A380_25_B2X1

Revision:

Author:

For Training Purposes Only

� LTT 2007

ATAEquipment/Furnishings

A380

Airbus

RR RB211 Trent 900

25

EASA Part-66

B2_(excluding−Level-1−Contents)

A380_25_B2x1

WzT

1NOV2008

Training Manual

For training purposes and internal use only.

� Copyright by Lufthansa Technical Training (LTT).

LTT is the owner of all rights to training documents andtraining software.

Any use outside the training measures, especiallyreproduction and/or copying of training documents andsoftware − also extracts there of − in any format all(photocopying, using electronic systems or with the aidof other methods) is prohibited.

Passing on training material and training software tothird parties for the purpose of reproduction and/orcopying is prohibited without the express writtenconsent of LTT.

Copyright endorsements, trademarks or brands maynot be removed.

A tape or video recording of training courses or similarservices is only permissible with the written consent ofLTT.

In other respects, legal requirements, especially undercopyright and criminal law, apply.

Lufthansa Technical Training

Dept HAM USLufthansa Base HamburgWeg beim Jäger 19322335 HamburgGermany

Tel: +49 (0)40 5070 2520

Fax: +49 (0)40 5070 4746

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Page 3ATA DOC

EQUIPMENT/FURNISHINGS A380

25

FRA US/T WzT Aug 7, 2008

ATA 25 EQUIPMENT/FURNISHINGS

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Page 43 |L3

EQUIPMENT & FURNISHINGEMERGENCY LOCATOR TRANSMITTER

A380

25−69


ELT REMOTE CONTROL PANEL

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Page 53 |L3


A380

25−69


111MV

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Figure 1 ELT Remote Control Panel

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A380

25−69


EMERGENCY LOCATOR TRANSMITTER

Description

The basic ELT system is a stand−alone system, that means there is nointerface to other A/C system are needed for operation. The basic ELT systemis specified as simple as possible, but as safe as possible too. To ensure thefunctionality of the basic functions of the system the ELT transmitter is housedin a very robust box, which protects the transmitter in case of fire, explosion orcrashes. To ensure the functionality even after a crash the ELTS−unit has beentested with a g−shock test at 500g for 4ms and at 100g for 13ms. Besides thecoaxial cable between the ELT transmitter and the antenna it is as short aspossible to ensure the connection in case of a crash, the max. length is 2meters.

General

� Cospas−Sarsat approved ELT operating on three frequencies (121.5, 243and 406 MHz)

� Automatic/Fixed ELT

� Compatible with any Cospas−Sarsat Protocol

� Meet both FAA and JAA requirements

� Easy maintenance: A programming module keeps aircraft identification onboard. Programming tool is not needed

� Automatic ELT can be installed in four positions

� High efficiency: 2 antennas (primary and back up)

� Connection to cockpit remote control panel

� Capability to transmit GPS location data

Main features

� Compact, light weight, stand alone

� Identification Module

� Selectable automatic activation direction

� Dual antenna access

� Easy maintenance and installation

� Possible connection to on−board GPS

� No false activation induced by EMI

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Page 74 |L3


A380

25−69


Antenna OutputRemote ControlorProgramming Tool

Backup AntennaOutput

Activation/IdentificationModule

Z293 , Z294

FR92

FR93

110MV

143MV

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Figure 2 Emergency Locator Transmitter

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A380

25−69


ELT ANTENNA LOCATION

Location

The ELT primary antenna is at the top of the fuselage at FR90 / STA59690 - FR91 / STA60325 and mounted by 6 screws.

Test after installation

After a new Antenna installation is a functional test of the ELT systemnecessary, to do with a VSWR test equipment.

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Page 95 |L3


A380

25−69


FR91

FR90

112MV

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Figure 3 ELT Antenna location

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A380

25−69


ELT SCHEMATIC

Operation

The ELT is powered from the DC Bus via the SEPDC 1 with 28 VDC and hasan internal battery, which have a life time of 5 years.

