Garmin G500 User manual

AFMS, GARMIN G500 PFD/MFD SYSTEM 190-01102-01 Rev. 9
FAA APPROVED Page 2 of 40
LOG OF REVISIONS
Revision
Number
Page
Number
Description
FAA Approval
1
All
Complete Supplement
David Armstrong
ODA STC Unit Administrator
GARMIN International, INC
ODA-240087-CE
Date: 07/30/2009
2
9
10
14
Remove requirement for
standby ADI for VFR
operations/installations.
Add maximum airspeed
limitation section.
Robert Grove
ODA STC Unit Administrator
GARMIN International, INC
ODA-240087-CE
Date: 12/10/2009
3
All
Correct page numbering.
Robert Grove
ODA STC Unit Administrator
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/WAAS to
GPS/SBAS. Corrected
typographical errors.
Robert Grove
ODA STC Unit Administrator
GARMIN International, Inc
ODA-240087-CE
Date: 02/23/2011
7
Updated section 1.1 for
new features.
10
Added new feature
descriptions to
sections1.7, 1.8, and1.9.
11, 12
Updated block diagrams
for new features.
14
Updated section 2.2 for
applicability to this AFMS
revision. Removed GPS
navigator software table.
14, 15
Updated section 2.3 with
limitation on use of
helicopter databases and
SD card usage with GSR
56 datalink. Added
information on airport
directory database.

AFMS, GARMIN G500 PFD/MFD SYSTEM 190-01102-01 Rev. 9
FAA APPROVED Page 3 of 40
LOG OF REVISIONS
Revision
Number
Page
Number
Description
FAA Approval
16
Updated section 2.8 to
reflect current airspeed
tape behavior.
18
Updated section 2.14 to
better describe the terrain
awareness function.
Updated section 2.16 for
GFDS weather function.
23
Corrected description of
heading and AHRS
failures.
24
Corrected description of
ADC failure.
26
Corrected table entry for
AHRS ALIGN.
28
Added new section 4.4 for
altitude 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
4.6.6.
32
Added Caution and Note
regarding GAD 43 AP
TEST function in section
4.6.7.
6
All
Changed GNS navigator
references to GPS/SBAS
navigator references.
Robert Grove
ODA STC Unit Administrator
GARMIN International, Inc
ODA-240087-CE
Date: 04/01/2011
11
Inserted new section 1.10
for HSDB interface
description.
15
Inserted new section 2.3
for moving map
limitations.
24
Moved rate-of-turn failure
description from section
3.3.1 to section 3.3.2.
29
Added checkbox for
disabled altitude alerter in
section 4.4.

AFMS, GARMIN G500 PFD/MFD SYSTEM 190-01102-01 Rev. 9
FAA APPROVED Page 4 of 40
LOG OF REVISIONS
Revision
Number
Page
Number
Description
FAA Approval
7
All
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 attitude/air data
interface to section 4.6.
Added GDU 620 as an
autopilot attitude source to
section 4.6.1.
Clarified dual autopilot
interface in section 4.6.9.

AFMS, GARMIN G500 PFD/MFD SYSTEM 190-01102-01 Rev. 9
FAA APPROVED Page 5 of 40
LOG OF REVISIONS
Revision
Number
Page
Number
Description
FAA Approval
8
All
Re-issue complete supplement.
Michael Warren
ODA STC Unit Admin.
Garmin Int’l, Inc.
ODA-240087-CE
Date: 12/26/2012
Revised information on system
power sources in section 1.2
Revised audio panel description
in section 1.6.
Updated block diagrams in
sections 1.11 and 1.12.
Updated System Software
Requirements in section 2.2.
Revised Moving Map limitation
in Section 2.3.
Revised SafeTaxi and Airport
Directory descriptions in 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
275/325 interface in section 2.21.
Added ESI-1000 limitation in
section 2.22.
Added EFB limitation in Section
2.23.
Added Surface Operations
limitation in Section 2.24.
Added MFD Video limitation in
Section 2.25.
Emergency Procedures
reorganized into Section 3.1.
Abnormal Procedures reorganized
into Section 3.2.
Added MISCOMP and NO AP
DATA annunciations in section
3.3.2.
Added airspeed bug description in
Section 4.1.
Removed Altitude Alerter section
4.4.
Added electric standby attitude
indicator procedure as new
section 4.4.
Updated autopilot procedures
throughout section 4.6.

