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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 Page 1
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 -Page 2
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
OPERATING MANUAL PSP 601A-6
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
OPERATING MANUAL PSP 601A-6
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
OPERATING MANUAL PSP 601A-6
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
OPERATING MANUAL PSP 601A-6
MACH/AIRSPEED INDICATOR
BARO COUNTERS
ALTIMETER
MEMORY INDEX POINTER (WHITE)
FAILURE WARNING FLAG
MEMORY INDEX POINTER (RED)
MEMORY INDEX POINTER (GREEN)
ALTITUDE ALERT ANNUNCIATOR
FAILURE WARNING FLAG
ALTITUDE COUNTER
PILOTS AND COPILOT'S INSTRUMENT PANELS
DADS - Mach/Airspeed Indicators and Altimeters Figure 5
SECTION 11 Page 7
Apr 02/87
OPERATING MANUAL PSP 601A-6
VERTICAL SPEED INDICATOR
POINTER
FAILURE WARNING FLAG
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.
CENTRE INSTRUMENT PANEL
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
OPERATING MANUAL PSP 601A-6
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
OPERATING MANUAL PSP 601A-6
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
OPERATING MANUAL PSP 601A-6
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
OPERATING MANUAL PSP 601A-6
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
OPERATING MANUAL PSP 601A-6
ATTITUDE FAILURE ANNUNCIATOR
ATTITUDE FAILURE
FLIGHT DIRECTOR FAILURE ANNUNCIATOR
FLIGHT DIRECTOR FAILURE
PILOTS AND COPILOT'S INSTRUMENT PANELS
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
OPERATING MANUAL PSP 601A-6
CAT 2 INVALID ANNUNCIATOR
FOOTS AND COPILOTS INSTRUMENT PANELS
EFIS - EADI Category 2 Annunciator Figure 12
SECTION 11 Page 16
Apr 02/87
OPERATING MANUAL PSP 601A-6
IAS COMPARISON MONITOR ANNUNCIATOR
LOCALIZER COMPARISON MONITOR ANNUNQATOR
ATTITUDE COMPARISON MONITOR ANNUNCIATOR
GLIDESLOPE COMPARISON MONITOR ANNUNCIATOR
PILOTS AND COPILOTS INSTRUMENT PANELS
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
PILOTS AND COPILOT'S INSTRUMENT PANELS
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
PILOTS AND COPILOTS INSTRUMENT PANELS
EFIS - EHSI Full Compass Mode Figure 15
SECTION 11 Page 19
Apr 02/87
OPERATING MANUAL PSP 601A-6
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
PILOTS AND COPILOTS INSTRUMENT PANELS
EFIS - EHSI ARC Mode Figure 16
SECTION 11 Page 20
ApT 02/87
ctiauenejer
COURSE SELECT DISPLAY
VOR STATION SYMBOL
SELECTED COURSE UNE
OPERATING MANUAL PSP 601A-6
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
OPERATING MANUAL PSP 601A-6
ALERT ANNUNCIATOR
RANGE RING
WX RETURN DISPLAY
RANGE ANNUNCIATOR
PILOTS AND COPILOTS INSTRUMENT PANELS
EFIS - EHSI Weather Radar Display Figure 18
SECTION 11 Page 22
Apr 02/87
OPERATING MANUAL PS? 601A-6
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
OPERATING MANUAL PSP 601A-6
IRS HEADING COMPARISON MONITOR ANNUNCIATOR
PILOTS AND COPILOTS INSTRUMENT PANELS
EFIS - EHSI Comparison Monitor Annunciator Figure 20
SECTION 11 Page 24
Apr 02/87
OPERATING MANUAL PSP 601A-6
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
OPERATING MANUAL PS? 601A-6
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
PILOTS AND COPILOTS INSTRUMENT PANELS
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
OPERATING MANUAL PSP 601A-6
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
CENTRE INSTRUMENT PANEL
EFIS - MFD MAP Mode Figure 23
SECTION 11 Page 27
Apr 02/87
OPERATING MANUAL PSP 601A-6
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
CENTRE INSTRUMENT PANEL
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
OPERATING MANUAL PSP 601A-6
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
OPERATING MANUAL PSP 601A-6
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
OPERATING MANUAL PSP 601A-6
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.
PILOTS AND COPILOTS INSTRUMENT PANELS
EFIS - Remote Switch/Lights Figure 28
SECTION 11 Page 32
Apr 02/87