34-navigation

A319/A320/A321TECHNICAL TRAINING MANUAL

MECHANICS / ELECTRICS & AVIONICS COURSE

34 NAVIGATION

This document must be used for training purpose only

Under no circumstances should this document be used as a reference.

It will not be updated.

All rights reserved.No part of this manual may be reproduced in any form,

by photostat, microfilm, retrieval system, or any other means,without the prior written permission of Airbus Industrie.

NAVIGATION GENERALSystem Presentation (1) 1..........................** Radio Navigation Control Presentation (1) 5....** System Controls Presentation (1) 9.............Standby Instrument Presentation (1) 19............Radio Management Panel (RMP) Presentation (1) 31..DDRMI Presentation (1) 35..........................

ADIRSADIRS Principle (1) 41..............................ADIRS Presentation (1) 55..........................** Air Data Probes Presentation (1) 61............** ADIRS CDU Presentation (2) 65...................** ADIRS Switching (2) 77..........................ADIRUs Interconnection (3) 83......................** ADIRS Alignment through MCDU (2) 87............ADIRS Alignment through CDU (2) 91.................ADIRS Back-up Operation (ATT MODE) (3) 95.........ADIRS Indications on PFD (2) 99....................ADIRS Indications on ND (2) 113....................** ADIRS Indications on ECAM DU (2) 121...........ADIRS ECAM Warnings (2) 125........................Standby Instrument Components (3) 137.............** ADIRS Components (3) 149........................

MULTI MODE RECEIVER (MMR) SYSTEMMMR System Description (1) 159.....................MMR Description/Operation (3) 175..................MMR Indications on PFD (2) 183.....................MMR Indications on ND (2) 191......................MMR Components (3) 201..............................

WEATHER RADAR (WR) & PREDICTIVE WINDSHEAR(PWS)WR/PWS System Presentation (1) 209.................WR/PWS Description/Operation (3) 219...............

WR/PWS Controls and Displays (2) 227...............WR/PWS Operational Precautions (2) 243............WR/PWS Components (3) 247..........................

RADIO ALTIMETER (RA) SYSTEMRadio Altimeter System Presentation (1) 255.......Radio Altimeter Description/Operation (3) 263.....** RA Indications on PFD & AUTO Call Out (2) 269..** Radio Altimeter Components (3) 275.............

TRAFFIC COLLISION AVOIDANCE SYSTEM (TCAS)TCAS Presentation (1) 283..........................TCAS Description/Operation (3) 291.................TCAS Control Panel Description/Operation (2) 297..TCAS Indications on PFD and Aural Alerts (2) 305..TCAS Indications on ND (2) 311.....................TCAS Components (3) 317.............................

ENHANCED GROUND PROXIMITY WARNING SYSTEM(EGPWS)** EGPWS Presentation (1) 333......................** EGPWS Description/Operation (3) 341............** EGPWS Modes (3) 347..............................** EGPWS Indications on ND (2) 365.................** EGPWS Components (3) 371........................

DISTANCE MEASURING EQUIPMENT (DME) SYSTEMDME System Presentation (1) 375....................DME Description/Operation (3) 383..................DME Indications on PFD and ND (2) 389.............DME Components (3) 395..............................

AIR TRAFFIC CONTROL (ATC) SYSTEMATC System Presentation (1) 405....................ATC Description/Operation (3) 411..................ATC Control Panel Description/Operation (2) 417...ATC Components (3) 425..............................

_A319/A320/A321 TECHNICAL TRAINING MANUAL34 NAVIGATIONMECHANICS / ELECTRICS & AVIONICS COURSE

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34 NAVIGATION

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AUTOMATIC DIRECTION FINDER (ADF) SYSTEMADF System Presentation (1) 439....................ADF Description/Operation (3) 449..................ADF Indications on ND (2) 455......................ADF Components (3) 463..............................

VOR/MARKERS SYSTEMVOR/MKR System Presentation (1) 469................VOR/MKR Description/Operation (3) 481.............VOR/MKR Indications on ND (2) 487..................VOR/MKR Components (3) 497.........................

WARNINGSECAM Warnings (Except ADIRS) (2) 503...............

MAINTENANCE PRACTICESSPECIFIC PAGES** ADIRS/CFDS Specific Page Present. (3) 509....RAD Alt./CFDS Specific Page Present. (3) 533....


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34 - NAVIGATION

34-00-00 SYSTEM PRESENTATION

CONTENTS:GeneralADIRSLanding and Taxiing Aids SystemsIndependent Position Determining SystemsDependent Position Determining Systems

TMUNA2001 LEVEL 1

EFFECTIVITY 34-00-00 Page 1May 31/00


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SYSTEM PRESENTATION

GENERAL

The aircraft navigation systems provide the crew withthe data required for flight within the mostappropriate safety requirements.This data is divided into four groups:

- AIR DATA/INERTIAL REFERENCE SYSTEM (ADIRS),- LANDING AND TAXIING AIDS,- INDEPENDENT POSITION DETERMINING,- DEPENDENT POSITION DETERMINING.

ADIRS

The ADIRS is an integrated Air Data System and anInertial Reference System. One part called Air DataReference mainly computes speed and altitudeinformation from air parameters. The other part calledInertial Reference mainly computes heading, attitudeand position from gyros and accelerometers.The ADIRS is composed of three Air Data/InertialReference Units (ADIRUs).Besides the ADIRUs, there are still standbyinstruments:

- Altimeter and Airspeed indicators directlysupplied by pressure lines,

- Standby Compass,- Standby Horizon.

LANDING AND TAXIING AIDS

The Head-Up Display (HUD) is used as a piloting aidssystem for roll out, take-off and landing (optional).The Instrument Landing System (ILS), is use to obtainthe optimum aircraft position during an approach andlanding phase.The Marker (MKR) system is used to indicate thedistance to the runway threshold during an ILS descent.The aircraft is equipped with:

- 1 HUD (optional),- 2 ILS,- 1 MARKER (Included in the VOR receiver).

Frequency Control is achieved either automatically ormanually (through the MCDU) by the Flight Managementand Guidance Computers (FMGCs) or manually through theRadio Management Panels (RMPs).

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SYSTEM PRESENTATION



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SYSTEM PRESENTATION

INDEPENDENT POSITION DETERMINING SYSTEMS

This part of the navigation systems, called independentsystem, provides information regarding the safety ofthe aircraft without taking reference from any groundstation.The Weather Radar / Predictive Windshear (WR/PWS)system detects the position and intensity ofprecipitations which are shown on the NavigationDisplays (ND’s).The windshear capability serves to detect any suddenchange of wind speed and/or direction (Optional).The Radio Altimeter (RA) system gives the aircraftheight above the ground, independently of theatmospheric pressure.The Traffic Collision Avoidance System (TCAS) detectsthe aircraft in the immediate vicinity.The Enhanced Ground Proximity Warning System (EGPWS)warns the flight crew about the aircraft behaviour indangerous configuration when approaching the ground.This part of the Navigation system includes:

- 1 Weather Radar / Predictive Windshear (WR/PWS)(the second is optional),

- 2 Radio Altimeter (RA),- 1 Traffic Collision Avoidance System (TCAS),- 1 Enhanced Ground Proximity Warning System(EGPWS).

DEPENDENT POSITION DETERMINING SYSTEMS

This part of the navigation system, called dependentsystem, provides various means of navigation throughdata exchange with ground installations or satellites.

The Distance Measuring Equipment (DME) system givesthe aircraft slant distance to a ground station.The Air Traffic Control system (ATC) enables a groundoperator to identify and track the aircraft withouthaving to communicate with the flight crew.The Automatic Direction Finder (ADF) system is a radiocompass system providing the azimuth of a NonDirectional Beacon (NDB) with respect to the aircraftcenter line.The VHF Omni Range (VOR) system gives the bearing ofa ground VOR Station with respect to the magnetic Northand the aircraft angular deviation related to apreselected course.The Global Positioning System (GPS) is based on themeasurement of the transmission time of signalsbroadcast by satellites.This part of the Navigation includes:

- 2 DME,- 2 ATC,- 1 ADF (the second is optional),- 2 VOR,- 2 GPS.

NOTE 1: The VOR or DME frequency control is achievedeither automatically or manually (through theMCDU) by the FMGCs or manually though the RMPs.

NOTE 2: Although the Marker Beacon belongs to theLanding Aids System, it is physicallyintegrated into the VOR receiver.




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34 - NAVIGATION

34-00-00 RADIO NAVIGATION CONTROLPRESENTATION

CONTENTS:Automatic TuningManual TuningBack-Up TuningSelf Examination

TMUNAV701 LEVEL 1

EFFECTIVITY 34-00-00 Page 1Jul 31/96


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RADIO NAVIGATION CONTROL PRESENTATION

AUTOMATIC TUNING

The Automatic Tuning permits the control of VOR / DME,ILS and ADF by the Flight Management and GuidanceSystem.In this case the RMP is transparent to its associatedFMGC.In normal operation FMGC1 tunes receivers 1, FMGC2tunes receivers 2.In case of failure of FMGC 1 or 2, the remaining FMGCcontrols all receivers.

MANUAL TUNING

The manual tuning permits the pilot to select, throughthe Multipurpose Control Display Unit, a specificfrequency for display on the EFIS.

NOTE: To return to the autotuning mode, the manualtuning has to be cleared.

BACK-UP TUNING

Radio Management Panels 1 and 2 located on the pedestalprovide back-up for Radio Navigation tuning.We are in the case of both FMGCs inoperative oremergency electrical supply.The ILS course and frequency are the only RadioNavigation data exchanged.The selected values on RMP 1 and RMP 2 are identicalfor ILS 1 and ILS 2.

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RADIO NAVIGATION CONTROL PRESENTATIONTMUNAV701-P01 LEVEL 1



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SELF EXAMINATION

Can VOR 2 frequency be changed through RMP 1?A - Yes.B - No.

In back-up mode, an ILS can be tuned through:A - RMP 1 or 2.B - RMP 1 only.C - The onside RMP only.

TMUNAV701 LEVEL 1



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34 - NAVIGATION

34-00-00 SYSTEM CONTROLS PRESENTATION

CONTENTS:Multipurpose Control Display Unit (MCDU)ADIRS Control Display Unit (ADIRS CDU)Radio Management Panel (RMP)Audio Control Panel (ACP)

TMUNA2101 LEVEL 1

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SYSTEM CONTROLS PRESENTATION

MULTIPURPOSE CONTROL DISPLAY UNIT (MCDU)

The Multipurpose Control and Display Unit (MCDU) allowsthe crew:

- To display the Radio Navigation frequencies(automatically or manually tuned) on a specificpage called RAD/NAV.

- To align the Inertial Reference systems froma specific page called INIT via the FMGC.

- To initiate tests for all navigationsystems and for troubleshooting via theCFDIU.




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SYSTEM CONTROLS PRESENTATION - MCDUTMUNA2101-P01 LEVEL 1



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ADIRS CONTROL DISPLAY UNIT (ADIRS CDU)

The ADIRS Control and Display Unit allows the followingfunctions:

- To switch on the ADR and IR by setting a singlecontrol to NAV.

- To disconnect the ADR output bus by a specificpushbutton.

- To check the ADIRU operation- To align the IR instead of using the MCDU.

NOTE: when set to ATT, the systems are still energizedbut the IR is in downgraded operation mode.




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SYSTEM CONTROLS PRESENTATION - ADIRS CDUTMUNA2101-P02 LEVEL 1



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RADIO MANAGEMENT PANEL (RMP)

The main function of the Radio Management Panels (RMP)is to control all communication frequencies. Howeverthey are also used for standby selection ofRadio/NAV frequencies.The standby operation is used in case of dual FMGCfailure, provided the NAV pushbutton switch has beenpressed.




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SYSTEM CONTROLS PRESENTATION - RMPTMUNA2101-P03 LEVEL 1



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AUDIO CONTROL PANEL (ACP)

The Audio Control Panels (ACP) enable to control thereception of all audio signals identifying the variousbeacons and stations.

NOTE: DME identification signals can be selected byusing the knob of the colocated VOR or ILS.




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SYSTEM CONTROLS PRESENTATION - ACPTMUNA2101-P04 LEVEL 1



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THIS PAGE INTENTIONALLY LEFT BLANK

TMUNA2101 LEVEL 1



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34 - NAVIGATION

34-20-00 STANDBY INSTRUMENT PRESENTATION

CONTENTS:Standby CompassStandby HorizonStandby AltimeterStandby Airspeed Indicator (ASI)Metric Altimeter (Option)

TMUNAVE03 LEVEL 1



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STANDBY INSTRUMENT PRESENTATION

STANDBY COMPASS

The standby compass is located on the top windshieldcenter post.It is stowed in normal configuration.A correction card is glued to the side of the compassassembly.Non-magnetic lamp:- A non-magnetic lamp assembly lights the compass card.It is controlled by a STBY COMPASS switch located onthe INT LT panel on the overhead panel.Graduated compass:- The graduated compass card is attached to a magneticelement. It is free to rotate inside the compass bowland is immersed in a damping liquid.Lubber line:- A lubber line indicates the magnetic heading.Compensation holes:- Two holes marked NS and EW, allow compensation bypositioning two small magnetic bars calledcompensators.

TMUNAVE03-T01 LEVEL 1



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STANDBY INSTRUMENT PRESENTATION - COMPASSTMUNAVE03-P01 LEVEL 1



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STANDBY HORIZON

The Standby horizon is located on the center instrumentpanel and comprises the following elements:Roll pointer:- The roll information is given by a pointer whichmoves in front of a graduated roll scale.Roll scale:- The roll scale is graduated in 10 degree incrementsbetween -30 and +30 degrees and 15 degree incrementsup to 60 degrees.Flag:- The flag comes into view if a failure is detectedin the electrical power supply or if the gyro rotorspeed drops below 18000 RPM.Pitch drum:- The pitch drum is divided into two zones separatedby the reference horizon.The pitch indications are displayed between -80 and +80 degrees.Aircraft symbol:- The aircraft symbol is fixed.Resetting knob:- Fast resetting can be performed by pulling the cagingknob (Also used for shipping to protect the gyro).




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STANDBY INSTRUMENT PRESENTATION - HORIZONTMUNAVE03-P02 LEVEL 1



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STANDBY ALTIMETER

The Standby Altimeter is located on the centerinstrument panel and comprises the following elements:Adjustable bugs:- Four manually adjustable bugs are provided forreference altitude setting.Altitude counter:- A display counter made up of two drums displays thetens of thousands, and the thousands of feet.When the altitude is below 10000 feet, the left drumdisplays black and white stripes.In case of negative altitude the left drum displaysorange and white stripes.Altitude pointer:- The pointer indicates the hundreds of feet with 20feet increments.To prevent the pointer from sticking, an internalvibrator is installed.It is only supplied in flight.Altitude dial:- The altitude dial is calibrated from O to 1000 feetwith 20 feet graduations.Baro correction counter:- The baro correction is displayed on a countergraduated in hecto Pascals.Adjustment baro setting knob:- The knob enables adjustment of the baro setting inthe range of 750 to 1050 hecto Pascals.




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STANDBY INSTRUMENT PRESENTATION - ALTIMETERTMUNAVE03-P03 LEVEL 1



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STANDBY AIRSPEED INDICATOR (ASI)

The Standby Airspeed Indicator (ASI) is located on thecenter instrument panel and comprises the followingelements:Ajustable bugs:- Four manually adjustable bugs are provided forreference speed setting.Speed pointer:- The pointer moves on a graduated dial.Speed dial:- The dial is made of two linear scales: one from 60ktto 250kt with 5kt increments, the other from 250 to450kt with 1Okt increments.




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STANDBY INSTRUMENT PRESENTATION - AIRSPEED INDICATORTMUNAVE03-P04 LEVEL 1



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METRIC ALTIMETER (OPTION)

The Metric Altimeter is located on the centerinstrument panel and comprises the following elements:A display counter, made up of two drums displays thetens of thousands and the thousands of meters.Altitude counter:- When the altitude is below 10,000 meters, the leftdrum displays black and white stripes.In case of negative altitude the left drum displaysorange and white stripes.Altitude pointer:- The pointer indicates the hundreds of meters with50 meter increments.Altitude dial:- The altitude dial is calibrated from O to 1000 meterswith 50 meter graduations.Baro correction counter:- The baro correction is displayed on a the lowercounter and is graduated in hecto Pascals.Adjustment baro setting knob:- The knob enables adjustment of the baro setting inthe range of 870 to 1050 hecto Pascals.




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STANDBY INSTRUMENT PRESENTATION - METRIC ALTIMETER (OPTION)



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34 - NAVIGATION

34-00-00 RADIO MANAGEMENT PANEL (RMP)PRESENTATION

CONTENTS:GeneralStandby Navigation KeysRotating KnobStandby/Course (STBY/CRS) WindowActive Window

TMUNA2201 LEVEL 1



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RADIO MANAGEMENT PANEL (RMP) PRESENTATION

GENERAL

The radio Nav frequency selection can only be performedwhen the guarded NAV key LED is on, after a dual FMGSlossThe ON/OFF switch controls the power supply of theRMP.

STANDBY NAVIGATION KEYS

As long as the NAV key is the only STBY NAV key selected,the windows still display communication frequencies.Then, pressing the VOR, ILS or ADF key changes thedisplays to the last RMP memorized values (frequencyand course).At any time, communication frequencies are stillselectable, simply by pressing the corresponding key.Beat Frequency Oscillator (BFO) is set on or off bypressing the key.

NOTE: The Microwave Landing System (MLS) key is aprovision.

ROTATING KNOB

Two concentric knobs allow preselection of frequencyfor radio communication and standby navigation systemsand selection of the required course for VORs and ILSs:

- the outer knob controls the most significantdigits,

- the inner knob controls the least significantdigits.

The desired frequency or course is set in the STBY/CRSwindow. Frequency becomes active by pressing thetransfer key.

STANDBY/COURSE (STBY/CRS) WINDOW

The STANDBY/COURSE window displays a standby frequencyor a course.Both can be changed by rotating the knob, but only thestandby frequency can be made active by pressing thetransfer key.If a course is displayed, the associated frequency isdisplayed in the ACTIVE window.

NOTE: If a course is displayed on the STBY/CRS window,pressing the transfer key will display the ACTIVEfrequency in both windows.

ACTIVE WINDOW

The active window shows the frequency in use of thesystem identified by the green LED on the selectedkey.




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RADIO MANAGEMENT PANEL (RMP) PRESENTATIONTMUNA2201-P01 LEVEL 1



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TMUNA2201 LEVEL 1



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34 - NAVIGATION

34-00-00 DDRMI PRESENTATION

CONTENTS:GeneralNormal OperationFailure and Non Computed Data (NCD)Self Examination

TMUNAVF02 LEVEL 1



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DDRMI PRESENTATION

GENERAL

The Digital Distance and Radio Magnetic Indicator(DDRMI) is located on the center instrument panel.It’s a combined VOR/ADF/DME RMI.

Note: Some DDRMIs are not equipped with the ADFcapability.

NORMAL OPERATION

The DME 1 Distance is displayed in the left hand window.The DME 2 Distance is displayed in the right handwindow.A single pointer indicates the VOR 1 or ADF 1 bearing.A double pointer indicates the VOR 2 or ADF 2 bearing.The selection of VOR or ADF is provided for each pointerby a selector switch.

TMUNAVF02-T01 LEVEL 1



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DDRMI PRESENTATION - NORMAL OPERATIONTMUNAVF02-P01 LEVEL 1



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DDRMI PRESENTATION

FAILURE AND NON COMPUTED DATA (NCD)

When a failure is detected by the DME or RMI monitoringcircuits, the corresponding DME display window isblanked.In case of Non Computed Data (NCD), for example:

- out-of-range station, the window shows whitehorizontal dashed lines.

Heading information normally comes from ADIRU 1.If it fails, the heading is provided by ADIRU 3 afterpilot switching.In case of VOR or ADF 1 or 2 receiver failure, a redflag comes into view and the corresponding pointer isset to the 3 o’clock position.In case of Non Computed Data (NCD), no failure flagappears, but the corresponding pointer is set to the3 o’clock position.

TMUNAVF02-T02 LEVEL 1



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DDRMI PRESENTATION - FAILURE AND NON COMPUTED DATA (NCD)



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SELF EXAMINATION

From which ADIRU can the DDRMI receive information ?A - ADIRU 1 or 2.B - ADIRU 2 or 3.C - ADIRU 1 or 3.

TMUNAVF02 LEVEL 1



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34 - NAVIGATION

34-10-00 ADIRS PRINCIPLE

CONTENTS:GeneralADM Functional DescriptionADM InputsADM OutputADR ComputationIR StrapdownRing Laser GyroAccelerometerIR Computation

TMUADI001 LEVEL 1



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ADIRS PRINCIPLE

GENERAL

The Air Data/Inertial Reference Unit (ADIRU) comprisesan Air Data Reference Unit and an Inertial ReferenceUnit, both included in a single unit.Data from external sensors (Angle of Attack, Total AirTemperature, Air Data Module) are used by the ADIRU.The ADIRUs are interfaced with the ADIRS DisplayControl Unit (CDU) for control and status annunciation.

TMUADI001-T01 LEVEL 1



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ADIRS PRINCIPLE - GENERALTMUADI001-P01 LEVEL 1



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ADIRS PRINCIPLE

ADM FUNCTIONAL DESCRIPTION

A microcomputer processes an ARINC signal accordingto the discrete inputs and to the digitized pressure.

ADM INPUTS

The ADM Inputs are one pressure input and severaldiscrete inputs.The ADMs are identical.The discrete inputs determine the ADM location and thetype of pressure data (Pitot or Static) provided tothe ADR.

ADM OUTPUT

The ADM output is an ARINC bus which provides digitalpressure information, type of pressure, ADMidentification and BITE status to the ADIRU.




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ADIRS PRINCIPLE - ADMTMUADI001-P02 LEVEL 1



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ADIRS PRINCIPLE

ADR COMPUTATION

The ADR processes sensor and ADM inputs in order toprovide air data to users.




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ADIRS PRINCIPLE - ADRTMUADI001-P03 LEVEL 1



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ADIRS PRINCIPLE

IR STRAPDOWN

In a strapdown Inertial Reference System the gyros andthe accelerometers are solidly attached to the aircraftstructure.The strapdown laser gyro provides directlyaccelerations and angular speeds.




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ADIRS PRINCIPLE - IRTMUADI001-P04 LEVEL 1



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ADIRS PRINCIPLE

RING LASER GYRO

The three ring laser gyros, one for each rotation axis,provide inertial rotation data and are composed of twoopposite laser beams in a ring.At rest, the two beams arrive at the sensor with thesame frequency.An aircraft rotation creates a difference offrequencies between the two beams.The frequency difference is measured by optical meansproviding a digital output which, after computation,will provide rotation information.

NOTE: Light Amplification Stimulated Emission ofRadiation (LASER)




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ADIRS PRINCIPLE - GYROTMUADI001-P05 LEVEL 1



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ADIRS PRINCIPLE

ACCELEROMETER

Three accelerometers, one for each axis, provide linearaccelerations.The acceleration signal is sent to a processor whichuses this signal to compute the velocity and theposition.

IR COMPUTATION

Each ADIRU computes the laser gyro and theaccelerometer outputs to provide Inertial Referencedata to users.




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TMUADI001 LEVEL 1



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34 - NAVIGATION

34-10-00 ADIRS PRESENTATION

CONTENTS:GeneralMCDUADIRS CDUProbesFCUGPSDMCDMC/PFD & NDADIRS SwitchingUsersSelf Examination

TMUADIA01 LEVEL 1



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ADIRS PRESENTATION

GENERAL

The Air Data Inertial Reference System (ADIRS) iscomposed of three Air Data Inertial Reference Units(ADIRU), each having their own set of probes andsensors and a common Control Display Unit (CDU).

MCDU

The Multipurpose Control and Display Units (MCDUs) arenormally used to align the Inertial References, toinitiate the ADIRU tests and to display ADIRUinformation.

ADIRS CDU

The ADIRS Control Display Unit is used as a back-upfor Inertial Reference alignment. It is also used formode selection, information display and statusindication.

PROBES

The Air Data input parameters, such as total and staticpressures, Angle Of Attack (AOA) and Total AirTemperature (TAT) are sent, from the related probesand sensors, to the three ADIRUs.

NOTE : static and total pressure are sent to the ADIRUsvia the ADMs.

FCU

The ADIRUs receive, from the Flight Control Unit (FCU),the Baro correction set by the crew.

GPS

The Global Positioning System (GPS) provides data tothe ADIRS, mainly A/C position and speed. The ADIRSprocesses the GPS data and provides pure GPS data,pure IR data and hybrid GPS/ADIRS data to users.

DMC

The Display Management Computers (DMCs) 1 and 2 receivetheir data from their related ADIRU and from ADIRU 3.The Display Management Computer 3 (DMC3) receivesinformation from all three ADIRUs, to operate as aback-up in case of DMC1 or 2 failure.

DMC/PFD & ND

ADIRU 1 and 2 display information via DMC 1 and 2, onthe corresponding Primary Flight Display (PFD) andNavigation Display (ND).ADIRU 3 operates as a back-up in case of ADIRU 1 or 2failure.

