ATR Pilots Guide 1-3

8/18/2019 ATR Pilots Guide 1-3

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THALES AVIONICS

ATR 600 Series AVS

Pilot’s Guide User guide for EngineersDe Rojas Florent

18/09/2011

This is a engineer oriented pilot’s guide for the ATR 600 series Avionic Suite develloped by Thales

Avionics


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R E F : C L A / 1 1 / 0 0 4 8 2 0 A T R 6 0 0 S E R I E S A V S P I L O T ’ S G U I D E

3

AVS PILOT’S GUIDE

FOR ATR 42 / 72 - 600

NomDépartementDepartment

Name

Fonction/Function Date Visa

Written by: De Rojas Florent 18/09/2011

Supported by :

Ricaud Denis AVS Architect

Gucemas Manuel AVS Architect

Hugues Gamonet AVS Architect

Eric Chevalier AVS Architect

Fabien Guilley AVS Architect

Damien Brocas AVS Architect

Laurent Fillol AVS Architect

Laurent Patau AVS Architect

Olivier Lemoine AVS Architect

BouardDominique

Christian Reunier

Laurent Frede

Cyril Therrat


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LIST OF RECIPIENTS

Intentionally left blank


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REVISIONS

REVISION DATE DESCRIPTION OF UPDATES


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SummarySummary................................................................................................................................................................. 6

General s ................................................................ ................................................................ .................................. 7

Cockpi t Display Management ............................................................... ............................................................... 11

Pr imary References ........................................................... ................................................................ ................... 27

Radio Management ........................................................... ................................................................ ................... 45

Radio Navigation ............................................................... ................................................................ ................... 57

Aircraf t System Parameters ....................................................... ................................................................. ......... 73

F light Warni ng ................................................................ ................................................................ ..................... 87

External Protections .......................................................... ................................................................ ................... 95

Airport Navigation ............................................................................................................................................. 119

F light Management System ....................................................... ................................................................. ....... 125

Autofl igh t ................................................................ ................................................................ ............................ 143

Function ................................................................ ................................................................ ............................. 143

Maintenance ........................................................... ................................................................ ............................ 199

Glossary ................................................................ ................................................................ .............................. 209


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Generals1 SCOPE ............................................................ ................................................................ ................................ 7

2 REFERERENCED DOCUMENTS .............................................................................................................. 7

3 INTRODUCTION .............................................................. ................................................................. ........... 7

3.1 What’s New ? ............................................................. ................................................................. ........... 8

1 SCOPE

This document is the ATR 600 series AVS pilot’s guide made for engineers according to the AVSFunction Content List (FCL) point of view.

It describes for a user point of view the main AVS functionnalities and operational modes.

It is supplemented by a FMS an IESI User Manuals and System/Segment Specification (SSS) andSystem / Segment Design Document (SSDD).

2 REFERERENCED DOCUMENTS

Document Title Reference

User guide for the IESI ASW/10/004799 rev01

FMS User’s Manual FMC2/ NAV/08/001108 -00

Previous documents should be used at the latest issue approved.

3 INTRODUCTION

The major design objective of new ATR avionics’ suite is to provide the crew with the mostrealistic picture of the in-flight situation and the most comprehensive displays of the aircraft systems.

The AVS provides the flight crew with information on:

Aircraft flight parameters Aircraft systems


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Aircraft environment,

Navigation data and flight plan management

Guidance or automatic control of the aircraft path,

Communication with ground and other aircraft

The AVS also eases maintenance through an AVS Centralized Maintenance concept.

3.1 What’s New ?

The ATR avionics have been improved and developed during recent years essentially to face requiredregulatory evolution, in connection with new required functionalities:

FM immunity, 8.33 KHz radio, B-RNAV, ACAS, TAWS

HF, ACARS, …

The cockpit is designed in order to replace most of the present instruments by five 6” x 8” LCD

displays composed of:

2 Primary Flight Displays (PFD),

2 Multi-Function Displays (MFD),

1 Engine & Warning Display (EWD)

Improved Operation and Situational Awareness :

Improved Dispatch Capability

RNP 0.3 ready with path for lower RNP

Enhanced Crew Alert System

Paper-Less cockpit with procedures and system page management

Basic WAAS capability


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Improved situational awareness and safety

Navigation Charts display with A/C position

Provision for Vertical Situation Display with terrain profile

Provision for ADS-B with CDTI for full traffic awareness

Enhanced maintenance abilities


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CockpitDisplay

Management1 GENERALS.................................................................................................................................................. 12

2 MANAGE DISPLAYS........................................................ ................................................................. ......... 12

2.1 General description .............................................................. ............................................................... 12 2.1.1 PFD’s ............................................................................................................................................ 13

2.1.2 MFD’s ........................................................................................................................................... 14 2.1.3 Engine Warning Displays (EWD) ........................................................ ......................................... 17

2.2 Display Control ................................................................................................................................... 18

2.3 Reconfigurations ................................................................................................................................. 20

2.4 Manage ND range and mode .......................................................... .................................................... 22

3 MANAGE COCKPIT LIGHTI NG .............................................................................................................. 23

4 MANAGE DH / MDA .................................................................................................................................. 24

5 MANAGE VIRTUAL CONTROL PANEL (VCP) ...................................................................................... 24

6 CAS MESSAGES ............................................................... ................................................................. ......... 25


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Control panels for system settings

Five 6x8’’ LiquidCrystal Display

Units (DU’s,) Called 1 to 5 from left toright

Two Primary Flight Displays(PFD) for EFIS functions(EADI/EHSI)

Two Multi Function Displays(MFD) for Navigation andaircraft system synoptic.

One Engine & WarningDisplay (EWD) for EngineInstruments and Crew AlertingSystem, Checklists/Procedures management and

permanent data.

1 GENERALS

The Cockpit Display System constitutes the vital interface for the pilots, via which all theinformation appears. It is thus essential to preserve a permanent readability of the presentedinformation and thus to supply to the pilots the means to adjust the luminance of their screens.

Better, an automatic adaptation of the luminance, will allow to take off and to cross a cloudycoat and to keep the same data readability in cruise phase while they will be in very sunnyenvironment.

2 MANAGE DISPLAYS

2.1 General description


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HSI or Navigation Display

2.1.1 PFD’s

PFD is the Primary Flight Display, attitude and andbasic navigation informations are diplayed on it.

PFD’s integrate multiple conventional instruments :

EADI on topo Digital ASIo Radio altitudeo Lateral & vertical deviationo FD guidance

EHSI on bottomo Bearing pointerso TAWS or WXR data

Rolling Air Speed Indicator with speed bugso V-speedso Low and over speedso Speed trendo Managed/selected speeds

Rolling barometric altitude display

Vertical speed

Flight mode, icing conditions annunciations

Take a look at Primary References function part formore informations


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2.1.2 MFD’s

The MFD upper area support following formats :

Navigation Display (ND),

System Display (SD),

Engine Run-up (RUN UP),

Perf Init (PERF),

Airport chart in option,

N A V I G A T I O N D I S P L A Y ( N D )

Navigation display format provides

o Actual & selected heading

o Bearing pointerso FMS datao Navaidso TAWS or WXR imageo TCAS data

Navigation Display (ND) format isconfigurable in 3 display format: ARC , PLAN an ROSE .

