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cacnhaaaiiaeinr cjer OPERATING MANUAL PSP 606 SECTION 5 AUXILIARY POWER UNIT (APU) Subject TABLE OF CONTENTS Page GENERAL APU CONTROL START SYSTEM SHUTDOWN IBLEED AIR SYSTEM OIL SYSTEM 1 1 3 5 5 7 Figure Number LIST OF ILLUSTRATIONS Title Page 1 APU Control Panels 2 APU Controls and Indicators 3 Auxiliary Battery Panel 4 APU Fault Indications 2 4 6 8
OPERATING MANUAL PSP 606 SECTION 5 AUXILIARY POWER UNIT (APU) GENERAL The auxiliary power unit (APU) is a gas turbine engine which provides bleed air for air conditioning and engine starting, and drive facilities to supply electrical power. Except for the aircraft battery and fuel supply, the APU is independent of other aircraft systems. It is mounted on a support skid assembly, within an aluminum enclosure, in the rear fuselage behind the rear pressure bulkhead. Access to the APU is by way of the rear equipment bay door. Clean compressed air can be supplied for cabin and flight compartment air conditioning on the ground or in the air, and for ground and in-flight engine starting (for limitations on in-flight use of the APU, refer to the LIMITATIONS section of the Airplane Flight Manual). Shaft power is used to drive a generator to supply ground electrical power and in-flight standby power. An APU control panel, located on the flight compartment overhead panel, contains a combined power and fuel supply switch/light, FUEL ON/OFF, a single START/STOP switch/light, a BLEED AIR supply switch/light, oil fault lights and rpm and exhaust gas temperature (EGT) indicators. An APU fault annunciator panel, located on the left side of the rear fuselage, contains fault indication flags, an IND RESET pushbutton and a remote APU STOP pushbutton. The APU has an independant fuel feed system which draws fuel from the right main fuel tank. In addition, a tapping from the left engine fuel system ensures that the supply of fuel to the APU is maintained during negative G conditions (refer to Section 12, FUEL for details of APU fuel feed system). Fire protection is from a single Firex bottle mounted on the fuselage structure outside the APU enclosure (refer to Section 9, FIRE PROTECTION). APU CONTROL (Figures 1 and 2) An electronic control unit (ECU) mounted on the APU support monitors engine speed, exhaust gas temperature, oil pressure and temperature and overcurrent conditions during APU operation. Signals from sensors on the APU are relayed through the ECU to the appropriate indicators on the APU CONTROL and APU FAULT panels. The ECU also shuts down the APU under certain fault conditions (refer to paragraph 4.). Flight crew control and monitoring is provided by the APU control panel on the flight compartment overhead panel. External shutdown control and fault finding indicators are provided on the APU FAULT panel on the left side of the rear fuselage (refer to Section 1, AIRCRAFT GENERAL, Figure 7). SECTION 5 Page 1 Jun 12/86 canadair chauencjer OPERATING MANUAL PSP 606 BLEED ADPTR FUEL APU START/ AIR OIL ON/OFF OIL STOP © ® APU FAULT OVER OVER EGT SPEED CURRENT HIGH o o o PRESS LOW o OIL TEMP HIGH o I GEN ADAPTER OIL PRESS LOW TEMP HIGH o o IND RESET APU STOP 0 EXTERNAL PANEL (LEFT SIDE OF REAR FUSELAGE) O APU Control Panels Figure 1 SECTION 5 Page 2 Feb 12/88 canadair chanencjer OPERATING MANUAL PSP 606 An exhaust gas temperature indicator and an engine speed indicator are located on the APU control panel. The exhaust gas temperature indicator is calibrated in degrees Celsius and the engine speed indicator gives a readout in percentage of maximum rpm. Fault lights and switch/lights are grouped above the APU gauges. The APU FAULT panel contains a STOP pushbutton and an IND RESET pushbutton. The fault warning indicators are flags in the form of three white triangles in a circle, on a black background. Flags indicate overspeed, overcurrent, high exhaust gas temperature, low oil pressure, high oil temperature, generator adapter low oil pressure and generator adapter high oil temperature. If the fault which caused the indicator to show has been rectified, pushing the RESET button causes the white triangles to rotate out of view. START SYSTEM (Figures 2 and 3) Electrical power for APU starting is provided by the aircraft 28-volt battery or by an external dc ground power supply. The selection of power source is www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：Bombardier-Challenger_00-Auxiliary_Power_Unit