TMUADIA01-T01 LEVEL 1



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ADIRS PRESENTATIONTMUADIA01-P01 LEVEL 1



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ADIRS PRESENTATION

ADIRS SWITCHING

Basically, ADIRU 1 is associated to the captaininstruments, ADIRU 2 to the first officer instrumentsand ADIRU 3 is in standby.In case of failure of the Air Data Reference (ADR) orInertial Reference (IR) function of ADIRU 1 or 2, theaffected instruments and displays may be manuallyswitched independently to ADIRU 3 by means of selectorswitches.

USERS

The ADIRUs are directly connected to other user system.

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SELF EXAMINATION

Which ADIRU does not supply DMC 1?A - ADIRU 1.B - ADIRU 2.C - ADIRU 3.

TMUADIA01 LEVEL 1



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TMUADIA01 LEVEL 1



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34 - NAVIGATION

34-13-00 AIR DATA PROBES PRESENTATION

CONTENTS:Pitot ProbesStatic PortsAOA SensorsTAT SensorsWater DrainSelf Examination

TMUADIB01 LEVEL 1



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AIR DATA PROBES PRESENTATION

PITOT PROBES

The total pressure is sent from the Pitot Probes tothe Air Data Modules which convert it into ARINC wordsused by the Air Data Inertial Reference Units.Three pitot probes provide total pressure to three AirData Modules (ADM) which convert this pressure intodigital format (ARINC 429).ARINC words are then sent to the corresponding AirData Inertial Reference Unit (ADIRU). The standby pitotprobe supplies the standby Airspeed Indicator (ASI)and ADR3 through its related ADM.

STATIC PORTS

Each Air Data Module transforms the static pressurecoming from the static ports into ARINC words.Six static ports provide static pressure to five ADMswhich convert this pressure into digital format (ARINC429).The standby static ports provide an average pressuredirectly to the standby instruments, and to ADR3through a single ADM.

AOA SENSORS

Each ADIRU receives angle of attack information fromits corresponding Angle Of Attack (AOA) sensors.The Angle Of Attack sensors are also called Alphaprobes.

TAT SENSORS

The three ADIRUs receive Total Air Temperatureinformation from two Total Air Temperature sensors.

NOTE: that ADIRU3 receives the Total Air Temperature(TAT) from the TAT 1 sensor which is composedof two elements.

WATER DRAIN

The probes are installed in such a way that theirpressure lines do not require a water drain, exceptfor that of the standby static ports.

TMUADIB01-T01 LEVEL 1



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AIR DATA PROBES PRESENTATIONTMUADIB01-P01 LEVEL 1



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SELF EXAMINATION

How do pitot and static probes supply the ADIRUs?A - Using ADMs which convert pressure into

digital format.B - Directly with total and static pressures.C - Directly with digital format.

Where does ADIRU3 receive TAT information from?A - Captain TAT sensor.B - First-Officer TAT sensor.C - Standby TAT sensor.

Which pressure line(s) need(s) to be drained?A - All pitot lines.B - All static lines.C - Only the standby static line.

TMUADIB01 LEVEL 1



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34 - NAVIGATION

34-10-00 ADIRS CDU PRESENTATION

CONTENTS:System SelectorKeyboardON BAT LightIR LightsMode Rotary SelectorADR P/BSWData SelectorData DisplayStatus MessagesStatus Action CodesSelf Examination

TMUNAV101 LEVEL 1



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ADIRS CDU PRESENTATION

SYSTEM SELECTOR

In OFF position, the CDU display is not energized(Blank Display).In position 1, 2 or 3 the corresponding system isselected for data display.

KEYBOARD

The keyboard is used to enter in the selected systemthe present position for alignment or Magnetic Headingif in ATTITUDE mode.N, S, E, W keys permit position entry.H allows heading entry in attitude mode.The green ENTER pushbutton light comes on when eitherthe NORTH, SOUTH, WEST, EAST, or HEADING has beenselected. When pressed the displayed data is enteredinto the Inertial Reference Systems.The green CLEAR pushbutton light comes on when any keyhas been pressed.When pressed, the displayed data, not yet entered, iscleared.

ON BAT LIGHT

The amber ON BAT light comes on when one or more AirData Inertial Reference Unit are operating on aircraftbatteries.The ON BAT light comes on for five seconds during thepower up test. ON BAT stays off in case of fastrealignment.

IR LIGHTS

An amber FAULT light comes on, accompanied by ECAMactivation when a fault affects the related InertialReference.When flashing, attitude and heading may be recoveredin ATT mode.A white ALIGN light illuminates steady when the relatedInertial Reference is in the alignment phase.The ALIGN light goes off when alignment has beencompleted.ALIGN light flashes in case of:

- An alignment error- No Present Position entry within ten minutesof NAV mode selection.

- Significant difference memorized position atshutdown and entered position.

MODE ROTARY SELECTOR

The mode rotary selector permits selection of threemodes for each Inertial Reference.In OFF position, the ADIRU is not energized (ADR andIR data not available).NAVIGATION is the normal mode of operation providingfull inertial data to the aircraft systems.ATTITUDE is a back-up mode, mainly providing attitudeand heading information in case of loss of navigationcapability.In ATT mode, the magnetic heading must be enteredthrough the CDU and has to be updated frequently.




UFD4200


ADIRS CDU PRESENTATION - SYSTEM SELECTORTMUNAV101-P01 LEVEL 1



UFD4200



AIR DATA REFERENCE P/BSW

The output buses of each air data reference aredisconnected when its related pushbutton switch is setto OFF position.An amber FAULT light comes on accompanied by ECAMactivation when a fault is detected in the related AirData Reference.




UFD4200



TMUNAV101 LEVEL 1



UFD4200



DATA SELECTOR

The Data Selector permits the display of the selectedInertial Reference data and status.




UFD4200


ADIRS CDU PRESENTATION - DATA SELECTORTMUNAV101-P02 LEVEL 1



UFD4200


ADIRS CDU PRESENTATION - DATA DISPLAYTMUNAV101-P03 LEVEL 1



UFD4200


ADIRS CDU PRESENTATION - STATUS MESSAGESTMUNAV101-P04 LEVEL 1



UFD4200


TMUNAV101-P05 LEVEL 1

ADIRS CDU PRESENTATION - STATUS ACTION CODES



UFD4200


SELF EXAMINATION

The inertial data, TK/GS, PPOS, WIND, HDG areavailable on:

A - ATT only.B - NAV only.C - ATT or NAV.

When does the ALIGN light flash?A - Within five minutes of NAV mode

selection, when present position has notbeen entered.

B - During the alignment phase in case ofIRS alignment error.

C - When alignment has been completed.

TMUNAV101 LEVEL 1



UFD4200



TMUNAV101 LEVEL 1



UFD4200


34 - NAVIGATION

34-10-00 ADIRS SWITCHING

CONTENTS:GeneralPrincipleSwitching Example

TMUNAV201 LEVEL 3

EFFECTIVITY 34-10-00 Page 1Apr 16/98


UFD4200


ADIRS SWITCHING

GENERAL

The Air Data Inertial Reference System (ADIRS) iscomposed of three Air Data Inertial Reference Units(ADIRUs)

PRINCIPLE

Various instruments and systems receive data fromthe ADIRS for inertial and air data display:

- The Primary Flight Displays (PFDs),- The Navigation Displays (NDs),- The ECAM System Display (SD)- The Digital Distance and Radio MagneticIndicator (DDRMI).

The ADIRS provides:- Barometric altitude to the Air Traffic Control(ATC) system for mode S.

- Data to the Flight Augmentation Computers(FACs) for computation of variouscharacteristic speeds.

- Data to the Weather Radar (WR) system forantenna attitude stabilization.

Basically, ADIRU1 is associated with systems 1 andthe DDRMI, ADIRU2 with systems 2, ADIRU3 is instandby.If an Air Data Reference (ADR) or an InertialReference (IR) fails, the AIR DATA or ATT HDGselectors enable the crew to use ADR 3 or IR 3.The manual switching is mainly performed to recoverdisplays.The computers select their inputs according to theswitching for consistency of computation and display.

NOTE: The ADIRU data sent to the ECAM System Display(E/SD) are Static Air Temperature (SAT) and TotalAir Temperature (TAT).




UFD4200


ADIRS SWITCHINGTMUNAV201-P01 LEVEL 3



UFD4200


ADIRS SWITCHING

SWITCHING EXAMPLE

Here is an example of ADIRS switching in order to seethe effects on the schematic.




UFD4200


ADIRS SWITCHING EXAMPLETMUNAV201-P02 LEVEL 3



UFD4200



TMUNAV201 LEVEL 3



UFD4200


34 - NAVIGATION

34-10-00 ADIRUS INTERCONNECTION

CONTENTS: ADR to IR ADR to ADR ADR Switching IR Switching Switching Control Self Examination

TMUADIE01 LEVEL 3



UFD4200


ADIRUS INTERCONNECTION

ADR TO IR

The ADR transmits information used to compute IR data.The ADR output buses are connected to the IR inputsrespectively called internal (INT) A and B. Basically, each IR receives 3 ADR outputs, but usesits own ADR output for IR data computation.

ADR TO ADR

Each ADR receives air data computed by the two otherADRs to crosscheck its own data. The 4 parameters checked are:

- static pressure,- total pressure, - Angle Of Attack (AOA),- Total Air Temperature (TAT).

ADR SWITCHING

When the Captain or First Officer ADR fails, the AIRDATA switch allows the crew to perform a manualswitching to ADR3 to recover air data display. Note: The basic purpose of the AIR DATA/ATT HDG

switching is to recover data display.

IR SWITCHING

When the Captain or First Officer IR fails, theattitude heading switch allows the crew to perform amanual switching to IR3 to recover inertial datadisplay. When a manual switching is performed, the ADRassociated to the failed IR is automatically switchedto IR3 to maintain a computation/display homogeneity.

If the associated ADR is not available, IR3 will workwith ADR3.

SWITCHING CONTROL

Two discretes, AUTO and MANUAL, permit each IR toselect a valid input. AUTO is always grounded for IR1 and IR2. The state of IR3 AUTO or MANUAL discrete depends onthe selector position. As soon as an ADR fails, before manual switching, theair data display is lost but the associated IRautomatically switches to ADR3 to ensure computationcontinuity as the internal bus is invalid.

TMUADIE01-T01 LEVEL 3



UFD4200


ADIRUS INTERCONNECTIONTMUADIE01-P01 LEVEL 3



UFD4200


SELF EXAMINATION

What must be done in case of ADR1 failure? A - Set AIR DATA switch to CAPT3 position.B - Set ATT HDG switch to CAPT3 position.C - Leave AIR DATA and ATT HDG switches on

NORM position.

What must be done in case of IR3 failure? A - Set AIR DATA switch to F/O3 position.B - Set ATT HDG switch to F/O3 position.C - Leave ATT HDG switch in NORM position.

When AUTO discrete is grounded, where does the IRreceive air data from?

A - Input bus A.B - Input bus B.C - Internal bus, then from bus A, then from

bus B depending on bus validity.

TMUADIE01 LEVEL 3



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34 - NAVIGATION

34-12-00 ADIRS ALIGNMENT THROUGH MCDU

CONTENTS:ADIRS Alignment Through MCDU

TMUADIS01 LEVEL 3



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ADIRS ALIGNMENT THROUGH MCDU

To perform the IRs alignment, select the FMGC then theINIT key.1. To perform the three Inertial Reference alignments,

the NAV position on the ADIRS CDU must be selected,and then the aircraft Present Position (PPOS) hasto be entered.To send Present Position (PPOS) you can either entera Company Route (CO RTE) or the Latitude (LAT) andLongitude (LONG) or a FROM/TO.We will here perform a FROM/TO insertion.For example LSGG/LGAT:- Departure from GENOVA,- Arrival at ATHENS.Use the keyboard to enter the LSGG/LGAT in thescratchpad and then the LS key 1R to valid it inthe FROM/TO field.

2. The route corresponding to the chosen FROM/TO isdisplayed on the MCDU.In our example only one company route is available,insert it by using LS key 6R.

3. The return to the INIT page is automatic after routeinsertion.Now the FROM airport position is given on the LATand LONG line. The ALIGN IRS prompt is displayed.As this airport position is preset, it can bemodified according to the real aircraft position,this explains the arrows displayed on the LAT line,which indicate that the LAT can be changed usingthe slew keys.You can now initiate the 3 IRs alignment by pressing3R key (ALIGN IRS). The present aircraft positionwill be automatically sent to the 3 IRs.

4. ALIGN IRS message has disappeared and IR alignmentis now in progress (10 minutes).ON ADIRS CDU, ALIGN annunciators will go off.If ALIGN annunciators remain on or begin to flashit means that the IR alignment phase isunsuccessful.

NOTE: If the INIT page A was left without having alignedthe IRs, an IR ALIGN message will be displayedin the scratchpad.

TMUADIS01-T01 LEVEL 3



UFD4200


TMUADIS01-P01 LEVEL 3

ADIRS ALIGNMENT THROUGH MCDU



UFD4200



TMUADIS01 LEVEL 3



UFD4200


34 - NAVIGATION

34-12-00 ADIRS ALIGNMENT THROUGH CDU

CONTENTS:ADIRS Alignment Through CDU

TMUNA1001 LEVEL 3



UFD4200


ADIRS ALIGNMENT THROUGH CDU

The aircraft is stationary on ground before take-off.The three mode selectors are in the OFF position, theADIRUs are not energized.1. When any mode selector is set to the NAV position,

the amber ON BAT light comes on for five secondsand goes off.When the ON BAT light is off, the white ALIGN lightcomes on.

NOTE: ALIGN light flashes if the aircraft position hasnot been entered 10 minutes after NAV modeselection (using MCDU or ADIRS CDU).

The three selectors are in the NAV position, the IRsare waiting for aircraft’s present position insertion.2. When the SYS selector is in position 1, 2 or 3, the

window display is energized and the system selectedis ready for display.DATA display selector must be set to PPOS in orderto enter the present position.

3. ADIRS CDU is now ready to accept the aircraft’spresent position (PPOS):TOULOUSE - BLAGNAC: N43-37-8, E122.6Present Position LATITUDE: N43-37-8The keyed latitude is displayed on the left sideof the window display.The PPOS Latitude is entered into the 3 IRs whichare in align mode whatever the system selected withthe SYS selector.Present Position LONGITUDE: E1-22-6The keyed longitude is displayed on the right sideof the window display.The PPOS Longitude is entered into the 3 IRs, theyare ready to be aligned.

NOTE: If the actual PPOS is different by more than1 degree in longitude and latitude from theprevious one it must be keyed and entered twice.

4. The DATA selector is now set to the HDG position.The TTN (Time To Nav) indication gives the renamingtime in minutes until completion alignment.The message IRS IN ALIGN appears on the MEMO pageof the ECAM DU.True Heading (HDG) is displayed at TTN 5.When the alignment is completed, TTN indicationdisappears and all ALIGN lights go off. The 3 IRsare now aligned.




UFD4200



ADIRS ALIGNMENT THROUGH CDU



UFD4200



TMUNA1001 LEVEL 3



UFD4200


34 - NAVIGATION

34-12-00 ADIRS BACK-UP OPERATION (ATTMODE)

CONTENTS:ADIRS Back-Up Operation (ATT Mode)

TMUNA1101 LEVEL 3

EFFECTIVITY 34-12-00 Page 1Sep 30/94


UFD4200


ADIRS BACK-UP OPERATION (ATT MODE)

The ATTITUDE mode (ATT) is a back-up mode providingonly attitude and magnetic heading information, incase of loss of navigation capability (temporary powercut-off or BITE failures causing excessive data errorsin NAV mode). We will see here the case of an IR2fault.1. The single chime sounds, the MASTER CAUT comes on

and the FAULT light on the ADIRS CDU flashesindicating an IR2 fault (HDG flag on PFD and ND andATT on PFD).NAV IR2 FAULT message appears followed by:- ATT HDG SWTG... F/O3, on the ECAM DU telling thecrew to switch to IR3 system.The IR2 fault is also confirmed by the followingstatus message on ADIRS CDU when system 2 and STSare selected:- STS-SELECT ATT

2. When the ATT position is selected, the respectiveIR is in ATTITUDE mode. The FAULT light goes off,the ALIGN light comes on and then goes off (after20 s).ATT MOD on the ADIRS CDU window indicates that youare in attitude mode (Pitch and Roll data againdisplayed on the EFIS).Note that the ATT mode must be engaged with aircraftin level flight.In ATT mode the crew can insert a magnetic heading.In order to perform the HEADING insertion, the DATAselector must be set to the HDG position.

3. When the DATA selector is in the HDG and the SYSselector is in position 2,the magnetic heading canbe keyed and entered into IR2.When the H key is selected the green ENT and CLRlights come on. HDG appears in the window display.The magnetic HDG which is 353.9° is typed on thekeyboard.

NOTE: the magnetic heading is indicated on theinstruments.

4. The ENT key is used to send the magnetic headingto IR2, when done the ENT and CLR lights go off.The IR2 is now in ATTITUDE mode and mainly sendsattitude and heading data.If the IR2 had to be used again, the crew shouldtake into account the gyro drift and updatefrequently the HDG reference.




UFD4200



ADIRS BACK-UP OPERATION (ATT MODE)



UFD4200



TMUNA1101 LEVEL 3



UFD4200


34 - NAVIGATION

34-10-00 ADIRS INDICATIONS ON PFD

CONTENTS:AttitudeHeadingAirspeedVertical SpeedAltitudeSelf Examination

TMUADIH01 LEVEL 2



UFD4200


ADIRS INDICATIONS ON PFD

ATTITUDE

The inertial attitude data is displayed by a spherein the middle of the Primary Flight Display (PFD).

1. PITCH SCALEThe aircraft pitch angle is given by the displacementof the pitch attitude scale (white) through a displaywindow.For pitch angles of more than 25° or than - 13°, theguidance symbols and the Flight Mode Annunciator (FMA)are removed.

2. ROLL SCALEThe fixed roll scale (white) comprises rollgraduations.For roll angles of more than 45° the guidance symbolsand the Flight Mode Annunciator (FMA) are removed.

3. ROLL INDEXThe roll index (yellow) attached to the sphere movesalong the fixed roll scale and provides the roll data(Aircraft bank angle).

TMUADIH01-T01 LEVEL 2



UFD4200


TMUADIH01-P01 LEVEL 2

ADIRS INDICATIONS ON PFD - ATTITUDE (SHEET 1/2)



UFD4200



4. FLIGHT PATH VECTORThe flight path vector (green) indicates the actualaircraft inertial trajectory.The flight path vector is used as a reference when theFlight Director (FD) is engaged in TRACK/FLIGHT PATHANGLE mode (TRK/FPA).

5. DISCREPANCYWhen an attitude discrepancy is detected between theCaptain display and the First Officer display, an amberCHECK ATT message is displayed on both PFDs associatedwith aural and visual ECAM cautions.The attitude discrepancy threshold is 5°.This discrepancy is detected by comparison of the 2 IRSsin use within the Flight Warning Computer (FWC).

6. FAILUREIn case of attitude failure, the attitude sphere iscleared and replaced by an attitude flag (ATT red).The red ATT flag first flashes then remains steady.The failure is detected by the associated Air DataInertial Reference Unit (ADIRU).




UFD4200


ADIRS INDICATIONS ON PFD - ATTITUDE (SHEET 2/2)TMUADIH01-P02 LEVEL 2



UFD4200



HEADING

The magnetic heading is displayed in the lower sectionof the Primary Flight Display (PFD) and with a whiteheading scale on the horizon line.

1. HEADING SCALESTwo moving heading scales (white) provide the crewwith heading data.

2. HEADING REFERENCE LINEA fixed heading reference line (yellow) shows theactual heading on the lower heading scale.

3. ACTUAL TRACK SYMBOLThe diamond shaped symbol (green) indicates the ActualTrack.

4. TRUE HEADINGTRU (white) indicates that true heading is displayedinstead of magnetic heading (automatically whenlatitude above 73° north or below 60° south for polarnavigation).

5. DISCREPANCYWhen a heading discrepancy is detected between theCaptain display and the First Officer display, an amberCHECK HDG message is displayed on both PFDs associatedwith aural and visual ECAM cautions.The heading discrepancy threshold is 5°.This discrepancy is detected by a comparison of the 2 IRsin use within the Flight Warning Computers (FWC).

6. FAILUREIn case of heading failure, the graduations from thetwo scales disappear and are replaced on the lowerscale by the red HDG flag.The red HDG flag first flashes then remains steady.The failure is detected by the associated ADIRU.




UFD4200


ADIRS INDICATIONS ON PFD - HEADINGTMUADIH01-P03 LEVEL 2



UFD4200



AIRSPEED

The Computed Airspeed (CAS),given by the ADR, isdisplayed on the left hand side of the PFD.

1. AIRSPEED SCALEA moving airspeed scale (white) with graduations inknots provides the crew with airspeed information.Airspeed display starts/stops at 30 kts. Below 30 kts,the CAS label is set to NCD (No Computed Data).The speed scale is graduated from 30 to 520 kts.

2. AIRSPEED REFERENCE LINEA fixed airspeed reference line (yellow) shows theactual airspeed on the airspeed scale.The MACH number (green) is displayed if above 0.5 Mand no ILS selection. It disappears at 0.45 M.

3. FAILUREIn case of airspeed failure, the airspeed scale isreplaced by the red SPD flag.The red SPD flag first flashes then remains steady.In case of mach failure, the mach number is replacedby the red MACH flag.




UFD4200


ADIRS INDICATIONS ON PFD - AIRSPEEDTMUADIH01-P04 LEVEL 2



UFD4200



VERTICAL SPEED

The inertial Vertical Speed (V/S) is displayed on theright hand side of the Primary Flight Display.

1. V/S SCALEA vertical speed scale (white) with graduations infeet per minute, provides the crew with vertical speedinformation.

2. V/S POINTERA pointer (green) provides the vertical speed in analogform.The pointer rotates around a point outside the V/Sscale.Only the portion of the needle inside the scale isdisplayed.

3. NUMERICAL VALUEAbove a V/S threshold, a numerical value (green) inhundreds of feet per minute comes into view and followsthe pointer.

4. EXCESSIVE V/SIn case of excessive vertical speed, the digital andanalog indications become amber.Excessive V/S when:- V/S > 6000 ft/mn or V/s < - 6000 ft/mn,- V/S < - 2000 ft/mn when 1000 < RA Height < 2500 ft,- V/S < - 1200 ft/mn below 1000 ft RA Height.

5. DEGRADED DATAWhen the inertial vertical speed is not available, thebaro vertical speed is automatically displayed.An amber box surrounds the numerical value.

6. FAILUREIn case of vertical speed failure, the scale isreplaced by the red V/S flag.




UFD4200


ADIRS INDICATIONS ON PFD - VERTICAL SPEEDTMUADIH01-P05 LEVEL 2



UFD4200



ALTITUDE

The Altitude is displayed on the right hand side ofthe Primary Flight Display.

1. ALTITUDE SCALEA moving altitude scale (white) with graduations everyhundred feet provides the crew with altitudeinformation.

2. ALTITUDE INDICATIONThe aircraft altitude is shown in a window (yellow)by a counter for hundreds of feet and a drum for tensand units.

3. BARO REFERENCEThe baro reference can be standard (STD), QNH or QFE(optional)(white) according to the selection made onthe EFIS control panel.

4. DISCREPANCYWhen an altitude discrepancy is detected between theCaptain display and the First Officer display, an amberCHECK ALT message is displayed on both PFDs associatedwith aural and visual ECAM cautions.The Altitude discrepancy threshold is:

- 250 ft with baro selected (QNH or QFE),- 500 ft with STD selected.

This discrepancy is detected by comparison of the 2ADRs in use within the Flight Warning Computers (FWC).

5. FAILUREIn case of altitude failure, the altitude scale isreplaced by the red ALT flag.The red ALT flag first flashes then remains steady.The failure is detected by the associated ADIRU.




UFD4200


ADIRS INDICATIONS ON PFD - ALTITUDE

TMUADIH01-P06 LEVEL 2



UFD4200


SELF EXAMINATION

What is displayed if the inertial vertical speed isnot available?

A - A red V/S flag comes on.B - A degraded V/S data provided by ADR.C - Nothing.

What information is displayed on the airspeed scale?A - CAS from ADR.B - CAS from ADR mixed with inertial speed.C - CAS from ADR, inertial speed if ADR

failure.

What happens if an altitude failure occurs?A - The altitude scale goes out of view.B - A red ALT flag is displayed.C - A and B.

TMUADIH01 LEVEL 2



UFD4200


34 - NAVIGATION

34-10-00 ADIRS INDICATIONS ON ND

CONTENTS:ROSE ModeARC ModePLAN ModeSelf Examination

TMUADII01 LEVEL 2



UFD4200


ADIRS INDICATIONS ON ND

ROSE MODE

The ROSE mode provides a 360 degree sector (compassrose) around the fixed aircraft symbol (yellow).

1. SPEEDThe speed information (green) is displayed in the leftupper corner.The True Airspeed (TAS) is displayed for speeds higherthan 100 kts.

2. WINDThe wind information (green) is displayed in the leftupper corner showing force and direction.

3. HEADINGThe magnetic heading is read on a full rotating dial,on a fixed lubber line (yellow).A TRU (white) message is displayed when in true headinginstead of magnetic heading in polar areas.A diamond shaped symbol (green) indicates the aircraftactual track.

