A320 ATA 33 L3 TECHNICAL TRAINING MANUAL
April 27, 2017 | Author: jimbokhepel | Category: N/A
Short Description
Austrian Airline A320 Family technical training manual LEVELIII...
Description
AIRBUS A318/319/320/321 CFM 56 / Level 3
Austrian Technical Training School Notes - For Training Purposes Only
LIGHTS
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This document must be used for training purpose only. Under no circumstances should this document be used as a reference. It will not be updated. All rights reserved. No part of this manual may be reproduced in any form, by photostat, microfilm, retrieval system, or any other means, without the prior written permission of AUSTRIAN AIRLINES.
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LIGHTS ............................................................................................... 1
COCKPIT LIGHTS SYSTEM ........................................................................ 8 CKPT ANNUNCIATOR LIGHT TEST & DIMMING D/O (3) ............................ 10 CABIN LIGHTS SYSTEM DESCRIPTION (3) ............................................... 20 FAP CABIN LIGHTING PAGE (3) .............................................................. 22 SEAT & FLOOR MOUNTED EMER LIGHTS SYS D/O (3) .............................. 28 Cabin Lights system description CLASSSIC (3) .......................................... 32 FAP CABIN LIGHTING PAGE CLASSIC (3) ................................................. 34 Reading/work light test using PTP CLASSIC (3)......................................... 36 SEAT & FLOOR mounted emer lights sys D/O CLASSIC (3) ........................ 44 Seat & floor mounted emer lights sys d/o CLASSIC (3) .............................. 46 Emergency lights test classic (3).............................................................. 52 Service Compartment Lights ................................................................... 62 EXTERIOR LIGHTS D/O (3) ..................................................................... 68 SAFETY PRECAUTIONS........................................................................... 84
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COCKPIT LIGHTS SYSTEM The cockpit lighting system include: 4 panel and instrument lighting, 4 general cockpit lighting (dome light), 4 ambient lighting.
COCKPIT LIGHTS CONTROL The cockpit panels and instrument lighting controls are located: 4 on three different panels, 4 and underneath the glareshield. The Captain and First Officer reading lights contain a potentiometer for brightness control and a slider for beam control. The internal light panel contains the controls for the overhead panel integral lighting, standby compass integral light, the dome lights, and the annunciator lights. Two potentiometers underneath the glareshield control the integral lighting of the glareshield and Flight Control Unit (FCU) displays. The FLOOD LT potentiometers control the flood lights of their respective areas and the INTEG LT potentiometer, the main panel and pedestal lighting. The side console light controls are on panels located on the left and right sides of the main instrument panel.
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COCKPIT LIGHTS SYSTEM - COCKPIT LIGHTS CONTROL
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CKPT ANNUNCIATOR LIGHT TEST & DIMMING D/O (3) SYSTEM DESCRIPTION An ANNunciator LighT test is used for the lighting of all ANN LTs mounted on the panels and instruments in the cockpit. A relay (relative to system) or internal contacts (case of P/BSWs position indication) control the lighting of each ANN LT. Four different busbars: 4 AC1 supply with 103XP,
correct dimming level (DIMmed position). If the 115 V supply is switched over to either input we obtain at the secondary winding: 4 the 5 VAC (BRighT position) or 3 VAC (DIM position), 4 the 6.3 VAC (BRT position) or 4.3 VAC (DIM position) for rectified voltages.
POWER SUPPLY AND ASSOCIATED C/B The power supply is composed of: 4 busbar 103XP (AC1) which supplies transformer 37LP through the circuit breaker 26LP located on the circuit breaker panel 122VU,
4 AC2 supply with 202XP, 4 115 VAC STATic INVerter bus with 901XP, 4 ESSential supply with 801XP, supply the ANN LTs with 5 VAC-400 Hz through the transformers. In the case of emergency supply only busbar 901XP is serviceable.
4 busbar 202XP (AC2) which supplies transformer 36LP through the circuit breaker 27LP located on the circuit breaker panel 122VU, 4 busbar 801XP supplies transformer 31LP through the circuit breaker 29LP located on the overhead panel 49VU,
There are four transformers; each is supplied with 115 V-400 Hz.
4 busbar 801XP supplies transformer 35LP through the circuit breaker 29LP and the busbar 901XP supplies emergency through the circuit breaker 28LP located on the circuit breaker panel 122VU,
Each one is connected to a different busbar. They supply:
4 busbar 206PP supplies the ANN LT test relay coils.
