How it Works
Garmin
Loading...
G600
Airplane Flight Manual Supplement
46 pgs803.86 Kb0
FAA Approved Airplane Flight Manual Supplement
15 pgs308 Kb0
PILOT'S GUIDE
314 pgs23.47 Mb0
PILOT'S GUIDE
76 pgs6.17 Mb0
User Manual
240 pgs13.8 Mb1
User Manual
374 pgs27.88 Mb0
Instructions
15 pgs735.58 Kb0
Instructions Manual
334 pgs17.41 Mb0
Maintenance Manual
137 pgs15.85 Mb0
Pilot's Manual
410 pgs51.34 Mb0
Reference Manual
104 pgs4.23 Mb0
User manual
55 pgs1.55 Mb0
User manual
52 pgs1.14 Mb0

Garmin G600 User manual

LOG OF REVISIONS
Rev
Page
FAA Approval
A
All
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. L FAA APPROVED Page 2 of 52
LOG OF REVISIONS
Rev
Page
Description
FAA Approval
B
7
Added GAD 43 to section 1.2
Seyed-Joussef Hashemi
Manager Flight Test Branch ANM-160L FAA, Los Angeles ACO Transport Airplane Directorate
Date: July 17, 2009
8
Added section 1.4
11
Added GAD 43 to diagram
12
Added GAD 43 to diagram
13
Added section 1.10
14
Changed GDU s/w to 3.01, AHRS 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. L FAA APPROVED Page 3 of 52
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 12 16
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: November 17, 2009
AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L FAA APPROVED Page 4 of 52
LOG OF REVISIONS
Rev
Page
Description
FAA Approval
E
All
Changed GPS/WAAS to GPS/SBAS. Corrected typographical errors.
Robert Grove
ODA STC Unit Administrator GARMIN International, Inc ODA-240087-CE
Date: January 28, 2011
7
Updated section 1.1 for new features.
9
Added new feature descriptions to sections 1.7, 1.8, and 1.9.
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. L FAA APPROVED Page 5 of 52
LOG OF REVISIONS
Rev
Page
Description
FAA Approval
F
All
Changed references to GNS navigators to GPS/SBAS navigators.
Robert Grove
ODA STC Unit Administrator GARMIN International, Inc ODA-240087-CE
Date: April 01, 2011
10
Inserted new section 1.10 for HSDB interface description.
14
Inserted new section 2.3 for moving map 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 ODA-240087-CE
Date: September 08, 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/G600 SYSTEM 190-00601-01 Rev. L FAA APPROVED Page 6 of 52
LOG OF REVISIONS
Rev
Page
Description
FAA Approval
H
All
Re-issue complete supplement.
Michael Warren
ODA STC Unit Administrator GARMIN International, Inc ODA-240087-CE
Date: October 25, 2012
Revised information on system power sources in section 1.2.
Revised audio panel description in section 1.6.
Updated block diagrams in sections 1.12 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. L FAA APPROVED Page 7 of 52
LOG OF REVISIONS
Rev
Page
Description
FAA Approval
J
All
Re-issue complete supplement.
Michael Warren
ODA STC Unit Administrator GARMIN International, Inc ODA-240087-CE
Date: December 12, 2013
Corrected navigation radio information in Section 1.1.
Corrected Auto Slew description in Section 2.11.
Updated Bendix/King Altitude Preselect functionality in Section 4.6.6.3.
K
All
Added G500 content to applicable sections.
Michael Warren
ODA STC Unit Administrator GARMIN International, Inc ODA-240087-CE
Date: April 1, 2015
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 sections 2.19 and 7.6.
Revised Standby Battery preflight check to include all. electronic indicators in Section 2.24
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.
L
All
Added GSU 75(B) to applicable sections.
See Page 1
Added reference to GTX 3X5 transponders to applicable sections.
Added limitation for database cards to section 2.4.
AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L FAA APPROVED Page 8 of 52
Added check box for GAD 43 function to section 4.6.
Added description of GDU control capabilities for GWX weather radars to section 7.9.
Edited information about obstacle and wire depiction to section 7.10.
FAA APPROVED Page 9 of 52
AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L
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
AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L
FAA APPROVED Page 10 of 52
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
4.4 ELECTRIC 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 ................... 40
4.7 TAWS ................................................................................................ 46
4.8 RADAR ALTIMETER ............................................................................. 46
SECTION 5. PERFORMANCE ..................................................................... 47
SECTION 6. WEIGHT AND BALANCE ...................................................... 47
SECTION 7. SYSTEM DESCRIPTIONS ..................................................... 48
7.1 DATABASES ........................................................................................ 48
7.2 ELECTRIC STANDBY ATTITUDE GYRO ................................................ 49
7.3 AUTOPILOT INTERFACE ....................................................................... 49
7.4 TAWS FUNCTION [GDU 620 UNITS WITH INTERNAL TAWS] ............ 50
7.5 TAWS ANNUNCIATIONS ON THE PFD [FROM A GARMIN NAVIGATOR] 50
7.6 STORMSCOPE® .................................................................................... 50
7.7 ADS-B TRAFFIC SYSTEM INTERFACE ................................................. 51
7.8 FLIGHT PLAN ...................................................................................... 51
7.9 GWX 68 AND GWX 70 WEATHER RADAR ......................................... 51
7.10 DEPICTION OF OBSTACLES AND WIRES ............................................... 52
AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L
FAA APPROVED Page 11 of 52
Section 1. GENERAL
1.1 G500/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. L
FAA APPROVED Page 12 of 52
Circuit
Breaker Label
Equipment
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)
1.2 System 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):
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.
1.3 Navigation 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. L
FAA APPROVED Page 13 of 52
1.4 Synthetic 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.
AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L FAA APPROVED Page 14 of 52
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.
1.5 Autopilot 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.
AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L
FAA APPROVED Page 15 of 52
1.6 Audio 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).
1.7 Traffic 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.
1.8 Weather 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.
1.9 Video 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.
AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L
FAA APPROVED Page 16 of 52
Loading...
+ 36 hidden pages
Buy Points How it Works FAQ Contact Us Questions and Suggestions Privacy Policy Cookie Policy Terms of Use