Airbus

A318/A319/A320/A321
Differences to Revision: 1MAR2010

ATA 33
Author: PoL
For Training Purposes Only
E LTT 2007
Lights

Line and Base Maintenance

Level 3

A318-21_33_L3
Training Manual

For training purposes and internal use only.

E Copyright by Lufthansa Technical Training (LTT).
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Lufthansa Base Hamburg
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Germany

Tel: +49 (0)40 5070 2520

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Revision Identification:
S The date given in the column ”Revision” on the face of S Dates and author’s ID, which may be given at the base S The LTT production process ensures that the Training
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latest revision of that page(s) only. in the latest finalized revision.
Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
LIGHTS
33

ATA 33 LIGHTS
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 12, 2010 ATA_DOC Page 1

Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
GENERAL
33−00

33−00 LIGHTS-GENERAL
INTRODUCTION
The aircraft lighting system provides internal and external illumination.
The lighting system comprises the following subsystems :
S cockpit lights
S cabin lights
S cargo and service compartment lights
S exterior lights
S emergency lights.

Cockpit Lights (33−10)

The cockpit lighting system consists of general and instrument illumination.

Cabin Lights (33−20)

The cabin lighting system provides illumination of the entry areas, the cabin,
the lavatories, the galleys and the attendant work areas.

Cargo And Service Compartment Lights (33−30)

The cargo and service compartment lighting system provides illumination of the
cargo and service compartments. Electrical outlets are also provided for
portable maintenance light connection.

Exterior Lights (33−40)

The exterior lighting system provides illumination of runway, taxiway, logo,
engine air intake and wing leading edge for ice detection, navigation and
anti−collision lights.
FOR TRAINING PURPOSES ONLY!

Emergency Lights (33−50)

The emergency lighting system provides illumination of the cabin, and the exit
signs, if the main lighting system fails.
EPSUs (Emergency Power Supply Units) supply electrical power independently
from the aircraft power supply.

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Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
GENERAL
33−00

COCKPIT LIGHTING (33−10) CABIN LIGHTING AND SIGNS

LIGHTS SYSTEM (33−20)
FOR TRAINING PURPOSES ONLY!

CARGO& SERVICE COMP. EXTERIOR LIGHTING (33−40) EMERGENCY LIGHTING (33−50)

LIGHTING (33−30)

Figure 1 Lights General

FRA US/T-5 PoL Mar 12, 2010 01|−00|General|L1 Page 3
Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
COCKPIT LIGHTS
33−10

33−10 COCKPIT LIGHTS

COCKPIT LIGHTS-DESCRIPTION
General Reading Lights
The cockpit light system consists of: The captain and the first officer reading lights are fitted on the upright of the
S general lighting of cockpit panel, instruments and work surfaces, cockpit side windows. Supplementary reading lights are located on the
overhead panel.
S integral lighting of panels and instruments,
The CAPT and F/O reading lights swivel in order to illuminate the captain and
S test system for annunciator lights,
first officer sliding tables, the consoles and the ceiling if necessary. The
S dimming system for annunciator lights. supplementary reading lights swivel.
The light system permits to see all equipment details, all inscriptions and
indications easily, whatever the level of darkness. It is especially used at night Panel/Inst Integral Lighting
for check lists. The panel and instrument integral lighting allow the crew to read the
The cockpit light system comprises: corresponding indications during night flights or flights in stormy conditions.
S cockpit lighting: dome lights This integral lighting consists of miniature lamps supplied by AC power from
lighting controllers.
S panel and instrument lighting: flood lights and lamps
There are 3 independent controllers to supply integral lighting of
S work surface lighting: reading lights
S the overhead panel,
S console lighting: lamps
S the instrument panels, consoles and the centre pedestal.
S integral lighting of VU panels and instruments
S glareshield and FCU (Flight Control Unit).
S lighting of annunciators and pushbuttons
Each controller generates a variable low voltage current source with high
There are also two electrical outlets in the cockpit.
intensity (from 0 to 5 Volts).
DESCRIPTION
Flood Lighting
The flood lighting of captain, first officer and centre main instrument panels is
FOR TRAINING PURPOSES ONLY!

ensured by four lights, located under the glareshield.

A flood light located on the overhead panel is used to illuminate the instruments
and panels on the pedestal.
The CAPT, F/O and Centre lights illuminate only the instruments and the
placards located in four zones of the main instrument panel (CAPT, LH
CENTRE, RH CENTRE, F/O).
NOTE: In electrical emergency configuration, the lighting of the CAPT
and LH CENTRE zones remains available. The pedestal flood
light swivels towards the rear of the pedestal.

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Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
COCKPIT LIGHTS
33−10

(25 VU)

READING LT PANEL (54 VU)

FLIGHT CONTROL UNIT (FCU)

POTENTIOMETERS

EFIS CONTROL PANEL (301 VU)

FOR TRAINING PURPOSES ONLY!

LEFT FLOOD LT PANEL (111 VU) RIGHT FLOOD LT PANEL (112VU)

Figure 2 Cockpit Controls

FRA US/T-5 PoL Mar 12, 2010 02|−10|General|L2 Page 5
Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
COCKPIT LIGHTS
33−10

Dome Light System

The cockpit lighting consists of two dome lights.
Each dome light has four halogen long life lamps.
NOTE: In electrical emergency configuration, the Dome light of the F/O
side remains available, provided the dome light control is not set
to OFF.

Console Lighting
Each console, briefcase and associated floor area are illuminated.
Three lights are used for each console lighting and one for each briefcase
lighting. Four lights, fitted at the base of CAPT and F/O seats, are used for
floor lighting.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 12, 2010 03|Dome|L2 Page 6

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LIGHTS A318/A319/A320/A321
COCKPIT LIGHTS
33−10

DOME LIGHTS

READING LIGHT
AMBIENT
ILLUMINATION

SIDE CONSOLE
LIGHTS
FOR TRAINING PURPOSES ONLY!

PANEL AND INSTRUMENT BRIEFCASE

LIGHTING LIGHT

Figure 3 Cockpit Lights

FRA US/T-5 PoL Mar 12, 2010 03|Dome|L2 Page 7
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LIGHTS A319/A320/A321
COCKPIT LIGHTS
33−10

DOME LIGHTS-OPERATION
The INT LT/DOME switch 14LE with 3 positions (OFF, DIM, BRIGHT) located
on the overhead control and indicating panel 25VU controls the two dome
lights.
Each dome light has four halogen long lasting lamps.
1. Normal Operation
When the INT LT/DOME switch 14LE is in the BRT position:
S the dome light in 453VU is supplied with 28VDC from busbar 601PP
through circuit breaker 3LE on the rear C/B panel 122VU.
S the dome light in 452VU is supplied with 28VDC from essential busbar
401PP through circuit breaker 1LE on the overhead C/B panel 49VU.
When the switch is in the DIM position the light intensity decreases.
In the BRT position, the lights are supplied in parallel and in the DIM position
they are supplied in series by groups of two.
2. Emergency Lighting
If the busbar 601PP is lost, only the dome light in 452VU on the cockpit right
side remains on. It is supplied by essential busbar 401PP through circuit
breaker 1LE.
In this configuration, the 3 positions: OFF, DIM and BRT of the switch 14LE
are operational.
FOR TRAINING PURPOSES ONLY!

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LIGHTS A319/A320/A321
COCKPIT LIGHTS
33−10

165LE

25VU
14LE
OFF
DIM CAPT
167LE
28VDC 3A BRT
601PP 161LE
3LE OFF
BRT

163LE
453VU

166LE

OFF
FOR TRAINING PURPOSES ONLY!

168LE
F/O
DIM
28VDC
401PP
3A BRT 164LE
1LE

BRT
14LE
DIM
162LE
452VU

Figure 4 Dome Lights Schematic

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Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
COCKPIT LIGHTS
33−10

CONSOLE AND FLOOR LIGHTING OPERATION

Four lights are used for the lighting of each console (3 for the console itself and
1 for the briefcase).
The associated floor lighting consists of four lights fitted at the base of the
Captain and First Officer seats.

(1) Captain Console And Floor Lighting

The CONSOLE/FLOOR switch 15LE with 3 positions: OFF−DIM−BRT controls
the 28VDC supply to these lighting systems.
The switch is located on the Captain lighting/loud speaker control panel 301VU.
The normal busbar 103PP supplies the 8 lights through the circuit breaker 5LE
located on the rear circuit breaker panel 122VU.

(2) First Officer Console And Floor Lighting

The CONSOLE/FLOOR switch 16LE with 3 positions:
OFF−DIM−BRT controls the 28VDC supply to these lighting systems.
The switch is located on the F/O lighting/loud speaker control panel 500VU.
The normal busbar 204PP supplies the 8 lights through the circuit breaker 4LE
located on the rear circuit breaker panel 122VU.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 12, 2010 06|Console/Op|L3 Page 10

Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
COCKPIT LIGHTS
33−10

F/O EFIS CONTROL PANEL F/O CONSOLE

CAPTAIN EFIS CONTROL PANEL

BRT
DIM
OFF

28VDC
204PP
3A
CAPT CONOLE

4MS

BRT
DIM
16LE
OFF
FOR TRAINING PURPOSES ONLY!

103PP
28VDC 3A
W
31LE

216XP−C
1
115VAC 10A 15LE
GR
OUTLETS
601PP
28VDC 1 32LE
10A
N

Figure 5 Side Console Lights and Cockpit Outlets Schematic

FRA US/T-5 PoL Mar 12, 2010 06|Console/Op|L3 Page 11
Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
COCKPIT LIGHTS
33−10

INSTRUMENT PANEL LIGHTING AND READING LIGHTS-OPERATION

INSTRUMENT PANEL LIGHTING READING LIGHTS
Three lights 36LE (First Officer), 37LE (Captain) and 38LE (center) provide the
Captain And First Officer Reading Lights
ambient lighting of the Captain, First Officer and center main instrument
panels. The two reading lights are fitted on the upright of the side windows of the
cockpit. They swivel and illuminate the sliding tables of the Captain and First
They are installed under the glareshield and illuminate only the instruments and
Officer, the consoles and the ceiling if necessary.
the placards located on four zones of the main instrument panels:
Each reading light has:
S 2 zones at the ends of the main instrument panels, 301VU and 500VU,
S a 11.5W, 28V halogen bulb of the long lasting type (2000 hours),
S 2 zones on the center instrument panel:
S a rheostat which provides the three functions OFF − DIM − BRIGHT,
One on the left side which has the emergency equipments, one on the right
side which has items of equipment such as the landing gear control lever, S a variable diameter diaphragm to reduce or increase the lighted surface (the
clock, the landing gear control and indicating panel 402VU etc. diameter varies from 100 mm to 350 mm).
The single control dual rheostat 35LE located on the center pedestal on the NOTE: Very often this light is named incorrectly as map light,
FLOOD LT/INTEG LT panel 111VU controls these lights:
Supplementary Reading Light (First Officer)
S The first rheostat controls:
The supplementary reading light 29LE is equipped with a long lasting halogen
− The brightness of the 11.5W halogen lamps of the First Officer light
lamp and swivels. The READING LT rheostat 30LE is used to control the
36LE:
reading light brightness.
− the section of the center instrument panel light 38LE which illuminates
the right zone. The normal busbar 103PP supplies the lamps with Center Pedestal Light
28VDC through circuit breaker 2LE located on rear circuit breaker panel The center pedestal light 27LE is equipped with a 11.5W long−lasting lamp. It
122VU. swivels towards the rear of the pedestal.
S The second rheostat controls: The FLOOD LT/PED rheostat 28LE is used to control the light brightness.
− The brightness of the 11.5W halogen lamps of the Captain light 37LE
and the section of the center instrument panel light 38LE which Second Supplementary Reading Light (Captain)
illuminates the left zone (standby equipment). The installation of the second supplementary reading light 29LE in 54VU, its
FOR TRAINING PURPOSES ONLY!

power supply (103PP) and control (rheostat 30LE) are identical to those of the
first supplementary reading light.

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LIGHTS A318/A319/A320/A321
COCKPIT LIGHTS
33−10

37LE

FLOOD LT PED
38LE
35LE
401PP
28VDC 3A
1LE

103PP
3A
28VDC 2LE

25LE 36LE
29LE 30LE

3A
5LE
CPT READING LIGHT 48VU
27LE 38LE
13VU

26LE 25LE 26LE

OR OR
41LE 42LE
204PP
28VDC 3A
37LE 36LE
4LE
F/O READING LIGHT 131VU 130VU

FLOOD LT MAIN PNL

FOR TRAINING PURPOSES ONLY!

28LE 27LE

35LE 28LE

30LE 29LE

READING LT PANEL

30LE 29LE

Figure 6 Instrument Panel Lighting and Reading Lights Schematic

FRA US/T-5 PoL Mar 12, 2010 07|Inst/Read/Op.|L3 Page 13
Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
COCKPIT LIGHTS
33−10

DOME LIGHTS/READING LIGHTS-LOCATION

CENTER PEDESTAL
LIGHT C
F/O SUPPLEMENTARY
READING LIGHT B
CPT SUPPLEMENTARY
READING LIGHT
A

FCU INTEGRAL LIGHTING

B
C
FOR TRAINING PURPOSES ONLY!

CONSOLE& BRIEF CASE LIGHTS

Figure 7 Cockpit Lights Location
FRA US/T-5 PoL Mar 12, 2010 08|Light/Location|L2 Page 14
Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
COCKPIT LIGHTS
33−10

READING LIGHT READING LIGHT

CAPT VER 2 F/O VER 2

READING LIGHT READING LIGHT

CAPT F/O
CAPT

F/O
CAPT F/O
FOR TRAINING PURPOSES ONLY!

READING LIGHT VERSION 1 READING LIGHT VERSION 2

Figure 8 Reading Lights Location

FRA US/T-5 PoL Mar 12, 2010 08|Light/Location|L2 Page 15
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LIGHTS A318/A319/A320/A321
COCKPIT LIGHTS
33−10

PANEL/ INST INTEGRAL LIGHTING-OPERATION 38LE

B
The panel and instrument integral lighting allow the crew to read the LIGHT-MAIN
corresponding indications during night flights or flights in stormy conditions. INSTRUMENT PANEL
This integral lighting consists of miniature lamps supplied by AC power from
lighting controllers. C FR24
There are 3 independent controllers to supply integral lighting of A
S the overhead panel,
S the instrument panels, consoles and the centre pedestal. D
S glareshield and FCU (Flight Control Unit). A
Each controller generates a variable low voltage current source with high intensity (from E
0 to 5 Volts).
E
30LF
A
6LF
16LF
F2
F1 F3
F1 F2 F3

F5
F4 F6

D C B
FOR TRAINING PURPOSES ONLY!

2FN
17LF PANEL 25VU
PANEL 111VU

7LF 2LF

Figure 9 Panel Integral Lighting Comp. Location

FRA US/T-5 PoL Mar 12, 2010 09|Integral|L3 Page 16

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LIGHTS A318/A319/A320/A321
COCKPIT LIGHTS
33−10

MAIN INSTR.PANEL
103XP-C & PED INST. LT INTEGRAL
115VAC LIGHTING MAIN INST
4LF CONTROLLER PANEL & PEDESTAL
5LF
OFF BRT

17LF
INTEGRAL
3LF LIGHTING
CONTROLLER
OVHD PANEL

16LF
111VU

OFF BRT GLARESHIELD

LIGHT CONTROL
ALTERNATE
7LF
CONFIGURATION

OVERHEAD
GLARESHIELD
PANEL

25VU
6LF 20VU
FOR TRAINING PURPOSES ONLY!

