PILOT TRAINING GUIDE FLIGHT INSTRUMENTS - … of Contents For Training Purposes Only May 03 11-i...

Table of Contents

For Training Purposes OnlyMay 03

11-i

FLIGHT INSTRUMENTSP I L O T T R A I N I N G G U I D E

Introduction .......................................................................................................................11-1Electronic Flight Instrument System (EFIS) ................................................................11-1Components and Operations ......................................................................................11-2

Primary Flight Display ...........................................................................................11-2Multifunction Display .............................................................................................11-4

EFIS Comparator Monitor ...........................................................................................11-6Full-Time Comparator ...........................................................................................11-6Pitch ......................................................................................................................11-6Roll ........................................................................................................................11-6Heading.................................................................................................................11-6Altitude ..................................................................................................................11-7Indicated Airspeed ................................................................................................11-7Category II Comparator.........................................................................................11-8LOC Deviation.......................................................................................................11-8G/S Deviation ........................................................................................................11-8RA Deviation .........................................................................................................11-9Comparator Indications and EFIS Failure Displays ............................................11-10

Air Data System ..............................................................................................................11-12Pitot-Static System....................................................................................................11-12Temperature-Sensing System ..................................................................................11-14Air Data Computers (ADCs)......................................................................................11-14

Air Data Calculations...........................................................................................11-14Air Data Computations ........................................................................................11-14Air Data Transmission.........................................................................................11-15

Controls and Indicators ...................................................................................................11-16Display Control Panel................................................................................................11-16

Format/Range Knob............................................................................................11-16Navigation Source Knob .....................................................................................11-16Bearing Pointers..................................................................................................11-16Information Overlay Buttons................................................................................11-16

Air Data Reference Panel .........................................................................................11-18Speed Reference Section ...................................................................................11-18Altitude Reference Section..................................................................................11-18Barometric Pressure Section ..............................................................................11-19

PFD Displays ............................................................................................................11-20Attitude Display ...................................................................................................11-20Slip/Skid indicator................................................................................................11-20Unusual Attitude Display .....................................................................................11-20Airspeed Displays ...............................................................................................11-22Altitude Displays..................................................................................................11-26Vertical Speed Display ........................................................................................11-30Navigation Displays.............................................................................................11-32

FLIGHT INSTRUMENTS

11-ii For Training Purposes OnlyMay 03

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

Multifunction Display Formats................................................................................... 11-34HSI Format.......................................................................................................... 11-35NAV Sector Format ............................................................................................. 11-38FMS Map Format ................................................................................................ 11-40Plan Map Format................................................................................................. 11-42TCAS Format ...................................................................................................... 11-43

Radio Altimeter ............................................................................................................... 11-44Description ................................................................................................................ 11-44Components and Operation...................................................................................... 11-44

Receiver/Transmitter........................................................................................... 11-44Antennae............................................................................................................. 11-44

Radio Altitude Display............................................................................................... 11-45Analog Radio Altitude Scale................................................................................ 11-45Ground Bar (Rising Runway) .............................................................................. 11-45

Standby Instruments ....................................................................................................... 11-47Standby Airspeed Indicator....................................................................................... 11-47Standby Altimeter...................................................................................................... 11-48Standby Attitude Indicator......................................................................................... 11-48Standby Compass..................................................................................................... 11-49

Aircraft Clocks................................................................................................................. 11-50Display Reversionary Panel ...................................................................................... 11-52

Abnormal Conditions........................................................................................... 11-52EICAS Messages...................................................................................................... 11-54

List of FiguresGraphic Title Figure


11-iii

FLIGHT INSTRUMENTSP I L O T T R A I N I N G G U I D E

Electronic Flight Displays..................................................................................................11-1Primary Flight Display (PFD) ............................................................................................11-2Multifunction Display (MFD)..............................................................................................11-3Altitude Comparator Graph ...............................................................................................11-4Radar Altimeter Deviation Limits Graph............................................................................11-5PFD Comparator Annunciations .......................................................................................11-6PFD Failure Displays ........................................................................................................11-7Pitot-Static Systems..........................................................................................................11-8Display Control Panel .......................................................................................................11-9Air Data Reference Panel ...............................................................................................11-10PFD Attitude Displays .....................................................................................................11-11PFD Airspeed Display and Underspeed / Overspeed Cues ...........................................11-12Speed Reference (Bug) Field .........................................................................................11-13PFD Altitude Displays .....................................................................................................11-14MDA and DH Displays ....................................................................................................11-15PFD Vertical Speed Display............................................................................................11-16Marker Beacon Annunciations ........................................................................................11-17PFD HSI Display .............................................................................................................11-18MFD Radar Mode and Status Lines................................................................................11-19MFD HSI Format.............................................................................................................11-20MFD Sector Format ........................................................................................................11-21MFD Data Window..........................................................................................................11-22MFD FMS Plan Map Format ...........................................................................................11-23MFD TCAS Format .........................................................................................................11-24Radar Altimeter Display ..................................................................................................11-25Standby Instruments Locator ..........................................................................................11-26Standby Airspeed Indicator.............................................................................................11-27Standby Altimeter............................................................................................................11-28Standby Attitude Indicator...............................................................................................11-29Standby Compass...........................................................................................................11-30Clock Prior to A/C 5331 ..................................................................................................11-31Clock A/C 5331 and Later...............................................................................................11-32Display Reversionary Panel ............................................................................................11-33

11-iv For Training Purposes OnlyMay 03

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

Page Intentionally Left Blank

FLIGHT INSTRUMENTS


11-1


CHAPTER 11: FLIGHT INSTRUMENTS

IntroductionThe flight instruments chapter includes the Electronic Flight Instruments System (EFIS), Air Data System (ADS), standby instruments, clock and radio altimeter.

Electronic Flight Instrument System (EFIS)The Electronic Flight Instrument System (EFIS) takes input data from airplane radios, sensors and control panels and displays the information on four Electronic Flight Displays (EFDs).

Two of the EFDs function as primary flight displays (PFD), and two EFDs function as multifunction displays (MFDs).

The color conventions used for the PFD and MFD symbology are:

Electronic Flight Displays Figure 11-1

White For all scales and on-side FMS sensor data

Green For on-side sensor data (non-FMS)

Yellow For cross-side sensor data and caution information

Magenta For pilot-selectable data

Cyan For secondary information

Red For warnings and failure flags

P6

04

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47

VFE (45 FLAPS)VFE (30 FLAPS)VFE (20 FLAPS)VA (MANEUVERING)(AT SEA LEVEL 48,200LB)(AT 20,000FT 26,000LB)VNO (BELOW 8,000FT)VNO (8,000 TO 22,150 FT)

AIRSPEED LIMITS - (INDICATED SPEEDS)

MMO (22,150FT TO 26,570FT)VMO (26,570FT TO 30,990FT)MMO (30,990FT TO 41,000FT)VLO (EXT) (L/G EXTENSION)VLO (RET) (L/G RETRACTION)VLE (L/G EXTENDED)

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512

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EICAS

EFD

PFD 1 MFD 1 PFD 2MFD 2

FLIGHT INSTRUMENTS

11-2 For Training Purposes OnlyMay 03


Components and Operations

Primary Flight Display

The Primary Flight Display (PFD) presents the flight instruments in a typical “T” formation, which includes both the Attitude Director Indicator (ADI) and the Horizontal Situation Indicator (HSI).

The two PFDs are the outboard EFDs of the instrument panel. The PFDs come on automatically upon receiving DC power.

The following data is displayed on the PFD:

• Attitude• Heading• Airspeed• Altitude• Vertical Speed• Flight Mode Annunciators• Nav source and navigation information• HSI

FLIGHT INSTRUMENTS


11-3


Primary Flight Display (PFD) Figure 11-2

80

60

40VT 150

V2 133

VR 121

V1 113

20

10

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100

000

8000

RA2IRS2ADC2DCP2

TERM

VOR1

HDG 340

TRU

NO FLIGHT PLAN

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29.85 IN

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TOLOC 1

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AttitudeIndicator

AirspeedTape

Nav Source

Flight ModeAnnunciators

Altitude

VerticalSpeed

Heading

HorizontalSituationIndicatorNavigation

Information

FLIGHT INSTRUMENTS



Multifunction Display

The MFDs present navigation information in pilot-selectable formats.

The MFDs are the displays located inboard of the PFDs. Like the PFDs, they come on automatically upon receiving DC power. The MFDs also provide reversionary backup displays for the PFD or the EICAS.

The following page formats may be displayed on the MFDs:

• HSI• Nav Sector Map• FMS Map• Plan Map• TCAS

Additional MFD information includes:

• Weather Radar• Terrain data (if EGPWS installed)• Checklist (operated from the EICAS Control Panel)• Reversion to PFD or EICAS• Remote Text (Maintenance Diagnostic Computer and FMS Text)

FLIGHT INSTRUMENTS

For Training Purposes OnlySept 04

11-5


Multifunction Display (MFD) Figure 11-3

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MFD FORMATS

ADDITIONAL INFORMATION DISPLAYS

FLIGHT INSTRUMENTS



EFIS Comparator MonitorData displayed on the two PFDs is continuously compared for deviations. When defined trip levels are exceeded, the EFIS COMP MON caution EICAS message is displayed, and the flashing MASTER CAUTION lights are triggered.

The comparator monitor has two sections; the full-time comparators and the Category II comparators.

Full-Time Comparator

Full-time comparator warning is performed for pitch, roll, heading, altitude and airspeed data. Comparator warnings appear in yellow and flash temporarily on the PFD. They then remain displayed while the condition exists.

