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1 2
1 2
QTY
ENG
APU
RES
OIL (QTS)
APU DOOR 11.2°
RPM EGT
BRAKE TEMP
11.5
100 650
03 06 03 03
11.5
5.2
6.0
%
% %
1300
0.00
0
0
90
13 13
20
19 20
22 22
20
OXYGEN
AFT
CABIN (°C)
FWD
CABIN (°C)
CKPT (°C)
OPEN OPEN
OUTFLOW VALVES
CAB ALT
P
CAB RATE
LDG ELEV
0 0
1 2
1 2
1 2
QTY
ENG
APU
RES
OIL (QTS)
APU DOOR 11.2°
RPM EGT
BRAKE TEMP
11.5
100 650
03 06 03 03
11.5
5.2
6.0
%
% %
TOTAL FUEL (LBS) 4155O
1.54
146OO 1OOOO 146OO
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4
575O
115
81
1.65
CRZ
EPR
I
G
N
START START
I
G
N
ND
STAB
1.54
1.65
73.3
T/O
N1
SYNC
73.3
789
ITT
SYNC
789 DN DN DN
OUT
3O
GEAR
–TRIMS–
NL RUDDER NR
AIL
LWD RWD
7.2
NU
93.4
575O
115
81
235O
NO TAKEOFF
PARK/EMER BRAKE ON
END
TOTAL FUEL (LBS) 4155O
1.54
146OO 1OOOO 146OO
N2
FF (PPH)
OIL TEMP
OIL PRESS
93.4
575O
115
81
1.65
CRZ
EPR
I
G
N
START START
I
G
N
ND
STAB
1.54
1.65
73.3
T/O
N1
SYNC
73.3
789
ITT
SYNC
789 DN DN DN
OUT
3O
GEAR
–TRIMS–
NL RUDDER NR
AIL
LWD RWD
7.2
NU
93.4
575O
115
81
235O
NO TAKEOFF
PARK/EMER BRAKE ON
END
For Training Purposes Only
Sept 04
7-41
P I LOT T R A I N I N G GU I D E
ELECTRONIC DISPLAY SYSTEM
FLIGHT DATA RECORDER
EICAS channels aircraft systems data (including altitude, airspeed, heading,
acceleration, and radio communications events) to the Flight Data Recorder (FDR).
DAU 4 gathers sensor data for transmission to the FDR.
DAU 4 is fully self-monitoring and provides CAS messages in the event of a failure. If
DAU 4B channel fails, FDR information is not available.
To record an additional event, in the FDR, push the PILOT EVENT button on the
landing gear control panel located on the pedestal. Pushing the PILOT EVENT will
also encode the Central Aircraft Information Maintenance System (CAIMS).
CENTRAL AIRCRAFT INFORMATION AND MAINTENANCE SYSTEM (CAIMS)
The CAIMS collects diagnostic and fault data from other airplane systems. From this
data, the CAIMS assembles a fault record that can be used to monitor system
performance during the flight. Maintenance personnel use CAIMS to accomplish
system tests and to isolate defective components.
The CAIMS supplies fault data during all phases of airplane operation through the
Portable Maintenance Access Terminal (PMAT) touch screen located in the passenger
cabin. The PMAT hard-disk contains approximately 8 MB of operational software
files and 25 MB of loadable diagnostic files. A CD-ROM of the Aircraft Maintenance
manual (AMM) can be installed in the PMAT CD-ROM drive.
The crew has the option of monitoring the PMAT display for active faults and/or may
print the report on the cockpit printer. For more information on the printer, refer to
chapter 5 COMMUNICATIONS.
The CAIMS is comprised of the following components:
• PMAT (located in the cabin)
7-42 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
ELECTRONIC DISPLAY SYSTEM
• DATA UPLOAD/DOWNLOAD switch and PRINT MAINT REPORT switch
(located on bulkhead behind pilot)
Honeywell
Power
Switch
Mode / Fault
Annunciation
3.5" Disk Drive
Access Port
POWER FAULT
HARD
DRIVE
OVER
TEMP
PORTABLE MAINTENANCE
ACCESS TERMINAL
AM-200
GX_07_035
Honeywell International Inc.
HoneywellInternational Inc.
AM–200
AM– 200
CD ROM Drive
Access Port
For Training Purposes Only
Sept 04
7-43
P I LOT T R A I N I N G GU I D E
ELECTRONIC DISPLAY SYSTEM
UP
DN
DN LCK
RELEASE
NOSE STEER LDG GEAR
HORN
BTMS OVHT
WARN RESET
EVENT
ARMED
OFF
RMED
MUTED
PRINT MAINT
REPORT
DATA
　
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