AFMS, GARMIN G500 PFD/MFD SYSTEM 190-01102-01 Rev. 9
FAA APPROVED Page 6 of 40
LOG OF REVISIONS
Revision
Number
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 Auto Slew description in
Section 2.12.
Updated Bendix/King Altitude
Preselect functionality in Section
4.6.6.3.

AFMS, GARMIN G500 PFD/MFD SYSTEM 190-01102-01 Rev. 9
FAA APPROVED Page 7 of 40
TABLE OF CONTENTS
SECTION PAGE
SECTION 1. GENERAL................................................................................... 9
1.1 GARMIN G500 PRIMARY FLIGHT /MULTI-FUNCTION DISPLAY SYSTEM .............9
1.2 SYSTEM POWER SOURCES..................................................................................9
1.3 NAVIGATION SOURCES ....................................................................................10
1.4 SYNTHETIC VISION TECHNOLOGY....................................................................10
1.5 AUTOPILOT INTERFACE....................................................................................11
1.6 AUDIO PANEL..................................................................................................12
1.7 TRAFFIC AND WEATHER SYSTEMS ................................................................... 12
1.8 VIDEO SOURCES...............................................................................................12
1.9 RADAR ALTIMETER .........................................................................................12
1.10 HIGH SPEED DATA BUS INTERFACE ................................................................. 12
1.11 SINGLE G500 OPERATIONAL BLOCK DIAGRAM................................................13
1.12 DUAL G500 OPERATIONAL BLOCK DIAGRAM..................................................14
1.13 DEFINITIONS....................................................................................................15
SECTION 2. LIMITATIONS......................................................................... 16
2.1 COCKPIT REFERENCE &PILOT’S GUIDE...........................................................16
2.2 SYSTEM SOFTWARE REQUIREMENTS................................................................16
2.3 MOVING MAP..................................................................................................16
2.4 DATABASE CARDS...........................................................................................16
2.5 AHRS OPERATIONAL AREA ............................................................................17
2.6 MAGNETIC VARIATION OPERATIONAL AREA ...................................................17
2.7 NAVIGATION ANGLE .......................................................................................18
2.8 AHRS NORMAL OPERATING MODE.................................................................18
2.9AIRSPEED LIMITATIONS AND INDICATOR MARKINGS........................................18
2.10 AEROBATIC MANEUVERS ................................................................................18
2.11 ELECTRIC STANDBY ATTITUDE GYRO..............................................................18
2.12 COURSE POINTER AUTO SLEWING ...................................................................19
2.13 SYNTHETIC VISION TECHNOLOGY....................................................................19
2.14 AUTOPILOT INTERFACE.................................................................................... 19
2.15 TERRAIN PROXIMITY FUNCTION ......................................................................20
2.16 TAWS ANNUNCIATIONS ON THE PFD [FROM A GARMIN NAVIGATOR] .............20
2.17 DATALINKED WEATHER DISPLAY (XM OR GFDS WEATHER) ..........................20
2.18 TRAFFIC DISPLAY............................................................................................20
2.19 ACTIVE WEATHER RADAR ............................................................................21
2.20 KINDS OF OPERATIONS ....................................................................................22
2.21 KFC 275/325 ALTITUDE PRESELECT ...............................................................22
2.22 L-3 ESI-1000 ELECTRONIC STANDBY INSTRUMENT.........................................23
2.23 ELECTRONIC FLIGHT BAG (EFB) APPLICATIONS..............................................23
2.24 SURFACE OPERATIONS ....................................................................................23
2.25 MFDVIDEO DISPLAY .....................................................................................23
SECTION 3. EMERGENCY PROCEDURES.............................................. 24
3.1 EMERGENCY PROCEDURES ..............................................................................24
3.2 ABNORMAL PROCEDURES................................................................................27
3.3 WARNINGS,CAUTIONS,AND ADVISORIES ........................................................29
SECTION 4. NORMAL PROCEDURES...................................................... 32
4.1 PFD KNOB &PFD SOFT KEYS........................................................................32
4.2 MFD KNOBS &MFD SOFT KEYS....................................................................32

