Level i - Ata 34 Navigation

A380 TECHNICAL TRAINING MANUAL MANUAL MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL I - ATA 34 Navigation

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A380 TECHNICAL TRAINING MANUAL

LEVEL I - ATA ATA 34 3 4 NAVIGATION NAVIGATION Navigation Systems Introduction (1) . . . . . . . . . . . . . . . . . . . . . . . . . . 2 Air Data & Inerti al Reference System Pres. (1 ) . . . . . . . . . . . . . . . . . . 4 Standby Navigation System Presentation (1) . . . . . . . . . . . . . . . . . . . 10 Multi-Mode Receiver Presentatio n (1) . . . . . . . . . . . . . . . . . . . . . . . . 12 IND POS DET SYS (Radio Altimeter) Pres. (1) . . . . . . . . . . . . . . . . 18 Dependant Position Determining SYS Pres. (1) . . . . . . . . . . . . . . . . 22 Onboard Airport Navigation System Pres. (1) . . . . . . . . . . . . . . . . . . 28 A/C Environment Surveillance System Pres. (1) . . . . . . . . . . . . . . . . 32 Navigation Systems Maintenan ce (1) . . . . . . . . . . . . . . . . . . . . . . . . . 46

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MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL I - ATA 34 Navigation

TABLE OF CONTENTS

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NAVIGA NA VIGATION TION SYSTEMS INTRODUCTION (1) General The navigation system comprises: - dependent position determining: VHF Omnidirectional Range (VOR)/Marker, (VOR)/Marker, Distance Measuring Equipment (DME), Automatic Direction Finder (ADF), - Air Data/Inertial Reference System (ADIRS), - Multi Mode Receiver (MMR), - Standby Navigation System (SNS), - Onboard Airport Navigation System (OANS), - independent position determining Radio Altimeter (RA), - Aircraft Environment Surveillance System (AESS).

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NAVIGATION SYSTEMS INTRODUCTION (1)

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NAVIGATION SYSTEMS INTRODUCTION (1)

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AIR DATA & INERTIAL REFERENCE SYSTEM PRES. (1) General The Air Data and Inertial Reference System (ADIRS) is the A/C navigation center. It is an autonomous system, independent of ground navigation aids. The ADIRS gives many A/C systems and the Control and Display System (CDS) with air data, inertial parameters and time reference through the Avionics Data Communication Network (ADCN) and ARINC bus.

- ADIRU 2 gives data to the F/O EFIS, - ADIRU 3 stays in s tandby. In case of ADIRU1 and/or ADIRU2 failure, ADR 3 and/or IR 3 outputs may be manually switched using the swit ching control panel.

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The ADIRS is composed of: - 3 Air Data and Inertial Reference Units (ADIRUs), - one Integrated Control Panel (ICP) located on the overhead panel, allowing ADIRUs powering and control, - one switching panel located on the main instrument panel, - air data sensors. The ADIRS interfaces with: - 2 EFIS Control Panels (EFIS CP), located on the glareshield, allowing the baro-reference setting, - 2 Keyboard Cursor and Control Units (KCCUs), located on the pedestal, allowing manual position IR alignment and controlling the status of the ADIRS on MultiFunction Displays (MFDs), - MMR for GPS signals and time reference. Each ADIRU is split in 2 parts: - the Air Data Reference (ADR) part receives the aerodynamic signals from various sensors and computes air data parameters, - the Inertial Reference (IR) part receives the GPS signal from Multi Mode Receiver (MMR) and computes the inertial parameters and the navigation parameters.

In normal condition: - ADIRU 1 gives data to the CAPT EFIS, 1

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AIR AI R DA DATA & IN INER ERTI TIAL AL RE REFE FERE RENC NCE E SYS SYSTE TEM M PRE PRES. S. (1 (1))

