Air Data Computers (Adcs); Adc Reversion - BOMBARDIER LEARJET 40 Pilot's Manual

Pilot's Manual

AIR DATA COMPUTERS (ADCs)

The Learjet 40 utilizes two, independent micro air data computers as
the primary source for air data. The is a self contained unit incorporat-
ing pressure sensing modules and all required processing and input/
output functions in a single unit. Each computer is independent of the
other and has independent circuit breakers.
The air data system provides the required airplane airspeed, air tem-
perature, altitude and vertical speed data for the Electronic Flight In-
strument System (EFIS) displays, Attitude and Heading Reference
System (AHRS), dual stall warning system, autopilot, transponders,
spoileron computer, cabin pressurization, Digital Electronic Engine
Control (DEEC) and landing gear warning system as required. The Air
Data System (ADS) accepts static air pressure, total air pressure, total
air temperature, various discrete signals and baro set inputs. The #1
and #2 ADCs receive power from the L and R ESS BUS respectively,
through ADC 1 and ADC 2 circuit breakers. The circuit breakers are lo-
cated on the pilot's and copilot's circuit breaker panels (INSTRU-
MENT/INDICATIONS group).

ADC REVERSION

Display of the ADS data on the EFIS display is controlled by the pilot
or copilot via the ADC reversionary control switch (Figure 5-14). The
reversionary control panel, located below the EICAS display (DU#2),
incorporates an ADC reversion switch which has three positions, 1 -
ADC NORM - 2. In the ADC NORM position, the IC-600s receive air
data from their on-side ADC. In the "1 or 2" position both IC-600s re-
ceive air data from the selected source. If the switch is not in the NORM
position, an annunciator of the selected source is displayed above and
to the left of the ADI on both PFDs.
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PM-132A