Garmin G500 Manual Download Page 18

 

AFMS, GARMIN G500 PFD/MFD SYSTEM 

190-01102-01 Rev. 9 

FAA APPROVED 

Page 18 of 40 

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

NE

/V

MO

/M

MO

).  This maximum allowable airspeed display 

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

NO

, landing gear, or flap speed limitations) for variations 

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 

Summary of Contents for G500

Page 1: ......

Page 2: ...rator GARMIN International INC ODA 240087 CE Date 07 30 2010 4 None Rerelease document Robert Grove ODA STC Unit Administrator GARMIN International INC ODA 240087 CE Date 08 24 2010 5 All Changed GPS...

Page 3: ...e alerter configuration 29 Added detail to section 4 6 regarding GAD 43 interface Corrected description of autopilot interfaces in section 4 6 1 31 Corrected altitude alerter description in section 4...

Page 4: ...l Re issue complete supplement Robert Grove ODA STC Unit Administrator GARMIN International Inc ODA 240087 CE Date 08 18 2011 Revised section 2 14 limitation on GPS SBAS vertical coupling Added attitu...

Page 5: ...section 2 4 Clarified applicability of section 2 11 Updated autopilot interface information in section 2 14 Revised external TAWS annunciation information in section 2 16 Added limitation for KFC 275...

Page 6: ...r Page Number Description FAA Approval 9 All Re issue complete supplement See Page 1 Corrected navigation radio information in Section 1 1 Updated applicable system software in Section 2 2 Corrected A...

Page 7: ...ON OPERATIONAL AREA 17 2 7 NAVIGATION ANGLE 18 2 8 AHRS NORMAL OPERATING MODE 18 2 9 AIRSPEED LIMITATIONS AND INDICATOR MARKINGS 18 2 10 AEROBATIC MANEUVERS 18 2 11 ELECTRIC STANDBY ATTITUDE GYRO 18 2...

Page 8: ...VED Page 8 of 40 4 3 ALTITUDE SYNCHRONIZATION 33 4 4 ELECTRIC STANDBY ATTITUDE GYRO 33 4 5 SYNTHETIC VISION TECHNOLOGY 33 4 6 AUTOPILOT OPERATIONS WITH THE G500 SYSTEM 34 SECTION 5 PERFORMANCE 40 SECT...

Page 9: ...e included in the pilot s normal instrument scan and may be referenced if the PFD data is in question A second G500 system installed on the co pilot s side does not require additional standby instrume...

Page 10: ...and the PFD attitude display will still be presented see Paragraph 2 8 The G500 HSI can be selected to display course deviation information from up to four independent sources two GPS and two VHF NAV...

Page 11: ...ay indicating the position of nearby airports that are in the G500 database Runway Highlight a highlighted presentation of the location and orientation of the runway s at the destination airport The s...

Page 12: ...various airborne weather radars is optionally available on the MFD The G500 supports Garmin GWX weather radar as well as certain 3rd party weather radars 1 8 Video sources The G500 Avionics Display Sy...

Page 13: ...cted if SVT is enabled Installation of a Mid Continent electric standby attitude indicator is approved by this STC Air Data Computer AHRS Magnetometer GMU 44 GRS 77 GDC 74 Temperature Probe GTP 59 No...

Page 14: ...e GTP 59 2 No 2 GPS SBAS Navigator required No 2 VOR Localizer GS optional Adapter optional GAD 43 43e to Aircraft Systems optional Existing Equipment already installed in aircraft Standby Attitude Ma...

Page 15: ...splay Unit GPS Global Positioning System GPSS GPS Roll Steering HDG Heading HSI Horizontal Situation Indicator IFR Instrument Flight Rules IMC Instrument Meteorological Conditions LOI Loss of Integrit...

Page 16: ...ss against the PFD HSI published charts or other approved sources of navigation information 2 4 Database Cards Databases identified as intended for helicopter use must not be used These databases may...

Page 17: ...charts database contains procedure charts for the coverage area purchased An own ship position icon will be displayed on these charts This database is updated on a 14 day cycle If not updated within 7...

Page 18: ...ximum allowable airspeed display is configured to indicate the appropriate maximum allowable airspeed for the airplane including variations for altitude or Mach number The G500 airspeed tape displays...

Page 19: ...und course pointer prior to initiating any transition on any VHF NAV approach Auto slewing the VHF NAV course pointer to the correct selected course is a database dependent function 2 13 Synthetic Vis...

