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cftsuencjer OPERATING MANUAL

PSP 601A-6

SECTION 11

FLIGHT INSTRUMENTS

TABLE OF CONTENTS

Page

1 . GENERAL 1

2 . PITOT-STATIC SYSTEM AND TEMPERATURE SENSING SYSTEM 1

3 . DIGITAL AIR DATA SYSTEM 1

4. ELECTRONIC FLIGHT INSTRUMENT SYSTEM 2

LIST OF ILLUSTRATIONS

Figure

Number T i t l e Page

1 Pi t o t - S t a t i c System - Schematic 3

2 Pi t o t - S t a t i c System - Components 4

3 P i t o t - S t a t i c System - Standby Indicators 5

4 DADS - S impl i f ied Block. Diagram 6

5 DADS - Mach/Airspeed Indicators and Al t imeters 7

6 DADS - Ver t i ca l Speed Indicators and Associated AFCS Advisory Display 8

7 DADS - EFIS EADI Air Data Displays (2 Sheets) 9

8 DADS - EFIS Instrument Remote Control lers 11

9 EFIS - S impl i f ied Block Diagram 12

10 EFIS - EADI Normal Displays 13

11 EFIS - EADI Failure Warning Annunciators (2 Sheets) 14

12 EFIS - EADI Category 2 Annunciator 16

13 EFIS - EADI Comparison Monitor Annunciators 17

14 EFIS - EADI Reversionary Source Annunciators 18

11-CONTENTS

Apr 02/87

Fi gure Number

16

17

18

19

20

21

22

23

24

25

26

27

28

EFIS

EFIS

EFIS

EFIS

EFIS

EFIS

EFIS

EFIS

EFIS

EFIS

EFIS

EFIS

EFIS

EFIS

OPERATING WIMWL PSP601A-6

Title Page

EHSI Full Compass Mode 19

EHSI ARC Mode 20

EHSI MAP Mode 21

EHSI Weather Radar Display 22

EHSI Failure Warning Annunciators 23

EHSI Comparison Monitor Annunciator 24

EHSI Reversionary Source Annunciators 25

Composite Display 26

MFD MAP Mode 27

MFD PLAN Mode 28

Display Controller 29

Instrument Remote Controllers 30

MFD Controller 31

Remote Switch/Lights 32

1 1 -

Apr 02/87

OPERATING MANUAL PSP 601A-6

SECTION 11

FLIGHT INSTRUMENTS

GENERAL

The flight instrument systems consist of the pi tot-static system, the temperature sensing system, the digital air data system, the electronic flight instrument system and the vertical gyros.

PITOT-STATIC SYSTEM AND TEMPERATURE SENSING SYSTEM (Figures 1 , 2 and 3)

The pi tot-static system provides the pi tot and static pressures required to operate the digital air data computers No- 1 and No. 2 (DADC 1 and DADC 2) and the standby pneumatic airspeed indicator (ASI). Static pressure is provided to operate the standby pneumatic altimeter (ALT), and the cabin pressure indicator (CPI). The pi tot-static system consists of the pilot's and copilot's pi tot-static heads, the left and right static ports, and the pilot's and copilot's STATIC PRESSURE SELECTOR valves. A dual temperature-sensing probe, located on the right side of the forward fuselage, provides a total-air-temperature (TAT) input to DADC 1 and DADC 2. The pi tot tubes, static ports and temperature probe contain anti-icing heater elements that are controlled from the A.D.S. HEATER CONT. panel.

For a description of the CPI, refer to Section 2.

DIGITAL AIR DATA SYSTEM (Figures 4 through 9)

The digital air data system provides the flight guidance computers and control systems with altitude hold, airspeed programming, vertical speed and Mach control information. The digital air data system also provides altitude alerting and reporting and indications of altitude, airspeed, vertical speed, true airspeed, static air temperature and total air temperature.