When ND is not displayed on MFD (in case ofsystem page consultation for exemple), a miniND is displayed on bottom part of the PFD

Ground speed True Airspeed

ind data

HDG selection

TCAS messages

FMS optional data reminders

Radionavigation aid

Tunedwaypoint

information

Lat/Long

Aircraft reference Navigation information

Map data FMS

Traffic data eather data

Terrain data

XR/TAWSmessages

Radionavigation aid

FMS

messages

COM Menu or VCP MenuTemporary

Selections


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A / C S Y S T E M D I S P L A Y F O R M A T ( S D )

For more information, and precise description of each SD pages take a look at to A/C systemparameter Function

SD format includes following pages:

o CABINo AC/DCo HYD/ACWo ENGINE

E N G I N E R U N - U P D I S P L A Y F O R M A T

Display A/C maintenance page function provideson 6 dedicated ENGINE RUN UP pages followinginformations :

- Conditions of current engine fixedpoint

- Computed targets, marging andrating value of following engines parameters

A/C maintenance page selection can be donethanks to VCP RUN UP software menu displayedon lower part of MFD format.

2.1.2.1.1.1.1.1.1 Onl y availab le on gro und

P E R F I N I T F O R M A T

PERF INIT Page display FMS fligh datas


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V I R T U A L C O N T R O L P A N E L A N D T E M P O R A R Y S E L E C T I O N

MFDUPPER

FORMAT

Virtual Control PanelTemporary

Selections

Virtual control panel area supports several display and controls functions:- VCP NAV,- VCP COM,- VCP SURV,- VCP PERF,- VCP RUN UP,

- VCP MAP

Temporary selection area Display basic A/C status function such as :

1. Fuel crossfeed control/failure device status2. Anti-icing control/failure devices status3. De-icing control/failure devices status4. Cabin seat belt/No smoking message status


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2.1.3 Engine Warning Displays (EWD)

The EWD format provides:

- Primary engine and fuel parameters and flight controldata (see A/C system parameter)

- Emergency / abnormal procedures or specific check-list and warning / caution list (see FWS)

Flight controlwindow

Warning andCautionwindow Procedure

window

Primaryengine andPermanentData window


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2.2 Display Control

The Display Units DU1, DU2, DU3, DU4 and DU5show to the flight crew the display images necessary

for the control, monitoring and safe navigation of theaircraft. They have interfaces with most of the aircraftsystems.

The DU control embeds:

A power control switch; A ON / OFF status light (white when

ON, dark when OFF); A brightness control via a rocker

switch to increase / decreasethe brightness;

A contrast control via a rocker switch

to increase / decrease thecontrast;

2 luminance sensors for integratedautomatic dimming (night and dayshading)

D U O P E R A T I O N A L M O D E M A N A G E M E N T

There are 9 DU modes:

1. OFF Activity: noneDisplay: black screen

2. Pin prog hard ERROR State: The hardware pinprog parity check on pinprogram is failed.

3. START Display: At the DU start,the screen stays blackduring a maximum of3 seconds.

4. EMPTYState: The DU firmwarehas detected that the DUis empty i.e. has nooperational software. 5. OPERATIONAL

Activity: OperationalDisplay: a format isdisplayed on the DU

6. PBIT, Power-on Built-In Test Activity: safety test are in progress

7. FAILState: A fatal failure hasbeen detected by DUsoftware or by hardware.

8. DATA LOADING Activity: data loading is inprogress on shop or onboard with data loadingcompact flash inserted.

9. END OF DATA LOADING Activity: None, DU software

data loading is ended.

Compact Flashslot for Softwareand databaseloading


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1 - POWER

DETECTION

START (black display duringa maximum of 3 seconds)

3 - PBIT (“T” duringa maximum of 40seconds)

4 – OPERATIONAL

1 - POWERDETECTION

START (blackdisplay during amaximum of 3seconds

3 - PBIT (“T” during amaximum of 7seconds or 40 if lastsafety test wasn’t OK)

4 – OPERATIONAL

1 - POWERDETECTION

START (blackdisplay during amaximum of 3seconds

3 - PBIT« IAD BITErecording » isdisplayed in greenwith progressinformation

« IAD BITEcompleted » isdisplayed in white

RESTART

Failure hasoccured

RESTART

If DU can’t restartbecause of failure,

DU is lit off

D U O P E R A T I O N S

On Ground Power on:

This sequence is realized in less than 45 seconds.

In f l igh Power on :

Thissequence isrealized inless than 10seconds or 45 if last safety test wasn’t OK.

Dump B ITE : allow to do wnload fai lure repor t on Com pact Flash on g round

Downloading a new so f tware or AVS conf :

Failures

POWER ON

Flashing


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2.3 Reconfigurations

A U T O M A T I C R E C O N F I G U R A T I O N

The CDS reversion system provides automatic DU reconfiguration in case of DU failure(s).The leading rule of the automatic reconfiguration is: following PFD or EWD failure, MFD isreconfigured in PFD or EWD.

The automatic reconfiguration takes into account the following parameters:

Flight/Gnd Status“Pilot Flying Side” : Right or Left

The tables hereunder list all the DU automatic configurations :

Single DU loss :

Double DU loss :

For triple and quadruple automaticreconfiguration look at the SSSconcerning CDM

Battery Power on :

During A/C power-up phase on ground, avionic can be only powered by batteries, in this case,electrical distribution makes that only inner DUs are powered and then available. As engines informations are the most important for this phase, EWD is displayed on DU2 and SDEngine format page is displayed onDU 4

EMER ELEC :

In case of in-flight total loss of electric generators, Only DU2 and 4 are powered by batteries, PFD isdisplayed on DU2 and EWD on DU 4. PFD is provided with left side informations

DU1 DU2 DU3 DU4 DU5

X PFD EWD MFD PFD

PFD MFD EWD PFD X

PF - left side PFD MFD X EWD PFD

PF - right side PFD EWD X MFD PFD

PFD X EWD MFD PFD

PFD MFD EWD X PFD

DU1 DU2 DU3 DU4 DU5

X X EWD MFD PFD

PFD MFD EWD X XX PFD X EWD PFD

PFD EWD X PFD X

X PFD EWD PFD X

X PFD EWD X PFD

PFD X EWD PFD X

PFD X X EWD PFD

PFD EWD X X PFD

PFD X EWD X PFD


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M A N U A L R E C O N F I G U R A T I O N

The CDS manual reconfiguration is controlled by “PFD/EWD/MFD” P/B on CAPT and F/O sides.

Manual reversion overrides a

DU automatic reconfigurationbut if a new automaticreconfiguration occurs,current manual reversion issuperseded by this newconfiguration.

M F D F O R M A T S E L E C T I O N

MFD modes display is control through dedicated EFCP (left EFCP for left MFD, right for right )

Note : In all other mode than ND, ND is then displayed on PFD lower part

Press to execute manualreconfiguration of DU’s

If DU2/4 is available,CAPT(F/O) “PFD/EWD/MFD”

P/B enables a circularreversion of PFD/EWD/MFDformat on DU2/4.

If DU2/4 is out of order, DU1/5takes into account thereversion command.

Display ND on MFD

Display Perf pageon MFD

Display Video(provision)

Display A/Csystem pages

Display ENGINERUN UP pages

Display Airport Navigationfunction page


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ND in ARC mode : A/C symbolalways pointing up, headingscale turning around

ND in ROSE mode : A/Csymbol always pointing up,heading scale turning around

ND in PLAN mode : A/C symbol moving ,heading scale pointingNorth

2.4 Manage ND range and mode

N D M O D E

Turn to display ND in ARC

ROSE or PLAN format


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N D R A N G E

3 MANAGE COCKPIT LIGHTING

D I S P L A Y A N D C O N T R O L P A N E L D I M M I N G

The CDS constitutes the vital interface for thepilots, via which all the information appears. It isthus essential to preserve a permanent readabilityof the presented information and thus to supply tothe pilots the means to adjust the luminance of

their screens.

Besides, an automatic adaptation of theluminance, allow to take off and to cross a cloudycoat and to keep the same data readability incruise phase while they will be in very sunnyenvironment.