4 5 VAC-400 Hz for the ANN LTs installed on the overhead panel and on the instrument panel,
COCKPIT ANN LT SWITCH
TRANSFORMERS
4 6.3 V voltage (full wave rectified) to supply the AUTO LAND, MASTER WARNING and CAUTION lights and Audio Control Panels (ACPs). The secondary winding of each transformer has:
A switch with 3 positions (DIM, BRT, TEST) is located on the overhead control and indicating panel 25VU. The crew uses this switch to dim the cockpit annunciator lights or to test their operation.
4 7 outputs of 5 VAC each mounted in parallel; each one is protected by a delayed action fuse set at 4 A, 4 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 the
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SYSTEM DESCRIPTION - TRANSFORMERS ... FOUR-STAGES RELAY
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ANN LT TEST AND INTERFACE BOARDS They are located in the avionics compartment in the annunciator light test unit 70VU: 4 4 are related to the ANN LTs supplied by the AC1 system, 4 3 are related to the ANN LTs supplied by the AC2 generation, 4 7 are related to the ANN LTs supplied by the ESS generation. Each board comprises: 4 2 relays supplied by busbar 206PP with 28 VDC through circuit breaker 30LP located on the rear circuit breaker panel 122VU. These 2 relays are used for the ANN LT tests when the switch 33LP is in the TEST position, 4 10 relays supplied by the various A/C systems with 28 VDC. They supply the ANN LT with 5 VAC whereas the system data are supplied with 28 VDC
FOUR-STAGES RELAY They are located in the relay box 103VU. They are used for the test of the equipment annunciator lights (high intensity) or of other annunciator lights (ON - OFF). The busbar 206PP supplies 28 VDC to the coil of these relays through the circuit breaker 30LP located on the rear circuit breaker panel 122VU
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SYSTEM OPERATION The cockpit ANN LT SW is mainly used to test all the ANN LTs in the cockpit or to dim the ANN LTs in night conditions.
ANN LT SW IN BRT POSITION In this position, the lighting of the ANN LT is activated: 4 either if the relative system failed, 4 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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ANN LT SW IN TEST POSITION In this position, the bus 206PP activates the internal coil of the interface board. So cockpit ANN LTs are powered on all cockpit panels.
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SYSTEM OPERATION - ANN LT SW IN TEST POSITION
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ANN LT SW IN DIM POSITION In this position, four-stages relays are activated and modify the transformer voltage output in order to dim the brightness of cockpit ANN LTs. The lighting of the ANN LT is activated: 4 either if the relative system failed, 4 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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PASSENGER READING LIGHTS
CABIN LIGHTS SYSTEM DESCRIPTION (3) GENERAL The cabin lights are controlled through the Cabin Intercommunication Data System (CIDS), which includes the Flight Attendant Panel (FAP), two directors (DIRs) one active, one in standby, and Decoder/Encoder Units (DEUs). Some DEUs are used for the light system, they are called type "A" DEUs. Signals from the FAP are processed by the DIRs to control the cabin lights. The DIRs transmit these signals to each DEU.
CABIN GENERAL LIGHTS The related DEUs control the cabin fluorescent lamps according to the selection on the FAP. The FAP controls the DEUs via the CIDS DIRs to give brightness (BRT) levels which are: full or 100% BRT, 50% BRT (Dimming 1) and 10% BRT (Dimming 2) for their related window and/or ceiling lights. The cabin fluorescent lamps have Advanced Integrated Ballast Units (AIBUs). The ballast units receive FAP commands for full BRT, dimming 1 and dimming 2 light BRT level. This is according to different lighting scenarios programmed in the Cabin Assignment Module (CAM) flash card. The ballast units are designed to get a continuous dimming from 100% to 5% light BRT level. There is one reading light for each passenger seat.
The FAP controls the activation of the passenger reading lights. The reading lights are not adjustable because the Light Emitting Diode (LED) light diffusion angle is sufficient. Reading lights are supplied by the active CIDS DIR via DEUs A and Passenger Interface and Supply Adapters (PISAs) installed in the Passenger Service Units (PSUs).
ATTENDANT WORK LIGHTS The FAP controls the activation of the attendant work lights. The attendant work lights have a LED technology, and are supplied by the active CIDS DIR via DEUs A and stand alone PISAs. The test of the passenger reading lights is done via the MCDU. NOTE: NOTE: THE MEAN TIME BETWEEN FAILURE (MTBF) OF LED READING LIGHTS IS 100,000 FLIGHT HOURS. THUS, THERE IS NO REPLACEMENT PROCEDURE 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 CABIN DECOMPRESSION OCCURS, THE ENTRANCE LIGHTING COMES ON AUTOMATICALLY TO 100% BRT LEVEL.
