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EICAS Messages................................................................................................................05-01-15
May 06/2005 Flight Crew Operating Manual Volume 2 REV 2 CSP 100-6
05-00-01
INTRODUCTION
The Honeywell 36-150BD constant-speed gas turbine auxiliary power unit (APU) is installed in a fire-proof compartment in the tailcone of the airplane. The APU is a fully automated gas turbine powerplant with automatic fault detection, auto-matic and remote shutdown, and in the event of an APU fire on the ground, automatic fire extinguishing.
The APU compartment is accessed by a single panel aft of the aft equipment bay door. The panel must be unscrewed from the fuselage underside. The APU is a self-contained unit.
The primary purpose of the APU is to provide power for the gearbox-mounted 400-amp DC generator. Secondary functions of the APU are bleed-air supply for the environmental control system (ECS) and main engine starting. Under high demand, the APU electrical loads take priority over pneumatic loads.
For APU maximum operating altitudes for ground and flight, and also for continuous starter attempts, refer to the Approved Airplane Flight Manual.
The APU should not be started above speed limits stated in the Approved Airplane Flight Manual, as the APU may reverse windmill.
An engine control unit (ECU) controls and monitors all facets of APU operation, including the recording of operating hours and start cycles. The DC-powered ECU sets up the appropriate fuel acceleration and EGT temperature schedules. It relays appropriate operating data to the pilots through the EICAS displays.
APU start is initiated by one switch on the APU control panel in the flight compartment. Operational control of the APU electric and bleed-air systems is performed at the ELECTRICAL and AIR COND/BLEED control panels.
COMPARTMENT
The APU is mounted in the airplane tailcone and is accessed via the access panel located on the fuselage underside. The APU compartment has a NACA inlet for ventilation. The air is pulled through the NACA inlet and routed through the com-partment to cool the APU and its mounted components. This air is then exhausted overboard via the APU exhaust eductor.
The APU-driven air-cooled DC generator also has a NACA inlet for cooling air flow. The air is pulled through the generator and dumped in the APU compartment. This air is then exhausted overboard via the APU exhaust eductor.
APU LOCATION
CFO0501002_002
Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6
05-01-01
APU ACCESS PANEL LOCATIONS
SIDE ACCESS PANEL
BOTTOM ACCESS PANEL
CFO0501002_007
Volume 2 Flight Crew Operating Manual Sep 13/2004 CSP 100-6 REV 1
05-01-02 APU SCHEMATIC
TORQUE CONTROL MORTOR PRESSURE
UNIT
AIR INLET
INLET AIR
BLEED AIR
CFO0501002_005
ELECTRICAL CIRCUITS
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