The digital air data system consists of two complete systems with two digital air data computers, DADC 1 and DADC 2. The DADCs receive total pi tot-static pressures from the pi tot-static system, and temperature signals from the total-air-temperature probe. Other inputs to the DADCs are from the BARO control on the barometric altitude indicator, the copilot's ALT SEL control on the electronic flight instrument system (EFIS) remote controller, and flap position information from the flap control unit. From these inputs, the DADCs compute and generate output signals for the following systems or components:

Pilot's and copilot's Mach/airspeed indicators (MASI)

Pilot's and copilot's altimeters

SECTION 11 Page 1

Apr 02/87

ctvanenaer OPERATING MANUAL

PSP 601A-6

Pi lo t s and copilot's vertical speed indicators (VSI)

P i lo t s and copilot's electronic flight instrument system (EFIS)

Automatic flight control system (AFCS)

Aural warning system

Flight management system (FMS)

ATC transponder system

Master caution and warning system

The AFCS advisory display panel displays static-air-temperature (SAT), total air temperature (TAT) and true airspeed (TAS).

The digital air data system consists of two digital air data computers, two Mach/airspeed indicators, two altimeters, two vertical speed indicators and a dual TAT probe.

ELECTRONIC FLIGHT INSTRUMENT SYSTEM (Figures 9 through 28)

The electronic flight instrument system (EFIS) converts inputs from the aircraft sensors, long-range navigation (LRN) and short-range navigation (SRN) systems into video signals for display on electronic display units.

The EFIS comprises three subsystems: the pilot's display system, the copilot's display system and the multifunction display (MFD) system.

The pilot's and copilot's display systems are identical, each using two electronic display units to provide conventional attitude director and horizontal situation information, using a display controller, an instrument remote controller and a symbol generator. In addition to the conventional displays, the electronic attitude director indicator (EADI) and electronic horizontal situation indicator (EHSI) provide a number of other displays such as IAS/Mach, map and weather radar displays, selectable from the display controllers. The display controllers also provide for navigation source selection and bearing source selection. The pilot's and copilot's instrument remote controllers provide for control of the flight director related displays on the EADI and EHSI-

The MFD system provides additional long-range mapping information, checklists and weather radar displays (refer to Section 11). The MFS system can also serve as a back-up system for either the pilot's or copilot's display system. The MFD controller provides for selection and control of the MFD formats, modes, waypoint designators and back-up modes.

SECTION 11 Page 2

Apr 02/87


LEGEND

PILOTS PITOT-STATIC HEAD

PITOT PRESSURE UNE STATIC PRESSURE LINE COPILOTS

PITOT-STATIC HEAD

• • •

•

01

ALT. STATIC SOURCE SW. PILOTS SIOE CONSOLE

DRAIN =<D>-fi

DRAIN

DADC1

SI DRAIN S2 DRAIN

CENTRE INSTRUMENT PANEL

P2

V

COPILOTS SIDE PANEL

anttp

MANIFOLD S-_ limit

DRAIN

© © STATIC PORT S3

STATIC PORT S3

atttittratintituiiii

ALT. STATIC SOURCE SW. COPILOTS SIDE CONSOLE

•-O DRAIN

DADC2

DRAIN

Pi tot-Static System - Schematic Figure 1

SECTION 11 Page 3

Apr 02/87

OPERATING MANUAL PSP G01A-6

f: IK ' .

PITOT HEAT FAIL ANNUNCIATOR

Indicates a failure of the on-side pitot-static tube heater.

O

HTR FAIL SWTTCrVUGHT

Indicates a static port, angie-of-attack <AOA> vane and/or totahair-temperture (TAT) probe heater failure.

PWR £> METER SELECT SWITCH

Turns on heater elements (when set to any position except HTRS OFF) for the static ports, the pitot-static tubes, the angje-of-attack (AOA) vanes, and the total-air-temperature (TAT) probe. The switch also selects the current readings indicated by the % HTR CURRENT meter.

% HTR CURRENT METER

Indicates the percentage of current drawn by the heater selected by the PWR B METER SELECT switch.