ENTRY LIGHTS The related DEUs control the entry fluorescent lamps according to the FAP selection. The FAP controls the DEUs via the CIDS DIRs in order to give BRT levels (100%, 50% or 10%). NOTE: IF THE ENGINES ARE RUNNING AND THE COCKPIT DOOR IS OPEN, THE CIDS DIRECTORS SIGNAL THE DEU OF THE LEFT FORWARD ENTRY LIGHT TO SET THE INTENSITY TO 10%.
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GENERAL ... ATTENDANT WORK LIGHTS
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cockpit door is opened and the engines are running. In case of cabin decompression, the passenger compartment lighting automatically switches to full brightness (100%).
FAP CABIN LIGHTING PAGE (3) GENERAL The Flight Attendant Panel (FAP) is the main user interface with the Cabin Intercommunication Data System (CIDS). It programs, monitors and indicates the status of the CIDS and related cabin systems. The following system pages are available by pressing the FAP system keys or the respective aircraft symbols on the screen: 4 AUDIO page, 4 CABIN LIGHTING page, 4 DOORS/SLIDES page, 4 CABIN TEMPERATURE page, 4 WATER/WASTE page.
STANDARD CABIN LIGHTING CONTROL Select Lights key on the FAP tool bar, to display the CABIN LIGHTING page. This page shows an aircraft symbol with the ENTRY and CLASS lighting zones. The ENTRY 1 and/or ENTRY 4 controls and display keys are used for the selection of FWD and aft entrance areas lighting, BRighTness (100%), DIMming 1 (50%), and DIM2 (10%). The cuttingup of the cabin is possible into 1, 2 or 3 independent zones (selection of 1 zone 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 cabin zone and entrance areas lighting with 100% intensity, this function is only available on ground. The AISLE key is used to switch ON/OFF the ceiling lighting, and the WinDOw key to switch ON/OFF the windows lighting. Additional functions are Reading/Light Set (on) and R/L Reset (off). An automatic DIM of the FWD entrance area is activated if the
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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 through preprogrammed scenarios. The CIDS gives up to 6 pre-programmed lighting scenarios defined in NIGHT and DAY modes for the entire cabin and/or per cabin zone. As an example, these scenarios can be used for the different cabin services (e.g. Wake up, Sleep, Video, Dinner,...) or flight phases (e.g. Boarding, Take/Off, Landing,...). All these scenarios are assigned in the Cabin Assignment Module (CAM). The GENERAL CABIN SETTINGS keys are used for the cabin lighting ON/OFF control and cabin lighting settings, the selections can be applied to individual class zones by selecting the class Select key. Continuous dimming for each cabin zone is possible by using "+" or "-" keys on the FAP CABIN LIGHTING page. The MAINTenance key is for lavatory light full brightness.
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SCENARIO BASED LIGHTING CONTROL (OPTIONAL)
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LAVATORY LIGHTING The lavatory lighting system consists of a fluorescent lamp, an integrated ballast unit and a halogen lamp installed in each lavatory. The POWER LAV membrane switch on the FAP controls the power for the fluorescent lamps. A microswitch is installed in each lavatory door frame and controls the halogen lamp and the illumination level of the fluorescent tube. The 115VAC from the busbar 214XP supplies the fluorescent lamps through the circuit breaker 1LQ and the power control relay 2LQ. The pushbutton membrane-switch POWER LAV, on the FAP, controls the power supply for the fluorescent lamps. The system is supplied with power when the busbars are energized and the circuit breakers 1LQ, 1WJ and 11WJ are closed. When the switch POWER LAV on the forward attendant panel 120RH is pushed relay 2LQ energizes. Each lavatory ballast unit is supplied with 115VAC and the fluorescent lamp comes on with 50 % intensity. With the door microswitch in the FREE position the halogen lamp is disconnected from the 28VDC. The DIM 1 (50 %) input of the ballast unit is supplied with 28VDC. When the lavatory door is locked, the related door microswitch changes over to the ENGAGED position and the halogen lamp is supplied with 28VDC. The 28VDC is disconnected from the DIM 1 input of the ballast unit and the fluorescent lamp illuminates with 100 % intensity. All fluorescent lights go off when the membrane switch LIGHT MAIN OFF on the forward attendant panel 120RH is pushed. Other systems are also switched off with this membrane switch at the same time.
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LAVATORY LIGHT CONTROL
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SEAT & FLOOR MOUNTED EMER LIGHTS SYS D/O (3) GENERAL The emergency lighting system supplies lighting in case of failure of the main lighting system or during emergency conditions. The Emergency Power Supply Units (EPSUs) supply all these different lights. The emergency lights have 6V DC Light Emitting Diodes (LEDs), except for lavatory auxiliary lights (28V DC LEDs). The external emergency lights such as over-wing and escape slide use bulbs technology.
