800, July 9, 2009; Amdt. 27–45, 75
FR 17045, Apr. 5, 2010]
§ 27.1461
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
(2) Equipment control devices, sys-
tems, and instrumentation must rea-
sonably ensure that no operating limi-
tations affecting the integrity of high
energy rotors will be exceeded in serv-
ice.
(c) It must be shown by test that
equipment containing high energy ro-
tors can contain any failure of a high
energy rotor that occurs at the highest
speed obtainable with the normal speed
control devices inoperative.
(d) Equipment containing high en-
ergy rotors must be located where
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