曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
are shown on the multi-function display.
Two dual channel Full Authority Digital Engine Controls
(FADECs), located in the tailcone, provide automation
and efficiency in thrust management. Throttle lever
angle signals are sent to the FADECs to indicate the
demanded thrust. Detents in the throttle quadrant (takeoff,
climb, cruise, and idle stops) give pilots the optimal
power settings for each phase of flight based on ambient
conditions. Note: Installed in each throttle handle are a
speed brake switch and a takeoff/go-around button.
The FADEC system also provides time-limited dispatch
(TLD), engine synchronization according to switch position,
an auto-relight function, and limited diagnostics as
indicated on the multi-function display (MFD). Extensive
engine diagnostic capability is available with specialized
maintenance equipment. Electrical power for the
FADECs comes from engine driven permanent magnet
alternators (PMAs) rectified to DC, or normal aircraft
voltage. If normal aircraft DC power is lost, the PMAs
ensure the FADECs remain powered.
The PW615F engine incorporates a modular design and
multiple borescope locations for easier maintenance and
inspections. A continuous loop fire detection system
monitors the nacelle area to detect and warn if a fire
occurs. A single-shot fire extinguishing system using
Halon is provided in the tailcone area.
September 2006
9
9 . S YSTEMS
9.1 Flight Controls
The Citation Mustang has traditional flight controls including
trim and autopilot for each axis. Dual pilot controls are
provided through panel mounted yokes for aileron and
elevator control and rudder pedals for rudder, brakes,
and nosewheel steering. All primary control surface connections
are mechanical using pushrod, bellcrank, sector,
and stainless steel cable systems. Dual rudder control
cables allow separate routing paths through the rotor
non-containment zone. Separate switches and knobs
control flaps, speed brakes, and trim. All control surface
trailing edges are equipped with static wicks.
Hinged aluminum flaps, one on each wing, are driven by a
single electric motor in the belly. Motion is transferred by a
flexible drive shaft to one jackscrew actuator in each wing
to push or pull the flap. The flap handle on the pedestal
commands three positions only: up, takeoff/approach, and
landing. Electric position sensing allows flap position to be
displayed on the MFD. A cable interconnect protects
against asymmetric extension in the event of a drive shaft
or actuator failure.
Speed brake panels extend above and below each wing
by electrically powered scissor style actuators and are
available at any speed. The speed brake switches are
located in the sides of the throttle handles.
Means are provided to trim the airplane in all three axes.
Electric trim switches are installed on the aft side of the
pedestal to drive actuators inside the rudder and left
aileron. For manual pitch trim an elevator trim wheel is
located left of the throttles and is connected to dual trim
tabs by cables. Interconnected to these cables is an electric
pitch trim servo allowing use of yoke mounted thumb
switches for elevator trim. Trim position is shown on the
MFD for the rudder and ailerons, and by a mechanical
position pointer on the pedestal for the elevator.
Three electric servos, in addition to the pitch trim servo,
are installed for autopilot functions in pitch, roll, and yaw.
The yaw servo also performs Dutch roll damping and turn
coordination even when the autopilot is disconnected.
A control lock (loose equipment) fits between the panel
and the yoke to hold the elevators and ailerons during
storage. Its rigid flag covers the PFD. A small lever on
the left side of the tailcone turns up to lock the rudder in
the centered position or down to unlock it. Aft movement
of the control yoke will also unlock it.
9.2 Fuel System
There are two integral fuel tanks, one per wing, providing
2,580 pounds (1,170 kg) total of usable fuel. System
operation is fully automatic throughout the normal flight
profile with each engine receiving fuel from its respective
wing tank. Fuel is heated through an oil heat exchanger
and anti-ice additive is not required.
One electric boost pump in each tank sump delivers fuel
during engine start, fuel transfer, and as activated by low
fuel pressure. Each engine has an engine driven fuel
pump and a fuel metering unit (FMU) controlled by the
respective FADEC to deliver high pressure fuel to the
engine. Some of that high pressure fuel from the FMU is
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
Specification & Description(6)