4. DISCREPANCYWhen a heading (HDG) discrepancy occurs between theCaptain and First Officer Navigation Displays (NDs),an amber CHECK HDG message is displayed on both NDsassociated with aural and visual ECAM cautions.The heading (HDG) discrepancy threshold is 5°.This discrepancy is detected by comparison of the 2 IRSin use within the Flight Warning Computer (FWC).

5. FAILUREWhen a heading failure is detected, a HDG red flag isdisplayed.The red HDG flag first flashes then remains steady.

TMUADII01-T01 LEVEL 2



UFD4200


TMUADII01-P01 LEVEL 2

ADIRS INDICATIONS ON ND - ROSE MODE



UFD4200



ARC MODE

The ARC mode provides a 90 degree sector ahead of thefixed aircraft symbol.


2. WINDThe wind information (green) is displayed in the leftupper corner showing force and direction.

3. HEADINGThe magnetic heading (white) is read on a partialrotating dial, on a fixed lubber line.A TRU (white) message is displayed when in true headinginstead of magnetic heading in polar areas.A diamond shaped symbol (green) indicates the aircraftactual track.

4. DISCREPANCYWhen a heading (HDG) discrepancy occurs between theCaptain and First Officer Navigation Displays (NDs),an amber CHECK HDG message is displayed on both NDsassociated with aural and visual ECAM cautions.The Heading (HDG) discrepancy threshold is 5°.This discrepancy is detected by comparison of the 2 IRsin use within the Flight Warning Computer (FWC).

5. FAILUREWhen a heading failure is detected, a red HDG flag isdisplayed.The red HDG flag first flashes then remains steady.




UFD4200


ADIRS INDICATIONS ON ND - ARC MODETMUADII01-P02 LEVEL 2



UFD4200



PLAN MODE

The PLAN mode provides a map display centeredautomatically on the active waypoint or any otherwaypoint of the flight plan after pilot action on theMCDU.


2. WINDThe wind information (green) is displayed in the leftupper corner.

3. HEADINGThe map displayed (white) is referenced to north up.




UFD4200


ADIRS INDICATIONS ON ND - PLAN MODETMUADII01-P03 LEVEL 2



UFD4200


SELF EXAMINATION

A heading discrepancy between the NDs is detectedby?

A - FWCs.B - DMCs.C - ADIRS.

How is the drift angle indicated?A - By a diamond shaped symbol rotating on

the heading dial.B - By the difference between heading

reference and actual track symbol.C - A or B, according to information

validity.

TMUADII01 LEVEL 2



UFD4200


34 - NAVIGATION

34-10-00 ADIRS INDICATIONS ON ECAMDISPLAY UNIT

CONTENTS:Total Air Temperature/Static Air TemperatureFailureSwitchingSelf Examination

TMUADIN01 LEVEL 2



UFD4200


ADIRS INDICATIONS ON ECAM DISPLAY UNIT

TOTAL AIR TEMPERATURE/STATIC AIR TEMPERATURE

The Total Air Temperature (TAT) (Green) and Static AirTemperature (SAT) (Green) are permanently displayed.TAT range: - 60°C + 99°C,SAT range: - 99°C + 80°C.

FAILURE

In case of failure or when no computed data informationis received, the data is replaced by amber crosses.

SWITCHING

Basically, ADR2 provides data.ADR3 provides data when the AIR DATA switch is set toFirst Officer 3 (F/O 3).Back up data is provided by setting the AIR DATA switchto the F/O 3 position.

TMUADIN01-T01 LEVEL 2



UFD4200


TMUADIN01-P01 LEVEL 2

ADIRS INDICATIONS ON ECAM DISPLAY UNIT



UFD4200


SELF EXAMINATION

The TAT and SAT data is provided by?A - ADR1 or ADR3.B - ADR2 or ADR3.C - ADR1 or ADR2.

TMUADIN01 LEVEL 2



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34 - NAVIGATION

34-10-00 ADIRS ECAM WARNINGS

CONTENTS:GeneralADR 1 or 2 FaultADR 3 FaultIR 1 or 2 FaultIR 3 FaultOverspeedStall WarningATT DiscrepancyHDG DiscrepancyALT Discrepancy

TMUADIR01 LEVEL 3

EFFECTIVITY 34-10-00 Page 1Oct 31/94


UFD4200


ADIRS ECAM WARNINGS

GENERAL

The ADIRS warning messages are shown on the lower partof the upper ECAM display unit.

IMPORTANT:Although the ADIRS warnings are amber, they aredirectly computed by the FWC from ADIRU data.

TMUADIR01-T01 LEVEL 3



UFD4200


ADIRS ECAM WARNINGS - ADR 1 OR 2 FAULTTMUADIR01-P01 LEVEL 3



UFD4200


ADIRS ECAM WARNINGS - ADR 3 FAULTTMUADIR01-P02 LEVEL 3



UFD4200


ADIRS ECAM WARNINGS - IR 1 OR 2 FAULTTMUADIR01-P03 LEVEL 3



UFD4200


ADIRS ECAM WARNINGS - IR 3 FAULTTMUADIR01-P04 LEVEL 3



UFD4200


ADIRS ECAM WARNINGS - OVERSPEEDTMUADIR01-P05 LEVEL 3



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ADIRS ECAM WARNINGS - STALL WARNINGTMUADIR01-P06 LEVEL 3



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ADIRS ECAM WARNINGS - ATT DISCREPANCYTMUADIR01-P07 LEVEL 3



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ADIRS ECAM WARNINGS - HDG DISCREPANCYTMUADIR01-P08 LEVEL 3



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ADIRS ECAM WARNINGS - ALT DISCREPANCYTMUADIR01-P09 LEVEL 3



UFD4200



TMUADIR01 LEVEL 3



UFD4200


34 - NAVIGATION

34-20-00 STANDBY INSTRUMENT COMPONENTS

CONTENTS:Airspeed IndicatorAltimeterCompassHorizon IndicatorVOR/DME RMIMetric Altimeter (Option)VOR/ADF/DME RMI (Option)ADF/RMI (Option)

TMUADIJ01 LEVEL 3



UFD4200


STANDBY INSTRUMENT COMPONENTS

AIRSPEED INDICATOR

IDENTIFICATIONFIN: 9FN

LOCATION:ZONE: 211

COMPONENT DESCRIPTIONThe standby Airspeed Indicator(ASI) contains acapsule operated mechanism which measures thepitot/static pressure differential from the standbystatic probes and the standby pitot.An integral lighting supplied with external 5VAC isprovided to illuminate the instrument.

ALTIMETER


LOCATION:ZONE: 211

COMPONENT DESCRIPTIONThe standby altimeter is supplied with static pressureby the standby probes to indicate the barometricaltitude of the aircraft.An integral lighting with external 5VAC is providedto illuminate the instrument.

TMUADIJ01-T01 LEVEL 3



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STANDBY INSTRUMENT COMPONENTS - AIRSPEED INDICATOR - ALTIMETERTMUADIJ01-P01 LEVEL 3



UFD4200



COMPASS


LOCATION:ZONE: 211

COMPONENT DESCRIPTIONThe magnetic compass, installed on the top of thewindshield center part, is an independent instrumentwhich provides the crew with the aircraft’s magneticheading.

NOTE: The calibration of the compass must be done afterthe radio receivers are switched on.




UFD4200


STANDBY INSTRUMENT COMPONENTS - COMPASSTMUADIJ01-P02 LEVEL 3



UFD4200



HORIZON INDICATOR


LOCATION:ZONE: 211

COMPONENT DESCRIPTIONThe gyroscopic horizon, installed on the centerinstrument panel, is an independent instrument whichprovides the crew with a constant indication of theaircraft’s attitude.

VOR/DME RMI


LOCATION:ZONE: 211

COMPONENT DESCRIPTIONThe VOR/DME Radio Magnetic Indicator (VOR/DME RMI)installed on the center instrument panel, uses digitalARINC 429 type inputs. It receives parameters from ADIRUs, VORs and DMEs forthe display of:- Magnetic or true heading,- VOR bearings,- DME distances.




UFD4200


STANDBY INSTRUMENT COMPONENTS - HORIZON INDICATOR - VOR/DME RMITMUADIJ01-P03 LEVEL 3



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METRIC ALTIMETER (OPTION)


LOCATIONZONE: 211

DESCRIPTIONThe metric altimeter is supplied with static pressureby the standby air data to indicate the barometricaltitude of the aircraft in meters.An integral lighting with external 5VAC is providedto illuminate the instrument.

VOR/ADF/DME RMI (OPTION)


LOCATION:ZONE: 211

DESCRIPTIONThe VOR/ADF/DME Radio Magnetic Indicator (VOR/ADF/DMERMI) installed on the center instrument panel, usesdigital ARINC 429 type inputs.It receives parameters from ADIRUs, VORs, ADFs andDMEs for the display of:- Magnetic or true heading,- VOR bearings,- ADF bearings,- DME distances.




UFD4200


STANDBY INSTRUMENT COMPONENTS - METRIC ALTIMETER AND VOR/ADF/DME RMI (OPTIONS)TMUADIJ01-P04 LEVEL 3



UFD4200



ADF/RMI (OPTION)


LOCATION:ZONE: 211

COMPONENT DESCRIPTIONThe ADF Radio Magnetic Indicator (ADF/RMI) installedon the center instrument panel, uses digital ARINC 429type inputs.It receives parameters from ADIRUs and ADFs for thedisplay of:- Magnetic or true heading,- ADF bearings.




UFD4200


STANDBY INSTRUMENT COMPONENTS - ADF/RMI (OPTION)

TMUADIJ01-P05 LEVEL 3



UFD4200



TMUADIJ01 LEVEL 3



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34 - NAVIGATION

34-10-00 ADIRS COMPONENTS

CONTENTS:Air Data ModuleAOA SensorsStatic ProbesTAT SensorsPitot ProbesADIRS CDUADIRUsVMO/MMO Switch

TMUADIO03 LEVEL 3

EFFECTIVITY 34-10-00 Page 1Nov 30/99


UFD4200


ADIRS COMPONENTS

AIR DATA MODULE

IDENTIFICATIONFIN: 19FP1, 19FP2, 19FP3, 19FP419FP5, 19FP6, 19FP7, 19FP8

LOCATIONZONE: 121, 125, 126, 127, 128

COMPONENT DESCRIPTIONThe ADMs are near and above the level of the pitot andstatic probes, this to permit the ADM pneumaticplumbing to be self draining (except stby static line).

AOA SENSORS

IDENTIFICATIONFIN: 3FP1, 3FP2, 3FP3

LOCATIONZONE: 127, 128

COMPONENT DESCRIPTIONThe AOA sensor is of the windvane type.The sensing element is a small wing, positioned in theairflow direction, linked to a free turning shaft.

TMUADIO03-T01 LEVEL 3



UFD4200


TMUADIO03-P01 LEVEL 3

ADIRS COMPONENTS - ADMs AND AOAS



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ADIRS COMPONENTS

STATIC PROBES

IDENTIFICATIONFIN: 7DA1, 7DA2, 7DA38DA1, 8DA2, 8DA3

LOCATIONZONE: 121, 122, 127, 128

COMPONENT DESCRIPTIONThe probes are protected from icing by a heatercircuit.

TAT SENSORS

IDENTIFICATIONFIN: 11FP1, 11FP2


COMPONENT DESCRIPTIONThere are 2 sensing elements in each sensor.The TAT sensors are heated through the Probe HeatingComputer (PHC).The heating element must not be energized on theground.

NOTE: The second sensing element on the TAT 2 sensoris not used.




UFD4200


ADIRS COMPONENTS - STATIC PROBES AND TATSTMUADIO03-P02 LEVEL 3



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ADIRS COMPONENTS

PITOT PROBES

IDENTIFICATIONFIN: 9DA1, 9DA2, 9DA3


COMPONENT DESCRIPTIONThe probes are protected from icing by a heatercircuit.

ADIRS CDU

IDENTIFICATIONFIN: 2FP

LOCATIONZONE: 211

COMPONENT DESCRIPTIONThe ADIRS CDU is located on overhead panel 20VU.It contains 3 identical connectors, each connector islinked to one ADIRU.




UFD4200


ADIRS COMPONENTS - PITOT PROBES AND ADIRS CDUTMUADIO03-P03 LEVEL 3



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ADIRS COMPONENTS

ADIRUs

IDENTIFICATIONFIN: 1FP1, 1FP2, 1FP3


COMPONENT DESCRIPTIONThe ADIRU is contained in a 4 MCU case as defined inARINC 600.The ADIRU contains an ADR and an IR portion suppliedby a common power source.

VMO/MMO SWITCH

IDENTIFICATIONFIN: 22FP

LOCATIONZONE: 128

COMPONENT DESCRIPTIONThis switch is selected for particular flights withthe landing gear down (Ferry flights for example).It allows the ADR to determine the normal or alternateVMO/MMO law.




UFD4200


ADIRS COMPONENTS - ADIRUS AND VMO/MMO SWITCHTMUADIO03-P04 LEVEL 3



UFD4200



TMUADIO03 LEVEL 3



UFD4200


34 - NAVIGATION

34-36-00 MMR SYSTEM PRESENTATION

CONTENTS:GeneralILS PrincipleGPS PrincipleComponentsILS IndicatingGPS IndicatingSelf Examination

TMUMMRA01 LEVEL 1



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MMR SYSTEM PRESENTATION

GENERAL

The Multi Mode Receiver (MMR) system is a NavigationSensor with 2 internal receivers.MMR = ILS + GPS

ILS PRINCIPLE

The function of the Instrument Landing System (ILS)is to provide the crew and airborne system users withsignals transmitted by a ground station.A descent axis is determined by the intersection of aLocalizer beam (LOC) and a Glide Slope beam (G/S)created by this ground station at known frequencies.The ILS allows measurement and display of angulardeviations and receives the Morse audio signal whichidentifies the ILS ground station.ILS operational frequency range:

- LOC: between 108.1 and 111.95 MHz,- G/S: between 329.15 and 335 MHz.

TMUMMRA01-T01 LEVEL 1



UFD4200


MMR SYSTEM PRESENTATION - ILS PRINCIPLETMUMMRA01-P01 LEVEL 1



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GPS PRINCIPLE

The NAVigation System Time And Ranging GlobalPositioning System ( NAV.S.T.A.R. GPS ) is a worldwidenavigation radio aid which uses satellite signals toprovide accurate navigation information.The architecture of the system is composed of 3 partscalled segments:

- Spatial Segment- Control Segment- User Segment

SPATIAL SEGMENTThe spatial segment is composed of a constellation of24 satellites.These satellites are arranged in six separate orbitalplanes of four satellites each on a circular orbit andhave the following characteristics:

- 55° inclination to the Equator,- an altitude of approx 20200 km with an orbitalperiod of 12 sideral hours.

These satellites give:- the satellite position (Ephemeris of theconstellation),

- the constellation data (Almanach).- the atmospheric corrections.




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MMR SYSTEM PRESENTATION - GPS PRINCIPLE - SPATIAL SEGMENTTMUMMRA01-P02 LEVEL 1



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GPS PRINCIPLE (Continued)

CONTROL SEGMENTThe control segment is composed of four monitorstations and one master control station which trackthe satellites, compute the ephemeris, clockcorrections and control the navigation parameters andtransmit them to the GPS users.The four monitor stations are located at:

- KWAJALEIN- HAWAII- ASCENCION ISLAND- DIEGO GARCIA

The master control station is located at:- COLORADO SPRINGS.




UFD4200


MMR SYSTEM PRESENTATION - GPS PRINCIPLE - CONTROL SEGMENTTMUMMRA01-P03 LEVEL 1



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GPS PRINCIPLE (Continued)

USER SEGMENTThe principle of GPS position computation is based onthe measurement of transmission time of the GPS signalsbroadcast by at least 4 satellites.This segment is constitued by the GPS receiver anddefined as follows:

- signal acquisition,- distance calculation,- navigation computation (Satellite choice,positioning, propagation corrections),

- detection and isolation of failed satellites(GPS PRIMARY).

NOTE: When GPS mode is active, no VOR/DME/ADF data isused for navigation.




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TMUMMRA01-P04 LEVEL 1

MMR SYSTEM PRESENTATION - GPS PRINCIPLE - USER SEGMENT



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COMPONENTS

The components are two ILS antennas, 2 GPS antennasand two MMR units.The MMR system is also connected to:

- Primary Flight Display (PFD) and NavigationDisplay (ND) for display.

- Electronic Flight Instrument System (EFIS)control unit for display control.

- Flight Management and Guidance Computer (FMGC)for ILS auto-tuning and GPS position.

- Multipurpose Control Display Units (MCDU) forILS manual tuning.

- Captain and First Officer Radio ManagementPanels (RMP) for ILS back-up tuning.

- Audio Control Panels (ACP) for ILS audiosignal.

- Air Data and Inertial Reference Unit forGPIR data.




UFD4200


MMR SYSTEM PRESENTATION - COMPONENTSTMUMMRA01-P05 LEVEL 1



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ILS INDICATING

The ILS data appears on the PFD as soon as the ILSpushbutton switch on the EFIS control panel has beenpressed in and on the ND when ROSE/ILS mode has beenselected.ILS information is displayed in magenta.The ILS1 information is displayed on PFD1 and ND2.The ILS2 information is displayed on PFD2 and ND1.




UFD4200


MMR SYSTEM PRESENTATION - ILS INDICATINGTMUMMRA01-P06 LEVEL 1



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GPS INDICATING

The GPS data is displayed on the MCDUs and on the NDs.- GPS data on MCDU (GPS MONITOR page): * GPS position (Lat, Long) * True Track * GPS altitude * Figure of Merit * Ground Speed * Number of satellites tracked * Mode.- GPS message on ND: * Availability of the GPS Primary navigation function.




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TMUMMRA01-P07 LEVEL 1

MMR SYSTEM PRESENTATION - GPS INDICATING



UFD4200


SELF EXAMINATION

The satellite orbital planes have an inclination of:A - 60°.B - 55° to the Equator.C - 45° to the Equator.

The control segment is composed of:A - 3 monitor stations.B - 5 monitor stations.C - 4 monitor stations and one master

control station.

TMUMMRA01 LEVEL 1



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34 - NAVIGATION

34-36-00 MMR DESCRIPTION/OPERATION

CONTENTS:GeneralILS FunctionGPS FunctionLGCIUCFDIUUsersIndicatingSelf Examination

TMUMMRC01 LEVEL 3



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MMR DESCRIPTION/OPERATION

GENERAL

The Multi Mode Receiver (MMR) system includes:- 2 MMR units,- 1 Glide Slope (G/S) antenna,- 1 Localizer (LOC) antenna,- 2 GPS antennas.

ILS FUNCTION

AUTO TUNINGIn normal operation, each Flight Management andGuidance Computer (FMGC) automaticaLly tunes itsownside ILS part (Port A) of the MMR unit through itsownside Radio Management Panel (RMP).If an FMGC failure occurs, a discrete (A/B switching)changes the tuning port (Port B) of the MMR unit, whichis directly connected to the opposite FMGC.

MANUAL TUNINGFrom each Multipurpose Control and Display Unit (MCDU)both MMR units can be manually tuned through theirownside FMGC.

NOTE: To return to the auto tuning mode, the manualmode has to be cleared.

BACK-UP TUNINGIn case of failure of both FMGCs, a back-up tuning isprovided by RMP 1 and 2.Either RMP controls both MMR units, if STBY NAV modeis activated on RMP 1 and 2 (RMP 3 not used for navaidstuning).In emergency electrical configuration RMP 1 only is supplied.

ANTENNASThe Glide Slope (G/S) and Localizer (LOC) antennas arecommon to both MMR units. Each antenna has two independentconnectors, for each MMR units.

TMUMMRC01-T01 LEVEL 3



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MMR DESCRIPTION/OPERATION - DATA ACQUISITIONTMUMMRC01-P01 LEVEL 3



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GPS FUNCTION

GPS OPERATIONThe Global Positioning System (GPS) function isachieved by a stand alone satellite navigation sensorusing the U.S GPS satellites constellation.The GPS primary function is to track the RF signalsreceived from the satellites and compute its ownposition and output the GPS data to the 3 ADIRUs.Receiver Autonomous Integrity Monitoring (RAIM) orAutonomous Integrity Monitored Extrapolation (AIME)provide integrity and availability of this data.

The GPS provides three dimensional aircraft position,velocities and exact time used for hybrid computationsby the 3 ADIRUs.In case of failure of one GPS, the ADIRU automaticallyselects the only operative GPS to compute hybrid GPIRdata.

ANTENNASThe GPS antenna is an L-band active antenna, with anintegrated preamplifier and filter, providing anomnidirectional upper hemispheric coverage.The GPS antenna operates at a frequency of 1575.42 Mhzcalled L1.A second frequency of 1227.6 Mhz, called L2, is usedto estimate the propagation error of L1 and to suppressit.

ADIRUTo reduce initialization time, MMR unit 1 and 2 receiveposition data (lat, long), time and date from theassociated ADIRU.

In case of failure of ADIRU2 the primary source ofADIRU3 being GPS1, it is necessary to select the secondinput port of ADIRU3 (GPS2) by means of the ATT/HDGswitching to preserve the side 1/side 2 segregation.

- MMR1/ADIRU1/FMGC1,- MMR2/ADIRU3/FMGC2.

FMGCThe IR portion of ADIRU1 or 2 provides FMGC1 or 2 withpure IR data, pure GPS data and hybrid GPIR data forposition fixing.The FMGC position is a mix of the hybrid GPS/IRSposition and the mixed IR position.

NOTE: As long as GPS/IRS mode is active, radio updatingDME/DME or VOR/DME is not allowed.

LGCIU

Each Landing Gear Control Interface Unit (LGCIU) sendsa Ground/Flight discrete signal which is used by thereceiver BITE module to count the flight legs in caseof CFDIU failure.




UFD4200


TMUMMRC01-P01 LEVEL 3

MMR DESCRIPTION/OPERATION - DATA ACQUISITION



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CFDIU

The Centralized Fault Display Interface Unit (CFDIU)enables tests and trouble shooting to be carried outon the MMR system using the MCDU.The test can be done only on ground.

USERS

The MMR data is sent to the FMGCs for aircraft guidanceduring take off, approach and landing phases.The MMR data is also sent to the ECAM for warnings.The MMR 1 data is send to the Ground Proximity WarningSystem (GPWS) for mode 5 computation (Descent below GS).

NOTE: A discrete signal sent by the FMGC inhibits anyfrequency change in the MMR unit when LAND modeis armed below 700 ft.

INDICATING

The ILS 1 data is sent, through the Display ManagementComputers (DMCs), to the CAPT PFD and F/O ND and theILS 2 data is sent to the F/O PFD and CAPT ND.An audio signal is also processed by the MMR unit (ILSpart) and sent to the Audio Management Unit (AMU) sothat it can be heard by the crew.Pure GPS data is available for display only on the GPSMONITOR page of the MCDUs. Operational messages mayalso be displayed on the NDs.




UFD4200


TMUMMRC01-P01 LEVEL 3

MMR DESCRIPTION/OPERATION - MONITORING AND DISPLAY



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SELF EXAMINATION

Which ILS receiver provides the Ground ProximityWarning Computer with data?

A - ILS 2 receiver.B - ILS 1 receiver.C - ILS 1 and ILS 2 receivers.

Where is ILS 2 data displayed?A - On Capt ND and F/O PFD.B - On Capt PFD and F/O ND.C - On F/O PFD and F/O ND.

The primary source of ADIRU3 is:A - GPS2.B - GPS1.C - GPS1 and 2.

The IR portion of the ADIRU provides the FMGC with:A - IR data, pure GPS data and hybrid GPIR

data.B - VOR/DME data.C - only GPS data.

TMUMMRC01 LEVEL 3



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34 - NAVIGATION

34-36-00 MMR INDICATIONS ON PFD

CONTENTS:ILS PushbuttonILS CharacteristicsVertical DeviationLateral DeviationFlagsSelf Examination

TMUMMRE01 LEVEL 2



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MMR INDICATIONS ON PFD

ILS PUSHBUTTON

The ILS data is displayed on the PFD if the ILSpushbutton is switched on the Electronic FlightInstrument System (EFIS) control panel.

ILS CHARACTERISTICS

The ILS characteristics are displayed in magenta inthe bottom left corner of the PFD.The ILS identification is displayed after decoding bythe ILS receiver.An amber ILS message flashes when APPR mode has beenarmed and ILS display not selected.

TMUMMRE01-T01 LEVEL 2



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TMUMMRE01-P01 LEVEL 2

MMR INDICATIONS ON PFD - ILS PUSHBUTTON AND CHARACTERISTICS



UFD4200



VERTICAL DEVIATION

The vertical deviation index (magenta) is associatedwith the Glide/Slope (G/S) beam reception.The vertical scale and the vertical index flash whenthe deviation is excessive.When the deviation is out of range, the vertical indexis against one stop and only its outer half remainsin view.

LATERAL DEVIATION

The lateral deviation index (magenta) is associatedwith the Localizer (LOC) beam reception.The lateral scale and the lateral index flash when thedeviation is excessive.When the deviation is out of range, the lateral indexis against one stop and only its outer half remainsin view.The ILS course is represented by a magenta coursepointer on the heading scale.




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MMR INDICATIONS ON PFD - VERTICAL AND LATERAL DEVIATIONTMUMMRE01-P02 LEVEL 2



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FLAGS

In case of failure, a corresponding flag is shown inred:

- if a LOC or G/S receiver fails, a red LOC orG/S flag appears on the corresponding deviationscale.