1LF 2LF 2FN

13VU
INTEGRAL
28VDC 38LE LIGHTING
25VU CONTROLLER
STBY COMPASS

LIGHT-MAIN
INSTRUMENT PANEL
30LF

Figure 10 Panel Integral Lighting Schematic

FRA US/T-5 PoL Mar 12, 2010 09|Integral|L3 Page 17
Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
COCKPIT LIGHTS
33−10

ANNUNCIATOR LIGHT TEST AND DIMMING-DESCRIPTION TEST

A
BRT B
DIM
General 206PP
TEST 37LP
Bulbs supplied with 5VAC−400Hz are used for the lighting of the sun readable

TRANSFORMER
30LP BRT
lights in the cockpit. The current is delivered by the 115V/5V transformers.

SYS 1
DIM 33LP
Each light is parted in two sections; each one has two 5V bulbs. 28V DC

An annunciator light test switch permits illumination of all annunciators and 103XP
therefore check of all lights.
26LP 38LP C
Switch 33LP 115V AC
A switch with 3 positions: DIM, BRT, TEST is located on the overhead control
and indicating panel 25VU. 36LP

TRANSFORMER
System Description

SYS 2
Miniature lamps (115 mA, 5VAC) are used for the lighting of the annunciator
lights mounted on the panels and instruments in the cockpit. 202XP
A relay (system) or internal contacts (case of ON−OFF position indication 27LP
39LP D
pushbutton switches) control illumination of each annunciator light. Four 115V AC
different busbars:
S AC1 supply: 103XP

SYS ESS
35LP

TRANSFORMER
S AC2 supply: 202XP
S 115VAC STAT INV BUS: 901XP
S Essential supply: 801XP 901XP
supply the annunciator lights with 5VAC−400Hz through the transformers. In 28LP
the case of emergency supply only busbar 901XP is serviceable. 115V AC
42LP E

The system comprises 40LP

S Four Identical Transformers
FOR TRAINING PURPOSES ONLY!

SYS ESS
S Five Circuit Breakers 31LP

TRANSFORMER
S Switch 33LP
S Fourteen Annunciator Light Test and Interface Boards
801XP
S Four−Stage Relays
29LP F
41LP
115V AC

Figure 11 Annunciator Light Test & Dimming Schematic

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LIGHTS A318/A319/A320/A321
COCKPIT LIGHTS
33−10

35 LP 31 LP

ANN. LIGHT TEST

AND INTERFACE
BOARD (TYPICAL)

37LP
FOR TRAINING PURPOSES ONLY!

36LP

SYS (25 VU)

TRANSFORMERS

Figure 12 Annunciater Light Test & Dimming-Location

FRA US/T-5 PoL Mar 12, 2010 10|Annu/Test/Dim|L2 Page 19
Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
COCKPIT LIGHTS
33−10

SPARE BULB BOX AND ANN. LIGHT LOCATION

EATON
58T−101
OR
ECE OUT74 851−30486−510
(EX MSC 584−901)
− THESE TOOLS ARE USED
TO REMOVE THE HEAD.

EATON
58T−108
ECE OUT75 OR ECE OUT217
851−30486−506
(EX MSC 584−501)

− THESE TOOLS ARE

OUT217
A SCREWDRIVER GUIDE.

ECE OUT87−1 (BLUE) OR POWELL DUFFRYN TLS022

+ AM DP27478 SP 0,3 X 3 OR ECE OUT87−2 (RED)
FOR TRAINING PURPOSES ONLY!

− THESE DYNAMOMETRIC
SCREWDRIVERS ARE USED TO
EATON 58T−106 OR 851−30486−508 (EX MSC 584−510) INSTALL PUSHBUTTON BODY.

Figure 13 Switch and Indicator Light Tools

FRA US/T-5 PoL Mar 12, 2010 10|Annu/Test/Dim|L2 Page 20

Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
COCKPIT LIGHTS
33−10

LOCKING CAMS

YELLOW BAND
SIDE

LOCKING CAM SCREWS RETRACTED EXTENDED

AA (BACK OFF) (TURN IN)
BB
B

A
SCREWDRIVER
BLADE WIDTH 3 mm
(NO SPECIFIC)
MOUNTING BASE
B
MOUNTING SLEEVE

SPACER

YELLOW BAND
FOR TRAINING PURPOSES ONLY!

F2 HOLES OF BODY
STOP ON EACH SIDE
OF TOOL
EXTRACTION TOOL
SPARE BULB BOX OUT 74 OR OUT 86

Figure 14 Spare Bulb Box and Ann. Lt. Removal/Installation

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LIGHTS A318/A319/A320/A321
COCKPIT LIGHTS
33−10

ANNUNCIATOR LIGHT TEST AND DIMMING-OPERATION

General S Four Identical Transformers
One adjustment light selector serves to test and to adjust the brightness of all They are supplied with 115V−400Hz.
annunciator lights. Each one is connected to a different busbar.
S TEST They supply 5VAC−400Hz for the annunciator lights installed on the
All annunciator lights illuminate. All LCDs (Liquid Crystal Displays) indicate overhead panel and on the instrument panel and 4.3V / 6.3V current (full
”eight”. On PFD (Primary Flight Display), ND (Navigation Display) and wave rectified) to supply the AUTO LAND, MASTER WARNING and
ECAM all flags appear. CAUTION lights and ACP (Audio Control Panels).
S BRT The secondary winding of each transformer has:
Full intensity. − seven 3V / 5VAC outputs mounted in parallel ; each one is protected by
S DIM a delayed action quick removable fuse set at 4A,
The annunciator light power supply voltage is reduced. − two 4.3V / 6.3V outputs protected by the same type of quick removable
fuse.
Lamps supplied with 5VAC−400Hz are used for the lighting of the sun readable
lights in the cockpit. The current is delivered by the 115/5VAC transformers. The primary winding of each transformer has two inputs to get the correct
Each light is divided in two sections; each one has two 5V lamps. An dimming level (DIM position).
annunciator light test permits illumination of all annunciators and therefore If the 115V supply is switched over to either input the secondary winding
check of the operation of all lights. delivers:
− the 5VAC,or
Supply
− the 3VAC for alternating voltages,
Four different busbars:
− the 6.3VAC or 4.3VAC for rectified voltages.
S SYS 1 supply: 103XP,
These four transformers are in the cockpit.
S SYS 2 supply: 202XP,
S Ann. Light Test and Interface Board (14 Places in 70 VU)
S Essential supply: 901XP,
Each board contains 10 relays for the annunciator light control and one test
S Essential supply: 801XP,
relay.
supply the annunciator lights with 5VAC−400Hz through the transformers. In
FOR TRAINING PURPOSES ONLY!

The location of 70 VU is in the mid right avionics compartment.

the case of emergency supply only the busbar 901XP is serviceable. The
system comprises:
S Four Stage Relays
They are located on removable cards in the box 70VU(mid, right avionics
compartment). They are used for the test of the annunciator lights on the
equipment (high intensity).The busbar 206PP supplies 28VDC to the coil of
these relays through the circuit breaker 30LP located on the circuit breaker
panel 122VU and through the switch 33LP in the TEST position.

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Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
COCKPIT LIGHTS
33−10
FOR TRAINING PURPOSES ONLY!

31LP

Figure 15 Annunciator Lights Test and Dimming Schematic

FRA US/T-5 PoL Mar 12, 2010 11|Test/Dim|L3 Page 23
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LIGHTS A319/A320/A321
CABIN LIGHTS
33−20

33−20 CABIN LIGHTS

CABIN LIGHTS-DESCRIPTION
General Lavatory Lighting
The cabin lighting system illuminates the cabin, the entrances, the lavatories, The lavatory lights are installed above each lavatory door.
the galley and the attendant work areas. A microswitch, installed at each lavatory door controls the brightness of the
The system has these sub−systems: lavatory lighting system and the indication signs.
S General Illumination (Ref. 33−21−00)
Passenger Reading And Cabin Attendant Work Lights
S Call System (Ref. 33−23−00)
The passenger reading and cabin attendant work lights are high intensity lights.
S Lavatory Lighting (Ref. 33−24−00)
Attendant work lights are installed at each attendant station.
S Passenger Reading Lights (Ref. 33−25−00)
Each passenger seat is provided with a reading light installed in the PSU
S Lavatory Lighted Signs (Ref. 33−26−00) (Passenger Service Unit).
S Cabin Attendant Work−Lights (Ref. 33−27−00).
Passenger Lighted Signs
NOTE: The Call System and the lighted signs NO SMOKING, FASTEN
There are four passenger lighted signs:
SEAT BELT and RETURN TO SEAT (NS/FSB/RTS) are part of
the CIDS (Cabin Intercommunication Data System) S The LAVATORY OCCUPIED sign
(Ref. 23−73−00) S The FASTEN SEAT BELT sign
S The NO SMOKING sign
Cabin General Illumination
S The RETURN TO SEAT sign.
The general illumination consists of fluorescent tubes installed in the hatracks
and the ceiling panels. In each cabin zone the four strips are divided into two
groups for control purposes.
Group I: Lighting strips on the outer side of the lateral hatracks (WINDOW
LIGHTS).
FOR TRAINING PURPOSES ONLY!

Group II: Lighting strips in the ceiling panels (inboard side) (CEILING LIGHTS).
The entry areas illumination consists of fluorescent tubes installed on the
entrance area ceiling panels.
The cabin attendants control the general illumination through the FAP (Forward
Attendant Panel) and the AAP (Additional Attendant Panel(s)), which are part
of the CIDS

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Lufthansa Technical Training
LIGHTS A319/A320/A321
CABIN LIGHTS
33−20

AFT ATTENDANT
PANEL

FWD PURSER STATION

PASSENGER
COMPARTMENT LIGHTING FWD ATTENDANT PANEL (FAP)
PROGRAMMING AND TEST PANEL

WINDOW CEILING READING PASSENGER

FOR TRAINING PURPOSES ONLY!

LIGHTS LIGHTS LIGHTS SIGNS

PASSENGER AND
ATTENDANT GALLEY LAVATORY LIGHTS
LIGHTS LAVATORY
WORK LIGHTS AND SIGNS
CALL LIGHTS

ENTRY
LIGHTS

Figure 16 Cabin Lights General

FRA US/T-5 PoL Mar 12, 2010 12|−20Cabin/Gen.|L1 Page 25
Lufthansa Technical Training
LIGHTS A319/A320/A321
CABIN LIGHTS
33−20

CABIN LIGHTS SYSTEM-DESCRIPTION

General Attendant Work Lights
The cabin lights are controlled through the CIDS (Cabin Intercommunication The FAP controls the activation of the attendant work lights. The power units
Data System) which includes a FAP (Forward Attendant Panel), two directors are installed in the overhead panels above the cabin attendant seats, and
(DIRs) one active and one in standby, and DEUs (Decoder/Encoder Units). receive 115V AC for the light operation. Each power unit is connected to a
Some DEUs are used for the light system, they are called type ”A” DEUs. DEU of the CIDS DIRs for light test activation, using the PTP.
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.

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%.
Passenger Reading Lights
There is one light for each passenger seat. Each passenger reading light is
controlled with an integrated pushbutton.
The FAP controls the activation of the passenger reading lights. The related
FOR TRAINING PURPOSES ONLY!

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 PTP (Programming and Test Panel).

FRA US/T-5 PoL Mar 12, 2010 13|sys Descr|L2 Page 26

Lufthansa Technical Training
LIGHTS A319/A320/A321
CABIN LIGHTS
33−20

CABIN AND ENTRY

115V AC FLUORESCENT LAMP

CONTROL (x3)

PASSENGER
115V AC READING LIGHTS

TOP LINES

ATTENDANT
FOR TRAINING PURPOSES ONLY!

115V AC WORK LIGHTS

FAP: FORWARD ATTENDANT PANEL

CIDS CABIN INTERCOMMUNICATION DATA SYS.
DEU: DECODER/ENCODER UNIT
PTP: PROGRAMMING AND TEST PANEL

Figure 17 Attendant Work Lights

FRA US/T-5 PoL Mar 12, 2010 13|sys Descr|L2 Page 27
Lufthansa Technical Training
LIGHTS A319/A320/A321
CABIN LIGHTS
33−20

CABIN LIGHTS LOCATION

FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 12, 2010 14|Location|L2 Page 28

Lufthansa Technical Training
LIGHTS A319/A320/A321
CABIN LIGHTS
33−20

A A
A, B A, B

LAMPHOLDER B
15 WATT LIGHT UNIT

BALLAST UNIT

WINDOW LIGHT A, B

FLUORESCENT
LAMP

A
30 WATT LIGHT UNIT

BALLAST UNIT PASSENGER READING LIGHTS

CONNECTOR
FOR TRAINING PURPOSES ONLY!

FLUORESCENT
LAMP

CEILING LIGHTS A
Figure 18 Cabin Lights Location
FRA US/T-5 PoL Mar 12, 2010 14|Location|L2 Page 29
Lufthansa Technical Training
LIGHTS A319/A320/A321
CABIN LIGHTS
33−20

FAP (CABIN LIGHTING PANEL) & PTP DESCRIPTION

FORWARD ATTENDANT PANEL
General
The FAP (Forward Attendant Panel) 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 DEUs (Decoder/Encoder
Units). The FAP is composed of four parts:
S the air conditioning panel,
S the light panel,
S the audio panel,
S 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, AFT and MID (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
FOR TRAINING PURPOSES ONLY!

ON and MAIN OFF, have integral lights for visual indication of the activated
functions.
Programming Test Panel (PTP)
The PTP is located next to the FAP. It is equipped with a CAM which contains
all the software of customer specific layouts.
The PTP is used for the reprogramming of lights related cabin items and a test
of the emergency lights system.
The TEST EMER LIGHT SYS switch, on the PTP, starts a test procedure of
the complete emergency light system

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Lufthansa Technical Training
LIGHTS A319/A320/A321
CABIN LIGHTS
33−20

ENTRY
POWER
FWD MID AFT FC BC YC

MAIN LAV
FWD PURSER STATION ON
BRT BRT BRT BRT WDO BRT WDO

DIM 1 DIM 1 DIM 1 DIM 1 DIM 1 DIM 1 CLG ATTN

RDL
MAIN DECOR
DIM 2 DIM 2 DIM 2 DIM 2 DIM 2 DIM 2 MAN READ
OFF LIGHT HOLD
FOR TRAINING PURPOSES ONLY!

