LOG OF REVISIONS Revision Number 1 Page Number All Description Complete Supplement FAA Approval 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.
LOG OF REVISIONS Revision Number Page Number 16 18 23 24 26 28 29 31 32 6 All 11 15 24 29 Description Updated section 2.8 to reflect current airspeed tape behavior. Updated section 2.14 to better describe the terrain awareness function. Updated section 2.16 for GFDS weather function. Corrected description of heading and AHRS failures. Corrected description of ADC failure. Corrected table entry for AHRS ALIGN. Added new section 4.4 for altitude alerter configuration. Added detail to section 4.
LOG OF REVISIONS Revision Number 7 Page Number All Description FAA Approval Re-issue complete supplement. 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. Robert Grove ODA STC Unit Administrator GARMIN International, Inc ODA-240087-CE AFMS, GARMIN G500 PFD/MFD SYSTEM FAA APPROVED Date: 08-18-2011 190-01102-01 Rev.
LOG OF REVISIONS Revision Number 8 Page Number All Description Re-issue complete supplement. 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.
LOG OF REVISIONS Revision Number 9 Page Number All Description FAA Approval Re-issue complete supplement. 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. See Page 1 AFMS, GARMIN G500 PFD/MFD SYSTEM FAA APPROVED 190-01102-01 Rev.
TABLE OF CONTENTS SECTION PAGE SECTION 1. GENERAL ................................................................................... 9 1.1 1.2 1.3 1.4 1.5 1.6 1.7 1.8 1.9 1.10 1.11 1.12 1.13 GARMIN G500 PRIMARY FLIGHT / MULTI-FUNCTION DISPLAY SYSTEM ............. 9 SYSTEM POWER SOURCES.................................................................................. 9 NAVIGATION SOURCES .................................................................................... 10 SYNTHETIC VISION TECHNOLOGY ..
4.3 4.4 4.5 4.6 ALTITUDE SYNCHRONIZATION ......................................................................... 33 ELECTRIC STANDBY ATTITUDE GYRO ............................................................. 33 SYNTHETIC VISION TECHNOLOGY ................................................................... 33 AUTOPILOT OPERATIONS WITH THE G500 SYSTEM .......................................... 34 SECTION 5. PERFORMANCE ..................................................................... 40 SECTION 6.
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).
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.
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.
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.
1.11 Single G500 Operational Block Diagram Equipment Installed per this STC Adapter (optional) GAD 43/43e to Aircraft Systems Magnetometer GMU 44 AHRS GRS 77 PFD/MFD Display GDU 620 Electric Standby Attitude*** (optional) Air Data Computer GDC 74() Temperature Probe GTP 59 Audio Panel (optional)** No. 1 GPS/SBAS Navigator (required) Traffic (optional) No. 2 GPS/SBAS Navigator (optional) XM WX/Entertainment GDL 69/69A (optional) No.
(required) Copilot PFD/MFD Display GDU 620 Equipment Installed per this STC AFMS, GARMIN G500 PFD/MFD SYSTEM FAA APPROVED Magnetic Compass Standby Altimeter (required on pilot side only) Standby Attitude* Standby Airspeed (optional)** Video Source Audio Panel Various Models (optional)*** Temperature Probe GTP 59 #1 Air Data Computer GDC 74() #1 (optional) (optional)** Iridium Data Link Radar Altimeter (optional)** Weather Radar XM WX/Entertainment GDL 69/69A (optional) (optional)** Auto
1.
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.
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.
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.
accelerated degradation. Extended storage in a discharged state and overcharging 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.
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.
2.19 Active Weather RADAR RADAR is broadcasting energy while in Weather or Ground mapping modes. If the G500 system is configured to control an airborne weather radar unit, observe all safety precautions, including: Do not operate in the vicinity of refueling operations. Do not operate while personnel are in the vicinity (approximately 20 feet) of the radar sweep area.
2.20 Kinds of Operations Unless placarded as limited to VFR only operations, G500 equipment installed in an appropriately certified aircraft is approved for Day and Night / VFR and IFR operations in accordance with 14 Code of Federal Regulations Part 91, Part 121, and Part 135 when appropriately maintained.
2.22 L-3 ESI-1000 Electronic Standby Instrument The independent power source for the L-3 ESI-1000 must be verified to be operational before flight, or the ESI-1000 must be considered inoperative. For the verification procedure, refer to the approved Airplane Flight Manual and/or Instructions for Continued Airworthiness for the independent power source. 2.23 Electronic Flight Bag (EFB) Applications Class 3 EFB applications have not been evaluated as part of this STC.
Section 3. EMERGENCY PROCEDURES 3.1 Emergency Procedures 3.1.1 PFD 1 Failure PFD 1 failure is indicated by the loss of displayed information on the PFD, including blank, frozen, or unresponsive display. 1. 2. Use standby flight instruments for attitude, airspeed, altitude, and heading reference. Refer directly to navigation source for navigation information (such as GPS). If autopilot is engaged: 3. Verify autopilot mode and cross check against standby flight and navigation data. 3.1.
3.1.3 Air Data Computer (ADC) Failure Air Data Computer failure is indicated by a red X and yellow text over the airspeed, altimeter, vertical speed, TAS and OAT displays. Some derived functions, such as true airspeed and wind calculations will also be lost. If valid GPS data is available, the PFD will automatically revert to display GPS calculated altitude relative to mean sea level. This GPS altitude is displayed above the altitude tape. 1. 2.
