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CABIN TEMP
BLEED PRESS
FUEL TEMP
ENGINE
BULK
OXY
C ALT
RATE
P
50
20
48
70 75
-20
2000
3200
200
SPOILERS -0.5
APU
95 430
RPM EGT
P604_03_001
BRT BRT
85.0 85.0
HOT
925 750
N1
90.0
ITT
N2
GEAR DISAGREE
AUTO PRESS
DN DN DN
- GEAR - - FLAPS -
C ALT
STAB
RATE
- TRIM -
P
3200 200 -0.5
20
NU
ND
4.0
RUDDER
AIL
LWD RWD
NL NR
FF
OIL PRESS
OIL TEMP
FAN VIB
7160 4870
20000
4.2
115
82
3500
3140
- FUEL QTY - TOTAL
3500
82
165
1.2
4870
75.0 95.0
VIB
REV APR
PRI STAT STEP CKLST RCL EMER
HYD ELEC L
MFD
R
MFD
SEL/AUTO
CAS F/CTL SKP/3D
UP/PLAN
DN/SIDE
M
P604_03_002
AURAL/VISUAL WARNING
For Training Purposes Only
May 03
3-3
P I LOT T R A I N I N G GU I D E
Engine Indicating and Crew Alerting System (EICAS)
Description
The function of the EICAS is to display the engine instruments and to provide visual
and aural crew-alert messages and real-time interpretation of aircraft system operation.
Two EICAS displays present the data on different selectable display pages. Some
display pages are shown by default, others are available through crew selection. The
EICAS control panel (ECP), located on the center pedestal, controls the displayed
information.
Engine indications are provided on the EICAS primary page. Color is used to depict
normal and non-normal ranges of operation.
The Crew Alerting System (CAS) provides visual and aural alerts as determined by
the Data Concentrator Unit (DCU) upon occurrence of a malfunction. The CAS
prioritizes messages by order of occurrence and order of importance.
Components and Operation
EICAS Control Panel
The EICAS control panel is located on the center pedestal. The panel remains
illuminated during a complete AC power failure and the PRI, STAT, STEP and CAS
keys remain operational.
EICAS Displays
The EICAS displays are computer-controlled video displays. EICAS display No. 1
(ED 1) is installed on the left of the center instrument panel and EICAS display No. 2
(ED 2) is installed on the right of the center panel (Figure 3-1).
The EICAS displays present system information on primary, status, synoptic and
menu pages. ED 1 displays the primary page by default. ED 2 is defaulted to the status
page. Page selection is accomplished via the ECP (Figure 3-2).
AURAL/VISUAL WARNING
3-4 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
Data Concentrator Unit (DCU)
The data concentrator unit is the heart of the EICAS. The DCU collects data from
various aircraft systems, processes the information and relays it to the proper
component or display. In a standard configuration, there are two DCUs installed in the
aircraft. They are designated DCU 1 and DCU 2. An optional third DCU can be
installed and is labeled DCU 3 as per service bulletin 604-31-001.
All DCUs share in providing information to the EICAS displays. Internal switching
logic determines how the information is provided by the two or three DCUs. If a
partial or complete failure of a DCU occurs, system redundancy ensures that no
displayed data is lost. In aircraft with the optional third DCU, an additional level of
redundancy is provided.
Data concentrator units receive inputs from the following systems:
• Engines
• Landing gear
• Flaps
• Spoilers
• Auxiliary Power Unit (APU)
• Flight controls
• Avionics
• Stall Protection System
• Ground Proximity Warning System (GPWS)
• Traffic Alert and Collision Avoidance System (TCAS)
• Crew Alerting System (CAS)
• Air Data Computer (ADC) altitude alerting
The DCUs process and format this information then transmit the data on the ARINC
bus to the following:
• EICAS displays
• Lamp Driver Unit (LDU)
• Audio Electronic Control Unit (AECU)
• Flight Data Recorder (FDR)
• Maintenance Diagnostic Computer (MDC)
The two-channel lamp driver unit receives information from the DCUs and controls
the associated panel and glareshield switch/light illumination.
When a DCU generates an EICAS message, the data is sent to the LDU. The LDU
then interprets the information and illuminates the switch/light on the appropriate
control panel.
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