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On the ground, the air inlet door has only two positions, closed or open (0 and 45
degrees). In flight, during APU start, the ECU limits the door position in response to
APU engine rpm and aircraft speed. This prevents excessive amounts of ram air which
could cause the APU to flameout. When the APU is not operating, the door remains
closed to prevent windmilling of the compressor. The inlet door also serves as a barrier
in the event of fire. The exhaust duct is composed of stainless steel and is centered in
the tailcone.
Vol. 1 04--30--2
AUXILIARY POWER UNIT
Systems Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
APU Controls and ECU Interface
Figure 04---30---1
PWR
FUEL
START/
STOP
APU
L
ENG
R
ENG
APU
BLEED SOURCE
BOTH ENG
LCV OPEN
EXTERNAL SERVICES
DC POWER 28 VOLTS
APU STARTER -- CONTACTOR
UNIT
ECU
AIR
T2 SENSOR
TO EDUCTOR
AIR/OIL COOLER
INLET DOOR ACTUATOR
INLET TEMPERATURE (T2)
INLET PRESSURE (P2)
BLEED FLOW
LOAD CONTROL
VALVE (LCV)
SURGE VALVE
LCV POSITION COMMAND (TORQUE MOTOR)
LCV POSITION (RVDT)
ON/OFF SURGE VALVE
INLET DOOR POSITION
EGT SENSOR
FUEL
NOZZLE
ASSEMBLY
IGNITION
EXCITER
APU
GEARBOX
STARTER
GEN
FUEL CONTROL
UNIT
OIL
PUMP
TORQUE MOTOR MET. VALVE
SPEED
IGNITION ON/OFF
IGNITION BUILT--IN TEST
EXHAUST GAS TEMPERATURE (EGT)
OIL/GEN. FILTERS DELTA P
STARTER VOLTS
LOP SWITCH
SPEED
SENSOR
INLET
AIR
P2 SENSOR
OIL TEMPERATURE
INLET
DOOR
APU GENERATOR READY TO LOAD
OIL TEMPERATURE SENSOR
RUN
START
LCV CLOSE
EICAS
STAT PAGE
MDC
PANEL
APU COMPARTMENT
SHUTDOWN SWITCH
DCU
GCU
GEN. LOAD LEVEL
GEN. OVERLOAD
AC TO AIRCRAFT
FUEL SOLENOID VALVE
DEPRIME
ADC
POWER
TO ECU
IOC
AIRCRAFT
BATTERY
AIR
GND
PSEU
P
FUEL
SOV
EGT
SPEED
Vol. 1 04--40--1
AUXILIARY POWER UNIT
Control REV 1, Jan 13/03
Flight Crew Operating Manual
CSP C--013--067
1. CONTROL
The APU electronic control unit (ECU) provides full automatic control of APU starting,
stopping, and protects the APU during all modes of operation. The control system ensures
that priority is given to electrical loads by reducing bleed airflow.
A. Starting
When the PWR FUEL switchlight, on the APU panel, is selected:
S The ECU is powered
S The air inlet door opens (position is displayed on the EICAS status page)
S The APU RPM and EGT gauges are displayed on the EICAS status page
S The fuel pump comes on
When the START/STOP switchlight, on the APU control panel, is selected:
S The ignition is activated
S The starter motor is energized
S The fuel shutoff valve opens
S The START legend on the APU panel comes on
S The APU START status message is displayed
The starter motor is deactivated at 46% rpm on the ground or at 60% rpm if in flight and
the START legend goes out. When the APU reaches 95% rpm, ignition is turned off.
Two seconds after the APU reaches 99% rpm, the AVAIL legend, in the START/STOP
switchlight, illuminates to notify the crew that the APU is ready for loading.
B. Stopping
To shutdown the APU, the crew pushes the START/STOP switchlight on the APU
panel. The APU will automatically shed its loading and shutdown. The PWR/FUEL
switch is deselected to close the fuel shutoff valve and to remove primary electrical
power to the ECU.
In the event of an emergency, the flight crew can press the APU FIRE PUSH switchlight
on the glareshield. On the ground, the APU can be shut down by pushing an APU
emergency stop button located in the APU compartment or by selecting an APU
shut--off switch on the external services panel on the RH forward fuselage. Either
selection sends a signal to the ECU to carry out an immediate shutdown.
Vol. 1 04--40--2
AUXILIARY POWER UNIT
Control REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Auxiliary Power Unit --- Control <1001, 1205>
Figure 04---40---1
APU Control Panel
Overhead Panel
APU SHUT--OFF (Guarded)
Used by maintenance personnel
to shut down the APU.
External Service Panel
Right Forward Fuselage
Fuel Page
APU Symbol
White -- APU not running
Half--Intensity Cyan --
APU ready to load
Half--Intensity Magenta --
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