CAE SimuFlite Citation Bravo, Pilot Training Manual

Page: 413 / 718

Avionics
Citation Bravo
Developed for Training Purposes
5B-39
September 2005
The NAV computer also computes fuel
flow information, providing current
fuel status and aircraft gross weight
throughout the flight if fuel and gross
weight are updated prior to takeoff.
The system provides best computed
position from the scanning DME and
long-range navigation sensors. This
position is used for navigating along
the programmed flight plan and dur-
ing approved instrument approach
procedures.
The UNS-1Csp provides advisory
VNAV information for up to nine
waypoints on the flight plan. Vertical
guidance appears on the PFDs.
The UNS-1Csp database incorporates
Standard Instrument Departures
(SIDs), Standard Terminal Arrival
Routes (STARs), and approaches
including GPS approaches. These pro-
cedures may be flown coupled to the
autopilot or flight director.
If one DME is inoperative and both
NAVs are tuned to the ILS frequency
during approach, the VPU may go
into DR.
This does not affect the accuracy of
other Universal UNS-1Csp sensors.
This situation should not occur unless
the remaining operational DME rov-
ing channel is unable to receive at
least two valid DME signals.
n
it is not the only sensor selected
for use
n
it is receiving four or more satel-
lites, the Geometric Dilution of
Position (GDOP) is six or less,
and the sensor is not using altitude
n
the system is receiving three or
more satellites and the GDOP,
using altitude, is 10 or less.
Manually entered altitude may be
used only after failure of the auto-
matic inputs and must be updated
every five minutes.
Consult the Universal UNS-1Csp or
UNS-1Esp Pilot’s Operating Man-
ual, Universal Systems report num-
ber 2423sv603.X (latest revision),
for detailed operating information.
Digital Flight Recorder
(Optional)
The optional Flight Data Recorder (FDR)
records information digitally by a solid-
state method and far exceeds the mini-
mum requirements for the number of
parameters (at least 16 parameters of con-
tinuously recorded aircraft and systems
operation) and recording time (at least
eight hours of continuous recording).
The FDR system consists of a solid-
state FDR, a G-switch, and a remotely
mounted accelerometer. The FDR inter-
faces with the flight guidance system to
obtain system and flight data informa-
tion. The accelerometer provides infor-
mation directly to the FDR. The G-
switch is a power interrupt switch that
removes power from the FDR to pre-
vent recording over data during a mis-
hap, if the recorder still has power
available.
The system also contains an automatic
delayed shutdown feature that disables
the recording function after a period of
eight to ten minutes upon the loss of oil
pressure in the engines. To restart flight
data recording and reset the shutdown
timer, electrical power must be recycled.
Recorder operation begins upon pow-
erup and continues until electrical
power shuts off. Recorder operation
requires no attention from crew mem-
bers. Continuous internal checking on
the transcribed data is accomplished by
the installation to ascertain that correct
data is being recorded. An amber
FLT
DATA RCDR FAIL light on the
annunciator panel illuminates if the
FDR malfunctions or power to the sys-
tem fails.