LEVEL III - ATA 31 Indicating_Recording Systems

 A380   TECHNICAL TRAINING MANUAL   MAINTENANCE COURSE - T1 & T2 (RR / Metric)   LEVEL III - ATA 31 Indicating/Recording Systems 

This document must be used for training purposes only

Under no circumstances should this document be used as a reference

It will not be updated.

All rights reserved No part of this manual may be reproduced in any form, by photostat, microfilm, retrieval system, or any other means, without the prior written permission of AIRBUS S.A.S.

A380 TECHNICAL TRAINING MANUAL

LEVEL III - ATA 31 INDICATING/RECORDING SYSTEMS Theory System

L1W06161 - L0KT0T0

Cockpit Control Panels Description (3) . . . . . . . . . . . . . . . . . . . . . . . . 2 Control & Display System Description (3) . . . . . . . . . . . . . . . . . . . . . 8 Flight Warning System Description (3) . . . . . . . . . . . . . . . . . . . . . . . 46 Tail Strike Indication System Description (3) . . . . . . . . . . . . . . . . . . 74 Electrical Clock System Description (3) . . . . . . . . . . . . . . . . . . . . . . 80 Interface for Video System Description (3) . . . . . . . . . . . . . . . . . . . . 84 Flight Data Recording System Description (3) . . . . . . . . . . . . . . . . . 92 Control & Display System Maintenance (3) . . . . . . . . . . . . . . . . . . . 96 Indicating/Recording Systems OPS, CTL & IND (3) . . . . . . . . . . . 102 Indicating/Recording Systems Component Loc. (3) . . . . . . . . . . . . 110

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

TABLE OF CONTENTS

Apr 21, 2006 Page 1

A380 TECHNICAL TRAINING MANUAL

COCKPIT CONTROL PANELS DESCRIPTION (3) GENERAL

L1W06161 - L0KT0T0 - LM31D1CKPTCP001

Both ICPs (VMs) and conventional control panels (VUs) are used in the A380 cockpit. The conventional control panels (VUs) are found on the consoles, the main instrument panel, the glareshield and partially on the overhead panel. The ICPs (VMs) are mainly installed on the overhead panel, and on a part of the pedestal.

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

COCKPIT CONTROL PANELS DESCRIPTION (3)

Apr 18, 2006 Page 2

L1W06161 - L0KT0T0 - LM31D1CKPTCP001

A380 TECHNICAL TRAINING MANUAL

GENERAL MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

COCKPIT CONTROL PANELS DESCRIPTION (3)

Apr 18, 2006 Page 3

A380 TECHNICAL TRAINING MANUAL

COCKPIT CONTROL PANELS DESCRIPTION (3) ICP (VM) Description LOCATION

L1W06161 - L0KT0T0 - LM31D1CKPTCP001

The ICPs 1211VM, 1212VM, 1215VM, 1221VM, 1222VM, 1225VM, 1231VM, 1245VM and 1255VM are installed on the overhead panel. The ICP 1135VM, which is called ECP is installed on the pedestal.

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

COCKPIT CONTROL PANELS DESCRIPTION (3)

Apr 18, 2006 Page 4

L1W06161 - L0KT0T0 - LM31D1CKPTCP001

A380 TECHNICAL TRAINING MANUAL

ICP (VM) DESCRIPTION - LOCATION MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

COCKPIT CONTROL PANELS DESCRIPTION (3)

Apr 18, 2006 Page 5

A380 TECHNICAL TRAINING MANUAL

COCKPIT CONTROL PANELS DESCRIPTION (3) ICP (VM) Description (continued) SYSTEM ARCHITECTURE The ICP system receives information and commands A/C systems (LRUs and LRMs). In the ICP system, we can divide the different panels into two categories : - Digital ICP also called ICP CAN, which uses discrete, analog and CAN interfaces. - ICP no CAN, which only uses discrete and analog interfaces. There are five ICPs CAN: 1211VM, 1212VM, 1215VM, 1225VM and 1235VM. These ICPs are connected to the A/C systems (LRUs and LRMs) through the CAN network and the IOMs 1, 2, 5 and 6. The analog and discrete signals are used as backup control. There is also an exchange of data between these ICPs. There are five ICPs no CAN: 1221VM, 1222VM, 1231VM, 1245VM and 1255VM. These ICPs are connected to the A/C systems (LRUs and LRMs) through analog and discrete signals (It is for the control of critical items like relay, pumps, valves...).

L1W06161 - L0KT0T0 - LM31D1CKPTCP001

CAN TECHNOLOGY The CAN bus for data transfer is used to realize a multiplexing, which reduces the wiring and consequently reduces the weight. Moreover it is particularly adapted to mobile systems like in A/C environment, and it is cost-effective with high quality components. The CAN characteristics are: - Multi-master priority based; it deals with periodical and asynchronous data transfer. - A 125 Kbits/s frequency is available. - The data frame format contains a 29-bit identifier field, which includes the priority level of the message (4 bits), the function code (19 bits) and the system identity (6 bits). MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

- The data frame has a 3 bits Inter-Frame Space that gives enough time to the bus handler to transfer a correctly received telegram to a buffer. - The system deals with erroneous frames with a recognition and correction error process. - The norm used is CAN 02B. The loss of one channel does not cause the complete loss of the CAN bus. A failure of the CAN network does not disturb the discrete links functioning. The ICP system is not sensitive to transients; it maintains its behaviour in case of undesirable electrical pulses. The ICP system architecture requires two sides and for each side there are two CAN channels (fulfill the segregation). The ICP system has then four segregated CAN channels , each ICP CAN panel is potentially connected to the 4 channels: Side 1: - CAN 1.1 - CAN 1.2 Side 2: - CAN 2.1 - CAN 2.2 The ECP is connected to another CAN network with two segregated channels: - CAN ECP1 (side 1) - CAN ECP2 (side 2)

COCKPIT CONTROL PANELS DESCRIPTION (3)

Apr 18, 2006 Page 6

L1W06161 - L0KT0T0 - LM31D1CKPTCP001

A380 TECHNICAL TRAINING MANUAL

ICP (VM) DESCRIPTION - SYSTEM ARCHITECTURE & CAN TECHNOLOGY MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

COCKPIT CONTROL PANELS DESCRIPTION (3)

Apr 18, 2006 Page 7

A380 TECHNICAL TRAINING MANUAL

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

L1W06161 - L0KT0T0 - LM31D2CDS000001

General The Control and Display System (CDS) is an avionics world system connected with most of other aircraft systems in order to display flight information, to allow systems monitoring and aircraft environment video monitoring, through eight identical and interchangeable Display Units (DUs). Some novelties regarding the DUs have been introduced on the A380. The Cathode Ray Tubes (CRTs) have been replaced by eight identical and interchangeable enlarged Smart Liquid Crystal Display Units (LCDUs), which support the following conventional display formats: - 2 Primary Flight Displays (PFDs) - 2 Navigation Displays (NDs) - 1 Engine Warning Display (EWD) - 1 System Display (SD) - 2 Multi-Function Displays (MFDs) The two Multi-Function Displays support several remote user applications and as well as fulfill part of the control and display capabilities carried out on the previous Airbus programs by the Multipurpose Control and Display Units (MCDUs). These LCDUs have more interactive capability through the use of cursors or focus, controlled by the Keyboard and Cursor Control Units (KCCUs). The KCCU is a new display control mean installed in the A380 cockpit. It is composed of two functionally redundant parts: the Cursor and Control Device (CCD), based on trackball technology, and the keyboard. There are two KCCUs, one dedicated to each pilot, installed on the pedestal. The CDS includes the Electronic Flight Instrument System (EFIS) and the Electronic Centralized Aircraft Monitoring (ECAM) system. It also supplies display capabilities dedicated to remote user applications fulfilling basic avionics functions. Finally, the CDS includes video capability, and supports various video monitoring functions. MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 8

L1W06161 - L0KT0T0 - LM31D2CDS000001

A380 TECHNICAL TRAINING MANUAL

GENERAL MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 9

A380 TECHNICAL TRAINING MANUAL

CONTROL & DISPLAY SYSTEM DESCRIPTION (3) CDS Architecture CDS Internal Architecture

L1W06161 - L0KT0T0 - LM31D2CDS000001

The CDS has eight identical DUs and two KCCUs. The dialog between DUs is done through Avionics Full Duplex Switched Ethernet (AFDX) via the Avionics Data Communication Network (ADCN). The dialog between KCCUs and DUs is done through CAN (Controler Area Network) buses dedicated to the CDS. There are two CAN buses by side, and each CAN bus on a dedicated side is redundant for reliability purposes. So each DU has two CAN connections. That means that each DU is connected to the ADCN through AFDX cables in order to have the capability to transmit and to share data with all other DUs. The CAN network is mainly used to enable the KCCU to control the DUs. Note that although Cursor Control Device (CCD) and keyboard are in the same equipment item, they are completely segregated; they have independent CAN bus connections.

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 10

L1W06161 - L0KT0T0 - LM31D2CDS000001

A380 TECHNICAL TRAINING MANUAL

CDS ARCHITECTURE - CDS INTERNAL ARCHITECTURE MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 11

A380 TECHNICAL TRAINING MANUAL

CONTROL & DISPLAY SYSTEM DESCRIPTION (3) CDS Architecture (continued)

L1W06161 - L0KT0T0 - LM31D2CDS000001

CDS Interfaces with other Systems In order to elaborate the appropriate displayed pages, the CDS acquires data from aircraft systems through the following way: - Most of the aircraft operational data are acquired in AFDX through the ADCN - Some systems also send data to CDS in A429 in order to overcome a complete loss of ADCN network - Data transmission in discrete for particular signal indication - Optic fibers are used to transmit video signals to the CDS for display on the DU In term of external control, note that the CDS and in particular the KCCUs are linked to the OANS by a CAN bus, in order to manage the display of Airport Navigation screen. Moreover the CDS transmits the following data to the OMS: - Fault messages from the BITE to the CMS for failure isolation, failure memorization and reports generation, - Its configuration to the DLCS for configuration monitoring and management The CMS can launch CDS interactive tests from the maintenance terminals. The DLCS loads the DUs applications, definition files and also DUs pin-programming configuration.

