CABIN INTERCOMMUNICATION DATA SYSTEM (CIDS) - DESCRIPTION AND OPERATION

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1. General
The Cabin Intercommunications Data System (CIDS) is used to operate, control, monitor and test various cabin functions. The functions are controlled by The CIDS if applicable for The configuration of the aircraft and the CIDS software.
The basic CIDS controls these cabin functions:

The Passenger Address (PA)
The Cabin and flight crew interphone
The Passenger Call system
The Passenger lighted signs
The General illumination
The Lavatory smoke system
The Service interphone
The Extended emergency lighting equipment

The monitoring of the pressure of the escape slide bottles installed in the door frames lining and/or the overwing-emergency exit doors.

The Evacuation signaling equipment

In addition to the above, the basic CIDS installation also has the capability to operate, functionally control, monitor and test any optional systems (passenger entertainment (video), advanced passenger services etc.).
The system permits different cabin configurations without the need for complex and costly hardware changes. The existing cabin equipment (loudspeakers, lighting units etc.) is retained and the cabin configuration is accomplished with software changes in the CIDS.
The main components of the CIDS are:

two CIDS directors,
a series of Decoder-Encoder Units (DEU),
a Programming and Test Panel (PTP),
the Forward Attendant Panel (FAP),
the Aft Attendant Panel (AAP),
the Attendant Indicating Panels (AIP).

With the exception of the ACPs, the above units have a Built-in Test Equipment (BITE) facility. The BITE detects faults in the systems connected to the CIDS and in the CIDS units. (The CIDS also uses the flight compartment handset and the passenger compartment handsets).
The CIDS directors are the central control components of the CIDS. Each director receives inputs from various aircraft systems and from the other components in the CIDS. Inputs and outputs to and from the CIDS directors are either connected directly to the directors or through the Decoder-Encoder Units (DEU). Two types of DEUs are installed, a type A and a type B.
The type A DEUs interface between the CIDS directors and:

the Cabin loudspeakers,
the Lighting units,
the Passenger lighted signs,
the Passenger call buttons and signs.

Depending on the aircraft configuration, the type B DEUs interface between the CIDS directors and:

the Attendant handsets,
the Attendant indication panels,
the Area call panels,
the Information signs,
the Emergency lighting power supply units (EPSU),
the Attendant panels,

the Pressure sensors of the emergency slide bottles,

the Emergency evacuation controls and indicators,

Communication between the type A DEUs and the CIDS directors is on two separate data bus lines installed along each side of the aircraft. The type B DEUs are connected to the CIDS directors on a second set of data bus lines. All other aircraft systems used by the CIDS are connected directly to the CIDS directors.
These different types of input signals are converted by the CIDS directors into low level digital data. The CIDS software program controls this digital data. For changes in aircraft configuration or CIDS upgrades only the software program is required to be changed. Two replaceable modules are used to accomplish these changes. To upgrade the CIDS software program, On-board Replaceable Modules (OBRM) are used. These removable memory modules are installed in the front face of the CIDS directors. To facilitate changes in aircraft configuration and system properties a second memory module, the Cabin Assignment Module (CAM), is installed in the Programming and Test Panel (PTP).
Controls for the cabin systems are centrally located at the attendant panels. The attendant handsets are used for interphone communications and for PA announcements. An associated Attendant Indication Panel (AIP) is used for PA/Interphone dialing and cabin call information. The AIP is also used for displaying CIDS warnings. Different colored lights in the Area Call Panels (ACP) give long range visual indications of CIDS information.

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2. Component Location

CIDS associated Components in the Cockpit - Component Location ** ON A/C NOT FOR ALL

FWD Attendant Station and Cockpit Handset - Component Location ** ON A/C NOT FOR ALL

MCDU - Component Location ** ON A/C NOT FOR ALL

CIDS Components in the Cabin - Component Location ** ON A/C NOT FOR ALL

DEU A, DEU Mount and CIDS Director - Component Location ** ON A/C NOT FOR ALL

DEU B and DEU Mount - Component Location ** ON A/C NOT FOR ALL

CIDS Components in the Cabin - Component Location ** ON A/C NOT FOR ALL

FIN	FUNCTIONAL DESIGNATION	PANEL	ZONE	ATA REF
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101RH	DIR-CIDS, 1	87VU	127	23-73-34
102RH	DIR-CIDS, 2	88VU	128	23-73-34
110RH	PROGRAMMING AND TEST PANEL		221	23-73-18
115RH	MODULE-CABIN ASSIGNMENT		221	23-73-19
120RH	FAP		221	23-73-12
126RH	AAP		261	23-73-13
130RH	HANDSET		210	23-73-44
132RH	SUPPORT BRACKET		210	23-73-44
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200RH7	DEU-A	231WW	241	23-31-00
200RH8	DEU-A	232WW	242	23-31-00
200RH9	DEU-A	231ZW	241	23-31-00
200RH10	DEU-A	232ZW	242	23-31-00
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200RH1	DEU-A	221BC	223	23-31-00
200RH2	DEU-A	221BC	224	23-31-00
200RH3	DEU-A	231JW	231	23-31-00
200RH4	DEU-A	232JW	232	23-31-00
200RH5	DEU-A	231QW	231	23-31-00
200RH6	DEU-A	232QW	232	23-31-00
200RH11	DEU-A	241QW	241	23-31-00
200RH12	DEU-A	242QW	242	23-31-00
200RH13	DEU-A	241WW	241	23-31-00
200RH14	DEU-A	242WW	242	23-31-00
200RH17	DEU-A	251MW	251	23-31-00
200RH18	DEU-A	252MW	252	23-31-00
200RH19	DEU-A	251TW	251	23-31-00
200RH20	DEU-A	252TW	252	23-31-00
200RH21	DEU-A	251ZW	251	23-31-00
200RH22	DEU-A	252ZW	252	23-31-00
200RH23	DEU-A	251CX	251	23-31-00
200RH24	DEU-A	252CX	252	23-31-00
200RH25	DEU-A		263	23-31-00
200RH26	DEU-A		263	23-31-00
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200RH7	DEU-A		241	23-31-00
200RH8	DEU-A		242	23-31-00
200RH9	DEU-A		241	23-31-00
200RH10	DEU-A		242	23-31-00
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200RH15	DEU-A	251FW	251	23-31-00
200RH16	DEU-A	252FW	252	23-31-00
200RH27	DECODER/ENCODER UNIT A		243	23-31-00
200RH28	DECODER/ENCODER UNIT A		244	23-31-00
200RH29	DECODER/ENCODER UNIT A		241	23-31-00
200RH30	DECODER/ENCODER UNIT A		242	23-31-00
200RH31	DECODER/ENCODER UNIT A		253	23-31-00
200RH32	DECODER/ENCODER UNIT A		254	23-31-00
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300RH1	DEU-B	222BC	223	23-31-00
300RH5	DEU-B		263	23-31-00
300RH6	DEU-B		263	23-31-00
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300RH4	DEU-B	242QW	200	23-31-00
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300RH4	DEU-B		200	23-31-00
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300RH8	DEU-B		244	23-31-00
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300RH3	DEU-B		253	23-31-00
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300RH7	DECODER/ENCODER UNIT B		243	23-31-00
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320RH1	AIP		221	23-31-00
320RH9	AIP		261	23-31-00
320RH11	AIP	2042VUA	262	23-31-00
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321RH	AIP	2045VUE	200	23-31-00
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330RH1	HANDSET		221	23-73-44
330RH9	HANDSET		261	23-73-44
330RH11	HANDSET		262	23-73-44
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330RH7	HANDSET		251	23-73-44
330RH13	HANDSET		241	23-73-44
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340RH1	AREA CALL PNL		223	23-31-00
340RH2	AREA CALL PNL		224	23-31-00
340RH7	AREA CALL PNL		241	23-31-00
340RH8	AREA CALL PNL		242	23-31-00
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340RH9	AREA CALL PNL	3701VU	263	23-31-00
340RH10	AREA CALL PNL	3701VU	264	23-31-00
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340RH1	AREA CALL PNL	3700VU	223	23-31-00
340RH2	AREA CALL PNL	3700VU	224	23-31-00
340RH7	AREA CALL PNL	3703VU	251	23-31-00
340RH8	AREA CALL PNL	3703VU	252	23-31-00
340RH13	AREA CALL PNL	3702VU	243	23-31-00
340RH14	AREA CALL PNL	3702VU	244	23-31-00

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3. System Description

A. Principle

(1) The Cabin Intercommunication Data System (CIDS) is a microprocessor based system. It operates, controls, monitors and tests these cabin functions:

The passenger address
The passenger call
The passenger lighted signs
The general cabin illumination control
The cabin and flight crew interphone
The lavatory smoke detection
The service interphone (partially integrated into the CIDS)
The extended emergency lighting test
The work light test
The passenger reading lights (control and test)
The boarding music and pre-recorded announcements
The emergency evacuation signaling
The monitor video system sound control.

(2) The Cabin Intercommunication Data System (CIDS) is a microprocessor based system. It operates, controls, monitors and tests these cabin functions:

the passenger address
the passenger call
the passenger lighted signs
the general cabin illumination control
the cabin and flight crew interphone
the lavatory smoke detection
the service interphone (partially integrated into the CIDS)
the extended emergency lighting test
the work light test
the passenger reading lights (control and test)
the escape slide bottle pressure monitoring

(3) 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.

(4) 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.

(5) 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. AMM D/O 31-30-00-00). 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.

B. General
The CIDS uses these components:

32 Decoder Encoder Units (DEU) type A 200RH,
5 Decoder Encoder Units (DEU) type B 300RH,
the forward attendant panel 120RH,
the programming and test panel 110RH,
the cabin assignment module 115RH,
the aft attendant panel 126RH,
the cabin equipment, see DEU type A,
the attendant equipment, see DEU type B.

The components of the CIDS are connected to two identical CIDS directors. The CIDS director 101RH is used as the active director. The CIDS director 102RH is used as the standby director.
The CIDS uses these components:

24 Decoder Encoder Units (DEU) type A 200RH,
4 Decoder Encoder Units (DEU) type B 300RH,
the forward attendant panel 120RH,
the programming and test panel 110RH,
the cabin assignment module 115RH,
the aft attendant panel 126RH,
the cabin equipment, see DEU type A,
the attendant equipment, see DEU type B.

The components of the CIDS are connected to two identical CIDS directors. The CIDS director 101RH is used as the active director. The CIDS director 102RH is used as the standby director.

(1) CIDS Directors 101RH (102RH)
The function of the standby CIDS director 102RH is identical to the function of the active CIDS director 101RH. In normal system operation the outputs from the standby CIDS director are disabled. Inputs and outputs to and from the two CIDS directors are connected in parallel except for:

the power supply,
the special relay,
the director BITE-monitoring connections,
certain outputs to other equipment or systems.

For more information refer to the block diagram, component descriptions and power supply description. Each director contains an OBRM module 101RH1 (102RH1).Inputs and outputs to and from the cabin equipment to the CIDS directors are made via the Decoder Encoder Units (DEU). ARINC links and discrete lines connect the director to individual controls, cockpit equipment and other systems.

(2) Decoder Encoder Unit (DEU) Type A 200RH
The DEUs A 200RH are installed along each side of the passenger cabin. Up to 3 passenger service units (PSU) and 3 passenger information units can be connected to each DEU A. The DEUs A are connected to the directors via a top-line twisted pair data bus. The physical form of this top-line bus are two twisted pairs along each side of the cabin. They are connected to every second DEU. This means that a break in one top-line twisted pair would disable only every second DEU A along one side of the cabin. A resistor terminates each top-line data bus for impedance matching. The DEUs type A are identical. The DEU mount 2010VU or 2014VU include coding switches. This gives each DEU location a different address.

(3) Decoder Encoder Unit (DEU) Type B 300RH
The DEUs B 300RH are installed in their DEU-mounts 2011VU or 2015VU in the door areas. In the door area where no DEU B is installed, empty wired-in mounts 2011VU with full provisions are installed. The DEUs B are connected to the flight attendant stations and safety equipment.
The DEUs B are connected with discrete lines to:

the area call panels,
the attendant handsets,
the slide-bottle and door-bottle pressure-sensors,
the EVAC switches and lamps,
the emergency power supply units,

The aft attendant panel receives and transmits serial data via a RS232 link, it is also connected to the DEU type B with discrete lines. A serial RS232 link also transmits data to each AIP. Discrete connections provide AIP power and reception of AIP BITE status. The DEUs type B connect to the directors via a middle-line twisted pair data bus. One twisted pair cable on each aircraft side connects to all DEUs type B on that side. A resistor 310RH terminates each middle-line data bus cable for cable impedance matching.
The DEUs type B are identical. Coding switches in each DEU mount are used to define a different address for each DEU B location.

(4) Decoder Encoder Unit (DEU) Type B 300RH
The DEUs B 300RH are installed in their DEU-mounts 2011VU or 2015VU in the door areas. In the door area where no DEU B is installed, empty wired-in mounts 2011VU with full provisions are installed. The DEUs B are connected to the flight attendant stations and safety equipment.
The DEUs B are connected with discrete lines to:

the area call panels,
the attendant handsets,
the slide-bottle and door-bottle pressure-sensors,
the emergency power supply units,

(5) Forward Attendant Panel 120RH
The forward attendant panel 120RH transmits data to the directors via a serial ARINC 429 link which are connected to both directors in parallel. For transmission of data from the directors to the forward attendant panel, two separate ARINC links are provided, one from each director. Separate discrete lines from the panel connect to the power supply units of reading lights, the attendant work lights and lavatory lights. Discrete lines also connect to an adjacent DEU B for EVAC control.

(6) Programming and Test Panel 110RH
The programming and test panel 110RH transmits data to the director via a serial ARINC 429 link which is connected to both directors in parallel. For transmission of data from the director to the panel, two separate ARINC links are provided, one from each director. The Cabin Assignment Module (CAM) 115RH plugs directly into the front face of the panel. Interaction between director and CAM is via the programming and test panel ARINC links.

(7) Forward Attendant Panel 120RH
The forward attendant panel 120RH transmits data to the directors via a serial ARINC 429 link which are connected to both directors in parallel. For transmission of data from the directors to the forward attendant panel, two separate ARINC links are provided, one from each director. Separate discrete lines from the panel connect to the power supply units of the reading lights, the attendant work lights and lavatory lights.

(8) Programming and Test Panel 110RH
The programming and test panel 110RH transmits data to the director via a serial ARINC 429 link which are connected to both directors in parallel. For transmission of data from the directors to the panel, two separate ARINC links are provided, one from each director. The Cabin Assignment Module (CAM) 115RH plugs directly into the front face of the panel. Interaction between director and CAM is via the programming and test panel ARINC links.

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4. Power Supply

Power Supply - CIDS Director, FAP and PTP ** ON A/C NOT FOR ALL

Power Supply NORM BUS - Top Line ** ON A/C NOT FOR ALL

Power Supply ESS BUS + HOT BAT BUS - Top Line ** ON A/C NOT FOR ALL

Power Supply ESS BUS - Top Line ** ON A/C NOT FOR ALL

Power Supply - Middle Line ** ON A/C NOT FOR ALL

The service bus 601PP and the essential bus 401PP supply electrical power to the CIDS.
The CIDS can operate in the normal mode or in the emergency mode.
The service bus 601PP, the essential bus 401PP and the hot battery bus 702PP supply electrical power to the CIDS.
The CIDS can operate in the normal mode or in the emergency mode.

A. Normal Mode
In the normal mode the CIDS uses 28VDC supplied from the service bus 601PP.

In the normal mode the service bus 601PP supplies 28VDC to the CIDS.
The DIR 2 is in standby.

B. Emergency Mode

(1) In the emergency mode the essential bus 401PP supplies 28VDC to the CIDS. The emergency system is used if there is a failure of the service bus 601PP and the essential bus 401PP is available.
The power consumption is reduced to a minimum.
The PTP and the FAP are not supplied.
The system operates with these minimum functions:

the PA system,
the Cabin Interphone,
the EVAC (if installed).

(2) Power transfer switching

Power Supply ESS BUS - Top Line ** ON A/C NOT FOR ALL

If there is no electrical power from the service bus 601PP, the essential bus 401PP supplies the top-lines only when an audio signal is present. If there is no audio signal the respective director operates the top-line cut-off relay 106RH to stop the essential power supply to the top-lines.

(3) In the emergency mode the essential bus 401PP or the hot battery bus 702PP supplies 28VDC to the CIDS.

