T-45C TS, ADV & IUT ENG-19
Flight Instruments
4.
Subsystem interface: Both indicators use same pitot
static system
D.
Pitot tube
1.
Location: nose of aircraft
2.
Function: provides ram air pressure and static air
pressure to pitot static system
3.
Controls/switches/indicators: PITOT HEAT switch,
on right instrument panel outboard in forward cockpit
only, for ice protection
4.
Subsystem interfaces:
a.
Power: 28 VDC essential services bus
b.
Standby barometric altimeter
c.
Standby airspeed indicator
d.
Standby vertical speed indicator
e.
Stability Augmentation Data Sensor (SADS)
f.
OBOGS
E.
Summary:
The pitot static system measures the static air pressure,
rate of change of static air pressure, and the difference
between pitot air pressure to provide airspeed, altitude,
and rate of climb information for the system. Standby
flight instruments receiving pitot static input are the
standby altimeter, standby airspeed indicator, and the
standby VSI
Original (9-98)
Page 19-15
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