LOG OF REVISIONS Page Revision Number Date Number Description FAA Approved 1 05/05/2014 All Complete Supplement See page 1 190-00792-13 Rev 1 Page 2 of 25 RFMS, Eurocopter AS350B2, B3 G500H System FAA APPROVED
SECTION 1. 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 1.14 SECTION 2. 2.1 2.2 2.3 2.4 2.5 2.6 2.7 2.8 2.9 2.10 2.11 2.12 2.13 2.14 2.15 SECTION 3. TABLE OF CONTENTS GENERAL ...................................................................... 5 System Description ....................................................... 5 System Power Sources .................................................. 6 Navigation Sources .......................................................
3.1 Loss of Electrical Power ............................................. 17 3.2 Malfunction Indications and Procedures..................... 17 SECTION 4. NORMAL PROCEDURES .......................................... 22 4.1 PFD Knob & PFD Soft Keys ...................................... 22 4.2 MFD Knobs & MFD Soft Keys .................................. 22 4.3 Helicopter Synthetic Vision Technology (HSVT) ...... 23 4.4 HSVT Terrain ............................................................. 23 4.
SECTION 1. GENERAL 1.1 System Description The G500H Flight Display System consists of a Primary Flight Display (PFD) and Multi- Function Display (MFD) housed in a single Garmin Display Unit (GDU 620), an Air Data Computer (GDC 74H ADC) and Attitude and Heading Reference Systems (GRS 77H AHRS). The G500H interfaces with a Garmin GNS 400W, 500W, or 480 series GPS/WAAS navigator and an audio panel.
The standby instruments (airspeed, altimeter and magnetic compass) are completely independent from the PFD and will continue to operate in the event the PFD is inoperative. These standby instruments should be included in the pilot’s normal instrument scan and must be utilized if the PFD data is in question. 1.2 System Power Sources The G500H system depends on electrical power to function.
purpose of the HSVT system is to assist the pilot in maintaining situational awareness with regard to the terrain and traffic surrounding the aircraft. A typical HSVT display is shown in Figure 1-2.
• Obstacles; obstacles such as towers, including buildings 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 displayed when synthetic terrain is selected for display and ground speed is more than 30 knots. • Horizon Line; a white line indicating the true horizon is always displayed on the SVT display.
Video GSR 56 Iridium Data link GNS 400W or 500W Series Navigator Radar Altimeter System 1.7 Traffic Display and Control (Optional) The G500H Flight Display System can display traffic from various sources including TIS data from the Garmin GTX Series Mode-S Transponders or TAS data from various active traffic awareness systems. The information from these systems is displayed on and controlled through the MFD. Traffic shown on the display may or may not have traffic alerting available.
1.12 Database Cards The G500H utilizes several databases. Database titles display in yellow if expired or in question (Note: the G500H 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.
G500H Avionics System Magnetometer GMU 44 Equipment Installed per this STC AHRS GRS 77H GDU 620 PFD/MFD Air Data Computer GDC 74H Temperature Probe GTP 59 Audio Panel Various models No. 1 GPS/WAAS Navigator and/or VOR/Localizer/GS GNS 400W/500W series or GNS 480 (required) Traffic Various Models (optional) No.
SECTION 2. LIMITATIONS 2.1 Types of Operation Rotorcraft equipped with the G500H Flight Display System are limited to VFR ONLY operations in accordance with Title 14 Code of Federal Regulations Part 91 and Part 135. 2.2 Cockpit Reference & Pilot’s Guides Garmin G500H Cockpit Reference Guide P/N 190-01150-03, Revision A or later appropriate revision must be immediately available to the flight crew. 2.
2.4 Databases 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. The obstacle database contains data for obstacles, such as towers, that pose a potential hazard to aircraft. It is very important to note that not all obstacles are necessarily charted and therefore may not be contained in the obstacle database.
When operating in no magnetometer or no magnetometer/no air data modes rapid pitch or roll movements may result in temporary loss of attitude indication. 2.7 Maximum Airspeed The airspeed markings on the G500H PFD match those on the standby indicator regardless of operating altitude. This rotorcraft was originally equipped only with a placard for determining maximum airspeed based on altitude; that placard remains as the means to determine maximum airspeed. 2.