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AIR DATA & INERTIAL REFERENCE SYSTEM PRES. (1) Air Data Reference Reference Acquisition The ADR part of each ADIRU receives air data from 3 types of sensors: - one MultiFunction Probe (MFP), located on the right or left hand side of the FWD fu selage, gives the Angle Of Attack (AOA), the Total Air Temperature (TA (TAT) and the Total Pressure (Pt), - two Integrated Static Probes (ISPs), l ocated on the FWD fuselag e, give the Static Pressure (Ps), - one Side Slip Angle (SSA), located on the FWD fuselage, gives the Side Slip Angle (SSA). Each probe has an internal air d ata/digital converter and transmits the air data parameters to the ADIRUs in digital format. Each probe has an integrated de-icing protection, which can be activated automatically by the ADIRS or manually through a PROBE/WINDOW HEAT HEAT P/B switch on the ICP. A rotary selector powers each ADIRU and the ADR P/B switch on the ICP individually controls each ADR part. The baro-setting on the EFIS control panel fulfills the barometric pressure correction.

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AIR DATA & INERTIAL REFERENCE SYSTEM PRES. (1) Inertial Reference Acquisition Each ADIRU IR part supplies navigation and inertial data to the CDS and to other A/C systems through the ADCN. The inertial data are computed by the ADIRU using internal accelerometers and gyrometers. The navigation data and time mark are given from the GPS. In normal operation the IR part is automatically aligned using the GPS position. It may also be aligned manually through the KCCU and MFD. Each ADIRU is powered by a rotary selector and each IR part is individually controlled by the IR P/BSW on the ICP.

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STANDBY NAVIGATION SYSTEM PRESENTATION (1) Standby Navigation System

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The Standby Navigation System (SNS) is the back-up system in case of ADIRS failure (Air Data and Inertial Reference System), CDS failure (Control and Display System) or ADCN failure (Avionics Data Communication Network). The SNS computes and provides: - standby Air Data Reference (ADR) information, - standby Inertial Reference (IR) information, - navigation information, - flight plan information. The SNS is composed of: - 2 independent Integrated Standby Instruments System (ISIS) units, located in the center of the main instrument panel. The ISIS computes and displays air data parameters, flight plan and navigation information. In normal configuration, ISIS 1 displays the standby flight display and ISIS 2 displays the standby navigation display. Each ISIS is capable of fulfilling all the functions of either standby flight display or standby navigation display. In case of failure of ISIS1, ISIS 2 is automatically reconfigured in standby flight display mode. In this configuration, it is possible to recover the standby navigation display again by an action on the MODE P/BSW, located on the front face of the ISIS. - one standby pitot probe, located on the left FWD fuselage, gives the Total Pressure (Pt), - two standby static probes, located on the left and right FWD fuselage on the nose front fairing, give the Static Pressure (Ps). All sensors are automatically or manually de-iced, - 1 standby compass, located on top of the windshield center post, gives A/C magnetic heading information. 0 L 1 6 1 6 0 W 1 L


STAN ST ANDB DBY Y NAVI VIGA GATI TION ON SY SYST STEM EM PR PRES ESEN ENT TATI TION ON (1 (1))

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STAN ST ANDB DBY Y NAVI VIGA GATI TION ON SY SYST STEM EM PR PRES ESEN ENT TATI TION ON (1 (1))

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MULTI-MODE MUL TI-MODE RECEIVER PRESENTA PRESENTATION TION (1) ( 1) General Description The Multi-Mode Receiver (MMR) is a radio navigation aid. The main functions computed by the Multi-Mode Receiver (MMR) are as follows: - the Instrument Landing System function (ILS) computes Localizer (LOC) and Glide Slope (G/S) deviations, for precision approach and landing, - the Flight management Landing System (FLS) computes pseudo LOC and pseudo G/S deviations, - the Global Positioning System (GPS) computes the Position Velocity and Time (PVT) for the aircraft systems, - the GNSS Landing System (GLS), optional, is used for precision approach and landing, - the Mix Locali zer/Vertical zer/Vertical Navigation functio n (MIX LOC/VNAV), LOC/VNAV), is used for non precision approach and landing.

