CABIN INTERCOMMUNICATION DATA SYSTEM (CIDS) - DESCRIPTION AND OPERATION

** ON A/C NOT FOR ALL

1. General
The Cabin Intercommunication Data System (CIDS) is a microprocessor-based system. It operates, controls and monitors the main cabin systems and can do different system and unit tests. The connected systems are:

Air conditioning
Communications
Fire protection
Escape facilities
Ice protection
Lights
Water/Waste.

If the cabin layout is changed, it is not necessary to make a complex and time-consuming hardware change of CIDS components. Only the software database has to be changed to adapt e.g. the new cabin zoning.

** ON A/C NOT FOR ALL

2. Component Location

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

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

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

Flight Attendant Panel (FAP) with integrated PRAM - Component Location ** ON A/C NOT FOR ALL

Flight Attendant Panel (FAP) - Component Location ** ON A/C NOT FOR ALL

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

Area Call Panel (ACP) - Component Location ** ON A/C NOT FOR ALL

Passenger Service Unit (PSU) - Component Location ** ON A/C NOT FOR ALL

Loudspeaker and cabin signs - Component Location ** ON A/C NOT FOR ALL

DEU type A with Connection and Termination Boxes - Component Location (Sheet 1) ** ON A/C NOT FOR ALL

DEU type A with Connection and Termination Boxes - Component Location (Sheet 2) ** ON A/C NOT FOR ALL

DEU type B with Connection and Termination Boxes - Component Location ** ON A/C NOT FOR ALL

FIN	FUNCTIONAL DESIGNATION	PANEL	ZONE	ATA REF
** ON A/C NOT FOR ALL
101RH	DIR-CIDS, 1	87VU	127	23-73-34
102RH	DIR-CIDS, 2	88VU	128	23-73-34
115RH	MODULE-CABIN ASSIGNMENT		221	23-73-19
116RH	CIDS OBRM		221	23-73-21
120RH	FAP		221	23-73-12
126RH	AAP		261	23-73-13
130RH	HANDSET		210	23-73-44
** ON A/C NOT FOR ALL
132RH	SUPPORT BRACKET		210	23-73-44
** ON A/C NOT FOR ALL
320RH11	AIP		263	23-31-00
** ON A/C NOT FOR ALL
320RH1	AIP		221	23-31-00
320RH9	AIP		261	23-31-00
** ON A/C NOT FOR ALL
320RH11	AIP		262	23-31-00
** ON A/C NOT FOR ALL
322RH11	AIP		200	23-31-00
** ON A/C NOT FOR ALL
320RH1	AIP		200	23-31-00
320RH9	AIP		200	23-31-00
** ON A/C NOT FOR ALL
330RH1	HANDSET		221	23-73-44
330RH11	HANDSET		262	23-73-44
** ON A/C NOT FOR ALL
330RH9	HANDSET		261	23-73-44
** ON A/C NOT FOR ALL
332RH1	SUPPORT BRACKET		221	23-73-44
332RH9	SUPPORT BRACKET		261	23-73-44
332RH11	SUPPORT BRACKET		262	23-73-44
** ON A/C NOT FOR ALL
330RH11	HANDSET		261	23-73-44
** ON A/C NOT FOR ALL
330RH1	HANDSET		200	23-73-44
** ON A/C NOT FOR ALL
330RH9	HANDSET		200	23-73-44
330RH11	HANDSET		200	23-73-44
** ON A/C NOT FOR ALL
340RH1	AREA CALL PNL	3700VU	223	23-31-00
340RH2	AREA CALL PNL	3700VU	224	23-31-00
340RH10	AREA CALL PNL	3701VU	264	23-31-00
** ON A/C NOT FOR ALL
340RH9	AREA CALL PNL	3701VU	263	23-31-00
** ON A/C NOT FOR ALL
340RH1	AREA CALL PNL		223	23-31-00
340RH2	AREA CALL PNL		223	23-31-00
340RH10	AREA CALL PNL		263	23-31-00
** ON A/C NOT FOR ALL
117RH	I-PRAM, CF-CARD		221	23-32-36
** ON A/C NOT FOR ALL
330RH8	HANDSET		252	23-73-44
** ON A/C NOT FOR ALL
332RH14	SUPPORT BRACKET		242	23-73-44
** ON A/C NOT FOR ALL
330RH14	HANDSET		242	23-73-44
** ON A/C NOT FOR ALL
340RH7	AREA CALL PNL		241	23-31-00
** ON A/C NOT FOR ALL
340RH7	AREA CALL PNL	3703VU	251	23-31-00
340RH8	AREA CALL PNL	3703VU	252	23-31-00
** ON A/C NOT FOR ALL
340RH13	AREA CALL PNL	3702VU	243	23-31-00
340RH14	AREA CALL PNL	3702VU	244	23-31-00
** ON A/C NOT FOR ALL
340RH7	AREA CALL PNL		250	23-31-00
340RH8	AREA CALL PNL		250	23-31-00
** ON A/C NOT FOR ALL
395RH1	PUSHBUTTON-SWITCH, ALERT	2080VU	221	23-31-00
395RH9	PUSHBUTTON-SWITCH, ALERT	2080VU	261	23-31-00
395RH10	PUSHBUTTON-SWITCH, ALERT	2080VU	262	23-31-00
320RH10	AIP		262	23-31-00
** ON A/C NOT FOR ALL
571RH1	PUSHBUTTON-SWITCH, SMOKE	2065VU	200	23-31-00
571RH5	PUSHBUTTON-SWITCH, SMOKE	2065VU	200	23-31-00
** ON A/C NOT FOR ALL
571RH4	PUSHBUTTON-SWITCH, SMOKE	2065VU	200	23-31-00
** ON A/C NOT FOR ALL
571RH6	PUSHBUTTON-SWITCH, SMOKE		250	23-31-00
** ON A/C NOT FOR ALL
322RH1	AIP		200	23-31-00
** ON A/C NOT FOR ALL
322RH4	AIP		200	23-31-00
** ON A/C NOT FOR ALL
330RH13	HANDSET		251	23-73-44
** ON A/C NOT FOR ALL
330RH7	HANDSET		251	23-73-44
** ON A/C NOT FOR ALL
330RH13	HANDSET		241	23-73-44
332RH13	SUPPORT BRACKET		241	23-73-44
** ON A/C NOT FOR ALL
332RH7	SUPPORT BRACKET		251	23-73-44
571RH9	PUSHBUTTON-SWITCH, SMOKE	2065VU	200	23-31-00
** ON A/C NOT FOR ALL
322RH3	AIP		200	23-31-00
** ON A/C NOT FOR ALL
322RH2	AIP		200	23-31-00
** ON A/C NOT FOR ALL
395RH4	PUSHBUTTON-SWITCH, ALERT	2080VU	240	23-31-00
395RH6	PUSHBUTTON-SWITCH, ALERT	2080VU	250	23-31-00
** ON A/C NOT FOR ALL
200RH1	DEU-A		231	23-31-00
200RH2	DEU-A		232	23-31-00
200RH1	DEU-A		231	23-31-00
200RH2	DEU-A		232	23-31-00
200RH3	DEU-A		231	23-31-00
200RH4	DEU-A		232	23-31-00
200RH7	DEU-A		241	23-31-00
200RH8	DEU-A		242	23-31-00
200RH13	DEU-A		251	23-31-00
200RH14	DEU-A		252	23-31-00
200RH15	DEU-A		251	23-31-00
200RH16	DEU-A		252	23-31-00
208RH1	DEU CONNECTION BOX		231	23-31-00
208RH2	DEU CONNECTION BOX		232	23-31-00
208RH3	DEU CONNECTION BOX		231	23-31-00
208RH4	DEU CONNECTION BOX		232	23-31-00
208RH7	DEU CONNECTION BOX		241	23-31-00
208RH8	DEU CONNECTION BOX		242	23-31-00
208RH13	DEU CONNECTION BOX		251	23-31-00
208RH14	DEU CONNECTION BOX		252	23-31-00
209RH1	DEU TERMINATION BOX		251	23-31-00
209RH2	DEU TERMINATION BOX		252	23-31-00
300RH1	DEU-B		223	23-31-00
300RH6	DEU-B		254	23-31-00
300RH7	DECODER/ENCODER UNIT B		263	23-31-00
300RH8	DEU-B		263	23-31-00
308RH1	DEU CONNECTION BOX		223	23-31-00
308RH6	DEU CONNECTION BOX		254	23-31-00
309RH1	DEU TERMINATION BOX		263	23-31-00
309RH2	DEU TERMINATION BOX		263	23-31-00
200RH11	DEU-A		251	23-31-00
200RH12	DEU-A		252	23-31-00
208RH11	DEU CONNECTION BOX		251	23-31-00
208RH12	DEU CONNECTION BOX		252	23-31-00
** ON A/C NOT FOR ALL
200RH9	DEU-A		241	23-31-00
200RH10	DEU-A		242	23-31-00
208RH5	DEU CONNECTION BOX		241	23-31-00
208RH6	DEU CONNECTION BOX		242	23-31-00
208RH9	DEU CONNECTION BOX		241	23-31-00
208RH10	DEU CONNECTION BOX		242	23-31-00
** ON A/C NOT FOR ALL
200RH5	DEU-A		243	23-31-00
200RH6	DEU-A		244	23-31-00
** ON A/C NOT FOR ALL
200RH5	DEU-A		241	23-31-00
200RH6	DEU-A		242	23-31-00
** ON A/C NOT FOR ALL
308RH2	DEU CONNECTION BOX		223	23-31-00
308RH5	DEU CONNECTION BOX		253	23-31-00
** ON A/C NOT FOR ALL
300RH4	DEU-B		244	23-31-00
308RH3	DEU CONNECTION BOX		243	23-31-00
308RH4	DEU CONNECTION BOX		244	23-31-00
** ON A/C NOT FOR ALL
300RH5	DEU-B		240	23-31-00
** ON A/C NOT FOR ALL
300RH5	DEU-B		253	23-31-00
** ON A/C NOT FOR ALL
601RH	PSU PCB SWITCH PANEL		200	23-33-00
602RH	PSU PISA		200	23-33-00
603RH	LIGHT READING, PSU LED		200	23-33-00
604RH	LIGHT READING, PSU LED		200	23-33-00
605RH	LIGHT READING, PSU LED		200	23-33-00
606RH	PSU INFO SIGN		200	23-33-00
607RH	PSU LOUDSPEAKER		200	23-33-00
621RH	PSU		200	23-33-00
622RH	PSU		200	23-33-00
623RH	PNL, RL, NS/FSB L		200	23-33-00
651RH	PSU		200	23-31-00
652RH	PSU		200	23-31-00
653RH	PNL, 3LIGHTS, NS/FSB		200	23-33-00

** ON A/C NOT FOR ALL

3. System Description

A. System Philosophy

To make it easy to change the cabin layout, the CIDS hardware has spare inputs, outputs and circuits. These allow the connection of new and additional equipment without a hardware change of CIDS components. Furthermore the software of the CIDS defines all operations. If any equipment is changed, only the CIDS software database must be modified.
To change the configuration refer to options, cabin reconfiguration or CIDS expansion it is only necessary to do a software database change. This decreases the time that the aircraft is out-of-service.
CIDS is also designed to sense faults in CIDS components and in the connected equipment by itself. Thus scheduled maintenance is unnecessary.
The system philosophy is based on:

A microprocessor-controlled data bus system
The connection of cabin systems via data bus cables
Four data bus lines (two top lines for PAX related systems and the cabin illumination and two middle lines for crew related systems)
Two functional units for the data bus control, the CIDS directors 1 and 2
One director in active mode and the second one in hot-standby
Immediate switchover to the second director if a failure of the first one occurs
A Flight Attendant Panel (FAP) to program, to control and to indicate the status of the CIDS and related cabin systems and to emulate CFDS reports
Provisions for additional Flight Attendant Panels (FAP)
Addressable Decoder/Encoder Units type A (DEU type A) for the interface between top line data buses and cabin related systems
Passenger Interface and Supply Adapters (PISA) for the interface between Decoder/Encoder Units type A (DEU type A) and some cabin related systems/units
Stand-Alone Passenger Interface and Supply Adapters (StA PISA) for the interface between Decoder/Encoder Units type A (DEU type A) and equipment/ indications installed near the forward and aft cabin attendant stations (Ref. 33-27-00)
Addressable Decoder/Encoder Units type B (DEU type B) for the interface between middle line data buses and crew related systems
Configuration of cabin zones and other system properties in address tables which are stored in a software database, the Cabin Assignment Module (CAM),
Easy exchange of the CAM which is plugged into the FAP
One On-Board Replaceable Module (OBRM) which is plugged into the FAP and where the whole system software is stored
A Vacuum System Control Function (VSCF) to control and indicate the status of the vacuum toilet system
Built-in Test Equipment (BITE) to make scheduled maintenance unnecessary.

The system philosophy is based on:

A microprocessor-controlled data bus system,
The connection of cabin systems via data bus cables,
Four data bus lines (two top lines for PAX related systems and the cabin illumination and two middle lines for crew related systems),
Two functional units for the data bus control, the CIDS directors 1 and 2,
One director in active mode and the second one in hot-standby,
Immediate switchover to the second director if a failure of the first one occurs,
A Flight Attendant Panel (FAP) to program, to control and to indicate the status of the CIDS and related cabin systems and to emulate CFDS reports,
Provisions for additional Flight Attendant Panels (FAP),
Addressable Decoder/Encoder Units type A (DEU type A) for the interface between top line data buses and cabin related systems,
Passenger Interface and Supply Adapters (PISA) for the interface between Decoder/Encoder Units type A (DEU type A) and some cabin related systems/units,
Stand-Alone Passenger Interface and Supply Adapters (StA PISA) for the interface between Decoder/Encoder Units type A (DEU type A) and equipment/ indications installed near the forward and aft cabin attendant stations (Ref. 33-27-00),
Addressable Decoder/Encoder Units type B (DEU type B) for the interface between middle line data buses and crew related systems,
Configuration of cabin zones and other system properties in address tables which are stored in a software database, the Cabin Assignment Module (CAM),
Easy exchange of the CAM which is plugged into the FAP,
One On-Board Replaceable Module (OBRM) which is plugged into the FAP and where the whole system software is stored,
One Prerecorded Announcement and Boarding Music (PRAM) audio database plugged into the FAP. This memory card contains the boarding music and the PRAM audio files,
A Vacuum System Control Function (VSCF) to control and indicate the status of the vacuum toilet system,
Built-in Test Equipment (BITE) to make scheduled maintenance unnecessary,

A Smoke Detection Function (SDF) to give a warning of smoke in the lavatories and in the cargo compartment.

B. System Architecture
The CIDS has these components:

Director,
Decoder/Encoder Unit (DEU) type A,
Decoder/Encoder Unit (DEU) type B,
Passenger Interface and Supply Adapter (PISA),
Stand-Alone Passenger Interface and Supply Adapter (StA PISA),
Flight Attendant Panel (FAP),
Cabin Assignment Module (CAM),
On-Board Replaceable Module (OBRM),
Integrated Prerecorded Announcement & Boarding Music (PRAM),
Additional Attendant Panel (AAP),
Attendant Indication Panel (AIP),
Area Call Panel (ACP),
Handsets,
Loudspeaker,
Passenger call/reset pushbutton,
Passenger call light,

The CIDS consists of these components:

Director,
Decoder/Encoder Unit (DEU) type A,
Decoder/Encoder Unit (DEU) type B,
Passenger Interface and Supply Adapter (PISA),
Stand-Alone Passenger Interface and Supply Adapter (StA PISA),
Flight Attendant Panel (FAP),
Cabin Assignment Module (CAM),
On-Board Replaceable Module (OBRM),
Additional Attendant Panel (AAP),
Attendant Indication Panel (AIP),
Area Call Panel (ACP),
Handsets,
Loudspeaker,
Passenger call/reset pushbutton,
Passenger call light,
Switch panel (2065VU),

The CIDS consists of these components:

Director,
Decoder/Encoder Unit (DEU) type A,
Decoder/Encoder Unit (DEU) type B,
Passenger Interface and Supply Adapter (PISA),
Stand-Alone Passenger Interface and Supply Adapter (StA PISA),
Flight Attendant Panel (FAP),
Cabin Assignment Module (CAM),
On-Board Replaceable Module (OBRM),
Integrated Prerecorded Announcement & Boarding Music (PRAM),
Additional Attendant Panel (AAP),
Attendant Indication Panel (AIP),
Area Call Panel (ACP),
Handsets,
Loudspeaker,
Passenger call/reset pushbutton,
Passenger call light,
Switch panel (2064VU),

The CIDS consists of these components:

Director,
Decoder/Encoder Unit (DEU) type A,
Decoder/Encoder Unit (DEU) type B,
Passenger Interface and Supply Adapter (PISA),
Stand-Alone Passenger Interface and Supply Adapter (StA PISA),
Flight Attendant Panel (FAP),
Cabin Assignment Module (CAM),
On-Board Replaceable Module (OBRM),
Integrated Prerecorded Announcement & Boarding Music (PRAM),
Additional Attendant Panel (AAP),
Attendant Indication Panel (AIP),
Area Call Panel (ACP),
Handsets,
Loudspeaker,
Passenger call/reset pushbutton,
Passenger call light,
Switch panel (2065VU),
Switch panel (2064VU),

NS, FSB and RTS signs.

PED, FSB and RTS signs.

NS, PED, FSB and RTS signs.

All components of the CIDS are connected to two identical directors. The connections are realized by data bus interfaces, audio interfaces and discrete interfaces.
Furthermore, CIDS has interfaces to other systems. The interfaces to these systems are realized as described above. The systems are connected to the CIDS components.

(1) CIDS directors

CIDS Director Interfaces - Block Diagram (Sheet 1) ** ON A/C NOT FOR ALL

CIDS Director Interfaces - Block Diagram (Sheet 2) ** ON A/C NOT FOR ALL

The two directors are the central control components of the CIDS. One director is in active mode, the other one is in hot standby mode.

(a) The CIDS directors have a data bus interface to the:

DEU type A,
DEU type B,
Flight Attendant Panel (FAP),
System Data Acquisition Concentrator 1+2 (SDAC),
Flight Warning Computer 1+2 (FWC),
Centralized Fault Display System (CFDS),
Air Conditioning System Controller (ACSC).

(b) The CIDS directors have a discrete interface to the:

Slat Flap Control Computer 1+2 (SFCC),
Landing Gear Control and Interface Unit 1+2 (LGCIU),
Cabin Pressure Controller 1+2 (CPC),
Cabin pressure relay,
Indicator Light Control Box (ILCB),
Cockpit call panel,
Service interphone override switch,
Exit signs relay,
Cockpit door switch,
System Data Acquisition Concentrator 1+2 (SDAC),
Flight Warning Computer 1+2 (FWC),
Top lines cut off relay,
Engine Interface Unit (EIU),
Motor start relay vacuum generator,
EVAC panel,
EVAC horn,
NS/FSB panel.

Audio Management Unit (AMU),
Cockpit handset,
Service interphone boomsets.

(2) CIDS directors

CIDS Director Interfaces - Block Diagram (Sheet 1) ** ON A/C NOT FOR ALL

CIDS Director Interfaces - Block Diagram (Sheet 2) ** ON A/C NOT FOR ALL

The two directors are the central control components of the CIDS. One director is in active mode, the other one is in hot standby mode.

(a) The CIDS directors have a data bus interface to the:

DEU type A,
DEU type B,
Flight Attendant Panel (FAP),
System Data Acquisition Concentrator 1+2 (SDAC),
Flight Warning Computer 1+2 (FWC),
Centralized Fault Display System (CFDS),
Air Conditioning Zone Controller (ZC).

(b) The CIDS directors have a discrete interface to the:

Slat Flap Control Computer 1+2 (SFCC),
Landing Gear Control and Interface Unit 1+2 (LGCIU),
Cabin Pressure Controller 1+2 (CPC),
Cabin pressure relay,
Indicator Light Control Box (ILCB),
Cockpit call panel,
Service interphone override switch,
Exit signs relay,
Cockpit door switch,
System Data Acquisition Concentrator 1+2 (SDAC),
Flight Warning Computer 1+2 (FWC),
Top lines cut off relay,
Engine Interface Unit (EIU),
Motor start relay vacuum generator,
EVAC panel,
EVAC horn,
NS/FSB panel.

Audio Management Unit (AMU),
Cockpit handset,
Service interphone boomsets.

(3) CIDS directors

CIDS Director Interfaces - Block Diagram (Sheet 1) ** ON A/C NOT FOR ALL

CIDS Director Interfaces - Block Diagram (Sheet 2) ** ON A/C NOT FOR ALL

The two directors are the central control components of the CIDS. One director is in active mode, the other one is in hot standby mode.

(a) The CIDS directors have a data bus interface to the:

DEU type A,
DEU type B,
Flight Attendant Panel (FAP),
System Data Acquisition Concentrator 1+2 (SDAC),
Flight Warning Computer 1+2 (FWC),
Centralized Fault Display System (CFDS),
Air Conditioning System Controller (ACSC).

(b) The CIDS directors have a discrete interface to the:

Slat Flap Control Computer 1+2 (SFCC),
Landing Gear Control and Interface Unit 1+2 (LGCIU),
Cabin Pressure Controller 1+2 (CPC),
Cabin pressure relay,
Indicator Light Control Box (ILCB),
Cockpit call panel,
Service interphone override switch,
Exit signs relay,
Cockpit door switch,
System Data Acquisition Concentrator 1+2 (SDAC),
Flight Warning Computer 1+2 (FWC),
Top lines cut off relay,
Engine Interface Unit (EIU),
Motor start relay vacuum generator,
EVAC panel,
EVAC horn,
PED/FSB panel.

Audio Management Unit (AMU),
Cockpit handset,
Service interphone boomsets.

(4) CIDS directors

CIDS Director Interfaces - Block Diagram (Sheet 1) ** ON A/C NOT FOR ALL

CIDS Director Interfaces - Block Diagram (Sheet 2) ** ON A/C NOT FOR ALL

The two directors are the central control components of the CIDS. One director is in active mode, the other one is in hot standby mode.

(a) The CIDS directors have a data bus interface to the:

DEU type A,
DEU type B,
Flight Attendant Panel (FAP),
System Data Acquisition Concentrator 1+2 (SDAC),
Flight Warning Computer 1+2 (FWC),
Centralized Fault Display System (CFDS),
Air Conditioning System Controller (ACSC),
In-Flight Entertainment System (IFE).

(b) The CIDS directors have a discrete interface to the:

Slat Flap Control Computer 1+2 (SFCC),
Landing Gear Control and Interface Unit 1+2 (LGCIU),
Cabin Pressure Controller 1+2 (CPC),
Cabin pressure relay,
Indicator Light Control Box (ILCB),
Cockpit call panel,
Service interphone override switch,
Exit signs relay,
Cockpit door switch,
System Data Acquisition Concentrator 1+2 (SDAC),
Flight Warning Computer 1+2 (FWC),
Top lines cut off relay,
Engine Interface Unit (EIU),
Motor start relay vacuum generator,
In-Flight Entertainment System (IFE),
EVAC panel,
EVAC horn,
PED/FSB panel.

Audio Management Unit (AMU),
Cockpit handset,
Service interphone boomsets,
In-Flight Entertainment System (IFE).

(5) CIDS directors

CIDS Director Interfaces - Block Diagram (Sheet 1) ** ON A/C NOT FOR ALL

CIDS Director Interfaces - Block Diagram (Sheet 2) ** ON A/C NOT FOR ALL

The two directors are the central control components of the CIDS. One director is in active mode, the other one is in hot standby mode.

(a) The CIDS directors have a data bus interface to the:

DEU type A
DEU type B
Flight Attendant Panel (FAP)
System Data Acquisition Concentrator 1+2 (SDAC)
Flight Warning Computer 1+2 (FWC)
Centralized Fault Display System (CFDS)
Air Conditioning System Controller (ACSC)
In-Flight Entertainment System (IFE).

(b) The CIDS directors have a discrete interface to the:

Slat Flap Control Computer 1+2 (SFCC)
Landing Gear Control and Interface Unit 1+2 (LGCIU)
Cabin Pressure Controller 1+2 (CPC)
Cabin pressure relay
Indicator Light Control Box (ILCB)
Cockpit call panel
Service interphone override switch
Exit signs relay
Cockpit door switch
System Data Acquisition Concentrator 1+2 (SDAC)
Flight Warning Computer 1+2 (FWC)
Top lines cut off relay
Engine Interface Unit (EIU)
Motor start relay vacuum generator
In-Flight Entertainment System (IFE)
EVAC panel
EVAC horn
EXIT/FSB panel.

Audio Management Unit (AMU)
Cockpit handset
Service interphone boomsets
In-Flight Entertainment System (IFE).

(6) CIDS directors

CIDS Director Interfaces - Block Diagram (Sheet 1) ** ON A/C NOT FOR ALL

CIDS Director Interfaces - Block Diagram (Sheet 2) ** ON A/C NOT FOR ALL

The two directors are the central control components of the CIDS. One director is in active mode, the other one is in hot standby mode.

