chapter 12 --- flight instruments - smartcockpit...pilot’s and copilot’s instrument panels...

12--00--1Vol. 1

REV 56, Jan 31/03FLIGHT INSTRUMENTS

Table of Contents

Flight Crew Operating ManualCSP A--013

MASTER

CHAPTER 12 --- FLIGHT INSTRUMENTS

Page

TABLE OF CONTENTS 12--00Table of Contents 12--00--1

INTRODUCTION 12--10Introduction 12--10--1

ELECTRONIC FLIGHT INSTRUMENT SYSTEM 12--20Electronic Flight Instrument System 12--20--1

Display Reversion 12--20--1Display Control 12--20--6Comparator Function 12--20--11System Circuit Breakers 12--20--11

AIR DATA SYSTEM 12--30Air Data System 12--30--1

Pitot Static System 12--30--1Air Data 12--30--3Air Data Reference Panels 12--30--4Altitude Alerts 12--30--11Acquisition Mode 12--30--13Cross Side Tracking 12--30--13Deviation Mode 12--30--13Air Data Reversion 12--30--13System Circuit Breakers 12--30--18

RADIO ALTIMETER SYSTEM 12--40Radio Altimeter System 12--40--1

System Circuit Breakers 12--40--5

ATTITUDE AND HEADING REFERENCE SYSTEM 12--50Attitude and Heading Reference System 12--50--1

Display Reversion 12--50--7Initialization and Alignment 12--50--11System Circuit Breakers 12--50--15

STANDBY INSTRUMENTS AND CLOCKS 12--60Standby Instruments and Clocks 12--60--1

Standby Attitude Indicator 12--60--1Standby Altitude/Airspeed Indicator 12--60--1Integrated Standby Instrument 12--60--1Standby Magnetic Compass 12--60--7Clocks 12--60--9System Circuit Breakers 12--60--11

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Vol. 1 12--00--2FLIGHT INSTRUMENTS

Table of Contents

MASTERFlight Crew Operating ManualCSP A--013

HEAD--UP GUIDANCE SYSTEM 12--70Head--Up Guidance System 12--70--1

Combiner Symbology 12--70--2Output to PFD’s 12--70--18Audio Callouts 12--70--18Output to FDR 12--70--18Output to MDC 12--70--18Approach Monitor for Category II Operations 12--70--19Approach Monitor for Category III Operations 12--70--19System Test/Fault Codes 12--70--19HGS Mode Selections/Indications 12--70--19System Circuit Breakers 12--70--63

LIST OF ILLUSTRATIONS

ELECTRONIC FLIGHT INSTRUMENT SYSTEMFigure 12--20--1 Electronic Flight Instrument System (EFIS) 12--20--2Figure 12--20--2 EFIS Interface -- Block Schematic 12--20--3Figure 12--20--3 Display Selection 12--20--4Figure 12--20--4 Primary Flight Display and Multifunction Display 12--20--5Figure 12--20--5 Display Control and Source Selector Panels 12--20--7Figure 12--20--6 Display Control Source Indications 12--20--8Figure 12--20--7 Display Control Source Flags 12--20--9Figure 12--20--8 EFIS Abnormal Indications 12--20--10

AIR DATA SYSTEMFigure 12--30--1 Pitot Static System -- General 12--30--2Figure 12--30--2 Air Data System 12--30--5Figure 12--30--3 Pitot Static System 12--30--6Figure 12--30--4 Air Data Reference Control Panel 12--30--7Figure 12--30--5 Indicated Airspeed and Mach Indications 12--30--8Figure 12--30--6 Indicated Airspeed Flag -- Primary Flight Director 12--30--9Figure 12--30--7 Altitude Indications 12--30--10Figure 12--30--8 Altitude Alerts 12--30--12Figure 12--30--9 Minimum Descent Altitude Indications 12--30--14Figure 12--30--10 Vertical Speed Indication and Flag 12--30--15Figure 12--30--11 Source Selector -- Air Data Panel 12--30--16Figure 12--30--12 Air Data Flags -- Primary Flight Display 12--30--17

RADIO ALTIMETER SYSTEMFigure 12--40--1 Radio Altimeter System 12--40--2

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Table of Contents


MASTER

Figure 12--40--2 Air Data Reference Control Panel 12--40--3Figure 12--40--3 Radio Altimeter Indication 12--40--4

INERTIAL REFERENCE SYSTEMFigure 12--50--1 Attitude Heading Reference Sysytem/Inertial

Refence System Interface 12--50--3Figure 12--50--2 Compass Control Panel/Inertial Reference

System Mode Select Unit 12--50--4Figure 12--50--3 Attitude Director Indications 12--50--5Figure 12--50--4 Selected Heading Readout 12--50--6Figure 12--50--5 Source Selector Panel 12--50--8Figure 12--50--6 Attitude and Heading Source Selection 12--50--9Figure 12--50--7 Attitude/Heading Source Failure Indications 12--50--10Figure 12--50--8 Attitude/Heading Source

Alignment Indications 12--50--12

STANDBY INSTRUMENTS AND CLOCKSFigure 12--60--1 Standby Attitude Indicator 12--60--2Figure 12--60--2 Standby Altitude/Airspeed Indicator 12--60--3Figure 12--60--3 Integrated Standby Instrument 12--60--4Figure 12--60--4 Integrated Standby Instrument Scales 12--60--5Figure 12--60--5 Integrated Standby Instrument Flags 12--60--6Figure 12--60--6 Standby Magnetic Compass 12--60--8Figure 12--60--7 Airplanes 7002 to 7672,

Clock Display 12--60--10Figure 12--60--8 Airplanes 7673 and Subsequent,

Clock Display 12--60--11

HEAD--UP GUIDANCE SYSTEMFigure 12--70--1 HGS System 12--70--6Figure 12--70--2 Head--Up Guidance System Sunvisor 12--70--7Figure 12--70--3 Head--Up Guidance System 12--70--8Figure 12--70--4 HGS Control Panel 12--70--10Figure 12--70--5 Airplanes equipped with the (--503) HGS Computer

HGS Control Panel 12--70--11Figure 12--70--6 Head--Up Guidance System -- Test Mode Selections 12--70--12Figure 12--70--7 HGS System -- EICAS Messages 12--70--20Figure 12--70--8 Primary Mode -- Radio Altitude Indications 12--70--21Figure 12--70--9 HGS /AFCS Modes 12--70--22Figure 12--70--10 HGS Combiner -- General 12--70--24Figure 12--70--11 Primary Mode -- Airspeed Indications 12--70--25Figure 12--70--12 Primary Mode -- On Ground 12--70--28

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Figure 12--70--13 Visual Meteorolical Conditions (VMC)Model -- Approach and Landing 12--70--31

Figure 12--70--14 Flight Director (F/D) Model -- Approach and Landing 12--70--33Figure 12--70--15 Category I or II (AI or AII) Model Approach and Landing 12--70--35Figure 12--70--16 Category IIIa (AIII) Model Approach and Landing 12--70--37Figure 12--70--17 Rollout Mode 12--70--41Figure 12--70--18 Primary Mode -- Attitude Indications 12--70--42Figure 12--70--19 Primary Mode -- Heading Indications 12--70--45Figure 12--70--20 Primary Mode -- Course Indications 12--70--47Figure 12--70--21 Primary Mode -- Barometric Altitude Indications 12--70--49Figure 12--70--22 Primary Mode -- Radio Altitude Indications 12--70--51Figure 12--70--23 Primary Mode -- Vertical Speed Indications 12--70--52Figure 12--70--24 Primary Mode -- Navigation/Position Indications 12--70--53Figure 12--70--25 Primary Mode -- Flight Path Indications 12--70--58Figure 12--70--26 Primary Mode -- Environmental Indications 12--70--60Figure 12--70--27 Unusal Attitude Display 12--70--61Figure 12--70--28 Primary Mode -- Autopilot/Flight Director 12--70--62

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Introduction


MASTER

1. INTRODUCTION

Flight instruments include the electronic flight instrument systems, standby instruments andclocks. Data for the flight instruments is provided by an air data system, radio altimeter andattitude and heading reference system (AHRS). Flight instruments provide the followingbasic information to the flight crew:

Flight instruments include the electronic flight instrument systems, standby instruments andclocks. Data for the flight instruments is provided by an air data system, radio altimeter andinertial reference system (IRS). Flight instruments provide the following basic information tothe flight crew: <0025>

S Altitude (barometric/radio)

S True Airspeed

S Airspeed (MACH/KIAS)

S Temperature Data

S Airspeed Trend

S Airplane Attitude

S Vertical Speed

S Heading Information

S Overspeed Warning

S Navigation Information.

Electronic flight instruments consists of a primary flight display (PFD) and a multifunctionaldisplay (MFD) for each pilot. A standby attitude indicator and standby altitude/airspeedindicator are provided. An independent standby compass provides aircraft heading inrelation to magnetic north. An electronic clock provides the time source for the aircraftavionics equipment.

Electronic flight instruments consists of a primary flight display (PFD) and a multifunctionaldisplay (MFD) for each pilot. An integrated standby instrument (ISI) provides standbyattitude, altitude and airspeed information to the flight crew. An independent standbycompass provides aircraft heading in relation to magnetic north. An electronic clockprovides the time source for the aircraft avionics equipment. <0083>

Air data provided by a pitot-static system and a temperature probe provide the flightinstruments with speed, altitude and temperature data. The radio altimeter provides anaccurate measurement of height above terrain at low altitudes. The attitude and headingreference system (AHRS) provides attitude, heading, position, angular rate and linearacceleration information.

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Introduction


Air data provided by a pitot-static system and a temperature probe provide the flightinstruments with speed, altitude and temperature data. The radio altimeter provides anaccurate measurement of height above terrain at low altitudes. The inertial referencesystem (IRS) provides attitude, heading, position, angular rate and linear accelerationinformation. <0025>

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Electronic Flight Instrument System


MASTER

1. ELECTRONIC FLIGHT INSTRUMENT SYSTEM

All basic flight information is presented to the flight crew on Electronic Flight InstrumentSystem (EFIS) displays. Each pilot instrument panel contains a primary flight display (PFD)and a multifunctional display (MFD). All four displays are electronically identical to permittransfer of display data.

Each PFD is a digital CRT and has the primary function of pictorially showing aircraftattitude, altitude, airspeed, flight director commands and flight mode annunciations. Inputsto the PFD’s are from the selected AHRS and ADC’s. Commands are set on the flightcontrol panel, air data reference panel and display control panels.

Each PFD is a digital CRT and has the primary function of pictorially showing aircraftattitude, altitude, airspeed, flight director commands and flight mode annunciations. Inputsto the PFD’s are from the selected IRS and ADC’s. Commands are set on the flight controlpanel, air data reference panel and display control panels.<0025>

The PFD’s function as the following instruments:

S Attitude heading indicator (ADI)

S Horizontal situation indicator (HSI)

S Radio magnetic indicator (RMI)

S Radio altimeter indicator

S Airspeed indicator (Mach and IAS)

S Vertical speed indicator (VSI).

Each of the MFDs acts as a navigation system display and has a primary function ofshowing current heading (compass) and course information. The MFDs can also displaymoving map navigation pictorials, navigation sensor data, weather radar targets, and TCAStraffic (see Chapter 18). Cross side compass information and backup navigation informationcan be superimposed on either display. EICAS information can also be displayed on eitherMFD.

A. Display Reversion

Two display reversionary panels are installed in the flight compartment. One panel isinstalled on the pilot’s side panel and the other panel is installed on the copilot’s sidepanel. In the event of a PFD failure, all data normally displayed on it can be transferredto the adjacent MFD by turning the display selector knob on the respectivereversionary panel to the PFD position. The MFD information cannot be transferred tothe PFD. Selecting the EICAS position will initially display the EICAS status page onthe respective MFD. All the other EICAS pages are available for display on the MFD,through selections on the EICAS control panel.

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<0015>

<0083><0015> <0015>

EICAS Displays

Multifunction Display (MFD)

Primary Flight Display (PFD)

Multifunction Display (MFD)

Primary Flight Display (PFD)

MLGBAYOVHT

DISPLAY COOL

Standby Airspeed/Altitude/AttitudeIndicator

StandbyAltimeter/IndicatedAirspeed Indicator

Standby AttitudeIndicator

MLGBAYOVHT

DISPLAY COOL

Electronic Flight Instrument System (EFIS) <MST>Figure 12--20--1

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MASTER

EFIS Interface --- Block Schematic <MST>Figure 12---20---2

CRSI AP AP XFR SPEED APPR HDG NAV ALT VS DOWN CRS2

MFD 2 PFD 2PFD 1 MFD 1

<0025> <0025>

<0040> <0040>

MACH,AIRSPEED,VERTICALSPEED.

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Display SelectionFigure 12---20---3

Pilot’s Display Reversionary PanelPilot’s Side Panel

Copilot’s Display Reversionary PanelCopilot’s Side Panel

Used to change the pilot or copilot MFD display.PFD 1 or 2 -- MFD changes to a PFD

display and PFD display goes blank.

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MASTER

Primary Flight Display and Multifunction Display <MST>Figure 12---20---4

Horizontal SituationIndicator (HSI)

Barometric Altitude

Airspeed Indicator (IAS)

Navigation Source/ Course Display

Flight Director / AutopilotMode Annunciator

Attitude DirectorIndicator (ADI)

Vertical Speed Indicator

Radar Mode Line

Time / Temperature /Performance Line

Onside Course Display

Cross--Side Course Display

Bearing Pointer

Lateral Deviation Scale

Vertical Deviation Scale

Selected Heading Display

Course Pointer

Lateral Deviation Bar

Airplane Symbol

Bearing Pointer Source

Bearing Pointer Source

Multifunction Display -- HSI ModePilot’s and Copilot’s Instrument Panels

<0015>

Primary Flight DisplayPilot’s and Copilot’s Instrument Panels

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B. Display Control

Two display control panels are installed in the flight compartment. One panel is installedon the pilot’s side panel and the other panel is installed on the copilot’s side panel.Each panel provides the pilot and copilot control of their respective PFD and MFD.

The control selections are as follows:

S MFD format selection

S Bearing pointer selection

S Navigation source selection

S Cross side navigation data and course display.

The rotary FORMAT knob can be used to select one of the following navigation formats:

S HSI compass

S Navaid sector map

S TCAS

S FMS present position map

S FMS plan map

S Weather radar.

If one display control panel fails, the other panel can be used to control all fourelectronic flight displays. This is done by selecting the DSPL CONT knob, on theSource Selector Panel, to the 1 or 2 position as required.

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MASTER

Display Control and Source Selector Panels <MST>Figure 12---20---5

TFC (TCAS)Used to directly selectTCAS traffic display onMFD. Range selectionsare 5, 10, 20 and 40 NM.

RANGE -- Inner SelectorUsed to select range displayedon MFD. Range selections are:5, 10, 20, 40, 80, 160, 320 and640 NM.

FORMAT -- Outer SelectorUsed to select MFD format.Format selections areHSI compass, navaid sector,present position map (PPSN),plan map, TCAS and weatherradar.

RDRUsed to select weatherradar display.

BRGUsed to select nextwaypoint thatbearing pointer willindicate direction to.

NAV SOURCEUsed to select navigation source.Clockwise rotation will be FMS1,VOR/LOC1, OFF, VOR/LOC2 andFMS2.

Display Control PanelPilot’s and Copilot’s Side Panels

PUSH X--SIDEUsed to displayopposite sidenavigationalsource on MFD.

<0040>

RDR / TERRUsed to select weatherradar display, terraindisplay or both.

Source Selector PanelCenter Pedestal

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Display Control Source Indications <MST>Figure 12---20---6


<0015>


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MASTER

Display Control Source Flags <MST>Figure 12---20---7


<0015>


DCP, DCP 1 or DCP 2 Flag (red)Indicates that selected display controlpanel has failed.

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EFIS Abnormal Indications <MST>Figure 12---20---8

EFIS COMP INOP caution (amber)Indicates that comparator informationfor one or both PFDs is not available.

EFIS COMP MON caution (amber)Indicates that a comparatormiscompare has been detected.

Comparator Warnings (amber)Indicate that a comparatormiscompare has been detected.

<0015>


Primary Page

<0006>

<0039>

EFIS COMP INOPEFIS COMPMON

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MASTER

C. Comparator Function

A comparison of displayed data is performed by each PFD to ensure that the samedata is shown on both PFDs. Comparison of roll, pitch, heading, altitude and airspeedinformation is performed continuously. Comparison for radio altitude, flight directorpitch, ILS localizer and ILS glide slope are performed during precision landing. When amiscompare condition is detected, the miscompare indicator on both PFDs will flashamber for 5 seconds then come on steady, as long as the miscompare exists. An EFISCOMP MON caution message is also displayed on the EICAS primary page.

D. System Circuit Breakers

SYSTEM SUB--SYSTEM CB NAME BUS BAR CBPANEL

CBLOCATION

NOTES

Pilot’s FlightInstruments

PFD 1 D10Instruments

MFD 1DC ESS 4

D11

ElectronicFlightI t t

Control Panel EFIS CONTPNL 1

DC ESS 4C9

gInstruments

Copilot’s Flight PFD 2 K1Copilot s FlightInstruments MFD 2

DC BUS 2 2K2

Control Panel EFIS CONTDC BUS 2 2

K3Control Panel EFIS CONTPNL 2 K3

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THIS PAGE INTENTIONALLY LEFT BLANK

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Air Data System


MASTER

1. AIR DATA SYSTEM

Two air data computers (ADC 1 and ADC 2) provide the primary flight displays (PFD) with airdata consisting of airspeed, altitude and vertical speed. The ADCs also provide computedair data (speed, altitude and temperature data) to various aircraft avionics systems. TheADCs convert pitot and static air pressure to electrical signals. The ADCs use staticpressure to produce the altitude data and combine static and pitot pressure to produce theairspeed data. Resistance changes from a total air temperature (TAT) probe provide theADCs with temperature data. The system is controlled by the air data reference panels andhas warning and alert capabilities integrated with the EICAS. Selected speeds and altitudeare set using the flight control panel (refer to Chapter 3).

