Garmin G500, G600 User manual

LOG OF REVISIONS

Rev	Page	Description	FAA Approval
A	All	Complete Supplement	Seyed-Joussef Hashemi
			Manager Flight Test Branch
			ANM-160L
			FAA, Los Angeles ACO
			Transport Airplane Directorate
			Date: July 15, 2008

AFMS, GARMIN G500/G600 SYSTEM	190-00601-01 Rev. N
FAA APPROVED	Page 2 of 55

LOG OF REVISIONS

	Rev	Page	Description	FAA Approval
	B	7	Added GAD 43 to section 1.2	Seyed-Joussef Hashemi
				Manager Flight Test Branch
		8	Added section 1.4
		11	Added GAD 43 to diagram	ANM-160L
				FAA, Los Angeles ACO
		12	Added GAD 43 to diagram
				Transport Airplane Directorate
		13	Added section 1.10
		14	Changed GDU s/w to 3.01, AHRS	Date: July 17, 2009
			s/w to 2.12, GNS 400W/500W
			software to 3.20, and added GAD 43
			to section 2.2
			Updated names of charting services in
			section 2.3
		15	Expanded AHRS operational area in
			section 2.4
			Added section 2.5
		16	Added section 2.6
		17	Added section 2.10
		18	Added section 2.13
			Updated section 2.14 to account for
			SVT
		19	Added section 2.17
			Updated section 2.18 to account for
			VFR only installations
		21	Added item 4 in section 3.2
		22	Updated section 3.3.1 to account for
			HSI track reversionary mode
		25	Added ‘check attitude’ and ‘AHRS
			Aligning’ alerts to table
		26	Updated section 3.6 to account for
			G600 internal TAWS
			Updated section 4.1 for new PFD
			knob mode annunciation
			Added note pertinent to dual G600
			installations in section 4.1
		27	Added section 4.4
		28	Added check boxes for FD with SVT
			and GAD 43 to section 4.5
		30	Updated section 4.5.7 to explain FD
			behavior with SVT enabled
			Added section 4.5.8
	AFMS, GARMIN G500/G600 SYSTEM			190-00601-01 Rev. N
	FAA APPROVED			Page 3 of 55

LOG OF REVISIONS

Rev	Page	Description	FAA Approval
C	16	Added section 2.8.	Robert Grove
			ODA STC Unit Administrator
			GARMIN International, Inc
			ODA-240087-CE
			Date: September 15, 2009
D	11	Remove requirement for standby ADI for	Robert Grove
	12	VFR operations/installations. Add	ODA STC Unit Administrator
	16	maximum airspeed limitation section.	GARMIN International, Inc
			ODA-240087-CE
			Date: November 17, 2009

AFMS, GARMIN G500/G600 SYSTEM	190-00601-01 Rev. N
FAA APPROVED	Page 4 of 55

LOG OF REVISIONS

Rev	Page	Description	FAA Approval
E	All	Changed GPS/WAAS to GPS/SBAS.	Robert Grove
		Corrected typographical errors.	ODA STC Unit Administrator
	7	Updated section 1.1 for new features.	GARMIN International, Inc
			ODA-240087-CE
	9	Added new feature descriptions to
		sections 1.7, 1.8, and 1.9.	Date: January 28, 2011
	10, 11	Updated block diagrams for new
		features.
	13	Updated section 2.2 for applicability
		to this AFMS revision. Removed
		GPS navigator software table.
	13	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.
	14	Updated section 2.8 to reflect current
		airspeed tape behavior.
	16	Updated sections 2.14, 2.15, and 2.16
		to better describe the various terrain
		awareness functions. Updated section
		2.17 for GFDS weather function.
	18	Corrected description of AHRS
		failure.
	18	Corrected description of heading
		failure.
	19	Corrected description of ADC failure.
	21	Corrected table entry for AHRS
		ALIGN.
	23	Added new section 4.4 for altitude
		alerter configuration.
	23	Added detail to section 4.6 regarding
		GAD 43 interface. Corrected
		description of autopilot interfaces in
		section 4.6.1.
	24	Corrected altitude alerter description
		in section 4.6.6.
	25	Added Caution and Note regarding
		GAD 43 AP TEST function in section
		4.6.8.

