ATA 33 - Linghting

B r i t i s h A i r w a y s E n g i n e e r i n g T r a i n i n g

Your Course NotesThese notes have been prepared by BritishAirways Engineering Training to provide asource of reference during your period oftraining.

The information presented is as correct aspossible at the time of printing and is notsubject to amendment action.

They will be useful to you during yourtraining, but I must emphasise that theappropriate Approved Technical Publicationsmust always be used when you are actuallyworking on the aircraft.

I trust your stay with us will be informativeand enjoyable.

JOHN QUINLISKTraining and Quality Delivery Manager

LIGHTS

COCKPIT

Cockpit Annunciator Light Test & Dimming D/O (3) . . . . . . . . . . . . . 2

CABIN

Cabin Lights System Description (3) . . . . . . . . . . . . . . . . . . . . . . . . . 12

CABIN (Classic)

FAP Cabin Lighting Page (3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16Reading/Work Light Test Using PTP (3) . . . . . . . . . . . . . . . . . . . . . . 18

CABIN (Enhanced)

FAP Cabin Lighting Page (3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

EMERGENCY LIGHTS (Classic)

Seat & Floor Mounted Emergency Lights SYS D/O(3) . . . . . . . . . . . 30Emergency Lights Test (3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

EMERGENCY LIGHTS (Enhanced)

Seat & Floor Mounted Emergency Lights SYS D/O(3) . . . . . . . . . . . 48

MAINTENANCE COURSE - T2 (V2500-A5/ME) 33 - LIGHTS

TABLE OF CONTENTS May 11, 2006Page 1

SINGLE AISLE TECHNICAL TRAINING MANUALU

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COCKPIT ANNUNCIATOR LIGHT TEST & DIMMING D/O (3)

SYSTEM DESCRIPTION

An ANNunciator LighT test is used for the lighting of all ANN LTsmounted on the panels and instruments in the cockpit. A relay (relativeto system) or internal contacts (case of P/BSWs position indication)control the lighting of each ANN LT. Four different busbars:- AC1 supply with 103XP,- AC2 supply with 202XP,- 115 VAC STATic INVerter bus with 901XP,- ESSential supply with 801XP,supply the ANN LTs with 5 VAC-400 Hz through the transformers. Inthe case of emergency supply only busbar 901XP is serviceable.

TRANSFORMERSThere are four transformers; each is supplied with 115 V-400 Hz.Each one is connected to a different busbar.They supply:- 5 VAC-400 Hz for the ANN LTs installed on the overhead paneland on the instrument panel,- 6.3 V voltage (full wave rectified) to supply the AUTO LAND,MASTER WARNING and CAUTION lights and Audio ControlPanels (ACPs).The secondary winding of each transformer has:- 7 outputs of 5 VAC each mounted in parallel; each one is protectedby a delayed action fuse set at 4 A,- 2 outputs of 6.3 V each protected by the same type of fuse.The primary winding of each transformer has two inputs to get thecorrect dimming level (DIMmed position).If the 115 V supply is switched over to either input we obtain at thesecondary winding:- the 5 VAC (BRighT position) or 3 VAC (DIM position),- the 6.3 VAC (BRT position) or 4.3 VAC (DIM position) for rectifiedvoltages.

POWER SUPPLY AND ASSOCIATED C/BThe power supply is composed of:- busbar 103XP (AC1) which supplies transformer 37LP through thecircuit breaker 26LP located on the circuit breaker panel 122VU,- busbar 202XP (AC2) which supplies transformer 36LP through thecircuit breaker 27LP located on the circuit breaker panel 122VU,- busbar 801XP supplies transformer 31LP through the circuit breaker29LP located on the overhead panel 49VU,- busbar 801XP supplies transformer 35LP through the circuit breaker29LP and the busbar 901XP supplies emergency through the circuitbreaker 28LP located on the circuit breaker panel 122VU,- busbar 206PP supplies the ANN LT test relay coils.

COCKPIT ANN LT SWITCHA switch with 3 positions (DIM, BRT, TEST) is located on theoverhead control and indicating panel 25VU. The crew uses this switchto dim the cockpit annunciator lights or to test their operation.