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 12

L1W06161 - L0KT0T0 - LM31D2CDS000001

A380 TECHNICAL TRAINING MANUAL

CDS ARCHITECTURE - CDS INTERFACES WITH OTHER SYSTEMS MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 13

A380 TECHNICAL TRAINING MANUAL

CONTROL & DISPLAY SYSTEM DESCRIPTION (3) Smart Display Unit Description

L1W06161 - L0KT0T0 - LM31D2CDS000001

Hardware Characteristics

Note that these definition files are located in the DUs but do not belong to the CDS. They can be considered as part of the remote user applications.

The CDS system is made of eight identical DUs. All DUs are identical in terms of hardware and software design and capabilities. CDS DUs are based on LCD technology. They are smart displays which means that each DU includes all resources to fulfill CDS functions. Each DU: - has a 6.17" x 8.22" usable display area - Has a video capability through optic fibers - Has bitmap display capabilities through AFDX DUs receive and transmit data to the source computers, remote user applications and control panels. All functions achieved or supported by the CDS are implemented in all DUs. According to the DU location in the cockpit, each implemented function is activated or not by means of pin programming. Besides, each DU includes the following software and data files: - System software for system management: configuration management, BITEs, resource allocation, crew control input management - EFIS/ECAM functions applications providing all display functions under the CDS responsibility - A380 objects library including a set of widgets (graphical interactive or not objects) - One CDS Definition File for EFIS/ECAM functions display definition (under CDS responsibility). A Definition File is a set of data, which specifies to the CDS the graphics/widgets to be displayed on the DUs. - All definition files out of the CDS responsibility for remote user applications display definition (FWS, FMS, FCU backup, AESS, ATC and CMV data)

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 14

L1W06161 - L0KT0T0 - LM31D2CDS000001

A380 TECHNICAL TRAINING MANUAL

SMART DISPLAY UNIT DESCRIPTION - HARDWARE CHARACTERISTICS MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 15

A380 TECHNICAL TRAINING MANUAL

CONTROL & DISPLAY SYSTEM DESCRIPTION (3) Smart Display Unit Description (continued) Display Unit Cooling System

L1W06161 - L0KT0T0 - LM31D2CDS000001

In order to regulate their internal temperature, each DU is connected to the avionics cooling air system. The connection is made at the rear of the equipment. Each DU has two connections: one for air blowing and one for air extraction. KCCUs are not connected to the cooling air system. The avionics cooling air system has two Avionics Ventilation System (AVS) Applications hosted in Core Processing Input/Output Modules (CPIOM) -B3 and B4, which regulate the blowing system. Cooling effect detectors monitor the blown massflow and air temperature. The information concerning the loss of air-cooling capacities (too high air temperature / or too low blown massflow) is provided to the CDS through AFDX bus by the AVS Application in CPIOM-B3/4. In case of emergency electrical configuration, information for loss of air-cooling is still available for remaining DUs.

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 16

L1W06161 - L0KT0T0 - LM31D2CDS000001

A380 TECHNICAL TRAINING MANUAL

SMART DISPLAY UNIT DESCRIPTION - DISPLAY UNIT COOLING SYSTEM MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 17

A380 TECHNICAL TRAINING MANUAL

CONTROL & DISPLAY SYSTEM DESCRIPTION (3) Smart Display Unit Description (continued)

L1W06161 - L0KT0T0 - LM31D2CDS000001

Display Generation and A661 Concept The ARINC 661 specification makes use of a windowing concept, which can be compared to a desktop computer system windowing, but with many restrictions due to the aircraft environment constraints. Each format on a display unit has a set of windows, defined by the current configuration of the CDS. A window is subdivided in layers. These layers are connected to the local or remote user applications, and have an area to display their widgets. Windows are owned and managed by the CDS: it defines a rectangular physical area of the display surface and is linked to a display function (ex: EFIS, FWS, FMS...). A window has one or more layers. A layer gives the mechanism to combine graphical information from several user applications inside one frame. A layer is connected to a unique Remote User Application, but a User Application can use several layers. The layer is the highest-level entity of the CDS known and managed by the Remote User Application. The layers layout effectively displayed in a window are defined according to the current DU configuration. To end, the layers define the widgets (graphical elements) to use in order to build screens display. These graphical elements, stored in the A380 object library can be interactive (accept and react to crew member actions).

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 18

L1W06161 - L0KT0T0 - LM31D2CDS000001

A380 TECHNICAL TRAINING MANUAL

SMART DISPLAY UNIT DESCRIPTION - DISPLAY GENERATION AND A661 CONCEPT MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 19

A380 TECHNICAL TRAINING MANUAL

CONTROL & DISPLAY SYSTEM DESCRIPTION (3) Smart Display Unit Description (continued)

L1W06161 - L0KT0T0 - LM31D2CDS000001

Display Unit Cross Monitoring In order to ensure a high level of reliability, each DU has monitoring capabilities. Each DU monitors its control and display capabilities and its input/output status, both with CDS internal and external equipments. In case of failure/fault detection, the DU automatically inhibits its display and switches in failure mode. The DUs are also feedback monitored in order to ensure the display of critical parameters. The feedback monitoring is done by other DUs. For example, L1 monitors L3, L3 monitors L2, L2 monitors C1. In case of L3 failure or power supply lost, L1 monitors L2. The feedback monitoring process is the following: - The monitored DU sends to the monitoring a display signature of what is display on its screen - The monitoring DU, which receives the same data than the monitored DU, computes the same display for comparison - Monitored DU display signature and monitoring DU recomputed display are compared - If displays are similar, the DU display is correct. In case of display inconsistency, the monitored DU (and the same related DU on the other side) shows the message "Check "DU" (DU = PFD, ND...). In addition, an alarm is sent to the FWS and to the CMS that respectively generate a warning and a fault message.

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 20

L1W06161 - L0KT0T0 - LM31D2CDS000001

A380 TECHNICAL TRAINING MANUAL

SMART DISPLAY UNIT DESCRIPTION - DISPLAY UNIT CROSS MONITORING MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 21

A380 TECHNICAL TRAINING MANUAL

CONTROL & DISPLAY SYSTEM DESCRIPTION (3) KCCU description

L1W06161 - L0KT0T0 - LM31D2CDS000001

The KCCU is a new display control mean installed in the A380 cockpit. It is composed of two functionally redundant parts: the CCD, based on trackball technology, and the keyboard. There are two KCCUs, one dedicated to each pilot, installed on the pedestal. The two keyboards are of QWERTY type. They are multifunction that means that they can control different applications at a given time. Each keyboard contains a classical keypad with supplemental keys dedicated to particular controls: - Function keys (operational shortcuts to increase effectiveness of crew control) - Alphanumeric keys - Arrow keys The two CCDs are based on trackball technology for Cursor/focus navigation on display unit screens. They also include a few buttons to select objects and to make other particular actions: - Validation knob - Scrolling wheel - Right/left navigation keys

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 22

L1W06161 - L0KT0T0 - LM31D2CDS000001

A380 TECHNICAL TRAINING MANUAL

KCCU DESCRIPTION MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 23

A380 TECHNICAL TRAINING MANUAL

CONTROL & DISPLAY SYSTEM DESCRIPTION (3) EFIS Description

L1W06161 - L0KT0T0 - LM31D2CDS000001

EFIS Function The EFIS function purpose is to collect and to display information related to the aircraft guidance and navigation. This information is presented in front of each pilot on the PFD Main Zone and on the ND. The PFD Main Zone displays, on the outer display unit, the flight information required for short-term flight. The ND displays, on the inner display unit, the information required for navigation. To display this information, each DU acquires data from the A/C systems. It mainly acquires: - Air Data Inertial Reference System (ADIRS) data, Concentrator and Multiplexer for Video (CMV) display request, Slat Flap Control Computer data through AFDX via ADCN - Backup connections, ADIRS and SFCC data in A429 - Video data from the CMV by optic fibers Moreover the EFIS, and in particular each PFD give independently to the Audio Management Unit (AMU) the "LS indication displayed on PFD" condition. This condition is triggered when the pilot selects the LS key on EFIS Control Panel. The selected Distance Measuring Equipment (DME) beacon indications are shown on the PFD. This indication is used by the AMU to retransmit to the crew the DME station collocated to the Instrument Landing System (ILS) station instead of the VHF Omni-directional Range (VOR) station. Interactivity with EFIS is given independently to each pilot, for display selection and reconfiguration, through: - The CAPT and F/O KCCUs, which enable to control cursor or focus in order to select interactive functions on their dedicated DUs, - The CAPT and F/O EFIS control panels which give the selection of the display modes, - The CAPT and F/O CDS Reconfiguration control panels, which enable DUs reconfigurations. MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 24

L1W06161 - L0KT0T0 - LM31D2CDS000001

A380 TECHNICAL TRAINING MANUAL

EFIS DESCRIPTION - EFIS FUNCTION MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 25

A380 TECHNICAL TRAINING MANUAL

CONTROL & DISPLAY SYSTEM DESCRIPTION (3) EFIS Description (continued)

Note that the VD also displays a ND FM Dialog Window.