120RH FORWARD ATTENDANT PANEL

PROGRAMMING AND TEST PANEL

Figure 19 FAP & PTP Location

FRA US/T-5 PoL Mar 12, 2010 15|FAP&PTP−Descr|L2 Page 31
Lufthansa Technical Training
LIGHTS A319/A320/A321
CABIN LIGHTS
33−20

CABIN LIGHT-OPERATION
Cabin Illumination
The cabin lamps are distributed in four strips throughout the cabin zones.The WDO − With the cabin lighting set on at any intensity. On pushing this
four strips in each cabin zone are divided into two pairs for control purposes. membrane switch, the window lights in each cabin zone and the light under the
The two outboard strips are designated as WINDOW (WDO) lights and the two membrane switch foil go off. Pushing the membrane switch again will cause the
center strips as CEILING (CLG) lights. The system is designed so that the lights to come on.
window and ceiling lights in each cabin zone can be on together or separately. CLG − With the cabin lighting set on at any intensity. On pushing this
When on, the fluorescent lamps can be selected to 100 % (BRT), 50 % (DIM 1) membrane switch, the ceiling lights in each cabin zone and the light under the
or 10 % (DIM 2) intensity. Each fluorescent lamp is installed in a holder which membrane switch foil go off. Pushing the membrane switch again will cause the
contains an integral ballast unit. The units are supplied with 115VAC from lights to come on.
busbars 212XP and 214XP through circuit breakers 300LG thru 307LG (cabin
Operation/Control and Indication
lighting) and 308LG (entrance lighting). The lighting system is controlled from
the forward attendant panel 120RH and the aft attendant panel 126RH, which The forward attendant panel 120RH and the aft attendant panel 126RH are
contains the following membrane switches: connected to the Directors 101RH and 102RH of the CIDS (Cabin
Intercommunication Data System).The input signals from the forward attendant
Forward Attendant Panel (FAP) panel 120RH and the aft attendant panel 126RH are processed by the director
MAIN ON when pushed, switches on the cabin zones and entrance areas and transmitted to the Decoder/Encoder Units (DEUs). The DEUs accept the
input data and activate the output to the fluorescent lamps with ballast units in
lighting with 100 % intensity. It also causes the integral light in all
accordance with the code presented at the input. The DEU is capable of
BRT, WDO and CLG membrane switches to come on.
handling up to four fluorescent lamps with ballast units. Three signal lines
MAIN OFF when pushed, the cabin zones and entrance area lights goes off connect each fluorescent lamp with ballast unit to the related DEU. The DEU
Also any light of the general illumination switch goes off. This output signal has two levels 0 (0VDC) and 1 (28VDC). As can be seen in the
function is disabled in flight. schematic with no output signal from the associated DEU the fluorescent lamps
ENTRY FWD BRT and ENTRY AFT BRT − when initially pushed, causes the will illuminate at full brightness.
related entrance area lighting to come on with 100 % intensity, The entrance lighting has fluorescent lamps with ballast units installed in the
ENTRY FWD DIM1 and ENTRY AFT DIM1 with 50 %,intensity and ceiling panels at the forward and aft entrances. Two fluorescent lamps are
installed in the LH and RH ceiling panels at each entrance. The operation is the
ENTRY FWD DIM2 and ENTRY AFT DIM2 with 10 % intensity.
same as the cabin lighting.
It also causes the integral light under the membrane switch foil to come on.
FOR TRAINING PURPOSES ONLY!

1. The entrance lighting at entrance 1 LH is automatically dimmed to DIM2

The lights may be switched off by pushing the membrane switch twice in
level (10%) whenever the cockpit door is opened with the engines running.
succession.
2. The CIDS directors 101RH and 102RH receive one signal from the engine
FWD BRT and AFT BRT − when initially pushed, causes the related cabin
oil−pressure system and another signal from the cockpit door microswitch.
zone lighting to come on with 100 % intensity,
The directors 101RH and 102RH transmit their output signal to the DEU which
FWD DIM1 and AFT DIM1 come on with with 50 % intensity and
controls the entrance 1 LH fluorescent lamp with ballast unit.The DEU provides
FWD DIM2 and AFT DIM2 come on with with 10 % intensity. a DIM2 signal and the light dims to 10% intensity.
It also causes the integral lights in the related BRT, WDO and CLG membrane
switch to come on. The lights may be switched off by pushing the membrane
switch twice in succession.

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Lufthansa Technical Training
LIGHTS A319/A320/A321
CABIN LIGHTS
33−20

OFF
DIM-1
DIM-2
212XP−A
307LG TO ADDITIONAL FLUORESCENT LAMP
CEILING 310LG COCKPIT BALLAST UNIT
DOOR SWITCH FLUORESCENT
AFT LH LAMPS/BALLAST
300LG
WINDOW OIL DOOR UNITS

DIM 2
DIM 1
FWD RH PRESS OPEN WINDOW FWD LH

OFF
SYSTEM
212XP−B
301LG
WINDOW
TO
AFT RH CIDS DIRECTOR DEU ADDITIONAL
1+2
DEUS
212XP−C
306LG CEILING
TO FLUORESCENT LAMPS/BALLAST UNITS, CEILING FWD LH
NORMAL BUS 115V AC

FWD LH

MAIN FC YC CALL
214XP−A ENTRY BC
ON BRT BRT BRT BRT RESET
302LG
WINDOW ENTRY FC BC YC
LAV
AFT LH DIM 1 DIM 1 DIM 1 DIM 1 WATER
HEAT

214XP−B MAIN
ENTRY FC BC YC

305LG
CEILING OFF DI M 2 DI M 2 DI M 2 DI M 2

FWD RH
308LG
ENTRY 126RH AFT ATTENDANT PANEL
AREA
FOR TRAINING PURPOSES ONLY!

ENTRY
214XP−C FWD MID AFT FC BC YC POWER
303LG WINDOW
FWD LH MAIN BRT BRT BRT BRT BRT BRT WDO LAV
ON
304LG
CEILING DIM 1 DIM 1 DIM 1 DIM 1 DIM 1 DIM 1 CLG ATTN
AFT RH
MAIN DECOR RDL
OFF DIM 2 DIM 2 DIM 2 DIM 2 DIM 2 DIM 2 MAN READ
LIGHT HOLD

120RH FORWARD ATTENDANT PANEL

Figure 20 Cabin Lights Block Diagram
FRA US/T-5 PoL Mar 12, 2010 16|Operation|L3 Page 33
Lufthansa Technical Training
LIGHTS A319/A320/A321
LAVATORY LIGHTING
33−24

33−24 LAVATORY LIGHTING

LAVATORY LIGHTING-DESCRIPTION
General
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 forward attendant panel 120RH
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.

System Description
The lavatory lighting system has:
S a fluorescent lamp with a ballast unit installed above the lavatory door in
each lavatory.
S a halogen lamp installed adjacent to the lavatory mirror in each lavatory.
S a microswitch installed at each lavatory door frame. The microswitch is part
of the lavatory lighted signs system (Ref. 33−26−00).
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 12, 2010 17|−24Lav−Desc|L2 Page 34

Lufthansa Technical Training
LIGHTS A319/A320/A321
LAVATORY LIGHTING
33−24

ENTRY
FWD MID AFT FC BC YC POWER

MAIN BRT BRT BRT BRT BRT BRT WDO LAV

ON

DIM 1 DIM 1 DIM 1 DIM 1 DIM 1 DIM 1 CLG ATTN

RDL
MAIN DIM 2 DIM 2 DIM 2 DIM 2 DIM 2 DIM 2 DECOR
LIGHT MAN READ
OFF HOLD

120RH FORWARD ATTENDANT PANEL

CIRCUIT BREAKER
PANEL

A FLUORESCENT
LAMP AND
HALOGEN LAMP BALLAST UNIT

B
A MICROSWITCH
FOR TRAINING PURPOSES ONLY!

LAVATORY A

Figure 21 Lavatory Lighting

FRA US/T-5 PoL Mar 12, 2010 17|−24Lav−Desc|L2 Page 35
Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
LAVATORY LIGHTING
33−24

LAVATORY LIGHTING OPERATION

SYSTEM OPERATION
Power Supply
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 forward attendant panel 120RH,
controls the power supply for the fluorescent lamps.
The 28VDC from the busbar 208PP supplies the lavatory occupied signs and
auxiliary lights through the circuit breakers 1WJ, 11WJ and the door
microswitches.
Operation
The system is supplied with power when the busbars are energized and the
circuit breakers 1LQ, 1WJ and 11WJ are closed. 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 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.
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.
The integral light under the POWER LAV membrane switch foil (on the forward
attendant panel 120RH) comes on when the membrane switch is initially
pushed.
FOR TRAINING PURPOSES ONLY!

When the membrane switch is pushed again, the fluorescent lamps in the
lavatory go off. Also the integral light under the POWER LAV membrane switch
foil goes off.
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.

FRA US/T-5 PoL Mar 12, 2010 18|Lav−Oper|L3 Page 36

Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
LAVATORY LIGHTING
33−24

LIGHT LAVATORY A

4
7
8
2

1
DIM 1

OFF
B
4
HALOGEN LAMP
115VAC 3 C/B LAV or
H

FLUORESCENT

UNSD
SVCE BUS 2 3

GND
D G
LAVATORY MAIN 45
LAMP AND

A
OFF F 2 E BALLAST UNIT

1
CIDS
LIGHTS DIRECTOR
5
A US
MICROSWITCH
MAIN
E 1 E
4 B
LAVATORY LAV
ON/OFF MAINTENANCE MAINT SCH01
A US

RAZOR SOCKET
MINI INVERTER
43
SCH07 D PSU LAV.A
A
RH1 A3 A L C/B
DEU−A A1 A2
UNSD
B3
LTG/EMER LT/
FLIGHT ATTENDANT PANEL (FAP)
B1 B2 PAX COMP 3 4
X1
A X2 3
A
AUX LT
RELAY LAVATORY A 28VDC
ESS BUS 1 2

MIRROR LT

FREE

ENGAGED 1+
EXAMPLE LAVATORY
FOR TRAINING PURPOSES ONLY!

NC
NO
C GREEN OCCUPIED SIGN
3+
MICRO ,
LAVATORY A 8 GND
2− RED
5VAC
A 7 9
10
A 45 4
OCCPD
5 J SIGN-OCCPD
21 A UNSD UNSD
28VDC
BUS 2
5 A 6
TOILET
LAVATORY A
C/B SCH20
6WJ
LAVATORY FWD
OCCUPIED LP BOARD−ANN ANN−TOILET/OCCPD
LT TEST & INTFC OVERHEAD PANEL

Figure 22 Lavatory Lighting Schematic

FRA US/T-5 PoL Mar 12, 2010 18|Lav−Oper|L3 Page 37
Lufthansa Technical Training
LIGHTS A319/A320/A321
PASSENGER READING LIGHTS
33−25

33−25 PASSENGER READING LIGHTS

PASSENGER READING LIGHTS-OPERATION
System Description
The reading lights are installed in the combi−panels. The combi−panels are
installed in the PSUs (Passenger Service Units) channel above the passenger
seats. The number of combi−panels on each side of the cabin must agree with
the number of seat rows.
Power Supply
115VAC is supplied to the reading lights from the busbars 110XP and 210XP.
This is controlled through the circuit breakers 1LW thru 6LW and the relays
7LW and 8LW.
The power units change the 115VAC to 6VAC for the light operation on classic
aircraft types. On enhanced systems the PISA (Passenger interface Supply
Adapter) changes the 115VAC into 28VDC. A fuse in each line gives protection
for the transformer and the related PCB (Printed Circuit Board). A membrane
switch POWER READ on the FAP (Forward Attendant Panel) 120RH controls
the power supply for the reading lights.
Operation
When the POWER READ membrane switch on the FAP 120RH is pushed, the
power units 511RH and 512RH are activated. The coils of the relays 7LW and
8LW in the panel 2000VU are energized. This closes the contacts of the relays
and 115VAC is supplied to the power units.
When the reading−light membrane switches 501RH thru 503RH are pushed, a
ground pulse is supplied to the voltage control circuit. This completes the
FOR TRAINING PURPOSES ONLY!

primary circuit of the step−down transformer. The transformer changes the

115VAC down to 6VAC which causes the lights to come on.
A test of the reading lights, the work lights and the PCB circuits is made by the
related BITE test on the PTP(Programming and Test Panel) 110RH. In this test
all reading lights and work lights come on for approximately 3 s and then go off.
After the test the PTP 110RH shows the status of the reading lights, the work
lights and the PCBs.

FRA US/T-5 PoL Mar 12, 2010 19|−25Read−Oper|L3 Page 38

Lufthansa Technical Training
LIGHTS A319/A320/A321
PASSENGER READING LIGHTS
33−25

210XP 7LW FROM DIRECTOR DATA BUS DEU’A’ 200RH

TO ADDITIONAL
1LW READING LIGHTS 503RH
A
2LW ABOVE RIGHT
B SEATS 502RH
3LW 526RH 524RH 522RH
C 501RH
115VAC
6 VAC

LAMP 3
LAMP 2
LAMP 1

LAMP FAIL
LOCKED

PCB FAIL
2000VU CIRCUIT

TEST
BREAKER PANEL IC11
IC12

VOLTAGE
CONTROL

6 VAC

VOLTAGE LAMP FAIL

IC4 CONTROL
FWD ATTD PANEL CONTROL
503RH CIRCUIT
120RH
POWER 6 VAC
502RH
525RH 523RH 521RH
READ MAIN MAIN
ON OFF 501RH PCB FAIL
VOLTAGE IC4 CONTROL
FOR TRAINING PURPOSES ONLY!

CONTROL CIRCUIT
110XP

512RH POWER UNIT

4LW 511RH POWER UNIT
A TO ADDITIONAL
5LW READING LIGHTS
B ABOVE LEFT SEATS
6LW
8LW DEU’A’
C
FROM DIRECTOR DATA BUS 200RH

Figure 23 Passenger Reading Lights Schematic

FRA US/T-5 PoL Mar 12, 2010 19|−25Read−Oper|L3 Page 39
Lufthansa Technical Training
LIGHTS A319/A320/A321
CABIN LIGHTS
33−20

BITE/TEST FUNCTION ON THE PTP

READING/WORK LIGHT
General
A test of the reading lights, the work lights and the PCB circuits is made by the
related BITE test on the PTP (Programming and Test Panel) 110RH. In this
test all reading lights and work lights come on for approximately 3 s and then
go off. After the test the PTP 110RH shows the status of the reading lights, the
work lights and the PCBs.
The test of the reading lights includes the test of the Attendant work lights, the
decoration lights (option) and the related reading light power unit (each power
unit can drive three separate lights).
Before activation of the test, the pushbuttons POWER ATTN and POWER
READ on the FWD ATTND PNL have to be pressed to energize the
reading/work light system. If not, a SWITCH ON POWER message will be
displayed on the PTP.
Failure Test
In case of failure, the respective result will appear on the PTP display and will
be written into the Director class 3 Fault-memory.
After the test, the Reading/work light system is still energized to give the
maintenance crew the possibility for visual check of the lamps.
FOR TRAINING PURPOSES ONLY!

PROGRAMMING AND TEST PANEL

Figure 24 PTP (Programming and Test Panel)

FRA US/T-5 PoL Mar 12, 2010 20|Read/WorkTest|L2 Page 40

Lufthansa Technical Training
LIGHTS A319/A320/A321
CABIN LIGHTS
33−20

PROGRAMMING AND TEST PANEL

CIDS RDG/WORK LIGHTS

SYSTEM TEST
READING/WORK LIGHTS
DIR 1 (ACT) RESET ATA 23−73−00
SYSTEM STATUS EMER LIGHT BATTERY
DIR 2 TEST OK
SYSTEM TEST DRAINMASTS
CONT
FOR TRAINING PURPOSES ONLY!

PROGRAMMING RET CONT RET

Figure 25 PTP-Reading Light Test

FRA US/T-5 PoL Mar 12, 2010 20|Read/WorkTest|L2 Page 41
Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
CARGO AND SERVICE COMPARTMENTS
33−30

33−30 CARGO AND SERVICE COMPARTMENTS

INTRODUCTION
General
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.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 12, 2010 21|33−30|Intro|L1 Page 42

Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
CARGO AND SERVICE COMPARTMENTS
33−30
FOR TRAINING PURPOSES ONLY!

FORWARD CARGO AVIONICS BAY

Figure 26 Cargo and Service Compartment Lights

FRA US/T-5 PoL Mar 12, 2010 21|33−30|Intro|L1 Page 43
Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
CARGO AND SERVICE COMPARTMENTS
33−30

33−30 CARGO AND SERVICE

COMPARTMENTS
AVIONICS COMPARTMENT LIGHTING-DESCRIPTION
General
To help servicing and maintenance operations, some of the compartments are
equipped with lighting facilities.
The lighting system comprises lamps, fluorescent tubes, control switches and
electrical outlets used for portable maintenance lights.