ANN LT TEST AND INTERFACE BOARDSThey are located in the avionics compartment in the annunciator lighttest unit 70VU:- 4 are related to the ANN LTs supplied by the AC1 system,- 3 are related to the ANN LTs supplied by the AC2 generation,- 7 are related to the ANN LTs supplied by the ESS generation.Each board comprises:- 2 relays supplied by busbar 206PP with 28 VDC through circuitbreaker 30LP located on the rear circuit breaker panel 122VU. These2 relays are used for the ANN LT tests when the switch 33LP is inthe TEST position,- 10 relays supplied by the various A/C systems with 28 VDC. Theysupply the ANN LT with 5 VAC whereas the system data are suppliedwith 28 VDC


COCKPIT ANNUNCIATOR LIGHT TEST & DIMMING D/O (3) May 10, 2006Page 2


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FOUR-STAGES RELAYThey are located in the relay box 103VU. They are used for the testof the equipment annunciator lights (high intensity) or of otherannunciator lights (ON - OFF). The busbar 206PP supplies 28 VDCto the coil of these relays through the circuit breaker 30LP located onthe rear circuit breaker panel 122VU




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SYSTEM DESCRIPTION - TRANSFORMERS ... FOUR-STAGES RELAY




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SYSTEM OPERATION

The cockpit ANN LT SW is mainly used to test all the ANN LTs in thecockpit or to dim the ANN LTs in night conditions.

ANN LT SW IN BRT POSITIONIn this position, the lighting of the ANN LT is activated:- either if the relative system failed,- or if there is an action on the relative P/BSW (OFF position).




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SYSTEM OPERATION - ANN LT SW IN BRT POSITION




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SYSTEM OPERATION (continued)

ANN LT SW IN TEST POSITIONIn this position, the bus 206PP activates the internal coil of theinterface board. So cockpit ANN LTs are powered on all cockpitpanels.




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SYSTEM OPERATION - ANN LT SW IN TEST POSITION




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SYSTEM OPERATION (continued)

ANN LT SW IN DIM POSITIONIn this position, four-stages relays are activated and modify thetransformer voltage output in order to dim the brightness of cockpitANN LTs. The lighting of the ANN LT is activated:- either if the relative system failed,- or if there is an action on the relative P/BSW (OFF position).




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SYSTEM OPERATION - ANN LT SW IN DIM POSITION




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CABIN LIGHTS SYSTEM DESCRIPTION (3)

GENERAL

The cabin lights are controlled through the Cabin IntercommunicationData System (CIDS) which includes a Forward Attendant Panel (FAP),two directors (DIRs) one active and one in standby, and Decoder/EncoderUnits (DEUs). Some DEUs are used for the light system, they are calledtype "A" DEUs. Signals from the FAP are processed by the DIRs tocontrol the cabin lights. The DIRs transmit these signals to each DEU.

CABIN GENERAL LIGHTS

The related DEUs control the cabin fluorescent lamps according to theselection on the FAP. The FAP controls the DEUs via the CIDS DIRs togive brightness (BRT) levels which are: full or 100% BRT, 50% BRT(Dimming 1) and 10% BRT (Dimming 2) for their related window and/orceiling lights.

ENTRY LIGHTS

The related DEUs control the entry fluorescent lamps according to theFAP selection. The FAP controls the DEUs via the CIDS DIRs in orderto give BRT levels (100%, 50% or 10%).

NOTE: If the engines are running and the cockpit door is open, theCIDS directors signal the DEU of the left forward entry lightto set the intensity to 10%.

PASSENGER READING LIGHTS

The FAP controls the activation of the passenger reading lights. Therelated DEU supplies DC control power (28V DC) for individualswitching. The power unit receives 115V AC for the light operation. Thetest of the passenger reading lights is done via the DEUs, using theProgramming and Test Panel (PTP).

ATTENDANT WORK LIGHTS

The FAP controls the activation of the attendant work lights. The powerunits are installed in the overhead panels above the cabin attendant seats,and receive 115V AC for the light operation. Each power unit is connectedto a DEU of the CIDS DIRs for light test activation, using the PTP.