(a) The CIDS directors have a data bus interface to the:

DEU type A,
DEU type B,
Flight Attendant Panel (FAP),
System Data Acquisition Concentrator 1+2 (SDAC),
Flight Warning Computer 1+2 (FWC),
Centralized Fault Display System (CFDS),
Air Conditioning System Controller (ACSC),
In-Flight Entertainment System (IFE),

(b) The CIDS directors have a discrete interface to the:

Slat Flap Control Computer 1+2 (SFCC),
Landing Gear Control and Interface Unit 1+2 (LGCIU),
Cabin Pressure Controller 1+2 (CPC),
Cabin pressure relay,
Indicator Light Control Box (ILCB),
Cockpit call panel,
Service interphone override switch,
Exit signs relay,
Cockpit door switch,
System Data Acquisition Concentrator 1+2 (SDAC),
Flight Warning Computer 1+2 (FWC),
Top lines cut off relay,
Engine Interface Unit (EIU),
Motor start relay vacuum generator,
In-Flight Entertainment System (IFE),
EVAC horn,
EXIT/FSB panel or NS / FSB panel or PED /FSB panel.

Audio Management Unit (AMU),
Cockpit handset,
Service interphone boomsets,
Prerecorded Announcement & Boarding Music (PRAM),
In-Flight Entertainment System (IFE).

(7) Decoder/Encoder Unit (DEU) Type A

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

DEU type A Interfaces - Block Diagram ** ON A/C NOT FOR ALL

The active director controls all the DEUs type A. Two data-bus top lines connect the DEUs type A to each other and to the directors. One top line is installed along each aircraft side. All DEUs type A on one aircraft side are connected to one top line.
Each DEU type A is installed on a connection box which is the interface to the related top line. Each connection box has coding switches which give a specified address to the related DEU type A. The last connection box on each top line also has a termination resistor for impedance matching. This connection box is thus called a termination box.

(a) The DEU type A has direct interfaces to the:

Directors
Passenger Interface and Supply Adapters (PISA)
Stand-Alone Passenger Interface and Supply Adapters (StA PISA)
Ballast units
Loudspeakers
NS, FSB and RTS signs.

(b) The DEU type A has interfaces via PISA or StA PISA to the:

Loudspeakers
Reading lights
Attendant work lights
Seat row identifiers
Passenger call/reset pushbuttons
Passenger call lights
NS, FSB and RTS signs.

(8) Decoder/Encoder Unit (DEU) Type A

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

DEU type A Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The DEU type A has direct interfaces to the:

Directors
Passenger Interface and Supply Adapters (PISA)
Stand-Alone Passenger Interface and Supply Adapters (StA PISA)
Ballast units
Loudspeakers
PED, FSB and RTS signs.

(b) The DEU type A has interfaces via PISA or StA PISA to the:

Loudspeakers
Reading lights
Attendant work lights
Seat row identifiers
Passenger call/reset pushbuttons
Passenger call lights
PED, FSB and RTS signs.

(9) Decoder/Encoder Unit (DEU) Type A

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

DEU type A Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The DEU type A has direct interfaces to the:

Directors
Passenger Interface and Supply Adapters (PISA)
Stand-Alone Passenger Interface and Supply Adapters (StA PISA)
Ballast units
Loudspeakers
NS, PED, FSB and RTS signs.

(b) The DEU type A has interfaces via PISA or StA PISA to the:

Loudspeakers
Reading lights
Attendant work lights
Seat row identifiers
Passenger call/reset pushbuttons
Passenger call lights
NS, PED, FSB and RTS signs.

(10) Decoder/Encoder Unit (DEU) Type B

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

DEU type B Interfaces - Block Diagram ** ON A/C NOT FOR ALL

The active director controls all the DEUs type B. Two data-bus middle lines connect the DEUs type B to each other and to the directors. One middle line is installed along each aircraft side. All DEUs type B on one aircraft side are connected to one middle line.
Each DEU type B is installed on a connection box which is the interface to the related middle line. Each connection box has coding switches which give a specified address to the related DEU type B. The last connection box on each middle line also has a termination resistor for impedance matching. This connection box is thus called a termination box.

(a) The DEU type B has data bus interfaces to the:

Directors
Additional Attendant Panel (AAP)
Attendant Indication Panel (AIP)
Emergency Power Supply Unit (EPSU)
Lavatory smoke detector.

(b) The DEU type B has discrete interfaces to the:

Area Call Panel (ACP)
Slide pressure sensor
Switch panel (2065VU)
Switch panel (2064VU)
Drain Mast Control Unit (DMCU)
Waste service panel
Vacuum generator
Fan phase off relay
Water service panel
Vacuum power control relay
Liquid Level Transmitter (LLT)
Liquid Level Sensor (LLS)
Flush Control Unit (FCU).

Handsets.

(11) Decoder/Encoder Unit (DEU) Type B

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

DEU type B Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The DEU type B has data bus interfaces to the:

Directors
Additional Attendant Panel (AAP)
Attendant Indication Panel (AIP)
Emergency Power Supply Unit (EPSU)
Lavatory smoke detector.

(b) The DEU type B has discrete interfaces to the:

Area Call Panel (ACP)
Door pressure sensor
Slide pressure sensor
Switch panel (2065VU)
Drain Mast Control Unit (DMCU)
Waste service panel
Vacuum generator
Fan phase off relay
Water service panel
Vacuum power control relay
Liquid Level Transmitter (LLT)
Liquid Level Sensor (LLS)
Flush Control Unit (FCU)
Switch panel (2080VU).

Handsets.

(12) Decoder/Encoder Unit (DEU) Type B

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

DEU type B Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The DEU type B has data bus interfaces to the:

Directors
Additional Attendant Panel (AAP)
Attendant Indication Panel (AIP)
Emergency Power Supply Unit (EPSU)
Lavatory smoke detector.

(b) The DEU type B has discrete interfaces to the:

Area Call Panel (ACP)
Door pressure sensor
Slide pressure sensor
Drain Mast Control Unit (DMCU)
Waste service panel
Vacuum generator
Fan phase off relay
Water service panel
Prime level indicator (Precharge)
Vacuum power control relay
Liquid Level Transmitter (LLT)
Liquid Level Sensor (LLS)
Flush Control Unit (FCU)
Water depressurisation valve.

Handsets.

(13) Decoder/Encoder Unit (DEU) Type B

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

DEU type B Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The DEU type B has data bus interfaces to the:

Directors
Additional Attendant Panel (AAP)
Attendant Indication Panel (AIP)
Emergency Power Supply Unit (EPSU)
Lavatory smoke detector.

(b) The DEU type B has discrete interfaces to the:

Area Call Panel (ACP)
Door pressure sensor
Slide pressure sensor
Switch panel (2064VU)
Drain Mast Control Unit (DMCU)
Waste service panel
Vacuum generator
Fan phase off relay
Water service panel
Vacuum power control relay
Liquid Level Transmitter (LLT)
Liquid Level Sensor (LLS)
Flush Control Unit (FCU)
Water depressurisation valve.

Handsets.

(14) Decoder/Encoder Unit (DEU) Type B

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

DEU type B Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The DEU type B has data bus interfaces to the:

Directors
Additional Attendant Panel (AAP)
Attendant Indication Panel (AIP)
Emergency Power Supply Unit (EPSU)
Lavatory smoke detector.

(b) The DEU type B has discrete interfaces to the:

Area Call Panel (ACP)
Slide pressure sensor
Drain Mast Control Unit (DMCU)
Waste service panel
Vacuum generator
Fan phase off relay
Water service panel
Vacuum power control relay
Liquid Level Transmitter (LLT)
Liquid Level Sensor (LLS)
Flush Control Unit (FCU)
Water depressurisation valve.

Handsets.

(15) Decoder/Encoder Unit (DEU) Type B

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

DEU type B Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The DEU type B has data bus interfaces to the:

Directors
Additional Attendant Panel (AAP)
Attendant Indication Panel (AIP)
Emergency Power Supply Unit (EPSU)
Lavatory smoke detector.

(b) The DEU type B has discrete interfaces to the:

Area Call Panel (ACP)
Door pressure sensor
Slide pressure sensor
Drain Mast Control Unit (DMCU)
Waste service panel
Vacuum generator
Fan phase off relay
Water service panel
Vacuum power control relay
Liquid Level Transmitter (LLT)
Liquid Level Sensor (LLS)
Flush Control Unit (FCU)
Water depressurisation valve.

Handsets.

(16) Decoder/Encoder Unit (DEU) Type B

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

DEU type B Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The DEU type B has data bus interfaces to the:

Directors
Additional Attendant Panel (AAP)
Attendant Indication Panel (AIP)
Emergency Power Supply Unit (EPSU)
Lavatory smoke detector.

(b) The DEU type B has discrete interfaces to the:

Area Call Panel (ACP)
Slide pressure sensor
Switch panel (2064VU)
Drain Mast Control Unit (DMCU)
Waste service panel
Vacuum generator
Fan phase off relay
Water service panel
Prime level indicator (Precharge)
Vacuum power control relay
Liquid Level Transmitter (LLT)
Liquid Level Sensor (LLS)
Flush Control Unit (FCU)
Water depressurisation valve.

Handsets.

(17) Decoder/Encoder Unit (DEU) Type B

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

DEU type B Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The DEU type B has data bus interfaces to the:

Directors
Additional Attendant Panel (AAP)
Attendant Indication Panel (AIP)
Emergency Power Supply Unit (EPSU)
Lavatory smoke detector.

(b) The DEU type B has discrete interfaces to the:

Area Call Panel (ACP)
Slide pressure sensor
Switch panel (2064VU)
Drain Mast Control Unit (DMCU)
Waste service panel
Vacuum generator
Fan phase off relay
Water service panel
Vacuum power control relay
Liquid Level Transmitter (LLT)
Liquid Level Sensor (LLS)
Flush Control Unit (FCU)
Water preselection unit.

Handsets.

(18) Flight Attendant Panel (FAP)

FAP Interfaces - Block Diagram ** ON A/C NOT FOR ALL

The FAP is used to control different cabin systems and the CIDS. The FAP shows the status of different systems and is used to change the CAM data (e.g. cabin layout and no smoking zones). The FAP is also used for the emulation of CFDS reports when the aircraft is in the ground status.

(a) The FAP has data bus interfaces to the:

Director 1
Director 2

(b) The FAP has discrete interfaces to the:

Director 1
Director 2
Emergency lighting system.

1 On-Board Replaceable Module (OBRM)
The OBRM contains the system software. For major changes of the CIDS software, the OBRM must be replaced.

2 Cabin Assignment Module (CAM)
The CAM gives many of the system properties and all cabin layout and zoning information (e.g. if a passenger announcement starts with chimes and if a loudspeaker is related to an attendant or a passenger seat). Minor CAM data changes are possible with on-board programming. For major CAM data changes, the CAM must be replaced.

3 Integrated Prerecorded Announcement & Boarding Music (PRAM)
The integrated PRAM stores pre-recorded announcement and boarding music audio data.

(19) Flight Attendant Panel (FAP)

FAP Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The FAP has data bus interfaces to the:

Director 1
Director 2

(b) The FAP has discrete interfaces to the:

Director 1
Director 2
Emergency lighting system
In-Flight Entertainment System (IFE).

1 On-Board Replaceable Module (OBRM)
The OBRM contains the system software. For major changes of the CIDS software, the OBRM must be replaced.

(20) Flight Attendant Panel (FAP)

FAP Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The FAP has data bus interfaces to the:

Director 1
Director 2

(b) The FAP has discrete interfaces to the:

Director 1
Director 2
Emergency lighting system
In-Flight Entertainment System (IFE).

1 On-Board Replaceable Module (OBRM)
The OBRM contains the system software. For major changes of the CIDS software, the OBRM must be replaced.

3 Integrated Prerecorded Announcement & Boarding Music (PRAM)
The integrated PRAM stores pre-recorded announcement and boarding music audio data.

(21) Flight Attendant Panel (FAP)

FAP Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The FAP has data bus interfaces to the:

Director 1,
Director 2,
Cabin Information Network System (CINS).

(b) The FAP has discrete interfaces to the:

Director 1,
Director 2,
Emergency lighting system,
In-Seat Power Supply System (ISPSS).

1 On-Board Replaceable Module (OBRM)
The OBRM contains the system software. For major changes of the CIDS software, the OBRM must be replaced.

3 Integrated Prerecorded Announcement & Boarding Music (PRAM)
The integrated PRAM stores pre-recorded announcement and boarding music audio data.

(22) Built-In Test Equipment (BITE)
The CIDS is designed to continuously monitor its own performance and that of the connected equipment.
The CIDS Directors (DIR), Decoder/Encoder Units (DEU), Passenger Interface and Supply Adapters (PISA), Flight Attendant Panel (FAP), Additional Attendant Panels (AAP) and Attendant Indication Panels (AIP) contain comprehensive BITE circuitry. This allows the CIDS to detect faults in the connected systems and in the CIDS units.
The DIRs store the detected faults and send them to the Warning and Maintenance System (WMS) and/or FAP. In the event of a major fault, related information is additionally sent to the

ECAM status page or
ECAM warning page.

(23) Interfaces
The CIDS components are connected to each other and to the other systems by these types of interfaces:

(a) Discrete
The discrete interface is an unidirectional interface which transmits a 28VDC or ground signal.

(b) Audio
The audio interface is an unidirectional interface. It transmits signals between 50Hz - 11kHz if connected to a DEU type A and 200Hz - 5.5kHz if connected to a DEU type B.

1 Unidirectional interfaces
CIDS uses three different unidirectional interfaces for data-transmission:

a ARINC 429
This data bus transmits 32-bit data words. The bus operates as a lowspeed (12KB/sec) or highspeed interface (100KB/sec).

b RS 232
This data bus transmits 8-bit data words with 9600B/sec.

c CAN
This data bus operates as a highspeed interface with a speed of 83.33KB/sec. It has a CAN bus terminator installed.

2 Bidirectional interfaces
CIDS uses the CIDS buses (Top Line and Middle Line) and the Ethernet for bidirectional transmissions.

a Top Line and Middle Line
These buses transmit data between director and all Decoder/Encoder Units (DEUs). The buses transmit 14 bit data words with 4MB/sec.

b Ethernet
This bus transmits data words with 10MB/sec.

C. System Functions

The CIDS provides these system functions:

(1) Passenger Address System (PA)
The passenger address system does the distribution of announcements from the cockpit and each attendant station through all assigned PAX loudspeakers.

(2) Cabin and Flight Crew Interphone System
The cabin interphone system permits the telephone communication between all attendant stations and between the attendant stations and the cockpit.

(3) Service Interphone System
The service interphone system permits the telephone communication between groundcrew, cockpit crew and cabin crew when the A/C is on the ground.

(4) Prerecorded Announcement and Boarding Music (PRAM) System
The CIDS transmits the prerecorded announcements and the boarding music to all passenger related loudspeakers.

(5) Prerecorded Announcement (PRAM) System
The CIDS transmits the prerecorded announcements to all passenger related loudspeakers.

(6) In-Flight Entertainment System (IFE)
The IFE transmits audio programs and video sound to the passengers and shows video programs through video display units in the passenger compartment. The passengers can hear the audio programs and the video sound through the headsets and the loudspeakers. In addition, PA announcement can be heard in the passenger cabin from the overhead loudspeakers or through the headsets. During a PA announcement IFE mutes any other audio signal.

(7) Passenger Lighted Signs
The system for the passenger lighted signs controls the No Smoking (NS), Fasten Seat Belt (FSB), Return To Seat (RTS) and Exit signs.

(8) Passenger Lighted Signs
The system for the passenger lighted signs controls the Please Turn Off Electronic Devices (PED), Fasten Seat Belt (FSB), Return To Seat (RTS) and Exit signs.

(9) Passenger Call
The passenger call system controls the illumination of the passenger call light and the activation of the call chime.

(10) Cabin Illumination
The cabin illumination system controls the illumination in the different cabin areas independently.

(11) Reading Lights
The reading light system controls the passenger reading lights and attendant work lights in the cabin.

(12) Passenger Service System (PSS)
The PSS is used for remote controlled operation of the passenger reading lights and the passenger call activation/deactivation.

(13) Lavatory Smoke Detection
The smoke detection system controls the visual and acoustic indications in the cabin, if smoke is sensed by the Lavatory Smoke Detectors.

(14) Cargo Smoke Detection
As part of the CIDS Smoke Detection Function (CIDS-SDF), the cargo smoke detectors sense smoke in the cargo compartment.

(15) Cargo Fire Extinguisher Monitoring
As part of the CIDS Smoke Detection Function (CIDS-SDF), the Cargo Fire Extinguisher Monitoring function controls and monitors these fire-extinguisher parts:

Bottle-reservoir pressure
Squib condition.

(16) Cabin Ready Signalling
The cabin ready signalling is used to inform the cockpit crew about the cabin status.

(17) Air Conditioning
The CIDS can select different temperatures for all defined zones. It is possible to do a fine adjustment of the preselected temperature for different cabin zones at the FAP. The temperatures which are in the different cabin zones are shown on the FAP.

(18) Emergency Evacuation Signaling (EVAC)
The EVAC system controls the evacuation signaling in all cabin areas and the cockpit. It can be operated from the cockpit, FAP or AAP during an emergency.

(19) Potable Water Indication
The potable water indication system shows the quantity of water, which is in the tank, on the FAP.

(20) Potable Water Indication & Preselection
The potable water indication and preselection system shows the quantity of water, which is in the tank, on the FAP and gives the commands for the preselection of the water quantity.

(21) Waste Indication
The waste indication system shows the quantity of waste water, which is in the tank, on the FAP. Also, unserviceable lavatories that do not operate are shown on the FAP and related messages come on.

(22) Vacuum System Control Function (VSCF)
The VSCF controls and monitors the Vacuum Toilet System. The system identifies each toilet assembly and starts the necessary actions of the related system components.

(23) Doors and Escape Slides Pressure Monitoring
The doors and escape slide control system monitors the pressure of the escape slide reservoir at the passenger doors and emergency exits. It also monitors the status of the doors (open/closed) and escape slides (armed/disarmed). The status shows on the FAP.

(24) Escape Slides Pressure Monitoring
The escape slides control system monitors the pressure of the escape slide reservoir at the emergency exits. It also monitors the status of all doors (open/closed) and escape slides (armed/disarmed). The status shows on the FAP.

(25) Doors and Escape Slides Monitoring
The doors and escape slide control system monitors the status of the doors (open/closed) and escape slides (armed/disarmed). The status shows on the FAP.

(26) Emergency Power Supply Unit (EPSU)
The CIDS director initiates the BITE test of the EPSU, if a related command is given by the Centralized Fault Display System (CFDS). The director also transmits the results to the CFDS.

(27) Drain Mast Control Unit (DMCU)
The CIDS directors monitor a test of the DMCU, if a related command is given by the CFDS. A detected fault causes a related message and the caution light on the FAP to come on. Also, the results are transmitted to the CFDS.

(28) Cabin/cockpit incident alert system
The Cabin/cockpit incident alert system is used to indicate a possible violent incident to cabin and/or cockpit crew members. It activates visual and acoustic indications in the cockpit, if the respective pushbutton in the cabin is pushed (cabin alert). It also activates visual and acoustic indications in the cabin, if the respective pushbutton in the cockpit is pushed (cockpit alert).

(29) CFDS Emulation on FAP
This function provides the possibility to emulate reports from the Centralized Fault Display System (CFDS) on the FAP, like it is possible on the Multi Purpose Control Display Unit (MCDU) in the cockpit.

** ON A/C NOT FOR ALL

4. Power Supply
The service bus and the essential bus supply electrical power to the CIDS (inclusive the SDF board of the CIDS director).
Depending on the available bus the CIDS operates in the:

Normal mode or
Emergency mode.

A. Normal Mode

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

Power Supply SERVICE + ESS BUS - Middle Line ** ON A/C NOT FOR ALL

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

In the normal mode the service bus supplies 28VDC to the CIDS. All functions of the system operate fully.
The BITE test function is only active if the essential busbar is also available.

B. Emergency Mode

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

Power Supply SERVICE + ESS BUS - Middle Line ** ON A/C NOT FOR ALL

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

In the emergency mode, only the essential bus supplies 28VDC to the CIDS.

(1) The essential bus supplies power to the CIDS, if the service bus is not available.

(2) The system operates with minimum functions. The ACPs and the AIPs do not operate. The remaining functions are:

Passenger address
Cabin interphone
EVAC
Smoke detection.

(3) The essential bus supplies power to the CIDS, if the service bus is not available.

(4) The system operates with minimum functions. The ACPs and the AIPs do not operate. The remaining functions are:

Passenger address,
Cabin interphone,
Smoke detection.

(5) The DEUs type A, which are connected to the top lines, are only supplied with power when there is an audio signal. If there is no audio signal, the director operates the Top Line cut-off relay to stop the power supply to the DEUs.

(6) It is possible to supply 28VDC from the hot battery bus to the CIDS, if the service bus and the essential bus are not available. For this purpose, the emergency lighting switch 4WL must be in the ARM or ON position.

C. Power Consumption
The power consumption of the CIDS components and the supplied cabin systems depends on the installed equipment. During normal operation all installed components are supplied with electrical power.
If the service bus is not available and the CIDS is in emergency mode, the power consumption is reduced to a minimum. Only the components which are needed for the minimum functions are supplied with electrical power.

D. Power Interruption
If a power interruption is longer than 5 sec., the CIDS software is reset and all components of the system are set to the predefined status.

** ON A/C NOT FOR ALL

5. Interface

A. CIDS system interfaces (external)

(1) Director

CIDS Director Interfaces - Block Diagram (Sheet 1) ** ON A/C NOT FOR ALL

CIDS Director Interfaces - Block Diagram (Sheet 2) ** ON A/C NOT FOR ALL

(a) The director has a data bus interface to the:

Flight Warning Computer 1+2 (FWC)
Air Conditioning System Controller (ACSC)
System Data Acquisition Concentrator 1+2 (SDAC)
Centralized Fault Display System 1+2 (CFDS)
In-Flight Entertainment System (IFE).

(b) The director has a discrete interface to the:

Slat Flap Control Computer 1+2 (SFCC)
Landing Gear Control and Interface Unit 1+2 (LGCIU)
Cabin Pressure Controller 1+2 (CPC)
Cabin pressure relay
Indicator Light Control Box (ILCB)
Service interphone override switch
Exit signs relay
Cockpit door switch
System Data Acquisition Concentrator 1+2 (SDAC)
Flight Warning Computer 1+2 (FWC)
Engine Interface Unit (EIU)
Motor start relay vacuum generator.

Audio Management Unit (AMU)
Service interphone boomsets
In-Flight Entertainment System (IFE).

(2) Director

CIDS Director Interfaces - Block Diagram (Sheet 1) ** ON A/C NOT FOR ALL

CIDS Director Interfaces - Block Diagram (Sheet 2) ** ON A/C NOT FOR ALL

(a) The director has a data bus interface to the:

Flight Warning Computer 1+2 (FWC)
Air Conditioning System Controller (ACSC)
System Data Acquisition Concentrator 1+2 (SDAC)
Centralized Fault Display System 1+2 (CFDS).

(b) The director has a discrete interface to the:

Slat Flap Control Computer 1+2 (SFCC)
Landing Gear Control and Interface Unit 1+2 (LGCIU)
Cabin Pressure Controller 1+2 (CPC)
Cabin pressure relay
Indicator Light Control Box (ILCB)
Service interphone override switch
Exit signs relay
Cockpit door switch
System Data Acquisition Concentrator 1+2 (SDAC)
Flight Warning Computer 1+2 (FWC)
Engine Interface Unit (EIU)
Motor start relay vacuum generator.

Audio Management Unit (AMU)
Service interphone boomsets.

(3) Director

CIDS Director Interfaces - Block Diagram (Sheet 1) ** ON A/C NOT FOR ALL

CIDS Director Interfaces - Block Diagram (Sheet 2) ** ON A/C NOT FOR ALL

(a) The director has a data bus interface to the:

Flight Warning Computer 1+2 (FWC)
Air Conditioning System Controller (ACSC)
System Data Acquisition Concentrator 1+2 (SDAC)
Centralized Fault Display System 1+2 (CFDS)
In-Flight Entertainment System (IFE).

(b) The director has a discrete interface to the:

Slat Flap Control Computer 1+2 (SFCC)
Landing Gear Control and Interface Unit 1+2 (LGCIU)
Cabin Pressure Controller 1+2 (CPC)
Cabin pressure relay
Indicator Light Control Box (ILCB)
Service interphone override switch
Exit signs relay
Cockpit door switch
System Data Acquisition Concentrator 1+2 (SDAC)
Flight Warning Computer 1+2 (FWC)
Engine Interface Unit (EIU)
Motor start relay vacuum generator
Cockpit alerting horn
Cockpit alert pushbutton - Captain
Cockpit alert pushbutton - F/O
Cockpit CAB ALERT pushbutton/indicator light.

Audio Management Unit (AMU)
Service interphone boomsets
In-Flight Entertainment System (IFE).

