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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)
LCV POSITION COMMAND (TORQUE MOTOR)
LCV POSITION (RVDT)
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--30--3
REV 56, Jan 31/03
AUXILIARY POWER UNIT
Systems
Flight Crew Operating Manual
CSP A--013
MASTER
Auxiliary Power Unit Door Position Chart
Figure 04---30---2
40K
30K
20K
13K
10K
0
0 100 200
210 260
300 400
500 ft
OUTSIDE OF SHADED AREA
DOOR IS POSITIONED TO 28
DOOR POSITIONED
TRUE AIRSPEED (TAS)
set point
change area
6 knots set point
change area
PRESSURE
ALTITUDE
-- MID
TO 42 -- OPEN
REV 56, Jan 31/03
Vol. 1 04--30--4
AUXILIARY POWER UNIT
Systems
Flight Crew Operating Manual MASTER
CSP A--013
THIS PAGE INTENTIONALLY LEFT BLANK
Vol. 1 04--40--1
REV 56, Jan 31/03
AUXILIARY POWER UNIT
Control
Flight Crew Operating Manual
CSP A--013
MASTER
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 50% rpm and the START legend goes out. When
the APU reaches 99% rpm, ignition is turned off and two seconds later the AVAIL
legend, in the START/STOP switchlight, illuminates to notify the crew that the APU is
ready to supply electrical power and bleed air.
(1) APU Starter Limits
SOURCE START # and TIME ON COOLING TIME
1 30 seconds No cooling required
Battery
2 30 seconds 20 minutes
3 30 seconds No cooling required
4 30 seconds 40 minutes
1 15 seconds No cooling required
External DC Power
2 15 seconds 20 minutes
3 15 seconds No cooling required
4 15 seconds 40 minutes
REV 56, Jan 31/03
Vol. 1 04--40--2
AUXILIARY POWER UNIT
Control
Flight Crew Operating Manual MASTER
CSP A--013
NOTE
It is recommended that a 2 minute delay be observed
between start attempts to allow for cooling of the APU
start contactor and for fuel drainage.
Effectivity:
S Airplanes 7003 to 7100 not incorporating Service Bulletin 601R--28--008
NOTE
During normal operations, a nuisance XFLOW/APU
PUMP cautionmessagemay come on. When this occurs,
selecting the APU PWR/FUEL switchlight to on then off
will usually clear the message. If the message clears,
there is no operational restrictions and the anomaly
should be disregarded.
B. Stopping
To shutdown the APU, the crew deselects 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
　
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