When properly installed on the airplane, the ELT will be activated automaticallyin a crash. It can also be operated by setting the switch on the ELT to ”ON” orthe remote switch on the ELT control panel to ”ON”.

For normal operation, the switch on the ELT is set to ”AUTO” or ”OFF” and theswitch on the control panel is set to ”ARMED”. The ELT light will be off.

Transmission is done by the normal ELT antenna or via the Backup antenna.

The output and input to/form the SCI (Secured Communication Interface) unitsare not jet connected (future connection).

Control

On ground and the ELT powered the ELT light at the maintenance servicepanel at the nose gear will illuminate.

For normal operation, set the switch on the ELT to ”AUTO” and the controlpanel switch (P5) to ”ARMED”. When the ELT is turned on, it starts a self−testof the transmitter. The battery voltage test is under maximum load. The ELTtone and front panel LED start immediately. A short interruption occurs at 50seconds. At 100 seconds, the tone and light begin to cycle on and off at a 1 Hzrate.

At 150 seconds, the ELT begins 406 MHZ transmissions each 50 seconds. TheLED and tone alternate 1 second on and 1.5 seconds off.

The LED on the front panel of the ELT will be continuously on for more than 10seconds if the self−test is passed.

A self test of the ELT and programming unit is activated when the control panelswitch is in the ”RESET” position for more than 1 second.

If the ELT is accidentally activated, reset it by setting the switch on the ELT to”ON” and immediately back to ”OFF” then to ”AUTO”, or by setting the controlpanel switch momentarily to ”RESET” and allowing it to return to the ”ARMED”position.

When the ELT is operated on ground the ELT will provide an aural warningsignal to the warning horn at the nose gear.

Installation of the ELT

When the programming unit is connected to the ELT, data is automaticallytransferred to the ELT to code it with the aircraft information.

Upon completion, verification is made of the validity of parameters transferredto the ELT.

In case of a failure, the red indicator on the programming unit will flash for 10seconds.

If verification is successful, the red indicator will illuminate continuously for 10seconds.

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A380

25−69


ELT BITE DSI

ELT BITE DSO

ELT BITE DSI

ELT BITE DSO

28VDC

DC GROUNDLIGHT TEST

OUTPUT

INPUT BITE

CHASSIS GND

0VDC

28VDC

DC GND

GND BACKLIGHT

BACKLIGHTHORN CONTROL

REARM/AUTOTEST

ON/AUTO

+LIGHTEXTL. WARNING

ELT ACTIVATED

TEST/RESET

ON/ARMED

V BATT

M

L

K

P

R

13H

13GG

J

A

A

ELT INDICATOR LIGHT

H

C 5

D 7

E 1

F 13

28VDC105PP

NETWORK BUS

3AN

111MVCTL PNL−ELT211

FR91

A

110MV

112MV

FR90

A B

B

112MVANTENNA−ELT290

ANTENNA−BACK UP290

110MVTRANSMITTER−ELT290

1TL1SCI−12314VU123

1TL2SCI−22413VU124

1GNMAINTENANCE−SERVICE PANEL120

33−14 SCH05

33−13 SCH03

B

15

46−11

46−11

19

24−68−00

SEPDC1123

801MV C/BELT RCP

SEPDC1 DC103111XZ6 PCB

3XZUNUSED

23−53 SCH03

143MV

A

A

A

C

C

B

B

A

A

AE

AE

AE

AE

A

A

A

A

A

K1A

K1A

24−73−12

13H

13G

16

25−69−01 SCH01 P003

APUCOCKPIT

AVNCS VENT ELT

HORN RESETLIGHT TEST

FLT INT SVCE INT

FIRECALL

APUSHUTOFF

6WC HORNMECH CALL

127

A/C ON GND

A/C ON GND

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Figure 4 ELT Schematic

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EMERGENCY EQUIPMENTEMERGENCY LOCATOR TRANSMITTER

A380Model RESCU

25−69


ELT PROTABEL “RESCU“

GENERAL

General

The beacon is a compact, bouyant, automatic unit, which consists of atransmitter, a water activated battery, a self−erecting antenna, and a tetheringlanyard assembly.