The CDS is fully dimmable thought a dedicateddimming function that manages DU front facedimming and control panels dimming.

F G C P L A M P T E S T

Manage cockpit dimming function shall allow crewmembers to test lamps of control panels. Notimplemented on SIB

Click on + to increase range onND / - to decrease.Can be set from 5NM to 320 NM.

By default Range is set to 80 NM

Range


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Turn the switch to selectDH or MDA.

Turn the upper rotary knobto increase (right) ordecrease (left) DH, MDA.

To desactivate the use ofDH or MDA, decrease the

value to 0 and turn onemore click to the right

DH or MDA readout onattitude sphere on PFD

The Multi-purpose Control Panelallows cockpit crew to control theVCP on MFD.

Transverse VCP are NAV for Radio nav settings,COM to tune radio, SURV for TCAS and XPDRsettings. They are accessible at all times on allpages of MCP, even if that MCP page has anassociated VCP

4 MANAGE DH / MDA

Decision Height is used for ILS approaches (Radioaltimeter values) while Minimum Descent Altitude(baro altitude value) is used fornon precisionapproaches, (LOC, VOR, ILS G/S out)

5 MANAGE VIRTUAL CONTROL PANEL

(VCP)

VCP is the lower part of the MFD, itconcentrates various controls andfunctionalities for the crew.

CAUTION : In this section it will only be explainhow to use VCP in general. For furtherexplanations on dedicated VCPsconsult the associated function part ofthe document.

V C P P H I L O S O P H Y

There are two types of VCP : Tansverse VCP andspecific VCP

Transverse VCP

Specif ic VCP

These are the VCP associated to a specific page/function, like Airport Map VCP for example

http://www.airliners.net/aviation-forums/tech_ops/read.main/84047/http://www.airliners.net/aviation-forums/tech_ops/read.main/84047/


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Press NAV to display VCP NAVon MFD.

Press again to change active tab

Use Arrow to select the box/button you want to activateinside the active tab.

ENTER to select or activate.Numbers to modify theselected value

ESC to cancelcurrent action

V C P M E N U T R E E M A N A G E M E N T

The example below’s purpose is to explain how to use a generic VCP (VCP NAV in example).

6 CAS MESSAGESCrew Alerting Messages are displayed on EWD in warning and caution window (see above)

CAS MESSAGE DESCRIPTIONASSOCIATED AURAL

ALERT

DU TEMP HI Only one DU TEMP HI and the other four DUs are in

normal operation mode and ON SINGLE CHIME + Caution

light alert

MULTI DUs T HI At least : 1 DU Overheat and 1 DU off or 2 DU overheat SINGLE CHIME + Caution

light alert

DUDISCREPENCY

PFD Critical Data DISCREPANCY SINGLE CHIME + Cautionlight alert

EWD Critical Data DISCREPANCY SINGLE CHIME + Caution

light alert

SD Critical Data DISCREPANCY SINGLE CHIME + Caution

light alert


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PrimaryReferences

1 GENERALS.................................................................................................................................................. 28

2 AI R DATA FUNCTI ON .............................................................................................................................. 28

2.1 General .............................................................. ................................................................ ................... 28

2.2 Compute Air Data Parameters .......................................................................................................... 29

2.3 Provide Air Data To System ........................................................... .................................................... 29

2.4 System Operation ...................................................... ................................................................. ......... 30 2.4.1 Air Data Function Control ......................................................... .................................................... 30 2.4.2 Air Data Display ........................................................................................................................... 32 2.4.3 Air Data Function Alerts And Monitoring ................................................................ .................... 35

3 INERTI AL DATA FUNCTI ON .................................................................................................................. 36 3.1 General .............................................................. ................................................................ ................... 36

3.2 Compute And Provide Ahrs Data To Systems ............................................................... ................... 36

3.3 System Operation ...................................................... ................................................................. ......... 38 3.3.1 Initialisation And Alignment ................................................................ ......................................... 38 3.3.2 Data Display ........................................................ ................................................................. ......... 38 3.3.3 Flags And Alerts ........................................................................................................................... 39


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1 GENERALS

The Primary REFerences function is the part of this AVS function which is in charge of providing the

primary flight parameters.

PREF aims to provide basic f l ight informat ions to pi lots such as Airspeed and Att i tude

indicat ion

PREF function performs the following functions :

Inertial data function : it computes, displays and transmits the inertial data to theavionics system (AVS) and to other Aircraft systems.

Air data function : it computes, displays and transmits the air data to the AVS andto the other Aircraft systems

Stand-by data function : it computes and displays stand-by air data and attitudedata

2 AIR DATA FUNCTION

2.1 General

The Air Data function is supported by an air data system, including:- 2 ADC- 4 static pressure (Ps) probes- 2 Pitot (Pt) probes,- 2 TAT probes

The Air Data System measurements performed by the probes are supplied to the Air Data Computerby :

4 Static Probes 2 Pitot Probes 2 Temperature Probes

The information from the Static probes, Pitot probes, and Temperature probes are processed by ADCso as to obtain pressure Altitude, Vertical Speed (VS), Computed Airspeed (Vc,) True Airspeed (TAS),Total Air Temperature (TAT) and Static Air Temperature (SAT) data


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2.2 Compute Air Data Parameters

The Air Data provides Calibrated AirSpeed (CAS), Altitude, Vertical Speedand True Air Speed (TAS) and isdisplayed to the cockpit crew on the

Control and Display System (CDS)which constitutes display capabilitiesand control means.

The Temperature Probe sends ananalog signal the ADC computes thisdata and provides Total AirTemperature and Static AirTemperature.

2.3 Provide Air Data To System

ADC1 and ADC2 provide outputs directly to:

- Display Units (DU) that makesuse of flight environment data(airspeed, altitude, airtemperature).

- Altitudes and Heading ReferenceSystem (AHRS)

- Air Traffic Control (ATC)

- Multi Function Computer (MFC)

- Multi Purpose Computer (MPC)

- And indirectly to pressurization,de-icing, Multi Function Computer(MFC1 & 2) and ElectronicEngine Control (EEC) 1 & 2 viaCore Avionics Cabinet (CAC) 1 &2.

The Total and Static Air Pressuresprovided by the Pitot and StaticProbes are processed by the ADC’swhich in turn supplies various aircraftsystems with Air Pressure Data.


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Click twice on PERFon EFCP to displayENG Outside AirTemperature (OAT)on VCP Perf page

Enter ISA temperaturedifference at Take offwith MCP

Choose the sign of thedifference betweenISA conditions by

clicking the rightticking box.

Select Total AirTemperature source :

Automatic selection, orforce pilot side (TAT1)or F/O side (TAT2)

2.4 System Operation

2.4.1 Air Data Function Control

C O N T R O L O F A I R T E M P E R A T U R E S O U R C E T H R O U G H T H E V C P

TAT is an essential input to an air data computer in order to enable computation of static airtemperature and hence true airspeed .

SAT is used in many calculations pertaining to flight planning , some of thembeing takeoff performance, density altitude, cruise performance and go-around performance.


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If required pressing the ADC reversionswitch will enable the CAPT or F/O todisplay data provided from theiropposite ADC.

The CAPT’s switch (Item A) haspriority over the F/O reversion switch.

C O N T R O L T H R O U G H T H E A D C R E V E R S I O N C O N T R O L P A N E L

In case of problem on one ADC, you can choose to inhibit it :

The ADC source is defined by the ADC reversion control switches

C O N T R O L T H R O U G H I C P

The Index Control Panels (ICP), one L/H CAPT and one R/H F/O

is linked to the PFD format and controls baro setting.

