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radar can also be used for ground mapping. The WU-650 is an integrated
unit which incorporates the receiver, transmitter and antenna (RTA)
into a single unit, located in the nose of the aircraft. The only remaining
radar component is the cockpit control panel which is mounted on the
center pedestal. The antenna is a 12-inch flat plate that is stabilized with
inputs from the #1 AHRS. Weather patterns can be displayed on both
PFDs, on the ARC or MAP format, and on the MFD MAP format. The
radar generates high-level RF pulses and should be operated with caution
while on the ground. When operating on the ground, position the
nose of the airplane so that the antenna scan sector is free of large metallic
objects such as hangers or other aircraft for a distance of at least
100 feet.
The weather radar is controlled from the WC-650 weather radar controller,
Figure 5-20. WX is selected for display on the PFDs by selecting
the WX button on the display controller, the HSI automatically switches
to the ARC mode. WX is selected for display on the MFD MAP by depressing
the WX bezel button on the MFD main menu.
A six-position rotary switch is provided on the radar control panel for
selecting the different radar modes. They are:
• OFF — removes electrical power from the system.
• SBY (standby) — in this position the RTA is powered up but
does not radiate any RF energy nor does the antenna scan.
+
-
STAB TGT SECT
OFF
0 15
TILT
RCT
GMAP
GAIN
FP
TST
WX
SBY
OFF
RADAR SLV
PULL
VAR
MIN MAX
WU-650 WEATHER RADAR CONTROL PANEL
Figure 5-20
Pilot’s Manual
5-78 PM-126A
• WX (weather) — selects the weather radar main operating
mode.
• GMAP (ground map) — in the ground mapping mode, the
system internal parameters are set to enhance returns from
ground targets.
• FP (flight plan) — selecting this position places the radar in the
flight plan mode.
• TST (test) — when this mode is selected the weather depiction
will be a special colored test pattern to allow verification of system
operation.
Power is provided to the RTA and cockpit controller from the right avionics
main bus with a 7.5-amp circuit breaker located in the INSTRUMENT/
INDICATIONS group of the copilot’s circuit breaker panel.
AVIONICS COOLING
INSTRUMENT PANEL COOLING
The instrument panel cooling system is located forward of the throttle
quadrant and is provided to draw flight deck ambient air through the
instrument panel and thus prevent overheating of avionics displays
and instruments. The system consists of an avionics cooling fan, an on/
off thermostat switch and an overtemperature thermostat circuit. The
avionics cooling fan is activated when the temperature sensing switch
reaches 90° F (32° C). The fan automatically turns off when the temperature
has been reduced below 70° F (21° C). If the temperature reaches
an extreme of 135° F (57° C) the overtemperature circuit is energized
and an annunciation is posted on the CAS. The CAS remains displayed
until the temperature has been reduced to 125° F (51.7° C).
The following CAS illumination is specific to the avionics cooling
system:
The instrument panel cooling system is powered from the L MAIN bus
and protected by the INSTR FAN 3-amp circuit breaker located on the
pilot’s circuit breaker panel (ENVIRONMENTAL group).
CAS Color Description
INSTR PNL TEMP White The temperature at the instrument panel is
higher than normal.
Pilot’s Manual
PM-126A 5-79
MISCELLANEOUS
COCKPIT VOICE RECORDER (CVR)
A solid state Cockpit Voice Recorder (CVR) is installed in the Learjet 45.
The standard CVR is a three-channel unit providing 30 minutes of recording.
An optional unit is available which provides 120 minutes of
recording. Two of the channels are used to record pilot and copilot
audio. The third channel is used for the area microphone. Located in
the tailcone, the CVR is painted international orange with reflective
tape added to aid in recovery following a mishap. It also has an underwater
locator beacon installed on one end of the unit. The recording is
converted to a digital format and stored in crash protected memory.
The area microphone is located in the upper center area of the instrument
panel. An erase button and headphone jack are located on the
CVR panel just beneath the copilot audio control panel. The CVR performs
a self-test at power-up and has a continuous self monitor. If a
fault is detected at any time, an annunciation is posted on CAS.
　
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