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The cooling system is independent of the heating system
and is divided into separate pilot-controlled cabin and
cockpit zones. The pilot controls temperatures and fan
speeds through independent cabin and cockpit rheostats
mounted on the RH tilt panel. The system consists of a
compressor and condenser assembly in the tailcone, two
evaporator fan assemblies inside the pressure vessel,
and cold air ducting. The cockpit evaporator fan assembly
is located in the lower right hand sidewall. A second
evaporator assembly located on the aft pressure bulkhead
serves the cabin. Each draws in surrounding air
and distributes chilled air through outlets in the cockpit
and overhead vents in the cabin, respectively. The system
may be operated anytime in flight, or on the ground
when ground power is connected or either engine is running.
In flight, the vapor cycle compressor automatically
shuts down if one generator falls off line. A fresh air vent
with a blower and a check valve is located beneath the
nose baggage compartment to provide outside air to the
cockpit whenever the cabin is not pressurized.
9.6 Oxygen System
A 22.0 cubic foot (.62 m3) oxygen bottle, located in the
nose, is provided with a high pressure gauge and bottle-
mounted pressure regulator. Quick-donning pressure
demand masks with microphones are provided at
each crew seat, while automatic dropout constant-flow
oxygen masks are provided at each passenger seat
and above the toilet. Oxygen flow to the cabin is controlled
by a sequencing regulator valve for optimal
passenger usage.
9 . S YSTEMS ( C o n t i nued)
September 2006
11
9.7 Ice and Rain Protection
The wing, horizontal stabilizer, and vertical stabilizer leading
edges are fitted with full span pneumatic de-ice boots
which are inflated by service air (pressure regulated bleed
air). The inflation cycle is managed automatically by a
timer in normal operation or by manual mode if necessary.
Unconditioned, pressure regulated engine bleed air is
used for anti-ice protection of the engine inlets.
The Mustang's glass windshields are electrically antiiced
and defogged by normal 28 volt DC power. Two
independent controllers regulate current in three zones
per windshield. Embedded wire filaments are arranged
to provide essential protection of one zone on the left
windshield in the event of loss of either generator.
Control switches on the LH tilt panel are designed to
remain on during all normal operations. For rain
removal, the windshields are coated with a water repellant.
The cockpit side windows are acrylic and use dual
frost panes for defogging.
The pitot tubes and static ports, and the stall warning
vane are electrically anti-iced using main DC power. One
pitot tube and set of static ports and the stall warning
vane are also protected through the emergency bus.
Two windshield ice detection lights are mounted on the
glareshield and a wing inspection light is mounted on the
left side of the fuselage to assist in detection of ice
buildup during night flights.
9 . S YSTEMS ( C o n t i nued)
12
September 2006
10. FLIGHT COMPARTMENT, I N S T RUMENTATION AND AVIONICS
10.1 General
The Citation Mustang features the Garmin G1000
advanced avionics system, a large-format glass cockpit
with integrated sensors and lightweight modular avionics.
The system presents to the crew all the flight, navigation,
and situational inputs as well as aircraft systems information
for a precise picture of the total flying environment.
Three active matrix liquid crystal displays (AMLCDs)--
designed with high resolution, wide viewing angles, and
clear sunlight readability--comprise the windows into
Garmin's sophisticated G1000 system. Complete flight
management functionality and a three axis digital autopilot
ease the workload for one or two pilots.
The Garmin G1000 avionics system and flight guidance
package on the Mustang consists of the following
components:
• Dual 10.4-inch (diagonal) TFT LCD Control Display Units
with integrated Terrain Awareness System (TAWS B) utilized
as Primary Flight Displays (PFD) - Garmin GDU 1040A
• Single 15-inch (diagonal) TFT LCD Control Display Unit with
integrated Terrain Awareness System (TAWS B) utilized as a
Multi-Function Display (MFD) - Garmin GDU 1500
• Dual Engine/Airframe Interface Units - Garmin GEA 71
• Dual digital Air Data Computers (ADC) - Garmin GDC 74B
• Dual digital Attitude Heading Reference Systems (AHRS) -
Garmin GRS 77
• Dual Magnetometers - Garmin GMU 44
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