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Expanded Lateral
Deviation Flag
FLIGHT INSTRUMENTS
For Training Purposes Only
May 03
11-11
P I LOT T R A I N I N G GU I D E
The following Failure Flags are available:
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,
slip/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, analog decision
height marker and digital
radio altitude
FLIGHT INSTRUMENTS
11-12 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
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 (TAT)
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 (AFCS), and
• Engine Indication and Crew Alerting System (EICAS)
The Air Data System contains the following subsystems:
• Pitot-Static System
• Temperature Sensing System
• Air Data Computer System (ADC)
• Air Data Reference Panels (ADRPs)
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.
FLIGHT INSTRUMENTS
For Training Purposes Only
May 03
11-13
P I LOT T R A I N I N G GU I D E
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.
Pitot-Static Systems
Figure 11-8
Standby
ALT
Standby
ASI
P604_11_027
P1 S1
NO. 1
ADC
CENTER
INSTRUMENT PANEL
Pilot's Pitot Pressure
Copilot's Pitot Pressure
Pilot's Static Pressure
Copilot's Static Pressure
LEGEND
Pitot Pressure
Static Pressure
TAT Probe Line
CABIN PRESS CTRL
S3
STANDBY
PITOT
(P3)
PILOT’S
PITOT-STATIC
(P1S1)
LEFT
STATIC PORT
(S3)
RIGHT
STATIC PORT
(S3)
COPILOT’S
PITOT-STATIC
(P2S2)
TAT PROBE
S2 P2
NO. 2
ADC
CPAM
S3
S3 S3
P3
FLIGHT INSTRUMENTS
11-14 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
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
　
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