CABIN LIGHTS SYSTEM DESCRIPTION (3) May 10, 2006Page 12


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GENERAL ... ATTENDANT WORK LIGHTS




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CABIN LIGHTS SYSTEM DESCRIPTION (3)

CIDS ENHANCED

The cabin lights are controlled through the CIDS, via the Flight AttendantPanel (FAP). The cabin fluorescent lamps have new Advanced IntegratedBallast Units (AIBUs). The ballast units receive FAP commands for fullBRT (100%), dimming 1 (50%) and dimming 2 (10%) light BRT level.This is according to different lighting scenarios programmed in the CabinAssignment Module (CAM) flash card. The ballast units are designed toget a continuous dimming from 100% to 5% light BRT level. There isone reading light for each passenger seat. The reading lights are notadjustable because the Light Emitting Diode (LED) light diffusion angleis sufficient. Reading lights are supplied by the active CIDS DIR viaDEUs A and Passenger Interface and Supply Adapters (PISAs) installedin the Passenger Service Units (PSUs). The attendant work lights alsohave a LED technology, and are supplied by the active CIDS DIR viaDEUs A and stand alone PISAs. The test of the passenger reading lightsis done via the MCDU.

NOTE: Note: The Mean Time Between Failure (MTBF) of LED readinglights is 100,000 flight hours. Thus, there is no replacementprocedure apart from replacing the complete light assembly.Cabin signs must be replaced if three or more LEDs have failed(de-graded performance).If a full failure of the FAP and/or CIDS occurs or cabindecompression occurs, the entrance lighting comes onautomatically to 100% BRT level.




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CIDS ENHANCED




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FAP CABIN LIGHTING PAGE (3)

GENERAL

The Forward Attendant Panel (FAP) is located at the purser's station.With the FAP the various cabin systems can be controlled and monitored.It is connected to the directors (DIRs) and to the type B Decoder/EncoderUnits (DEUs). The FAP is composed of four parts:- the air conditioning panel,- the light panel,- the audio panel,- the water and miscellaneous panel.

CABIN LIGHTING

The cabin light panel comprises control keys for the various cabin lights.There are controls for the entrance areas and the different cabin sections.The MAIN ON key when pushed, switches on the cabin zones andentrance areas lighting with 100% intensity, and contrary the MAIN OFFkey when pushed, switches off the cabin zones and entrance areas lighting.The BRighTness, DIMming 1 and DIM2 keys respectively switch on thelights at 100%, 50% and 10% intensity, for the FWD, after and middle(only for A321) entrance areas. In addition, POWER LAVatory,ATTeNdant and READing keys provide the supply respectively for thelavatory lights, attendant work lights and the passenger reading lights.The WinDoW and CeiLinG keys enable respectively to control windowsand ceiling lights. Specific zone such as first class, business class ortourist class can be controlled via the FAP, the light intensity for thesezones is adjustable with the BRT, DIM1 or DIM2 key. All pushbuttons,except for MAIN ON and MAIN OFF, have integral lights for visualindication of the activated functions.


FAP CABIN LIGHTING PAGE (3) May 10, 2006Page 16


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GENERAL & CABIN LIGHTING




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READING/WORK LIGHT TEST USING PTP (3)

OPERATIONAL TEST OF THE READING/CABINATTENDANT WORK LIGHTS

JOB SET-UPThe aircraft has to be put in maintenance configuration.Energize the aircraft electrical circuits.Energize the Cabin Intercommunication Data System (CIDS), andmake sure that C/Bs listed in AMM on panels 49VU, 121VU, 122VUare closed.If you close all C/Bs in the correct sequence, the CIDS does apower-up test.On panel 2000VU, make sure that all the PASSENGER READINGLIGHT and ATTeNDant WORK C/Bs are closed.


READING/WORK LIGHT TEST USING PTP (3) May 10, 2006Page 18


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OPERATIONAL TEST OF THE READING/CABIN ATTENDANT WORK LIGHTS - JOB SET-UP




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OPERATIONAL TEST OF THE READING/CABINATTENDANT WORK LIGHTS (continued)

PROCEDURE (1/2)On the Forward Attendant Panel (FAP):- push the POWER READ and POWER ATTeNdant keys.On the FAP, the POWER READ and POWER ATTN integral lightsof the membrane switches come on.On the Programming and Test Panel (PTP):- push the DiSPLay ON key, the CIDS menu comes on.