L1W06161 - L0KT0T0 - LM31D2CDS000001

EFIS Display Zone Allocation The EFIS information is presented on the PFDs Main Zone and on the NDs. Each PFD displays short-term flight information and is divided into two zones. The PFD Main Zone shows conventional Primary Flight Display data such as: - Aircraft attitudes - Air speed - Altitude and vertical speed - Heading - Information on flight modes - Radio altitude - Landing system data The lower zone, which is not part of the EFIS, is related to the ECAM system. Each ND displays medium/long term flight information dedicated to navigation and is also divided into two different zones. The upper part called ND Main Zone displays - Aircraft location with respect to the flight plan and/or navaids, - Weather radar information - Surveillance information The lower part called Vertical Display (VD) Zone, which displays vertical information, takes into account the vertical selected or managed profile, and improves crew awareness on A/C vertical situation by providing a synthetic view of vertical parameters such as: - Aircraft altitude - Safe altitude - Trajectory - Terrain and weather MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 26

L1W06161 - L0KT0T0 - LM31D2CDS000001

A380 TECHNICAL TRAINING MANUAL

EFIS DESCRIPTION - EFIS DISPLAY ZONE ALLOCATION MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 27

A380 TECHNICAL TRAINING MANUAL

CONTROL & DISPLAY SYSTEM DESCRIPTION (3) EFIS Description (continued) EFIS Control Panels

L1W06161 - L0KT0T0 - LM31D2CDS000001

The flight crew interacts with the EFIS through: - The KCCUs - The EFIS control panels - The CDS RECONF control panels for reconfigurations The EFIS-CP is mainly composed of: - Navigation data display settings buttons - Barometer settings which have a barometer reference display window and a barometer reference selector - PFD controls: localizer and glide slope scales and velocity vector - ND controls: ND mode and range selection Each CDS RECONF CP is composed of: - PFD, ND, MFD brightness selector - PFD, ND switching button - Reconfiguration buttons

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 28

L1W06161 - L0KT0T0 - LM31D2CDS000001

A380 TECHNICAL TRAINING MANUAL

EFIS DESCRIPTION - EFIS CONTROL PANELS MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 29

A380 TECHNICAL TRAINING MANUAL

CONTROL & DISPLAY SYSTEM DESCRIPTION (3) ECAM Description

L1W06161 - L0KT0T0 - LM31D2CDS000001

ECAM Function The ECAM gives information to the flight crew about normal and abnormal procedures. The ECAM system displays A/C system information for monitoring purposes and provides a display support to the Flight Warning System (FWS) as well. ECAM information is presented to both pilots on: - A single Engine Warning Display (EWD) in normal configuration installed on the upper ECAM DU. - The main zone of a single System Display (SD) installed normally on the lower ECAM DU. - Both PFDs lower zone in normal configuration installed on the outer DUs. The ECAM architecture is based on LCD smart DUs. Each ECAM LCDU acquires data from A/C systems to elaborate the Engine Primary display on the EWD and the A/C systems synoptics pages on the SD. It also acquires and displays data from the FWS. In normal systems operation, the ECAM function gives the necessary information to assist the flight crew to operate and monitor the aircraft systems: - System synoptic pages on the SD - Memos on the E/WD and PFD Lower zone from the FWS - Normal checklists on the E/WD, on flight crew request, also generated by the FWS In abnormal systems operation, the ECAM function helps the flight crew to manage system failures and aircraft abnormal configuration: - It displays visual warning and caution generated by the FWS - It displays associated procedures, limitations and memos also generated by the FWS - It displays synoptic pages related to system failure To display this information, each DU acquires data from the aircraft systems. It acquires mainly: MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

- Aircraft data in order to build SD synoptic pages in AFDX - SFCC data for synoptic pages in AFDX and in A429 for backup connections - Flight Warning System (FWS) data in AFDX (ARINC 429 backup) for warning/caution, memos/limitations and procedures Interactivity with the ECAM is given to both pilots, for display selection and reconfiguration: - Through a single ECAM Control Panel (ECP) for pages control and selection. - The CAPT and F/O CDS Reconfiguration control panels, which enable DUs reconfigurations. Note that the ECP controls the ECAM and the FWS via the ADCN or directly through backup connections. In case of ECP failure, some commands ("CLR", "RCL", "STS", "EMER CANC", "VALID" keys and SCROLL UP/DOWN device) are directly connected to FWS in discrete signal to fulfil the main ECP function. In the same way, the "ALL" key is directly connected to the CDS in discrete in case of ECP failure.

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 30

L1W06161 - L0KT0T0 - LM31D2CDS000001

A380 TECHNICAL TRAINING MANUAL

ECAM DESCRIPTION - ECAM FUNCTION MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 31

A380 TECHNICAL TRAINING MANUAL

CONTROL & DISPLAY SYSTEM DESCRIPTION (3) ECAM Description (continued)

L1W06161 - L0KT0T0 - LM31D2CDS000001

ECAM Display Zone Allocation The ECAM information is presented on several display units: - The EWD - The SD - The PFDs A/C Configuration and Flight Limitation Zone The Engine Warning Display is shown to both pilots and divided into two zones: - The Engine Display (ED), which displays all engine primary parameters. These data are driven by the ECAM itself. - The Warning Display (WD), which supplies Warning/Caution messages and related procedures, Memos, general Limitations, normal checklists and abnormal procedures. These data are driven by the FWS. The SD image is presented to both pilots and is divided into three zones: o An upper zone called SD Main Zone displays the A/C systems synoptic pages driven by the ECAM itself or the Status page driven by the FWS. o A middle zone dedicated to permanent data related to temperature, time, weight and fuel, driven by the ECAM as well. o A lower zone called Air Traffic Control (ATC) Mail Box, which is not driven by the ECAM. The A/C Configuration and Flight Limitation Zone installed on the lower part of the PFDs gives slats, flaps and trim position, memos and limitations. Note that all memos and limitations generated by the FWS are displayed on the WD while PFDs display only Memos and Limitations related to short-term flight.

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 32

L1W06161 - L0KT0T0 - LM31D2CDS000001

A380 TECHNICAL TRAINING MANUAL

ECAM DESCRIPTION - ECAM DISPLAY ZONE ALLOCATION MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 33

A380 TECHNICAL TRAINING MANUAL

CONTROL & DISPLAY SYSTEM DESCRIPTION (3) ECAM Description (continued) ECAM Control Panel

L1W06161 - L0KT0T0 - LM31D2CDS000001

The ECP is an Integrated Control Panel (ICP) and is used to control the E/WD and the SD DUs. It is the main interface between the flight crew and the ECAM. It lets the pilots: - Manage alert messages ("CLR", "RCL", "EMER CANC", "RCL LAST", cursor moving and "MORE INFO" page - Call for the manual checklists and abnormal/supplementary procedures - Manually call the STATUS page - Manually select the necessary synoptic page on SD - Select video source to display - Switch ON/OFF E/WD an SD and to control the brightness of these DUs The ECP is connected via the CAN bus to IOMs7 and 8 in order to send manual crew requests to the dedicated system via the ADCN. Note that in order to overcome an ECP failure, some buttons (cf illustration) are directly connected to the FWS or CDS in discrete to fulfil ECP main capabilities.

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 34

L1W06161 - L0KT0T0 - LM31D2CDS000001

A380 TECHNICAL TRAINING MANUAL

ECAM DESCRIPTION - ECAM CONTROL PANEL MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 35

A380 TECHNICAL TRAINING MANUAL

CONTROL & DISPLAY SYSTEM DESCRIPTION (3) ECAM Description (continued)

In the same way if the ECAM is in a manual mode configuration, an incoming warning automatically triggers the failure related mode.

L1W06161 - L0KT0T0 - LM31D2CDS000001

ECAM Modes Description The ECAM operates according to four modes related to the A/C system synoptic pages presentation on the SD. These modes are: - The Normal mode - The Manual mode - The Advisory mode - The Failure related mode In Normal mode, without any A/C system failure, the SD presents automatically A/C system synoptic page according to the current flight phase computed by the FWS. In Manual mode, without any A/C system failure, the SD presents A/C system synoptic page selected by the crew via the ECP. Note that the manual mode can override all other modes. The ECAM permanently monitors the value of some critical system parameters. When a value drifts from its normal range, the Advisory mode is triggered and the ECAM displays automatically the related SD page, with the affected parameter pulsing. When an A/C system failure occurs the ECAM displays on the EWD the warning and caution messages generated by the FWS. In this case the failure related mode displays automatically on the SD the related A/C system synoptic page. The image displayed on the DU, which process SD format is the result of the CDS SD selector logic which manages the priorities between the different ECAM modes. ECAM modes are triggered according to the following higher to lower priority order: - Manual mode/failure related mode - Failure related mode/manual mode - Advisory mode - Flight phase related mode Note that a manual crew input automatically triggers the ECAM manual mode, even if the ECAM failure related mode was operating. MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 36

L1W06161 - L0KT0T0 - LM31D2CDS000001

A380 TECHNICAL TRAINING MANUAL

ECAM DESCRIPTION - ECAM MODES DESCRIPTION MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 37

A380 TECHNICAL TRAINING MANUAL

CONTROL & DISPLAY SYSTEM DESCRIPTION (3) ECAM Description (continued) Advisory mode

L1W06161 - L0KT0T0 - LM31D2CDS000001

When a monitored parameter is deviating from its defined operational range, an "ADV" indication appears on the bottom line of the E/WD. The advisory indication may appear together with other cockpit indications, depending on the aircraft configuration: - If the SD displays a flight phase page, in case of an advisory condition, the SD automatically displays the associated system display page, and the associated pushbutton white light on the ECP comes on - If the SD already displays a system page following an advisory occurrence: if there is another advisory condition, there will be no additional indication, until the first advisory is cleared - If the SD displays a crew-requested system page: if there is an advisory condition, the associated pushbutton on the ECP will flash. This prompts the flight crew to press it - If the SD displays a system page following an ECAM alert, there will be no further indication on the E/WD The ADV indication disappears from the E/WD when: - The flight crew presses the associated pushbutton on the ECP - The parameter returns to its defined operational range

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 38

L1W06161 - L0KT0T0 - LM31D2CDS000001

A380 TECHNICAL TRAINING MANUAL

ECAM DESCRIPTION - ADVISORY MODE MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 39

A380 TECHNICAL TRAINING MANUAL

CONTROL & DISPLAY SYSTEM DESCRIPTION (3) Remote Users Applications Description Remote Users Applications Architecture

L1W06161 - L0KT0T0 - LM31D2CDS000001

In addition to the EFIS and ECAM functions, the CDS also gives interactive display resources for the following systems: - The Flight Warning System (FWS) - The Concentrator and Multiplexor for Video (CMV) - The Flight Management System (FMS) - The Aircraft Environment Surveillance System (AESS) - The Air Traffic Control System (ATCS) - The Flight Control Unit (FCU) Backup These systems are not hosted in the CDS. The CDS acquires their parameters through AFDX via the ADCN, except for the Concentrator and Multiplexer for Video (CMV) that is directly connected to CDS via optic fibers. These parameters are used to build the related page on the DUs. The CDS gives to most of these systems a dedicated Human-Machine Interface (HMI) called Multi-Function Display (MFD).