The essential bus 401PP supplies 28 V DC to the CIDS if there is a failure of the service bus 601PP.
The hot battery bus 702PP supplies 28 V DC to the CIDS if both the service bus 601PP and the essential bus 401PP are not available. For this reason, the emergency lighting switch 4WL must be in the ARM or ON position.
When the essential bus 401PP or the hot battery bus 702PP supplies the CIDS, the power consumption is reduced to a minimum.
The DIR 2 is in standby, the PTP and the FAP are not supplied.
The system operates with the subsequent minimum functions:
the PA system,
the Cabin interphone,
the EVAC (if installed).

(4) Top Line cut-off switching

Power Supply ESS BUS + HOT BAT BUS - Top Line ** ON A/C NOT FOR ALL

If there is no electrical power from the service bus 601PP, the essential bus 401PP or the hot battery bus 702PP supplies the Top-Lines only when an audio signal is present. If there is no audio signal the respective director operates the Top-Line cut-off relay 106RH to stop the essential or the hot battery bus power supply to the Top-Lines.

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5. Interface

A. CIDS Equipment Connections

(1) The CIDS Director 101RH (102RH) is connected to:

the Audio management unit 1RN (81VU) (235134)
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 EVAC horn 5WP (48VU) (256300)
the EVAC SIGNAL switch 2WP (21VU) (256300)
the EVAC COMMAND key 3WP (21VU) (256300)
the EVAC HORN SHUT OFF pushbutton 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 CIDS Director 101RH (102RH) is connected to:

the Audio management unit 1RN (81VU) (235134)
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 EVAC horn 5WP (48VU) (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).

B. CIDS Equipment Connections

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

the General illumination ballast units (LG).
the Reading light power unit for test function (LW).

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

the Escape slide bottle pressure sensors (360RH).

(3) 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.

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

Emergency lighting system (WL).

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6. Component Description

A. CIDS Director FIN: 101-RH FIN: 102-RH

(1) Description

CIDS Director ** ON A/C NOT FOR ALL

CIDS DATA BUS - Top Line ** ON A/C NOT FOR ALL

CIDS Director - Block Diagram ** ON A/C NOT FOR ALL

CIDS DATA BUS - Middle Line ** ON A/C NOT FOR ALL

(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 gives 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 through the data bus
The transmission of control data and commands through the data bus
The adaptation of received DEU data.

2 Control of other CIDS functional units:

The forward attendant panel
The aft attendant panel (through the DEU B)
The programming and test panel
The data transfer to the second director
The area call panel (through the DEU B)
The attendant indication panel (through the DEU B).

3 Interface between the flight compartment and the avionics compartment for:

The handling of cabin systems-related inputs/outputs
The control of interfaces to other systems in the flight compartment and avionics compartment.

4 Realization of the system function of connected cabin systems.

5 Realization of the programming function:

The director keeps the current cabin layout and and these properties of layout-related equipment in its memory, that it can store.

6 Realization of the test function:

The director performs the test of all connected cabin systems and of the CIDS.

7 Activation of emergency mode with minimum power consumption.

(c) Architecture
The director changes all signals from its inputs into a low-level digital format. It stores signals temporarily, changes the formats of these signals and transmits them. To do this, the director has the following functional modules:

The audio input module
The audio output module
The digital input/output module
The CIDS bus-interface
The power supply
The microcomputer.

The modules have sufficient inputs/outputs for expansion of the basic CIDS functions.

1 Audio Input and Output modules
The audio input and output modules receive and send signals from these sources:

The flight compartment PA
The service interphone
The boomset microphones
The entertainment equipment
All other audio sources are separately buffered and the audio input module shapes them where necessary.

The signals are then multiplexed into PA-zones and DEU audio channels together with the outputs of programmable chime, telephone tone and evacuation tone-generators. Under control of the processing module, the input module transfers the audio signal to the bus interface module for transmission to the DEUs.
It also routes audio signals to the audio output module. The audio outputs from the input module are designed to drive a Passenger Entertainment System (PES)- Multiplexer with three zones of audio. Digitally-encoded audio signals are sent from the audio input module and from the CIDS bus interface to the audio output module. The audio signals to the CIDS bus interface are sent from the DEU type B on the middle line bus. The four PA amplifiers connect to the service interphone system, Audio Management Unit (AMU) (interphone output and PA output) and cockpit PA handset.

2 Digital Input/Output Module
The digital I/O module contains the circuitry necessary for the director to handle ARINC 429 and RS232C links, and discrete inputs/outputs. The ARINC 429 serial interface is programmable in speed of operation. It is the interface between:

The directors internal, parallel, low-level digital environment
The serial, higher-level, digital environment of ARINC 429 communication.

Shielded twisted pair cables make the connections. The RS232 interface is provided for test-purposes and is not used for regular CIDS operation. As with the ARINC 429 interface (but with a different protocol and signal-level) the RS232 module interfaces serial data communications equipment to the directors internal parallel data bus.
The director gets inputs from:

The sensors
The switches
The other equipment in two basic states.

The two basic states are open-circuit and active ground, or open-circuit and 28 V DC. In the same way, connected equipment requires either presence of an active ground or 28 V DC, or an open-circuit for their function. The discrete interface provides the necessary isolation and buffers the inputs/outputs, and interfaces them to the director's microcomputer.

3 CIDS Bus Interface
The CIDS bus interface handles all communication between the director and DEUs. Top-line data buses used for DEUs A, and middle-line data buses for DEUs B. Four top lines and two middle lines are provided. One bus protocol is defined for each line type, for example one protocol for the top lines and another for the middle lines. Each protocol allows the director to transmit data to the connected DEUs and to receive data from the DEUs. The respective bus protocol handles all digitized audio signals, control data and commands to the DEUs. Coded addresses are also included which permit the director to address the DEUs individually. The contents of data depends on the respective inputs and outputs and on a zoning table stored in the director. The bus interfaces tests each connected bus line for breaks.

4 Power Supply
The power unit derives all necessary internal supply voltages from the 28 V DC essential and service bus inputs.

5 Microcomputer and OBRM
Under control of its high-performance microprocessor, the microcomputer performs these functions:

The collection of discrete CIDS data bus information
The generation of discrete information to be transferred via the CIDS data bus
The monitoring of CIDS data bus connection
The control of chime, telephone tone and evacuation tone-generators
The collection and processing of discrete input information
The control of discrete output information
The communication with equipment connected via the serial interfaces
The built-in test function check
The BITE operation.

Fundamental director control software and data tables, including back-up layout and system properties information, are permanently stored in the processing module. It allows a basic, limited operation of CIDS in the absence of the CAM. The Onboard Replaceable Module (OBRM) compliments this permanently stored data. The OBRM is a solid-state memory module and plugs into the front of the director.
The software routines which makes the CIDS (and some parts of the director-control software) function, are stored in the OBRM. Installation of a different OBRM updates these software routines. The details of the aircraft cabin layout and of the system properties (chimes used, etc.) are permanently stored in the Cabin Assignment Module (CAM). This plugs into the front of the programming and test panel. The director copies the CAM data into a semi-permanent (electrically-erasable) memory during system initialization. It is termed the 'zoning table'. Once copied, the zoning table remains in the processing module memory until the next 'copy' from the CAM is loaded . A similar type of director memory is assigned as the CIDS 'BITE memory'. CIDS components and connected system faults are stored in the BITE memory for reporting to the aircraft CFDS when requested.
In addition to providing the regular CIDS system functions, the processing module implements monitoring of:

The director operation
The operation of connected systems and components
The data bus performance
The BITE status of the other director.

(2) Operation

CIDS Director - Connections ** ON A/C NOT FOR ALL

(a) Initialization
Two identical directors 101RH and 102RH are installed in the avionics compartment. An identical OBRM, 101RH1 and 102RH1 respectively, plugs into each director. Each director has a dedicated ARINC transmission link to the other, to do a cross check of each others BITE status. With the exception of the dedicated ARINC links, they are connected in parallel as shown below:

Most of the ARINC 429 links
The power supply lines
All inputs and outputs of the two directors.

The power connections are arranged such that director 1 is normally fully active and in control of the CIDS. Director 2 is normally partially active, in a 'hot-standby' mode. The two units basically run in parallel with exactly the same system-status information at any given moment. Director 2 has its outputs deactivated.
On CIDS energization or reset:

All director interfaces are disabled
All Random Access Memory (RAM) is cleared
The system software flags are present
The directors are initialized.

A failure in the initialized process in CIDS director 101RH causes:

The CIDS CAUTION light on the Forward Attendant Panel (FAP) to come on
Display of CIDS CAUTION message at the ECAM
A deactivation of the CIDS director 101RH hardware
A switchover of control to CIDS director 102RH
the CIDS director 101RH software execution halt.

Once the directors have been initialized, the data contained in the CAM is copied into their zoning tables. In the absence of the CAM, the directors own back up data is used.
The directors now hold the data necessary for the active unit to configure and initialize the:

Cabin system functions
Director interface modules
DEUs and connected equipment and components.
For each PA amplifier in each DEU A, the gain, the frequency characteristic, and the channel-assignment is programmed.
Forward Attendant Panel (FAP)
Programming and Test Panel (PTP).

When this has been completed, the CIDS is fully operational.

(b) BITE Operation
The built-in test equipment of the director detects at least 95 % of the failures that could occur in the director. These detected failures are isolated with a confidence level of better than 85 %. The director performs a self-test each time it is initially switched on or reset. The self-test checks for correct operation of the whole director and of its individual parts.
The self-test is repeated periodically. The director periodically loads each CIDS data bus line with a DC current. When a current flow occurs the line is known to be serviceable.
The equipment shown below have their own BITE functions, and signal their BITE status to the director:

Each DEU
The Programming and Test Panel (PTP)
the Forward Attendant Panel (FAP)
the connected equipment such as PES and PSS.

The DEUs are able to test the cabin equipment to which they are connected.
The director keeps all BITE results in a BITE-dedicated memory. Failures show on:

The CIDS CAUTION light
The ECAM status page
The ECAM warning
The respective Multifunction Control & Display Unit (MCDU) pages
The Programming and Test Panel (PTP).

The following failures or combinations of failures cause immediate indications at the Electronic Centralized Aircraft Monitoring (ECAM) and the Programming and Test Panel (PTP):

1 'CIDS INOP' on ECAM
The director output 'CIDS OPERATION STATUS' to the SDAC is at active ground when the CIDS is operative. A change in this state causes to display 'CIDS 1+2 FAULT' on upper ECAM and 'CIDS INOP ' on lower ECAM when:

Both directors have a failure
More than 50 % of all DEU A or 20 % of adjacent DEU A (zonewise) have a failure or
More than 50 % of all NS-FSB Signs and PA inoperative (resp. DEU A) have a failure (the CIDS CAUTION light also comes on)
All DEU B with connected handset have a failure (the CIDS CAUTION light also comes on).

2 'CIDS CAUTION' on ECAM
The directors output 'CIDS CAUTION' to the SDAC is at active ground when there are no failures in the CIDS. A change in this state results in 'CIDS CAUTION' 'CIDS 1' or 'CIDS 2' at the ECAM when:

One director has a failure
There is no data from the other director via crosslink.
The director continues to signal CIDS CAUTION to the SDAC until the fault is corrected.

The director continues to signal CIDS CAUTION to the SDAC until the fault is corrected.

3 CIDS CAUTION light activated at the Forward Attendant Panel (FAP)
The director sends a signal to the FAP via the ARINC link to activate the CIDS CAUTION light when:

One director has a failure
Two directors have a failure
All DEU B with connected handsets have a failure
More than 50% of all DEU A or 20% of adjacent DEU A per zone have a failure
No data from SDCU channel 1 and 2 is available
The drainmast system have a failure
The emergency slide-bottle pressure is low
The slide bottle pressure is low
The door bottle pressure is low
The lavatory smoke detection has a failure
One DEU A has a failure
One DEU B has a failure
The CIDS top bus has a failure
The CIDS mid bus has a failure
The FAP has a failure
The PTP has a failure
The CAM has a failure
No data from FAP is available
No data from CAM is available
No data from PTP is available.

In flight, you can reset the CIDS CAUTION light, but it comes on again on the ground (landing gear down and locked). The light cannot be reset on the ground. When a CIDS CAUTION occurs, the respective failure message shows on the Programming and Test Panel (PTP). From the PTP you can send a command to the director to perform or start a CIDS component test. This is described under 'System Testing and Programming'.
The function of the director related to the systems that follow is described in the 'System Operation' section:

The passenger address system
The interphone system
The lighted signs
The passenger call.

For other systems, refer to the appropriate system chapters.
The other aspects of the operation of the CIDS director are described in the text that follows. (Ref. Fig. 010).

(3) Operation

CIDS Director - Connections ** ON A/C NOT FOR ALL

Most of the ARINC 429 links
The power supply lines
All inputs and outputs of the two directors.

All director interfaces are disabled
All Random Access Memory (RAM) is cleared
The system software flags are present
The directors are initialized.

A failure in the initialized process in CIDS director 101RH causes:

The CIDS CAUTION light on the Forward Attendant Panel (FAP) to come on
Display of CIDS CAUTION message at the ECAM
A deactivation of the CIDS director 101RH hardware
A switchover of control to CIDS director 102RH
the CIDS director 101RH software execution halt.

Cabin system functions
Director interface modules
DEUs and connected equipment and components.
For each PA amplifier in each DEU A, the gain, the frequency characteristic, and the channel-assignment is programmed.
Forward Attendant Panel (FAP)
Programming and Test Panel (PTP).

When this has been completed, the CIDS is fully operational.

Each DEU
The Programming and Test Panel (PTP)
the Forward Attendant Panel (FAP)
the connected equipment such as PES and PSS.

The DEUs are able to test the cabin equipment to which they are connected.
The director keeps all BITE results in a BITE-dedicated memory. Failures show on:

The CIDS CAUTION light
The ECAM status page
The ECAM warning
The respective Multifunction Control & Display Unit (MCDU) pages
The Programming and Test Panel (PTP).

The following failures or combinations of failures cause immediate indications at the Electronic Centralized Aircraft Monitoring (ECAM) and the Programming and Test Panel (PTP):

Both directors have a failure
More than 50 % of all DEU A or 20 % of adjacent DEU A (zonewise) have a failure or
More than 50 % of all NS-FSB Signs and PA inoperative (resp. DEU A) have a failure (the CIDS CAUTION light also comes on)
All DEU B with connected handset have a failure (the CIDS CAUTION light also comes on).

One director has a failure
There is no data from the other director via crosslink.
The director continues to signal CIDS CAUTION to the SDAC until the fault is corrected.

The director continues to signal CIDS CAUTION to the SDAC until the fault is corrected.

3 CIDS CAUTION light activated at the Forward Attendant Panel (FAP)
The director sends a signal to the FAP via the ARINC link to activate the CIDS CAUTION light when:

One director has a failure
Two directors have a failure
All DEU B with connected handsets have a failure
More than 50% of all DEU A or 20% of adjacent DEU A per zone have a failure
No data from SDCU channel 1 and 2 is available
The drainmast system have a failure
The emergency slide-bottle pressure is low
The slide bottle pressure is low
The door bottle pressure is low
The lavatory smoke detection has a failure
One DEU A has a failure
One DEU B has a failure
The CIDS top bus has a failure
The CIDS mid bus has a failure
The FAP has a failure
The PTP has a failure
The CAM has a failure
No data from FAP is available
No data from CAM is available
No data from PTP is available.

The passenger address system
The interphone system
The lighted signs
The passenger call.

For other systems, refer to the appropriate system chapters.
The other aspects of the operation of the CIDS director are described in the text that follows. (Ref. Fig. 010).

(4) Emergency Mode Activation
For reduction of power consumption, the director has the capability to activate an emergency mode. The emergency mode causes all sections of the director which are not permanently in use to switch off. The sections of the director and the cabin systems control circuits which are not switched off are:

The power supply
The microcomputer
The CIDS data bus driver
The PA system
The interphone.

The power supply for top lines is also disconnected. This is done when no power is detected at the 'normal power sensing' input and no PA announcement is made. The director then applies a 28 V DC output to the 'Top Line Cut-off Relay 106RH' output.

(5) Power Sensing
As long as power is available at power input one, it supplies the director. In the event of a power failure at this input, the director automatically switches over to supply input two. If power is detected at the 'Normal Power Sensing' input (and the director is operative), then the output 'Power Transfer Relay' is switched to active ground. The connected relay 105RH is held in the energized state. Failure in the output de-energizes the relay. This connects essential power and transfers control of the top-line cut-off relay 106RH to the other director.

