Level III - Ata 44 Cabin Systems

A380 TECHNICAL TRAINING MANUAL MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems

This document must be used for training purposes only

Under no circumstances should this document be used as a reference

It will not be updated.

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A380 TECHNICAL TRAINING MANUAL

LEVEL III - ATA 44 CABIN SYSTEMS Theory System

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Cabin Intercommunication Data System Desc. (3) . . . . . . . . . . . . . . . 2 Cockpit Door Surveillance System Description (3) . . . . . . . . . . . . . . 44 Cabin Video Monitoring System Description (3) . . . . . . . . . . . . . . . . 48 Cabin Systems Maintenance (3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52 Cabin Systems Operation, Control & Indicating (3) . . . . . . . . . . . . . 60

MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems

TABLE OF CONTENTS

Apr 21, 2006 Page 1


CABIN INTERCOMMUNICATION DATA SYSTEM DESC. (3) General

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The CIDS is designed in a modular way, that means the number of installed components will be adapted to the cabin layout and functional requirements. The general CIDS system architecture is based on computers (3 directors), bus lines and network concept.


CABIN INTERCOMMUNICATION DATA SYSTEM DESC. (3)

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GENERAL MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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CABIN INTERCOMMUNICATION DATA SYSTEM DESC. (3) System Description

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Directors The three Directors are the heart of the CIDS. They are fully identical and have the same outputs and inputs. They give to each other their operational status through a discrete signal plus data and failure information through CAN busses. In normal operation, one director is operative and the two others are in hot stand-by. The Directors integrate a smoke detection function, which is an independent hardware part. This function is linked to the cargo and avionics smoke detectors by CAN busses. The Directors are linked with the MD and UD Flight Attendant Panels (FAP): - by Ethernet for data exchange, - by discrete for reset. The Directors are linked with the DEU A by Ethernet data busses called "TOP LINES". They are also linked with the DEU B by Ethernet data busses called "MIDDLE LINES". The system reconfiguration (installation of options, cabin reconfiguration or CIDS expansion) is achieved through Field Loadable Software (FLS). These FLS are in the OBRM and the CAM flash memory cards. They are loaded from the Main Deck (MD) FAP (Master) flash cards at power-up. The CIDS transmits the following data to the OMS : - fault messages from the BITE to the CMS for failure isolation, failure memorization and reports generation - its configuration to the DLCS for configuration monitoring and management. The CMS can launch CIDS interactive tests from the maintenance terminals.



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SYSTEM DESCRIPTION - DIRECTORS MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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CABIN INTERCOMMUNICATION DATA SYSTEM DESC. (3) System Description (continued)

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DEU Type A The Directors and Decoder/Encoder Units (DEUs) type A for passenger functions are connected to the Top line data busses. There are six independent top line data-buses installed on the Main Deck (MD) and six on the Upper Deck (UD). On both decks the six top lines are installed along both aircraft sides and on the center of the aircraft. They are all located above the ceiling of the cabin. The four top line data bus, in the Lower Deck (if applicable), are installed along each A/C side. Top lines are Ethernet data busses (10Mb/sec). Each line is connected to the three Directors. A failure of one top line disables all passenger functions controlled by this bus. But in this case, the level of the loudspeaker connected through the other bus is increased. The lines run through connection boxes. Each connection box is connected on a DEU A. A coding switch on the connection box supplies the DEU A with its own address. Control commands and audio signals from the Director are decoded by the DEU A and transmitted to the respective connected equipment. There are power supply monitoring lights on each connection box. The green light (NORMal) is on if the DC SERVICE BUS power is available. The amber light (ESSential) is on if the DC ESSENTIAL BUS power is available. Note that the last connection box on the top line includes a termination resistor for impedance matching. Up to 192 DEUs A (12 DEU A per Top line) can be installed in the cabin (85 in the typical configuration). The CIDS uses each DEU A to control cabin lighting, signs, calls and cabin loudspeakers according to the program hosted in the CAM. The passenger functions are centralized in the PSUs. The Passenger Interface and Supply Adapter (PISA) is the PSU interface with the MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems

DEU A. A PISA is integrated into each PSU. Each DEU A can control up to 8 PISAs. The PISAs or std alone PISAs are connected to the following equipment: - Reading-light switches and reading lights, - PAX call button and call light, - Loudspeakers, - No Smoking (NS), Fasten Seat Belt (FSB) and Return To Seat (RTS) signs, The DEU A is the interface for the Stair Electrical Load Adapter (STELLA), Spot Array Light Supply Adapter (SALSA), Lavatory Interface and Light Adapter (LAILA) and the ballast units (up to 8 per DEU A). The Stand alone PISA are basically connected to attendant reading lights and loudspeakers. The stand alone PISA are installed in the cabin attendant stations, door, entrance and bar areas. The LAILA supplies dimmable lighting of lavatories and lavatory signs. The STELLA, SALSA supplies stair case area lighting and spot light arrays. The DEU A supplies 28VDC normal or essential power to the PISA, StA PISA and LAILA.