ADC 1 has beenforced to be the ADC in use for bothsides

ADC 1 has beenforced to be the ADC inuse for both sides

Baro setting knob on ICP :

Turn to change barometricpressure value of thereference altitude(QNH,QFE), displayed ininHg and Hpa


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Displayed in ft

In case of negative altitude, awhite “NEG” label is added inplace of the thousands digit fornegative values in the altitudereadout.

In case of displayed altitudediscrepancy CHECK ALT” flagis displayed.

Alt_gap (ft) = 60 (ft)+ (Hp1 +Hp2)/460 with Hp1, Hp2 :standard altitude in ftcomputed by ADC1 and

In the case of invalidbarometric altitude, a red

“ALT FAIL” label isdisplayed on the altitudevertical tape.

2.4.2 Air Data Display

Air Data set is displayed through different CDS interfaces. It is organized in format to provide acoherent set of information.

- Primary Flight Display (PFD) provides Air Speeds, Altitude, Vertical Air Speed.

- Multi-Function Display (MFD) True Air Speed along with Ground Speed.

- Engine and Warning display Total Air Temperature and Static Air Temperature

A L T I T U D E

Push to changepressure reference toStandard (1013 Hpa)

Reference is now Standard (ie 1013 Hpa),and target altitude is now displayed inFlight Levels


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You can also choose to display altitude in meters :

V E R T I C A L S P E E D : V S

Press to selectaltitude in

meters

VS pointer

VS scale, inthousands offt/min

VS target bug andreadout (in hundredsof ft/min)

VS readoutin hundredsof ft/min

In case ofinvalid verticalspeed, a red“VS FAIL” labelis displayed onthe speedvertical tape


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Total AirTemperature(measured)

Static AirTemperature(computed)

C A L I B R A T E D A I R S P E E D : C A S

T R U E A I R S P E E D : T A S

TAS is displayed on MFD/ND format & PFD format in normal conditions

In case of failure dashes will be displayed in the corresponding numerical readout.

S T A T I C A I R T E M P E R A T U R E – T O T A L A I R T E M P E R A T U R E

SAT and TAT is displayed on the EWD format in normal conditions

In case of failuredashes will bedisplayed in thecorrespondingnumerical

readout.

Airspeedindicator

Airspeed trendindicator (next 10 s)

In case ofdisplayed airspeeddiscrepancy (10kt)“CHECK IAS” flagwill be displayed.

In case of invalidaircraft computedspeed, a redIndicated Air SpeedFailed “IAS FAIL”label is displayed

True Air Speed

Ground speed iscomputed by FMSapplication

VMO warning indicator

VMO = min [250 kt ; 0.55 Mach]


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2.4.3 Air Data Function Alerts And Monitoring

S Y S T E M C A S M E S S A G E S

The crew is alerted of a failure via the Crew Alerting System (CAS).

CAS MessageLabel

Independentfailure case

Aural Signal PFD Visual

ADC ADC fault Single Chime

ADC 1+2 Both ADC fault Single Chime IAS,V/S,Alt Fail

IAS DISAGREE IAS disagree : 10 kt ofdiffercence between

ADC 1 and 2

Single Chime

ALT DISAGREE Altitude disagree : Alt_gap (ft) = 60 (ft)+(Hp1 + Hp2)/460 withHp1, Hp2 : standard

altitude in ft computedby ADC1 and

ADC2

Single Chime

S Y S T E M M O N I T O R I N G

ADC computer internal monitoring is performed automatically within the computation program throughself-tests :

- An automatic Power-On Self Test (POST) : detected failures are stored in the CentralizedMaintenance System (CMS)

- An automatic Continuous Built in Test (CBIT) and Initiated Built in Tests (IBIT) only if needed :will be performed in operational mode, detected failures are stored in the CentralizedMaintenance System (CMS).


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Removabe MemoryModule (RMM) tostore compensationparameters whichserve to correct themagnetic field lineinterference induced

Attitude & HeadingReference Unit (AHRU) which integrates theinertial components, theHeading, the Attitude andthe Vertical Speedcomputation section.

Flux Valve whichdetects the directionof the earth’smagnetic field linewith respect to theaircraft centerline(magneticheading).

3 INERTIAL DATA FUNCTION

3.1 General

The Inertial Data function is supported by the AHRS system, composed of :

The AHRS is a system which provides the crew and the autopilot with magnet ic heading ,

att i tude, l inear accelerat ion , angular rates and and B aroiner tia l Vzand Alt i tude required for flightcontrol and weather radar.

3.2 Compute And Provide Ahrs Data To Systems

The Inertial Data function computes and provide- Heading with respect to magnetic north- Pitch and Roll

- Linear accelerations along body axes (Jx, Jy, Jz)- Angular rates along body axes ( roll, pitch , yaw)- Baro-inertial altitude : ZBi - Baro-inertial vertical speed : VzBi


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DCA : Roll angle, Pitchangle and Heading aretransferred to WeatherRadar.

AFCA : Heading, RollPitch, the 3 angularates, the three

accelerations and theVzBi for Auto Pilotunction.

AL IGN / Maintenance : Aground is delivered via MCDU,from CMA to the computers tocommand alignment

CompensatedFlux Valve input

IAD : Roll, Pitch , VzBi, magneticheading, lateral acceleration fordisplay purpose

MCDU

ADC TAS and Baro Altitude arerespectively used by AHRU for Zbiand VzBi (consolidation ofanemometrical data)

1) Input signals

Each AHRU receives the following signals:

2) Output signals

Output data are transmitted to:


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For high pitch angles, small,medium, large red chevronsare respectively displayed

If roll or pitch angle is not valid,ATT FAIL is displayed insteadof the attitude sphere


3.3.1 Initialisation And Alignment

A L I G N M E N T O N T H E G R O U N D

On unit energization (energization of aircraft electrical network) the AHRU executes a 1 minutealignment phase. During this time, the aircraft must remain strictly immobile. Any aircraft movementmay retrigger this alignment phase.

Self-test mode (hardware tests, functional initialization) is performed before alignment just after power-up.

The AHRS has to be in operational mode within a max time of 90 seconds after power-up (on groundand in straight level flight), without any specific crew action.

I N - F L I G H T A L I G N M E N T

In case of total loss of primary and secondary AHRU power supplies, the aircraft stability constraints tobe maintained are such that it is difficult to perform in flight realignment

A C C U R A C Y O F D A T A

- Heading data: ± 1.5 degrees (included flux valve errors)- Pitch data: ± 0.5 degree

- Roll data: ± 0.5 degree

3.3.2 Data Display

A T T I T U D E

Aircraft mockup

Roll index


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L A T E R A L A C C E L E R A T I O N

H E A D I N G

Heading is displayed in the same way on PFD and ND format :

3.3.3 Flags And Alerts

M I S M A T C H F L A G S

Slip/ skid indicator : issituated under roll index

The slip/skid indicator moves left and right below the roll index according to lateralacceleration.

The maximum displacement from the null position is one and half time the length of theslip/skid indicator upper part, which corresponds to +/- 0.10g.

If the lateral acceleration is not valid, the slip/skid indicator is not displayed.

Static marker and aircraftsymbol

Rotatingheading dial

In case of invalid heading,“HDG FAIL” is displayed

“CHECK ATT” is displayed below thelateral acceleration indicator when adiscrepancy (3°) exists between pitchor roll data of AHRS 1 and AHRS 2.

The flag flashes during 9 seconds andbecomes steady afterwards

“CHECK HDG” is displayed below thelubber line when a discrepancy (8°)exists between heading data of AHRS 1

and AHRS 2.

The flag flashes during 9 seconds andbecomes steady afterwards


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A L E R T S : C R E W A L E R T I N G S Y S T E M M E S S A G E S

Alerts are displayed on the lower part of EWD.