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OPERATIONAL TEST OF THE READING/CABIN ATTENDANT WORK LIGHTS - PROCEDURE (1/2)




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PROCEDURE (2/2)On the PTP:- push the SYSTEM TEST line select key, the SYSTEM TEST menucomes on,- push CONTinuous until the READING/WORK LIGHTS displaycomes on,- push the READING/WORK LIGHTS line select key.The page ReaDingG/WORK LIGHTS TEST comes on and the WAITFOR RESPONSE display comes on and flashes. In the cabin all thecabin attendant work-lights and passenger reading lights come on forapproximately 3 s then go off.On the PTP:- a message which validate the test comes on,- push the DSPL ON key, the CIDS menu comes on.On the FAP:- push the POWER READ and POWER ATTN membrane switches,integral lights of the keys go off.




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OPERATIONAL TEST OF THE READING/CABIN ATTENDANT WORK LIGHTS - PROCEDURE (2/2)




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CLOSE-UPDe-energize the CIDS, and the aircraft electrical circuits.




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OPERATIONAL TEST OF THE READING/CABIN ATTENDANT WORK LIGHTS - CLOSE-UP




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GENERAL

The Flight Attendant Panel (FAP) is the main user interface with theCabin Intercommunication Data System (CIDS). It programs, monitorsand indicates the status of the CIDS and related cabin systems. Thefollowing system pages are available by pressing the FAP system keysor the respective aircraft symbols on the screen:- AUDIO page,- CABIN LIGHTING page,- DOORS/SLIDES page,- CABIN TEMPERATURE page,- WATER/WASTE page.

STANDARD CABIN LIGHTING CONTROL

Select Lights key on the FAP tool bar, to display the CABIN LIGHTINGpage. This page shows an aircraft symbol with the ENTRY and CLASSlighting zones. The ENTRY 1 and/or ENTRY 4 controls and displaykeys are used for the selection of FWD and aft entrance areas lighting,BRighTness (100%), DIMming 1 (50%), and DIM2 (10%). The cutting-upof the cabin is possible into 1, 2 or 3 independent zones (selection of 1zone is standard, and optional for 2 and 3 zones) such as FIRST CLASS,BUSINESS CLASS and TOURIST CLASS. To control these zones,controls and displays are available with three levels of lighting, BRT,DIM1 and DIM2. The Main On/Off key is used to switch ON/OFF cabinzone and entrance areas lighting with 100% intensity, this function isonly available on ground. The AISLE key is used to switch ON/OFF theceiling lighting, and the WinDOw key to switch ON/OFF the windowslighting. Additional functions are Reading/Light Set (on) and R/L Reset(off). An automatic DIM of the FWD entrance area is activated if thecockpit door is opened and the engines are running. In case of cabindecompression, the passenger compartment lighting automaticallyswitches to full brightness (100%).




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GENERAL & STANDARD CABIN LIGHTING CONTROL




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SCENARIO BASED LIGHTING CONTROL (OPTIONAL)

This function is used for the control of the cabin lighting throughpre-programmed scenarios. The CIDS gives up to 6 pre-programmedlighting scenarios defined in NIGHT and DAY modes for the entire cabinand/or per cabin zone. As an example, these scenarios can be used forthe different cabin services (e.g. Wake up, Sleep, Video, Dinner,...) orflight phases (e.g. Boarding, Take/Off, Landing,...). All these scenariosare assigned in the Cabin Assignment Module (CAM). The GENERALCABIN SETTINGS keys are used for the cabin lighting ON/OFF controland cabin lighting settings, the selections can be applied to individualclass zones by selecting the class Select key. Continuous dimming foreach cabin zone is possible by using "+" or "-" keys on the FAP CABINLIGHTING page. The MAINTenance key is for lavatory light fullbrightness.




