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APU Fire Protection 05−10−14
APU Control Panel 05−10−14
Start Sequence 05−10−15
Normal Shut down 05−10−15
Emergency Shut down 05−10−15
APU Emergency Shutoff
Buttons 05−10−16
Restart After Emergency Shut Down 05−10−16
Protective Shut downs 05−10−17
System Overview Schematic 05−10−18
Electrical Power and Distribution 05−10−19
Start Control Schematic 05−10−19
FADEC Inputs and Outputs 05−10−20
ECU Schematic 05−10−21
EICAS Messages 05−10−22
EMS CIRCUIT PROTECTION
CB − APU System 05−20−1
AUXILIARY POWER UNIT
TABLE OF CONTENTS
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
05−00−2
Page
GENERAL
An AlliedSignal
RE 220 gas turbine Auxiliary Power Unit (APU) is installed in a fire proof enclosure
in the tail cone of the airplane (beneath the airplane rudder and elevator control systems) and has a
fire detection element system (see Fire Protection System Chapter 9). The APU is installed outside
of the main engine rotor burst zone which enhances airplane high altitude operation.
GF0510_001
APU LOCATION
The APU provides bleed air for cabin cooling and heating through the Environmental Control System
(ECS), Main Engine Starting (MES) and electrical power on the ground and in flight.
Under high demand load conditions, the APUs electrical loads take priority over pneumatic loads.
The main component of the electrical system is the Full Authority Digital Engine Control (FADEC).
The APU FADEC interfaces with EICAS and the Central Aircraft Information Maintenance System
(CAIMS), providing failure detection and isolation to faulty components.
Control of APU speed is automatic and monitoring of APU Exhaust Gas Temperature (EGT), speed,
fuel and oil pressure is through the FADEC. The FADEC also records operating hours and start
cycles.
The engine speed for normal continuous steady state is displayed as 100% RPM and overspeed
protection is provided. The APU has automatic protective shut down for abnormal ground and in flight
conditions.
APU start and run is initiated by a single switch, located on the APU control panel in the flight
compartment. Operation and control of the APU electric and bleed system is performed at the
ELECTRICAL and BLEED/AIR CONDITIONING ANTIICE
PANEL respectively.
For APU operating limitations refer to the Flight Crew Operating Manual (FCOM) CSP 7006
VOL 1,
Chapter 2 LIMITATIONS.
AUXILIARY POWER UNIT
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
05−10−1
APU ACCESS AND COMPONENT LOCATION
GF0510_002
APU INLET DOOR
APU ACCESS DOORS
APU EXHAUST
EXHAUST DISCHARGE
EXHAUST BAFFLE
INLET DUCT
APU INLET DOOR
INLET OIL COOLER
OIL COOLER
APU Compartment
The APU is mounted in the tail cone by a multiaxis
suspension rod system, securing it in all axes.
The APU compartment is completely sealed from the atmosphere with the exception of the inlet to
the oil cooler system and the APU air inlet. The APU utilizes exhaust flow to pump cooling air
through the oil cooler and to the APU and its associated components. The APU compartment is
also isolated from the rest of the airplane for fire protection.
Cooling of the APU compartment is accomplished by an air to oil heat exchanger and by air flow
over the APU through the enclosure (via the APU inlet). The airflow through the inlet splits in two
sections. One section allows air to flow to the inlet plenum (to the compressor), while the other
section allows the air to flow through the oil cooler to provide cooling for the APU oil. The air
flowing through the oil cooler then passes through the compartment to cool the APU and its
mounted components. This air is then exhausted overboard via the APU eductor.
AUXILIARY POWER UNIT
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
05−10−2
APU GENERAL ARRANGEMENT
The APU consists of the following:
· Inlet Door − Variable position. The door schedules are sequenced as a function of
weightonwheels,
airplane MACH number and APU speed.
· Compressor − Is a single stage centrifugal impeller. Delivers approximately 52 psia bleed
pressure at normal operating speed.
· Combustor − Contains 10 fuel nozzles and 2 igniters.
· Turbine − Two stage axial flow turbine which drives the compressor/gearbox.
　
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