AVIONICS COMPARTMENT LIGHTING

The avionics compartment lighting system consists of a number of lights and
maintenance outlets. The busbar 601PP supplies the five maintenance outlets
with 28 VDC through circuit breaker 11LS. The busbar 216XP supplies the
three maintenance outlets with 115 VAC through circuit breaker 12LS. The
outlets are located in the forward and aft parts of the avionics compartment.
Six dome lights provide the illumination of the avionics compartment.
The busbar 601PP supplies the lights with 28 VDC through circuit breaker 1LS
and relays 24LS and 25LS. The relay 24LS controls the power supply to the
lateral L, aft L and R dome lights. The relay 25LS controls the power supply to
the lateral R, forward L and R dome lights. The door proximity switches
transmit the ground signal to relays 24LS and 25LS.
Auto Mode
When the service door in zone 125 or zone 128 is open, the associated
proximity switch removes the ground for relay 24LS. Relay 24LS de−energizes
FOR TRAINING PURPOSES ONLY!

and the L lateral, L and R aft dome lights come on.

When the service door in zone 120 or zone 126 is open, the associated
proximity switch removes the ground for relay 25LS. Relay 25LS de−energizes
and the R lateral, L and R forward dome lights come on.

Manual Mode
When the pushbutton switch 23LS is pressed, the two relays 24LS and 25LS
de−energize and the avionics compartment lights come on. The integral light in
the pushbutton switch comes on.
Figure 27 Avionics Comp. Sw. Location

FRA US/T-5 PoL Mar 12, 2010 22|Avionics Comp|L2 Page 44

Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
CARGO AND SERVICE COMPARTMENTS
33−30

AVIONICS COMPARTMENT
LIGHTING
50VU

AVIONICS
COMPT LT
A
U TO ADDITIONAL
T
ON
O DOME LIGHTS
6LS
25LS 7LS
8LS

206PP
1LS
AUTO DOME LIGHT
ON
PROXIMITY SWITCHES
DOORS CLOSED
NORMAL
23LS
BUS
28V DC AVIONICS BAY (DOME LIGHT)
9LS
10LS
22LS

ADDITIONAL DOME LIGHTS

FOR TRAINING PURPOSES ONLY!

24LS 17LSOUTLETS
212XP
18LS
12LS
TO ADDITIONAL 19LS

DOME LIGHT SERVICE

13LS AVIONICS COMPARTMENT BUS 2
14LS
OUTLETS 115V AC
15LS 601PP
16LS
11LS
20LS

ADDITIONAL SERVICE
OUTLETS BUS
28V DC

Figure 28 Avionics Compartment Lights

FRA US/T-5 PoL Mar 12, 2010 22|Avionics Comp|L2 Page 45
Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
CARGO AND SERVICE COMPARTMENTS
33−30

WHEEL WELL LIGHTING−DESCRIPTION

General
The wheel well lighting−system has the lighting of the main wheel wells and the
hydraulic compartment. For maintenance practices an electrical outlet is
installed at the front wheel well and in the hydraulic compartment.

Wheel Well Lighting

One dome light is installed in each of the main−wheel well compartments. Two
dome lights are installed in the hydraulic compartments LH and RH. The
busbar 202PP supplies 28 V DC to all four lights through the circuit breaker
2LL and the control switch 12LL. An outlet 3LL is provided in the nosewheel
well for maintenance purposes. Another outlet 4LL is provided in the hydraulic
compartment, adjacent to the control switch 12LL, on panel 2025VU. When the
control switch is placed to the ON position, all lights come on.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 12, 2010 23|Wheel Well|L2 Page 46

Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
CARGO AND SERVICE COMPARTMENTS
33−30

WHEEL WELL LIGHT

LIGHT 7LL
8LL
206PP
28VDC HYDRAULIC COMPARTMENT LIGHT
1LL BUS 2
206PP
28VDC
BUS 2 2LL

12LL

9LL
10LL

4LL 3LL
FOR TRAINING PURPOSES ONLY!

WHEEL WELL

Figure 29 Wheel Well Compartment Lights

FRA US/T-5 PoL Mar 12, 2010 23|Wheel Well|L2 Page 47
Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
CARGO AND SERVICE COMPARTMENTS
33−30

SERVICE&CARGO COMPARTMENT LIGHTING-DESCRIPTION

Service Area Lighting
The service area lighting system comprises the lights installed in the APU
compartment and in Section 19. Electrical outlets are provided for portable
maintenance lights.
The lights and outlets are supplied with 28 V DC from busbar 208PP through
the circuit breakers 2LJ and 1LJ. Switch 11LJ controls the APU light 6LJ and
switch 3LJ controls the two lights 4LJ and 5LJ in Section 19. When busbar
208PP is energized and the circuit breaker 1LJ is closed, power is available at
the two maintenance outlets in Section 19. 208PP

2LJ 6LJ
Air−conditioning and Accessory Compartment Lighting APU LIGHT
The air conditioning compartment is provided with a 28 VDC outlet for a
portable maintenance light. 11LJ

28V DC
Cargo Compartment Lighting NORMAL
Forward, aft and bulk cargo compartments are lit by fluorescent tubes. Lighting BUS

is also available at the forward and aft loading areas.

The fluorescent tubes are installed in the ceilings of the FWD, AFT and BULK
cargo compartments. They are controlled by three switches, located close to
the doors.
Each loading area light is controlled by a switch, located close to the cargo
door. The loading area light is bracket mounted and its direction can be 208PP 4LJ
adjusted. 5LJ 8LJ
1LJ TO SERVICE 10LJ
AREA LIGHT

28V DC
FOR TRAINING PURPOSES ONLY!

NORMAL 3LJ
BUS

208PP

1LK

28V DC
NORMAL
BUS
2LK

Figure 30 Service Area Lighting

FRA US/T-5 PoL Mar 12, 2010 24|Cargo/Service|L2 Page 48

Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
CARGO AND SERVICE COMPARTMENTS
33−30

TO ADDITIONAL
LIGHTS
214XPA
1LU
13LU
SVCE 14LU
BUS 6LU
115V AC
FORWARD CEILING LIGHT
LOADING AREA LIGHT FORWARD CARGO
602PP COMPARTMENT
3LU
11LU

7LU
SERVICE
BUS
28V DC

214XPB TO ADDITIONAL
2LU
LIGHTS 15LU
16LU
8LU

SERVICE
BUS CEILING LIGHT
115V AC TO ADDITIONAL AFT CARGO
LIGHTS COMPARTMENT

18LU 17LU
FOR TRAINING PURPOSES ONLY!

AFT CEILING LIGHT

LOADING AREA LIGHT AFT CARGO
12LU COMPARTMENT
602PP
3LU

9LU
SERVICE
BUS
28V DC
CARGO LOADING LIGHT
Figure 31 Cargo Compartment Lights
FRA US/T-5 PoL Mar 12, 2010 24|Cargo/Service|L2 Page 49
Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
EXTERIOR LIGHTS
33−40

33−40 EXTERIOR LIGHTS NOSE TO.

GENERAL NOSE TAXI

The exterior lighting system fulfils various functions:
S illuminating the runway and taxiway
RWY TURN-OFF
S illuminating the wing leading edges and engine air intakes
S indicating the aircraft position and direction LAND
S reducing collision risk in flight and on ground.

BEACON

WING
STROBE

EXT LT PANEL (25VU)

NAV
FOR TRAINING PURPOSES ONLY!

LOGO

STROBE/NAV
Figure 32 EXT Light Panel
Figure 33 Exterior Lights-General

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Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
EXTERIOR LIGHTS
33−40
FOR TRAINING PURPOSES ONLY!

STROBE LIGHT

NAVIGATION LIGHTS

Figure 34 Exterior Lights-Component Location

FRA US/T-5 PoL Mar 12, 2010 25|−40Exterior|L1 Page 51
Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
EXTERIOR LIGHTS
33−40

TAXI AND TAKE OFF LIGHTS-DESCRIPTION

General 8LR LT−TAXI
RELAY 6LR
The taxi and take−off light system illuminates the runway during the taxi and
the take off phase. Two light units provide the lighting. They are installed on the 204XP 1LR
nose landing gear. BUS 2
115VAC
System Description
The taxi and take−off light system consists of:
S a single filament light (or halogen lamp in alternate solution) 8LR, rated at
450 Watts, installed on the nose landing gear in a fixed position,
S a transformer, to produce rated operating voltage,
S a single filament light (or halogen lamp in alternate solution) 7LR, rated at T.O.
600 Watts, installed on the nose landing gear in a fixed position, TAXI
OFF
S a transformer, to produce rated operating voltage,
S two power supply relays 5LR for the takeoff and 6LR for the taxi light, 202PP
2LR
GROUND WHEN
S a switch 4LR, on the cockpit overhead panel. NOSE WHEEL
BUS 2
28VDC LOCKED DOWN
The 115 VAC busbar 204XP supplies power to the taxi light through the circuit
breaker 1LR and relay 6LR. The 115 VAC busbar 103XP supplies power to the 5GA2 LGCIU 2
take off light through the circuit breaker 3LR and relay 5LR. The 28 VDC SWITCH 4LR
busbar 202PP supplies power to the switch 4LR through the circuit breaker
2LR. The landing−gear computer supplies the power supply relays 5LR and
6LR with a ground signal when the nose landing gear is downlocked.
Operation
With energized busbars and closed circuit breakers, 115 VAC is supplied to the 7LR LT−TAKE OFF
contacts of the power relays. The control switch is supplied with 28 VDC. When
FOR TRAINING PURPOSES ONLY!

the nose landing gear is downlocked, the power supply relays get a ground 3LR
103XP
signal. When the control switch 4LR is in the TAXI position, the relay 6LR
BUS 1
energizes and the taxi light 8LR comes on. 115VAC
With the switch 4LR in the T.O position, the relay 5LR energizes and continues
to energize the relay 6LR. The taxi light 8LR and the take off light 7LR come
RELAY 5LR
on. When the nose landing gear is unlocked, the ground signal for the power
supply relays is removed.
The take off light and the taxi light go off. You can also switch off the lights with
the switch 4LR in the OFF position.
Figure 35 Taxi&Take-off Lights-Schematic

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Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
EXTERIOR LIGHTS
33−40

NOSE TO.

NOSE TAXI

RWY TURN-OFF

EXT LT PANEL (25VU)

TAXI AND TAKE-OFF LIGHTS

The taxi and take-off lights illuminate the runway during the take-off phase.
There is one taxi and one take-off light installed on the nose landing gear in
a fixed position.
NOTE: The power supply of the lights is only provided when the nose
landing gear is downlocked

RUNWAY TURN OFF LIGHTS

FOR TRAINING PURPOSES ONLY!

The runway turn off lights illuminate the lateral areas of the runway.
Two turn off lights are installed on the nose landing gear in a fixed position.
NOTE: The power supply of the lights is only provided when the nose
landing gear is downlocked

Figure 36 Exterior Lights: Taxi/Take−off,Runway Turn Off

FRA US/T-5 PoL Mar 12, 2010 26|Taxi/Light|L2 Page 53
Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
EXTERIOR LIGHTS
33−40

WING & ENGINE SCAN LIGHTS DESCRIPTION

General
Two lights are installed, one on each side of the forward fuselage. They
illuminate the engine air intakes and the wing leading edges. It is possible to
examine these areas in flight; for example, to determine the build up of ice.
The toggle switch 2LX controls the lights.

Description
The wing and engine scan light system has two lights 3LX and 4LX with a
fixed single filament. The lights are installed one on each side in the forward
fuselage of the aircraft. An attached transformer gives the rated operation
voltage to each light. Electrical power comes from the 115 VAC busbars 202XP
and 103XP through the circuit breakers 1LX and 5LX.

Operation
The switch 2LX is supplied with 115 VAC when:
S the busbars 202XP and 103XP are energized,
S the circuit breakers 1LX and 5LX are closed.
The wing and engine scan lights come on when the switch 2LX is in the ON
position.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 12, 2010 27|ENG Scan/Light|L2 Page 54

Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
EXTERIOR LIGHTS
33−40

WING&ENGINE SCAN LIGHTS

The wing and engine scan lights illuminate the wing leading edge and the
engine nacelle on each side of the aircraft fuselage. These areas can be
examined in flight or on the ground.
There is one light installed on each side in the forward fuselage.

EXT LT PANEL (25VU)

WING
ON
LH SHOWN
RH SIMILAR
103XP−C
115VAC
OFF
5LX
FOR TRAINING PURPOSES ONLY!

3LX
202XP−C L WING AND ENGINE
115VAC SCAN LIGHT
1LX
TO R WING AND ENGINE
SCAN LIGHT
4LX
2LX

Figure 37 External Lights: Wing and Engine Scan

FRA US/T-5 PoL Mar 12, 2010 27|ENG Scan/Light|L2 Page 55
Lufthansa Technical Training
LIGHTS A319/A320/A321
EXTERIOR LIGHTS
33−40

NAV&LOGO LIGHTS-DESCRIPTION VERSION 1

NAVIGATION LIGHTS With the switch 3LA set to OFF:
The Navigation Light system gives an external, visual indication of the position S the relay 6LA is de−energized
of the aircraft and its direction of flight. S the lamps go off.
A forward−facing light is installed at the edge of each wing tip. When the towing tractor is connected it supplies 115V AC through:
A rearward−facing light is installed on the tail cone below the Auxiliary Power S the electrical box 5GC,
Unit (APU) exhaust.
S the closed contacts in the relay 6LA to the step−down transformer in the
System Description wingtip navigation light assemblies 9LA(10LA),
A forward−facing navigation light assembly is installed at the leading edge of S the closed contact in the relay 6LA to the step−down transformer 13LA.
each wing tip. A rearward−facing navigation light assembly is installed on the The step−down transformers in the wing−tip navigation light assemblies supply
tail cone, below the APU exhaust. Each light assembly has a different colored 12.15V AC to the lights. The lamps come on.
lens: The step−down transformer 13LA supplies 12V AC to the tail navigation light.
S the left wing−tip navigation light has a red lens The lamp comes on. When the towing tractor is disconnected the lamps go off.
S the right wing−tip navigation light has a green lens
LOGO LIGHTS
S the tail navigation light has a clear lens.
The logo lights 4LY and 5LY are installed on the horizontal stabilizer in the
The navigation lights are controlled by the toggle switch 3LA which is installed zones 334 and 344. Each logo light consists of a housing which contains the
on the overhead panel 25VU in the cockpit. The switch has two positions, lamp assembly and a step−down transformer. The step−down transformer
which are identified NAV & LOGO ON/OFF lower the aircraft’s 115VAC to 28VAC power supply.
Operation/Control and Indicating The toggle switch ’NAV/LOGO’ 3LA, installed on the cockpit overhead panel
25VU, controls the logo lights together with the navigation lights.
With the switch 3LA set to ON, the 115V AC SERVICE BUS 2, 216XP supplies
power through: The toggle switch has an ON and OFF position.
S the circuit breaker 1LA When you set the toggle switch 3LA to the ON position the logo lights come on
automatically during taxiing, take-off and landing.
S the switch 3LA (to energize the relay 6LA)
With the switch NAV & LOGO (3LA) set to ON,115 V AC is supplied to the
S the relay 6LA to the step−down transformers of the wing−tip navigation light
FOR TRAINING PURPOSES ONLY!

relay 6LA. When the flaps are lowered to 15 degrees or more, or the
assemblies 9LA(10LA)
landing−gear struts are compressed, a ground signal is received. This
S the relay 6LA to the step−down transformer 13LA. energizes the coil of the relay 5LY. Power is then supplied to the step−down
The step−down transformers in the wing−tip navigation light assemblies supply transformer of the light assemblies. From these transformers a decreased
12.15V AC to the lights. The lamps come on. voltage of 28 V DC is supplied to the logo lights 3LY (4LY) which causes the
The step−down transformer 13LA supplies 12V AC to the tail navigation light. logo lights to go on.
The lamp comes on. When the landing−gear is retracted, and the flaps are retracted to less than 15
degrees, the ground signal is removed. In this condition, the logo lights go out.
Also, with the switch NAV & LOGO (3LA) set to OFF, the relay 6LA is
de−energized which causes the logo lights to go out.