(4) Director

CIDS Director Interfaces - Block Diagram (Sheet 1) ** ON A/C NOT FOR ALL

CIDS Director Interfaces - Block Diagram (Sheet 2) ** ON A/C NOT FOR ALL

(a) The director has a data bus interface to the:

Flight Warning Computer 1+2 (FWC)
Air Conditioning Zone Controller (ZC)
System Data Acquisition Concentrator 1+2 (SDAC)
Centralized Fault Display System 1+2 (CFDS)

(b) The director has a discrete interface to the:

Slat Flap Control Computer 1+2 (SFCC)
Landing Gear Control and Interface Unit 1+2 (LGCIU)
Cabin Pressure Controller 1+2 (CPC)
Cabin pressure relay
Indicator Light Control Box (ILCB)
Service interphone override switch
Exit signs relay
Cockpit door switch
System Data Acquisition Concentrator 1+2 (SDAC)
Flight Warning Computer 1+2 (FWC)
Engine Interface Unit (EIU)
Motor start relay vacuum generator.

Audio Management Unit (AMU)
Service interphone boomsets

(5) DEU type A

DEU type A Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The DEU type A has direct interfaces to the:

Ballast units,
Loudspeakers,
NS, FSB and RTS signs.

(b) The DEU type A has interfaces via PISA or StA PISA to the:

Reading lights,
Seat row identifier,
Passenger call lights,
Loudspeakers,
NS, FSB and RTS signs,
Attendant work lights.

(6) DEU type A

DEU type A Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The DEU type A has direct interfaces to the:

Ballast units
Loudspeakers
PED, FSB and RTS signs.

(b) The DEU type A has interfaces via PISA or StA PISA to the:

Reading lights
Seat row identifier
Passenger call lights
Loudspeakers
PED, FSB and RTS signs
Attendant work lights.

(7) DEU type A

DEU type A Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The DEU type A has direct interfaces to the:

Director 1 and 2
Passenger Interface and Supply Adapter (PISA)
Ballast units
Loudspeakers
NS, PED, FSB and RTS signs.

(b) The DEU type A has interfaces via PISA or StA PISA to the:

Reading lights
Seat row identifier
Passenger call lights
Passenger call / reset pushbuttons
Loudspeakers
NS, PED, FSB and RTS signs
Attendant work lights

(8) DEU type B

DEU type B Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The DEU type B has data bus interfaces to the:

Emergency Power Supply Unit (EPSU)
Lavatory smoke detector.

(9) DEU type B

DEU type B Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The DEU type B has data bus interfaces to the:

Emergency Power Supply Unit (EPSU)
Lavatory smoke detector.

(b) The DEU type B has discrete interfaces to the:

Drain Mast Control Unit (DMCU)
Slide pressure sensor
Flush Control Unit (FCU)
Liquid Level Transmitter (LLT)
Liquid Level Sensor (LLS)
Water and waste service panel
Vacuum Generator
Fan phase off relay
Vacuum power control relay.

(10) DEU type B

DEU type B Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The DEU type B has data bus interfaces to the:

Emergency Power Supply Unit (EPSU),
Lavatory smoke detector.

(b) The DEU type B has discrete interfaces to the:

Drain Mast Control Unit (DMCU),
Slide and door pressure sensor,
Flush Control Unit (FCU),
Liquid Level Transmitter (LLT),
Liquid Level Sensor (LLS),
Water and waste service panel,
Vacuum generator,
Fan phase off relay,
Vacuum power control relay,
Water depressurisation valve.

(11) DEU type B

DEU type B Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The DEU type B has data bus interfaces to the:

Emergency Power Supply Unit (EPSU),
Lavatory smoke detector.

(b) The DEU type B has discrete interfaces to the:

Drain Mast Control Unit (DMCU),
Slide pressure sensor,
Flush Control Unit (FCU),
Liquid Level Transmitter (LLT),
Liquid Level Sensor (LLS),
Water and waste service panel,
Vacuum Generator,
Fan phase off relay,
Vacuum power control relay,
Water preselection unit.

(12) DEU type B

DEU type B Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The DEU type B has data bus interfaces to the:

Emergency Power Supply Unit (EPSU),
Lavatory smoke detector.

(b) The DEU type B has discrete interfaces to the:

Drain Mast Control Unit (DMCU),
Slide pressure sensor,
Flush Control Unit (FCU),
Liquid Level Transmitter (LLT),
Liquid Level Sensor (LLS),
Water and waste service panel,
Vacuum Generator,
Fan phase off relay,
Vacuum power control relay,
Water depressurisation valve.

(13) DEU type B

DEU type B Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The DEU type B has data bus interfaces to the:

Emergency Power Supply Unit (EPSU),
Lavatory smoke detector.

(b) The DEU type B has discrete interfaces to the:

Drain Mast Control Unit (DMCU),
Slide and door pressure sensor,
Flush Control Unit (FCU),
Liquid Level Transmitter (LLT),
Liquid Level Sensor (LLS),
Water and waste service panel,
Vacuum generator,
Fan phase off relay,
Vacuum power control relay,
Switch panel (2080VU).

(14) Flight Attendant Panel (FAP)

FAP Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The FAP has discrete interfaces to the:

Emergency lighting system.

(15) Flight Attendant Panel (FAP)

FAP Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The FAP has data bus interfaces to the:

In-Flight Entertainment System (IFE).

(b) The FAP has discrete interfaces to the:

Emergency lighting system,
In-Flight Entertainment System (IFE).

(16) Flight Attendant Panel (FAP)

FAP Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The FAP has data bus interfaces to the:

In-Flight Entertainment System (IFE).

(b) The FAP has discrete interfaces to the:

Emergency lighting system
In-Flight Entertainment System (IFE)
In-Seat Power Supply System (ISPSS).

(17) Flight Attendant Panel (FAP)

FAP Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The FAP has discrete interfaces to the:

In-Seat Power Supply System (ISPSS).

(18) Flight Attendant Panel (FAP)

FAP Interfaces - Block Diagram ** ON A/C NOT FOR ALL

(a) The FAP has data bus interfaces to the:

Director 1,
Director 2,
Cabin Information Network System (CINS).

(b) The FAP has discrete interfaces to the:

Director 1,
Director 2,
Emergency lighting system,
In-Seat Power Supply System (ISPSS).

** ON A/C NOT FOR ALL

6. Component Description

A. General
The CIDS has these main components:

Director
Decoder/Encoder Unit (DEU) type A
Decoder/Encoder Unit (DEU) type B
Passenger Interface and Supply Adapter (PISA)
Stand-Alone Passenger Interface and Supply Adapter (StA PISA)
Flight Attendant Panel (FAP)
Cabin Assignment Module (CAM)
On-Board Replaceable Module (OBRM)
Additional Attendant Panel (AAP)
Attendant Indication Panel (AIP)
Area Call Panel (ACP)
Handset
Loudspeaker
Passenger call/reset pushbutton
Passenger call light.

NS, FSB and RTS signs.

PED, FSB and RTS signs.

NS, PED, FSB and RTS signs.

B. Director

(1) General
For redundancy, the system has two identical directors. One director is in hot-standby mode and has the same inputs and outputs as the active director. Both directors are connected in parallel except for:

The power supply connection,
Certain outputs to other equipment and systems.

The CIDS directors are installed in the pressurized area of the electronic compartment.
The CIDS directors give an interface to:

Components in the cockpit
Components in the electronic compartment
The Decoder/Encoder Units via the CIDS data buses
The Flight Attendant Panel (FAP).

The connections to the equipment and other systems are realized with discrete, audio and data bus interfaces.

(2) Architecture
The director has the following modules and circuits:

Processing module
Bus interface circuits
Digital/analogue (audio) circuits
Discrete input/output circuits
Serial input/output (ARINC/Ethernet) circuits
Mandatory layout memory (non-volatile)
Cabin assignment data memory (non-volatile) and working memory (volatile)
Data transfer interface to second director
Smoke detection function module
BITE/WATCHDOG circuits
Power supply circuits.

(3) Functions

(a) Processing module
This module has supervisory functions, controls the CIDS data bus interface and all other interfaces. It can download software from the FAP. The director's BITE function is partly incorporated in the module.

(b) Bus interface circuits
The bus interface circuits do the synchronization of the CIDS data bus, transmit data packets from the director and buffer all incoming data from the DEUs.

(c) Digital/analogue (audio) circuits
These circuits convert incoming audio signals to a digital format and convert these digital signals back to analogue audio signals for output.

(d) Discrete input/output circuits
These circuits convert discrete input levels to digital levels and these digital levels back to discrete output levels.

(e) Serial input/output (ARINC/Ethernet) circuits
Serial interfaces support connection of conventionally connected terminals (e.g. FAP, SDAC, CFDS).

(f) Mandatory layout memory (non-volatile)
This memory stores mandatory cabin layout information. The On-Board Replaceable Module (OBRM), which is located in the FAP, can modify this memory.

(g) Cabin assignment data memory (non-volatile)
This memory stores cabin assignment data and system properties information. This memory is modified through the Cabin Assignment Module (CAM), which is located in the FAP, or through programming on the FAP.

(h) Data transfer interface to second director
This interface provides facilities to transfer data and failure information between the two CIDS directors.

(i) Smoke detection function module
This module processes the control and indication functions of the smoke detectors in the cargo compartment.

(j) BITE/WATCHDOG circuits
The BITE circuits enable tests of the internal modules and inputs/outputs. The WATCHDOG circuits control the uninterrupted function of the processing module.

(k) Power supply circuits
These circuits provide the necessary electrical power.

C. Decoder/Encoder Unit (DEU) type A

(1) General
The DEU type A provides an interface between the CIDS DATA BUS (top line) and different cabin systems. The information from the bus is transformed by the DEU type A into control signals which are sent to the respective cabin systems. The information from the cabin systems is transformed into data bus information and transmitted to the director.
The DEUs type A are installed in the cabin.
An interface is provided to this equipment:

Ballast units
PISAs
StA PISAs
Reading lights
Seat row identifier
Loudspeakers
NS, FSB and RTS signs.

(2) General
The DEU type A provides an interface between the CIDS DATA BUS (top line) and different cabin systems. The information from the bus is transformed by the DEU type A into control signals which are sent to the respective cabin systems. The information from the cabin systems is transformed into data bus information and transmitted to the director.
The DEUs type A are installed in the cabin.
An interface is provided to this equipment:

Ballast units,
PISAs,
StA PISAs,
Reading lights,
Seat row identifier,
Loudspeakers,
PED, FSB and RTS signs.

(3) General
The DEU type A provides an interface between the CIDS DATA BUS (top line) and different cabin systems. The information from the bus is transformed by the DEU type A into control signals which are sent to the respective cabin systems. The information from the cabin systems is transformed into data bus information and transmitted to the director.
The DEUs type A are installed in the cabin.
An interface is provided to this equipment:

Ballast units
PISAs
StA PISAs
Reading lights
Seat row identifier
Loudspeakers
NS, PED, FSB and RTS signs.

(4) Architecture
The DEU type A has the following modules and circuits:

Bus interface circuits
Processing module
System interface circuits
Power supply circuits.

(5) Functions

(a) Bus interface circuits
The bus interface buffers all incoming data bus information and sends selected data to the processing module. Data packets from the processing module and system interface are transmitted to the data bus.

(b) Processing module
This module decodes the data packets and activates the related outputs of the system interface. Inputs from the system interface are coded into data packets. Control commands and audio signals from the director are decoded and transmitted to the related connected equipment.
The DEU BITE function is incorporated in the processing module.

(d) Power supply circuits
This unit provides all necessary power to the DEU circuits and to the outputs.

D. Passenger Interface and Supply Adapter (PISA)

(1) General
The PISA is the interface between the DEU type A and components of the Passenger Service Unit (PSU).
The PISAs are installed in each PSU in the pressurized area of the cabin.
The PISA has interfaces to the following equipment:

Reading-light switches and reading lights
Passenger-call button and passenger-call lights
Seat row identifier
Loudspeakers
NS, FSB and RTS signs.

(2) General
The PISA is the interface between the DEU type A and components of the Passenger Service Unit (PSU).
The PISAs are installed in each PSU in the pressurized area of the cabin.
The PISA has interfaces to the following equipment:

Reading-light switches and reading lights
Passenger-call button and passenger-call lights
Seat row identifier
Loudspeakers
PED, FSB and RTS signs.

(3) General
The PISA is the interface between the DEU type A and components of the Passenger Service Unit (PSU).
The PISAs are installed in each PSU in the pressurized area of the cabin.
The PISA has interfaces to the following equipment:

Reading-light switches and reading lights
Passenger-call button and passenger-call lights
Seat row identifier
Loudspeakers
NS, PED, FSB and RTS signs.

(4) Architecture
The PISA has two boards:

Main board
Audio board.

(5) Functions

(a) Main board
The main board can operate independently. It contains the functions for:

Reading light control
Reading light switch monitoring
Passenger call button monitoring and seat row indication.
The main board also receives the necessary power for both boards and all outputs.

(b) Audio board
The audio board can only operate with the main board. It contains the functions for audio output and control of the NS, FSB and RTS signs.

E. Stand-Alone Passenger Interface and Supply Adapter (StA PISA)

(1) General
The StA PISA is the interface between the DEU type A and the equipment/ indications installed near the forward and aft cabin attendant stations.

The StA PISA has interfaces to the:

Attendant work light switches
Attendant work lights
NS, FSB and RTS signs.

For further information refer to 33-27-00.

(2) General
The StA PISA is the interface between the DEU type A and the equipment/ indications installed near the forward and aft cabin attendant stations.

The StA PISA has interfaces to the:

Attendant work light switches
Attendant work lights
PED, FSB and RTS signs.

For further information refer to 33-27-00.

(3) General
The StA PISA is the interface between the DEU type A and the equipment/ indications installed near the cabin attendant stations and in the door-, entrance- and bar-areas. The StA PISAs are installed in the pressurized area of the cabin.

The StA PISA has interfaces to the:

Attendant work lights switches
Attendant work lights
Reading lights switches
Reading lights
Loudspeakers
NS, PED, FSB and RTS signs.

For further information refer to 33-27-00.

F. Decoder/Encoder Unit (DEU) type B

(1) General
The DEU type B provides an interface between the CIDS DATA BUS (middle line) and certain attendant related systems. The information from the bus is transformed by the DEU type B into control signals which are sent to the respective attendant systems. The information from the attendant systems is transformed into data bus information and transmitted to the director.
The DEUs type B are installed in the pressurized area of the cabin.
An interface is provided to the following equipment:

Additional Attendant Panel (AAP),
Attendant Indication Panel (AIP),
Area Call Panels (ACP),
Handsets,
Slide pressure sensors,
Emergency Power Supply Unit (EPSU),
Drain Mast Control Unit (DMCU),
Smoke sensors,
Switch panel (2065VU),
Switch panel (2064VU),
Waste and water service panel,
Fan phase off relay,
Liquid Level Sensor (LLS),
Liquid Level Transmitter (LLT),
Vacuum generator,
Flush Control Unit (FCU),
Vacuum power control relay.

(2) General
The DEU type B provides an interface between the CIDS DATA BUS (middle line) and certain attendant related systems. The information from the bus is transformed by the DEU type B into control signals which are sent to the respective attendant systems. The information from the attendant systems is transformed into data bus information and transmitted to the director.
The DEUs type B are installed in the pressurized area of the cabin.
An interface is provided to the following equipment:

Additional Attendant Panel (AAP),
Attendant Indication Panel (AIP),
Area Call Panels (ACP),
Handsets,
Slide and door pressure sensors,
Emergency Power Supply Unit (EPSU),
Drain Mast Control Unit (DMCU),
Smoke sensors,
Waste and water service panel,
Fan phase off relay,
Liquid Level Sensor (LLS),
Liquid Level Transmitter (LLT),
Vacuum generator,
Flush Control Unit (FCU),
Vacuum power control relay,
Water depressurisation valve.

(3) General
The DEU type B provides an interface between the CIDS DATA BUS (middle line) and certain attendant related systems. The information from the bus is transformed by the DEU type B into control signals which are sent to the respective attendant systems. The information from the attendant systems is transformed into data bus information and transmitted to the director.
The DEUs type B are installed in the pressurized area of the cabin.
An interface is provided to the following equipment:

Additional Attendant Panel (AAP),
Attendant Indication Panel (AIP),
Area Call Panels (ACP),
Handsets,
Slide and door pressure sensors,
Emergency Power Supply Unit (EPSU),
Drain Mast Control Unit (DMCU),
Smoke sensors,
Switch panel (2064VU),
Waste and water service panel,
Fan phase off relay,
Liquid Level Sensor (LLS),
Liquid Level Transmitter (LLT),
Vacuum generator,
Flush Control Unit (FCU),
Vacuum power control relay,
Water depressurisation valve.

(4) General
The DEU type B provides an interface between the CIDS DATA BUS (middle line) and certain attendant related systems. The information from the bus is transformed by the DEU type B into control signals which are sent to the respective attendant systems. The information from the attendant systems is transformed into data bus information and transmitted to the director.
The DEUs type B are installed in the pressurized area of the cabin.
An interface is provided to the following equipment:

Additional Attendant Panel (AAP),
Attendant Indication Panel (AIP),
Area Call Panels (ACP),
Handsets,
Slide pressure sensors,
Emergency Power Supply Unit (EPSU),
Drain Mast Control Unit (DMCU),
Smoke sensors,
Switch panel (2064VU),
Waste and water service panel,
Fan phase off relay,
Liquid Level Sensor (LLS),
Liquid Level Transmitter (LLT),
Vacuum generator,
Flush Control Unit (FCU),
Vacuum power control relay,
Water depressurisation valve.

(5) General
The DEU type B provides an interface between the CIDS DATA BUS (middle line) and certain attendant related systems. The information from the bus is transformed by the DEU type B into control signals which are sent to the respective attendant systems. The information from the attendant systems is transformed into data bus information and transmitted to the director.
The DEUs type B are installed in the pressurized area of the cabin.
An interface is provided to the following equipment:

Additional Attendant Panel (AAP),
Attendant Indication Panel (AIP),
Area Call Panels (ACP),
Handsets,
Slide and door pressure sensors,
Emergency Power Supply Unit (EPSU),
Drain Mast Control Unit (DMCU),
Smoke sensors,
Switch panel (2065VU),
Waste and water service panel,
Fan phase off relay,
Liquid Level Sensor (LLS),
Liquid Level Transmitter (LLT),
Vacuum generator,
Flush Control Unit (FCU),
Vacuum power control relay,
Switch panel (2080VU).

(6) General
The DEU type B provides an interface between the CIDS DATA BUS (middle line) and certain attendant related systems. The information from the bus is transformed by the DEU type B into control signals which are sent to the respective attendant systems. The information from the attendant systems is transformed into data bus information and transmitted to the director.
The DEUs type B are installed in the pressurized area of the cabin.
An interface is provided to the following equipment:

Additional Attendant Panel (AAP),
Attendant Indication Panel (AIP),
Area Call Panels (ACP),
Handsets,
Slide pressure sensors,
Emergency Power Supply Unit (EPSU),
Drain Mast Control Unit (DMCU),
Smoke sensors,
Waste and water service panel,
Fan phase off relay,
Liquid Level Sensor (LLS),
Liquid Level Transmitter (LLT),
Vacuum generator,
Flush Control Unit (FCU),
Vacuum power control relay,
Water depressurisation valve.

(7) General
The DEU type B has an interface between the CIDS DATA BUS (middle line) and a number of attendant related systems. The information from the bus changes by the DEU type B into control signals. These signals are sent to the related attendant systems. The information from the attendant systems changes into data bus information and transmits to the director.
The DEUs type B are installed in the pressurized area of the cabin.
There is an interface to the following equipment:

Additional Attendant Panel (AAP)
Attendant Indication Panel (AIP)
Area Call Panels (ACP)
Handsets
Slide pressure sensors
Emergency Power Supply Unit (EPSU)
Drain Mast Control Unit (DMCU)
Smoke sensors
Switch panel (2064VU)
Waste and water service panel
Fan phase off relay
Liquid Level Sensor (LLS)
Liquid Level Transmitter (LLT)
Vacuum generator
Flush Control Unit (FCU)
Vacuum power control relay
Water preselection unit.

(8) Architecture
The DEU type B consists of the following modules and circuits:

Bus interface circuits
Processing module
System interface circuits
Power supply circuits.

(9) Functions
The functions of the different components are the same as described for the DEU type A.

G. Flight Attendant Panel (FAP)

(1) General
The FAP enables the cabin crew to control certain cabin systems and CIDS, to indicate the status of several cabin systems and to provide cabin programming. It can also be used to emulate CFDS reports when the aircraft is in the ground status.
The FAP is installed in the pressurized area of the cabin.

(2) Architecture
The FAP has the following modules:

Display unit
Sub-panel.

(3) Functions

(a) Display unit
The display unit has these parts:

Ethernet bus interface
This interface buffers all incoming information and transfers selected data to the processing module. It also receives data from the processing module and transmits this information on the ethernet bus.
Processing module
This module decodes the incoming data packets and activates the graphic module, which is part of the processing module. It also activates the respective hardkeys of the sub-panel. Inputs from the touch screen or the sub-panel are coded into data packets and sent to the ethernet bus interface.
In case of emergency mode the processing module switches the FAP to minimum power consumption.
The FAP BITE function is incorporated into the processing module.
Touch screen panel
This panel indicates all information. It is used to select functions (e.g. cabin illumination) and for the cabin programming.
System interface
This unit gives an interface to certain connected cabin systems.
Power supply circuits
These supply all necessary power to the FAP circuits.

(b) Sub panel
The sub-panel contains hardkeys and some interfaces (e.g. USB).

H. On-Board Replaceable Module (OBRM)
This module is the storage device for system software (e.g. director, forward attendant panel). It is installed in the sub-panel of the FAP.

I. Cabin Assignment Module (CAM)
In this module the CIDS configuration data base is stored. It is installed in the sub-panel of the FAP and includes the cabin definition, e.g. for:

Cabin zoning
Seat relation to loudspeakers and passenger lighted signs,
Chime sequences
Audio levels.

J. Integrated Prerecorded Announcement & Boarding Music (PRAM)
This module stores the prerecorded announcement and boarding music audio data. It is installed in the sub-panel of the FAP.

K. Additional Attendant Panel (AAP)

Additional Attendant Panel - 126RH ** ON A/C NOT FOR ALL

(1) General
The AAP enables the attendants to control certain cabin systems.

(2) Architecture
The AAP has these modules and circuits:

RS232 data bus receiver and transmitter
Processing module
Power supply circuits
Output circuitry.

(3) Functions

(a) RS232 data bus receiver and transmitter
The RS232 data bus receiver and transmitter receives data from the DEU type B and sends it to the processing module. It also receives data from the processing module and transmits this information to the DEU type B.

(b) Processing module
This module carries out all internal operations of the AAP. It connects the membrane switches and indicators to the RS232 data bus receiver and transmitter. The AAP BITE function is incorporated into the processing module.

(d) Output circuitry
All outputs of the AAP are short-circuit protected.

L. 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 RH and exit RH attendant station.

(b) Function
The switch panel performs these functions:

Indication of the EVAC alert,
Reset of the acoustic and visual EVAC alert indications, related to the respective attendant station,
Reset of all acoustic and visual lavatory smoke warnings.

The EVAC alert indication light,
The RESET membrane switch.

(2) 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 acoustic and visual EVAC alert indications, related to the respective attendant station.

The EVAC alert indication light,
The RESET membrane switch.

(3) Description

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

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

(b) Function
The switch panel performs these functions:

Indication of the EVAC alert
Reset of the acoustic and visual EVAC alert indications, related to the respective attendant station
Reset of all acoustic and visual lavatory smoke warnings.

The EVAC alert indication light
The RESET membrane switch.

(4) 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 acoustic and visual EVAC alert indications, related to the respective attendant station,
Reset of all acoustic and visual lavatory smoke warnings.

The EVAC alert indication light,
The RESET membrane switch.

M. Switch panel (2065VU)

(1) Description

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

(a) General
If applicable, the switch panel 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 SMOKE RESET membrane switch.

(2) Description

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

(a) General
If applicable, the switch panel is installed adjacent to the mid and exit attendant station.

(b) Function
The switch panel performs this function:

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

The SMOKE RESET membrane switch.

N. Attendant Indication Panel (AIP)

(1) General
The AIP (320RH) provides an attendant far call function. Its display shows dial and call information from the PA/Interphone system and other system-related information (e.g. Lavatory Smoke Location/PAX Calls).
The AIPs are installed adjacent to the cabin attendant stations.

(2) Architecture
The AIP has these modules and circuits:

Display
Display controller
Display driver
Single chip microcomputer
RAM and Read Only Memory (ROM)
Erasable Programmable Read Only Memory (EPROM)
Line receiver/transmitter
Power supply circuits
Two indicator lights.

(3) Functions

(a) Display
The display has two rows where all messages are displayed.

(b) Display controller
This unit generates all characters which are shown on the display.

(d) Single chip microcomputer
This unit coordinates the operation of the different modules and the operation of the software.

(e) RAM and Read Only Memory (ROM)
This unit contains the AIP software program.

(f) Erasable Programmable Read Only Memory (EPROM)
All messages for the display are stored in the EPROM as alphanumeric text data.

(g) Line receiver/transmitter
This unit receives and sends information from and to the DEU type B via a RS-232 data bus.