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SCENARIO BASED LIGHTING CONTROL (OPTIONAL)




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SEAT & FLOOR MOUNTED EMERGENCY LIGHTS SYS D/O(3)

GENERAL

The emergency lighting system provides illumination in case of failureof the main lighting system or during emergency conditions. TheEmergency Power Supply Units (EPSUs) supply all these different lights.The emergency lights are equipped with 6V DC lamps, the lavatoryauxiliary lights are equipped with 28V DC lamps.

ELECTRICAL SUPPLY

The EPSUs are supplied with 28V DC from the ESSential SHEDdableBUS for operation and 115V AC from the NORMal BUS voltage sensing.

EPSU

The EPSUs supply the following lights:- exit location signs,- exit marking signs,- cabin emergency lights,- Floor Proximity Emergency Escape Path Marking System (FPEEPMS)lights,- wall mounted emergency exit location light,- wall mounted exit marking sign,- wall mounted emergency exit,- wall mounted emergency light,- escape slide lights,- over-wing emergency lights,- lavatory auxiliary lights,- and escape hatch-handle lights.The EPSUs also monitor the correct voltage of the AC and DC buses.The EPSUs convert 28V DC into 6V DC to operate their associated lights.An internal 6V DC battery in each EPSU is charged continuously whenthe ESS SHED BUS is energized and the system is not activated.

NOTE: The FPEEPMS is installed on the floor or on the seats (asapplicable). The system provides floor-level illumination ofthe passenger aisles and escape routes in the event that smokeobscures normal emergency lighting.


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GENERAL ... EPSU




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OPERATION

The EMERgency EXIT LighT switch on the overhead panel controls theemergency lighting system. The EMER EXIT LT switch has threepositions: OFF, ARMed and ON. Each of these positions sends a discreteground signal to the EPSUs.

OFF POSITIONIn the OFF position a ground signal prevents the emergency lightingsystem from being switched on when the AC NORM and DC ESSSHED BUS voltages are not available. The EMER EXIT LT OFFannunciator light comes on. The Batteries are no longer charged.

NOTE: Note: The EXIT signs and the emergency escapehatch-handle lights come on with EMER EXIT LT switchOFF, when the NO SMOKING switch is in ON position orin AUTO position with landing gear extended.

ARM POSITIONIn the ARM position the EMER EXIT LT OFF annunciator light goesoff. When the 115V AC NORM BUS voltage is not available, thecabin emergency lighting and the FPEEPMS lights come on. Thepower is supplied from the 28V DC/6V DC converter in thecorresponding EPSU. When the 28V DC ESS SHED BUS voltage isnot available, the batteries of all EPSUs supply the emergency lightingsystem for few minutes. The batteries are no longer charged.

ON POSITIONIn the ON position the emergency lighting system comes on, as if theLIGHT EMER P/B on the Forward Attendant Panel (FAP) was pushed.The cabin emergency lights, the exit signs, the escape hatch-handlelights and the floor proximity lights come on. The 28V DC/6V DCconverters of the EPSUs supply these loads as long as the 28V DCESS SHED BUS is available. If the 28V DC ESS SHED BUS voltage

falls below 16V, the EPSUs internal batteries continue to supply theloads for few minutes. The batteries are no longer charged.

OTHER CASESIndependently of the switch positions, the integral lights in therespective escape slides come on when the passenger/crew doors orthe emergency exit doors are opened with the escape slides armed.When the emergency exit hatches are open and the slides are released,the respective over-wing emergency lights and the integral lights inthe respective escape slide come on. In the event of excessive cabindepressurization, the exit marking signs and the exit location signsautomatically come on.

TEST

Each EPSU has a test circuit which test the condition of the battery unit,the logic unit and the related loads. This test is first performed from theProgramming and Test Panel (PTP), but if the BATtery OK or SYStemOK annunciator light does not come on, an isolated test must be performedwith the P/B located on each EPSU.




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OPERATION & TEST




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OTHER POWER SUPPLY

Depending on the emergency lighting system vendor installed in theaircraft, the emergency lighting system can be equipped with powersupply units associated to the EPSUs, which supply the FPEEPMS lightsand the wall-mounted exit marking signs.

