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2.7

Navigation Angle

The GDU 620 Navigation Angle can be set to either True or Magnetic on the

AUX page. The Navigation Angle defines whether the GDU 620 headings are

referenced to True or Magnetic North. The Navigation Angle set in the GDU

620 must match that which is set on all GPS/SBAS navigators interfaced to the

unit.

2.8

AHRS Normal Operating Mode

The Attitude and Heading Reference System integrity monitoring features

require the availability of GPS and Air Data. Although the attitude will remain

valid if one of these systems becomes inoperative, IFR flight is not authorized

unless both integrity systems are fully operational. The G500 monitors these

integrity systems automatically and will alert the pilot when the AHRS is not

receiving GPS or Air Data. Note: In dual GPS installations, only one GPS needs

to be available for IFR use.

2.9

Airspeed Limitations and Indicator Markings

The original type design approved airspeed limitations remain in effect. The

airspeed limitations imposed by the AFM/POH, standby airspeed indicator

and/or airspeed limitation placards must be observed.

The G500 airspeed tape displays red/white striping to indicate the maximum

allowable airspeed (V

is configured to indicate the appropriate maximum allowable airspeed for the

airplane, including variations for altitude or Mach number.

The G500 airspeed tape displays a red low-speed awareness band at the lower

range of the airspeed tape. This low-speed awareness band is configured to a

fixed value. It does not indicate an actual or calculated stall speed and does not

adjust with variations in aircraft weight or other factors.

All other G500 airspeed tape indications are configured to indicate the original

type design limitations. The G500 airspeed tape does not adjust these additional

markings (including V

with aircraft weight, altitude, or other factors.

2.10 Aerobatic Maneuvers

Conducting aerobatic maneuvers may cause the attitude information displayed

on the G500 to be incorrect or temporarily removed from the display.

2.11 Electric Standby Attitude Gyro

If an electric standby attitude gyro is installed, the gyro operates from the

aircraft electrical system with a dedicated emergency battery specific to the

electric gyro. The electric attitude gyro battery capacity may vary considerably

depending on temperature, charge status, and battery life condition. Low

temperatures below 32°F will temporarily degrade battery capacity. Internal

chemistry will slowly degrade battery capacity over several years of operation

even when correctly maintained. A poorly maintained battery will suffer

AFMS, GARMIN G500 PFD/MFD SYSTEM

FAA APPROVED

). This maximum allowable airspeed display

, landing gear, or flap speed limitations) for variations

190-01102-01 Rev. 9

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