(h) Power supply circuits
This unit supplies all necessary power to the AIP circuits and to the outputs. The unit switches the AIP into a standby mode with lowest power consumption while indications are displayed.

(i) Two indicator lights
One red and one green indicator light are installed. They are used to show the attendant the importance of the related message over a distance.

O. Area Call Panel (ACP)

(1) General
The ACP (340RH) gives a long-range visual indication related to system information (e.g. Lavatory Smoke Location/PAX Calls).

(2) Architecture
The ACP has four separately controlled fields. Each field contains colored LEDs. They are visible from the front and the rear of the ACP.

(3) Functions
The four fields are separately activated to show the different system information. The LEDs flash or come on steady. They are used as a far-call facility to inform cabin attendants of passenger call, interphone call, lavatory smoke and EVAC signals.

P. Cabin handsets

Cabin handset ** ON A/C NOT FOR ALL

(1) General
The attendants use the cabin handsets for the Cabin and Flight Crew Interphone functions and for PA announcements. An integrated keyboard is used to make different types of calls/announcements.

(2) Architecture
The handset has these components:

Integrated keyboard,
'Push To Talk' button,
Microphone,
Earphone,
Tone dialling interface circuit,
Reed contact,

(3) Functions

(a) Integrated keyboard
With the integrated keyboard the related functions are selected and establish a communication link.

(b) 'Push To Talk' button
This button activates the microphone in the handset. In special cases this button establishes also a communication link.

(d) Earphone
The earphone changes the related signals into the voice.

(e) Tone dialling interface circuit
The interface decodes the keyboard signals and generates Dual Tone Multiple Frequency (DTMF) coded dial signals. Voice signals are routed through to the outputs of the interface.

(f) Reed contact
When the handset is not in its cradle, the reed contact connects electrical power to the handset.

(4) General
The attendants use the cabin handsets for the Cabin and Flight Crew Interphone functions and for PA announcements. An integrated keyboard is used to make different types of calls/announcements.
The cabin handsets are installed in a vertical position near the attendant stations in the pressurized area of the cabin.

(5) Architecture
The handset has these components:

Integrated keyboard
'Push To Talk' pushbutton
Microphone unit with a pre-amplifier
Earphone
Tone dialling interface circuit
Hall-effect switch.

(6) Functions

(a) Integrated keyboard
With the integrated keyboard the related functions are selected and establish a communication link. The keys give a tactile feedback when you push them.

(b) 'Push To Talk' (PTT) pushbutton
This pushbutton activates the microphone in the handset. In special cases this button establishes also a communication link.

(c) Microphone unit with a pre-amplifier
The microphone changes the voice into the related signals. The pre-amplifier provides a stable output power in all environmental conditions.

(d) Earphone
The earphone changes the related signals into the voice.

(f) Hall-effect switch
When the handset is in its cradle, the hall-effect switch senses the field of a permanent magnet in the handset cradle. The hall-effect switch then transmits an internal command to set the handset into a standby mode with minimized power consumption. When the handset is not in its cradle, the hall-effect switch connects electrical power to the handset.

Q. Cockpit handset

Cockpit handset ** ON A/C NOT FOR ALL

(1) General
The cockpit crew uses the handset for PA announcements and interphone communication.

(2) Architecture
The handset has these components:

'Push To Talk' button,
Microphone,
Earphone,
Reed contact.

(3) General
The cockpit crew uses the handset for PA announcements and interphone communication.

(4) Architecture
The handset has these components:

'Push To Talk' pushbutton
Microphone unit with a pre-amplifier
Earphone
Hall-effect switch.

(5) Functions
The functions of the different components are the same as those of the components of the cabin handsets.

** ON A/C NOT FOR ALL

7. Operation/Control and Indicating

A. CIDS energization
The CIDS is energized when the essential busbars or the service busbars are energized and the CIDS-related circuit breakers are closed.

(1) Service busbars
When the service busbars supply 28VDC to the CIDS, the system operates with full capability.
The BITE test function is only active if the essential busbar is also available.
To energize all CIDS components, the 601PP service busbar has to be energized.
For the CIDS-SDF, the 204PP (Ref. AMM D/O 26-16-00-00) service busbar has to be energized.

(2) Essential busbars
The essential busbars supply power to the CIDS if the service busbars are not available.
When only essential power is available, the system is in emergency mode and operates with the minimum functions. These functions are:

Passenger Address
Cabin Interphone
Smoke detection and indication (except cabin indications)
EVAC.

To supply all CIDS components with essential electrical power the 401PP essential busbar has to be energized.
For the CIDS-SDF, the 801PP (Ref. AMM D/O 26-16-00-00) busbar has to be energized.

(3) Hot battery busbars
It is possible to supply 28VDC from the hot battery-bus to the CIDS, if the essential power is not available, and the EMER EXIT light switch is in the AUTO or ON position.
The CIDS has the same restrictions as with only essential power.

(4) Power Supply
To supply power to the CIDS components these circuit breakers have to be closed:

(a) Director power

150RH DIR 1 ESS
157RH DIR 2 ESS
151RH DIR 1 NORM
156RH DIR 2 NORM.

(b) FAP power

171RH FAP 1 ESS
170RH FAP 1 NORM.

158RH DEU A ESS FWD R
159RH DEU A ESS FWD L
172RH DEU A ESS AFT R
179RH DEU A ESS AFT L
163RH DEU A NORM FWD L
164RH DEU A NORM FWD R
167RH DEU A NORM AFT L
168RH DEU A NORM AFT R

(d) DEUs type B power

153RH DEU B ESS
162RH DEU B NORM.

(5) Power Supply
To supply power to the CIDS components these circuit breakers have to be closed:

(a) Director power

150RH DIR 1 ESS
157RH DIR 2 ESS
151RH DIR 1 NORM
156RH DIR 2 NORM
147RH DIR 1 BAT
146RH DIR 2 BAT.

(b) FAP power

171RH FAP 1 ESS
170RH FAP 1 NORM
149RH FAP 1 BAT.

158RH DEU A ESS FWD R
159RH DEU A ESS FWD L
172RH DEU A ESS AFT R
179RH DEU A ESS AFT L
163RH DEU A NORM FWD L
164RH DEU A NORM FWD R
167RH DEU A NORM AFT L
168RH DEU A NORM AFT R
258RH DEU A BAT FWD R
259RH DEU A BAT FWD L
272RH DEU A BAT AFT R
279RH DEU A BAT AFT L.

(d) DEUs type B power

153RH DEU B ESS
162RH DEU B NORM
143RH DEU B BAT.

(6) Power Supply
To supply power to the CIDS components these circuit breakers have to be closed:

(a) Director power

150RH DIR 1 ESS
157RH DIR 2 ESS
151RH DIR 1 NORM
156RH DIR 2 NORM.

(b) FAP power

171RH FAP 1 ESS
170RH FAP 1 NORM.

158RH DEU A ESS FWD R
159RH DEU A ESS FWD L
196RH DEU A ESS MID R
195RH DEU A ESS MID L
172RH DEU A ESS AFT R
179RH DEU A ESS AFT L
164RH DEU A NORM FWD R
163RH DEU A NORM FWD L
198RH DEU A NORM MID R
197RH DEU A NORM MID L
174RH DEU A NORM AFT R
173RH DEU A NORM AFT L.

(d) DEUs type B power

153RH DEU B ESS
193RH DEU B NORM FWD
194RH DEU B NORM AFT.

(7) Power Supply
To supply power to the CIDS components these circuit breakers have to be closed:

(a) Director power

150RH DIR 1 ESS
157RH DIR 2 ESS
151RH DIR 1 NORM
156RH DIR 2 NORM
147RH DIR 1 BAT
146RH DIR 2 BAT.

(b) FAP power

171RH FAP 1 ESS
170RH FAP 1 NORM
149RH FAP 1 BAT.

158RH DEU A ESS FWD R
159RH DEU A ESS FWD L
196RH DEU A ESS MID R
195RH DEU A ESS MID L
172RH DEU A ESS AFT R
179RH DEU A ESS AFT L
164RH DEU A NORM FWD R
163RH DEU A NORM FWD L
198RH DEU A NORM MID R
197RH DEU A NORM MID L
174RH DEU A NORM AFT R
173RH DEU A NORM AFT L
258RH DEU A BAT FWD R
259RH DEU A BAT FWD L
296RH DEU A BAT MID R
295RH DEU A BAT MID L
272RH DEU A BAT AFT R
279RH DEU A BAT AFT L.

(d) DEUs type B power

153RH DEU B ESS
193RH DEU B NORM FWD
194RH DEU B NORM AFT
143RH DEU B BAT.

(8) Power Supply
To supply power to the CIDS components these circuit breakers have to be closed:

(a) Director power

150RH DIR 1 ESS
157RH DIR 2 ESS
151RH DIR 1 NORM
156RH DIR 2 NORM
147RH DIR 1 BAT
146RH DIR 2 BAT.

(b) FAP power

171RH FAP 1 ESS
170RH FAP 1 NORM
149RH FAP 1 BAT.

464RH DEU A ESS 1 R
463RH DEU A ESS 1 L
466RH DEU A ESS 2 R
465RH DEU A ESS 2 L
663RH DEU A NORM FWD L
664RH DEU A NORM FWD R
665RH DEU A NORM MID L
666RH DEU A NORM MID R
667RH DEU A NORM AFT L
668RH DEU A NORM AFT R
764RH DEU A BAT 1 R
763RH DEU A BAT 1 L
766RH DEU A BAT 2 R
765RH DEU A BAT 2 L.

(d) DEUs type B power

420RH DEU B ESS R
419RH DEU B ESS L
620RH DEU B NORM R
619RH DEU B NORM L
720RH DEU B BAT R
719RH DEU B BAT L.

B. Handling of Flight Attendant Panel (FAP)

(1) General

FAP - Overview ** ON A/C NOT FOR ALL

The FAP has two main areas, the touch screen and the sub panel.

(a) Touch screen
The touch screen has these components:

A heading row
A display area
System and function keys.

1 Heading row
The heading row shows the title of every selected page.

2 Display area
The display area shows every selected page.

3 System and function keys
The system and function keys are used to select system pages.

(b) Sub panel
The sub-panel controls major functions that operate independently from the FAP touch screen.
These hard keys are installed on the sub panel:

LIGHTS MAIN ON/OFF
LAV MAINT
SCREEN 30 sec LOCK
EVAC CMD
EVAC RESET
SMOKE RESET.

These switches are installed on the sub panel:

EMER (light).

These interfaces are installed on the sub panel:

USB plug
Headphone plug.

(2) General

FAP - Overview ** ON A/C NOT FOR ALL

The FAP has two main areas, the touch screen and the sub panel.

(a) Touch screen
The touch screen has these components:

A heading row
A display area
System and function keys.

1 Heading row
The heading row shows the title of every selected page.

2 Display area
The display area shows every selected page.

3 System and function keys
The system and function keys are used to select system pages.

(b) Sub panel
The sub-panel controls major functions that operate independently from the FAP touchscreen.
These hard keys are installed on the sub panel:

PED POWER
LIGHTS MAIN ON/OFF
LAV MAINT
SCREEN 30 sec LOCK
EVAC CMD
EVAC RESET
SMOKE RESET.

These switches are installed on the sub panel:

EMER (light).

These interfaces are installed on the sub panel:

USB plug
Headphone plug.

(3) General

FAP - Overview ** ON A/C NOT FOR ALL

The FAP is divided into two main areas, the touch screen and the sub panel.

(a) Touchscreen
The touch screen has these components:

a Heading row,
a Display area,
System and function keys.

1 Heading row
The heading row shows the title of every selected page.

2 Display area
The display area shows every selected page.

3 System and function keys
The system and function keys are used to select system pages.

(b) Sub panel
The sub-panel is used for major functions that operate independently from the FAP touchscreen.
These hardkeys are installed on the sub panel:

LIGHTS MAIN ON/OFF,
LAV MAINT,
SCREEN 30 sec LOCK,
SMOKE RESET.

These switches are installed on the sub panel:

EMER (light).

These interfaces are installed on the sub panel:

USB plug,
Headphone plug.

(4) General

FAP - Overview ** ON A/C NOT FOR ALL

The FAP is divided into two main areas, the touch screen and the sub panel.

(a) Touchscreen
The touch screen has these components:

a Heading row,
a Display area,
System and function keys.

1 Heading row
The heading row shows the title of every selected page.

2 Display area
The display area shows every selected page.

3 System and function keys
The system and function keys are used to select system pages.

(b) Sub panel
The sub-panel is used for major functions that operate independently from the FAP touchscreen.
These hardkeys are installed on the sub panel:

PED POWER,
LIGHTS MAIN ON/OFF,
LAV MAINT,
SCREEN 30 sec LOCK,
EVAC CMD,
EVAC RESET,
SMOKE.

These switches are installed on the sub panel:

EMER (light).

These interfaces are installed on the sub panel:

USB plug,
Headphone plug.

(5) General

FAP - Overview ** ON A/C NOT FOR ALL

The FAP has two main areas, the touch screen and the sub panel.

(a) Touchscreen
The touchscreen has these components:

a Heading row
a Display area
System and function keys.

1 Heading row
The heading row shows the title of every selected page.

2 Display area
The display area shows every selected page.

3 System and function keys
The system and function keys are used to select system pages.

(b) Sub panel
The sub-panel controls major functions that operate independently from the FAP touch screen.
These hard keys are installed on the sub panel:

LIGHTS MAIN ON/OFF
LAV MAINT
SCREEN 30 sec LOCK
EVAC CMD
EVAC RESET
SMOKE.

These switches are installed on the sub panel:

EMER (light).

These interfaces are installed on the sub panel:

USB plug
Headphone plug.

(6) Operation

(a) Selection of system pages

FAP - Cabin Status Page - Example ** ON A/C NOT FOR ALL

You can use the function keys to select a system page (e.g. cabin illumination). There are different sets of system and function keys. A set has of a max. of nine keys. You can go to the next or the previous set with the forward or the backward button.
To select a system page push the related key. Then the selected page is shown in the display area.
To select the CABIN STATUS page push the button in the lower right corner of the touchscreen. The CABIN STATUS page gives an overview of these pages:

AUDIO
CABIN LIGHTING
DOORS/SLIDES
CABIN TEMPERATURE
WATER/WASTE
SEAT SETTINGS.

On the CABIN STATUS page you can select one of the shown system pages also by pushing on the related A/C symbol.

(b) Automatic activation of system pages
If CIDS receives an important message the related system page shows automatically. The automatically activated pages are shown until the page is closed manually or automatically.
A smoke alert automatically calls up the SMOKE DETECTION page and overrides any other page.

FAP - Cabin Status Page - Example ** ON A/C NOT FOR ALL

The CAUT button is always shown in the upper left corner of the touchscreen.
If CIDS receives a message which cannot be shown immediately, the CAUT button turns amber and flashes. After displaying the pages related to the messages or after pushing the CAUT button, the CAUT button comes on steady. The CAUT illumination goes off, if CIDS does not receive any further messages. A information text shows in the heading row of the touch screen as long as the respective page is not shown on the touchscreen.

(d) Status indication

FAP - System Info Page - Example ** ON A/C NOT FOR ALL

The SYSTEM INFO page on the FAP shows the status of several cabin systems.

1 Operation
After selection of the SYSTEM INFO page, an indicator light next to the respective system button comes up in amber, if there is a fault message on another page. To display the faults of the different systems, push the related button on the SYSTEM INFO page.

2 Indication
The faults of these systems are indicated on the SYSTEM INFO page:

CIDS INTERNALS
ICE PROTECTION.

(e) Screen off function

FAP - Cabin Status Page - Example ** ON A/C NOT FOR ALL

The SCREEN OFF button is in the lower left corner of the touchscreen. If you push this button, it switches off the screen. The screen is also switched off, if no input is made for more than 10 minutes. The screen is switched on again, if you touch the screen or if there is an auto event.
These system pages are protected by a password:

SOFTWARE LOADING
LAYOUT SELECTION
CABIN PROGRAMMING
LEVEL ADJUSTMENT
CIDS MCDU MENU.

(7) Operation

(a) Selection of system pages

FAP - Cabin Status Page - Example ** ON A/C NOT FOR ALL

You can use the function keys to select a system page (e.g. cabin illumination). There are different sets of system and function keys. A set has a max. of nine keys. You can go to the next or the previous set with the forward or the backward button.
To select a system page push the related key. Then the selected page is shown in the display area.
To select the CABIN STATUS page push the button in the lower right corner of the touchscreen. The CABIN STATUS page gives an overview of these pages:

AUDIO
CABIN LIGHTING
DOORS/SLIDES
CABIN TEMPERATURE
WATER/WASTE
SEAT SETTINGS.

On the CABIN STATUS page you can select one of the shown system pages also by pushing on the related A/C symbol.

FAP - Cabin Status Page - Example ** ON A/C NOT FOR ALL

(d) Status indication

FAP - System Info Page - Example ** ON A/C NOT FOR ALL

The SYSTEM INFO page on the FAP shows the status of several cabin systems.

2 Indication
The faults of these systems are indicated on the SYSTEM INFO page:

CIDS INTERNALS
ICE PROTECTION.

(e) Screen off function

FAP - Cabin Status Page - Example ** ON A/C NOT FOR ALL

The SCREEN OFF button is in the lower left corner of the touchscreen. If you push this button, it switches off the screen. If no input is made for more than 10 minutes, a customized screensaver shows. The screen is switched on again, if you touch the screen or if there is an auto event.

(f) Screensaver
A customized screensaver shows, if you switch off the screen with the SCREEN OFF button on the related FAP page. The screensaver also shows automatically, if no input is made for more than 10 minutes.
These system pages are protected by a password:

SOFTWARE LOADING
LAYOUT SELECTION
CABIN PROGRAMMING
LEVEL ADJUSTMENT
CIDS MCDU MENU.

(8) Operation

(a) Selection of system pages

FAP - Cabin Status Page - Example ** ON A/C NOT FOR ALL

You can use the function keys to select a system page (e.g. cabin illumination). There are different sets of system and function keys. A set has a maximum of nine keys. You can push the forward and backward buttons to go to the next set or to the previous set.
To select a system page, push the related key. The selected page then comes into view on the display area.
To select the CABIN STATUS page, push the button in the lower right corner of the touch screen. The CABIN STATUS page gives an overview of these pages:

CABIN LIGHTING
DOORS/SLIDES
CABIN TEMPERATURE
WATER/WASTE
SEAT SETTINGS.

On the CABIN STATUS page you can also touch the related A/C symbol to select one of these system pages.

(b) Automatic activation of system pages
If CIDS receives an important message, the related system page comes into view automatically. A page that shows automatically, will show until you close the page or until it closes automatically.
A smoke alert automatically brings the SMOKE DETECTION page into view. The SMOKE DETECTION page will then show before all other pages.

FAP - Cabin Status Page - Example ** ON A/C NOT FOR ALL

The CAUT button always shows in the upper left corner of the touch screen.
If CIDS receives a message which it cannot show immediately, the CAUT button turns amber and flashes. The CAUT button stops to flash and stays on, after the related pages showed or after you pushed the CAUT button. The CAUT illumination goes off, if CIDS receives no more related messages. An information text shows in the heading row of the touch screen until the related page shows on the touch screen.

(d) Status indication

FAP - System Info Page - Example ** ON A/C NOT FOR ALL

The SYSTEM INFO page on the FAP shows the status of a number of cabin systems.

2 Indication
The faults of these systems are indicated on the SYSTEM INFO page:

CIDS INTERNALS
ICE PROTECTION.

(e) Screen off function

FAP - Cabin Status Page - Example ** ON A/C NOT FOR ALL

The SCREEN OFF button is in the lower left corner of the touch screen. If you push this button, it switches off the screen. A customized screen saver shows if there is no operation of the FAP for more than 10 minutes. The screen comes on again after you touch it, or if it is started automatically.

(f) Screen saver
A customized screen saver shows when you touch the SCREEN OFF button on the related FAP page. The screen saver also shows automatically, if there is no operation of the FAP for more than 10 minutes.
These system pages have a password protection:

SOFTWARE LOADING
LAYOUT SELECTION
CABIN PROGRAMMING
LEVEL ADJUSTMENT
CIDS MCDU MENU.

(9) Operation

(a) Selection of system pages

FAP - Cabin Status Page - Example ** ON A/C NOT FOR ALL

AUDIO
CABIN LIGHTING
DOORS/SLIDES
CABIN TEMPERATURE
WATER/WASTE
SEAT SETTINGS.

On the CABIN STATUS page you can select one of the shown system pages also by pushing on the related A/C symbol.

FAP - Cabin Status Page - Example ** ON A/C NOT FOR ALL

The CAUT button is always shown in the upper left corner of the touchscreen.
If CIDS receives a message which cannot be shown immediately, the CAUT button turns amber and flashes. After displaying the pages related to the messages or after pushing the CAUT button, the CAUT button stays on. The CAUT illumination goes off, if CIDS does not receive any other messages. A information text shows in the heading row of the touchscreen as long as the respective page is not shown on the touchscreen.

(d) Status indication

FAP - System Info Page - Example ** ON A/C NOT FOR ALL

The SYSTEM INFO page on the FAP shows the status of a number of cabin systems.

1 Operation
After selection of the SYSTEM INFO page, an indicator light next to the related system button comes up in amber, if there is a fault message on another page. To display the faults of the different systems, push the related button on the SYSTEM INFO page.

2 Indication
The faults of these systems show on the SYSTEM INFO page:

CIDS INTERNALS
ICE PROTECTION.

(e) Screen off function

FAP - Cabin Status Page - Example ** ON A/C NOT FOR ALL

The SCREEN OFF button is in the lower left corner of the touchscreen. If you push this button, the screen goes off. If no input is made for more than 10 minutes, a customized screensaver shows. The screen is switched on again, if you touch the screen or if there is an auto event.

SOFTWARE LOADING
LAYOUT SELECTION
LEVEL ADJUSTMENT
CIDS MCDU MENU.

C. System Functions
The CIDS provides these system functions:

Passenger Address
Cabin and Flight Crew Interphone
Service Interphone
Passenger Lighted Signs
Passenger Call
Cabin Illumination (control)
Reading Lights (control/test)
Lavatory Smoke Detection (cabin signalling)
Vacuum System Control,

Prerecorded Announcement & Boarding Music (control),

Prerecorded Announcement & Boarding Music (control),
Cabin Ready Signalling,

Prerecorded Announcement & Boarding Music (control),
Cabin Ready Signalling,
In-Flight Entertainment System (interface),

In-Flight Entertainment System (interface),
Prerecorded Announcement & Boarding Music (control),
Passenger Service System,
Cabin Ready Signalling,

In-Flight Entertainment System (interface),
Cabin Ready Signalling,

Air Conditioning (temperature indication and control),

Emergency Evacuation Signaling (EVAC)

Potable Water Indication & Preselection.

Potable Water Indication
Waste Indication
Doors and Escape Slides Bottle Pressure Monitoring
Emergency Power Supply Unit (test).

Drain Mast Control Unit (test/signalling).

Cabin/cockpit incident alert system,

(1) Passenger Address system (PA)

Passenger Address - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The passenger address system distributes the PA related announcements from the cockpit, the attendant stations and the PRAM to all assigned passenger loudspeakers.

(b) PA announcement from the cockpit
From the cockpit a PA announcement is started with the handset or with the equipment connected to the Audio Management Unit (boomset, microphone and oxygen mask). The audio signal is transmitted from the handset directly or from the equipment connected to the AMU via AMU to the director.
From the director the signals are transmitted to the DEU type A, which sends the signals either directly or via PISA to the loudspeakers.
For a detailed description, how to use the AMU, see Audio Management (Ref. 23-51-00).
On the Audio Control Panel (ACP) in the cockpit these functions can be selected:

PA from AMU:
If you push the PA button, it starts a link between the equipment connected to the AMU and all loudspeakers.

(c) PA announcement from an attendant handset
During a PA announcement from an attendant handset, the audio signal is transmitted through the DEU type B to the director. From the director the signal is transmitted on the same way as described for the cockpit equipment.
These functions are available with each attendant handset:

DIRECT PA:
If you push the PTT button, it starts a link between the handset and all loudspeakers.
PA ALL:
If you push the PA button, it starts a link between the handset and all loudspeakers in the cabin area.

(d) Functional priorities
The PA functions have different priorities. The PA function with the higher priority overrides the function with lower priority. The function priority levels are given in this table:

1. DIRECT PA and PA from AMU
2. All remaining PA functions.

(e) Source priorities
The PA sources have different priorities. A source with a higher PA priority interrupts a PA announcement from a source with lower priority. Only the announcement from the source with the higher priority is heard. An announcement with higher functional priority also interrupts a source with higher PA priority, if its source has a lower priority.
The sources have the following priorities:

1. AMU
2. Cockpit handset
3. Forward attendant handset
4. Cabin attendant handsets
5. PRAM
6. EVAC
7. Video (if installed)
8. Boarding Music (if installed).