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SYSTEM DESCRIPTION - DEU TYPE A MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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CABIN INTERCOMMUNICATION DATA SYSTEM DESC. (3) - Optional cabin alert push button, - Lavatory occupied sign.

System Description (continued)

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DEU Type B The CIDS Directors and DEUs type B for cabin crew related functions are connected to the Middle line data busses. On each deck, there are two independent middle line data-buses installed, each on the A/C deck. The middle lines are installed along each aircraft side and are located above the ceiling of the cabin. Middle lines are Ethernet data busses (10Mb/sec). Each line is connected to the three Directors. The lines run through connection boxes. Each connection box is connected on a DEU B. A physical mount coding device prevents the mechanics to mount a DEU A in place of a DEU B and vice versa. There are power supply monitoring lights on each connection box. The green light (NORMal) is on if the DC SERVICE BUS power is available. The amber light (ESSential) is on if the DC ESSENTIAL BUS power is available. Note that the last connection box on the middle line includes a termination resistor for impedance matching. Up to 72 DEUs B (12 DEU B per Middle line) can be installed in the cabin (18 in the typical configuration). The CIDS uses each DEU B to control the different cabin crew related functions and other cabin support systems. The following equipment are connected to the DEUs B: - ACP - AIP - AAP - Cabin handset - Ice Protection Control Unit (IPCU), - Emergency Power Supply Unit (EPSU), - Trolley Lift Controller (TLC), - Cabin smoke detectors, - Temperature sensors, MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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SYSTEM DESCRIPTION - DEU TYPE B MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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CIDS Cabin Crew Related Equipment There are two types of ACPs: integrated in EXIT signs or stand alone. The ACP has five separately controlled fields. Each field contains coloured LEDs activated either continuously or flashing. They inform cabin attendants of PAX-call, interphone call, sterile cockpit request, smoke detection and EVAC. The AIPs display dial and call information from Passenger Address (PA), interphone and PAX call and other cabin systems information like the LAV smoke location. The AIP display is composed of two lines and two indicator lights. These indicator lights are used to attract cabin crew attention (when a message is displayed). The optional AAPs control a specific cabin zone. They are 3 AAPs types: With 18, 12 or 6 keys. Their basic functions are the cabin lights control, smoke detection indication and EVAC alert. Up to 144 AAPs can be installed. The cabin and cockpit handsets are used for Interphone functions and for PA announcements. In typical configuration there are 20 handsets installed (up to 144 can be installed). The handset has the following main components: - An integrated keyboard with 18 keys (17 for cockpit handset) which is used to initiate different types of calls/announcements, - An integrated display which provides the related PA/Interphone dialling and calling information, - A PTT switch which is used for PA function.



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SYSTEM DESCRIPTION - CIDS CABIN CREW RELATED EQUIPMENT MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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FAP Presentation The FAP is the main user interface with the CIDS. It programs, controls and indicates the status of the CIDS and of some cabin support systems. Basically, there is one FAP installed on the UD and one on the MD (which is the master) and they are installed in the door area. Up to 10 FAPs can be installed. The FAP comprises a touch screen and a hard key panel. The touch screen has the following functional areas: - Heading row for each selected title page. - Display area to show each selected page. - System and function keys to navigate through the different pages. The hard key panel is used for major functions, which have to be operated independently from the FAP touch screen. The hard key panel has the following hard keys: - PED POWER, - LIGHTS MAIN ON/OFF to switch the main cabin lights ON or OFF (100% or 0%), - LAV MAINT (standing for lavatory maintenance) to switch lavatory lights on (100%), - SCREEN 30 sec LOCK to lock the touch function of the screen and be able to clean it, - EVAC CMD to initiate an emergency evacuation, - EVAC RESET to reset the evacuation lights and audio alert, - SMOKE RESET to reset the audio smoke alert, - FAP - PC RESET to reset the PC part of the FAP. The hard key panel has the following switches: - EMER LIGHT for emergency, - PAX SYS to cut off the In-Flight Entertainment System (normally enabled upon power-up). And it has also the following interfaces: MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems

- USB plug for printer, mouse, software or data loading for NSS applications, - Headphone plug to listen to PRAM before broadcasting. On the lower part of the FAP panel, part hidden by the lining, 3 flash card readers are installed: - One for the OBRM flash card containing the system software, - One for the CAM flash card containing all cabin layout and zoning information (Cabin zoning, seat relation to loudspeakers and passenger lighted signs, chime sequences, Audio levels). - The third flash card is the integrated PRAM which stores prerecorded announcement and boarding music audio. As an option it is possible to connect a keyboard.


