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Radar Altimeter Deviation Limits Graph
Figure 11−10−5
Comparator Indications and EFIS Failure Displays
The comparator warning icon on the PFD will remain displayed while the condition exists. If the
comparator monitor fails, the amber EFIS COMP MON INOP caution EICAS message is
displayed, and the flashing MASTER CAUTION lights will be triggered.
FLIGHT INSTRUMENTS
Description
Vol. 2 11−10−8
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS) (CONT'D)
PFD Comparator Annunciations
Figure 11−10−6
The failure of a selected source removes the respective scale or display and presents a red flag.
PFD FAilure Displays
Figure 11−10−7
The following failure flags are available:
FLIGHT INSTRUMENTS
Description
Vol. 2 11−10−9
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS) (CONT'D)
Failure Flags
FAILURE FLAG LABEL MEANING ITEMS REMOVED FROM DISPLAY
ALT Air data computer failure
Barometric altitude tapes, digital
altitude readout, preselected
altitude reference, digital preselect
altitude, metric altitude readout and
metric preselected altitude.
ATT Inertial reference system failure
Sky/ground raster, pitch tape, roll
pointer, roll scale, skip/skid indicator
DCP Display control panel failure Flight director bars
MAG, TRK, TRU
Heading sensor input failure
Inertial reference system failure
The heading display is not removed,
but the heading is not updated.
FD Flight director failure Flight director bars
FMS/GS/LOC/VOR
Respective navigation system
failure
Flight director bars
Lateral deviation scale
Red boxed Nav source
GS Glideslope failure Vertical deviation scale and pointer
IAS Air data computer failure Airspeed tape and information
VS Air data computer failure
Vertical speed scale pointer, digital
readout
RA Radio altimeter failure
Analog radio altitude symbology,
analogy decision height marker and
digital radio altitude
AIR DATA SYSTEM
The air data system (ADS) uses air pressure and temperature information to calculate all of the
parameters related to flight. It supplies the following information to EFIS for display:
• Altitude (ALT);
• Indicated airspeed (IAS);
• Vertical speed (VS);
• True airspeed (TAS);
• Static air temperature (SAT); and
• Total air temperature.
The ADS also provides computed data to:
• Inertial reference system (IRS);
• Flight data recorder (FDR);
• Stall protection and flap systems;
• Air traffic control (ATC) transponders;
• Traffic collision avoidance system;
• Automatic flight control system; and
FLIGHT INSTRUMENTS
Description
Vol. 2 11−10−10
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
AIR DATA SYSTEM (CONT'D)
• Engine indication and crew alerting system (EICAS).
Pitot-Static System
The pitot-static system includes:
• Two main pitot-static systems
• One standby pitot-static system
The two main pitot-static systems, designated P1/S1 and P2/S2, supply variable pressure inputs to
the ADCs. The pitot pressure is sensed through an opening in the forward end of the pitot heads.
The static pressure is ported through eight holes on the contoured midsection of the pitot head.
Each static port consists of four holes; two on the upper side and two on the lower side of the pitot
head. The S1 static port holes are forward and the S2 holes are aft along the pitot head. The
contoured surface provides aerodynamic compensation to correct static pressure position error.
The P3 standby pitot system supplies pitot air pressure to the standby airspeed indicator. Two S3
standby static ports supply static pressure to the cabin pressure acquisition module (CPAM), cabin
pressure controller, standby airspeed indicator and standby altimeter.
Ice protection is provided by electric heating elements for all pitot-static probes.
FLIGHT INSTRUMENTS
Description
Vol. 2 11−10−11
REV 66, Feb 01/07
CL−604 Operating Manual
PSP 604−6
AIR DATA SYSTEM (CONT'D)
Pitot−Static Systems
Figure 11−10−8
Temperature-Sensing System
The temperature-sensing system receives data from a total air temperature (TAT) probe. The
ADCs use the outputs from the probe to calculate the static air temperature (SAT) and the true
　
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