(6) External Test Equipment Connection
An RS232C 7-wire bus is provided on the main director connector. External test equipment is connected to this connector.

(7) Bus Protocol Line A

CIDS Data Bus Protocols ** ON A/C NOT FOR ALL

Data is transmitted via the data bus in frames of constant length. The director signals the start of a frame with a unique SYNC-sequence. The director then continues with the transmission of Pulse Code Modulation (PCM) data of six audio channels.
After this the director addresses one DEU and transmits discrete data or a command. It then pauses and the previously addressed DEU can then transmit one data word, which terminates the frame. The timeslot for transmission of the DEU is called a 'window' and is long enough to cope with transients and propagation times.
In case of collision, the protocol ensures correct synchronization of the next frame. For discrete data transmission, the director addresses all DEUs in a sequence, one per frame. For audio transmission, all audio data is provided in each frame (six channels). A command in an initial sequence programs each DEU to receive up to two channels. This is dependent on the seat layout of the cabin. This may be altered with a new program of the director's zoning table contained in the CAM.
All data words on the data bus have a length of twelve bits.
The data transfer on the top data line contains data for these cabin system components:

The passenger lighted signs
The reading lights
The general cabin illumination
The passenger address loudspeaker
The call switch and call light.

(8) Bus Protocol Line B

CIDS Data Bus Protocols ** ON A/C NOT FOR ALL

Data are transmitted via the data bus in frames of constant length. The director signals the start of a frame with a unique SYNC-sequence. Next, the director addresses one DEU and transmits discrete data or a command in this sequence:

The broadcast interphone channel
The captain audio channel.

Then come ten windows for audio transmission from the DEUs. The director allocates a DEU to a certain window with a respective command. Normally not all windows are used. In case of collision, the protocol ensures correct synchronization of the next frame. At the end of a frame the DEU addressed at the beginning of the frame has the opportunity to transmit discrete information to the director. All data words on the data bus have a length of twelve bits. The data transfer on the middle data line contains data for these cabin system and components:

The passenger address
The cabin and flight crew interphone
The attendant indication panel
The area call panel
The lavatory smoke detection
The aft attendant panel.

(9) Audio Signal Handling
These inputs are provided in the director for connection of audio signals from:

The AMU (PA and interphone)
The flight compartment handset (PA) service interphone
The pre-recorded announcement sources
The PES tape reproducer.

Additionally, interphone audio arrives via the middle line data bus. There are also internally generated chimes and telephone tones.

(a) Balanced PA Inputs
Each balanced PA input has a software programmable filter. It is adjusted according to the zoning table in nine bass-range steps and nine treble-range steps.

(b) Unbalanced PA Inputs
The Automatic Gain Control (AGC) circuits control the level of each unbalanced microphone input and middle line inputs. Furthermore, each microphone input is high pass filtered according to the zoning table.

(c) Chime Generation
The director contains three independent programmable chime generators. The zoning table data controls the sequences and combinations of each chime. The table also specifies when chimes are generated.

(d) Channeling
When the director has processed the audio inputs, (and generated any sounds),it digitizes them and multiplies them according to its zoning table. The director assigns audio to software-defined combinations (of six middle-line data bus audio channels) for up to three passenger and three attendant zones in the cabin.

(10) Emergency Mode Activation
For reduction of power consumption, the director has the capability to activate an emergency mode. The emergency mode causes all sections of the director which are not permanently in use to switch off. The sections of the director and the cabin systems control circuits which are not switched off are:

The power supply
The microcomputer
The CIDS data bus driver
The PA system
The interphone.

(11) Power Sensing
As long as power is available at power input one, it supplies the director. In the event of a power failure at this input, the director automatically switches over to supply input two. If power is detected at the 'Normal Power Sensing' input (and the director is operative), then the output 'Power Transfer Relay' is switched to active ground. The connected relay 105RH is held in the energized state. Failure in the output de-energizes the relay. This connects essential power and transfers control of the top-line cut-off relay 106RH to the other director.

(12) External Test Equipment Connection
An RS232C 7-wire bus is provided on the main director connector. External test equipment is connected to this connector.

(13) Bus Protocol Line A

CIDS Data Bus Protocols ** ON A/C NOT FOR ALL

The passenger lighted signs
The reading lights
The general cabin illumination
The passenger address loudspeaker
The call switch and call light.

(14) Bus Protocol Line B

CIDS Data Bus Protocols ** ON A/C NOT FOR ALL

The broadcast interphone channel
The captain audio channel.

The passenger address
The cabin and flight crew interphone
The attendant indication panel
The area call panel
The lavatory smoke detection
The aft attendant panel.

(15) Audio Signal Handling
These inputs are provided in the director for connection of audio signals from:

The AMU (PA and interphone)
The flight compartment handset (PA) service interphone.

Additionally, interphone audio arrives via the middle line data bus. There are also internally generated chimes and telephone tones.

(a) Balanced PA Inputs
Each balanced PA input has a software programmable filter. It is adjusted according to the zoning table in nine bass-range steps and nine treble-range steps.

B. Decoder Encoder Units (DEU)

(1) Description

DEU - Physical Appearance ** ON A/C NOT FOR ALL

(a) General
CIDS uses two types of DEUs, type A 200RH and type B 300RH. The director transmits address coded data to all DEUs of one type, but only one DEU A responds. The addressed DEU serves as an interface between the encoded bus data and the connected cabin systems and components.

(b) Common Functions
Each DEU has specialized functions appropriate to the connected systems. But these functions are the same to both types of DEU:

The adaptation of received data bus signals
The comparison of received addresses with wired DEU addresses
The processing of addressed commands and controls
The commands to control the cabin system interface
The conversion of processed control data for initiation of the interface circuitry
The adaptation of cabin system interface signals
The processing of inputs from cabin systems
The transmission of data at assigned intervals via the data bus
The fail passive for data bus transmission and reception in case of DEU failure
The fail passive for system interface in case of DEU failure
The transmission of status results to the director
The short-circuit protection of discrete outputs
The activation of emergency mode with minimum power consumption
The conversion of preselected audio channel.

The Passenger address loudspeakers
The Passenger call switches and lamps
The Cabin illumination ballast-units
The Passenger lighted signs
The Passenger reading lights.

The DEU A has these specialized functions:

A test of lamp current
A test of connected loudspeaker impedance and level
A frequency filtering according to bus commands.

(d) DEU B Functions
The DEU B has interfaces with these components:

The Attendant handset(s)
The Attendant Indication Panels (AIP)
The Area Call Panels (ACP)
The Emergency slide-bottle pressure-sensors
The Information signs
The Emergency evacuation controls and indicators
The Emergency-Lighting Power-Supply units (EPSU)
The Aft Attendant Panel (AAP).

(2) Description

DEU - Physical Appearance ** ON A/C NOT FOR ALL

(b) Common Functions
Each DEU has specialized functions appropriate to the connected systems. But these functions are the same to both types of DEU:

The adaptation of received data bus signals
The comparison of received addresses with wired DEU addresses
The processing of addressed commands and controls
The commands to control the cabin system interface
The conversion of processed control data for initiation of the interface circuitry
The adaptation of cabin system interface signals
The processing of inputs from cabin systems
The transmission of data at assigned intervals via the data bus
The fail passive for data bus transmission and reception in case of DEU failure
The fail passive for system interface in case of DEU failure
The transmission of status results to the director
The short-circuit protection of discrete outputs
The activation of emergency mode with minimum power consumption
The conversion of preselected audio channel.

The Passenger address loudspeakers
The Passenger call switches and lamps
The Cabin illumination ballast-units
The Passenger lighted signs
The Passenger reading lights.

The DEU A has these specialized functions:

A test of lamp current
A test of connected loudspeaker impedance and level
A frequency filtering according to bus commands.

(d) DEU B Functions
The DEU B has interfaces with these components:

The Attendant handset
The Attendant Indication Panels (AIP)
The Area Call Panels (ACP)
The Emergency slide-bottle pressure-sensors
The Information signs
The Emergency-Lighting Power-Supply units (EPSU).
The Aft Attendant Panel (AAP).

(3) Operation

DEU Connection to Data Bus Power Supply and Address Coding ** ON A/C NOT FOR ALL

DEU A - Connections to Cabin Systems ** ON A/C NOT FOR ALL

DEU B - Connections to Cabin Systems ** ON A/C NOT FOR ALL

(a) CIDS Power-Up
When the CIDS is powered-up or reset, the director follows a power-up routine. This includes the initialization and testing of each DEU and connected equipment. Each of the two DEU A PA amplifiers are assigned to one of the six top-line audio channels. The gain and frequency response of each amplifier is set. The test results are transmitted to the director which compares them with its programmed data to decide on their OK/NOT OK status.

(b) DEU A Power-Up Tests
These are tested at this stage

1 Discrete outputs

All discrete outputs are switched to the passive state. Then each output is activated separately and looped back to the DEU gate array and measured. All the discrete outputs are then switched to the active state. The director checks that all the DEU current-sensing bits are activated. There is no test available for the opto-coupled outputs.

2 Discrete inputs

The director checks that no discrete inputs are active. Some input circuit failures cannot be detected by the director. These failures are only apparent when the appropriate input is activated. It is also possible that a fault in equipments connected to the director to mistaken for a faulty input circuit.

3 PA amplifier volume control, frequency control and audio output

The director generates a test signal, and the DEU audio outputs are monitored for correct action of the respective circuits. These tests are only done if a loudspeaker is connected.

4 No smoking, fasten seat belt, return to seat and passenger call lamps (not applicable for LED NS/FSB signs)

All lamp-outputs are set to OFF. The director controls the DEU's current-limit threshold for the lamp drivers. It also commands the DEU to turn on one lamp at a time. In this way, any open-circuit lamps are detected. This test also detects a failed current-detector.

5 The DEU A power supply, gate array, bus interface and BITE status are also checked.

The major DEU tests are continuously done for the whole time that the CIDS is switched on. In normal operation the director transmits information continuously to the DEUs. When a DEU is addressed, it must respond with a parity bit-coded message. If this response message is absent (or the parity bit is wrong for a minimum of 4 transmissions), then the DEU is declared to be unserviceable.

1 Discrete outputs, as for DEU A described in paragraph 6.B.(2)(b)-1.

2 Discrete inputs, as for DEU A described in paragraph 6.B.(2)(b)-2.

3 Audio Input/Output. The DEU B is commanded to perform a loop-back operation, where the handset output is electronically connected to the handset input. The director transmits a test signal to the DEU B. After all the audio circuitry of the DEU B have processed this signal, it is transmitted back to the director. The director can analyse the signal for frequency response and audio level. The test is also automatically performed, when a handset is unhooked. Signal-to-noise ratio, total distortion, and handset supply are not tested.

4 Serial Input/Output. Under control of the director, several types of tests are performed to check for faulty operation:

the register read/write test,
the timing test,
the status bit test,
the parity bit test,
the data loopback test (in conjuction with the connected hardware).

The results of the loopback test assume the connected device is operational.

5 EVAC indicator lamp. As for discrete outputs described in paragraph 6.8.(2)(b)-1.

6 Attendant Indication Panel (AIP) testing. The DEU checks the status of the AIP BITE.

7 The DEU B power supply, gate array, bus interface and BITE status are also checked. The procedure is as for DEU A, described in paragraph 6.B(2)(b)-6. This is continuously done while the CIDS is switched on.

(d) Interfacing and control of cabin equipment sub-sections:

1 General Cabin Illumination Control
This director addresses each of the four connected illumination units on command from:

the FWD ATTND panel,
the Programming and Test Panel (PTP),
the response to certain discrete inputs.

The DEU responds and switches each of the three outputs to the addressed ballast unit to open-circuit ('logic O') or to 28 V DC ('logic 1'). The table below shows the illumination level versus logic levels:

CONNECTOR PIN 1, 4, 2,5, 3,6,

9,12, 10,13 11,14

OPERATION MODE S I G N A L

-------------- ---------------------------

bright 0 0 0

dim 1 (50 %) 1 0 0

dim 2 (10 %) 0 1 0

off 0 0 1

DEU or CIDS failure results in no 28 V DC outputs. This gives a 100 % illumination fail-state situation.

2 Flashing of Audio Control Panel and Lighted Sign Lamps
The DEU responds to lamp ON or OFF control commands. It latches the respective outputs at 28 V DC or at open circuit. The director causes the flashing of any of these lamps by repeatedly transmitting ON commands followed by OFF commands.

3 Emergency Lighting Test (DEU B)
When activated at the programming and test panel, Emergency Power Supply Units (EPSUs), connected to the DEU, are interrogated for their status. Fault situations in the EPSU are held in coded form. The code number corresponds to the fault type. A DEU B reads this failure number:
The serial clock output pulses to the ON-state. The EPSU then replies and transmits an ON pulse to the DEUs 'Serial In' input, interpreted as a logic one. The process is repeated until there is a logic zero response from the EPSU. The number of received logic ones corresponds to the EPSU failure number.

4 Reading Lights (DEU A)
All connections to the reading lights system are opto-coupled to maintain isolation of the DEUs DC ground from the reading lights AC ground. The director receives activation commands for lights via the PSS. It then signals to the respective DEU A to turn on the requested light. The DEU A then provides a connection between the respective reading light connection and the AC ground connection (from the reading light unit).
The lights and lights Printed Circuit Boards (PCBs) are tested on command from the director. The R/L TEST output is activated. The DEU reads the logic level present on the R/L LAMP FAIL and R/L PCB FAIL inputs. It transmits the information to the director. This test is done via the programming and test panel.

5 Attendant Handsets (DEU B)
Up to two handsets may be connected in parallel to each DEU B. The DEU performs hook-off sensing, and decodes the dial information which arrives on the handset microphone line.

6 Area Call Panels (ACP) (DEU B)
Two sets of ACP outputs are provided. Each set can drive up to two ACPs in parallel.

7 Attendant Indication Panels (AIP) (DEU B)
The director operates the AIPs via DEU B. A serial link from the DEU B can be connected to two AIPs in parallel. Separate service bus 28 V DC outputs and AIP BITE inputs are provided for each AIP.

8 EVAC Equipment (DEU B)
The DEU B has two essential 28 V DC outputs to drive EVAC indicator lights. It also has three inputs for EVAC pushbutton connection. The input detection circuitry is on the essential bus and remains functional in an aircraft emergency.

9 Additional Attendant Panel (DEU B)
The DEU B has a serial input, output and normal 28 V DC for connection of an additional attendant panel.

(e) Emergency Mode Activation
In an aircraft emergency, the DEU operates in emergency mode. All impermanently used parts of the DEU switch off. The DEU A PA circuits and DEU B interphone and EVAC circuits remain energized.

(f) Fail Safe States
When a failure of the data bus interface, the director, or the data bus occurs the DEU maintains the current status of the discrete cabin systems outputs for approximately 3 minutes. After this delay the outputs switch into their pre-defined fail safe states. All audio input/outputs are immediately switched off.

(g) DEU Addressing
The coding switch in the DEU mount gives each DEU a different address. This method lets you remove, interchange and replace DEUs without the need to consider the address.

(4) Operation

DEU Connection to Data Bus Power Supply and Address Coding ** ON A/C NOT FOR ALL

DEU A - Connections to Cabin Systems ** ON A/C NOT FOR ALL

DEU B - Connections to Cabin Systems ** ON A/C NOT FOR ALL

(b) DEU A Power-Up Tests
These are tested at this stage

1 Discrete outputs

All discrete outputs are switched to the passive state. Then each output is activated separately and looped back to the DEU gate array and measured. All the discrete outputs are then switched to the active state. The director checks that all the DEU current-sensing bits are activated. There is no test available for the opto-coupled outputs.

2 Discrete inputs

The director checks that no discrete inputs are active. Some input circuit failures cannot be detected by the director. These failures are only apparent when the appropriate input is activated. It is also possible that a fault in equipments connected to the director to mistaken for a faulty input circuit.

3 PA amplifier volume control, frequency control and audio output

The director generates a test signal, and the DEU audio outputs are monitored for correct action of the respective circuits. These tests are only done if a loudspeaker is connected.

4 No smoking, fasten seat belt, return to seat and passenger call lamps (not applicable for LED NS/FSB signs)

All lamp-outputs are set to OFF. The director controls the DEU's current-limit threshold for the lamp drivers. It also commands the DEU to turn on one lamp at a time. In this way, any open-circuit lamps are detected. This test also detects a failed current-detector.