2.11 Terrain and Obstacle Display Terrain elevation information can be selected for display on the MFD as red, orange, yellow, green, and black tiles. Obstacles are displayed in red, yellow, and gray towers. The information is depicted for advisory purposes only and is not to be used for aircraft maneuvers or navigation. Terrain HSVT alerts are not equivalent to warnings provided by HTAWS. 2.12 Datalinked Weather Display XM weather data is provided by an optional GDL 69 or GSR 56 interface.
Table 2-3 Equipment Requirements Number Installed VFR Primary/ Multi Flight Display 1 0 Attitude/ Heading Unit (AHRS) 1 0 Air Data Computer (ADC) 1 0 Magnetometer 1 0 Standby Altimeter 1 1 Standby Airspeed 1 1 Magnetic Compass 1 1 GNS 400W, 500W or 480 series navigator 1 0 Equipment 2.15 Placards If NAV 2 system is not compatible with G500H, NAV 2 must be labeled “NAV 2 NOT DISPLAYED ON THE G500H” unless otherwise displayed on a separate unit.
SECTION 3. EMERGENCY PROCEDURES 3.1 Loss of Electrical Power In th e event of a total loss of electrical power, the G500H system will cease to operate and the pilot must utilize the standby instruments and visual references to fly the aircraft 3.2 Malfunction Indications and Procedures These procedures supersede those presented as markings or placards, or documented in the aircraft’s FAA approved Rotorcraft Flight Manual as a result of the installation of the G500H system.
A complete Heading Failure (magnetometer and GPS ground track failure) is indicated by the digital heading presentation being replaced with a red X and the compass rose digits being removed. The course pointer will indicate straight up and operate much like a traditional CDI, with the Omni-Bearing Selector being adjusted by the PFD knob set to CRS. Under this condition, the pilot must use the standby compass.
Display Dimming When operating at high Outside Air Temperatures, typically in excess of 20°C, the GDU 620 display may automatically dim to reduce equipment temperatures. The display will return to full brightness when operating temperatures are reduced. Warnings, Cautions, and Advisory Annunciations The following tables show the color and significance of the warning, caution, and advisory messages which may appear on the G500H displays.
Table 3-1 Warning Annunciations – Red Annunciation Pilot Action Cause ATTITUDE FAIL Use visual references Display system is not receiving attitude reference information from the AHRS; accompanied by the removal of sky/ground presentation and a red X over the attitude area AIRSPEED FAIL Use Standby Airspeed Display system is not receiving airspeed input from the air data computer; accompanied by a red X through the airspeed display.
Table 3-2 Caution Annunciations – Yellow Annunciation Pilot Action Cause AHRS AligningKeep Wings Level Limit rotorcraft bank to less than 10 degrees as AHRS Aligns Attitude and Heading Reference System is aligning. Keep attitude level using outside references. AHRS will not align if bank angle remains over 10 degrees. NO GPS POSITION If the system is configured with dual GPS, press the 1-2 button GPS data on the selected system is no longer valid. The Moving Map and associated data are not updating.
SECTION 4. NORMAL PROCEDURES Refer to the Garmin G500H PFD/MFD System Cockpit Reference Guide P/N 19001150-03 or G500H Pilot’s Guide P/N 190-01150-02, for detailed operating procedures. This includes all Primary Flight Display and Multi-Function Display information. Although intuitive and user friendly, the G500H PFD/MFD System requires a reasonable degree of familiarity to avoid becoming too engrossed at the expense of situational awareness.
Keys at the bottom of the display allow for the rapid selection of pre-defined 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, located on the right side of the display. Pressing and holding down the CLR key will display the main map page on the MFD. Details of the functions available on the MFD are explained in the Garmin G500H Cockpit Reference Guide defined in Paragraph 1.1. 4.
SECTION 5.
SECTION 6. WEIGHT AND BALANCE - No Change from the Basic Flight Manual.