A subsequent EFIS comparator monitor indication will not cause another Master Caution to flash. Only the comparator indication on the PFD will flash.

Pitch

Pitch comparator monitoring is enabled if both sides are using different Inertial Reference System (IRS) sources and both sources have not failed (any ATT flag). When enabled, if the pilot’s and copilot’s displayed pitch difference is greater than 4° when en route, or greater than 3° during approach, the pitch comparator warning “PIT” shows on the attitude indicator.

Roll

Roll comparator monitoring is enabled if both sides are using different IRS sources, and both sources have not failed (any ATT flag). When enabled, if the pilot’s and copilot’s roll difference is greater than 4° when en route, or greater than 3° during approach, the comparator warning “ROL” shows on the attitude indicator.

Heading

The heading comparator is enabled when:

• both sides are using the same heading reference (MAG or TRU)• both sides are using different IRS sources, and • both sources have not failed (no HDG flag)

If the heading comparator is enabled and the heading difference is greater than 6°, the heading comparator warning “HDG” shows on the compass arc.

NOTE

FLIGHT INSTRUMENTS


11-7


Altitude

The altitude comparator is enabled if both sides are using different air data sources and both sides have not failed (no ALT flag). If the altitude comparator is enabled and the altitude difference is not within limits, the altitude comparator warning “ALT” shows vertically on the lower portion of the altitude scale. As the altitude increases, so do the altitude difference limits, as indicated by the following formula: if the ALT difference exceeds [60 + (pilot’s altitude + copilot’s altitude)/460] feet, the altitude comparator warning shows.

Altitude Comparator Graph Figure 11-4

Indicated Airspeed

The airspeed comparator is enabled if both sides are using different air data sources, both sides have not failed (no IAS flag), and the indicated airspeed is greater than 90 knots. If the airspeed comparator is enabled and the airspeed difference is greater than 10 knots, the airspeed comparator warning “IAS” shows on the upper portion of the airspeed scale.

The following table summarizes the trip values for the full-time comparator monitoring functions:

250

150

0

Alt

ime

ter

dif

fere

nc

e

Altitude difference = [60 + (pilot’s altitude + copilot’s altitude)/460]

0 10,000 15,000

P6

04

_11

_0

45

300

200

100

50

5,000 20,000 25,000 30,000 35,000 40,000 45,000

Aircraft Altitude

FLIGHT INSTRUMENTS



Category II Comparator

Category II comparators are enabled if approach mode is selected and the DH is set below 200 feet. Comparator monitoring is performed for LOC, G/S and Radio Altimeter deviations.

The following conditions must be valid to enable the CAT II comparisons:

• the on-side RA is valid and RA is less than 1000 feet• the cross-side data is valid• the LOC on both sides are tuned identically and are valid• approach mode is selected

LOC Deviation

When the LOC comparator is enabled and the pilot’s and copilot’s lateral deviations differ by more than a predetermined amount, a yellow “LOC” comparator flag shows in the compass arc. The amount of difference allowed varies with the location of the pilot’s localizer. As the pilot’s localizer moves toward the center of the display, the comparison tolerance decreases.

For example, when the pilot’s side deviation pointer is at the center of the scale, the comparator allows up to approximately +½ dots of deviation error on the copilot’s side before showing the comparator warning flag.

G/S Deviation

When the G/S comparator is enabled and the pilot’s and copilot’s lateral deviations differ by more than a predetermined amount, a yellow “GS” comparator flag shows below the glideslope scale. The limits vary with the position of the pilot’s deviation pointer. As it moves closer to the centerline of the scale, the comparison tolerance decreases.

SYSTEM FLAG VALUE

HEADING HDG > 6°

ROLL ROL > 3° Approach, > 4° En route

PITCH PIT > 3° Approach, > 4° En route

ALTITUDE ALT 60 ft with BARO set within 0.02 inches.The amount of difference required to trigger the flag increases as altitude increases.

AIRSPEED IAS > 10 kts above 90 kts

FLIGHT INSTRUMENTS


11-9


For example, when the pilot’s side deviation pointer is at the center of the scale, the comparator allows up to approximately +¾ dots of deviation error on the copilot’s side before showing the comparator warning flag.

RA Deviation

When the RA comparator is enabled and the pilot’s and copilot’s RA difference is not within limits, a yellow “RA” comparator flag shows below the attitude indicator. To enable the RA comparator, the on-side RA altitude is less than 1000 feet and the cross-side RA is valid. As the altitude increases, so do the RA difference limits increase as per the following formula: [30 feet + 0.028 X (pilot’s RA height + copilot’s RA height)].

Radar Altimeter Deviation Limits Graph Figure 11-5

100

70

60

40

30

0

Ra

dio

Alt

ime

ter

dif

fere

nc

e

Altitude difference = [30 + 0.028 X (pilot’s RA height + copilot’s RA height)]

RAD ALT Diff

0 250 500 750 1000

P6

04

_11

_0

31

ALT Diff90

80

50

20

10

Aircraft Altitude

FLIGHT INSTRUMENTS



Comparator Indications and EFIS Failure Displays

The Comparator warning icon on the PFD will remain displayed while the condition exists. If the comparator monitor fails, the Amber EFIS COMP MON INOP caution EICAS message is displayed, and the flashing MASTER CAUTION lights will be triggered.

PFD Comparator Annunciations Figure 11-6

The failure of a selected source removes the respective scale or display and presents a red flag.

PFD Failure Displays Figure 11-7

2R

T

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ADF1

NO FLIGHT PLAN

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N33

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1

580MDA

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ALTS PATH GS2500

IAS

ROL PIT

GS

RA

LOC HDG

ALT

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FD

143

IAS

ADF1

CRS

- - - NM

MSG1MSG2

310

NO FLIGHT PLAN

N33

30

W24

E6

3

FDATT

GS

LOC

RA

TRUDCP2

LOC1FMS1

ADF2

ALTVS

GS

1

AirspeedFlag

FlightDirectorFlag

AttitudeFlag

DisplayControl PanelSource Flag

NavigationSource Flag

VerticalDeviationFlag

BarometricAltitudeFlag

VerticalSpeedFlag

OvertemperatureWarning

RadioAltitudeFlag

HeadingFlag

P6

04

_11

_0

18

DISPLAY TEMP

Expanded LateralDeviation Flag

FLIGHT INSTRUMENTS


11-11


The following Failure Flags are available:

Failure flag label Meaning Items removed from display

ALT Air Data Computer failure Barometric altitude tapes, digital altitude readout, preselected altitude reference, digital preselect altitude, metric altitude readout and metric preselected altitude

ATT Inertial Reference System failure

Sky/ground raster, pitch tape, roll pointer, roll scale, slip/skid indicator

DCP Display Control Panel failure Flight director bars

MAG, TRK, TRU Heading Sensor input failure

Inertial Reference System failure

The heading display is not removed, but the heading is not updated

FD Flight Director failure Flight director bars

FMS/GS/LOC/VOR Respective Navigation System failure

Flight director bars

Lateral deviation scale

Red boxed Nav Source

GS Glideslope failure Vertical deviation scale and pointer

IAS Air Data Computer failure Airspeed tape and information

VS Air Data Computer failure Vertical speed scale pointer, digital readout

RA Radio Altimeter failure Analog radio altitude symbology, analog decision height marker and digital radio altitude

FLIGHT INSTRUMENTS



Air Data SystemThe Air Data System (ADS) uses air pressure and temperature information to calculate all of the parameters related to flight. It supplies the following information to EFIS for display:

• Altitude (ALT)• Indicated Airspeed (IAS)• Vertical speed (VS)• True airspeed (TAS)• Static Air Temperature (SAT), and • Total Air Temperature (TAT)

The ADS also provides computed data to:

• Inertial Reference System (IRS)• Flight Data Recorder (FDR)• Stall Protection and Flap systems• Air Traffic Control (ATC) transponders• Traffic Collision Avoidance System• Automatic Flight Control System (AFCS), and• Engine Indication and Crew Alerting System (EICAS)

The Air Data System contains the following subsystems:

• Pitot-Static System• Temperature Sensing System• Air Data Computer System (ADC)• Air Data Reference Panels (ADRPs)

Pitot-Static SystemThe pitot-static system includes:

• two main pitot-static systems• one standby pitot-static system

The two main pitot-static systems designated P1/S1 and P2/S2 supply variable pressure inputs to the ADCs. The pitot pressure is sensed through an opening in the forward end of the pitot heads. The static pressure is ported through eight holes on the contoured midsection of the pitot head. Each static port consists of four holes; two on the upper side and two on the lower side of the pitot head. The S1 static port holes are forward and the S2 holes are aft along the pitot head. The contoured surface provides aerodynamic compensation to correct static pressure position error.

FLIGHT INSTRUMENTS


11-13


The P3 standby pitot system supplies pitot air pressure to the standby airspeed indicator. Two S3 standby static ports supply static pressure to the Cabin Pressure Acquisition Module (CPAM) Cabin Pressure Controller, standby airspeed indicator and standby altimeter.

Ice Protection is provided by electric heating elements for all pitot-static probes.