A. Pitot Static System

The pitot static system supplies pitot and static air pressures to the ADCs, the standbyaltitude/attitude/airspeed indicator and the cabin pressure control panel (CPCP). Thesystem consists of two pitot/static probes, an alternate pitot probe, alternate static portsand a total air temperature probe (TAT).

The pitot static system supplies pitot and static air pressures to the ADCs, theintegrated standby instrument (ISI) and the cabin pressure control panel (CPCP). Thesystem consists of two pitot/static probes, an alternate pitot probe, alternate static portsand a total air temperature probe (TAT).<0083>

The pilots and copilots pitot static probes each consist of a pitot mast (P1 and P2) andtwo static ports (S1 and S2). Pitot pressure from each probe is supplied to the sameside ADC. Static pressure from each probe is supplied to each ADC.

The alternate pitot probe (P3) supplies pressure inputs to the standbyaltitude/attitude/airspeed indicator.

The alternate pitot probe (P3) supplies pressure inputs to the integrated standbyinstrument (ISI).<0083>

Electric heating elements protect the pitot-static and TAT probes from icing (refer toChapter 15, Ice and Rain Protection).

NOTE

TAT probe readings are inaccurate when the aircraftis on the ground, due to probe heating to protect it fromicing. TAT probe readings cannot be used to obtainthe ambient static temperature before take-off.

Two Mach transducers supply primary Mach compensation data to the stall protectioncomputer. The transducers are connected to the left and right pitot static system andprovide a means of isolating a leaky transducer from the rest of the pitot static system.via the static source selectors. The selectors are controlled by mechanical selectors onthe pilot’s and copilot’s side consoles.

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Air Data System


Pitot Static System --- GeneralFigure 12---30---1

RIGHT PITOT--STATIC PROBE

LEFT PITOT--STATIC PROBE

ALTERNATE PITOT TUBE

TOTALAIR TEMPERATURE PROBE

ALTERNATE STATIC PORT

ALTERNATE STATIC PORT

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Air Data System


MASTER

B. Air Data

The air data system provides computed air data (speed, altitude and temperature)information to the following systems:

S Integrated avionics preocessor system (IAPS)

S Attitude and heading reference system (AHRS)

S Inertial reference system (IRS) <0025>

S Stall protection computer and flap ECU

S Air traffic control transponders and TCAS

S Flight control computers and flight director

S Electronic flight instrument system (EFIS) and engine indication and crew alertingsystem (EICAS) displays.

The air data system provides the following air data parameters:

S Pressure altitude and barometric--corrected altitude

S Vertical speed, indicated airspeed, Mach number and true airspeed (TAS)

S IAS reference (automatically through the AP control or manually through the air datareference panel)

S Static air temperature (SAT)

S Calibrated and indicated airspeed (CAS / IAS)

S Overspeed warning (present airspeed and Vmo)

S Total air temperature (TAT)

S Temperature variations from international standard atmosphere (ISA).

In addition to the above parameters, the air data system computes and controls thefollowing reference values and parameters:

S Preselect altitude

S Airspeed trend vector

S Maximum allowable speed (VMO)

S Maximum allowable Mach (MMO)

S Vertical speed references.

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Air Data System


C. Air Data Reference Panels

The air data reference panels (ARP) are located on the pilot’s and copilot’s side panels.Each ARP is used to enable selection of airspeed reference pointers and barometriccorrection for altitude.

Each ARP functions with the same-side ADC, display control panel, primary flightdisplay and multifunctional display. The ARP is divided into three sections:

S The speed references section is used to select and input changes to the varioustarget and speed settings (V1, VR, V2 and VT). Both PFDs will display the samevalues.

S The altitude references section is used to set minimum descent altitude (MDA) anddecision height (DH) values and to initiate radio altimeter self test.

S The barometric references section is used to select and input changes to the ADCbarometric pressure, to select indicating units (hPa or inHg) and to set standardbarometric pressure. Each PFD can have a different barometric pressure setting.The last value selected is retained in the ADC memory for the next power up.

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Air Data System


MASTER

Air Data System <MST>Figure 12---30---2

HEAD--UPGUIDANCESYSTEM

INTEGRATEDAVIONICS

PROCESSORSYSTEM AIR DATA

COMPUTER2 TOTAL

AIRTEMPERATURE

PITOT

STATIC

AIR TRAFFICCONTROL

TRANSPONDER1

AIR TRAFFICCONTROL

TRANSPONDER2

AIR DATACOMPUTER

1TOTALAIR

TEMPERATURE

ATTITUDEAND HEADING

AHRS 1 / IRS 1

PITOT

STATIC

COPILOT’S AIR DATAREFERENCE PANELFLIGHT CONTROL PANEL

PILOT’S AIR DATAREFERENCE PANEL

ATTITUDE/ACCELERATION

ATTITUDE/ACCELERATION

ATTITUDEAND HEADING

AHRS 2 / IRS 2

<0025><0025>

<0026>

ALTITUDE;MACH/AIRSPEED;VERTICAL SPEED(AHRS ONLY).


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Air Data System


Pitot Static SystemFigure 12---30---3

Mach Transducer 1 (Pilot’s Side)

Pilot’s Mach TransducerSource Selector /Isolation Valve

Mach Transducer 2 (Copilot’s Side)

Copilot’s Mach TransducerSource Selector /Isolation Valve

(Mach data to SPS Channel 1) (Mach Data to SPS Channel 2)

SELECTORVALVE CLOSED

MACHTRANSDUCER

PITOT

MACH

STATIC


TRANSDUCERSELECTOR

VALVE CLOSED

MACHTRANSDUCER

PITOT

MACH

STATIC


TRANSDUCERSTATIC

MACHTRANS

2

MACHTRANS

1

StandbyInstrument

WaterDrains

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Air Data System


MASTER

Air Data Reference Control PanelFigure 12---30---4

SELUsed to alternatelyselect V1, VR or V2to the edit fieldwhen VSPDS isselected.

PUSH / SET / OFFUsed to adjusts the selected speedreadout displayed on the edit field.When pushed, the selected speedreadout is displayed.When rotated, the selected speedreadout is adjusted.When pushed again, the selectedspeed readout is removed.

RA TESTUsed to initiateradio altitude test.

HPA / INUsed to alternatelyselect the barometricpressure to bedisplayed inhectoPascals orinches of mercury.

BAROUsed to adjustbarometric pressure.When pushed, thebarometric pressureis set to the standardvalue of 29.92 inHgor 1013 hPa.When rotated, thebarometric pressuresetting is adjusted.

BARO

MDADH

SPEED REFS

RATEST

HPA / IN

TGT VSPDS

SEL

Air Data Reference PanelPilot’s and Copilot’s

Side Panels

DH / MDAUsed to select decision height orminimum descent altitude.DH -- Decision height readout isselected to be adjusted.MDA -- Minimum descent altitudereadout is selected to be adjusted.

TGT / VSPDSUsed to select target or V speeds.TGT -- VT speed is selected tobe displayed on the edit field.VSPDS -- V1, VR and V2speeds are selected to bedisplayed on the edit field.Alternate selection of V1, VRand V2 is made using SEL.

PUSH / SET / OFFUsed to adjust selected altitude readout.When pushed, the selected altitude readout(DH or MDA) is displayed on the PFD.When rotated, the selected altitude readoutis adjusted (DH in 1--ft. increments, MDA in10--ft. increments).When pushed again, the selected altitudereadout is removed.

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Air Data System


Indicated Airspeed and Mach Indications <MST>Figure 12---30---5

IAS Bug (magenta)Indicates airspeed reference marker as setby pilot using the speed knob on flightcontrol panel.

Indicated Airspeed Tape (white)Moving tape that indicates current airspeed.Tape range is 40 to 400 knots with a displayof 80 knots.Marks at 5 knot increments.Digits at 20 knot increments.

Trend Vector (magenta)Indicates predicated airspeedwithin next 10 seconds.

Indicated Airspeed Pointer (white)Indicates current airspeed.

IAS /Mach Reference (magenta)Indicates airspeed as selectedusing the speed knob on flightcontrol panel.

Mach Readout (white)Indicates Mach speed.Displayed when Mach isabove 0.45 and is removedwhen Mach is below 0.40.

Overspeed Cue (red/black checkerboard)Assends from Vmo/Mmo to top of tapewindow to indicate maximum speed allowable.If speed is more than 3 kts greater than Vmoor equivalent Mmo, overspeed clacker sounds.Warning continues until speed is 3 kts belowVmo/Mmo.

Low Speed Cue (red/black checkerboard)Descends from stick shaker speed to edge oftape window and acts as cue to impendingstall speed. Displayed 3 seconds after lift--off.If AOA data fails, checkerboard stops at 100 kts.and is replaced by a yellow line up to 120 kts.

CLACKERTONE

Speed Reference Bugs (cyan)Removed 7.5 seconds after speedis exceeded (except target speed).1 Takeoff decision speed (V1)R Rotate airspeed (VR)2 Take--off safety speed (V2)T Target speed (VT)

Stall Speed Indicator (green line)Indicates 1.25 times the computed stall speed.Displayed in flight only.

2

120

180

160

140

T

R1

Airspeed Indicator

Speed Reference (cyan)Indicates reference speed as setby pilot using the speed referenceknob on air data reference panel.

Airspeed Indicator


<0015>

10

AP

10

<FAA>

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Air Data System


MASTER

Indicated Airspeed Flag --- Primary Flight Director <MST>Figure 12---30---6


IAS Flag (red)Indicates that airspeeddata has failed. Appearsin place of airspeed tape.

Speed Reference Table (cyan)Displayed on ground only.Indicates reference speeds as setusing speed reference knob on theair data reference panel.

IAS

VT 170

80

60

40

VR 136V2 142

V1 131

Airspeed Indicator

0

29.92 IN

5000

1 2 4

1 2 4

0.0

200

200

BRT

V2 142

S15

12

2124 W

3033

N

140 0 FT

100

000

100

ADF1ADF2

10

10

TOTO

FMSCRS 2394.2 NM

YUL

1

2

<0015>

10

10

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Air Data System


Altitude Indications <MST>Figure 12---30---7

Altitude Readout (white)Indicates airplane barometric altitude.

Preselect Altitude Bug (magenta)Lines at coarse and fine tapeindicate preselected altitude as setusing altitude knob on flight controlpanel.

Preselected Altitude Readout (magenta)Indicates preselected altitude to nearest 100 feet,as set using altitude knob on flight control panel.

Barometric Altitude Tape (white)Moving tape with fixed window(digital readout) that indicatesbarometric altitude from --1,000 to50,000 feet with a display of450 feet.

Fine TapeMarks at 20 foot increments.Digits at 100 foot increments.

Coarse TapeSmall rectangles at 500 footincrements.Large rectangles at 1000 footincrements.Altitude Indicator

2

800

900

000

100

200

Barometric Pressure Setting Readout (cyan)Indicates selected barometric pressure expressedin inches of mercury or hectoPascals, as set usingbarometric knob and on air data reference panel.

Altitude Indicator

METRIC ALTON -- Metric altitude readout and metricpreselected altitude readout are displayedon PFDs.OFF -- Metric altitude readout and metricpreselected altitude readout go out.

Metric Altimeter SwitchCenter Pedestal

METRICALTON

OFF

Metric Preselected Altitude Readout (magenta)Indicates preselected altitude in meters.Displayed when metric altimeter is selected on.

Metric Altitude Readout (white)Indicates airplane altitude in meters.Displayed when metric altimeter is selected on.

<0015>

10

AP

10

<0029>

<0023> Barometric pressure setting readout flashes when:Airplane climbs through 17,800 ft and barometricpressure setting is not set to standard value.Airplane descends through 18,500 ft andbarometric pressure setting is set to standard value.

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Air Data System


MASTER

D. Altitude Alerts

The altitude alert system alerts the flight crew that a preselected altitude has beenreached or a deviation from a preselected altitude has occurred. When the aircraft iscleared to change altitude, the preselected altitude is set on the PFD through the flightcontrol panel (FCP). There are three types of alerts that can occur:

S Acquisition mode

S Cross side tracking

S Deviation mode.

Pending Rectification

NOTE

An anomaly has been discovered in the ADCsoftware which causes the aural altitude alerter(C--Chord) not to cancel if an AFCS transfer ismadewhile the aural alert relay is energized. If thealtitude alerter does not cancel automatically after1 second because the AFCS transfer wasoperatedwhile the aural alert relaywasenergized,briefly switch the AFCS transfer back to theprevious setting. Once the aural altitude alertercancels the AFCS transfer may be reselected asrequired.

REV 56, Jan 31/03


Air Data System


Altitude Alerts <MST>Figure 12---30---8

Altitude Flag (red)Indicates altitude data has failed.Appears in place of altitude tape.

Altitude Indicator

700

800

900

000

100

NEG

Negative AltitudeFlag (yellow)Appears at altitudesless than 0 feet.

<0015>

12--30--13Vol. 1


Air Data System


MASTER

E. Acquisition Mode

Altitude alerts are inhibited in approach mode, when glideslope is captured and thereare valid autopilot steering commands. The ADC will set a one second acquisition alertwarning (altitude C-cord warning aural) and flash the preselected altitude readout whenthe present altitude is within ±1,000 feet of capturing the preselected altitude. Thereadout will stop flashing when the altitude is within ±200 feet of the preselectedaltitude. The alert can be cancelled by pressing the altitude knob on the flight controlpanel.

F. Cross Side Tracking

Each ADC compares the preselect altitude value from both computers for equality. Ifthe values are not equal, the preselect altitude digits on the display change frommagenta to cyan.

G. Deviation Mode

After the preselected altitude is captured, if the altitude deviates from the preselectedaltitude by more than ±200 feet, a deviation alert warning (aural “C” chord) will be setand the preselected altitude readout and bug will change from magenta to amber andbegin to flash. The readout and bug will return to normal once the altitude is backwithin deviation limits. A deviation alert will also be made if the airplane has gone withinthe acquisition limits on an altitude capture but then deviates by more than 100 feetfrom the preselected altitude.

H. Air Data Reversion

Normally, each ADC provides data to the same side PFD. If one ADC should fail, theother computer may be used to supply data to both PFDs. This is done by selecting theAIR DATA knob, to the 1 or 2 position, on the Source Selector Panel.

REV 56, Jan 31/03


Air Data System


Minimum Descent Altitude Indications <MST>Figure 12---30---9

Minimum Descent Altitude Alert (amber)Indicates that airplane has arrived atminimum descent altitude.

Minimum Descent Altitude Pointer (cyan)Indicates MDA, as set on the air datareference panel.Disappears when out of range.Flashes during MDA alert.

Minimum Descent Altitude Readout (cyan)Indicates MDA as set on the air datareference panel.

<0015>

12--30--15Vol. 1


Air Data System


MASTER

Vertical Speed Indication and Flag <MST>Figure 12---30---10

Vertical Speed Scale (white)Non--linear scale of vertical speed between4,000 feet per minute.Small ticks at 250 FPM.Large ticks at 500 FPM.Digits at 1,000, 2,000 and 4,000 FPM.

Vertical Speed Flag (red)Indicates that vertical speeddata has failed. Appears inplace of vertical speed scale,pointer and readout.

Vertical Speed Pointer (green)Indicates vertical speed in feet per minute.

Vertical Speed Readout (green)Indicates current vertical speedfrom 0 to 15,000 FPM.From 0 to 9,950 FPM, display is at 100 FPM.Above 9,950 FPM, display is at 1,000 FPM.If rate is greater than 10,000 FPM, decimalpoint disappears.

NOTEVertical speed pointer and readout turnred when a TCAS resolution advisoryis issued and speed is not withincorrective limits (refer to Chapter 18).

<0015>

REV 56, Jan 31/03


Air Data System


Source Selector --- Air Data PanelFigure 12---30---11


AIR DATANORM -- Each air data computersupplies data to the same side display.1 -- Air data computer 1 supplies datato both pilot and copilot displays.An amber source message isdisplayed on both PFDs.2 -- Air data computer 2 supplies datato both pilot and copilot displays.An amber source message isdisplayed on both PFDs.

12--30--17Vol. 1


Air Data System


MASTER

Air Data Flags --- Primary Flight Display <MST>Figure 12---30---12

ADC 1 or 2 (amber)Indicates that single air data computersource has been selected.ADC 1 -- Air data computer 1 selected.ADC 2 -- Air data computer 2 selected.

ADC 2<0015>

REV 56, Jan 31/03


Air Data System


I. System Circuit Breakers


CBLOCATION

NOTES

Air Data ADC 1 DC ESS 4 D3

Flight DataAir DataComputer ADC STBY DC BAT 1 P8g

ADC 2 DC BUS 2 2 H6

12--40--1Vol. 1

REV 56, Jan 31/03FLIGHT INSTRUMENTSRadio Altimeter System


MASTER

1. RADIO ALTIMETER SYSTEM

The radio altimeter (RADALT) system provides an accurate measurement of absolutealtitude (height above terrain) from 0 to 2500 feet AGL. Radio altitude information issupplied to the following:

There are two radio altimeter (RADALT) systems installed on the aircraft. Each systemprovides an accurate measurement of absolute altitude (height above terrain) from 0 to 2500feet AGL. Radio altitude information is supplied from both radio altimeters to the following:<0045>

S PFD’s

S Flight control systems

S Ground proximity warning system (GPWS)

S Enhanced ground proximity warning system (EGPWS) <0040>

S Traffic alert and collision avoidance (TCAS).