- if both LOC and G/S signals have failed, anILS 1 (or 2) flag is also displayed.




UFD4200


MMR INDICATIONS ON PFD - FLAGSTMUMMRE01-P03 LEVEL 2



UFD4200


SELF EXAMINATION

When do the G/S and LOC scales appear on the PFD?A - When the ILS pushbutton is selected.B - When G/S and LOC beams are received.C - A and B.

When does the lateral deviation scale flash?A - When the LOCALIZER receiver is faulty.B - When the deviation is excessive.C - When the aircraft is out of range.

When does the red ILS flag appear?A - When both LOC and G/S signals have

failed.B - When ILS frequency is not available.C - When the ILS is not selected on the FCU.

TMUMMRE01 LEVEL 2



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34 - NAVIGATION

34-36-00 MMR INDICATIONS ON ND

CONTENTS:ILS DataGPS DataSelf Examination

TMUMMRG01 LEVEL 2



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MMR INDICATIONS ON ND

ILS DATA

DATA DISPLAYAll the indications are displayed in ROSE-ILS mode.Only the ILS course pointer (magenta) is displayed inROSE-NAV or ARC mode if the ILS pushbutton is selectedon EFIS control panel.

ILS CHARACTERISTICSIn ROSE-ILS mode, the ILS characteristics are displayedin magenta, in the top right corner of the ND.The ILS identification is displayed after decoding bythe ILS receiver.The ILS information is crossed over on the NDs (ILS 1on ND 2; ILS 2 on ND 1).A green ILS APP message appears on the top middle ofthe ND when an ILS approach has been selected on theMCDU.

TMUMMRG01-T01 LEVEL 2



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TMUMMRG01-P01 LEVEL 2

MMR INDICATIONS ON ND - ILS DATA - DATA AND ILS CHARACTERISTICS



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ILS DATA

VERTICAL DEVIATIONThe vertical deviation index (magenta) is associatedwith the Glide/Slope (G/S) beam reception.The vertical scale (white) and the vertical index (G/S)flash when the deviation is excessive.When the deviation is out of range, the vertical indexis against one stop and only its outer half remainsin view.

LATERAL DEVIATIONThe lateral deviation bar (magenta) is associated withthe Localizer (LOC) beam reception.The lateral scale (white) and the lateral bar (LOC)flash if the deviation is excessive.The lateral bar, corresponding to the center part ofthe ILS course pointer (magenta), can move on thedeviation scale and gives the Localizer deviation.




UFD4200


MMR INDICATIONS ON ND - ILS DATA - VERTICAL AND LATERAL DEVIATIONSTMUMMRG01-P02 LEVEL 2



UFD4200



ILS DATA

FLAGSIn ROSE-ILS mode, if a failure occurs, a correspondingflag is displayed in red.In case of ILS failure, the ILS course pointer becomesred and points to 12 o’clock and the lateral bar isremoved.




UFD4200


MMR INDICATIONS ON ND - ILS DATA - FLAGSTMUMMRG01-P03 LEVEL 2



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GPS DATA

GPS data indications are displayed in all ND modes.A green GPS APP message appears on the top middle ofthe ND when a GPS approach has been selected in theMCDU.When, for any reason, the GPS primary navigation islost, the navigation function is degraded and revertsto traditional navigation function (IRS, Radio Nav...). An amber GPS PRIMARY LOST message is alsodisplayed at the bottom of the ND. In turn when theGPS is used by the FMGC for navigation, the GPS PRIMARYmessage is displayed in white at the bottom of the ND.




UFD4200


TMUMMRG01-P04 LEVEL 2

MMR INDICATIONS ON ND - GPS DATA



UFD4200


SELF EXAMINATION

What is displayed in ROSE-NAV mode when the ILSpushbutton is selected on the EFIS control panel?

A - An ILS course pointer.B - A lateral deviation bar.C - A and B.

How is the excessive deviation displayed onvertical scale?

A - The Glide/Slope index disappears.B - A red "G/S" symbol appears in the middle

of the scale.C - The Glide/Slope index and the scale

flash permanently.

TMUMMRG01 LEVEL 2



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34 - NAVIGATION

34-36-00 MMR COMPONENTS

CONTENTS:MMR UnitGlide/Slope AntennaLocalizer AntennaGPS Antenna

TMUMMRJ01 LEVEL 3



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MMR COMPONENTS

SAFETY PRECAUTIONS

Before working on the ILS antennas, put a warningnotice in the cockpit, on the pedestal, to tell personsnot to operate the radar system.

MMR UNIT

IDENTIFICATIONFIN: 40RT1, 40RT2

LOCATIONZONE: 120

COMPONENT DESCRIPTIONThe front face of the MMR unit is fitted with fourLEDs and a TEST pushbutton.When the TEST pushbutton is pressed in, the functionaltest starts, the 4 LEDS come on.If the test is OK, the green TEST OK LED comes on, theother LEDs should go off when the TEST pushbutton isreleased.The back is fitted with an ARINC 600 connector.

TMUMMRJ01-T01 LEVEL 3



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TMUMMRJ01-P01 LEVEL 3

MMR COMPONENTS - MMR UNIT



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MMR COMPONENTS

GLIDE/SLOPE ANTENNA

IDENTIFICATIONFIN: 4RT

LOCATIONZONE: 110

COMPONENT DESCRIPTIONThe Glide/Slope (G/S) antenna is a folded half looptype driven by capacitance coupling.The G/S antenna is horizontally polarized and has animpedance of 50 ohms.The antenna has two independent RF connectors used tofeed two independent ILS receivers.

LOCALIZER ANTENNA

IDENTIFICATIONFIN: 3RT

LOCATIONZONE: 110

COMPONENT DESCRIPTIONThe Localizer (LOC) antenna is a folded half loop typedriven by capacitance coupling.The LOC antenna is horizontally polarized and has animpedance of 50 ohms.The antenna has two independent RF connectors used tofeed two independent ILS receivers.




UFD4200


MMR COMPONENTS - GLIDE/SLOPE AND LOCALIZER ANTENNASTMUMMRJ01-P02 LEVEL 3



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GPS ANTENNA

IDENTIFICATIONFIN: 43RT1, 43RT2

LOCATIONZONE: 210

COMPONENT DESCRIPTIONThe GPS antenna is an active antenna with an integratedpreamplifier and filter and has a right hand circularpolarized and omnidirectional radiation pattern.A 50 ohm impedance coaxial cable connects the antennato the MMR.The power supply of the preamplifier is provided bythe MMR unit.




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MMR COMPONENTS - GPS ANTENNATMUMMRJ01-P02 LEVEL 3



UFD4200



TMUMMRJ01 LEVEL 3



UFD4200


34 - NAVIGATION

34-41-00 WR/PWS SYSTEM PRESENTATION

CONTENTS:GeneralWeather Radar (WR) PrinciplePredictive Windshear (PWS) Principle (Option)ComponentsWR IndicatingPWS Indicating (Option)Self Examination

TMUWPWA02 LEVEL 1



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WR/PWS SYSTEM PRESENTATION

GENERAL

The Airborne Weather Radar and Predictive WindshearSystem (WR/PWS) detects and localizes atmosphericdisturbances and windshear events in the area scannedby the antenna.

Note: The PWS (Predictive Windshear System) functionis optional.

WEATHER RADAR (WR) PRINCIPLE

The WR helps the pilots to avoid these areas and theassociated turbulences by determining their range andbearing.It can also be used for ground mapping.The radar emits microwave pulses through a directiveantenna which picks up the return signals.The distance is determined by the time taken for theecho to return.The azimuth is given by the antenna position when theecho is received.

TMUWPWA02-T01 LEVEL 1



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WR/PWS SYSTEM PRESENTATION - WEATHER RADAR (WR) PRINCIPLETMUWPWA02-P01 LEVEL 1



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PREDICTIVE WINDSHEAR (PWS) PRINCIPLE (OPTION)

A windshear event is a sudden change of wind speedand/or direction over a small distance due to downwardsand/or upwards movement of the air.The most critical moment for the aircraft is near theground level during the approach or in take-off.




UFD4200


TMUWPWA02-P02 LEVEL 1

WR/PWS SYSTEM PRESENTATION - PREDICTIVE WINDSHEAR (PWS) PRINCIPLE



UFD4200



COMPONENTS

The main components are an antenna, a wave guide, atransceiver and a control unit.The WR/PWS system is also connected to the NavigationDisplays (NDs) via the DMCs for display.

Note: The control panels shown here after are givenas examples. They may differ according to youraircraft configuration.




UFD4200


TMUWPWA02-P03 LEVEL 1

WR/PWS SYSTEM PRESENTATION - COMPONENTS



UFD4200



WR INDICATING

The Weather Radar image is shown on the Captain andFirst Officer Navigation Displays.Radar image and radar information status (TILT, GAIN,failure) are displayed in the different EFIS modes(ARC and ROSE) except in PLAN mode.

PWS INDICATING (OPTION)

The Predictive Windshear indications are shown on theCaptain and F/O PFDs and NDs.The windshear phenomenon is indicated by an iconsuperimposed on the radar image in the different EFISmodes (ARC and ROSE) except in PLAN mode.




UFD4200


WR/PWS SYSTEM PRESENTATION - WR AND PWS INDICATINGTMUWPWA02-P04 LEVEL 1



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SELF EXAMINATION

Windshear indications are shown:A - Only on the NDs.B - On the PFDs and the NDs.C - On the Upper ECAM DU.

TMUWPWA02 LEVEL 1



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34 - NAVIGATION

34-41-00 WR/PWS DESCRIPTION/OPERATION

CONTENTS:GeneralSystem DescriptionSystem InterfacesIndicatingSelf Examination

TMUWPWC01 LEVEL 3



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WR/PWS DESCRIPTION/OPERATION

GENERAL

The Weather Radar and Predictive Windshear System(WR/PWS) is composed of:

- 1 control unit,- 1 transceiver (WR/PWS),- 1 antenna,- 1 wave guide.

Note: The PWS function is optional.

SYSTEM DESCRIPTION

CONTROL UNITThe Control Unit provides modes of operation, antennatilt and gain of the receiver digitized information,via an ARINC 429 bus.An ON/OFF discrete ensures the energization of thetransceiver which in turn supplies the control unitand the antenna.Two other discrete signals enable:

- the windshear function (through AUTO/OFFswitch)

- BITE management, sent to the CFDIU.

TRANSCEIVERThe Weather Radar uses the principle of radio echoingto detect the level of precipitation, the ground map,and the principle of Doppler effect to detect theturbulence areas.The transmitter operates in X-Band frequency at 9345MHz.The PWS function also uses the principle of Dopplereffect to detect windshear events.

Horizontal and vertical wind velocity, gravity andaircraft true airspeed are the different windshearcomponents for the determination of the windshearthreshold.

ANTENNAThe Weather Radar antenna is energized and controlledin azimuth and elevation by the transceiver.The radio frequency signals are exchanged between thetransceiver and the antenna, via a wave guide.The antenna scans a 180° sector in azimuth and has atilt coverage of + or - 15°.An internal circuit of the transceiver ensures antennastabilization.The stabilization data is: pitch and roll angles,selected tilt, antenna azimuth and elevation angle.

TMUWPWC01-T01 LEVEL 3



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WR/PWS DESCRIPTION/OPERATION - GENERAL - SYSTEM DESCRIPTIONTMUWPWC01-P01 LEVEL 3



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SYSTEM INTERFACES

ADIRUsThe WR receives, from Air Data and Inertial ReferenceUnits (ADIRUs) one and three, pitch and roll data, forthe stabilization and control of the antenna, andground speed for Doppler mode correction.The ADIRU, which provides data, is selected by meansof the ATT/HDG selector switch.The PWS function receives data from ADIRU 1 and 3 forvelocity calculations:

- TAS, Altitude (or corrected altitude), EW andNS velocity GS, TRK angle, TRUE HDG and MAGHDG.

LGCIUThe Landing Gear Control Interface Unit (LGCIU) sendsFlight/Ground information to the transceiver.This discrete signal is used by the receiver BITEmodule to count the flight legs.In windshear condition, a landing gear extended signalis used in order to determine the transition from thelanding mode to the take-off mode.

CFDIUThe Multipurpose Control and Display Units (MCDUs)allow the system to be tested via the Centralized FaultDisplay Interface Unit (CFDIU).The test is only available on ground.During the test, the antenna carries out an elevationand an azimuth scanning sequence.

QUALIFIERS A AND B SIGNALSTwo types of qualifier inputs are required to preventautomatic activation of the windshear function.- Qualifier A: 2 qualifiers are used (QA1 and QA2).Provided by the ATC/TCAS control unit, whichindicates the position of the AUTO/ON/STBY switch.Qualifier A is valid when AUTO or ON is selected.

- Qualifier B: 2 qualifiers are used (QB1 and QB2).Provided by EIU 1 and 2, which indicates a normalengine oil pressure.Qualifier B is valid when the engine is running(high oil pressure).

The Windshear function is automatically activatedbelow 2300ft RA and at least one of the two qualifierinputs, of both qualifiers A and B, has to be valid.

RAThe Radio Altimeter provides altitude informationthrough an ARINC 429 bus.This data is used for automatic activation of thewindshear function.

AUDIO INHIBIT SIGNALSThese discretes are used to indicate whether the auralalert output has to be active or not.

- predictive windshear aural alerts (discreteinput) inhibited by stall warning,

- predictive windshear discrete output is usedto inhibit aural alerts generated by TCAS orGPWS or other FWC warnings.

AUDIO MIXING BOXAn analog audio output allows the transmission of theaural alert windshear to an audio mixing box connectedto loudspeakers.




UFD4200


TMUWPWC01-P02 LEVEL 3

WR/PWS DESCRIPTION/OPERATION - SYSTEM INTERFACES



UFD4200



SYSTEM INTERFACES (Cont’d)

EGPWSThe Enhanced GPWS receives Predictive Windshear alertsfrom the radar hazard bus to determine the priorities.Alert Priorities:

- WR/PWS warning,- WR/PWS caution,- GPWS Terrain warning,- GPWS Terrain caution.

INDICATING

The Weather Radar transceiver is connected to the DMCsby means of two ARINC 453 buses.Each data cable is terminated at one end by a lowinductance resistor (68 ohms) to avoid a signal return.The Weather Radar image is shown on the CAPT and F/ONDs when ROSE or ARC mode is selected on the EFIScontrol panel.The Windshear events are shown on the CAPT and F/O NDsand all visual alerts on the CAPT and F/O PFDs.

NOTE: When both EFIS control panels are in PLAN mode,the WR/PWS transceiver is de-energized.




UFD4200


TMUWPWC01-P03 LEVEL 3

WR/PWS DESCRIPTION/OPERATION - INDICATING



UFD4200


SELF EXAMINATION

Which component controls antenna stabilization?A - ADIRU.B - Transceiver.C - Antenna.

Which data is used for antenna stabilization?A - Pitch and roll.B - Selected tilt angle, antenna azimuth

angle and elevation angle.C - A and B.

When is the Windshear function automaticallyactivated?

A - Below 2300ft and one of the twoqualifier inputs, of both qualifiers Aand B, is valid.

B - Always when a windshear event isencountered.

C - When the AUTO/ON/STBY selector on theATC/TCAS Control Unit is in STBYposition.

The Predictive Windshear discrete output is used to:A - Inhibit the windshear function.B - Inhibit aural alerts generated by TCAS

or GPWS or other FWC warnings.C - Transmit the aural alert to the Audio

Mixing Box.

TMUWPWC01 LEVEL 3



UFD4200


34 - NAVIGATION

34-41-00 WR/PWS CONTROLS AND DISPLAYS

CONTENTS:Control PanelControl Panel With Split Function (Option)WR Failure MessagesPWS Indications (Option)PWS Alert Levels (Option)Self Examination

TMUWPWE02 LEVEL 2



UFD4200


WR/PWS CONTROLS AND DISPLAYS

CONTROL PANEL

OFF/SYS/ON SYSTEM SWITCHWhen the system switch is set to ON, the Weather Radarsystem is energized and operates if at least one NDis set to ROSE or ARC mode.

NOTE: The operative radar transceiver is de-energizedwhen both EFIS selectors are in PLAN mode.

GAIN KNOBThe GAIN Knob permits receiver sensitivity adjustmentin the different modes.In AUTO position, the optimum setting is automaticallyadjusted.Clockwise rotation of the GAIN knob (manual gainsetting) adjusts the sensitivity to the MAX position.When not in AUTO mode, MAN is displayed in green inthe right lower corner on the NDs except in case offailure or system TEST.

MODE SELECTOR

1 - WX PositionWhen the mode selector is in the WX position, the radaris in normal mode of operation and the colors on theNDs depend on the intensity of the precipitation.Precipitation rate and related color echoes(P: precipitation rate):

- P < 1 mm/h: Black.- 1 < P < 4 mm/h: Green.- 4 < P < 12 mm/h: Yellow.- P > 12 mm/h: Red.

2 - WX/TURB positionThis mode corresponds to operation in weather andturbulence detection.The turbulence detection is limited to the first 40 NMfrom the A/C, beyond, the turbulence is displayed inthe conventional colors as in WX mode.The turbulence areas are displayed in magenta on theNDs (P > 5 mm/s).

3 - MAP positionThe MAP mode is useful for back-up navigation, todisplay mountains, cities, coast lines or land/waterboundaries.The colors on the NDs depend on the ground map:

- Mountains and cities: Amber.- Ground: Green.- Calm water: Black.

NOTE: A manual gain control is recommended when in MAPmode.

TMUWPWE02-T01 LEVEL 2



UFD4200


TMUWPWE02-P01 LEVEL 2

WR/PWS CONTROLS AND DISPLAYS - CONTROL PANEL



UFD4200



CONTROL PANEL (CONT’D)

TILT KNOBThe TILT knob allows manual control of the antennaelevation. The antenna elevation angle can be adjustedin 1/4 degree steps within a range of - 15° up to +15°.

NOTE: TILT information is displayed in cyan in theright lower corner of the NDs except in case offailure or system TEST.

NOTE: During a windshear detection event, the TILTantenna is automatically controlled. However,the TILT displayed on the NDs corresponds to thecontrol panel setting.

WINDSHEAR SWITCH (OPTION)The WINDSHEAR AUTO/OFF switch enables theactivation/deactivation of the predictive windshearfunction.When in AUTO position the predictive windsheardetection is automatically activated below 2500ftwhatever the OFF/SYS/ON system switch position.The predictive windshear function detection canoperate either with weather radar modes activated orindependently.A dedicated windshear icon is superimposed on the radarimage, displayed on the NDs, when the phenomena isdetected.




UFD4200



WR/PWS CONTROLS AND DISPLAYS - CONTROL PANEL



UFD4200



CONTROL PANEL WITH SPLIT FUNCTION (OPTION)

1/OFF/2 SYSTEM SWITCHThis three stable position switch enables theactivation of the transceiver 1 or 2 (if installed).When the switch is set to 1 or 2, the selected weatherradar system is energized and operates if at least oneND is set to ROSE or ARC mode.

MODE SELECTORSTwo mode selector switches are available. The left oneis dedicated to the CAPT and the right one to the F/O.

1 - WX Position:When the mode selector is in the WX position, the radaris in normal mode of operation and the colors on theNDs depend on the intensity of the precipitation.Precipitation rate and related color echoes(P: precipitation rate):

- P < 1 mm/h: Black.- 1 < P < 4 mm/h: Green.- 4 < P < 12 mm/h: Yellow.- P > 12 mm/h: Red.

2 - WX/TURB position:This mode corresponds to operation in weather andturbulence detection.The turbulence detection is limited to the first 40 NMfrom the A/C, beyond, the turbulence is displayed inthe conventional colors as in WX mode.The turbulence areas are displayed in magenta on theNDs (P > 5 mm/s).

TILT KNOBSTwo TILT knobs are available. The left one is dedicatedto the CAPT and the right one to the F/O.The TILT knobs allow manual control of the antennaelevation.The antenna elevation angle can be adjusted in 1/4 degreesteps within a range of - 15° up to + 15°.

NOTE: TILT information is displayed in cyan in theright lower corner of the NDs except in case offailure or system TEST.

NOTE: During a windshear detection event, the TILTantenna is automatically controlled. However,the TILTs displayed on the NDs correspond to thecontrol panel settings.




UFD4200



WR/PWS CONTROLS AND DISPLAYS - CONTROL PANEL WITH SPLIT FUNCTION



UFD4200



CONTROL PANEL WITH SPLIT FUNCTION (OPTION) (CONT’D)

CAPT/BOTH/FO SWITCH (OPTION)1 - BOTH POSITION:The CAPT and the F/O can operate separately the controlpanels using their associated controls. Thus, twodifferent weather radar images, with differentsettings, can be displayed on the CAPT and F/O NDs.Each scan of the weather radar alternately refreshesthe CAPT and the F/O displays.2 - CAPT Position:The weather radar image with the CAPT setting isdisplayed on both NDs.3 - F/O Position:The weather radar image with the F/O setting isdisplayed on both NDs.

NOTE: Below 2500ft the switch must be set to CAPT orF/O position in order to keep an appropriaterefresh rate of the radar image in case ofwindshear event detection.

WINDSHEAR SWITCH (OPTION)The WINDSHEAR AUTO/OFF switch enables theactivation/deactivation of the predictive windshearfunction.When in AUTO position the predictive windsheardetection is automatically activated below 2500 ftwhatever the 1/OFF/2 system switch position.The predictive windshear function detection canoperate either with weather radar modes activated orindependently.

A dedicated windshear icon is superimposed on the radarimage, displayed on the NDs, when the phenomena isdetected.




UFD4200



WR/PWS CONTROLS AND DISPLAYS - CONTROL PANEL WITH SPLIT FUNCTION



UFD4200



WR FAILURE MESSAGES

Two types of failures are likely to affect the radarsystem:

- Failures which result in a loss of radar image,displayed in red (loss of a radar systemcomponent).

- Failures which affect the radar image,displayed in amber (loss of a function).

EXAMPLE: Transceiver failure red message: WXR T/R(Red) appears in the right lower corner ofthe ND.




UFD4200


WR/PWS CONTROLS AND DISPLAYS - WR FAILURE MESSAGESTMUWPWE02-P05 LEVEL 2



UFD4200



PWS INDICATIONS (OPTION)

The windshear information is presented on the NDs onlyin the 10NM range.If not in this range and a windshear alert is generated,the message:

- W/S: SET RNG 10 NM is shown on the NDs.

When a windshear fault occurs, the radar image remainsavailable if the fault does not affect the radar modesor detection function.When a fault is detected amber PRED W/S message appearson the NDs if:

- A/C on ground or flap/slat lever not in 0position.

- WINDSHEAR AUTO/OFF switch on W/R controlpanel in AUTO position.




UFD4200


WR/PWS CONTROLS AND DISPLAYS - PWS INDICATIONSTMUWPWE02-P06 LEVEL 2



UFD4200



PWS ALERT LEVELS (OPTION)

There are three alert levels defined in function ofevent seriousness and distance from the aircraft.Visual and aural warnings are provided in function ofthe level detected.

- LEVEL 3: between 50ft and 1200ft (Warning Alert)* Aural warning message: GO AROUND WINDSHEARAHEAD (Approach), WINDSHEAR AHEAD WINDSHEARAHEAD (Take-Off)* Visual warning: red W/S AHEAD message on PFD.

- LEVEL 2: between 50ft and 1200ft (Caution Alert)* Aural warning message: MONITOR RADAR DISPLAY* Visual warning: amber W/S AHEAD message onPFD.

- LEVEL 1: No windshear advisory above 1500ft.No aural or visual warnings only the windshear iconsuperimposed on the radar image.




UFD4200


WR/PWS CONTROLS AND DISPLAYS - PWS ALERT LEVELSTMUWPWE02-P07 LEVEL 2



UFD4200


SELF EXAMINATION

In which mode is the manual gain adjustmentrecommended?

A - In any mode.B - In MAP mode.C - In WX/TURB mode.

Can a radar image be displayed in PLAN mode?A - Yes.B - No.

Does an amber warning mean the loss of radar image?A - Yes.B - No.

When the radar system switch is in OFF position?A - The predictive windshear function is not

activated.B - The predictive windshear function is

active until the WINDSHEAR/AUTO/OFF isin the AUTO position.

B - The predictive windshear function isalways available.

TMUWPWE02 LEVEL 2



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34 - NAVIGATION

34-41-00 WR/PWS OPERATIONAL PRECAUTIONS

CONTENTS:Special Precautions

TMUWPWG01 LEVEL 2



UFD4200


WR/PWS OPERATIONAL PRECAUTIONS

TRAINING INFORMATION POINT

SPECIAL PRECAUTIONSSome special precautions must be taken before usingthe weather radar system on the ground in MAP, WX orWINDSHEAR mode.

- The dangerous zone forward of the aircraft must befree of metallic obstacles such as hangars or aircraft,within 5 meters in an arc of + or - 90º on either sideof the aircraft centerline.

- Make sure that nobody is within a distance of 1.5meters from the antenna, in an arc of + or - 135º oneither side of the aircraft centerline.

- The system must not be operated during the refuelingof the aircraft or during any refueling operationwithin 100 meters.

