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GF0510_012
Rev 3, Apr 25, 2005 Flight Crew Operating Manual Volume 2
PROTECTIVE SHUTDOWNS
The FADEC will automatically shut down the APU when any of the following are detected:
SHU DOWN CONDITIONS GROUND FLIGHT NOTE: An X in one or both right columns indicate when shutdown can or will occur. FADEC Failure . Internal failure.
X Inlet Door . Not in commanded position. X
X Loss of Overspeed Protection . Loss of any combination of X speed sensors, FADEC overspeed circuitry or fuel solenoid that results in a loss of both overspeed systems. Overspeed . APU speed greater than 106%. X Loss Of Speed . Loss of both APU speed signals. X X Fire . Fire input signal received by FADEC. DC Loss . Loss of DC power to the FADEC. X Slow Start . No crank, slow start, no acceleration, no flame or X X fallback (Starter cutout speed and subsequentially drops below 25%). High Oil Temperature . Oil temperature limit exceeded. X Low Oil Pressure . Low oil pressure condition detected. X LOP Switch Fail . Low oil pressure switch failed. X Loss of Both EGT Sensors . Failure of both EGT X thermocouples. Reverse Flow . APU inlet temperature exceeded. X Underspeed . APU drops below 80%. X X Overtemperature . EGT exceeds scheduled limits.
X
Volume 2 Flight Crew Operating Manual Rev 3, Apr 25, 2005
SYSTEM OVERVIEW SCHEMATIC
BLEED AIR/ANTI-ICE SYNOPTIC PAGE
ENVIRONMENTAL CONTROL SYSTEM
LOAD CONTROL VALVE
EGT RPM
ON OFF
GF0510_014
GENERATOR OUTPUT
TO BUS DISTRIBUTION
Rev 3, Apr 25, 2005 Flight Crew Operating Manual Volume 2
AUXILIARY POWER UNIT
ELECTRICAL POWER AND DISTRIBUTION
The electrical control of the APU consists of electrical sensing, starting, ignition and the electronic control system through the FADEC.
APU electrical power may be used in flight or on ground. Electrical power is extracted from the APU in the form of horsepower which drives the APU generator and may be used to feed the airplane electrical power system.
Under high electrical load demands, the APUs electrical loads take priority over pneumatic load demands.
The FADEC is mounted remotely from the APU in a compact enclosure located in the aft equipment bay.
The FADEC is powered up when the BATT MASTER switch is selected ON. The BATT MASTER switch powers the airplane battery bus, which provides electrical power to the FADEC.
The FADEC uses the APU acceleration rate to calculate when to de-energize the starter motor and the ignition exciter. The values shown (START CONTROL SCHEMATIC below) are the maximum speeds at which the starter motor and the ignition exciter are permitted to operate.
START CONTROL SCHEMATIC
The FADEC control outputs include fuel metering, arming and regulation of the LCV and control of the surge valve. It also performs protective shut downs when the APU is not within allowable operating limits.
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