AFMS, GARMIN G500/G600 SYSTEM	190-00601-01 Rev. N
FAA APPROVED	Page 5 of 55

LOG OF REVISIONS

Rev	Page	Description	FAA Approval
F	All	Changed references to GNS navigators	Robert Grove
		to GPS/SBAS navigators.	ODA STC Unit Administrator
	10	Inserted new section 1.10 for HSDB	GARMIN International, Inc
			ODA-240087-CE
		interface description.
	14	Inserted new section 2.3 for moving map	Date: April 01, 2011
		limitations.
	20, 21	Moved rate-of-turn failure description
		from section 3.3.1 to section 3.3.2.
	25	Added checkbox for disabled altitude
		alerter in section 4.4.
G	All	Re-issue complete supplement.	Robert Grove
			ODA STC Unit Administrator
			GARMIN International, Inc
		Revised section 2.14 limitation on
			ODA-240087-CE
		GPS/SBAS vertical coupling.
		Added attitude/air data interface to	Date: September 08, 2011
		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/G600 SYSTEM	190-00601-01 Rev. N
FAA APPROVED	Page 6 of 55

LOG OF REVISIONS

	Rev	Page	Description	FAA Approval
	H	All	Re-issue complete supplement.	Michael Warren
				ODA STC Unit Administrator
			Revised information on system power	GARMIN International, Inc
			sources in section 1.2.	ODA-240087-CE
			Revised audio panel description in	Date: October 25, 2012
			section 1.6.
			Updated block diagrams in sections 1.12
			and 1.13.
			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 2.13.
			Added limitation for KFC 275/325
			interface in section 2.21.
			Added Type Ratings limitation in section
			2.22.
			Added ESI-1000 limitation in section
			2.23.
			Added EFB limitation in Section 2.24.
			Added Surface Operations limitation in
			Section 2.25.
			Added MFD Video limitation in Section
			2.26.
			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/G600 SYSTEM			190-00601-01 Rev. N
	FAA APPROVED			Page 7 of 55

LOG OF REVISIONS

Rev	Page	Description	FAA Approval
J	All	Re-issue complete supplement.
			Michael Warren
		Corrected navigation radio information
		in Section 1.1.	ODA STC Unit Administrator
		Corrected Auto Slew description in	GARMIN International, Inc
			ODA-240087-CE
		Section 2.11.
		Updated Bendix/King Altitude Preselect	Date: December 12, 2013
		functionality in Section 4.6.6.3.
K	All	Added G500 content to applicable
		sections.
		Added Terrain Alerting and Terminal
		Procedures to section 1.1.
		Moved Traffic and Weather Systems to
		separate sections, 1.7 and 1.8.
		Updated software versions in section
		2.2.
		Moved sections 2.4 (DB Card) and 2.11
		(Elec Stby) to section 7.
		Added TAWS Annun from Garmin
		Navigator to section 2.17.
		Added Stormscope Display to	Michael Warren
		sections 2.19 and 7.6.	ODA STC Unit Administrator
		Revised Standby Battery preflight check	GARMIN International, Inc
			ODA-240087-CE
		to include all. electronic indicators in
		Section 2.24	Date: April 1, 2015
		Added GAD 43 AC Reference loss to
		section 3.2.7.
		Added TER, TAWS, NO DATA, and
		A/C Ref Lost description to section 3.3
		Revised sections 1.5, 2.10, 2.14, 2.18,
		and 3.17 for EASA.
		Added Cessna autopilots to
		section 4.6.6.4.
		Added detail to GAD 43 AC Ref to
		section 4.6.9.
		Included select systems descriptions in
		section 7.