AFMS, GARMIN G500 PFD/MFD SYSTEM 190-01102-01 Rev. 9
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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
SECTION 6. WEIGHT AND BALANCE......................................................40
SECTION 7. SYSTEM DESCRIPTIONS .....................................................40

AFMS, GARMIN G500 PFD/MFD SYSTEM 190-01102-01 Rev. 9
FAA APPROVED Page 9 of 40
Section 1. GENERAL
1.1 Garmin G500 Primary Flight / Multi-Function Display System
The G500 PFD/MFD System consists of a Primary Flight Display (PFD) and
Multi-Function Display (MFD) housed in a single Garmin Display Unit (GDU),
plus an Air Data Computer (ADC) and Attitude and Heading Reference System
(AHRS). The G500 interfaces with other installed systems in the aircraft,
including Garmin GPS/SBAS navigators, VHF navigation radios, Garmin GDL
69 data link radios, Garmin GSR 56 Iridum transceivers, and various weather
radars, audio panels, video sources, radar altimeters, traffic systems and ADF
navigators.
The primary function of the PFD is to provide attitude, heading, air data and
navigation information to the pilot. The primary function of the MFD is to
provide mapping, terrain, and flight plan information.
The standby instruments (altimeter, airspeed, attitude, and magnetic compass)
are completely independent from the PFD and will continue to operate in the
event the PFD is not usable. These standby instruments should be 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 instruments.
1.2 System Power Sources
The G500 system depends on electrical power to maintain proper operation. The
Garmin Display Unit (GDU), Attitude and Heading Reference System (AHRS),
and Air Data Computer (ADC) are directly tied to the aircraft’s main or essential
bus and energized when the aircraft master switch is turned on. Other systems,
like the navigation equipment, weather datalink, autopilot and Adapter (GAD)
are typically located on the avionics bus and may not be operable during engine
start.
The major components of the G500 are circuit breaker protected with resettable
type breakers available to the pilot. These breakers are located at the main or
essential bus circuit breaker panel and labeled as follows:
1. PFD - Garmin Display Unit (PFD/MFD), GDU 620
2. AHRS - Attitude and Heading Reference System, GRS 77
3. ADC - Air Data Computer, GDC 74A
4. GAD - Garmin Adapter, GAD 43/43e (optional)
5. STBY ATT- Electric Standby Attitude Gyro
In dual installations the pilot side equipment is suffixed with the number 1 and
the copilot side equipment is suffixed with the number 2. For example: PFD 1
and PFD 2.

AFMS, GARMIN G500 PFD/MFD SYSTEM 190-01102-01 Rev. 9
FAA APPROVED Page 10 of 40
Equipment that receives power from two different circuit breakers will be
suffixed with the letters A and B. For example: PFD 1A and PFD 1B, or PFD
2A and PFD 2B.
1.3 Navigation Sources
The G500 requires at least one Garmin GPS/SBAS navigation unit to ensure the
integrity of the Attitude and Heading Reference System. The AHRS will still
operate in a reversionary mode if the GPS fails, 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. In addition, the HSI can display two simultaneous
bearing pointers sourced from GPS, VHF NAV, or ADF.
1.4 Synthetic Vision Technology
SVT uses an internal terrain database and GPS location to present the pilot with
a synthetic view of the terrain in front of the aircraft. The purpose of the SVT
system is to assist the pilot in maintaining situational awareness with regard to
the terrain and traffic surrounding the aircraft. A typical SVT display is shown
below:

