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Measuring Equipment
(DME) System
GTX 33 Transponder Mode S transponder—Conventional Mode C transponder plus additional capability for
data communications with ground radar and traffic information systems.
GTX 33D Diversity Transponder Mode S transponder—Conventional Mode C transponder plus additional capability for
data communications with ground radar and traffic information systems and Mode S
diversity.
GWX 68 Weather Radar Provides airborne weather and ground map weather radar to MFD.
GDL 69A Datalink Satellite radio receiver that provides real-time weather information to the MFD
as well as digital audio entertainment. Communicates with the MFD via HSDB
connection. A subscription service required to enable.
RA350 2 Automatic Direction Provides ADF bearing to the G1000 displays (optional).
Finder (ADF) System
C406-N Emergency Locator When activated, the ELT sends out a distress signal of 121.5, 243.0, and 406.028 MHz.
Transmitter (ELT) The 406.028 MHz signal includes important information about the airplane including
System latitude and longitude, which is detected by the CosPas Sarsat Satellite System for
search and resue operations.
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CITATION MUSTANG OPERATING MANUAL
Table 16-1. G1000 SYSTEM COMPONENTS
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CITATION MUSTANG OPERATING MANUAL
NOTE
Marker beacon reception is in the
audio panel, which connects to the
GIAs.
DISPLAYS
Two PFDs and one MFD provide a central display
and crew interface for the G1000. Various
knobs and softkeys provide system control.
The PFDs are two identical, 10.4-inch color
liquid crystal displays (LCDs) in the instrument
panel (see Figure 16-1). Each PFD provides
flight instrument displays and basic
avionics indications (NAV/COM and transponder
settings, course deviation indicator (CDI)
and ILS indications.
The 15-inch MFD provides a moving-map display
and indications for most airframe and engine
systems. The moving map display indicates
current aircraft position relative to topography
and surface features, terrain obstructions, airspace
boundaries, airways, aviation facilities (including
airports and navaids), and weather. The
left side of the MFD provides indications for engine
and aircraft systems and crew alerts.
Reversionary Mode
Information from the PFDs may be partially or
completely added to the MFD, and vice versa,
through “reversionary mode.” If any display
fails, the essential information from that display
automatically reverts to another display, through
reversionary mode, to ensure availability of adequate
information for continued flight.
Display Controls
The crew uses controls on the bezels of each PFD
and MFD to command various instrument,
avionics, and aircraft system settings. Along
the bottom of each display, variable-purpose
“softkeys” provide multiple control functions,
depending upon flight conditions or settings
selected by the crew. The function of each softkey
appears immediately above it on the display.
Additional control of avionics and systems is
provided through the AFCS controller on the
top center panel, and by the MFD/FMS controller
on the lower cockpit pedestal.
OTHER UNITS
Most elements of the Mustang avionics system
are LRUs. Each LRU is a self-contained avionics
module that can be removed from the airplane
and replaced, independent of all other systems.
Most LRUs are panel-mounted or in a rack immediately
behind the MFD in the center panel.
See Table 16-1 for a general overview of
Mustang avionics modules, including LRUs.
Attitude and Heading Reference
System
The remote-mounted GRS 77 AHRS and GMU
44 magnetometer combine to replace conventional
gyros and magnetic compass systems
with long-life, solid-state sensors. Each PFD
has its own AHRS (AHRS1 for pilot PFD,
AHRS2 for copilot PFD), which also connects
to the same-side GIA.
An AHRS combines the functions of an attitude
gyro, directional gyro and turn-and-slip
instrument.
Each AHRS is electrically stabilized by retrieving
information from three other sources besides
itself. The magnetometer, ADC, and GIAs provide
this supplemental data. These three external
sources provide reference information that
also enables the AHRS to function if powered
on after power interruption in flight, and begin
providing valid guidance within seconds.
Magnetometer
Each GMU 44 magnetometer is a magnetic
sensor that provides local magnetic field information
to its corresponding AHRS. The
　
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