5 The DEU A power supply, gate array, bus interface and BITE status are also checked.

The major DEU tests are continuously done for the whole time that the CIDS is switched on. In normal operation the director transmits information continuously to the DEUs. When a DEU is addressed, it must respond with a parity bit-coded message. If this response message is absent (or the parity bit is wrong for a minimum of 4 transmissions), then the DEU is declared to be unserviceable.

1 Discrete outputs, as for DEU A described in paragraph 6.B.(2)(b)-1.

2 Discrete inputs, as for DEU A described in paragraph 6.B.(2)(b)-2.

4 Serial Input/Output. Under control of the director, several types of tests are performed to check for faulty operation:

the register read/write test,
the timing test,
the status bit test,
the parity bit test,
the data loopback test (in conjuction with the connected hardware).

The results of the loopback test assume the connected device is operational.

5 Attendant Indication Panel (AIP) testing. The DEU checks the status of the AIP BITE.

6 The DEU B power supply, gate array, bus interface and BITE status are also checked. The procedure is as for DEU A, described in paragraph 6.B(2)(b)-6. This is continuously done while the CIDS is switched on.

(d) Interfacing and control of cabin equipment sub-sections:

1 General Cabin Illumination Control
This director addresses each of the four connected illumination units on command from:

the Forward Attendant Panel (FAP),
the Programming and Test Panel (PTP),
the response to certain discrete inputs.

CONNECTOR PIN 1, 4, 2,5, 3,6,

9,12, 10,13 11,14

OPERATION MODE S I G N A L

-------------- ---------------------------

bright 0 0 0

dim 1 (50 %) 1 0 0

dim 2 (10 %) 0 1 0

off 0 0 1

DEU or CIDS failure results in no 28 V DC outputs. This gives a 100 % illumination fail-state situation.

3 Emergency Lighting Test (DEU B)
When activated at the programming and test panel, the Emergency Power Supply Units (EPSUs), connected to the DEU, are interrogated for their status. Fault situations in the EPSU are held in coded form. The code number corresponds to the fault type. A DEU B reads this failure number.
The serial clock output pulses to the ON-state. The EPSU then replies and transmits an ON pulse to the DEUs 'Serial In' input, interpreted as a logic one. The process is repeated until there is a logic zero response from the EPSU. The number of received logic ones corresponds to the EPSU failure number.

5 Attendant Handsets (DEU B)
Up to two handsets may be connected in parallel to each DEU B. The DEU performs hook-off sensing, and decodes the dial information which is sent on the handset microphone line.

6 Area Call Panels (ACP) (DEU B)
Two sets of ACP outputs are provided. Each set can drive up to two ACPs in parallel.

8 Additional Attendant Panel (DEU B)
The DEU B has a serial input, output and normal 28 V DC for connection of an additional attendant panel.

(g) DEU Addressing
The coding switch in the DEU mount gives each DEU a different address. This method lets you remove, interchange and replace DEUs without the need to consider the address.

C. Forward Attendant Panel

(1) Description

Connections to the Forward Attendant Panel. ** ON A/C NOT FOR ALL

(a) General
The forward attendant panel 120RH is installed in the forward entrance area of the aircraft. The attendant controls the different cabin systems from the attendant panel.

(b) The forward attendant panel performs these functions:

adaptation of signals received on the ARINC data bus links from each CIDS director,
processing of addressed commands and controls,
processing of inputs from cabin systems,
processing of inputs from the membrane switches on the front face of the FWD ATTND panel,
transmission of data at assigned intervals via the ARINC data bus between the panel and both directors,
fail-passive for data bus transmission and reception in the event of FWD ATTND panel failure,
short-circuit protection of all discrete outputs,
BITE functions for detection and location of faults which occur in the panel.

(c) Architecture
The forward attendant panel is in modular form with a master circuit board and sub-panels which connect to the master board. The visible part of the panel consists of colored membrane switches and indicator lights in a common grid pattern. Blank face-plates replace unused sub-panels.

(d) Master Board
The master board contains all parts which are common to all configurations of the FWD ATTND panel. This includes the power supply, ARINC 429 transmitter and ARINC 429 receiver.

(2) Forward Attendant Panel - Light Module

Light Module ** ON A/C NOT FOR ALL

(a) Description of the switches

1 MAIN OFF
The MAIN OFF membrane switch, switches off the following systems:

General illumination in the cabin and the entrance areas
Reading lights
Attendant work light
Lavatory light.

The function MAIN OFF is disabled in flight.

2 MAIN ON
The MAIN ON membrane switch, switches on the general illumination in the cabin and entrance areas with a brightness of 100%. The integral light in the membrane switches BRT, WDO, and CLG comes on. If a membrane switch for the cabin or entry area is already pressed the MAIN ON membrane switch has no effect for the respective area.

3 ENTRY FWD BRT/ENTRY AFT BRT
The ENTRY FWD BRT or ENTRY AFT BRT membrane switches, switch on the general illumination in the respective entrance area with a brightness of 100%. The integral light in the membrane switch comes on. Pushing the membrane switch a second time, switches off the general illumination of the respective entrance areas and the integral lights.

4 ENTRY FWD DIM 1/ENTRY AFT DIM 1
The ENTRY FWD DIM 1 or ENTRY AFT DIM 1 membrane switches, switch on the general illumination in the respective entrance areas with a brightness of approx 50%. The integral lights in the membrane switches come on. Pushing the membrane switches a second time, switches off the general illumination in the respective areas and the integral lights.

5 ENTRY FWD DIM 2/ENTRY AFT DIM 2
The ENTRY FWD DIM 2 or ENTRY AFT DIM 2 membrane switches, switch on the general illumination in the respective entrance areas with a brightness of approx. 10%. The integral lights in the membrane switches come on. Pushing the membrane switches a second time, switches off the general illumination in the respective entrance areas and the integral lights.

6 CABIN LIGHTING/BRT/DIM 1/DIM 2
The CABIN LIGHTING/BRT/DIM 1/DIM 2 membrane switches, for the cabin, have the same function as the ENTRY/BRT/DIM 1/DIM 2 membrane switches, for the entrance area.

7 CABIN LIGHTING WDO
When the general illumination for a cabin area is switched on, the CABIN LIGHTING WDO membrane switch integral light comes on. Pushing the membrane switch, switches off the general illumination at the windows left and right and the integral light. Pushing the membrane switch a second time, switches on the general illumination at the windows and the membrane switch integral light comes on.

8 CABIN LIGHTING CLG
When the general illumination for a cabin area is switched on, the CABIN LIGHTING CLG membrane switch integral light goes on. Pushing the membrane switch, switches off the general illumination in the ceiling and the integral light. Pushing the membrane switch a second time switches on the general illumination in the ceiling and the membrane switch integral light comes on.

9 POWER READ
The POWER READ membrane switch, switches on the power supply for the reading lights. The integral light in the membrane switch comes on. Pushing the membrane switch a second time switches off the power supply and the membrane switch integral light goes off.

10 POWER ATTN
The POWER ATTN membrane switch, switches on the power supply for the attendant work lights. The integral light in the membrane switch comes on. Pushing the membrane switch a second time switches off the power supply and the membrane switch integral light goes off.

11 POWER LAV
The POWER LAV membrane switch, switches on the power supply for the lavatory lights to a brightness of approx. 50%. The integral light of the membrane switch comes on. Pushing the membrane switch a second time switches off the power supply and the membrane switch integral light goes off.

(3) Forward Attendant Panel - Light Module

Light Module ** ON A/C NOT FOR ALL

(a) Description of the switches

1 MAIN OFF
The MAIN OFF membrane switch, switches off the following systems:

General illumination in the cabin and the entrance areas
Reading lights
Attendant work light
Lavatory light.

The function MAIN OFF is disabled in flight.

6 CABIN LIGHTING FWD/AFT-BRT-DIM 1-DIM 2
The CABIN LIGHTING FWD/AFT-BRT-DIM 1-DIM 2 membrane switches, for the cabin area, have the same function as the ENTRY-BRT-DIM 1-DIM 2 membrane switches, for the entrance area.

11 ENTRY FWD DIM 2/ENTRY AFT DIM 2
The ENTRY FWD DIM 2 or ENTRY AFT DIM 2 membrane switches, switch on the general illumination in the respective entrance areas with a brightness of approx. 10%. The integral lights in the membrane switches come on. Pushing the membrane switches a second time, switches off the general illumination in the respective entrance areas and the integral lights.

(4) Forward Attendant Panel - Audio Module

Audio Module ** ON A/C NOT FOR ALL

The Audio Module gives centralized control over boarding music and prerecorded announcements.

(a) Description of the switches and controls

1 MUSIC ON/OFF
The MUSIC ON/OFF membrane switch switches on the boarding music. If you push the membrane switch, its integral light comes on. Pushing the membrane switch a second time switches off the boarding music and the integral light goes off.

2 MUSIC SEL
The MUSIC SEL membrane switch switches the boarding music to the next channel The selected channel shows on the numerical display.

3 MUSIC+/MUSIC-
If you push the MUSIC+/MUSIC- membrane switch you increase/decrease the loudness of the boarding music. The loudness is indicated on a 10 step rectangular LED row.

4 PRERECORDED ANNOUNCEMENT
This area on the front face of the audio module includes a display for the selected announcements and a keyboard and function keys.
To start a prerecorded announcement, push the related key and then the ENTER membrane switch. The READY indicator comes on when the recorder has found the correct announcement. When you push the START NEXT membrane switch, the announcement starts and the READY indicator goes off. If you select more than one announcement, the START ALL membrane switch activates all announcements. If the ENTER membrane switch is not pushed, the selected announcement will be accepted after a delay of approx. 5 s.

(5) Forward Attendant Panel - Audio Module

Audio Module ** ON A/C NOT FOR ALL

The Audio Module gives centralized control over boarding music and prerecorded announcements.

(a) Description of the switches and controls

2 MUSIC SEL
The MUSIC SEL membrane switch switches the boarding music to the next channel The selected channel shows on the numerical display.

3 MUSIC+/MUSIC-
If you push the MUSIC+/MUSIC- membrane switch you increase/decrease the loudness of the boarding music. The loudness is indicated on a 10 step rectangular LED row.

(6) Forward Attendant Panel - Miscellaneous Module

Miscellaneous Module ** ON A/C NOT FOR ALL

(a) Description of the switches and indicators

1 LIGHT EMER
The LIGHT EMER pushbutton-switch switches on the emergency lighting system. If you push the pushbutton-switch, its integral light comes on. Pushing the pushbutton switch a second time switches off the emergency lighting system and the integral light. The function of the pushbutton is independent from the CIDS power supply.

2 CIDS PNL LIGHT TEST
If you push the CIDS PNL LIGHT TEST membrane-switch, all the lights in the panel and the membrane switch integral light come. The lights will stay on while you hold the membrane switch.

3 EVAC
The indicator light EVAC is controlled by a discrete input.

4 EVAC CMD
The EVAC CMD membrane-switch switches on the evacuation system. If you push the membrane switch, its integral light comes on. Pushing the membrane switch a second time switches off the evacuation system and the integral light. The membrane switch switches a discrete input to ground.

5 RESET
The RESET membrane switch switches off the warning horn, if the evacuation system operates. The membrane switch switches a discrete input to ground.

6 CIDS CAUTION
The CIDS CAUTION light can be switched off in flight, but comes on again on the ground (landing gear down and locked). You cannot switch off the light on the ground. When a CIDS CAUTION occurs, the respective failure message shows on the programming and test panel.

7 SMOKE LAV
The SMOKE LAV indicator light comes on when a signal from the smoke detector is received.

8 WATER QTY
WATER QTY LED-display shows the water level in the water tank divided into 20 steps. Each step is equal to 5%.

9 WASTE QTY
The WASTE QTY LED-display shows the liquid level in the waste tank divided into 20 steps. Each step is equal to 5%.

10 IND ON
The IND ON membrane switch switches on the water and waste indicating system.

11 SYSTEM INOP, LAV INOP
The SYSTEM INOP indicator light comes on, if the vacuum waste system fails.

12 SLIDES ARMED
The SLIDES ARMED indication light is off when all slides are disarmed.
When at least one slide is armed the indication light flashes (green).
When all slides are armed the indication light (green) is steady on.

13 DOORS CLOSED
The DOORS CLOSED indication light comes on, when all doors are closed.
When at least one door is opened, the indication light goes off.

(7) Forward Attendant Panel - Miscellaneous Module

Miscellaneous Module ** ON A/C NOT FOR ALL

(a) Description of the switches and indicators

3 RESET
The RESET membrane switch switches off the warning horn, if the evacuation system operates. If the lavatory smoke warning is on, the RESET membrane switch switches it off also. The membrane switch switches a discrete input to ground.

4 CIDS CAUTION
The CIDS CAUTION light can be switched off in flight, but comes on again on the ground (landing gear down and locked). You cannot switch off the light on the ground. When a CIDS CAUTION occurs, the respective failure message shows on the programming and test panel.

5 SMOKE LAV
The SMOKE LAV indicator light comes on when a signal from the smoke detector is received.

6 WATER QTY
WATER QTY LED-display shows the water level in the water tank divided into 20 steps. Each step is equal to 5%.

7 WASTE QTY
The WASTE QTY LED-display shows the liquid level in the waste tank divided into 20 steps. Each step is equal to 5%.

8 IND ON
The IND ON membrane switch switches on the water and waste indicating system.

9 SYSTEM INOP, LAV INOP
The SYSTEM INOP indicator light comes on, if the vacuum waste system fails.

D. Aft Attendant Panel

Aft Attendant Panel ** ON A/C NOT FOR ALL

Connections to the Aft Attendant Panel ** ON A/C NOT FOR ALL

Aft Attendant Panel ** ON A/C NOT FOR ALL

Connections to the Aft Attendant Panel ** ON A/C NOT FOR ALL

(1) Description

(a) General
The Aft Attendant Panel (AAP) 126RH is installed in the aft entrance area of the aircraft. It enables the aft attendant to control different cabin systems.

(b) Function
The aft attendant panel performs these functions:

the adaptation of received data bus signals
the processing of addressed commands and controls
the processing of inputs from cabin systems
the processing of inputs from membrane switches on aft attendant panel
the transmission of data at assigned intervals via the data bus
the fail passive for data bus transmission and reception in case of aft attendant panel failure
the short-circuit protection of discrete outputs.

the power supply
the RS 232 data bus receiver and transmitter
the processing module
the I/O circuitry

1 Power Supply
The power supply derives from the service busbar 601PP for all the necessary internal voltages from a 28 V DC input.

2 RS 232 Interface
The RS 232 interface receives serial data from the DEU B and converts it into the parallel data format. The RS 232 interface also takes parallel data from the processing module, serializes it and transmits it to the DEU B. Separate lines are used for transmission and reception of data.

3 Processing Module
The processing module carries out all internal operations of the aft attendant panel. It interfaces the membrane switches and indicators to the RS 232 interface. The processing module also does BITE functions and control of any discrete inputs or outputs (e.g. for EVAC controls and the water system). Where no discrete output is provided, a membrane switch reports its operation to the DEU. The DEU reports it to the director. The director performs the actions associated with pressing a membrane switch.

4 Output Circuitry
All outputs of the aft attendant panel are short-circuit protected.

(d) Description
The aft attendant panel comprises of:

the ENTRY BRT/DIM 1/DIM 2 membrane switches
the CABIN BRT/DIM 1/DIM 2 membrane switches
the SMOKE RESET membrane switch.

(2) Description

(a) General
The Aft Attendant Panel (AAP) 126RH is installed in the aft entrance area of the aircraft. It enables the aft attendant to control different cabin systems.

(b) Function
The aft attendant panel performs these functions:

the adaptation of received data bus signals
the processing of addressed commands and controls
the processing of inputs from cabin systems
the processing of inputs from membrane switches on aft attendant panel
the transmission of data at assigned intervals via the data bus
the fail passive for data bus transmission and reception in case of aft attendant panel failure
the short-circuit protection of discrete outputs.

the power supply
the RS 232 data bus receiver and transmitter
the processing module
the I/O circuitry

1 Power Supply
The power supply derives from the service busbar 601PP for all the necessary internal voltages from a 28 V DC input.

4 Output Circuitry
All outputs of the aft attendant panel are short-circuit protected.

(d) Description
The aft attendant panel comprises of:

the ENTRY BRT/DIM 1/DIM 2 membrane switches
the AFT BRT/DIM 1/DIM 2 membrane switches
the EVAC RESET membrane switch
the EVAC indicator.

E. Switch panel (2064VU)

(1) Description

Switch panel (2064VU) ** ON A/C NOT FOR ALL

(a) General
The switch panel is installed adjacent to the mid LH and exit LH attendant station.

