T-45A UJPT, E2-C2, ADV, & IUT Eng-19
Flight Instruments
a.
Airspeed measured as relationship
between pitot RAM pressure and static
pressure
b.
Mach information: derived as a
function of indicated airspeed and
pressure altitude as determined by an
aneroid capsule that drives the rotating
Mach scale
c.
Moving Mach scale viewed through
window in fixed dial
d.
Pointer indicates airspeed and Mach
e.
Front cockpit altimeter provides
170 KIAS reference for wheels warning
light activation
f.
Rear cockpit altimeter provides
217 KIAS reference for slats caution
light and yaw damper controller
activation
3.
Controls/switches/indicators: none in
cockpit
4.
Subsystem interfaces
a.
Power: 28 VDC generator bus (for
wheels warning and flight control
augmentation switch)
b.
Both indicators driven by same pitot
static system
c.
Internal switch in the forward cockpit
indicator set at 170 KIAS provides
wheels warning
d.
Internal switch in the aft cockpit
indicator set at 217 KIAS provides input
to the CONTR AUG system and slats
(8-03) Original
Page 19-5
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