A320飞机维护手册 AMM 机载辅助动力 AIRBORNE AUXILIARY POWER1(78)

曝光台 注意防骗 网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者

 The PN and the SERIES number on the identification plate indicates the APU modification status after the last shop maintenance. When a Vendor SB is imbodied during line maintenance, the 'change' number is stemped adjacent to the MOD RECORD on the modification plate.
 Within this ATA 49 AMM there are some AMM TASKs, which are in relation to different APU modification status. The different procedures within a TASK are identified by the P/N, SERIES number and CHANGE number. Compared with the identification plate of the APU you can find the applicable procedure in this manual.

 R EFF : 001-003, 051-099, 401-499,  49-00-00Page 1
 

 Identification Plate Figure 001 
R  EFF :  001-003, 051-099, 401-499,  Page 249-00-00 Config-1 Aug 01/05
 CES 

 

 2. Component Location__________________
 A. Tailcone (Ref. Fig. 002)
 B. Cockpit (Ref. Fig. 003, 004, 005)
 C. Avionic Compartment/Aft Cargo Compartment 
R  **ON A/C 001-003, 051-099,
 (Ref. Fig. 006) 
R  **ON A/C 401-499, 
R  (Ref. Fig. 006A) 
R  **ON A/C 001-003, 051-099, 401-499,
 3. System Description__________________
 A. Power Plant (Ref. 49-10-00) The power plant is installed in the rear fuselage aft of the passenger compartment. It occupies the tailcone, the rearmost portion of the fuselage. The tailcone has been fitted with a fireproof compartment to house the APU. Peripheral systems are installed both in the APU compartment as well as to the front and rear of it. Doors permit access to all components of the power plant.
 B. Engine (Ref. 49-20-00) The engine supplies: - pneumatic power, - electrical power, and - cooling air. To fulfill these requirements, the engine consists essentially of a power section to generate shaft power. A load compressor is flanged to this shaft to generate pneumatic power. Subject shaft also drives a gearbox. A generator is attached to this gearbox to generate electrical power. A fan to provide cooling air is also attached to the gearbox. 

 

 Power Plant - Component Location
 Figure 002

 CES

 Auxiliary Power System - Component Location (Flight Deck) Figure 003

R EFF : 001-003, 051-099, 401-499, 49-00-00Page 5 Config-1 Aug 01/05
 CES

 Auxiliary Power System - Component Location (ECAM System) Figure 004

R EFF : 001-003, 051-099, 401-499, 49-00-00Page 6 Config-1 Aug 01/05
 CES

 Auxiliary Power System - Component Location (Maintenance System) Figure 005

R EFF : 001-003, 051-099, 401-499, 49-00-00Page 7 Config-1 Aug 01/05
 CES

 Auxiliary Power System - Component Location (Avionic Compartment/Aft Cargo

 EFF :  001-003, 051-099,  Compartment) Figure 006 Page 849-00-00 Config-1 May 01/05
 CES 

 

R Auxiliary Power System - Component Location (Avionic Compartment/Aft Cargo R Compartment) R Figure 006A

R EFF : 401-499, 49-00-00Page 9 Config-1 Aug 01/05
 CES

 C. Engine Fuel and Control (Ref. 49-30-00) The APU system receives fuel from the A/C APU fuel supply system (Ref. 28-22-00). Incoming fuel is metered by the fuel control unit (FCU) and delivered to the flow divider and drain valve assembly (FDDVA). From there it is routed via 2 fuel manifolds to the fuel nozzles, located in the combustion chamber.
 D. Ignition and Starting (Ref. 49-40-00) The APU is fitted with a DC starter motor, which draws its power from the electrical system battery bus. It turns the engine to such speed that self-sustained engine operation becomes possible. The fuel-air mixture in the combustion chamber is ignited by the ignition system, also fitted to the APU. Electrical power to the ignition system is supplied through the ECB.
 E. Air (Ref. 49-50-00) The engine is equipped to provide 2 separate air sources:
 -pneumatic power (bleed air) for main engine start (MES) and the
 environmental control system (ECS),

 -cooling air for ventilation of the APU compartment and cooling of the APU lubrication system.
 F. Engine Controls (Ref. 49-60-00) In order to start, control its performance and to shut off the auxiliary power system, manual and automatic controls are provided. Manual control of the APU is possible through the crew interfaces in the cockpit. Automatic control is accomplished through the ECB.
 G. Indicating (Ref. 49-70-00) The ECB monitors the operation of the auxiliary power system. It transmits operation information to the A/C indicating and recording systems ECAM, CFDS and AIDS. It also records system faults in its internal memory. Display of subject data is in the cockpit on the CFDS monitor.
 H. Exhaust (Ref. 49-80-00) The APU exhaust system serves to duct the engine exhaust overboard. Its secondary purpose is to reduce the exhaust noise level. In order to minimize aerodynamic losses during APU operation, the duct is designed sufficiently large in diameter. Also, exhaust discharge takes place at the very aft end of the A/C, where a low pressure area exists during flight. Thus it is also assured that exhaust gas does not re-enter the APU air intake system.
　
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：A320飞机维护手册 AMM 机载辅助动力 AIRBORNE AUXILIARY POWER1(78)