NOTE: Although the power radiated by the system islow, the above written safety precautions shouldbe observed for obvious routine reasons(behaviour with respect to other types of radarsystems).To avoid radiating danger, and nuisance auralalerts the WINDSHEAR AUTO/OFF selector switchmust be selected OFF independently of the radarselector switch.

TMUWPWG01-T01 LEVEL 2



UFD4200


WR/PWS OPERATIONAL PRECAUTIONS - SPECIAL PRECAUTIONSTMUWPWG01-P01 LEVEL 2



UFD4200


THIS PAGE LEFT INTENTIONALLY BLANK.

TMUWPWG01 LEVEL 2



UFD4200


34 - NAVIGATION

34-41-00 WR/PWS COMPONENTS

CONTENTS:WR/PWS TransceiverWR/PWS Mounting TrayWR/PWS AntennaWR/PWS Control Unit

TMUWPWJ01 LEVEL 3



UFD4200


WR/PWS COMPONENTS

SAFETY PRECAUTIONS

Move the radar antenna assembly carefully to preventinjury to persons and damage to equipment (approximateweight: 15kg (33lb)).

Note: The PWS function is optional.

WR/PWS TRANSCEIVER

IDENTIFICATIONFIN: 1SQ1

LOCATIONZONE: 121

COMPONENT DESCRIPTIONThe face of the transceiver is fitted with a TESTpushbutton and a Liquid Crystal Display (LCD) on thefront of the transceiver.The back is equipped with an ARINC 600 size connectorincluding the wave guide insert.When the TEST pushbutton is pressed, a test sequenceis started, RADAR OK and INPUT OK appear at the endwhen no faults have been detected.

WR/PWS MOUNTING TRAY

IDENTIFICATIONFIN: 9SQ

LOCATIONZONE: 121

COMPONENT DESCRIPTIONThe WR transceiver is cooled by the avionicsventilation system. The wave guide switch ensuresswitching of the RF signal from the antenna to thetransceiver in the case of dual weather radarinstallation.

TMUWPWJ01-T01 LEVEL 3



UFD4200


TMUWPWJ01-P01 LEVEL 3

WR/PWS COMPONENTS - TRANSCEIVER AND MOUNTING TRAY



UFD4200


WR/PWS COMPONENTS

WR/PWS ANTENNA

IDENTIFICATIONFIN: 7SQ (Antenna Drive)FIN: 11SQ (Antenna Plate)

LOCATIONZONE: 110

COMPONENT DESCRIPTIONThe antenna movements are ensured by 2DC motors andthe angular positions are copied by synchros.Two switches for Azimuth (AZ) and Elevation (EL) areinstalled on the antenna drive.They are normally mechanically locked in the ONposition.When in OFF position, the command of the correspondingmotor is cancelled.

NOTE: A position indicator for the elevation axis (+ or-45°) is used to check the antenna drivecalibration with AZ switch in OFF position.




UFD4200


WR/PWS COMPONENTS - ANTENNATMUWPWJ01-P02 LEVEL 3



UFD4200


WR/PWS COMPONENTS

WR/PWS CONTROL UNIT

IDENTIFICATIONFIN: 3SQ

LOCATIONZONE: 210

COMPONENT DESCRIPTIONThe gain and tilt data are digitized by an 8 bit analogto digital converter.Moreover, the different positions of the mode selectorswitch and the data, from the potentiometer, areformatted to ARINC 429 words.




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WR/PWS COMPONENTS - CONTROL UNITTMUWPWJ01-P03 LEVEL 3



UFD4200



TMUWPWJ01 LEVEL 3



UFD4200


34 - NAVIGATION

34-42-00 RADIO ALTIMETER SYSTEMPRESENTATION

CONTENTS:PrincipleComponentsIndicating

TMURADG01 LEVEL 1



UFD4200


RADIO ALTIMETER SYSTEM PRESENTATION

PRINCIPLE

The Radio Altimeter (RA) System determines the heightof the aircraft above the terrain during initial climb,approach and landing phases.The RA can therefore operate over non-flat groundsurface.The principle of the radio altimeter is to transmit afrequency modulated signal, from the aircraft to theground, and to receive the ground reflected signalafter a certain delay.The time between the transmission and the receptionof the RA signal is proportional to the A/C height.

TMURADG01-T01 LEVEL 1



UFD4200


RADIO ALTIMETER SYSTEM PRESENTATION - PRINCIPLETMURADG01-P01 LEVEL 1



UFD4200



COMPONENTS

The components are two transceivers, two fans, twotransmission antennae and two reception antennae.The RA system is also connected to the DMCs for displayon the Primary Flight Displays (PFDs).




UFD4200


RADIO ALTIMETER SYSTEM PRESENTATION - COMPONENTSTMURADG01-P02 LEVEL 1



UFD4200



INDICATING

The aircraft height data is displayed on the PrimaryFlight Displays for heights less than or equal to 2500ft.The altitude is also shown by means of:

- A ground line rising on to the pitch down area(Below 300 ft).

- A red ribbon next to the altitude scale(Below 500 ft).




UFD4200


RADIO ALTIMETER SYSTEM PRESENTATION - INDICATINGTMURADG01-P03 LEVEL 1



UFD4200



TMURADG01 LEVEL 1



UFD4200


34 - NAVIGATION

34-42-00 RADIO ALTIMETERDESCRIPTION/OPERATION

CONTENTS:GeneralTransceiverAntennaeFanIndicatingUsersEIULGCIUCFDIUSelf Examination

TMURADA01 LEVEL 3



UFD4200


RADIO ALTIMETER DESCRIPTION/OPERATION

GENERAL

The Radio Altimeter (RA) system consists of twoindependent systems comprising :

- Two transceivers with associated mounts andfans,

- Two transmission antennae,- Two reception antennae.

TRANSCEIVER

The RA transceiver measures the radio height of theaircraft in relation to the ground.The transceiver operates in a frequency range of 4200to 4400 Mhz.

ANTENNAE

The RA system includes two identical transmission andreception antennae.The operating range of the antenna according to theaircraft attitude is limited to + or - 30 degree forpitch and roll.

FAN

Each RA transceiver is cooled by an associated fan,attached under the transceiver mount.A capacitor is mounted on the fan case in order tosuppress the parasites.

INDICATING

In normal operation, RA 1 provides the radio heightto the Captain Primary Flight Display (PFD) and RA 2to the First Officer PFD through the Display ManagementComputers (DMCs).In case of one transceiver failure the DMCautomatically switches to the other one.The radio height information appears on the PFDs whenless than or equal to 2500 ft.

USERS

The RA information is sent to various systems throughARINC 429 buses.

- EGPWS for terrain warnings,- FMGCs for processing data,- FWCs for call out indications and warnings,- ELACs for integration into various flightparameters.

TMURADA01-T01 LEVEL 3



UFD4200


RADIO ALTIMETER DESCRIPTION/OPERATIONTMURADA01-P01 LEVEL 3



UFD4200


RADIO ALTIMETER DESCRIPTION/OPERATION

EIU

The Engine Interface Unit (EIU) 1(2) sends a grounddiscrete to the RA 1(2) to inhibit the test on groundwhen the associated engine is operating.N2 rating > minimum idle rating.

LGCIU

The Landing Gear Control Interface Unit (LGCIU)provides the flight/ground information which is usedby the receiver BITE module to count the flight legs.

CFDIU

The Multipurpose Control and Display Units (MCDUs)allow the systems to be tested via the CentralizedFault Display and Interface Unit (CFDIU).The tests are only available on ground.

TMURADA01-T01 LEVEL 3



UFD4200



TMURADA01 LEVEL 3



UFD4200


SELF EXAMINATION

In normal operation, how is the height dataprovided ?

A - By system 1 to Capt PFD and F/O PFDB - By system 2 to CAPT PFD and F/O PFDC - By system 1 to CAPT PFD and by system 2

to F/O PFD

What happens if Radio Altimeter 1 fails ?A - RA 2 provides data to the EGPWC.B - FMGC 1 provides data to the EGPWC.C - The EGPWC no longer receives Radio

Altitude.

TMURADA01 LEVEL 3



UFD4200


34 - NAVIGATION

34-42-00 RA INDICATIONS ON PFD ANDAUTOMATIC CALL OUT

CONTENTS:Decision Height (DH)Radio HeightAnalog IndicationRising Runway IndicatingFailureAutomatic Call OutSelf Examination

TMURADB01 LEVEL 2



UFD4200


RA INDICATIONS ON PFD AND AUTOMATIC CALL OUT

DECISION HEIGHT (DH)

After the selection made by the pilot on theMultipurpose Control Display Unit (MCDU), the DecisionHeight (DH) data is displayed in the fourth column ofthe Flight Mode Annunciator as soon as Radio Altimetersoperate.When the radio height reaches the Decision Height (DH),an amber DH message flashes then remains steady.

RADIO HEIGHT

The radio height is displayed at the bottom of theattitude sphere for heights less than 2500 feet.The indication accuracy is in function of the height.

- H > 50 ft: 10 ft increments,- 5 ft < H <= 50 ft: 5 ft increments,- H <= 5 ft: 1 ft increments.

ANALOG INDICATION

A red ribbon is displayed on the right of the altitudescale representing the field elevation.This red ribbon is displayed below 570 ft.On ground the top of the ribbon is on the middle ofthe altitude window.

TMURADB01-T01 LEVEL 2



UFD4200


RA INDICATIONS ON PFD: DH AND RADIO HEIGHTTMURADB01-P01 LEVEL 2



UFD4200


RA INDICATIONS ON PFD AND AUTOMATIC CALL OUT

RISING RUNWAY INDICATING

In the final phase of an approach, below 150 feet, thewhite lower limit of the attitude sphere moves up asthe aircraft approaches the ground.This lower limit line covers the graduations of thepitch scale when it moves up.

FAILURE

When the slat/flap lever is not at zero, if both RadioAltimeters fail, a red RA flag is shown in place ofthe radio height information.Independently of slat/flap position, with failure ofboth RA, the red ribbon indication goes out of viewand the white lower limit line remains in its position.

AUTOMATIC CALL OUT

Below 400 feet, the radio altitude is announced by asynthetic voice,generated by the Flight WarningComputer (FWC).The altitude call out corresponds to predeterminedthresholds selected by pin programming listedhereafter:

- 400: four hundred- 300: Three hundred- 200: two hundred- 100: one hundred- 50: fifty- 40: forty- 30: thirty- 20: twenty- 10: ten- 5: five- DH + 100: hundred above- DH: minimum

TMURADB01-T02 LEVEL 2



UFD4200


TMURADB01-P02 LEVEL 2

RA INDICATIONS ON PFD: RISING RUNWAY INDICATING AND FAILURE



UFD4200


SELF EXAMINATION

With DH of 100ft entered on the MCDU, when will theradio altitude indication become amber?

A - At 100 ft.B - At 200 ft.C - At 400 ft.

When does the red RA flag appear on the PFD?A - When one RA fails.A - When both RAs fail and the slats are

extended.A - When both RAs fail below 2500ft.

TMURADB01 LEVEL 2



UFD4200


34 - NAVIGATION

34-42-00 RADIO ALTIMETER COMPONENTS

CONTENTS:RA TransceiversRA FansRA Antennae

TMURADD01 LEVEL 3



UFD4200


RADIO ALTIMETER COMPONENTS

RA TRANSCEIVERS

IDENTIFICATIONFIN: 2SA1, 2SA2

LOCATIONZONE: 152

COMPONENT DESCRIPTIONThe face of the transceiver is fitted with a TEST p/b,a TEST connector and four LEDS.When the TEST p/b is pressed in, the four LEDs comeon.If the test is OK, the four LEDs go off when the TESTp/b is released out.The back is fitted with an ARINC 600 electricalconnector.

TMURADD01-T01 LEVEL 3



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RA COMPONENTS - TRANSCEIVERSTMURADD01-P01 LEVEL 3



UFD4200



RA FANS

IDENTIFICATIONFIN: 3SA1, 3SA2

LOCATIONZONE: 152

COMPONENT DESCRIPTIONThe six-blade fan is integral with a removal base plateattached under the transceiver mount. It is containedin a square aluminium alloy case. It is supplied with115VAC through the electrical circuit of the associatedtransceiver.Parasites are suppressed by a capacitor mounted on thefan.




UFD4200


RA COMPONENTS - FANSTMURADD01-P02 LEVEL 3



UFD4200



RA ANTENNAE

IDENTIFICATIONFIN: - Reception : 5SA1, 5SA2 - Transmission : 6SA1, 6SA2

LOCATIONZONE: 153

COMPONENT DESCRIPTIONThe transmission and the reception antennae areidentical.The small thickeners antenna is installed on theaircraft’s skin.Each antenna is supplied through a coaxial connectorlinked to the transceiver.




UFD4200


RA COMPONENTS - ANTENNAETMURADD01-P03 LEVEL 3



UFD4200



TMURADD01 LEVEL 3



UFD4200


34 - NAVIGATION

34-43-00 TCAS PRESENTATION

CONTENTS:PrincipleComponentsIndicatingSelf Examination

TMUTCAB05 LEVEL 3



UFD4200


TCAS PRESENTATION

PRINCIPLE

The Traffic Collision Avoidance System (TCAS) is asystem whose function is to detect and display aircraftin the immediate vicinity and to provide the flightcrew with indications to avoid these intruders.The TCAS indications for flight plan modifications arein the vertical plane only.The TCAS detects the air traffic control system orTCAS equipped aircraft and maintains surveillancewithin a range determined by its sensivity.To evaluate threat potential of other aircraft thesystem divides the space around aircraft into 4volumes.- OTHER TRAFFIC VOLUME.The OTHER TRAFFIC VOLUME is the first volume providingthe presence and the progress of on intruder.(No collision threat).- PROXIMATE TRAFFIC VOLUME.The proximate traffic volume is defined by a givenvolume around the TCAS equipped aircraft.(No collision threat, but in vicinity).

- TRAFFIC ADVISORY VOLUME (TA).When the intruder is relatively near but does notrepresent an immediate threat, the TCAS provides anaural and visual information known as Traffic Advisory(TA).The TCAS aural messages can be inhibited depending onhigher priority aural messages.- RESOLUTION ADVISORY VOLUME (RA).When the intruder represents a collision threat, theTCAS triggers an aural and visual alarm known asResolution Advisory (RA), which informs the crew aboutavoidance maneuvers.

TMUTCAB05-T01 LEVEL 3



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TCAS PRESENTATION - PRINCIPLETMUTCAB05-P01 LEVEL 3



UFD4200


TCAS PRESENTATION

COMPONENTS

The TCAS components are two antennae, one TCAS computerand one TCAS/ATC control panel.Note: The TCAS/ATC control panels shown here after are

given as examples. They may differ according tothe aircraft configuration.




UFD4200


TCAS PRESENTATION - COMPONENTSTMUTCAB05-P02 LEVEL 3



UFD4200


TCAS PRESENTATION

INDICATING

The TCAS indications appear on the PFD and the ND.The visual resolution and traffic advisory indicationsare associated with aural indications such as "TRAFFIC,TRAFFIC", "CLIMB, CLIMB"...The TCAS displays only the most threatening intruders.




UFD4200


TCAS PRESENTATION - INDICATINGTMUTCAB05-P03 LEVEL 3



UFD4200


SELF EXAMINATION

Which aircraft are detected by the TCAS ?A - All.B - Only ATC Mode S equipped A/C.C - ATC equipped A/C.

TMUTCAB05 LEVEL 3



UFD4200


34 - NAVIGATION

34-43-00 TCAS DESCRIPTION/OPERATION

CONTENTS:GeneralAntennaeControl PanelComputerATCRadio AltimeterADIRUCFDIULGCIUIndicatingInhibitionPin ProgrammingDATA LoaderSelf Exination

TMUTCAF01 LEVEL 3



UFD4200


TCAS DESCRIPTION/OPERATION

GENERAL

The Traffic Collision Avoidance System (TCAS)includes:

- 1 control unit (common with ATC system),- 1 computer,- 2 antennae (1 top and 1 bottom).

ANTENNAE

The TCAS directional antennae provide azimuthinformation on aircraft located within the TCASsurveillance range.They transmit at 1030 MHz and receive at 1090 MHz.The phase and amplitude of the received signal dependon the direction of the signal source which permitsthe relative bearing of the transmitting aircraft tobe determined.

CONTROL PANEL

The operating modes of the TCAS are selected on acommon TCAS/ATC control panel.The TCAS information is transmitted to the TCAScomputer via the ATC transponder.

COMPUTER

The TCAS computer ensures two main functions:- a transmission/reception function for intruderacquisition,

- a processing function for operation control.

(Digital, discrete and analog types interfaces,intruder trajectory computation and tracking, visualand aural alert commands).

ATC

The operative ATC Mode S transponder transmits responseto ATC ground station interrogations and data to theTCAS.(Baro altitude, TCAS mode from control panel, TCASbroadcast messages).The Mode S transponder permits communication betweenthe TCAS and a TCAS equipped and detected aircraftthrough the communication link function for exchangingcoordination messages.

RADIO ALTIMETER

The Radio Altimeter (RA) provide radio height used asreference to determine the computation sensitivitylevel and triggers the inhibit orders.The radio height is used in the 0 to 2500Ft range.

ADIRU

The IR part ADIRU provides the magnetic heading andthe pitch and roll attitude information to the TCAScomputer.

NOTE:The Baro altitude is transmitted via the ATCtransponder.

TMUTCAF01-T01 LEVEL 3



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TCAS DESCRIPTION/OPERATIONTMUTCAF01-P01 LEVEL 3



UFD4200


TCAS DESCRIPTION/OPERATION

CFDIU

The Centralized Fault Display Interface Unit (CFDIU)allows testing and trouble-shooting of the TCAS throughthe MCDU.The tests are only available on ground.

LGCIU

The Landing Gear Control and Interface Unit (LGCIU)provides a flight ground signal used by the BITE modulefor flight leg counting.It provides also a landing gear extended signal forTCAS operation.

INDICATING

Visual indications are presented on the NDs and PFDs.The NDs present the location of intruders in thetraffic area.The PFDs present the avoidance maneuver indicationson the vertical speed scale.The FWCs monitor the validity of the information.Synthesized voice announcements generated by the TCAScomputer and broadcast by the loudspeakers accompanythe visual indications.

INHIBITION

Various discrete signals are used for inhibition byequipment with higher priority than the TCAS.These priorities are:

- windshear- stall- EGPWS messages

Consequently Traffic Advisory (TA) mode is selectedand the voice announcements are cancelled (MasterWarning P/B switch).

PIN PROGRAMMING

Some pin programs define the operating mode of theTCAS.Operating mode:

- audio level output,- all traffic/threat traffic display,- ground display mode (TA mode),- number of intruders displayed, (8 maximum),- aircraft altitude limit (48000Ft).

DATA LOADER

It will be possible to load software data into theTCAS computer by means of a DATA loader.The remote loading capability is linked by 2 ARINC 429low speed buses to a dedicated connector in theaircraft.

TMUTCAF01-T01 LEVEL 3



UFD4200



TMUTCAF01 LEVEL 3



UFD4200


SELF EXAMINATION

The TCAS/ATC control panel controls:A - ATC transponders and TCAS computer

directly.B - ATC transponders directly and TCAS

computer through the ATC transponders.C - TCAS computer directly and ATC

transponders through the TCAS computer.

The TCAS receives heading, pitch and roll data from:A - ADIRU 1.B - ADIRU 1 or 3 according to AIR DATA

switch status.C - Selected ATC transponder.

TMUTCAF01 LEVEL 3



UFD4200


34 - NAVIGATION

34-43-00 TCAS CONTROL PANEL D/O

CONTENTS:COLLINS Control PanelSEXTANT ControL PanelGABLES Control PanelSelf Examination

TMUTCAH05 LEVEL 2



UFD4200


TCAS CONTROL PANEL D/O

COLLINS CONTROL PANEL

GENERALThe purpose of this module is to understand the useof the various controls of the TCAS part of theTCAS/ATC control panel.

MODE SELECTORThe TCAS mode of operation is selected by means of arotary mode selector.- STBY and XPDR position:The advisory generation and surveillance functions areinhibited.- TA position:This mode provides only traffic advisories, it doesn’tgenerate any resolution advisories.- TA/RA position:This is the normal operating mode, it provides thepreventive and the corrective advisories in order toavoid conflicts with other aircraft.-TFC position:This mode provides all traffic indications of allaircraft in the other, proximate, TA and RA volumes (8 maximum).

ABOVE/N/BELOW SWITCHESThe TCAS surveillance envelope is expanded above orbelow the TCAS equipped aircraft whatever the modeselected (TA-TA/RA-TFC).-ABOVE position:From -2700 ft to +9900 ft.-N (normal position):From -2700 ft to +2700 ft.-BELOW position:From +2700 ft to -9900 ft.

INOP SWITCHESThe functions under INOP placards are reserved for afuture use.

TMUTCAH05-T01 LEVEL 2



UFD4200


TCAS CONTROL PANEL D/O - COLLINSTMUTCAH05-P01 LEVEL 2



UFD4200



SEXTANT CONTROL PANEL

STBY/TA/TA/RA MODE SELECTORThe TCAS mode of operation is selected by means of arotary mode selector.- STBY position:The advisory generation and surveillance functions areinhibited.- TA position:This mode provides only traffic advisories, it doesn’tgenerate any resolution advisories.- TA/RA position:This is the normal operating mode, it provides thepreventive and the corrective advisories in order toavoid conflicts with other aircraft.

THRT/ALL/ABV/BLW MODE SELECTORTwo other types of targets for TCAS traffic can beselected by means of a rotary mode selector.- THRT position:The THRT function (THREAT TRAFFIC), defined asPROXIMATE traffic, is conditioned by the presence ofa TA or RA intruder.- ALL position:The ALL function, defined as OTHER traffic, providesall intruders that do not enter in the proximate, TAand RA categories.

The TCAS surveillance envelope is expanded above orbelow the TCAS equipped aircraft for Traffic Advisory.-ABV position:From -2700 ft to +9900 ft.-BLW position:From +2700 ft to -9900 ft.In normal operation (non selection of ABV or BLW), thevertical surveillance taken into account is between+/- 2700ft.




UFD4200


TCAS CONTROL PANEL D/O - SEXTANTTMUTCAH05-P02 LEVEL 2



UFD4200



GABLES CONTROL PANEL

TCAS MODE SELECTORThe TCAS mode of operation is selected by means of arotary mode selector.-OFF position:TCAS advisory generation and surveillance functionsare inhibited- TA position:The TCAS computer is fully operational but providesonly traffic advisories, it doesn’t generate anyresolution advisories. TA intruders are displayed onthe NDs.- TA/RA position:This is the normal operating mode, it provides thepreventive and the corrective advisories in order toavoid conflicts with other aircraft.




UFD4200


TCAS CONTROL PANEL D/O - GABLESTMUTCAH05-P03 LEVEL 2



UFD4200


SELF EXAMINATION

With mode selector in TA position:A - Only traffic advisories are provided.B - All traffic indications are provided.C - No TCAS information is provided.

TMUTCAH05 LEVEL 2



UFD4200


34 - NAVIGATION

34-43-00 TCAS INDICATIONS ON PFD ANDAURAL ALERTS

CONTENTS:GeneralPreventive Resolution AdvisoryCorrective Resolution AdvisoryAural AlertsV/S FailureTCAS FailureSelf Examination

TMUTCAJ01 LEVEL 2



UFD4200


TCAS INDICATIONS ON PFD AND AURAL ALERTS

GENERAL

The PFD presents indications on the Vertical Speed(V/S) scale, only in case of Resolution Advisories(RA) detection.The indications, given in the form of red or greenpartially colored sectors, advise the crew of theaction necessary to resolve the conflict.

PREVENTIVE RESOLUTION ADVISORY

A preventive resolution advisory informs the crew toavoid certain deviations from current vertical speed.It can be represented by one or two red sectors on theV/S scale.

CORRECTIVE RESOLUTION ADVISORY

A corrective resolution advisory informs the crew toperform a vertical avoidance maneuver.The grey background of the V/S scale is totallyreplaced by red/green sectors.The V/S indications (Digital value and needle) are inthe colour of the corresponding sector.

AURAL ALERTS

Trajectory correction or holding visual orders areaccompanied by synthesized voice announcementsgenerated by the TCAS computer, whose level can beadjusted by the crew.

- PREVENTIVE RESOLUTION ADVISORY

"TRAFFIC, TRAFFIC" (Only in case of TA detection)"MONITOR VERTICAL SPEED, MONITOR VERTICAL SPEED"

- CORRECTIVE RESOLUTION ADVISORY

"CLIMB, CLIMB, CLIMB""CLIMB, CROSSING CLIMB, CLIMB, CROSSING CLIMB""REDUCE CLIMB, REDUCE CLIMB""INCREASE CLIMB, INCREASE CLIMB""CLIMB, CLIMB NOW, CLIMB, CLIMB NOW"

"DESCEND, DESCEND, DESCEND""DESCEND, CROSSING DESCENT, DESCEND, CROSSING DESCENT""REDUCE DESCENT, REDUCE DESCENT""INCREASE DESCENT, INCREASE DESCENT""DESCEND, DESCEND NOW, DESCEND, DESCEND NOW"

- AIRCRAFT SEPARATION HAS BEEN ACHIEVED:

"CLEAR OF CONFLICT"

TMUTCAJ01-T01 LEVEL 2



UFD4200


TCAS INDICATIONS ON PFD AND AURAL ALERTS - PREVENTIVE AND CORRECTIVE ADVISORIESTMUTCAJ01-P01 LEVEL 2



UFD4200


TCAS INDICATIONS ON PFD AND AURAL ALERTS

V/S FAILURE

In case of vertical speed indication failure, a redV/S flag appears.TCAS information, if any, are presented without V/Sindications.

