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The pilot’s AHRU receives primary power from the left essential bus
and a secondary or backup power from the right essential bus. The copilot’s
AHRU receives primary power from the right essential bus and
secondary power from the left essential bus. Should either essential bus
fail in flight, power to both AHRUs is uninterrupted. Separate circuit
breakers for each system, primary and secondary, are provided in the
INSTRUMENT/INDICATIONS group on the pilot’s and copilot’s circuit
breaker panels. The AHRS #1 PRI and #2 SEC circuit breakers are
located on the pilot’s side, and the AHRS #2 PRI and #1 SEC circuit
breakers are located on the copilot’s side. The AHRUs are equipped
with cooling fans which operate automatically to keep the AHRU within
proper temperature limits.
AHRS REVERSION
Failure of an AHRS is apparent when the on-side horizon and pitch
lines are removed from the ADI and a red ATT FAIL annunciator
appears in the upper center of the ADI. The heading compass rose will
display a HDG FAIL annunciator on the HSI. If either AHRS fail, the
AHRS reversion switch on the reversionary control panel (Figure 5-14)
will allow the pilot to select the remaining AHRS to provide attitude
and heading information to both displays. The three-position switch is
labeled 1 - AHRS NORM - 2.
Pilot’s Manual
PM-132A 5-41
ELECTRONIC DISPLAY SYSTEM (EDS)
Four electronic displays are used to provide the display formats for the
Primary Flight Displays (PFDs), the Multi-Function Display (MFD) and
the EICAS display in the electronic flight instrument system. The four
display units are large format 8 x 7 inch, 16 color high resolution display
tubes. The display units are identical and interchangeable, except
for the bezel controllers attached to the front of the units. The bezel controllers
for the outboard DUs are the same and the bezel controllers for
the inboard DUs are the same. A display controller (two) provides the
means for each pilot to control the display of the on-side PFD and to activate
the EFIS test function. A display unit reversion panel, located
above the PFDs, provides reversion control capability.
The display unit configuration powers up with the following displays:
DU #1 - Pilot’s Primary Flight Display (PFD #1)
DU #2 - EICAS Display
DU #3 - Multi-Function Display (MFD)
DU #4 - Copilot’s Primary Flight Display (PFD #2)
The above configuration can be changed using the EICAS reversion
switch. This provides the ability to swap the DU #2 and DU #3 displays
between EICAS and MFD as the pilots desire.
The display units require forced air circulation for cooling which is provided
by two fans mounted on the rear of each DU. If a DU fan fails, a
CAS will illuminate, indicating DU 1, 2, 3, or DU 4 fail. If the temperature
of the DU reaches approximately 120° F, a CAS will illuminate.
The following CAS illuminations are specific to the DUs:
CAS Color Description
DU 1-2 OVHT Amber #1 and/or #2 Display Unit (DU) is overheated.
DU 3-4 OVHT Amber #3 and/or #4 Display Unit (DU) is overheated.
DU1-2 FAN FAIL White #1 and/or #2 Display Unit (DU) cooling fan
has failed.
DU3-4 FAN FAIL White #3 and/or #4 Display Unit (DU) cooling fan
has failed.
Pilot’s Manual
5-42 PM-132A
PRIMARY FLIGHT DISPLAY (PFD)
The PFD (DU #1 and DU #4) is a single display in which all of the required
flight and navigation data is displayed for each pilot. The PFD
(Figure 5-10) format is divided into two main sections. The top half displays
an Attitude Director Indicator (ADI) with an airspeed tape to the
left, and a barometric altitude tape to the right. A Horizontal Situation
Indicator (HSI) is located on the lower half of the PFD. The HSI can be
displayed in three different formats. The three options are full 360°
compass rose (HSI), a 120° compass arc display (ARC), and a 120° map
display (MAP). The MAP cannot be displayed on the PFD if the adjacent
display (DU #2 or DU #3) is already displaying an MFD MAP format.
Weather information can be displayed on the PFD ARC or MAP
format. To the right of the HSI, a Vertical Speed Indicator (VSI) is displayed,
and to the left, navigation information is annunciated.
Comparison monitors provide indications to the pilots that there is a
difference between the data displayed on each PFD. This monitoring is
a function within the IC-600s that compares what is being displayed on
one side with either the cross-side displayed data or the secondary
source data. Should data be out of tolerance between what is being reported
from the source, and what is being sent to the display units, or
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