(f) PA monitoring
If the cockpit handset is removed from the cradle, the PA monitoring function starts. The PA announcement with the highest priority, which is done by another source, is heard in the handset.
The cockpit crew can monitor the PA announcements through the AMU as long as no other function is selected on the AMU and the PA rotary switch is pushed and turned clockwise on the ACP.

(g) Reset of selected PA functions
If the PA function is started by the handset functional keys, the function is cancelled after you put the handset back on the cradle or you pushed the reset button on the handset.
If the function is started with the PTT button, release of the PTT button cancels the function.

(h) Attention chimes
From the loudspeakers in the related cabin and attendant areas, you hear a PA attention chime (Lo-Hi-Lo) when a PA call is selected at one of these sources:

AMU (Audio Management Unit)
Cockpit Handset
Attendant Handset.

(i) PA indications
Dial and status information related to PA system functions is displayed on the related Attendant Indication Panel (AIP).

(j) Gain adjustment
If low cabin-pressure occurs or engine operate (high oil-pressure) the volume of a PA announcement is increased. The volume is also increased if a data bus failure (top line) occurs.
If during a PA the cockpit door is open, the volume of the PA in the cockpit door area decreases. This will prevent acoustic feedback.

(2) Passenger Address system (PA)

Passenger Address - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The passenger address system supplies the PA related announcements from the cockpit, the attendant stations and the PRAM to all assigned passenger loudspeakers.

(b) PA announcement from the cockpit
A PA announcement is started with the handset or with the equipment connected to the Audio Management Unit (boomset, microphone and oxygen mask). The handset transmits the audio signal directly or from the equipment connected to the AMU, via AMU to the director.
The director transmits the signals to the DEU type A, which sends the signals directly or via PISA to the loudspeakers.
For a detailed description, how to use the AMU, see Audio Management (Ref. 23-51-00).
On the Audio Control Panel (ACP) in the cockpit you can select the functions that follow:

PA from AMU:
If you push the PA button, it starts a link between the equipment connected to the AMU and all loudspeakers.

(c) PA announcement from an attendant handset
During a PA announcement from an attendant handset, the handset transmits the audio signal through the DEU type B to the director. The director transmits the signal on the same way as described for the cockpit equipment.
These functions are available with each attendant handset:

DIRECT PA:
If you push the PTT button, it starts a link between the handset and all loudspeakers.
PA ALL:
If you push the PA button, it starts a link between the handset and all loudspeakers in the cabin area.

1. DIRECT PA and PA from AMU
2. All remaining PA functions.

(e) Source priorities
The PA sources have different priorities. A source with a higher PA priority interrupts a PA announcement from a source with lower priority. You only hear the announcement from the source with the higher priority. An announcement with higher functional priority also interrupts a source with higher PA priority, if its source has a lower priority.
The sources have the following priorities:

1. AMU
2. Cockpit handset
3. Cabin attendant handsets
4. PRAM
5. EVAC
6. Video (if installed)
7. Boarding Music (if installed).

(f) PA monitoring
If you remove the cockpit handset from the cradle, the PA monitoring function starts. You hear the PA announcement with the highest priority in the handset. It comes from another source.
The cockpit crew can monitor the PA announcements through the AMU while no other function is selected on the AMU. You must push and turn the PA rotary switch clockwise on the ACP.

(g) Reset of selected PA functions
If you start the PA function with the handset functional keys, you cancel the function like this: You put the handset back on the cradle or you push the reset button on the handset.
If you start the function with the PTT button, you release the PTT button to cancel the function.

(h) PA indications
You see dial and status infromation related to PA system functions on the related Attendent Indication Panel (AIP).

(i) Gain adjustment
If low cabin-pressure occurs or if the engines are on (high oil-pressure), the volume of a PA announcement increases. The volume also increases if a data bus failure (top line) occurs.
If during a PA the cockpit door is open, the volume of the PA in the cockpit door area decreases. This will prevent acoustic feedback.

(3) Passenger Address system (PA)

Passenger Address - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The passenger address system distributes the PA related announcements from the cockpit, the attendant stations and the PRAM to all assigned passenger loudspeakers.

PA from AMU:
If you push the PA button, it starts a link between the equipment connected to the AMU and all loudspeakers.

DIRECT PA:
If you push the PTT button, it starts a link between the handset and all loudspeakers.
PA ALL:
If you push the PA ALL button, it starts a link between the handset and all loudspeakers in the cabin area.

1. DIRECT PA and PA from AMU
2. All remaining PA functions.

1. AMU
2. Cockpit handset
3. Forward attendant handset
4. Cabin attendant handsets
5. PRAM
6. EVAC
7. Video (if installed)
8. Boarding Music (if installed).

(h) PA indications
Dial and status information related to PA system functions is displayed on the related Attendant Indication Panel (AIP).
If you make a PA announcement, a discrete signal activates the PA IN USE indicator light in the cockpit.

(i) Gain adjustment
If low cabin-pressure occurs or engine operate (high oil-pressure) the volume of a PA announcement is increased. The volume is also increased if a data bus failure (top line) occurs.
If during a PA the cockpit door is open, the volume of the PA in the cockpit door area decreases. This will prevent acoustic feedback.

(4) Passenger Address system (PA)

Passenger Address - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The passenger address system supplies the PA related announcements from the cockpit, the attendant stations and the PRAM to all assigned passenger loudspeakers.

(b) PA announcement from the cockpit
From the cockpit you start a PA announcement with the handset or with the equipment connected to the Audio Management Unit (boomset, microphone and oxygen mask). The handset transmits the audio signal directly or from the equipment connected to the AMU via AMU to the director.
The director transmits the signals to the DEU type A, which sends the signals directly or via PISA to the loudspeakers.
For a detailed description, how to use the AMU, see Audio Management (Ref. 23-51-00).
On the Audio Control Panel (ACP) in the cockpit you can select the functions that follow:

PA from AMU:
If you push the PA button, it starts a link between the equipment connected to the AMU and all loudspeakers.

(c) PA announcement from an attendant handset
During a PA announcement from an attendant handset, the audio signal is transmitted through the DEU type B to the director. The director transmits the signal on the same way as described for the cockpit equipment.
These functions are available with each attendant handset:

DIRECT PA:
If you push the PTT button, it starts a link between the handset and all loudspeakers.
PA ALL:
If you push the PA ALL button, it starts a link between the handset and all loudspeakers in the cabin area.

(d) Functional priorities
The PA functions have different priorities. The PA function with the higher priority overrides the function with lower priority. These are the function priority levels:

1. DIRECT PA and PA from AMU
2. All remaining PA functions.

1. AMU
2. Cockpit handset
3. Cabin attendant handsets
4. PRAM
5. EVAC
6. Video (if installed)
7. Boarding Music (if installed).

(f) PA monitoring
If you remove the cockpit handset from the cradle, the PA monitoring function starts. In the handset you hear the PA announcement with the highest priority, which is done by another source.
The cockpit crew can monitor the PA announcements through the AMU while no other function is selected on the AMU. You must push and turn the PA rotary switch clockwise on the ACP.

(g) Reset of selected PA functions
If you start the PA function with the handset functional keys, you cancel the function like this: you put the handset back on the cradle or you push the reset button on the handset.
If you start the function with the PTT button, you release the PTT button to cancel the function.

(h) PA indications
The related Attendant Indication Panel (AIP) shows the dial and status information related to PA system functions.

(5) Passenger Address system (PA)

Passenger Address - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The passenger address system supplies the PA related announcements from the cockpit, the attendant stations, the PRAM and the In-Flight Entertainment system (IFE) to all assigned passenger loudspeakers.

(b) PA announcement from the cockpit
From the cockpit you start a PA announcement with the handset or with the equipment connected to the Audio Management Unit (boomset, microphone and oxygen mask). The handset transmits the audio signal directly or the equipment connected to the AMU transmits it through the AMU to the director.
The director transmits the signals to the DEU type A, which sends the signals either directly or through the PISA to the loudspeakers.
For a detailed description, how to use the AMU, see Audio Management (Ref. 23-51-00).
The director transmits the signal also to the In-Flight Entertainment system (IFE).
On the Audio Control Panel (ACP) in the cockpit you can select the functions that follow:

PA from AMU:
If you push the PA button, it starts a link between the equipment connected to the AMU and all loudspeakers.

DIRECT PA:
If you push the PTT button, it starts a link between the handset and all loudspeakers.
PA ALL:
If you push the PA button, it starts a link between the handset and all loudspeakers in the cabin area.

1. DIRECT PA and PA from AMU
2. All remaining PA functions.

(e) Source priorities
The PA sources have different priorities. A source with a higher PA priority interrupts a PA announcement from a source with lower priority. You hear only the announcement from the source with the higher priority. An announcement with higher functional priority also interrupts a source with higher PA priority, if its source has a lower priority.
The sources have the following priorities:

1. AMU
2. Cockpit handset
3. Cabin attendant handsets
4. PRAM
5. EVAC
6. Video (if installed)
7. Boarding Music (if installed).

(f) PA monitoring
If you remove the cockpit handset from the cradle, the PA monitoring function starts. In the handset you hear the PA announcement with the highest priority, which is done by another source.
The cockpit crew can monitor the PA announcements through the AMU as long as no other function is selected on the AMU. You must push and turn the PA rotary switch clockwise on the ACP.

(g) Reset of selected PA functions
If you start the PA function with the handset functional keys, you cancel the function like this: you put the handset back on the cradle or you push the reset button on the handset.
If you start the PA function with the PTT button, you release the PTT button to cancel the function.

(h) PA indications
The related Attendant Indication Panel (AIP) shows the dial and status information related to PA system functions.

(i) Gain adjustment
If low cabin-pressure occurs or engine operate (high oil-pressure), the volume of a PA announcement increases. The volume increases also if a data bus failure (top line) occurs.
If during a PA the cockpit door is open, the volume of the PA in the cockpit door area decreases. This will prevent acoustic feedback.

(6) Passenger Address system (PA)

Passenger Address - Block Diagram ** ON A/C NOT FOR ALL

(b) PA announcement from the cockpit
You start a PA announcement from the cockpit with the handset or with the equipment connected to the Audio Management Unit (boomset, microphone and oxygen mask). The handset transmits the audio signal directly or the equipment connected to the AMU transmits it through the AMU to the director.
The director transmits the signals to the DEU type A, which sends the signals through PISA to the loudspeakers.
For a detailed description, how to use the AMU, see Audio Management (Ref. 23-51-00).
The director transmits also the signals to the In-Flight Entertainment system (IFE).
On the Audio Control Panel (ACP) in the cockpit you can select the functions that follow:

PA from AMU:
If you push the PA button, it starts a link between the equipment connected to the AMU and all loudspeakers.

DIRECT PA:
If you push the PTT button, it starts a link between the handset and all loudspeakers.
PA ALL:
If you push the PA ALL button, it starts a link between the handset and all loudspeakers in the cabin area.

1. DIRECT PA and PA from AMU
2. All remaining PA functions.

1. AMU
2. Cockpit handset
3. Cabin attendant handsets
4. PRAM
5. EVAC
6. Video (if installed)
7. Boarding Music (if installed).

(f) PA monitoring
If you remove the cockpit handset from the cradle, the PA monitoring function starts. You hear the PA announcement with the highest priority in the handset.
The cockpit crew can monitor the PA announcements through the AMU while no other function is selected on the AMU. You must push and turn the PA rotary switch clockwise on the ACP.

(g) Reset of selected PA functions
If you start the PA function with the handset functional keys, you cancel the function like this: you put the handset back on the cradle or you push the reset button on the handset.
If you start the PA function with the PTT button, you release the PTT button to cancel the function.

(h) PA indications
The related Attendant Indication Panel (AIP) shows the dial and status information related to PA system functions.

(7) Passenger Address system (PA)

Passenger Address - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The passenger address system supplies the PA related announcements from the cockpit, the attendant stations and the In - Flight Entertainment system (IFE) to all assigned passenger loudspeakers.

(b) PA announcement from the cockpit
From the cockpit you start a PA announcement with the handset or with the equipment connected to the Audio Management Unit (boomset, microphone and oxygen mask). The handset transmits the audio signal directly or the equipment connected to the AMU transmits it through the AMU to the director.
The director transmits the signals to the DEU type A, which sends the signals either directly or through the PISA to the loudspeakers.
For a detailed description, how to use the AMU, see Audio Management (Ref. 23-51-00).
On the Audio Control Panel (ACP) in the cockpit you can select the functions that follow:

PA from AMU:
If you push the PA button, it starts a link between the equipment connected to the AMU and all loudspeakers.

DIRECT PA:
If you push the PTT button, it starts a link between the handset and all loudspeakers.
PA ALL:
If you push the PA button followed by the ALL button, it starts a link between the handset and all loudspeakers in the cabin area.
PA 1:
If you push the PA button followed by the 1 button, this starts a link between the handset and all loudspeakers in the forward cabin area.
PA 2:
If you push the PA button followed by the 2 button, this starts a link between the handset and all loudspeakers in the mid cabin area.

1. DIRECT PA and PA from AMU
2. All remaining PA functions.

1. AMU
2. Cockpit handset
3. Forward attendant station
4. Other cabin attendant stations
5. Video (if installed)
6. Boarding Music (if installed).

(f) PA monitoring
If you remove the cockpit handset from the cradle, the PA monitoring function starts. In the handset you hear the PA announcement with the highest priority, which is done by another source.
The cockpit crew can monitor the PA announcements through the AMU as long as no other function is selected on the AMU and the PA rotary switch is pushed and turned clockwise on the ACP.

(g) Reset of selected PA functions
If you start the PA function with the handset functional keys, you cancel the function like this: you put the handset back on the cradle or you push the reset button on the handset.
If you start the PA function with the PTT button, you release the PTT button to cancel the function.

(h) PA indications
The related Attendant Indication Panel (AIP) shows the dial and status information related to PA system functions.

(i) Gain adjustment
If low cabin-pressure occurs or engine operate (high oil-pressure) the volume of a PA announcement increases. The volume also increases if a data bus failure (top line) occurs.
If during a PA the cockpit door is open, the volume of the PA in the cockpit door area decreases. This will prevent acoustic feedback.

(8) Cabin and flight crew interphone system

Cabin and Flight Crew Interphone - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The cabin and flight crew interphone system allows the telephone communication between all attendant stations and the cockpit. One or more links can be started at the same time. In conference mode the communication is possible between more than two interphone stations.

(b) Interphone functions from cockpit
From the cockpit an interphone communication is started with the Cockpit Call Panel or with the equipment connected to the Audio Management Unit (boomset, microphone and oxygen mask). The audio signal is transmitted from the Cockpit Call Panel directly to the director. The audio signal from the equipment connected to the AMU is transmitted through the AMU to the director.
The audio signal is transmitted from the director to the handset of the selected attendant station through the related DEU type B.
For a detailed description of the AMU handling see Audio Management (Ref. 23-51-00).

(9) Cabin and flight crew interphone system - Cockpit call panel functions
These functions are available on the call panel by function keys:

Emergency call:
If you push the EMER button, it starts an interphone connection between the cockpit and all attendant stations in the cabin.
All attendant call:
If you push the ALL button, it starts an interphone connection between the cockpit and all attendant stations in the cabin.
Forward attendant call:
If you push the FWD button, it starts an interphone connection between the cockpit and the forward attendant station in the cabin.
Aft attendant call:
If you push the AFT button, it starts an interphone connection between the cockpit and the aft attendant station in the cabin.

(10) Cabin and flight crew interphone system - Cockpit call panel functions
These functions are available on the call panel by function keys:

Emergency call:
If you push the EMER button, it starts an interphone connection between the cockpit and all attendant stations in the cabin.
All attendant call:
If you push the ALL button, it starts an interphone connection between the cockpit and all attendant stations in the cabin.
Forward attendant call:
If you push the FWD button, it starts an interphone connection between the cockpit and the forward attendant station in the cabin.
Mid attendant call:
If you push the MID button, it starts an interphone connection between the cockpit and the mid attendant station in the cabin.
Exit attendant call:
If you push the EXIT button, it starts an interphone connection between the cockpit and the exit attendant station in the cabin.
Aft attendant call:
If you push the AFT button, it starts an interphone connection between the cockpit and the aft attendant station in the cabin.

(11) Cabin and flight crew interphone system - Cockpit call panel functions
These functions are available on the call panel by function keys:

Emergency call:
If you push the EMER button, it starts an interphone connection between the cockpit and all attendant stations in the cabin.
Forward attendant call:
If you push the FWD button, it starts an interphone connection between the cockpit and the forward attendant station in the cabin.
Aft attendant call:
If you push the AFT button, it starts an interphone connection between the cockpit and the aft attendant station in the cabin.

(12) Cabin and flight crew interphone system - Cockpit call panel functions
These functions are available on the call panel by function keys:

Emergency call:
If you push the EMER button, it starts an interphone connection between the cockpit and all attendant stations in the cabin.
All attendant call:
If you push the ALL button, it starts an interphone connection between the cockpit and all attendant stations in the cabin.
Forward attendant call:
If you push the FWD button, it starts an interphone connection between the cockpit and the forward attendant station in the cabin.
Exit attendant call:
If you push the EXIT button, it starts an interphone connection between the cockpit and the exit attendant station in the cabin.
Aft attendant call:
If you push the AFT button, it starts an interphone connection between the cockpit and the aft attendant station in the cabin.

(13) Cabin and flight crew interphone system - Interphone functions from the cabin handset
During an interphone connection the audio signals are transmitted from the cabin handset through the DEU type B to the director. The connection is started by the keypad on the handset.
These functions are available on the cabin handset by function keys:

Emergency call:
If you push the EMER CALL button, it starts an interphone connection between the calling station and the cockpit.
Cockpit call:
If you push the CAPT button, it starts an interphone connection between the calling station and the cockpit.
All attendant call:
If you push the ALL ATTND button, it starts an interphone connection between all attendant stations in the cabin.
Forward attendant call:
If you push the FWD ATTND button, it starts an interphone connection between the calling station and the forward attendant station in the cabin.
Aft attendant call:
If you push the AFT L ATTND button, is starts an interphone connection between the calling station and the aft left attendant station in the cabin.
If you push the AFT R ATTND button, it starts an interphone connection between the calling station and the aft right attendant station in the cabin.

(14) Cabin and flight crew interphone system - Interphone functions from the cabin handset
During an interphone connection the audio signals are transmitted from the cabin handset through the DEU type B to the director. The connection is started by the keypad on the handset.
These functions are available on the cabin handset by function keys:

Emergency call:
If you push the EMER CALL button, it starts an interphone connection between the calling station and the cockpit.
Cockpit call:
If you push the CAPT button, it starts an interphone connection between the calling station and the cockpit.
All attendant call:
If you push the ALL ATTND button, it starts an interphone connection between all attendant stations in the cabin.
Forward attendant call:
If you push the FWD ATTND button, it starts an interphone connection between the calling station and the forward attendant station in the cabin.
Mid attendant call:
If you push the MID ATTND button, it starts an interphone connection between the calling station and the mid attendant station in the cabin.
Exit attendant call:
If you push the EXIT ATTND button, it starts an interphone connection between the calling station and the exit attendant station in the cabin.
Aft attendant call:
If you push the AFT ATTND button, it starts an interphone connection between the calling station and the aft attendant station in the cabin.

(15) Cabin and Flight Crew Interphone System - Interphone functions from the cabin handset
During an interphone connection the audio signals are transmitted from the cabin handset through the DEU type B to the director. The connection is started by the keypad on the handset.
These functions are available on the cabin handset by function keys:

Emergency call:
If you push the EMER CALL button, it starts an interphone connection between the calling station and the cockpit.
Cockpit call:
If you push the CAPT button, it starts an interphone connection between the calling station and the cockpit.
All attendant call:
If you push the INTPH button followed by the ALL button, this starts an interphone connection between all attendant stations in the cabin. The Flight crew can monitor on ground the all attendant call when the CAB reception knob on the Audio Control Panel is activated.
Forward attendant call:
If you push the INTPH button followed by the "1/FWD" button, this starts an interphone connection between the calling station and the forward attendant station in the cabin.
Mid attendant call:
If you push the INTPH button followed by the "2/MID" button, this starts an interphone connection between the calling station and the mid attendant stations in the cabin.
Exit attendant call:
If you push the INTPH button followed by the "3/EXIT" button, this starts an interphone connection between the calling station and the exit attendant station in the cabin.
Aft attendant call:
If you push the INTPH button followed by the "4/AFT" button, this starts an interphone connection between the calling station and the aft attendant stations in the cabin.

(16) Cabin and flight crew interphone system - Interphone functions from the cabin handset
During an interphone connection the audio signals are transmitted from the cabin handset through the DEU type B to the director. The connection is started by the keypad on the handset.
These functions are available on the cabin handset by function keys:

Emergency call:
If you push the EMER CALL button, it starts an interphone connection between the calling station and the cockpit.
Cockpit call:
If you push the CAPT button, it starts an interphone connection between the calling station and the cockpit.
All attendant call:
If you push the ALL ATTND button, it starts an interphone connection between all attendant stations in the cabin.
Forward attendant call:
If you push the FWD ATTND button, it starts an interphone connection between the calling station and the forward attendant station in the cabin.
Exit attendant call:
If you push the EXIT ATTND button, it starts an interphone connection between the calling station and the exit attendant station in the cabin.
Aft attendant call:
If you push the AFT ATTND button, it starts an interphone connection between the calling station and the aft attendant station in the cabin.

(17) Cabin and flight crew interphone system - Priorities

(a) Functional priorities
The functions have different priorities. Every function will override a function with a lower priority:

1. EMERGENCY CALL
2. CALLS FROM COCKPIT
3. ALL ATTENDANT CALL
4. NORMAL CALL

(b) Source priorities
The interphone sources have different priorities. A source with higher priority interrupts a link to an interphone station with a lower priority. A source with lower priority that selects a function with higher priority also interrupts an existing link.
The sources have these priorities:

1. AMU (cockpit)
2. cockpit handset
3. attendant handsets

(18) Cabin and flight crew interphone system - Interphone monitoring
The interphone monitoring function supplies the audio signal from the interphone station with the highest priority which is in use to the AMU, as long as no interphone link to the AMU is established.

(19) Cabin and flight crew interphone system - Reset of selected interphone functions
A call started from the call panel in the cockpit is cancelled, when all requested handsets reset the function. The function is automatically cancelled after 2 minutes, when the interphone function was not activated. It is also automatically cancelled after approx. 5 minutes, when the interphone function was activated but no requested handset has accepted the call.
An interphone function is reset when you put the handset back on the cradle or after you push the reset button on the handset.

(20) Cabin and flight crew interphone system - Call chime
When an attendant call comes to the cockpit, the Flight Warning Computer (FWC) generates a buzzer sound which comes from the cockpit loudspeakers. The FWC receives the related signal from the active CIDS director.

(21) Cabin and flight crew interphone system - Indications
For visual call indication, a message shows on the AIP and the related ACP light segment comes on.
In the cockpit, the related call indicator on the Cockpit Call Panel and the AMU come on.

(22) Service Interphone System

Service Interphone - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The service interphone system allows the telephone communication between ground crew, cockpit crew and cabin crew.
(Ref. AMM D/O 23-44-00-00)

(b) Activation of the Service Interphone link
The CIDS enables the communication between the service interphone jacks and the communication equipment in the cockpit and in the cabin.
When the landing gear is extended and compressed for more than 10 seconds a link is automatically made from the director to the service interphone jacks.
If the link is not automatically made (e.g. A/C on jacks), you can set the link manually, when you press the service interphone override switch. In case of manual set of the link, the status is indicated by a service interphone indicator light in the cockpit.

(c) Service interphone from interphone jacks
When the link is made, the audio signals are transmitted from the interphone jacks to the director. The director sends the signals to the cockpit handset, to the AMU and through DEU type B to the cabin handsets. The AMU sends the signals to the cockpit boomset.

(d) Service interphone from cockpit equipment
The service interphone function from cockpit boomset is activated at the Audio Control Panel (ACP).
The audio signals are transmitted from the cockpit boomset through AMU to the director. The director sends the signals to the interphone jacks, to the cockpit handset and through DEU type B to the cabin handsets.
For a detailed description of the AMU and ACP handling see Audio Management (Ref. AMM D/O 23-51-00-00).

(e) Service interphone from handsets
After dialling the related code on the cabin handset, the audio signals are transmitted via DEU type B to the director. The director sends the signals to the service interphone jacks, via AMU to the cockpit boomset and via DEU type B to the cabin handsets.

(f) Reset of service interphone link
The link between ground-crew boomsets and handsets is cancelled when the handset is put back on the cradle.
The link between ground-crew boomsets and director is cancelled when the service interphone system becomes inactive.

(g) Service interphone indications
As long as a ground-crew boomset is connected to the system, you see the message 'SERVICE INTPH AVAIL' on all assigned AIPs.

(23) Prerecorded Announcement and Boarding Music (PRAM) System

Prerecorded Announcement and Boarding Music with integrated PRAM - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The CIDS transmits the prerecorded announcements and the boarding music to all passenger related loudspeakers.
(Ref. AMM D/O 23-32-00-00)

(b) Selection of prerecorded announcement and boarding music

FAP - Audio Page (only PRAM related buttons labeled) - Example ** ON A/C NOT FOR ALL

From the AUDIO page of the FAP the prerecorded announcement function and the boarding music function can be remotely controlled.