The radio altimeter provides the pilot’s and copilot’s PFDs with the following:

S Radio altitude readout

S Decision height readout

S Decision height alerts and radio altimeter fail flags.

When a failure is detected during flight, a red warning flag is displayed on the PFD’s.

The radio altitude display is displayed as both a digital and a moving tape readout. Thedigital readout appears as the aircraft descends through 2,500 feet. The tape is an analogscale that is displayed when the airplane is below an altitude of 1,225 feet.

Decision height is set (from 0 to 999 feet) using either pilot’s air data reference panel. A testbutton is provided on the air data reference panel to verify the operation of the radioaltimeter system.

REV 56, Jan 31/03

Vol. 1 12--40--2FLIGHT INSTRUMENTSRadio Altimeter System


Radio Altimeter System <MST>Figure 12---40---1


<0040><0040> <0040>

12--40--3Vol. 1



MASTER

Air Data Reference Control PanelFigure 12---40---2

RA TESTUsed to initiateradio altitude test.

BARO

MDADH

SPEED REFS

RATEST

HPA / IN

TGT VSPDS

SEL

Air Data Reference PanelPilot’s and Copilot’s Side Panels

DH / MDAUsed to select decision height orminimum descent altitude.DH -- Decision height readout isselected to be adjusted.MDA -- Minimum descent altitudereadout is selected to be adjusted.

PUSH / SET / OFFUsed to adjust selected altitude readout.When pushed, the selected altitude readout(DH or MDA) is displayed on the PFD.When rotated, the selected altitude readoutis adjusted (DH in 1 ft increments, MDA in10 ft increments).When pushed again, the selected altitudereadout is removed.

REV 56, Jan 31/03



Radio Altimeter Indication <MST>Figure 12---40---3


Radio Altimeter

DECISIONHEIGHT

Ground Bar (amber)Indicates terrain.

RA Flag (red)Indicates that radio altitude data has failed.Appears in place of radio altitude readout.

2

3

1


Decision Height Readout (cyan)Indicates selected decision height as set on theair data reference panel (range is 0 to 999 feet).Red dashes indicate failed input.

<0015>

not included in <JAA>

Decision Height Pointer (cyan)Indicates selected decision height asset on the air data reference panel.Disappears when out of range.

Radio Altitude Readout (green)Indicates radio altitude from 0 to 2,500 feet.At decision height, readout turns amber.Displayed upon descent below 2,500 feet RA.

Decision Height Alert (amber)Indicates that airplane has arrived at decision height.During go--around, alert is disabledat decision height +100 feet.Alerts inhibited below 5 feet.

Radio AltimeterIndicates current radio altitude.Displayed upon descent below 1,225 feet RA.

12--40--5Vol. 1



MASTER

A. System Circuit Breakers


CBLOCATION

NOTES

Radio AltimeterRAD ALT 1 DC BUS 1 1 K7Radio

Altimeter AltimeterRAD ALT 2 DC BUS 2 2 L1 <0045>

REV 56, Jan 31/03




12--50--1Vol. 1


Attitude and Heading Reference System


MASTER

1. ATTITUDE AND HEADING REFERENCE SYSTEM

The attitude and heading reference system (AHRS) is a gyro reference system thatgenerates angular rate and linear acceleration information about the aircraft axis.

The AHRS is a dual system with two independent attitude and heading computers. Eachcomputer receives corrected heading information from an individual flux detector whichsense the earth’s magnetic field. Each computer also receives information from the sameside air data system. This information, together with accelerometer sensor data, isprocessed and sent to the integrated avionics processor system which interfaces with theflight control computers and flight management computers.

These signals are also routed to the TCAS, GPWS, weather radar, fuel system, stallprotection system, flight data recorder and data concentrator units.

These signals are also routed to the TCAS, EGPWS, weather radar, fuel system, stallprotection system, flight data recorder and data concentrator units. <0040>

AHRS provides attitude and heading information to the electronic flight instruments. ThePFD’s display AHRS alignment flags during initialization (30 to 70 seconds). If aircraftprimary power is lost, the AHRS will continue to operate on battery bus power for 11minutes. Attitude is displayed on the attitude direction indicator (ADI) of the primary flightdisplays and heading is displayed on the horizontal situation indicator (HSI) portions of thedisplays.

AHRS mode selections are made using the pilot or copilot compass control panel. TheAHRS normally operates in magnetic (MAG) mode. Directional gyro (DG) mode is intendedto operate as a heading reference, only for a short period of time, near areas wheremagnetic disruptions exist and does not use data from the flux detector.

A slew switch is provided to change heading direction. The switch is operational in bothMAG and DG modes. In DG mode it is used periodically to correct for drift. In MAG mode, italso causes the heading to slew in the selected direction. When the switch is released inMAG mode, the heading will slowly slave back to the heading defined by the flux detector.

2. INERTIAL REFERENCE SYSTEM <0025>

The inertial reference system (IRS) provides inertial outputs of attitude, heading, angularrates, linear acceleration and present position to be displayed on the flight displays and tobe used by other avionics systems.

The IRS is a dual system with two inertial reference units (IRU) and a dual mode select unit(MSU). Each IRU receives information from the same side air data system. The IRUmeasures inertial motion sensed by the inertial instruments and computes attitude andheading data. This information is processed and sent to the integrated avionics processorsystem which interfaces with the flight control computers and flight management computers.These signals are also routed to the TCAS, EGPWS, weather radar, fuel system, stallprotection system, flight data recorder and data concentrator units. The MSU provides pilotselection of the IRS modes.

REV 56, Jan 31/03




The IRS provides attitude and heading information to the electronic flight instruments.Attitude is displayed on the attitude direction indicator (ADI) of the primary flight displays andheading is displayed on the horizontal situation indicator (HSI) portions of the displays.Heading is selected to magnetic or true using the flight management system (refer toChapter 18).

The IRS normally operates in navigation mode. In navigation mode, it is not possible toupdate the IRS position, however, it is possible to perform a rapid realignment while on theground.

Attitude mode is a reversionary mode, used when the IRU has detected an inertial failure orinaccuracies of the navigation operation in flight. Attitude mode does not provide positiondata. In attitude mode, the heading may drift and must be corrected using the flightmanagement system (FMS). If the FMS is not available, the EICAS control panel can beused to make heading corrections. Attitude mode is annunciated on the EICAS status page.

12--50--3Vol. 1




MASTER

Attitude and Heading Reference System/Inertial Reference System <MST>Figure 12---50---1

COMPENSATOR (COMP)

PITCH/ROLL/HEADING ANGLESPITCH/ROLL/YAW RATESLONG./LAT./NORMAL/CROSSHEADING ACCELERATIONSALONG HEADING/VERTICALACCELERATIONS

ERROR COMPENSATION ANDFLUX DETECTOR MISALIGNMENT

HEAD--UPGUIDANCESYSTEM

<0026>

PFD 1 MFD 1 MFD 2 PFD 2

<0025>

IR S1

NAVOFF

2

ATT NAVOFF ATT

INERTIALREFERENCESYSTEM

1

ATTITUDEHEADINGCOMPUTER

1

DCU 1, 2 & 3

INERTIALREFERENCESYSTEM

2

ATTITUDEHEADINGCOMPUTER

2

<PRE0025>

<PRE0025>

<PRE0025><0025> <0025>

<PRE0025>

<PRE0025>

<PRE0025><0025> <0025>

<0025>

<PRE0025>

<0019>

DCU 1 & 2

REV 56, Jan 31/03




Compass Control Panel/Inertial Reference System Mode Select Unit <MST>Figure 12---50---2

1 -- IRS -- 2Used to select IRS mode.OFF -- Removes power

from IRS.NAV -- IRS operates in

navigation mode.ATT -- IRS operates in

attitude mode.

Pilot’s and Copilot’s Compass Control PanelCenter Pedestal

IRS Mode Select UnitCenter Pedestal

IRS1 2

NAVOFF ATT NAVOFF ATT

SLEWMAG

+

DG

--

COMPASS

DG / MAGUsed to set AHRS modeDG -- HSI performs like adirectional gyro and doesnot use data from theflux detectors.MAG -- HSI is continuouslyadjusted using data fromthe flux detectors.

SLEWUsed to periodically correct headingwhen in DG mode. Will move readingin MAG mode, but returns to previousheading when switch is released.

-- Slews HSI graphic reading to the right.-- Slews HSI graphic reading to the left.

<0025>

12--50--5Vol. 1




MASTER

Attitude Director Indications <MST>Figure 12---50---3

Roll Pointer (white)Indicates roll anglePointer rotates alongfixed roll scale.

Slip / Skid Indicator (white)Indicates lateral acceleration.Moves with roll pointer.Lateral displacement fromcenter of roll pointer indicatesairplane is slipping or skidding.

Airplane Symbol (black)Indicates position of airplanein relation to horizon index.

Horizon Line (white)Indicates roll and pitch attituderelative to airplane symbol.Horizon bar rotates to display rollattitude and moves vertically todisplay pitch attitude.The boxes at ends of horizon barrepresent airplane wing tips.

Attitude Director Indicator

Attitude DirectorIndicator

Roll Scale (white)Fixed scale that indicatesroll attitude.Small marks at 10 and 20Large marks at 30 and 60Small triangle at 45


10

10

<0015>

REV 56, Jan 31/03




Selected Heading Readout <MST>Figure 12---50---4

Selected Heading Readout (magenta)Indicates selected heading as set usingheading knob on flight control panel.Removed 5 seconds after heading isselected.

Horizontal Situation Indicator

Selected Heading Bug (magenta)Indicates selected heading as setusing heading knob on flight controlpanel. When bug is off scale, adashed line is displayed from centerof compass to selected heading.

Lubber Line (white)Fixed reference for readingcurrent airplane heading.Fixed index marks are locatedaround compass rose at45 degree increments.

Airplane Symbol (white)Indicates center of compassrose.


Horizontal SituationIndicator

<0015>

Compass Rose (white)Rotating card indicates airplanecurrent magnetic heading underfixed lubber line.Small marks at 5 degree increments.Larger marks at 10 degree increments.Digits and cardinal points at 30 degreeincrements.

12--50--7Vol. 1




MASTER

A. Display Reversion

Display capability is maintained when sensor data failure occurs. Either PFD (or MFDwhen in PFD format) can be configured to display data from either attitude and headingreference system by operation of a reversionary switch on the source selector panel.Selection of alternate data sources is indicated to the flight crew by yellow single sourceflag on the PFD and MFD.

Display capability is maintained when sensor data failure occurs. Either PFD (or MFDwhen in PFD format) can be configured to display data from either inertial referencesystem by operation of a reversionary switch on the source selector panel. Selection ofalternate data sources is indicated to the flight crew by yellow single source flag on thePFD and MFD. <0025>

REV 56, Jan 31/03




Source Selector Panel <MST>Figure 12---50---5

NORM -- Each attitude and headingcomputer supplies data to the sameside display.1 -- Attitude and heading computer 1supplies data to both pilot and copilotdisplays. An amber source message isdisplayed on both PFDs.2 -- Attitude and heading computer 2supplies data to both pilot and copilotdisplays. An amber source messageis displayed on both PFDs.


NORM -- Each inertial reference unitsupplies data to the same side display.1 -- Inertial reference unit 1 suppliesdata to both pilot and copilot displays.An amber source message is displayedon both PFDs.2 -- Inertial reference unit 2 suppliesdata to both pilot and copilot displays.An amber source message is displayedon both PFDs.


Used to revert inertial reference systems.ATTD HDG

ATTD HDG

<0025>

Used to revert attitude and headingreference systems.

12--50--9Vol. 1




MASTER

Attitude and Heading Source Selection <MST>Figure 12---50---6



MAG 1, MAG 2, DG 1 or DG 2 (amber)Indicates heading selection when a singleattitude and heading source has beenselected.

ATT 1 or 2 (amber)Indicates that single inertial reference sourcehas been selected.ATT 1 -- Inertial reference unit 1 selected.ATT 2 -- Inertial reference unit 2 selected

<0025>

<0015>

MAG 1, MAG 2, TRU 1 or TRU 2 (amber)Indicates heading selection when a singleInertial reference source has been selected.

<0025>

REV 56, Jan 31/03




Attitude/Heading Source Failure Indications <MST>Figure 12---50---7

MAG 1 or DG Flag (red)Indicates that onside or both attitudeand heading systems are faulty or outof tolerance.

ATT Flag (red)Indicates that onside or both attitudeand heading systems have failed.



MAG or TRU Flag (red)Indicates that onside or both inertialreference systems are faulty or outof tolerance.

ATT Flag (red)Indicates that onside or both inertialreference systems have failed.

ATT

<0025>

<0015>

<0025>

ATT

MAG

TAT 15C

BRT

TAS 0WXUTC 16:13FMS 2YULTTG

CRS 24313.0 NM

SAT 12CGS 0

MAG

12--50--11Vol. 1




MASTER

B. Initialization and Alignment

AHRS initialization and operation occurs automatically when electrical power isestablished and the aircraft is stationary. Initialization in MAG mode takes about 70seconds. DG mode requires a much longer time to initialize. In flight, initializationrequires straight, unaccelerated level flight. The primary flight displays (PFD’s) presenta flashing initialization alignment message during initialization.

IRS initialization takes about 7 minutes at normal temperature. The IRS requires thatthe initial position be entered using the flight management system (FMS). The primaryflight displays (PFD’s) present a flashing initialization alignment message duringinitialization. Upon successful alignment, the IRS will automatically sequence intonavigation mode. Attitude alignment takes 1 minute or 34 seconds when switchingfrom navigation to attitude mode, provided the aircraft is stationary on the ground or instraight and level flight. <0025>

The magnetic flux detectors used to originate heading information are sensitive tolocalized magnetic fields and magnetic anomalies. The effects and the proceduralresponses to these conditions are presented in the Collins AHS-85 / 85E AttitudeHeading System Pilot’s Guide.

REV 56, Jan 31/03




Attitude/Heading Source Alignment Indications <MST>Figure 12---50---8

Alignment Annunciator (white)Indicates inertial referencealignment in process.

IRS 1 (2) OVERTEMP status (white)Indicates that an overtemperaturecondition exists.

IRS 1 (2) IN ATT status (white)Indicates that IRS is operating inattitude mode.


Status Page

Alignment Annunciator (white)Indicates attitude and headingalignment in process.DO NOT TAXI is also displayedwhen airplane is on the ground.

DO NOT TAXIATT / HDG ALIGNING

<0025>

<0015>

ATT / HDG ALIGNINGDO NOT TAXI

<0025>

<0025>

<0039>

<0039>

IRS 1 OVERTEMPIRS 2 OVERTEMPIRS 1 IN ATTIRS 2 IN ATT

12--50--13Vol. 1




MASTER

AHRS ALIGNMENT

Mode Time to Align

MAG(normal or on the ground)

70 seconds(No adverse motion sensed by the aircraft;Normal passenger movement is acceptable.)

DG 10 minutes

Airborne10 to 35 seconds(The aircraft must remain in straight and level,unaccelerated flight.

REV 56, Jan 31/03




IRS --- EICAS Messages <MST>Figure 12---50---9

Status Page

<0039>

<0039>

IRS 1 OVERTEMPIRS 2 OVERTEMPIRS 1 ON BATTIRS 2 ON BATTIRS 1 DC FAILIRS 2 DC FAILIRS 1 IN ATTIRS 2 IN ATT

IRS 1/2 OVERTEMP Status(white)Comes on to indicate that anovertemperature condition exists.

IRS 1/2 ON BATT Status(white)Comes on to indicate that IRS isoperating on back--up power.

IRS 1/2 DC FAIL Status(white)Comes on to indicate that IRSback--up power has failed.

IRS 1/2 IN ATT Status (white)Comes on to indicate that IRSis operating in attitude mode.

12--50--15Vol. 1




MASTER

C. System Circuit Breakers


CBLOCATION

NOTES

AHRS FAN 1 DC ESS 4 D9

Pilots SystemAHRS 1 DC ESS 4 D8

Attitude andHeading

Pilots SystemATT/HDG 1 MAIN BAT

DIR 5 A8HeadingSystems(AHRS)

AHRS FAN 2DC BUS 2 2

H15(AHRS)

CopilotsS

AHRS 2DC BUS 2 2

H14pSystem

ATT/HDG 2 MAIN BATDIR 5 A9

Inertial Pilots SystemATT/HDG 1 MAIN BAT

DIR 5 A8InertialReference

Pilots SystemIRU 1 AC ESS 3 C2Reference

System (IRS)0025 Copilots

IRU 2 AC BUS 2 2 B14<0025> Copilots

System ATT/HDG 2 MAIN BATDIR 5 A9

REV 56, Jan 31/03





12--60--1Vol. 1


Standby Instruments and Clocks


MASTER

1. STANDBY INSTRUMENTS AND CLOCKS

A standby attitude indicator and a standby altimeter/airspeed indicator is located betweenthe EICAS displays on the center instrument panel. A standby compass is located belowthe center of the overhead instrument panel. A clock is installed on both the pilot and copilotside panels.