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SYSTEM DESCRIPTION - FAP PRESENTATION MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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CABIN INTERCOMMUNICATION DATA SYSTEM DESC. (3) System Description (continued) FAP Interfaces

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Only the first two FAPs are directly connected to the Directors. Any other FAP is connected in series with one of the first two FAPs. The FAPs installed on the UD are independent from the FAPs installed on the MD. A faulty FAP on the UD has no influence on the MD FAP and vice versa. The FAP is connected to the following equipments: - Director 1, - Director 2, - Director 3, - Next FAP, - Mini FAPs, - IFE, - Emergency lighting system, - NSS - SIRU (for CCOM, cabin log book and OMS applications), - NSS - CRU (for CVMS display, IFE control and other).



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SYSTEM DESCRIPTION - FAP INTERFACES MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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MINI FAP (Optional) The MINI FAP is a touch screen panel and has FAP limited functions. It is used for local cabin control (up to 4 zones can be controlled and up to 28 mini FAPs can be installed). In case of MINI-FAP installation, there is a data link between one MINI-FAP on Main Deck (MD) and one MINI-FAP on Upper Deck (UD). This data link is always active, data from CIDS directors goes via master FAP and MD MINI-FAP to UD MINI-FAP and then to the UD FAP and the other MINI-FAPs. In case of failure of the Master FAP, the back up bus becomes active, and data from the CIDS directors goes to UD FAP, UD MINI-FAPs and then to the MD MINI-FAPs via the data link. The MINI-FAP comprises a touch screen and an hard key panel. The MINI-FAP has the basic following pages: - Cabin lighting - Smoke detection - MINI-FAP set-up. This can be extended to include up to 10 pages: cabin ready function, air conditioning control,... The MINI-FAP has the basic following hard keys: - SCREEN OFF - EVAC RESET - SMOKE RESET.



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SYSTEM DESCRIPTION - MINI FAP (OPTIONAL) MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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Power Supply In the normal mode, the normal bus supplies 28VDC to CIDS Directors and DEUs. The system operates with full capability. In the emergency mode, only the essential bus supplies 28 VDC to the CIDS if the normal bus is not available. If the normal bus is not available and the CIDS is in emergency mode, the power consumption is reduced to a minimum. The system operates with minimum capabilities. The remaining functions are: - Passenger Address, - Cabin Interphone, - EVAC, - Smoke detection. The CABIN lighting is set to 100%. The DEUs A, which are connected to the top lines, are only supplied when an audio signal is present. If there is no audio signal, the active Director energizes the Top Line cut-off relays not to power the DEUs. If a power interruption is longer than 5 sec. the CIDS software is reset and all the components of the system are set to the predefined status. After an interrupt of 0.2s the smoke detectors are reinitialized. Note that the BITE and test functions are only active when both essential and normal busses are available.



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SYSTEM DESCRIPTION - POWER SUPPLY MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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CABIN INTERCOMMUNICATION DATA SYSTEM DESC. (3) System Functions The CIDS system has several functions, which are: - Passenger Address - Cabin and service interphone - ECAS (optional) - Crew signalling - EVAC - PAX Signs - PAX Call - Software Loading - Layout Selection - Cabin Programming - Loudspeaker Level Adjustement

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PA The passenger address system distributes the PA announcements from the cockpit, the attendant stations, the PRAM and, the In-Flight Entertainment System (IFES) to all assigned cabin loudspeakers. PA announcements are also transmitted through the passenger headset, if the IFES is activated. Cockpit and cabin crew make PA announcements using handsets (PTT and handset functional keys). The following functions are available: - DIRECT PA: pushing the PTT button broadcasts the announcement in all the cabin (all decks including crew rests if installed), - PRIO PA: pushing the PRIO then PTT buttons broadcasts the announcement in all the cabin (all decks except in crew rests), - DECK PA UD, MD or LD: pushing the PA button followed by DECK selection (MD, UD or LD) and the PTT button, transmits the announcement to the loudspeakers in the selected deck (except in crew rest). MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems

Announcements can be made in a specific cabin zone and also to all or to one crew rest. Cockpit crew can also make PA announcements using the acoustic devices (boomset, microphone and oxygen mask) and selecting the PA key on the RMP. The audio signal will then transit via the Audio Management Unit (AMU). When the PTT key is pressed, corresponding to the direct PA function, the confirmation message "DIRECT PA/PA ALL/PRIO PA IN USE" is displayed on all the AIPs and a high-low chime is broadcasted to all the cabin loudspeakers and passenger headsets. In the cockpit, the "PA IN USE" message is displayed on the left memo area of the ECAM E/WD memo. The function of the PRAM is to play prerecorded messages. It also plays boarding music programs to the passengers through the aircraft passenger address system. The selection of prerecorded announcement is made on the PRE ANNOUNCEMENT page of the FAPs and/or boarding music is made on the MUSIC page of the FAP (these pages are also available with the optional MINI-FAPs). In case of low cabin-pressure or engine on (high oil-pressure) the volume of a PA announcement is increased. The volume is also increased in case of a data bus failure (top line). If a cabin handset is in use, the volume of the PA announcement in the respective handset area is decreased to avoid a feedback. The volume is also decreased when the cockpit door is opened to avoid a feedback between cockpit audio equipment and cabin loudspeakers. The PA functions have priorities: 1 - PA from cockpit acoustic devices (AMU) 2 - DIRECT PA, 3 - PRIO PA, 4 - Normal PA. The PA sources have the following priorities: 1- cockpit acoustic devices (AMU), 2- cockpit handset,


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3- cabin handsets, 4- PRAM, 5- IFES. A source with 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. However, there is an exception, if the lower priority source makes an announcement with a higher functional priority.