AFMS, GARMIN G500 PFD/MFD SYSTEM 190-01102-01 Rev. 9
FAA APPROVED Page 11 of 40
SVT provides additional features on the G500 primary flight display (PFD)
which display the following information:
Synthetic Terrain; an artificial, database derived, three dimensional
view of the terrain ahead of the aircraft within a field of view of
approximately 25 degrees left and 25 degrees right of the aircraft
heading.
Obstacles; obstacles such as towers, including buildings over 200 AGL
that are within the depicted synthetic terrain field of view.
Flight Path Marker (FPM); an indication of the current lateral and
vertical path of the aircraft. The FPM is always displayed when
synthetic terrain is selected for display.
Traffic; a display on the PFD indicating the position of other aircraft
detected by a traffic system interfaced to the G500 system.
Horizon Line; a white line indicating the true horizon is always
displayed on the SVT display.
Horizon Heading; a pilot selectable display of heading marks
displayed just above the horizon line on the PFD.
Airport Signs; pilot selectable “signposts” displayed on the synthetic
terrain display 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 synthetic terrain depiction displays an area approximating the view from the
pilot’s eye position when looking directly ahead out the windshield in front of
the pilot. Terrain features outside this field of view are not shown on the display.
The synthetic terrain display is intended to aid the pilot awareness of the terrain
and obstacles in front of the airplane. It may not provide either the accuracy or
fidelity, or both, on which to solely base decisions and plan maneuvers to avoid
terrain or obstacles. The synthetic vision elements are not intended to be used
for primary aircraft control in place of the primary flight instruments.
1.5 Autopilot Interface
The G500 may be interfaced to an optional autopilot. The G500 typically
provides course and heading datum to the autopilot based on the data selected
for display on the HSI. For multiple GPS/NAV systems, the G500 acts as a
selection hub for the autopilot’s NAV mode, and the G500 may also provide
GPS Steering data. Some autopilots may provide Flight Director capabilities
which can be displayed on the G500 Attitude Indicator as a Single Cue Flight
Director.

AFMS, GARMIN G500 PFD/MFD SYSTEM 190-01102-01 Rev. 9
FAA APPROVED Page 12 of 40
1.6 Audio Panel
The G500 PFD/MFD system should be interfaced into the aircraft audio panel to
provide aural altering generated by the G500 (required for SVT installations).
1.7 Traffic and Weather Systems
The G500 PFD/MFD system supports TIS traffic via the Garmin GTX Series
Mode-S Transponders. The system also supports TAS/TCAS/TIS traffic from
various active traffic awareness systems. The information from these systems is
available and controllable on the MFD.
The G500 PFD/MFD system supports XM datalink weather via the Garmin
GDL69 and GDL69A receivers. If an optional XM datalink receiver is installed,
the pilot will be able to access graphical and text weather products on the MFD
and control the audio entertainment data from the MFD while listening via an
appropriately installed audio panel.
Datalink weather is also available via the Garmin GSR 56 Iridium Transceiver.
The control and display of Iridium satellite weather on the MFD is similar to
XM weather.
Control and display of 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 System can display images from up to 2 video
inputs. Video images are displayed on the MFD. The G500 does not provide a
means to control the video source; however the digital images from the video
source can be adjusted using the G500.
1.9 Radar Altimeter
The G500 supports the display of radar altitude on the PFD from supported
radar altimeters.
1.10 High Speed Data Bus Interface
Some Garmin equipment connected to the G500 system utilizes the High Speed
Data Bus (HSDB) interface. HSDB is similar to an Ethernet bus and provides a
high-speed interface between Garmin avionics. Like Ethernet, data between two
units may be passed through intermediate “hub” units. Interfaced equipment
that uses HSDB includes the GTN 6XX/7XX navigators, GDL 69 datalink
receiver, GWX 68, and GTS 8XX traffic systems.
The HSDB interfaces are installed to so that maximum data path redundancy is
achieved. However, depending on the number of HSDB units installed, failure
of one HSDB unit may result in loss of data on the G500 from “downstream”
HSDB units. Any loss of data will be annunciated on the G500.