An integrated standby instrument is located between the EICAS displays on the centerinstrument panel. A standby compass is located below the center of the overheadinstrument panel. A clock is installed on both the pilot and copilot side panels. <0083>

A. Standby Attitude Indicator

The standby attitude indicator displays aircraft pitch and bank angles. It is a 28 VDCdriven gyro that provides pitch and roll information for at least nine minutes after apower failure. It also serves as a standby ILS indicator to provide localizer andglideslope indications.

B. Standby Altitude/Airspeed Indicator

The standby altimeter/airspeed indicator displays barometric altitude from --1000 to+50,000 feet (±20). A BARO set knob is provided. The standby airspeed portion ofthe indicator displays non--corrected indicated airspeed from 60 to 450 knots(±3 knots).

C. Integrated Standby Instrument <0083>

The integrated standby instrument (ISI) provides standby attitude, altitude and airspeedinformation to the flight crew. To retain full operational capability under emergencyconditions the ISI is powered by the battery bus. The ISI uses inputs from the alternatepitot probe and static ports.

The ISI displays the following information:

S Attitude display

S ILS deviation

S Altitude display (corrected)

S VMO display

S Airspeed display

S Static source error correction (SSEC)

S Mach number

S Barometric pressure

S Slip-skid indication

REV 56, Jan 31/03




Horizon Line

TO

Roll Scale and IndexMarkings at 10, 20,30, 45 and 90degrees.Roll/Sky Pointer

Indicates bank anglesreferenced against rollindex.

Glideslope FlagWhen in view, indicatesselected signal is notreliable or not present.

Glideslope PointerIndicates position inrelation to theglideslope path.

Localizer PointerIndicates position inrelation to localizerbeam.

Localizer Fail FlagWhen in view, indicatesselected signal isunreliable or notpresent.

Slip/Skid Indicator(inclinometer)

Fixed AirplaneSymbolIndicates roll and pitchattitude relative to thehorizon.

Power OFF FlagAppears when powerto indicator is lost orduring gyro failure.Gyro will continue torun for approximately9 minutes after poweris lost.

SphereIndicates airplanemovement in pitch.Marked at 5--degreeincrements.

Standby Attitude Indicator (1)Center Instrument Panel

Standby Attitude IndicatorFigure 12---60---1

12--60--3Vol. 1




MASTER

Standby Altitude/Airspeed IndicatorFigure 12---60---2

ALT

.3000

0

5

1

2

3

46

7

9

0

1021 3015

120 150

BARO

NOTENormal operation of standby altimeter/indicated airspeed indicators is vibratoron. (circuit breaker CBP 1--1P2 closed).

Altitude Pointer andScalePointer indicatesaltitude in 100--footincrements as readfrom scale. Full circlefor each 1,000 feet ofaltitude

HPA/IN HG ReadoutsIndicates selected barometricpressure as expressed inHectopascals and inches ofmercury.

Indicated Airspeed IndicatorIndicates speed in knots, from0 to 450 KIAS.

Altitude ReadoutIndicates barometricaltitude from --1000 to50 000 feet, in1,000--foot and 100 footincrements.

Barometric Set KnobUsed to changebarometric pressurevalues as read atHPA/IN HG readouts.Range for this standbyinstrument is as follows:from 952 to 1049 Hpaandfrom 28.2 to 30.99 in. Hg.

Standby Altimeter/Airspeed Indicator

REV 56, Jan 31/03




Integrated Standby Instrument <0083>Figure 12---60---3

STD

M.47 ILS 1013 hPa

20

10

240

220

200

18010

900

800

700

600

500

CAGE BARO

29.92 in

12

Integrated Standby InstrumentCenter Instrument Panel

CAGEUsed to reset horizonline.Use only duringstabilized level flight.Will not operate duringpower up.

STDUsed to select eitherstandard pressurereference, 1013 hPa(29.92 inHg), or baro--correctionpressure reference.

BAROUsed to adjust baro--correctionpressure reference.Setting stored in non--volatilememory to prevent loss duringpower failure.

BrightnessControls

12--60--5Vol. 1




MASTER

Integrated Standby Instrument Scales <0083>Figure 12---60---4

Horizon Line

IAS TapeRange 40 -- 520 Kts.Graduations every 5 Kt.

Roll ScaleGraduations every 5 degrees.

MACH NumberDisplayed whenabove 0.45 andremoved whendrops below 0.40.

Selected Standardor Baro--correctedPressurePressure displayedabove (hPa) andbelow (inHg) altitudetape.

Altitude TapeTape reads hundredswith graduationsevery 20 feet. Boxcontains thousands.

Slip/Skid IndicatorWhite trapezoidslides left or rightdepending on lateralacceleration.

VMO Band (red)From Vmo valueupwards. Roll/Sky Pointer

Pitch ScaleGraduations every 2.5 degrees.

Fixed Cross--Pointer

STD

M.47 ILS 1013 hPa

20

10

240

220

200

18010

900

800

700

600

500

CAGE BARO

29.92 in

12

Integrated Standby InstrumentCenter Instrument Panel ILS Symbols

LocalizerGreen diamond withvertical line onhorizontal scale withsquare deviation dots.GlideslopeDisplays green diamondon vertical scale withsquare deviation dots.

ILS information is removedwhen the ILS receiver is nottuned to an ILS frequency.

NOTE

REV 56, Jan 31/03




Integrated Standby Instrument Flags <0083>Figure 12---60---5

G/S Flag (red)or

LOC Flag (red)Displayed when a glideslopeor localizer failure is detected.Corresponding glideslope orlocalizer scale and pointer areremoved.

G/S

CAGE

+

_

BARO

STD

ATT

ALTIAS

LOC

SSEC ILS

ALIGNING

SSEC Flag (yellow)Displayed when static sourceerror correction cannot becomputed.

ILS Flag (red)Displayed when both localizerand glideslope functions fail.Localizer and glideslopescales and pointers areremoved.

ATT Flag (red)Displayed when an attitudefailure is detected.Blue and brown background,pitch and roll scales androll/sky pointer are removed.

ALT Flag (red)Displayed when acomputation or displaymalfunction is detected.Altitude scale is removed.

IAS Flag (red)Displayed when airspeedcannot be computed ordisplayed. Airspeed tape andpointer are removed.

Standby InstrumentCenter Instrument Panel

ALIGNING FlagDisplayed duringpower--up andinitialization.

CAGE

+

_

BARO

STD

Standby InstrumentCenter Instrument Panel

12--60--7Vol. 1




MASTER

D. Standby Magnetic Compass

The standby compass is independent and does not interface with other systems. It is aself contained dry compass which uses eddy current damping to prevent overshooting.A miniature aircraft pointer indicates aircraft heading in relation to magnetic north on arotating vertical compass card. The compass can be illuminated by operating thestandby compass switch on the miscellaneous lights panel.

A compass correction card, mounted above the instrument, is used to record the valuesthat must be added to, or subtracted from the compass indications to correct for theinfluence of magnetic materials contained in the aircraft and magnetic fields from theavionics systems near the compass.

REV 56, Jan 31/03




Standy Magnetic CompassFigure 12---60---6

Standby Magnetic CompassWindshield Center Post

Compass Correction CardUsed to record compassinstrument errors at theheadings indicated. Theerrors are noted during acompass ”swing” operation.

Magnetic CompassIndicates heading ofairplane in relation tomagnetic north.

STANDBY COMPASS WITH ALL RADIOS ON SWUNG BY

TO FLY

STEER

N 45 E 135 S 225 W 315

12--60--9Vol. 1




MASTER

E. Clocks

Effectivity:

S Airplanes 7002 to7672

A digital electronic clock is installed on the pilot and copilot side panels. Each clockcontains its own time base and each has GMT, CHR, local and ET functions. The clocksare the time base source for the aircraft avionics equipment. The clocks receiveair/ground information from the PSEU to control the elapsed time function (flight time).The Pilots clock is powered from the DC battery bus and the copilots clock is poweredfrom DC bus 2. In the event of a power failure, both clocks will be powered by the mainbattery direct bus. Current time is also displayed on the multifunctional displays.

Effectivity:

S Airplanes 7673 and subsequent

A digital electronic clock is installed on the pilot and copilot side panels. Each clock iscapable of displaying date (GPS or internal UTC), current time (GPS, internal UTC, orlocal), chronometer (CHR), as well as elapsed time (ET) functions. The clocks aresynchronized to the GPS input as soon as valid GPS information is received. In the caseof invalid GPS data or signal loss, the clocks will operate in internal (INT) mode using theintegrated time base of each clock. If there is a valid GPS signal, the clocks do not needto be set, as this will be done automatically at power up. The flight crew can disable thethe GPS signal by entering the time setting mode. The clocks will then ignore the GPSsignal until the next primary power reset. The MODE, ET SEL and ET RST buttons areused to set the time and date. To set the clock, push the MODE button for two seconds,then push the MODE button again to toggle between UTC hours and minutes (when theINT is lit), year, month, and day, (when the DT is lit), and local time hours and minutes(when the LT is lit). In any of these modes, the ET SEL button is used to decrease thedata and the ET RST button is used to increase the data. Data changes are inincrements of one digit for each press of the ET SEL or ET RST button. At any timeduring the time setting process, pressing the MODE button for a minimum of two secondswill exit the time setting mode and restart the clock operation.

REV 56, Jan 31/03




Clock Display <Airplanes 7002 to 7672>Figure 12---60---7

Time Setting/Display SelectorUsed in conjunction withET/CHR buttons to setapplicable readouts.SET cycles through GMT,LOC and day/month/year.GMT/LOC/DATE displays timeor date at upper readout.

Time/Date DisplayDisplays Greenwichmean time, local time ordate.GMT is displayed inhours and minutes.LOC is displayed inhours and minutes.Date; alternately indicatesmonth/day onthe GMT display (forfirst second) and year(for next second).DATE alternatelydisplays month/day(for first second) andyear (for next second).

ET/CHR DisplayDisplays elapsed timeor chronometer time.ET time is displayedin hours and minutes.CHR time is displayedin minutes.

CHRUsed to start, stop andreset the CHR displayand second hand.Overrides existingelapsed time display.First push startschronometerSecond push holdschronometer readoutand second handThird push resetssecond hand to zeroand returns display toelapsed time

During time setting,CHR button is used toincrement applicablevalue.

ETControls elapsed timereadout and during timesetting, selects theparameter to be set.Flashing parameter canbe incremented bypressing CHR.

Second Hand

NOTEET time corresponds toairplane flight time andstarts when the airplanetakes off and stops attouch down. ET canonly be reset on ground.

Effectivity:Airplanes 7002 to 7672.

12--60--11Vol. 1




MASTER

Clock Display <Airplanes 7673 and Subsequent>Figure 12---60---8

MODEUsed in conjunction with ET SELand ET RST buttons to set UTCtime, date, and local time.

CHRUsed to start, stop andreset the chronometerdisplay. Overridesexisting elapsed timedisplay.

ET RSTUsed to reset theelapsed time functionwhen the airplane is onthe ground.Also used to increase thedata in one digitincrements duringmanual setting of theclock.

ET/CHR DisplayDisplays elapsed timeor chronometer time.

RST

SEL

ET

MODE

CHR

INT

CHR

Time/Date DisplayDisplays GPS time,internal UTC time, localtime or date.Time is displayed inhours, minutes, andseconds (HH:MMss)DATE is displayed asDay/Month/Year.

Mode annunciatorIndicates the presentmode of operation.DT -- dateGPS -- GPS synchro--nization enabledINT -- internal time/date operation (GPSdisabled).LT -- local time

NOTEET time corresponds toairplane flight time andstarts when the airplanetakes off and stops attouch down. ET canonly be reset on ground.

Effectivity:Airplanes 7673 and subsequent.

ET SELUsed to select theelapsed time functionwhen the chronometerfunction is active.Also used to decrease thedata in one digitincrements duringmanual setting of theclock.

REV 56, Jan 31/03




F. System Circuit Breakers


CBLOCATION

NOTES

StandbyAttitudeIndicator

STBY HORIZ

StandbyAirspeed,Altitude,AttitudeIndicator

STBY INSTRDC BAT 2 N10

Standby

IntegratedStandbyInstrument<0083>

INT STBYINST

StandbyInstruments

CLK 1 MAIN BATDIR 5 A10

Clocks (A/C CLOCK 1 DC BAT 2 N11Clocks (A/C7002 to 7672)

CLK 2 MAIN BATDIR 5 A11

CLOCK 2 DC BUS 2 2 H5

CLOCK 1DC BAT 2 N11

Clocks (A/C7673 and

CLOCK 1MAIN BAT 6

B77673 andsubsequent) CLOCK 2

MAIN BATDIR 6

B8subsequent) CLOCK 2DC BUS 2 2 H5

12--70--1Vol. 1


Head--Up Guidance System


MASTER

1. HEAD--UP GUIDANCE SYSTEM <0026>

The head--up guidance system (HGS) projects instrument and airplane systems dataholographically between the pilot and the pilot’s windshield. Attitude, airspeed, flight pathguidance and other information are displayed in symbolic format. HGS allows the pilot to flythe airplane during Category IIIa instrument approaches in a head--up position. A combineroptically diffracts (reflects) flight symbology to infinity and allows the pilot to look through thedisplay without eye movement or shift in eye focus.

HGS consists of the following:

S Combiner,The combiner is mounted on the pilot’s windshield frame and can be used during groundand flight operations. The combiner is deployed and stowed by actuating a lever on theRH side. An infrared transmitter and alignment detector automatically check if the opticalelement/combiner is out of position. The combiner also incorporates a manual/automaticbrightness control.

S Control Panel,The control panel is used to set system references, flight and system test modes.

S Overhead Unit,The overhead unit contains a CRT to generate symbology and a lens to project thesymbology on the combiner.

S Drive Electronics Unit,The drive electronics unit contains the CRT drive circuitry and power supplies.

S Computer Unit,The computer unit creates the flight symbology from airplane sensor data. HGS combinesairplane situational information (speed, heading, pitch, roll, attitude), inertially sensedflight path and flight path acceleration information and guidance directed control inputs.Integration of airplane systems information and inputs, combined with flight data, allowsthe pilot to maneuver the airplane along the flight path with precise straight--in and glidepath tracking.

If guidance data is being provided by AFCS, the combiner will echo AFCS data. During aHGS--guided approach, once the localizer and glideslope have been captured and theairplane has descended below 2,000 feet, the HGS can be selected to provide the desiredtype of approach guidance.

HGS modes are as follows:

S Primary (PRI) Mode,PRI mode can be used for take--off, cruise and landing.

S Flight Director (F/D) Mode,F/D mode can be used to fly F/D--generated approach guidance or to monitor a coupledapproach.

S Visual Meteorological Conditions (VMC) Mode,VMC mode is used for visual approaches and landings without guidance.

REV 56, Jan 31/03




S Modes AI and AII,These modes are used to manually fly precision approaches.

S Mode AIII,This mode is used for approach and landings to category IIIa minima.

NOTE

The provision of data for Low Visibility Take--offs, orCategory II Operations or Category IIIa Operationsdoes not constitute operational approval to conductsuch operations.

S Clear (CLR) Mode,Clear mode is typically used during taxi to clear all symbology from the combiner.

S Test (TEST) Mode,Test mode is used by maintenance staff to diagnose faults, checkout and troubleshootthe system.

A. Combiner Symbology

Dependent upon HGS mode (see “DISPLAY CRITERIA” table) the combiner will displaythe following:

(1) Align HGS Message,An ALIGN HUD message is displayed to indicate a combiner alignment problem.

(2) Boresight Symbol,Pitch and roll data are referenced to the boresight symbol.

(3) Attitude Data,Standard symbology is used for pitch and roll scales, pitch and roll indicator, slip /skid indicators. Pitch bars may be compressed. Extreme pitch attitude symbols(up / down pointing chevrons) are also used. Flags are used to indicate IRSsource failures and IRS data miscompare.

(4) Heading Data,A horizon line with a heading scale, index and heading readout and selectedcourse data is provided. A 200--degree compass card is displayed during primarymode. Flags are used to indicate IRS source failures and heading datamiscompare.

(5) Flight Path Data,A flight path symbol indicates the airplane’s lateral and vertical flight path. Theflight path symbol will mask (blank) other data. An acceleration symbol is alsoprovided.

12--70--3Vol. 1




MASTER

(6) Airspeed Data,Standard symbology is provided for the airspeed indications; airspeed scale andtape, speed bugs, trend vectors and for the setting of V--speeds. An airspeederror symbol is provided that indicates a deviation (+/-- 15 KIAS) from theselected airspeed. Checkerboard symbols are used as overspeed / low speedcues. The Mach readout comes on when Mach is greater than 0.45. Flags areused to indicate IAS and ADC failures and miscompares.

(7) Baro Altimeter Data,Standard symbology is provided for the barometric altitude indications; altitudetape, altitude readout and altitude preselect. Barometric prerssure settingindications are not provided. MDA alert and readout data are provided. Displayof metric altimeter data or preselects is not provided. Flags are used to indicateALT failures.

(8) Radio Altimeter Data,The selected decision height readout is displayed and decision height alerting isprovided. Flags are used to indicate RA failures and miscompares are detectedbelow 1,000 feet AGL. Radio altitude readouts are as follows:

S 2,500 feet to 1,000 feet -- 50 foot increments

S 1,000 feet to 50 feet -- 10 foot increments

S 50 feet to 10 feet -- 5 foot increments

S Below 10 feet -- 1 foot increments.

