R Mod : 3952 or 4890 or 5021 or 5022
ATR 42 Model : 400/500
AIR DATA SYSTEM
FLIGHT INSTRUMENTS
P 1
NOV 00
080
1.10
.
10
10.1 DESCRIPTION
(See schematic p. 9/10)
The flight environment data are provided by three independent air data systems :
- two main systems,
- one standby system.
MAIN SYSTEMS
Aircraft is equipped with two independent AIR DATA COMPUTERS (ADC). Each
computer is supplied with :
- static air pressure provided by its specific static ports,
- total air pressure provided by its specific pitot probe,
- total air temperature provided by its specific TAT probe.
Probes and ports are located on the LH and RH side of the fuselage and are electrically
heated.
From this data, each ADC computes :
- pressure altitude,
- vertical speed,
- Indicated Air Speed (IAS),
- True Air Speed (TAS),
- Total Air Temperature (TAT),
- Static Air Temperature (SAT).
ADC 1 supplies :
- CAPT flight instruments (altimeter, airspeed ind., vertical speed ind.),
- other systems : AHRS 1, FDAU, ATC 1, MFC, GPWS, pressurization, AFCS.
ADC 2 supplies :
- F/O flight instruments (altimeter, airspeed ind., vertical speed ind.),
- other systems : AHRS 2, FDAU, MFC, pressurization, AFCS and ATC 2 (if
installed).
EEC's, TAT/SAT/TAS indicator and GPS are supplied either by ADC 1 or ADC 2
according to ADC selector on capt panel.
STANDBY SYSTEM
The standby system consist of :
- two static ports,
- a pitot probe.
Standby airspeed ind. and standby altimeter are directly supplied by raw data.
AA
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