Central Display System
Last updated
Last updated
The central display system shows flight instruments, helicopter systems, and navigation information processed by the G1000H Integrated Avionics System (IAS). It is also used to interact with the various helicopter systems. Components provide a reversionary mode to show all the information on one display unit when a unit fails.
Fans are provided to cool the display units. Refer to .
The central display system consists of the components that follow:
Primary Flight Display (PFD)
Multi-Function Display (MFD)
REV switch
The PFD is the main display to show the flight, powerplant and systems information necessary to the pilot to safely fly the helicopter.
The PFD is located on the right side of the instrument panel. It is mounted on the instrument panel with four captive screws. It has a 10.4 inch (264.2 mm) LCD display with a resolution of 1024 x 768 pixels. It has knobs and keys on both sides to control communication and navigation frequencies, flight planning interfaces, barometric correction inputs, cursor control, and map range selection and panning. Context-sensitive softkeys are located along the bottom of the screen and change purpose depending on the displayed page.
The connector on the helicopter harness for the PFD contains the PFD config module that stores system configuration information. It serves as master configuration module and lets you replace some of the Line Replaceable Units (LRUs) without having to reconfigure them. Refer to the Garmin Maintenance Manual for more information.
The MFD shows other information through selectable pages. It is physically identical to the PFD and they are interchangeable.
The MFD automatically becomes the main display in case the PFD fails, or it can be selected as the main display by the pilot with the REV switch.
The MFD is located on the left side of the instrument panel. It is mounted on the instrument panel with four captive screws.
The REV switch selects the reversionary mode of operation. It controls the mode of operation of the PFD and the MFD. It is located on the miscellaneous control panel.
The PFD and MFD are energized with 28 VDC from the MAIN bus. The PFD can be isolated with the PFD circuit breaker. The MFD can be isolated with the MFD circuit breaker.
The PFD and the MFD communicate with each other via an HSDB.
The integrated avionics unit (GIA) communicates to both PFD or the MFD via two separate HSDBs.
The SIGNAL GROUND connections from the PFD and the MFD are tied together and then applied to their REVERSIONARY MODE SELECT 1 connections when the REV switch is set to NORM. The REVERSIONARY MODE SELECT 1 connections are open when the REV switch is set to PFD or MFD.
The Air Data Computer (ADC) provides environment data to the PFD via an ARINC-429 data bus.
The Attitude and Heading Reference System (AHRS) provides flight data to the MFD via an ARINC-429 data bus.
The intensity of the lighting of the PFD and the MFD is controlled by the cockpit lighting.