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NAV 1 radio. The CDR will tune the VHF COM radio prior to applying
electrical power to the airplane. The CDR control head is normally
powered by the left essential bus through the AUDIO 1 circuit breaker;
however, it and other communication related equipment can be powered
from the right forward hot bus, prior to applying electrical power
to the aircraft.
With airplane batteries OFF, depressing the momentary action RADIO
CTL HOT BUS switch on the center pedestal applies power from the
right hot bus to the left audio control panel, CDR control panel, COM
section of the integrated communications unit, and NAV section of the
integrated navigation unit. The display on the CDR is liquid crystal
type with white letters on a black background. The push button, display,
and control identifier legend are on a black background displayed
with electroluminescent lighting.
In the emergency mode, RMU and FMS tuning capabilities are inhibited
and the COM and NAV units are tuned exclusively by the CDR. An
AUX ON caption replaces the NB or WB annunciators on the RMUs to
indicate that tuning through the RMUs is inhibited. Tuning through the
CDR is no different when EMRG is selected, but the CDR does not look
at the radio bus data to check the echoed frequency.
Pilot’s Manual
5-64 PM-126A
The CDR controls are as follows:
• Transfer Key — Alternately selects either the COM (top) or
NAV (bottom) frequency to be connected to the tuning
knobs.
•Tuning Knobs — Used to change the frequency indicated
by the tuning cursor.
•Normal/Emergency Mode Switch — This rotary knob provides
alternate selection of Normal and Emergency modes.
•NAV AUDIO On/Off Switch — This alternate action push
button switch is used to toggle NAV audio ON or OFF
when in the EMER audio mode on the audio control panel.
• Squelch (SQ) Switch — Used to toggle COM squelch on or
off.
123RMT
COM
NAV
NAV AUDIO
PRE
NAV
TX SQ
E
MR
G
F40-050000-517-01
SQ NAV
AUDIO
MODES
CLEARANCE DELIVERY RADIO
Figure 5-17
F40-050000-517-01
Pilot’s Manual
PM-126A 5-65
FLIGHT GUIDANCE CONTROL SYSTEM
The Primus 1000 system includes an autopilot, yaw damper and dual
synchronized flight directors. These are all co-located in two IC-600 display
flight guidance computers located in the nose avionics bay. Each
IC-600 houses a flight director; however, only the copilot IC-600 is connected
to the pitch, roll and yaw servos for the autopilot/yaw damper
and rudder boost functions. A flight guidance controller, located in the
center of the glareshield, provides the means of engaging the autopilot/
yaw damper and controlling both Flight Director (FD) systems. It
also contains a transfer (XFR) switch that allows the crew to select either
the left or right flight director as master and for autopilot coupling.
The autopilot is a single channel with a fail passive design. The monitor
system provides for automatic disconnect in the event of a malfunction
in autopilot, yaw damper, or rudder boost. All automatic disconnects,
which result from monitor trips, will be stored in a non-volatile memory
for later recall by technicians.
FLIGHT DIRECTOR
The flight director system, utilizing two separate IC-600 computers,
provides dual flight director computations, either of which can be coupled
to the autopilot. Only one flight director can be coupled to the autopilot
at a time. In this case the coupled flight director is classified as
the master flight director, and the other flight director is classified as the
slave flight director. The flight director can couple to Short Range Navigation
(SRN) units (e.g. VOR, ILS), dependent upon which SRN is being
displayed as a NAV data source on the Primary Flight Display
(PFD). The flight director will use the displayed SRN data on the associated
PFD for command-bar control computations. The flight director
can be coupled to optional Long-Range Navigation (LRN) units (e.g.
flight management system) if it is installed and selected as the NAV
data source and displayed on the associated PFD. The flight director
utilizes the lateral and/or vertical steering commands from the LRN in
the command control computations. Each flight director uses the displayed
on-side Air Data Computer (ADC) data for all vertical modes
and gain programing. The flight director modes are synchronized in a
manner that allows selection of the modes to be accomplished by the
single set of FD mode select buttons on the flight guidance controller
　
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