AFMS, GARMIN G500/G600 SYSTEM	190-00601-01 Rev. N
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L	All	Added GSU 75(B) to applicable
		sections.
		Added reference to GTX 3X5
		transponders to applicable sections.
		Added limitation for database cards to	Michael Warren
		section 2.4.	ODA STC Unit Administrator
		Added check box for GAD 43 function	GARMIN International, Inc
			ODA-240087-CE
		to section 4.6.
		Added description of GDU control	Date: November 17, 2016
		capabilities for GWX weather radars to
		section 7.9.
		Edited information about obstacle and
		wire depiction to section 7.10.
M	Pg. 28	Update AHRS in-flight Alignment	Erik Frisk
		Guidance.	ODA STC Unit Administrator
			GARMIN International, Inc
			ODA-240087-CE
			Date: July 7, 2017

N17 Added GMC 605 autopilot to HSDB description and removed sentence about HSDB redundant paths

	18-19	Removed irrelevant notes from block
		diagrams
	20	Added VNAV acronym
	21	Updated reference to cockpit reference
		guide to J from G and software versions
	34	Added G5 reset guidance
	38	Added G5 lacking NAV side (1/2)
		indication note	See Page 1
	39	Added note about G5 BARO sync and
		recommending cross side PFD BARO
		SYNC for VNAV operations
	41	Added GFC 500 and GFC 600 autopilot
		operations
	42	Added G5 as an acceptable source for
		GFC 500 autopilots
	43	Added note for GFC 500 autopilots not
		capturing CDI preview needles
	43	Added GFC 500 and GFC 600 heading
		bug information
	54	Added along track waypoint description

AFMS, GARMIN G500/G600 SYSTEM	190-00601-01 Rev. N
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	TABLE OF CONTENTS
SECTION 1. GENERAL .................................................................................			12
1.1	G500/G600 PRIMARY FLIGHT / MULTI-FUNCTION DISPLAY SYSTEM..		12
1.2	SYSTEM POWER SOURCES...................................................................		13
1.3	NAVIGATION SOURCES........................................................................		13
1.4	SYNTHETIC VISION TECHNOLOGY (SVT)............................................		14
1.5	AUTOPILOT INTERFACE .......................................................................		15
1.6	AUDIO PANEL......................................................................................		16
1.7	TRAFFIC DISPLAY................................................................................		16
1.8	WEATHER DATA .................................................................................		16
1.9	VIDEO DISPLAY...................................................................................		16
1.10	RADAR ALTIMETER .............................................................................		16
1.11	HIGH SPEED DATA BUS INTERFACE ....................................................		17
1.12	SINGLE G500/G600 OPERATIONAL BLOCK DIAGRAM .........................		18
1.13	DUAL G500/G600 OPERATIONAL BLOCK DIAGRAM ...........................		19
1.14	DEFINITIONS........................................................................................		20
SECTION 2. LIMITATIONS .........................................................................			21
2.1	COCKPIT REFERENCE & PILOT’S GUIDE ..............................................		21
2.2	SYSTEM SOFTWARE REQUIREMENTS...................................................		21
2.3	MOVING MAP......................................................................................		21
2.4	DATABASE CARDS ..............................................................................		21
2.5	ADAHRS AND AHRS OPERATIONAL AREA .......................................		21
2.6	MAGNETIC VARIATION OPERATIONAL AREA ......................................		22
2.7	NAVIGATION ANGLE ...........................................................................		22
2.8	ADAHRS AND AHRS NORMAL OPERATING MODE ...........................		22
2.9	AIRSPEED LIMITATIONS AND INDICATOR MARKINGS ..........................		22
2.10	AEROBATIC MANEUVERS....................................................................		23
2.11	COURSE POINTER AUTO SLEWING.......................................................		23
2.12	SYNTHETIC VISION TECHNOLOGY.......................................................		23
2.13	AUTOPILOT INTERFACE .......................................................................		23
2.14	TERRAIN PROXIMITY FUNCTION .........................................................		23
2.15	TAWS FUNCTION [GDU 620 UNITS WITH INTERNAL TAWS] ............		24
2.16	DATALINKED WEATHER DISPLAY (XM, GFDS, FIS-B WEATHER)......		24
2.17	TRAFFIC DISPLAY................................................................................		24
2.18	ACTIVE WEATHER RADAR ................................................................		25
2.19	STORMSCOPE® DISPLAY .....................................................................		25
2.20	KINDS OF OPERATIONS........................................................................		26
2.21	KFC 275/325 ALTITUDE PRESELECT ..................................................		26
2.22	TYPE RATINGS ....................................................................................		26
2.23	ELECTRONIC STANDBY INSTRUMENT POWER .....................................		27
2.24	ELECTRONIC FLIGHT BAG (EFB) APPLICATIONS .................................		27
2.25	SURFACE OPERATIONS ........................................................................		27
2.26	MFD VIDEO DISPLAY .........................................................................		27
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SECTION 3. EMERGENCY PROCEDURES ..............................................		28
3.1	EMERGENCY PROCEDURES .................................................................	28
3.2	ABNORMAL PROCEDURES...................................................................	32
3.3	WARNINGS, CAUTIONS, AND ADVISORIES...........................................	35
SECTION 4. NORMAL PROCEDURES ......................................................		38
4.1	PFD KNOB & PFD SOFT KEYS ...........................................................	38
4.2	MFD KNOBS & MFD SOFT KEYS.......................................................	38
4.3	ALTITUDE SYNCHRONIZATION ............................................................	39

