R **ON A/C 001-049, 051-099, 101-105, 151-199, 201-299,
R -------------------------------------------------------------------------------R FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA R | | | | DOOR | REF. R -------------------------------------------------------------------------------R 511RH POWER UNIT, RL 2041VU 200 23-73-38 R 512RH POWER UNIT, RL 2040VU 200 23-73-38
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3. System Description
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A. Principle
(1) The Cabin Intercommunication Data System (CIDS) is a microprocessor based system. It operates, controls, monitors and tests these cabin functions:
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the passenger address,
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the passenger call,
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the passenger lighted signs,
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the general cabin illumination control,
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the cabin and flight crew interphone,
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the lavatory smoke detection,
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the service interphone (partially intergrated into the CIDS),
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the extended emergency lighting test,
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the work light test,
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the passenger reading lights (control and test),
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the boarding music pre-recorded announcements,
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-the passenger entertainment system,
**ON A/C 001-049, 051-099, 101-105, 151-199, 201-299,
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the emergency evacuation signalling,
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the escape slide bottle pressure monitoring,
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the monitor video system sound control.
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the monitor video system sound control.
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(2)
Because of the need for flexibility, the CIDS uses software to define any parts of its operation. The software program is dependant on individual aircraft layouts and optional system functions. The software is stored on two replaceable modules.
(3)
The CIDS hardware is provisioned with enough spare inputs, outputs and circuits to allow connection of new and additional equipment without having to make changes to the CIDS hardware. The appropriate memory module can be reprogrammed aboard the aircraft. The CIDS programming and test panel 110RH is provided for this. It is also possible to replace the memory module with a new pre-programmed unit for cabin layout changes.
(4)
A scheduled maintenance of the CIDS is unnecessary as the CIDS automatically does a self-check. It also monitors the performance of certain connected equipment. Several levels of system and component failure are defined for which CIDS gives immediate warning to the cabin and flight crew. Information on all faults is permanently stored in the CIDS. This information is also sent to the CFDS. (Ref. 31-30-00). A failure in the controlling CIDS director causes the system to switch control to the other CIDS director. In the case of failures on both CIDS directors, control of the system is given to the CIDS director with the less serious fault.
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B. General
The CIDS uses these components:
-26 Decoder Encoder Units (DEU) type A 200RH,
-4 Decoder Encoder Units (DEU) type B 300RH,
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the forward attendant panel 120RH,
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the programming and test panel 110RH and CAM 115RH,
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the aft attendant panel 126RH,
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the cabin equipment, see DEU type A,
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the attendant equipment, see DEU type B.
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