SAFETY GUARD REMOVED FOR CLARITY

PILOTS AND COPILOTS SELECTOR VALVES

STATIC TUBE - The on-side cfigrtaJ air data computer receives static pressure inputs from the primary source.

ALTERNATE SOURCE - The on-side dgrtai air data computer receives stauc pressure from the secondary (alternate) source.

Pitot-Statlc System - Components Figure 2

SECTION 11 Page 4

Apr 02/87

BARO CONTROL


STANDBY AIRSPEED INDICATOR

ALTITUDE POINTER

ALTITUDE INDICATOR

BARO INDICATOR

CENTRE INSTRUMENT P A N E L

Pi tot-Static System - Standby Indicators Figure 3

SECTION 11 Page 5

Apr 02/87


ATC1

PfTOT-STATIC INPUTS

[FLAP .CONTROL

UNIT

FLAP POSITION

COPILOTS INSTRUMENT REMOTE CONTROLLER

ALTSEL

TAT

AFCS ADVISORY DISPLAY

ALTITUDE REPORTING

DADC1

MACH/AIRSPEED

ALTTTUDE/BARO CORRECTION

TO MASTER CAUTION AND WARNING SYSTEM

VERTICAL SPEED

PiLOT S MACH/AIRSPEED INDICATOR

PILOTS ALTIMETER

PILOTS VERTICAL SPEED INDICATOR

ALTITUDE ALERT/OVERSPEED

PILOTS EADI

K ASCB

ALTSEL

TAT { PROBE

TAT

FLAP POSITION

PfTOT-STATIC INPUTS

DADC2

2EL/ TO FMS, EFIS IRS AND AFCS

AURAL WARNING SYSTEM

MACH/AIRSPEED

ALTITUDE ALERT/OVERSPEED

COPILOTS MACH/AIRSPEED INDICATOR

^ TO MASTER CAUTION ^ AND WARNING SYSTEM

COPILOTS ALTIMETER

COPILOTS VERTICAL SPEED INOICATCP.

COPILOTS EADI

ALTITUDE REPORTING

A T C 2

DADS - Simplified Block Diagram Figure 4

SECTION 11 Page 6

Apr 02/87

MACH COUNTER

VMO POINTER

AIRSPEED POINTER

MEMORY INDEX POINTER (YELLOW)

POINTBl

BARO SET KNOB

canaaair ctianentjer


MACH/AIRSPEED INDICATOR

BARO COUNTERS

ALTIMETER

MEMORY INDEX POINTER (WHITE)

FAILURE WARNING FLAG

MEMORY INDEX POINTER (RED)

MEMORY INDEX POINTER (GREEN)

ALTITUDE ALERT ANNUNCIATOR


ALTITUDE COUNTER

PILOTS AND COPILOT'S INSTRUMENT PANELS

DADS - Mach/Airspeed Indicators and Altimeters Figure 5

SECTION 11 Page 7

Apr 02/87


VERTICAL SPEED INDICATOR

POINTER


PILOTS AND COPILOrS INSTRUMENT PANELS

SAT DISPLAY

Displays SAT in < t Celsius.

TAT DISPLAY Displays TAT in degrees Celsius.

TAS DISPLAY Displays TAS in knots.

BRT CONTROL Controls the overall display brightness.


DADS - Vertical Speed Indicators and Associated AFCS Advisory Display

Figure 6

SECTION 11 Page 8

Apr 02/87

ctianenefer OPERATING MANUAL

PSP 601A-6

IAS ACCELERATION TREND VECTOR

Indicates the air a aft IAS trend based on acceleration. Displayed in magenta and inhibited below GO knots.

IAS/MACH REFERENCE BUG

Indicates the IAS or Mach reference selected on the pilot's instrument remote controller. Displayed in cyan.

MACH DISPLAY

Displays Mach number at or above 0.45 Mach. Display is removed below 0.40 Mach. Resolution is 0.002 Mach.

The colour of the Mach display is the same as described for the IAS display.