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 when the ESS SHED BUS is energized and the system is not activated.
ELECTRICAL SUPPLY The EPSUs are supplied with 28V DC from the ESSential SHEDdable BUS for operation and 115V AC from the NORMal BUS voltage sensing.
EPSU The EPSUs supply the following lights: 4 exit signs lights, 4 cabin emergency lights, 4 seat mounted emergency lights and exit location lights, 4 wall mounted emergency exit location light, 4 wall mounted exit marking sign, 4 wall mounted emergency exit, 4 wall mounted emergency light, 4 escape slide lights, - over-wing emergency lights, 4 lavatory auxiliary lights, 4 and escape hatch-handle lights.
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GENERAL ... EPSU
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The EMERgency EXIT LighT switch on the overhead panel controls the emergency lighting system. The EMER EXIT LT switch has three positions: OFF, ARMed and ON. Each of these positions sends a discrete ground signal to the EPSUs.
cabin emergency lights, the exit signs, the escape hatch-handle lights and the seat mounted lights come on. The 28V DC/6V DC converters of the EPSUs supply these loads as long as the 28V DC ESS SHED BUS is available. If the 28V DC SHED ESS BUS voltage falls below 16V, the EPSUs internal batteries continue to supply the loads for few minutes. The batteries are no longer charged.
OFF POSITION
OTHER CASES
OPERATION
In the OFF position a ground signal prevents the emergency lighting system from being switched on when the AC NORM and DC ESS SHED BUS voltages are not available. The EMER EXIT LT OFF annunciator light comes on. The Batteries are no longer charged. NOTE: NOTE: THE EXIT SIGNS AND THE EMERGENCY ESCAPE HATCH-HANDLE LIGHTS COME ON WITH EMER EXIT LT SWITCH OFF, WHEN THE NO SMOKING SWITCH IS IN THE ON POSITION OR IN AUTO POSITION WITH LANDING GEAR EXTENDED.
ARM POSITION In the ARM position the EMER EXIT LT OFF annunciator light goes off. When the 115V AC NORM BUS voltage is not available, the cabin emergency lighting and the FPEEPMS light come on. The power is supplied from the 28V DC/6V DC converter in the related EPSU. When the 28V DC ESS SHED BUS voltage is not available, the batteries of all EPSUs supply the emergency lighting system for few minutes. The batteries are no longer charged.
Independently of the switch positions, the integral lights in the respective escape slides come on when the passenger/crew doors or the 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 in the respective escape slide come on. In the event of excessive cabin depressurization, the exit marking signs and the exit location signs automatically 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 EPSU BATtery TEST or the EPSU SYStem TEST through the MCDU fails. This isolated test starts when you push the TEST P/B on the EPSU
ON POSITION In the ON position the emergency lighting system comes on, as if the EMERgency P/B on the Flight Attendant Panel (FAP) was pushed. The
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OPERATION & TEST
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CABIN LIGHTS SYSTEM DESCRIPTION CLASSSIC (3) GENERAL The cabin lights are controlled through the Cabin Intercommunication Data System (CIDS) which includes a Forward Attendant Panel (FAP), two directors (DIRs) one active and one in standby, and Decoder/Encoder Units (DEUs). Some DEUs are used for the light system, they are called type "A" DEUs. Signals from the FAP are processed by the DIRs to control the cabin lights. The DIRs transmit these signals to each DEU.
CABIN GENERAL LIGHTS The related DEUs control the cabin fluorescent lamps according to the selection on the FAP. The FAP controls the DEUs via the CIDS DIRs to give brightness (BRT) levels which are: full or 100% BRT, 50% BRT (Dimming 1) and 10% BRT (Dimming 2) for their related window and/or ceiling lights.
PASSENGER READING LIGHTS The FAP controls the activation of the passenger reading lights. The related DEU supplies DC control power (28V DC) for individual switching. The power unit receives 115V AC for the light operation. The test of the passenger reading lights is done via the DEUs, using the Programming and Test Panel (PTP).
ATTENDANT WORK LIGHTS The FAP controls the activation of the attendant work lights. The power units are installed in the overhead panels above the cabin attendant seats, and receive 115V AC for the light operation. Each power unit is connected to a DEU of the CIDS DIRs for light test activation, using the PTP.
ENTRY LIGHTS The related DEUs control the entry fluorescent lamps according to the FAP selection. The FAP controls the DEUs via the CIDS DIRs in order to give BRT levels (100%, 50% or 10%). NOTE: IF THE ENGINES ARE RUNNING AND THE COCKPIT DOOR IS OPEN, THE CIDS DIRECTORS SIGNAL THE DEU OF THE LEFT FORWARD ENTRY LIGHT TO SET THE INTENSITY TO 10%.