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SYSTEM FUNCTIONS - PA MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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CABIN INTERCOMMUNICATION DATA SYSTEM DESC. (3) System Functions (continued)

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Interphone The cabin and service interphone systems will provide communication between cockpit crew, cabin crew and ground mechanics. One or more links can be initialized at the same time. In conference mode, communication is possible between more than two and up to 24 interphone stations. From the cockpit, interphone communications are achieved using cockpit handset or the cockpit call panel and the cockpit acoustic devices (boomset, microphone and oxygen mask) connected to the AMU. The following functions are available to call the cabin from the cockpit call panel: - EMER call (to call all cabin crew stations in emergency mode), - ALL call (to call all cabin crew stations), - PURS call (to call the purser), - UPPER DECK call, - MAIN DECK call, - SECURITY call (optional), - PILOT REST FWD call (to upper flight crew rest compartment) - PILOT REST MAIN call (to lower flight crew rest compartment) Note: before initiating an interphone communication with the cabin, the pilot must select the CABin transmission key and reception knob on the RMP. Calls from the cabin are initiated with the cabin handset or with the wireless handset (optional). From the cabin and the cockpit handset, the interphone basic functions are: - EMER (emergency call to all stations), - PRIO CAPT/CONF/PURS (priority call), - CAPT (to call the captain) (only available from cabin handset), - PURS (to call the purser), MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems

- CONF (conference mode), - Miscellaneous (crew rests, stairs area, lift, galley...). The interphone system has a maximum of 42 functions. The interphone calls have the following priorities: 1- EMERGENCY CALL 2- SECURITY CALL (optional, only from CCP) 3- PRIORITY CALLS 4- PURSER CALLS 5- CONFERENCE CALLS 6- NORMAL CALLS (lowest priority) The sources have the following priorities: 1- cockpit acoustic devices (AMU) 2- cockpit handset 3- cabin handsets A source with higher priority interrupts interphone communication of station with lower priority. A function with higher priority selected on a source with lower priority also interrupts an existing link. The dial information is displayed on the related AIP then a chime will be activated in the respective cabin area. After finishing the procedure the respective light field in the ACP comes on and the related message is shown on the assigned AIP. If the cockpit is called from an interphone station, a buzzer is activated (normal or emergency) via the Flight Warning System (FWS). If the cockpit is called from an interphone station the ATT light on the RMP comes on and the dial information is displayed on the optional cockpit AIP. In case of emergency call the corresponding light on the cockpit call panel comes on. The interphone is reset by hanging up the handsets or by pushing the reset button. This reset function is automatically done after approximately 5 minutes, when no requested handset accepts the call. The service interphone system enables voice communications, on ground only, between the cockpit, the cabin crew stations and the service interphone jacks located around and in the aircraft.


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The service interphone is automatically activated when the CIDS directors receive LGERS on-ground or GGPCU external power available signal. The AIPs in the cabin will indicate that the service interphone is in use. If LGERS on-ground information or GGPCU external power are not sent to the Directors, the SerViCE INTerphone OVerRiDe pushbutton has to be set to ON to force the service interphone activation.



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SYSTEM FUNCTIONS - INTERPHONE MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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CABIN INTERCOMMUNICATION DATA SYSTEM DESC. (3) System Functions (continued) ECAS (Optional)

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The Emergency Crew Alerting System (ECAS) is an optional system which is highly customized. It is used to signal an incident in the cabin or in the cockpit. If a cabin alert is initiated (hidden/guarded switch), the DEU B transmits the signal to the Directors. The Directors send the signal to the cockpit to activate visual and aural indications. The directors also send the signal via the middle line data-bus to the DEUs B, which activate visual indications on the AIPs in the area where the key had been pressed (if enabled in the CAM). Furthermore, the Director sends the ECAS status to the optional CVMS (activation of some camera display on the cockpit SD). If a cockpit alert is initiated, the signal is transmitted directly to the Directors. The Directors send the signal via the middle line data-bus to the DEUs B, which activate visual indications on the AIPs and ACPs in the cabin. Furthermore, the Directors send the signal on the top line data-bus to the DEUs A. The DEU A transmits the signal trough PISA or Sta PISA to emit a special chime sequence.