FRA US/T-5 PoL Mar 12, 2010 28|Nav/Logo−Vers1|L2 Page 56

Lufthansa Technical Training
LIGHTS A319/A320/A321
EXTERIOR LIGHTS
33−40

5GC ELEC BOX−

N/W STEERING
DEACTIVATION
LH SHOWN 115VAC
RH SIMILAR TRACTOR
28VDC
POWER
TO LH LOGO
LIGHT 3LY

RH LOGO
LIGHT 4LY EXT LT PANEL (25VU) VERSION 2
LANDING GEAR SLATS FLAPS
CONTROL AND CONTROL
202XP−A INTERFACE UNIT COMPUTERS
115VAC
1LY 5GA2 21CV
22CV

2LY

101XP−A
115VAC 5LY

1LA

216XP−C
STROBE
9LA (10LA)
115VAC
WING TIP
6LA NAVIGATION LIGHT
FOR TRAINING PURPOSES ONLY!

3LA LH SHOWN
2LR RH SIMILAR NAV
202PP
103VU
28VDC
LOGO
TO WING TIP
NAVIGATION LIGHT 10LA
15LA
13LA TAIL NAVIGATION LIGHT STROBE/NAV
NAV & LOGO SWITCH
TRANSFORMER (ONE LAMP)
Figure 38 Nav&Logo Lights Schematic Vers. 1
FRA US/T-5 PoL Mar 12, 2010 28|Nav/Logo−Vers1|L2 Page 57
Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
EXTERIOR LIGHTS
33−40

NAV & LOGO LIGHTS-DESCRIPTION VERSION 2

NAVIGATION LIGHTS VERSION LOGO LIGHTS DESCRIPTION VERSION
The Navigation Light system gives an external, visual indication of the position
Operation/Control and Indicating
of the aircraft and its direction of flight.
The logo lights 4LY and 5LY are installed on the horizontal stabilizer . Each
System Description logo light consists of a housing which contains the lamp assembly and a
A forward−facing navigation light assembly is installed at the leading edge of step−down transformer. The step−down transformer lower the aircraft’s
each wing tip. A rearward−facing navigation light assembly is installed on the 115VAC to 28VAC power supply.
tail cone, below the APU exhaust. Each light assembly has a different colored The toggle switch ’NAV/LOGO’, installed on the cockpit overhead panel 25VU,
lens: controls the logo lights together with the navigation lights.
S the left wing−tip navigation light 9LA has two lamps and a red lens The toggle switch has the positions 2, 1 and OFF.
S the right wing−tip navigation light 10LA has two lamps and a green lens When you set the toggle switch 3LA to the 1 (2) position the logo lights come
S the tail navigation light 15LA has two lamps and a clear lens. on automatically with the NAV1 (NAV2) lights during taxiing, take off and
landing.
The navigation lights are controlled by the toggle switch 3LA which is installed
on the overhead panel 25VU in the cockpit. The switch has three positions, Operation
which are identified NAV & LOGO 2/1/OFF.
115 V AC is supplied to each logo light from the normal busbars 101XP and
Operation/Control and Indicating 202XP. This is controlled through the circuit breakers 1LY and 2LY.
With the switch 3LA set to position 1, the 115V AC SERVICE BUS 2, 216XP With the switch NAV & LOGO (3LA) set to 1 or 2, 115V AC is supplied to the
supplies power through: relays 6LA and 7LA. When the flaps are lowered to 15 degrees or more, or the
landing−gear struts are compressed, a ground signal is received. This
S the circuit breaker 1LY
energizes the coil of the relay 5LY. Power is then supplied to the step−down
S the switch 3LA (to energize the relay 6LA) transformer of the light assemblies. From these transformers a decreased
S the relay 6LA to the step−down transformers of the related navigation lights. voltage of 28V AC is supplied to the logo lights which causes the logo lights to
The step−down transformers in the wing−tip navigation light assemblies supply go on.
28V AC to the related lamp. The lamp comes on. When the landing−gear is retracted, and the flaps are retracted to less than 15
Each step−down transformer in the step−down transformer assembly 13LA degrees, the ground signal is removed. In this condition, the logo lights go out.
FOR TRAINING PURPOSES ONLY!

supplies 12V AC to its related tail navigation light. The lamp comes on. With Also, with the switch 3LA set to OFF, the relays 6LA and 7LA are
the switch 3LA set to position 2, the operation is almost the same, but this time de−energized which causes the logo lights to go out.
the power is supplied through the circuit breaker 2LA and the relay 7LA.
With the switch 3LA set to OFF:
S the relays 6LA and 7LA are de−energized
S the lamps go off.

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Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
EXTERIOR LIGHTS
33−40

LH SHOWN
RH SIMILAR
2
1
LOGO LIGHT

TO LOGO LIGHT

LANDING GEAR SLATS FLAPS EXT LT PANEL (25VU) VERSION 2

CONTROL AND CONTROL
INTERFACE UNIT COMPUTERS
202XP−A 5GA2 21CV
22CV
115VAC
1LY

2LY

101XP−A
5LY
115VAC
1LY
STROBE
2LA
9LA (10LA)

WING TIP
216XP−C NAVIGATION LIGHT
6LA
FOR TRAINING PURPOSES ONLY!

115VAC LH SHOWN
3LA RH SIMILAR NAV
2LR

202PP
28VDC LOGO
2
7LA
1 103VU 15LA
TO WING TIP STROBE/NAV
NAVIGATION LIGHT 10LA 13LA TAIL NAVIGATION LIGHT
NAV & LOGO SWITCH TRANSFORMER (TWO LAMPS)
Figure 39 Nav&Logo Lights Schematics Vers.2
FRA US/T-5 PoL Mar 12, 2010 29|Nav/Logo−Vers2|L2 Page 59
Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
EXTERIOR LIGHTS
33−40

ANTICOLLISION LIGHTS DESCRIPTION

ANTICOLLISION LIGHTS
General The strobe light system operates, when the ”STROBE ON−AUTO−OFF”
The aircraft recognition lighting system is designed as a visual aid to other control switch (11LV), located on the overhead panel 25VU, is in the
aircraft, so reducing the possibility of a collision. ”ON/AUTO” position. This causes the power supply units (14LV), (15LV) and
(18LV) to energize and supply the two strobe lights (16LV) and (17LV) on each
The system consists of:
wing tip and the strobe light (19LV) on the tailcone with power.
S an anti−collision light providing a high−intensity red flashing light on the top
If a malfunction should occur at the high−intensity strobe lights (white) or their
and on the bottom of the aircraft fuselage.
power supply units, this does not have an affect of the function of the fuselage
S a strobe light providing a high−intensity white flashing light. One light is anti−collision light (red).
installed in each wing tip facing forward and one is installed in the tailcone,
below the APU exhaust, facing rearwards.
Description
Two anticollision/beacon lights are installed, 7LV on the top and 6LV on the
bottom of the aircraft fuselage. The anticollision/beacon lights are high intensity
red discharge lamps. Each lamp is supplied from an individual power unit. The
anticollision/beacon lights flash at approx. 60 flashes per minute, when the
BEACON switch 2LV is in the ON position.
Three strobe lights are installed, two at each wing tip on the leading edges
16LV and 17LV and one on the tail cone 19LV. The strobe lights are high
intensity white lights synchronized to operate alternately with the
anticollision/beacon light. The forward facing strobe lights flash at approx. 120
flashes per minute and the rearward facing strobe light flashes at approx. 60
flashes per minute. This occurs when the STROBE switch 11LV is either in the EXT LT PANEL (25VU)
ON or AUTO position.
BEACON sw
Operation This switch turns on and off the two flashing red lights, one on top and
FOR TRAINING PURPOSES ONLY!

The aircraft recognition lighting system consists of two independent systems one on the bottom of the fuselage.
which are designed to operate alternately in synchronization:
STROBE sw
S the anti−collision light system and
This switch turns on and off the three synchronized strobe lights, one
S the strobe light system. on each wing tip and one below the tail cone.
The anti−collision/beacon light system operates, when the ”BEACON ON: The strobe lights flash white.
ON−OFF” control switch (2LV), located on the overhead panel 25VU, is in the
AUTO: The strobe lights come on automatically when the main gear
”ON” position. This causes the power supply units (3LV) and (4LV) to energize
strut is not compressed.
and supply the upper and lower anti−collision lights/beacon lights (6LV) and
(7LV) with power. OFF : The strobe light are off.
Figure 40 Strobe & Beacon Light Switches

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Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
EXTERIOR LIGHTS
33−40

101XP
115VAC 1LV FR16
103VU
A
B
RELAY BOX
ANTICOLLISION/BEACON LIGHTS
C
EXAMPLE
UPPER
FR1
BEACON
8LV POWER
2LV SUPPLY 7LV UPPER
UNIT
BEACON BEACON
ON 3LV LIGHT
202XP LOWER
115VAC 5LV BEACON
OFF POWER 6LV
A
SUPPLY
B UNIT LOWER BEACON LIGHT
C 4LV
ANTICOLLISION/STROBE LIGHTS
202XP 9LV
R WING EXAMPLE
115VAC 10LV TIP
A STROBE
LIGHT
B BEACON
POWER
16LV
C SUPPLY
UNIT
14LV R WING TIP STROBE LIGHT
28VDC 12LV L WING STROBE
TIP
FOR TRAINING PURPOSES ONLY!

STROBE
LIGHT 17LV
LANDING POWER
GEAR 11LV SUPPLY L WING TIP
CONTROL UNIT STROBE LIGHT
AND 13LV 15LV
INTERFACE STROBE
ON TAIL CONE
UNIT STROBE
A LIGHT
U 103LV 19LV
5GA2 T POWER
O SUPPLY
OFF UNIT TAIL CONE
STROBE LIGHT STROBE/NAV
18LV

Figure 41 Anticollision & Strobe Lights Schematic

FRA US/T-5 PoL Mar 12, 2010 30|Strobe/Beac−Light|L2 Page 61
Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
EXTERIOR LIGHTS
33−40

LANDING LIGHT DESCRIPTION

General
Two retractable landing lights are installed on the bottom of the wings. The
lights operate through maximum operating speeds (VMo).
The landing light system provides lighting to illuminate the runway when the
aircraft lands at night. Two landing lights 7LB and 8LB are installed one on the
underside of each wing. Each light has a separate control switch 5LB and 6LB.
They can be extended at all aircraft speeds.

System Description
The left−hand (LH) landing light 7LB and the right−hand (RH) landing light 8LB
are installed on the bottom of the LH and RH wings. Each landing light has an
independent extension/retraction and illumination circuit. Two toggle switches,
LAND L 5LB and LAND R 6LB, control the landing light system.
These switches are installed on the overhead panel 25VU in the cockpit. When
the landing lights are extended, an indication ’LAND LT’ is shown on the CRT EXT LT PANEL (25VU)
(Cathode Ray Tube) as a memo message. The CRT is a part of the Electronic
Centralized Aircraft Monitoring system (ECAM) (Ref. 31−52−00).

L and R LAND SELECTOR

These selectors control the landing light.
ON: Extends the (left or right) landing light which comes on
automatically when fully extended.
OFF: Shut off the landing light but leaves it extended.
RETRACT: Retracts the landing light and shuts it off.
FOR TRAINING PURPOSES ONLY!

Figure 42 L&R Landing Light Switches

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Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
EXTERIOR LIGHTS
33−40

5LB 6LB

103XP (204XP) SELECTOR SW

115V AC

400HZ
LIGHT ON CRT
MEMO MESSAGE
3LB(4LB) LIGHT EXTEND
LIGHT RETRACT
LIGHT POWER LANDING LIGHT
1LB(2LB)
LIMIT LH SHOWN RH SIMILAR
MICRO SWITCHES
DRIVE MOTOR
7LB(8LB)

LIMIT
MICROSWITCHES
FOR TRAINING PURPOSES ONLY!

LANDING LAMP HOUSING

LANDING LAMP 7LB, 8LB

Figure 43 Landing Lights

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Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
EXTERIOR LIGHTS
33−40

LANDING LIGHT OPERATION

Power Supply
The 115V AC busbars, 101XP and 202XP, supply power to the LH and RH
landing lights through the circuit breakers 1LB, 2LB, 3LB and 4LB. These
circuit breakers are installed on panel 122VU in the cockpit. The circuit
breakers 1LB and 2LB control the power supply to the LH and RH landing light
step−down transformers. The circuit breakers 3LB and 4LB control the power
supply to the LH and RH single−phase motors of the landing lights.

Operation/Control and Indicating

Two control switches 5LB and 6LB are installed on the overhead panel 25VU.
The switch LAND L controls the left−hand landing light and the switch LAND R
controls the right−hand landing light. These switches are operated from
RETRACT to OFF to ON for extension and illumination of the landing lights.
Then from ON to OFF to RETRACT, to set the landing lights to off and to
retract them.
These operations are as follows:
S RETRACT to OFF
Power is supplied to the extend coil of the related motor, through a
microswitch, to extend the related landing light.
S OFF to ON
Power is supplied to the related power relay, through the full−wave rectifier
and the closed contacts of a microswitch. This connects 115V AC, 400Hz,
to the step−down transformer which decreases the voltage to 28V AC. The
related landing light comes on.
S ON to OFF
FOR TRAINING PURPOSES ONLY!

This removes power from the related power relay and opens the contacts of
the microswitch. This removes 115V AC, 400 Hz, from the step−down
transformer and the related landing light goes off.
S OFF to RETRACT
Power is supplied to the retract coil of the related motor, which retracts the
related landing light. The landing light stays off.

FRA US/T-5 PoL Mar 12, 2010 32|Land Light Oper|L3 Page 64
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LIGHTS A318/A319/A320/A321
EXTERIOR LIGHTS
33−40

7LB RETRACTABLE LANDING LIGHT 8LB RETRACTABLE LANDING LIGHT

K K

28VAC 28VAC
101XP
1LB
600W 202XP
2LB 600W
L L
L R
LAND
LAND
NORMAL ON NORMAL ON
BUS BUS
OFF OFF
FOR TRAINING PURPOSES ONLY!

BAR 31−59−00
RETRACT BAR
31−59−00
RETRACT
3LB C 4LB C
EXTEND EXTEND
M/SW M/SW
115V AC 115V AC
400Hz A 400Hz A
H EXTEND H EXTEND
31−59−00 31−59−00
31−54−00 31−54−00
F M F M

RETRACT B
RETRACT
B
RETRACT RETRACT
M/SW M/SW

Figure 44 Landing Lights Schematic

FRA US/T-5 PoL Mar 12, 2010 32|Land Light Oper|L3 Page 65
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LIGHTS A318/A319/A320/A321
EXTERIOR LIGHTS
33−40

ANTICOLLISION & STROBE LIGHT COMP. LOCATION

BEACON STROBE LIGHT

FOR TRAINING PURPOSES ONLY!

FR41

FR40

Figure 45 Upper Anticollision Light Comp. Location

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Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
EXTERIOR LIGHTS
33−40

ANTICOLLISION BEACON LIGHT

FR39
FR38

FR37
FOR TRAINING PURPOSES ONLY!

Figure 46 Lower Anticollision Light Compartment Location

FRA US/T-5 PoL Mar 12, 2010 33|Location|L2 Page 67
Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
EXTERIOR LIGHTS
33−40

543AB
(643AB)
STROBE LIGHT

FR77

TAIL NAVIGATION
FR70
LIGHT
FOR TRAINING PURPOSES ONLY!