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The MMR system is composed of: - two MMR receivers, - two GPS antennae, - a common Localizer antenna, - a common G/S track antenna, - a common G/S capture antenna. M 3 P 4 3 M L 0 T 0 T K 0 L 1 6 1 6 0 W 1 L


MULTI-MODE RE RECEIVER PR PRESENTATION (1 (1)

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MULTI-MODE MUL TI-MODE RECEIVER PRESENTA PRESENTATION TION (1) ( 1) Control and Indicating The MMR sends data to the Control and Display System (CDS): PFD and ND. The EFIS Control Panel (EFIS_CP) is used for modes selection. The Multifunction Display (MFD) and Keyboard and Cursor Control Unit (KCCU) are used for the selection of the relevant radio navaid. Each Radio Management Panel (RMP) tunes the related MMR in back-up mode (FMS failure).

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MULTI-MODE MUL TI-MODE RECEIVER PRESENTA PRESENTATION TION (1) ( 1) Location Antennae Each MMR system is composed of: - 2 active GPS antennae installed on the top of the fuselage, in the A/C longitudinal axis, - one common Localizer antenna located in the radome, - one common G/S track antenna located on the nose landing gear, - on common G/S capture antenna located in the radome.

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IND POS DET SYS (RADIO ALTIMETER) PRES. (1) Independent position determining The Independent Position Determining system is a Radio Navigation aid, and basically independent of ground installations. This system includes: - the Radio Altimeter (RA) system, - the Aircraft Environment Surveillance System (AESS). Only the RA system is described in this document.

General The RA system supplies the radio height information. The RA transceiver measures the vertical distance between the A/C and the ground. This distance is valid up to 5500 ft. The information is displayed on the Primary Flight Display (PFD) and sent to: - PRIM for the Auto Flight System (AFS), - Flight Warning System (FWS) to generate warning and auto call-out, - Terrain Awareness Awareness Warning Syst em (TAWS) (TAWS) host ed in AESS.

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IND POS DET SYS (RAD IO IO ALTIMETER) PRES. (1)

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IND POS DET SYS (RADIO ALTIMETER) PRES. (1) Location The RA system includes: - 3 RA transceivers installed in the aft cargo compartment, - 3 transmission antennae and 3 reception antennae, all installed at the bottom of the rear fuselage.

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DEPENDANT POSITION DETERMINING SYS PRES. (1) General This system is dependent on ground stations. It supplies navigation data to the Control and Display System (CDS), the Flight Management System, and Communication System. The system includes: - Distance Measuring Equipment (DME) with 2 antennae located at the bottom of the fuselage, - VHF Omnidirectional Range (VOR) with an antenna located on the top of the vertical stabilizer, - Marker with an antenna at the bottom of the aircraft, - Automatic Direction Finder (ADF), optional, with antenna(e) located on the top of the aircraft.

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DEPE DE PEND NDAN ANT T POS POSIT ITIO ION N DE DETE TERM RMIN ININ ING G SYS SYS PRE RES. S. (1 (1))

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DEPENDANT POSITION DETERMINING SYS PRES. (1) - one ADF transceiver, - one ADF antenna.

Principle The VOR, DME, ADF and Marker systems are radio navigation aids, which compute navigation data (bearing, slant distance) from ground stations.

DME equipment The DME gives a slant distance from the A/C to a selected ground station. The system generates interrogation pulses and sends them to the DME ground station. The A/C is equipped with 2 DME systems. Each system is composed of: - one DME transceiver, - one DME antenna.

VOR/Marker VOR/Marker equipment

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The ADF gives a relative bearing wi th respect to the A/C. The ADF receives and processes the signal supplied by ADF ground stations called Non Directional Beacon (NDB). The A/C might be equipped with 2 ADF systems. Each system includes: L

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The VOR system receives, decodes and processes bearing information from an omni-directional ground station. The VOR system includes: - two VOR receivers, - one VOR antenna. The Marker function is to give aural and visual indications when the A/C is flying over a marker beacon. The Marker system includes: - Marker function only active within VOR1 receiver, - one Marker antenna.



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DEPENDANT POSITION DETERMINING SYS PRES. (1) Control and indicating These systems supply the A/C with navigation data displayed on the Control and Display System (CDS). They are tuned: - automatically by FMS in normal operation, - manually by the crew, using: - the Keyboard and Cursor Control unit (KCCU) and Multifunction Display (MFD) on POSITION/NAV POSITION/NAVAIDS page, - the Radio Management Panel (RMP). All these systems are connected to both Audio Management Units (AMUs) for ground station audio identification.