FMS SPEED BUG

indicates the FMS reference speed when the flight director VNAV mode is selected. Displayed in magenta.

IAS/MACK REFERENCE DISPLAY

Provides a readout of the lAS/Mach reference bug with respect to the

PILOTS AND COPILOT'S INSTRUMENT PANEL

DADS - EFIS EADI Air Data Displays Figure 7 (Sheet 1)

SECTION 11 Page 9

Apr 02/87


IAS COMPARISON MONITOR ANNUNCIATOR

Rashes (amber) for 10 seconds and then comes on steady to indicate a 5 knots or more difference between tne on-side and cross-side (AS sources, for greater than 2 seconds. The IAS comparison monitor function is inhibited at SO knots or less.

VMO INDICATOR

Indicates the aircraft maximum operating velocity (VMO}. Displayed in red.

AoLl. DISPLAY

Ots&toys the selected amurfe for the flight atrector A 5 £ L mode, nartge & from 0 to 60,000 feet, selectable in 100 foot increments.

When the on-side EHSI and DADC are coupled to the master flight guidance computer, the Display and surrounding box are displayed in cyan. When the cross-side EHSI and DADC are coupled to the master FGC. the surrounding box is changed to yellow.

IAS DISPLAY AND SCALE

The IAS display and scale provide an indication of the IAS from 40 to 450 knots. Below 40 knots the IAS display is removed.

When the IAS data source is on-side the IAS display is green. When the source is cross-side, the cSsptay is yeBow. When the IAS exceeds the rafetence IAS. in the fSght director FLC or VFLC modes, by ± 5 knots. the display is amber. When the IAS exceeds VMO. as indicated by the VMO indicator, the olspiay is red. Whan the IAS acceleration trend vector exceeds the VMO, the display is smber.

IAS REVIS ION ANNUNCIATOR

Indicates a cross-side transfer of IAS data. An amber boxed XIAS is displayed on the receiving side and an amber boxed green IAS is displayed on the transferring side

NOTES 1 When IAS data from the coupled-side DADC is not

vafid, an IAS related displays are removed and a ted boxed IAS annunciation is displayed.

2 When the altitude preselect "function faSs the ASEL display is removed and a red boxed ASEL is displayed.

DADS - EFIS EADI Air Data Displays Figure 7 (Sheet 2)

SECTION 11 Page 10

Apr 02/87


PILOT'S INSTRUMENT REMOTE CONTROLLER

IAS/MACH PUSH CHG CONTROL/ SWITCH

Rotating the IAS/MACH PUSH CHG control/switch causes the IAS or Mach references displayed on the pilot's and copilot's EADls, to change. Pressing the IAS/MACH PUSH CHG control/switch causes the IAS reference to change to a Mach reference and vice versa. The push-to-change function is inhibited when the aircraft is on the ground.

GLARESHIELD (PILOT'S SIDE)

ALT SEL CONTROL

Rotating the ALT SEL control causes the ASEL displays, on the pilot's and copilot's EADls to change.

COPILOTS INSTRUMENT REMOTE CONTROLLER

GLARESHIELD (COPILOTS SIDE)

DADS - EFIS Instrument Remote Controllers Figure 8

SECTION 11 Page 11

Apr 02/87


IRS1

D M E :

NAV 1 -

ADF1

PILOT'S SIDE

EADI

CENTRE

EHSi

DISPLAY CONTROLLER

Q O © O

PILOTS SYMBOL

SENERATORl

IRS1 -

D M E 1 -

N A V 1 -

ADF1 -

WX-

INSTRUMENT REMOTE CONTROLLER

MFD

MFD CONTROLLER

00O®OD °og®8§

MFD SYMBOL

GENERATOR

ASCB

COPILOTS SIDE

e~L>:

K>—K^A V

EHSI

DISPLAY CONTROLLER

n M i i n Q O O O

IRS 2

DME 2

NAV2 AOF2 RA

COPILOTS SYMBOL

GENERATOR

IRS 2

O M E 2

N A V 2

A D F 2

RA

W X

TO/FROM FMS 1 AND FMS 2 IRS 1 AND IRS 2. AFCS 1 AND AFCS 2 AND DADS 1 AND DADS 2

INSTRUMENT REMOTE CONTROLLER

EFIS - Simplified Block Diagram Figure 9

SECTION 11 Page 12

Apr 02/87


FLIGHT DIRECTOR MODE ANNUNCIATORS

DECISION HEIGHT ANNUNCIATOR

ROLL SCALE

VMO INDICATOR

FLIGHT DIRECTOR COMMAND CUE

IAS DISPLAY

IAS ACCEL TREND VECTOR

IAS SCALE

FMS SPEED BUG

IAS/MACH REFERBSICE BUG

MACH DISPLAY

MARKER BEACON ANNUNCIATOR

AUTOPILOT ANNUNCIATOR

ALTITUDE PRESELECT DISPLAY

VERTICAL TRACK ALERT ANNUNCIATOR

VERTICAL NAVIGATION POINTER

GUDESLOPE POINTER

AIRCRAFT SYMBOL

LOCALIZER POINTER/ RISING RUNWAY

RADIO ALTITUDE DISPLAY

DECISION HEIGHT DISPLAY

INCLINOMETER

PILOTS AND COPILOTS INSTRUMENT PANELS

EFIS - EADI Normal Displays Figure 10

SECTION 11 Page 13

Apr 02/87


ATTITUDE FAILURE ANNUNCIATOR

ATTITUDE FAILURE

FLIGHT DIRECTOR FAILURE ANNUNCIATOR

FLIGHT DIRECTOR FAILURE


EFIS - EADI Failure Warning Annunciators Figure 11 (Sheet 1)

SECTION 11 Page 14

Apr 02/87

cftanerujer OPERATING MANUAL

PSP 601A-6

IAS FAILURE ANNUNCIATOR

LOCALIZER FAILURE ANNUNCIATOR

ASEL FAILURE ANNUNCIATOR

CROSS-SIDE DATA FAILURE ANNUNCIATOR

GLIDESLOPE FAILURE ANNUNCIATOR

RADIO ALTITUDE FAILURE ANNUNCIATOR

IAS, ALTITUDE PRESELECT. CROSS-SIDE DATA. GLIDESLOPE. VERTICAL NAVIGATION, RADIO

ALTITUDE AND LOCALIZER FAILURES

SYMBOL GENERATOR INTERNAL FAILURE ANNUNCIATOR

SYMBOL GENERATOR INTERNAL FAILURE

EFIS - EADI Failure Warning Annunciators Figure 11 (Sheet 2)