Page 20: ...ted TAWS The required TAWS annunciations appear in the upper right of the PFD These annunciations include PULL UP red TERRAIN yellow TERR N A white TERR INHB white These annunciations are not relative...

Page 21: ...all safety precautions including Do not operate in the vicinity of refueling operations Do not operate while personnel are in the vicinity approximately 20 feet of the radar sweep area WARNING If a r...

Page 22: ...r ADC 1 or 2 1a 1 Magnetometer GMU 1 or 2 1 Standby Attitude Indicator 1 1 Standby Airspeed Indicator 1 1b 1 Standby Altimeter 1 1b 1 Magnetic Compass 1 1 1 For VFR operations under 14 CFR Part 91 the...

Page 23: ...he system for EFB applications such as the moving map or electronic charts may require additional evaluation or operational approval 2 24 Surface Operations Do not use SafeTaxi or Chartview functions...

Page 24: ...fer directly to navigation source for navigation information such as GPS If autopilot is engaged 3 Verify autopilot mode and cross check against standby flight and navigation data 3 1 2 AHRS Failure A...

Page 25: ...ents to fly the aircraft 3 1 5 Loss of Electrical Power to 3 inch Electric Standby Attitude Indicator flashing amber STBY PWR light When a 3 inch electric standby attitude indicator is installed loss...

Page 26: ...uminated 3 Verify that the red gyro warning flag is not displayed 4 Seek visual meteorological conditions VMC or land as soon as practical operation of standby attitude indicator is limited by battery...

Page 27: ...instead of magnetic heading If GPS track is not available 1 Use standby compass for heading reference 2 Verify selected course using CRS button and PFD knob CAUTION No directional references will be...

Page 28: ...ing CDI 1 2 or BRG softkeys on PFD or refer directly to external navigation data 3 2 4 Synthetic Vision SVT Failure Several data sources are required to display SVT on the PFD GPS terrain database att...

Page 29: ...r the attitude area AIRSPEED FAIL Use Standby Airspeed Display system is not receiving airspeed input from the air data computer accompanied by a red X through the airspeed display ALTITUDE FAIL Use S...

Page 30: ...ence detected between displayed attitude airspeed or altitude dual installations only AHRS ALIGN Keep Wings Level Limit aircraft attitude to 10 bank and 5 pitch as AHRS Aligns OK to taxi Attitude and...

Page 31: ...sories White Annunciation Pilot Action Various Alert Messages may appear under the MFD ALERTS soft key View and understand all advisory messages Typically they indicate communication issues within the...

Page 32: ...the knob is providing a HDG function Assigning the function of the knob is done by pressing releasing one of the dedicated function buttons to the left of the display The knob defaults back to HDG if...

Page 33: ...the pilot Reference the Garmin G500 Cockpit Reference Guide for a complete description and the usage of synchronization in dual installations 4 4 Electric Standby Attitude Gyro When an electric stand...

Page 34: ...Synthetic Vision enabled A GAD 43 Adapter is installed in this aircraft GAD 43 provides attitude to the autopilot GAD 43 provides yaw rate to the yaw damper GAD 43 provides baro correction to the alt...

Page 35: ...he bug is turned more then 180 degrees the autopilot may turn the airplane in the opposite direction of the desired turn 4 6 4 Roll Steering emulated via HDG mode For autopilots that do not support di...

Page 36: ...ror signal to the autopilot When the autopilot is operated in HDG mode the autopilot will fly the turn commands from the GPS navigator selected on PFD 1 If the GPSS data is invalid for example if ther...

Page 37: ...elected altitude bug while ALT SEL mode is selected may result in autopilot mode changes Verify the autopilot mode after changing the selected altitude 4 6 6 3 Bendix King Autopilots To preselect and...

Page 38: ...appear in the vertical speed PFD knob mode indicator when vertical speed is being reduced automatically Manually changing the selected vertical speed while AUTO is displayed will cancel automatic ver...

Page 39: ...ce allowed by the G500 the command bars will be displayed at the maximum distance allowed by the G500 As the aircraft pitch changes to satisfy the command bars the bars will continue to be displayed a...

Page 40: ...opilot disconnects CAUTION Do not use the autopilot if the AP TEST key fails to disengage the autopilot normally NOTE Pressing and holding the AP TEST key for longer than 1 second will prevent the tes...

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