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 40

L1W06161 - L0KT0T0 - LM31D2CDS000001

A380 TECHNICAL TRAINING MANUAL

REMOTE USERS APPLICATIONS DESCRIPTION - REMOTE USERS APPLICATIONS ARCHITECTURE MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 41

A380 TECHNICAL TRAINING MANUAL

CONTROL & DISPLAY SYSTEM DESCRIPTION (3) Remote Users Applications Description (continued)

L1W06161 - L0KT0T0 - LM31D2CDS000001

MFD Description and Control The MFD is an interactive display resource, which allows the crew to control the following remote user applications: - FMS - The ATCS - The AESS - The FCU Back-up functions In addition it lets these systems to display computed data. The MFD human-machine interface is based on KCCU interactivity, which enables pages selection via different menus, and data insertion. There is one MFD for each pilot, and each MFD is divided into two different zones: - The upper MFD zone specific to each system, is used for the page selection - The MFD Main Display, which is dedicated to the display of remote user application functions. The MFD can show four different menus: - FMS managed by the FMS - ATC COM managed by the ATC system - SURV managed by the Aircraft Environment Surveillance - FCU BKUP managed by the FCU Backup The MFD is divided into four areas: - One small area at the top, to show the MFD menu - One small area at the top, below the MFD menu, to show the system sub-menu - One large area in the middle, to show the page content of the system sub-menu - One small area at the bottom, to show messages. This area is referred to as the "bottom message area".

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 42

L1W06161 - L0KT0T0 - LM31D2CDS000001

A380 TECHNICAL TRAINING MANUAL

REMOTE USERS APPLICATIONS DESCRIPTION - MFD DESCRIPTION AND CONTROL MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 43

A380 TECHNICAL TRAINING MANUAL

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

L1W06161 - L0KT0T0 - LM31D2CDS000001

CDS Display Allocation Synthesis

- Permanent data Zone

The A380 cockpit CDS functions allocation philosophy is based on the Airbus family T: PFD-ND Capt, EWD-SD, ND-PFD F/O. These functions are shared out in the cockpit on the LCDUs and controlled by different interactive control means. The KCCU is a new display control mean installed in the A380 cockpit: it introduces more interactivity between the DUs and the crew through the use of cursors/focus. There are two KCCUs, one dedicated to each pilot, installed on the pedestal. Each KCCU controls: - The onside ND, for medium/long term lateral navigation - The onside MFD, for FMS, Air Traffic Control Communication (ATC-COM) system, Aircraft Environment Surveillance system (AESS) and FCU backup functions. - The SD lower part, which displays the ATC Mail Box The ECP controls the WD part of the EWD for the management and the display of Warning and Cautions, Normal Checklist, and abnormal procedures. It controls also the SD Main Zone for the selection of A/C systems synoptics and Status pages. Each EFIS CP controls: - The onside PFD Main Zone for short-term guidance - The onside ND Main Zone and Vertical Display for Medium/Long term navigation pages selection and display range. Each cockpit side is fully redundant: same processing, display and control capabilities Each EFIS-CP is used for the control of: - PFD Main Zone (not directly) - ND (directly) Note that the following Display Unit zones cannot be reached through control panels: - PFD Lower Zone (A/C configuration and flight limitation) - Engine parameters Zone MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 44

L1W06161 - L0KT0T0 - LM31D2CDS000001

A380 TECHNICAL TRAINING MANUAL

CDS DISPLAY ALLOCATION SYNTHESIS MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 45

A380 TECHNICAL TRAINING MANUAL

FLIGHT WARNING SYSTEM DESCRIPTION (3) General

L1W06161 - L0KT0T0 - LM31D3FWS000001

The Flight Warning System (FWS) is a centralized system improving the crew situation awareness in normal and abnormal A/C system operation. In case of aircraft systems failure or A/C dangerous configuration, the FWS:   Alerts the crew in real time about the seriousness level of the failure   Gives failure identification and categorization through caution and warning messages   Helps pilots to isolate the failure through a correct procedure   Gives failure consequences on A/C status and flight operations (limitations) For that the FWS monitors all the A/C system, identifies and classifies failures, and activates aural and visual alert indications thanks to cockpit peripherals. It gives also abnormal procedures related to systems undetectable events. In normal operations, the FWS provides also an operational assistance to the crew via Normal Checklist, memos and aural announcements in approach.

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 46

L1W06161 - L0KT0T0 - LM31D3FWS000001

A380 TECHNICAL TRAINING MANUAL

GENERAL MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 47

A380 TECHNICAL TRAINING MANUAL

FLIGHT WARNING SYSTEM DESCRIPTION (3)

L1W06161 - L0KT0T0 - LM31D3FWS000001

FWS Architecture The FWS is mainly composed of two FWS Applications hosted in the Core Processing Input/Output Modules (CPIOM) -C1 and C2. These CPIOM-C1 and C2 acquire data from A/C systems, which can be Line Replaceable Modules (LRM), Line Replaceable Unit (LRUs) with Avionics Full Duplex Switched Ethernet (AFDX) interface, or conventional LRUs. This data acquisition is done in AFDX via the Aircraft Data Communication Network (ADCN) for LRMs and LRUs with AFDX interface, and in A429 for conventional LRUs. Moreover, in order to overcome a total loss of the ADCN, LRMs, and LRUs with AFDX interface are also directly connected in A429. Then if an A/C system failure or configuration change is detected, or in case of A/C abnormal configuration, the FWS generates alert analog signals controlling directly the loudspeakers trough the Audio Management Units (AMUs). The FWS generates discrete signals to control visual Attention Getters, and A429 alerts for warning and cautions messages to display on the Control and Display System (CDS). This is the alert processing. The crew interfaces with the FWS through the ECAM Control Panel (ECP). Regarding the FWS, the ECP mainly: - Manages caution and warning related procedures - Calls the Status page on the System Display (SD) - Calls and handles the normal checklists and abnormal procedures. The ECP is connected to the FWS applications via Input/Output Modules (IOMs) (through CAN buses connections) and via the ADCN in AFDX. Note that in case of ADCN loss, discrete backup connections keep all its functions operational. In addition, the FWS sends its own BITE messages, and data such as alerts and flight phases to the Central Maintenance System (CMS) for broadcasting and maintenance data consolidation. MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 48

L1W06161 - L0KT0T0 - LM31D3FWS000001

A380 TECHNICAL TRAINING MANUAL

FWS ARCHITECTURE MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 49

A380 TECHNICAL TRAINING MANUAL

FLIGHT WARNING SYSTEM DESCRIPTION (3) Alerts and Flight Phases Computation

L1W06161 - L0KT0T0 - LM31D3FWS000001

The FWS fulfils the following functions: - Relevant FW data acquisition and computation: signals acquisition and computation from different sensors in order to detect an A/C system failure. It also has a flight phase's calculation - Alerts Identification: this step identifies "Normal alerts" and "failure-linked" alerts - Alerts Management: identify accurately the situation and classify system failures (according to emergency level, consequences...). It has an alert level classification, alert prioritization, and inhibition - Automatic alerts and associated information display and recording: Alert the crew in case of a failure. Give to the crew (flight and maintenance) all the relevant information to make the accurate action - Alerts and associated info display on crew input: let pilots isolate failures and make the necessary corrective actions.

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 50

L1W06161 - L0KT0T0 - LM31D3FWS000001

A380 TECHNICAL TRAINING MANUAL

ALERTS AND FLIGHT PHASES COMPUTATION MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 51

A380 TECHNICAL TRAINING MANUAL

FLIGHT WARNING SYSTEM DESCRIPTION (3)

L1W06161 - L0KT0T0 - LM31D3FWS000001

Flight Phases Characteristics

If the data are not available to compute the flight phases, the FWS selects by default the cruise phase (8).

Normal aircraft flight is divided by the FWS into 12 phases. Each flight phase agrees with either an A/C or a flight configuration change. These flight phases are then used by the CDS to compute the ECAM normal mode or by the FWS itself to inhibit during critical flight phases alerts related to non-critical flight failures. Moreover, the flight phases will provide contextual information about failures to the CMS. The flight phases definition is based on the following criterion: - Flight phase 1: A/C at the gate (parking), some tests and verifications may be done before flight (engine are shut down) - Flight phase 2: Taxi out - Flight phase 3: 1st step of TO, engines are set to take-off power - Flight phase 4: 2nd step of TO, A/C speed is between 80kts and V1 - Flight phase 5: 3rd step of TO, A/C speed is above V1, A/C is still on ground - Flight phase 6: 1st step of climb, A/C takes off (flight condition) and starts climb phase until 400ft - Flight phase 7: 2nd step of climb, A/C climb phase from 400ft until 1500ft - Flight phase 8: Cruise - Flight phase 9: Descent phase before landing - Flight phase 10: Landing phase, A/C is on ground and speed decreases - Flight phase 11: Taxi in - Flight phase 12: A/C at the gate (parking), A/C is stopped (engines are shut down) FWS computes the flight phases according to: - Engine parameters - Computed Air Speed - Altitude - Gear compressed information from L/G system. MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 52

L1W06161 - L0KT0T0 - LM31D3FWS000001

A380 TECHNICAL TRAINING MANUAL

FLIGHT PHASES CHARACTERISTICS MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 53

A380 TECHNICAL TRAINING MANUAL

FLIGHT WARNING SYSTEM DESCRIPTION (3) FWS Functions in A/C and System Normal Configuration