(9) Vertical Speed Data,Vertical speed readouts are in 100 fpm or 1,000 fpm increments. A VS flag isused to indicate loss of vertical speed data from IRS 1.

(10) Navigation Data,Standard symbology is used to depict navigation systems data:

S Lateral Deviation,Localizer deviation and excessive deviation are displayed. LOC flags are usedto indicate a localizer failure or miscompare

S DME distance readouts are in 1 nm or 0.1 nm increments

S Selected VOR or LOC indications are provided. Navigation source failureflags are provided

S Marker beacon indications (OM, MM, IM) are provided

S Vertical Deviation,Glideslope deviation and excessive deviation indications are provided. GSangle readouts are provided. GS flags are used to indicate a glideslopefailure or miscompare.

REV 56, Jan 31/03




Effectivity:

S Airplanes equipped with the --503 HGS computer

NOTE

When the navigation source is the FMS, the bearingpointer will not be displayed on the HUD. The bearingpointerwill only be displayedwhen the navigation sourceis provided by the ADF or VOR.

(11) Symbolic Runway,During a Category IIIa approach, a runway symbol is displayed from 300 to 60feet AGL. The runway is scaled (200 feet wide and 10,000 feet long) with ticmarks representing the runway aim point (1,050 feet from the threshold).

(12) Windspeed and Direction,A windspeed readout (up to 256 knots) and a direction arrow are provided.

(13) Windshear Indications and Guidance,Windshear indications and guidance data are provided. Primary mode willautomatically pop--up to provide guidance data.

(14) Groundspeed Readout,Groundspeed indications are provided.

(15) Flare Cue,The Flare Cue symbol comes on at 60 feet AGL and flashes until removed at 30feet AGL. Indicates that the flare should be initiated but does not provide anyguidance as to how the flare should be performed. The symbol is provided duringall approaches except IIIa mode.

(16) Flare Command,The Flare command symbol comes on during a Category IIIa approach andlanding and provides guidance in performing the flare maneuver.

(17) Idle Message,An IDLE message is provided indicating to the pilot to reduce the airplane’s thrustto idle for touchdown. The message is displayed when the airspeed exceeds thecorrect airspeed (plus a wind factor) based upon the present altitude. If theairspeed is less than the desired, the message is delayed. The IDLE message,however, is forced to come on at 5 feet AGL regardless of airspeed.

(18) Approach Warning Message,During a Category II or IIIa approach, below 500 feet AGL, an approach warningmessage is provided if the approach conditions exceed present tolerances or ifany HGS failures are detected.

12--70--5Vol. 1




MASTER

(19) Angle of Attack Limit,Airplane angle of attack relative to stick shaker is indicated by distance betweenthe AOA symbol and flight path symbol.

S If AOA and flight path symbol are aligned, then airplane is at stick shaker

S AOA symbol comes on below 1,500 feet if a windshear has been detected

S AOA symbol comes on when the airplane is within 2 degrees of stick shaker.

(20) Flight Director Guidance Cue,The guidance cue represents lateral and vertical attitude commands required forthe selected low visibility approach and landing:

S During Category I or II operations, displayed until 80 feet AGL, and

S During Category IIIa operations, displayed until touchdown

S An F/D flag is used to indicate flight director failure.

(21) Flight Mode Annunciations,Lateral armed / captured and vertical mode annunciations are provided. Autopilotstatus indications and mistrim indications (aileron, elevator and rudder) areprovided.

(22) Autopilot, Yaw Damper & Mistrim Indications,A yaw damper message is provided to indicate that the yaw damper isdisengaged. Mistrim flags (elevator, aileron and rudder trims) are provided toindicate out--of--trim conditions.

NOTE

HGS entry of landing runway elevation is to be madeprior to any type of landing using the HGS.

REV 56, Jan 31/03




HGS SystemFigure 12---70---1

OVERHEADPANEL

ACT

STBY

ELV

G/S

FAULT CLR BRT + DIM --

1 2 3

4 5 6

7 8 9

ENTER 0 TEST

HGS

HGS

Combiner Brightness ControlUsed to adjust brightnessof holographic image.Push in for automaticcontrol.Pull out and rotateclockwise for manualcontrol.

12--70--7Vol. 1




MASTER

Head---up Guidance System SunvisorFigure 12---70---2

1. Ultrasuede material2. Sunvisor holder3. Velcro strip4. Decal5. Velcro strip6. Sunvisor

LEGEND

25

4

6

GLARESHIELD

FCCCONTROLPANEL

3

TURBTURB

HGS SUNVISOR

1

Sunvisor Stowed

REV 56, Jan 31/03




Head---up Guidance SystemFigure 12---70---3 Sheet 1

ACT

STBY

ELV

G/S


1 2 3

4 5 6

7 8 9

ENTER 0 TEST

HGS

HGS Control Panel (1)Center Pedestal

FAULT lamp(amber)Comes on to indicatecommunications faultbetween computer unitand control panel.

ELV and G/Smode select keys(momentary action)Used in conjunctionwith numeric keypadand + /-- keys to inputrunway elevation andglideslope angle datainto HGS.CRT line cursorcomes on toindicate entry area.

LED DisplayIndicates modeselected for display onHGS combiner unit

TEST key(momentary action)Used by maintenancestaff to initiate systemtest.When pressed,active mode displayline indicates TESTTest mode haspriority over all modes.To start test mode:Press TEST &ENTER.To halt test mode:Press TEST again.

Numeric KeypadUsed to inputnumeric data(runway elevation andglideslope angleinto HGS.

o Key annunciatorlamp that comes onwhen the applicablemode / function hasbeen selected.

ENTER key(momentary action)Used to enter keypaddata into HGS.

ACT and STBYmode select keys(momentary action)Used to selectapplicable HGS mode.

BRT+ and DIM -- keys(momentary action):BRT/DIM: Used toadjust brightness ofCRT.+ / -- : Used with 0 to 9number keys to inputnumerical data intoHGS.

CLR key(momentary action)When pressed:clears active modedisplayed HGScombiner.

12--70--9Vol. 1




MASTER

Head---up Guidance SystemFigure 12---70---3 Sheet 2

Selectable HGS Mode

Active HGS Mode

PRI PrimaryAIII Approach Category IIIAII Approach Category IIAI Approach Category IF/D Flight DirectorVMC Visual Meteorological

Conditions

NO AIII Loss of Approach Category IIINO AII Loss of Approach Category IINO AI Loss of Approach Category ICLR Combiner Clear Mode Selected.TEST HGS Test Mode Selected

ACT

STBY

ELV

G/S


Selectable Capability

Elevation

Glideslope

PRI PrimaryAIII Approach Category IIIAII Approach Category IIAI Approach Category IF/D Flight DirectorVMC Visual Meteorological

Conditions

ElevationReadoutIndicatesrunwayelevation asentered onnumerickeypad.default islast entry.

GlideslopeReadoutIndicatesglideslopeangle asentered onnumerickeypad.default is--3.00

Approach Capability

AIII Approach Category IIIAII Approach Category IIAI Approach Category I

Active Mode

FAULT lamp

CRT Brightness Controland +/--Keys

Active ModeSelect Key

Standby ModeSelect Key

Runway ElevationSelect Key

Glideslope AngleSelect Key

Key annunciatorlamp that comes onwhen the applicablemode / function hasbeen selected.

Clear KeyUsed to obtain a clear viewthrough the HGS combiner.Clears display without havingto stow the combiner.

To disengage clear mode,press CLR or ACT key.

REV 56, Jan 31/03




HGS Control PanelFigure 12---70---4

Glideslope Reference Line

ACT

STBY

ELV

G/S



Indicatesglideslope angleselection(0.00 to --9.99).

“” ” used to indicatedegrees. Decimalposition isautomatic.

--3.00 --3.00

HGS Combiner

Glideslope (G/S) Mode SelectKeyPress G/S to enter glideslopedata. Arrow and CRT line cursorprompt to indicate entry. Usekeypad to enter 3--digitglideslope angle. Use ENTERkey to select value for use.

Use CLR key to correct entries.

During G/S data entry,BRT+ and DIM keysdo not function.

upon airplane

ACT

STBY

ELV

G/S



Indicatesrunway elevationselection in feet(--9999 to 99999).Default is lastentry.

ELEV Mode SelectKeyPress ELEV to enterrunway elevationdata. CRT line cursorprompts to indicateentry. Use DIM-- keyto enter negativevalue. Use keypad toenter number. UseENTER key to selectvalue for use.

Use CLR key tocorrect entries.

Glideslope Angle Readout

Glideslope

Elevation

Runway SymbolDisplayed from 300to 60 feet AGL.Position depends

course, airplaneheading, and radioaltitude.Tic marks indicaterunway aim point.

HGS Combiner

12--70--11Vol. 1




MASTER

HGS Control Panel <Airplanes equipped with the (--503) HGS Computer>Figure 12---70---5


ACT

STBY

ELV

G/S



--3.00 --3.00

HGS Combiner

Glideslope (G/S) Mode SelectKeyPress G/S to enter glideslopedata. Arrow and CRT line cursorprompt to indicate entry. Usekeypad to enter 3--digitglideslope angle. Use ENTERkey to select value for use.

Use CLR key to correct entries.

During G/S data entry,BRT+ and DIM keysdo not function.

upon airplane

ACT

STBY

ELV

G/S



Indicatesrunway elevationselection in feet(--9999 to 99999).Default is lastentry.

ELEV Mode SelectKeyPress ELEV to enterrunway elevationdata. CRT line cursorprompts to indicateentry. Use DIM-- keyto enter negativevalue. Use keypad toenter number. UseENTER key to selectvalue for use.

Use CLR key tocorrect entries.

Glideslope Angle Readout

Glideslope

Elevation

Runway SymbolDisplayed from 300to 60 feet AGL.Position depends

course, airplaneheading, and radioaltitude.Tic marks indicaterunway aim point.

HGS Combiner

NOTEThe reference glideslopeentry is limited to a rangeof --2.00 thru to --6.00.

OutofRngdisplayed if theentry is not within the range.

Indicatesglideslope angleselection(0.00 to --9.99).

“” ” used to indicatedegrees. Decimalposition isautomatic.

REV 56, Jan 31/03




Head---up Guidance System --- Test Mode SelectionsFigure 12---70---6 Sheet 1

RECORDED FAULTSEXISTING FAULTSSENSOR DATAAIRCRAFT IDENTIFICATIONHGS SW P/N

A/C ID #7002HGS TEST MENU

>

ACT

STBY

ELV

G/S


1 2 34 5 6

7 8 9ENTER 0 TEST

HGS

Test mode:Engaged by pressing TESTkey when airplane on theground or in flight above 500feet AGL.Disengaged by pressingTEST key again.Test mode is automaticallydisengaged on descentthrough 500 feet AGL.

HGS Control Panel(1)Center Pedestal

HGS CombinerPilot’s Windscreen Area

Test sub--modes:The BRT + and DIM -- keys areused to scroll through data.Selections made by pressingBRT+ key to move cursor up,then pressing ENTER key toactivate selection.Selections made by pressingDIM -- key to move cursor down,then pressing ENTER key toactivate selection.The CLR key used to back outof sub--modes.

CLR BRT + DIM --

ENTER 0

1 2

4 5

7 8

HGS Test Menu Page

12--70--13Vol. 1




MASTER


A/C ID #7002LEG #1

ENTER LEG #

EFFECT

APPCH WARN

FAULT

ADC1 SELCT ALTHGS HCP/90APM NO AIII CAP

REF MACHAPM APCH WARN

NO AIII CAP

25 FAULTS

ApplicableAirplaneTail Number

ScrollIndicators

Scrolling / Clear :BRT+ key used to movecursor up,DIM -- key used to movecursor down,CLR key used to back out ofsub--modes.

Fault Effects ColumnIndicates effect ofcorresponding recorded fault(located on adjacent line).Indication can be blank (noeffect), or a loss of category IIIacapability (NO AIII CAP) orfault resulted in an approachwarning (APPCH WARN)

Recorded Faults ColumnIdentifies failure andfailed unit.

Total Number Faults for this Leg(Max 126 faults per leg)

Enter LegNumber Prompt/ ReadoutUsed along withHGS control Panelto enter a specificleg number.

Recorded Faults PageUsed to gain access torecorded fault data for currentflight leg or one of thepreceding legs (max 127 legsstored in memory)Table format used to displayfault information.

Leg NumberIndicatorRange is from #1hru #127,progressing fromcurrent leg (#1)backwards thruprevious legs.

INVALID

INACINVALID

ADC2

REV 56, Jan 31/03




Head --- up Guidance System --- Test Mode SelectionsFigure 12---70---6 Sheet 3

EXISTING FAULTS

ACTIVE FAULT

HGS REF G/SHGS RUNWAY/ELEV

W/S VALIDHGS OHU/60APM MARKERS

8 FAULTS


Existing Faults PageIndicates faults detectedwithin the last 2 seconds.Table format used to displayfault information.

Total Number Faults Detected(last 2 seconds)(Max 256 faults)

ScrollIndicators

Recorded Faults ColumnIdentifies failure and failed unit.

ACT

STBY

ELV

G/S



Fault Lamp(amber)

Fault Code / MessagesLED panel indicatescorresponding fault code /system message:HC 10 thru HC 57 (Computer)OHU 60 thru OHU 68(Overhead Unit)DEU 70 thru DEU 78 (DisplayElectronics Unit)HC 88 (System in Test Mode)HC89 (Vector Generator inTest Mode)HCP 90 thru HCP 98 (ControlPanel Fault)Combiner B1 (Combiner notaligned)

FAILINACFAIL

FAILFAIL

GPW1

12--70--15Vol. 1




MASTER


SENSOR MENU

RAAHGSANAGPWSSWITCH

>

Inertial ReferenceSystem Units

Air DataComputer Units

IntegratedAvionicsProcessorSystem

DME 1Transceiver

VHFNavigationReceivers

Traffic Alert &Collision AvoidanceSystem

Radio AltimeterUnits

AnalogEquipment

GroundProximityWarningSystem

Thrust LeverTake--off /Go--aroundSwitches

IRU/AHRSADCIAPSDMEVHFTCAS

Sensor Menu PageUsed to gain access to HGSdata for corresponding airplanesystem or equipment.

HGS Control PanelData Entry Readout

Runway elevation,Glideslope angle.

Menu Page Selections:BRT+ key used to movecursor up, then ENTER key usedto activate selection.DIM -- key used to movecursor down, then ENTER keyused to activate selection.CLR key used to back out ofsub--modes.

REV 56, Jan 31/03





AIRCRAFT IDENTIFICATION

CURRENT ID: 7002

ENTER NEW ID:>

Airplane Identification PageUsed to tag HGS computerand all fault records withairplane tail / ident number.

New AirplaneTail or IdentNumber FieldWhen ENTER NEW IDis selected, ELEV readout onHGS control panel will indicateID. Keypad is then used toinput 5--digit number. ENTERis then used to store number inmemory.

Current AirplaneTail or IdentificationNumberReadout


12--70--17Vol. 1




MASTER


HGS SW P/N

CLPSMIOS1IOS2VGHCP

Software Part Number PageUsed for softwareconfiguration control, test andvalidation purposes.

NOTEOnly the computer unit and theHGS control panel contain software.

CorrespondingSoftware Part Number

HGSControl Panel

Clear:CLR key used to back out ofsub--modes.

Circuit Cards withinComputer Unit:CLP -- Control LawProcessor Card,SM -- System MonitorCard,IOS 1/2 -- Input / OutputSystem Cards,VG -- Vector GeneratorCard.

9801--1300--xxx9801--1310--xxx9801--1320--xxx9801--1330--xxx9801--1340--xxx9801--1350--xxx

REV 56, Jan 31/03




B. Output to PFD’s

HGS provides information via IAPS to enable the copilot to monitor the airplane’sapproach to the runway, check the performance of the HGS, and monitor the pilot’sresponse to HGS commands. The PFDs will display the following:

(1) Excessive Lateral DeviationExcessive localizer deviation is displayed.

(2) Excessive Vertical DeviationExcessive glideslope deviation is displayed.

(3) Approach StatusThe flight mode annunciator area will indicate the following:

S Selectable HGS mode (AIII, AII, or AI) displayed as a white message

S Captured HGS Mode (AIII, AII, or AI) displayed as a green message

S Loss of HGS Mode (AIII, AII, or AI) displayed as a red line through the greenmessage

S HGS approach warning (APCH WARN) and HGS failure (HGS FAIL) displayedas red flags. EICAS will echo HGS FAIL as a status message (white)

S FLARE (amber) message (mode IIIa only) in the ADI area.

C. Audio Callouts

Ground proximity warning system mode 6 audio callouts are provided for groundclosure awareness. Callouts are as follows:

S 500, approaching minimums, 100, minimums, and then

S 50 (if DH was not 50 feet), 40, 30, 20, 10.

D. Output to FDR

The HGS transmits the following data to the flight data recorder:

S HGS in use

S HGS fail message

S Approach warning.

E. Output to MDC

The HGS transmits the following data to the maintenance diagnostic computer:

12--70--19Vol. 1




MASTER

S HGS unit failures; combiner, control panel, overhead unit, drive electronics unit orcomputer unit (when they occur)

S Input failures; RA 1 and RA 2, DME 1, VHF 1 and VHF 2, ADC 1 and ADC 2, IRS 1and IRS 2, IAPS and TCAS (when they occur).

F. Approach Monitor for Category II Operations

The HGS monitors approach parameters during Category II operations (500 feet to 100feet AGL) as follows:

S Tracking Monitor -- This function evaluates the airplane’s approach relative tolocalizer and glideslope deviation.