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GENERAL ... ATTENDANT WORK LIGHTS
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FAP CABIN LIGHTING PAGE CLASSIC (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/Encoder Units (DEUs). The FAP is composed of four parts: 4 the air conditioning panel, 4 the light panel, 4 the audio panel, 4 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 and entrance areas lighting with 100% intensity, and contrary the MAIN OFF key when pushed, switches off the cabin zones and entrance areas lighting. The BRighTness, DIMming 1 and DIM2 keys respectively switch on the lights 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 the lavatory lights, attendant work lights and the passenger reading lights. The WinDoW and CeiLinG keys enable respectively to control windows and ceiling lights. Specific zone such as first class, business class or tourist class can be controlled via the FAP, the light intensity for these zones is adjustable with the BRT, DIM1 or DIM2 key. All pushbuttons, except for MAIN ON and MAIN OFF, have integral lights for visual indication of the activated functions.
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GENERAL & CABIN LIGHTING
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READING/WORK LIGHT TEST USING PTP CLASSIC (3) OPERATIONAL TEST OF THE READING/CABIN ATTENDANT WORK LIGHTS JOB SET-UP The aircraft has to be put in maintenance configuration. Energize the aircraft electrical circuits. Energize the Cabin Intercommunication Data System (CIDS), and make sure that C/Bs listed in AMM on panels 49VU, 121VU, 122VU are closed. If you close all C/Bs in the correct sequence, the CIDS does a power-up test. On panel 2000VU, make sure that all the PASSENGER READING LIGHT and ATTeNDant WORK C/Bs are closed.
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OPERATIONAL TEST OF THE READING/CABIN ATTENDANT WORK LIGHTS - JOB SET-UP
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PROCEDURE (1/2) On the Forward Attendant Panel (FAP): 4 push the POWER READ and POWER ATTeNdant keys. On the FAP, the POWER READ and POWER ATTN integral lights of the membrane switches come on. On the Programming and Test Panel (PTP): 4 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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AIRBUS A318/319/320/321 CFM 56 / Level 3
Austrian Technical Training School Notes - For Training Purposes Only
PROCEDURE (2/2) On the PTP: 4 push the SYSTEM TEST line select key, the SYSTEM TEST menu comes on, 4 push CONTinuous until the READING/WORK LIGHTS display comes on, 4 push the READING/WORK LIGHTS line select key. The page ReaDingG/WORK LIGHTS TEST comes on and the WAIT FOR RESPONSE display comes on and flashes. In the cabin all the cabin attendant work-lights and passenger reading lights come on for approximately 3 s then go off. On the PTP: 4 a message which validate the test comes on, 4 push the DSPL ON key, the CIDS menu comes on. On the FAP: 4 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-UP De-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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AIRBUS A318/319/320/321
Austrian Technical Training
CFM 56 / Level 3
School Notes - For Training Purposes Only
SEAT & FLOOR MOUNTED EMER LIGHTS SYS D/O CLASSIC (3) GENERAL The emergency lighting system provides illumination in case of failure the passenger aisles and escape routes in the event that smoke of the main lighting system or during emergency conditions. The Emergency Power Supply Units (EPSUs) supply all these different lights. The emergency lights are equipped with 6V DC lamps, the lavatory auxiliary lights are equipped with 28V DC lamps.
ELECTRICAL SUPPLY The EPSUs are supplied with 28V DC from the ESSential SHEDdable BUS for operation and 115V AC from the NORMal BUS voltage sensing.
4 lavatory auxiliary lights, 4 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 when the ESS SHED BUS is energized and the system is not activated. NOTE: THE FPEEPMS IS INSTALLED ON THE FLOOR OR ON THE SEATS (AS APPLICABLE). THE SYSTEM PROVIDES FLOORLEVEL ILLUMINATION OF THE PASSENGER AISLES AND ESCAPE ROUTES IN THE EVENT THAT SMOKE OBSCURES NORMAL EMERGENCY LIGHTING.
EPSU 4 The EPSUs supply the following lights: 4 exit location signs, 4 exit marking signs, 4 cabin emergency lights, 4 Floor Proximity Emergency (FPEEPMS) lights,
Escape
Path
Marking
System
4 wall mounted emergency exit location light, 4 wall mounted exit marking sign, 4 wall mounted emergency exit, 4 wall mounted emergency light, 4 escape slide lights, - over-wing emergency lights,
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Austrian Technical Training School Notes - For Training Purposes Only
GENERAL ... EPSU
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AIRBUS A318/319/320/321 CFM 56 / Level 3
Austrian Technical Training School Notes - For Training Purposes Only
SEAT & FLOOR MOUNTED EMER LIGHTS SYS D/O CLASSIC (3)
ON POSITION
The EMERgency EXIT LighT switch on the overhead panel controls the emergency lighting system. The EMER EXIT LT switch has three positions: OFF, ARMed and ON. Each of these positions sends a discrete ground signal to the EPSUs.