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ONBOARD AIRPORT NAVIGA NAVIGATION TION SYSTEM S YSTEM PRES. (1) Onboard Airport Navigation System : Presentation

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Airport Navigation is an on-board function giving the flight crew improved situational awareness on the airport surface. The aims of Airport Navigation function are firstly to ease pilot workload in the day-to-day task of navigation around complex airfields; and secondly, secondly, an important safety function, is to help prevent dangerous errors in surface navigation such as runway incursion or take-off from the wrong runway/taxiway. Then, the function will contribute to potentially reduce taxiing delays thanks to improved navigation. The Airport Navigation function is done by the Onboard Airport Navigation System (OANS), which is composed of one OANC and other A/C systems described here after. The Airport Navigation function is, by default, displayed on the Navigation Display (ND) via the Concentrator and Multiplexor Video (CMV) and controlled by the Keyboard and Cursor Control Unit (KCCU) and the EFIS control panel. The ND is used as a display unit and does not make any computation on the OANS image, which is received by the video input. The computation of the function is allocated to a dedicated Line Replaceable Unit (LRU), which exchanges data with other systems and generates two independent images to display respectively on ND CAPT and ND F/O. The Airport Navigation image is generated by the Onboard Airport Navigation Computer (OANC) using: - airport data stored in the Airport data base, - A/C data coming from data sources such as Flight Management System (FMS), Air Data and Inertial Reference Unit (ADIRU), or stored in the LRU - pilot data entries. 0 L 1 6 1 6 0 W 1 L


ONBO ON BOAR ARD D AIR AIRPO POR RT NA NAVI VIGA GATI TION ON SY SYST STEM EM PR PRES ES.. (1) (1)

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ONBOARD AIRPORT NAVIGA NAVIGATION TION SYSTEM S YSTEM PRES. (1) Control and Indicating The OANS provides the flight crew with permanent knowledge of the A/C location on the airport surface. The fixed A/C symbol is displayed on an electronic moving airport map, in three different display modes: ARC, NAV NAV, and PLAN. The function displays a set of information su ch as the name of displayed airport, taxiways, runways, gates and important building, current ground speed, and ground path (graphical and textual). The onside EFIS control panel range selector (ZOOM position) enables the display of the Airport Navigation image, on each ND. The KCCU is used for direct interactivity with the Airport Navigation image.

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A/C ENVIRONMENT SURVEILLANCE SYSTEM PRES. (1) General The Independent Position Determining system is a Radio Navigation aid, and basically independent of ground installations. This system includes: - the Radio Altimeter (RA) system, - the Aircraft Environment Surveillance System: (AESS). Only the AESS system is described in this document. The general purpose of the AESS is to tell the flight crew about all kind of existing hazards external to the aircraft, which may be: - weather, - windshear, - turbulence, - airborne collision, - collision with terrain. For each hazard, the AESS: - detects the hazards, - sends a warning to the crew in case of imminent hazard, - tells the crew about the A/C environment, - whenever possible, proposes an escape maneuver. 1 0 0 0 0 S S E A 7 P 4 3 M L 0 T 0 T K 0 L 1 6 1 6 0 W 1 L


A/C A/ C ENV ENVIR IRON ONME MENT NT SU SUR RVE VEIL ILLA LANC NCE E SYS SYSTE TEM M PRE PRES. S. (1 (1))

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A/C ENVIRONMENT SURVEILLANCE SYSTEM PRES. (1) Presentation

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The AESS includes: - 2 identical Aircraft Environment Surveillance Units (AESUs), - 2 identical Radar Transceiver Units (RTUs), - 1 Weather Antenna D rive Unit (WADU), (WADU), - 1 Weather Flat-plate Antenna, - 1 AESS Control Panel, - 4 identical combined Traffic alert and Collision Avoidance System (TCAS)/Mode-S antennae. The two AESUs are the main AESS equipment, which integrate and fulfill: - the Terrain Awareness Awareness and War Warning ning Sy stem (TAWS) (TAWS) function s, - the Weather Radar (WXR) and Predictive Windshear System (PWS) functions with the weather radar antenna through the Weather Radar Antenna Drive Unit (WRADU) and the two RTUs, - the TCAS surveillance function, Mode-S function and transponder (XPDR) for the Air traffic Control (ATC). In case of failure, the system may be reconfigured using the AESS control panel. The data are displayed on the: - Multifunction Display (MFD), controlled by the Keyboard and Cursor Control Units (KCCU), - The Control and Display System (CDS) controlled by the EFIS CP for range. The aural warnings generated by the AESS are sent via the Audio Management Units (AMUs). The Radio Management Panels (RMPs) control the transponder function. T K 0 L 1 6 1 6 0 W 1 L