CAS Message Label Independent failure case

AHRS AHRS 1 or 2 failure

AHRS 1+2 Both AHRS failure

AHRS NOT ALIGN AHRS not aligned

ATT DISAGREE Attitude disagree

HDG DISAGREE Heading disagree

M A N A G E A L E R T S T H R O U G H T H E A D C R E V E R S I O N C O N T R O L P A N E L

In case of problem on one AHRS, you can choose to inhibit it (see ADC reversion) :

AHRS 1 has beenforced to be the AHRS in use forboth sides


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4 STANDBY FLIGHT INFORMATION

4.1 General

The SNS is used by the flight crew in the event of loss of primary information from Air Data System,Inertial System, Radio Communication System or Radio Navigation System.

The Standby Flight Information function is supported by : – 1 Integrated Electronic Standby Instrument (IESI), – 3 standby probes (2 PS and 1 Pt) installed on the nose forward fuselage,

which provide the IESI with air data information, – one standby compass installed under the glareshield


4.2.1 Power-Up Sequence


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4.2.2 Standby Attitude

4.2.3 Standby Air Data

A I R S P E E D

A L T I T U D E

Pitch angle is given by bicolor tapemoving below a fixed Aircraftsymbol.

A triangular pointer moving on agraduated circular scale givesaircraft roll angle.

Excessive pitch angleRed chevrons pointedto horizon

Airspeed movingscale : graduationevery 10 kts

Airspeed pointer:3 digits drumNo numerical dis la if less than 30 kts

Altitude scale graduatedevery 100FtNumerical indication

every 500Ft

Black "N" letter on greenbackground indicatesnegative altitude


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When MACH number / Airspeed greaterthan MMO / VMO, MACH / IAS indicationturns red

B A R R O M E T R I C C O R R E C T I O N

4.2.4 Secondary Functions

1) Lateral Acceleration

2) VMO information

3) MACH number

Barometriccorrection values(inHg or Hp)

Barometric correction valueis modified by turningclockwise (increasing) orturning counterclockwise(decreasing ) the “BARO”knob.

Push to reset to standardvalue (1013.25 hPa and29.92 In.Hg) the barometriccorrection

Slip skid indicator

Airspeed valuesgreater than VMO

Mach number

To changeBaro units on

IESI, follow thissequence


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4.2.5 Failures Mode

IESI is not connected to the Flight warning System. It is a standalone equipment.

When the IESI monitoring function detects an internal failure which prevents information to bedisplayed on the IESI operational page, a flag is displayed allowing the flight crew to know whichfunction is lost.


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RadioManagement

1 GENERALS.................................................................................................................................................. 46

2 RAD IO MANAGEMENT ............................................................................................................................ 46

2.1 System Description ............................................................... ............................................................... 46

2.2 Control and Display ............................................................................................................................ 47 2.2.1 VCP / MCP : ................................................................................................................................. 47 2.2.2 Multi purpose control display unit (mcdu) : ............................................................... ................... 48 2.2.3 Integrated electronic standby instrument (IESI) : ................................................................ .......... 48

2.3 Normal Operation ............................................................................................................................... 50 2.3.1 Radio-communication tuning ........................................................................................................ 50 2.3.2 • Radio-navigation tuning sub-function : ...................................................................................... 51

2.3.3 • ATC/TCAS mode selection and control sub

-function : .............................................................. 52 2.4 Degraded Operation (Backup Means) ................................................................ ............................... 52

2.4.1 MCDU Backup ............................................................... ............................................................... 52

3 RAD IO COMUN ICAT ION .......................................................................................................................... 56

3.1 Voice Communication .......................................................... ............................................................... 56

3.2 Datalink ............................................................. ................................................................ ................... 56

4 CAS MESSAGES ............................................................... ................................................................. ......... 56

Ref : Thales’ user’s guide for the iesi PN : C16786VA02

DLM-900/CMU-900 Data Link Management and Communications Management Units Pilot's Guide (CPN 523-

0780471-101117)


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1 GENERALS

The Radio Management function provides pilots with a means to manage and tune radios (Radio

Communications and Radio Navigation) and external protection equipment (XPDR : Transponder,TCAS : Traffic Collision Avoidance System) during flight.

Management of Radio COM, Radio NAV and External Protection functions from the cockpit areperformed by two Radio Management Applications (RMAs).The RMAs check validity of input data andprovide feedbacks.

The tuning of RMA information is provided :

Firstly via Multifunction Control Panels (MCP) associated with the Virtual Control Panel (VCP)displayed on the Multi-Function Display (MFD).

Secondly via the Multipurpose Control Display Units (MCDU).

2 RADIO MANAGEMENT

2.1 System Description

The RMS (Radio Management System) is composed of two redundant RMAs and each RMAmanages its own side. However critical data are synchronized between the both RMA’s upon newcommand.

The RMAs (Radio Management Applications 1/2) are software applications hosted in Multi FunctionDisplay MFD1 (DU2) and MFD2 (DU4) that manage radio parameters (frequencies, modes…)through VCP and MCDU.

The flight crew interact with the RMA software via the VCP and the MCDU.

The RMA is redundant and each RMA is affected as follows :

- RMA1 (respectively RMA2) manages pilot interface with VCP1(resp VCP2) and MCDU 1 and2 for radio tuning and for ATC/TCAS control. For ATC/TCAS control, RMA1 provides deportedcommands to RMA 2 innominal conditions

- SYSTEM LOCATION

The two Radio Management Applications (RMA1 and RMA2) aresoftware hosted inside Multi FunctionDisplay MFD1 (DU2) and MFD2(DU4)

The tuning means are listed below :

MCP (Multi function ControlPanel)

VCP (Virtual Control Panel) MCDU (Multi purpose ControlDisplay Unit)


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2.2 Control and Display

The control of radio parameters sent to RMA and the display of radio feedback checked by RMA aredone via VCP and MCDU :

2.2.1 VCP / MCP :

VCP is a part of MFD (DUs 2 and 4). It is displayed on the bottom right of MFD (see CDS part).

The Multi Function Control Panel (MCP) provides the control of VCP. It permits to access to the VirtualControl Panel on the same side.

The VCP page is displayed by :

- Pressing “COM” button on MCP for radio-communication tuning,

- Pressing “NAV” button on MCP for Radio-navigation tuning,

- Pressing “SURV” button on MCP for TCAS/XPDR controls.

VHF is default pagewhen VCP COM isin action

VOR ILS is default page when VCPNAV is active

XPDR is default when

VCP SURV is active


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2.2.2 Multi purpose control display unit (mcdu) :

MCDU is a device used to tune several equipment.

To tune radio or TCAS/XPDR parameters, an RMS has to be

selected on the first menu page. Then Communication page isdisplayed with the possibility to select the radio-communication, Radio-navigation or TCAS/XPDR parametersto be tuned.

MCDU use for radio com/nav management and use will beexplained in the “degraded operation”, as it is the same innormal operation.

2.2.3 Integrated electronic standby instrument (IESI) :

The IESI belongs to Standby Navigation System (SNS, see IESI user guide and Primary referencespart).The SNS is used by the flight crew in the event of loss of primary information from Air Data System,Inertial System, Radio Communication System or Radio Navigation System.

The IESI equipment provides:

- Air Data Information: indicated air speed and altitude. IESI also provides baro-setting.- Inertial Information: Attitude parameters (Roll, Pitch and Lateral acceleration).

IESI is also interfaced with others systems in case of emergency mode for:

- Tuning and display of Radio Communication information from VHF1.- Tuning and display of Radio Navigation information from VOR/ ILS1.


