I A P 2 0 2 3 . 0 0 1 - A F M / I R I S T E X A N I I P A G E | 82
FOR SIMULATION USE ONLY – NOT A TRAINING AID
AIR DATA COMPUTER (ADC)
The ADC receives pitot/static air inputs and calculates airspeed, altitude, and climb
rate parameters for use by the primary flight display and navigation multifunction
display.
The ADC includes a configuration module which contains VMO/MMO data. The ADC
is automatically powered up when the avionics master switch is set to ON.
Power for the air data computer is provided through a circuit breaker, placarded
ADC, located on the generator bus circuit breaker panel in the front cockpit.
The ADC provides air data outputs to the following instruments/ systems:
IAC 1 and IAC 2
ATC transponder
Integrated data acquisition recording system (IDARS)
Inertial Reference System (IRS)
Trim aid device (TAD)
Traffic collision advisory system (TCAS)
Power management unit (PMU)
The ADC transmits air data outputs over multiple data buses, using ADC A or ADC B
channels. If an output is bad, or if either data bus channel fails, an amber ADC A or
ADC B FAIL status illuminates on the EICAS display.
If the ADC fails, a warning on the EICAS display displays ADC FAIL in red text.
TOTAL AIR TEMPERATURE
A heated total air temperature (TAT) probe is mounted on the underside of the left
wing inboard of the pitot tube. The TAT probe provides air temperature input to the
ADC that in turn provides airspeed, altitude, and vertical speed information used by
the integrated avionics system and displayed on the multifunction displays.
The TAT probe is heated when PROBES ANTI-ICE switch is in the ON position.
Power for TAT heat is provided by a circuit breaker placarded TAT HT on the front
cockpit generator bus circuit breaker panel.
NOTE
Avoid sustained ground operations with the PROBES ANTI-ICE switch ON.
Sustained ground operation with the PROBE ANTIICE switch ON may result in
a true airspeed (TAS) failure indication on the MFDs due to a TAT probe
overheat condition that prevents reliable TAT information to the ADC.
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