Pitot-Static Systems Figure 11-8

StandbyALT

StandbyASI

P6

04

_11

_0

27

S1P1

NO. 1ADC

CENTERINSTRUMENT PANEL

Pilot's Pitot Pressure

Copilot's Pitot Pressure

Pilot's Static Pressure

Copilot's Static Pressure

LEGEND

Pitot Pressure

Static Pressure

TAT Probe Line

CABIN PRESS CTRLS3

STANDBYPITOT(P3)

PILOT’SPITOT-STATIC

(P1S1)

LEFTSTATIC PORT

(S3)

RIGHTSTATIC PORT

(S3)

COPILOT’SPITOT-STATIC

(P2 )S2

TAT PROBE

S2 P2

NO. 2ADC

CPAMS3

S3 S3

P3

FLIGHT INSTRUMENTS



Temperature-Sensing SystemThe temperature-sensing system receives data from a Total Air Temperature (TAT) Probe. The ADCs use the outputs from the probe to calculate the Static Air Temperature (SAT) and the True Airspeed (TAS)/Mach number. This information is displayed on the Primary Flight Displays (PFDs) and Multifunction Displays (MFDs).

Ice Protection is provided by electric heating elements.

Air Data Computers (ADCs)The ADCs are digital, microprocessor-controlled units. The two ADCs receive on-side pitot and static air pressure information from the pitot-static system and air temperature information from the TAT probe.

The ADCs also receive operator/display selected input from the ADRPs and the Automatic Flight Control System (AFCS). From these inputs, the ADC calculates all necessary air data parameters and transmits the information to the applicable systems.

Air Data Calculations

The ADC calculates air data parameters for the following:

• Pressure altitude (corrected for static-port pressure errors)• Barometric corrected altitude (inches of mercury or hectopascals)• Vertical Speed• Indicated airspeed (IAS)/Calibrated airspeed (CAS)• Mach number• Maximum airspeed (VMO/MMO)• True airspeed (TAS)• Static air temperature (SAT)• Total air temperature (TAT)

Air Data Computations

The ADC computes data for the following:

• Preselect altitude• Vertical speed reference• Airspeed reference• Mach reference• IAS trend vector• Secondary speed reference (V1, VR, V2 and VT)• Flap overspeed limits (231, 197 and 189 Kts)

FLIGHT INSTRUMENTS


11-15


Air Data Transmission

The ADC sends the computed air data to the following systems and components:

• Flight Data Recorder (FDR)• Radio Tuning Unit (RTU)• Mode S Transponder• Traffic Alert and Collision Avoidance System (TCAS)• Primary Flight Display (PFD)/Multifunction Display (MFD)• AFCS• IRSs• DCUs• Ground Proximity Warning System (GPWS)• Horizontal Stabilizer Trim Control Unit (HSTCU)• Stall protection computer• Flap Electronic Control Unit (FECU)

FLIGHT INSTRUMENTS



Controls and Indicators

Display Control PanelThe DCP provides the pilot and copilot with the controls needed to select the desired navigational features of the EFIS system. For the PFDs, this includes lateral and vertical navigation source information and bearing pointers. For the MFDs, this includes the format, range and display overlays. Each MFD/PFD pair has a dedicated DCP. If one of the DCPs should fail, the other DCP may be used to control both EFIS displays.

Format/Range Knob

Turning the (outer) FORMAT knob selects a desired on-side MFD display format for the associated MFD. There are five selectable display formats: HSI, NAV Sector, FMS Map, Plan Map and TCAS. The (inner) RANGE knob varies the display range scale on the MFD.

Navigation Source Knob

The NAV SOURCE knob selects the active navigation source. This action controls the selection of displayed information on each pilot’s PFD/MFD. Possible selections are FMS 1, VOR 1, (or LOC 1), VOR 2 (or LOC 2) FMS 2 and FMS 3. Pushing the center of the knob alternately adds or removes cross-side NAV data on the MFD HSI and NAV sector displays only.

Bearing Pointers

The single-bar BRG pointer selects the No. 1 Bearing pointer for each pilot’s PFD/MFD. Possible selections are VOR 1, ADF 1, FMS 1, and FMS 3 (if installed). The double-bar BRG pointer selects the No. 2 Bearing pointer for each pilot’s PFD/MFD. Possible selections are VOR 2, ADF 2, FMS 2, and FMS 3 (if installed).

Information Overlay Buttons

The WX button selects weather radar and lightning detection system depictions on the MFD. This button sequentially selects weather radar information, or adds radar/lightning overlays. The Weather Radar is available on all dynamic map MFD formats, but is not available for HSI and Plan Map. The TFC button alternately selects or deselects the TCAS Traffic Map Overlay display on the associated MFD. The TERR button selects the terrain information and replaces the Weather Radar information. For more details about terrain overlay information, see the EGPWS section in Chapter 17 Navigation Systems.

FLIGHT INSTRUMENTS


11-17


Display Control Panel Figure 11-9

NAVSOURCE

FORMAT RANGE

BRG TERR WX TFC

PUSH

X- S I D

E

P6

04

_11

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03

Weather Radar DisplaySelect SwitchUsed to select ordeselect Weather RadarDisplay

MFD FormatSelector SwitchUsed to select basicformat/modedisplayed on MFD

Range SelectorSwitchUsed to select rangedisplayed on MFD

TFC SwitchUsed to directly selectTCAS traffic display onMFD

Cross-Side CourseSelection Push-Button SwitchUsed only on MFD;in HSI and NAVSector formats

Terrain InformationDisplay Select SwitchUsed to select ordeselect TerrainInformation Display

No. 1 Bearing PointerSource SwitchPush to select No. 1source

No. 2 Bearing PointerSource SwitchPush to select No. 2source

Navigation SourceKnobRotate to selectnavigation source

FLIGHT INSTRUMENTS



Air Data Reference PanelThe Air Data Reference Panel (ADRP) is used to set speed, altitude and barometric pressure values, which are then sent to the EFIS for display. The two ADRPs are installed on the center pedestal. Each panel has three rotary knobs with inset pushbutton switches. The panel is divided into three sections: the speed reference section, the altitude reference section and the barometric pressure section.

• the Speed Reference section is used to make changes to airspeed references (V1, VR, V2 and VT)

• the Altitude Reference section is used to control the Minimum Descent Altitude (MDA) and Decision Height (DH) display on the EFIS. It also incorporates a test switch for the Radio Altimeter (RA)

• the Barometric Pressure section is used to make changes to the ADC barometric correction function

Speed Reference Section

To manually change the speeds posted on the V-Speed table, turn the TGT/VSPDS outer knob to either TGT (VT), or VSPDS (V1, VR and V2). Rotate the SET (inner) knob to change the speed values. In the VSPDS position the reference speeds can be alternately edited by pushing the SEL button and rotating the SET knob. The SET switch (inner knob) enables/disables the PFD display of the selected target or reference airspeed. These speeds are displayed below the IAS scale on the PFD and are located on the speed tape in their respective positions (V1, VR, V2 and VT).

Manually entered V-speeds will be displayed in cyan. For Precision-Plus-equipped aircraft, V-speeds can be computed and entered via the FMS where they will be displayed in cyan. Manually entered V-speeds in Precision-Plus-equipped aircraft are displayed in magenta.

Altitude Reference Section

To change the altitude value displayed for either the Minimum Descent Altitude (MDA) or the Decision Height (DH), rotate the DH/MDA (outer) knob to select the altitude to be amended. The SET (inner knob) switch is rotated to change the values. These altitudes are displayed on the PFD below the altitude scale. The SET switch is pushed to enable or disable the display of either the DH or the MDA.

The Radio Altimeter (RA) test switch is depressed to conduct an internal test on the Radio Altimeter. The RA value on the bottom of the Attitude Direction Indicator will change to 50 feet and the rising runway symbology, located on the Radio Altimeter analog scale, moves down 50 feet.

FLIGHT INSTRUMENTS


11-19


Barometric Pressure Section

The Barometric (BARO) knob changes the barometric pressure. Pushing the SET switch selects standard barometric pressure (29.92 inches of mercury, or 1013 hectopascals). The value is displayed below the PFD altitude scale. The HPA/IN switch alternately selects barometric pressure correction in hectopascals (hPa), or inches of mercury (inHg).

Air Data Reference Panel Figure 11-10

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44

P

USH

SET

O F F

SEL

SPEED REFSTGT VSPDS

BARO

HPA/INDH MDA

RA TEST

P

USH

SET

O F F

PUSH

ST D

SEL ButtonToggles between V ,V or V

1

R 2

SPEED REFS KnobOuter knob

Inner set knob

PUSH OFF

- Selects targetspeed or V speeds V , V , V .

- Adjusts value ofselected V-speed.

- Removes display ofselected speed.

VT 1 R 2

RA TESTInitiates radioaltimeter test

BARO KnobKnob - rotate to setbarometric pressure.

HPA/INToggles between hPa/mbor inches of mercury

DH/MDA KnobOuter knobInner set knob

PUSH OFF

- Select DH/MDA.- Rotate to

set.- removes display

from PFD.

FLIGHT INSTRUMENTS

11-20 For Training Purposes OnlyJan 04


PFD Displays

Attitude Display

The attitude symbology provides pitch, roll and slip/skid information. IRS information is used to drive the attitude symbology. An inverted black V-bar airplane symbol denotes the aircraft’s relative attitude on the Attitude Director Indicator (ADI).

Large-scale markings are placed at 10, 20, 30, 40, 50, and 65 degrees of pitch. Medium markings are placed at 5-degree intervals up to ± 30 degrees. Small tick marks are placed at 2.5-degree intervals up to ± 20 degrees.