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2.3 Normal Operation

The Radio Management System manages radio tuning for the following sub-functions :

2.3.1 Radio-communication tuning

Basic VHF-COM radios are tuned to providepilots with a means to communicate in voicewith the ground or another aircraft.

o Optional HF-COM radios (Single HF, DUAL) are tuned to provide pilots with a meansto communicate in voice with the ground or another aircraft, when VHF coverage ispoor or unavailable.

Use arrows key to select thefield you want inside the rightside of the VCP Use keyboard to

enter a frequency

Switch betweenSTBY and Activefrequency by pressingenter

Press enter tovalidate yourfrequency / choice

Press « COM » twiceto access HF 1

Press enter on + or – toincrease or decreasesquelch : 3 level available

Modulation mode, andemission power, to beselected via MCDU,VCP only displays

current status in green

VHF is default page forCOM


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2.3.2 • Radio-navigation tuning sub-function :

- VOR (VHF omnidirectional range) for bearing to the selected VOR ground station.

- IL S (instrument landing system) for the vertical (glide slope) and the horizontal (localizer)deviations to the ILS centerline.

- DME (distance measurement equipment) : dme provides pilots with distance information withthe selected beacon. DME is usually associated with a VOR station.

- ADF (automatic direction finder) for the relative bearing to the adf selected ground station.

- ND/ OVLY to display traffic/ weather/ navaid/ airport info on nd

TRAFFIC : Traffic advisory displayoption (see External protectionpart)

WX/ TERR : Weather terraindisplay option (see Externalprotection part)

Click the AUTO tick boxto active auto-tune ofVOR/ILS station (FMS)

Click DME HOLD to

hold a DME stationwhile another VOR isactive

Hear the morse code ofthe station, selection viaMCDU pages, seebelow.

Click the tick boxyou want to displayon ND, displaynavaid (vor,…) andairport.

VCP just displays currentstatus because ADF Toneis note a criticalparameters and iscontrolled by MCDU


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2.3.3 • ATC/TCAS mode selection and control sub-function :

- XPDR modes to provide aircraft parameters to the ground, and support the tcas function.

o

- TCAS to manage tcas mode

2.4 Degraded Operation (Backup Means)

2.4.1 MCDU Backup

NORMAL OPERATION THROUGH MCD IS THE SAME

On loss of one RMA (degraded scenario in flight), two AFDX links between VCPs and RMAsallow pilots to tune radios on their own VCPs with the RMA still available.

Moreover, the pilot can tune through his ow n side MCDU the RMA still available (both RMAsare connected to each MCDU).

Any parameter or control that is no more available or failed will be displayed in amber; the

label will depend on the source of the error.

Select thedesiredtransponder

Click to engage mode A

only (no altitudeinformation)

Enter XPDRcode withkeyboard

Click IDENT to make yourplane flash on ATC radarscreen

Display onlyTraffic Advisory

TCAS standby

TCAS choosewhat to display

Flight IDdisplay, FlightID has to beenteredthrough MCDU


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RMS 1 is pilotedby RMA 1, RMS2by RMA2

The default page isCOMMUNICATION, MCDUdisplays it after A/C powerup and the last valid page inanother case

The figure below explains the “communications” pages organization and utilization.


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To select theadjustable value

Adjustvalue of

selecteddata

Allowsvalidating newfrequency

IESI backup

Integrated Electronic Standby Instrument (IESI) provides pilots with a backup means to tune radios(only VHF COM1, VHF NAV1 (VOR1/ILS1/), DME1 and DME2 through VOR/ILS1 frequency inaddition to VCPs and MCDUs.

H O W T O T U N E A F R E Q U E N C Y

The SEL button shall be used to select the followingadjustable value:

- VHF frequency- ILS or VOR frequency - Course- Reference barometric pressure

R A D I O C O M M U N I C A T I O N D I S P L A Y :

THE RADIO COMMUNICATION

INDICATIONS FROM VHF1

ARE AUTOMATICALLY

DISPLAYED ON IESI AT

POWER ON.

The VHF1 transceiver is tuned inthe 118.00 to 136.975 MHzrange with 8.33 KHz spacing.

R A D I O N A V I G A T I O N D I S P L A Y

RADIO NAVIGATION INDICATIONS FROM ILS/VOR1 ARE NOT DISPLAYED ON IESI AT POWER

ON.

IN THE RANGE [108.00; 111.95] WITH A SPACING OF 50 KHZ:

- When the NAV frequency type is odd (e.g.: 109.55), the ILS mode is displayed,

- When the NAV frequency type is even (e.g.: 108.20), the VOR mode is displayed.

IN THE RANGE [111.95; 117.95] WITH A SPACING OF 50 KHZ:

- NAV frequency type is always VOR.


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ILS indications :

VOR indications :

Note:

IESI enables to tune the associated DME frequency via VOR/ILS tuning.

DME response (distance to the DME station) is not displayed on IESI but is displayed on each screenof PFD (lower part, left and right corners) and ND.

Furthermore, an audio signal (Morse) is sent to the Remote Control Audio Unit to provide in thecockpit an audio identification of the ground station.


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3 RADIO COMUNICATION

3.1 Voice Communication

Use your voice and speak into the microphone ( don’t sing please)

3.2 Datalink

ACARS (Aircraft Communication Addressing andReporting System) is a system that provides for thetransmission of digital data to and from aircraft via VDL, andSATCOM subnetworks. These messages, facilitate two-waycommunication for applications such as digital ATIS,

clearances, weather/turbulence reports, delay reports, andfree text messaging with airline Dispatch and Maintenance.

AVS applications include automated OOOI (Out-Off-On-In)reports, engine data reports, position reports, gateassignment uplinks, and connecting gate uplinks, just toname a few.

This equipement is provided by Rockwell Collins and isinterfaced through MCDU.

Datalink provid es the fol lowin g ATS (Air Traff ic Services)

- Automatic Terminal Information Services (ATIS),- Pre-Departure Clearance (PDC)- Oceanic Clearance (CC)- Flight Status Message (FSM) uplinks- Terminal Weather Information for pilots (TWIP)

Datal ink provid es the fo l lowing AOC (Air l ine Operat ing contro l)

- Free Text,- Engine Report- Maintenance Report- OOOI, … etc

4 CAS MESSAGES

Displayed on EWD in warning area

CONDITIONALERT MESSAGE

DISPLAYEDASSOCIATEDAURAL ALERT

If RMA1 or RMA2 is not healthy RMS 1 (or 2) SINGLE CHIME

If RMA1 and RMA2 are not healthy RMS 1+2 SINGLE CHIME

AOC Menu.

For more information on

datalink see the :User guide provided by R&C forDLM-900/CMU-900Data Link Management andCommunications ManagementUnits


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RadioNavigation

1 GENERALS.................................................................................................................................................. 58

2 MARKER SYSTEM ........................................................... ................................................................. ......... 59

2.1 General Description ............................................................................................................................ 59

2.2 Marker System Opération .............................................................. .................................................... 59 2.2.1 Marker control on mcdu ............................................................ .................................................... 59 2.2.2 Marker Display And Indicating ............................................................ ......................................... 60

3 VOR SYSTEM ................................................................................................................ .............................. 61


3.2 Vor System Operation ........................................................................................................................ 61

3.2.1 General operation .......................................................................................................................... 61 3.2.2 Vor control .................................................................................................................................... 61 3.2.3 Vor display on HSI and ND .......................................................................................................... 63 3.2.4 Vor Alerts ............................................................ ................................................................. ......... 64

4 I LS SYSTEM ............................................................. ................................................................ ................... 65


4.2 ILS System Operation .......................................................... ............................................................... 65 4.2.1 ILS control .................................................................................................................................... 65 4.2.2 ILS display .................................................................................................................................... 66 4.2.3 ILS Alerts ............................................................ ................................................................. ......... 66

5 ADF SYSTEM ........................................................... ................................................................ ................... 66


5.2 ADF System Operation ........................................................ ............................................................... 67 5.2.1 ADF control .................................................................................................................................. 67 5.2.2 ADF Display On HSI And ND...................................................................................................... 68 5.2.3 ADF alerts ..................................................................................................................................... 69

6 DME SYSTEM .......................................................... ................................................................ ................... 70


6.2 DME system operation........................................................................................................................ 70 6.2.1 DME Control ....................................................... ................................................................. ......... 70 6.2.2 DME display on HSI and PFD ............................................................. ......................................... 71 6.2.3 DME alerts .................................................................................................................................... 72 6.2.4 DME CAS messages ...................................................... ............................................................... 72


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1 GENERALS

In operational mode, the Radio Navigation function (VOR, ILS, ADF, DME, Marker) provides the crewand the avionics with position information relative to ground station to follow standard arrival orstandard departure and to navigate on route.

