Aspen Avionics EVOLUTION EFD1000 PRO MAX PFD - System Overview

CHAPTER 1 WELCOME
EFD1000 PRO MAX PFD Pilot’s Guide
Page 1-4
091-00005-002 () EFD1000 PRO MAX PFD Pilot’s Guide
Page 1-5
091-00005-002 ()
1.1 System Overview
The PFD system typically consists of four components:
1. EFD1000 Pro MAX Display Unit (PFD)
2. Configuration Module (CM)
3. Remote Sensor Module (RSM)
4. Analog Converter Unit (ACU)
1
The ACU converts older analog signals and interfaces to the
industry-standard digital ARINC 429 interface, which is the
native language of the PFD. In some installations, generally
when the aircraft is not equipped with an autopilot and has
only digital GPS/Nav/Comm, the ACU may be omitted.
The system architecture in (Figure 1-5) shows the
relationships of the PFD, RSM, CM and ACU.
Digital GPS/VLOC
Analog GPS/VLOC via ACU
EFD1000 Pro MAX PFD
(Primary Flight Display)
Analog
Converter Unit
(ACU)
Aircraft Power
Configuration
Module (CM)
Optional Tone Generator
12C
SPI
RS-232
Digital VLOC/GPS
Sources
Analog NAV Sources
Radar Altimeter
Autopilot
Legacy GPS
RS-232
Discrete
Pitot Static
Existing Aircraft
Static Line
Existing Aircraft
Pitot Line
Remote
Sensor
Module
(RSM)
ARINC 429
Figure 1-5
Pro PFD System Architecture