Velocity Edge GX570 Manual de usuario descargar pdf (Pagina 15)

August 2011, Preliminary

10. FLIGHT COMPARTMENT, INSTRUMENTATION AND AVIONICS

(Continued)

F. Air Data and Attitude information

The pitot-static system includes two electrically heated

pitot and static sources. Each is cross-plumbed into dual

air data computers (ADCs) located in the forward nose

behind the radar bulkhead. The ADCs perform source

error corrections and calculate indicated airspeed, true

airspeed, mach number, vertical speed, density altitude,

pressure altitude, and total temperature for output to the

Interface Adapters and the PFDs.

In addition, ADC output is received by the Attitude and

Heading Reference Systems (AHRS). Two solid state

digital AHRS reside behind the MFD and are each tied to

the three-axis magnetometers located in the tail. The

AHRS are capable of in-flight and on-the-move initializa-

tion. Output from the AHRS is received and processed

by the Interface Adapter Units and the PFDs. The sys-

tem meets RVSM requirements.

Input from an electrically heated stall warning vane on

the right side of the forward cabin is processed by the

Interface Adapter Units for display on the PFDs and for

input to the aural warning system.

G. VHF Communications Transceivers

Dual VHF communications transceivers are part of the

Interface Adapter units and produce 16 watts of trans-

mission power. They are compliant with European 8.33

kHz channel spacing requirements. Tuning and man-

agement is accomplished through dual touch screen

GTC 570 controllers. There is also an emergency radio

tuning switch located on the right side tilt panel that will

tune the VHF radio to 121.5 bypassing all other tuning

controls.

H. Remote Audio Processor

Dual GMA 36 Remote Audio Processors controlled

through the dual GTC 570 touch screen controllers pro-

vide transmitter section for microphone inputs and direct

audio outputs from all receivers to the speakers and/or

headphones at each crew station. The system includes

crew and cabin intercom and the ability to record and

playback up to 2 ½ minutes of incoming audio. Two

handheld microphones are connected to the audio

processors and installed on each of the control columns.

I. Navigation

Dual Garmin navigation receivers located in the

Interface Adapter Units provide VOR, Localizer and

Glideslope functions. The Marker Beacon receivers are

integrated into the Audio Processors. Navigation infor-

mation is displayed on both PFDs and the reversionary

mode of the MFD. Tuning and management is accom-

plished through the dual touch screen controllers.

J. Global Positioning System (GPS)

Each Interface Adapter Unit includes a WAAS capable

GPS receiver. Both receivers are capable of monitoring

12 channels to provide satellite-based position data for

use by the FMS.

K. Flight Management System (FMS)

The Garmin FMS provides a multiple waypoint naviga-

tion solution suitable for enroute, terminal, and WAAS

precision approach navigation. The touch screen con-

trollers (GTC570) on the pedestal are the FMS interface

to the MFD. It includes controls for selection and manip-

ulation of moving map functions such as range and pan.

Each PFD calculates and displays the current flight plan

using the onside GPS sensor. Automatic GPS sensor

reversion occurs in the event the onside sensor is

degraded or failed.

Airway flight planning, plain language identifiers, airport

communication and navigation frequency lookup fea-

tures are included. Flight plans may be created, stored,

accessed, and activated as needed and are shown on

the MFD moving map. Both lateral and vertical modes

(to the final approach fix) may be displayed and coupled

to the autopilot. Present position referenced geopolitical

and airspace boundaries, and airways may be overlaid

on any of the FMS map formats.

Precision guidance from the FMS meets the operational

requirements of oceanic/remote, NAT MNPS, RNP10,

and RNP5/BRNAV. The navigation database requires

periodic updates via subscription and must be uploaded

to the aircraft through the upper SD flash card port on

each of the three displays.

L. Automatic Flight Control System (AFCS)

Automatic flight control is provided in the M2 by the

Garmin GFC 700 system. The autopilot system (AP)

includes dual flight director computers (integrated in the

Interface Adapter Units), a single Garmin Mode

Controller (GMC 710), and four electric servos for roll,

yaw, pitch, and pitch trim.

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