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Monitor the oil level on EICAS for both the engine and reservoir (example: if approximately 1 US quart is added to the engine, the oil replenishment tank level should have reduced by the same amount).
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When the engine reaches maximum level confirm that the “PUMP ON”legend on the oil replenishment panel goes out (indicating pump stops). Also confirm that the “VLV OPEN” legend on the oil replenishment panel goes out (indicating valve closed).
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It is recommended to manually stop replenishment when the gauge reads 11.0 quarts to avoidoverservicing.
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
POWER PLANT
The fuel system provides engine fuel for combustion, HP compressor Variable Stator Vanes (VSV) actuation and engine oil cooling.
The main components that are contained in the fuel system are as follows:
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Fuel Pump Unit . The fuel pump unit contains both the LP and HP pumps. Fuel supplied from the airplane fuel system passes through the (centrifugal type) LP pump, is pressurized and is delivered to the Fuel Cooled Oil Cooler (FCOC).
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LP Filter . Fuel from the FCOC enters the LP fuel filter, where any debris is trapped before proceeding on to the HP pump. The fuel filter contains a combined ΔP switch /indicator. The combined unit provides indications on EICAS of low pressure fuel or an impending LP fuel filter blockage. A FUEL FILTER (single) or L.R FUEL FILTER (both) message is displayed on EICAS. If a fuel low pressure switch is also provide to alert the crew of low fuel pressure in the supply line to the HP pump. A FUEL LO PRESS message will be displayed on EICAS.
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HP Fuel Pump . The HP fuel pump increase the pressure of the fuel for delivery to the Fuel Metering Unit (FMU).
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The FMU meters the fuel required by the engine in response to the Electronic Engine Controller (EEC) and provides pressure which is used as a motive force for the VSVs. The variable inlet guide vanes and the first three stages of stators of the HP compressor adjust the airflow entering the compressor to assist during engine starts, help prevent compressor surges and maintain best specific fuel consumption. The FMU also prevents fuel flowing to the fuel spray nozzles in the event of an engine overspeed and drains the fuel manifold into the drains tank on engine shut down. The desired fuel flow is maintained by controlling the position of the fuel metering valve. A constant pressure drop is maintained across the fuel metering valve by the spill valve, which diverts unused fuel back to the fuel pump. The spill diverter valve allows spill return fuel to the FCOC at low engine speeds to prevent fuel from recirculating around the HP pump, which could cause excessive fuel temperatures. The high pressure shutoff valve (HPSOV) allows the fuel to enter the HP fuel filter and is controlled by the FMU and the engine run switches.
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本文链接地址：庞巴迪环球5000公务机机组操作手册 Bombardier Global-动力装置(7)
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