-
the cabin pressure controller 1 11HL (91VU) (213134),

 -
the cabin pressure controller 2 12HL (96VU) (213134),

 -
the PASS INFO relay 19WR (103VU) (352300),

 -
the centralized fault display interface unit 1TW (87VU) (313234),

 -
the cockpit door switch 310LG (332100),

 -
the cockpit EVAC horn 5WP (48VU) (256300),

 -
the cockpit EVAC SIGNAL switch 2WP (21VU) (256300),

 1EFF : 001-049, 051-099, 101-105, 151-199, 1 23-73-00Page 35 1201-299, 1Config-1 Aug 01/05R 1 1 1CES 1

 -
the cockpit EVAC CONTROL switch 3WP (21VU) (256300),

 -
the cockpit EVAC HORN OFF switch 7WP (21VU) (256300),

 -
the CTL PWR SPLY relay 8WL ( 335100),

 -
the flight warning computer 1 1WW1 (85VU) (315334),

 -
the flight warning computer 2 1WW2 (86VU) (315334),

 -
the board-ann LT test & interface 1LP (70VU) (331433),

 -
the board-ann LT test & interface 9LP (70VU) (331433),

 -
the landing gear control and interface unit switch 5GA1 (93VU) (323171),

 -
the landing gear control and interface unit switch 5GA2 (94VU) (323171),

 -
the oil pressure warning system (103VU) (732500),

 -
the service interphone ovrd switch 15RJ (50VU) and jack sockets (234400),

 -
the slats and flaps control computer 1 21CV (85VU) (275134),

 -
the slats and flaps control computer 2 22CV (86VU) (275134),

 -
the smoke detection control unit 10WQ (94VU) (261734),

 -
the system data acquisition concentrator 1 1WV1 (85VU) (315534),

 -
the system data acquisition concentrator 2 1WV2 (86VU) (315534).

 (2)
 The DEU type A 200RH is connected to:

 -
The general illumination ballast units LG.

 -
The reading light power unit for test function LW.

 (3)
 The DEU Type B 300RH is connected to:

 -The escape slide bottle pressure sensors 360RH.

 (4)
 The Forward Attendant Panel 120RH is connected to:

 -
the attendant work light relay 2LZ,

 -
the lavatory lighting power supply LQ,

 -
the emergency lighting system WL,

 -
the reading light power supply relay.

 (5)
 The Programming and Test Panel 110RH is connected to:

 -emergency lighting system WL.
 6. Component Description
_____________________
 A. CIDS Director
 (1) Description
 (Ref. Fig. 012)

 **ON A/C 001-049, 051-099, 101-105, 201-299,
 (Ref. Fig. 013)
 1EFF : 001-049, 051-099, 101-105, 151-199, 1 23-73-00Page 36 1201-299, 1Config-1 Aug 01/05R 1 1 1CES 1

 CIDS Director .
 Figure 012

R 1EFF : 001-049, 051-099, 101-105, 151-199, 1 23-73-00Page 37 1201-299, 1Config-1 May 01/05 1 1 1CES 1

 CIDS DATA BUS - Top Line
 Figure 013

R 1EFF : 001-049, 051-099, 101-105, 201-299, 1 23-73-00Page 38 1 1 Config-1 May 01/05 1 1 1CES 1 **ON A/C 151-199,

 (Ref. Fig. 013A)
 **ON A/C 001-049, 051-099, 101-105, 151-199, 201-299,
 (Ref. Fig. 014, 015)
 (a)
 General The director is a 3-Modular-Concept-Unit (3MCU) sized unit. It is installed in the pressurized avionics compartment. The internal construction is modular, which allows straightforward upgrades and improved maintenance feasibility. A memory module called the Onboard Replaceable Module (OBRM) plugs into the front face of the director. Software, basic to the directors internal function, is stored in a nonvolatile memory inside the director. System related software which is likely to be changed or upgraded when options are installed is stored in the OBRM.

 (b)
 Function The CIDS director is the central control and interface component of the CIDS. The CIDS director does these functions:

 -Control of data bus lines,
 -control of CIDS units,
 -interface between flight compartment and avionics compartment.
 1 Handling of three data bus lines:
_
 -
the transmission of digitized audio signals via data bus,

 -
the transmission of control data and commands via data bus,

 -
the adaption of received DEU data.

 2 Control of other CIDS functional units:
_
 -
the forward attendant panel,

 -
the aft attendant panel (via DEU B),

 -
　
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