G. Approach Monitor for Category III Operations

The HGS monitors approach parameters during Category III operations (from 500 feetAGL). The following are checked:

S The autopilot has been disengaged

S The airplane’s approach relative to airspeed, localizer and glideslope deviation andcrosstrack rate, vertical speed, lateral and longitudinal position

S For possible unsafe landings by evaluating the sink rate, lateral displacement fromrunway centerline, airspeed relative to selected airspeed, crosstrack rate, roll angle,and distance traveled along the runway.

H. System Test/Fault Codes

The HGS continuously checks its operational status and if a fault is detected the systemwill blank the CRT and the combiner. EICAS and the PFDs will display applicable HGSfailure / approach warning messages. The HGS control panel FAULT lamp will comeon, the HGS control panel LED unit will display an applicable fault code.

I. HGS Mode Selections/Indications

The HGS control panel is used to enter runway and glideslope data, to accomplishtesting troubleshooting, to select HGS modes and to display the mode in use. Modesare indicated on the control panel as follows:

S The CRT line adjacent to the ACT key indicates the current active mode

S The CRT line adjacent to the STBY key indicates the next available / next selectablemode

S The CRT line to the far right side of the STBY key indicates HGS capability (AIII,AII, AI).

The flight mode annunciator area of the HGS combiner and the PFDs will echo thecorresponding HGS mode.

REV 56, Jan 31/03




HGS System --- EICAS Messages <MST>Figure 12---70---7

Status Page

HGS FAIL

<0039>

<0039>

HGS FAILStatus (White)Comes on to indicatehead up guidancesystem failure.

12--70--21Vol. 1




MASTER

Primary Mode --- Radio Altitude IndicationsFigure 12---70---8

AP10

SYNCPRIHDGALT

LOC 1GS

21

1700

M .545240

220

200

180

160

VOR 1

10.0 NM

190 GS

ADF1ADF2

0.0 VS

21

30

2 000

100

900

800

00

000

1

Flashing charactersindicate that theairplane has arrived atthe selected decisionheight.During go--around,alert is disabled atDH +100 feet.Alerts inhibitedbelow 5 feet.

Selected DecisionHeight Readout(Example: DH 100)Indicates decision height, in1--foot increments as set atDH knob on altitudereference panel (range is 0 to999 feet).

Radio Altitude ReadoutIndicates radio altitudefrom 0 to 2,500 feet.50--foot increments from2,500 to 1,000 feet;

10--foot increments from1,000 to 50 feet;5--foot increments from50 to10 feet;1--foot increments from10 to 0 feet;Negative radio altitudeis displayed as 0 feet.

Below 2,500 feet AGL, a radio altimeter failure isindicated by the above failure flag and the radioaltitude readout is removed.A comparison between the two radio altitudesources is only performed below 1,000 feetAGL. A miscompare is indicated by the samefailure flag but the radio altitude readout isretained. The flag flashes for 5 seconds whenthe miscompare is first detected and thereafterremains displayed until the condition iscorrected.

APPROACHING MINIMUMSMINIMUMSFIVE HUNDREDDECISION HEIGHTFIFTYFORTYTHIRTYTWENTYTEN

Decision Height AlertExample: DH 100

RA Failure Flag

10

32 000100DH740MDA

RA

REV 56, Jan 31/03




HGS /AFCS ModesFigure 12---70---9 Sheet 1

10 10

AP

SYNC

PRIHDGALT

ALOC 1

GS

5 5

24

M .5452 000

100

900

000

1

HGS/ AFCS Mode Annunciator

Selectable Approach Mode(HGS)

Armed Lateral Mode(AFCS)

Armed Vertical Mode(AFCS)

Active Mode(HGS)

Captured Lateral Mode(AFCS)

Captured Vertical Mode(AFCS)

Active HGS ModePRI PrimaryAIII Approach Category IIIAII Approach Category IIAI Approach Category IF/D Flight DirectorVMC Visual Meteorological

Conditions

Selectable Approach HGS ModePRI PrimaryAIII Approach Category IIIAII Approach Category IIAI Approach Category I

Loss of Approach Capability

A boxed and flashing active AIII, or AII or AI modeannunciator indicates a loss of the indicated approachcapability.HGS control panel will echo NO AIII, NO AII or NO AI,as applicable.

AIII

Autopilot ModeAnnunciator

AII AI

Autopilot Mode1/2 BNK Half Bank SelectedDR Dead ReckonningSYNC Sync ModeTEST Diagnostics Mode

Autopilot EngagementAP Pilot’s SideAP Copilot’s Side

NOTE1. On the ground, the PRI mode

is the system default.2. Annunciators flash to indicate a

change.

240

220

200

12--70--23Vol. 1




MASTER

HGS /AFCS ModesFigure 12---70---9 Sheet 2

10 10

AP

SYNC

PRIHDGALT

ALOC 1

GS

5 5

24

M .5452 000

100

900

000

1

HGS Mode AnnunciatorSelectable Approach Mode(HGS)



Active Mode(HGS)



Captured Lateral ModeROLLGATOLOC 1(2)B/C1(2)VOR1(2)HDGFMS1(2)

Captured Vertical ModeGA/WSIASMACHVSGSALTALTSCAPDES DescentGA Go--aroundTO/WS

TOPTCHALTS

Armed Lateral ModeLOC 1(2)B/C1(2)VOR1(2)FMS1(2)

Armed Vertical Mode

GSALTSALTS

240

220

200

3. PRI mode will automaticallypop--up during windshear.

NOTE1. On the ground, the PRI mode

is the system default.2. Annunciators flash to indicate a

change.

LOC ArmedBack Course LOC ArmedVOR ArmedFMS Armed

ILS GS ArmedSelected Altitude ArmedSelected Altitude Abort(if Flashing)

Roll HoldGo aroundLateral Take--offLOC CapturedBack Course LOC CapturedVOR CapturedHeading ModeFMS Captured

Escape Guidance During WSIAS Hold (ovsp if flashing)Mach Hold (ovsp if flashing)Vertical Speed HoldGlideslope CapturedAltitude HoldSelected Altitude CapturedDescentGo--aroundTake--off Escape GuidanceDuring WindshearVertical Take--offPitch HoldSelected Altitude Track

REV 56, Jan 31/03




HGS Combiner --- GeneralFigure 12---70---10

AP

180

160

140

120

100

100

200

300

000

900

Roll Indicator

Represents theairplane’s longitudinalaxis (boresight).Middle peak in thesymbol is theboresight position.

Horizon Line

24

PRI

SelectedCourse Mark

Airspeed Indicator

Heading Readout

Heading TickMark

BarometricAltitudeIndicator

15 15

10 10

5 5

Pitch Indicator

Boresight Symbol

ALIGN HUD

ALIGN HUD MessageDisplayed when the combiner isnot properly aligned mechanically(not in the correct operatingposition).

Slip/Skid Indicator

Flight Path Symbol

Guidance Cue

Centre of symbolindicates actual airplaneflight path (lateral andvertical).

Driven by flight directoror HGS computer.

Compass Rose

SYNC

HDGALT

ALOC 1

HGS AFCS ModeAnnunciator

Autopilot EngagementAnnunciator


12--70--25Vol. 1




MASTER

Primary Mode --- Airspeed IndicationsFigure 12---70---11 Sheet 1

Angle of Attack LimitSymbol

Indicates airplane’sangle of attack relativeto stick shaker point.Displayed if windshearhas been detected byGPWS or when within

10 10

AP10

SYNCPRI

ALTLOC 1

GS

5 5

21

1700

--5 --5

M .545240

220

200

180

160

VOR 1

10.0 NM

190 GS

ADF1ADF2

0.0 VS

21

30

2 000

100

900

800

00

000

1

240

220

200

180

160

IndicatedAirspeedScale / Tape

Moving scalewith fixed pointer(speed index)that indicatescurrent airspeed.

Range is 40 to400 knots with80 knots in view.

Displayed onlywhen the HGS isin the primarymode.

IndicatedAirspeed Bug

Indicates airspeedas selected atSPEED knob onflight control panel

Indicated MachReadout

Indicates Mach to thenearest hundredth.Displayed at and above0.45 Mach.

M .545

250

Selected AirspeedReadoutDisplays selected airspeedwhen the airspeed value isout of range of the currentlydisplayed airspeed scale(only during flight).In the approach mode (AIII,AII, AI, F/D and VMC), thereadout is displayed at alltimes.1--knot increments

250

Speed Index

HDG

1--knot increments

REV 56, Jan 31/03





10 10

AP10

SYNCPRIHDGALT

LOC 1GS

5 5

21

1700

--5 --5

120

100

80

60

400.0 VS

21

302 000

100

900

800

00

000

1

180

160

140

120

2

1R

T

Reference Speed BugsDisplayed above 40 KIAS.

Disappear after take--off:1 -- take--off decision speed (V1).R -- rotate airspeed (VR)2 -- take--off safety speed (V2).

Target Speed BugDisplayed and stays onabove 40 KIAS.Set to indicate VT.

OverspeedClacker

180

V1 125

VT 170V2 142VR 133V1 125

Low Speed Cue(Checkerboard)

Cue forimpending stallspeed

350

140

120

100

OverspeedVMO / MMO Cue(Checkerboard)

Cue formaximum speedallowable.

Speed ReferenceTableDisplayed below40 KIAS, in 1--knotincrements.Corresponds toselected take--offreference speeds.The referencetable disappearsas the speedmarks (bugs) onthe airspeed scaleappear. Range isfrom 40 to 400knots.

Displayed (in 1--knot)ReadoutReference Speed

increments) duringselection of referencespeed. Prefix dependsupon which referencespeed is beingchanged or entered.Value stays on for 5seconds when atake--off referencespeed is changed.

12--70--27Vol. 1




MASTER


10 10

AP10

SYNCPRIHDGALT

LOC 1GS

5 5

21

1700

--5 --5

M .545240

220

200

180

160

VOR 110.0 NM

190 GS

ADF1ADF2

0.0 VS

21

30

2 000

100

900

800

00

000

1

Air Data SourceDefault source is ADC 1 and is not annunciated.Common source is displayed as ADC 1 or ADC 2,depending upon the air data source selected.

160

140

Vector travellingabove the speedindex indicatesairplaneacceleration.

160

140

Vector travellingbelow the speedindex indicatesairplanedeceleration.

Air Data FailureAn IAS failure is indicated by the abovefailure flag and all airspeed data areremoved.A miscompare is indicated by the samefailure flag but airspeed data isretained. The flag flashes for 5 secondswhen the miscompare is first detectedand thereafter remains displayed untilthe condition is corrected.

Airspeed Error SymbolIndicates airplane’sdeviation (max 15 KIAS)from selected airspeed.The symbol has amasking window whichobscures most othersymbols that it overlaysexcept the guidancecue, runway lines,approach statusmessage, TCAS box andwindshear messsage.

Faster than selectedairspeed --approx 5 KIAS

Slower than selectedairspeed --approx 15 KIAS

200Airspeed TrendVectorPredicted speedvalue, in the next10 seconds, fromcurrent airspeed.

An ADC failure is indicated by displaying both theIAS and ALT failure flags, and all ADC--driven dataare removed.A miscompare is indicated by the same failureflags but all ADC--driven data are retained. Theflags flash for 5 seconds when the miscompare isfirst detected and thereafter remain displayed untilthe condition is corrected.

IAS Failure Flag

ALT

ALT Failure Flag

-- Masking window

IAS

5 knots = 1 degree

REV 56, Jan 31/03




Primary Mode --- On GroundFigure 12---70---12 Sheet 1

80

60

40

LOC 1

5.1 NM

0.0 VS

PRITOTO

100

200

300

000

900

21

HDG 210CRS 210V1 130

200

V1 130VR 134V2 141VT 177

PRIHGS/AFCS Mode Annunciator




Active Mode(HGS)




TO

TO

24

Selected Course Bug Lateral DeviationLine

Lateral Deviation Line(On Ground)Provides a reference fortake--off and roll out, of theairplane’s lateral deviation fromthe selected course.Airplane is on track when thelateral deviation line is alignedwith the selected course mark(on the horizon line).Displayed during HGS

the horizon line, and thenavigation source is LOC 1or LOC 2.

Horizon Line &Heading Scale

10 10

5 5

--5 --5

12--70--29Vol. 1




MASTER


80

60

40

LOC 1

5.1 NM

PRITOTO

100

200

300

000

900

21

HDG 210CRS 210V1 130

200

V1 130VR 134V2 141VT 177

Roll Scale

VerticalSpeedReadout

Selected HeadingReadout

SelectedAirspeed Bug

Course Readout

Flight PathAcceleration Symbol

Slip/Skid IndicatorRoll Indicator

Reference SpeedReadout

SpeedReferenceTable

AirspeedIndicator(Tape)

BarometricAltitudeIndicator

Boresight Symbol

DME DistanceReadout

NavigationSourceIndicator

Heading Bugand Index

10 10

5 5

--5 --5

Pitch Scale / Bars

REV 56, Jan 31/03





80

60

40

LOC 1

5.1 NM

PRITOTO

100

200

300

000

900

21

HDG 210CRS 210V1 130

200

V1 130VR 134V2 141VT 177

Flight Path Symbol

Airspeed Error Symbol

Guidance Cue

Windspeed andWind Vector

Baro AltitudeReadout

Airspeed readout, radio altitudereadout and ground speed readout.

The following symbols / readouts are not available when on the ground:

Compass rose and its associatedsymbols.

10 10

5 5

--5 --5

Vertical Speed Symbol

101820 B

0.0 VS

12--70--31Vol. 1




MASTER

Visual Meteorological Conditions (VMC) Model --- Approach and LandingFigure 12---70---13 Sheet 1

80

60

40

LOC 1

5.1 NM

0.0 VS

PRITOTO

100

200

300

000

900

21

HDG 210CRS 210V1 130

200

V1 130VR 134V2 141VT 177

PRIHGS/AFCS Mode Annunciator




Active Mode(HGS)




TO

TO

24

Selected Course Bug Lateral DeviationLine

Lateral Deviation Line(On Ground)Provides a reference fortake--off and roll out, of theairplane’s lateral deviation fromthe selected course.Airplane is on track when thelateral deviation line is alignedwith the selected course mark(on the horizon line).Displayed during HGS

the horizon line, and thenavigation source is LOC 1or LOC 2.

Horizon Line &Heading Scale

10 10

5 5

--5 --5

REV 56, Jan 31/03




Visual Meteorological Conditions (VMC) Model --- Approach and LandingFigure 12---70---13 Sheet 2

Comes on at 60 feet AGL,and flashes until 30 feet AGL,to indicate that the flaremaneuver should be initiated.

Guidance Cue


Marker Beacon (IM, MM, OM) flags.Compass rose, Airspeed Tape,Altitude Tape and theirassociated symbols.

Pitch Scale / Bars

5 5

RadioAltitudeReadout

Flight PathAccelerationSymbol

2423

VMC

5.7 NM

--0.7 VS

5

1700140 --5

130 GS

--3.00

--5

--10 --10

1820 B

--3.00

5 10

Roll ScaleSlip/Skid Indicator

Roll Indicator

Vertical SpeedReadout

Boresight Symbol


Flight PathSymbol

+

Flare Cue

(Double cross symbol)

The following symbols / readouts are not available when in VMC mode:

Lateral Deviation Lineand Glideslope Line

SelectedCourseBug

Flare Command(Single cross symbol)

+

+

12--70--33Vol. 1




MASTER

Flight Director (F/D) Model --- Approach and LandingFigure 12---70---14 Sheet 1

LOC 1

GS

HGS/AFCS Mode Annunciator




Active Mode(HGS)




Boresight Symbol

F/D

2423

F/D

LOC 1

5.7 NM

--0.7 VS

5

AP10

1700140 --5

130 GS

--3.00

--5

--10 --10

1820 B

--3.00

5LOC 1GS

DME DistanceReadout

GroundspeedReadout

Navigation SourceIndicator

Wind Speedand Direction

Horizon Line

Heading Scale

BarometricAltitudeReadout


IndicatedAirspeedReadout

Pitch Scale / Bars

--10 --10


Marker BeaconFlags(IM, MM, OM)Displayed whenairplane passes overthe applicable markerbeacon transmitter.

Autopilot EngagementAnnunciator

Roll Scale

REV 56, Jan 31/03




Flight Director (F/D) Model --- Approach and LandingFigure 12---70---14 Sheet 2

Flight PathSymbol

2423

F/D

LOC 15.7 NM

--0.7 VS

5

AP10

1700140 --5

130GS

--3.00

--5

--10 --10

1820 B

--3.00

5LOC 1GS

Flight PathAcceleration Symbol Roll Indicator


++

Flare Cue


Slip/Skid Indicator


GlideslopeReferenceLine

GlideslopeReadout

F/D GuidanceCue

Removed fromthe display at80 feet AGL.

LateralDeviationLine andGlideslopeLine

SelectedCourseBug


Indicates current airspeeddeviation from selectedairspeed.

Compass rose, Airspeed Tape,Altitude Tape and theirassociated symbols.

The following symbols / readouts are not available when in F/D mode:


+

The glideslope line isremoved from thedisplay at 70 feet AGL.