AFMS, GARMIN G500 PFD/MFD SYSTEM 190-01102-01 Rev. 9
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1.11 Single G500 Operational Block Diagram
Standby
Attitude*
Standby
Airspeed
Standby
Altimeter
Magnetic
Compass
Equipment Installed per this STC
(required)
PFD/MFD Display
GDU 620
*Standby Attitude: may be replaced
with electric attitude indicator with
integral / dedicated backup battery.
**Audio panel connection to GDU 620
is recommended for tones and aural
alerts generated by the GDU 620.
This MUST be connected 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. 1 GPS/SBAS Navigator
(required)
No. 1 VOR/Localizer/GS
(optional)
No. 2 GPS/SBAS Navigator
(optional)
No. 2 VOR/Localizer/GS
(optional)
Autopilot/Flight Director
(optional)
ADF
(optional)
Audio Panel
(optional) **
Traffic
(optional)
XM WX/Entertainment
GDL 69/69A
(optional)
Adapter (optional)
GAD 43/43e
to Aircraft Systems
Weather Radar
(optional)
Electric
Standby
Attitude***
(optional)
Radar Altimeter
(optional)
Iridium Data Link
(optional)
Existing Equipment
(already installed in aircraft)
Video Source
(optional)

AFMS, GARMIN G500 PFD/MFD SYSTEM 190-01102-01 Rev. 9
FAA APPROVED Page 14 of 40
1.12 Dual G500 Operational Block Diagram
Equipment Installed per this STC
Air Data Computer
AHRS
Magnetometer
GMU 44 #1
GRS 77 #1
GDC 74() #1
Temperature Probe
GTP 59 #1
Pilot PFD/MFD Display
GDU 620
Copilot PFD/MFD Display
GDU 620
Audio Panel
Various Models
(optional)
***
XM WX/Entertainment
GDL 69/69A
(optional)
Autopilot/Flight Director
(optional)**
Flight Director Only
ADF
(optional)**
No. 1 VOR/Localizer/GS
(optional)**
Standby
Attitude*
Standby
Airspeed
Standby
Altimeter
Magnetic
Compass
(required on pilot side only)
No. 1 GPS/SBAS Navigator
(required)
Air Data Computer
AHRS
Magnetometer
GMU 44 #2
GRS 77 #2
GDC 74() #2
Temperature Probe
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: May be replaced with electric attitude indicator with integral /dedicated backup battery. **
Optional Equipment: Connection
of optional equipment to both GDUs is not required. Functions provided by the optional equipment will only be available on the GDU to which the optional equipment is connected. ***Audio Panel connection to GDU 620 is recommended for tones and aural alerts generated by the GDU 620. This MUST be connected if SVT is enabled. **** Installation of the Mid-Continent electric standby attitude indicator is approved by this STC.
Weather Radar
(optional)**
Electric
Standby
Attitude****
Traffic
(optional)**
Radar Altimeter
(optional)
Iridium Data Link
(optional)**
Video Source
(optional)**
Video Source
(optional)**

AFMS, GARMIN G500 PFD/MFD SYSTEM 190-01102-01 Rev. 9
FAA APPROVED Page 15 of 40
1.13 Definitions
The following terminology is used within this document:
ADC:Air Data Computer
ADF: Automatic Direction Finder
AHRS: Attitude & Heading Reference System
AUX: Auxiliary
BARO: Barometric Pressure
BRG: Bearing
CDI: Course Deviation Indicator
CRS:Course
FD:Flight Director
FPM: Flight Path Marker
GDU: Garmin Display 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 Integrity
MFD: Multi Function Display
PFD: Primary Flight Display
SBAS: Space-based Augmentation System
SD:Secure Digital
SVT:Synthetic Vision Technology
TAS: Traffic Awareness System
TAWS: Terrain Awareness and Warning System (a TSO-C151b
function)
TCAS: Traffic Collision and Avoidance System
TIS: Traffic Information Service
VFR: Visual Flight Rules
VMC: Visual Meteorological Conditions
V/S: Vertical Speed