3.1.6 Loss of Electrical Power to 2-inch Electric Standby Attitude Indicator (flashing or steady amber STBY text) When a 2-inch electric standby attitude indicator is installed, loss of primary electrical power to the attitude indicator is annunciated by amber STBY text on the Annunciation Control Unit. The attitude indicator is operating on backup battery power, and pilot action may be required for the gyro to continue operating. If the amber STBY text is flashing (manual operation): 1.
3.2 Abnormal Procedures 3.2.1 Heading Failure Heading failure is indicated by replacement of the digital heading display with amber “HDG” text and a red X. If valid GPS ground track is available, it will automatically be displayed in place of heading. The HSI heading bug and course pointer will continue to function normally, using GPS ground track as a reference instead of magnetic heading. If GPS track is not available: 1. 2. Use standby compass for heading reference.
3.2.2 GPS Data Failure GPS data failure may be indicated by any or all of following: Loss of GPS course deviation information on HSI Amber “LOI” text on the HSI Amber “NO GPS POSITION” text on the MFD moving map Loss of waypoint bearing or distance information 1. Select alternate GPS source, if available, by pressing “1-2” softkey on PFD. If alternate GPS source is not available: 2.
3.3 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 displays. NOTE The G500 Cockpit Reference Guide and the G500 Pilot’s Guide contain detailed descriptions of the annunciator system and all warnings, cautions and advisories. 3.3.1 Warning annunciations – Red Annunciation Pilot Action ATTITUDE FAIL Use Standby Attitude. AIRSPEED FAIL Use Standby Airspeed.
3.3.2 Caution annunciations – Yellow Annunciation Pilot Action Fly the aircraft CHECK manually and ATTITUDE crosscheck GDU 620 attitude Autopilot will indication with automatically standby attitude disconnect. indicator and other sources of attitude Note: Only appears with information the installation of an (airspeed, heading, optional GAD 43 adapter altitude, etc.
3.3.3 Advisories – White Annunciation Pilot Action Various Alert View and understand all advisory messages. Messages may appear Typically, they indicate communication issues under the MFD within the G500 System. Refer to the G500 Cockpit ALERTS soft key. Reference for appropriate pilot or service action. AFMS, GARMIN G500 PFD/MFD SYSTEM FAA APPROVED 190-01102-01 Rev.
Section 4. NORMAL PROCEDURES Refer to the Garmin G500 PFD/MFD System Cockpit Reference Guide P/N 190-01102-03 or G500 Pilot’s Guide P/N 190-01102-02, presented in Paragraph 2.1 of this document, for normal operating procedures. This includes all Primary Flight Display and Multi-Function Display information.
Soft keys at the bottom of the display allow for some quick functions to be performed on each page. The soft keys operate by press and release. More detailed configuration is typically available by pressing the MENU button, which is on the right side of the display. Pressing and holding down the CLR key is a shortcut to get back to the main map page on the MFD. This can be used as a quick way back, or when the pilot has selected a submenu within the system.
4.6 Autopilot Operations with the G500 System The G500 PFD/MFD System offers various integration capabilities dependent mainly upon the type of autopilot installed in a particular aircraft. The G500 installation in this aircraft provides the following autopilot integration capabilities: This installation does not interface with the autopilot (basic wing leveling autopilot or no autopilot is installed in the aircraft). Course / NAV Selection coupling to the autopilot.
4.6.2 Course / NAV Selection coupling to the autopilot 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 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. 4.6.
When GPSS is selected on the PFD, GPSS is annunciated in the lower left portion of the PFD. The GPSS mode annunciation depends on the location of the NAV STATUS information, as shown below. NAV STATUS STYLE 1 NAV STATUS STYLE 2 NOTE GPSS mode is selectable from PFD 2, but GPSS is not annunciated on PFD 2. The GPSS commands to the autopilot are based on the GPS source displayed on PFD 1. When GPSS is selected on the PFD, GPSS turn commands are converted into a heading error signal to the autopilot.
4.6.6 Selected Altitude Bug Coupling When installed appropriately, certain autopilots may be coupled to the PFD selected altitude bug for altitude preselect and capture. Except as described in this section, refer to the autopilot AFMS and/or Pilot’s Guide for autopilot system operation. 4.6.6.1 S-Tec Autopilots To preselect and capture a selected altitude: 1. Select the desired altitude with the PFD selected altitude bug. 2.
4.6.7 Vertical Speed Bug Coupling Certain autopilots may be coupled to the PFD vertical speed bug for maintaining a selected vertical speed. Except as described in this section, refer to the autopilot AFMS and/or Pilot’s Guide for autopilot system operation. 4.6.7.1 S-Tec Autopilots To select and maintain a vertical speed: 1. Select the desired vertical speed with the PFD vertical speed bug. 2. Press VS on the autopilot programmer computer to engage vertical speed mode.
4.6.8 Flight Director Display If autopilot flight director commands are interfaced to the G500, they will be presented as a single cue flight director on the PFD. Control of the flight director is accomplished via the autopilot/flight director controller; there are no pilot controls or adjustments for the flight director on the G500. The G500 system limits the distance the flight director pitch commands may deviate from the aircraft attitude icon.
4.6.9 GAD 43 Operation The GAD 43 Adapter provides attitude, heading, and barometric correction information from the G500 System to the autopilot. The GAD 43 can also be configured to provide synchro heading output to other systems and its attitude output can be used for RADAR stabilization. The GAD 43 has the ability to disconnect the autopilot if an error in the GAD 43 output or GRS 77 is detected. This disconnect mechanism must be tested prior to each flight in the following manner: 1. 2. 3.