4.4ELECTRIC STANDBY ATTITUDE GYRO (MID CONTINENT 4200 AND 4300

SERIES)...........................................................................................................		39
4.5	SYNTHETIC VISION TECHNOLOGY.......................................................	39
4.6	AUTOPILOT OPERATIONS WITH THE G500/G600 SYSTEM ...................	41
4.7	TAWS ................................................................................................	49
4.8	RADAR ALTIMETER.............................................................................	49
SECTION 5. PERFORMANCE .....................................................................		50
SECTION 6. WEIGHT AND BALANCE......................................................		50
SECTION 7. SYSTEM DESCRIPTIONS .....................................................		51
7.1	DATABASES ........................................................................................	51
7.2	ELECTRIC STANDBY ATTITUDE GYRO ................................................	52
7.3	AUTOPILOT INTERFACE.......................................................................	52
7.4	TAWS FUNCTION [GDU 620 UNITS WITH INTERNAL TAWS] ............	53

7.5TAWS ANNUNCIATIONS ON THE PFD [FROM A GARMIN NAVIGATOR] 53

7.6	STORMSCOPE®....................................................................................	53
7.7	ADS-B TRAFFIC SYSTEM INTERFACE .................................................	54
7.8	FLIGHT PLAN ......................................................................................	54
7.9	GWX 68 AND GWX 70 WEATHER RADAR .........................................	54
7.10	DEPICTION OF OBSTACLES AND WIRES ...............................................	55

AFMS, GARMIN G500/G600 SYSTEM	190-00601-01 Rev. N
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Section 1. GENERAL

1.1G500/G600 Primary Flight / Multi-Function Display System

The G500/G600 System consists of a Primary Flight Display (PFD) and MultiFunction Display (MFD) housed in a single Garmin Display Unit (GDU), plus an Air Data Attitude and Heading Reference System (ADAHRS), and optional signal adapter (GAD). Alternatively, the G500/G600 System may include a separate Air Data Computer (ADC) and Attitude and Heading Reference System (AHRS) in place of an ADAHRS.

The G500/G600 interfaces with other installed systems in the aircraft, including Garmin GPS/SBAS navigators, VHF navigation radios, datalinks, traffic systems, weather radars, audio panels, video sources, radar altimeters, ADF receivers, DME receivers, and autopilots.

The G500/G600 system can optionally provide Terrain Alerting functions and display of Terminal Procedures.

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 data which will facilitate the pilot’s awareness with respect to surrounding factors that may affect the overall conduct of the flight.

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/G600 system installed on the co-pilot’s side does not require additional standby instruments.

AFMS, GARMIN G500/G600 SYSTEM	190-00601-01 Rev. N
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1.2System Power Sources

The G500/G600 system depends on electrical power to function. The Garmin Display Unit (GDU) and Air Data Attitude and Heading Reference System (ADAHRS) (or separate AHRS and 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 functional when this bus is powered off.