TCAS FAILURE

In case of TCAS failure, a red TCAS flag is displayedwhen the system cannot deliver Resolution Advisories(RA) data.

TMUTCAJ01-T02 LEVEL 2



UFD4200


TCAS INDICATIONS ON PFD AND AURAL ALERTS - FAILURES

TMUTCAJ01-P02 LEVEL 2



UFD4200


SELF EXAMINATION

The PFD presents TCAS indications:A - On the V/S scale in case of TA and RA

detection.B - On the SPEED scale as Preventive

Advisoriy.C - On the V/S scale only in case of RA

detection.

The colour of the V/S indications change to:A - red when in presence of a corrective RA

detectionB - green when a in presence of corrective

RA detectionC - red or green when in presence of a

corrective RA detection depending on thesector band in which they are.

TMUTCAJ01 LEVEL 2



UFD4200


34 - NAVIGATION

34-43-00 TCAS INDICATIONS ON ND

CONTENTSDisplay ConditionsIntruderNo Bearing IntruderMessagesSelf Examination

TMUTCAL01 LEVEL 2



UFD4200


TCAS INDICATIONS ON ND

DISPLAY CONDITIONS

The ND presents traffic indication using differentsymbols corresponding to the type of intrudersThese indications are displayed only in ROSE and ARCmodes, and ONLY in the 10, 20 and 40 NM range.

NOTE: If the PLAN mode is selected, a message informsthe crew to change mode.

INTRUDER

The intruders are displayed with range, bearing,reative altitude and vertical speed tendancy dependingon the setting of the mode selector on the TCAS/ATCcontrol panel.Only the eight most threatening intruders aredisplayed.

TMUTCAL01-T01 LEVEL 2



UFD4200


TCAS INDICATIONS ON ND - INTRUDER TYPETMUTCAL01-P01 LEVEL 2



UFD4200


TCAS INDICATIONS ON ND

NO BEARING INTRUDER

The TCAS can detect an intruder not equipped with TCASwithout acquiring its bearing.Its characteristics are displayed on the lower partof the ND.Only the two most threatening intruders are displayed,the most dangerous is displayed on the left side.

MESSAGES

Different type of messages can be displayed:- Mode and Range messages,- TCAS operations and failure messages.

TMUTCAL01-T02 LEVEL 2



UFD4200


TCAS INDICATIONS ON ND - NO BEARING INTRUDER AND TCAS MESSAGESTMUTCAL01-P02 LEVEL 2



UFD4200


SELF EXAMINATION

A RA is represented on the ND with:A - a red squareB - A red circleC - a white filled diamond shape.

TMUTCAL01 LEVEL 2



UFD4200


34 - NAVIGATION

34-43-00 TCAS COMPONENTS

CONTENTS:TCAS Computer (Collins)TCAS Computer (Honeywell)TCAS Computer (Bendix)TCAS AntennaeTCAS Control Panel (Collins)TCAS Control Panel (Sextant)TCAS Control Panel (Gables)

TMUTCAN05 LEVEL 3



UFD4200


TCAS COMPONENTS

TCAS COMPUTER (COLLINS)

IDENTIFICATIONFIN: 1SG

LOCATIONZONE: 128

COMPONENT DESCRIPTIONThe front face of the computer is fitted with 9 LEDsand a TEST pushbutton.When the TEST pushbutton is pressed in, the 9 LEDscome on.If the test is OK, the LEDs should go off when theTEST pushbutton is released out.The back is fitted with an ARINC 600 electricalconnector.

TMUTCAN05-T01 LEVEL 3



UFD4200


TMUTCAN05-P01 LEVEL 3

TCAS COMPONENTS - COMPUTER (COLLINS)



UFD4200


TCAS COMPONENTS

TCAS COMPUTER (HONEYWELL)


LOCATIONZONE: 128

COMPONENT DESCRIPTIONThe front face of the computer is fitted with 11 LEDsand a TEST pushbutton.When the TEST pushbutton is pressed in, the 11 LEDscome on (lAMP Test first then SELF-TEST).If the test is OK, the LEDs should go off.The TEST can be repeated until a maximun of 10 flightlegs have been displayed.The back is fitted with an ARINC 600 electricalconnector.




UFD4200



TCAS COMPONENTS - COMPUTER (HONEYWELL)



UFD4200


TCAS COMPONENTS

TCAS COMPUTER (BENDIX)


LOCATIONZONE: 128

COMPONENT DESCRIPTIONThe front face of the computer is fitted with a dataloading connector which enables data to be loaded froma portable data loader.The front face is also fitted with a test connector.The back is fitted with an ARINC 600 electricalconnector.




UFD4200



TCAS COMPONENTS - COMPUTERS (BENDIX)



UFD4200


TCAS COMPONENTS

TCAS ANTENNAE

IDENTIFICATIONFIN: 7SG1, 7SG2


COMPONENT DESCRIPTIONThe TCAS directional antennae are composed of fourpassive and independent vertically-polarizedelements.A teflon gasket is located between the fuselage andthe base of the antenna in order to facilitate theremoval of the antenna.




UFD4200


TCAS COMPONENTS - ANTENNAETMUTCAN05-P04 LEVEL 3



UFD4200


TCAS COMPONENTS

TCAS CONTROL PANEL (COLLINS)

IDENTIFICATIONFIN: 3SH

LOCATIONZONE: 211

COMPONENT DESCRIPTIONThe processor of the TCAS/ATC control panel controlsthe ATC and TCAS function via an ARINC 429 bus.




UFD4200


TCAS COMPONENTS - CONTROL PANEL (COLLINS)TMUTCAN05-P05 LEVEL 3



UFD4200


TCAS COMPONENTS

TCAS CONTROL PANEL (SEXTANT)


LOCATIONZONE: 211





UFD4200


TCAS COMPONENTS - CONTROL PANEL (SEXTANT)TMUTCAN05-P06 LEVEL 3



UFD4200


TCAS COMPONENTS

TCAS CONTROL PANEL (BENDIX)


LOCATIONZONE: 211





UFD4200


TCAS COMPONENTS - CONTROL PANEL (BENDIX)TMUTCAN05-P07 LEVEL 3



UFD4200



TMUTCAN05 LEVEL 3



UFD4200


34 - NAVIGATION

34-48-00 ENHANCED GROUND PROXIMITYWARNING SYSTEM PRESENTATION

CONTENTS:GeneralPrincipleComponentsIndicating

TMUEGPA01 LEVEL 1

EFFECTIVITY 34-48-00 Page 1Feb 28/98


UFD4200


ENHANCED GROUND PROXIMITY WARNING SYSTEM PRESENTATION

GENERAL

The Enhanced Ground Proximity Warning System (EGPWS)is built over the current GPWS.

- EGPWS = GPWS + "ENHANCED" functions.

PRINCIPLE

The purpose of the Enhanced Ground Proximity WarningSystem (EGPWS) is to help prevent accidents caused byControlled Flight Into Terrain (CFIT).When boundaries of any alerting envelope are exceeded;aural alert messages, visual annunciations anddisplays are generated.The basic GPWS modes generate aural and visual warningscorresponding to an aircraft behaviour when the alertenvelope is penetrated.The "ENHANCED" features complete the basic GPWS modes:

- Terrain Clearance Floor (TCF): Increase theterrain clearance envelope around the airportrunway.

- Terrain Awareness alerting and Display (TAD):Incorporation of a terrain database to predictconflict between flight path and terrain andto display the conflicting terrain.

TMUEGPA01-T01 LEVEL 1



UFD4200


ENHANCED GROUND PROXIMITY WARNING SYSTEM PRESENTATION - PRINCIPLETMUEGPA01-P01 LEVEL 1



UFD4200



COMPONENTS

The system comprises an EGPWC, a control panel, twowarning lights and two TERRAIN ON ND mode pushbuttonswitches.The EGPWS is connected to various navigation systems(WR, RA, ADIRS, ILS...).It processes the navigation data and generates alarms.




UFD4200


ENHANCED GROUND PROXIMITY WARNING SYSTEM PRESENTATION - COMPONENTS

TMUEGPA01-P02 LEVEL 1



UFD4200



INDICATING

The basic GPWS modes generate visual warnings throughassociated lights and synthetic warnings through theloudspeakers.The "ENHANCED" GPWS functions allow the terrain hazardsto be displayed on the Navigation Display (ND).




UFD4200


ENHANCED GROUND PROXIMITY WARNING SYSTEM PRESENTATION - INDICATINGTMUEGPA01-P03 LEVEL 1



UFD4200



TMUEGPA01 LEVEL 1



UFD4200


34 - NAVIGATION

34-48-00 EGPWS DESCRIPTION/OPERATION

CONTENTS:GeneralDigital InputsDigital OutputsEnhanced FunctionEGPWS ControlsAural WarningsVisual WarningsFWCLGCIUSelf Examination

TMUEGPC01 LEVEL 3



UFD4200


EGPWS DESCRIPTION/OPERATION

GENERAL

The Enhanced Ground Proximity Warning System (EGPWS)consists of:

- 1 computer,- 2 GPWS / G/S pushbutton with integral lights,- 1 GPWS control panel,- 2 TERRAIN ON ND pushbuttons.

DIGITAL INPUTS

The EGPWS receives ARINC 429 data inputs from thenavigation sensors in order to monitor the aircraftposition with respect to the terrain and provide audioand visual warnings when in hazardous situation.

DIGITAL OUTPUTS

An ARINC 429 transmitter provides a maintenance outputdata bus.This output bus is used by the CFDIU for maintenancepurposes and by the Aircraft Integrated Data System(AIDS) for the Data Management Unit (DMU).

ENHANCED FUNCTION

The EGPWC outputs a display of terrain data in ARINC453 data bus format to the DMCs.The terrain data is displayed on the ND automaticallyin place of the radar image when a Terrain Caution orWarning is detected or any time by using the TERR ONND pushbutton.

The EGPWS receives the Predictive Windshear (PWS)alerts from the weather radar hazard bus to determinethe priority. The PWS has priority over EGPWS modes.

EGPWS CONTROLS

Various pushbuttons allow the crew to control theactions of the EGPWS.When pressed in, on the GPWS control panel:

- The TERR p/b (white legend) inhibits theterrain awareness.

- The SYS p/b (white legend) inhibits all theGPWS warnings (mode 1 to 5).

- The G/S MODE p/b (white legend) inhibits theglide/slope mode (mode 5).

- The FLAP MODE p/b (white legend) inhibits flapabnormal condition input (mode 4) and generatesthe green "GPWS FLAP MODE OFF" message on theECAM MEMO page (EWD).

- The LDG FLAP 3 p/b (white legend) selects thelanding FLAP 3 position and generates the green"GPWS FLAP 3" message on the ECAM MEMO page(EWD).

When pressed in the GPWS / G/S p/b, on the instrumentpanels, has two functions:

- The GPWS / G/S p/b sends a ground signal totrigger the self test sequence (available onground or above 2000 ft Above Ground Level:AGL),

- or cancels the glide/slope aural and visualwarnings when triggered.

When the TERRAIN ON ND p/b is pressed in, on the centerinstrument panel, the green ON legend comes on toindicate that terrain data is displayed on the ND.

TMUEGPC01-T01 LEVEL 3



UFD4200


EGPWS DESCRIPTION/OPERATIONTMUEGPC01-P01 LEVEL 3



UFD4200


EGPWS DESCRIPTION/OPERATION

AURAL WARNINGS

The audio output is used to broadcast aural warningmessages which identify the activated mode.The ECAM control panel sends an audio suppressionsignal, when the EMERG CANCEL p/b is pressed, to theEGPWC in order to momentarily cancel the EGPWSwarnings.

VISUAL WARNINGS

In hazardous flight configurations or system failuresthe EGPWC provides discretes for the illumination ofwarning legends.Five discretes control the warning legends:

- One for red GPWS legends, for ground proximitywarning (mode 1 to 4) and for Terrain Cautionand Warning Alert.

- One for amber G/S legends, for Glide/Slopeadvisory alert (mode 5).

- Two monitor outputs for the amber FAULT legendson the SYS and TERR p/b of the GPWS controlpanel.These discretes are also sent to the SystemData Acquisition Concentrators (SDACs) togenerate the ECAM "GPWS FAULT" and "GPWS TERRDET FAULT" warning messages.

- One monitor output for the availability of theterrain mode.In case of FMS low accuracy agreen TERR STBY is sent through the SDACs tothe ECAM MEMO page (EWD).

FWC

The Flight Warning Computers (FWCs) send a discreteto the EGPWC to inhibit all warnings when a stall orwindshear warning is triggered.The EGPWC sends two discretes to the FWCs and the TCASin order to inhibit auto call out and low speed warningsand change TCAS mode from Resolution Advisory (RA) toTraffic Advisory (TA) when the GPWS or G/S warningsare in progress.These discretes are also used by the Digital FlightData Recorder (DFDR).

LGCIU

The Landing Gear Control Interface Unit sends aflight/ground discrete signal to the EGPWC BITE modeto count the flight legs.This discrete is also used for Mode 4 (Unsafe TerrainClearance).




UFD4200


SELF EXAMINATION

What happens to the EGPWS when the stall warning istriggered?

A - All modes are inhibited.B - Mode 4 is inhibited.C - Mode 5 is inhibited.

What happens when the G/S p/b is pressed in on theGPWS control panel?

A - The Glide/Slope mode is inhibited.B - Only Glide/Slope mode is valid.C - The self test sequence is initiated.

What happens when the TERR ON ND p/b is pressed in?A - The ND displays the terrain image.B - The terrain image is superposed with the

radar image on the ND.C - The radar image is present until a

terrain caution or warning is detected.

The EGPWS has priority over:A - All systems.B - Auto call out, low speed warning and

TCAS.C - Stall and windshear.




UFD4200



TMUEGPC01 LEVEL 3



UFD4200


34 - NAVIGATION

34-48-00 EGPWS MODES

CONTENTS:GeneralWarning ModesMode 1Mode 2Mode 3Mode 4Mode 5Terrain Awareness And Display (TAD)(JAA & FAA)Terrain Clearance Floor (TCF)Self Examination

TMUEGPE01 LEVEL 3

EFFECTIVITY 34-48-00 Page 1Aug 31/98


UFD4200


EGPWS MODES

GENERAL

The Enhanced Ground Proximity Warning System (EGPWS)computes and compares the aircraft behaviour with apredermined envelope.

WARNING MODES

When the warning envelope is penetrated, visual andaural warnings are generated.The aural messages are broadcast through the cockpitloudspeakers and visual warnings are indicated by theGPWS / G/S pushbutton lights and the GPWS controlpanel.A terrain image is displayed on the ND.

NOTE: A number of airports through the world haveapproaches or departures which are not entirelycompatible with the standard GPWS operation.These airports are identified in the data base,the GPWS recognizes them and modifies the profileand triggers the warning in accordance.

TMUEGPE01-T01 LEVEL 3



UFD4200


EGPWS MODES - WARNING MODESTMUEGPE01-P01 LEVEL 3



UFD4200


EGPWS MODES

MODE 1

Mode 1 provides an alert warning for high descent ratesinto terrain and for rapidly increasing sink ratesnear the runway when landing.The SINK RATE voice message changes into PULL UP whenthe aircraft reaches the inner boundary.These alerts will continue until the boundarypenetration is corrected.




UFD4200


TMUEGPE01-P02 LEVEL 3

EGPWS MODES - MODE 1



UFD4200


EGPWS MODES

MODE 2

Mode 2 provides a warning based on the radio heightand on how rapidly the radio height decreases.

Mode 2A: Landing flaps not down and not in the glideslope beam (TERRAIN, TERRAIN).

Mode 2B: Landing flaps down or in the glide slope beamwithin +/- 2 dots of deviation (ILS approach) (PULLUP).

When in landing configuration the voice message willonly be "TERRAIN" until the barometric altitudeincreases by 300 ft.




UFD4200


EGPWS MODES - MODE 2TMUEGPE01-P03 LEVEL 3



UFD4200


EGPWS MODES

MODE 3

Mode 3 provides a warning for excessive altitude lossafter take-off, climb or during a go-around (DON’TSINK).This mode is based on radio height, altitude (inertial,barometric or computed altitude) and altitude rate(IVS computed altitude rate or barometric altituderate).




UFD4200





UFD4200


EGPWS MODES

MODE 4

Mode 4 generates warnings based on the radio height,computed airspeed and aircraft configuration.TOO LOW TERRAIN is broadcast when the aircraft is below1000 ft with landing gear retracted and/or flaps notin landing configuration.TOO LOW GEAR or TOO LOW FLAPS are broadcast dependingon the aircraft configuration (gear up or down, flapsextended or retracted, aircraft speed in relation tothe radio height).

NOTE: The TOO LOW GEAR message has priority over theTOO LOW FLAPS message.




UFD4200





UFD4200


EGPWS MODES

MODE 5

Mode 5 provides warnings when the aircraft flight pathdescends below the Glide/Slope beam during ILSapproaches.The amplitude of the GLIDE SLOPE voice message and therepetition rate are increased when closing to theground.




UFD4200


EGPWS MODES - MODE 5

TMUEGPE01-P06 LEVEL 3



UFD4200


EGPWS MODES

TERRAIN AWARENESS AND DISPLAY (TAD)(JAA & FAA)

When a terrain threat forward of the aircraft path isdetected, with respect to the aircraft position andthe local terrain database, caution and warning alertsare triggered.When the envelope boundaries are met the followingalerts are generated:

- Terrain Caution Alert: "TERRAIN AHEAD" isbroadcast (JAA).

- Terrain Caution Alert: "CAUTION TERRAIN,CAUTION TERRAIN" is broadcast (FAA).

- Terrain Warning Alert: "TERRAIN AHEAD, PULLUP" is broadcast (JAA).

- Terrain Warning Alert: "TERRAIN, TERRAIN, PULLUP" is broadcast (FAA).

These alerts are completed by a terrain image on theNDs:

- Red area for warnings.- Yellow area for cautions.




UFD4200


EGPWS MODES - TADTMUEGPE01-P07 LEVEL 3



UFD4200


EGPWS MODES

TERRAIN CLEARANCE FLOOR (TCF)

The Terrain Clearance Floor is an increasing terrainclearance enveloppe around the airport runway toprovide protection against Controlled Flight IntoTerrain (CFIT).The TCF alert function complements the existing Mode4. When TCF alert envelope is penetrated "TOO LOWTERRAIN" is broadcast.It is based on current A/C position, nearest runwaycenter point position and Radio Altitude.




UFD4200


EGPWS MODES - TCFTMUEGPE01-P08 LEVEL 3



UFD4200


SELF EXAMINATION

If the voice message "TERRAIN, TERRAIN" is heard,in which mode and configuration are you?

A - In mode 2A, with flaps down or in theglide slope beam.

B - In mode 2B, with flaps down or in theglide slope beam.

C - In mode 2A, with flaps not down and notin the glide slope beam.

Which synthetic voice is broadcast in case of anexcessive rate of descent?

A - SINK RATE.B - TERRAIN TERRAIN.C - GLIDE SLOPE.

TMUEGPE01 LEVEL 3



UFD4200


34 - NAVIGATION

34-48-00 EGPWS INDICATIONS ON ND

CONTENTS:GeneralBackground DisplayTerrain Caution AlertTerrain Warning AlertSelf Examination

TMUEGPG01 LEVEL 2



UFD4200


EGPWS INDICATIONS ON ND

GENERAL

The Terrain Awareness alerting and Display (TAD)function displays the background terrain and terrainalerts, forward of the aircraft, in the ROSE and ARCmode navigation displays.

BACKGROUND DISPLAY

The background terrain display is depicted as variabledensity dot patterns in green, yellow or red dependingon how close the terrain is relative to aircraftaltitude.

NOTE: Terrain is not shown if more than 2000 feet belowthe reference altitude and if the terrainelevation is within 400 ft of the runwayelevation nearest the aircraft.

TMUEGPG01-T01 LEVEL 2



UFD4200


EGPWS INDICATIONS ON ND - BACKGROUND DISPLAYTMUEGPG01-P01 LEVEL 2



UFD4200


EGPWS INDICATIONS ON ND

TERRAIN CAUTION ALERT

When the conditions of terrain caution alerts are met,the background image is enhanced to highlight theterrain caution threats by coloring them in solidyellow.

TERRAIN WARNING ALERT

When the conditions of terrain warning alerts are met,the background image is enhanced to highlight theterrain warning threats by coloring them in solid red(caution threats are also available).

TMUEGPG01-T02 LEVEL 2



UFD4200


EGPWS INDICATIONS ON ND - TERRAIN CAUTION AND WARNING ALERTS

TMUEGPG01-P02 LEVEL 2



UFD4200


SELF EXAMINATION

A yellow high density indication means that:A - An unknown terrain is being overflown.B - Terrain is between 1000 ft and 2000 ft

above A/C altitude.C - There is no close terrain.

When a Terrain Warning Alert is triggered:A - The red GPWS warning comes on with

"TERRAIN ALERT" alert caution.B - "TERRAIN ALERT, PULL UP" alert warning

is heard continuously associated with ared GPWS warning and the red "TERRAHEAD" message on ND.

C - the amber G/S warning comes on with acyan "TERR" message on ND.

TMUEGPG01 LEVEL 2



UFD4200


34 - NAVIGATION

34-48-00 EGPWS COMPONENTS

CONTENTS:EGPWC

TMUEGPJ01 LEVEL 3



UFD4200


EGPWS COMPONENTS

EGPWC

IDENTIFICATIONFIN: 1WZ

LOCATIONZONE: 128

COMPONENT DESCRIPTIONBehind the latched door, the computer is fitted with:

- a self test switch- a headphone jack- an RS232 test connector for a CRT or a PC- a PCMCIA interface for uploading or downloadinginternal EGPWC information.

The back is fitted with an ARINC 600 connector.

TMUEGPJ01-T01 LEVEL 3



UFD4200


EGPWS COMPONENTS - COMPUTERTMUEGPJ01-P01 LEVEL 3



UFD4200



TMUEGPJ01 LEVEL 3



UFD4200


34 - NAVIGATION

34-51-00 DME SYSTEM PRESENTATION


TMUDMEH01 LEVEL 1



UFD4200


DME SYSTEM PRESENTATION

PRINCIPLE

The Distance Measuring Equipment (DME) providesdigital readout of the aircraft slant range distancefrom a selected ground station.The system generates interrogation pulses from anonboard interrogator and sends them to a selectedground station.After a 50 micro seconds delay, the ground stationreplies.The interrogator determines the distance in NauticalMiles (NM) between the station and the aircraft.The interrogator detects the Morse audio signal whichidentifies the ground station.

TMUDMEH01-T01 LEVEL 1



UFD4200


DME SYSTEM PRESENTATION - PRINCIPLETMUDMEH01-P01 LEVEL 1



UFD4200



COMPONENTS

The components are two antennae and two interrogators.The DME system is also connected to:

- Primary Flight Displays (PFD), NavigationDisplays (ND) and Digital Distance RadioMagnetic Indicator (DDRMI) for display.

- Electronic Flight Instrument System (EFIS)control unit for display control.

- Flight Management and Guidance Computers (FMGC)for tuning (manual and auto).

- Captain and F/O Radio Management Panels (RMP)for back-up tuning.

- Audio Control Panels (ACPs) for DME audiosignal.




UFD4200


DME SYSTEM PRESENTATION - COMPONENTSTMUDMEH01-P02 LEVEL 1



UFD4200



INDICATING

The DME distance is shown on the Primary Flight Display(PFD) (if ILS/DME) and on the Navigation Display (ND)(if VOR/DME).The DME distance is also shown on the two windows ofthe Digital Distance Radio Magnetic Indicator (DDRMI).




UFD4200


DME SYSTEM PRESENTATION - INDICATINGTMUDMEH01-P03 LEVEL 1



UFD4200



TMUDMEH01 LEVEL 1



UFD4200


34 - NAVIGATION

34-51-00 DME DESCRIPTION/OPERATION

CONTENTS:GeneralAuto TuningManual TuningBack Up TuningAntennaUsersSuppressorAMULGCIUIndicatingCFDIUSelf Examination

TMUDMEA01 LEVEL 3



UFD4200


DME DESCRIPTION/OPERATION

GENERAL

The Distance Measuring Equipment (DME) Sytem includes:- 2 DME Interrogators,- 2 DME Antennae.

AUTO TUNING

In normal operation each Flight Management GuidanceComputer (FMGC) automatically tunes its ownside DMEinterrogator through its ownside Radio ManagementPanel (RMP) via port A.When the FMGC fails, the DME receives a discrete signalthrough the RMP to automatically select port B.With failure of one FMGC the other FMGC can controlthe DME interrogators, one directly, the other throughits RMP.

MANUAL TUNING

From each Multipurpose Control and Display Unit (MCDU)both DMEs can be manually tuned through their ownsideFMGC (via port A).

BACK UP TUNING

In case of dual FMGC failure the RMPs enable BACK-UPtuning.

