CS 25.1459 Flight data recorders
(See AMC 25.1459)
(a) Each flight data recorder required by the operating
rules must be approved and must be installed so that –
(1) It is supplied with airspeed, altitude,
and directional data obtained from sources that meet the accuracy requirements
of CS 25.1323, 25.1325 and 25.1327, as appropriate;
(2) The vertical acceleration sensor is
rigidly attached, and located longitudinally either within the approved centre
of gravity limits of the aeroplane, or at a distance forward or aft of these
limits that does not exceed 25% of the aeroplanes mean aerodynamic chord;
(3) (i) It
receives its electrical power from the bus that provides the maximum reliability
for operation of the recorder without jeopardising service to essential or
emergency loads; and
(ii) It remains powered for as long as possible
without jeopardising the emergency operation of the aeroplane;
(4) There is an aural or visual means for
pre-flight checking of the recorder for proper recording of data in the
storage medium;
(5) If the recorder has a recording duration
of less than 25 hours, there is an automatic means to stop the recording
within 10 minutes after crash impact. This requirement does not apply to
recorders that are powered solely by the engine-driven electrical generator
system;
(6) There is a means to record data from which
the time of each radio transmission either to or from ATC can be determined;
(7) If another recorder is installed to
perform the cockpit voice recorder function, any single electrical failure
that is external to the recorder dedicated to the flight data recorder
function does not disable both the recorders; and
(8) If the recorder is deployable, it complies
with CS 25.1457(d)(7).
(b) If the recorder is not deployable, the
container of the recording medium must be located and mounted so as to
minimise the probability of the container rupturing, the recording medium
being destroyed, or the underwater locating device failing as a result of any
possible combinations of:
(1) impact with the Earth’s surface;
(2) the heat damage caused by a post-impact
fire; and
(3) immersion in water.
If the
recorder is deployable, the deployed part must be designed and installed so as
to minimise the probability of the recording medium being destroyed or the
emergency locator transmitter failing to transmit (after damage or immersion
in water) as a result of any possible combinations of:
(1) the deployment of the recorder;
(2) impact with the Earth’s surface;
(3) the heat damage caused by a post-impact
fire; and
(4) immersion in water.
(c) A correlation must be established between
the flight data recorder readings of airspeed, altitude, and heading and the
corresponding readings (taking into account correction factors) of the first
pilot’s instruments. The correlation must cover the airspeed range over which
the aeroplane is to be operated, the range of altitude to which the aeroplane
is limited, and 360° of heading. Correlation may be established on the ground
as appropriate.
(d) The container of the flight data recorder
must comply with the specifications in CS 25.1457(g) that are applicable to
the container of the cockpit voice recorder.
(e) Any novel or unique design or operational
characteristics of the aeroplane must be evaluated to determine if any
dedicated parameters must be recorded on the flight data recorder in addition
to, or in place of, the parameters that are required by the existing
requirements.
[Amdt
25/11]
[Amdt
25/18]
[Amdt
25/23]
Loading collections...