Roll scale markings are used to indicate airplane roll angles between ± 60 degrees. The roll pointer is used with the roll scale to indicate the airplane roll angle. The pointer is oriented perpendicular to the horizon line and next to the roll scale to represent degrees of roll (bank) angle. The roll pointer rotates about the center of the airplane symbol in response to changes in airplane roll angle.

Slip/Skid indicator

The slip/skid indicator is located just below the roll pointer and approximates the displacement of an inclinometer. The indicator is a small rectangular symbol. The slip/skid indicator is driven by lateral accelerations.

Unusual Attitude Display

If the airplane is flown into an unusual attitude, all non-necessary indications are removed. Unusual attitudes occur when pitch exceeds +30 degrees (up), or –20 degrees (down), or when roll exceeds 65 degrees. During excessive attitude, only pitch, roll airspeed and altitude are displayed. Red chevrons point toward zero in extreme pitch attitudes. A portion of blue or brown coloring representing sky or ground remains displayed, regardless of pitch attitude, to assist with orientation.

FLIGHT INSTRUMENTS


11-21


PFD Attitude Displays Figure 11-11

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NORMAL ATTITUDE DISPLAY

UNUSUAL PITCH ATTITUDE UNUSUAL BANK ANGLE ATTITUDE

3

Roll Pointer

Slip/SkidIndicator

Roll Scale Roll Pointer

Slip/SkidIndicator

PitchScale

FLIGHT INSTRUMENTS



Airspeed Displays

IAS ScaleThe indicated airspeed scale is a vertical “moving tape” display. The IAS scale contains a line marking every 5 and 10 knots and a numeric label every 20 knots. If airspeed data becomes invalid, the scale is replaced with a red IAS annunciation.

IAS PointerThis stationary triangle is displayed at the center of the IAS window. The current indicated airspeed is the IAS scale indication at the pointer.

IAS Trend VectorThe IAS Trend Vector is a magenta line that extends from the IAS pointer to predicted future airspeed. The head of the trend vector aligns with the IAS scale to predict what the airspeed will be in 10 seconds (if present acceleration is maintained). The vector extends up as airspeed increases and down as airspeed decreases. The trend vector is not displayed when the airplane is on the ground.

Mach DisplayThe current indicated Mach speed automatically displays below the airspeed scale with an M label as Mach increases above 0.450. This display is removed when Mach decreases below 0.400. Mach display changes in 0.002 increments.

Overspeed CueThe overspeed reference is shown de-emphasized (red triple-width vertical bar) on the airspeed scale ascending from VMO/MMO to the top of the airspeed tape. The de-emphasized overspeed reference changes to an emphasized overspeed reference (red and gray checkerboard symbol) when the airspeed is two knots or greater into the VMO/MMO region. The de-emphasized overspeed reference also changes to an emphasized overspeed reference when the airspeed trend has been two knots or greater into the VMO/MMO region for five seconds or more.

Low Speed CueThe Low Speed Cue indicates the aircraft’s impending stall speed and is generated by Angle-of-Attack information from the Auxiliary Angle-of-Attack vane. The Low Speed Cue indication is shown de-emphasized (red triple-width vertical bar) on the airspeed scale descending from impending stall speed to the bottom of the airspeed tape. The de-emphasized cue changes to an emphasized cue (red and gray checkerboard symbol) when airspeed is two knots or greater into the impending stall speed region. The de-emphasized cue also changes to an emphasized cue when the airspeed trend has been two knots or greater into the impending stall speed region for five seconds or more.

FLIGHT INSTRUMENTS


11-23


PFD Airspeed Display and Underspeed / Overspeed Cues Figure 11-12

Speed Reference (Bug) FieldThis line display shows a selected speed reference (bug) value that can be controlled using either Air Data Reference Panel (ADRP). The SPEED REFS knob and SEL button are used to sequentially select one of four available bugs, 1, R, 2, or T, corresponding to (V1, VR, V2, or VT) for display in this field.

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IAS Scale

IAS Pointer

Mach Display

IAS Trend Vector

FLIGHT INSTRUMENTS



The SET knob on the ADRP is used to change this value. The PUSH OFF switch on the ADRP enables/disables display of the selected bug. The bug position on the IAS scale automatically updates as the numeric values change. After five seconds of inactivity, the speed reference field display blanks.

Speed Reference (Bug) TableThe table displays on the lower portion of the IAS scale when airspeed is less than 40 knots. When the table displays, use the ADRP to select and change one of four airspeed bugs (V1, VR, V2 or VT).

For Precision-Plus-equipped aircraft, V-speeds can be computed and entered via the FMS.

V1 BugThe reference marker is a cyan line followed by a 1. The V1 bug is the takeoff decision speed reference. The V1 bug is automatically removed at lift-off.

VR BugThe reference marker is a cyan line followed by an R. The VR bug is the rotation speed reference. The bug display is automatically removed after the V2 speed is exceeded.

V2 BugThe reference marker is a cyan line followed by a 2. The V2 bug is the takeoff safety speed reference. The bug display is automatically removed after the V2 speed is exceeded (V2 + 40 knots + weight off wheels for 7 seconds).

VT BugThe reference marker is a cyan line followed by a T. The VT bug is the target speed reference.

IAS Reference FieldThe magenta display shows the selected IAS reference value. The value is marked by the notched-box (bucket) symbol on the IAS scale. Turn the SPEED knob on the FCP to set this value. While in Mach mode, turning the SPEED knob then sets a magenta selected Mach number at the top of the IAS scale and correspondingly moves the notched-box symbol on the IAS scale.

NOTE

FLIGHT INSTRUMENTS


11-25


IAS Reference MarkerThe magenta notched-box symbol is the IAS reference marker. The IAS reference marker is always selected for display and is set by the SPEED knob on the FCP. While in Mach mode, the IAS reference marker corresponds to the selected Mach number set in the reference field at the top of the IAS scale.

Speed Reference (Bug) Field Figure 11-13

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DISPLAY BEFORE TAKEOFF

DISPLAY BEFORE ROTATION DISPLAY WHEN AIRBORNE

ManuallyEnteredV Speeds

FMSComputedV Speeds

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IASReferenceField

IASReferenceMarker(Bucket)

FLIGHT INSTRUMENTS



Altitude Displays

Barometric Altitude DisplayThe display simulates a rolling drum mechanism and is outlined by a white window. The present barometric corrected altitude displayed is the sum of the numeric “thousands” readout and the “hundreds” moving tape indication at the window. If barometric altitude data becomes invalid, the altitude displays are replaced with a red ALT annunciation.

A metric barometric altitude readout may also be displayed below the pressure display. This boxed readout with an “M” label displays the barometric altitude in meters.

Fine Barometric Altitude ScaleThe fine barometric altitude scale is a vertical “moving tape” display. The display window range is 450 feet. The scale contains a line marking every 20 feet and a numeric label every 100 feet. The scale moves down for increasing altitude.

Coarse Barometric Altitude ScaleThe coarse barometric altitude scale is a non-numbered vertical “moving tape” display that helps visualize (preselected) altitude captures. Large rectangles on the scale represent 1000-feet altitude increments and small rectangles represent 500-foot increments. The display window range is 2250 feet. The scale moves down for increasing altitude.

Barometric Pressure DisplayBarometric pressure correction is numerically displayed in either inches of mercury or in hectopascals (hPa). The correction value and format are set by the on-side ADRP.

Preselect Altitude DisplayThe preselected altitude is numerically displayed in magenta above the barometric altitude scales. The ALT knob on the FCP sets the value.

A metric preselected altitude readout with an “M” label may also be displayed below the normal display. The boxed readout displays the preselected altitude in meters.

NOTE

NOTE

FLIGHT INSTRUMENTS


11-27


PFD Altitude Displays Figure 11-14

Preselect Altitude BugThe ALT set knob on the FCP is used to set the preselected altitude value. The preset altitude is displayed on the top of the altitude scale in magenta, and as a window on the coarse and fine altitude scales.

This four-line marker displays on the coarse and fine barometric altitude scales to mark the preselected altitude value. The marker is always in view on the coarse barometric altitude scale and then shows on the fine barometric altitude scale when in range.

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CoarseAltitudeScale

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PreselectAltitude

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PreselectAltitude Bug(Coarse Scale)

PreselectAltitude Bug(Fine Scale)

Selected AltitudeMetric Readout

Altitude MetricReadout

BarometricPressureDisplay

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FLIGHT INSTRUMENTS



The preselected altitude display and bug both change colors and/or flash as the airplane acquires a preselected altitude. These displays are normally magenta. Both displays flash magenta when the airplane approaches the preselected altitude and then become steady again at altitude capture.

Preselect Altitude WarningsPreselect altitude warnings provide aural and visual signals. The aural warning signal is a one-second C-chord tone. After capture, the digital display flashes amber for minor altitude deviations. The bug and numeric display both flash amber for major altitude deviations.

The Air Data Computers use the preselected altitude data to initiate two different types of cues and warnings. These cues and warnings are initiated when the difference between the preselected and barometric altitude is greater than the programmed limits. The programmed limits are:

• minor deviation is ± 200 feet• major deviation is ± 1000 feet

(See Chapter 4 Automatic Flight Control System for additional altitude preselect tracking information)

Preselect Altitude Cross-Side TrackingEach ADC receives the preselected altitude via its on-side ADRP and the cross data bus. The ADCs compare the preselected altitude values of the two computers. If the values are not equal due to a bus failure, the digital preselect altitude indication changes from magenta to cyan when the adjustment knob is turned. If full bus operation is recovered, the two sides will synchronize to the value held by the coupled side ADC. The indication returns to magenta after synchronization has been achieved.