In the ON position the emergency lighting system comes on, as if the LIGHT EMER P/B on the Forward Attendant Panel (FAP) was pushed. The cabin emergency lights, the exit signs, the escape hatch-handle lights and the floor proximity lights come on. The 28V DC/6V DC converters of the EPSUs supply these loads as long as the 28V DC ESS SHED BUS is available. If the 28V DC ESS SHED BUS voltage falls below 16V, the EPSUs internal batteries continue to supply the loads for few minutes. The batteries are no longer charged.
OFF POSITION
OTHER CASES
In the OFF position a ground signal prevents the emergency lighting system from being switched on when the AC NORM and DC ESS SHED BUS voltages are not available. The EMER EXIT LT OFF annunciator light comes on. The Batteries are no longer charged.
Independently of the switch positions, the integral lights in the respective escape slides come on when the passenger/crew doors or the 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 in the respective escape slide come on. In the event of excessive cabin depressurization, the exit marking signs and the exit location signs automatically come on.
OPERATION
NOTE: NOTE: THE EXIT SIGNS AND THE EMERGENCY ESCAPE HATCH-HANDLE LIGHTS COME ON WITH EMER EXIT LT SWITCH OFF, WHEN THE NO SMOKING SWITCH IS IN ON POSITION OR IN AUTO POSITION WITH LANDING GEAR EXTENDED.
ARM POSITION In the ARM position the EMER EXIT LT OFF annunciator light goes off. When the 115V AC NORM BUS voltage is not available, the cabin emergency lighting and the FPEEPMS lights come on. The power is supplied from the 28V DC/6V DC converter in the corresponding EPSU. When the 28V DC ESS SHED BUS voltage is not available, the batteries of all EPSUs supply the emergency lighting system for few minutes. The batteries are no longer charged.
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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 the Programming and Test Panel (PTP), but if the BATtery OK or SYStem OK annunciator light does not come on, an isolated test must be performed with the P/B located on each EPSU.
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OPERATION & TEST
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AIRBUS A318/319/320/321 CFM 56 / Level 3
Austrian Technical Training School Notes - For Training Purposes Only
OTHER POWER SUPPLY Depending on the emergency lighting system vendor installed in the aircraft, the emergency lighting system can be equipped with power supply units associated to the EPSUs, which supply the FPEEPMS lights and the wall-mounted exit marking signs.
POWER SUPPLY UNIT (6V DC) The power supply units convert 28V DC into 6V DC to operate their associated lights. An internal 6V DC battery supplies the loads whenever the emergency system is not set to off and the power supply from the 28V DC ESS SHED BUS is not available. The 28V DC ESS SHED BUS charges continuously the battery through the 28V DC/6V DC converter. The power supply units also monitor the correct voltage of the DC ESS SHED BUS.
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OTHER POWER SUPPLY - POWER SUPPLY UNIT (6V DC)
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POWER SUPPLY UNIT (115V DC) The power supply units convert 28V DC into 9.6V DC, and invert 9.6V DC into 115V AC to operate their associated lights. An internal 9.6V DC battery supplies the loads whenever the emergency system is not set to off and the power supply from the 28V DC ESS SHED BUS is not available. The 28V DC ESS SHED BUS charges continuously the battery through the 28V DC/6V DC converter. The power supply units also monitor the correct voltage of the DC ESS SHED BUS.