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A/C ENVIRONMENT SURVEILLANCE SYSTEM PRES. (1) Presentation (continued) TAWS Function The TAWS provides: - basic Ground Proximity Warning System (GPWS), - Terrain and runway Clearance Floor (TCF), - terrain/obstacle awareness alerting and warning (TAD), - horizontal profile terrain display, - vertical profile terrain display. Terrain conflict detection is done by a comparison between A/C position and trajectory, and a worldwide database. Each AESU interfaces with Radio Altimeters, so the sys tem is capable to provide data for the Vertical Display (VD). The system gives the crew aural alert messages and visual annunciations. The current TAWS status is displayed on the MFD.

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A/C ENVIRONMENT SURVEILLANCE SYSTEM PRES. (1) Presentation (continued) WXR/PWS Function The Weather Radar includes PWS and Turbulence detection. The WXR/PWS enables detection, localization and display of the atmospheric disturbances. The weather radar also provides a ground mapping display mode for terrain features presentation. The images corresponding to these atmospheric disturbances are displayed on the ND and VD. The WXR status is displayed on MFD and controlled by the AESS control panel. The PWS supplies aural alerts.

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A/C ENVIRONMENT SURVEILLANCE SYSTEM PRES. (1) Presentation (continued) ATC XPDR Function The ATC XPDR system replies to the ground station and other A/C interrogations for altitude reporting and identification. The ATC XPDR automatically replies to interrogations: - from the ATC ground station for t he air traffic surveillance, - from an A/C with TCAS and/or mode S transponder, to fulfill the traffic alert; The AESS control panel controls the ATC XPDR. . The XPDR data are displayed on MFD (SURV/CONTROL page). The transponder code is selected on the RMP.

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A/C ENVIRONMENT SURVEILLANCE SYSTEM PRES. (1) Presentation (continued) TCAS Function The TCAS interrogates ATC equipped A/C in the vicinity. The TCAS acquires the intruder parameters in order to give advisories. The TCAS shows intruders relative altitude, relative bearing, and range. TCAS data are displayed on the MFD and controlled by the AESS control panel. In case of hazardous situation the system warns the crew by a TCAS aural and visual message.

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A/C ENVIRONMENT SURVEILLANCE SYSTEM PRES. (1) AESS Location The AESUs are located in the avionics bay. The RTUs are installed on the WADU WADU in t he radome. The combined TCAS/ Mode S antennae are located on the top and bottom of the fuselage. The AESS control panel located on the pedestal.

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NAVIGA NA VIGATION TION SYSTEMS MAINTENANCE (1) Navigation safety items When you work on the navigation system, in particular on the weather radar antenna, make sure that you obey all the AMM safety precautions. This will prevent injury to persons and/or damage to the A/C. Here is an overview of the main safety precautions relative to the navigation system. Before any maintenance operation, make sure that all persons are at 5 meters away from the antenna in an area made by an arc of 135 . There is a minimum safety distance of 60 meters between the antenna and any refueling operation. There is a minimum safety dist ance of 5 meters between the A/C and any obstacle in the area made by an arc of 90 . On the A380, the weather radar antenna is accessible through the inside of the Nose Landing Gear (NLG) compartment. Before any maintenance operation in NLG compartment, NLG doors must be secured. Put on and attach a safety harness before you start working in the area. The weather radar antenna assembly is heavy (13.64 kg). °

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NAVIGATION SY SYSTEMS MA MAINTENANCE (1 (1)

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NAVIGATION SY SYSTEMS MA MAINTENANCE (1 (1)

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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

Level i - Ata 34 Navigation

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