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Monitor the oil level on EICAS for both the APU and reservoir (example: if approximately 1 liter or 1 US quart is added to the APU, the oil replenishment tank level should have reduced by the same amount).
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When the APU reaches its designed level (between 4.5 and 5.5 qts.) confirm that the “PUMP ON”legend on the oil replenishment panel goes out (indicating pump stoppage). Also confirm that the “VLV OPEN”legend on the oil replenishment panel goes out (indicating valve closure).
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Select the “POWER”switch, “SYSTEM ON”legend extinguishes. Record the amount of oil added and a walk around for external leakage (oil overfill) should be carried out.
Rev 3, Apr 25, 2005 Flight Crew Operating Manual Volume 2
AUXILIARY POWER UNIT
FUEL CONTROL AND INDICATION
The fuel system is a fully automatic electronic control system. The fuel control unit provides metered fuel to 10 fuel dual orifice nozzles regulated by signals received from the FADEC.
During start, the fuel system provides the correct amount of fuel to support combustion and for smooth acceleration of the engine to full rated speed. Once rated speed is reached, fuel flow is modulated as necessary to meet the demands of varying pneumatic and electrical loads, while maintaining a constant speed.
Airframe Fuel
Fuel is normally supplied to the APU from the right engine feed line or from the left engine feed line by opening the crossfeed shutoff valve. The left example below represents APU start operation with battery electrical power. The right example below represents APU on-speed operation with AC electrical power. For further information on the airframe fuel system operations, refer to the FUEL SYSTEM Chapter of this manual.
CROSSFEED PRIMARYSHUTOFF
AUXILIARY PUMP PUMPS
VALVE
engines running:The right PRI pumps feed the APU through the right engine feed line.
FGF0510_001
Volume 2 Flight Crew Operating Manual Rev 3, Apr 25, 2005
FUEL CONTROL AND INDICATION (CONT'D)
Ignition
The ignition system consists of a dual output ignition unit, two (2) ignition leads and two (2) igniter plugs. There are two cycles of operation: “BURST”for starting (at 5%) and “MAINTENANCE”for acceleration (duration of the start).
The ignition system is fully automatic and controlled by the FADEC. Ignition occurs at 5% APU RPM.
During APU operation in non-essential mode (ground operation), ignition is terminated at 50% RPM. During essential mode (in flight), ignition is terminated at 98% RPM.
Should flameout occur during operation, the ignition unit will automatically start through the “Auto Relight”function of the FADEC.
Start System
Operation of the starter is automatically controlled by the FADEC, through the APU control switch.
Starter operation begins by selecting the START position on the APU control panel. At sea level, starter cutout occurs at 46%. At altitude, starter cutout may be as high as 60% APU RPM to ensure a positive start.
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