(c) Sources and signal transmission
The source of the prerecorded announcements and the boarding music is the PRAM.
The audio signals are transmitted from the sources via the director to the DEU type A. The DEU type A sends the audio signal either directly or via PISA to the loudspeakers.

(d) Gain adjustment
In case of low cabin-pressure or engine on (high oil-pressure) the volume of prerecorded announcement is increased.

(24) Prerecorded Announcement and Boarding Music (PRAM) System

Prerecorded Announcement and Boarding Music with integrated PRAM - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The CIDS transmits the prerecorded announcements and the boarding music to all passenger related loudspeakers.
(Ref. AMM D/O 23-32-00-00)

(b) Selection of prerecorded announcement and boarding music

FAP - Audio Page (only PRAM related buttons labeled) - Example ** ON A/C NOT FOR ALL

From the AUDIO page of the FAP the prerecorded announcement function and the boarding music function can be remotely controlled.

(d) Sources and signal transmission
The source for the prerecorded announcements and the boarding music is the In-Flight Entertainment System (IFE).
The audio signals are transmitted from the sources via the director to the DEU type A. The DEU type A sends the audio signal either directly or via PISA to the loudspeakers.

(e) Gain adjustment
In case of low cabin-pressure or engine on (high oil-pressure) the volume of prerecorded announcement is increased.

(25) Prerecorded Announcement and Boarding Music (PRAM) System

Prerecorded Announcement and Boarding Music with integrated PRAM - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The CIDS transmits the prerecorded announcements and the boarding music to all passenger related loudspeakers.
(Ref. AMM D/O 23-32-00-00)

(b) Selection of prerecorded announcement and boarding music

FAP - Audio Page (only PRAM related buttons labeled) - Example ** ON A/C NOT FOR ALL

From the AUDIO page of the FAP the prerecorded announcement function and the boarding music function can be remotely controlled.

(d) Sources and signal transmission
A second source for the boarding music is the In-Flight Entertainment system (IFE).
The audio signals are transmitted from the sources via the director to the DEU type A. The DEU type A sends the audio signal either directly or via PISA to the loudspeakers.

(e) Gain adjustment
In case of low cabin-pressure or engine on (high oil-pressure) the volume of prerecorded announcement is increased.

(26) Prerecorded Announcement and Boarding Music (PRAM) System

Prerecorded Announcement and Boarding Music with integrated PRAM - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The CIDS transmits the prerecorded announcements to all passenger related loudspeakers.
(Ref. AMM D/O 23-32-00-00)

(b) Selection of prerecorded announcement

FAP - Audio Page (only PRAM related buttons labeled) - Example ** ON A/C NOT FOR ALL

From the AUDIO page of the FAP the prerecorded announcement function can be remotely controlled.
The audio signals are transmitted from the sources via the director to the DEU type A. The DEU type A sends the audio signal either directly or via PISA to the loudspeakers.

(c) Gain adjustment
In case of low cabin-pressure or engine on (high oil-pressure) the volume of prerecorded announcement is increased.

(27) In-Flight Entertainment system (IFE)

Passenger Entertainment System - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The CIDS director transmits system information and PA related announcements from and to the IFE system.
(Ref. AMM D/O 23-33-00-00),
(Ref. AMM D/O 23-36-00-00).

(b) Signal transmission
The IFE interface receives system information and PA related audio signals from the CIDS director. The IFE additionally sends system information to the director.
CIDS transmits the following system information to the IFE:

Activation/deactivation of PAX calls
Activation/deactivation of NS/PED, FSB and RTS signs
Layout data
Illumination data
Landing gear down and compressed
Landing gear down and locked
Oil pressure low
Cabin pressure low
Excessive altitude
Slats out
Flaps out
All doors closed.

CIDS receives the following system information from the IFE system:

Activation/Deactivation of passenger calls
Activation/Deactivation of reading lights
Activation/Deactivation of video in use.

The IFE transmits the audio signals to the CIDS director. From the director the signals are transmitted via the DEU type A directly or via PISA to the loudspeakers.

(c) Gain adjustment
In case of low cabin-pressure or engine on (high oil-pressure), the volume of the audio programs or video sound is automatically increased.

(28) In-Flight Entertainment system (IFE)

Passenger Entertainment System - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The CIDS director transmits system information and PA related announcements from and to the IFE system.
(Ref. AMM D/O 23-33-00-00),
(Ref. AMM D/O 23-36-00-00).

Activation/deactivation of PAX calls
Activation/deactivation of NS/PED, FSB and RTS signs
Layout data
Illumination data
Landing gear down and compressed
Landing gear down and locked
Oil pressure low
Cabin pressure low
Excessive altitude
Slats out
Flaps out
All doors closed.

The IFE transmits the audio signals to the CIDS director. From the director the signals are transmitted via the DEU type A directly or via PISA to the loudspeakers.

(c) Gain adjustment
In case of low cabin-pressure or engine on (high oil-pressure), the volume of the audio programs or video sound is automatically increased.

(29) Passenger Lighted Signs

Passenger Lighted Signs - Block Diagram - Example ** ON A/C NOT FOR ALL

(30) Passenger Lighted Signs - General
The passenger lighted signs system controls the No Smoking (NS), Fasten Seat Belt (FSB), Return To Seat (RTS) and Exit Signs. The control switches for the signs are located in the cockpit.

(31) Passenger Lighted Signs

Passenger Lighted Signs - Block Diagram - Example ** ON A/C NOT FOR ALL

(32) Passenger Lighted Signs - General
The passenger lighted signs system controls the Please Turn Off The Electronic Devices (PED), Fasten Seat Belt (FSB), Return To Seat (RTS) and Exit Signs. The control switches for the signs are located in the cockpit.

(33) Passenger Lighted Signs

Passenger Lighted Signs - Block Diagram - Example ** ON A/C NOT FOR ALL

(34) Passenger Lighted Signs - General
The passenger lighted signs system controls the No Smoking (NS), Please Turn Off The Electronic Devices/Portable Electronic Devices (PED), Fasten Seat Belt (FSB), Return To Seat (RTS) and Exit Signs. The control switches for the signs are located in the cockpit.

(35) Passenger Lighted Signs - Operation of the passenger lighted signs
The NS and FSB/RTS signs are operated in the following control modes:

ON,
AUTO, (NS signs only)
OFF.

(a) NS switch in 'ON' position
The NS control switch on the cockpit overhead panel in the 'ON' position sets a director discrete to ground and the director sends a signal to the DEU type A. The DEU switches on all NS signs directly or via PISA.
Additionally the NS sign status is transferred to the PRAM and via the SDAC a NO SMOKING message is indicated on the ECAM display.
The EXIT signs are switched on via the exit sign relay.

(b) NS switch in 'AUTO' position
The NS control switch on the cockpit overhead panel in the 'AUTO' position sets a director discrete to ground to activate the NS and EXIT signs if:

The landing gear is down and locked (LGCIU).
Additionally the NS sign status is transferred to the PRAM and via the SDAC a NO SMOKING message is indicated on the ECAM display.

(c) NS switch in 'OFF' position
If the NS switch on the cockpit overhead panel is in the 'OFF' position, all NS and Exit signs are switched off.

(36) Passenger Lighted Signs - Operation of the passenger lighted signs
The NS and FSB/RTS signs are operated in the following control modes:

ON,
AUTO,
OFF.

(b) NS switch in 'AUTO' position
The NS control switch on the cockpit overhead panel in the 'AUTO' position sets a director discrete to ground to activate the NS and EXIT signs if:

The landing gear is down and locked (LGCIU).
Additionally the NS sign status is transferred to the PRAM and via the SDAC a NO SMOKING message is indicated on the ECAM display.

(c) NS switch in 'OFF' position
If the NS switch on the cockpit overhead panel is in the 'OFF' position, all NS and Exit signs are switched off.

(37) Passenger Lighted Signs - Operation of the passenger lighted signs
The PED and FSB/RTS signs are operated in the following control modes:

ON,
AUTO,
OFF.

(a) PED switch in 'ON' position
The PED control switch on the cockpit overhead panel in the 'ON' position sets a director discrete to ground and the director sends a signal to the DEU type A. The DEU switches on all PED signs directly or via PISA.
Additionally the PED sign status is transferred to the PRAM and via the SDAC a NO PORTABLE DEVICES message is indicated on the ECAM display.
The EXIT signs are switched on via the exit sign relay.

(b) PED switch in 'AUTO' position
The PED control switch on the cockpit overhead panel in the 'AUTO' position sets a director discrete to ground to activate the PED and EXIT signs if:

The landing gear is down and locked (LGCIU) or the slats or the flaps are extended to lever 1 or 2 (SFCC).
Additionally the PED sign status is transferred to the PRAM and via the SDAC a NO PORTABLE DEVICES message is indicated on the ECAM display.

(c) PED switch in 'OFF' position
If the PED switch on the cockpit overhead panel is in the 'OFF' position, all PED and Exit signs are switched off.

(38) Passenger Lighted Signs - Operation of the passenger lighted signs
The EXIT and FSB/RTS signs are operated in the following control modes:

ON,
AUTO, (EXIT signs only)
OFF.

(a) EXIT switch in 'ON' position
The EXIT control switch on the cockpit overhead panel in the 'ON' position sets a director discrete to ground and the director sends a signal to the DEU type B.
NO SMOKING signs are permanently switched on.
The DEU switches on the EXIT signs through the exit sign relay.

(b) EXIT switch in 'AUTO' position
The EXIT control switch on the cockpit overhead panel in the 'AUTO' position sets a director discrete to ground to activate the EXIT signs if:

The landing gear is down and locked (LGCIU).

(c) EXIT switch in 'OFF' position
If the EXIT switch on the cockpit overhead panel is in the 'OFF' position, all Exit signs are switched off.

(39) Passenger Lighted Signs - Operation of the passenger lighted signs
The NS and FSB/RTS signs are operated in the following control modes:

ON,
AUTO,
OFF.

(b) NS switch in 'AUTO' position
The NS control switch on the cockpit overhead panel in the 'AUTO' position sets a director discrete to ground to activate the NS and EXIT signs if:

The landing gear is down and locked (LGCIU).
Additionally the NS sign status is transferred to the PRAM and via the SDAC a NO SMOKING message is indicated on the ECAM display.

(c) NS switch in 'OFF' position
If the NS switch on the cockpit overhead panel is in the 'OFF' position, all NS, NSS and Exit signs are switched off.

(40) Passenger Lighted Signs - Operation of the passenger lighted signs
The EXIT and FSB/RTS signs are operated in the following control modes:

ON,
AUTO, (EXIT signs only)
OFF.

(a) EXIT switch in 'ON' position
The EXIT control switch on the cockpit overhead panel in the 'ON' position sets a director discrete to ground and the director sends a signal to the DEU type B.
Additionally the NS sign status is transferred to the PRAM and via the SDAC a NO SMOKING message is indicated on the ECAM display.
The DEU switches on the EXIT signs through the exit sign relay.

(b) EXIT switch in 'AUTO' position
The EXIT control switch on the cockpit overhead panel in the 'AUTO' position sets a director discrete to ground to activate the EXIT signs if:

The landing gear is down and locked (LGCIU).

(c) EXIT switch in 'OFF' position
If the EXIT switch on the cockpit overhead panel is in the 'OFF' position, all Exit signs are switched off.

(41) Passenger Lighted Signs - Operation of the passenger lighted signs
The EXIT and FSB/RTS signs are operated in the following control modes:

ON,
AUTO,
OFF.

(a) EXIT switch in 'ON' position
The EXIT control switch on the cockpit overhead panel in the 'ON' position grounds the discrete output of the director and the director sends a signal to the DEU type B.
Additionally the PED sign status transfers to the PRAM and via the SDAC a NO PORTABLE DEVICES message is indicated on the ECAM display.
The DEU switches on the EXIT signs through the exit sign relay.

(b) EXIT switch in 'AUTO' position
The EXIT control switch on the cockpit overhead panel in the 'AUTO' position grounds the discrete output of the director to set on the EXIT signs if:

The landing gear is down and locked (LGCIU).

(c) EXIT switch in 'OFF' position
If the EXIT switch on the cockpit overhead panel is in the 'OFF' position, all Exit signs are switched off.

(42) Passenger Lighted Signs - FSB switch

(a) FSB switch in 'ON' position
The FSB control switch on the cockpit overhead panel in the 'ON' position sets a director discrete to ground and the director sends a signal to the DEU type A. The DEU switches on all FSB signs and the RTS signs directly or via PISA.
Additionally the FSB sign status is transferred to the PRAM and via the SDAC a FASTEN SEAT BELT message is indicated on the ECAM display.

(b) FSB switch in 'AUTO' position
The FSB control switch on the cockpit overhead panel in the 'AUTO' position sets a director discrete to ground to activate the FSB and RTS signs in case of:

The landing gear is down and locked, from the Landing Gear Control and Interface Unit (LGCIU).
and/or
The slats or the flaps are extended to lever 1 or 2, from the Slat Flap Control Computer (SFCC).

Additionally the FSB sign status is transferred to the PRAM and via the SDAC a FASTEN SEAT BELT message is initiated on the ECAM display.

1 FSB switch in 'OFF' position
If the FSB switch on the cockpit overhead panel is in the 'OFF' position, all FSB and RTS signs are switched off.

(43) Passenger Lighted Signs - FSB switch

(b) FSB switch in 'AUTO' position
The FSB control switch on the cockpit overhead panel in the 'AUTO' position sets a director discrete to ground to activate the FSB and RTS signs in case of:

The landing gear is down and locked, from the Landing Gear Control and Interface Unit (LGCIU).
and/or
The slats or the flaps are extended to lever 1 or 2, from the Slat Flap Control Computer (SFCC).
and
The oil pressure is high / the engines are running, from the Engine Interface and Vibration Monitoring Unit (EIVMU).

Additionally the FSB sign status is transferred to the PRAM and via the SDAC a FASTEN SEAT BELT message is initiated on the ECAM display.

1 FSB switch in 'OFF' position
If the FSB switch on the cockpit overhead panel is in the 'OFF' position, all FSB and RTS signs are switched off.

(44) Passenger Lighted Signs - FSB switch

1 FSB switch in 'OFF' position
If the FSB switch on the cockpit overhead panel is in the 'OFF' position, all FSB and RTS signs are switched off.

(45) Passenger Lighted Signs - NON SMOKER A/C

FAP - Cabin Programming Page (only Cabin Programming related buttons labeled) - Example ** ON A/C NOT FOR ALL

On the FAP, on the CABIN PROGRAMMING page you can activate the NON SMOKER A/C function. All No Smoking signs in the cabin are switched on, regardless of the position of the cockpit switch.

(46) Passenger Lighted Signs - NON SMOKER A/C
All No Smoking signs in the cabin are permanently switched on. A manual switch off of the No Smoking signs is not possible.

(47) Passenger Lighted Signs - Cabin decompression
In case of cabin decompression all NS and FSB signs are switched on and a signal is sent to the PRAM, regardless of the position of the cockpit switches. The RTS signs are switched off.

(48) Passenger Lighted Signs - Attention chime
At activation of the NS and/or FSB/RTS signs, you hear a passenger attention chime in the respective cabin area and lavatory.
At deactivation of the NS and/or FSB/RTS signs, you hear a passenger attention chime in the respective cabin area and lavatory.

(49) Passenger Lighted Signs - Attention chime
At activation of the PED and/or FSB/RTS signs, you hear a passenger attention chime in the respective cabin area and lavatory.
At deactivation of the PED and/or FSB/RTS signs, you hear a passenger attention chime in the respective cabin area and lavatory.

(50) Passenger Lighted Signs - Attention chime
At activation of the EXIT and/or FSB/RTS signs, you hear a passenger attention chime in the respective cabin area and lavatory.
At deactivation of the EXIT and/or FSB/RTS signs, you hear a passenger attention chime in the respective cabin area and lavatory.

(50) Passenger Lighted Signs - Signs dimming
The signs are dimmed with the general illumination.

(51) Passenger Lighted Signs - Signs dimming
The signs are dimmed with the general illumination.
It is also possible to make the signs more bright or less bright when the general illumination dimming passes a specified level. When the intensity of the cabin illumination is below this level, the signs become less bright. The time for dimming the signs is programmable.
When the cabin illumination is above this level, the signs become more bright in the same way.

(52) Passenger Call

Passenger Call - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The passenger call system controls the passenger call activation and the illumination of passenger call lights.

(b) Initialization
A passenger call is started by pushing the passenger call button which is installed at each seat row and in each lavatory.

(c) Signal transmission
A passenger call initiated from the Passenger Service Unit (PSU) sends a signal from the PISA via DEU type A to the director. The director transmits a signal via the DEU type A to the respective PISA and the related call light comes on.
If the call is started from a lavatory, a signal is sent via DEU type A to the director. The director transmits a signal to the DEU type A and the related call light comes on.

(d) Indication
After call activation the director switches on the respective ACP light segment and a message on the AIP shows the location of the call. The ACPs and AIPs are connected to a DEU type B.
It is possible to suppress the chime activation if a predefined number of calls is active in one zone.

(e) Call inhibition

FAP - Seat Settings Page ** ON A/C NOT FOR ALL

After pushing the 'CHIME INHIBIT' key on the SEAT SETTINGS page of the FAP the passenger call chime is inhibit. All visual indications remain. This function is only available for calls from the seat rows.

(f) Call reset

FAP - Seat Settings Page ** ON A/C NOT FOR ALL

Pushing the call button a second time resets the call indications. The related call light goes off and the AIP indications for this call go off. The assigned ACP goes off, if no other call assigned to this ACP is active.
Pushing the 'CALL RESET' key on the SEAT SETTINGS page of the FAP resets the related call. The reset command includes the reset of all indications.

(53) Passenger Call

Passenger Call - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The passenger call system controls the passenger call activation and the illumination of passenger call lights.

(b) Initialization
A passenger call is started by pushing the passenger call button which is installed at each seat row and in each lavatory.

(e) Chime
You hear a call chime from all loudspeakers in the respective cabin area after every call activation.

(f) Call inhibition

FAP - Seat Settings Page ** ON A/C NOT FOR ALL

(g) Call reset

FAP - Seat Settings Page ** ON A/C NOT FOR ALL

(54) Passenger Call

Passenger Call - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The passenger call system controls the passenger call activation and the illumination of passenger call lights.

(b) Initialization
A passenger call is started by pushing the passenger call button which is installed at each seat row and in each lavatory.

(e) Call inhibition

FAP - Seat Settings Page ** ON A/C NOT FOR ALL

(f) Call reset

FAP - Seat Settings Page ** ON A/C NOT FOR ALL

(55) Cabin Illumination

Cabin Illumination - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The cabin illumination system controls the illumination in the different areas.
(Ref. AMM D/O 33-21-00-00)
(Ref. AMM D/O 33-24-00-00)

(b) General settings
When the CIDS is not active all CIDS controlled lights are on with full brightness. After CIDS activation the lavatory lights are dimmed, all other lights stay on with full brightness.

FAP - Cabin Lighting Page (only Cabin Lighting related buttons labeled) - Example ** ON A/C NOT FOR ALL

(d) Signal transmission
The settings initiated on the FAP are sent directly to the CIDS director, whereas the AAP settings are sent via the respective DEU type B to the CIDS director. The director sends commands via the top lines to the DEUs type A. The DEUs type A control with help of these commands the light intensity of the general illumination ballast units.

(e) Automatic activation
With one or more engines running (oil pressure high), the light intensity is dimmed automatically in the forward entrance area if the cockpit door is open.
In case of low cabin-pressure all lights are switched on with full brightness independently from all other light volume settings.
If boarding function is activated and at least one door is open the passenger call lights are switched on automatically and will stay on continuously. The passenger call lights cannot be switched off through FAP when boarding function is activated.

(56) Cabin Illumination

Cabin Illumination - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The cabin illumination system controls the illumination in the different areas.
(Ref. AMM D/O 33-21-00-00)
(Ref. AMM D/O 33-24-00-00)

FAP - Cabin Lighting Page (only Cabin Lighting related buttons labeled) - Example ** ON A/C NOT FOR ALL

On the 'CABIN LIGHTING' page of the FAP it is possible to set the lights to a predefined intensity (BTR, DIM1, DIM2) or turn them off in certain areas.
Via the MAINT button on the FAP the light in the lavatories can be controlled. As long as the MAINT button is not activated, the light in the lavatories is dimmed. The light switches to bright, when the MAINT button is pushed.
In the cabin the light can be dimmed in certain preprogrammed sequences. These sequences are defined by a start value, a stop value and a time base in which the light intensity gradually moves from the start to the stop value. A time delay for the beginning of the sequence can be defined. In the following areas a fine adjustment of the light intensity is possible:

Cabin area.

Additionally the light control is available on the AAP.

(57) Reading Lights

Reading Lights - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The reading light system controls the passenger reading lights and attendant work lights in the cabin.
(Ref. AMM D/O 33-25-00-00)

(b) Operation
The reading lights are controlled by the pushbuttons on the overhead Passenger Service Unit (PSU). The attendant work lights are controlled by pushbuttons in the attendant area.

(c) Signal transmission
If the reading lights are switched on/off from the PSUs, a signal is sent directly to the PISA or reading light.
If the attendant work lights are switched on/off from the attendant work stations, a signal is sent directly to the StA PISA.
When the signal is sent to the reading light, the reading light is switched on/off directly. When the PISAs or StA PISAs receive the signal, they switch on/off the reading lights and attendant work lights.

(d) Reset function

FAP - Cabin Lighting Page (only Reading Lights related buttons labeled) - Example ** ON A/C NOT FOR ALL

It is possible to reset all reading lights from a pushbutton on the FAP. This function is only available with the landing gear down and compressed (LGCIU).

(e) All reading lights on
It is possible to switch on all reading lights via FAP. This function is only available with the landing gear down and compressed (LGCIU).

(58) Reading Lights

Reading Lights - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The reading light system controls the passenger reading lights and attendant work lights in the cabin.
(Ref. AMM D/O 33-25-00-00)

(b) Operation
The reading lights are controlled by the pushbuttons on the overhead Passenger Service Unit (PSU) and by the seat-mounted Passenger Control Unit (PCU). The attendant work lights are controlled by pushbuttons in the attendant area.

(c) Signal transmission
If the reading lights are switched on/off from the PCUs, a signal is sent via the IFE system to the director, which transmits a signal via DEU type A to the PISA or reading light.
If the reading lights are switched on/off from the PSUs, a signal is sent directly to the PISA or reading light.
If the attendant work lights are switched on/off from the attendant work stations, a signal is sent directly to the StA PISA.
When the signal is sent to the reading light, the reading light is switched on/off directly. When the PISAs or StA PISAs receive the signal, they switch on/off the reading lights and attendant work lights.

(d) Reset function

FAP - Cabin Lighting Page (only Reading Lights related buttons labeled) - Example ** ON A/C NOT FOR ALL

It is possible to reset all reading lights from a pushbutton on the FAP. This function is only available with the landing gear down and compressed (LGCIU).

(e) All reading lights on
It is possible to switch on all reading lights via FAP. This function is only available with the landing gear down and compressed (LGCIU).

(59) Passenger Service System (PSS)

Passenger Service System - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The PSS is used for remotely controlled operation of the passenger reading lights and the passenger call activation/deactivation. The functions are available via the Passenger Control Unit (PCU) in the armrest of each passenger seat.
(Ref. AMM D/O 23-33-00-00)

(b) Signal transmission
When a passenger call is activated/deactivated or the reading lights are switched on/off, a signal is sent to the In-Flight Entertainment system (IFE). From the IFE system a signal is transmitted to the director which activates/deactivates the respective lights as described for the Passenger Call System and the Reading Lights.

(60) Passenger Service System (PSS)

Passenger Service System - Block Diagram ** ON A/C NOT FOR ALL

(d) Chimes
The chime activation is the same as described for the passenger call system.

(61) Lavatory smoke detection

Lavatory Smoke Detection - Block Diagram ** ON A/C NOT FOR ALL

FAP - Smoke Detection Page (only Smoke Detection related buttons labeled) - Example ** ON A/C NOT FOR ALL

(a) General
The lavatory smoke detection function is part of the CIDS Smoke Detection Function (CIDS-SDF). The CIDS does the visual and acoustic indications in the cabin, if a lavatory smoke alert is detected by the CIDS-SDF.
(Ref. AMM D/O 26-17-00-00)

(b) Signal transmission
The lavatory smoke detectors are connected via a CAN bus to a DEU type B and linked via the CIDS middle line bus to the CIDS directors. They communicate internally with the respective CIDS-SDF channels. The director sends a signal to the FAP where the SMOKE DETECTION page comes up automatically. On the SMOKE DETECTION page the location of the smoke alert is displayed.

(c) Indication
A smoke alert from the lavatory makes the respective ACP light segment come on in the flashing mode. The related message is shown on the assigned AIP. Also, the respective lavatory call-light comes on in the flashing mode.

(d) Chimes
In case of a smoke alert the director transmits a signal to the DEU type A. The DEU type A activates directly or via PISA a chime sequence emitted through the loudspeaker.