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SYSTEM FUNCTIONS - ECAS (OPTIONAL) MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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CABIN INTERCOMMUNICATION DATA SYSTEM DESC. (3) System Functions (continued) Crew Signalling

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The cabin crew can send a cabin ready status to the cockpit for take-off and landing. First an "area ready" signal is initiated on each assigned optional MINI-FAP or FAP, and the area status of all areas is collected on a Cabin ready page on FAPs. Thus the purser is able to initiate a "cabin ready" signal which is then displayed on the ECAM. The enable/reset logic of the cabin ready is programmed in the CAM. It will depend on flight phases and other customized conditions (L/G down and locked, oil pressure low on ground or slats or flaps extended). If the flight crew does not want to be disturbed by the cabin crew, an optional "sterile cockpit" switch may be activated from the cockpit to trigger visual indications on AIPs and ACPs. It can only be reset by the sterile cockpit switch.



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SYSTEM FUNCTIONS - CREW SIGNALLING MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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EVAC The emergency evacuation signaling system is used to initiate the evacuation in all cabin areas and in the cockpit. The EMER command can be initiated from the FAP, the optional MINI-FAP, the optional AAP, using the EVAC CMD buttons, and/or from the cockpit on the EVAC panel. The EVAC switch (CAPT & PURS position) allows the cabin crew to initiate the evacuation process. In the CAPT position, only the cockpit crew can activate the EVAC command. In this case, if an evacuation is initiated from the cabin, it activates visual indication (EVAC light on EVAC panel) and aural indications (cockpit horn and normal buzzer) in the cockpit. The horn can be shut off using the HORN OFF button. The EVAC command can be confirmed by the cockpit crew pushing the COMMAND button. The ON indication comes on in white. Indication in the cabin is given through an emergency tone broadcast by the loudspeakers. At the same time, the AIPs will display "EVACUATION ALERT" and their red light will flash. The pink led of the ACPs will be on. And the EVAC RESET button will flash on the FAPs, optional AAPs and optional MINI-FAPs. The EVAC reset is done: - in the cockpit by pushing the EVAC CMD push button switch. - in the cabin using the EVAC RESET button on the FAP, optional MINI-FAP and optional AAP. If assigned in the CAM, CIDS also sends EVAC status to the Doors and Slides Management Control Unit (DSMCU) and to the IFE CENTER, as long as an EVAC command is active.



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SYSTEM FUNCTIONS - EVAC MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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PAX Signs The passenger lighted signs system controls the No Smoking (NS), Fasten Seat Belt (FSB), Return To Seat (RTS) and EXIT Signs. The control switches are located on the SIGNS panel on the cockpit overhead panel. Except for the EXIT sign, these signs are connected to a PISA, std alone PISA or LAILA and are controlled by the Directors via DEUs A. The EXIT signs are controlled by the Directors via the Emergency Power Supply Unit (EPSU). As an option, it is possible to install NO PED (Passenger carried Electronic Devices) signs instead of NS signs. When the FSB control switch is in the ON position, the director sends a signal to the DEU A to switch on all FSB and RTS signs. When the FSB control switch is in the AUTO position, the director sends a signal to switch on all FSB and RTS signs in case of: - Nose landing gear down and locked (LGERS) or Slats extended (SFCC), - and Engine running (EIPM) Note that these conditions are customized. When the FSB control switch is in the OFF position, all FSB and RTS signs are off. When the FSB signs are ON, a FASTEN SEAT BELT message is displayed on the ECAM. When the NS control switch is in the ON position, the director switches on all NS signs. Optionally, the EXIT signs are also switched on. When the NS control switch is in the AUTO position, the director sends a signal to switch on all NS and Exit signs when the Nose landing gear is down and locked (LGERS) or Slats are extended (SFCC) (Note that these conditions are customized). MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems

When the NS signs are ON, a NO SMOKING message is displayed on the ECAM. When the NS control switch is in the OFF position, the director sends a signal to switch off all NS and EXIT signs. Only the NS signs in the no smoking areas are constantly switched on. The no smoking areas are modified on the CABIN PROGRAMMING page of the FAP. On the FAP, on the CABIN PROGRAMMING page, you can activate the NON SMOKER A/C function. In this case, all NS signs are switched on, regardless of the position of the cockpit switches. The PED signs are controlled together with the NS signs or from an optional NO PED control switch in the cockpit. In case of low cabin pressure (CPCS) all NS, FSB and EXIT signs are switched on, regardless of the position of the cockpit switches (The RTS, PED and RTC signs stay OFF). In case of low air flow (VCS) in lower crew rest compartment (if installed) the RTC signs are switched on. The 'sign flash' function is an option, which can be defined in the CAM. After activation the NS, PED (if installed), FSB, RTS and RTC signs flash for a pre-defined time and then remain on. Activating and deactivating of the NS, PED (if installed), FSB, RTS and RTC signs initiate an attention chime in the cabin. In addition, the active Director transfers the signs activation to the PRAM to broadcast special announcements. The active director also transfer the signs activation to the IFE system for display on the IFE equipments. Different modes are available to decrease or increase the lighting level of the passenger lighted signs: - The lighting level of the passenger lighted signs decreases or increases in the same rate as the general lighting (proportional mode). - The lighting level of the passenger lighted signs decreases or increases when the general lighting goes through a pre-defined level (trigger level mode).


