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will be provided on both PFDs, and the green bar on the YD
push button will illuminate. Manual disengagement of the yaw damper
via the YD button will cause the YD annunciation to flash amber then
be removed from both PFDs and the green bar on the YD push button
will extinguish. In the case of a monitored disconnect, the YD annunciation
will turn amber and flash for five seconds and then remain steady.
Other actions that will disengage yaw damper include:
(1) Control wheel master switch activation.
(2) YD Switch on the FGC disengaged.
(3) Yaw damper monitor trip.
Mistrim Annunciation
When the autopilot is engaged and the roll or pitch servo remains energized
for a longer than normal period, this condition will be annunciated
with a CAS. The autopilot does not have a capability to trim in
the roll axis; therefore, if there is a mistrim in the roll axis, this will also
display a CAS.
The following CAS illuminations are specific to the autopilot:
Power Supply Configuration
The power supply for all the AFCS servos is supplied from the L MAIN
bus, and is routed through the #2 IC-600 to the servos. The system is designed
so that power failure to any major component in the system will
result in the system reverting to the safe, disconnect mode. The AFCS
SERVOS circuit breaker is located in the FLIGHT group of the pilot’s
circuit breaker panel.
CAS Color Description
AP AIL MISTRIM Amber Autopilot is engaged and autopilot aileron
servo is holding excessive torque. Disengage
autopilot.
AP ELEV MISTRIM Amber Autopilot is engaged and autopilot elevator
servo is holding excessive torque. Disengage
autopilot.
AP ELEV MISTRIM White Autopilot is engaged and autopilot elevator
servo is holding torque. Disengage autopilot.
Pilot’s Manual
PM-126A 5-73
GO-AROUND (GA) BUTTON
The GA button is located on the outboard side of the left thrust lever.
Selection of the GA button disconnects the autopilot (but not the yaw
damper) and cancels all other vertical and lateral modes except automatic
altitude preselect arm. The flight director provides a wings level
command bar display in the lateral axis and a fixed pitch-up vertical
command. The pitch command does not guarantee that the go around
airspeed will be achieved. If used on takeoff, the pitch attitude will not
guarantee achieving the V2.
FLIGHT MANAGEMENT SYSTEM (FMS)
The UNS-1E is a fully integrated Flight Management System (FMS).
The FMS provides centralized navigation sensor control, flight planning,
lateral and vertical flight guidance, steering enroute, terminal and
approach modes of operation. Database management, fuel management,
and maintenance functions are also provided by the FMS.
The UNS-1E accepts position information from up to five long-range
navigation sensors as well as DME, VOR, or TACAN sensors. The data
from these sensors is used to determine the best computed position.
The UNS-1E incorporates an internal GPS sensor with Receiver Autonomous
Integrity Monitoring (RAIM) as a standard part of the FMS configuration.
The FMS interfaces with the IC-600s for a transfer of
information to the FMS and lateral and vertical steering commands
back to the EFIS and FD/AP.
If a single FMS is installed, it can receive ADC, AHRS, EFIS, and AP
data from either IC-600 but will use the #1 IC-600 as the primary source.
If dual FMSes are installed, FMS 1 will use the #1 IC-600 as the primary
source and FMS 2 will use #2 IC-600 as its primary source. With dual
FMS installation, the pilots can use either FMS as the navigation source
on their PFDs/MFD. In the material that follows, the FMS unit will be
referred to as the Control Display Unit (CDU). The CDU contains a color,
flat panel display, ten Line Select Keys (LSK) and dedicated function
keys.
The FMS is powered from the left essential bus by a 5-amp circuit
breaker labeled FMS located on the pilot’s circuit breaker panel (AVIONICS
[NAVIGATION] group).
Pilot’s Manual
5-74 PM-126A
CONTROL DISPLAY UNIT (CDU)
The CDU (Figure 5-19) is the primary interface to the pilot. It provides
keypad input for selection of NAV modes and entering of waypoints
and a display to indicate current operational modes. The CDU contains
all the components required for the FMS functions. Other functions that
are provided include:
• Radio tuning and RMU interface — The CDU allows
remote tuning of the VHF COMM, VOR/ILS, ADF and
ATC radios.
• Flight planning — The CDU can store a fixed number of
flight plans into the FMS database.
ENTER
DIM
MSG
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