L1W06161 - L0KT0T0 - LM31D3FWS000001

Normal Checklists On the A380, the normal checklists, which can be carried out by the crew at different flight phases, have been implemented into the FWS. The crew has the capability to choose the related checklist and their associated procedures on the EWD. For non-sensed items, actions are manually confirmed through the ECP. An automatic feedback is given for sensed items. T he C/L Menu page, which is either manually called by pushing the NORM C/L pushbutton or automatically activated, lists and designates the C/L that must be done during the different flight phases. The C/L Menu is automatically activated in the following cases: - When the last warning message (independent, primary, secondary) is cleared on the EWD, and if there is at least one active deferred procedure - In approach phase, below 2000 ft, when the baro-corrected altitude is selected by the crew or when slats are extended, and if there is at least one active deferred procedure - When the C/L menu page is activated, the cyan designation frame is automatically located on the first incomplete C/L appearing after the last complete C/L. The designation frame can be manually moved by the crew so as to validate the desired C/L. Validate (VALID pushbutton) the designated line calls the selected C/L. - A normal C/L page is manually activated from the C/L Menu page. The « C/L COMPLETE » item is used to manually declare a normal C/L complete. When declared complete, the C/L page is automatically deactivated and frozen in its current state: the C/L title turns from cyan to grey in the C/L Menu and the C/L items are greyed. The "RESET " item lets manually reset the whole content of a C/L. The "CLEAR" pushbutton activated on a normal C/L page lets go back to the C/L Menu page. MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 54

L1W06161 - L0KT0T0 - LM31D3FWS000001

A380 TECHNICAL TRAINING MANUAL

FWS FUNCTIONS IN A/C AND SYSTEM NORMAL CONFIGURATION - NORMAL CHECKLISTS MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 55

A380 TECHNICAL TRAINING MANUAL

FLIGHT WARNING SYSTEM DESCRIPTION (3) FWS Functions in A/C and System Normal Configuration (continued) Memos

L1W06161 - L0KT0T0 - LM31D3FWS000001

The FWS generates all memos indications, which inform the crew about the A/C configuration following routine crew action. Memos are displayed on the PFDs Lower Zone and on the EWD. All memos generated by the FWS are displayed on the EWD. In addition the memos directly related to the flight are also displayed on the PFDs lower zone. Note that all these memo information are strings of twenty characters maximum.

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 56

L1W06161 - L0KT0T0 - LM31D3FWS000001

A380 TECHNICAL TRAINING MANUAL

FWS FUNCTIONS IN A/C AND SYSTEM NORMAL CONFIGURATION - MEMOS MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 57

A380 TECHNICAL TRAINING MANUAL

FLIGHT WARNING SYSTEM DESCRIPTION (3) FWS Functions in A/C or System Abnormal Configuration

L1W06161 - L0KT0T0 - LM31D3FWS000001

Alerts Categorization Display Effects on ECAM There are three types of failures: - Independent failure - Primary failure - Secondary failure An Independent failure is a failure, which affects an isolated system or item of equipment without affecting another one. A Primary failure is a failure of a system or of an item of equipment, which causes the loss of other systems or equipments. A secondary failure is the loss of a system or of an item of equipment resulting from a Primary failure These failures are displayed on the EWD, but depending on the type of the failure, they are not displayed in the same way. Independent failures display characteristics: - Red or amber message - System indication underlined Primary failures display characteristics: - Red or amber message - System indication underlined - Warning text surrounded Secondary failures display characteristics: - Amber asterisked message

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 58

L1W06161 - L0KT0T0 - LM31D3FWS000001

A380 TECHNICAL TRAINING MANUAL

FWS FUNCTIONS IN A/C OR SYSTEM ABNORMAL CONFIGURATION - ALERTS CATEGORIZATION DISPLAY EFFECTS ON ECAM MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 59

A380 TECHNICAL TRAINING MANUAL

FLIGHT WARNING SYSTEM DESCRIPTION (3) FWS Functions in A/C or System Abnormal Configuration (continued)

L1W06161 - L0KT0T0 - LM31D3FWS000001

Alerts Priorities and Inhibitions In order to manage the display of warning / caution and the generation of attention getters alerts and aural announcements, the FWS applies a priority and inhibition logic. Alerts are classified in three levels, based on the following priority order: - Level 3 alerts - Level 2 alerts - Level 1 alerts The most critically classified alerts have preeminence over less critically alerts and the last has preeminence over prior alerts of the same criticism: Level 3 has priority over the Level 2 and Level 1, and within each level, an order of priority between warnings is also defined. Note that several warning messages with their relevant procedures may be displayed in the limit of the available area on the EWD. They are always displayed in the same order, which is not dependant on the chronology of the occurence of the different warnings. Two different sounds cannot be broadcasted at the same time and two different synthetic voices cannot be broadcasted at the same time. But one sound and one synthetic voice can be broadcasted together. The MASTER WARN and MASTER CAUT lights can come on simultaneously. The inhibition logic is implemented so as to fulfill the following functions: - Ensure proper alerts only when necessary; a warning or indication which has no signification on a given configuration is not activated (e.g.: hydraulic low pressure warning is inhibited before engine starting)

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

- Avoid alerts without interest for a flight phase. The inhibition logic filters the presentation of alerts according to the flight phase knowing that the flight is divided into 12 phases. - Let the crew cancel alerts presentation when corrective actions have been done (CLEAR function). - During takeoff and landing phases, lots of warnings and cautions are inhibited to avoid nuisances and useless workload to the crew This information is given in MAGENTA in the memo list presented on the EWD:"T.O INHIB" and "LDG INHIB".

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 60

L1W06161 - L0KT0T0 - LM31D3FWS000001

A380 TECHNICAL TRAINING MANUAL

FWS FUNCTIONS IN A/C OR SYSTEM ABNORMAL CONFIGURATION - ALERTS PRIORITIES AND INHIBITIONS MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 61

A380 TECHNICAL TRAINING MANUAL

FLIGHT WARNING SYSTEM DESCRIPTION (3) FWS Functions in A/C or System Abnormal Configuration (continued)

L1W06161 - L0KT0T0 - LM31D3FWS000001

Status The Status Page is an operational status of the A/C after system failure. It draws crew attention to limitations and deferred procedures (part of the normal checklist). It presents inoperative systems and general information. Note that when the MORE indication is displayed, deeper information is available within the Status More Info Page. In normal operation, the EWD, PFD and SD can display status messages, which are: - An operational summary of the aircraft condition, - An explanation of possible auto land capability downgrading, - Indications of the aircraft status (inoperative systems) following all the failures, some affecting the flight, and some not affecting the flight (redundancy loss) - General contents, limitations (speed, altitude), peculiar or emergency deferred procedures, information, etc.... The Memos/limitations page on the EWD indicates the active limitations, which are messages indicating some operational constraints following a degradation of the aircraft capability. Up to 8 of them can also be displayed on the PFD. The Status page on the SD gathers the messages necessary to the operational evaluation of the aircraft configuration. This page gathers the following status messages: - The « LIMITATIONS » reminder recalling the presence of limitations on the EWD (and the PFD) - the deferred procedure reminder recalling the presence of postponed procedures in the C/L pages. Its wording depends on the category of active deferred procedures

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

- the inoperative systems of the types « ALL PHASES » and « APPR & LDG », indicating the functions that are unavailable over the whole flight or only during approach and landing phases. This page also mentions, through the « MORE » reminder in the title, the presence of messages in the Status More info page. If the Status page is not empty, a « STS » reminder is displayed at the bottom of the memos/limitations page on the EWD. This Status page mainly appears once the crew has cleared all the pages related to the current warning/caution management, or upon manual call. The Status More Info page on the SD gathers the complementary messages enabling a better analysis and understanding of the aircraft global configuration. This page gathers the following status messages: - The inoperative systems of the type « REDUND LOSS », indicating the functions that are no longer redundant - The cancelled cautions list, which indicates the cautions that have been cancelled by the EMER CANC function - Some complementary information

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 62

L1W06161 - L0KT0T0 - LM31D3FWS000001

A380 TECHNICAL TRAINING MANUAL

FWS FUNCTIONS IN A/C OR SYSTEM ABNORMAL CONFIGURATION - STATUS MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 63

A380 TECHNICAL TRAINING MANUAL

FLIGHT WARNING SYSTEM DESCRIPTION (3) FWS Functions in A/C or System Abnormal Configuration (continued) Limitations

L1W06161 - L0KT0T0 - LM31D3FWS000001

The FWS also generates all limitations indications, which inform the crew about the A/C flight capabilities. Limitations are displayed on the EWD and on the PFDs Lower Zone. All limitations generated by the FWS are displayed on the EWD. In addition, the limitations related to the flight are also displayed on the PFDs Lower zones (ex: Speed limitation).

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 64

L1W06161 - L0KT0T0 - LM31D3FWS000001

A380 TECHNICAL TRAINING MANUAL

FWS FUNCTIONS IN A/C OR SYSTEM ABNORMAL CONFIGURATION - LIMITATIONS MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 65

A380 TECHNICAL TRAINING MANUAL

FLIGHT WARNING SYSTEM DESCRIPTION (3) FWS Functions in A/C or System Abnormal Configuration (continued)

L1W06161 - L0KT0T0 - LM31D3FWS000001

Abnormal and Deferred Procedures The crew can manually activate some emergency and abnormal procedures that are not sensed by the systems (e.g. « COCKPIT WINDOW CRACKED »). These procedures are called « Supplementary Abnormal Procedures ». Pushing the ABN PROC pushbutton manually activates the Supplementary Abnormal Procedures Menu page. This menu is organized in different sub-menus, which let reach and activate various abnormal procedures. The CLEAR command lets navigate and go back to the previous Menu level. The procedure titles presented at the top of the Supplementary Abnormal Procedures Menu are red or amber alerts requiring a quick access. The other lines presented in white at the bottom of the menu are sub-menu titles related to less critical warnings (generally amber cautions, and eventually red warnings). The activation is performed by validating the « ACTIVATE » line located below the heading and title of the selected failure. The Supplementary Abnormal Procedures differ from the other procedures by their activation mode. However, once activated, they are displayed and processed in the same way as the other warnings on the Alert/Supplementary Abnormal Procedures page on the EWD. The crew can manually deactivate this kind of procedures: - By means of the EMER CANC function - By un-ticking the ACTIVE line at the top of the procedure If a Supplementary Abnormal Procedure is cleared and if the crew tries to re-access it through the Supplementary Abnormal Procedure Menu, it will automatically be recalled. The C/L Menu page, that is either manually called by pushing the NORM C/L pushbutton or automatically activated, is used to list and manually designate the « deferred procedures » to make (if present). MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

. The « deferred procedures », which are of three types (APPROACH, LANDING and PENDING), are displayed at fixed positions in the C/L menu only if some deferred procedures of the related type are really active. A « deferred procedure » page is manually activated from the C/L Menu page. When the whole items of a « deferred procedure » are done, its title turns from amber to white in the C/L Menu. The CLEAR command applied on a « deferred procedure » page enables to go back to the C/L Menu page.