The frequency of operation and modulation is dependant on the beacon underdiscussion.

Characteristics

The characteristics for the beacons are as follows:

RESCU 99

Frequency:

� 121.5 MHz. Civil aircraft distress frequency.

� 243 MHz. Military aircraft distress frequency.

Modulation:

� The transmission is on both frequencies simultaneously and is a sweptdownward tone

RF Output Power:

� 250mW (typically).

Range:

� 200 to 250 nautical miles at 30,000ft.

Battery Endurance:

� 48 hours minimum.

Physical:

� Length: 55cm

� Width: 8.5cm

RESCU 406

Frequency:

� 121.5 MHz. Civil aircraft distress frequency.

� 243 MHz. Military aircraft distress frequency.

� 406.025 MHz. Satellite frequency.

Modulation:

� Data biphase L encoding, short message, Serialized Aviation User Protocol.

RF Output Power:

� 5 Watts.

Battery Endurance:

� 50 hours minimum.

Physical:

� Length: 68cm

� Width: 8.5cm

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Page 137 |L2

EMERGENCY EQUIPMENTEMERGENCY LOCATOR TRANSMITTER

A380Model RESCU

25−69


.

TRANSMITTER

SECTION

OPERATION

INSTRUCTION

PLATE

ANTENNA

RETAINING

CLIP

SWITCHING

INSTRUCTION

PLATE

BATTERY

COVER

BATTERY SECTION

CONTAINING BATTERY

LIQUID CONTAINER

LANYARD ASSEMBLY

LANYARD

(ATTACHED TO

SLIDE RAFT)

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Figure 5 ELT portabel “RESCU“

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COMMUNICATIONEMERGENCY LOCATOR TRANSMITTER(ELT) TECHTEST 500−12Y

A380Model “TECHTEST 500−12Y“

25−69


ELT TECHTEST 500−12Y

EMERG. LOCATOR TRANSMITTER (ELT) SYSTEM:

Background

Due to JAR OPS 1.820 and JAR OPS 1.830 all aircraft shall be equipped withan ELT which is capable of transmitting on the frequencies 406 MHz and 121.5MHz simultaneously. Therefore it was necessary to replace the old ELT”Rescue 99”.

Location

The new ELT Techtest 500−12Y (HR Smith) is installed inside of theemergency equipment overhead bins, forward of door 2L/H and door 5L/H(STA 760 and STA 2200).

Technical Details

The ELT size is 150 x 87.5 x 37.5 mm and weights around 600 gm.When activated the beacon transmits on 406,025 MHz to the satelite and121.5/ 243,0 MHz to mark its position for rescue.The satelite cover extends to all parts of the world but the time between passesover any point on the globe differs. It can pinpoint the A/C location within 5square kilometer. The 500−12Y beacon continues to transmit 406,025 MHz tothe satelite for 24 hours before shutting down.The 121,5 MHz and 243,0 MHz, which is used for location, is switched on atbeacon activation and continues through until the battery is discharged (at least48 hours).

The ELT can be switched on by pulling the lanyard, or place the activationswitch to the ON position.

A dual frequency (121,5 and 243,0 MHz) transceiver facility is provided andtransmissions by the survivor can be initiated by pressing the „Press to talk“.

All necessary maintenance to be done on this ELT will be done „on wing“.

The ELT is COSPAS−SARSAT and FAA TSO C91A and C126A approved as atype ”S” survival ELT

NOTE: THE ELT IS NOT REPAIRABLE. IT IS ONLY POSSIBLE TOCHANGE THE BATTERY AND TO REPLACE THE ANTENNA IFNECESSARY.

NOTE: THE ELT IS NOT INTERCHANGEABLE BETWEEN THEAIRCRAFTS WITHOUT REPROGRAMMING!REPROGRAMMING WILL BE DONE BY THE WORKSHOP.FOR DLH IT IS (LHT HAM WG 234) WITH SPECIAL TOOLING.

NOTE: THE ELT WILL BE STOWED AND SECURED IN A BRACKET WITHA SPECIAL TAMPER PROOF SEAL.

