After exiting the oil pump, the pressurized oil
passes through a filter located on the aft right
side of the accessory gearbox. A filter by-
pass valve is provided as an alternate flow
path around the filter to allow uninterrupted
oil flow should the filter become obstructed.
If differential pressure on the inlet port and out-
let port of the filter exceeds a preset amount,
impending bypass is indicated and a switch
will close initiating a “L/R OIL FILTER” mes-
sage on the CAS (Figure 7-23).
An amber “L or R OIL FILTER” CAS message
will appear if oil filter bypass is impending
while on the ground. If oil filter bypass is im-
pending while in flight, the CAS message will
be white. An additional increase of approxi-
mately 5 PSID will cause the oil to actually by-
pass the filter. If it comes on inflight, moni-
tor oil pressure and temperature, while refer-
ring to the AFM.
After the oil passes through the filter (Figure
7-22), it is routed through three sections of
finned air-oil coolers located in the engine
bypass duct. A temperature control/bypass
valve will cause oil to flow through the finned
air-oil coolers when the oil is hot and bypass
the coolers when the oil is cold.
That portion of the oil that is dispensed to the
fan reduction gearbox (planetary gears), the
transfer gearbox, and to bearings #4 and #5 is
routed through the fuel heater/oil cooler
(FHOC) (Figure 7-22). This heat exchanger
provides for additional oil cooling and for
LEARJET 45 PILOT TRAINING MANUAL
7-30
FOR TRAINING PURPOSES ONLY
FlightSafety
international
NO. 4 AND NO. 5
NO. 4 AND NO. 5
NO. 6 BEARING
NO. 6 BEARING
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