POWER SUPPLY UNIT (6V DC)The power supply units convert 28V DC into 6V DC to operate theirassociated lights. An internal 6V DC battery supplies the loadswhenever the emergency system is not set to off and the power supplyfrom the 28V DC ESS SHED BUS is not available. The 28V DC ESSSHED BUS charges continuously the battery through the 28V DC/6VDC converter. The power supply units also monitor the correct voltageof the DC ESS SHED BUS.




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OTHER POWER SUPPLY - POWER SUPPLY UNIT (6V DC)




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OTHER POWER SUPPLY (continued)

POWER SUPPLY UNIT (115V DC)The power supply units convert 28V DC into 9.6V DC, and invert9.6V DC into 115V AC to operate their associated lights. An internal9.6V DC battery supplies the loads whenever the emergency systemis not set to off and the power supply from the 28V DC ESS SHEDBUS is not available. The 28V DC ESS SHED BUS chargescontinuously the battery through the 28V DC/6V DC converter. Thepower supply units also monitor the correct voltage of the DC ESSSHED BUS.




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OTHER POWER SUPPLY - POWER SUPPLY UNIT (115V DC)




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EMERGENCY LIGHTS TEST (3)

BATTERY CAPACITY TEST USING PTP

Before activating a test, it is necessary to set the NO SMOKING and theEMERgency EXIT LighTing switches to the OFF position. The batterycapacity test indicates the battery capacity condition of the EmergencyPower Supply Units (EPSUs). To start the test, the DiSPLay ON keymust be pressed to activate the CIDS menu. The SYSTEM TEST functionis available in order to test the battery. The SYSTEM TEST functionallows the following units to be tested on ground only:- active director (DIR),- Cabin Intercommunication Data System (CIDS) BUS,- Decoder/Encoder Unit (DEU) A,- DEU B,- Cabin Assignment Module (CAM),- Programming and Test Panel (PTP),- Forward Attendant Panel (FAP),- Additional Attendant Panel (AAP),- Attendant Indication Panel (AIP),- loudspeakers,- sign lamps,- Area Call Panels (ACPs),- passenger call lamps,- reading work lights,- emergency light battery,- drainmasts.To prevent unauthorized access it is necessary to enter a code for thebattery test. The duration of the test will be up to two hours. During thetest, it is possible to use the PTP for other functions. When the test isactivated the BATtery light in the BAT key comes on. An internal timecount is started in the CIDS DIR. If the test is OK, the BAT OK lightbeside the BAT key comes on. If there is a failure message on the PTPand if annunciator light does not come on, you have to test each EPSUwith their individual test button. When the BAT TEST RESET has been

selected, the BAT OK light and the BAT key light go off. In case of afailure, the respective result will be written into DIRs ground scanmemory.


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EPSU TEST

The test is activated by pressing the TEST P/B on the EPSU. The greenLight Emitting Diode (LED) related to SYSTEM OK comes on if all testloops are completed without malfunctions. If a failure occurs, for exampleon the cabin emergency lighting network, the red "INTERIOR LIGHTSFAULT" LED comes on.




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EPSU TEST




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EMERGENCY LIGHTING SYSTEM TEST

The system test mode, tests the emergency lighting battery and the wholeof the emergency lighting system. The system test is activated by selectingthe SYStem key at the bottom of the PTP. If the test is OK, the SYS OKlight comes on, and goes off automatically after a few seconds. If noother test or program is running on the PTP, the system test result appearson the PTP display. If a failure is present, the test result is stored in theDIR BITE ground memory.




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EMERGENCY LIGHTING SYSTEM TEST




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MAINTENANCE REPORT USING PTP

A MAINTENANCE mode within the SYSTEM STATUS mode isincluded for detailed CIDS failure description. To gain access to thismode, first press the SYSTEM STATUS key then the CONTinuous keyuntil the MAINTENANCE mode is reached. For detailed failuredescription, the MAINTENANCE mode can be entered directly bypressing the MAINTENANCE key. Failures are stored in the DIR BITEground/flight memory and can be read via this mode. The LAST LEGREPORT contains failures of the last flight leg. The PREV LEGSREPORT contains failures of the 64 previous flight legs. Flight legswithout a failure produce no entries but flight leg counting will beincremented. Both reports include the date, the time and the ATA chapterfor each failure.




