Rotation of the engine-driven oil pump draws
oil from the reservoir. Oil under pressure
flows through a pressure regulator, filter
and temperature control components to the
engine bearings, the transfer gearbox, ac-
cessory gearbox and the front fan planetary
gear assembly.
The reservoir has a liquid level sight gage and
a filler cap on the right side of the tank. A filler
tube and cap are located on the left side of the
tank which allows for oil tank replenishing when
access to the right side is restricted.
Oil Pump Assembly
An oil pump assembly is located on the ac-
cessory drive gearbox. It contains a single oil
pressure pump and four scavenge pumps.
The pressure pump draws oil from the reser-
voir and supplies sufficient pressure to force
the oil through the engine components that
require lubricating.
The scavenge pumps collect oil from the plan-
etary gear assembly and the forward engine
bearings, the aft engine bearings, the transfer
gearbox and the mid engine bearings, and the
accessory drive gearbox. A common discharge
line connects the four scavenge pumps to the
engine oil reservoir.
An adjustable pressure regulator in the pumps
helps to provide a constant oil pressure by com-
pensating for changes in the aircraft altitude.
Oil Filter
A filter is provided to remove impurities from
the oil. The oil filter consists of a disposable
element enclosed in a metal housing on the
right side of the accessory drive gearbox.
Oil Tank
A 1.65 U.S. gallon capacity oil reservoir is
located on the right side of the engine fan by-
pass housing.
Engine protection against filter clogging is
provided by an oil filter bypass indicator valve
located adjacent to the oil filter. The valve
opens when the pressure drop across the fil-
ter is excessive to bypass lubricating oil around
the filter.
An integral differential (
∆
P) pressure indica-
tor on the valve visually flags a clogged filter
condition before bypassing occurs. A thermal
lockout device on the
∆
P indicator prevents ac-
tuation under cold oil conditions although the
bypass valve will bypass oil under these con-
ditions.
Fuel Heater
An externally mounted fuel heater is located
on the left side of the engine. The fuel heater
provides oil-to-fuel heat exchanging to prevent
ice formation in the fuel system from clogging
the fuel filter and any other components.
Fuel flow through the fuel heater is thermo-
statically controlled to provide the optimum op-
erating temperature. Excess oil pressure with
cold oil is prevented by a pressure bypass valve.
Air/Oil Cooler
After oil leaves the fuel heater, it passes through
the air/oil coolers in the engine bypass duct. The
air/oil cooler consists of three segments: one
half segments and two quarter segments.
Each segment is a finned unit with oil lines
running through it. Together the three seg-
ments form the inner surface the fan duct. A
temperature controlled integral bypass valve
directs oil that is hotter than 65° C through the
three segment of the air/oil cooler. Air flow-
ing through the duct cools the oil that passes
through the cooler. Below this temperature, the
valves bypass the oil around the air/oil cooler.
Revision 1
7-7
FOR TRAINING PURPOSES ONLY
HAWKER 800 XP
PILOT TRAINING MANUAL
FlightSafety
international
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