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 66

L1W06161 - L0KT0T0 - LM31D3FWS000001

A380 TECHNICAL TRAINING MANUAL

FWS FUNCTIONS IN A/C OR SYSTEM ABNORMAL CONFIGURATION - ABNORMAL AND DEFERRED PROCEDURES MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 67

A380 TECHNICAL TRAINING MANUAL

FLIGHT WARNING SYSTEM DESCRIPTION (3) Aural Announcements

L1W06161 - L0KT0T0 - LM31D3FWS000001

Aural Announcements Generation Architecture Aural announcement generation and management is based on the communication between the FWS and the Audio Management Units (AMUs) that are part of the Radio and Audio Management System (RAIMS). The AMUs send to the FWS the CALL indication (SELCAL, SATCOM) in discrete for aural warning transmission. These signals are received by IOMs 7/8 and then sent to the FWS Applications in AFDX through the ADCN. In case of SELCAL or SATCOM CALL detection by an AMU, it sends continuous discrete information to trigger the aural alert. When the crew triggers the CALL reset in the RAIMS, it resets only the aural alert. The FWS generates various analog aural warning signals and transmit them to the RAIMS for amplification and diffusion via the cockpit loudspeakers (analog signals). The AMU manages cockpit aural alarms routing (SOUND&SYNTHESIS) supplied by the FWS. The audio warning inputs are dispatched on each AMU, which are connected to the audio outputs of the FWS. The AMU1 tells the FWS that a permanent Push To Talk (PTT) is activated for display of a level 1 cockpit warning (Crew awareness). AMU1 monitoring informs both FWS Applications that a permanent PTT has been detected. The AMU1 tells the FWS about the ON/OFF status of the RAIMPs through A429 signals to give Captain and F/O audio and radio reconfiguration information for display of a cockpit warning (ECAM memo in AMBER). AMU1 tells the two FWS Applications about the RAIMP activation (ON/OFF position) in order to confirm the reconfiguration status.

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 68

L1W06161 - L0KT0T0 - LM31D3FWS000001

A380 TECHNICAL TRAINING MANUAL

AURAL ANNOUNCEMENTS - AURAL ANNOUNCEMENTS GENERATION ARCHITECTURE MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 69

A380 TECHNICAL TRAINING MANUAL

FLIGHT WARNING SYSTEM DESCRIPTION (3) Aural Announcements (continued)

L1W06161 - L0KT0T0 - LM31D3FWS000001

List of Aural Announcements

o STICK PRIORITY (PRIORITY LEFT, PRIORITY RIGHT), V_ONE and DUAL INPUT o PITCH-PITCH, TIME, DOOR

The FWS generates various aural announcements according to systems status and A/C configuration received from A/C systems. Then the FWS transmits these aural announcements to the Radio and Audio Integrated Management System (RAIMS) for amplification and broadcasting through cockpit loudspeakers. These aural announcements can be classified in 2 families: the sounds and the synthetic voices. They are used: - To draw the crew attention in case of warning or caution, or - For instinctive reaction in relation to specific events or configuration. The two cockpit loud speakers send to the crew the following aural alerts general sounds to draw attention: - The Single Chime (SC) associated to the cautions, - The Continuous Repetitive Chime (CRC) associated to most of the warnings - Specific sounds for instinctive reactions: o Cavalry charge for unvoluntary AP disconnect o Cavalry charge for voluntary AP disconnect o Triple click for landing capability downgrading o Hybrid audio: (cricket stall) for stall warning o Buzzer for calls and SELCAL calls o "C" chord for altitude alert o RING for ATC messages o Cockpit door for cockpit door emergency opening - Synthetic voices o Reporting of significant radio altitudes o HUNDRED ABOVE, MINIMUM and PLUS_HUNDRED for decision height o WINDSHEAR, STALL warning, SPEED/SPEED/SPEED o RETARD, TEN RETARD, TWENTY RETARD MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 70

L1W06161 - L0KT0T0 - LM31D3FWS000001

A380 TECHNICAL TRAINING MANUAL

AURAL ANNOUNCEMENTS - LIST OF AURAL ANNOUNCEMENTS MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 71

A380 TECHNICAL TRAINING MANUAL

FLIGHT WARNING SYSTEM DESCRIPTION (3)

L1W06161 - L0KT0T0 - LM31D3FWS000001

Class 4 Alerts A detected failure will generate a Class 4 failure message under the following conditions: - Failure is time limited, therefore the associated flight deck effect can be deferred - Exceptionally, on a case by case basis, to cover specific MEL conditions likely to lead to heavy maintenance operations The Class 4 failure message objectives are to: - Increase operational reliability through less or postponed logbook entries / flight crew complaints for which maintenance actions are not immediately required - Enable airline to manage repair of faults within an airworthiness agreed time limit - Give maintenance operator the adequate maintenance information: o Identification of the Fault, o Time remaining before flight crew is alerted, o Associated TSM / AMM procedure. The A380 implementation of Class 4 failure messages leads to the introduction of "timers" in the FWS. These timers will count the presence of the Class 4 failure, and will trigger the FWS warning message related to the Class 4 failure when the timer has reach its pre-defined maximum value limit (time-out). In terms of system architecture, aircraft systems send alarm to the FWS. The FWS identifies Class 4 alert, relates a timer to these alerts and sends this information to the CMS. This information can be retrieved through the Onboard Maintenance System (OMS) Human Machine Interface (HMI). If the timer reaches its maximum value, the FWS generates associated alerts (warning, attention getters and aural announcements) in order to inform the flight crew.

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 72

L1W06161 - L0KT0T0 - LM31D3FWS000001

A380 TECHNICAL TRAINING MANUAL

CLASS 4 ALERTS MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT WARNING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 73

A380 TECHNICAL TRAINING MANUAL

TAIL STRIKE INDICATION SYSTEM DESCRIPTION (3) General

L1W06161 - L0KT0T0 - LM31D4TSI000001

The TSI System is made of two Tail Strike Indicators, installed on the rear fuselage, one on the right side and the other one on the left side. These Tail Strike indicators fulfill the detection of rear fuselage chafes or loads on the ground during takeoff or landing. The two TSIs transmit Tail strike detection data through IOMs, via the Avionics Data Communication Network (ADCN) to the Flight Warning System (FWS). Then the FWS computes the Tail Strike alert and depending on the flight phase, sends it via the ADCN to the Control and Display System (CDS). This alert indication is shown on the Electronic Centralized Aircraft Monitoring (ECAM) Engine Warning Display (EWD) and on the PFDs Lower zone.

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

TAIL STRIKE INDICATION SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 74

L1W06161 - L0KT0T0 - LM31D4TSI000001

A380 TECHNICAL TRAINING MANUAL

GENERAL MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

TAIL STRIKE INDICATION SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 75

A380 TECHNICAL TRAINING MANUAL

TAIL STRIKE INDICATION SYSTEM DESCRIPTION (3) Detection and warning display

L1W06161 - L0KT0T0 - LM31D4TSI000001

The LH and RH Tail Strike Indicators (TSI 1, TSI 2) have two wires. These wires can easily be damaged if the rear fuselage chafes on the ground during take-off or landing. In normal configuration the two circuits send ground signal to the IOMs. If one or two discrete signals change their status from ground to open during takeoff (phase 5 or 6) or landing phases (phase 9 or 10), the IOMs indicate this as a Tail Strike. The Flight Warning System (FWS) receives the data from the IOMs and sends aural and visual messages: - On the glareshield the MASTER CAUTION lights come on, - SINGLE CHIME transmitted to loudspeakers, - On the WARNING area of the Engine / Warning display (EWD) the message TAIL STRIKE (amber) is displayed, - On the MEMO area of the Engine / Warning display (EWD) the message LAND ANSA (amber) is displayed, - On the MEMO/LIMITATION page of the PFD the message LAND ANSA (amber) is displayed. In order not to disturb the crew during critical phases, this alert will only be displayed 15s after the beginning of phase 6 and during phase 11.

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

TAIL STRIKE INDICATION SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 76

L1W06161 - L0KT0T0 - LM31D4TSI000001

A380 TECHNICAL TRAINING MANUAL

DETECTION AND WARNING DISPLAY MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

TAIL STRIKE INDICATION SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 77

A380 TECHNICAL TRAINING MANUAL

TAIL STRIKE INDICATION SYSTEM DESCRIPTION (3) Abnormal configuration

L1W06161 - L0KT0T0 - LM31D4TSI000001

During abnormal configuration, if one or two TSI discretes signals change their status from ground to open during flight phases (different from take off or landing), the IOMs indicate this as a TSI detector fault. The Flight Warning System (FWS) receives the data from the IOMs and sends visual messages: - On the WARNING area of the Engine / Warning display (EWD) the message TAIL STRIKE DET FAULT (amber) is displayed. - On the INOP SYSTEM area of the SD Status page, the message TAIL STRIKE DET is displayed.

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

TAIL STRIKE INDICATION SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 78

L1W06161 - L0KT0T0 - LM31D4TSI000001

A380 TECHNICAL TRAINING MANUAL

ABNORMAL CONFIGURATION MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

TAIL STRIKE INDICATION SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 79

A380 TECHNICAL TRAINING MANUAL

ELECTRICAL CLOCK SYSTEM DESCRIPTION (3) General

L1W06161 - L0KT0T0 - LM31D5CLOCK0001

The Electrical Clock displays and outputs UTC and date synchronized either on an external time reference or on an internal time reference.

