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position. The four digits of the code are entered by pressing corresponding buttons. After a digit is entered, the next dash starts to
blink, until all four are entered. Any input mistake can be erased by pushing CLR button, which erases last entered digit.
The active transponder code is not altered until the new entry is complete.
A319/320/321
Systems Manual
Phoenix Simulation Software P 71
REV 01 SEQ 001 APU
Overview
The Auxiliary Power Unit (APU) is a small jet engine located in the aircraft tailcone. It allows the aircraft to be independent of
external pneumatic and electrical power supplies. The APU can provide bleed air for starting engines and for air conditioning, and
drives a generator that provides electrical power. The APU can be started and used on ground and in the air.
APU Controls and indications
The APU is controlled from APU panel on the overhead. Its operating status can be monitored on ECAM APU
page, which is automatically displayed during APU startup.
The MASTER SW button controls the power supply for automatic sequencing and protection during start up,
operation, and shutdown. When selected ON - blue “ON” illuminates - the APU system is armed for automatic
startup sequence. The APU intake ap automatically opens.
Pushing the button with APU running extinguishes the ON light and initiates automatic shutdown sequence,
during which the APU rpm decreases for a brief cooling period, after which APU is
stopped.
The START button initiates APU startup sequence. It cannot be selected until APU
intake ap opens, which is indicated by green “FLAP OPEN” indication on ECAM
APU page.
When the START button is pushed, blue “ON” light illuminates on the button. APU
spools up. After automatic startup is complete, “ON” light disappears and green “AVAIL”
light illuminates. “AVAIL” is also shown on ECAM APU page. From this moment, the
APU is available.
The ECAM APU page shows gauges for APU rpm percentage and exhaust gas temperature.
Also, when APU is running, the APU generator load, voltage and frequency is
displayed, along with APU bleed air pressure and position of APU bleed valve.
The fuel for APU operation is automatically fed from left inboard wing tank. Fuel is normally available from tank pumps. If tank fuel
pumps are selected off, the APU uses its own dedicated pump to supply fuel.
A319/320/321
Systems Manual
Phoenix Simulation Software P 72
REV 01 SEQ 001 Electrical system
Overview
The electrical power system consists of an AC system and a DC system. The power is normally provided by engine driven
generators installed on each engine. The APU generator can be used before engine start.
On the ground, external power can be used. In case of loss of normal generation in ight, the aircraft can be supplied by an
emergency generator driven by automatically deployed ram air turbine.
An automatic bus tie maintains power to AC1 and AC2 buses regardless of power sources being used: engine generators, single
generator, APU or external power. Bus ties can be manually opened using BUS TIE overhead switch.
The power sources are prioritized. Each AC bus will use the rst available source in this order: Own engine generator, External
power, APU, opposite engine generator, Emergency generator, Batteries. If APU power was used and external power is connected,
the external power takes over the supply and APU is disconnected. If, after this, engine generator comes online, it replaces the
external power. A bus can be powered only from a single power source.
Each generator, and EXT PWR, can power entire aircraft electrical system with this exceptions:
• On the ground, if single engine generator powers entire system, the Main Galley is shed.
• In ight, if Any single generator powers entire system, the Main Galley is shed.
The AC ESSential bus powers most vital aircraft systems, and is normaly fed from AC 1 bus. If AC 1 is unpowered, the AC ESS can
be powered from AC 2 using AC ESS FEED switch on the overhead. If both AC buses are unpowered in ight, the Ram Air Turbine
is automatically deployed which powers AC ESS bus via Emergency Generator. RAT is disabled with landing gear down, and when
this occurs, the AC ESS bus is fed from Batteries via Static Invertor.
Two DC buses are fed from respective AC buses via Transformer Rectiers (TRs), and power the DC BAT bus. if one of AC
buses is unpowered, the corresponding DC bus is fed from opposite DC bus via DC BAT bus. if both AC buses unpowered,
the DC 1 and 2 buses are lost.
The DC ESSential bus is powered by DC BAT bus, or (DC1 and DC2 buses off) by AC ESS bus via ESS TR, or directly by
　
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本文鏈接地址：PSS A319/A320/A321 Systems Manual 系統手冊(26)