MDA DisplayThe Minimum Descent Altitude (MDA) is numerically displayed below the altitude scale. The on-side ADRP is used to select this display and set the appropriate value. An MDA alert displays near the left center of the ADI when the airplane is at the Minimum Descent Altitude. During the MDA alert the icon flashes yellow.

MDA PointerA cyan pointer marks the selected Minimum Descent Altitude on the fine barometric altitude scale. This pointer appears when the MDA display is selected and the value is in the display range. This pointer flashes during an MDA alert.

FLIGHT INSTRUMENTS

For Training Purposes OnlyJan 04

11-29


Decision Height DisplayThe Decision Height value is selected for display and set by the on-side ADRP. If this display is selected, it is automatically displayed once the aircraft has descended through 2500 feet above ground. If Decision Height data becomes invalid, the numeric values are replaced with red dashes.

A DH alert displays when the airplane is at or below Decision Height. On the right center of the attitude indicator, DH flashes in yellow, accompanied by the voice alert “MINIMUMS”.

There is also a DH Pointer which marks the selected Decision Height on the analog radio altitude scale. This pointer appears when the DH display is selected and the value is in the display range.

MDA and DH Displays Figure 11-15

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DH Display

DH Alert“MINIMUMS”Voice AlertMDA

Alert

MDADisplay

FLIGHT INSTRUMENTS



Vertical Speed Display

The current vertical speed is shown by a green pointer on a vertical white scale; the green pointer drags a green vertical line from the center of the scale. Vertical speed (when 200 feet/minute or greater) is numerically repeated at the bottom of the scale followed by an arrow pointing “up” for climb, or “down” for descent.

The vertical speed is selected by using the VS/Pitch Wheel on the FCP and the magenta numerical value is displayed at the top of the Vertical Speed scale with a corresponding up or down arrow as selected.

The FMS Vertical Navigation computer continuously calculates vertical speed required to reach the next point on the flight plan at the altitude required. The required vertical speed when greater than 500 fpm for FMS VNAV is displayed on the vertical speed scale in the form of a cyan circle.

For Precision-Plus-equipped aircraft, the cyan circle will be displayed if VNAV is selected or VNAV advisory enabled.

TCAS advisories display on the VS scale as green or red lines. A green line shows a recommended “fly-to” range of vertical speeds. A red line shows “avoidance” or “exit” vertical speeds. TCAS modes and messages are also displayed below the VS scale as appropriate (see Chapter 17 Navigation Systems for further details).

NOTE

FLIGHT INSTRUMENTS

For Training Purposes OnlySept 04

11-31


PFD Vertical Speed Display Figure 11-16

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400

500

6001

2

4

1

2

4

Selected VS

VS Pointer

Selected VS Bug

VS Digital Readout

VS Advisory

TCAS ResolutionAdvisory

VS Pointer

VS Digital Readout

FLIGHT INSTRUMENTS



Navigation Displays

Vertical Deviation Display (GS, FMS and VNAV)The ILS glideslope vertical deviation display appears when all conditions are met. Use the on-side DCP to select FMS or LOC as the active NAV source. If deviation data becomes invalid, this display is replaced with a red GS (flag) annunciation. When conducting a back course approach, the scale displays without a pointer or flag annunciation.

With LOC selected as the active NAV source, glideslope deviation is shown by the position of a diamond-shaped pointer relative to the deviation scale. The scale consists of two dots above and two dots below center. When the pointer moves to the top or bottom of the scale, it changes to a half diamond (triangle) pointing in the direction of the glideslope. A star against the same scale displays FMS glideslope vertical deviation.

Marker Beacon AnnunciationMarker beacon status is annunciated by a cyan boxed “OM” (Outer Marker), yellow boxed “MM” (Middle Marker), or by an empty white box (Inner Marker).

Marker Beacon Annunciations Figure 11-17

Horizontal Situation Indicator (HSI) FunctionThe PFD has a Horizontal Situation Indicator located at the bottom center. It consists of an airplane symbol and a compass rose. The compass rose is graduated in five-degree marks, with numeric labels at every 10 degrees and letters at N, E, S and W. Airplane heading is read against the fore lubber line. Selected heading is set by the HDG knob on the Flight Control Panel, which moves a heading bug on both PFDs together. The digital value is displayed at the top left of the HSI while turning the HDG knob and remains displayed for a period of three seconds once HDG knob rotation is stopped.Selected course VOR, LOC or desired FMS track is digitally presented, and also displayed by an arrow. Course or track deviation is displayed against a scale centered on the airplane. Two bearing pointers are available to display bearing to navigation stations or a flight plan TO waypoint.

20

10

OM

P6

04

_11

_0

50

20

10

MM

20

10

FLIGHT INSTRUMENTS

For Training Purposes OnlyJan 04

11-33


PFD HSI Display Figure 11-18

N

S

15

12E

6

3

20

10

10

20

T

200

180

160

140200

300

400

500

600

ADF1

29.96 IN

1/2BNK HDG DR GS

AP

1

2

4

1

2

4

0.6

190

2

580MDA

M.452

LOC1CRS

8.IOW

9H

071

LOC10.9

VT 170VSPD

GS

FD2

2500VS

ALTS

2000FT

P6

04

_11

_0

38

N33

S15

12

E6

3

20

10

10

20

T

200

180

160

140 300

400

500

600

700

ADF1

29.96 IN

LOC1 DR GS

AP

1

2

4

1

2

4

173

2

580MDA

M.452

LOC1CRS

7.0H

IOW

071

ALTS PATH GS2500

2100FT

N33

S15

12

E6

3

20

10

10

20

2R

T

160

140

120

100

800

700

600

500

400

RWY

ADF1

29.96 IN

1/2BNK LNV1 DR VGP

AP

1

2

4

1

2

4

0.7

128

1

840MDA

M.452

FMS1DTK

3.8NMRW07

GPS APPRMSG

072

LOC1

25

ADF2

ALTS PATH GS900

HDG 072

1200FT

Full ScaleDeflection of Glideslope

GlideslopeCaptured

FMS VNAVGlide PathCaptured

HeadingBug

25

2525

FLIGHT INSTRUMENTS



Multifunction Display FormatsVarious information can be displayed on the five different display formats available on the Multifunction Display (MFD). Weather Radar or EGPWS Terrain information can be overlaid only on the active (dynamic) maps: Nav Sector, FMS Map, and TCAS formats.

The top two lines of all the different display formats present the following data (except for the remote text pages).

• Radar mode line (top line): Weather Radar mode of operation, gain, antenna stabilization and tilt; this is replaced with TERRAIN when in Terrain mode of EGPWS

• Status line (bottom line): UTC time, True Airspeed, Ground Speed, Static Air Temp and Total Air Temp

MFD Radar Mode and Status Lines Figure 11-19

LX/WX+TRB+GCS G+3 USTB T+10.7

UTC TAS GS TAT11:42 250 254 SAT 12 C -15 C

Radar ModeLine

Status Line P6

04

_11

_0

48

FLIGHT INSTRUMENTS


11-35


HSI Format

This display shows navigation information in a traditional 360-degree full compass rose format.

Weather Radar, Terrain and TCAS information cannot be displayed in HSI format.

The following sections are part of the HSI format:

• Status Line: This line displays the current UTC time, True Airspeed (from ADC), Ground Speed (from FMS) and temperatures (from ADC)

• On-side Course Display: The (left) display window shows on-side course information in green, yellow or white (VOR / LOC on-side green, VOR / LOC cross-side yellow, FMS on-side white or FMS cross-side yellow). This information is the active NAV course data displayed on the on-side PFD

The top line annunciates the NAV source and shows a numeric course readout. The NAV source is selected on the DCP. The CRS readout shows the course to the selected navaid station or next waypoint (also indicated by a single-line course pointer).

The next line is a station identifier and numeric distance readout. The station identification of the tuned navaid or next waypoint displays with the distance to that position (in nautical miles). The NAV source is boxed and red if the NAV data is invalid.

• Cross-side Course Display: The (right) display window shows cross-side course information in cyan. This information is the active NAV course data displayed on the cross-side PFD. A dual dashed-line course cyan pointer also indicates cross-side course

Cross-side course information is selected or deselected for display by the PUSH X-SIDE switch on the DCP.

Compass RoseThe compass rose contains index markings every five degrees and alphabetic or numeric markings displayed at 30-degree intervals. Additional fixed index marks display outside the compass rose perimeter at 45-degree intervals with respect to the lubber line.

NOTE

NOTE

FLIGHT INSTRUMENTS



Airplane SymbolA stationary airplane symbol displays in the center of the compass rose. This symbol points directly toward the lubber line.

Lubber LineThe lubber line is a fixed symbol at the top of the compass rose. The current airplane heading is the compass reading directly under the lubber line.

Selected Heading BugA heading bug symbol marks a selected heading reference. Turn the HDG knob on the FCP to move the heading bug around the compass rose. Momentarily pushing the center switch (PUSH SYNC) of the knob resets the heading bug to the current airplane heading.

Selected Heading DisplayThis display numerically shows the position of the selected heading bug. This display appears when the HDG knob is turned and disappears three seconds after rotation stops.

Drift Angle PointerThis pointer is a small green circle that shows the airplane drift angle.

Bearing PointersThere are two bearing pointers that may be selected for display (BRG buttons on DCP). One pointer is a single bar and the other pointer is a dual bar. Each pointer shows the bearing to a selected navaid station or the next FMS waypoint. The appropriate source for the bearing pointer is displayed below it.