ANTI-COLLISION
STROBE LIGHT STROBE LIGHT

NAVIGATION LIGHTS POWER UNIT

Figure 47 Wing&Tail Strobe Light Comp Location
FRA US/T-5 PoL Mar 12, 2010 33|Location|L2 Page 68
Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
EXTERIOR LIGHTS
33−40

HALOGEN LAMP
FOR TRAINING PURPOSES ONLY!

NOTE: HALOGEN BULBS ARE AVAILABLE FOR TAXI,

TAKE OFF, RUNWAY TURNOFF & LANDING LIGHTS
Figure 48 Example for Halogen Bulb Installation
FRA US/T-5 PoL Mar 12, 2010 33|Location|L2 Page 69
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LIGHTS A318/A319/A320/A321
EXTERIOR LIGHTS
33−40

SAFETY PRECAUTIONS
When you work on the lights system, make sure that you obey all the AMM
(Aircraft Maintenance Manual) 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, the landing light must not be operated.
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:
S the flight controls,
S the flight control surfaces,
S the landing gear and the related doors,
S components that move.
Do not remove a strobe light for at least ten minutes after you de−energize the
electrical circuits. The high voltage electrical current in the capacitor of the
strobe light is dangerous.
FOR TRAINING PURPOSES ONLY!

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.

FRA US/T-5 PoL Mar 12, 2010 34|Safety|L1 Page 70

Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
EXTERIOR LIGHTS
33−40
FOR TRAINING PURPOSES ONLY!

Figure 49 Safety Precautions

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Lufthansa Technical Training
LIGHTS A319/A320/A321
EMERGENCY LIGHTING
33−50

33−50 EMERGENCY LIGHTING

EMERGENCY LIGHTING-DESCRIPTION
General Test
The Emergency Lighting System of the cabin is separately controlled and The Emergency Lighting System can be tested via the PTP (Programming and
supplied from the other lighting system. Test Panel) of the CIDS.
There are lights installed in the hatracks, in the areas of exits, in the escape When you push the SYS pb−switch on the PTP the EPSUs will be tested one
slides and in the fuselage in the overwing area. after another. If all EPSUs monitor no failures of the connected internal and
They shall be supplied automatically by the EPSU (Emergency Power Supply external loads and the battery packs, the SYS OK light on the PTP illuminates
Units) with 6V DC, after loss of AC BUS 1. In this case the lights will be after approximately 30s.
supplied from the DC ESS SHED BUS via 28/6V DC/DC Converters. When you push the BAT pb−switch on the PTP a test of the batteries capacity
If the DC ESS SHED BUS is loss of power, the lights will be supplied by the will be initiated. A security code has to be entered first on the PTP.
battery packs installed on the EPSUs. The test lasts app. 2h because the batteries will be discharged and recharged
During normal operation the battery packs will be charged by a battery charge after that.
device inside the EPSU. (The exact test description follows in the chapter 23 CIDS).
The EXIT signs will be switched on (except automatic), when:
S NO SMOKING switch in ON, or
S NO SMOKING switch in AUTO and landing gear extended, or
S a very low cabin pressure is monitored by the Cabin Pressure Controllers.
If the Emergency Exit Doors are open and the Slides are armed, the Overwing
Emergency lights and the Escape Slide lights illuminate.
If the Main Doors are open and the Slides are armed, the lights in the Main Exit
Escape Slides illuminate. ESCAPE ROUTE OVER THE WING EMER-
GENCY LIGHTING
The control of the Emergency Lighting system happens via the following
switches:
FOR TRAINING PURPOSES ONLY!

S EMER EXIT light switch on the cockpit overhead panel

S EMER pushbutton switch on the FAP (Fwd Attendant Panel).
Housed in the fuselage, there are 4 exterior emergency lights. These
lights are automatically activated when an overwing emergency exit
door is opened in the armed configuration. The lights come on all
along the escape route leading to the aft wing slide. Each escape
slide has integrated lighting strips.

Figure 50 Exterior Emergency Lights

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Lufthansa Technical Training
LIGHTS A319/A320/A321
EMERGENCY LIGHTING
33−50

EMERGENCY EXIT SIGNS CABIN EMER. EXIT LOCATION CEILING EMERGENCY LIGHTS CEILING EMERGENCY LIGHTS
LIGHT VERSION 1 VERSION 2

EMER EXIT LT

FWD PURSER STATION

FOR TRAINING PURPOSES ONLY!

ESCAPE PATH LIGHTING EMERGENCY POWER SUPPLY UNIT

(EPSU)

EMERGENCY LIGHT
PUSHBUTTON
Figure 51 Emergency Lights Component Location
FRA US/T-5 PoL Mar 12, 2010 35|−50Emergency|L2 Page 73
Lufthansa Technical Training
LIGHTS A319/A320/A321
EMERGENCY LIGHTING
33−50

EPSU FUNCTIONAL OPERATION Load Programming (Teach in)

The EPSU determines INTERNAL respectively EXTERNAL faults by
The EPSUs (Emergency−Power Supply Units) supply different lights. These
measuring the resistance of the connected loads. Therefore the resistance
lights are exit signs, cabin emergency lights, overwing emergency lights,
value has once to be covered and memorized. This happens by removing the
escape slide lights, emergency−escape hatch−handle lights and, through the
battery pack for more than 15s from the EPSU, with 28V DC available from the
inverter units, floor−proximity lights.
network. As the EPSU accepts each value, it must be controlled before, that all
The emergency−power supply unit consists of: connected lights function.
Electronic logic and switching circuits.
EPSU BITE
A 28 V DC/6 V DC converter which supplies the loads whenever the essential
busbar is energized and the emergency lighting system is activated. Each EPSU has two different integrated BITE functions:
A 6 V battery supplies the loads whenever the system is not selected OFF and S A system test
the power supply from the DC ESS SHED BUS is not available. The DC ESS S A battery capacity test
SHED BUS charges the battery through the 28 V DC/6 V DC unit converter. The EPSUs have an interface to the CIDS to read the BITE results of a system
Whenever the ambient temperature falls below +20 DEG. C (68 DEG. F) the test and a battery capacity test.
28 V DC ESS SHED provides electrical heating for the battery. The battery is
changed without removal of the power supply unit. System Test
A test circuit tests the condition of the unit battery, the unit logic and the related The system test monitors the subsequent functions:
loads. The battery test procedure starts after coding selection when the TEST S The aircraft AC power supply
EMER LIGHT BAT membrane switch on the programming and test panel S The aircraft DC power supply
110RH (CIDS) is pushed.
S A short circuit on each output
If all batteries are serviceable, the annunciator BAT OK adjacent to
S An overvoltage on each output
the membrane switch comes on. The system test procedure starts when
the TEST EMER LIGHT SYS membrane switch on the programming and S The output voltage of the battery pack
test panel 110RH is pushed. The test circuit carries out an interrogation of the S The battery heating device
units and monitors the output current. S The proper function of the EPSU logic and switching circuits
If all units are serviceable the annunciator SYS OK adjacent to the membrane S If the connected loads are in the pre−determined values
switch comes on. This test loop completes only when all unit output currents
The system test has a limit of 20 seconds to prevent discharge of the battery
FOR TRAINING PURPOSES ONLY!

are within the expected value. An individual test on each power supply unit
pack.
must be carried out when either the BAT OK or SYS OK annunciator does not
come on. Battery Capacity Test
The individual test starts when the pushbutton on the unit is pushed. A The battery capacity test monitors:
defective unit will cause a red LED on the unit to come on. A green light in
If the capacity of each EPSU battery is sufficient enough to supply its
the LED indicates a serviceable power supply unit. There are three pairs of red
emergency lights for at least 10 minutes
and green LEDs. One pair provides indication of defects in the external loads
(i.e. slides, overwing lights). If the loss of the capacity of each battery, between two consecutive battery
capacity tests, is smaller than 0.40 Ah
One pair provides indication of defects in the internal loads. One pair provides
indication of defects in the battery. Each output is separately fused. The fuses It can take up to three hours to complete the battery capacity test.
are installed on top of the power supply unit.

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Lufthansa Technical Training
LIGHTS A319/A320/A321
EMERGENCY LIGHTING
33−50

EMERGENCY POWER SUPPLY UNIT

E.P.S.U.
13 WL

GREEN
RED
FOR TRAINING PURPOSES ONLY!

E.P.S.U.

E.P.S.U.
13 WL
EMERGENCY POWER SUPPLY UNIT

WALL MOUNTED EXIT MARKING SIGN

FLOOR PROXIMITY EMERGENCY ESCAPE
PATH MARKING PHOTOLUMINESCENT STRIP

Figure 52 EPSU (Emergency Power Supply Unit)

FRA US/T-5 PoL Mar 12, 2010 36|EPSU|L3 Page 75
Lufthansa Technical Training
LIGHTS A319/A320/A321
EMERGENCY LIGHTING
33−50

25VU 25VU
115 28VDC EMER EXIT LT FAP 120RH NO SMOKING 25VU SLIDE ARMED & LANDING EMERGENY OVERWING EXIT
VAC ESS LIGHT PAX/CREW DOOR GEAR CEILING EMERGENCY SIGNS
ON ON
NORM SHED OPEN POSITION LIGHTS LIGHTS &
BUS BUS A EMER
EMER + ESCAPE
103XP 801PP ARM U OFF SLIDE
T SLIDE RELEASED PATH
LIGHTS
O & EMER EXIT OPEN MARKING
OFF OFF LIGHTS
YES YES OFF OFF OFF ON NO UP/DOWN OFF OFF OFF
YES YES OFF OFF AUTO ON NO DOWN OFF OFF ON 1
YES YES OFF OFF AUTO ON NO UP OFF OFF OFF
YES YES OFF OFF ON ON NO UP/DOWN OFF OFF ON 1
YES YES OFF OFF OFF ON YES UP/DOWN OFF ON 1 OFF
YES YES ARM OFF OFF OFF NO UP/DOWN OFF OFF OFF
YES YES ARM OFF AUTO OFF NO DOWN OFF OFF ON 1
YES YES ARM OFF AUTO OFF NO UP OFF OFF OFF
YES YES ARM OFF ON OFF NO UP/DOWN OFF OFF ON 1
YES YES ARM OFF OFF OFF YES UP/DOWN OFF ON 1 OFF
YES YES ON ON/OFF ON/AUTO/OFF OFF NO UP/DOWN ON 1 OFF ON 1
YES YES OFF ON ON/AUTO/OFF ON NO UP/DOWN ON 1 OFF ON 1
YES YES ON ON/OFF ON/AUTO/OFF OFF YES UP/DOWN ON 1 ON 1 ON 1
NO NO OFF OFF ON/AUTO/OFF OFF YES/NO UP/DOWN OFF OFF OFF
NO NO A ARM/ON ON/OFF ON/AUTO/OFF OFF NO UP/DOWN ON 2 OFF ON 2
NO YES B ARM/ON ON/OFF ON/AUTO/OFF OFF NO UP/DOWN ON 1 OFF OFF
NO NO C ARM/ON ON/OFF ON/AUTO/OFF OFF NO UP/DOWN ON 2 OFF ON 2
FOR TRAINING PURPOSES ONLY!

NO NO C NO D NO D ON/AUTO/OFF OFF NO UP/DOWN ON 2 OFF ON 2

NO NO C NO D NO D ON/AUTO/OFF OFF YES UP/DOWN ON 2 ON 2 ON 2

OFF FOR APPROX. 10S. UNTIL RAM AIR TURBINE IS EXTENDED 1 SUPPLIED BY 28V TO 6V CONVERTER
A
AND CSM/G IS ON-LINE
2 SUPPLIED BY INTEGRATED BATTERY PACK
B RAM AIR TURBINE IS EXTENDED AND CSM/G IS ON-LINE
SPEED < 50KTS. RAM AIR TURBINE IS NO MORE ACTIVE
C
(GSM/G IS OFF)
NO SIGNAL FROM ’EMER EXIT LT’ AND ’EMER LT’ SWITCHES
D
(BROKEN FUSELAGE)

Figure 53 Emergency Lights Function Table

FRA US/T-5 PoL Mar 12, 2010 36|EPSU|L3 Page 76
Lufthansa Technical Training
LIGHTS A319/A320/A321
EMERGENCY LIGHTING
33−50

FLOOR PROXIMITY
EXIT LOCATION EMERG ESCAPE
SIGN PATH MARKER
3 SEGMENT STRIP

EXIT MARKING
SIGN

- +
CAPACITY
UNIT

6VDC

115VAC
FLOOR PROXIMITY
EMERGENCY EMERG. ESCAPE
CEILING LIGHTS PATH MARKER
INVERTER UNIT

EMERGENCY - +
DOOR LIGHTS 2 SEGMENT STRIP
CAPACITY
UNIT
FOR TRAINING PURPOSES ONLY!

OVERWING 6VDC
EMERG LIGHTS
115VAC

FLOOR PROXIMITY
INTEGRATED EMERG. ESCAPE
ESCAPE SLIDE PATH MARKER
LIGHTS INVERTER UNIT WALL MOUNTED
SIGNS

Figure 54 Emergency Lights Schematic

FRA US/T-5 PoL Mar 12, 2010 36|EPSU|L3 Page 77
Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
COCKPIT enhanced
33−10

33−10 COCKPIT
COCKPIT LIGHT DESCRIPTION (ENHANCED)
Annunciator Lights
The pushbutton switches annunciator lights have Light Emitting Diodes (LEDs)
instead of bulbs. They are electrically and mechanically interchangeable with
the classic A320 bulb type.
The Power Supply is still 5VAC generated by the four Annunciator Light
Transformers.
FOR TRAINING PURPOSES ONLY!

FRA US/T-5 PoL Mar 12, 2010 01|−10Cockpit|D−NE|L1 Page 78

Lufthansa Technical Training
LIGHTS A318/A319/A320/A321
COCKPIT enhanced
33−10

COCKPIT COMPARTMENT
FOR TRAINING PURPOSES ONLY!

OVERHEAD PANEL COCKPIT PUSHBUTTON SWITCH

Figure 55 Cockpit (Bulbless) Push Button
FRA US/T-5 PoL Mar 12, 2010 01|−10Cockpit|D−NE|L1 Page 79
Lufthansa Technical Training
LIGHTS ENHANCED A318/A319/A320/A321
CABIN LIGHTS enhanced
33−20

33−20 CABIN
INTRODUCTION (ENHANCED)
Cabin Lights Description
The cabin fluorescent lamps have new AIBU (Advanced Integrated Ballast LOUDSPEAKER
Units). The ballast units receive FAP commands for BRT (100%) DIM 1 (50%) SAFETY CLAMP
and DIM 2 (10%) light intensity. Optionally they can provide variable dimming, LOUDSPEAKER
from 0 to 100% brightness. The number of brightness levels is 128 so that it
seems to be without steps. This is according to different lighting scenarios
programmed in the CAM (Cabin Assignment Module). LRL-BODY
There is one reading light for each passenger seat. There are LEDs (Light PISA INSIDE
Emitting Diodes) installed instead of halogen bulbs. The reading lights are not (NOT VISIBLE) NS-FSB LENS
adjustable because the LED light diffusion angle is sufficient. Reading lights are
supplied by the active CIDS Director via type A DEUs and PISA (Passenger
Interface Supply Adapters). The PISAs are in the Passenger Service Units
(PSU).
Passenger Interface Supply Adapter (PISA)
The PISA is the interface between the DEU type A and components of the
PSU (Passenger Service Unit).
The PISAs are installed in each PSU in the pressurized area of the cabin. PSU BODY
NOTE: The MTBF (Mean Time Between Failure) of LED reading lights is
100,000 flight hours. Thus, there is no replacement procedure PSU CLAMP
CABLE BUNDLE HOLDER
apart from replacing the complete light assembly. Cabin signs
must be replaced if three or more LEDs have failed (de−graded
performance).
FOR TRAINING PURPOSES ONLY!

