spaschal on DSK3GDR082PROD with CFR

Section 23.1459

14 CFR Ch. I (1-1-19 Edition)

listed in paragraphs (c)(1), (2), and (4) of
this section must be recorded without
interruption irrespective of the position of the interphone-transmitter key
switch. The design shall ensure that
sidetone for the flightcrew is produced
only when the interphone, public address system, or radio transmitters are
in use.
(d) Each cockpit voice recorder must
be installed so that:
(1)(i) It receives its electrical power
from the bus that provides the maximum reliability for operation of the
cockpit voice recorder without jeopardizing service to essential or emergency
loads.
(ii) It remains powered for as long as
possible without jeopardizing emergency operation of the airplane.
(2) There is an automatic means to
simultaneously stop the recorder and
prevent each erasure feature from functioning, within 10 minutes after crash
impact.
(3) There is an aural or visual means
for preflight checking of the recorder
for proper operation.
(4) Any single electrical failure external to the recorder does not disable
both the cockpit voice recorder and the
flight data recorder.
(5) It has an independent power
source - 
(i) That provides 10 Section1 minutes of
electrical power to operate both the
cockpit voice recorder and cockpitmounted area microphone;
(ii) That is located as close as practicable to the cockpit voice recorder;
and
(iii) To which the cockpit voice recorder and cockpit-mounted area
microphone are switched automatically in the event that all other power
to the cockpit voice recorder is interrupted either by normal shutdown or
by any other loss of power to the electrical power bus.
(6) It is in a separate container from
the flight data recorder when both are
required. If used to comply with only
the cockpit voice recorder requirements, a combination unit may be installed.
(e) The recorder container must be
located and mounted to minimize the
probability of rupture of the container
as a result of crash impact and con-

sequent heat damage to the recorder
from fire.
(1) Except as provided in paragraph
(e)(2) of this section, the recorder container must be located as far aft as
practicable, but need not be outside of
the pressurized compartment, and may
not be located where aft-mounted engines may crush the container during
impact.
(2) If two separate combination digital flight data recorder and cockpit
voice recorder units are installed instead of one cockpit voice recorder and
one digital flight data recorder, the
combination unit that is installed to
comply with the cockpit voice recorder
requirements may be located near the
cockpit.
(f) If the cockpit voice recorder has a
bulk erasure device, the installation
must be designed to minimize the probability of inadvertent operation and actuation of the device during crash impact.
(g) Each recorder container must - 
(1) Be either bright orange or bright
yellow;
(2) Have reflective tape affixed to its
external surface to facilitate its location under water; and
(3) Have an underwater locating device, when required by the operating
rules of this chapter, on or adjacent to
the container, which is secured in such
manner that they are not likely to be
separated during crash impact.
Section 23.1459

Flight data recorders.

(a) Each flight recorder required by
the operating rules of this chapter
must be installed so that - 
(1) It is supplied with airspeed, altitude, and directional data obtained
from sources that meet the aircraft
level system requirements and the
functionality specified in Section 23.2500;
(2) The vertical acceleration sensor is
rigidly attached, and located longitudinally either within the approved center of gravity limits of the airplane, or
at a distance forward or aft of these
limits that does not exceed 25 percent
of the airplane-s mean aerodynamic
chord;
(3)(i) It receives its electrical power
from the bus that provides the maximum reliability for operation of the

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