EFD1000 Installation Manual
DOCUMENT # A-01-126-00 PAGE 37-225 Revision H
© Copyright 2009 Aspen Avionics Inc.
5.2.5 GPS Annunciators
The EFD1000 is capable of displaying GPS annunciations on the HSI portion of the
display from those ARINC 429 connected GPS receivers that output these labels. If
using the PFD display for any required GPS annunciations verify that the GPS receiver
outputs these messages on the ARINC 429 bus.
GPS Annunciations on PFD (if provided by GPS):
• MSG
• WPT
• TERM
• APPR
• INTEG
5.2.6 Aircraft Power Requirements
An electrical load analysis must be performed to ensure the installed EFD1000
components do not exceed the current capacity of the aircrafts charging system (see
Section 7.1).
The EFD1000 system uses an internal battery to permit operation of the EFD1000
during an aircraft charging system failure. If the aircraft bus voltage falls below a
nominal 12.5V +/-0.3V (14V electrical system) or 25.0V +/-0.6V (28V electrical
system), the EFD1000 will switch to the internal battery. The installer must ensure that
the aircraft electrical system attains the minimum voltage when the electrical system is
loaded to flight configuration and engine RPM is at or above the level necessary for
nominal alternator/generator output.
5.2.7 EFD1000 Power Requirements
An “EFIS MASTER” switch or switch breaker to the PFD should be installed so the PFD
can remain off during engine start. Use of the EFIS MASTER switch will ensure that
electrical spikes and interrupts that can accompany engine start will not damage the
system or affect the long-term reliability of the equipment. The use of the EFIS
MASTER is recommended.
The PFD circuit breaker must be a trip free pull type and should be connected to the
switched battery bus as noted in the EFD1000 wiring diagram.
If available, connect the ACU to the avionics electrical bus. Otherwise, connecting the
ACU to the switched battery bus is permissible.
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