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

ELECTRICAL CLOCK SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 80

L1W06161 - L0KT0T0 - LM31D5CLOCK0001

A380 TECHNICAL TRAINING MANUAL

GENERAL MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

ELECTRICAL CLOCK SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 81

A380 TECHNICAL TRAINING MANUAL

ELECTRICAL CLOCK SYSTEM DESCRIPTION (3) Purpose The need for Universal Time Coordinated (UTC) time/date reference and the accuracy of this time/date reference mainly relates to operational issues : - Clock is used to indicate time and date to the crew, - Time and date are used to report incidents, - Time and date are used in the Air Traffic Control (ATC), particularly in transoceanic areas or in relation with particular waypoints, Flight Management System (FMS), Cockpit Voice Recorder (CVR), and Control & Display System (CDS), Time and date are used to date BITE/OMS maintenance failure messages and also ECAM operational warning messages.

External mode In normal configuration (external mode) the MMR1 (GPS1) sends time reference to the electrical clock then the clock transmits time and date to the clock users through ADCN.

degraded mode of operation: the Clock shall increment automatically, and without action from the crew, time and date on its internal time base, based on the last valid external data. When the external source becomes available, the Clock displays and outputs the data of the external source (MMR/GPS1). When the Clock is operating on the degraded Mode of operation, the time reference is considered as UTC data during 24 hours. After that time duration, the accuracy of the Clock does not guarantee that the Clock data is a UTC data.

A/C Back Up Clock In case of Clock data failure or the clock is in "SET" mode, the time reference back up is provided by the three ADIRUs. Time reference users will then use the time reference provided by the ADIRUs via ADCN. The three ADIRUs output the GPS time and date data continuously, whatever the mode of operation of the Clock. In case of the MMR-GPS data are lost, the ADIRUs internally provide the time reference.

L1W06161 - L0KT0T0 - LM31D5CLOCK0001

Internal Mode When the crew detects erroneous or inaccurate time that the MMR/GPS1 ("GPS" mode) gives, the crew correct this time by selecting the "INT" mode. The crew has the capability to set the time to the correct UTC reference by a procedure ("SET" mode). The Clock increments time and date on its internal time base (based on the last valid data received from the GPS or on the time set manually) and transmits these data to the clock users.

Degraded Mode When the Mode selected by the crew is "external" ("GPS" mode) and the external source is not available (GPS failed), the Clock enters in a MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

ELECTRICAL CLOCK SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 82

L1W06161 - L0KT0T0 - LM31D5CLOCK0001

A380 TECHNICAL TRAINING MANUAL

PURPOSE ... A/C BACK UP CLOCK MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

ELECTRICAL CLOCK SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 83

A380 TECHNICAL TRAINING MANUAL

INTERFACE FOR VIDEO SYSTEM DESCRIPTION (3) General

L1W06161 - L0KT0T0 - LM31D6CMV000001

The CMV is the core unit, which is used to concentrate video signals coming from several A/C video sources. These video sources are the External and Taxing Camera System (ETACS), and the optional: - Cockpit Door Surveillance System (CDSS), - Cabin Video Monitoring System (CVMS), - Onboard Airport Navigation System (OANS) Different control means give to the crew the capability to make a video source selection. This selection is transmitted in parallel to the Control and Display System (CDS) and to the CMV, which sends it to the different video sources available. The CMV treats the video sources signals in order to make them compatible with the CDS specific video protocol and transmits them for display to the CDS via direct links.

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

INTERFACE FOR VIDEO SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 84

L1W06161 - L0KT0T0 - LM31D6CMV000001

A380 TECHNICAL TRAINING MANUAL

GENERAL MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

INTERFACE FOR VIDEO SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 85

A380 TECHNICAL TRAINING MANUAL

INTERFACE FOR VIDEO SYSTEM DESCRIPTION (3)

L1W06161 - L0KT0T0 - LM31D6CMV000001

CMV description and interfaces The CMV is a video interface adapting a standard video signal to the CDS specific video protocol and capable of routing (not simultaneously) several video inputs to one CDS DU. Each CDS DU has only one video input. In case of total loss of CMV (internal failure, power supply failure) all the video sources connected to CMV are lost. Moreover, even if the CMV sends a video signal to the CDS, this video is not displayed on the CDS until the CDS is in video mode (in that case, the CMV cannot be the cause of an inadvertent display of one video source on the CDS). The CMV transmits the video signal related to the crew request to the applicable DU. In CDS normal mode, the DUs that show video displays are: the two PFDs, the two NDs, the SD. In CDS reconfiguration mode, the two MFDs can show video displays. The CDS sends its current configuration (normal mode or reconfiguration mode) and its healthy status to the CMV. The CMV uses this information to route the requested video to the applicable DU. The Camera Interface Unit (CIU) transmits the video signal related to the crew request to the CMV (via three optical fibers) The CMV transmits the crew selection signal to the CIU via ARINC 429 bus and then tells the CDS to show the video data on the SD + PFD. For the PFD, the request for video display is directly acquired by the CIU from the EFIS control panels via ARINC 429. The CDSS controller transmits the video signal related to the crew request to the CMV (via optical fiber) The CMV transmits the crew selection signal to the CDSS controller via ADCN and then tells the CDS to show the video data on the SD. In case of a cockpit entry and if video is selected on ECP, the CDSS controller can make a priority request to the CMV via ADCN. The Data Acquisition Unit (DAU) transmits the video signal related to the crew request to the CMV (via optical fiber) MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

The CMV transmits the crew selection signal to the DAU (via ADCN and NSS) and then tells the CDS to show the video data on the SD. In case of an important situation (cabin alert) and if video is selected on ECP, the DAU can make a priority request to the CMV via discrete signal. The Onboard Airport Navigation Computer (OANC) transmits the video signal related to the crew request to the CMV. The CMV transmits the crew selection signal to the OANC and then tells the CDS to show the video data on the ND. The CMV transmits data to the FWS for the alert computation need. The crew uses the EFIS - CP (on the FCU) for the display of video images on the PFD and ND. The crew uses the ECP for the display of video images on the SD. In case of EFIS-CP failure, the FCU backup function can also ask for the display of video images on the PFD and ND. The LGERS application sends the flight/ground status information to the CMV via the ADCN. This information is used to enable or disable the ETACS display on the PFDs. The lights of the taxiing aid cameras are supplied with electrical power through the Secondary Electrical Power Distribution Centers (SEPDC) and circuit breakers when the CMV has a request for the ETACS display. As an option, in case of Hi-jacking it is possible to deactivate all the video links (no video display on the cockpit DUs) via optional CAPT and F/O RATC push button switches (part of the AESS). The Ground Security Panel (GSP) Shut off switch (option) disables the CMV view (all video sources display are inhibited) from outside the A/C (discrete to CMV). The CMV system transmits the following data to the OMS : - fault messages from the BITE to the CMS for failure isolation, failure memorization and reports generation, - configuration to the DLCS for configuration monitoring and management.

INTERFACE FOR VIDEO SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 86

L1W06161 - L0KT0T0 - LM31D6CMV000001

A380 TECHNICAL TRAINING MANUAL

CMV DESCRIPTION AND INTERFACES MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

INTERFACE FOR VIDEO SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 87

A380 TECHNICAL TRAINING MANUAL

INTERFACE FOR VIDEO SYSTEM DESCRIPTION (3)

L1W06161 - L0KT0T0 - LM31D6CMV000001

Video display and control On the ECP, the VIDEO pushbutton switch is used to select the VIDEO page. The VIDEO selector knob (with two concentric knobs) is used as follows: The outer rotary knob is used to select the video source system and the inner rotary knob is used only to select video views from different cameras of a video source system, such as camera 1 of the CDSS. The indication of the selected source system is shown on a menu on the CKPT for the CDSS, EXT (optional) and TAXI for the ETACS, CABIN for the CVMS. On the EFIS-CPs: The TAXI pushbutton switch is used to show the ETACS video images. The ZOOM position of the ND range selector knob is used to show the OANS video images. When the crew press "Video" Key on the ECP, the last system displayed on the SD comes back. Some system can transmit to the CMV a priority to be displayed fir the first time (before the crew selects an other system to display). The order of priority is: 1- CDSS through ADCN. 2- CVMS through a discrete. 3- Other video systems have no priority. In the case of "no priority" provided to the CMV, the last video displayed on SD will be displayed when the system will be again selected.

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

INTERFACE FOR VIDEO SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 88

L1W06161 - L0KT0T0 - LM31D6CMV000001

A380 TECHNICAL TRAINING MANUAL

VIDEO DISPLAY AND CONTROL MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

INTERFACE FOR VIDEO SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 89

A380 TECHNICAL TRAINING MANUAL

INTERFACE FOR VIDEO SYSTEM DESCRIPTION (3) Allocation of the video sources to the DUs with CDS Reconfiguration

L1W06161 - L0KT0T0 - LM31D6CMV000001

It is possible to do some reconfigurations on the video displays with pushbutton switches installed on the CAPT and F/O displays brightness panels (1313VU and 1314VU). With the PFD/ND pushbutton switch, the crew can move the OANS display from the ND DU to the PFD window of the PFD DU. In case of DU failure, the crew can transfer using the RECONF pushbutton switch: - The video display from the SD DU to the MFD DU, - The OANS display from the ND DU to the MFD DU. NOTE: The CAPT pushbutton switches are related to the CAPT DUs and the F/O pushbutton switches are related to the F/O DUs.