(b) Function
The switch panel performs these functions:

indication of the EVAC alert,
reset of the EVAC signaling.

the EVAC alert indication light,
the RESET membrane switch.

F. Switch panel (2065VU)

(1) Description

Switch panel (2065VU) ** ON A/C NOT FOR ALL

(a) General
The switch panel, if applicable, is installed at the front wall of the lavatory, adjacent to the lavatory call light.

(b) Function
The switch panel performs this function:

reset of the acoustic and visual smoke warnings, related to the respective lavatory.

the RESET membrane switch.

G. Programming and Test Panel

(1) Description

Programming and Test Panel ** ON A/C NOT FOR ALL

(a) General
The Programming and Test Panel (PTP) 110RH is installed in the rear wall of lavatory A. It is located at the FWD attendant station, behind a hinged access door next to the installed FWD attendant panel. For correct CIDS operation, the Cabin Assignment Module (CAM) must be installed in the socked. This is provided on the panel front face. The PTP enables the forward attendant and other personnel to extensively test and re-program the CIDS.

(b) Function and Layout
The functions of the PTP are as follows:

To program the CIDS properties and cabin layout information into the CIDS directors, which are copied from the CAM.
To manually down-load the alternative CAM layout into the directors and cause this layout to be down-loaded automatically in subsequent CIDS start-ups.
To onboard re-program:
CAM data,
activation of the provisioned CIDS extra functions,
change cabin layout,
implement cabin zoning.
To monitor the failure status of the CIDS and some of the connected systems.
To examine the fault data held in the director BITE memory.
To activate CIDS component tests and the readout of the results.

The PTP has an alphanumeric display with four rows of twenty characters. The display is used to present messages, test results and selection menus. At either end of each display row are blank keys. They are labelled on the display with '<' or '>' characters. A conventional keypad is provided for entry of numerical data. One membrane switch switches the display on and two membrane switches test the emergency lights. Three indicator lamps are provided for emergency lighting system/testing indications. The Cabin Assignment Module (CAM) 115RH plugs into a socket on the front face of the panel.

(c) Architecture
An ARINC 429 interface handles all communications between the PTP and the directors. A single output is connected to both directors. Two separate buffered inputs are provided, one for each director. The PTP power supply derives all the internal voltages from one 28 V DC input.
The display switches off automatically after ten minutes without operation of the panel (i.e. no key pressed).
The CAM has an interface within the PTP to allow the panel to read, and also to to modify the CAM data. The PTP is able to transfer any of the CAMs internal layouts to the director.
BITE is incorporated into all the circuits of the PTP.

(d) Cabin Assignment Module
The Cabin Assignment Module (CAM) 115RH defines all of the modifiable system properties and layout information for the CIDS. It contains the possibility for four cabin layouts, (LAYOUT 1 - 3 and LAYOUT M.

--------------

! LAYOUT 1 ! ------ Marker

--------------

! LAYOUT 2 ! ------

--------------

! LAYOUT 3 ! ------

--------------

! LAYOUT M ! ------

--------------

All cabin layouts are programmed according to the airlines requests. You can modified these layouts via the PTP.

At the end of the modification procedure the new layout is automatically stored as layout M.

(2) Mandatory Layout
For security reasons, there is a mandatory layout laid down in the directors to ensure the operation of the system in all conditions.
The mandatory layout is used in following conditions:

if normal power is not available,
if the CAM is inoperative,
if the PTP is inoperative.

(3) Operation

Programming and Test Panel-System Connections ** ON A/C NOT FOR ALL

(a) General
The Programming and Test Panel (PTP) 110RH transmits data to both CIDS directors via a single ARINC 429 bus. It receives data via two ARINC 429 buses, one from each director.
Four discrete connections are provided to the emergency lighting system. A DC ground and 28 V DC line connect to the PTP for BAT indication and for switch-over functions. +28 V DC is fed to the PTP from service busbar 601PP circuit breaker 161RH.

After CIDS power-up the panel display stays on for approx. 10 minutes, then the DSPL ON membrane switch must be pressed to activate the panel display. The first selection menu then appears and shows the modes available. The various modes are explained under the separate section. 'System Testing and Programming' in this chapter (Ref. paragraph 8).

The selection of displayed RET function returns to the previous menu when the display labelled key is pushed. When the DSPL ON key is pushed, it always returns the user to the first menu. When numerical data is to be entered, one of the blank keys displays ENTER. The word ENTER is displayed on the blank keys when a data input is required. A sign flashes to show the correct position for the data input. When the data is entered, the sign does not flash. The digits of the data input replace the sign. The sign will flash in the next row which now requires an input. Pushing the CLR membrane switch deletes all the digits so far entered. Pushing the menu-labelled ENTER key enters the complete number and the PTP can then use it.
For correct CIDS operation, the CAM must be plugged in. There is no possibility of programming the CIDS while the CAM is missing.

(b) CAM LAYOUT Marking
The four CAM layout memories are nonvolatile, and one of them is always electronically marked as the current layout. When the CIDS is powered-up, the marked layout is automatically down loaded via the PTP ARINC 429 link to the memories of both directors. The sub-menu listing the layouts displays the marked layout in flashing mode.
When any change of parameters via the PTP is done, the resulting modified layout is stored in the CAM layout M. The marker is automatically set to layout M. Each time a modified layout is transferred to the Layout M, a CAM internal software count is incremented for documentation purposes.

H. Attendant Indication Panel

(1) Description

Attendant Indication Panel ** ON A/C NOT FOR ALL

(a) General
An Attendant Indication Panel (AIP) 320RH is installed at each attendant station. The panel lights are visible from at least ten meters away. They provide an attendant far call function, and its alphanumeric display is readable from about two meters distance. The display provides system-related information. It is divided into two rows of sixteen characters each.

(2) Attendant Indication Panel - Architecture

Attendant Indication Panel - Block Diagram ** ON A/C NOT FOR ALL

The AIP comprises of these modules:

A display panel with two lines, each with sixteen characters
A display controller which includes a character generator
A display driver
A single chip microcomputer which includes a serial interface
A RAM and READ Only Memory (ROM) as program memory
An erasable Programmable Read Only Memory (EPROM), as a memory for the indicated texts, alternatively the EPROM can be part of the single chip microcomputer and can also be used as a program memory
A line receiver
A power supply circuit
An additional circuits to provide an optimized visual range and a far reaching call function
One pink indicator light
One green indicator light.

The microcomputer coordinates the operation of all the AIP modules and running of the software contained in the ROM. 14 to 32 V DC powers the AIP with a voltage regulator which derives the necessary internally used voltages. The line receiver/serial interface is for RS232 reception. One output is provided and is used to signal the BITE status of the AIP (see the BITE description in the 'Operation' section (Ref. paragraph 6.F.(2)(f). All messages for alphanumeric display are stored in the EPROM. They are selected and transferred to the display according to commands received from the RS232 interface. The parallel interface connects to the two lamps. These can be switched on in either continuous or flashing mode (1Hz) according to the commands received.

I. Area Call Panel

Area Call Panel ** ON A/C NOT FOR ALL

(1) Description

(a) General
The Area Call Panel (ACP) 340RH is installed at each end and in the middle of the passenger compartment to the left and right of center in the ceiling. The ACP has four separately controlled fields, each contains two parallel connected lamps. The lights are visible from the front or rear of the ACP. They are colored in one of two available cover lenses. The colors are as follows:

color 1 = amber,
color 2 = green,
color 3 = pink,
color 4 = blue.

The fields are activated either continuously or are flashed. They are used as a far-call facility to warn cabin attendants of passenger call, interphone call, and lavatory smoke. The green segment illuminates if the switch ATTND ADV installed in the cockpit is in the ON position.

(2) Description

(a) General
Eight Area Call Panels (ACPs) 340RH are installed in the ceiling of the passenger compartment, two at each door area. The ACP has four separately controlled fields. Each contains parallel connected colored LEDs. The ACP is covered by a milk-colored cover. The illuminated lights are visible from the front or rear of the ACP.
The colors are as follows:

color 1 = amber,
color 2 = pink,
color 3 = pink,
color 4 = blue.

The fields are activated either continuously or flashing. They are used as a far-call facility to inform cabin attendants of passenger call, interphone call and lavatory smoke.

(3) Operation

(a) General
Five discrete connections connect each ACP to a DEU B. One for each field and one for a common connection. The DEU B switches the fields separately. Any field or combinations of fields can be OFF, steady ON or flashing ON. For flashing the DEU B repeatedly switches the field(s) on and off.

(b) Call Functions
The ACP performs call functions which are described fully under the appropriate 'System Operation' section of this chapter (Ref. paragraph 7.). For lavatory smoke, the respective chapter must be referred to.

J. Interphone Handsets

Cabin Handset ** ON A/C NOT FOR ALL

(1) Description

(a) General
Each attendant station has a handset 330RH installed for PA and interphone dialing and communication. The flight compartment has a handset 130RH installed for PA use only. Handset 330RH is kept in a cradle 332RH and handset 130RH in a cradle 132RH.

(b) Function
The handsets and cradles include these functions:

The hook-off sensing
The Press-To-Talk (PTT) switching
The PA announcements
The single-key call-activiation via integral keypad
Telephone conversation (cabin handset 330RH only).

The microphone unit which includes a pre-amplifier
The earphone
The push-to-talk switch
The handset support bracket with a permanent magnet.

The cabin handset 330RH also has:

A keyboard with 9 touch keys
A tone-dialling interface circuit.

(d) Cabin Handset Keyboard
The handset has 9 keys in a 3 x 3 matrix, the keys are used for:

Emergency call: push the EMER CALL key
Flight compartment call: push the CPT key
All attendant call: push the ALL ATTND key
Forward attendant call: push the FWD ATTND key
Aft left attendant call: push the AFT L ATTND key
Aft right attendant call: push the AFT R ATTND key
PA ALL: push the PA ALL key
Service Interphone: push the SVCE key
Clear handset operation: push the RESET key.

(e) Cabin-Handset Interface Circuit
The interface circuit decodes the keyboard matrix and generates Dual Tone Multiple Frequency (DTMF) coded dial signals. The interface usually sends the speech signal through to its output. When you push a key, it disconnects the speech and supplies the DTMF signals to the output.

(2) Description

(a) General
Each attendant station is equipped with a handset 330RH for PA and interphone dialing and communication. The flight compartment is equipped with a handset 130RH for PA use only. Handset 330RH rests in a cradle 332RH and handset 130RH in a cradle 132RH.

(b) Function
The handsets and cradles provide these functions:

the hook-off sensing,
the Press-To-Talk (PTT) switching,
the PA announcements,
the single-key call-activation via integral keypad,
telephone conversation (cabin handset 330RH only).

the microphone unit which includes a pre-amplifier,
the earphone,
the push-to-talk switch,
the handset support bracket including a permanent magnet.

The cabin handset 330RH also contains:

a keyboard with 12 touch keys,
a tone dialing interface circuit.

(d) Cabin Handset Keyboard
The handset has 12 keys arranged on a 3 x 4 matrix, the keys are used for:

Cockpit call: push CAPT
Conference call: push INTPH and ALL
Fwd attnd call: push INTPH and FWD
Mid attnd call: push INTPH and MID
Exit attnd call: push INTPH and EXIT
AFT L/R attnd call: push INTPH and AFT
PA ALL: push the PA and PTT
Direct PA: push the PTT
Service Interphone: push 2x INTPH
Emergency call: push EMER CALL
Clear handset operation: push RESET.

(e) Cabin-Handset Interface Circuit
The interface circuit decodes the keyboard matrix and generates Dual Tone Multiple Frequency (DTMF) coded dial signals. The interface normally routes the speech signal through to its output. When a key is pressed, it disconnects the speech and supplies the DTMF signals to the output.

K. PA Loudspeaker

(1) Description
The PA loudspeakers are used for:

the PA announcements,
the broadcast of boarding music,
the attendant call chimes,

Each loudspeaker is connected to a DEU A. Fine adjustment of volume and frequency characteristics for each loudspeaker is possible. This is done according to CAM data.

(2) Description
The PA loudspeakers are used for:

the PA announcements,
the broadcast of boarding music,
the broadcast of video sound,
the attendant call chimes,
the evacuation tone signalling.

Each loudspeaker is connected to an DEU A. Fine adjustment of volume and frequency characteristics for each loudspeaker is possible. This is done according to CAM data.

** ON A/C NOT FOR ALL

7. Operation/Control and Indicating

A. CIDS Energization
The CIDS is designed to operate whenever the essential busbar 401PP and service busbar 601PP are energized. It has no ON/OFF switches. Circuit breakers protect the CIDS components and will remain normally closed, except for tests or current overload.
All the CIDS units are supplied with 28 VDC.
When electrical power is supplied to the CIDS, a power-up test is done.

B. Passenger Address System

(1) PA System Architecture

PA System Architecture ** ON A/C NOT FOR ALL

The components, interfaces and signal sources of the CIDS which are related to the PA system are:

(a) Flight Compartment

The audio selector panels
The flight compartment boomset
The hand microphones
The oxygen mask microphones
The flight compartment handset located at the center pedestal.

(b) Avionics Compartment

The audio management unit
The link to CFDS
The two CIDS directors
The oil pressure switch
The flight compartment pressure controller
The link to the prerecorded announcement reproducer.

The cabin Loudspeakers
The CIDS DEU A, with two independent amplifiers
The attendant handset with integrated keyboard
The attendant indication panels
The CIDS DEU B, with two handset interfaces
The programming and test panel
The forward attendant panel.

(2) PA System Architecture

PA System Architecture ** ON A/C NOT FOR ALL

The components, interfaces and signal sources of the CIDS which are related to the PA system are:

(a) Flight Compartment

The audio selector panels
The flight compartment boomset
The hand microphones
The oxygen mask microphones
The flight compartment handset located at the center pedestal.

(b) Avionics Compartment

The audio management unit
The link to CFDS
The two CIDS directors
The oil pressure switch
The flight compartment pressure controller
The link to the prerecorded announcement reproducer
the link to video control unit.

The cabin Loudspeakers
The CIDS DEU A, with two independent amplifiers
The attendant handset with integrated keyboard
The attendant indication panels
The CIDS DEU B, with two handset interfaces
The programming and test panel
The forward attendant panel.

(3) System Description

(a) General
The CIDS director accepts audio signals from the various PA sources in the aircraft. It assigns priorities to each source. It transmits the signal in digital form via the four top line data buses to the DEUs A. These send it to the cabin loudspeakers for broadcasting. The passenger address system has different announcement modes. Each mode uses a different PA function. These functions are assigned with the CAM software.

You can perform PA announcements from different sound sources. The director can route the broadcasts to any combination of six audio channels. A separate amplifier drives each cabin loudspeaker. It is programmed on the CIDS initialization for the gain, the frequency characteristic and the assignment to one of the six audio channels. Three channels are reserved for attendant broadcasts, and three for passenger announcements. This lets you assign each cabin loudspeaker to one of up to three zones. A PA chime capability is also given. The PA system remains available during aircraft emergency conditions. It is powered down as long as no PA announcements are in progress.

(b) Annunciation and Source Priority
An indication is shown on all attendant indication panels whenever a PA broadcast is performed (e.g. PA IN USE). The sound sources are divided into these priorities:

the 1st priority: Flight compartment station - AMU
the 2nd priority: Flight compartment station - Handset
the 3rd priority: Cabin attendant stations
the 4th priority: PRAM
the 5th priority: Video
the 6th priority: Boarding music.

(c) Volume Control
When an engine is running, the PA volume is increased automatically by +6 dB. The PA volume is also increased by +4 dB in the event of cabin depressurization.
PA loudspeakers are installed on the RH and the LH side of the cabin in the Passenger Information Units (PIUs). Separate audio amplifiers in the CIDS DEUs A drive each loudspeaker independently. The output level range of this amplifier is -20 dB up to +10 dB in 2 dB steps. The CIDS director software controls the output level. 0 dB represents an output level of 500 mW continuous power. The peak power is limited to 5 W.
The level control is divided into two sections. Section one is the master audio level adjustment with a level range of 0 to -12 dB. This means that all audio amplifiers in DEU A will alter their respective output level over this range.
Section two is the local audio level adjustment with a level range of +/-6 dB. This means that only the respective DEU A audio amplifier will alter its output level. Each loudspeaker is adapted to the respective ambient noise conditions.
The passenger address level is also selectable via PTP (only on ground and landing gear compressed) for:

three cabin segments,
four attendant areas,
increased by oil pressure high,
increased by cabin pressure low.