Course PointersThe on-side course pointer is a solid-line pointer. This pointer shows the on-side NAV course. This value is numerically repeated in the on-side course display. Push the DCP X-SIDE button to display the cross-side cyan course pointer.

The cross-side course pointer is a dual dashed-line cyan pointer. This pointer shows the cross-side NAV course. This value is numerically repeated in the cross-side course display.

To/From SymbolA triangle symbol shows “to” or “from” direction. This symbol turns as a part of the on-side course pointer and points toward the tuned station or next waypoint.

FLIGHT INSTRUMENTS


11-37


Lateral Deviation BarsThe lateral deviation bars are the center portions of the course pointers. Each bar moves left or right from the pointer to show lateral deviation from the NAV course.

Lateral Deviation ScaleThe lateral deviation scale consists of four dots that display perpendicular to the on-side course lateral deviation bar. Two dots display on either side of the airplane symbol.

Vertical Deviation DisplayThe ILS glideslope or the FMS VNAV vertical deviation display appears when all appropriate conditions are met. The on-side DCP selects LOC/FMS as the active NAV source. If, or as deviation data becomes invalid, this display is replaced with a red GS icon. When FMS VNAV deviation data is invalid, the deviation scale and pointer are removed. When making a back course approach, the scale displays without a pointer or flag annunciation.

ILS/GS vertical deviation is shown by the position of a green diamond-shaped pointer relative to the deviation scale; whereas a white star pointer shows the FMS VNAV vertical deviation. The scale consists of two dots above and two dots below center. If GS deviation becomes excessive, the pointer and scale flash yellow.

MFD HSI Format Figure 11-20

P6

04

_11

_0

39

VOR1

RADAR OFFUTC22 : 40

TTG : 04

FMS1YUL



YUL12.7NM 12.7NMTTG : 04

N3

330

W24

21

S1

512

E6

3

059

FLIGHT INSTRUMENTS



NAV Sector Format

This display shows navigation information on an enlarged section of the compass rose. The following sections are part of the NAV sector format.

On-side Course DisplayThe (left) display window shows on-side course information in green, yellow or white (VOR/LOC on-side green, VOR/LOC cross-side yellow, FMS on-side white or FMS cross-side yellow). This information is the active NAV course data displayed on the on-side PFD.

Cross-side Course DisplayThe (right) display window shows cross-side course information in cyan. This information is the active NAV course data displayed on the cross-side PFD.

Cross-side course information is selected or deselected for display by the PUSH X-SIDE switch on the DCP.

Range RingsThere are two range rings, which provide a distance scale to help visualize the airplane position relative to navaid symbols and weather radar targets. A distance annunciator displays by each ring. The RANGE knob (on the DCP) selects a desired display range. The possible full-scale ranges are 5, 10, 25, 50, 100, 200, 300 and 600 nm (maximum is 300 nm with WX selected on).

The outer range ring is a 120-degree sector of the compass rose. This arc contains index markings every five degrees and alphabetic or numeric markings every 30 degrees. The inner range ring is a circle that is centered on the airplane.

NAVAID DisplayThe NAVAID display shows airplane heading, selected heading, on-side course, cross-side course, bearing, vertical deviation and wind information.

The sector format may display (only) two or three navaid symbols. These symbols are generated using bearing/distance information (not FMS map data). VORTAC symbols with station identifiers display if the two actively tuned VOR stations are within range and data is valid. The TO waypoint of the FMS flight plan will also display. No other navaid symbols display on the sector format.

NOTE

FLIGHT INSTRUMENTS


11-39


MFD Sector Format Figure 11-21

ADF

UTC01 : 50

TTG : 0411

LOC1IUL

CRS 059 FMS2 DTK 030



5

10

059

NAV SECTOR

RADAR OFF

VOR1 VOR2

UTC22 : 40

TTG : 0411

FMS1YUL



YUL12.7NM 12.7NMTTG : 0411

YUL

HOKKE

CYUL

12.5

25

059

NAV SECTOR

LX/RADAR OFF

P6

04

_11

_0

40

SECTOR FORMAT WITH CROSS-SIDEDATA SELECTED AND WEATHER RADAR OVERLAY

SECTOR FORMAT APPROACH

ABOVEBELOW

FLIGHT INSTRUMENTS



FMS Map Format

This format shows a dynamic geographic depiction of the flight as it occurs. The map display is always centered on the airplane present position with current heading toward the top of the screen. The screen shows a moving map display of flight plan symbols and background navaid symbols relative to airplane present position.

An FMS data window may be displayed on the FMS map.

Airplane SymbolThis symbol is a reference used to visualize airplane position relative to the geographic map and radar targets. The airplane symbol is stationary and always displayed in the center of the screen. The navaid symbol, radar targets and flight plan line move down the screen as the flight progresses.

Range RingsThere are two range rings displayed, which provide a distance measuring scale. These rings show distance from the airplane. A distance annunciator displays by each ring. The RANGE knob (on the DCP) selects a desired display range. The possible full-scale ranges are the same as for NAV Sector format.

NAV DisplayThe NAV display shows the FMS flight plan line and a background navigation map. The map consists of navaid symbols generated from the FMS database. The FMS flight plan displays on the map as a solid white line. This track line consists of straight-line segments connecting consecutive flight plan waypoints. The TO waypoint displays in magenta. FMS-generated navaid and map symbols are cyan.

Data WindowThe data window displays FMS progress parameters for the FROM, TO, NEXT and Destination waypoints in the flight plan. The CDU is used to select the various options of the data window. The data window can be selected to ON, COMP, VNAV, or OFF.

NOTE

FLIGHT INSTRUMENTS


11-41


MFD Data Window Figure 11-22

P6

04

_11

_0

41

LEFT DISPLAY MENU 1/2

HI NAVAIDS

LO NAVAIDS

INTERS

ARPTS

TERM WPTSWINDOW

OFF/ON/VNAV/COMP

SPEED

ALTITUDE

MISS APPR

ETA

NDBS

MAP DISPLAY

[ ]OFF

SIDEL/R>


HI NAVAIDS

LO NAVAIDS

INTERS

ARPTS

TERM WPTSWINDOW

OFF/ /VNAV/COMPON

SPEED

ALTITUDE

MISS APPR

ETA

NDBS

MAP DISPLAY

[ ]ON

SIDEL/R>

LX/RADAR OFF G+3 USTB T+10.7TAS 342 342

DME1

YUL

121.

G+3 USTB T+5.0UTC01: 07 GS SAT-29C TAT-13C

HOKKE

THURO

25

50

/2600A

DME2

YUL

221.

ABOVEBELOW

/2600

/2900A

/2900

TEXEN

[ 2900 ]

YOW

YRENSRW32

YUL


YUL

THUROCYOW

HOKKE23NM

18NM58NM

1NM0:030:14

0:0001:1101:21

00:5501:08

9670 LB 37.0GW

DME1

YUL

423.


VOR1 ADF2

HOKKE

THURO

25

50

280

2600A

DME2

YUL

423.

ABOVEBELOW

TEXEN

YRANS2600

RW32


HI NAVAIDS

LO NAVAIDS

INTERS

ARPTS

TERM WPTSWINDOW

OFF/ON/ /COMPVNAV

SPEED

ALTITUDE

MISS APPR

ETA

NDBS

MAP DISPLAY

[ ]VNAV

SIDEL/R>


HI NAVAIDS

LO NAVAIDS

INTERS

ARPTS

TERM WPTSWINDOW

OFF/ON/VNAV/COMP

SPEED

ALTITUDE

MISS APPR

ETA

NDBS

MAP DISPLAY

[ ]COMP

SIDEL/R>

VOR1 VOR2

UTC01 : 07

TTG11 : 42

LOC1IUL

CRS FMS2 DTK 030

TAS GS SAT343 343 –29C TAT–13CTGT


25

50

279

NAV SECTOR

RADAR OFF

DME1

YUL

818.

HOKKE

THURO

26000A

YUL

ABOVEBELOW

TEXEN

DME2

YUL

818.

YUL


YUL

THUROCYOW

HOKKE15NM

26NM66NM

9NM0:050:15

0:02::::

DIRECTTEXEN

3.3°2600A0:11/

2000

56NM

DME1

YUL

615.


VOR1 ADF2

HOKKE

THURO

25

50

280

26000A

DME2

YUL

615.

ABOVEBELOW

OFF

ON

VNAV

COMP

FLIGHT INSTRUMENTS



Plan Map Format

This format shows a static geographic depiction of a section of the flight plan (or a selected route). Use this map as a visual aid to enter a new flight plan/route or to plan a deviation from the flight plan/route.

The plan map is always presented with true North at the top of the screen. This screen shows flight plan/route symbols and background navaid symbols within range. The (dynamic) weather radar, terrain and TCAS cannot be overlaid onto the (static) plan map.

Optional “Precision Plus” FMS upgrades incorporate a 3D-map capability on the plan map page.

Range RingA range ring provides a distance measuring scale. This ring shows distance from the center waypoint. The range rings also display a range distance. The RANGE knob on the DCP selects the desired range. The possible full-scale ranges are 5, 10, 25, 50, 100, 200, 300, and 600 nm.

NAV DisplayThe NAV display shows the FMS flight plan or route line and a background navigation map. The map consists of navaid symbols generated from the FMS database. The FMS-generated navaids and map symbols are cyan. The active FMS flight plan/route displays on the map as a solid white line. This track line consists of straight line segments connecting consecutive waypoints. The TO waypoint displays in magenta.

