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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 ANTI-ICE PANEL respectively. For APU operating limitations refer to the Flight Crew Operating Manual (FCOM) CSP 700-6 VOL 1, Chapter 2 LIMITATIONS. GF0510_001 Rev 3, Apr 25, 2005 Flight Crew Operating Manual Volume 2 AUXILIARY POWER UNIT INLET OIL COOLER INLET DUCT Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005 . |