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OTHER POWER SUPPLY - POWER SUPPLY UNIT (115V DC)
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EMERGENCY LIGHTS TEST CLASSIC (3) BATTERY CAPACITY TEST USING PTP Before activating a test, it is necessary to set the NO SMOKING and the EMERgency EXIT LighTing switches to the OFF position. The battery capacity test indicates the battery capacity condition of the Emergency Power Supply Units (EPSUs). To start the test, the DiSPLay ON key must be pressed to activate the CIDS menu. The SYSTEM TEST function is available in order to test the battery. The SYSTEM TEST function allows the following units to be tested on ground only: 4 active director (DIR),
4 drainmasts. To prevent unauthorized access it is necessary to enter a code for the battery test. The duration of the test will be up to two hours. During the test, it is possible to use the PTP for other functions. When the test is activated the BATtery light in the BAT key comes on. An internal time count is started in the CIDS DIR. If the test is OK, the BAT OK light beside the BAT key comes on. If there is a failure message on the PTP and if annunciator light does not come on, you have to test each EPSU with 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 a failure, the respective result will be written into DIRs ground scan memory
4 Cabin Intercommunication Data System (CIDS) BUS, 4 Decoder/Encoder Unit (DEU) A, 4 DEU B, 4 Cabin Assignment Module (CAM), 4 Programming and Test Panel (PTP), 4 Forward Attendant Panel (FAP), 4 Additional Attendant Panel (AAP), 4 Attendant Indication Panel (AIP), 4 loudspeakers, 4 sign lamps, 4 Area Call Panels (ACPs), 4 passenger call lamps, 4 reading work lights, 4 emergency light battery,
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BATTERY CAPACITY TEST USING PTP
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THIS PAGE INTENTIONALLY LEFT BLANK
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BATTERY CAPACITY TEST USING PTP
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EPSU TEST The test is activated by pressing the TEST P/B on the EPSU. The green Light Emitting Diode (LED) related to SYSTEM OK comes on if all test loops are completed without malfunctions. If a failure occurs, for example on the cabin emergency lighting network, the red "INTERIOR LIGHTS FAULT" 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 whole of the emergency lighting system. The system test is activated by selecting the SYStem key at the bottom of the PTP. If the test is OK, the SYS OK light comes on, and goes off automatically after a few seconds. If no other test or program is running on the PTP, the system test result appears on the PTP display. If a failure is present, the test result is stored in the DIR 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 is included for detailed CIDS failure description. To gain access to this mode, first press the SYSTEM STATUS key then the CONTinuous key until the MAINTENANCE mode is reached. For detailed failure description, the MAINTENANCE mode can be entered directly by pressing the MAINTENANCE key. Failures are stored in the DIR BITE ground/flight memory and can be read via this mode. The LAST LEG REPORT contains failures of the last flight leg. The PREV LEGS REPORT contains failures of the 64 previous flight legs. Flight legs without a failure produce no entries but flight leg counting will be incremented. Both reports include the date, the time and the ATA chapter for each failure.
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Austrian Technical Training School Notes - For Training Purposes Only
MAINTENANCE REPORT USING PTP
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SERVICE COMPARTMENT LIGHTS The cargo and service compartment lighting-system provides illumination to the service area, forward and aft cargo compartment, avionics compartment and wheel wells. A maintenance outlet is installed in the air conditioning duct and accessory compartment.
SERVICE AREA LIGHTING The service area lighting comprises the lighting installation of the equipment compartment in Section 19 and the APU compartment. Electrical outlets are provided for portable maintenance lights. The lights and outlets are supplied with 28VDC.
AIR CONDITIONING DUCT AND ACCESSORY COMPARTMENT A single outlet is installed for portable maintenance light. The outlet is supplied with 28VDC.
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SERVICE AND AIR CONDITIONING DUCT LIGHTING
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FORWARD AND AFT CARGO COMPARTMENT LIGHTING The fluorescent lamps illuminate the cargo compartment. They are installed in the ceiling. A loading light is installed in each compartment. Electrical outlets are provided for portable maintenance lights. The fluorescent lamps are supplied with 115VAC, the electrical outlets and loading lights are supplied with 28VDC.
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CARGO COMPARTMENT LIGHTS
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AVIONICS COMPARTMENT LIGHTING The system comprises a number of lights and electrical maintenance outlets. The lights are supplied with 28VDC. A number of outlets are supplied with 28VDC and the remainder with 115VAC. The lights may come on automatically when an equipment bay door is opened. You can also switch them on with the control switch in the cockpit.
WHEEL WELL LIGHTING The system comprises the lighting installation of the wheel wells and the hydraulic compartment. Electrical outlets are provided in the wheel wells for maintenance purposes. A switch in the left hand wheel well controls the lights.
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AVIONICS COMPARTMENT LIGHTS
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EXTERIOR LIGHTS D/O (3) NAVIGATION LIGHTS The navigation lights have two systems, which operate independently. Each system is able to supply one set of navigation lights (RH wing-tip, LH wing-tip and tail cone). An integrated transformer for the wing tips and an external transformer for the tail cone, are linked to each lamp. The navigation lights are controlled by a three-position NAVigation & LOGO switch (OFF/1/2). 4 1: turns on the logo lights and the first set of navigation lights, 4 2: turns on the logo lights and the second set of navigation lights, 4 OFF: all lights are off.
