Page 1 18.03.2017 Rosdol G500 UPD...
Page 268 Remove “FAA Approved” language. Update IM rev. Add additional 08/31/11 instructions for Mid-Continent standby attitude indicator installations. Added GAD 43e. Removed reference to Pilot’s Guide. Revised lightning 10/12/12 strike inspection. 09/30/13 Added RVSM support for TBM700(850). 03/18/15 Added support for G500 part numbers. 11/17/16 Added GSU 75(B).
Page 269: Table Of Contents
2.17 Implementation and Record Keeping ..............10 3. APPENDIX A ......................... 11 System ........................11 LRU Locations ...................... 11 Wire Routing – Single-Engine ................12 Wire Routing – Twin-Engine ................. 13 G500/G600 PFD/MFD System 190-00601-00 Rev. M Instructions for Continued Airworthiness Page ii...
Page 271: Introduction
2.1 Introduction Content, Scope, Purpose and Arrangement: This document identifies the Instructions for Continued Airworthiness for the modification of the aircraft by installation of the Garmin G500/G600 PFD/MFD System. Applicability: Applies to aircraft altered by installation of the Garmin G500/G600 PFD/MFD System.
Page 272: Description Of Alteration
A and B (i.e. PFD 1A and PFD 1B). The GDU 620 has a PFD and MFD display and front panel controls for performing all G500/G600 normal and configuration operations. Knobs at the lower left and right corners are used for selecting and entering data on each screen.
Page 273: Servicing Information
Xs or system alerts on the GDU 620. To enter into Configuration Mode for the G500/G600 system, verify that the GDU 620 is off and an Installer Unlock Card is inserted in the SD card slot of the GDU 620. Apply power to the GDU 620 while holding the ENT key.
Page 274: Periodic Maintenance Instructions
LRU. The electro-mechanical and electronic standby indicator (if installed) may have a TVS located at the indicator and/or at the power bus. See G500/G600 AML STC Installation Manual Table K-2 to help locate TVS installations. These components must be tested every 24 calendar months in accordance with section 8.3.1 of the G500/G600 AML STC Installation Manual.
Page 275 2.5.9 Mid-Continent Instruments Attitude Indicator Models 4300-4( ), or 4200-( ) with MD420 If a Mid-Continent Instruments Attitude Indicator is installed as part of the G500/G600 AML STC, the battery pack must be tested by one of the following means: 1.
Page 276: Troubleshooting Information
G500/G600 AML STC Installation Manual. The ‘G500/G600 System Post-Installation Checkout Log’ in the aircraft permanent records includes the configuration information for the installation (see section 5.11.3 in the G500/G600 System AML STC Installation Manual for a sample Log). G500/G600 PFD/MFD System 190-00601-00 Rev.
Page 277: Removal And Replacement Information
Aircraft specific LRU locations and wire routing diagram are recorded during installation using the forms in Appendix A of this document. Refer to the G500/G600 AML STC Installation Manual (listed under reference documentation in Section 2.1 of this document) for drawings applicable to this installation and for instructions to complete the forms in Appendix A.
Page 278: Application Of Protective Treatments
The system does not require overhaul at a specific time period. Power on self-test and continuous BIT will monitor the health of the G500/G600 system. If any LRU indicates an internal failure, the unit may be removed and replaced. See the troubleshooting section (section 6) contained in the G500/G600 AML STC Installation Manual, listed under reference documentation in paragraph 2.1 of this document.
Page 279: Assistance
The latest revision of this document will be available on the Garmin website (www.garmin.com). A Garmin Service Bulletin, describing ICA revision, will be sent to dealers if revision is determined to be significant. 2.16 Assistance Flight Standards Inspectors or the certificate holder’s PMI have the required resources to respond to questions regarding this ICA.
Page 280: System
3.1 System System Installed  Single  Dual G500  Single  Dual G600 3.2 LRU Locations The following table describes the locations of the G500/G600 LRUs: Aluminum included in foil tape Description of Location this used for installation? grounding? ...
Page 281: Wire Routing - Single-Engine
3.3 Wire Routing – Single-Engine The following diagram depicts the wire routing for the G500/G600 LRUs throughout the aircraft structure for a single-engine aircraft: G500/G600 PFD/MFD System 190-00601-00 Rev. M Instructions for Continued Airworthiness Page 12 of 13...
Page 282: Wire Routing - Twin-Engine
3.4 Wire Routing – Twin-Engine The following diagram depicts the wire routing for the G500/G600 LRUs throughout the aircraft structure for a twin-engine aircraft: G500/G600 PFD/MFD System 190-00601-00 Rev. M Instructions for Continued Airworthiness Page 13 of 13...
Page 283 Aquila AT01 D-EAVZ AT01-224...
Page 284 LOG OF REVISIONS Page Description FAA Approval 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. L FAA APPROVED Page 2 of 52...
Page 285 Added section 4.4 Added check boxes for FD with SVT and GAD 43 to section 4.5 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...
