spaschal on DSK3GDR082PROD with CFR

Section 29.1461

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

(3)(i) It receives its electrical power
from the bus that provides the maximum reliability for operation of the
flight data recorder without jeopardizing service to essential or emergency
loads.
(ii) It remains powered for as long as
possible without jeopardizing emergency 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 storage medium;
(5) Except for recorders powered solely by the engine-drive electrical generator system, there is an automatic
means to simultaneously stop a recorder 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 recorder 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 container must be located and mounted so
as to minimize the probability of container rupture resulting from crash impact 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 account correction factors) of the first pilot-s instruments. This correlation
must cover the airspeed range over
which the aircraft is to be operated,
the range of altitude to which the aircraft is limited, and 360 degrees of
heading. Correlation may be established 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 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
a manner that it is not likely to be separated during crash impact.

(e) When both a cockpit voice recorder 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]

Section 29.1461 Equipment containing high
energy rotors.
(a) Equipment containing high energy 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, vibration, abnormal speeds, and abnormal
temperatures. In addition - 
(1) Auxiliary rotor cases must be able
to contain damage caused by the failure of high energy rotor blades; and
(2) Equipment control devices, systems, and instrumentation must reasonably ensure that no operating limitations affecting the integrity of high
energy rotors will be exceeded in service.
(c) It must be shown by test that
equipment containing high energy rotors 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 energy rotors must be located where
rotor failure will neither endanger the
occupants nor adversely affect continued safe flight.
[Amdt. 29-3, 33 FR 971, Jan. 26, 1968]

Subpart G - Operating Limitations
and Information
Section 29.1501

General.

(a) Each operating limitation specified in SectionSection 29.1503 through 29.1525 and
other limitations and information necessary for safe operation must be established.
(b) The operating limitations and
other information necessary for safe
operation must be made available to

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