The passenger address audio settings are stored in the CAM for all installed layouts.

(d) Frequency Control
The PA system is equipped with several frequency control facilities:
The input frequency controls are different:

for balanced audio inputs in the CIDS director (for example boarding music),
for unbalanced audio inputs in the director and DEU B (e.g. PA announcements via cabin handset).

Each input bus has its own filter which is independently programmable. The unbalanced PA inputs circuits are equipped with Automatic Gain Control (AGC) . Additionally the DEU A audio is equipped with a bass filter for special ambient noise equalization. The director frequency controls are the main frequency controls. The DEU A output filters are independently programmable for each output. The different frequency control ranges are shown in the DEU and the director component descriptions in this chapter (Ref. paragraph 6.).

(e) Pre-recorded Announcements
You hear pre-recorded announcements in the cabin(s) and in the attendant areas.

(4) System Description

the 1st priority: Flight compartment station - AMU
the 2nd priority: Flight compartment station - Handset
the 3rd priority: Forward attendant station
the 4th priority: Cabin attendant stations
the 5th priority: PRAM
the 6th priority: Video
the 7th priority: Boarding music.

three cabin segments,
four attendant areas,
increased by oil pressure high,
increased by cabin pressure low.

The passenger address audio settings are stored in the CAM for all installed layouts.

(d) Frequency Control
The PA system is equipped with several frequency control facilities:
The input frequency controls are different:

for balanced audio inputs in the CIDS director (for example boarding music),
for unbalanced audio inputs in the director and DEU B (e.g. PA announcements via cabin handset).

(5) Operation of the PA System

(a) Energization
Energization of the PA System is as for 'CIDS Energization'.

(b) PA Announcements from Flight Compartment Handset
The handset is mounted at the flight compartment center pedestal and contains an integral PTT switch. Pressing the PTT switch to key the PA system. It overrides lower priority PA sources, and broadcasts the speech over all PA loudspeakers. Sidetone is heard over the handset earpiece. A PA IN USE indication at all attendant indication panels accompanies these announcements.

(c) PA Announcements from other flight compartment audio equipment
Any of these flight compartment audio equipment may be selected to make a PA announcement:

the boomset microphone
the hand microphone (with internal PTT switch)
the oxygen mask integral microphone.

Three audio selector panels are available on the left and right sides of the center pedestal, and on the flight compartment overhead panel respectively. They provide identical facilities. To select the PA system, the rectangular PA button is pressed. It lights up green and connects the microphone audio to the PA system. The integral PTT switch in the hand microphone is pressed to key the PA system. When the boomset or oxygen mask is used, pushing the combined PA volume control/PA sidetone switch, switches the sidetone audio to the boomset or headset earpieces. The switch illuminates yellow. The knob adjusts the sidetone volume. Pushing the respective PA green and yellow switches a second time, disconnects the flight compartment audio source and flight compartment earpieces respectively from the PA system. You can monitor the PA sidetone at any time when you only select the volume/sidetone switch.
When the PA (green) selector switch is activated, PA ALL IN USE is displayed at all attendant indication panels. PA announcements from the selected flight compartment audio equipment are broadcast over all PA loudspeakers. They immediately override PA audio from any other source.

(d) PA Announcements from Attendant Handsets

Attendant Indication Panel - PA Selection Messages ** ON A/C NOT FOR ALL

An attendant handset is mounted at each attendant station. An AIP is installed near to each handset for display of PA-use information. When the handset is lifted a 400 Hz tone is heard. The top line of the AIP displays a number symbol.
When the PTT key is pressed (direct PA function) or the 'PA' and 'ALL' pushbutton and PTT keys are pressed a confirmation message is displayed on the AIP. If the PA call is impossible due to the priority of a call already in progress, then the word BUSY appears on the AIP display.
To press the keypad RESET key always clears any handset operation and new key selection.
The numbers of all selectable PA zones, for example 3, and the respective keypad keys, are stored in the CAM. The CAM also contains a priority list which is divided into priority levels.
It starts with:

the flight compartment as the highest priority
the attendant stations
the prerecorded announcement system
the entertainment PA sources.

Once a PA call is established, the bottom line of all AIPs displays the respective PA IN USE message. Flight compartment PA IN USE indicator is provided as an option. Pressing the PTT switch keys the PA system. Sidetone audio is fed to the handset earpiece. When the PA announcement is over, you can disconnect the handset from the PA system as follows:

put the handset into the cradle or
press the RESET button.

C. Cabin and Flight Crew Interphone System

(1) Interphone System Architecture

Interphone System Architecture . ** ON A/C NOT FOR ALL

The components, interfaces and signal sources of the CIDS which are related to the interphone are as follows:

(a) Flight Compartment
The main interphone components are:

the audio control panels,
the flight compartment boomset,
the oxygen mask microphones,
the call panel with the call-buttons and integrated emergency call indicator,
the crew call buzzer for audible call indications (through FWC),
the flight compartment handset.

The audio control panels, the flight compartment boomset and the oxygen mask microphones interface with the director through the Audio Management Unit (AMU). The call panel is connected directly to the directors. The crew call buzzer has an interface with the directors through the Flight Warning Computer (FWC).
The main interphone components are:

the audio management unit,
the link to CFDS,
the two CIDS directors.

Additional signal sources are:

the oil pressure switch,
the cabin pressure switch.

(2) System Description
The CIDS director accepts audio signals from the various interphone sources in the aircraft and assigns priorities to each source. The director performs telephone exchange switching and call functions from flight compartment call switch settings or the attendant handset keypad entries. All this is done with reference to the parameters defined in the CAM. Chimes are transmitted via the top line data bus and the PA loudspeakers. In the flight compartment, integral lamps in the call switches annunciate interphone calls. In the cabin, the ACPs and AIPs are used for annunciation.

(3) Interphone Modes

(a) General
The cabin and flight crew interphone system offers different communication modes. Each mode can lead to different call activations which are assigned in the CAM.
The assigned visual and aural indications are listed below:

(4) Interphone Modes - EMER CALL

-------------------------------------------------------------------------------

! ! INDICATION !

! -------------------------------------------------------------

! ACTION ! AURAL ! VISUAL !

-------------------------------------------------------------------------------

! CALL EMERGENCY ! CHIME ! ALL CABIN + ! ALL AIP: ! ALL ACP: !

! CAPT- ATTND ! 3x HIGH-LOW ! ATTND LS ! TEXT FLASH, ! PINK FLASH !

! ! ! ! PINK IND ! !

! ! ! ! FLASH ! !

-------------------------------------------------------------------------------

(5) Interphone Modes - CALL from Cockpit

-------------------------------------------------------------------------------

! ! INDICATION !

! -------------------------------------------------------------

! ACTION ! AURAL ! VISUAL !

-------------------------------------------------------------------------------

! CALL ! CHIME ! ALL ATTND LS ! RESP AIP: ! RESP ACP: !

! CAPT- ATTND ! 1x HIGH-LOW ! ! TEXT ON, ! PINK ON !

! ! ! ! GREEN IND ! !

! ! ! ! ON ! !

-------------------------------------------------------------------------------

(6) Interphone Modes - CALL from Cockpit

-------------------------------------------------------------------------------

! ! INDICATION !

! -------------------------------------------------------------

! ACTION ! AURAL ! VISUAL !

-------------------------------------------------------------------------------

! CALL ! CHIME ! ALL ATTND LS ! RESP AIP: ! RESP ACP: !

! CAPT- ATTND ! 1x HIGH-LOW ! ! TEXT ON, ! PINK ON !

! ! ! ! PINK IND ! !

! ! ! ! ON ! !

-------------------------------------------------------------------------------

(7) Interphone Modes - ALL ATTND CALL from Cockpit

-------------------------------------------------------------------------------

! ! INDICATION !

! -------------------------------------------------------------

! ACTION ! AURAL ! VISUAL !

-------------------------------------------------------------------------------

! CALL ! CHIME ! ALL ATTND LS ! ALL AIP: ! ALL ACP: !

! CAPT- ALL ATTND ! 1x HIGH-LOW ! ! TEXT ON, ! PINK ON !

! ! ! ! GREEN IND ! !

! ! ! ! ON ! !

-------------------------------------------------------------------------------

(8) Interphone Modes - EMER CALL from the cabin

-------------------------------------------------------------------------------

! ! INDICATION !

! -------------------------------------------------------------

! ACTION ! AURAL ! VISUAL !

-------------------------------------------------------------------------------

! CALL EMERGENCY ! BUZZER ! ! RESP AIP: ! EMER CALL IND:!

! ATTND - CAPT ! 3x ! ! TEXT FLASH ! FLASH !

! ! ! ! ! ATT IND: !

! ! ! ! ! FLASH !

-------------------------------------------------------------------------------

(9) Interphone Modes - CALL from the cabin

-------------------------------------------------------------------------------

! ! INDICATION !

! -------------------------------------------------------------

! ACTION ! AURAL ! VISUAL !

-------------------------------------------------------------------------------

! CALL ! BUZZER ! ! RESP AIP: ! ATT IND: !

! ATTND - CAPT ! 1x ! ! TEXT ON ! FLASH !

! ! ! ! ! !

-------------------------------------------------------------------------------

(10) Interphone Modes - CALL from the cabin

-------------------------------------------------------------------------------

! ! INDICATION !

! -------------------------------------------------------------

! ACTION ! AURAL ! VISUAL !

-------------------------------------------------------------------------------

! CALL ! BUZZER ! ! RESP AIP: ! ATT IND: !

! ATTND - CAPT ! 1x ! ! TEXT ON ! FLASH !

! ! ! ! ! !

-------------------------------------------------------------------------------

(11) Interphone Modes - ALL ATTND CALLcabin

-------------------------------------------------------------------------------

! ! INDICATION !

! -------------------------------------------------------------

! ACTION ! AURAL ! VISUAL !

-------------------------------------------------------------------------------

! CALL ! CHIME: ! ALL ATTND LS ! ALL AIP: ! ALL ACP: !

! ATTND - ! 1x HI LO ! ! TEXT ON, ! PINK ON !

! ALL ATTND ! ! ! PINK IND ! !

! ! ! ! ON ! !

-------------------------------------------------------------------------------

(12) Interphone Modes - ALL ATTND CALL

-------------------------------------------------------------------------------

! ! INDICATION !

! -------------------------------------------------------------

! ACTION ! AURAL ! VISUAL !

-------------------------------------------------------------------------------

! CALL ! CHIME: ! ALL ATTND LS ! ALL AIP: ! ALL ACP: !

! ATTND - ! 1x HI LO ! ! TEXT ON, ! PINK ON !

! ALL ATTND + ! BUZZER: ! ! GREEN IND ! ATT IND: !

! CAPT ! 1x ! ! ON ! FLASH !

-------------------------------------------------------------------------------

(13) Interphone Modes - ATTND CALL from the cabin

-------------------------------------------------------------------------------

! ! INDICATION !

! -------------------------------------------------------------

! ACTION ! AURAL ! VISUAL !

-------------------------------------------------------------------------------

! CALL ! CHIME: ! ALL ATTND LS ! RESP AIP: ! RESP ACP: !

! ATTND - ATTND ! 1x HI LO ! ! TEXT ON, ! PINK ON !

! ! ! ! GREEN IND ! !

! ! ! ! ON ! !

-------------------------------------------------------------------------------

(14) Interphone Modes - ATTND CALL from the cabin

-------------------------------------------------------------------------------

! ! INDICATION !

! -------------------------------------------------------------

! ACTION ! AURAL ! VISUAL !

-------------------------------------------------------------------------------

! CALL ! CHIME: ! ALL ATTND LS ! RESP AIP: ! RESP ACP: !

! ATTND - ATTND ! 1x HI LO ! ! TEXT ON, ! PINK ON !

! ! ! ! PINK IND ON ! !

-------------------------------------------------------------------------------

(15) Interphone - Priorities

(a) Definition of Priorities
All communication modes are handled with respect to the predefined priorities listed below:

1 Emergency Call

2 An call from flight compartment which includes:

an all call from flight compartment,
a normal call from flight compartment.

3 An all call from cabin station

4 A normal call from cabin station
Additionally, all interphone sources have interrelated priorities, as assigned in the CAM. There are eight priorities (1A, 1B to 4A, 4B) which can be individually assigned to the different interphone sources.
If more than one interphone source requests the same communication mode, the source with the higher priority will have precedence.
If they have the same priority, the interphone source which was dialled first will be given preference.
When an interphone source requests a station which is engaged in another communication link:

a busy indication at the AIP appears,
a busy tone via the sidetone output will be transmitted.
if this interphone source has equal priority to, or lower priority than the existing link. If this interphone source has a higher priority, a then following action will be executed.

The existing communication link will be interrupted and the new link will be established. The audible and visual calls will be activated as assigned for this communication mode. An "OVER" indication will be displayed at the AIP of the station.

(16) Operation of the Interphone System

Interphone System Architecture . ** ON A/C NOT FOR ALL

(a) Energization
Energization of the Interphone System is as for 'CIDS Energization'.

D. Passenger Lighted Signs

(1) Architecture

Passenger Lighted Signs - System Architecture ** ON A/C NOT FOR ALL

The components, interfaces and signal sources of the CIDS which are related to the passenger lighted signs system are as follows:

(a) Flight Compartment

the NO SMOKING switch
the FASTEN SEAT BELT switch.

(b) Avionics Compartment

the link to CFDS
the link to SDAC 1 and SDAC 2
the two CIDS directors
the link to Emergency Lighting System (EMLS)
the cabin pressure controller
the link to Landing Gear control Interface Unit (LGCIU)
the link to SFCC 1 and SFCC2.

the cabin loudspeakers
the CIDS DEU A (PA amplifiers and signs lamp drivers)
the PTP including CAM.

(2) Architecture

Passenger Lighted Signs - System Architecture. ** ON A/C NOT FOR ALL

The components, interfaces and signal sources of the CIDS which are related to the passenger lighted signs system are as follows:

(a) Flight Compartment

the NO SMOKING switch
the FASTEN SEAT BELT switch.

(b) Avionics Compartment

the link to CFDS
the link to SDAC 1 and SDAC 2
the two CIDS directors
the link to Emergency Lighting System (EMLS)
the cabin pressure controller
the link to Landing Gear control Interface Unit (LGCIU).

the cabin loudspeakers
the CIDS DEU A (PA amplifiers and signs lamp drivers)
the PTP including CAM.

(3) System Description
Input signals to the director control these signs:

the NO SMOKING and FASTEN SEAT BELT lighted signs in the cabin
the RETURN TO SEAT signs in the lavatories
the EXIT signs.

Manual commands are received from the cockpit NS and FSB switches. These are grounded inputs NO SMOKING COMMAND or NO SMOKING AUTO, and grounded input FASTEN SEAT BELT COMMAND or FASTEN SEAT BELT AUTO respectively. The director interprets open circuited NS inputs and open circuited FSB input as NS OFF and FSB OFF commands respectively. Director software uses data from the CAM to activate signs which opened on:

the cockpit commands
the discrete inputs LANDING GEAR DOWN LOCKED
an EXCESSIVE ALTITUDE
the NS AUTO input,
the FSB AUTO input.

(4) System Description
Input signals to the director control these signs:

the NO SMOKING and FASTEN SEAT BELT lighted signs in the cabin,
the RETURN TO SEAT signs in the lavatories,
the EXIT signs.

Manual commands are received from the cockpit NS and FSB switches. These are grounded inputs NO SMOKING COMMAND or NO SMOKING AUTO, and grounded input FASTEN SEAT BELT COMMAND respectively. The director interprets open circuited NS inputs and open circuited FSB input as NS OFF and FSB OFF commands respectively. Director software uses data from the CAM to activate signs which opened on:

the cockpit commands,
the discrete inputs LANDING GEAR DOWN LOCKED,
an EXCESSIVE ALTITUDE.
the NS AUTO input,

(5) System Description - additional input

the inputs SLATS and FLAPS.

(6) System Description - additional commands
The director also provides NS AUTO input for the optional NS AUTO flight compartment commands.
The interface to the EXIT signs is via a connection from the director to the emergency lighting system. DEUs type A drive and interface all other signs. The director addresses each sign independently via DEU A. Switching on of any signs is signalled to the SDAC via the respective director output NO SMOKING. Switching on of any NS sign is also signalled to the EMLS.

(7) System Description - additional commands
The director also provides FSB AUTO or NS AUTO input for the optional FSB AUTO or NS AUTO flight compartment commands.
The interface to the EXIT signs is via a connection from the director to the emergency lighting system. DEUs type A drive and interface all other signs. The director addresses each sign independently via DEU A. Switching on of any signs is signalled to the SDAC via the respective director output NO SMOKING or FASTEN SEAT BELT. Switching on of any NS sign is also signalled to the EMLS.

