Velocity Edge GX570 Instrukcja Użytkownika Pobierz pdf (Strona 14)

August 2011, Preliminary

10. FLIGHT COMPARTMENT, INSTRUMENTATION AND AVIONICS

(Continued)

10.3 Avionics

Described below is the Citation M2 standard avionics

suite as referred to in section 17, Limited Warranties.

The Garmin G3000 is an integrated avionics and flight

guidance system providing flight, navigation, communi-

cation, surveillance, situational awareness, and aircraft

systems status and alerting on three large glass dis-

plays.

A. Electronic Flight Instrument System (EFIS)

The G3000 system utilizes three 14.1 inch (diagonal)

Control display units (GDU1400W) as Primary Flight

Displays (PFD) and Multi-Function Display (MFD). All

three are WXGA Liquid Crystal Displays (LCD) with LED

backlighting and a resolution of 1280 x 800.

Behind the MFDs and within the pressure vessel are the

two remote audio processors (GMA 36). Located in the

nose of the aircraft are the main Garmin Interface

Adapter Units (GIA 63W) incorporating all communica-

tion, navigation, automatic flight control, and extensive

data management functions. These two interface

adapter units are directly linked to the AHRS, ADCs,

transponders, audio controllers, and Engine/interface

units (GEA 71, located in the tail cone). Data from each

source is processed and sent to the PFDs and MFD.

Ethernet architecture and various ARINC cabling are

used for high-speed data transfer. Most components are

line replaceable units (LRUs) contained in individual

trays and racks.Two glareshield cooling fans continu-

ously circulate cockpit air around the avionics.

B. Primary Flight Display (PFD)

The following elements are shown on the PFDs in nor-

mal mode: attitude (full screen horizon line), altitude tape

(feet or meters with six-second trend vectors), airspeed

tape (with six-second trend vectors), Mach, vertical

speed, flap limit speeds, slip/skid, heading, horizontal

situation, glide slope, flight director (cross pointer or sin-

gle cue), navigation and communication frequencies

(active and standby), navigation station/waypoint identi-

fication, track, distance, transponder code, altimeter set-

ting (inches or hectopascals), clock, timer (up or down),

temperature (RAT), ISA deviation, and many other

items. V-speeds can be automatically generated or are

entered manually by the pilot and will appear on the air-

speed tape. At the bottom edge of the display several

menu items are shown directly above corresponding soft

keys on the bezel. The soft keys are used to select the

menu and submenu items. Selection of the "Inset" soft

key places a smaller version of the MFD navigation map

in the lower corner of the PFD for added situational

awareness. The Crew Alerting (CAS) information will be

presented on the PFDs.

C. Multi-Function Display

The MFD serves primarily as a moving map and EIS

platform. The moving map may be populated with a wide

variety of information including traffic, terrain, airborne

weather radar, data link weather, political and airspace

boundaries, airports, navaids, way points, cities, roads,

Garmin FlightCharts and Safe Taxi, and many others, all

at various ranges, The pilot may choose a north-up or

track-up orientation. These and many other options may

be selected using the soft keys along the bottom edge of

the bezel or by using the touch screen GTC 570. A sub-

scription though Garmin is required for database

updates.

D. Secondary Controller

The GCU 275 is a PFD controller used to perform inset

map panning and ranging, to adjust the barometric set-

ting, and to access often used and high-workload flight

planning functions such as the active flight plan on the

lower inset window on the PFD. The GCU 275 will also

control the MFD unit when it is operating in reversionary

mode and presenting primary flight information.

E. Engine Indicating (EIS) and Crew Alerting

System (CAS)

The EIS information is presented on the left side of the

MFD and includes: engine speeds and temperatures; oil

pressures and temperatures; fuel flow, quantity and tem-

perature; oxygen pressure and electrical and pressuriza-

tion systems data. The Crew Alerting (CAS) is presented

on the lower part of each PFD and shows colored text

messages as determined by system inputs. Up to 10

messages are shown in the CAS box; additional mes-

sages may be scrolled into view by using the PFD soft

keys. Pre-programmed logic determines the color, order,

and flashing characteristics of all messages.

Each display may show the essential components of the

EIS and CAS in reversionary mode. Reversion may be

selected manually for either the pilot or copilot side using

switches located below the glareshield.

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