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SYSTEM FUNCTIONS - PAX SIGNS MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


Apr 18, 2006 Page 35



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PAX Call The passenger call system controls the passenger call activation and indications. A passenger call is initiated by pushing the PAX CALL button at each seat row (PSU) or in the lavatory. The call can also be initiated from the Passenger Control Unit (PCU), which is located in the armrest of each seat. When the PAX CALL button is pressed, a signal is sent to the Directors, via the DEU A or the IFES. The active Director will then send a signal to the DEU A to switch on the related call light. At the same time, it will switch on the respective ACP light and the AIP will indicate the origin of the call. As an option, the call location can also be indicated on the PAX CALL pages of the FAP and/ or of the dedicated optional MINI-FAP. A call chime is heard from the loudspeakers in the respective cabin area upon call activation. As an option, it is possible to suppress the chime activation (eg for night flight). Pushing the call button a second time resets the all call indications. Pushing the CALL RESET button on the SEAT SETTING page of the FAP or on the MISCELLANEOUS page of the optional MINI-FAP or on the optional AAP resets all calls in the assigned zone. After pushing the Chime Inhibit button on the SEAT SETTING page of the FAP or on the MISCELLANEOUS page of the optional MINI-FAP, the call chime is inhibited. All visual indications remain. As an option, it is possible to activate this function on the assigned AAP. All inhibitions are reset when the A/C transits from flight phase to landing phase (Nose landing gear down and locked).



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SYSTEM FUNCTIONS - PAX CALL MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


Apr 18, 2006 Page 37


CABIN INTERCOMMUNICATION DATA SYSTEM DESC. (3) System Functions (continued) Layout Selection

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The CIDS cabin layout selection is done from a FAP. Maximum of three predefined modifiable cabin layouts can be selected. The CAM Layouts may be changed only when the aircraft is on ground (EIPM and LGERS signal detection) and when there is no CMS Interactive mode activated. After a layout change, the information is sent to the IFE system. The layout modification are saved and dated. Note that this function is protected by a three digit access code.



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SYSTEM FUNCTIONS - LAYOUT SELECTION MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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CABIN INTERCOMMUNICATION DATA SYSTEM DESC. (3) System Functions (continued) Cabin Programming

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The cabin programming function permits the modification of the cabin zones predefined in the CAM. There are up to 8 cabin zones, on each deck, which are used by different CIDS functions: - Passenger Lighted Signs (no smoking signs) - Cabin Interphone - Cabin lighting - Passenger Call - Passenger Address - IFE system - Electrical window shades (option) The cabin programming can be also used to modify the smoking zones. Without saving the new entries, the previous settings remain valid after leaving the programming page. To save the changes, push the SAVE button. The layout is saved in the CAM as a modified layout. Note that this function is protected by a three digit access code.



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SYSTEM FUNCTIONS - CABIN PROGRAMMING MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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CABIN INTERCOMMUNICATION DATA SYSTEM DESC. (3) System Functions (continued) Loudspeaker Level Adjustement

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The FAP level adjustment page enables to adjust the loudspeakers level (announcement and/or chimes) in the cabin zones, attendant areas, rooms, lavatory and stairs. This function is protected by an access code and is available on ground or in flight. The announcement volume and the chime volume are modifiable within a range from -4dB +6dB, in steps of 2dB. When modifications are saved they are stored in the CAM. Note that this function is protected by a three digit access code.



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SYSTEM FUNCTIONS - LOUDSPEAKER LEVEL ADJUSTEMENT MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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COCKPIT DOOR SURVEILLANCE SYSTEM DESCRIPTION (3) General

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The CDSS is designed to help the cockpit crew to identify a person requesting entrance to the cockpit and to survey the doors 1 hidden cross section via video camera observation. The CDSS is mainly composed of: - 3 video cameras installed in the cockpit entrance area (a maximum of 6 can be installed), - 1 CDSS controller The pictures of the cameras are shown on the cockpit System Display (SD) (part of the Control and Display System (CDS)).


COCKPIT DOOR SURVEILLANCE SYSTEM DESCRIPTION (3)

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Description The CDSS controller manages video signals from the CDSS cameras. The CDSS controller sends CDSS images to the SD via the CMV through optical fiber. It sends also the images to the optional GSP (access to the camera images via a connected laptop) and to the optional CVMS. The system is composed of three black and white video cameras (up to 6 can be installed), which are supplied by the CDSS controller: - Camera 1 is installed above the cockpit door. It shows pictures of the area directly in front of the cockpit door. This camera includes infrared lighting. - Camera 2 is installed in the ceiling of the right Door-1-Area. It shows pictures of the area directly below the camera 2 in the right Door-1-Area. - Camera 3 is installed in the ceiling of the left Door-1-Area. It shows pictures of the area directly below the camera 3 in the left Door-1-Area. An optional CDSS in use light can be installed in the cabin, which will be lighted each time the cameras of the CDSS are active. An optional CDSS_FAULT indication light can be installed in the cockpit. The Concentrator Multiplexer for Video (CMV) sends the CDDS images to the cockpit System Display (SD): - if a cockpit door entrance is requested by the Cockpit Door Lock System (CDLS) or the optional Private Door Locking System (PDLS) (automatic activation of camera 1) - or if the cockpit crew selects the CDSS video. It is then possible to change the active camera by turning the Camera Select knob on the ECAM CTL panel. As an option, in case of Hi-jacking it is possible to deactivate, the video link (no video display on the cockpit SD) as well as the CDSS in use light (no indication whether a camera is displayed). This is done via the optional GSP or via optional CAPT and F/O RATC push buttons switches. The CDSS controller is also able to send all the cameras images to an optional Video Recorder Capability (VRC). MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems

