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the RAT extension command is generated
- the AC and DC essential busbars are immediately supplied by the batteries.
-after 7s the AC and DC essential busbars are supplied by the standby generator. The RAT extension can be manually controlled.
R **ON A/C 001-049, 051-099, 101-149, 201-299, (2) Interface with the EFCS The ELAC1 and the SEC1 are supplied from a DC essential busbar (4PP for the ELAC1 and SEC1), the battery 1 taking over instantaneously through a dedicated diode device (Power Supply Decoupling Unit) when the voltage level drops below the battery output voltage. (Ref. Fig. 006) A relay ensures the battery supply line breaking on the ground 30s after the second engine is shut down. (after the third hydraulic pressure drop down). The ELAC2, and the THS motor 1 are normally supplied from a DC normal busbar 2PP. In case of loss of this busbar (particularly after loss of both main generation channels, or after a double main TRU failure),these supplies are automatically switched over to the battery 2 by means of two relays, for a fixed period of 30s. (Ref. Fig. 007) These relays are automatically re-energized if later on the Blue hydraulic pressure to falls, and during the landing phase as soon as the nose landing gear is extended. On each of these four supply lines must be added the solenoid valves associated with the computer and one of the four accelerometers, with the following distribution:
-------------------------------------| COMPUTER | ACCELEROMETER | |---------------|-------------------| | ELAC 1 | 1 | | SEC 1 | 2 | | ELAC 2 | 3 | | SEC 2 | 4 | ------------------------------------- The SEC 2, SEC 3, the THS electric motor 3, and the FCDC 2 are supplied from theDC normal busbar 2PP. The THS electric motor 2 is supplied from the DC essential busbar 4PP. The FCDC 1 is supplied from the DC essential busbar 8PP.
R **ON A/C 151-199, 301-399, 401-499, (2) Interface with the EFCS The ELAC1 and the SEC1 are supplied from a DC essential busbar (4PP for the ELAC1 and SEC1), the battery 1 taking over instantaneously through a dedicated diode device (Power Supply Decoupling Unit) when the voltage level drops below the battery output voltage. (Ref. Fig. 006) A relay ensures the battery supply line breaking on the ground 30s after the second engine is shut down. (after the third hydraulic pressure drop down). The ELAC2, and the THS motor 1 are normally supplied from a DC normal busbar 2PP.
Electrical Power Supply (General) Figure 004
1EFF : ALL 1 27-90-00Page 11/12 1 1 May 01/04R 1 1 1CES
Electrical Power Supply (EFCS) Figure 005 1EFF : 1 1R 1CES ALL 1 11 1 27-90-00 Page 13 May 01/04
ELAC 1 and SEC 1 Power Supplies - Principle Figure 006 R 1EFF : 1 1 1CES ALL 1 111 27-90-00 Page 14 May 01/04
ELAC 2 Power Supply - Principle Figure 007
R 1EFF : 001-049, 051-099, 101-149, 201-299, 1 27-90-00Page 15 1 1 May 01/05 1 1 1CES 1 In case of loss of this busbar (particularly after loss of both main generation channels, or after a double main TRU failure),these supplies are automatically switched over to the battery 2 by means of two relays, for a fixed period of 30s. (Ref. Fig. 007A) These relays are automatically re-energized if later on the Blue hydraulic pressure to falls, and during the landing phase as soon as the nose landing gear is extended. On each of these four supply lines must be added the solenoid valves associated with the computer and one of the four accelerometers, with the following distribution:
-------------------------------------| COMPUTER | ACCELEROMETER | |---------------|-------------------| | ELAC 1 | 2 | | SEC 1 | 1 | | ELAC 2 | 3 | | SEC 2 | 4 |
------------------------------------- The SEC 2, SEC 3, the THS electric motor 3, and the FCDC 2 are supplied from theDC normal busbar 2PP. The THS electric motor 2 is supplied from the DC essential busbar 4PP. The FCDC 1 is supplied from the DC essential busbar 8PP. **ON A/C ALL 5. Functions Performed in Normal Configuration ___________________________________________ This section briefly describes the functions of the electrical flight controls in normal mode, i.e without failures which cause law degradation. A. Pitch Control (1) General The C* law is the fundamental mode of manual pitch control. The law generates a load factor demand from the position of the side stick and the inertial feedbacks. Protection against excessive load factor, Mach or speed or angle of attack pitch attitude are also provided. R 1EFF : ALL 1 27-90-00Page 16 1 1 May 01/04 1 1 1CES 1
ELAC 2 Power supply - Principle www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：A320飞机维护手册 AMM FLIGHT CONTROLS 飞行操纵9