SECTION 11 Page 15

Apr 02/87


CAT 2 INVALID ANNUNCIATOR

FOOTS AND COPILOTS INSTRUMENT PANELS

EFIS - EADI Category 2 Annunciator Figure 12

SECTION 11 Page 16

Apr 02/87


IAS COMPARISON MONITOR ANNUNCIATOR

LOCALIZER COMPARISON MONITOR ANNUNQATOR

ATTITUDE COMPARISON MONITOR ANNUNCIATOR

GLIDESLOPE COMPARISON MONITOR ANNUNCIATOR


EFIS - EADI Comparison Monitor Annunciators Figure 13

SECTION 11 Page 17

Apr 02/87

OPERATING MANUAL PS? 601A-6

IAS REVERSION ANNUNCIATOR

SG REVERSION ANNUNCIATOR

IRS REVERSION ANNUNCIATOR


EFIS - EADI Reversionary Source Annunciators Figure 14

SECTION 11 Page 18

Apr 02/87

ctvanenaer OPERATING MANUAL

PSP601A-6

WIND VECTOR DISPLAY

HEADING SELECT BUG

FORE LUBBER LINE

HEADING SOURCE ANNUNCIATOR

COURSE SELECTS DESIRED TRACK DISPLAY

BEARING POINTS? NO. 1

NAVIGATION* SOURCE ANNUNCIATOR

COURSE PRESELECT SOURCE ANNUNCIATOR

BEARING POINTER SOURCE ANNUNCIATOR

COURSE DEVIATION 8AR

FMS FMS MESSAGE DRIFT ANNUNCIATOR BUG

TARGET ALERT ANNUNCIATOR

DISTANCE DISPLAY

WAYPOINT/DME RECIPROCAL IDENTIFIER COURSE

PRESELECT POINTER

RECIPROCAL COURSE POINTER

COURSE •PRESELECT POINTER

GLIDESLOPE POINTER

COURSE SELECT/DESIRED TRACK POINTER

• TO-FROM POINTER

"AIRCRAFT SYMBOL

COURSE PRESELECT DEVIATION BAR

TIME-TO-GO DISPLAY


EFIS - EHSI Full Compass Mode Figure 15

SECTION 11 Page 19

Apr 02/87


PARTIAL HEADING DIAL

COURSE/DESIRED TRACK DISPLAY

OFF SCALE ARROW

NAV SOURCE ANNUNCIATOR

COURSE PRESELECT ANNUNCIATOR

BEARING POINTER SOURCE ANNUNCIATOR

DISTANCE DISPLAY

WIND VECTOR DISPLAY

COURSE SELECT/ DESIRED TRACK POINTER

FORE HEADING FMS LUBBER SOURCE MESSAGE UNE ANNUNCIATOR ANNUNCIATOR

TARGET ALERT ANNUNCIATOR

HEADING SELECT DISPLAY

HEADING SELECT BUG

FMS DRIFT BUG

COURSE PRESELECT POINTER

GUDESLOPE POINTER

COURSE PRESELECT DEVIATION BAR

GROUND SPEED DISPLAY

WAYPOINT/DME IDENTIFIER

BEARING POINTS NO. 1

COURSE AIRCRAFT TO/FR DEVIATION SYMBOL ANNUNCIATOR BAR


EFIS - EHSI ARC Mode Figure 16

SECTION 11 Page 20

ApT 02/87

ctiauenejer

COURSE SELECT DISPLAY

VOR STATION SYMBOL

SELECTED COURSE UNE


SELECTED BEARING NO. 2 DISPLAY

CROSS-TRACK DISTANCE DlSP! * v

VOR NAVIGATION SOURCE

VOR BEARING

WAYPOINTS

STATION SYMBOLOGY

VOR ONLY - O «=MS ONLY)

VOR/DME- £ >

DME ONLY -<£> (FMS ONLY)

