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• It is recommended to manually stop
replenishment when oil quantity
reaches 11.0 quarts.
17-18 For Training Purposes Only
Sept 04
P I LOT T R A I N I N G GU I D E
POWER PLANT
OIL REPLENISHMENT SCHEMATIC
The following procedural steps outlined are to be used only as a guide to replenish the
engine oil system. The Airplane Maintenance Manual takes precedence over all
servicing procedures.
• Select the POWER switch on the oil replenishment panel, SYSTEM ON legend on
• Confirm that the LO OIL lamp on the oil replenishment panel corresponds to the
condition indicated on EICAS L-R OIL LO QTY caution message (if message
present)
• Select the switch labeled LH or RH ENG on the oil replenishment panel
• Confirm that the PUMP ON (below reservoir label) and VLV OPEN (below the
engine to be filled) legends are displayed on the oil replenishment panel
• Monitor the oil level on EICAS for both the engine and reservoir (example: if
approximately 1 liter or 1 U.S. quart is added to the engine, the oil replenishment
tank level should have reduced by the same amount)
• 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)
• It is recommended to manually stop the replenishment when the gauge reads 11.0
quarts to avoid overservicing
OIL REPLENISHMENT
RESERVOIR
TANK
LO
PUMP
ON
LH ENG APU RH ENG
POWER
SYSTEM
ON
LO
OIL
LO
OIL
LO
OIL
VLV
OPEN
VLV
OPEN
VLV
OPEN
GX_17_036
LH ENGINE FADEC RH ENGINE FADEC
APU FADEC
EICAS/
CAIMS
DC MOTOR
DAU 3
Left Engine Oil Tank
Oil Quantity
Transmitter
Airframe-
Mounted
Oil Tank
Airframe-
Mounted
Oil Tank
Probe
Oil Quantity
Transmitter
APU Oil
Tank Check Valve
DRAIN
A/C
Fuselage
Skin
Selector
Valve
Engine Pylon Firewall Right Engine
Oil Tank
Oil
Replenishment
Pump
Filter
Cap
Relief
Valve
For Training Purposes Only
Sept 04
17-19
P I LOT T R A I N I N G GU I D E
POWER PLANT
ENGINE FUEL SYSTEM
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:
• 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)
• 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
DP switch/indicator. The combined unit provides indications on EICAS of low
pressure fuel or an impending LP fuel filter blockage. A FUEL FILTER message
will be displayed on EICAS. A fuel low pressure switch is also provided 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
• HP Fuel Pump - The HP fuel pump increases the pressure of the fuel for delivery
to the Fuel Metering Unit (FMU)
• 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 drain tank on
engine shutdown. 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
• Fuel Flow Transmitter - Provides an indication of fuel flow to the EEC and to
　
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