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Power Supply - CIDS Director and FAP
Figure 019
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Power Supply SERVICE + ESS BUS - Middle Line
Figure 020
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Power Supply SERVICE + ESS BUS - Middle Line
Figure 020A
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R **ON A/C 106-149, 401-499,
(Ref. Fig. 021) **ON A/C 301-399,
R (Ref. Fig. 021A) **ON A/C 106-149, 301-399, 401-499,
In the normal mode the service bus supplies 28VDC to the CIDS. All functions of the system operate fully. The BITE test function is only active if the essential busbar is also available.
R B. Emergency Mode (Ref. Fig. 019) **ON A/C 106-149, 401-499,
(Ref. Fig. 020) **ON A/C 301-399,
R (Ref. Fig. 020A) **ON A/C 106-149, 401-499,
(Ref. Fig. 021) **ON A/C 301-399,
R (Ref. Fig. 021A) **ON A/C 106-149, 301-399, 401-499,
In the emergency mode, only the essential bus supplies 28VDC to the CIDS.
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Power Supply SERVICE + ESS BUS - Top Line
Figure 021
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Power Supply SERVICE + ESS BUS - Top Line
Figure 021A
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(1) The essential bus supplies power to the CIDS, if the service bus is not available.
(2) The system operates with minimum functions. The ACPs and the AIPs do not operate. The remaining functions are: - Passenger Address, - Cabin Interphone, - EVAC, - Smoke detection.
(3) The DEUs type A, which are connected to the top lines, are only supplied with power when there is an audio signal. If there is no audio signal, the director operates the Top Line cut-off relay to stop the power supply to the DEUs.
C. Power Consumption The power consumption of the CIDS components and the supplied cabin systems depends on the installed equipment. During normal operation all installed components are supplied with electrical power. If the service bus is not available and the CIDS is in emergency mode, the power consumption is reduced to a minimum. Only the components which are needed for the minimum functions are supplied with electrical power.
D. Power Interruption If a power interruption is longer than 5 sec., the CIDS software is reset and all components of the system are set to the predefined status.
R 5. Interface_________
R **ON A/C 106-149, 301-399,
A. CIDS system interfaces (external)
(1) Director
R **ON A/C 106-149,
R (Ref. Fig. 012)
R **ON A/C 301-399,
R (Ref. Fig. 012A)
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R **ON A/C 106-149, 301-399,
R (Ref. Fig. 013)
(a) The director has a data bus interface to the: - Flight Warning Computer 1+2 (FWC), - Air Conditioning Zone Controller (ZC), - System Data Acquisition Concentrator 1+2 (SDAC), - Centralized Fault Display System 1+2 (CFDS),
R **ON A/C 401-499,
R A. CIDS system interfaces (external)
R R (1) Director (Ref. Fig. 012B, 013)
R R R R R (a) The director has a data bus interface to the: - Flight Warning Computer 1+2 (FWC), - Air Conditioning System Controller (ACSC), - System Data Acquisition Concentrator 1+2 (SDAC), - Centralized Fault Display System 1+2 (CFDS),
R **ON A/C 301-399,
- Prerecorded Announcement & Boarding Music (PRAM),
**ON A/C 106-149, 301-399,
R - In Flight Entertainment System (IFE),
R **ON A/C 106-149, 301-399, 401-499,
R R R R (b) The director has a discrete interface to the: - Slat Flap Control Computer 1+2 (SFCC), - Landing Gear Control and Interface Unit 1+2 (LGCIU), - Cabin Pressure Controller 1+2 (CPC), - Cabin pressure relay, - Indicator Light Control Box (ILCB), - Service interphone override switch, - Exit signs relay, - Cockpit door switch,
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