Garmin AS-350B2, AS-350B3 Rotorcraft Flight Manual Supplement
Page
Revision
Number
Date
Number
Description
FAA Approved
LOG OF REVISIONS
1 05/05/2014 All Complete Supplement See page 1
190-00792-13 Rev 1 RFMS, Eurocopter AS350B2, B3 G500H System
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TABLE OF CONTENTS
SECTION 1. GENERAL ...................................................................... 5
1.1 System Description ....................................................... 5
1.2 System Power Sources .................................................. 6
1.3 Navigation Sources ....................................................... 6
1.4 Helicopter Synthetic Vision Tec hnolo gy (Optional) .... 6
1.5 Audio Pane l .................................................................. 8
1.6 Interfaced Equipment .................................................... 8
1.7 Traffic Display and Control (Optional) ........................ 9
1.8 XM Data link (Optional)............................................... 9
1.9 Video Input (Optional).................................................. 9
1.10 Iridium Data link (Optional) ......................................... 9
1.11 Radar Altimeter (Optional) ........................................... 9
1.12 Database Cards ........................................................... 10
1.13 System Description ..................................................... 10
1.14 Pitot-Static System ...................................................... 10
SECTION 2. LIMITATIONS ............................................................. 12
2.1 Types of Operation ..................................................... 12
2.2 Cockpit Reference & Pilot’s Guides ........................... 12
2.3 System Software Requirements .................................. 12
2.4 Databases .................................................................... 13
2.5 AHRS Operational Area ............................................. 13
2.6 AHRS Operation ......................................................... 13
2.7 Maximum Airspeed .................................................... 14
2.8 Navigation A ngl e ........................................................ 14
2.9 Course Pointer Auto Slewing ..................................... 14
2.10 Helicopter Synthetic Vision Tec hnolo gy (HSVT) ...... 14
2.11 Terrain and Obstacle Display ..................................... 15
2.12 Datalinked Weather Display ....................................... 15
2.13 Traffic Display ............................................................ 15
2.14 Equipment Requirements ............................................ 15
2.15 Placards ....................................................................... 16
SECTION 3. EMERGENCY PROCEDURES ................................... 17
RFMS, Eurocopter AS350B2, B3 G500H System 190-00792-13 Rev 1
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Loss of Electrical Power ............................................. 17
3.1
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 Tec hnolo gy (HSVT) ...... 23
4.4 HSVT Terrain ............................................................. 23
4.5 Altitude Alerter ........................................................... 23
SECTION 5. PERFORMANCE ......................................................... 24
SECTION 6. WEIGHT AND BALANCE ......................................... 25
TABLE OF FIGURES
Figure 1-1- GDU 620 PFD/MFD Displays ............................................ 5
Figure 1-2- Typical HSVT Display ....................................................... 7
Figure 1-3 – G500H Flight Display System Block Diagram ............... 11
190-00792-13 Rev 1 RFMS, Eurocopter AS350B2, B3 G500H System
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SECTION 1. GENERAL
1.1 System Description The G500H Flight Display System co nsists 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.
Optionally, the G500H may interface with other systems installed in the
rotorcraft including a Garmin GT X330 transponder, TAS traffic system, GDL
69(A) satellite data link, video sources, radar altimeter and GSR 56 Iridium data
link.
The primary function of the PFD is to provide attitude, heading, air data and
navigation information (from GNS units) to the pilot. The primary function of
the MFD is to display supplemental data including mapping, terrain, video,
charts, and flight plan information.
Figure 1-1- GDU 620 PFD/MFD Displays
RFMS, Eurocopter AS350B2, B3 G500H System 190-00792-13 Rev 1
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Table 1-1
Label
Unit Controlled
PFD
Garmin Display Unit (PFD/MFD),
AHRS
Attitude and Heading Reference
ADC
Air Data Computer, GDC 74H
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. The Garmin
Display Unit (GDU), Attitude and Heading Reference System (AHRS), and Air
Data Computer (ADC) are connected to the aircraft main bus.
The major components of the G500H are circuit breaker protected with pushpull type circuit breakers available to the pilot. These breakers are located in the
pedestal (30 α) circuit breaker panel and are labeled as shown in Table 1-1.
GDU 620
System, GRS 77H
1.3 Navigation Sources The G500H requires at least one Garmin GPS/WAAS navigation unit to be
installed t o ensure the integrit y of the Atti tude and He ading Re ference Sys tem.
The AHRS will still operate in reversionary mode if all GPS sources fail, and
the PFD attitude display will still be presented.
The HSI on the G500H can display course deviation information from up to four
sources: GPS 1, GPS 2, VLOC 1, or VLOC 2. (IF NAV 2 source is compatible
with G500H). In addition, the HSI can display two simultaneous bearing
pointers sourced from GPS 1, GPS 2, VLOC 1, VLOC 2.
1.4 Helicopter Synthetic Vision Technolog y (Optional) HSVT uses an internal terrain database and GPS location to present the pilot
with a synthetic view of the terrain and obstacles in front of the aircraft. The
190-00792-13 Rev 1 RFMS, Eurocopter AS350B2, B3 G500H System
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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.
Figure 1-2- Typical HSVT Display
HSVT provides additional features on the G500H primary flight display (PFD)
which include the following informati on:
• 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.
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• 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.
• Horizon Heading; a pilot selectable display of heading marks
displayed just above the horizon line o n the PFD.
• Airpor t Signs; pilot selecta ble “signposts” d isplayed on the s ynthetic
terrain display indicating the position o f nearby airports that are in the
G500H database.
• Runway Highlight; a highlighted presentation of the location and
orientation of the runway(s) at the d e stination airport.
• Traffic (Optional); a display on the PFD indicating the position of
other aircraft detected by a traffic system interfaced to the G500H
system. The synthetic terrain depiction displays an area approximating
the view from the pilot’s eye p osition when looking directly ahead o ut
the windshield in front of the pilo t. Terrain features o utside the field o f
view are not shown on the display.
The synthetic terrain displa y is intended to aid the p ilot aware ness of the terr ain
and obstacles in front of the aircraft. 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 p la c e of the primary flight instruments.
1.5 Audio Panel The G500H Flight Display System is interfaced with the audio panel insta lle d in
the rotorcraft to provide aural altering generated by the G500H.
1.6 Interfaced Equipment The G500H Flight Display System is designed to interface with other avionics
systems inc luding:
TIS Traffic
TAS Traffic
GDL 69 XM Data link
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