Rotorcraft Flight Manual Supplement

190-00792-13 Rev 1 RFMS, Eurocopter AS350B2, B3 G500H System
Page 6 of 25 FAA APPROVED
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 push-
pull 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.
Table 1-1
Label
Unit Controlled
PFD
Garmin Display Unit (PFD/MFD),
GDU 620
AHRS
Attitude and Heading Reference
System, GRS 77H
ADC
Air Data Computer, GDC 74H
1.3 Navigation Sources
The G500H requires at least one Garmin GPS/WAAS navigation unit to be
installed to ensure the integrity of the Attitude and Heading Reference System.
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 Technology (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