(e) Reset
If there is no more smoke detected, the CIDS-SDF resets all visual and acoustic indications automatically.
To reset the visual and acoustic indication in the cabin manually you have to push the 'SMOKE RESET' button either on the SMOKE DETECTION page on the FAP touch screen, the FAP sub panel or on the AAP. This affects only the cabin indications. The indications on the FAP stay as long as the smoke is detected.

(62) Lavatory smoke detection

Lavatory Smoke Detection - Block Diagram ** ON A/C NOT FOR ALL

FAP - Smoke Detection Page (only Smoke Detection related buttons labeled) - Example ** ON A/C NOT FOR ALL

(d) Chimes
In case of a smoke alert the director transmits a signal to the DEU type A. The DEU type A activates directly or via PISA a chime sequence emitted through the loudspeaker.

(e) Reset
If there is no more smoke detected, the CIDS-SDF resets all visual and acoustic indications automatically.
To reset the visual and acoustic indications in the cabin manually you have to push the 'SMOKE RESET' button either on the SMOKE DETECTION page on the FAP touch screen, the FAP sub panel or on the AAP. This affects only the cabin indications. The indications on the FAP stay as long as the smoke is detected.
The EVAC/SMOKE RESET button (2064VU) in the mid and exit attendant area also resets the visual and acoustic indications in the cabin.

(63) Lavatory smoke detection

Lavatory Smoke Detection - Block Diagram ** ON A/C NOT FOR ALL

FAP - Smoke Detection Page (only Smoke Detection related buttons labeled) - Example ** ON A/C NOT FOR ALL

(d) Chimes
In case of a smoke alert the director transmits a signal to the DEU type A. The DEU type A activates directly or via PISA a chime sequence emitted through the loudspeaker.

(e) Reset
If there is no more smoke detected, the CIDS-SDF resets all visual and acoustic indications automatically.
To reset the visual and acoustic indications in the cabin manually you have to push the 'SMOKE RESET' button either on the SMOKE DETECTION page on the FAP touch screen, the FAP sub panel or on the AAP. This affects only the cabin indications. The indications on the FAP stay as long as the smoke is detected.
The SMOKE RESET button (2065VU) in the mid and exit attendant area also resets the visual and acoustic indications in the cabin.

(64) Lavatory smoke detection

Lavatory Smoke Detection - Block Diagram ** ON A/C NOT FOR ALL

FAP - Smoke Detection Page (only Smoke Detection related buttons labeled) - Example ** ON A/C NOT FOR ALL

(d) Chimes
In case of a smoke alert the director transmits a signal to the DEU type A. The DEU type A activates directly or via PISA a chime sequence emitted through the loudspeaker.

(65) Cargo smoke detection

Cargo Smoke Detection - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The cargo smoke detection is part of the CIDS Smoke Detection Function (CIDS-SDF). The CIDS-SDF detects smoke alerts in certain cargo compartments.
(Ref. AMM D/O 26-16-00-00)

(b) Signal transmission
The cargo smoke detectors are connected via a CAN bus to the CIDS-SDF channels of both CIDS directors. The CIDS-SDF channel transmits the smoke alert via a discrete signal directly to the cockpit indicator and via an ARINC 429 bus to the FWCs.

(66) Cargo fire-extinguisher monitoring

(a) General
The cargo fire-extinguisher monitoring is part of the CIDS Smoke Detection Function (CIDS-SDF). The CIDS-SDF controls and monitors the fire-extinguisher bottle-pressure reservoir and squib condition in certain cargo compartments.
(Ref. AMM D/O 26-23-00-00)

(b) Signal transmission
The fire-extinguisher bottle pressure sensor and the discharge cartridge conditions are transmitted via the Cargo Smoke panel with discrete outputs to CIDS-SDF. The CIDS-SDF has an ARINC 429 bus interface to the FWC and to the CFDS.

(c) Indication
A low pressure of the fire extinguishing bottles and a fault condition of the discharge cartridges (SQUIB) are indicated on the CFDS.

(67) Cabin Ready function

Cabin Ready Signalling - Block Diagram ** ON A/C NOT FOR ALL

Flight Phases - Block Diagram (Sheet 1) ** ON A/C NOT FOR ALL

Flight Phases - Block Diagram (Sheet 2) ** ON A/C NOT FOR ALL

The cabin ready signaling is related to the different Flight Phases (FP). The cabin crew can indicate the status cabin ready for take-off and landing.
The status is indicated on:

the ECAM upper display unit, on the take-off check-list (on 2min. after both engines running) or on the landing check-list (on below 2000ft and landing gear extended),
on the CABIN STATUS page on the FAP the cabin ready button changes color.

The take-off check-list and landing check-list shows the message CABIN READY, when the function is activated. It shows the message CABIN CHECK, when the function is not activated or reset.
The function is activated, when you push the cabin ready button on the cabin status page on the FAP:

in FP1, when oil press is high,
in FP2, FP3,
in FP5, when a GO AROUND is performed with slats extended,
in FP6, FP7, FP8 and slats extended,
in FP9, until 80kts +30sec.

The function is reset or blocked:

when you push the cabin ready button a second time (FP conditions as for activation),
at take-off when the A/C is faster than 80kts (FP4) and in FP5,
if an approach in FP6, FP7 is rejected,
after landing in FP9 when the A/C is slower than 80kts +30sec,
after touch and go FP8, with retracted slats.

(68) Cabin Ready function

Cabin Ready Signalling - Block Diagram ** ON A/C NOT FOR ALL

Flight Phases - Block Diagram (Sheet 1) ** ON A/C NOT FOR ALL

Flight Phases - Block Diagram (Sheet 2) ** ON A/C NOT FOR ALL

The cabin ready signalling is related to the different Flight Phases (FP). The cabin crew can indicate the status cabin ready for take-off and landing.
The status is indicated on:

the ECAM upper display unit, on the take-off check-list (on 2min. after both engines running) or on the landing check-list (on below 2000ft and landing gear extended),
on the CABIN STATUS page on the FAP the cabin ready button changes color.

in FP1, when oil press is high,
in FP2, FP3,
in FP5, when a GO AROUND is performed with slats extended,
in FP6, FP7, FP8 and slats extended,
in FP9, until 80kts +30sec.

The function is reset or blocked:

when you push the cabin ready button a second time (FP conditions as for activation),
after a predefined time.

(69) Air Conditioning

Air Conditioning - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The CIDS has the capability to do a fine adjustment of the temperature in the separate cabin zones.
(Ref. AMM D/O 21-63-00-00)

(b) Operation

FAP - Cabin Temperature Page (only Cabin Temperature related buttons labeled) - Example ** ON A/C NOT FOR ALL

FAP - Cabin Temperature Page (only Cabin Temperature related buttons labeled) - ** ON A/C NOT FOR ALL

On the CABIN TEMPERATURE page of the FAP the actual temperature in the separate cabin zones is indicated in relation to the seatrows. For a fine adjustment push the button next to the related cabin zone. Then the cockpit selected temperature for this cabin area is indicated in a new window, where the new target temperature can be selected.

(c) Signal transmission
The actual temperature data are transmitted from the Air Conditioning System Controller (ACSC) to the director. The director sends these signals to the FAP where the temperature is indicated. If a new target temperature is selected the signals are sent from the FAP via the director to the ACSC.

(70) Emergency Evacuation Signaling (EVAC)

Emergency EVAC Signaling - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The Emergency-Evacuation Signaling (EVAC) system controls the evacuation signaling in all cabin areas and the cockpit. It is activated from the cockpit or the Flight Attendant Panel (FAP) during an emergency evacuation.

(b) Cockpit operation
Push the EVAC COMMAND button in the cockpit to activate the EVAC function.
The indicator light of the EVAC COMMAND button in the cockpit flashes.
The indicator light of the EVAC RESET button on the FAP hardkey panel flashes.
The EVAC indicator light of the AAP flashes.
The EVAC signaling tone sounds through all attendant station loudspeakers.
On all AIPs the message EVACUATION ALERT shows and the pink indicator light flashes.

1 EVAC switch in the cockpit in CAPT+PURS position
Push the EVAC CMD button on the FAP hardkey panel to activate the EVAC function.
The indicator light of the EVAC CMD button on the FAP hardkey panel comes on.
The indicator light of the EVAC RESET button on the FAP hardkey panel flashes.
The indicator light of the EVAC button on the AAP flashes.
The indicator light of the EVAC CMD button in the cockpit flashes.
The EVAC warning tone sounds through the EVAC horn in the cockpit.
The EVAC warning tone sounds through all attendant station loudspeakers.
On all AIPs the message EVACUATION ALERT shows and the pink indicator light flashes.
A discrete output goes to the FWC.

2 EVAC switch in the cockpit in CAPT position
Push the EVAC CMD button on the FAP hardkey panel to activate the EVAC request function.
The indicator light of the EVAC CMD button on the FAP hardkey panel comes on.
The indicator light of the EVAC CMD button in the cockpit flashes.
The EVAC warning tone sounds through the EVAC horn in the cockpit for three seconds.
A discrete output goes to the FWC.

(d) Signal transmission
After EVAC activation from the cockpit or FAP a signal goes to the director.
The director transmits signals to the EVAC horn in the cockpit and via DEU type B to the assigned AIPs.
A signal also goes to the DEU type A. The DEU sends a signal directly or via PISA to the attendant stations where the attendants hear an EVAC tone through the loudspeakers.

(e) EVAC reset

1 Reset from cockpit
If the EVAC signaling is activated from the cockpit, the function is reset after pushing the 'EVAC COMMAND' button in the cockpit a second time. If the EVAC signaling is activated from the cabin the function is reset, after pushing the 'EVAC COMMAND' button in the cockpit two times.

(f) Horn shut off
Pushing the HORN SHUT OFF button in the cockpit cancels the chime in the cockpit.

(71) Emergency Evacuation Signaling (EVAC)

Emergency EVAC Signaling - Block Diagram ** ON A/C NOT FOR ALL

(b) Cockpit operation
Push the EVAC COMMAND button in the cockpit to activate the EVAC function.
The indicator light of the EVAC COMMAND button in the cockpit flashes.
The indicator light of the EVAC RESET button on the FAP hardkey panel flashes.
The EVAC indicator light of the AAP flashes.
The EVAC indicator light of the switch panel (2064VU) flashes.
The EVAC signaling tone sounds through all attendant station loudspeakers.
On all AIPs the message EVACUATION ALERT shows and the pink indicator light flashes.

1 EVAC switch in the cockpit in CAPT+PURS position
Push the EVAC CMD button on the FAP hardkey panel to activate the EVAC function.
The indicator light of the EVAC CMD button on the FAP hardkey panel comes on.
The indicator light of the EVAC RESET button on the FAP hardkey panel flashes.
The indicator light of the EVAC button on the AAP flashes.
The indicator light of the switch panel (2064VU) flashes.
The indicator light of the EVAC CMD button in the cockpit flashes.
The EVAC warning tone sounds through the EVAC horn in the cockpit.
The EVAC warning tone sounds through all attendant station loudspeakers.
On all AIPs the message EVACUTATION ALERT shows and the pink indicator light flashes.
A discrete output goes to the FWC.

(d) Signal transmission
After EVAC activation from the cockpit or FAP a signal is sent to the director.
The director transmits signals to the EVAC horn in the cockpit and via DEU type B to the assigned AIPs and to the switch panel 2064VU at the related attendant stations.
Furthermore a signal is sent to the DEU type A. The DEU sends a signal directly or via PISA to the loudspeakers where an EVAC tone is emitted.

(e) EVAC reset

2 Reset from cabin
If the EVAC signaling is activated from the cabin, the function is reset after pushing the 'EVAC CMD' button on the related attendant panel a second time. Pushing the 'EVAC/RESET' button on the FAP hardkey panel or AAP of another attendant station causes that all visual and acoustic indications in the related attendant area are cancelled. The EVAC/RESET button is illuminated until the initial station cancels the EVAC command.
Pushing the 'RESET' button on the switch panel 2064VU at the mid or exit attendant station causes that the AIP indications and the EVAC signalling tone in the related attendant area are cancelled. The EVAC indicator light on the switch panel 2064VU flashes until the initial station cancels the EVAC command.

(f) Horn shut off
Pushing the HORN SHUT OFF button in the cockpit cancels the chime in the cockpit.

(72) Emergency Evacuation Signaling (EVAC)

Emergency EVAC Signaling - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The Emergency-Evacuation Signaling (EVAC) system controls the evacuation signaling in all cabin areas and the cockpit. It is activated from the cockpit, the Flight Attendant Panel (FAP) or the Additional Attendant Panel (AAP) during an emergency evacuation.

1 EVAC switch in the cockpit in CAPT&PURS position
Push the EVAC CMD button on the FAP hardkey panel or on the AAP to activate the EVAC function.
The indicator light of the EVAC CMD button on the FAP hardkey panel or on the AAP comes on.
The indicator light of the EVAC RESET button on the FAP hardkey panel flashes.
The indicator light of the EVAC button on the AAP flashes.
The indicator light of the EVAC CMD button in the cockpit flashes.
The EVAC warning tone sounds through the EVAC horn in the cockpit.
The EVAC warning tone sounds through all attendant station loudspeakers.
On all AIPs the message EVACUATION ALERT shows and the pink indicator light flashes.
A discrete output goes to the FWC.

2 EVAC switch in the cockpit in CAPT position
Push the EVAC CMD button on the FAP hardkey panel or on the AAP to activate the EVAC request function.
The indicator light of the EVAC CMD button on the FAP hardkey panel or on the AAP comes on.
The indicator light of the EVAC CMD button in the cockpit flashes.
The EVAC warning tone sounds through the EVAC horn in the cockpit for three seconds.
A discrete output goes to the FWC.

(d) Signal transmission
After EVAC activation from the cockpit, FAP or AAP a signal goes to the director.
The director transmits signals to the EVAC horn in the cockpit and via DEU type B to the assigned AIPs.
A signal also goes to the DEU type A. The DEU sends a signal directly or via PISA to the attendant stations where the attendants hear an EVAC tone through the loudspeakers.

(e) EVAC reset

(f) Horn shut off
Pushing the HORN SHUT OFF button in the cockpit cancels the chime in the cockpit.

(73) Emergency Evacuation Signaling (EVAC)

Emergency EVAC Signaling - Block Diagram ** ON A/C NOT FOR ALL

(b) Cockpit operation
Push the EVAC COMMAND button in the cockpit to activate the EVAC function.
The indicator light of the EVAC COMMAND button in the cockpit flashes.
The indicator light of the EVAC RESET button on the FAP hardkey panel flashes.
The EVAC indicator light of the AAP flashes.
The EVAC indicator light of the switch panel (2064VU) flashes.
The EVAC signaling tone sounds through all attendant station loudspeakers.
On all AIPs the message EVACUATION ALERT shows and the pink indicator light flashes.

1 EVAC switch in the cockpit in CAPT+PURS position
Push the EVAC CMD button on the FAP hardkey panel or on the AAP to activate the EVAC function.
The indicator light of the EVAC CMD button on the FAP hardkey panel or on the AAP comes on.
The indicator light of the EVAC RESET button on the FAP hardkey panel flashes.
The indicator light of the EVAC button on the AAP flashes.
The indicator light of the switch panel (2064VU) flashes.
The indicator light of the EVAC CMD button in the cockpit flashes.
The EVAC warning tone sounds through the EVAC horn in the cockpit.
The EVAC warning tone sounds through all attendant station loudspeakers.
On all AIPs the message EVACUTATION ALERT shows and the pink indicator light flashes.
A discrete output goes to the FWC.

(d) Signal transmission
After EVAC activation from the cockpit, FAP or AAP a signal goes to the director.
The director transmits signals to the EVAC horn in the cockpit and via DEU type B to the assigned AIPs and to the switch panel (2064VU) at the related attendant stations.
Furthermore a signal goes to the DEU type A. The DEU sends a signal directly or via PISA to the loudspeakers where an EVAC tone is emitted.

(e) EVAC reset

(f) Horn shut off
Pushing the HORN SHUT OFF button in the cockpit cancels the chime in the cockpit.

(74) Emergency Evacuation Signaling (EVAC)

Emergency EVAC Signaling - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The Emergency-Evacuation Signaling (EVAC) system controls the evacuation signaling in all cabin areas and the cockpit. You can start it from the cockpit or the Flight Attendant Panel (FAP) during an emergency evacuation.

(b) Cockpit operation
Push the EVAC COMMAND button in the cockpit to start the EVAC function.
The indicator light of the EVAC COMMAND button in the cockpit flashes.
The indicator light of the EVAC RESET button on the FAP hardkey panel flashes.
The EVAC indicator light of the AAP flashes.
The EVAC indicator light of the switch panel (2064VU) flashes.
You hear the EVAC signaling chime through all attendant station loudspeakers.
On all AIPs the message EVACUATION ALERT shows and the pink indicator light flashes.

1 EVAC switch in the cockpit in CAPT+PURS position
Push the EVAC CMD button on the FAP hardkey panel to start the EVAC function.
The indicator light of the EVAC CMD button on the FAP hardkey panel comes on.
The indicator light of the EVAC RESET button on the FAP hardkey panel flashes.
The indicator light of the EVAC button on the AAP flashes.
The indicator light of the switch panel (2064VU) flashes.
The indicator light of the EVAC CMD button in the cockpit flashes.
You can hear the EVAC warning chime through the EVAC horn in the cockpit.
You can hear the EVAC warning chime through all attendant station loudspeakers.
On all AIPs the message EVACUTATION ALERT shows and the pink indicator light flashes.
A discrete output goes to the Flight Warning Computer (FWC).

2 EVAC switch in the cockpit in CAPT position
Push the EVAC CMD button on the FAP hardkey panel to start the EVAC request function.
The indicator light of the EVAC CMD button on the FAP hardkey panel comes on.
The indicator light of the EVAC CMD button in the cockpit flashes.
You can hear the EVAC warning chime through the EVAC horn in the cockpit for three seconds.
A discrete output goes to the FWC.

(d) Signal transmission
After you start EVAC activation from the cockpit or FAP a signal transmits to the director.
The director transmits signals to the EVAC horn in the cockpit and via DEU type B to the related AIPs. The director also transmits signals to the switch panel 2064VU at the related attendant stations and to the DEU type A.
The DEU sends a signal directly or through the PISA to the loudspeakers from where an EVAC tone comes.

(e) EVAC reset

1 Reset from cockpit
If you start the EVAC signaling from the cockpit, the function is set back after you push the 'EVAC COMMAND' button in the cockpit a second time. If you start the EVAC signaling from the cabin, you can set back the function like this:

Push the 'EVAC COMMAND' button in the cockpit two times.

2 Reset from cabin
If you start the EVAC signaling from the cabin, you can set back the function like this:

Push the 'EVAC CMD' button on the related attendant panel a second time.
If you push the 'EVAC/RESET' button on the FAP hardkey panel, you cancel all visual and acoustic indications in the related attendant area. You get the same result if you push the 'EVAC/RESET' button on the AAP of another attendant station. The EVAC/RESET button is illuminated until the initial station cancels the EVAC command.
If you push the 'RESET' button on the switch panel 2064VU at the exit attendant station, you cancel these items:
The AIP indications
The EVAC signalling chime in the related attendant area.
The EVAC indicator light on the switch panel 2064VU flashes until the initial station cancels the EVAC command.

(f) Horn shut off
Pushing the HORN SHUT OFF button in the cockpit cancels the chime in the cockpit.

(75) Emergency Evacuation Signaling (EVAC)

Emergency EVAC Signaling - Block Diagram ** ON A/C NOT FOR ALL

1 EVAC switch in the cockpit in CAPT+PURS position
Push the EVAC CMD button on the FAP hardkey panel or on the AAP to start the EVAC function.
The indicator light of the EVAC CMD button on the FAP hardkey panel or on the AAP comes on.
The indicator light of the EVAC RESET button on the FAP hardkey panel flashes.
The indicator light of the EVAC button on the AAP flashes.
The indicator light of the switch panel (2064VU) flashes.
The indicator light of the EVAC CMD button in the cockpit flashes.
You can hear the EVAC warning chime through the EVAC horn in the cockpit.
You can hear the EVAC warning chime through all attendant station loudspeakers.
On all AIPs the message EVACUTATION ALERT shows and the pink indicator light flashes.
A discrete output goes to the Flight Warning Computer (FWC).

2 EVAC switch in the cockpit in CAPT position
Push the EVAC CMD button on the FAP hardkey panel or on the AAP to start the EVAC request function.
The indicator light of the EVAC CMD button on the FAP hardkey panel or on the AAP comes on.
The indicator light of the EVAC CMD button in the cockpit flashes.
You can hear the EVAC warning chime through the EVAC horn in the cockpit for three seconds.
A discrete output goes to the FWC.

(e) EVAC reset

Push the 'EVAC COMMAND' button in the cockpit two times.

2 Reset from cabin
If you start the EVAC signaling from the cabin, you can set back the function like this:

Push the 'EVAC CMD' button on the related attendant panel a second time.
If you push the 'EVAC/RESET' button on the FAP hardkey panel, you cancel all visual and acoustic indications in the related attendant area. You get the same result if you push the 'EVAC/RESET' button on the AAP of another attendant station. The EVAC/RESET button is illuminated until the initial station cancels the EVAC command.
If you push the 'RESET' button on the switch panel 2064VU at the exit attendant station, you cancel these items:
The AIP indications
The EVAC signalling chime in the related attendant area.
The EVAC indicator light on the switch panel 2064VU flashes until the initial station cancels the EVAC command.

(f) Horn shut off
Pushing the HORN SHUT OFF button in the cockpit cancels the chime in the cockpit.

(76) Potable Water Indication

Potable Water Indication - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The potable water indication system shows the filling level of the water tank on the FAP.

(b) Operation

FAP - Water/Waste Page (only Water/Waste related buttons labeled) - Example ** ON A/C NOT FOR ALL

The indication is done on the WATER/WASTE page of the FAP.
(Ref. AMM D/O 38-13-00-00)

(77) Potable Water Indication & Preselection

Potable Water Indication - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The potable water indication & preselection system shows the filling level of the water tank on the FAP and gives the commands for the preselection of the water quantity.

(b) Operation

FAP - Water/Waste Page (only Water/Waste related buttons labeled) - Example ** ON A/C NOT FOR ALL

The indication & preselection is done on the WATER/WASTE page of the FAP.
(Ref. AMM D/O 38-13-00-00)

(c) Signal transmission
The water quantity is transmitted from the Liquid Level Transmitter (LLT) via DEU type B to the director. The director sends the signal to the FAP where the actual quantity is indicated.
After preselection and display of a new filling level on the FAP, the information is transmitted from the FAP to the director. The director sends this information via the middle line data bus to the DEU type B, which transmits a related signal to the Water Preselection Unit.

(78) Potable Water Indication

Potable Water Indication - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The potable water indication system shows the filling level of the water tank on the FAP.

(b) Operation

FAP - Water/Waste Page (only Water/Waste related buttons labeled) - Example ** ON A/C NOT FOR ALL

The indication is done on the WATER/WASTE page of the FAP.
(Ref. AMM D/O 38-13-00-00)

(c) Signal transmission
The water quantity is transmitted from the Liquid Level Transmitter (LLT) via DEU type B to the director. The director sends the signal to the FAP where the actual quantity is indicated.
You can activate or deactivate the output from the FAP to the water depressurisation relay through a FAP internal toggle relay. The active/passive status of the water depressurisation relay shows by the water depr. key on the FAP and stored internally. The water depressurisation relay is connected to the Landing Gear Control and Interface Unit (LGCIU). Only if the LGCIU status is active (aircraft on ground) and the FAP output to the water depressurisation relay is also active, the water depressurisation is performed. On the FAP the message 'NO WATER PRESSURE' appears as an overlap of the aircraft symbol.

(79) Waste quantity indication

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

(a) General
The waste quantity indication system shows the filling level of the waste tanks on the FAP. Additionally fault, system and inoperative messages for the vacuum lavatories are indicated on the FAP.

(b) Operation

FAP - Water/Waste Page (only Water/Waste related buttons labeled) - Example ** ON A/C NOT FOR ALL

The operation and indication is performed via the WATER/WASTE page of the FAP.
(Ref. AMM D/O 38-30-00-00)

(c) Signal transmission
The water quantity is transmitted from the Liquid Level Sensor (LLS) and the Liquid Level Transmitter (LLT) via DEU type B to the director. The director sends the signal to the FAP where the actual quantity is indicated.
If the Liquid Level Sensor (LLS) indicates a failure, the respective signal is sent via DEU type B to the director. The director transmits the signal to the FAP where a related message indicates the faulty lavatory. The WATER/WASTE page comes up automatically, if a new failure occurs and no other system page is displayed.

(d) Visual and acoustical indication
If there is a rinse valve failure, the director sends signals to the DEU type B and to the DEU type A. After signals from the DEU type B, the related ACP light segment comes on and the related message shows on the AIP. After signals from the DEU type A, you can hear a chime in the cabin and the related lavatory call light comes on. The DEU type A transmits the related signals directly or through the PISA.
You can push the RESET WARN button on the FAP to cancel all these indications.

