(c)
Electric panel 35VU includes:
-The APU GEN switch which disconnects the electrical load from the APU generator during operation of the APU. Part of the switch is a white 'OFF' annunciator light and an amber 'FAULT' annunciator light.
(d)
Fire panel 20VU includes:
-
the APU FIRE pushbutton switch 1WD which starts the APU
shutdown procedure when a fire warning is indicated,
-
the APU AGENT push switch which operates the fire extinguisher. Part of the switch is a white 'SQUIB' annunciator light and an amber 'DISCH' annunciator light,
-
the TEST switch for the continuity test on the APU fire warning loops, and the cartridge, of the fire extinguisher bottle.
(e)
The indicating system (Ref. 49-70-00) supplies the flight crew with data on the APU system configuration during flight operation. The data is supplied on two display units as memo messages and system diagrams. During satisfactory system configuration, the system page (lower ECAM display unit) indicates the data shown below:
-speed (rpm) in % of nominal speed (Ref. 49-71-00),
-Exhaust Gas Temperature (EGT) in deg. C (Ref. 49-72-00),
-APU bleed air pressure in psi and the position of the APU bleed valve (Ref. 49-51-00),
-AVAIL if the APU speed is above 95 % rpm,
-APU generator load in %, voltage (V) and frequency (Hz),
-the air-intake flap open indicator.
The system page is shown in these modes:
-manual mode (pushed APU button on the ECAM control panel),
-flight phase related automatic mode,
-advisory automatic mode,
-failure related automatic mode.
During satisfactory flight operation, the engine/warning page (upper ECAM display unit) indicates a memo message if no warning is to be shown:
-
APU AVAIL,
-
APU BLEED.
When an unsatisfactory operation condition occurs, the lower part
of the engine/warning page supplies better failure-analysis. The
failure is clearly shown and the correct action to follow is
indicated.
Example of failure mode indicated is:
-
APU AUTO SHUT DOWN,
-MASTER SW ... OFF.
When the aircraft is on the ground and the main engines have stopped, the ECAM will show any faults. The light in the status (STS) button comes on if class 2 faults have occurred. Operation of the STS button selects the STATUS page and 'APU' is indicated in the lower right-hand corner of the display.
(2) Maintenance Interface (Ref. Fig. 005) Two Multifunction Control and Display Units (MCDUs) and a multipurpose printer (optional) are installed on the center pedestal in the cockpit. The MCDUs are at the front and the printer at the rear of the center pedestal. This equipment gives access to the APU maintenance information, the APU interfaces with the CFDS and the AIDS. The interface between the ECB and the CFDS agrees with the type 1 system (Ref. 31-32-00).
(a) The MCDU displays the defective Line Replacable Units (LRUs) through the CFDS. This is possible in two modes:
-NORMAL mode.
During NORMAL mode, the ECB transmits all the defects and
messages continuously to the CFDS. The MCDU displays all the
defects and messages when the 'LAST LEG REPORT' is selected. The
Centralized Fault Display Interface Unit (CFDIU) identifies all
the defects and messages and stores them in memory. These are
released and indicated on the MCDU when selected:
-MENU mode.
The MENU mode is available when the 'SYSTEM REPORT/ TEST' and
'APU' is selected on the MCDU.
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機維護手冊 AMM 機載輔助動力 AIRBORNE AUXILIARY POWER1(80)