12--70--35Vol. 1




MASTER

Category I or II (AI or AII) Model Approach and LandingFigure 12---70---15 Sheet 1





Active Mode(HGS)




BoresightSymbol

AI or AII

2423

A I

LOC 1

5.7 NM

--0.7 VS

510

1700140 --5

130 GS

--3.00

--5

--10 --10

1820 B

--3.00

5

DME DistanceReadout

GroundspeedReadout



Horizon Line

Heading Scale




Pitch Scale / Bars

--10 --10


Marker BeaconFlags(IM, MM, OM)

Autopilot EngagementAnnunciatorArrow indicates whichFCC will drive theautopilot when engaged.

Roll Scale

A I A IIor

-- FCC 1

-- FCC 2

REV 56, Jan 31/03




Category I or II (AI or AII) Model Approach and LandingFigure 12---70---15 Sheet 2

Flight PathSymbol

2423

LOC 15.7 NM

--0.7 VS

5

AP10

1700140 --5

130 GS

--3.00

--5

--10 --10

1820 B

--3.00

5


Roll Indicator


++

Flare Cue


Slip/Skid Indicator


GlideslopeReferenceLine

GlideslopeReadout

HGS GuidanceCue

Removed fromthe display at80 feet AGL.


SelectedCourseBug


Compass rose, Airspeed Tape,Altitude Tape and theirassociated symbols.

The following symbols / readouts are not available when in AI or AII mode:


+

A I A IIor

A loss of the applicable approach capability isindicated by boxing and flashing the active AIor AII mode annunciator.HGS control panel will annunciate ‘NO AI’ or’NO AII’.Copilot’s PFD will display AI , AII (red)message.

Loss of Approach Capability Flags

A I

Approach Warning Message (Category II)(500 ft to 100 ft AGL)

Indicates that HGS Category II limits havebeen exceeded.Copilot’s PFD will display APCH WARN (redand boxed) message.

APCH WARN


12--70--37Vol. 1




MASTER

Category IIIa (AIII) Model Approach and LandingFigure 12---70---16 Sheet 1





Active Mode(HGS)




Boresight Symbol

AIII

2423

A III

LOC 1

5.7 NM

--0.7 VS

5

AP10

1700140 --5

130 GS

--3.00

--5

--10 --10

1820 B

--3.00

5

DME DistanceReadout

GroundspeedReadout



Horizon Line

Heading Scale




Pitch Scale / Bars

--10 --10


Marker BeaconFlags(IM, MM, OM)Autopilot Engagement

Annunciator

Roll Scale

REV 56, Jan 31/03





Flight PathSymbol

2423

LOC 15.7 NM

--0.7 VS

5

AP10

1700140 --5

130 GS

--3.00

--5

--10 --10

1820 B

--3.00

5


Roll Indicator

Slip/Skid Indicator

Heading Bugand IndexGlideslope

ReferenceLine

GlideslopeReadout

HGS GuidanceCue

Removed fromthe display attouchdown.


SelectedCourseBug


A III

A loss of the applicable approach capability isindicated by boxing and flashing the active AIIImode annunciator.HGS control panel will annunciate ‘NO AIII’.Copilot’s PFD will display a red AIII message.

Loss of Approach Capability Flag

A III

Approach Warning Message(Category IIIa at 500 feet)Indicates that HGS Category IIIa limits havebeen exceeded, or the autopilot is stillengaged at 500 feet.Copilot’s PFD will display APCH WARN (redand boxed) message.

APCH WARN


12--70--39Vol. 1




MASTER


160

2423

LOC 15.7 NM

--0.7 VS

5

AP10

140 --5

130 GS

--3.00

--5

--10 --10

280 B

--3.00

5A III

Runway SymbolRepresents the airplane’s orientation relative to the runway.Displayed from 300 feet to 60 feet AGL. Position depends uponrunway elevation, airplane heading, altitude, course setting,localizer deviation, and system resolution.Tick marks indicate runway aim point, whichrepresents 1,050 feet from the runway threshold.Lines represent outline of runway threshold,scaled to a width of 200 feet.

MM

During a Category IIIapproach, messagecomes on at 1,000 feetand at 650 feet AGL,flashes for 10 seconds,to indicate that theautopilot must bedisconnected. Anapproach warningmessage comes on ifthe autopilot is notdisengaged by 500feet AGL.

Autopilot DisconnectMessage

DISC

IDLE CommandDisplayed duringCategory IIIaoperations, whenthe HGS hasdetermined thatthe thrust leversmust be selectedto IDLE.

IDLE

LOC 1NM

--0.6 VS

138 --5

GS

--3.00

--5

--10 --10

B

--3.00

125

1.1

30150

The symbol cues the pilot as to where to expect the real runwaywhen adequate visibility is achieved and is used as an additionalaltitude awareness cue.

REV 56, Jan 31/03





5 510

2423

LOC 1

NM

VS5--5

GS

--3.00

--5

--10 --10

B

--3.00



Comes on if a flare command is not available.Indicates that the flare maneuver should beinitiated but not how to perform the maneuver.

++

Flare Cue


Flare cue, when flare command is available;Compass rose, Airspeed Tape, Altitude Tapeand their associated symbols.

The following symbols / readouts are not available when in AIII mode:

Flare Command

+

(Single cross symbol)

Displayed only during a Category IIIaapproach. Provides guidance on howto perform the correct flare maneuver.

125135

123

0.9

--0.4

If pitch compressionoccurs in AIII mode,a “NO AIII” messageis annunciated on theHCP and the HGSmode is removedfrom the combiner.

NOTE

A III

Active Mode(HGS)

AIII

+

IM

12--70--41Vol. 1




MASTER

Rollout ModeFigure 12---70---17

24

80

23

LOC 10.7 NM

0.0 VS

Active Mode(HGS)


Roll Scale

Boresight Symbol

AirspeedReadout


Pilot’s and copilot’s PFDs willdisplay a ‘ROLLOUT’ messageupon airplane touchdown.

Rollout Indications on EFIS

AIII

Roll Indicator

Slip/Skid Indicator

Heading Bug

SelectedCourseBug

DME DistanceReadout


Horizon Line

Heading Scale

LateralDeviation Line

REV 56, Jan 31/03




Primary Mode --- Attitude IndicationsFigure 12---70---18 Sheet 1

Slip/Skid Indicator

If displaced fromcentre, the airplane iseither slipping orskidding.

Roll Scale Roll Pointer

Roll angle is displayedby pointer read againstfixed roll scale .

10 10

AP10

SYNCPRIHDGALT

LOC 1GS

5 5

21

--5 --5

M .545240

220

200

180

160

VOR 1

10.0 NM

190 GS

ADF1ADF2

0.0 VS

21

30

2 000

100

900

800

00

000

1

A fixed symbol

centre of thedisplay),wherein theairplaneattitude (pitchand roll) isreferenced to.

Pitch Scale

5 5

Slip/Skid Indicator(single engine)During one--engineinoperative conditions,the slip/skid indicatoris repeated below thethe flight path symbolto reduce pilotscanning.

Used with theboresight symbol toindicate currentairplane pitch attitude.Vertical tick markspoint to the directionof the horizon line.

Pitch Scale(Take--Off / Go--Around Mode)

15 15

When the airplane is in the take--offmode or the go--around mode (TO,GA, TO/WS or GA/WS), either the

is displayed without a gap in themiddle (drawn solid) to be used asa pitch reference during take--off orgo--around.

Markings indicate bank angle (degrees of roll).

tick marks areonly displayedwhen the rollpointer gets to

these tick marksor beyond. .

BoresightSymbol

12--70--43Vol. 1




MASTER


10 10

AP10

SYNCPRIHDGALT

LOC 1GS

5 5

21

--5 --5

M .545240

220

200

180

160

VOR 1

10.0 NM

190 GS

ADF1ADF2

0.0 VS

21

30

2 000

100

900

800

00

000

1Extreme PitchChevronPoints to thedirection of levelflight duringextreme pitch

Horizon LineThe horizon line representsthe airplane’s zero degrees ofpitch attitude (an artificialhorizon which is not adjustedfor the curvature of the earth).

20 20

15 15

10 10

5 5

Pitch Compression

The point of a downwardpointing chevron represents

The point of an upwardpointing chevron represents

Unusual attitudes / Unusual AOAsAn unusual attitude or unusual AOA would result ineither the horizon line or the flight path symbolexceeding the limits of their display areas. The affectedsymbol will then be ghosted (displayed in dashed lines).In this event, the vertical components of the attitudedisplay will be compressed to provide a consistentdisplay which is relatively correct to each other,although no longer conformal to the outside scene.

REV 56, Jan 31/03





Attitude Failure Flags

and/or and/orROL PIT

An IRS failure is indicated by the abovefailure flags and the affected attitude data isremoved from the display.A miscompare is indicated by the samefailure flags but affected attitude data isretained. The flags flash for 5 secondswhen the miscompare is first detected andthereafter remain displayed until thecondition is corrected.

V/S

Attitude SourceDefault source is ATT 1 and isnot annunciated.Common source is displayedas ATT 1 or ATT 2, dependingupon the attitude sourceselected.The flight path symbolis not displayed when theoff--side IRS is selected.

240

220

200

180

AP10

SYNCPRIHDGALT

LOC 1GS

21

1700

M .545

160

VOR 1

10.0 NM

190 GS

ADF1ADF2

0.0 VS

21

30

2 000

100

900

800

00

000

1

Pitch Attitude FailureFlag

Roll AttitudeFailure Flag

NOTEThe HGS does not display IRSalignment messages, whetheron the ground or during flight.

,

The roll scale isremoved if valid rolldata from theselected attitudesource is lost.

The pitch scale isremoved if validpitch data from theselected attitudesource is lost.

Vertical SpeedFailure Flag

V/S

The vertical speedscale is removed ifvalid vertical speeddata from theselected attitudesource is lost.

PIT

ROL

12--70--45Vol. 1




MASTER

Primary Mode --- Heading IndicationsFigure 12---70---19 Sheet 1

Selected Heading Bug(Compass Rose)

Indicates headingselected at HDG knob onflight control panel.When selected headingis off--scale, bug isremoved and a line isdisplayed from thecentre of the compassrose to selectedheading.

Heading Index

Indicates currentmagnetic (or true)heading when readagainst heading scale.

10 10

AP10

SYNCPRIHDGALT

LOC 1GS

5 5

21

1700

--5 --5

M .545240

220

200

180

160

VOR 1

10.0 NM

190 GS

CRS 240

ADF1ADF2

HDG 210

0.0 VS

21

30

2 000

100

900

800

00

000

1

21

30

Heading Scale (Compass Rose)Displayed as a 200--degreecompass rose at the bottom centreof the field.Indicates current magnetic (or true)heading, similar to the PFD.

Labeled with corresponding

of degrees.Cardinal headings are labeledwith the characters N, S, E and W.

The compass rose is displayed onlyduring flight, when the HGS is in theprimary mode.

Selected HeadingReadoutIndicates headingselected at HDG knobon flight control panel.

Heading Scale (Artificial Horizon)21

its corresponding value, in tens of degrees.

on the horizon line.Cardinal headings are labeled with thecharacters N, S, E and W.

Displayed andremains on for 5seconds, anytimethe heading value ischanged or whenvalue is off--scale.

REV 56, Jan 31/03




Primary Mode --- Heading IndicationsFigure 12---70---19 Sheet 2

MAG 2

Heading Scale (Compass Rose)

10 10

AP10

SYNCPRIHDGALT

LOC 1GS

5 5

21

1780

--5 --5

M .545240

220

200

180

160

VOR 1

10.0 NM

190 GS

CRS 240

ADF1ADF2

0.0 VS

21

30

2 000

100

900

800

00

000

1

21

30

Heading SourceHeading source is annunciated only whencommon source is selected.Heading source characters (TRU) displayedwhen true heading is selected from on--side IRS.Heading source characters (TRU 1 and TRU 2)displayed when true heading is selected from acommon source.The flight path symbol is not displayed when the#2 IRS is selected as the common source.

Heading Failure FlagA heading failure is indicated by the abovefailure flag and heading information(heading scale on horizon line and headingscale on compass rose) is removed fromthe display.A miscompare is indicated by the samefailure flag but heading data is retained. Theflag flashes for 5 seconds when themiscompare is first detected and thereafterremains displayed until the condition iscorrected.

HDG

12--70--47Vol. 1




MASTER

Primary Mode --- Course IndicationsFigure 12---70---20 Sheet 1

Indicate airplane positionrelative to the selectedbearing source. The head ofthe pointers extend awayfrom the bearing value, whilethe tails point toward thereciprocal value. At least thehead or the tail will bedisplayed at all times,indicating the current bearingvalues.

Heading Scale (Compass Rose) Selected Course Bug

10 10

AP10

SYNCPRIHDGALT

LOC 1GS

5 5

21

1700

--5 --5

M .545240

220

200

180

160

VOR 1

10.0 NM

190 GS

CRS 240

ADF1ADF2

0.0 VS

21

30

2 000

100

900

800

00

000

1

21

30

Heading Scale (Artificial Horizon)21

Selected Course BugTravels along the horizon line if theselected course is within the displayedportion of the heading scale. Theselected course bug is limited at theedges of the heading scale and isghosted (drawn with dashed lines) ifthe value is off--scale.

Indicates course as set at CRS knobon flight control panel. The head ofthe bug points to the selected coursevalue while the tail points to thereciprocal value. At least the head orthe tail will be displayed on theheading scale at all times, indicatingthe currently selected course.

TAIL HEAD

Bearing Pointers

Selected Heading Bug(Artificial Horizon)Indicates heading selected at HDGknob on flight control panel.When selected heading is off--scale,bug is removed.

Heading IndexIndicates current magnetic (or true)heading when read against headingscale.

BEARING POINTERNo. 1

HEAD TAIL

BEARING POINTERNo. 2

REV 56, Jan 31/03




Primary Mode --- Course IndicationsFigure 12---70---20 Sheet 2

000

VOR2

Also known as the coursedeviation indicator (CDI),indicates airplane deviationfrom the selected course ( leftor right of VOR or localizerradial) relative to the coursedeviation scale.An excessive localizerdeviation (more than 2 dots)at an altitude of less than 600feet AGL, is annunciated bya continuous flashing of theCDI.

Lateral Deviation Bar Heading Scale (Compass Rose)

10 10

AP10

SYNCPRIHDGALT

LOC 1GS

5 5

24

1700

--5 --5

M .545240

220

200

180

160

VOR 1

10.0 NM

190 GS

CRS 240

ADF1ADF2

0.0 VS

21

302

100

900

800

00

000

1

21

30

Bearing Source IndicatorsIndicates the current bearinginformation sources. Theindications consist of thecharacters VOR 1, ADF1, VOR2 and ADF 2 (1 is on--side; 2 isoff--side), depending upon thebearing sources selected. Thecharacters are followed by areplica of the correspondingbearing pointer head.An FMS bearing source is notannunciated.

Selected CourseReadoutIndicates course asselected at CRS knobon flight control panel.Displayed andremains on for 5seconds, anytimethe course value ischanged or whenvalue is off--scale.

Marks representing --2, --1,0, +1 and +2 dots oflocalizer or VOR deviation.

Course Deviation Scale

The To/From pointer isadded to the coursedeviation scale whenever aVOR deviation exists. Pointsin the same direction as theselected course bug torepresent a ‘To’ indicationand in the oppositedirection to represent a‘From’ indication.

To/From Indicator

ADF1ADF2

Bearing Source Failure Flags

A bearing source failure isindicated by boxing the affectedbearing source characters andthe corresponding bearinginformation removed from thedisplay.

, ,

, .

ADF1 ADF2

VOR1

NOTEThe CDI is limited tothe edge of thecourse deviationscale in view. Whenthe localizer deviationis 2 dots or less but isoutside of the coursedeviation scale’s fieldof view, the CDI isghosted (drawn withdashed lines).

12--70--49Vol. 1




MASTER

Primary Mode --- Barometric Altitude IndicationsFigure 12---70---21 Sheet 1

Analog indication of theairplane’s barometric correctedaltitude. Displayed only duringthe primary mode.Moving vertical scale with fixedindex (digital readout window)that indicates barometriccorrected altitude, rangingfrom --200 to 50,000 feet, with440 feet always in view.The scale is similar in formatand operation to the altitudetape in the PFDs.Small tick marks every20 feet.Large tick marks every 100feet with their correspondingnumerical values inhundreds.The thousands numericalvalues are contained withinthe altitude index (window).

Altitude Select BugDouble lines indicateselected altitude as set atALT knob on flight controlpanel. Displayed only whenselected altitude is withinthe scale in view.

Altitude IndexAltitude readoutwindow which indicatesthe airplane’s currentbarometric correctedaltitude.

200

100

000

900

800

2003

3

NOTEEnsure that the landing fieldelevation is correctly set at theHGS control panel and the cabinpressurization selector panel.Cross--check barometric pressuresetting on PFDs and standbyaltimeter.

10 10

AP10

SYNCPRIHDGALT

LOC 1GS

5 5

21

1700

--5 --5

M .545240

220

200

180

160

VOR 110.0 NM

190 GS

ADF1ADF2

HDG 210

0.0 VS

2130

2 000

100

900

800

00

000

1

Barometric Altitude Indicator(Tape)

ELV 200

Runway Elevation Readout(Example: ELV 200)Digital indication of therunway’s elevation, in 1--footincrements.Displayed and remains onfor 5 seconds, anytime therunway elevation value ischanged at the HGS controlpanel..

REV 56, Jan 31/03




Primary Mode --- Barometric Altitude IndicationsFigure 12---70---21 Sheet 2

Selected Altitude ReadoutIndicates the selectedaltitude value, with doublelines drawn over and underthe hundreds digits.Displayed in 100--footincrements (rounded--off tothe nearest 100 feet).Flashes for 5 secondswhen1,000 feet away fromtarget (selected) altitude.