(8) System Description - Indications

-------------------------------------------------------------------------------

! ! Indications !

! ------------------------------------------------------

! Action ! Aural ! Visual !

-------------------------------------------------------------------------------

! SIGN: ! CHIME: ! ALL CABIN + ! SIGNS: !

! NO SMOKING, ! 1x LOW ! ALL ATTND LS ! ALL NS !

! ON ! ! ! ECAM: !

! ! ! ! MESSAGE !

-------------------------------------------------------------------------------

! SIGN: ! CHIME: ! ALL CABIN + ! !

! NO SMOKING, ! 1x LOW ! ALL ATTND LS ! !

! OFF ! ! ! !

-------------------------------------------------------------------------------

! SIGN: ! CHIME: ! ALL CABIN + ! SIGNS: !

! FASTEN SEAT BELT/ ! 1x LOW ! ALL ATTND LS ! ALL FSB + RTS !

! RETURN TO SEAT, ! ! ! ECAM: !

! ON ! ! ! MESSAGE !

-------------------------------------------------------------------------------

! SIGN: ! CHIME: ! ALL CABIN + ! !

! FASTEN SEAT BELT/ ! 1x LOW ! ALL ATTND LS ! !

! RETURN TO SEAT, ! ! ! !

! OFF ! ! ! !

-------------------------------------------------------------------------------

(9) System Description - Indications

-------------------------------------------------------------------------------

! ! Indications !

! ------------------------------------------------------

! Action ! Aural ! Visual !

-------------------------------------------------------------------------------

! SIGN: ! CHIME: ! ALL CABIN + ! SIGNS: !

! FASTEN SEAT BELT/ ! 1x LOW ! ALL ATTND LS ! ALL FSB + RTS !

! RETURN TO SEAT, ! ! ! ECAM: !

! ON ! ! ! MESSAGE !

-------------------------------------------------------------------------------

! SIGN: ! CHIME: ! ALL CABIN + ! !

! FASTEN SEAT BELT/ ! 1x LOW ! ALL ATTND LS ! !

! RETURN TO SEAT, ! ! ! !

! OFF ! ! ! !

-------------------------------------------------------------------------------

(10) Operation of Passenger Lighted Signs

(a) Energization
Energization of the lighted signs system is as for CIDS Energization.

(b) Operation of NO SMOKING/EXIT Signs
With cockpit NO SMOKING switch on overhead panel in OFF position, all cabin and galley NO SMOKING signs, and all EXIT signs are off.
With cockpit NO SMOKING switch in AUTO position and landing gear down and locked, all cabin and galley NO SMOKING signs, and all EXIT signs are on.
With cockpit NO SMOKING switch in AUTO position and landing gear up and locked, the cabin NO SMOKING signs are on, the galley NO SMOKING signs, and EXIT signs are off.
With cockpit NO SMOKING switch in ON position, all cabin and galley NO SMOKING signs, and all EXIT signs are on.
With excessive aircraft decomporession, irrespective of the NO SMOKING switch position, all cabin and galley NO SMOKING signs, and all EXIT signs are on.

NOTE: A NO SMOKING placard is installed over all galley NO SMOKING signs.

(c) Operation of FASTEN SEAT BELT/RETURN TO SEAT Signs
The FSB and RTS lighted signs in the cabin and lavatories respectively are all switched on under any of these conditions:

The flight compartment FASTEN SEAT BELT switch in overhead panel is switched on,
The FSB signs are also activated in the event of excessive aircraft decompression, when the FSB switch is in AUTO or OFF position. The RTS signs are not illuminated during this event.

(d) General Operation Information
The PAX lighted signs are deactivated in the event of an aircraft emergency.

(11) Operation of Passenger Lighted Signs

(a) Energization
Energization of the lighted signs system is as for CIDS Energization.

(b) Operation of NO SMOKING Signs
All NS signs are always switched on if:

The CIDS is programmed for a non-smoking flight
The NO SMOKING switch in the flight compartment overhead-panel is set to the AUTO position.

Flight compartment NO SMOKING switch in overhead panel is switched to ON.
Excessive aircraft decompression, irrespective of the NS switch position.
Landing gear down and locked when the flight compartment NS switch is in the AUTO position.

(d) Operation of FASTEN SEAT BELT/RETURN TO SEAT Signs
The FSB and RTS lighted signs in the cabin and lavatories respectively are all switched on under any of these conditions:

The flight compartment FASTEN SEAT BELT switch in overhead panel is switched on,
The FSB signs are also activated in the event of excessive aircraft decompression, when the FSB switch is in AUTO or OFF position. The RTS signs are not illuminated during this event.
Slats or flaps operated, when the FSB switch is in AUTO position.

(e) General Operation Information
The PAX lighted signs are deactivated in the event of an aircraft emergency.

(12) Lighted Signs System Testing and Programming (testing is not applicable for LED cabin signs)
The fault status of the lighted signs is stored in the director BITE memory and is examined with the PTP. The CAM data which define the lighted signs system characteristics can be changed. Also additional functions which use the panel can be activated.
The 'NON SMOKER A/C' configuration is memorized in the layout of the CAM. The configuration is enabled after the CIDS power-up. All NS signs operate as defined for non smoker.
The 'NORMAL SIGNS MODE' (smoker A/C) configuration is memorized in the M-layout of the CAM after selection of NORMAL on the PTP.

E. Passenger Call System

(1) Architecture

Passenger Call System - Architecture . ** ON A/C NOT FOR ALL

Passenger Call System - Architecture ** ON A/C NOT FOR ALL

The components, interfaces and signal sources of the CIDS which are related to the passenger call system are as follows:

(a) Avionics Compartment

the link to SDAC
the two CIDS directors
the link to the Centralized Fault Display Interface Unit (CFDIU)

(b) Cabin

the DEUs A
the PA loudspeakers
the passenger call pushbutton
the DEUs B
the ACPs
the PTP

(2) Architecture

Passenger Call System - Architecture ** ON A/C NOT FOR ALL

The components, interfaces and signal sources of the CIDS which are related to the passenger call system are as follows:

(a) Avionics Compartment

the link to SDAC,
the two CIDS directors,
the link to the Centralized Fault Display Interface Unit (CFDIU).

(b) Cabin

the DEUs A
the PA loudspeakers
the passenger call pushbutton
the DEUs B
the ACPs
the PTP
the AIPs

(3) System Description
The equipment interface to the directors via DEUs A as follows:

one passenger call pushbutton and the seat row numbering light at each passenger seat row,
one passenger call pushbutton with an integral lamp in each lavatory.

Each DEU A interfaces up to three passenger call pushbuttons and lights. Each pushbutton and light is separately addressable. The CAM data assigns each pushbutton and light to a LH or RH cabin zone.
First activation of a passenger or lavatory pushbutton activates a chime. Visual indications come on. A second activation of a passenger or lavatory pushbutton reset the visual indications.

(4) Operation of the Passenger Call System

(a) Energization
The energization of the passenger call system is as for the CIDS energization.
On energization of the CIDS, the passenger call function of the CIDS becomes fully operational. The cabin is divided into forward and aft zones as set in the CAM data. All seat row numbering lights are on during the boarding.

(b) Call to the Attendants from a Passenger Seat
If you push a passenger call pushbutton-switch:

The related seat row identification comes on
You hear a high chime at the attendant stations
The blue light of the respective ACP comes on.

If you push a passenger call pushbutton a second time, the related indications go off.

(5) Operation of the Passenger Call System

(b) Call to the Attendants from a Passenger Seat
If you push a passenger call pushbutton-switch:

The related seat row identification comes on
You hear a high chime at the attendant stations
The blue light of the respective ACP comes on
The seat row number with a LH/RH reference as well as the location of the related lavatory shows on the AIPs. The AIPs are related to the passenger call zones. If you start more than one Pax call at the same time, only the first Pax call gives an indication on the related AIP. The respective indication goes off when the call is stopped and the indication of the second calling Pax comes on.

If you push a passenger call pushbutton a second time, the related indications go off.

(6) Passenger Call System Testing and Programming
The BITE status in the DEUs A signals defective passenger call lamps to the director. Faults may be examined via the PTP.

** ON A/C NOT FOR ALL

8. Test Bite
When the CIDS is energized, the directors perform a comprehensive hardware and software self-test. The CIDS top and middle line data buses, the PTP with the CAM, the FAP and the DEUs with the connected loads are tested.

A. Programming and Test Modes

PTP Menu Guided Structure ** ON A/C NOT FOR ALL

The first menu is the main menu. It shows the three main modes of the PTP:

the SYSTEM STATUS mode,
the SYSTEM TEST mode,
the PROGRAMMING mode.

(1) Access Regulation
The SYSTEM STATUS, the SYSTEM TEST and the ZONING (part of the PROGRAMMING mode) are entered without access code.
For the CABIN PROGRAMMING mode an access code must be entered. This protects the CABIN PROGRAMMING (part of the PROGRAMMING mode) against unauthorized access.
The A/C is delivered with the access code '333' for CAM LAYOUT SELECTION and '333 123' for PA LEVEL ADJUSTMENT.

(2) Access Code Entering
For the access to the CABIN PROGRAMMING mode it is necessary to enter:

a 3 digit code (level 1) CAM LAYOUT SELECTION
a 6 digit code (level 2) PA LEVEL ADJUSTMENT
a 9 digit code (level 3) SINGLE PARAMETER

The 9 digit code (level 3) is only be used by the A/C manufacturer.

A * symbol appears on the display after the input of each digit. The complete access code will be accepted by selecting the displayed ENTER function via the labelled key.
Entering an incorrect access code initiates the PTP display message
USER AUTHORIZATION FAILURE.

A new entry can be made after activation of the displayed RET function.

B. System Status Mode

SYSTEM STATUS - Example ** ON A/C NOT FOR ALL

(1) System Status Mode
The SYSTEM STATUS mode monitors the current status of the CIDS. This includes the directors, the DEUs, the data buses, the CAM, the FWD ATTND PANEL, the PTP and the interfaces to other systems. For detailed failure description the mode MAINTENANCE, which is part of the SYSTEM STATUS mode, can be selected.

For support of the maintenance/cabin crew, the status of the following systems is also monitored:

Lavatory Smoke Detection
Slides Bottle Pressure
Drain masts

After selection of SYSTEM STATUS mode, when there are no failures, the following messages are displayed on the PTP:

CIDS OK
LAV SMOKE Data OK
SLIDES PRESS OK
DRAINMASTS OK

A failure in one of these systems causes an annunciation. (Ref. Para. 9E).
The SYSTEM STATUS mode is displayed automatically on the PTP, except when the PTP is in the MAINTENANCE, the SYSTEM TEST or the PROGRAMMING mode. The sequence of the messages in this case is variable, the last received failure is indicated first. Any change of the status (e.g. a failure disappears) initiates a return to the first SYSTEM STATUS menu except when the MAINTENANCE, the SYSTEM TEST or the PROGRAMMING mode is selected.

In case of failure the respective following messages are:

<CIDS FAIL or <CIDS DEGRADATION
<LAV SMOKE SYS FAIL
<SLIDES PRESS LOW
<DRAINMASTS FAIL

For detailed information about the failure, push the related membrane switch.

(2) System Status
The SYSTEM STATUS mode monitors the current status of the CIDS. This includes the directors, the DEUs, the data buses, the CAM, the FWD ATTND PANEL, the PTP and the interfaces to other systems. For a detailed failure description the mode MAINTENANCE, which is part of the SYSTEM STATUS mode,can be selected.

For support of the maintenance/cabin crew, the status of the following systems is also monitored:

Lavatory Smoke Detection
Slides Bottle Pressure
Doors Bottle Pressure
Drainmasts

After selection of SYSTEM STATUS mode, when there are no failures, the following messages are displayed on the PTP:

CIDS OK
LAV SMOKE SYS OK
SLIDES PRESS OK
DOORS BOTTLE PRESSURE
DRAINMASTS OK

<CIDS FAIL or <CIDS DEGRADATION or <CIDS NO DEGRADE
<LAV SMOKE SYS FAIL
<SLIDES PRESS LOW
<DOORS PRESS LOW
<DRAINMASTS FAIL

For detailed information about the failure, push the related membrane switch.

(3) Detailed Messages

System Status - Failure Examples 1 ** ON A/C NOT FOR ALL

System Status - Failure Examples 2 ** ON A/C NOT FOR ALL

(a) Messages in case of <CIDS FAIL:

CHECK CIDS FUNCTIONS
CHECK CIDS FUNCTIONS
AT ATTND STATIONS
Priority
The first CIDS FAIL message has priority over the second, which has priority over the CIDS DEGRADATION messages. Higher priority messages inhibit the display of lower priority messages.

(b) Messages in case of <CIDS DEGRADATION:

CHECK CIDS FUNCTIONS
LAV X (example, the respective lavatory is shown)
CHECK CIDS FUNCTIONS
ATT FWD L (example, the respective attendant station is shown)
CHECK CIDS FUNCTIONS
SR 02 L (example, the respective seatrow is shown)
CHECK FWD ATTND PANEL
CHECK PROG & TEST PANEL
DON'T USE PROGRAMMING MODE

SMOKE DET FAIL
LAV X (example, the respective lavatory is shown)
NO DATA AVAILABLE

(d) Messages in case of <SLIDES PRESS LOW:

CHECK SLIDES PRESS
FWD L (example, the location of the respective slide is shown)

(e) Messages in case of <DOORS PRESS LOW:

CHECK DOOR PRESS
FWD L (example, the location of the respective door is shown)

(f) Messages in case of <DRAINMASTS FAIL:

CHECK WASTE WATER OVERFLOW FWD (example, the respective location is shown)
MAINTENANCE
CHECK AFT CARGO DRAINAGE

(g) The DOORS-CLOSED/SLIDES-ARMED status indication
The doors-closed/slides-armed status is received from the SDAC and indicated on PTP in the SYSTEM STATUS mode. The SLIDES STATUS and DOORS STATUS page must be selected manually. The displayed status is updated automatically. It will not be disturbed or interrupted by other incoming system status information. A respective OPEN or DISARMED indication is flashing. A CLOSED or ARMED indication is a steady on.
Messages in case of SLIDES STATUS:

ALL ARMED
ALL DISARMED
FWD: L=ARMED; R=DISA. (example, the respective location is shown)
NO INFORMATION AVAILABLE

Messages in case of DOORS STATUS:
ALL CLOSED
FWD: L=OPEN; R=CLOS. (example, the respective location is shown)
NO INFORMATION AVAILABLE

(4) Detailed Messages

System Status - Failure Examples 1 ** ON A/C NOT FOR ALL

System Status - Failure Examples 2 ** ON A/C NOT FOR ALL

(a) Messages in case of <CIDS FAIL:

CHECK CIDS FUNCTIONS
CHECK CIDS FUNCTIONS
AT ATTND STATIONS
Priority
The first CIDS FAIL message has priority over the second, which has priority over the CIDS DEGRADATION messages. Higher priority messages inhibit the display of lower priority messages.

(b) Messages in case of <CIDS DEGRADATION:

CHECK CIDS FUNCTIONS
LAV X (example, the respective lavatory shows)
CHECK CIDS FUNCTIONS
ATT FWD L (example, the respective attendant station is shown)
CHECK CIDS FUNCTIONS
SR 02 L (example, the respective seat row shows)
CHECK FWD ATTND PANEL
CHECK PROG & TEST PANEL
DON'T USE PROGRAMMING MODE

SMOKE DET FAIL
LAV X (example, the respective lavatory shows)
NO DATA AVAILABLE

(d) Messages in case of <DRAINMASTS FAIL:

CHECK WASTE WATER OVERFLOW FWD (example, the respective location is shown)
MAINTENANCE
CHECK AFT CARGO DRAINAGE

(e) The DOORS-CLOSED/SLIDES-ARMED status indication

SLIDES STATUS indication - Example ** ON A/C NOT FOR ALL

DOORS STATUS indication - Example ** ON A/C NOT FOR ALL

The doors-closed/slides-armed status is received from the SDAC and indicated on PTP in the SYSTEM STATUS mode. The SLIDES STATUS and DOORS STATUS page must be selected manually. The displayed status is updated automatically. It will not be disturbed or interrupted by other incoming system status information. A respective OPEN or DISARMED indication is flashing. A CLOSED or ARMED indication is a steady on.
Messages in case of SLIDES STATUS:

ALL ARMED
ALL DISARMED
FWD: L=ARMED; R=DISA. (example, the respective location is shown)
NO INFORMATION AVAILABLE

Messages in case of DOORS STATUS:
ALL CLOSED
FWD: L=OPEN; R=CLOS. (example, the respective location is shown)
NO INFORMATION AVAILABLE

(5) MAINTENANCE MODE

System Status - Example ** ON A/C NOT FOR ALL

(a) A MAINTENANCE mode for detailed CIDS failure description is part of the SYSTEM STATUS mode.
Failures are written into the directors BITE ground/flight memory and can be read via this mode and via the CFDS in the flight compartment. The last occurred failure is the first shown. For failures of continuously monitored systems the BITE ground memory will be updated when the failure has been cancelled.