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GENERAL

The emergency lighting system supplies lighting in case of failure of themain lighting system or during emergency conditions. The EmergencyPower Supply Units (EPSUs) supply all these different lights. Theemergency lights have 6V DC Light Emitting Diodes (LEDs), except forlavatory auxiliary lights (28V DC LEDs). The external emergency lightssuch as over-wing and escape slide use bulbs technology.

ELECTRICAL SUPPLY

The EPSUs are supplied with 28V DC from the ESSential SHEDdableBUS for operation and 115V AC from the NORMal BUS voltage sensing.

EPSU

The EPSUs supply the following lights:- exit signs lights,- cabin emergency lights,- seat mounted emergency lights and exit location lights,- wall mounted emergency exit location light,- wall mounted exit marking sign,- wall mounted emergency exit,- wall mounted emergency light,- escape slide lights,- over-wing emergency lights,- lavatory auxiliary lights,- and escape hatch-handle lights.The EPSUs also monitor the correct voltage of the AC and DC buses.The EPSUs convert 28V DC into 6V DC to operate their associated lights.An internal 6V DC battery in each EPSU is charged continuously whenthe ESS SHED BUS is energized and the system is not activated.




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OPERATION

The EMERgency EXIT LighT switch on the overhead panel controls theemergency lighting system. The EMER EXIT LT switch has threepositions: OFF, ARMed and ON. Each of these positions sends a discreteground signal to the EPSUs.

OFF POSITIONIn the OFF position a ground signal prevents the emergency lightingsystem from being switched on when the AC NORM and DC ESSSHED BUS voltages are not available. The EMER EXIT LT OFFannunciator light comes on. The Batteries are no longer charged.

NOTE: Note: The EXIT signs and the emergency escapehatch-handle lights come on with EMER EXIT LT switchOFF, when the NO SMOKING switch is in the ON positionor in AUTO position with landing gear extended.

ARM POSITIONIn the ARM position the EMER EXIT LT OFF annunciator light goesoff. When the 115V AC NORM BUS voltage is not available, thecabin emergency lighting and the FPEEPMS light come on. The poweris supplied from the 28V DC/6V DC converter in the related EPSU.When the 28V DC ESS SHED BUS voltage is not available, thebatteries of all EPSUs supply the emergency lighting system for fewminutes. The batteries are no longer charged.

ON POSITIONIn the ON position the emergency lighting system comes on, as if theEMERgency P/B on the Flight Attendant Panel (FAP) was pushed.The cabin emergency lights, the exit signs, the escape hatch-handlelights and the seat mounted lights come on. The 28V DC/6V DCconverters of the EPSUs supply these loads as long as the 28V DCESS SHED BUS is available. If the 28V DC SHED ESS BUS voltage

falls below 16V, the EPSUs internal batteries continue to supply theloads for few minutes. The batteries are no longer charged.

OTHER CASESIndependently of the switch positions, the integral lights in therespective escape slides come on when the passenger/crew doors orthe emergency exit doors are opened with the escape slides armed.When the emergency exit hatches are open and the slides are released,the respective over-wing emergency lights and the integral lights inthe respective escape slide come on. In the event of excessive cabindepressurization, the exit marking signs and the exit location signsautomatically come on.

TEST

Each EPSU has a test circuit which tests the condition of the battery unit,the logic unit and the related loads. This test is done first from the MCDU,but an individual test on each EPSU must be carried out when the EPSUBATtery TEST or the EPSU SYStem TEST through the MCDU fails.This isolated test starts when you push the TEST P/B on the EPSU




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AIRBUS S.A.S.31707 BLAGNAC cedex, FRANCE

STMREFERENCE U3U06191

MAY 2006PRINTED IN FRANCEAIRBUS S.A.S. 2006

ALL RIGHTS RESERVED

AN EADS JOINT COMPANYWITH BAE SYSTEMS

Documents

ATA 33 - Linghting