This system includes :

- The VHF Omnidirectional Range (VOR1 and VOR2) for bearing to theselected VOR ground station. VORhelps to the navigation in flight, or inapproach.

- The Instrument Landing System

(ILS1 and ILS2) for the vertical (GlideSlope) and the horizontal (LOC)deviations to the ILS centerline.

- The Marker system to confirm theposition on the centerline of therunway.

- The Automatic Direction Finder (ADF1 and ADF2) for the relative bearing to the ADFselected ground station.

- The Distance Measuring Equipment for the slant distance to the ground station usuallypaired to the selected VOR. DME provides pilots with distance information with the selected

beacon.

R A D I O M A N A G E M E N T A P P L I C A T I O N S ( R M A )

In normal condition, RMA is managing MCDU interface as follows:

RMA1 → MCDU1 or MCDU2 depending on Pilot/Co-Pilot selectionRMA2 → MCDU1 or MCDU2 depending on Pilot/Co-Pilot selection

Pilots have to select the RMA they want to use on the first menu page.


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HI (Default position) : receiver sensitivity is

increased so that beacons can be detectedat high altitude.

LO: normal position in approach

2 MARKER SYSTEM

2.1 General Description

The MARKER beacon system is a radio navigation aid used together with the ILS during theapproach. It provides distance marking with respect to the runway threshold.

During approach three distinct beacons give A/C position:

- Outer marker ispositioned at 7Km ofrunway begin activateOuter symbol and anaudio signal at 400Hz;

- Middle marker is

positioned at 2Km ofrunway begin activateMiddle symbol and anaudio signal at 1300Hz;

- Inner Marker ispositioned at 100m ofrunway begin activateInner symbol and anaudio signal at 3000Hz.

2.2 Marker System Opération

2.2.1 Marker control on mcdu

A switch, available through the NAV1 for marker 1 and NAV2 for marker 2 pages on both MCDU1and MCDU2, enables receiver sensitivity to be selected.


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2.2.2 Marker Display And Indicating

M A R K E R D I S P L A Y O N T H E P F D

The MARKER symbols (MARKER Beacon Annunciator) are displayed at the bottom right corner of the

PFD as follow :

M A R K E R A L E R T S O N M C D U

“Fail status” : Equipment return is different than command

MARKER beacon

Annunciator


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ACTIVE : this field is used totune and display the activeVOR / ILS frequency

STBY : this field includesthe standby frequency

3 VOR SYSTEM


The VHF Omnidirectional Range system isa Radio Navigation aid, which providesaircraft position regarding to a VORground station. It also provides lateraldeviation between the course selected bythe crew and the actual course the aircraftis flying.

The VOR funct ion o perates over

the ran ge 108 and 117.95 MHz

3.2 Vor System Operation

3.2.1 General operation

To “recognize” the ground stations, theVOR receiver must be “tuned” on groundstations specific frequencies. Tuning and selection course can be made by 2 different means :automatic tuning (auto-tuning) and manual tuning.

A U T O T U N I N G ( D E F A U L T T U N I N G C ON T R O L L E D B Y F M S )

The pilot select, through the Virtual Control Panel or MCDU interface, Autotuning mode for VORfunction. See FMS part for more informations.

M A N U A L L Y T U N I N G

It is manually possible to tune VOR frequency on the V/ILS widgets of the Virtual Control Panel (VCP)by using of the Multi Control Panel (MCP) or on the NAV page on the MCDU.

3.2.2 Vor control

V O R C O N T R O L O N V I R T U A L C O N T R O L P A N E L ( V C P )

VCP allow to tune VOR frequencies and to set Tune Mode


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EFCPs (EFCP-L or EFCP-R) allow toselect bearing source of data and itdisplaying (BRG1 for VOR 1 and/orBRG2 for VOR 2 data selection)

STBY : this field displays thestandby frequency

ACTIVE : this field is used totune and display the activeVOR/ILS frequency

ON FGCP Radio NavigationData source is selectable

through rotary switch.

Information is displayedaccordingly to the selection.

V O R C O N T R O L O N M U L T I - P U R P O S E C O N T R O L A N D D I S P L A Y U N I T ( M C D U )

V O R C O N T R O L O N F G C P A N D O N E F I S C O N T R O L P A N E L S


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3.2.3 Vor display on HSI and ND

Radio-navigationfrequency/FMS ident

DME/FMS distance

Navigation source annunciation

Selectedcourse/desired tracknumeric value

Hold mode

Selected course/desired trackpointer

Course/desired track

TO/FROM pointer

ND Display in Rose mode


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3.2.4 Vor Alerts

O N V C P

O N M C D U


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R E F : C L A / 1 1 / 0 0 4 8 2 0 A T R 6 0 0 S E R I E S T H A L E S A V S

65

4 ILS SYSTEM


The Instrument Landing System (ILS) enables measurement of : Angular deviation between aircraft flight path and glide slope (GS) (3°inclination) Angular deviation between aircraft flight path and runway alignment plane (localizer)

The glide slope transmitter operates on a frequency of 329.150 to 335.000 MHz.

The localizer transmitter operates at frequencies of 108.1 to 111.95 MHz.The ILS receiver function (LOC part) shall use a channel spacing of 50 kHz minimum

Dif ference with VOR system is do ne only by the frequency, which is odd for ILS and even for

VOR .

4.2 ILS System Operation

4.2.1 ILS control

ILS control is the same as VOR operating protocole, see this part au-dessus for more informations


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4.2.2 ILS display

4.2.3 ILS Alerts

ILS alerts are the same as VOR alert, take a look at this part au-dessus .

5 ADF SYSTEM


The ADF is a radio navigation aid which provides therelative bearing between the aircraft centerline and thedirection of a selected ground station.

Aircrafts can be equipped either with one ADF or two.

ADF Bearing pointer symbols and reminders aredisplayed on both PFD compass (HSI) and NavigationDisplay. Green is the color associated to the ADFindications (white is for the VOR indications).

The ADF functio n operates over the range 190 to

1750.5 kHz and 2181.0 to 2183.0 kHz (ADF

emergency range) with a channel sp acing of 0,5

kHz.

ILS informations arethe same as VORinformations

Excessive deviation

Normaloperations

Invaliddeviation : lossof deviationindication


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ACTIVE : this field is used to tuneand display the active ADFfrequency

STBY : this field is includes thestandby frequency

ACTIVE : this field is used totune and display the ADFfrequency

Tune Mode : this field allowssetting, modifications anddisplay of the ADF/ANTmode selection


5.2 ADF System Operation

5.2.1 ADF control

A D F C O N T R O L O N V I R T U A L C O N T R O L P A N E L ( V C P )

A D F C O N T R O L O N M U L T I - P U R P O S E C O N T R O L A N D D I S P L A Y U N I T ( M C D U )

A D F C O N T R O L O N E F I S C O N T R O L P A N E L S ( E F C P - L , E F C P - R )

ADF is controlled by EFIS CP the same way VOR is, so take a look at this part au-dessus.