AFMS, GARMIN G500 PFD/MFD SYSTEM 190-01102-01 Rev. 9
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Section 2. LIMITATIONS
2.1 Cockpit Reference & Pilot’s Guide
The Garmin G500 Cockpit Reference Guide P/N 190-01102-03, Revision A or
later appropriate revision must be immediately available to the flight crew.
Garmin also provides a detailed G500 Pilot’s Guide P/N 190-01102-02. This
reference material is not required to be on board the aircraft but does contain a
more in depth description of all the functions and capabilities of the G500.
2.2 System Software Requirements
The G500 must utilize the following or later FAA approved software versions
for this AFMS revision to be applicable:
Component
Identification
Software Version
GDU 620
PFD/MFD
6.21
GRS 77
AHRS
3.04
2.3 Moving Map
The moving map on the MFD is advisory in nature and is not approved for
course guidance. The moving map on the MFD must be cross checked for
correctness 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 be identified by the word “HELI” or “HELICOPTER” in their
title.
The G500 utilizes several databases. Database titles display in yellow if expired
or in question (Note: the G500 receives the calendar date from the GPS, but only
after acquiring a position fix.). Database cycle information is displayed at power
up on the MFD screen, but more detailed information is available on the AUX
pages. Internal database validation prevents incorrect data from being displayed.
The upper Secure Digital (SD) data card slot is typically vacant as it is used for
software maintenance and navigational database updates. The lower data card
slot should contain a data card with the system’s terrain / obstacle information
and optional data including Safe Taxi, FliteCharts and ChartView electronic
charts.
CAUTION
When interfaced with a GSR56 Iridium transceiver only one SD card may be
present in the GDU620 and it must be in the lower slot.

AFMS, GARMIN G500 PFD/MFD SYSTEM 190-01102-01 Rev. 9
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The terrain databases are updated periodically and have no expiration date.
Coverage of the terrain database is between North 75° latitude and South 60°
latitude in all longitudes. Coverage of the airport terrain database is worldwide.
The obstacle database contains data for obstacles, such as towers, that pose a
potential hazard to aircraft. Obstacles 200 feet and higher are included in the
obstacle database. It is very important to note that not all obstacles are
necessarily charted and therefore may not be contained in the obstacle database.
Coverage of the obstacle database includes the United States and Europe. This
database is updated on a 56-day cycle.
The Garmin SafeTaxi database contains airport diagrams for selected airports.
This database is updated on a 56-day cycle.
The Garmin FliteCharts database contains procedure charts for the coverage area
purchased. This database is updated on a 28-day cycle. If not updated within 180
days of the expiration date, FliteCharts will no longer function.
The Jeppesen ChartView electronic 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
70 days of the expiration date, ChartView will no longer function.
The airport directory database contains information on landing facilities, such as
operating hours, services available, and transportation/lodging resources.
Airport directory information may be available from multiple sources and
coverage areas. This database is updated on a 56-day cycle.
2.5 AHRS Operational Area
The AHRS used in the G500 is limited in its operational area: IFR Operations
are prohibited north of 72N and south of 70S latitudes. In addition, IFR
operations are prohibited in the following four regions:
1) North of 65° North latitude between longitude 75° W and 120° W
2) North of 70° North latitude between longitude 70° W and 128° W
3) North of 70° North latitude between longitude 85° E and 114° E
4) South of 55° South latitude between longitude 120° E and 165° E
Loss of the G500 heading and attitude may occur near the poles, but this will not
affect the GPS track or standby attitude indicator.
2.6 Magnetic Variation Operational Area
IFR operations are prohibited in areas where the magnetic variation is greater
than 99.9 degrees East or West.