Operation and BITE

The ELT has a three position switch on the left hand side. The positions are:

− Test : ELT performs a BITE, and the result will be indicated by thebeacon active LED

− OFF: ELT is switched OFF

− ON: ELT is activated and transmits. The ELT can also be activated bypulling the lanyard

Bite results indicated by the LED are

− steady ON: ELT is operational

− fast flashing: Battery failure

− slow flash (flash with pause): Internal fault

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25−69


1.) Switch (On/Off/Test) 2.) Beacon active lamp (LED) 3.) Press to Talk key 4.) Hi/Lo volume switch 5.) Antenna 6.) Battery replacement & antenna torque tool (delivered with new battery)

4

1

5

3

2

6

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Figure 6 ELT TECHTEST 500−12Y

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25−69


Inspection / Check of Battery

− Check the ELT for proper attachment and unbroken seal.

− Check expiry date of ELT battery through the cutout in the bottom of thebracket (The remaining time until next check according to CMS must be morethan 3 month).

NOTE: IF IT IS IMPOSSIBLE TO CHECK THE EXPIRATION DATETHROUGH THE CUTOUT (A MIRROR MIGHT BE NECESSARYFOR THAT INSPECTION) REMOVE THE ELT FROM THEBRACKET TO GET ACCESS TO THE IDENTIFICATION LABLE.

− After this inspection install the ELT in the bracket as described in theTechtest Operating Manual.

NOTE: USE ONLY A TAMPER PROOF SEAL TO SECURE THE ELT INTHE BRACKET.

− To make this inspection easier for the next time install a placard with theexpiration date and your ID stamp on it.

Replacement of Battery

− Remove the tamper proof seal.

− Release the strap which secures the ELT in the bracket.

− Remove the ELT from the bracket.

− Replace ELT Battery

− For battery replacement refer to the Techtest Operating Manual.

LHT only: Send the completed data sheet (SPM 25−66−01 Page 5) toHAM WG234. WG234 makes an entry in the „Lebenslaufkarte“ with thenew battery expiry date.

− After battery replacement perform ELT selftest according TechtestOperating Manual.

− Install the ELT into the bracket. Fasten the strap which secures the ELTin the bracket.

− Install a new tamper proof seal.

NOTE: IF THE SELF TEST FAILS AND THIS IS NOT CAUSED BY THEBATTERY THE ELT MUST BE REPLACED.

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25−69


THIS PAGE INTENTIONALLY LEFT BLANK

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TABLE OF CONTENTS

A380 25 B2X1

Page i

ATA 25 EQUIPMENT/FURNISHINGS 1. . . . . . . . .

ELT REMOTE CONTROL PANEL 2. . . . . . . . . . . . . . . . . . .

EMERGENCY LOCATOR TRANSMITTER 4. . . . . . . . . . .

ELT ANTENNA LOCATION 6. . . . . . . . . . . . . . . . . . . . . . . .

ELT SCHEMATIC 8. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ELT PROTABEL “RESCU“ 10. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

GENERAL 10. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ELT TECHTEST 500−12Y 12. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

EMERG. LOCATOR TRANSMITTER (ELT) SYSTEM: 12.

TABLE OF CONTENTS

A380 25 B2X1

Page ii

TABLE OF FIGURES

A380 25 B2X1

Page i

Figure 97 ELT Remote Control Panel 3. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Figure 98 Emergency Locator Transmitter 5. . . . . . . . . . . . . . . . . . . . . . . .

Figure 99 ELT Antenna location 7. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Figure 100 ELT Schematic 9. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Figure 101 ELT portabel “RESCU“ 11. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Figure 102 ELT TECHTEST 500−12Y 13. . . . . . . . . . . . . . . . . . . . . . . . . . . .

TABLE OF FIGURES

A380 25 B2X1

Page ii

TABLE OF FIGURES

A380 25 B2X1

Page iii

TABLE OF FIGURES

A380 25 B2X1

Page iv

Documents

A380_25_B2X1