R Mod : (3832 or 8259) + (3952 or 4890 or 5021 or 5022)
ATR 42 Model : 400/500
AIR DATA SYSTEM
FLIGHT INSTRUMENTS
P 1
NOV 01
150
1.10
.
10
10.1 DESCRIPTION
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, MFC, GPWS, pressurization, AFCS, ATC 1 and
ATC 2 through TCAS control box, and TCAS through ATC 1 and ATC (if installed and
mode S only).
ADC 2 supplies :
- F/O flight instruments (altimeter, airspeed ind., vertical speed ind.),
- other systems : AHRS 2, FDAU, MFC, pressurization, AFCS, ATC 1 and ATC 2
Note : If ATC 2 mode S is installed, ADC 2 supplies TCAS through ATC 1 and ATC 2
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.
These supply raw data directly to the standby airspeed ind. and the standby altimeter.
AA
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