**ON A/C 001-049, 051-099, 101-105, 201-203,
In case of loss of AC BUS 1 and AC BUS 2 (emergency configuration),
DC ESS BUS and DC SHED ESS BUS are recovered by the CSM/G (via the
ESS TR) when the RAT hydraulic generation is available.
When landing gear is extented, DC ESS BUS only is supplied by battery
2.
1EFF : ALL 1 24-00-00Page 30 1 1 Aug 01/05R 1 1 1CES 1
NOTE : The external power receptacle directly energizes the TR 2
____ which can independently supply a part of the DC normal network. (Ground service configuration).
R **ON A/C 106-149, 151-199, 204-299, 301-399, 401-499,
In case of loss of AC BUS 1 and AC BUS 2 (emergency configuration),
DC ESS BUS and DC SHED ESS BUS are recovered by the CSM/G (via the
ESS TR) when the RAT hydraulic generation is available.
During RAT deployment or when the following two conditions are both
met:
-main landing gear compressed,
-and A/C speed below 100 Knots,
DC ESS BUS only is supplied by battery 2.
NOTE : The external power receptacle directly energizes the TR 2
____ which can independently supply a part of the DC normal network. (Ground service configuration).
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 301-399,
C. Power Supply Via the External Power Receptacle
(Ref. Fig. 004)
(1) AC External Power Control Supply An external power receptacle located in front of the nose landing gear well enables power supply of the aircraft network. This is performed by means of the three-phase, 400 Hz, 115/200 V ground power unit. External power supply is controlled from the ELEC panel on the cockpit overhead panel and via the GPCU. The GPCU includes a BITE and a self monitoring system which analyzes most of the faults which may affect the channel. The system memorizes the corresponding information in a non-volatile memory. This memory also memorizes the fault information from each main GCU. Finally, the GPCU delivers all fault information to the CFDS. The test is initialized:
-either on the ground by the CFDS,
- or automatically at each power-up.
Each main GCU or APU GEN GCU then receives the test request.
R **ON A/C 401-499,
R C. Power Supply Via the External Power Receptacle
R
R (Ref. Fig. 004A)
R (1) AC External Power Control Supply
R An external power receptacle located in front of the nose landing
R gear well enables power supply of the aircraft network. This is
R performed by means of the three-phase, 400 Hz, 115/200 V ground power
R unit.
R External power supply is controlled from the ELEC panel on the
R cockpit overhead panel and via the GAPCU.
R The GAPCU includes a BITE and a self monitoring system which analyzes
R most of the faults which may affect the channel. The system memorizes
R the corresponding information in a non-volatile memory.
R This memory also memorizes the fault information from each main GCU.
R Finally, the GAPCU delivers all fault information to the CFDS.
R The test is initialized:
R - either on the ground by the CFDS,
R - or automatically at each power-up.
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 301-399,
In addition, the GPCU delivers electrical parameters relative to its
channel to the EGIU 1, channel 2.
R **ON A/C ALL
(2) Ground Service Bus Control
**ON A/C 001-049, 051-060, 101-102, 201-201,
(Ref. Fig. 003)
**ON A/C 061-099, 103-105, 151-158, 202-209,
(Ref. Fig. 003A)
R **ON A/C 106-149, 159-199, 210-299, 301-399, 401-499,
(Ref. Fig. 003B)
**ON A/C ALL
It is possible to supply a part of the aircraft electrical network as follows, directly from the external power receptacle, to carry out ground service operations :
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