CROSS-TRACK DISTANCE DISPLAY

FMS NAVIGATION SOURCE

WAYPOINT LEG

TO WAYPOINT IDENTIFIER

WAYPOINT FLIGHT LEVEL

P I L O T S AND C O P I L O T S INSTRUMENT PANELS

EFIS - EHSI MAP Mode Figure 17

SECTION 11 Page 21

Apr 02/87

MODS ANNUNCIATOR


ALERT ANNUNCIATOR

RANGE RING

WX RETURN DISPLAY

RANGE ANNUNCIATOR


EFIS - EHSI Weather Radar Display Figure 18

SECTION 11 Page 22

Apr 02/87


IRS FAILURE ANNUNCIATOR

/ t

IOI

CRS 349

^ \

V o £: R -=-£ 1 r

.xXM'i'/'/,. HDG 340

v§>

ir DME • ' ' , /? s • \ \

^

180 RNE

I

TTG 34.5

o

V^z J X^LS

HEADING FAILURE

NAV SOURCE FAILURE ANNUNCIATOR

/Z N j

Q MAG

V HDG 340

= > GLIDESLOPE FAILURE ANNUNCIATOR

NAVIGATION SOURCE AND GUDESLOPE FAILURE

PILOT'S A N D COPILOTS I N S T R U M E N T PANELS

EFIS - EHSI Failure Warning Annunciators Figure 19

SECTION 11 Page 23

Apr 02/87


IRS HEADING COMPARISON MONITOR ANNUNCIATOR


EFIS - EHSI Comparison Monitor Annunciator Figure 20

SECTION 11 Page 24

Apr 02/87


SG REVERSION ANNUNCIATOR

IRS REVERSION ANNUNCIATOR

PILOT'S A N D COPILOTS I N S T R U M E N T PANELS

EFIS - EHSI Reversionary Source Annunciators Figure 21

SECTION 11 Page 25

Apr 02/87


COURSE SELECT/ DESIRED TRACK DISPLAY

NAVIGATION SOURCE ANNUNCIATOR $

TO/!=R A*NEL,rrtClATC=:

COURSE DEVIATION COURSE POINTER SELECT/DESIRED

TRACK POINTER

GLIDESLOPE POINTER

HEADING SELECT DISPLAY

HEADING SELECT BUG

MOTE


The composite cfisptey is a reversionary mode, used to provide both essential attitude cfirector and horumiuri situation information on one display, in the event that an electrooic OBptoy unit fafls.

EFIS - Composite Display Figure 22

SECTION 11 Page 26

Apr 02/87


DISTANCE AND COURSE TO DESIGNATOR

HEADING DIAL

LUBBER LINE

TUNED VOR/DME

NAVIGATION SOURCE ANNUNCIATOR

VOR/DME NAVAID SYMBOL

^ ^ VOR/DME

^ ^ D M E ONLY

O VORONLY

AIRPORT IDENTIFIER

RANGE RING

DESIRED TRACK LINE

WEATHER RADAR MODE

DESIGNATOR LATITUDE/ LONGITUDE DISPLAY

TGT/VAR ANNUNCIATOR

AIRCRAFT SYMBOL

-TO** WAYPOINT DISPLAY

ETA TTG IN OR IN GMT HR:MN

DISTANCE T O T O ' WAYPOINT DISPLAY

DESIGNATOR DISPLACEMENT LINE

CROSS-TRACK DEVIATION DISPLAY


EFIS - MFD MAP Mode Figure 23

SECTION 11 Page 27

Apr 02/87


DISTANCE AND COURSE TO DESIGNATOR

AIRCRAFT SYMBOL

TUNED VOR/DME

SELECTED NAV SOURCE

MAG ANNUNCIATOR

-NORTH-UP* IDENTIFIER

DISPLACEMENT LINE

DESIGNATOR

RANGE

AIRPORT ANNUNCIATOR

WEATHER RADAR MODE

TGT/VAR ANNUNCIATOR

T O " WAYPOINT

DESIGNATOR LATITUDE/ LONGITUDE DISPLAY

ETA TTG IN OR IN

GMT HRrMN

RANGE RING

WAYPOINT DISTANCE TO T O " WAYPOINT


EFIS - MFD PLAN Mode Figure 24

SECTION 11 Page 28

Apr 02/87

cttanenefer OPERATING MANUAL

PSP 601A-6

GSPD/TTG PUSHBUTTON

Alternately selects ground speed (GS) or time-to-go (TTG) for display. /<

WX PUSHBUTTON

Selects weather radar returns for display in partial compass format.

MAP PUSHBUTTON

Selects display of active waypornts and VOR/DME ground station positions on partial compass display.

ET PUSHBUTTON

Selects elapsed time display instead of GS/TTG display.

V/L PUSHBUTTON

Selects between the on-side and cross-side SRN systems (see note).

FULL/ARC PUSHBUTTON

Selects full compass (360 degrees of heading} or partial compass (90 degrees of heading) format for display.

BRG O KNOB

Selects the bearing source for the No. 1 bearing pointer on the EHSl.

ADl DIM (OUTER) CONTROL

Adjusts the brightness of the EAOI display. When set to OFF. the EHSl displays a composite EAOI and EHSl.

FMS PUSHBUTTON

Selects between the on-side and cross-side LRN system (FMS).