The CDSS controller transmits fault messages from the BITE to the CMS for failure isolation, failure memorization and reports generation. In case that the whole a/c is not powered, it is possible by using an external power supply (via the optional GSP) to energize all cameras and transmit the captured images to a laptop connected to the optional GSP.


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DESCRIPTION MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


Apr 18, 2006 Page 47


CABIN VIDEO MONITORING SYSTEM DESCRIPTION (3) General

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The CVMS is basically composed of cameras, ADUs and one DAU. The cockpit crew, the cabin crew, the passengers, and the ground staff can view the CVMS camera images.


CABIN VIDEO MONITORING SYSTEM DESCRIPTION (3)

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Description The CVMS has up to 15 cameras (As an option it is possible to install up to 60 cameras). These cameras are color cameras with microphone. Each ADU receives video signal from the cameras, it can control up to 10 cameras (the number depends on the installation location). There are basically 5 ADUs, up to 10 can be installed (including 1 ADU for lower deck facilities). The ADUs convert the camera analog video signal into a digital signal. The DAU is the video controller of the CVMS. There are two USB drives connected to the DAU: One USB drive is used to safe/archive events recorded from a dedicated video-camera. The cabin crew can request (using the FAP) to store the last 5 minutes recording of a selected camera to the USB video storage drive in the DAU. One other USB drive is used to store the CVMS configuration file. The DAU sends upon request the video images to the following basic equipment: - SD through the CMV (optic fiber technology) for cockpit crew, - FAPs with associated audio (through Ethernet bus via optional CRU) for cabin crew, The DAU sends upon request the video images to the following optional equipment: - IFE Center (through Ethernet busses via CRU or via a direct link if NSS is not available) for passengers, - GSP with associated audio (through Ethernet bus) available via a laptop for ground staff when A/C is on ground, The DAU receives CDSS videos images (analog signals), which can also be sent to the previous equipment. The cockpit crew has access to the CVMS video by turning the rotary knob on the ECAM control panel. The camera selection is sent via the ADCN to the CDAM, optional ARU-OPS, optional OWD and finally to the DAU. MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems

By activation of the PUSH key on the FAP, the cabin crew sends a dedicated camera image to be displayed automatically on the SD for the cockpit crew. In case of an ECAS alert from the CIDS directors (cabin alert switch activated) the nearest camera will automatically be selected and displayed on the SD (priority request to CMV via discrete signal). The ECAS alert signal is sent to the DAU via the same path as the camera selection signal. Basically each camera has a 5 minutes audio and video recording (buffer memory). As an option it is possible to record all the video images and audio with an optional digital recorder (optic fiber). From the FAP and/or the optional GSP it is possible to control the storing and to retrieve the video with the associated audio. Two optional CVMS Kill switches are installed in the cockpit to allow the manual and irreversible deactivation of the CVMS (discrete signals to DAU). Once OFF, the CVMS can only be reset by Maintenance on ground. The manual deactivation of the CVMS and CDSS is also possible using a dedicated ON/OFF switch on the optional GSP (discrete signal to DAU). As an option, A/C data are sent to the DAU via the same path as the camera selection signal. They are used to activate the surveillance of specific cabin area during specific flight phases and/or to deactivate automatically the CVMS display when the A/C is on ground. In case the whole a/c is not powered (ex in case of Hi jacking on ground) it is possible to energize all the cameras from the optional GSP external power connector. The CVMS has a Local Maintenance Function (LMF). This LMF is displayed on an airline cabin laptop (used as a maintenance terminal).


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DESCRIPTION MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


Apr 18, 2006 Page 51


CABIN SYSTEMS MAINTENANCE (3) CIDS tests In the cabin systems (except In Flight Entertainment System) , only the CIDS has some specific tests.

OMS Interactive Tests Overview The CIDS fulfills the following interactive tests : - TESTS - REPORTS - SPECIFIC FUNCTIONS These tests are launched from the OMS HMI (using the OMT, OIT or PMAT).

Reports The report gives access to the system configuration which is stored in the CAM.