The major components of the G500/G600 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 (appropriate boxes will be checked):

		Circuit	Equipment
		Breaker Label
		PFD	Garmin Display Unit (PFD/MFD), GDU 620
		ADAHRS	Air Data Attitude and Heading Reference System,
			GSU 75(B)
		AHRS	Attitude and Heading Reference System, GRS 77
		ADC	Air Data Computer, GDC 74A/B
		GAD	Garmin Adapter, GAD 43/43e
		STBY ATT	Electric Standby Attitude Indicator (Except L-3
			Trilogy and Mid Continent SAM installations)

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.

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.

1.3Navigation Sources

The G500/G600 requires at least one Garmin GPS/SBAS navigation unit to ensure the integrity of the Attitude and Heading Reference System. The ADAHRS or AHRS will still operate in a reversionary mode if the GPS fails, and the attitude display on the PFD will still be presented; see Paragraph 2.8. The G500/G600 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. DME distances can be displayed adjacent to the HSI.

AFMS, GARMIN G500/G600 SYSTEM	190-00601-01 Rev. N
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1.4Synthetic Vision Technology (SVT)

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:

SVT provides additional features on the G500/G600 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. Powerlines are not depicted in synthetic vision.

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•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/G600 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/G600 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.

1.5Autopilot Interface

The G500/G600 may optionally be interfaced to an autopilot. The G500/G600 typically provides course and heading datum to the autopilot based on the data selected for display on the HSI. For aircraft equipped with multiple GPS/NAV systems, the G500/G600 acts as a selection hub for the autopilot’s NAV mode, and the G500/G600 may also provide GPS Steering (GPSS) data. Some autopilots may have Flight Director capabilities which can be displayed on the G500/G600 Attitude Indicator as a Single Cue Flight Director.

Optionally, the autopilot can capture the pre-selected altitude or couple to the selected vertical speed if these capabilities are supported by the autopilot equipment installed. Refer to the autopilot operator’s manual or autopilot Airplane Flight Manual Supplement for the proper operation of the autopilot system.

Not all autopilot systems are approved for coupling to vertical guidance on GPS based approaches; consult the AFMS for the autopilot system.

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1.6Audio Panel

The G500/G600 system may be interfaced to the aircraft audio panel to provide aural alerting generated by the G500/G600 (required for TAWS-B installations).

1.7Traffic Display

The G500/G600 system can display traffic data from interfaced traffic systems. Sources of traffic data include TIS-A traffic via the Garmin GTX Series Mode-S Transponders, TAS/TCAS traffic from various active traffic awareness systems, and ADS-B traffic from Garmin ADS-B transceivers and ADS-B In capable Garmin transponders. The information from these systems is displayed on and controlled using the MFD.

1.8Weather Data

The G500/G600 system can display weather data from interfaced datalink systems. Sources of weather data include the Garmin “GDL 69(A)” and “GDL 69(A) SXM” Sirius XM receivers, Garmin GSR 56 Iridium Transceiver, Garmin GDL 88 ADS-B transceiver, and GTX 345 Transponder. If one of these optional weather datalink receivers is installed, the pilot will be able to access graphical and text weather products using the MFD.

The G500/G600 system can control various airborne weather radars and display their data. Compatible weather radars include Garmin GWX weather radars, as well as certain 3rd-party weather radars.

The G500/G600 system can display data from StormScope™ lightning detection systems.

1.9Video Display

The G500/G600 can display images from up to 2 video inputs. Video images are displayed on the MFD. The G500/G600 does not provide a means to control the video source; however the digital images from the video source can be adjusted using the G500/G600.

1.10 Radar Altimeter

The G500/G600 supports the display of radar altitude on the PFD from certain radar altimeters.

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1.11 High Speed Data Bus Interface

Some Garmin equipment connected to the G500/G600 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 series datalink receivers, GDL 88 ADS-B transceiver, GWX 68/70(R) weather radars, GTS 8XX traffic systems, GTX 3X5 Mode S/ES transponders, and the GMC 605 autopilot.

Depending on the number of HSDB units installed, failure of one HSDB unit may result in loss of data on the G500/G600 from “downstream” HSDB units. Any loss of data will be annunciated on the G500/G600.

AFMS, GARMIN G500/G600 SYSTEM	190-00601-01 Rev. N
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