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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.
J. Oil (Ref. 49-90-00)
The APU oil system lubricates and cools the power section, load
compressor, gearbox and AC-Generator. This system is made up of:
-
an integral wet-sump lubrication system with an APU mounted oil cooler,
-
an oil level, high oil temperature and low oil-pressure monitoring
system. The Electronic Control Box (ECB) 59KD monitors these parameters.
4. Power Supply____________ (Ref. Fig. 006)
5. Interface_________
A. Fuel Supply
Fuel is supplied to the APU by the A/C APU fuel supply system (Ref.
28-22-00 and 28-29-00).
B. Pneumatic Power Pressurized air generated by the APU is fed into the A/C pneumatic power distribution system (Ref. 36-12-00).
C. APU Fire Protection The APU and most of its peripheral subsystems are installed in the APU compartment, a designated fire zone. This compartment therefore is equipped with a fire detection (Ref. 26-13-00) and fire extinguishing system (Ref. 26-22-00).
D. Electrical Power The APU is equipped with a 115VAC electrical power generator, which feeds into the A/C electrical power distribution system (Ref. 24-23-00).
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6. Operation/Control and Operation_______________________________ (Ref. Fig. 007)
The APU system operates independently of the other engine systems, in the conditions of operation shown below:
A. Normal Conditions of Operation (APU not essential)
(1)
Ground Operation.
The APU will:
-
supply bleed air for the Main Engines Start (MES) on the ground in an altitude range between -305 m (-1000 ft.) and 4420 m (14500 ft.) at -54 DEG C to +55 DEG C (-65 DEG F to +130 DEG F),
-
supply bleed air for the air conditioning of the passenger compartment and the cockpit,
-
supply shaft power to a 90 kVA generator while the air conditioning is necessary.
(2)
Flight Operation.
The APU will:
-
supply bleed air in flight up to an altitude of 7630 m (25000 ft.),
-
supply shaft power to a 90 kVA generator.
If an increase in input to the aircraft systems is necessary, the
supply of the electrical power has priority over the supply of bleed
air.
(3)
An electric DC motor starts the APU:
-in ground operation conditions, the APU is started by the aircraft batteries or Transformer Rectifier Unit (TRU) or a combination of both,
-a start in flight is possible up to an altitude of 11900 m (39000 ft.) with the use of TRUs. A start in flight is possible up to an altitude of 7630m (25000 ft.) with the use of the aircraft batteries only.
B. Operation in Icing Conditions The APU will safely operate in ground icing conditions and during a subsequent flight in icing conditions, with it operating as an essential unit. It can be started in climb and flight after APU operation in icing conditions on the ground.
C. Control and Monitoring The ECB 59KD controls and monitors the APU operation. The Built-In Test Equipment (BITE) of the ECB is connected to the CFDS (Ref. 31-32-00). The components that control and monitor the system are divided into two interfaces:
-Flight Crew Interface,
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Auxiliary Power System - Power Supply
Figure 006 (SHEET 1)
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Auxiliary Power System - Power Supply
Figure 006 (SHEET 2)
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Auxiliary Power System - Operating Envelope/APU Performance Figure 007 (SHEET 1)
R EFF : 001-049, 101-105, 107-107, 151-199, 49-00-00Page 12 201-210, Config-2 Aug 01/05 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(82)
