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• 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
Temperature (SAT) and the True Airspeed (TAS)/Mach number. This information is
displayed on the Primary Flight Displays (PFDs) and Multifunction Displays (MFDs).
Ice Protection is provided by electric heating elements.
Air Data Computers (ADCs)
The ADCs are digital, microprocessor-controlled units. The two ADCs receive on-side
pitot and static air pressure information from the pitot-static system and air
temperature information from the TAT probe.
The ADCs also receive operator/display selected input from the ADRPs and the
Automatic Flight Control System (AFCS). From these inputs, the ADC calculates all
necessary air data parameters and transmits the information to the applicable systems.
Air Data Calculations
The ADC calculates air data parameters for the following:
• Pressure altitude (corrected for static-port pressure errors)
• Barometric corrected altitude (inches of mercury or hectopascals)
• Vertical Speed
• Indicated airspeed (IAS)/Calibrated airspeed (CAS)
• Mach number
• Maximum airspeed (VMO/MMO)
• True airspeed (TAS)
• Static air temperature (SAT)
• Total air temperature (TAT)
Air Data Computations
The ADC computes data for the following:
• Preselect altitude
• Vertical speed reference
• Airspeed reference
• Mach reference
• IAS trend vector
• Secondary speed reference (V1, VR, V2 and VT)
• Flap overspeed limits (231, 197 and 189 Kts)
FLIGHT INSTRUMENTS
For Training Purposes Only
May 03
11-15
P I LOT T R A I N I N G GU I D E
Air Data Transmission
The ADC sends the computed air data to the following systems and components:
• Flight Data Recorder (FDR)
• Radio Tuning Unit (RTU)
• Mode S Transponder
• Traffic Alert and Collision Avoidance System (TCAS)
• Primary Flight Display (PFD)/Multifunction Display (MFD)
• AFCS
• IRSs
• DCUs
• Ground Proximity Warning System (GPWS)
• Horizontal Stabilizer Trim Control Unit (HSTCU)
• Stall protection computer
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