DRIP WATER COVER CABLE TIES

CABLE BUNDLE

Figure 56 PSU Backside

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Lufthansa Technical Training
LIGHTS ENHANCED A318/A319/A320/A321
CABIN LIGHTS enhanced
33−20

PISA
TOP LINE LVDS
BUSES DEU A

FLIGHT ATTENDANT PANEL

DEU A

DEU A
CIDS
DIRECTOR 1
CIDS DEU A
DIRECTOR 2
PASSENGER SERVICE UNIT

DEU A

Fluorescent Lamp
FOR TRAINING PURPOSES ONLY!

DEU A RS 485
AIBU

AIBU: Advanced Integrated Ballast Unit

PISA: Passenger Interface Supply Adapter
LVDS: Low Voltage Digital Serial Bus
RS485 is a two−wire, half−duplex, multipoint serial communications channel.
Figure 57 Cabin Light Signal
FRA US/T-5 PoL Mar 12, 2010 02|−20|Cabin|D−NE|L1 Page 81
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LIGHTS ENHANCED A318/A319/A320/A321
CABIN LIGHTS enhanced
33−20

FLIGHT ATTENDANT PANEL DESCRIPTION (ENHANCED)

Cabin Lighting Page
Select LIGHTS 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 1/4 touch switches enable selection of entry lighting BRT, DIM 1,
DIM 2. The GENERAL CABIN SETTINGS touch switches enable cabin lighting
ON/OFF control and cabin lighting settings for Boarding, Take off, Climb,
Cruise, Descent and DAY/NIGHT modes.
Additional functions are Reading light (R/L) SET (on) and RESET (off). The
MAINT switch is for lavatory light full brightness control. The general cabin
settings selections can be applied to individual class zones by selecting the
Class SELECT touch switches.
Other optional light control functions are for selection and brightness control in
the class zones, for various in flight situations (Duty free, Read, Video, Dinner,
Sleep and Wakeup).
NOTE: There are variations of lighting control functions, depending on
the options selected by the operator.
FOR TRAINING PURPOSES ONLY!

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Lufthansa Technical Training
LIGHTS ENHANCED A318/A319/A320/A321
CABIN LIGHTS enhanced
33−20

GENERAL CABIN
AIRCRAFT SYMBOL
SETTINGS CONTROL PANEL
ENTRANCE LIGHT
CONTROL PANEL

PASSENGER
COMPARTMENT
CONTROL PANEL
FOR TRAINING PURPOSES ONLY!

CABIN LIGHTING FLIGHT

ATTENDANT PANEL PAGE

PASSENGER COMPARTMENT
ZONE SELECTING PANEL

Figure 58 FAP CABIN LIGHTING page

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LIGHTS ENHANCED A318/A319/A320/A321
CABIN LIGHTS enhanced
33−20

HANDRAIL LIGHTING DESCRIPTION

The LED strips are located on the LH and RH handrail. The two LED−strips are
A A
installed and integrated with the hatrack. The strips are supplied with 28VDC LH SHOWN
from the busbar 214XP through the circuit breaker 312LG and the STair RH SYMMETRICAL
ELectrical Load−Adapters 481LG and 482LG (STELLA).
The STELLA changes the 115VAC to 28VDC for the operation of the
LED−strips. The handrail lighting system is controlled from the FAP 120RH.

Removal of the LED Handrail Strips

Put the SCREWDRIVER − SMALL through the cable conduit of the related
overhead stowage compartment into the handrail end cap.
Push the SCREWDRIVER − SMALL against the rear side of the LED handrail
light strip. Do this to disengage the LED handrail light strip (2) from the recess. B B
LH SHOWN
Remove the LED handrail light strip. RH SYMMETRICAL
Test is done via the general illumination test on the FAP.

C
C
FOR TRAINING PURPOSES ONLY!

LH SHOWN
RH SYMMETRICAL

Installed in Zone 200 (ceiling) between FR41 and FR43

Figure 59 STELLA Figure 60 LED Handrail Strip Installation

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Lufthansa Technical Training
LIGHTS ENHANCED A318/A319/A320/A321
CABIN LIGHTS enhanced
33−20

402LG SHOWN AS TO ADDITIONAL

214XP-C EXAMPLE. ALL OTHER HANDRAIL STRIPS:
115VAC STRIPS ARE THE SAME
AC BUS 2 312LG 406LG, 408LG, 410LG,
POWER 412LG, 414LG, 418LG,
SUPPLY 420LG, 422LG, 424LG,
426LG, 428LG, 430LG,
432LG, 434LG, 436LG, FR21
438LG, 440LG, 442LG,
404LG 444LG, 446LG, 448LG, 401LG 402LG
450LG, 452LG, 454LG,
456LG 403LG 404LG
402LG
405LG 406LG
407LG 408LG
409LG 410LG
28VDC
STELLA 411LG 412LG
482LG 413LG 414LG

28VDC TO ADDITIONAL HANDRAIL STRIPS:

STELLA 417LG 418LG
403LG, 405LG, 407LG, 409LG, 411LG, 413LG,
481LG 417LG, 419LG, 421LG, 423LG, 425LG, 427LG, 419LG 420LG
429LG, 431LG, 433LG, 435LG, 437LG, 439LG,
441LG, 443LG, 445LG, 447LG, 449LG, 451LG, 421LG 422LG
453LG, 455LG
ON/OFF

ON/OFF

423LG 424LG
425LG 426LG

401LG 427LG 428LG

429LG 430LG
431LG 432LG
433LG 434LG
435LG 436LG
DEU A DEU A 437LG 438LG
EXAMPLE 439LG
200RH6 200RH5 440LG
FOR TRAINING PURPOSES ONLY!

441LG 442LG
LED− STRIP 443LG 444LG
CIDS DIR
FAP 445LG 446LG
1&2
120RH 447LG 448LG
101 & 102 RH 449LG 450LG
451LG 452LG
453LG 454LG
STELLA: STair ELectrical Load−Adapters 455LG 456LG
DIR: Director FR65
FAP: Flight Attendant Panel
DEU: Decorder Encoder Unit

Figure 61 Handrail Lighting Schematic

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LIGHTS A318/A319/A320/A321
CABIN EMERGENCY LIGHTING enhanced
33−51

33−51 CABIN EMERGENCY LIGHTING

INTRODUCTION (ENHANCED)
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 LEDs (Light Emitting Diodes), except for
lavatory auxiliary lights (28V DC LEDs).
The external emergency lights such as over−wing and escape slide use bulbs
technology.

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

EPSU
The EPSUs supply the following lights:
S exit signs lights,
S cabin emergency lights,
S seat mounted emergency lights and exit location lights,
S wall mounted emergency exit location light,
S wall mounted exit marking sign,
S wall mounted emergency exit,
S wall mounted emergency light,
S escape slide lights,
FOR TRAINING PURPOSES ONLY!

S over−wing emergency lights,

S lavatory auxiliary lights,
S 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.

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LIGHTS A318/A319/A320/A321
CABIN EMERGENCY LIGHTING enhanced
33−51
FOR TRAINING PURPOSES ONLY!

(OPTION)
(OPTION)

Figure 62 General Cabin and Exterior Emergency Lights

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LIGHTS A318/A319/A320/A321
CABIN EMERGENCY LIGHTING enhanced
33−51
PHOTOLUMINESCENT FLOOR PATH−MARKING−SYSTEM
Lufthansa Technik developed an easy−to−install non−electric floor path The charging and discharging time can be increased and decreased by the
marking system called GUIDELINE. It has a significantly lower level of related conditions:
complexity, requires no maintenance and has 100% reliability compared to the S Length of time of the charging
standard electrically operated systems.
S Light intensity during the charging
This emergency light system has already been installed and certified in all
S Color filter film (if installed).
major types of Airbus, Boeing, ATR, CRJ, DO, EMB and Fokker aircraft.
The luminescence is a physical process without a half−time period, it can be
General repeated infinitely. Our environmental tests have proved an unlimited life−time
The system consists of a number of flexible photoluminescent strips. They are for these photo luminescent strips. Once installed the photoluminescent strips
installed on the floor and on convertible seats (if applicable) on the two sides of will last longer than an aircraft life.
the aisle and the emergency−exit area. The system gives the floor−level The system is designed for a very easy installation, no special tools are
illumination of the passenger aisles and escape routes in the event that smoke needed.
obscures normal emergency lighting. The brand new generation of the photoluminescent strips offers innovative
The photoluminescent marking system supplies sufficient light for minimum design elements including a choice between many additional colors. In terms of
eight hours in a dark area when it is fully charged. When the system is fully color they fit in optimally with the carpeting, the galley and the cabin interior.
discharged, a charge time of at least ten minutes with full brightness of the With regard to efficiency the photoluminescent strips can guarantee longer
cabin lighting is necessary flight time in combination with shortest charging times due to the superior photo
The non−electric photoluminescent marking system consists of luminescent material.
photo−luminescent material. It does not need electricity or batteries. The strips emit their yellow light only when the cabin is in darkness. Offering
The scratch, shock−resistant and fluid−resistant strips absorb energy when interior designers new options, this world premiere gives airlines an additional
exposed to light and gradually release it in the form of light when in the dark. tool for individualized configuration of their cabins. The Guideline does pioneer
In operation time with darkness the photoluminescent marking system safely work and holds the market leadership for aircraft types such as single aisle
leads the way to the exits up to 22 hours. Airbus or Bombardier.
FOR TRAINING PURPOSES ONLY!

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Electrical Escape Lighting System (Old Fashioned) Non Electric Floor Path Marking System (Today Standard)
FOR TRAINING PURPOSES ONLY!

A choice between many colors

Figure 63 Photoluminescent Floor Path-Marking-System
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EMERGENCY LIGHTS SYSTEM OPERATION (ENHANCED)

EMERGENCY LIGHTS SYSTEM S ON Position
The new EPSUs have internal software changes and are not interchangeable In the ON position the emergency lighting system comes on, as if the
with the other A320 family members. The EPSU functions are the same but the EMERgency P/B on the Flight Attendant Panel (FAP) was pushed.
related ceiling and escape path lights are LED technology. The external The cabin emergency lights, the exit signs, the escape hatch−handle lights
emergency lights (over wing and escape slide) are unchanged (bulbs). and the seat mounted lights come on.
There are no more Static Inverter Units installed. The 28V DC/6V DC converters of the EPSUs supply these loads as long as
the 28V DC ESS SHED BUS is available.
Operation
If the 28V DC SHED ESS BUS voltage falls below 16V, the EPSUs internal
The EMERgency EXIT LighT switch on the overhead panel controls the
batteries continue to supply the loads for few minutes. The batteries are no
emergency lighting system. The EMER EXIT LT switch has three positions
longer charged.
such as OFF, ARMed and ON. Each of these positions sends a discrete
ground signal to the EPSUs. S Other Cases
S OFF Position Independently of the switch positions, the integral lights in the respective
escape slides come on when the passenger/crew doors or the emergency
In the OFF position a ground signal prevents the emergency lighting system
exit doors are opened with the escape slides armed.
from being switched on when the AC NORM and DC ESS SHED BUS
voltages are not available. The EMER EXIT LT OFF annunciator light When the emergency exit hatches are open and the slides are released, the
comes on. The Batteries are no longer charged. respective over−wing emergency lights and the integral lights in the
respective escape slide come on. In the event of excessive cabin
NOTE: The EXIT signs and the emergency escape hatch−handle depressurization, the exit marking signs and the exit location signs
lights come on with EMER EXIT LT switch OFF, when the NO automatically come on.
SMOKING switch is in the ON position or in AUTO position
with landing gear extended. Test
S ARM Position Each EPSU has a test circuit which tests the condition of the battery unit, the
In the ARM position the EMER EXIT LT OFF annunciator light goes off. logic unit and the related loads. This test is done first from the MCDU, but an
When the 115V AC NORM BUS voltage is not available, the cabin individual test on each EPSU must be carried out when the EPSU Battery
emergency lighting and the FPEEPMS light come on. TEST or the EPSU SYStem TEST through the MCDU fails.
FOR TRAINING PURPOSES ONLY!

The power is supplied from the 28V DC/6V DC converter in the related This isolated test starts when you push the TEST P/B on the EPSU
EPSU. NOTE: The EPSU System Test may be also carried out vie the CIDS
When the 28V DC ESS SHED BUS voltage is not available, the batteries of BITE menu on the FAP, but the Capacity Test can only be
all EPSUs supply the emergency lighting system for few minutes. activated from the CIDS-MCDU menu.
The batteries are no longer charged. The access code is still 3351.

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OPTION

TEST VIA CIDS

BITE MENU ON
MCDU

NORMAL POWER SENSING

FOR TRAINING PURPOSES ONLY!

Figure 64 Emergency Light System Schematic

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33

CABIN LIGHTS TESTS (ENHANCED) EPSU Local Test P/B

The isolated test starts when you push the TEST membrane switch on the
MCDU pages EPSU. A defective emergency lighting system will cause a red LED on the
Lighting systems tests are done through the CFDS MCDU. Select the EPSU to come on. The green LED SYSTEM OK on the EPSU shows a
SYSTEM REPORT/TEST < COM < CIDS 1 (2) menu for the following sub serviceable emergency lighting system.
menus: The four red LEDs show the indication of defects:
S SYSTEM TESTS, S in the exterior lights (external loads),
S EPSU BAT CAP TEST, S in the interior lights (internal loads),
S OP TESTS. S in the battery,
SYSTEM TESTS opens a menu which includes S in the unit.
< ILLUMINATION TEST and Each output has its own fuse. The fuses are installed inside the EPSU.
< EPSU SYS TEST. (ASM 33−51−00 SCH01 P119 Figure 3)
EPSU SYS and EPSU BAT CAP TEST are similar to the tests done through
the PTP (Programming and Test Panel) on the classic A320 family members.
On enhanced aircraft types the PTP does not exist, therefore these tests are
performed via the BITE menu of the CIDS on the MCDU.
NOTE: The EPSU BAT CAPACITY TEST can only be performed via the
MCDU located in the cockpit (Code: 3351).
OP TESTS opens a menu which includes READING LIGHT + ACP + PAX
CALL + SIGN < LAMPS ACTIVATION. This test activates all the related lights
in the passenger cabin. The READING LIGHT + ACP + PAX CALL + SIGN
LAMPS ACTIVATION test is similar to the tests done individually, through the
MCDU on other A320 family members.
However, on the enhanced system the tests are all done at the same time. The
related lights and signs are illuminated during the test. The ILLUMINATION
TEST opens a ’set up’ menu and request <START TEST. „TEST IN
FOR TRAINING PURPOSES ONLY!

PROGRESS 5 S“ is displayed and then goes to „FAULT“ displays or „TEST

OK“.
Faults are identified by ATA reference, FIN and CLASS.

Figure 65 EPSU Local Test

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33

 
 
   
  
    

    
      
 
     
  
 
 A   
 
  

  
   B    
    
  
 
 
    

EMERGENCY POWER SUPPLY UNIT

B

 
  
     

  
 
    

FOR TRAINING PURPOSES ONLY!