(80) Vacuum System Control Function (VSCF)

Vacuum System Control Function - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The Vacuum System Control Function is an extension of the CIDS operation software. It monitors and controls the Vacuum Toilet System (Ref. AMM D/O 38-31-00-00).
This includes the following functions:

Control of toilet assemblies
Monitoring of waste tank level
Control of vacuum generator
Servicing procedure
Communication with other systems
BITE-monitoring of vacuum system components
C/B monitoring.

(b) Operation
The VSCF receives signals from several components of the Vacuum Toilet System that report the current status of the Vacuum Toilet System. The VSCF examines these signals and then starts the necessary actions. Detected faults are either sent to the FAP and displayed there or they are sent to the CFDS for display on the MCDU. It depends on the quality of the fault on which system the fault is displayed.

(c) Signal transmission
Most of the signals monitored by the VSCF are transmitted from the related components via DEU type B to the director. When the signals have been processed, the director sends a signal to the FAP, where the related messages are displayed. The director also sends a signal to the CFDS to show failure messages on the MCDU. Also, the director sends signals to the related components of the Vacuum Toilet System to start the necessary actions.

(d) BITE test initialization
The CFDS transmits respective signals via the director and DEU type B to the components of the Vacuum Toilet System, if a BITE test is initiated via the MCDU. The results of the test are transmitted via DEU type B to the director, which sends the results to the CFDS. The results are indicated on the MCDU.

(81) Doors and Escape Slides Pressure Monitoring

Doors and Escape-Slides Pressure Monitoring - Block Diagram ** ON A/C NOT FOR ALL

(a) General

FAP - Doors/Slides Page (only Doors/Slides related buttons labeled) - Example ** ON A/C NOT FOR ALL

The DOORS/SLIDES page of the FAP shows the status of each door (open/closed) and slide (armed/disarmed) and the status of each door bottle and slide bottle (pressure).
(Ref. AMM D/O 25-62-00-00)
(Ref. AMM D/O 52-71-00-00).

(b) Signal transmission
The pressure sensors send the signals via the related DEU type B to the director. The status of the doors and slides is transmitted from the System Data Acquisition Concentrator (SDAC) to the director. The director transmits the signals to the FAP where all information is indicated on the DOORS/SLIDES page.

(82) Doors and Escape Slides Pressure Monitoring

Doors and Escape-Slides Pressure Monitoring - Block Diagram ** ON A/C NOT FOR ALL

(a) General

FAP - Doors/Slides Page (only Doors/Slides related buttons labeled) - Example ** ON A/C NOT FOR ALL

The DOORS/SLIDES page of the FAP shows the status of each door (open/closed) and slide (armed/disarmed) and the status of the connected slide bottles (pressure).
(Ref. AMM D/O 25-62-00-00)
(Ref. AMM D/O 52-71-00-00).

(b) Signal transmission
The pressure sensors send the signals via the related DEU type B to the director. The status of the slides is transmitted from the System Data Acquisition Concentrator (SDAC) to the director. The director transmits the signals to the FAP where all information is indicated on the DOORS/SLIDES page.

(83) Doors and Escape Slides Monitoring

Doors and Escape-Slides Pressure Monitoring - Block Diagram ** ON A/C NOT FOR ALL

(a) General

FAP - Doors/Slides Page (only Doors/Slides related buttons labeled) - Example ** ON A/C NOT FOR ALL

The DOORS/SLIDES page of the FAP shows the status of each door (open/closed) and slide (armed/disarmed).
(Ref. AMM D/O 25-62-00-00)
(Ref. AMM D/O 52-71-00-00).

(b) Signal transmission
The status of the doors and slides is transmitted from the System Data Acquisition Concentrator (SDAC) to the director. The director transmits the signals to the FAP where all information is indicated on the DOORS/SLIDES page.

(84) Emergency Power Supply Unit (EPSU)

Emergency Power Supply - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The EPSU supplies electrical power to the emergency lighting system.
(Ref. AMM D/O 33-51-00-00)

(b) BITE test initialization
The Centralized Fault Display System (CFDS) transmits respective signals via director and DEU type B to the EPSU, if one of the following BITE test is initiated via the MCDU:

System test
Battery capacity test.

The EPSU does the test. When the test is finished, the results are transmitted via DEU type B to the director which sends the results to the CFDS. The test results are indicated on the MCDU.

(85) Drain Mast Control Unit (DMCU)

Drain Mast Control - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The DMCUs monitor and control the drainmast heaters. There is a separate DMCU for every heater.

(b) Signal transmission
The drainmast system status is transmitted from the DMCU via DEU type B to the director. In case of a failure, the director sends the signal to the FAP and to the CFDS. On the FAP the CIDS Info light comes on to indicate that there is a new failure message. Via the CFDS the failure message shows on the MCDU.

(c) Internal test
Via a test button located at the front of the DMCU an internal drainmast-system test can be started. This test does not have any effect on the monitoring function done by CIDS.

(d) BITE test initialization
The Centralized Fault Display System (CFDS) transmits respective signals via director and DEU type B to the DMCU, if the following BITE test is initiated via the MCDU:

System test.

The DMCU does the test. When the test is finished the results are transmitted via DEU type B to the director, which sends the results to the CFDS. The results are indicated on the MCDU.

(86) Cabin/cockpit incident alert system (cabin to cockpit)

Cabin/cockpit incident alert system (cabin to cockpit) - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The Cabin/cockpit incident alert system is used to indicate a possible violent incident to cabin crewmembers. It activates visual and acoustic indications in the cockpit, if the respective button in the cabin is pushed (cabin alert).

(b) Signal transmission (cabin alert)
If the alert pushbutton in the door frame lining at the respective attendant station is pushed, the DEU type B transmits the signal to the director. The director uses the signal to indicate the alert via the CAB ALERT pushbutton (indicator light) located on the pedestal panel 119VU and to initiate an acoustic signal via the alerting horn in the cockpit. For visual confirmation in the cabin, the DEU type B also initiates an indication on the respective AIP where the alert was started. The acoustic and visual indications in the cockpit are reset when the CAB ALERT pushbutton located on the pedestal panel 119VU is pushed.

(87) Cabin/cockpit incident alert system (cockpit to cabin)

Cabin/cockpit incident alert system (cockpit to cabin) - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The Cabin/cockpit incident alert system is used to indicate a possible violent incident to cockpit crewmembers. It activates visual and acoustic indications in the cabin if the respective pushbutton in the cockpit is pushed (cockpit alert).

(b) Signal transmission (cockpit alert)
If one of the alert pushbutton (Captain or F/O) is pushed, the signal is transmitted directly to the director. The director sends the signal via the middle line data bus to the DEUs type B, which initiate visual indications on the ACPs and AIPs in the cabin. Furthermore, the director sends the signal via the top line data bus to the DEUs type A. The DEU type A transmits the signal to the loudspeakers, where the related acoustic annunciation is emitted. The visual indications in the cabin are reset after a specified time period written in the CAM.

(88) Cabin/cockpit incident alert system (cockpit to cabin)

Cabin/cockpit incident alert system (cockpit to cabin) - Block Diagram ** ON A/C NOT FOR ALL

(a) General
The Cabin/cockpit incident alert system is used to indicate a possible violent incident to cockpit crewmembers. It activates visual and acoustic indications in the cabin and automatically transmits a hijacking code to the Air Traffic Control (ATC), if the respective pushbutton in the cockpit is pushed (cockpit alert).

D. Programming
The CIDS can do an on-board programming of cabin zones and change the complete layout information by a CAM layout change or by a CAM replacement. The changed contents of the CAM can be downloaded into the memories of both directors via commands from the FAP. Modifications of the cabin zones of a CAM layout can be done via the FAP.
It is also possible to do an adjustment of the announcement and chime volume via the FAP.
Furthermore it is possible to change FAP set-up information.

(1) Programming of cabin zones

(a) General
The CIDS lets you move and change the cabin zone boundaries and the no-smoking zone boundaries. This programming function is available on ground and in flight.

(b) Operation

FAP - Cabin Programming Page (only Cabin Programming related buttons labeled) - Example ** ON A/C NOT FOR ALL

To change the boundaries of cabin zones or no smoking zones, select the CABIN PROGRAMMING page.

1 Change of cabin zone boundaries
To move or change the boundary between two cabin zones, push the CABIN ZONES button. The CABIN ZONES programming-panel comes on. Push the UP/DOWN buttons to change the boundary. Each cabin zone must have a minimum of one seat row.

2 Change of no-smoking zone boundaries
To more or change the boundary of a no smoking zone in a given cabin zone, push the related SMOKE PROG. button. The NON SMOKER AREAS programming-panel comes on. Push the UP/DOWN buttons to change the boundary.

3 Activation of non-smoker a/c mode
To activate/deactivate this mode push the NON SMOKING A/C ON/OFF button.

4 Save changes
To keep the changes push the SAVE button. If you do not do this before you leave the CABIN PROGRAMMING page:

The changes that you made will have no effect
The programming that was stored before is used again.

(2) Programming of cabin zones

(a) General
The CIDS lets you move and change the cabin zone boundaries. This programming function is available on ground and in flight.

(b) Operation

FAP - Cabin Programming Page (only Cabin Programming related buttons labeled) - Example ** ON A/C NOT FOR ALL

To change the boundaries of cabin zones, select the CABIN PROGRAMMING page.

2 Save changes
To keep the changes push the SAVE button. If you do not do this before you leave the CABIN PROGRAMMING page:

The changes that you made will have no effect
The programming that was stored before is used again.

(3) CAM layout change

(a) General
The CIDS gives the possibility to select different layouts which are stored in the CAM. The CAM can contain up to three pre-programmed cabin layouts. For additional modifications done in the CABIN PROGRAMMING mode, the CAM can store up to three modified layouts.

(b) Operation

FAP - Layout Selection Page (only Layout Selection related buttons labeled) - Example ** ON A/C NOT FOR ALL

To activate a new layout select the LAYOUT SELECTION page on the FAP. This page is protected by an access code and is only available on ground. It shows on the FAP when the correct access code has been entered and lists all available layouts. The active layout is indicated by a textbox.
To select a new layout push the UP/DOWN buttons on the FAP. The selected layout is highlighted by a colored bar. The selected layout is activated after pushing the LOAD button.

(4) Volume adjustment

(a) General
The CIDS gives the possibility to change the volume of chimes and announcements in all defined cabin areas independently.

(b) Operation

FAP - Level Adjustment Page (only Level Adjustment related buttons labeled) - Example ** ON A/C NOT FOR ALL

To change the settings in one area, select the LEVEL ADJUSTMENT page on the FAP. Push the related ADJUST button on the LEVEL ADJUSTMENT page to open the related VOLUME ADJUSTMENT sub panel.
To select the respective location push the UP/DOWN buttons on the VOLUME ADJUSTMENT sub panel. The selected location is highlighted by a colored bar.

1 Volume change
The volume of announcements and chimes is increased/decreased by pushing the related PLUS/MINUS button on the sub panel.

2 Default values
Push the DEFAULT button on the sub panel to reset all modifications to the CAM default values.

3 Save changes
To keep the changes push the SAVE button. If you do not do this before you leave the LEVEL ADJUSTMENT page:

The changes that you made will have no effect
The programming that was stored before is used again.

(5) Change of FAP Set-Up information

(a) General
The CIDS makes it possible to change the brightness of the screen and to change the volume settings for the FAP related loudspeaker and headphone.
It is also possible to replace the three memory cards (I-PRAM, CAM and OBRM) directly on the FAP, when the system is energized.

(b) Operation

FAP - FAP Set-Up Page (only FAP Set-Up related buttons labeled) - Example ** ON A/C NOT FOR ALL

To change the settings, select the FAP SET-UP page on the FAP.

1 Brightness change
To increase/decrease the brightness of the FAP, touch the related PLUS/MINUS button.

2 Headphone volume
To increase/decrease the volume of the headphone connected to the FAP, touch the related PLUS/MINUS button.

3 Acoustic activation
To activate/deactivate the key click which is emitted when you touch a button on the FAP, touch the TOUCHSCREEN CLICK ON/OFF button.

4 Loudspeaker volume for key click
To increase/decrease the volume of the loudspeaker that is integrated in the FAP, touch the related PLUS/MINUS button.

5 Default values
Touch the DEFAULT button to reset the changes to the CAM default values.

6 Save changes
To save the changes touch the SAVE button. If you do not save the new entries, the previous settings will stay valid after you leave the page.

7 Replace memory card
To replace one of the memory cards, touch the related REMOVE button. If the replacement of the memory card was successful, the respective part number of the installed memory card shows. The replacement works independently for each memory card but the procedure is the same.
For the CAM and the OBRM, the part number reflects only the installed memory card and not the active one. To set the memory card active, change to the SOFTWARE LOADING page.

NOTE: The status indication of I-PRAM is optional and depends on the respective CAM configuration.

** ON A/C NOT FOR ALL

8. Test Bite

A. General
The CIDS has an extensive self-monitoring capability. When all electrical power (normal and essential power at director inputs) is connected to the CIDS, a power-up test of the system is started. The progress of the test is shown with a bar graph on the FAP.
The BITE finds at least 95% of the failures and isolates at least 85%. These failures are written into the BITE memory of the directors and are sent to the Centralized Fault Display System (CFDS) in normal and interactive mode. The display units of the CFDS are called MCDUs. There are two MCDUs in the cockpit.
The indication of the failures depends on their importance.
Example:

The CIDS caution light comes on (flashing)
The messages are shown on the FAP and/or on the ECAM in the cockpit (the ECAM is activated via SDAC).

The CIDS also memorizes failures which are reported from the connected systems and sends the failure messages to the CFDS.
Parts of the failure messages (ATA references, FIN's and locations) are stored in the Cabin Assignment Module (CAM).
The failure handling/memorization is done in relation to the flight phases. The commands are sent from the CFDS to the CIDS. The failures are classified as class 1, 2 or 3 and as internal or external failures.

B. Normal Mode
In the normal mode only failures (class 1 and 2) which are detected during the current/last flight are sent continuously to the CFDS. It is started when the system is supplied with power. If a failure is detected during a flight, the related failure message is stored in the BITE memory and transmitted continuously to the CFDS until the start of the next flight. A disappearance of the failure has no effect, the failure is still in the BITE memory.

C. Interactive Mode
In the interactive mode a dialogue between the CIDS and the CFDS happens.
On request from the MCDU, the CIDS sends menu pages related to the MCDU keys.
The interactive mode is not related to the flight phases or to the landing gear status. Instead, the interactive mode is operated by commands. This means for example that when a DC1 or DC2 command is received, the interactive mode is stopped.
The interactive mode also stops and the normal mode comes on, when the RETURN command is pushed on the MAIN MCDU page.
Each A/C has a printer. The print function is available on every MCDU page except for the MAIN page.
For additional information about:
MCDU (Ref. AMM D/O 22-82-00-00)
Printer (Ref. AMM D/O 31-35-00-00)

D. Fault annunciations in the cockpit and in the cabin

(1) Status of fault messages on the upper and lower ECAM, CFDS/MCDU and FAP

.---------------------------------------------------------------------------.

! 1) COCKPIT: amber caution, level 2 !

! --> on upper ECAM: "CIDS 1+2 FAULT" !

! on lower ECAM: "CIDS 1+2" (INOP SYS) !

! single chime !

! - for related class 1 fault !

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

! 2) COCKPIT: maintenance status !

! --> on lower ECAM: "CIDS1" or "CIDS2" !

! - for class 2 faults !

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

! 3) COCKPIT: maintenance messages !

! --> on CFDS/MCDU !

! - for related class 1, 2 and 3 faults !

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

! 4) CABIN: CIDS Caution Light and FAP Auto page or Info Row message !

! --> on FAP !

! - for related class 1 faults !

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

! 5) CABIN: specific messages !

! --> on FAP !

! for related class 1 faults !

'---------------------------------------------------------------------------'

(2) Test Types to confirm or locate faults

.-------------------.-------------------------------------------------------.

! Test Types: ! 1. Power-Up Test !

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

! ! 2. continuous test, monitoring, !

! ! 'GROUND SCANNING' (via CFDS/MCDU) !

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

! ! 3. test that can be started manually !

! ! 'INTERFACE + POWER-UP TEST' (via CFDS(MCDU) !

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

! ! 4. test that can be started manually (via CFDS/MCDU) !

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

! ! 5. audible/visual test, !

! ! 'OP Test' (via CFDS/MCDU) no BITE messages !

'-------------------'-------------------------------------------------------'

E. SYSTEM REPORT/TEST

MCDU - CIDS System Report/Test ** ON A/C NOT FOR ALL

The system report/test is a part of the main maintenance menu and gives a dialogue between the MCDU and each system connected to the CFDS. This is only possible when the A/C is in the ground configuration. When you are on the SYSTEM REPORT/TEST menu, push the up or down arrow keys on the MCDU keyboard until you get to the item <COM.
To get to the CIDS main page, push <COM then <CIDS 1 or CIDS 2>.

(1) CIDS Main Page
The CIDS Main page shows the subsequent selectable pages:

<LAST LEG REPORT
<PREVIOUS LEGS REPORT
<LRU IDENT
<GND SCANNING
<TROUBLE SHOOT DATA
CLASS 3 FAULTS>
SYSTEM TESTS>
EPSU BAT CAP TEST> (Ref. AMM D/O 33-51-00-00)
OP TESTS>
GROUND REPORT>
SYSTEM CONFIG>
<RETURN (when you push this line select key you go back to the CIDS Main page).

NOTE: The <RETURN legend shows on all pages of the CIDS menu but not on the TEST IN PROGRESS pages.

Only if the FAP LAYOUT SELECTION or MAINTENANCE mode is active, the following message shows in the centre of the CIDS Main page:
INTERACTIVE MODE CURRENTLY DISABLED -LAYOUT SELECTION MODE OR MAINTENANCE MODE

(2) LAST LEG REPORT

MCDU - CIDS Last Leg Report ** ON A/C NOT FOR ALL

When you push the <LAST LEG REPORT line select key, the LAST LEG REPORT page comes on. This page shows the failure messages that came on during the last flight and it shows the subsequent data:

The date of the last flight
The time when the failure occurred
The ATA reference
The identity of the unserviceable LRU
The class of the failure (1 or 2).

This page can show a maximum of two failures. If there are more failures, you must push the next page key on the MCDU keyboard. If there are no failures found during the last flight, the message NO FAULT DETECTED is shown in the centre of the screen.

(3) PREVIOUS LEGS REPORT

MCDU - CIDS Previous Legs Report ** ON A/C NOT FOR ALL

When you push the <PREVIOUS LEGS REPORT line select key, the PREVIOUS LEGS REPORT page comes on.
This page is a sum of the LAST LEG REPORTS and shows the failure messages that came on during the 63 flights before.
This page shows the subsequent data:

The aircraft identification,

NOTE: CIDS monitors the aircraft ident parameter and updates it for all new records. This is necessary if a director is changed from one aircraft to another. In this case there may be two idents on a page. The related aircraft ident is shown above the related failure message.

The leg number (1-63)
The date of the flight when the failure occurred
The time when the failure occurred
The ATA reference
The class of the failure (1 or 2)
The identity of the unserviceable LRU.

This page can show a maximum of two failures. If there are more failures, you must push the next page key on the MCDU keyboard. If there are no failures found during the last 63 flights, the message NO FAULT DETECTED is shown in the centre of the screen.

(4) LRU IDENT

MCDU - CIDS LRU Identification ** ON A/C NOT FOR ALL

When you push the <LRU IDENT line select key, the LRU IDENTIFICATION page comes on. This page shows the identity of all electronic LRUs which can report their part number and serial number.

(5) CLASS 3 FAULTS

MCDU - CIDS Class 3 Faults ** ON A/C NOT FOR ALL

When you push the CLASS 3 FAULTS> line select key, the LAST LEG CLASS 3 FAULTS page comes on. This page shows each class 3 failure message that came on during the last flight and shows:

The time when the failure occurred
The ATA reference
The identity of the unserviceable LRU.

This page can show a maximum of two failures. If there are more failures, you must push the next page key on the MCDU keyboard. If there are no class 3 failures found during the last flight, the message NO FAULT DETECTED is shown in the centre of the screen.

(6) SYSTEM TESTS

MCDU - CIDS System Tests ** ON A/C NOT FOR ALL

When you push the SYSTEM TESTS> line select key, the SYSTEM TEST menu page comes on.
This page shows the subsequent legends:

DIR STATUS,
INTERFACE + POWER-UP TEST,
ILLUMINATION TEST (Ref. AMM D/O 33-21-00-00)
EPSU SYS TEST (Ref. AMM D/O 33-51-00-00)
DRAINMAST SYS TEST (Ref. AMM D/O 30-73-00-00).

(a) INTERFACE + POWER-UP TEST if active director is selected

MCDU - CIDS Interface + Power-Up Test (act. Director) ** ON A/C NOT FOR ALL

When you push the <INTERFACE + POWER-UP TEST line select key, the INTERFACE + POWER-UP TEST page with the messages DIRx ACTIVE and TEST IN PROGRESS 6 MIN comes on.
The CIDS does a power-up test of certain CIDS components and starts the internal BITE of the associated systems. It can last up to 6 minutes. If there is a failure, the subsequent data about this failure come on:

The ACTIVE DIR
The ATA reference
The identity of the unserviceable LRU
The class of the failure (1, 2 or 3) with a prompt > (if applicable) to get access to the trouble shooting data or to the submenus for the class 3 failures.

This page can show a maximum of two failures. If there are more failures you must push the next page key on the MCDU keyboard. If there are no failures found during the test, the message TEST OK is shown in the centre of the screen.

(b) INTERFACE + POWER-UP TEST if passive director is selected

MCDU - CIDS Interface + Power-Up Test (pas. Director) ** ON A/C NOT FOR ALL

When you push the <INTERFACE + POWER-UP TEST line select key, the INTERFACE + POWER-UP TEST page with the messages DIRx PASS., DIR TEST ONLY and TEST IN PROGRESS 30 S comes on.
The passive director tests only itself, checks all power related conditions, all FAP/CAM/Dir. interlink and ARINC/ETHERNET items.

(7) OP TEST

MCDU - CIDS Operational Tests ** ON A/C NOT FOR ALL

When you push the OP TEST> line select key, the OP TEST menu page comes on.
This page shows the subsequent legends:

<LOUDSPEAKERS ACTIVATION
<READING LT + ACP + PAX CALL + SIGN LAMPS ACTIVATION

(a) When you push the <LOUDSPEAKERS ACTIVATION line select key, all CIDS loudspeakers are supplied with a test tone until you push the <RETURN line select key.

(b) When you push the LAMPS ACTIVATION line select key, all lamps in the READING LTs, ACPs, PAX CALLs and SIGNS are illuminated until you push the <RETURN line select key.

NOTE: There is no CAM relation, all DEU outputs are activated.

NOTE: After the test (when you push the <RETURN line select key) the system performs a reset.

(8) TROUBLE SHOOTING DATA

MCDU - CIDS Trouble Shooting Data ** ON A/C NOT FOR ALL

When you push the <TROUBLE SHOOT DATA line select key, the TROUBLE SHOOTING DATA page comes on.
This page shows:

The date and the time of the message in clear language,
Snapshot data at the moment of the fault (e.g. aircraft configuration etc.) shown in hexadecimal code.

NOTE: The TROUBLE SHOOTING DATA Report contains data of system faults which occurred in flight.

(9) GROUND SCANNING

MCDU - CIDS Ground Scanning ** ON A/C NOT FOR ALL

When you push the <GROUND SCANNING line select key, the GROUND SCANNING page comes on. The GND SCANNING does an analysis of the CIDS status at this time and in case of a failure all existing internal and external failures are shown.
This page shows:

The date and the time at which the failure occurred,
The ATA reference,
The identity of the unserviceable LRU,
The class of the failure (1, 2 or 3) with a prompt > to get access to the trouble shooting data.

This page can show a maximum of two failures. If there are more failures, you have to push the next page key on the MCDU keyboard.
Each failure which is detected during the monitoring mode is written at the end of the report. The page counter is updated automatically. If there is no fault detected, the message NO FAULT DETECTED is shown. When you push the <RETURN line select key, the memory of the GND SCANNING is reset.
After activating the GND SCANNING mode it is necessary to wait approx. 3 min. to make sure that all failures are detected.

(10) GROUND REPORT

MCDU - CIDS Ground Report ** ON A/C NOT FOR ALL

The characteristics of this page are identical to those of the LAST LEG REPORT. This page shows the internal failure messages that come on when the aircraft is in ground configuration. Failures detected during the last flight which are still valid are not shown in the GROUND REPORT.

(11) SYSTEM CONFIG

MCDU - CIDS System Configuration ** ON A/C NOT FOR ALL

The SYSTEM CONFIGURATION page shows:

The current date,
The UTC,
The aircraft ident,
The ACTIVE DIR,
The CAM P/N,
The ACTIVE LAYOUT,
The LAST CAM MODIFICATION,
Informative text,
<LSP VOLUME REPORT.

(a) When you push the <LSP VOLUME REPORT line key, the system shows pages where the CAM defined loudspeaker volume is shown.

[Rev.10 from 2021] 2026.04.02 06:12:21 UTC