BRG O KNOB

Selects the bearing source for the No. 2 bearing pointer on the EHSl.

WX DIM (INNER) CONTROL

Adjusts the brightness of the weather radar returns on the EHSl.

OH/TST (INNER) CONTROL

Rotating the control adjusts the decision height display on the EAOI. When pressed activates the test mode.

HSl DIM (OUTER) CONTROL

Adjusts the brightness of the EHSl display. When set to OFF. the EADl displays a composite EAOI and EHSL

PILOT'S AND COPILOT'S SIDE PANELS

NOTE SRN systems are the VHF navigation system and the DME system.

EFIS - Display Controller Figure 25

SECTION 11 Page 29

Apr 02/87


HDG PUSH SYNC PUSHBUTTON

When rooted, moves the heading bug on the p8ot's EHSl. When pressed, causes the heading bug to synchronize to the aircraft heading.

IAS/MACH PUSH CHG CONTROL/ SWITCH

When rotated, adjusts the lAS/Mach reference on the pilot's and copilot's EAOis. When pressed. change the IAS reference to the Mach reference or vice versa. The push-to-change function is inhibited with the aircraft on the ground.

CRS PUSH OCT CONTROL/ SWITCH

When rotated, rnoves the course select pointer on the associated EHSl. When pressed, causes the course pointer to indicate the 2ero deviation course to the tuned VOR station. When an FMS source is selected, rotating the control causes the preselect course pointer to move.

ALT SEL CONTROL

When rotated, adjusts the AScL display on the pilot's and copilot's EADJs.

HOG PUSH SYNC PUSHBUTTON

When rotated, moves the heading bug on the copdot's EHSl. When pressed, causes the heading bug to synchronize to the aircraft heading.

GlARESHiELD

EFIS - Instrument Remote Controllers Figure 26

SECTION 11 Page 30

Apr 02/87


WX PUSHBUTTON

Selects the weather radar information for display on the MFD indicator.

NORM PUSHBUTTON

Selects checklist index page for display on MFD indicator.

SRC PUSHBUTTON

Selects long range navigation source for MAP and PLAN modes.

MAP/PLAN PUSHBUTTON

Alternately selects MAP or PLAN format for MFD indicator display.

VOR PUSHBUTTON

Selects VOR/DME information for display on MFD indicator.

INC/DEC RNG CONTROL

Increases or decreases the range display on the MFD indicator.

EMER PUSHBUTTON

Selects emergency checklist index page for display on MFD indicator.

SKP PUSHBUTTON

Allows skipping of designator or active lines.

DAT PUSHBUTTON

Allows additional long range navigation information to be added to the MAP or PLAN mode display

ENT PUSHBUTTON

Enters designator as a waypotm. checks off a line or selects an index line item for display.

RCL PUSHBUTTON

Recalls designator to home position or recalls lowest numbered skipped tine in a checklist.

PAG PUSHBUTTON

Advances the page count and places the active line selection at first line of the page.

CENTRE PEDESTAL

EFIS - MFD Controller Figure 27

SECTION 11 Page 31

Apr 02/87


COMP WON SWITCH/LIGHT

Comes on (amber) to indicate that a difference exists between one of the on-side and cross-side sources. The out-of -tolerance source is indicated on the EADl. When pressed, resets the comparison circuits.

SG REV SWITCH/UGHT

When pressed, selects the cross-side symbol generator as a back-up when the on-side symbol generator fafls.

IAS REV SWITCH/LIGHT

When pressed, selects the cross-side OADC as a back-up IAS source when the on-side source fails.

IRS REV SWTTCH/UGHT

When pressed, selects the cross-side IRS as back-up when the on-side IRS source fails.

FD REV SWITCH/LIGHT

When pressed, selects the cross-side flight guidance computer (FGC) as a back-up flight director when the on-side FGC fails.


EFIS - Remote Switch/Lights Figure 28

SECTION 11 Page 32

Apr 02/87

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