Page 286 Remove requirement for standby ADI for Robert Grove VFR operations/installations. Add ODA STC Unit Administrator GARMIN International, Inc maximum airspeed limitation section. ODA-240087-CE Date: November 17, 2009 AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L FAA APPROVED Page 4 of 52...
Page 287 4.6.1. Corrected altitude alerter description in section 4.6.6. 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...
Page 288 Added attitude/air data interface to Date: September 08, 2011 section 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...
Page 289 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...
Page 290 ODA-240087-CE Section 2.11. Updated Bendix/King Altitude Preselect Date: December 12, 2013 functionality in Section 4.6.6.3. 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.
Page 291 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. AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L FAA APPROVED Page 9 of 52...
Page 292 2.23 ........27 LECTRONIC TANDBY NSTRUMENT OWER 2.24 (EFB) A ......... 27 LECTRONIC LIGHT PPLICATIONS 2.25 ................ 27 URFACE PERATIONS 2.26 MFD V ................. 27 IDEO ISPLAY AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L FAA APPROVED Page 10 of 52...
Page 293 ADS-B T ..........51 RAFFIC YSTEM NTERFACE ..................51 LIGHT GWX 68 GWX 70 W ......... 51 EATHER ADAR 7.10 ..........52 EPICTION OF BSTACLES AND IRES AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L FAA APPROVED Page 11 of 52...
Page 294: Section 1. General
Section 1. GENERAL G500/G600 Primary Flight / Multi-Function Display System The G500/G600 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 Attitude and Heading Reference System (ADAHRS), and optional signal adapter (GAD).
Page 295: System Power Sources
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...
Page 296: Synthetic Vision Technology (Svt)
A typical SVT display is shown below: SVT provides additional features on the G500/G600 primary flight display (PFD) which display the following information: ...
Page 297: Autopilot Interface
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.
Page 298: Audio Panel
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.
Page 299: High Speed Data Bus Interface
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/G600 from “downstream” HSDB units. Any loss of data will be annunciated on the G500/G600.
Page 300: Single G500/G600 Operational Block Diagram
Video Source (optional) ADF, DME (optional) Existing Equipment (already installed in aircraft) [1] Alternatively, the G500/G600 system can include both the GRS 77 AHRS Standby Standby and GDC 74( ) ADC in place of the GSU 75(B) ADAHRS. Airspeed Attitude [2] Audio panel connection to GDU 620 is recommended for tones and aural alerts generated by the GDU 620.
Page 301: Dual G500/G600 Operational Block Diagram
1.13 Dual G500/G600 Operational Block Diagram AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L FAA APPROVED Page 19 of 52...
Page 302: Definitions
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/G600 SYSTEM 190-00601-01 Rev. L FAA APPROVED Page 20 of 52...
Page 303: Section 2. Limitations
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/G600 heading and attitude may occur near the poles, but this will not affect the GPS track or standby attitude indicator.
Page 304: Magnetic Variation Operational Area
Mach number. The G500/G600 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.
Page 305: Aerobatic Maneuvers
PFD. 2.11 Course Pointer Auto Slewing The G500/G600 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.
Page 306: Taws Function [Gdu 620 Units With Internal Taws]
2.16 Datalinked Weather Display (XM, GFDS, FIS-B weather) This limitation applies to datalinked weather products from SiriusXM via a GDL 69/69A, FIS-B via a Garmin ADS-B receiver, and Connext via a GSR 56. Do not use data link weather information for maneuvering in, near, or around areas of hazardous weather.
Page 307: Active Weather Radar
2.18 Active Weather RADAR RADAR is broadcasting energy while in Weather or Ground mapping modes. If the G500/G600 system is configured to control an airborne weather radar unit, observe all safety precautions, including:  Do not operate in the vicinity of refueling operations.
Page 308: Kinds Of Operations
This may be from either the PFD or the standby instruments. (i.e. all “1a” items or all “1b” items from the table above) ** For IFR flight a fully functional G500/G600 system shall not generate system alerts, which indicate faults within the system or any interfaced equipment.
Page 309: Electronic Standby Instrument Power
Video images displayed on the MFD are intended for use as an aid to situational awareness only. Aircraft maneuvering based solely on the MFD video display is prohibited. AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L FAA APPROVED Page 27 of 52...
Page 310: Section 3. Emergency Procedures
PFD. Rate-of-turn information (heading trend vector) will not be available. A heading failure will also occur as described in Section 3.2.1. Use Standby Attitude Indicator. Seek VFR conditions or land as soon as practical. AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L FAA APPROVED Page 28 of 52...
Page 311 ALT NO COMP and IAS NO COMP alerts will be present. 3.1.5 Loss of Electrical Power In the event of a total loss of electrical power, the G500/G600 system will cease to operate and the pilot must utilize the standby instruments to fly the aircraft.
Page 312 STBY PWR button again to return to battery power operation (red gyro warning flag should not be displayed). AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L FAA APPROVED Page 30 of 52...
Page 313 (VMC), or the flight crew determines, based on all available information, that turning in addition to the vertical escape maneuver is the safest course of action, or both. AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L FAA APPROVED Page 31 of 52...
