T-45A UJPT, E2-C2, ADV, & IUT Eng-26
Engineering Review
NOTE: As long as the HYD 2
pressure gauge is cycling between
2,500 and 3,000 psi, the emer-
gency hydraulic system is func-
tioning and is producing hydraulic
pressure to power the flight con-
trols. Loss of HYD 2 fluid will
render the HYD 2 and the emer-
gency hydraulic system inopera-
tive. A subsequent loss of the
HYD 1 system will result in loss of
control of the aircraft.
NOTE: Sustained high-frequency,
high amplitude control inputs
during flight with RAT only hydrau-
lic pressure could result in loss of
aircraft control. Ejection outside
of the safe ejection envelope may
occur if control is lost during a
landing attempt.
2.
Exterior:
a.
Wheel brake/emergency flap
accumulator pressure gauge
b.
HYD 1 and 2 FC accumulator gauges
c.
HYD 1 and 2 hydraulic reservoir
gauges
d.
HYD 1 and 2 filter pin indicators
I.
Aircraft interfaces
1.
Inputs
a.
Electrical system: all WCP lights,
HYD 2 RESET button, and system
solenoid valves supplied by 28 VDC
essential services bus
Page 26-31
(8-03) Original
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