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RES
RPM EGT
10.4
22
1300
85 %
0.00
20
100 400
4.5
5.0
10.4
CKPT (5C)
OXYGEN
CAB ALT
CAB RATE
P
FWD
APU
RWD
CABIN (5C)
AFT
CABIN (5C)
21
29
23
20
"1300
LDG ELEV 1000 TOC
3
KSRP
KPHX
WX SAT
GSPD
−56
TAT
TAS
−40
234
345
LX
HDG
330
ETE 1+36
KLAX
TOC KPHX
KDVT KSRP
4000 4000
FL180
12.5NM
KDVT
LUF
KDVT
5
N
5
360
TERR
OFF
30
6
33
VS 2000
180
220
210
200
170
160
150
0.88
0.856 M
190
FMS1
DTK
360
20
20
10
10
20
20
10
10
33
30
W
24
21 15
12
E
6
3
0
1
2
1
2
3
VAPP VNAV
HDG AP1 ASEL 10400
29.92 IN
H23.4NM
SRP
BARO
9500
10500
10000
HDG
330
3
1300
1000
S
N
185
6
4 0
1 2
13% 13 %
OPEN OPEN
OUTFLOW VALVES
EICAS provides display of:
· Primary engine parameters
· Fuel quantities
· Flaps/slats/spoilers positions
· Crew Alerting System (CAS) messages
· Secondary engine parameters
· Landing gear position
· Surface trim indication
SYSTEMS provides synoptics display of:
· Bleed/AntiIce
Air
· Hydraulics
· DC Electrical
· Flight Controls
· Air Conditioning
· AC Electrical
· Fuel
· Status
AURAL AND VISUAL WARNINGS
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
03−10−1
CENTRAL DISPLAY SYSTEM
The central display system provides crew with displays for aircraft control, navigation, engine control
and monitoring and systems synoptic. Other systems information provided for display are WX
display, TCAS, EGPWS and Lightning Sensor System (LSS) display.
Airplane data is transmitted from airplane systems to 4 dual channel, Data Acquisition Units (DAU),
through the Avionics Standard Communication Bus (ASCB), to 3 Integrated Avionics Computers
(IAC), to the Display Units (DU).
The 4 dual channel DAUs operate with one channel active and the other channel on standby, with
both channels updating data at the same time.
The ASCB is the principal communications network interconnecting the system components. Data
traffic flow on the ASCB is managed by 3 bus controllers (one bus controller in each IAC). Only one
bus controller is in control at a time, with the other 2 in standby status.
The three IACs, each contain a Symbol Generator (SG) and a Fault Warning Computer (FWC). The
SGs process data from various sources and output the data to the 6 DUs. The FWC compares
sensor input data, verifies all critical display data and displays warning, caution, advisory and status
messages as applicable.
DU 1 DU 2 DU 3 DU 4 DU 5 DU 6
The IACs perform the following functions:
IAC 1 IAC 2 IAC 3
EFIS, EICAS, FWC, CAIMS EFIS, EICAS, FWC, CAIMS EFIS, EICAS, FWC, CAIMS
Tone/Aural generator Tone/Aural generator LASERTRACK (if installed)
Flight Management System Flight Management System FMS 3 (if installed)
Autothrottle Autothrottle Autothrottle
AFCS AFCS AFCS
AURAL AND VISUAL WARNINGS
Flight Crew Operating Manual Rev 2A, Apr 11, 2005
CSP 700−5000−6
Volume 2
03−10−2
CREW ALERTING MESSAGES
The crew alerting system portion of EICAS continually monitors all airplane systems. If an
operationally significant fault occurs on a system, EICAS displays a crew alerting message on the
EICAS display unit. In addition to the display messages, some crew alerts are also indicated by aural
tones, voice advisories, MASTER WARNING and MASTER CAUTION lights.
All crew alerting system messages are divided into one of four categories and in the following priority:
Warning messages are generated when immediate recognition and corrective or
compensatory action is required. They are the most urgent type of crew alerts. They always
appear at the top of the message stack on the EICAS primary display. All warnings cause the
MASTER WARNING lights on the glareshield to flash and have an aural alert consisting of a
unique tone or a triple chime plus a voice advisory. Once acknowledged flashing stops.
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