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NAVIGATION LIGHTS
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LANDING LIGHTS One landing light underneath each wing can be extended at all A/C speeds. Each landing light has an independent extension/retraction and lighting circuit. Each landing light is controlled by a three-position LAND switch (ON/OFF/RETRACT): 4 ON, extends the left (or right) landing light, which comes on automatically when fully extended, 4 OFF, shut off landing light but leaves it extended, 4 RETRACT, retracts the landing light and shuts it off. When the landing lights are extended, the "LAND LT" memo message is displayed on the EWD.
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LANDING LIGHTS
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AIRBUS A318/319/320/321
Austrian Technical Training
CFM 56 / Level 3
School Notes - For Training Purposes Only
RUNWAY TURN-OFF LIGHTS Two runway turn-off lights are installed on the NLG. The RunWaY TURN OFF SW controls the runway turn-off lights: 4 ON: Both lights are on, only if the NLG is downlocked, 4 OFF: Both lights are off.
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RUNWAY TURN-OFF LIGHTS
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TAXI AND TAKE-OFF LIGHTS The taxi and takeoff lights are installed on the NLG, in a fixed position. The taxi and takeoff lights are controlled by the three position NOSE selector: 4 T.O: taxi and takeoff lights are on if the NLG is downlocked, 4 TAXI: taxi light is on if the NLG is downlocked, 4 OFF: all lights are off.
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TAXI AND TAKE-OFF LIGHTS
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LOGO LIGHTS The logo lights are installed in the upper surface of each Trimmable Horizontal Stabilizer (THS) to light the company logo on the vertical stabilizer if the main gear struts are compressed or the flaps are extended at least 15°. The logo lights are controlled together with the navigation lights by the NAV & LOGO SW (OFF/1/2): 4 1: turns on the logo lights and the first set of navigation lights, 4 2: turns on the logo lights and the second set of navigation lights, 4 OFF: all lights are off.
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LOGO LIGHTS
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BEACON LIGHTS Two beacon lights supply high-intensity red flashing light on the top and at the bottom of the aircraft fuselage. The beacon lights operate alternately in synchronization with the strobe lights. They are supplied and controlled through their related Power Supply Unit (PSU), if the BEACON SW (ON/OFF) is ON.
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BEACON LIGHTS
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STROBE LIGHTS Three strobe lights are installed at each wing tip and at tail cone. They are synchronized and operate alternatively with the beacon lights. They are supplied and controlled through their related PSU according to the STROBE switch position (ON/AUTO/OFF): 4 ON: the strobe lights flash white, 4 AUTO: the strobe lights come on automatically when the main gear strut is not compressed, 4 OFF: the strobe lights are off. The "STROBE LT OFF " ECAM memo message is displayed if the strobe lights are set to OFF during the flight. NOTE: THE POWER SUPPLY UNIT FOR THE TAIL CONE STROBE LIGHT IS LOCATED IN THE THS COMPARTMENT.
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STROBE LIGHTS
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WING AND ENGINE SCAN LIGHTS Two wing and engine scan lights are installed: one on each side of the fuselage. These lights light the leading edge of the wing and the engine air intake to show if ice is accumulating there. The WING switch (ON/OFF) controls these lights.
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WING AND ENGINE SCAN LIGHTS
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SAFETY PRECAUTIONS When you work on the lights system, make sure that you obey all the Aircraft maintenance Manual (AMM) safety procedures. This will prevent injury to persons and/or damage to the aircraft. Here is an overview of main safety precautions related to the lights system. Isolate the electrical circuits from the related equipment and the environment to prevent injury to persons and/or aircraft damage. Do not disconnect the electrical connections for at least two minutes after you de-energize the electrical circuits. When you change a lamp, do not touch the glass with your fingers. The oils from your skin will quickly cause deterioration of the lamp. If you accidentally touch the lamp glass, clean it with a lint-free cloth. Do not look directly towards the lights without eyes protection. Their intensity can be high enough to cause permanent damage to your eyes. Make sure that there are no signs of fuel contamination in the landing light assembly. If you find fuel contamination, no person must operate the landing light until:
Do not remove a strobe light for at least ten minutes after you deenergize the electrical circuits. The high voltage electrical current in the capacitor of the strobe light is dangerous. Do not touch the strobe lights for at least 5 minutes after operation. The strobe light will still be hot. Use gloves when removing lamps, oils from your skin can deteriorate the life of the bulbs. Be careful if you touch the strobe light with the cover removed and the power on. Some components have dangerous voltages.
4 you repair the fuel leak, 4 you replace the landing light assembly. If you do not obey this precaution, ignition of the remaining fuel in the landing light can occur. Put the safety devices and the warning notices in position before you start a task on or near: 4 the flight controls, 4 the flight control surfaces, 4 the landing gear and the related doors, 4
components that move.
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SAFETY PRECAUTIONS
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