Page 314: Abnormal Procedures
TO/FROM indication. Localizer deviations will not be affected by the selected course, and reverse sensing will occur when tracking inbound on a localizer back course. AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L FAA APPROVED Page 32 of 52...
Page 315 SVT display and the actual terrain around the aircraft, SVT should be turned off manually. To turn off SVT: Press the “PFD” softkey on the PFD. Press the “SYN VIS” softkey to turn off SVT. AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L FAA APPROVED Page 33 of 52...
Page 316 Immediately disengage the autopilot and do not re-engage. AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L FAA APPROVED Page 34 of 52...
Page 317: Warnings, Cautions, And Advisories
Warnings, Cautions, and Advisories The following tables show the color and significance of the warning, caution, and advisory messages which may appear on the G500/G600 displays. NOTE The G500/G600 Cockpit Reference Guide and the G500/G600 Pilot’s Guide contain detailed descriptions of the annunciator system and all warnings, cautions and advisories.
Page 318 NO AP DATA Verify autopilot Autopilot mode of operation is not mode of operation available. using alternate means. AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L FAA APPROVED Page 36 of 52...
Page 319 Various Alert View and understand all advisory messages. Typically, they Messages may indicate communication issues within the G500/G600 appear under the System. Refer to the G500/G600 Cockpit Reference for MFD - appropriate pilot or service action. ALERTS soft key. A/C Reference...
Page 320: Section 4. Normal Procedures
(BRG1 and BRG2 button) which may be overlaid in the HSI presentation on the PFD. The soft keys operate by press and release. Note: In dual G500/G600 installations, the CDI key located on the GNS units is not operational. Consult the Garmin G500/G600 PFD/MFD System Cockpit Reference Guide for a complete description.
Page 321: Altitude Synchronization
PFD will adjust both PFDs, but the standby must still be set by the pilot. Reference the Garmin G500/G600 Cockpit Reference Guide for a complete description and the usage of synchronization in dual installations.
Page 322: Autopilot Operations With The G500/G600 System
The G500/G600 System offers various integration capabilities dependent mainly upon the type of autopilot installed in a particular aircraft. The G500/G600 installation in this aircraft provides the following autopilot functions (appropriate boxes will be checked):  This installation does not interface with the autopilot (basic wing leveling autopilot or no autopilot is installed in the aircraft).
Page 323 When operating the autopilot in NAV mode, the deviation information from the installed navigation sources (i.e. GPS1, GPS2, NAV1, NAV2) is switched via the G500/G600 PFD display. Whatever is displayed on the HSI is the NAV source the autopilot is following. Most autopilots also use the course datum to determine the best intercept angles when operating in NAV mode.
Page 324 4.6.5 Roll Steering capable autopilots If the autopilot is already designed to receive Roll Steering information, the data is transmitted via a digital communications bus from the G500/G600 to the autopilot. The G500/G600 receives this data from the GPS. In dual GPS installations, the G500/G600 sends Roll Steering information for the GPS which is currently selected for use via the PFD 1-2 button.
Page 325 Press and hold the ALT button on the PFD to arm or disarm the selected altitude. NOTE When the selected altitude is armed for capture, ARMED is displayed in white text next to the selected altitude. AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L FAA APPROVED Page 43 of 52...
Page 326 Press and hold the vertical trim rocker switch on the autopilot in the desired direction, or  Press the CWS button on the control wheel to synchronize the vertical speed bug to the current vertical speed. AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L FAA APPROVED Page 44 of 52...
Page 327 G500/G600, the command bars will be displayed at the maximum distance allowed by the G500/G600. As the aircraft pitch changes to satisfy the command bars, the bars will continue to be displayed at the maximum distance from the aircraft attitude icon until the aircraft pitch deviation is within the command display limit.
Page 328: Taws
Adjust headset volumes as necessary. Radar Altimeter If the installation of the G500/G600 is interfaced to a radar altimeter the radar altitude can be displayed on the PFD. If the installed radar altimeter includes self-test capability the Test controls are provided on the AUX/System Setup age.
Page 329: Section 5. Performance
Section 5. PERFORMANCE No change. Section 6. WEIGHT AND BALANCE See current weight and balance data. AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L FAA APPROVED Page 47 of 52...
Page 330: Section 7. System Descriptions
Databases The G500/G600 utilizes several databases. Database titles display in yellow if expired or in question (Note: the G500/G600 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.
Page 331: Electric Standby Attitude Gyro
Autopilot Interface The G500/G600 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.
Page 332: Taws Function [Gdu 620 Units With Internal Taws]
G500/G600 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/G600 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/G600.
Page 333: Ads-B Traffic System Interface
PFD. When waypoints are removed from the Flight Plan on the GPS navigator or when the entire flight plan is deleted it may take as long as 20 seconds for the change to be reflected on the G500/600 Flight Plan page and map.
Page 334: Depiction Of Obstacles And Wires
The settings chosen by the pilot on the Map page menu (including obstacle and wire display ranges) are saved over a power cycle. AFMS, GARMIN G500/G600 SYSTEM 190-00601-01 Rev. L Page 52 of 52...

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