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

INTERFACE FOR VIDEO SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 90

L1W06161 - L0KT0T0 - LM31D6CMV000001

A380 TECHNICAL TRAINING MANUAL

ALLOCATION OF THE VIDEO SOURCES TO THE DUS WITH CDS RECONFIGURATION MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

INTERFACE FOR VIDEO SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 91

A380 TECHNICAL TRAINING MANUAL

FLIGHT DATA RECORDING SYSTEM DESCRIPTION (3) General

L1W06161 - L0KT0T0 - LM31D7REC000001

The Flight Data Recording System (FDRS) is composed of : - A Flight Data Interface Function (FDIF) located in the CDAM - A Flight Data Recorder (FDR) installed at the rear part of the A/C (unpressurised section 19 near the pressure bulkhead) - An optional Quick Access Recorder or alternatively a Virtual QAR hosted on the NSS - A Linear 3-axis Accelerometer installed in the center of gravity. - A DFDRS Event Button - A DFDRS Ground Control Switch

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT DATA RECORDING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 92

L1W06161 - L0KT0T0 - LM31D7REC000001

A380 TECHNICAL TRAINING MANUAL

GENERAL MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT DATA RECORDING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 93

A380 TECHNICAL TRAINING MANUAL

FLIGHT DATA RECORDING SYSTEM DESCRIPTION (3)

L1W06161 - L0KT0T0 - LM31D7REC000001

FDRS architecture In normal operation the FDIF receives critical flight data from the following A/C systems: LRUs (MMR, PRIM, ADIRS, ISIS,...) and LRMs with AFDX busses through the ADCN. In abnormal operation (ADCN backup), the FDIF receives flight data from the following A/C systems: Vertical, lateral and longitudinal acceleration signals from the linear accelerometer, LRUs and LRMs with ARINC 429 busses. The FDIF formats the critical flight data and sends it to the following recording devices: - The FDR via ARINC 717 data bus (Havard bi-phase), - The optional Quick Access Recorder (QAR) via ARINC 717 data bus (Havard bi-phase). Note that the QAR can be used as a QAR or as Digital ACMS Recorder (DAR) (using software pin programming), - The optional Virtual QAR (VQAR) via Ethernet data bus. Note that QAR and VQAR record the same data than the FDR. The VQAR is able to record data related to the last four flights with a maximum duration of 16 hours each. The DFDR Ground Control Switch enables to supply at any time the FDRS on ground for test and maintenance purposes, or for preflight check. The EVENT pushbutton is used to record an event mark on each FDRS recording device.

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT DATA RECORDING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 94

L1W06161 - L0KT0T0 - LM31D7REC000001

A380 TECHNICAL TRAINING MANUAL

FDRS ARCHITECTURE MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

FLIGHT DATA RECORDING SYSTEM DESCRIPTION (3)

Apr 18, 2006 Page 95

A380 TECHNICAL TRAINING MANUAL

CONTROL & DISPLAY SYSTEM MAINTENANCE (3) CDS Tests

L1W06161 - L0KT0T0 - LM31Y1MAINT0001

The CDS provides the following interactive BITE/system tests via CMS application: - Safety test, - System test, - Pin Programming Status Report, - Display Unit tests, - Data bus test, - KCCU test, - CDS Identification, - DU memory dump, - Switching test These tests are launched from the OMS HMI (using the OMT, OIT or PMAT).

CDS Pin Programming Status Report The Pin Programming Status Report enables to check the configuration of elements of the CDS (DUs side assignment, functions activations, etc) To make this test, all DUs and KCCUs must be "ON".

Data Bus Test You must do a test of all input/outputs of the CDS DUs, in order to check data transmission and reception.

KCCU Test This test lets check the capabilities of the KCCUs and in particular KCCU controls (KCCU keys, trackball, validation click, scrolling wheel). In order to make this test, at least one DU on KCCU side must be "ON".

CDS Safety Test

CDS Identification

Safety tests are integrated tests of the display units of the CDS. Safety test is triggered either according to an input command from AFDX (e.g.: power-up test) or manually through BITE interactive mode (from OMS) In order to perform this test, all DUs must be "ON". The maximum duration associated to this test is 150s. This test cannot be aborted.

The CDS Identification gives access to each DU internal software configuration (CDS and Definition Files configuration). To make this test, all DUs and KCCUs must be "ON".

CDS System Test This test is used to check the integrity of all DUs of the CDS, in order to help fault isolation during maintenance operation. This test automatically starts a safety test and the data bus test of the system.

DU tests The DUs Test fulfills the following tests: - Brightness test (before launching test, DU to test must be "ON" for at least 120s) - Pixel default test (DU must be on the "ON" position); it checks the acceptance of pixel performances for dedicated DU using pattern, according to criterion found in the AMM. - Color test: checks acceptance of color performances for EWD DU according to criterion found in the AMM

CDS DU Memory Dump (Specific Functions) The CDS DU Memory Dump lets dump the memory of each DU, in case a failure for example. MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM MAINTENANCE (3)

Apr 18, 2006 Page 96

A380 TECHNICAL TRAINING MANUAL

L1W06161 - L0KT0T0 - LM31Y1MAINT0001

- To make this test, all DUs and KCCUs must be "ON".

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM MAINTENANCE (3)

Apr 18, 2006 Page 97

L1W06161 - L0KT0T0 - LM31Y1MAINT0001

A380 TECHNICAL TRAINING MANUAL

CDS TESTS - CDS SAFETY TEST ... CDS DU MEMORY DUMP (SPECIFIC FUNCTIONS) MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM MAINTENANCE (3)

Apr 18, 2006 Page 98

A380 TECHNICAL TRAINING MANUAL

L1W06161 - L0KT0T0 - LM31Y1MAINT0001

This Page Intentionally Left Blank

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM MAINTENANCE (3)

Apr 18, 2006 Page 99

A380 TECHNICAL TRAINING MANUAL

CONTROL & DISPLAY SYSTEM MAINTENANCE (3) CDS Tests (continued) Switching Test The switching test lets test the switching capabilities of the CDS. The test verifies that PFD/ND, RECONF and CHRONO buttons switching functions operate normally. To make the test, push the switching buttons and check that the switching is effective on the display units. The switching test lets test both CAPT and F/O sides.

Dataloading Specific Uploading Items

L1W06161 - L0KT0T0 - LM31Y1MAINT0001

Obey these safety precautions: CAUTION: AFTER YOU UPLOAD EACH DU SOFTWARE COMPONENT, MAKE SURE THAT YOU ALWAYS UPLOAD THE RELATED USER APPLICATION DEFINITION FILE SOFTWARE COMPONENTS. THE DU SOFTWARE ERASES THE USER APPLICATION DEFINITION FILE SOFTWARE. FOR SAFETY REASON, WHEN THE UPLOADING IS COMPLETED, IT IS NECESSARY TO DO TWO DIFFERENT CHECKS OF THE DU SOFTWARE CONFIGURATION (THROUGH THE SYSTEM IDENTIFICATION REPORT AND THE INFORMATION MODE RESULT). YOU CAN USE THE BITE FUNCTION OF THE CDS AS AN ALTERNATIVE METHOD. THIS METHOD HAS TWO OTHER DIFFERENT CHECKS, AVAILABLE AT THE END OF THIS PROCEDURE (CDS IDENTIFICATION REPORT AND BITE TEST OF THE CDS (COLOR TEST)). MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM MAINTENANCE (3)

Apr 18, 2006 Page 100

A380 TECHNICAL TRAINING MANUAL

L1W06161 - L0KT0T0 - LM31Y1MAINT0001

This Page Intentionally Left Blank

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

CONTROL & DISPLAY SYSTEM MAINTENANCE (3)

Apr 18, 2006 Page 101

A380 TECHNICAL TRAINING MANUAL

INDICATING/RECORDING SYSTEMS OPS, CTL & IND (3)

L1W06161 - L0KT0T0 - LM31O1LEVEL0301

General

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

INDICATING/RECORDING SYSTEMS OPS, CTL & IND (3)

Apr 18, 2006 Page 102

L1W06161 - L0KT0T0 - LM31O1LEVEL0301

A380 TECHNICAL TRAINING MANUAL

GENERAL MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

INDICATING/RECORDING SYSTEMS OPS, CTL & IND (3)

Apr 18, 2006 Page 103

A380 TECHNICAL TRAINING MANUAL

INDICATING/RECORDING SYSTEMS OPS, CTL & IND (3)

L1W06161 - L0KT0T0 - LM31O1LEVEL0301

ECAM

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

INDICATING/RECORDING SYSTEMS OPS, CTL & IND (3)

Apr 18, 2006 Page 104

L1W06161 - L0KT0T0 - LM31O1LEVEL0301

A380 TECHNICAL TRAINING MANUAL

ECAM MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

INDICATING/RECORDING SYSTEMS OPS, CTL & IND (3)

Apr 18, 2006 Page 105

A380 TECHNICAL TRAINING MANUAL

INDICATING/RECORDING SYSTEMS OPS, CTL & IND (3)

L1W06161 - L0KT0T0 - LM31O1LEVEL0301

Display Units Reconfiguration

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

INDICATING/RECORDING SYSTEMS OPS, CTL & IND (3)

Apr 18, 2006 Page 106

L1W06161 - L0KT0T0 - LM31O1LEVEL0301

A380 TECHNICAL TRAINING MANUAL

DISPLAY UNITS RECONFIGURATION MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

INDICATING/RECORDING SYSTEMS OPS, CTL & IND (3)

Apr 18, 2006 Page 107

A380 TECHNICAL TRAINING MANUAL

INDICATING/RECORDING SYSTEMS OPS, CTL & IND (3)

L1W06161 - L0KT0T0 - LM31O1LEVEL0301

Clock setting

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

INDICATING/RECORDING SYSTEMS OPS, CTL & IND (3)

Apr 18, 2006 Page 108

L1W06161 - L0KT0T0 - LM31O1LEVEL0301

A380 TECHNICAL TRAINING MANUAL

CLOCK SETTING MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

INDICATING/RECORDING SYSTEMS OPS, CTL & IND (3)

Apr 18, 2006 Page 109

A380 TECHNICAL TRAINING MANUAL

INDICATING/RECORDING SYSTEMS COMPONENT LOC. (3) Control Panels A/C Zone 210 Cockpit Display System A/C Zone 210 Flight Warning System A/C Zone 120 A/C Zone 210 Clock A/C Zone 210 Tail Strike Indicators A/C Zone 170

L1W06161 - L0KT0T0 - LM31C1LEVEL0301

Interface for Video System A/C Zone 123 Flight Data Recording System A/C Zone 145 A/C Zone 123 A/C Zone 210 A/C Zone 260 A/C Zone 290 MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

INDICATING/RECORDING SYSTEMS COMPONENT LOC. (3)

Apr 18, 2006 Page 110

A380 TECHNICAL TRAINING MANUAL

L1W06161 - L0KT0T0 - LM31C1LEVEL0301

This Page Intentionally Left Blank

MAINTENANCE COURSE - T1 & T2 (RR / Metric)  LEVEL III - ATA 31 Indicating/Recording Systems

INDICATING/RECORDING SYSTEMS COMPONENT LOC. (3)

Apr 18, 2006 Page 111

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