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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
magnetometers are in the vertical tail to minimize
magnetic influence from aircraft structures
and contents.
Air Data Computer
Each GDC 74B air data computer (ADC1 for
pilot, ADC2 for copilot) is a remote-mounted
device that provides air data to the GIAs and
the PFDs, including:
• Air temperature
• Pressure altitude
• Density altitude
• Vertical speed
• Indicated airspeed
• True airspeed
• Mach number
Each ADC measures aircraft static and impact
pressure information from pressure transducers
connected to the same-side (pilot or
copilot) pitot-static system and raw air temperature
data from its own outside temperature
probe. Using the raw data, each ADC unit
computes the air data values, then sends them
to its corresponding GIA and PFD. The system
is reduced vertical separation minimum
(RVSM) compliant. Each ADC also communicates
with the AHRS to provide stabilization
and orientation information.
Engine/Airframe Interface Unit
Each GEA 71 interface unit is a computer that
monitors analog and discrete (digital) sensors
on airframe and engine systems, and translates
these into system indications and alerting outputs
to the GIAs. Each GEA interface unit supplies
information to both GIAs. The GIAs
process this information further, and distribute
it to other systems, particularly to the engine indicating
and crew alerting system (EICAS) display
(normally presented on the MFD).
FMS and MFD Controller
A flight management system (FMS) is integrated
into the processors for the displays and
GIAs. The system is controlled with the the
GCU 475 FMS and MFD controller, which
is on the cockpit pedestal below the throttles.
The FMS controller also duplicates many of
the functions of comparable controls on the
PFDs when used to control settings and displays
on the MFD.
Automatic Flight Control
System
The Mustang has a GFC700 AFCS.
The system functions are distributed across
various units:
• The AFCS controller is under the center
glareshield and has the mode-select
buttons.
• Each GIA performs mode logic and FD
computations.
• The servos compute and monitor for the
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