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ND display in ARC mode

First bearing pointerindication : ADFpointer

First bearing pointerindication : ADFpointer

Second bearingpointer indication :VOR pointer

Second bearingpointer indication :VOR pointer

5.2.2 ADF Display On HSI And ND

In case of loss of RF input signal due tomask or excessive distance from the NDB,the pointer is not displayed.

If any installed HF system is transmitting,the pointer position is frozen to its lastposition then removed to prevent fromerroneous bearing display due to HFinterferences.


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5.2.3 ADF alerts

A D F A L E R T S O N V C P

O N M C D U


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DME HOLD : This fieldenables to HOLDDME currentfrequency while using anotherVOR frequency (used inapproach procedures)

DME HOLD : This fieldenables to HOLDDMEcurrent frequency whileusing another VORfrequency (used inapproach procedures)


6 DME SYSTEM


The Distance Measuring Equipment (DME) providesa slant range distance from an aircraft to aselected ground station.The aircraft is basically equipped with DME1 and anoptional DME2

The DME signals are processed and conditioned toprovide the crew with:

- A digital readout of the slant distance of theaircraft from a selected ground station.

- Associated ground station frequencyDME frequencies are tuned w ith VOR/ILS receiver, as DME frequenc ies are paired w ith the VOR

/ ILS ones .

6.2 DME system operation

6.2.1 DME ControlC O N T R O L T H R O U G H V C P

C O N T R O L T H R O U G H M C D U


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DME Distance information : the distance value is displayed in gree in Nautical Miles (NM) : Itcorresponds on DU2 ND to Captain frequency and on DU 4 ND to F/O frequency, when associatedVOR is selected as Bearing display.

HOLD infos : When HOLD mode selected, a Cyan H is displayed

6.2.2 DME display on HSI and PFD

DME Distance

DME Distance information : the distance value is displayed in gree in Nautical Miles (NM) : It

corresponds on DU1 HSI to Captain frequency and on DU 5 HSI to F/O frequency, whenassociated VOR is selected as Bearing display.HOLD infos : When HOLD mode selected, a Cyan H is displayed

To note that with ADF displayed, no DME info is shown


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6.2.3 DME alerts

O N V C P

O N M C D U

6.2.4 DME CAS

messagesCONDITION CAS MESSAGE

DME 1 loss or DME 2 loss in caseDME 2 is embedded

SINGLE DME

DME 1 loss in case DME 2 notembeded

DME LOSS

DME 1 + DME 2 loss DME LOSS

DME tuned frequency is not thesame that has been entered


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Aircraft SystemParameters

1 GENERALS.................................................................................................................................................. 74

2 DI SPLAY AI RCRAF T SYSTEMS PAGES ................................................................................................. 74

2.1 Electrical AC/DC system page ........................................................................................................... 75

2.2 CABIN system page ............................................................................................................................ 76

2.3 Hydraulic / ACW format system page .............................................................................................. 78

2.4 Engine secondary system page ....................................................... .................................................... 79

3 DI SPLAY ENGINE PRIMARY INFORMATIONS ................................................................................... 81

4 DI SPLAY BASIC AI RCRAFT STATUS ..................................................................................................... 82

4.1 Flight Control and emergency break indications .......................................................... ................... 82 4.2 Permanent data and fuel system informations .............................................................. ................... 83

4.3 Temporary selections – Memo panel ........................................................ ......................................... 84

5 AI RCRAFT MAI NTENANCE PAGES ....................................................................................................... 85

5.1 Engine Run up pages .......................................................................................................................... 85


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Press several times todisplay the desired A/Csystem page on MFD

MFC

MPC

AVSCACs

DisplayUnits

FCU (FuelControl Unit)

EEC En ine

A/C sensors signals (discreteand analogic)1 GENERALS

The AVS A/C system parameters function mainly provides to the crew monitoring capacity offollowing aircraft systems:

- Engines- Flight controls- Fuel systems- Hydraulic systems- Alternate network (ACW)- AC/DC electrical systems- Cabin systems

For maintenance purpose A/C system parameters function provides also capacity to monitor enginerun-up operation.

A memo panel that provides crew with reminders and status of device activation is also accessible.

2 DISPLAY AIRCRAFT SYSTEMS PAGES

Display A/C systems page function is in charge of acquisition of A/C systems parameters inorder to provide to the flight crew synthetic view of main systems status through MFD format whichis composed of four pages:

- One for engines secondary informations (primary data are displayed on EWD format) and fuelsystems information

- One for A/C cabin systems informations- One for ACW electrical system informations and hydraulic systems informations- One for AC and DC electrical systems informations

COLOR CODE : STATUS

GREEN Normal operation

AMBER System in fault CAUTION

RED System in fault WARNING

CYAN Set by the crewWHITE Titles or system Off

YELLOW Transitory state


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2.1 Electrical AC/DC system page

- GENERAL LAYOUT

ELECTRIC system page providse the crew with thefollowing information :

- AC/DC SYSTEM STATUS

- BA TTERIES STATUS

DCBUS 1

DC EmergencyBus

DC Standby Bus

DC ServiceBus

DCBUS 2

DC Bus TieContactor

DC Essential Bus

External powerUsually Blue DC Generator 1 DC Generator 2

DC UtilityBus 1

DC UtilityBus 2

UNDV messageOverride message

Transformer RectifierUnit

ConnectionStatus :Green : OK,Black : noconnection

A/C Bus 1 or

A/C standbybus

EmergencyBattery

Mainbattery

Emergencybatterycharger

Main batterycharger

Override

Main batteryabnormaldischarge

DC HotEmergencybus voltage

DC Hot Mainbus voltage

AC/DC Systems with batteriesconnected and generators Off.Inverter 1 is on (inverters transform thedirect current into alternating current.)


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Abnormal status : valve closed but shouldbe open

Normal status : valve closed, engine off

Normal status : valve open, engine on

Abnormal status :valve status invalid

Abnormal status : valveopen, should be closed

and engine off

Abnormalstatus : valveopen, should beclosed andengine on

2.2 CABIN system page

- GENERAL LAYOUT

- AIRFLOW STATUS

Airflow starts with engineignition.

Airflow Status, Doorsstatus and miscellaneousindicators

Pressure and altitudePanel


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Alt < 6800 ft

6800 ft


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2.3 Hydraulic / ACW format system page

- GENERAL LAYOUT

The HYD-ACW format presents the main basicinformation concerning the hydraulic systems.It is composed of two parts:

- The lower par t describes the currentstate of the power supply of thehydraulic system

- The upper par t gives information on thedifferent elements of the hydraulicsystem or on elements connected to it.

- ELECTRIC PART (lower)

This part is located at thebottom of the Hydraulic page andrepresents the power supply of the

hydraulic system.

The following configurationis not an operational one but will beuseful to define the differentsymbols of this part and theconnections (Wx) between them.

HYD-ACW in nominalconfiguration (with ExternalPower ON)


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- HYDRAULICPART (upp er)

- DUCTS

Different ducts represent thehydraulic circuit.

The following examplecorresponds to an operationalconfiguration

2.4 Engine secondary system page

- GENERAL LAYOUT

The ENGINE format presents the main basic informationconcerning the engine systems.It is composed of four parts:

- The oil informations at the top, on each side of engineinformations,

- The engine information system, between oil informations,- The fuel flow informations , below the engine in

Documents

ATR Pilots Guide 1-3