AFMS, GARMIN G500 PFD/MFD SYSTEM 190-01102-01 Rev. 9
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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 (VNE/VMO/MMO). 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 VNO, 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

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accelerated degradation. Extended storage in a discharged state and over-
charging will permanently damage the battery. Complete charging is required to
bring the battery up to full capacity if it has been unused for more than four
months or partially discharged.
2.12 Course Pointer Auto Slewing
The G500 HSI will auto slew, i.e. automatically rotate the GPS course pointer to
the desired course defined by each GPS leg. The system will also auto slew the
VHF NAV course pointer when the CDI transitions to a LOC setting if an ILS,
LOC, LOC BC, LDA, or SDF approach is loaded in the GPS/SBAS navigator.
The VHF NAV (green) course pointer will only auto slew if the approach is
loaded in the navigator, a LOC frequency is loaded in the active NAV
frequency, and then the HSI source is changed to the corresponding VHF NAV
for the approach. Back Course approaches will auto slew to the reciprocal
course.
The system is not capable of automatically setting the inbound VHF NAV
course pointer if an approach is not loaded in the GPS/SBAS Navigation
System.
The pilot should always double check the inbound 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 Vision Technology
The use of the synthetic vision display elements alone for aircraft control
without reference to the G500 primary flight instruments or the aircraft standby
instruments is prohibited.
The use of the synthetic vision display alone for navigation, or obstacle, terrain,
or traffic avoidance is prohibited.
2.14 Autopilot Interface
The G500 acts as a navigation source switching hub to an interfaced autopilot
when multiple navigation sources are available. The autopilot will only couple
to the heading, navigation, altitude, and vertical speed selections on PFD 1.
Some autopilots may have navigation source selection integral to their system;
this feature is overridden by the G500 navigation source selection described
herein. Changing the navigation sources displayed on the HSI (by pressing the
CDI button or the 1-2 button) may result in some autopilots disconnecting or
entering a wings level mode.
The autopilot will not couple to the pre-selected altitude or vertical speed if not
properly configured or supported by the installation. Refer to the autopilot
operators manual or Airplane Flight Manual Supplement for the proper
operation of that system.

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Not all autopilot systems are approved for GPS vertical coupling; therefore
consult the AFMS for the GPS/SBAS system and/or the autopilot system.
Flight director commands on PFD 2 are repeated from PFD 1. When utilizing
the flight director display on PFD 2, ensure that the CDI source and BARO
settings on PFD 2 match those on PFD 1.
For installations where the GAD 43 provides attitude information to the
autopilot, the GAD 43 autopilot disconnect mechanism must be tested and
operational before flight using the autopilot. Refer to Section 4.6.9.
2.15 Terrain Proximity Function
The G500 terrain configuration is indicated on the dedicated terrain page of the
MAP group. “TERRAIN PROXIMITY” will be displayed as the page title if
this function is configured. The G500 terrain and obstacle information appears
on the MFD display as red and yellow tiles or towers, and is depicted for
advisory only. Aircraft maneuvers and navigation must not be predicated upon
the use of the terrain display. Terrain unit alerts are advisory only and are not
equivalent to warnings provided by TAWS.
2.16 TAWS Annunciations on the PFD [from a Garmin navigator]
The G500 can display TAWS (Terrain Awareness and Warning System)
annunciations on the PFD if the G500 is interfaced to a Garmin navigator with
integrated 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
to the terrain displayed on the MFD or the yellow/red terrain shading of the
Synthetic Vision displayed on the PFD of the G500 system. Refer to the Garmin
navigator Airplane Flight Manual Supplement for proper pilot action and
information on these alerts.
TAWS alerts on the PFD of the G500 System are only displayed from the
GPS/TAWS navigator interfaced as GPS 1 and are displayed regardless of the
system 1-2 setting, which drives all other PFD and MFD data used by the G500.
2.17 Datalinked Weather Display (XM or GFDS weather)
Datalink weather data is provided by an optional GDL 69 (XM) or GSR 56
(GFDS) interface. The weather information display on the MFD of the G500 is
limited to supplemental use only and may not be used in lieu of an official
weather data source. Use of the datalink weather display for hazardous weather
(e.g thunderstorm) penetration is prohibited. The datalink weather display is
intended for use as an aid to situational awareness only.
2.18 Traffic Display
Traffic may be displayed on the G500 System when connected to an approved
optional TCAS, TAS, or TIS traffic device. These systems are capable of
providing traffic monitoring and alerting to the pilot. Traffic shown on the
display may or may not have traffic alerting available. The display of traffic is
an aid to visual acquisition and may not be utilized for aircraft maneuvering.