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Cockpit indications remain quiet and dark during the following:
- Normal operation (no abnormalities or failures)
- Daylight
- Visual meteorological conditions (VMC)
- Non-icing conditions
- Cruise flight
Color Logic is used to depict system values:
- Red — Warning condition or system limit exceeded
- Amber — Component or function failed or there is no flow, energy or pressure
- Green — Normal operation for digital values. Normal flow, energy or pressure in flowlines
- White — Normal status of component (pump, valve, etc.) or no flow through the flowline
- Magenta — Invalid or unknown data
REV 1
CFO0302002_ 004
WARNING
CAUTION
WARNING
CAUTION
0
ANTI-ICE
AURAL/VISUAL ALERTS
Volume 2 Flight Crew Operating Manual Sep 13/2004
03-02-02 CSP 100-6 REV 1
COMPONENTS AND OPERATION
DISPLAYS
The PFDs and MFDs are computer controlled liquid crystal adaptive flight displays (AFDs). All four displays are identical
and interchangeable.
DISPLAY LIGHTING ADJUSTMENT
Two separate concentric knobs (PFD and MFD) adjust display lighting intensity on the COCKPIT LIGHTS panel. They
are located on the left and right side panels.
DISPLAY COOLING
Cooling and ventilation of the PFD and MFD displays is achieved by the cockpit air distribution system. The avionics cooling
fan and cockpit air conditioning systems is designed to maintain the ambient temperature of the displays.
DATA CONCENTRATOR UNITS
The two data concentrator units (DCU A and DCU B), are essential to the EICAS. The DCUs collect data from various
aircraft systems, process the information and relay it to the proper component or display.
SYSTEMS TEST CONTROL PANEL
DESCRIPTION
The SYSTEMS TEST control panel is installed in the center pedestal. The switch is used to start a pilot initiated test of
several systems. The switch is momentarily pushed to start the applicable test.
The aural warnings other than TCAS and TAWS occur in sequence of importance. Once the test has started, the switch may
be released. Pressing the switch again will cancel the test.
COMPONENTS AND OPERATION
Selecting ANUN A or ANUN B on the SYSTEMS TEST panel and pressing and holding the switch for 15 seconds illuminates
all panel lights and gives the aural warnings as follows:
- Triple or single chimes
- Aural warning tones
- Voice alarms
The other systems tests are as follows:
- PROBES — tests air data probes and sensors
- STALL RUD/LIM — tests the stall protection system
- ICE DET — tests the ice detection system
- FIRE DET — tests the fire detection and extinguishing (FIREX) system
- TAWS — tests the terrain avoidance warning system
SYSTEMS TEST
ANNUN A
CFO0901002_010
PUSH
TO
TEST
OFF
ANNUN B
PROBES
STALL/RUD LIM
TAWS
FIRE DET
ICE DET
AURAL/VISUAL ALERTS
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 03-02-03
ENGINE INDICATING AND CREW ALERTING SYSTEM (EICAS) (Cont)
CFO0302002_008
RIGHT
AIRCRAFT
SYSTEMS
RDC
CHANNEL B
B-RDC-2 (HS)
RDC A-RDC-1 (HS)
CHANNEL A
A-RDC-2 (HS)
A-RDC-9 (HS)
A-RDC-10 (LS)
INTERIOR
DISCONNECT
STATION
LEFT
AIRCRAFT
SYSTEMS
B-DCU-6
DCU
CHANNEL B
B-DCU-1 (HS)
A-DCU-8 (HS)
DCU
CHANNEL A
A-DCU-2 (HS)
A-DCU-5 (HS)
A-DCU-1 (HS)
A-DCU-6
B-RDC-1 (HS)
B-DCU-8 (HS)
B-DCU-2 (HS)
B-DCU-5 (HS)
RADIO
INTERFACE
UNIT (RIU)
NO. 1
RADIO
INTERFACE
UNIT (RIU)
NO. 2
B-DCU-4
LB-RIU-6 (HS)
RB-RIU-6 (HS)
LAMP DRIVER
UNIT (LDU)
TO COCKPIT
B-LDU-1 LAMPS
A-LDU-1
L-GPBUS-5 (HS)
A-DCU-4
R-GPBUS-5 (HS)
A-DCU-FDR
FDR-1
FLIGHT DATA
RECORDER
(FDR)
RH IOC
LH IOC
PFD NO. 2
MFD NO. 2
MFD NO. 1
PFD NO. 1
RA-FADEC-1 (LS)
RB-FADEC-1 (LS)
LA-FADEC-1 (LS)
LB-FADEC-1 (LS)
GENERAL
AIRCRAFT
SYSTEMS
FADEC
SYSTEM NO. 1
IAPS CARD
CAGE
FADEC
SYSTEM NO. 2
DCP CCP
AURAL/VISUAL ALERTS
Volume 2 Flight Crew Operating Manual Sep 13/2004
03-02-04 CSP 100-6 REV 1
ENGINE INDICATING AND CREW ALERTING SYSTEM (EICAS) (Cont)
MASTER WARNING/MASTER CAUTION SWITCHES
The master warning/master caution switches are located on the glareshield. When the DCUs generate a warning message,
the master warning half of the two switches flash red. A triple chime accompanies the master warning lights. In addition,
　
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