MFD FMS Plan Map Format Figure 11-23

P6

04

_11

_0

42

25

LX/RADAR OFF G+3 USTB T+10.7UTC TAS GS22:48 378 378 SAT-9C TAT 10C

THURO

FANOLCYOW

AGLIN4NM

16NM29NM

9NM20:48

0:040:09

0:0220:48

20:5220:57

20:5020:4820:5020:52

6930 LB 343GW

DME1

– – – –

TO WPT UNLOCKED V=000°L=360T

DME2

– – – –

THURO

/2600

AGLIN

FANOLTEFLY

FF25/2600A

774A

/2500A/2500A

TOCONE

RW25

FLIGHT INSTRUMENTS


11-43


TCAS Format

The TCAS format provides a dynamic map with a complete 360-degree circular representation which is dedicated to TCAS information. Weather radar information can be overlaid on this page.

For further details on TCAS see Chapter 17 Navigation Systems.

MFD TCAS Format Figure 11-24

P6

04

_11

_0

43

USTB T+10.70 0 SAT 15C

10

LX/WX USTB T+10.7TAS 0

USTB T+5.0UTC04:30 GS TAT 15C

FMS2YUL

-10 -04

FLIGHT INSTRUMENTS



Radio Altimeter

DescriptionThe radio altimeter measures direct radio height (distance above terrain) for use by the Flight Control Computers (FCCs) and for display on the PFDs.

Components and OperationThe radio altimeter (RA) system consists of the following components:

• one Receiver/Transmitter• one Radio Altitude Converter• one Transmit Antenna• one Receive Antenna• Associated Components:

• two Air Data Reference Panels (ADRPs)• two PFD Indicators

In order to conform to JAA CAT II certification requirements, service bulletin 604-34-005 indicates that the installation of a second RA is required.

Receiver/Transmitter

The receiver/transmitter transmits, receives and processes RF signals to provide a display of radio altitude and decision height information on the pilot’s and copilot’s PFDs. The receiver/transmitter performs this function by measuring the difference in frequency between the transmitted and received signals. Internal monitoring and self-test capabilities are also provided.

Antennae

The system uses two identical, linearly polarized antennae, flush-mounted on the underside of the airplane along the centerline. The forward antenna is used to transmit and the aft antenna to receive.

NOTE

FLIGHT INSTRUMENTS


11-45


Radio Altitude DisplayThe radio altitude of the aircraft is displayed both in digital and analog format on the PFD.

This numeric display appears at the bottom of the attitude indicator as the airplane descends through 2500 feet above ground level (AGL) and disappears as the airplane climbs through 2500 feet AGL.

Analog Radio Altitude Scale

A small window appears at the center of the scale as the airplane descends through 1250 feet AGL. This window marks the current radio altitude. This value is numerically repeated in the bottom portion of the attitude indicator.

An analog radio altitude scale appears as the airplane descends through 1100 feet AGL. This analog scale is used in conjunction with the ground bar (rising runway) to assist in visualization of the aircraft’s height above terrain. The scale contains line marks and single-digit numeric labels. Each digit indicates 100 feet of radio altitude.

At Decision Height (DH), the numeric label and scale change from green to yellow.

Ground Bar (Rising Runway)

A ground bar displays on the analog radio altitude scale to represent the terrain. As the airplane descends through 200 feet AGL, the ground bar rises on the analog scale. At 0 feet radio altitude, the top of the ground bar aligns with the center of the scale.

NOTE

FLIGHT INSTRUMENTS



Radar Altimeter Display Figure 11-25

P6

04

_11

_0

25

30

00

’

25

00

’

12

00

’

11

00

’

20

0’

0’

0

2 1

20

10

10

20

30

0F

T

0

4 3 2 1

20

10

10

20

30

20

0F

T

20

10

10

20

1

30

11

00

FT

20

10

10

20

1

29

12

00

FT

20

10

10

20

1

30

25

00

FT

10

10

20

301

No

te:

No

tto

Sca

le

FLIGHT INSTRUMENTS


11-47


Standby InstrumentsThe standby instruments include an airspeed indicator, altimeter, attitude indicator and compass.

Standby Instruments Locator Figure 11-26

Standby Airspeed IndicatorThe airspeed indicator supplies non-corrected (indicated) airspeed. It uses the standby pitot source P3 and the standby static ports S3.

Standby Airspeed Indicator Figure 11-27

400

350

300 250

200

150

10060

KTS

IAS

Speed PointerIndicates speed readoutin knots indicated

P6

04

_11

_0

19

FLIGHT INSTRUMENTS



Standby AltimeterThe standby altimeter incorporates an altitude pointer and an altitude counter. The altitude pointer and altitude counter operate through a mechanical linkage connected to a pressure capsule. The pressure capsule moves with changes in static pressure. Barometric correction is selected by a knob at the bottom right of the instrument and displayed in inches of mercury and hectopascals. The instrument receives its static pressure from the standby static ports S3.

Standby Altimeter Figure 11-28

Standby Attitude IndicatorThe standby attitude indicator has an electrically-operated vertical gyroscope. The gyroscope is mechanically connected to the sphere to show attitude information. To cage or uncage the instrument, the PULL TO CAGE knob is pulled and turned. When the instrument is uncaged, the cage knob is turned to adjust the pitch reference.

Standby Attitude Indicator Figure 11-29

2 000234ALT

0

7 3

2

1

4

9

6 29925

1014

in Hgmb/hPa

Altitude Pointer and ScalePointer indicates altitude in100-foot increments as readfrom scale. Full circle foreach 1,000 feet of altitude.

Altitude CounterIndicates barometric altitudefrom - 1,000 to 50 000 feet,in 1,000 foot increments.

Barometric PressureIndicatorsIndicates selected barometricpressure as expressed inhectopascals or inches ofmercury.

P6

04

_11

_0

20

Barometric Set KnobUsed to changebarometric pressurevalues as read at hPa/in Hgreadouts.Range for this standbyInstrument is as follows:

from 952 to 1049 mb/hPaand

from 28.02 to 30.99 in Hg.

�

�

P

UL L

P

UL L

TO

C A G

E

C A G

E

CLI MB

DI VE

OFF

Roll/Sky PointerIndicates bank anglesreferenced againstindex.

roll

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

SphereIndicates airplane movement in pitch.Marked at 5-degree increments

Fixed Airplane SymbolIndicates roll and pitchattitude relative to thehorizon.

Power Off FlagAppears when power toindicator is lost orduring gyro failure. Gyrowill continue to run forapproximately 9minutes after power islost.

Horizon Line

Caging/Pitch -Adjust Knob

P6

04

_11

_0

21

FLIGHT INSTRUMENTS


11-49


Standby CompassThe standby magnetic compass is a self-contained dry unit, which uses eddy current damping to prevent overshooting. The standby compass is installed below the overhead panel.

Standby Compass Figure 11-30

N33

30

W24

21 S15

12

E6

3

TO FLY

STEER

N 30 E 120 W

Fixed AirplaneSymbol

CompensatingScrews

Rotating Compass Dial

Magnetic CompassIndicates heading ofairplane in relation tomagnetic north.

P6

04

_11

_0

22

60 150 S 210 240 300 330

STANDBY COMPASS WITH ALL RADIOS ON SWUNG BY

FLIGHT INSTRUMENTS



Aircraft ClocksThe digital clocks are located on the side panels of the pilot and copilot.The clocks can display local time, flight time and elapsed time.Starting with A/C 5331, the clocks have been changed to add a GMT time display.

Clock Prior to A/C 5331 Figure 11-31

P6

04

_11

_0

26

DAVTRONTIME ZERO

UP D B

SET DIM

RUNE.T.

stop

F.T.

1hrup

Set Switch

UP

D

�

�

�

Sprung to center position.Hold to left ( ) positionadvances clock 1 secondfor every second held.Hold to right ( ) positionretards clock 1 second forevery second held.

Time SwitchTIME

F.T.

E.T.

�

�

�

Select to displaylocal or standard time.Select to displayflight time.Select to displayelapsed time.

Bright/Dim SwitchBD1 hr up

�

�

�

Select for bright display.Select for dim display.Select momentaryposition and release toadvance clock 1 hour.

Elapsed Time SwitchZERO

STOP

RUN

�

�

�

momentary positionsets elapsed time to zero.Also zeros flight time ifaircraft power is removed.

position stops elapsedtime meter.

position starts elapsedtime meter.

Press to ResetAllow the clock's flighttime recorder to be resetto zero without turning offaircraft electrical power

Hours

Seconds

Minutes

Press ToReset

FLIGHT INSTRUMENTS


11-51


Clock A/C 5331 and Later Figure 11-32

P6

04

_11

_0

49

SELECT CONTROL

GMT LT FT ET

SEL CTL

12 00

DAVTRON

CHRONOMETER

M877

Greenwich Mean Time

Local Time12-hour format with24-hour option

Flight Time

Elapsed Time

Audio AlarmSpeaker

Select ButtonGMT LT FT ET�

�

To select , , , andback when momentarily pressed.To turn off alarm.

Control Button

FT

�

�

�

�

Starts and resets elapsed time whenmomentarily pressed.Press and hold for 3 seconds for test mode.With selected, press and hold for 3 secsto reset flight time.To turn off alarm.

