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510OM-00 1-11
each produces approximately 1,460 pounds
of thrust (sea level ISA + 10°C).
To improve automation and efficiency, the engines
are controlled by dual-channel full authority
digital engine controls (FADECs).
Engines are started with electrical starter-generators,
which are powered by the onboard
battery or a ground power unit (GPU).
Ice-protection, fire-detection, and fire-extinguishing
systems are provided for each engine.
The engine pylons have ram-air inlets and
exhausts to provide cooling airflow through the
cabin air heat exchangers.
ICE PROTECTION SYSTEM
Anti-ice protection is provided to the engine inlets,
and deice protection is provided to the
wings, and empennage by engine bleed air.
Engine bleed air directly heats the engine inlets
and generator cooling inlets. The wings,
vertical tail, and horizontal stabilizers are deiced
by boots inflated by engine bleed air regulated
to 20 psig (service air). The windshields
are electrically anti-iced and defogged. Electric
heat also anti-ices the pitot-static systems, stallwarning
vane, and engine inlet-mounted T2
sensors. Ice detection lights on the glareshield
help the pilot detect icing on the windshield.
A light on the outside left fuselage helps the
pilot detect icing on the wings.
HYDRAULIC SYSTEM
A single electrically driven hydraulic pump
supplies pressure for operation of the landing
gear and wheel brakes through a closed center
system. The main gear are equipped with hydraulically
operated antiskid-controlled wheel
brakes. Pneumatic backup is available for emergency
landing gear extension and braking.
FLIGHT CONTROLS
Primary flight control is accomplished through
conventional cable-operated surfaces. An
aileron-rudder interconnect provides improved
lateral stability. Trimming is provided by
aileron, elevator, and rudder tabs. The elevator
trim is both mechanically and electrically
actuated. Aileron and rudder trim are electrically
activated. The flaps are electrically actuated
and are on the trailing edges of the
wing. Electrically powered speedbrakes are on
the upper and lower wing surfaces. Nosewheel
steering is mechanically controlled by the rudder
pedals through steering bungees.
ENVIRONMENTAL SYSTEM
The aircraft has a two-zone automatic temperature
control system that is split into cabin and
cockpit. An independent vapor cycle air-conditioning
system provides cooling to the cabin
and cockpit.
Conditioned engine bleed air is used for cabin
pressurization and temperature control. Cabin
pressurization is controlled by an autoscheduling
pressurization system. The crew need
only to adjust destination elevation any time
prior to or during flight and the controller automatically
controls cabin pressure for operation
at the highest practical differential
pressure with minimum rates and changes.
A 22-cubic-foot oxygen bottle (40-cubic-foot
optional) supplies oxygen to the quick-donning
masks for the crew and automatic dropout
masks for each passenger. If cabin altitude
becomes excessive, passenger oxygen masks
deploy automatically (by electrical release)
and can be deployed manually (by oxygen
pressure) upon pilot command.
AVIONICS
The Mustang uses a Garmin G1000 three-display
“glass cockpit” to present most indications
for flight instrumentation, navigation,
avionics, and aircraft systems. The displays include
two 10.4-inch primary flight displays
(for pilot and copilot) and a 15-inch multifunction
display.
The standard factory-installed avionics package
includes the fully integrated flight instruments,
flight guidance, communications,
and navigation systems. The navigation system
includes GPS, ground-based navigation,
and is WAAS-capable. An integrated engine
indicating and crew alerting system (EICAS)
is included. The Garmin G1000 system manages
the instrument and engine displays, the
autopilot, flight guidance systems, and the
flight director. Terrain and traffic avoidance
systems and color radar are standard equipment.
Data link weather capability is available
with subscription.
PUBLICATIONS
The following publications must be immediately
available to the flight crew:
• FAA-approved Airplane Flight Manual
(AFM) contains the limitations, data pertinent
to takeoffs and landings, and
weight and balance data. Information in
the AFM always takes precedence over
any other publication.
• FAA-approved Citation Mustang
　
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本文鏈接地址：CITATION MUSTANG OPERATING MANUAL 1(6)