With the airbrakes shut, proper reservoir fluid
level can be determined by sighting the fluid
level sight gage against the marks on the ad-
jacent indicating plate (Figure 13-3).
Air supply low pressure is indicated by the
HYD TANK pressure gage (Figure 13-5). The
gage should indicate approximately 15 psi.
OPERATION
When the right engine is started, the pump re-
ceives fluid through the suction filter and the
open on-off valve. As pressure increases to
1,750 psi, the amber HYD 2 LO PRESS an-
nunciator goes out (Figure 13-2). Increasing
pressure from the pump opens the pressure-
maintaining valve, and pressure is indicated
on the supply scale of the pressure indicator.
Normal system pressure will stabilize at 3,000
psi. The system is now capable of actuating all
subsystems.
As the left engine is started, the pressure out-
put of the left pump is added to the system
(Figure 13-2). The amber HYD 1 LO PRESS
annunciator goes out as pressure increases.
The system is now operating at full potential.
If either pump fails, the low pressure switch
operates when the pressure has fallen to 1,500
psi. The contact of the low pressure switch
causes the HYD 1(2) LO PRESS annunciator
on the roof panel to be lit, after an initial delay
of 57 seconds to allow the pressure to recover
should the low pressure condition be due to
system fluctuation rather than a malfunction.
If both pumps fail, or if system fluid is lost,
both low-pressure annunciators will come on,
but the pressure indicator will show 2,300 psi
(the pressure-maintaining valve has closed,
trapping pressure in the main accumulator for
normal brake operation). The landing gear
and flaps can be lowered with the auxiliary hy-
draulic system.
Two full-flow relief valves are provided, one
in each pressure line. In the event of pump fail-
ure (loss of pump pressure control), the asso-
ciated relief valve opens at approximately
4,000 psi to return fluid to the reservoir.
Leakage from any pressure line, suction line,
or system component will deplete system fluid.
Since there is no indication of decreasing fluid
level, fluid loss may not be noticed until the
pumps cavitate and the annunciators come on.
Leakage within a subsystem may be detected
by an abnormal drop in pressure as that sub-
system is actuated.
In the event system fluid overheat is indicated
by illumination of the HYD OVHT annunci-
ator, continue the flight. The fault must be
corrected prior to the next flight.
13-4
FOR TRAINING PURPOSES ONLY
HAWKER 800 XP
PILOT TRAINING MANUAL
FlightSafety
international
Figure 13-5. Reservoir Pressure Gage
Figure 13-3. Reservoir Pressurization and
Fluid Level Indication
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