Eagle ICA-D212-725, Instructions Manual

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ICA-D212-725 (79)
Page 3 of 10
CHAPTER 79 – ENGINE OIL SYSTEM (79-00-00)
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COPYRIGHT

2007 BY DART AEROSPACE LTD.
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THIS DOCUMENT IS PRIVATE AND CONFIDENTIAL AND IS SUPPLIED ON THE EXPRESS CONDITION THAT IT IS NOT TO BE USED FOR ANY PURPOSE OR COPIED OR COMMUNICATED TO ANY
OTHER PERSON WITHOUT WRITTEN PERMISSION FROM DART AEROSPACE LTD.
Revision:
0
Date: 07.05.31
79.1 Engine Oil System – General
Engine lubricating oil is supplied from a tank
mounted on the forward firewall at right side of
engine compartment. The oil flows to inlet port of
an engine-driven, dual-element pump on front of
the engine accessory gearbox. Oil is delivered
under a relatively constant volume and variable
pressure, maintained by a pressure relief valve
on the pump, to a filter on the left side of
accessory gearbox. Through a system of
external transfer tubes and internal passages,
the engine receives adequate gear and bearing
lubrication. A scavenge section of engine oil
pump directs oil through external lines to an oil
filter, then to the oil cooler. Depending upon
temperature of the scavenged oil, it is either
circulated through cooler or routed directly back
to oil supply tank through a bypass valve. (Refer
to Figure 79-1 for engine oil system
components.)
79.2 Engine Oil Cooler
A cooler for engine oil is mounted in the bottom
of the fuselage behind the engine, and is
connected into the oil return line through a
thermal bypass valve. Cooling air flow is
provided by a bleed air driven turbo blower.
79.2.1 Removal – Engine Oil Cooler
79.2.1.1
Drain oil cooler by opening
valve below cooler outlet. (Refer to Figure 79-1.)
79.2.1.2
Disconnect inlet, outlet, and
drain tubes ‘from cooler fittings and valve.
79.2.1.3
Remove four bolts and washers
at lower side flange to detach engine cooler from
support. Remove oil cooler.