Note:SEL CTL GMT LT FT ETPress and buttons simultaneously to enter set mode for , , and Countdown

FLIGHT INSTRUMENTS



Display Reversionary PanelThe display reversionary switches on the Display Reversionary Control Panel are used to select the desired reversion mode of the L(R) MFD.

Both the L MFD and the R MFD can be set to one of three positions:

• Norm: The MFD operates in the NORM position and displays navigation, weather radar, terrain or TCAS information as selected on the Display Control Panel

• PFD: By turning either the L MFD or the R MFD rotary selector to PFD, the associated PFD is now transferred to the selected MFD

• EICAS: By turning either the L MFD or the R MFD rotary selector to EICAS, the STATUS page will be displayed on the selected MFD. The EICAS Control Panel then controls EICAS page selections

Abnormal Conditions

In the event of a DCP failure, a red boxed DCP shows on the affected PFD. To allow selection of the operating DCP, a reversionary selector switch is provided on the reversionary panel. This switch has three positions, NORM, 1, or 2. In the NORM position, each DCP controls its own MFD. In either the 1 or the 2 position, the remaining DCP controls the display on both MFDs.

FLIGHT INSTRUMENTS


11-53


Display Reversionary Panel Figure 11-33




189197231

248187300348

0.783180.85197197250

P

UL L

P

UL L

TO

C A G

E

C A G

E

CLI MB

DI VE

OFF

BRT

BRT

BRT

0.0

0.0

0.0

0.0

180 180

N1

ITT

N2

STAB- TRIM -

NU

ND

5.0

RUDDER

AIL

RWDLWD

NRNL

FF (PPH)

OIL PRESS

OIL TEMP

FAN VIB

0 4050

81000.0

33

0

0

0


0

0

33

0.0

4050

DN DN DN



BRT

CABIN TEMP

BLEED PRESS

FUEL TEMP

ENGINE

BULK

OXY

C ALT

RATE

P

47

23

0

36 35

1820

100

0

0.0

APU

100 323

RPM EGT


SPOILERS

15

2 000234

ALT

0

7 3

2

1

4

9

6 29925

1014

400

350

300 250

200

150

10060

KTS

IAS

FEET

X 1000

CABIN

ALTITUDE

0

4

2

68

10

20

30

45

BRT

BRT

80

60

20

00

20

10

10

20

300

200

100

100

000

80004

RA2IRS2ADC2DCP2

TERM

VOR1

TRU

NO FLIGHT PLAN

TCASOFF

29.92 IN

2400M

GSRA

TOLOC 1

DR TOALTS

FMS1

12DTK 333

.7YUL

NM

4

4

2

2

1

1

2500M200

N33 1

512

E6

3

0

3000

40

VT 150

V2 133

VR 121

V1 113

ADF2

0FT

2

1




189197231

248187300348

0.783180.85197197250

80

60

20

00

20

10

10

20

300

200

100

100

000

80004

RA2IRS2ADC2DCP2

VOR1

TRU

TCASOFF

29.92 IN

2400M

GSRA

TOLOC 1

DR TOALTS

4

4

2

2

1

1

2500M200

0

3000

40

VT 150

V2 133

VR 121

V1 113

ADF2

0FT

2

1

FMS2

12DTK 056

.2LONNA

NM

TERM

N33 1

512

E6

3

CABIN TEMP

BLEED PRESS

FUEL TEMP

ENGINE

BULK

OXY

C ALT

RATE

P

47

23

0

36 35

1820

100

0

0.0

APU

100 323

RPM EGT


SPOILERS

15

PFD EICASNORM

L MFD

EICAS PFDNORM

R MFD

ED1

ED2

NORMEICAS

D EIC2

AS PF

PFD EICASNORM

L MFD

1 2

NORMADC

1 2

NORMDCP

EICAS PFDNORM

R MFD

ED1

ED2

NORMEICAS

2

D EIC2

AS PF

2

REVERSIONARY SELECTORS -DISPLAY REVERSIONARY CONTROL PANEL

P6

04

_11

_0

04

Display ReversionarySelector must be selectedto display PFD on MFD




189197231

248187300348

0.783180.85197197250

P

UL L

P

UL L

TO

C A G

E

C A G

E

CLI MB

DI VE

OFF

BRT

BRT

BRT

0.0

0.0

0.0

0.0

180 180

N1

ITT

N2

STAB- TRIM -

NU

ND

5.0

RUDDER

AIL

RWDLWD

NRNL

FF (PPH)

OIL PRESS

OIL TEMP

FAN VIB

0 4050

81000.0

33

0

0

0


0

0

33

0.0

4050

DN DN DN



BRT

CABIN TEMP

BLEED PRESS

FUEL TEMP

ENGINE

BULK

OXY

C ALT

RATE

P

47

23

0

36 35

1820

100

0

0.0

APU

100 323

RPM EGT


SPOILERS

15

2 000234

ALT

0

7 3

2

1

4

9

6 29925

1014

400

350

300 250

200

150

10060

KTS

IAS

FEET

X 1000

CABIN

ALTITUDE

0

4

2

68

10

20

30

45

BRT

BRT

80

60

20

00

20

10

10

20

300

200

100

100

000

80004

RA2IRS2ADC2DCP2

TERM

VOR1

TRU

NO FLIGHT PLAN

TCASOFF

29.92 IN

2400M

GSRA

TOLOC 1

DR TOALTS

FMS1

12DTK 333

.7YUL

NM

4

4

2

2

1

1

2500M200

N33 1

512

E6

3

0

3000

40

VT 150

V2 133

VR 121

V1 113

ADF2

0FT

2

1




189197231

248187300348

0.783180.85197197250

80

60

20

00

20

10

10

20

300

200

100

100

000

80004

RA2IRS2ADC2DCP2

VOR1

TRU

TCASOFF

29.92 IN

2400M

GSRA

TOLOC 1

DR TOALTS

4

4

2

2

1

1

2500M200

0

3000

40

VT 150

V2 133

VR 121

V1 113

ADF2

0FT

2

1

FMS2

12DTK 056

.2LONNA

NM

TERM

N33 1

512

E6

3




189197231

248187300348

0.783180.85197197250

P

UL L

P

UL L

TO

C A G

E

C A G

E

CLI MB

DI VE

OFF

BRT

059

WX + TRBUTC TAS GS TAT11:01 0 0 15 C

VOR 1 ADF 2

VOR1YULTTG--:--

CRS 01212.7NM

SAT 15 C

FMS2LONNA

DTK05612.2 NMTTG --:--

33

30

21

S15

12

6

3

N

E

W

24

BRT

BRT

0.0

0.0

0.0

0.0

180 180

N1

ITT

N2

STAB- TRIM -

NU

ND

5.0

RUDDER

AIL

RWDLWD

NRNL

FF (PPH)

OIL PRESS

OIL TEMP

FAN VIB

0 4050

81000.0

33

0

0

0


0

0

33

0.0

4050

DN DN DN



BRT

CABIN TEMP

BLEED PRESS

FUEL TEMP

ENGINE

BULK

OXY

C ALT

RATE

P

47

23

0

36 35

1820

100

0

0.0

APU

100 323

RPM EGT


SPOILERS

15

2 000234

ALT

0

7 3

2

1

4

9

6 29925

1014

400

350

300 250

200

150

10060

KTS

IAS

FEET

X 1000

CABIN

ALTITUDE

0

4

2

68

10

20

30

45

BRT

BRT

80

60

20

00

20

10

10

20

300

200

100

100

000

80004

RA2IRS2ADC2DCP2

TERM

VOR1

TRU

NO FLIGHT PLAN

TCASOFF

29.92 IN

2400M

GSRA

TOLOC 1

DR TOALTS

FMS1

12DTK 333

.7YUL

NM

4

4

2

2

1

1

2500M200

N33 1

512

E6

3

0

3000

40

VT 150

V2 133

VR 121

V1 113

ADF2

0FT

2

1

CYUL

TOC

ALEXS

3

059

N

E

12

25

WX+TRB

UTC TAS GS TAT11:01 0 0 SAT 15 C 15 C

VOR 1 FMS MAP ADF 2

CYULLONNAALEXSCYUL

1NM12NM20NM

111NM

0:030:040:23

11:0211:0511:0711:25 7137LB 35.6GM

12.5

DME 1

YUL12.7

DME 2–– – –

LONNA




189197231

248187300348

0.783180.85197197250

80

60

20

00

20

10

10

20

300

200

100

100

000

80004

RA2IRS2ADC2DCP2

VOR1

TRU

TCASOFF

29.92 IN

2400M

GSRA

TOLOC 1

DR TOALTS

4

4

2

2

1

1

2500M200

0

3000

40

VT 150

V2 133

VR 121

V1 113

ADF2

0FT

2

1

FMS2

12DTK 056

.2LONNA

NM

TERM

N33 1

512

E6

3

PFD EICASNORM

L MFD

EICAS PFDNORM

R MFD

ED1

ED2

NORMEICAS

D EIC2

AS PF

Display ReversionarySelector must be selectedto display EICAS on MFD

FLIGHT INSTRUMENTS



EICAS Messages

MESSAGE MEANING AURAL WARNING (IF ANY)

EFIS COMP MON Indicates mismatch detected between on-side and cross-side data.EFIS COMP INOP EFIS comparator has failed.

EICAS Messages Table 11-1

PILOT TRAINING GUIDE FLIGHT INSTRUMENTS - … of Contents For Training Purposes Only May 03 11-i...

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Transcript of PILOT TRAINING GUIDE FLIGHT INSTRUMENTS - … of Contents For Training Purposes Only May 03 11-i...