Specific funtions

L1W06161 - L0KT0T0 - LM44Y1MAINT0001

The lamps activation activates all the reading/work/decor/ spot lights, ACPs, PAX call lights and signs in the cabin, lavatories and rooms. The loudspeakers activation distributes a test tone to all loudspeakers in the cabin, lavatories and rooms.


CABIN SYSTEMS MAINTENANCE (3)

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CIDS TESTS - OMS INTERACTIVE TESTS OVERVIEW ... SPECIFIC FUNTIONS MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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CABIN SYSTEMS MAINTENANCE (3) Dataloading In the cabin systems (except In Flight Entertainment System), only the CIDS has a specific data loading process.

L1W06161 - L0KT0T0 - LM44Y1MAINT0001

CIDS software Loading The CIDS system software loading, which is only available on ground, is done in two steps: - Step 1: Data loading from the DLCS into the OBRM (DLCS initiated action). - Step 2: Data loading from the OBRM into the respective CIDS components (FAP initiated action). Step 1: The updating of the CIDS software is done by the DLCS from the OMT or from the PMAT using a Compact Disc (CD) or Digital Video Disc (DVD) which contains the CIDS software package. Then the active director transmits this new CIDS software package transmits to the OBRM data base. During this step 1, the active director stops all other CIDS functionalities and the FAPs are not available. Moreover there is a progress and loading status message on FAPs. Step 2: The CIDS software loading from OBRM to CIDS components is done using the software loading page on FAPs. This FAP page displays the CIDS hardware and software details of : - Directors, FAP, optional MINI-FAP, Handset, DEU-B Part numbers, Serial numbers and Functional Item Number, - Active OBRM part number and software part number, - In slot OBRM part number and software part number. If the software of one or several components is different from the one stored in the OBRM database, the dedicated window goes amber. If there is no difference, the window is green. After starting the software loading process, the software, which is memorized in the OBRM, is distributed to the CIDS selected components. The active director manages this process for all components including the passive directors. MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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DATALOADING - CIDS SOFTWARE LOADING MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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DATALOADING - CIDS SOFTWARE LOADING MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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CABIN SYSTEMS MAINTENANCE (3) Specific Maintenance Items Removal/installation of the Compact Flash Cards (IPRAM, CAM, OBRM)

L1W06161 - L0KT0T0 - LM44Y1MAINT0001

The compact flash cards (I-PRAM, CAM, OBRM) can be removed either using the FAP SET-UP page on the MD FAP (it is then called Hot plug replacement) or via a standard procedure from the OMT. The hot plug replacement of the compact flash cards is only available on ground and is protected by an access code. Then press the compact flash card remove key on the FAP SET-UP page and follow the displayed instructions.



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SPECIFIC MAINTENANCE ITEMS - REMOVAL/INSTALLATION OF THE COMPACT FLASH CARDS (IPRAM, CAM, OBRM) MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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CABIN SYSTEMS OPERATION, CONTROL & INDICATING (3)

L1W06161 - L0KT0T0 - LM44O1LEVEL0301

General



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CABIN SYSTEMS OPERATION, CONTROL & INDICATING (3) FAP - General Pages

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Cabin Status



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FAP - GENERAL PAGES - CABIN STATUS MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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CABIN SYSTEMS OPERATION, CONTROL & INDICATING (3) FAP - General Pages (continued)

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System Info



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FAP - GENERAL PAGES - SYSTEM INFO MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


Apr 18, 2006 Page 65


CABIN SYSTEMS OPERATION, CONTROL & INDICATING (3) FAP - Specific Pages

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Music



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FAP - SPECIFIC PAGES - MUSIC MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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CABIN SYSTEMS OPERATION, CONTROL & INDICATING (3) FAP - Specific Pages (continued)

L1W06161 - L0KT0T0 - LM44O1LEVEL0301

Announcements



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FAP - SPECIFIC PAGES - ANNOUNCEMENTS MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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Seat Settings



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FAP - SPECIFIC PAGES - SEAT SETTINGS MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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Cabin Ready



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FAP - SPECIFIC PAGES - CABIN READY MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


Apr 18, 2006 Page 75



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IFE Power



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FAP - SPECIFIC PAGES - IFE POWER MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


Apr 18, 2006 Page 77



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Cabin Programming



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FAP - SPECIFIC PAGES - CABIN PROGRAMMING MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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Cabin Layout



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FAP - SPECIFIC PAGES - CABIN LAYOUT MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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Level Adjustment



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FAP - SPECIFIC PAGES - LEVEL ADJUSTMENT MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


Apr 18, 2006 Page 83



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Set-up



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FAP - SPECIFIC PAGES - SET-UP MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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Sofware Loading



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SOFWARE LOADING MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL III - ATA 44 Cabin Systems


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AIRBUS S.A.S. 31707 BLAGNAC cedex, FRANCE STM REFERENCE L1W06161 APRIL 2006 PRINTED IN FRANCE AIRBUS S.A.S. 2006 ALL RIGHTS RESERVED AN EADS JOINT COMPANY WITH BAE SYSTEMS

Level III - Ata 44 Cabin Systems

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