No entries into the BITE memory are made in case of emergency conditions (normal power is not available or the CIDS is working with the mandatory layout).

No subsequent related failures will be entered into the memory after the original failure has been entered:

Examples:

If one DEU A fails, no further entries into memory are made for the associated components.
If one DEU B fails, no further entries into memory are made for the associated slides bottle pressure, but the system status on the PTP displays SLIDES PRESS LOW.

(b) The following items from the directors BITE memory are selectable:

1 LAST LEG REPORT
In flight, this report is called CURRENT LEG REPORT.
It is the only displayed and accessible item within the MAINTENANCE mode in flight.

The LAST/CURRENT LEG REPORT contains class 2 + 1 failures (Ref. Para. 8F) of the last/current flight leg.

The report includes the date, the time and the ATA chapter for each failure. There are no entries for flight legs without failures but the flight leg counts are incremented.

2 PREV LEGS REPORT
The PREV LEGS REPORT contains 1 + 2 failures of the last 64 flight legs.
The PREV LEGS REPORT has all data, which are stored in the LAST LEG REPORT.

3 LRU INDENTIFICATION
Messages for LRU IDENTIFICATIONS (examples):

DIRECTOR
1: Z010H0004114

DIRECTOR
2: Z010H0004114

CAM M-COUNT=030

Z050H0000343 (1) (example, the active layout is shown)

PROG AND TEST PNL
Z020H0001112

NOTE : M-COUNT = modification count, incremented after any programming/saving

to Layout M.

4 FAULT DATA
The FAULT DATA mode includes the flight leg, the date, the time (UTC), the number of occurrences (max 4 counts, for intermittent failures) and coded trouble shooting data for internal director and DEU failures.
Present failures on ground are marked with GND (Ref. Para. 8.B.(3)(b)5 GND SCAN), failures of the last leg with LEG -00, (Ref. Para. 8.B.(3)(b)1 LAST LEG REPORT) and failures of the previous legs with -01, -02 and up (Ref.Para. 8.B.(3)(b)2 PREV LEGS REPORT).

a CIDS Trouble Shooting Data Table
These tables show the meaning of the last 6 digits appearing in the FAULT DATA mode (PTP) and TROUBLE SHOOTING DATA mode (MCDU) for each class 1 and 2 failure of the Directors, the DEUs, FAP and PTP. These data give more detailed information of the failures found in the 'normal' clear language reports. No trouble shooting data will be kept in the memory (only clear language messages) for failures of:

The CAM
The Slide/Door Pressure
The Drain masts

The SDCUs.

DIRECTOR FAILURES:

a a: 0 1 = Director 101RH

0 2 = Director 102RH

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! code ! meaning !

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! 1 0 0 0 a a ! no data from other computer (a a) !

----------------------------------------------------------------------

! 1 1 0 0 a a ! power supply !

----------------------------------------------------------------------

! 1 2 0 0 a a ! microcomputer !

----------------------------------------------------------------------

! 1 2 0 2 a a ! timer !

----------------------------------------------------------------------

! 1 2 0 3 a a ! memory !

----------------------------------------------------------------------

! 1 2 0 4 a a ! OBRM !

----------------------------------------------------------------------

! 1 3 0 0 a a ! bus interface total !

----------------------------------------------------------------------

! 1 3 5 1 a a ! bus driver or TOP LINE 1R !

----------------------------------------------------------------------

! 1 3 5 2 a a ! bus driver or TOP LINE 1L !

----------------------------------------------------------------------

! 1 3 5 3 a a ! bus driver or TOP LINE 2R !

----------------------------------------------------------------------

! 1 3 5 4 a a ! bus driver or TOP LINE 2L !

----------------------------------------------------------------------

! 1 3 5 5 a a ! bus driver or MID LINE L !

----------------------------------------------------------------------

! 1 3 5 6 a a ! bus driver or MID LINE R !

----------------------------------------------------------------------

! 1 6 0 0 a a ! audio output !

----------------------------------------------------------------------

! 1 7 0 0 a a ! audio input total !

----------------------------------------------------------------------

! 1 7 0 1 a a ! audio input signal conditioning !

----------------------------------------------------------------------

! 1 7 0 2 a a ! audio input multiplexer !

----------------------------------------------------------------------

! 1 7 0 4 a a ! audio input gain control !

----------------------------------------------------------------------

! 1 7 0 6 a a ! EVAC tone generator !

----------------------------------------------------------------------

! 1 7 0 7 a a ! chime generator !

----------------------------------------------------------------------

! 1 7 0 8 a a ! telephone tone generator !

----------------------------------------------------------------------

DEU A FAILURES:

b b = DEU-A FIN (HEX-code)

b b: b b:

0 1 = 200RH01 1 1 = 200RH17

0 2 = 200RH02 1 2 = 200RH18

0 3 = 200RH03 1 3 = 200RH19

0 4 = 200RH04 1 4 = 200RH20

0 5 = 200RH05 1 5 = 200RH21

0 6 = 200RH06 1 6 = 200RH22

0 7 = 200RH07 1 7 = 200RH23

0 8 = 200RH08 1 8 = 200RH24

0 9 = 200RH09 1 9 = 200RH25

0 A = 200RH10 1 A = 200RH26

0 B = 200RH11 1 B = 200RH27

0 C = 200RH12 1 C = 200RH28

0 D = 200RH13 1 D = 200RH29

0 E = 200RH14 1 E = 200RH30

0 F = 200RH15 1 F = 200RH31

1 0 = 200RH16 2 0 = 200RH32

----------------------------------------------------------------------

! code ! meaning !

----------------------------------------------------------------------

! 2 1 0 0 b b ! DEU A power supply !

----------------------------------------------------------------------

! 2 4 0 0 b b ! DEU A discrete output or wiring conn.-pin J2-14 !

----------------------------------------------------------------------

! 2 4 0 1 b b ! DEU A discrete output or wiring conn.-pin J2-13 !

----------------------------------------------------------------------

! 2 4 0 2 b b ! DEU A discrete output or wiring conn.-pin J2-12 !

----------------------------------------------------------------------

! 2 4 0 3 b b ! DEU A discrete output or wiring conn.-pin J2-11 !

----------------------------------------------------------------------

! 2 4 0 4 b b ! DEU A discrete output or wiring conn.-pin J2-10 !

----------------------------------------------------------------------

! 2 4 0 5 b b ! DEU A discrete output or wiring conn.-pin J2-09 !

----------------------------------------------------------------------

! 2 4 0 6 b b ! DEU A discrete output or wiring conn.-pin J2-06 !

----------------------------------------------------------------------

! 2 4 0 7 b b ! DEU A discrete output or wiring conn.-pin J2-05 !

----------------------------------------------------------------------

! 2 4 0 8 b b ! DEU A discrete output or wiring conn.-pin J2-04 !

----------------------------------------------------------------------

! 2 4 0 9 b b ! DEU A discrete output or wiring conn.-pin J2-03 !

----------------------------------------------------------------------

! 2 4 0 A b b ! DEU A discrete output or wiring conn.-pin J2-02 !

----------------------------------------------------------------------

! 2 4 0 B b b ! DEU A discrete output or wiring conn.-pin J2-01 !

----------------------------------------------------------------------

! 2 4 0 C b b ! DEU A discrete output or wiring conn.-pin J2-18 !

----------------------------------------------------------------------

! 2 4 0 D b b ! DEU A discrete output or wiring conn.-pin J2-17 !

----------------------------------------------------------------------

! 2 4 0 E b b ! DEU A discrete output or wiring conn.-pin J2-16 !

----------------------------------------------------------------------

! 2 4 0 F b b ! DEU A discrete output or wiring conn.-pin J3-11 !

----------------------------------------------------------------------

! 2 4 1 0 b b ! DEU A discrete output or wiring conn.-pin J3-26 !

----------------------------------------------------------------------

! 2 4 1 1 b b ! DEU A discrete output or wiring conn.-pin J3-25 !

----------------------------------------------------------------------

! 2 4 1 2 b b ! DEU A discrete output or wiring conn.-pin J3-48 !

----------------------------------------------------------------------

! 2 4 1 3 b b ! DEU A discrete output or wiring conn.-pin J3-09 !

----------------------------------------------------------------------

! 2 4 1 4 b b ! DEU A discrete output or wiring conn.-pin J3-24 !

----------------------------------------------------------------------

! 2 4 1 5 b b ! DEU A discrete output or wiring conn.-pin J3-23 !

----------------------------------------------------------------------

! 2 4 1 6 b b ! DEU A discrete output or wiring conn.-pin J3-15 !

----------------------------------------------------------------------

! 2 4 1 7 b b ! DEU A discrete output or wiring conn.-pin J3-07 !

----------------------------------------------------------------------

! 2 4 1 8 b b ! DEU A discrete output or wiring conn.-pin J3-22 !

----------------------------------------------------------------------

! 2 4 1 9 b b ! DEU A discrete output or wiring conn.-pin J3-21 !

----------------------------------------------------------------------

! 2 4 1 A b b ! DEU A discrete output or wiring conn.-pin J3-13 !

----------------------------------------------------------------------

DEU B, FAP and PTP FAILURES:

c c = DEU-B FIN (HEX-code)

c c:

0 1 = 300RH01

0 2 = 300RH02

0 3 = 300RH03

0 4 = 300RH04

0 5 = 300RH05

0 6 = 300RH06

0 7 = 300RH07

0 8 = 300RH08

----------------------------------------------------------------------

! code ! meaning !

----------------------------------------------------------------------

! 3 1 0 0 c c ! DEU B power supply !

----------------------------------------------------------------------

! 3 4 0 0 c c ! DEU B discrete output or wiring conn.-pin J2-12 !

----------------------------------------------------------------------

! 3 4 0 1 c c ! DEU B discrete output or wiring conn.-pin J2-11 !

----------------------------------------------------------------------

! 3 4 0 2 c c ! DEU B discrete output or wiring conn.-pin J2-10 !

----------------------------------------------------------------------

! 3 4 0 3 c c ! DEU B discrete output or wiring conn.-pin J2-09 !

----------------------------------------------------------------------

! 3 4 0 4 c c ! DEU B discrete output or wiring conn.-pin J2-04 !

----------------------------------------------------------------------

! 3 4 0 5 c c ! DEU B discrete output or wiring conn.-pin J2-03 !

----------------------------------------------------------------------

! 3 4 0 6 c c ! DEU B discrete output or wiring conn.-pin J2-02 !

----------------------------------------------------------------------

! 3 4 0 7 c c ! DEU B discrete output or wiring conn.-pin J2-01 !

----------------------------------------------------------------------

! 3 4 0 8 c c ! DEU B discrete output or wiring conn.-pin J2-08 !

----------------------------------------------------------------------

! 3 4 0 9 c c ! DEU B discrete output or wiring conn.-pin J2-07 !

----------------------------------------------------------------------

! 3 4 0 A c c ! DEU B discrete output or wiring conn.-pin J3-45 !

----------------------------------------------------------------------

! 3 4 0 B c c ! DEU B discrete output or wiring conn.-pin J3-42 !

----------------------------------------------------------------------

! 3 4 0 C c c ! DEU B discrete output or wiring conn.-pin J3-09 !

----------------------------------------------------------------------

! 4 0 0 0 0 1 ! Programming and Test Panel !

----------------------------------------------------------------------

! 5 0 0 0 0 1 ! FWD Attendant Panel !

----------------------------------------------------------------------

5 CLASS 3 FAULTS
Some CLASS 3 FAULTS are only detected and written into the BITE memory at director power on or after a manual test activation via the PTP. On the ground, after you cancel a class 3 fault, it is removed from the memory after the next director power on or after a new test activation.
Some CLASS 3 FAULTS are detected and written into the BITE memory due to continuous monitoring. Such a class 3 fault is removed from the memory when the failure no longer occurs.

Messages for CLASS 3 FAULTS: (Ref. Para. 8F)

6 GND SCAN

The GND SCAN indicates all class 1 and 2 failures which are present on the ground. For the continuously monitored systems, the ground memory is updated when the failure is cancelled. For other systems, the ground memory is updated after a director power on or after a test activation via PTP.

(6) MAINTENANCE MODE

System Status - Example ** ON A/C NOT FOR ALL

If one DEU A fails, no further entries into memory are made for the associated components.
If one DEU B fails, no further entries into memory are made for the associated slides bottle pressure, but the system status on the PTP displays SLIDES PRESS LOW.

(b) The following items from the directors BITE memory are selectable:

2 PREV LEGS REPORT
The PREV LEGS REPORT contains 1 + 2 failures of the last 64 flight legs.
The PREV LEGS REPORT has all data, which are stored in the LAST LEG REPORT.

3 LRU INDENTIFICATION
Messages for LRU IDENTIFICATIONS (examples):

DIRECTOR
1: Z010H0004114

DIRECTOR
2: Z010H0004114

CAM M-COUNT=030

Z050H0000343 (1) (example, the active layout is shown)

PROG AND TEST PNL
Z020H0001112

NOTE : M-COUNT = modification count, incremented after any programming/saving

to Layout M.

a a: 0 1 = Director 101RH

0 2 = Director 102RH

----------------------------------------------------------------------

! code ! meaning !

----------------------------------------------------------------------

! 1 0 0 0 a a ! no data from other computer (a a) !

----------------------------------------------------------------------

! 1 1 0 0 a a ! power supply !

----------------------------------------------------------------------

! 1 2 0 0 a a ! microcomputer !

----------------------------------------------------------------------

! 1 2 0 2 a a ! timer !

----------------------------------------------------------------------

! 1 2 0 3 a a ! memory !

----------------------------------------------------------------------

! 1 2 0 4 a a ! OBRM !

----------------------------------------------------------------------

! 1 3 0 0 a a ! bus interface total !

----------------------------------------------------------------------

! 1 3 5 1 a a ! bus driver or TOP LINE 1R !

----------------------------------------------------------------------

! 1 3 5 2 a a ! bus driver or TOP LINE 1L !

----------------------------------------------------------------------

! 1 3 5 3 a a ! bus driver or TOP LINE 2R !

----------------------------------------------------------------------

! 1 3 5 4 a a ! bus driver or TOP LINE 2L !

----------------------------------------------------------------------

! 1 3 5 5 a a ! bus driver or MID LINE L !

----------------------------------------------------------------------

! 1 3 5 6 a a ! bus driver or MID LINE R !

----------------------------------------------------------------------

! 1 6 0 0 a a ! audio output !

----------------------------------------------------------------------

! 1 7 0 0 a a ! audio input total !

----------------------------------------------------------------------

! 1 7 0 1 a a ! audio input signal conditioning !

----------------------------------------------------------------------

! 1 7 0 2 a a ! audio input multiplexer !

----------------------------------------------------------------------

! 1 7 0 4 a a ! audio input gain control !

----------------------------------------------------------------------

! 1 7 0 6 a a ! EVAC tone generator !

----------------------------------------------------------------------

! 1 7 0 7 a a ! chime generator !

----------------------------------------------------------------------

! 1 7 0 8 a a ! telephone tone generator !

----------------------------------------------------------------------

DEU A FAILURES:

b b = DEU-A FIN (HEX-code)

b b: b b:

0 1 = 200RH01 0 D = 200RH13

0 2 = 200RH02 0 E = 200RH14

0 3 = 200RH03 1 1 = 200RH17

0 4 = 200RH04 1 2 = 200RH18

0 5 = 200RH05 1 3 = 200RH19

0 6 = 200RH06 1 4 = 200RH20

0 7 = 200RH07 1 5 = 200RH21

0 8 = 200RH08 1 6 = 200RH22

0 9 = 200RH09 1 7 = 200RH23

0 A = 200RH10 1 8 = 200RH24

0 B = 200RH11 1 9 = 200RH25

0 C = 200RH12 1 A = 200RH26