Velocity Edge GX570 Manual do Utilizador descarregar pdf (Página 12)

August 2011, Preliminary

10.1 General

The Citation M2 features the Garmin G3000 advanced

avionics system, a large-format glass cockpit with inte-

grated sensors and lightweight modular avionics. The

system presents to the crew all the flight, navigation, and

situational inputs, as well as aircraft systems informa-

tion, for a precise picture of the total flying environment.

Three liquid crystal displays (LCDs) offer high resolution,

wide viewing angles, and clear sunlight readability.

Complete flight management functionality and a three

axis digital autopilot ease the workload for one or two

pilots.

10.2 Instrument and Control Panels

A. Installed on Center Glareshield Panel:

• LH and RH Master Caution / Master Warning Lights

• LH and RH Engine Fire Control Switches

• Reversionary and Dimming Controls

• Flight Director / Autopilot Controller

• Electronic Standby Instrument System

• LH and RH Display Control Units

B. Installed on Instrument Panel (left to right):

• Electrical Power Panel

• LH Primary Flight Display (PFD)

• Multi-Function Display (MFD)

• RH Primary Flight Display (PFD)

C. Installed on Tilt Panel (left to right):

• Pressurization Controls

• Ice Protection Controls

• Windshield Anti-ice Controls

• Fuel Controls

• Ignition Controls

• Landing Gear Control Module

• Lighting Controls

• Emergency Comm Switch

• Event Marker

• Cockpit Voice Recorder Controller

• Flight Hour Meter

• ELT Remote Switch

D. Installed on Pedestal:

• GTC 570 (2) each

• Engine Start Control

• Engine Power Levers

• Flap Control Handles

• Speed Brake Control

• Elevator Trim Control and Indicator

• Takeoff / Go-Around Button

• Rudder Trim Control

• Aileron Trim Control

• Environmental Controls

E. Installed Beneath the Instrument Panel:

• Emergency Brake Handle

• Parking Brake Handle

• Emergency Gear Release

• Control Locks

• Rain Removal levers

10. FLIGHT COMPARTMENT, INSTRUMENTATION AND AVIONICS

9. SYSTEMS (Continued)

9.7 Ice and Rain Protection

Engine bleed air is used for anti-ice protection of the

engine inlets, pylon inlet ducts, wings, and windshields.

The pilot's windshield also utilizes a back-up alcohol

anti-ice system. The horizontal stabilizer leading edges

are fitted with pneumatic de-ice boots, inflated by

engine bleed air (23 psi service air system). A timer

manages the inflation cycle. The pitot tubes, static

ports, and the AOA sensor are electrically anti-iced. Two

windshield ice detection lights are mounted on the

glareshield and a wing inspection light is positioned on

the left side of the fuselage to assist in the detection of

ice buildup during night flights.

Windshield rain removal is accomplished with engine

bleed air during normal operations and by mechanical-

ly actuated rain doors to provide deflected airflow in

heavy rain.

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