DESCRIPTION
General 05−10−1
APU Access and Component Location 05−10−2
APU Compartment 05−10−2
APU General Arrangement 05−10−3
APU System Schematic 05−10−3
Lubrication 05−10−4
Oil Pressure 05−10−4
Gravity Oil Fill 05−10−4
Oil Replenishment System 05−10−4
Oil Replenishment System Filling 05−10−6
Oil Replenishment Panel 05−10−7
Operation 05−10−7
Fuel Control and Indication 05−10−8
Airframe Fuel 05−10−8
Ignition 05−10−9
Start System 05−10−9
Speed Indication 05−10−9
Temperature Indication 05−10−9
Hourmeter/Cycle Counter 05−10−9
ECU Component Control Schematic 05−10−10
Control System 05−10−10
Pneumatic 05−10−10
APU System Operating Modes 05−10−12
ECU Powerup
05−10−12
Start Mode 05−10−12
Onspeed
Mode 05−10−12
Cooldown Mode 05−10−12
Shutdown Mode 05−10−12
APU System Operating Sequence 05−10−12
APU Starting 05−10−12
APU Door Positioning 05−10−12
APU Loading 05−10−13
APU Shutdown 05−10−13
APU Door Operation and Indication 05−10−14
Door Operation 05−10−14
Door Indication 05−10−14
AUXILIARY POWER UNIT
TABLE OF CONTENTS
CHAPTER 5
05−00−1
Rev 3, Apr 25, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
05−00−1
Page
TABLE OF CONTENTS
DESCRIPTION
APU RPM and EGT Indications 05−10−14
APU Fire Protection 05−10−15
APU Control Panel 05−10−15
Start Sequence 05−10−16
Normal Shutdown 05−10−16
Emergency Shutdown 05−10−16
APU Emergency Shutoff
Buttons 05−10−17
Restart After Emergency ShutDown 05−10−17
Protective Shutdowns 05−10−18
System Overview Schematic 05−10−19
Electrical Power and Distribution 05−10−20
Start Control Schematic 05−10−20
FADEC Inputs and Outputs 05−10−21
ECU Schematic 05−10−22
EICAS Messages 05−10−23
EMS CIRCUIT PROTECTION
CB − APU System 05−20−1
AUXILIARY POWER UNIT
TABLE OF CONTENTS
Flight Crew Operating Manual Rev 3, Apr 25, 2005
CSP 700−5000−6
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 3, Apr 25, 2005 Flight Crew Operating Manual
CSP 700−5000−6
Volume 2
05−10−1
APU ACCESS AND COMPONENT LOCATION
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