ANTENNA

The DME antenna transmits the DME interrogation andreceives the reply from the selected ground station.The DME antenna operates within the low band from 962to 1213 Mhz (1025 to 1150 Mhz for interrogation and962 to 1213 Mhz for reply).

USERS

The DME data is sent to the FMGCs for radio distancecomputation.

SUPPRESSOR

The DME and the Air Traffic Control (ATC) operate inthe same frequency range.A suppressor coaxial between the ATC transponders andDME interrogators is necessary to prevent simultaneoustransmission and to interrupt reception of the othersystems.

AMU

The DME audio signals are transmitted to the AudioManagement Unit (AMU) and then dispatched to theheadsets and/or loudspeakers.The pilot can adjust the volume of the DME groundstation by pressing the VOR pushbutton on the AudioControl Panel (ACP) or the ILS pushbutton in case ofcollocated ILS/DME (if ILS mode is selected on EFISCTL Panel).

TMUDMEA01-T01 LEVEL 3



UFD4200


DME DESCRIPTION/OPERATIONTMUDMEA01-P01 LEVEL 3



UFD4200


DME DESCRIPTION/OPERATION

LGCIU

Each Landing Gear Control Interface Unit (LGCIU) sendsa discrete signal to the associated DME interrogator.This is a Ground/Flight information used by thereceiver BITE module to count the flight legs.

INDICATING

DME data is sent to the Navigation Displays (NDs) andthe Primary Flight Displays (PFDs) through the DisplayManagement Computers (DMCs) and directly to the DigitalDistance and Radio Magnetic Indicator (DDRMI).

CFDIU

The MCDUs allow the systems to be tested and troubleshooting to be performed via the Centralized FaultDisplay Interface Unit (CFDIU).The tests are only available on ground.

TMUDMEA01-T01 LEVEL 3



UFD4200



TMUDMEA01 LEVEL 3



UFD4200


SELF EXAMINATION

What is the suppressor coaxial between DME and ATCused for ?

A - To inhibit DME operation.B - To prevent simultaneous transmission and

to interrupt reception of the othersystems.

C - To prevent simultaneous transmission andto inhibit the transmission of the othersystems.

Where is the DME 1 information displayed ?A - On CAPT PFD and F/O PFD.B - On CAPT PFD, CAPT and F/O ND and DDRMI.C - On CAPT F/O PFD and ND.

TMUDMEA01 LEVEL 3



UFD4200


34 - NAVIGATION

34-51-00 DME INDICATIONS ON PFD AND ND

CONTENTS:On PFDOn NDVOR-D PusbuttonFailureSelf Examination

TMUDMEB01 LEVEL 2



UFD4200


DME INDICATIONS ON PFD AND ND

ON PFD

When an Instrument Landing System (ILS) station iscollocated with a Distance Measuring Equipment (DME)station, the ILS/DME distance is displayed in magentain the left lower corner of the Primary Flight Display(PFD).This data comes into view when the ILS P/B on the EFIScontrol panel is pressed in.

ON ND

When the mode selector on the EFIS control panel, isset to ROSE or ARC mode and the ADF/VOR selector isset to VOR the DME distance is displayed in green inthe left or right lower corner of the NavigationDisplay (ND).Nothing is displayed if non collocated VOR/DME groundstation.

TMUDMEB01-T01 LEVEL 2



UFD4200


DME INDICATIONS ON PFD AND ND (SHEET 1/2)TMUDMEB01-P01 LEVEL 2



UFD4200


DME INDICATIONS ON PFD AND ND

VOR-D PUSHBUTTON

In ROSE-NAV and ARC mode it is possible to show theDME and VOR/DME ground stations which are included inthe navigation data base.If not tuned nor included in the flight plan the DMEor VOR/DME ground stations are displayed in magentawhen the VOR-D pushbutton is pressed in on the EFIScontrol panel.

FAILURE

When a failure occurs, the corresponding red DME flagis displayed in place of the distance, in the lowercorner of the corresponding side for the ND and in theleft lower corner for the PFD.

TMUDMEB01-T02 LEVEL 2



UFD4200


DME INDICATIONS ON PFD AND ND (SHEET 2/2)TMUDMEB01-P02 LEVEL 2



UFD4200


SELF EXAMINATION

What does it mean when dashes are displayed insteadof DME1 distance indication on the ND ?

A - DME1 interrogator has failed.B - DME1 interrogator is not receiving the

ground station signal.C - There is no DME station collocated to

the VOR station selected.

When the VOR-D pushbutton is pressed in, on theEFIS control panel,the ND shows:

A - The DME and the VOR/DME ground stationsincluded in the data base.

B - Only the VOR/DME ground stations.C - The DME and the VOR/DME ground stations

included in the flight plan.

TMUDMEB01 LEVEL 2



UFD4200


34 - NAVIGATION

34-51-00 DME COMPONENTS

CONTENTS:DME Interrogators (Collins)DME Interrogators (Allied)DME Interrogators (Thomson)DME Antennae

TMUDMEF04 LEVEL 3



UFD4200


DME COMPONENTS

DME INTERROGATORS (COLLINS)

IDENTIFICATIONFIN: 2SD1, 2SD2

LOCATIONZONE: 127,128

COMPONENT DESCRIPTIONThe front face of the interrogator is fitted with 2LEDs and a TEST pushbutton.When the TEST pushbutton is pressed in, the functionaltest starts.At the end of the test, the color of the LEDs indicatesthe status of the LRU.

- CONTROL FAIL LED red: test not completed.- LRU STATUS LED red: fault detected during test.- LRU STATUS LED green: no fault detected duringtest.


TMUDMEF04-T01 LEVEL 3



UFD4200


DME COMPONENTS - INTERROGATORS (COLLINS)TMUDMEF04-P01 LEVEL 3



UFD4200


DME INTERROGATORS (ALLIED)



COMPONENT DESCRIPTIONThe face of the interrogator is fitted with twopushbutton switches and a Liquid Cristal Display (LCD).The LCD provides user interfaces for test, faultdisplay and troubleshooting.The front face is also fitted with an RS-232 connectorfor interfacing with personal computers.The back is fitted with an ARINC 600 connector.




UFD4200


DME COMPONENTS - INTERROGATORS (ALLIED)TMUDMEF04-P02 LEVEL 3



UFD4200


DME INTERROGATORS (THOMSON)



COMPONENT DESCRIPTIONThe face of the interrogator is fitted with a TESTpushbutton switch and six LEDs.

- R/T OK (green): DME OK.- R/T FAIL (red): DME faulty.- BUS IN FAIL (amber): invalid input.- ANT FAIL (amber): antenna faulty.- IND No 1 FAIL: indicator No 1 faulty.- IND No 2 FAIL: indicator No 2 faulty.





UFD4200


DME COMPONENTS - INTERROGATORS (THOMSON)TMUDMEF04-P03 LEVEL 3



UFD4200


DME COMPONENTS

DME ANTENNAE



COMPONENT DESCRIPTIONThe DME antenna is of the blade type with a radiatingcavity driven by capacitance coupling.It is vertically polarized and has an impedance of 50ohms.DME and ATC antennae are interchangeable.




UFD4200


DME COMPONENTS - ANTENNAETMUDMEF04-P04 LEVEL 3



UFD4200



TMUDMEF04 LEVEL 3



UFD4200


34 - NAVIGATION

34-52-00 ATC SYSTEM PRESENTATION

CONTENTS:PrincipleComponents

TMUATCF08 LEVEL 1



UFD4200


ATC SYSTEM PRESENTATION

PRINCIPLE

The Air Traffic Control (ATC) transponder is anintegral part of the Air Traffic Control Radar BeaconSystem (ATCRBS).The transponder is interrogated by radar pulsesreceived from the ground station.It automatically replies by a series of pulses.These reply pulses are coded to supply identification(Mode A) and automatic altitude reporting (Mode C) ofthe aircraft on the ground controller’s radar scope.These replies enable the controller to distinguish theaircraft and to maintain effective ground surveillanceof the air traffic.The ATC transponder also responds to interrogationsfrom aircraft equipped with a Traffic CollisionAvoidance System (TCAS) (Mode S).

TMUATCF08-T01 LEVEL 1



UFD4200


ATC SYSTEM PRESENTATION - PRINCIPLETMUATCF08-P01 LEVEL 1



UFD4200


ATC SYSTEM PRESENTATION

COMPONENTS

The components are two transponders, four antennae,and one ATC/TCAS control panel.Note: The TCAS/ATC control panels shown here after are

given as examples. They may differ according tothe aircraft configuration.

TMUATCF08-T02 LEVEL 1



UFD4200


ATC SYSTEM PRESENTATION - COMPONENTSTMUATCF08-P02 LEVEL 1



UFD4200



TMUATCF08 LEVEL 1



UFD4200


34 - NAVIGATION

34-52-00 ATC DESCRIPTION/OPERATION

CONTENTS:GeneralControl PanelTransponderAntennaeSuppressorADIRUFMGCCFDIUTCASSelf Examination

TMUATCA04 LEVEL 3



UFD4200


ATC DESCRIPTION/OPERATION

GENERAL

The Air Traffic Control (ATC) system includes:- 1 control panel (common to both systems andTCAS),

- 2 transponders,- 4 antennae.

CONTROL UNIT

A single ATC/TCAS control panel enables systemselection. It provides the selected transponder withcode and function data and,in return, receives statusdata.The ATC control panel converts selected mode andselected code data into digital data and transmitsthis data in ARINC 429 format to the selectedtransponder.The Landing Gear Control and Interface Units (LGCIUs)provide a ground/flight signal to the ATC transpondervia the ATC control panel for BITE purposes.

TRANSPONDER

In normal operation, one ATC transponder operates andthe other is in standby mode.The operating mode (A, C or S) of the transponder isdetermined by the decoding of the time between theinterrogation pulses.The main function of the mode S transponder issurveillance. Each transponder has its own and uniqueaddress coded on 24 bits so that every interrogationcan be directed to a specific aircraft preventingmultiple replies.

The mode S is also used in collision avoidance (TCAS).

ANTENNAE

The ATC antennae transmit replies to interrogationsfrom the ATC ground station. Top and bottom antennaeprovide the antenna diversity features that allow abetter radar coverage.The antenna operates in the 960 MHz to 1220 MHzfrequency band with an interrogation frequency of1030 MHz and a reply frequency of 1090 MHz.

SUPPRESSOR

The ATC, the DME and the TCAS operate in the samefrequency range. A suppressor signal is transmitted,via a coaxial, by the operating system to inhibit theother systems and to prevent simultaneoustransmission.

ADIRU

ADIRU 1 and ADIRU 2 provide barometric altitude toassociated transponders for mode C.In case of failure of ADIRU 1 or 2, the pilot canswitch to ADIRU 3 through the AIR DATA selector switch.

FMGC

The Flight Management and Guidance Computers (FMGCs)provide the flight number.This data will be transmitted to an ATC ground stationafter a mode S interrogation.

TMUATCA04-T01 LEVEL 3



UFD4200


TMUATCA04-P01 LEVEL 3




UFD4200



CFDIU

The Centralized Fault Display Interface Unit (CFDIU)allows testing and trouble-shooting of the ATC systemthrough the Multipurpose Control and Display Units(MCDUs).The tests are only available on ground.

TCAS

The Traffic Collision Avoidance System (TCAS) allowsindividual communications with each TCAS equippedaircraft through the Mode S transponder.This enables a coordination of avoidance manoeuversby acquisation, at regular intervals, of the relativealtitude and the separation range.

TMUATCA04-T01 LEVEL 3



UFD4200



TMUATCA04 LEVEL 3



UFD4200


SELF EXAMINATION

The ATC transponders and DME transponders are:A - Connected by ARINC buses to exchange

distance data.B - Connected by a suppressor coaxial which

transmits an analog signal preventingsimultaneous transmission.

C - Not connected.

If ADIRU 2 fails, is the ATC 2 transponder stillable to operate in altitude reporting mode?

A - Yes, because altitude data isautomatically received from ADIRU 3.

B - Yes, because altitude data will berecovered after manual switching of theAIR DATA selection to ADIRU 3.

C - No, ATC 2 will be definitively lost.

TMUATCA04 LEVEL 3



UFD4200


34 - NAVIGATION

34-52-00 ATC CONTROL PANEL D/O

CONTENTS:COLLINS Control PanelSEXTANT Control PanelGABLES Control Panel

TMUNAV308 LEVEL 2



UFD4200


ATC CONTROL PANEL D/O

COLLINS CONTROL PANEL

GENERALThe purpose of this module is to understand the useof the various controls of the common ATC/TCAS controlpanel.

MODE SELECTORThe mode selector enables the ATC transponder operationmode to be selected.- STBY position :No transmission and the answers of the two transpondersare inhibited (electrically supplied but notoperating).- XPDR position :The answers are transmitted on ground and in flightby the selected transponder.- TA-TA/RA-TFC positions :Enables the selection of the TCAS modes.

NOTE: In STBY or XPDR position the TCAS advisorygeneration and surveillance functions areinhibited.

SELECTOR KNOBThe selector knob enables the selection of the ATCtransmission code.The code range is 0000 to 7777.

CODE DISPLAY WINDOWThe liquid crystal display window shows the selectedATC identification code.

There are specific ranges for emergency codes on ModeA, as for example :- 7700 to 7777 for emergency configuration,- 7600 for total failure of radio communication system.

ATC FAIL LIGHTThis FAULT light comes on in case of failure of theselected transponder.The ATC FAIL light also comes on during a functionalor a lamp test.

NOTE: In case of ATC control panel failure, thetransponder continues to transmit the lastdisplayed code.

IDENT PUSHBUTTONWhen the IDENT pushbutton is pressed in, an additionalidentification pulse is generated in mode A and modeC replies.This is to obtain a more precise location of theaircraft.

1/2 SELECTORThis switch enables the selection of the desired activeATC system.When transponder 1 is active, transponder 2 is instandby.

ABOVE/BELOW SWITCHESUsed when TCAS system is installed.




UFD4200


ATC CONTROL PANEL D/O - COLLINSTMUNAV308-P01 LEVEL 2



UFD4200



SEXTANT CONTROL PANEL

GENERALThe purpose of this module is to understand the useof the various controls of the common ATC/TCAS controlunit.

STBY/AUTO/ON SELECTORThis selector enables the ATC transponder operationmode to be selected.- STBY position:Transmission and answers to ground station or otheraircraft are inhibited (electrically supplied but notoperating).- AUTO POSITION:In this mode, the transponder only operates in flightexcept for mode S which also operates on ground.- ON POSITION:In this position, the transponder operates in flightand on ground.

1/2 SELECTORThis selector enables the selection of the desiredactive ATC system.When transponder 1 is active, transponder 2 is instandby.

ALT RPTG SELECTORThe ALT RPTG selector, when in ON position, enablesthe altitude transmission for the ATC mode C.Selection of the OFF position suppresses the altitudeinformation transmission. The altitude is provided byADIRU1 ( For ATC1) or 2 (For ATC2) or ADIRU3 in caseof failure of ADIRU1 or 2.

ATC FAIL LIGHTThis FAULT light comes on in case of failure of theselected transponder.The ATC FAIL light also comes on during a functionalor a lamp test.

NOTE: In case of ATC control unit failure, thetransponder continues to transmit the lastdisplayed code.

KEYBOARDThe keyboard enables the selection of the ATCtransmission code.When pressed in, the CLR key clears the code displayand, when pressed twice, restores the previous codeby the active code.The code range is from 0000 to 7777.




UFD4200


ATC CONTROL PANEL D/O - SEXTANTTMUNAV308-P02 LEVEL 2



UFD4200



GABLES CONTROL PANEL

GENERALThe purpose of this module is to understand the useof the various controls of the common ATC/TCAS controlpanel.

1/2 SELECTORThis switch enables the selection of the desired activeATC system.When transponder 1 is active, transponder 2 is instandby.

XPNDR FAULT LIGHTThis FAULT light comes on in case of failure of theselected transponder.The XPNDR FAULT light also comes on during a functionalor a lamp test.

NOTE: In case of ATC control panel failure, thetransponder continues to transmit the lastdisplayed code.

KEYBOARDThe keyboard enables the selection of the ATCtransmission code.When pressed in, the CLR key clears the code displayand, when pressed twice restores the previous code bythe active code.The code range is 0000 to 7777.

CODE DISPLAY WINDOWThe liquid crystal display window shows the selectedATC identification code and the system in use.There are specific ranges for emergency codes on modeA, as for example :- 7700 to 7777 for emergency configuration.- 7600 for total failure of radio communication system.Fault indications can also be displayed.

IDENT PUSHBUTTONWhen the IDENT pushbutton is pressed in, an additionalidentification pulse is generated in mode A and modeC replies.This is to obtain a more precise location of theaircraft.

STBY/AUTO/ON MODE SELECTORA mode selector switch enables the ATC transponderoperation mode to be selected.- STBY position :No transmission and the answers of the two transpondersare inhibited (electrically supplied but notoperating).- AUTO position :The answers are transmitted only when the aircraft isin flight.- ON position :The answers are transmitted on ground and in flight.

OFF-TA-TA/RA MODE SELECTORUsed when TCAS system is installed.




UFD4200


ATC CONTROL PANEL D/O - GABLESTMUNAV308-P03 LEVEL 2



UFD4200



TMUNAV308 LEVEL 2



UFD4200


34 - NAVIGATION

34-52-00 ATC COMPONENTS

CONTENTS:ATC Transponders (Collins)ATC Transponders (Honeywell)ATC AntennaeATC Control Panel (Collins)ATC Control Panel (Sextant)ATC Control Panel (Gables)

TMUATCD0J LEVEL 3



UFD4200


ATC COMPONENTS

ATC TRANSPONDERS (COLLINS)

IDENTIFICATIONFIN: 1SH1, 1SH2


COMPONENT DESCRIPTIONThe front face of the transponder is fitted with 5LEDs and a TEST pushbutton.When the TEST pushbutton is pressed in, the 5 LEDscome on.If the test is OK, the LEDs should go off when theTEST pushbutton is released out.The back is fitted with an ARINC 600 electricalconnector.

TMUATCD0J-T01 LEVEL 3



UFD4200


ATC COMPONENTS - TRANSPONDERS (COLLINS)TMUATCD0J-P01 LEVEL 3



UFD4200


ATC COMPONENTS

ATC TRANSPONDERS (HONEYWELL)

IDENTIFICATIONFIN: 1SH1, 1SH2


COMPONENT DESCRIPTIONThe front face of the transponder is fitted with 6LEDs, a PUSH TO TEST pushbutton switch and a DATALOADER plug.When the PUSH TO TEST pushbutton is pressed in, the 6LEDs come on for approximately three seconds.After three others seconds, the XPDR PASS LED comeson green if the test is successfuly passed.The back is fitted with an ARINC 600 electricalconnector.




UFD4200


TMUATCD0J-P02 LEVEL 3

ATC COMPONENTS - TRANSPONDERS (HONEYWELL)



UFD4200


ATC COMPONENTS

ATC ANTENNAE

IDENTIFICATIONFIN: 7SH1, 7SH2, 7SH3, 7SH4

LOCATIONZONE: 127,128,223,224

COMPONENT DESCRIPTIONThe ATC antenna is of the blade type with a radiatingcavity driven by capacitance coupling.It is vertically polarized and has an impedance of 50ohms.ATC and DME antennae are interchangeable.




UFD4200


TMUATCD0J-P03 LEVEL 3

ATC COMPONENTS - ANTENNAE



UFD4200


ATC COMPONENTS

ATC CONTROL PANEL (COLLINS)


LOCATIONZONE: 211

COMPONENT DESCRIPTIONThe control panel is composed of two independentmodules, each dedicated to one transponder.A monitoring function checks that the transmitted datacorresponds to the displayed data.




UFD4200


ATC COMPONENTS - CONTROL PANEL (COLLINS)TMUATCD0J-P04 LEVEL 3



UFD4200


ATC COMPONENTS

ATC CONTROL PANEL (SEXTANT)


LOCATIONZONE: 211





UFD4200


ATC COMPONENTS - CONTROL PANEL (SEXTANT)TMUATCD0J-P05 LEVEL 3



UFD4200


ATC COMPONENTS

ATC CONTROL PANEL


LOCATIONZONE: 211





UFD4200


ATC COMPONENTS - CONTROL PANEL (GABLES)TMUATCD0J-P06 LEVEL 3



UFD4200



TMUATCD0J LEVEL 3



UFD4200


34 - NAVIGATION

34-53-00 ADF SYSTEM PRESENTATION


TMUADFF01 LEVEL 1



UFD4200


ADF SYSTEM PRESENTATION

PRINCIPLE

The Automatic Direction Finder (ADF) is a radionavigation aid.The ADF system provides:

- An identification of the relative bearing toa selected ground station called NonDirectional Beacon (NDB).

- Aural identification of the ground station.The relative bearing is the angle between the aircraftheading and the aircraft/ground station axis.

TMUADFF01-T01 LEVEL 1



UFD4200


ADF SYSTEM PRESENTATION - PRINCIPLETMUADFF01-P01 LEVEL 1



UFD4200



The combination of signals, received from two loopantennae and from one omni-directional sense antenna,provides bearing information.The ground stations operate in a frequency range of190 to 1750 Khz.An additional Morse signal is provided to identify theselected ground station.




UFD4200


TMUADFF01-P02 LEVEL 1

ADF SYSTEM PRESENTATION - PRINCIPLE



UFD4200



COMPONENTS

The Automatic Direction Finder system is composed oftwo receivers and two antennae.

The ADF system is also connected to:- Navigation Displays (ND) and Digital DistanceRadio Magnetic Indicator (DDRMI) for display.

- Electronic Flight Instrument System (EFIS)panels for control display.

- Flight Management and Guidance Computer (FMGC)for auto-tuning.

- Multipurpose Control Display Units (MCDU) formanual tuning.

- Captain and First Officer Radio ManagementPanels (RMP) for back-up tuning.

- Audio Control Panels (ACP) for ADF audiosignal.

Note: ADF 2 system is optional.




UFD4200


ADF SYSTEM PRESENTATION - COMPONENTSTMUADFF01-P03 LEVEL 1



UFD4200



INDICATING

The Automatic Direction Finder (ADF) systeminformation can be displayed on the Navigation Displays(ND) system and on the Digital Distance Radio MagneticIndicator (DDRMI).On the NDs, depending on the position of the ADFselector switch on the EFIS control panel:

- ADF 1 is represented by a single pointer- ADF 2 is represented by a double pointer.

On the DDRMI, depending on the position of the ADFselector switch:

- ADF 1 is represented by a single pointer- ADF 2 is represented by a double pointer.

Note: Some DDRMIs are not equipped with the ADFcapability.




UFD4200


ADF SYSTEM PRESENTATION - INDICATINGTMUADFF01-P04 LEVEL 1



UFD4200



TMUADFF01 LEVEL 1



UFD4200


34 - NAVIGATION

34-53-00 ADF DESCRIPTION/OPERATION

CONTENTS:GeneralAuto TuningManual TuningBack Up TuningAntennaeLGCIUIndicatingCFDIUSelf Examination

TMUADFA01 LEVEL 3

EFFECTIVITY 34-53-00 Page 1Jun 30/00


UFD4200


ADF DESCRIPTION/OPERATION

GENERAL

The Automatic Direction Finder (ADF) System includes:- 2 Identical ADF receivers,- 2 Identical ADF antennae.

NOTE: ADF 2 system is optional.

AUTO TUNING

In NDB approach each Flight Management and GuidanceComputer (FMGC) automatically tunes its ownside ADFreceiver through its ownside Radio ManagementPanel(RMP).With failure of one FMGC, the other FMGC can controlthe two ADF receivers, one directly, the other throughits Radio Management Panel (RMP).When the FMGC fails, the ADF receives a discretethrough the RMP to automatically select port B.

MANUAL TUNING

From each Multipurpose Control and Display Unit (MCDU)both ADFs can be manually tuned through their ownsideFMGC .

BACK UP TUNING

In case of dual FMGC failure, the RMPs enable BACK-UPtuning.

ANTENNAE

The ADF antenna provides three signals and consistsof one sense antenna and two loop antennae calledlongitudinal antenna and lateral antenna.The ADF antenna comprises:

- One pre-amplifier, for each antenna, suppliedby the ADF receiver in + or - 12 VDC.

- A test loop which enables a self test.The ADF ground stations operate in a frequency rangeof 190 to 1750 KHz divided into two parts:

- Non Directional Beacons (NDB):190 to 550 KHz,

- Standard commercial broadcast AM stations:550 to 1750 KHz.

LGCIU

Each Landing Gear Control Interface Unit (LGCIU) sendsdiscrete signals to the associated ADF receiver.This Ground/Flight information is used by the receiverBITE module to count the flight legs.

TMUADFA01-T01 LEVEL 3



UFD4200


ADF DESCRIPTION/OPERATIONTMUADFA01-P01 LEVEL 3



UFD4200


ADF DESCRIPTION/OPERATION

INDICATING

The ADF data is sent to the Navigation Displays (NDs)through the Display Management Computers (DMCs) andalso to the DDRMI.The ADF audio signal is processed by the receiver andsent to the Audio Management Unit (AMU) and can beheard by the crew.

NOTE: Some DDRMIs are not equipped with the ADFcapability.

CFDIU

The MCDUs allow the systems to be tested and troubleshooting to be performed via the Centralized FaultDisplay Interface Unit (CFDIU).The tests are only available on ground.