 

 
 

   

Figure 66 Cabin Lights BITE

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EPSU BITE TESTS (ENHANCED)

General The procedure is accomplished as follows:
Each EPSU has two different integrated BITE functions: S disconnect EPSU from 28 V DC aircraft power supply,
S a system test, S remove EPSU battery,
S a battery capacity test. S re−connect EPSU to 28 V DC aircraft power supply,
The EPSUs have an interface to the CIDS to read the BITE results of a system S install EPSU battery.
test and a battery capacity test.
NOTE: It is essential that all connected lights to the EPSU are operative
The EPSUs and the CIDS use a RS232 interface for the data exchange of both when the TEACH-IN is done, otherwise the EPSU will declare a
BITE functions. You can start the two different BITE functions only on the defective light as normal.
ground with a related CFDS/MCDU test menu page.
During the system test each EPSU measure the resistance values of its
Additionally the start of the battery capacity test is code protected against connected loads. These measured values are compared with the reference
inadvertent action, because the batteries are discharged during the battery values.
capacity test.
The system test has a limit of 60 seconds to prevent discharge of the battery
The EPSUs only accept the test start commands when the subsequent pack.
conditions are fulfilled:
S aircraft on ground, Emer Light System Test Description/Operation
S all emergency lights OFF, When you start the system test via a CFDS/MCDU test page action the CIDS
transmit the ’EPSU SYS TEST’ data word through the related DEU Bs to the
S 28 V DC available,
EPSUs. When the ’EPSU SYS TEST’ data word is accepted the EPSUs are
S 115 V AC available, set to the system test mode.
S control switch ’EMER EXIT LT’ 4WL in OFF position, When the EPSUs can start the system test the status message
S pushbutton ’EMER’ on the FAP in OFF position, ’TEST IN PROGRESS’ is send to the CIDS. The system test will be completed
S control switch ’NO SMOKING’ 190RH in OFF position within approximately 60 seconds.
When the system test is completed the test results are sent to the CIDS and
Emer Light System Test shown as a test result message on the CFDS/MCDU.
The system test monitors the subsequent functions: When the EPSUs cannot start the system test the reason for not starting the
FOR TRAINING PURPOSES ONLY!

S a short circuit on each output, system test is sent to the CIDS and shown as a status message on the
CFDS/MCDU.
S an overvoltage on each output,
S the output voltage of the battery pack, NOTE: This test can also be activated from the optional CIDS BITE
menu on the FAP (Flight Attendant Panel).
S the battery heating device,
S the proper function of the EPSU logic and switching circuits,
S if the connected loads are in the pre−determined values.
The pre−determined resistance values are used as reference values.
The referenced values are stored in a memory of the EPSU electronic and
monitoring circuits during a load programming (TEACH−IN) procedure.

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33

STEP 1 STEP 2 STEP 3

 
 
 

          
  
      
  

      
 
           
 
    
   
  !
 
   
 ! 

  
            
     "    
    
 
 
        

RESULT: OK RESULT: NOT OK

 
 
 

        
 
  
  


 
# 
        $
 
    
FOR TRAINING PURPOSES ONLY!

#%
     

         

Figure 67 Emergency Light System Test

FRA US/T-5 PoL Mar 12, 2010 07|BITE|D−NE|L2 Page 95
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33
EMERGENCY LIGHT SYSTEM TESTS
Emer Light Capacitiy Test
The battery capacity test monitors: The status message ’EPSU BAT CAP TEST IN PROGRESS’ is sent to the
S if the capacity of each EPSU battery is sufficient enough to supply its CFDS/MCDU. Before the main battery capacity test starts a system test is
emergency lights for at least 10 minutes, automatically done. If there is a system failure the battery capacity test is
stopped.
S if the loss of the capacity of each battery, between two consecutive battery
capacity tests, is smaller than 0.40 Ah. After approximately 3 hours, when the battery capacity is completed, a test
result message or a status message comes on
S The battery capacity test requires up to three hours to be completed.
When the battery capacity test is started during high environmental
External loads are:
temperature conditions, e.g. Aircraft in sunlight without Air Conditioning and the
S the overwing emergency lights, battery temperature exceeds more than 45 deg.C, the test is delayed.
S the escape slide lights. When the temperature falls to a normal day profile, the normal battery test
Internal loads are: cycle continuous. The message on the MCDU remains for information. The
S the cabin emergency lights, maximum time for a delayed battery capacity test is 24 hours.
After a delay of more than 24 hours, the battery capacity test is stopped.
S the escape hatch−handle lights,
S the exit location signs, NOTE: This test can not be activated from the optional CIDS BITE menu
on the FAP (Flight Attendant Panel).
S the exit marking signs.
Emer Light Capacitiy Test Description/Operation
You can start the battery capacity test via a CFDS/MCDU test page action.
The test start procedure is protected against accidental operation with a code.
When the EPSUs accept the code you can start the battery capacity test and
the EPSUs are set to the battery capacity test mode.
As long as the correct code is not entered and there are no test results of a
previous test available there are no ’<’ prompts in front of the ’START TEST’
and ’TEST RESULT’ messages.
FOR TRAINING PURPOSES ONLY!

When you enter the code, the ’<’ prompt comes on in front of the ’START
TEST’ message. Now you can push the ’START TEST’ line key and the ’<
CONFIRM START OF TEST’ message comes on.
Push the ’CONFIRM START OF TEST’ line key and the battery capacity test
starts.
The message ’TEST IN PROGRESS 3HR’ comes on.
When the battery capacity test cannot start, a status message shows the
reason for not start the test.

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33

 
STEP 1 STEP 2 STEP 3

 
  $'
  '$'

          
  
      
  

    
   
   
   
  
  
  
 
         
 
     
  !  



 
 !  
  
            
     "    
    
 
 
        
#

ENTER ACCESS CODE 3351 INTO SCRATCHPAD,

THEN LSK 4L. AFTER THAT TEST CAN BE ACTIVATED

STEP 4 AFTER MAX 3 HRS IN CASE OF FAILURE

  '$'
 
 

 
   
   
 

 
#% 
FOR TRAINING PURPOSES ONLY!

 $
           
   &!&&
#&& 
  $
    

           

Figure 68 Emergency Light Capacitiy Test

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A318−21 33 L3

TABLE OF CONTENTS
ATA 33 LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 SERVICE&CARGO COMPARTMENT
LIGHTING-DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . 48
33−00 LIGHTS-GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 33−40 EXTERIOR LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50
INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 GENERAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50
33−10 COCKPIT LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 TAXI AND TAKE OFF LIGHTS-DESCRIPTION . . . . . . . 52
COCKPIT LIGHTS-DESCRIPTION . . . . . . . . . . . . . . . . . . 4 WING & ENGINE SCAN LIGHTS DESCRIPTION . . . . . 54
DOME LIGHTS-OPERATION . . . . . . . . . . . . . . . . . . . . . . . 8 NAV&LOGO LIGHTS-DESCRIPTION VERSION 1 . . . . 56
CONSOLE AND FLOOR LIGHTING OPERATION . . . . 10 NAV & LOGO LIGHTS-DESCRIPTION VERSION 2 . . . 58
INSTRUMENT PANEL LIGHTING AND ANTICOLLISION LIGHTS DESCRIPTION . . . . . . . . . . . 60
READING LIGHTS-OPERATION . . . . . . . . . . . . . . . . . . . . 12 LANDING LIGHT DESCRIPTION . . . . . . . . . . . . . . . . . . . 62
DOME LIGHTS/READING LIGHTS-LOCATION . . . . . . . 14 LANDING LIGHT OPERATION . . . . . . . . . . . . . . . . . . . . . 64
PANEL/ INST INTEGRAL LIGHTING-OPERATION . . . . 16 ANTICOLLISION & STROBE LIGHT COMP. LOCATION 66
ANNUNCIATOR LIGHT TEST AND SAFETY PRECAUTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . 70
DIMMING-DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . 18
33−50 EMERGENCY LIGHTING . . . . . . . . . . . . . . . . . . . . . . . . . . 72
SPARE BULB BOX AND ANN. LIGHT LOCATION . . . . 20
EMERGENCY LIGHTING-DESCRIPTION . . . . . . . . . . . . 72
ANNUNCIATOR LIGHT TEST AND
DIMMING-OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22 EPSU FUNCTIONAL OPERATION . . . . . . . . . . . . . . . . . . 74
33−20 CABIN LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 33−10 COCKPIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 78
CABIN LIGHTS-DESCRIPTION . . . . . . . . . . . . . . . . . . . . . 24 COCKPIT LIGHT DESCRIPTION (ENHANCED) . . . . . . 78
CABIN LIGHTS SYSTEM-DESCRIPTION . . . . . . . . . . . . 26 33−20 CABIN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 80
CABIN LIGHTS LOCATION . . . . . . . . . . . . . . . . . . . . . . . . 28 INTRODUCTION (ENHANCED) . . . . . . . . . . . . . . . . . . . . 80
FAP (CABIN LIGHTING PANEL) & PTP DESCRIPTION 30 FLIGHT ATTENDANT PANEL DESCRIPTION
CABIN LIGHT-OPERATION . . . . . . . . . . . . . . . . . . . . . . . . 32 (ENHANCED) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 82
HANDRAIL LIGHTING DESCRIPTION . . . . . . . . . . . . . . 84
33−24 LAVATORY LIGHTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34
LAVATORY LIGHTING-DESCRIPTION . . . . . . . . . . . . . . 34 33−51 CABIN EMERGENCY LIGHTING . . . . . . . . . . . . . . . . . . . 86
LAVATORY LIGHTING OPERATION . . . . . . . . . . . . . . . . 36 INTRODUCTION (ENHANCED) . . . . . . . . . . . . . . . . . . . . 86
EMERGENCY LIGHTS SYSTEM OPERATION
33−25 PASSENGER READING LIGHTS . . . . . . . . . . . . . . . . . . . 38 (ENHANCED) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 90
PASSENGER READING LIGHTS-OPERATION . . . . . . . 38 CABIN LIGHTS TESTS (ENHANCED) . . . . . . . . . . . . . . . 92
BITE/TEST FUNCTION ON THE PTP . . . . . . . . . . . . . . . 40 EPSU BITE TESTS (ENHANCED) . . . . . . . . . . . . . . . . . . 94
33−30 CARGO AND SERVICE COMPARTMENTS . . . . . . . . . . 42
INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42
33−30 CARGO AND SERVICE COMPARTMENTS . . . . . . . . . . 44
AVIONICS COMPARTMENT LIGHTING-DESCRIPTION 44
WHEEL WELL LIGHTING−DESCRIPTION . . . . . . . . . . . 46

Page i
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TABLE OF CONTENTS

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A318−21 33 L3

TABLE OF FIGURES
Figure 1 Lights General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 Figure 36 Exterior Lights: Taxi/Take−off,Runway Turn Off . . . . . . . . . . . 53
Figure 2 Cockpit Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 Figure 37 External Lights: Wing and Engine Scan . . . . . . . . . . . . . . . . . . 55
Figure 3 Cockpit Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7 Figure 38 Nav&Logo Lights Schematic Vers. 1 . . . . . . . . . . . . . . . . . . . . 57
Figure 4 Dome Lights Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 Figure 39 Nav&Logo Lights Schematics Vers.2 . . . . . . . . . . . . . . . . . . . . 59
Figure 5 Side Console Lights and Cockpit Outlets Schematic . . . . . . . . 11 Figure 40 Strobe & Beacon Light Switches . . . . . . . . . . . . . . . . . . . . . . . . 60
Figure 6 Instrument Panel Lighting and Reading Lights Schematic . . . 13 Figure 41 Anticollision & Strobe Lights Schematic . . . . . . . . . . . . . . . . . . 61
Figure 7 Cockpit Lights Location . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 Figure 42 L&R Landing Light Switches . . . . . . . . . . . . . . . . . . . . . . . . . . . 62
Figure 8 Reading Lights Location . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 Figure 43 Landing Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 63
Figure 9 Panel Integral Lighting Comp. Location . . . . . . . . . . . . . . . . . . . 16 Figure 44 Landing Lights Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 65
Figure 10 Panel Integral Lighting Schematic . . . . . . . . . . . . . . . . . . . . . . . 17 Figure 45 Upper Anticollision Light Comp. Location . . . . . . . . . . . . . . . . 66
Figure 11 Annunciator Light Test & Dimming Schematic . . . . . . . . . . . . . 18 Figure 46 Lower Anticollision Light Compartment Location . . . . . . . . . . 67
Figure 12 Annunciater Light Test & Dimming-Location . . . . . . . . . . . . . . 19 Figure 47 Wing&Tail Strobe Light Comp Location . . . . . . . . . . . . . . . . . . 68
Figure 13 Switch and Indicator Light Tools . . . . . . . . . . . . . . . . . . . . . . . . 20 Figure 48 Example for Halogen Bulb Installation . . . . . . . . . . . . . . . . . . . 69
Figure 14 Spare Bulb Box and Ann. Lt. Removal/Installation . . . . . . . . . 21 Figure 49 Safety Precautions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 71
Figure 15 Annunciator Lights Test and Dimming Schematic . . . . . . . . . 23 Figure 50 Exterior Emergency Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 72
Figure 16 Cabin Lights General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 Figure 51 Emergency Lights Component Location . . . . . . . . . . . . . . . . . 73
Figure 17 Attendant Work Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 Figure 52 EPSU (Emergency Power Supply Unit) . . . . . . . . . . . . . . . . . . 75
Figure 18 Cabin Lights Location . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 Figure 53 Emergency Lights Function Table . . . . . . . . . . . . . . . . . . . . . . . 76
Figure 19 FAP & PTP Location . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 Figure 54 Emergency Lights Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . 77
Figure 20 Cabin Lights Block Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33 Figure 55 Cockpit (Bulbless) Push Button . . . . . . . . . . . . . . . . . . . . . . . . . 79
Figure 21 Lavatory Lighting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 Figure 56 PSU Backside . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 80
Figure 22 Lavatory Lighting Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . 37 Figure 57 Cabin Light Signal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 81
Figure 23 Passenger Reading Lights Schematic . . . . . . . . . . . . . . . . . . . 39 Figure 58 FAP CABIN LIGHTING page . . . . . . . . . . . . . . . . . . . . . . . . . . . 83
Figure 24 PTP (Programming and Test Panel) . . . . . . . . . . . . . . . . . . . . . 40 Figure 59 STELLA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 84
Figure 25 PTP-Reading Light Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41 Figure 60 LED Handrail Strip Installation . . . . . . . . . . . . . . . . . . . . . . . . . . 84
Figure 26 Cargo and Service Compartment Lights . . . . . . . . . . . . . . . . . 43 Figure 61 Handrail Lighting Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . 85
Figure 27 Avionics Comp. Sw. Location . . . . . . . . . . . . . . . . . . . . . . . . . . . 44 Figure 62 General Cabin and Exterior Emergency Lights . . . . . . . . . . . . 87
Figure 28 Avionics Compartment Lights . . . . . . . . . . . . . . . . . . . . . . . . . . 45 Figure 63 Photoluminescent Floor Path-Marking-System . . . . . . . . . . . . 89
Figure 29 Wheel Well Compartment Lights . . . . . . . . . . . . . . . . . . . . . . . . 47 Figure 64 Emergency Light System Schematic . . . . . . . . . . . . . . . . . . . . 91
Figure 30 Service Area Lighting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48 Figure 65 EPSU Local Test . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 92
Figure 31 Cargo Compartment Lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49 Figure 66 Cabin Lights BITE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 93
Figure 32 EXT Light Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50 Figure 67 Emergency Light System Test . . . . . . . . . . . . . . . . . . . . . . . . . . 95
Figure 33 Exterior Lights-General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50 Figure 68 Emergency Light Capacitiy Test . . . . . . . . . . . . . . . . . . . . . . . . 97
Figure 34 Exterior Lights-Component Location . . . . . . . . . . . . . . . . . . . . . 51
Figure 35 Taxi&Take-off Lights-Schematic . . . . . . . . . . . . . . . . . . . . . . . . 52

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