ALTAltitude Failure Flag

An altitude failure is indicated by theabove failure flag and all altitudeinformation is removed from the display.A miscompare between the altitudesources is indicated by the same failureflag but altitude data is retained. Theflag flashes for 5 seconds when themiscompare is first detected andthereafter remains displayed until thecondition is corrected.

10 10

AP10

SYNCPRIHDGALT

LOC 1GS

5 5

21

1700

--5 --5

M .545240

220

200

180

160

VOR 110.0 NM

190 GS

ADF1ADF2

0.0 VS

21

30

2 000

100

900

800

00

000

1

ELV 200

1. The HGS does not displaybarometric pressure indications.Cross--check barometric pressuresetting on PFDs and standbyaltimeter.

2. The HGS does not displaybarometric altitude in meters.

NOTE

Negative AltitudeIndicatorAnnunciates altitudesless than 0 feet.

000

900

800

700

600

Consists of the characters ‘MDA’which indicates the airplane’spassage of the selected minimumdescent altitude. The MDAmessage comes on at the MDAand flashes for 2 seconds andthereafter remains displayed untiltouchdown or until the airplaneclimbs above the selected MDAplus 100 feet.

MDA 740 B

Selected MDA Readout(Example: MDA 740)Digital indication of theselected MDA, in 10--footincrements.Displayed and remains onfor 5 seconds, anytime theMDA value is selected on theair data reference panel.

Minimum Descent Altitude(MDA) Alert

10

32 000

100DH740MDA

12--70--51Vol. 1




MASTER

Primary Mode --- Radio Altitude IndicationsFigure 12---70---22

AP10

SYNCPRIHDGALT

LOC 1GS

21

1700

M .545240

220

200

180

160

VOR 1

10.0 NM

190 GS

ADF1ADF2

0.0 VS

21

30

2 000

100

900

800

00

000

1

Flashing charactersindicate that theairplane has arrived atthe selected decisionheight.During go--around,alert is disabled atDH +100 feet.Alerts inhibitedbelow 5 feet.

Selected DecisionHeight Readout(Example: DH 100)Indicates decision height, in1--foot increments as set atDH knob on altitudereference panel (range is 0 to999 feet).

Radio Altitude ReadoutIndicates radio altitudefrom 0 to 2,500 feet.50--foot increments from2,500 to 1,000 feet;

10--foot increments from1,000 to 50 feet;5--foot increments from50 to10 feet;1--foot increments from10 to 0 feet;Negative radio altitudeis displayed as 0 feet.

Below 2,500 feet AGL, a radio altimeter failure isindicated by the above failure flag and the radioaltitude readout is removed.A comparison between the two radio altitudesources is only performed below 1,000 feetAGL. A miscompare is indicated by the samefailure flag but the radio altitude readout isretained. The flag flashes for 5 seconds whenthe miscompare is first detected and thereafterremains displayed until the condition iscorrected.

APPROACHING MINIMUMSMINIMUMSFIVE HUNDREDDECISION HEIGHTFIFTYFORTYTHIRTYTWENTYTEN

Decision Height AlertExample: DH 100

RA Failure Flag

10

32 000100DH740MDA

RA

REV 56, Jan 31/03




Primary Mode --- Vertical Speed IndicationsFigure 12---70---23

Vertical Speed Failure FlagV/S

Indicates current vertical speed in feetper minute (fpm). Range is from--15,000 fpm to +15,000 fpm.

Displayed in increments of 100 fpmwhen the vertical speed is less than10,000 fpm (e.g. 2,500 fpm isdisplayed as 2.5).Displayed in increments of 1,000 fpmwhen the vertical speed is equal toor greater than 10,000 fpm (e.g.10,000 fpm is displayed as 10).

10 10

AP10

SYNCPRIHDGALT

LOC 1GS

5 5

21

1700

--5 --5

M .545240

220

200

180

160

VOR 110.0 NM

190 GS

ADF1ADF2

0.0 VS

21

30

2 000

100

900

800

00

000

1

ELV 200

Indicates loss ofvertical speed datafrom pilot’s IRS.Flag appears in placeof vertical speedreadout.

Vertical Speed Readout

12--70--53Vol. 1




MASTER

Primary Mode --- Navigation/Position IndicationsFigure 12---70---24 Sheet 1

DME Hold (H) Symbol( Example: 10.0 H )When DME hold isselected, ‘H’ replaces‘NM’ characters onDME distance readout.

Indicates DME distance (slantrange) to tuned navigation aid:From 0 to 99.9 nautical miles(nm), displayed in 0.1--nmincrements;Above 100 nm, displayed in1.0--nm increments;Dashes (------ NM) replacereadout if DME data is invalid;If DME information is lost(loss of signal), readout isremoved.

Ground Speed ReadoutAirplane’s ground speeddisplayed in 1--knotincrements during flight.Dashes (------ GS) replacereadout if ground speeddata is invalid;If ground speed informationis lost (loss of signal),readout is removed.

Marker Beacon FlagsIndicates airplane passageover the applicable markerbeacon transmitter.

IM -- Inner markerMM -- Middle markerOM -- Outer marker

10 10

AP10

SYNCPRIHDGALT

LOC 1GS

5 5

21

1700

--5 --5

M .545240

220

200

180

160

VOR 1

10.0 NM

190 GS

ADF1ADF2

0.0 VS

21

30

2 000

100

900

800

00

000

1

ELV 200

CRS 240

DME Distance ReadoutNavigation SourceIndicatorIndicates navigation sourceas set at NAV SOURCE knobon display control panel.The selected navigationsource is displayed usingthe characters:VOR 1 or VOR 2,LOC 1 or LOC 2.(1 is on--side; 2 is off--side)

An FMS navigation source isnot annunciated.

REV 56, Jan 31/03





Glideslope Failure Flag GS

AP10

SYNCPRILOC 1GS

VOR 1

21

1700

M .545240

220

200

180

160

LOC 1

10.0 NM

190 GS

ADF1ADF2

0.0 VS

21

30

2 000

100

900

800

00

000

1

Vertical deviation pointer whichretains its full diamond shapewhen travelling within the scale.The pointer changes to ahalf--diamond shape whenthe vertical deviationexceeds 2 dots.At altitudes below 600 feetAGL, the pointer will flash, foras long as the excessiveglideslope deviation exists.

Glideslope Index+2 dots

+1 dot

--1 dot

--2 dots

CRS 240

Glideslope Scale

0 dot

Indicates the airplane’s verticaldeviation relative to the ILSglideslope beam. Displayed inthe following conditions:Navigatioin source is LOC;Armed or captured verticalAFCS mode is GS;Altitude is above 50 feet AGL.

A glideslope failure is indicated by the above failure flagand all glideslope information is removed from the display.A miscompare between the glideslope deviation sourcesis indicated by the same failure flag but glideslope data isretained. The flag flashes for 5 seconds when themiscompare is first detected and thereafter remainsdisplayed until the condition is corrected.

+2 dots

12--70--55Vol. 1




MASTER


AP10

SYNCPRILOC 1GS

AVOR 1

21

1800

M .545240

220

200

180

160

--0.7 VS

21

30

2 000

100

900

800

00

000

1


--3.00 --3.00

--3.00 --3.00

Glideslope Line

Glideslope Readout

LOC 1

10.0 NM

190 GS

ADF1ADF2

Provides a visual reference of the desired glide path to beflown, as entered through the HGS control panel (HCP).The glideslope reference line also represents 0 glideslopedeviation when it overlays the glideslope line.Display criteria are:Always displayed during approach and landing, at anymode, except Rollout;In flight, other than during the approach and landingmodes, the reference line is displayed for five secondswhenever the selected glideslope value is changedthrough the HCP.

Provides an accurate indication of theairplane’s glideslope deviation.Glideslope deviation is 0 when theglideslope line is aligned with theglideslope reference line.Display criteria are:Displayed during approach and landing(AI, AII, AIII and F/D modes);Removed from the display 70 feet AGL.

Digital indication of the selectedreference glideslope value.Displayed in conjunction withthe glideslope reference line.

CRS 240

Lateral Deviation Line(In Flight)Provides an accurateindication of the airplane’slateral deviation from theselected course.Airplane is on track whenthe lateral deviation line isaligned with the selectedcourse mark (on thehorizon line).Displayed during HGSapproach and F/Dmodes.

REV 56, Jan 31/03





N33

1700

10.0 NM

190 GS

0.0 VS

21

30

800

00


Selected Course Bug

CRS 310

Bearing Source IndicatorsIndicates navigation sourceselected to obtain bearings.

Lateral Deviation Bar(Course Deviation Indicator)Indicates left or right deviation from VOR or LOCbeam.The CDI is limited to the edge of the coursedeviation scale in view. When the lateraldeviation is outside of the field of view, theCDI is ghosted (drawn with dashed lines).

To/From IndicatorTo--points to head side ofselected course bugFrom--points to tail side ofselected course bug.

VOR mode:

LOC mode (dependingupon runway length):

#1 Bearing Pointer

#2 Bearing Pointer

24W

30 36

ADF1ADF2

Bearing Pointers

#1 -- Pilot’s side

#2 -- Copilot’s side

10.0 NM

VOR 1

VOR 1

Course DeviationScale

When both ADFs aretuned to the samestation, the tails of thebearing pointers tendto appear merged.

NOTE

12--70--57Vol. 1




MASTER


AP10

SYNCPRIHDGALT

LOC 1GS

21

1700

M .545240

220

200

180

160

10.0 NM

190 GS

ADF1ADF2

0.0 VS

21

30

2 000

100

900

800

00

000

1

The HGS does not display aback course annunciation.

NOTE

A loss of valid information fromthe selected navigation sourcewill cause the correspondingnavigation data to be removedand the displayed navigationsource indicator is boxed, asshown above.

Navigation Source Failure Flags

A loss of valid localizer information fromthe selected navigation source will causethe CDI to be removed and a failure flag,as shown above is displayed.A miscompare between the two sources oflocalizer deviaiton is indicated by the samefailure flag but the CDI is retained. Theflag flashes for 5 seconds when themiscompare is first detected and thereafterremains displayed until the condition iscorrected.

Localizer Failure FLag

LOCLOC 1 LOC 2

VOR 1 VOR 2

REV 56, Jan 31/03




Primary Mode --- Flight Path IndicationsFigure 12---70---25 Sheet 1

Indicates bank relative to horizon.

10 10

AP10

SYNCPRIHDGALT

LOC 1GS

5 5

24

1700

--5 --5

M .545240

220

200

180

160

VOR 1

10.0 NM

190 GS

ADF1ADF2

0.0 VS

21

30

2 000

100

900

800

00

000

1

Centre of symbol indicates actual airplane flight path(lateral and vertical).The flight path symbol is limited laterally and verticallyso as not to overlay the indications at the edges of thedisplay (i.e. airspeed and altitude scales).The flight path symbol has a masking window whichobscures most other symbols it overlays except:Guidance cue; TCAS box; andRunway lines; Windshear message.Approach status message;

The flight path symbol is removed when an off--sideattitude or heading source is selected.

Flight Path Symbol

Guidance Cue

Provides lateral and vertical attitude guidance withcommand inputs from either the flight director (F/D) orthe HGS computer.Echos F/D commands during Primary (Flight) mode orF/D approach and landing mode.Displays HGS commands during Category I, II or IIIapproach and landing modes.

To track F/D or HGS commands, overlay the flight pathsymbol on the guidance cue, using normal pitch, roll andyaw control inputs.

Display conditions:During an approach, the F/D guidancecue is removed at 80 feet AGL unless:a windshear condition exists; orduring take--off or go--around, whenthe TO or GA mode is engaged.During an AI or an AII approach, theHGS guidance cue is removed at 80feet AGL.During an AIII approach, the HGSguidance cue is removed at touchdown.

5

5

24

-- Maskingwindow

12--70--59Vol. 1




MASTER

Primary Mode --- Flight Path IndicationsFigure 12---70---25 Sheet 2

10 10

AP10

SYNCPRIHDGALT

LOC 1GS

5 5

24

1700

--5 --5

M .545240

220

200

180

160

VOR 1

10.0 NM

190 GS

ADF1ADF2

0.0 VS

21

30

2 000

100

900

800

00

000

1

Acceleration Deceleration

On the ground

Provides an indication of when the flare maneuver shouldbe initiated, but not how to perform the flare maneuver.Display criteria:Displayed in flight during Primary (Flight) mode andF/D, VMC, AI and AII approach and landing modes.Comes on at 60 feet AGL, and flashes until 30feet AGL.

++

Flare Cue

Flight Path Acceleration Symbol

Displays the inertial acceleration of the airplane along theflight path.If displayed above the flight path symbol, the airplane isaccelerating. If displayed below the flight path symbol, theairplane is decelerating.On the ground, the flight path acceleration symbol isdisplayed off the left wing of the boresight symbol.During windshear conditions, below 400 feet AGL, the flightpath acceleration symbol is removed.The symbol has a masking window which obscures mostother symbols that it overlays except the guidance cue,runway lines, approach status message, TCAS box andwindshear messsage.

Displayed only during aCategory III approach. Providesguidance on how to perform thecorrect flare maneuver.

Flare Command(Double cross symbol)

(Single cross symbol)+

-- Maskingwindow

REV 56, Jan 31/03




Primary Mode --- Environmental IndicationsFigure 12---70---26

10 1030

SYNCPRIGAGA/WS

5 5

24

1700

--5 --5

M .545240

220

200

180

160

VOR 1

10.0 NM

GS

--0.9 VS

21

30

2 000

100

900

800

00

000

1

Wind Speed andDirectionDisplayed only in flightand when wind speedis more than 3 knots.Digital readoutindicates wind speedfrom 0 to 256 knots at1--knot increments.Wind vector (arrow)indicates relativedirection.

The windshear warningmessage is driven by theairplane’s GPWS. Themessage flashes initiallyfor 3 seconds, thencomes on steady toindicate that a severedecreasing performancewindshear condition hasbeen encountered.

(siren)“WINDSHEAR”“WINDSHEAR”“WINDSHEAR”

WINDSHEAR

WINDSHEARCAUTION

Displayed during a windshearwarning or caution, when below1,500 feet radio altitude, and / orwhen airplane is 25 from stickshaker point.Displays amount of pitch

attitude change that can bemade before airplane reachesstick shaker angle--of--attack.

The F/D guidance cue becomessolid and flashes for 3 seconds,then remains solid for as longas windshear escape guidance(TO/WS or GA/WS mode) isactive.

If the HGS is operating duringa windshear, the HGS primarymode (PRI) will automaticallypop--up to provide guidance.

NOTE F/D Guidance Cue(Windshear)

Windshear WarningMessage

Windshear CautionMessage

The windshear cautionmessage is driven by theairplane’s GPWS. Themessage indicates that anincreasing performancewindshear condition hasbeen encountered.

Pitch Limit Marker(alpha--margin indicator)

170

12--70--61Vol. 1




MASTER

Unusual Attitude DisplayFigure 12---70---27

900

000

100

800

700

--1.5 VS

10

240

220

200

180

160

This symbol provides anindication of which way is upduring unusual attitudes.Thesymbol is centered on the FlightPath symbol that points towardsthe Roll Pointer.

220 GS

Unusual Attitude Up Arrow

--5

15

15 21

10

10

NoteThe unusual attitude up arrowcomes on and asssociateddisplay declutter when:

REV 56, Jan 31/03




Primary Mode --- Autopilot/Flight DirectorFigure 12---70---28

During a Category IIIapproach, messagecomes on at 1,000feet and at 650 feetAGL to indicate thatthe autopilot must bedisconnected. Anapproach warningmessage comes on ifthe autopilot is notdisengaged by 500feet AGL.

Autopilot DisconnectMessage (flashing)

Mistrim FlagsDisplayed when autopilotmonitoring system detectsfailure in trim systems:

-- elevatormistrimmed.

-- aileronmistrimmed.

-- ruddermistrimmed.

FD2AP

1/2BNK

A

180

160

140

120

100

100

200

300

000

900

MAG2

EAR

Flight Director SourceThe on--side source isconsidered the normal sourceand is not annunciated.FD2 indicates that thecopilot’s (cross--side) flightdirector has been selected asthe source.

Flight Director Fail Flag

FD1Boxed flag indicates that selectedsource is invalid or flight directorhas failed.Guidance cue is simultaneouslyremoved.

FD2or

Flight DirectorGuidance Cue

Echos FDcommands.

Yaw DamperFailure FlagDisplayed whenyaw damper isdisengaged.

Indicates the following autopilotmodes;1/2 BNK -- Half bank selectedDR -- Dead reckoningTEST -- DiagnosticsSYNC -- Synchronize.

Autopilot Engagement AnnunciatorIndicates engagement/ disengagement / sidetransfer:Blank -- Indicates autopilot is notselected.AP -- Indicates autopilot has beenengaged (horizontal arrow points to coupledside).An autopilot disengagement isindicated by the AP characters flashingfor 2 seconds before being removed fromthe display. An EICAS aural warning (clacker)comes on.

1700

Autopilot Mode Annunciator

E

A

R

DISC

YD

12--70--63Vol. 1




MASTER

J. System Circuit Breakers


CBLOCATION

NOTES

Head--upGuidance HGS

AC ESS 3 C4GuidanceSystem

HGSDC ESS 4 C5

REV 56, Jan 31/03





chapter 12 --- flight instruments - smartcockpit...pilot’s and copilot’s instrument panels...

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