TMUADFA01-T01 LEVEL 3



UFD4200



TMUADFA01 LEVEL 3



UFD4200


SELF EXAMINATION

How are the antenna amplifiers supplied ? A - By the 28 DC NORM BUS.B - By the 115 VAC NORM BUS.C - By + or - 12 VDC through the ADF

Receiver.

If FMGC 1 has failed, is the ADF 1 receiver tuned ?A - Yes, from the opposite FMGC.B - Yes, through RMP1.C - No, ADF 1 cannot be tuned.

TMUADFA01 LEVEL 3



UFD4200


34 - NAVIGATION

34-53-00 ADF INDICATIONS ON ND

CONTENTS:ADF CharacteristicsADF PointersNDB PushbuttonFailuresSelf Examination

TMUADFB02 LEVEL 2



UFD4200


ADF INDICATIONS ON ND

ADF CHARACTERISTICS

DISPLAY IN ROSE OR ARC MODEWhen the mode selector is set to ROSE or ARC mode, andthe ADF/VOR selectors are set to ADF, the ADF stationcharacteristics are displayed in green in the leftlower corner (ADF1) or right lower corner (ADF2) ofthe ND.

Note: ADF 2 system is optional

POINTERSTwo kinds of green pointer can show the ADF groundstation bearings on the heading dial.

- Single green pointer for ADF1- Double green pointer for ADF2

TMUADFB02-T01 LEVEL 2



UFD4200


TMUADFB02-P01 LEVEL 2




UFD4200



NDB PUSHBUTTON

In ROSE-NAV and ARC modes, when the Non DirectionalBeacon (NDB) pushbutton is selected on the ElectronicFlight Instrument System (EFIS) control panel, magentatriangle symbols show the ADF ground stations.




UFD4200


ADF INDICATIONS ON NDTMUADFB02-P02 LEVEL 2



UFD4200



FAILURES

When a failure occurs, a red flag is displayed in theleft lower corner (ADF1) or right lower corner (ADF2)on the ND and the corresponding pointer disappear.




UFD4200


ADF INDICATIONS ON NDTMUADFB02-P03 LEVEL 2



UFD4200


SELF EXAMINATION

What is displayed in case of Non Computed Data?A - A RED flag.B - Dashes in place of identification.C - The ground station characteristics and

pointer disappear.

What is displayed in case of ADF failure?A - The pointer symbol and the ADF flag

appear in RED.B - The ground station characteristics and

pointer disappear and the RED ADF flagappears.

C - No ADF indications on ND.

TMUADFB02 LEVEL 2



UFD4200


34 - NAVIGATION

34-53-00 ADF COMPONENTS

CONTENTS:ADF Receiver (Collins)ADF Receiver (Allied)ADF Antennae

TMUADFD02 LEVEL 3



UFD4200


ADF COMPONENTS

ADF RECEIVER (COLLINS)

IDENTIFICATIONFIN: 2RP1, 2RP2


COMPONENT DESCRIPTIONThe face of the ADF Receiver is fitted with two LEDsand a TEST pushbutton switch. When it is pressed in,the functional test starts.If no fault is detected during the test the green LRUSTATUS LED comes on.The back is fitted with an ARINC 600 connector.

ADF RECEIVER (ALLIED)



COMPONENT DESCRIPTIONThe face of the ADF Receiver is fitted with twomomentary pushbutton switches and a Liquid CristalDisplay (LCD).The LCD provides user intefaces for test, fault displayand troubleshooting.The front face is also fitted with an RS-232 connectorfor interfacing with personnal computers.The back is fitted with an ARINC 600 connector.

TMUADFD02-T01 LEVEL 3



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ADF COMPONENTS - ADF RECEIVERSTMUADFD02-P01 LEVEL 3



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ADF ANTENNAE



COMPONENT DESCRIPTIONIt is a combined loop and sense antenna enclosed in afiberglass housing.The omnidirectional sense antenna is verticallypolarized.The directional loop antennae are horizontallypolarized.The output impedance of the antenna is 78 ohms.

TMUADFD02-T02 LEVEL 3



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TMUADFD02-P02 LEVEL 3

ADF COMPONENTS - ADF ANTENNAE



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TMUADFD02 LEVEL 3



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34 - NAVIGATION

34-55-00 VOR/MARKER SYSTEMS PRESENTATION

CONTENTS:VOR PrincipleMKR PrincipleComponentsVOR IndicatingMKR Indicating

TMUVORG02 LEVEL 1



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VOR/MARKER SYSTEMS PRESENTATION

VOR PRINCIPLE

The Very high frequency Omni-directional Range(VOR)system is a medium-range radio navigation aid.The VOR system receives, decodes and processes bearinginformation from the omni-directional ground station(working frequency range: 108 to 117.95 Mhz)The ground VOR station generates a reference phasesignal and a variable phase signal.The phase difference between these signals, calledbearing, is function of the aircraft position withrespect to the ground station.The bearing is the angle between the Magnetic Northand the ground station/aircraft axis.Furthermore, the VOR station provides a Morseidentification which identifies the station.

TMUVORG02-T01 LEVEL 1



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VOR/MARKER SYSTEMS PRESENTATION - VOR PRINCIPLETMUVORG02-P01 LEVEL 1



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MRK PRINCIPLE

The MARKER (MKR) system is a radio navigation aid whichindicates the distance between the aircraft and therunway threshold.The MARKER (MKR) system is normally used together withthe ILS system during an ILS approach.




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VOR/MARKER SYSTEMS PRESENTATION - MKR PRINCIPLETMUVORG02-P02 LEVEL 1



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COMPONENTS

The VOR and MKR systems are composed of two receivers,one marker antenna and one dual VOR antenna.The VOR/MKR system is also connected to:

- Navigation Displays (ND), Primary FlightDisplays (PFD) and VOR/ADF/DME Radio MagneticIndicator (VOR/ADF/DME RMI) for display.

- Electronic Flight Instrument System (EFIS)panels for control display.

- Flight Management and Guidance Computers (FMGC)for auto-tuning.

- Multipurpose Control Display Units (MCDU) formanual tuning.

- Captain and First Officer Radio ManagementPanels (RMP) for back-up tuning.

- Audio Control Panels (ACP) for VOR/MKRaudio signal.




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VOR/MARKER SYSTEMS PRESENTATION - COMPONENTSTMUVORG02-P03 LEVEL 1



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VOR INDICATING

The indicators show that the aircraft is flying fromthe ground station and is on the right,crossing andthen on the left hand side of the course selected bythe pilot.




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VOR/MARKER SYSTEMS PRESENTATION - VOR INDICATING (EXAMPLE)TMUVORG02-P04 LEVEL 1



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MKR INDICATING

When the aircraft overflies the Marker, the type ofMarker is display on the PFDs in different colors, andis indicated by an aural identification.




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VOR/MARKER SYSTEMS PRESENTATION - MKR INDICATINGTMUVORG02-P05 LEVEL 1



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TMUVORG02 LEVEL 1



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34 - NAVIGATION

34-55-00 VOR/MKR DESCRIPTION/OPERATION

CONTENTSGeneralVOR Auto TuningVOR Manual TuningVOR Back Up TuningVOR AntennaVOR UsersMKR ControlMKR AntennaAMULGCIUIndicatingCFDIUSelf Examination

TMUVORA01 LEVEL 3



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VOR/MKR DESCRIPTION/OPERATION

GENERAL

The Very High Frequency Omni-Directional Range (VOR)and Marker (MKR) system includes:

- 2 Identical VOR/MKR receivers (only MKR1 systemis installed on aircraft),

- 1 Dual VOR ANTENNA,- 1 MKR ANTENNA.

VOR AUTO TUNING

In normal operation each Flight Management and GuidanceComputer (FMGC) automatically tunes its ownside VORreceiver through its ownside Radio Management Panel(RMP) via port A.With failure of one FMGC, the other FMGC can controlthe two VOR/MKR receivers, one directly, the otherthrough its Radio Management Panel (RMP).When the FMGC fails, the VOR receives a discretethrough the RMP to automatically select port B.

VOR MANUAL TUNING

From each Multipurpose Control and Display Unit (MCDU)both VORs can be manually tuned through their ownsideFMGC .

VOR BACK UP TUNING

In case of dual FMGC failure, the RMPs enable BACK-UPtuning.

VOR ANTENNA

The dual VOR antenna receives the signals coming fromthe ground stations.The VOR Antenna operates in the 108 to 117.95 Mhzrange.

VOR USERS

The VOR data is sent to the FMGCs for aircraft positioncomputation.

MKR CONTROL

The system consists of two identical VOR/MKR receiversbut only MKR one is operative as it is connected tothe MKR antenna.The MKR system operates at a fixed frequency and doesnot need any control.

MKR ANTENNA

The MKR antenna receives MKR signals when the aircraftflies over the MKR beacons.The MKR Antenna operates at 75 Mhz.

TMUVORA01-T01 LEVEL 3



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VOR/MKR DESCRIPTION/OPERATIONTMUVORA01-P01 LEVEL 3



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VOR/MKR DESCRIPTION/OPERATION

AMU

The pilot can adjust the volume of the VOR groundstation and MKR beacon identification signals usingthe VOR and MKR pushbuttons on the AUDIO CONTROL PANEL(ACP).Selected VOR ground station and MKR beaconidentification audio signals are transmitted to AudioManagement Unit (AMU) and then dispatched to theheadsets and/or loudspeakers

LGCIU

Each Landing Gear Control Interface Unit (LGCIU) sendsdiscrete signals to the associated VOR receiver.This Ground/Flight information is used by the receiverBITE module to count the flight legs.

INDICATING

VOR data is sent to the Navigation Displays (ND)through the Display Management Computers (DMC) and tothe Digital Distance and Radio Magnetic Indicator(DDRMI).The MKR data is sent to the Primary Flight Displays(PFD) through the Display Management Computers (DMC).

CFDIU

The MCDUs allow the systems to be tested and troubleshooted via the Centralized Fault Display InterfaceUnit (CFDIU).The tests are only available on ground.

TMUVORA01-T01 LEVEL 3



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TMUVORA01 LEVEL 3



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SELF EXAMINATION

To which of the following is the MKR Antennaconnected ?

A - VOR/MKR receiver 2.B - VOR/MKR receiver 1.C - VOR/MKR receivers 1 and 2.

If FMGC 2 has failed, is VOR 2 receiver tuned ?A - Yes, from the opposite FMGC.B - Yes, from the opposite FMGC but after

switching.C - No, the VOR 2 cannot be tuned.

TMUVORA01 LEVEL 3



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34 - NAVIGATION

34-55-00 VOR INDICATIONS ON ND

CONTENTS:VOR CharacteristicsPointersCourse/Lateral DeviationVOR-D PushbuttonFailuresSelf Examination

TMUVORB01 LEVEL 2



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VOR INDICATIONS ON ND

VOR CHARACTERISTICS

DISPLAY IN ROSE OR ARC MODEWhen the mode selector is set to ROSE or ARC mode, andthe ADF/VOR selector is switched to VOR, the VORstation characteristics are displayed in white in theleft lower corner (VOR 1) or right lower corner (VOR2) of the ND.

POINTERS

DISPLAY IN ROSE AND ARC MODESTwo types of white pointer can show the VOR groundstation bearings on the heading dial.

- Single white bearing pointer for VOR 1- Double white bearing pointer for VOR 2

TMUVORB01-T01 LEVEL 2



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TMUVORB01-P01 LEVEL 2




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COURSE/LATERAL DEVIATION

CONDITIONS OF DISPLAYAdditionally, in ROSE-VOR mode, other information isdisplayed on the ND.




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VOR INDICATIONS ON NDTMUVORB01-P02 LEVEL 2



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VOR-D PUSHBUTTON

CONDITIONS OF DISPLAYIn ROSE-NAV and ARC positions, it is possible to showin magenta the VOR ground stations which are not tunednor already included in the flight plan.




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FAILURES

CONDITIONS OF DISPLAYDepending on the mode selected on the EFIS controlpanel, red flags are displayed.




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SELF EXAMINATION

In which ND mode is the VOR course deviationinformation displayed ?

A - In ROSE-VOR mode.B - In ROSE-NAV mode.C - In any mode.

When is the "M" symbol displayed in the VORcharacteristics ?

A - When the VOR is tuned from the MCDU.B - When the VOR is tuned from the RMP.C - When a failure occurs.

TMUVORB01 LEVEL 2



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34 - NAVIGATION

34-55-00 VOR/MKR COMPONENTS

CONTENTS:VOR/MKR Receiver (Collins)VOR/MKR Receiver (Allied)VOR AntennaMKR Antenna

TMUVORE03 LEVEL 3



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VOR/MKR COMPONENTS

VOR/MKR RECEIVER (COLLINS)

IDENTIFICATIONFIN: 3RS1,3RS2

LOCATIONZONE:127,128

COMPONENT DESCRIPTIONThe face of the VOR/MKR Receiver is fitted with twoLEDs and a TEST pushbutton switch. When it is pressedin, the functional test starts.If no fault is detected during the test the green LRUSTATUS LED comes on.The back is fitted with an ARINC 600 connector.

VOR/MKR RECEIVER (ALLIED)

IDENTIFICATIONFIN: 3RS1,3RS2

LOCATIONZONE:127,128

COMPONENT DESCRIPTIONThe face of the VOR/MKR Receiver is fitted with twomomentary pushbutton switches and a Liquid CristalDisplay (LCD).The LCD provides user intefaces for test, fault displayand troubleshooting.The front face is also fitted with an RS-232 connectorfor interfacing with personal computers.The back is fitted with an ARINC 600 connector.

TMUVORE03-T01 LEVEL 3



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VOR/MKR COMPONENTS - RECEIVERSTMUVORE03-P01 LEVEL 3



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VOR/MKR COMPONENTS

VOR ANTENNA

IDENTIFICATIONFIN: 4RS

LOCATIONZONE: 324

COMPONENT DESCRIPTIONThe dual VOR antenna is located on the top of the tail.It is a small-sized half-wave folded dipole type.The antenna is horizontally polarized and has animpedance of 50 ohms.

MKR ANTENNA

IDENTIFICATIONFIN: 1RS

LOCATIONZONE: 133

COMPONENT DESCRIPTIONThe dielectric, foam-filled, polyester fiberglasshousing, fitted with a metal leading edge, protectsagainst moisture and erosion. The antenna is horizontally polarized and has animpedance of 50 ohms.

TMUVORE03-T02 LEVEL 3



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TMUVORE03-P02 LEVEL 3

VOR/MKR COMPONENTS - ANTENNAE



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TMUVORE03 LEVEL 3



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34 - NAVIGATION

34-00-00 ECAM WARNINGS (EXCEPT ADIRS)

CONTENTS:GeneralILS FaultPRED W/S FaultRA FaultTCAS FaultGPWS FaultGPWS TERR DET FaultGPS FaultFM/GPS POS DISAGREE

TMUWARN01 LEVEL 3



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ECAM WARNINGS

GENERAL

Note: There are no dedicated ECAM pages for thenavigation system.In case of a NAV FAULT, there will be no systempage called for the corresponding failure.

ILS FAULT

This warning is triggered in case of an ILS1 (or 2 orILS1+2) receiver failure (LOC and G/S parts).In case of failure of one ILS receiver, the landingcapability is limited to CAT1 (CAT1 inoperative whenboth receivers have failed).

PRED W/S FAULT

This warning is triggered in case of a detectedwindshear fault.

RA FAULT

This warning is triggered in case of an RA1 (or 2 orRA1+2) failure.In case of failure of both RAs, the landing capabilityis limited to CAT1.When only one RA has failed, no local warnings areshown but CAT3 is inoperative.

TCAS FAULT

This warning is triggered in case of a TCAS internalfailure.

TMUWARN01-T01 LEVEL 3



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ECAM WARNINGSTMUWARN01-P01 LEVEL 3



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ECAM WARNINGS

GPWS FAULT

This warning is triggered in case of a GPWS failure.Notice the amber FAULT light on the GPWS control panel.

NOTE: In case of ILS1 failure, only mode 5 is inhibited,consequently the FAULT light does not come onand the GPWS FAULT message is not triggered.

GPWS TERR DET FAULT

This warning is triggered in case of terrain detectionfailure as well as the amber TERR FAULT light on theGPWS control panel.

GPS FAULT

This warning is triggered in case of a GPS1 (or 2 or1+2) failure.

FM/GPS POSITION DISAGREE

When latitude or longitude from either GPSSU1 or 2deviates more than 0.5 Nm the amber NAV FM/GPS POSDISAGREE is triggered.

TMUWARN01-T02 LEVEL 3



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ECAM WARNINGSTMUWARN01-P02 LEVEL 3



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TMUWARN01 LEVEL 3



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34 - NAVIGATION

34-10-00 ADIRS/CFDS SPECIFIC PAGESPRESENTATION

CONTENTS:GeneralADR SYSTEM TESTADR OUTPUT TESTSADR GROUND REPORTADR INPUT STATUSIR SYSTEM TESTIR INTERFACE TESTIR GROUND REPORTIR INPUT STATUSADR Self Test ValuesIR Self Test Values

TMUADIL04 LEVEL 3



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ADIRS/CFDS SPECIFIC PAGES PRESENTATION

GENERAL

The tests for ADR 1,2 and 3 are identical and the testsfor IR 1,2 and 3 are also identical.Therefore, we will only see system 1 for each one.Remember that the ADR and IR are Type 1 systems.

ADR SYSTEM TEST

The activation of the SYSTEM TEST allows the power-uptest and the continuous BITE test resident in the ADIRUto be repeated (check of the system integrity afteran ADIRU replacement).When a fault is detected by the system, during thetest, the failure data will be listed on the MCDU inthe same way as trouble shooting data page (HEXcoding).

TMUADIL04-T01 LEVEL 3



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TMUADIL04-P01 LEVEL 3

ADIRS/CFDS SPECIFIC PAGES PRESENTATION (ADR SYSTEM TEST)



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ADR OUTPUT TESTS

1.SLEW TESTS- ALT DYNAMIC SLEW testThe activation of the ALT DYNAMIC SLEW test causes theADR to output a simulated ramp of altitude (Label 203).The low and the high altitude limits, as well as theslew rate, are specified by the operator.The altitude increasing or decreasing is visualizedon the PFD.The test is inhibited if TAS > 100 kts.- CAS DYNAMIC SLEW testThe activation of the CAS DYNAMIC SLEW test causes theADR to output a simulated ramp of Computed Air Speed(Label 206).The low and the high speed limits, as well as the slewrate, are specified by the operator.The speed increasing or decreasing is visualized bythe operator on the PFD.The test is inhibited if TAS > 100 Kts.




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ADIRS/CFDS SPECIFIC PAGES PRESENTATION (SLEW TESTS)TMUADIL04-P02 LEVEL 3



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ADR OUTPUT TESTS (CONT)

2.INTERFACE TESTSWhen the test input command to the ADIRU is activated,a sequence is initiated which simulates an actualflight state of the ADIRU.The ADR will provide calibrated test values to theinstruments.This checks the computer, the transmission and thedisplay of the air data parameters.Test sequence:-0 to 5 seconds: failure warning mode tested (seetables).-5 to 10 seconds: Altitude Ramp test (rate of 600ft/mn).-10 seconds until test completion: fixed output testvalues.




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ADIRS/CFDS SPECIFIC PAGES PRESENTATION (ADR INTERFACE TEST)



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ADR OUTPUT TESTS (CONT)

3.AOA SENSOR TESTSThe activation of the AOA SENSOR TEST causes theAOA sensor to be commanded to a fixed position (40degrees) greater than the stall warning thresholdthus, the Flight Warning Computer activates theaural STALL warning and the cricket sound.

ADR GROUND REPORT

When the GROUND REPORT line select key is pressed in,it reports all internal faults detected since the lastlanding.When a fault is detected by the system, during thetest, the failure data will be listed on the MCDU inthe same way as trouble shooting data page (HEXcoding).




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ADIRS/CFDS SPECIFIC PAGES PRESENTATION (AOA SENSOR TEST AND GROUND REPORT)



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ADR INPUT STATUS

When the INPUT STATUS line select key is pressed in,it describes the current state/value of the selectedADR inputs (discrete, analog and ARINC inputs).Example on the INPUT STATUS page 2/8:

- WMO/MMO DISC 1 OPEN- WMO/MMO DISC 2 GND- WMO/MMO DISC 3 OPEN- WMO/MMO DISC 4 OPEN

When no discrete is in the ground state (open), theADR uses the BASIC LAW values for WMO/MMO (350 Kts,0.82M).Only one of the four WMO/MMO program discretes can bein the ground state at any one time.Ex: The WMO/MMO DISC 2 is available and is provided

by the L/G DOWN WMO/MMO SELECTION switch (22FP).The normal position of this switch is open and itis grounded after crew action for particularflights (ex: ferry flight).




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ADIRS/CFDS SPECIFIC PAGES PRESENTATION (ADR INPUT STATUS)



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IR SYSTEM TEST

When the SYSTEM TEST line select key is pressed in, acomplete test of the IR system is activated (power-upand continuous BITE tests).When a fault is detected by the system, during thetest, the failure data will be listed on the MCDU inthe same way as trouble shooting data page (HEXcoding).NOTE: A lockout display is presented in case of a

disagreement between ground information fromCFDIU and ADIRU when the TEST mode is addressed(with TAS or Inertial GS > or = 100 Kts).




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ADIRS/CFDS SPECIFIC PAGES PRESENTATION (IR SYSTEM TEST)



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IR INTERFACE TEST

When the test input command to the ADIRU isactivated, a sequence is initiated which simulatesan actual flight state of the ADIRU.The IR will provide calibrated test values to theinstruments.This checks the computer, the transmission and thedisplay of inertial reference parameters.The test mode is inhibited whenever any of thefollowing conditions exist:

- Ground speed > or = 20 Kts- IR in ATT mode.

Test sequence:- 0 to 2 seconds: Output set to functional test,annunciator discretes energized (see table).

- After 2 seconds: Output set to functionaltest, annunciator discretes released tonormal status (see table).




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ADIRS/CFDS SPECIFIC PAGES PRESENTATION (IR INTERFACE TEST)



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IR GROUND REPORT

When the GROUND REPORT line select key is pressed in,it reports all internal faults detected since the lastlanding.




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ADIRS/CFDS SPECIFIC PAGES PRESENTATION (IR GROUND REPORT)



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IR INPUTS STATUS

When the INPUT STATUS line select key is pressed in,it describes the current state of the selected IRinputs (discrete, analog and ARINC inputs).Example on the INPUT STATUS page 4/6, ARINC input valuefrom the Control Display Unit (CDU):

- The SET LAT, SET LONG and SET HEADINGdisplayed values are copies of datareceived from each of the listed signalsources (here the CDU).The latitude and the longitude inputs areprocessed during the ALIGN mode, theheading input is processed during the ATTmode.These displayed data are latched as displayvalues until new valid source data isreceived from each signal source.In case of invalid inputs dashes (-----)are displayed.




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ADR SELF TEST VALUES (IR INPUT STATUS)TMUADIL04-P09 LEVEL 3



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TMUADIL04 LEVEL 3



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ADR SELF TEST VALUES (OUTPUT BINARY WORD)(1/2)



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ADR SELF TEST VALUES (2/2)TMUADIL04-P11 LEVEL 3



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IR SELF TEST VALUES (1/2)TMUADIL04-P12 LEVEL 3



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IR SELF TEST VALUES (2/2)TMUADIL04-P13 LEVEL 3



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34 - NAVIGATION

34-42-00 RADIO ALTIMETER/CFDS SPECIFICPAGE PRESENTATION

CONTENTS:GeneralLRRA ARINC TestLRRA RAMP Test

TMURADE02 LEVEL 3



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RADIO ALTIMETER/CFDS SPECIFIC PAGE PRESENTATION

GENERAL

The RA is a type 1 system.The RA system is not available in CFDS back-up mode.

LRRA ARINC TEST

During the ARINC TEST, an integrity test is performed,the antena circuit and the CFDIU input data are tested.This test is performed after a Removal/Installationof a Radio Altimeter antenna or transceiver.During the test (0.8 second), observe the followingindications on the CAPT PFD:

- the bottom sector line moves down from thehorizon line.

- the radio altitude value indicates 40 ft.If no failure, at the end of the test, NO FAILUREDETECTED message appears on the MCDU.

LRRA RAMP TEST

The RAMP TEST tests the complete Radio Altimetricchain.A start altitude, a stop altitude and a slope must beentered prior to triggering the test.Then, the line key adjacent to TRIGGER has to bepressed.Observe on the CAPT PFD that:

- Radio Altitude starts from the entered value,0 ft in this example, then increases at aconstant rate of 25 ft/s until reaching theStop Altitude of 2500 ft. Also notice themovement of the red ribbon and the lower lineof the attitude sphere on the PFD.

NOTE: The REPLAY line key restarts the test.The CONTINUE line key continues the RAMP TESTif it was interrupted before the end.

TMURADE02-T01 LEVEL 3



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RADIO ALTIMETER/CFDS SPECIFIC PAGE PRESENTATIONTMURADE02-P01 LEVEL 3



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TMURADE02 LEVEL 3



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34-navigation

Documents

adirs presentation

adirs indications

egpws presentation

adirs components

adirs cdu presentation

system controls presentation

ddrmi presentation

tcas indications