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chanentjer
OPERATING MANUAL
SECTION 16
NAVIGATION
TABLE OF CONTENTS
Subject Page
GENERAL 1
INDEPENDENT POSITION DETERMINING SYSTEMS 1
Weather Radar
Radio Altimeter Display 5
Gyro Compass 8
DEPENDENT POSITION DETERMINING SYSTEMS 11
VHF Navigation
VOR Mode
ILS Mode
Marker Beacon Receiver
VOR Test Mode 12
ILS Test Mode
Flight Director Switching 19
Automatic Flight Control System Interface
Instrument Comparator
Automatic Direction Finder
VOR Interface 21
Compass System Interface
Distance Measuring Equipment
ATC Transponder 22
MISCELLANEOUS INSTRUMENTS 22
Digital Clock
LIST OF ILLUSTRATIONS
Figure
Number Title Page
1 Indicator Controls (2 Sheets) 2
2 Mode Display 4
3 Radio Altimeter Display (2 Sheets) 6
16 - CONTENTS
Page 1
Oct 03/83
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OPERATING MANUAL
LIST OF ILLUSTRATIONS
Figure
Number Title Page
4 Compass Control Panel (2 Sheets) 9
5 NAV-1 Control Panel 13
6 NAV-2 Control Panel 14
7 Radio Magnetic Indicator 15
8 Horizontal Situation Indicator ( 2 Sheets) 16
9 Marker Lights with High/Low Switch 18
10 ADF Control Unit 20
11 Transponder Control Unit 23
12 Digital Clock 24
16 - CONTENTS
Page 2
Oct 03/83
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OPERATING MANUAL
SECTION 16
NAVIGATION
GENERAL
There are two types of airborne navigation systems, the independent positioning
determining systems (IPDS), and the dependent positioning determining systems
(DPDS). The IPDS consists of three systems, weather radar, a radio altimeter,
and a gyro compass. The DPDS consists of four systems, VHF navigation,
automatic direction finding (ADF), distance measuring equipment (DUE), and an
ATC transponder. Miscellaneous instruments are described in this Section.
INDEPENDENT POSITION DETERMINING SYSTEMS
A. Weather Radar (Figures 1 and 2)
The weather radar is used for weather detection and analysis. A ground
mapping mode is provided as a modified display. It has a three-colour
presentation on a black background. Each colour represents a different
level. A three-coloured bar legend display defines the meaning of each
colour.
WEATHER
Level 3 Red Heaviest rainfall
Level 2 Yellow Next heaviest rainfall
Level 1 Green Least rainfall
Black No reflective target
GROUND MAPPING
Level 3 Magenta Most reflective target
Level 2 Yellow Next level of reflective target
Level 1 Cyan Least level of reflective target
The system consists of three line replaceable units, a receiver-transmitter,
a digital indicator and an antenna pedestal with flat-plate radiator. All
the system controls are on the front of the indicator (Figure 1).
The system operates in the cyclic, weather and mapping modes. In the
cyclic mode, high-level signals flash. In the weather mode, azimuth strobe
lines, mode and range alphanumerics are displayed to assist in evaluating
weather data. In the ground mapping mode, the display is available as a
secondary source of navigational information.
SECTION 16
Page 1
Oct 03/83
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OPERATING MANUAL
TARGET ALERT SWITCH/LIGHT
When pressed enables target alert in WX
mode only. Amber light comes on and T is
displayed if there are no targets in the target
alert sector. If there are targets TGT is
displayed and flashes at 0.5 second intervals.
FREEZE SWITCH
When pressed, freezes the display
and prevents updating. FRZ is
displayed in the auxiliary field and
flashes at 0.5 second intervals.
AZIMUTH REFERENCE POINTS
Provides azimuth reference points, in 30
degree increments, to assist display analysis.
SECTOR SCANNING SWITCH
In normal position 120 degrees scanning selected.
When pressed 60 degree scanning selected.
AZIMUTH STROBE SWITCH
When pressed azimuth strobe lines
appear on the display.
Indicator Controls SECTION 16
Figure 1 (Sheet 1) Page 2
May 28/82
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OPERATING MANUAL
'o
WX (Weather mode)
When pressed radar is in weather
mode and WX is displayed.
STANDBY MODE SWITCH
Enables radar to be on without transmitting. During warmup
period of 70 seconds WAIT is displayed, after which STBY is
displayed.
RANGE
50 TOO 200
| 2 5 . / >2fc<v300
C\F SIVY V\X ClrX bh?
CYCLIC MODE
When pressed in WX or MAP mode high level targets flash at
0.5 second intervals. CYC is displayed and AGC is
automatically selected.
MAP MODE
When pressed radar is in ground mapping mode and MAP is
displayed.
•DDDD TILT
STAB
RANGE/TEST SWITCH
Provides six range positions from 10 to 300 nautical miles. In
TEST position displays a test pattern.
ON~^T^~OFF
GAIN CONTROL
In PRESET automatic gain control is applied to the receiver.
Out of PRESET manual gain is available.
TILT CONTROL
Controls angle of antenna beam tilt with
regard to earth plane.
INTENSITY CONTROL
Controls intensity of the display.
STABILISATION
ON/OFF control of antenna stabilisation.
Indicator Controls SECTION 16
Figure 1 (Sheet 2) Page 3
May 28/82
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OPERATING MANUAL
STANDBY MODE WX MODE WITH TARGET ALERT DISPLAYED
MAP MODE CYCLIC MODE
.
FRZ
LTEST
.—-^M-—
~ *
^J^
/ - - • • • > . - •
x
:
• ^ T3M|
3
60
TEST PATTERN IN WX MODE TEST PATTERN IN MAP MODE
Mode Display
Figure 2
SECTION 16
Page 4
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OPERATING MANUAL
The antenna is stabilized in line of sight and controlled by a vertical
gyro in pitch and roll. A tilt control enables any desired antenna beam
angle between +15 degrees. This includes any elevation correction made by
the stabilizing circuits. When the 60-degree SEL SCAN is selected the
antenna scans at 28 scans per minute, and at 14 scans per minute in the
120-degree SEL SCAN.
Radio Altimeter Display (Figure 3)
The radio altimeter consists of a receiver-transmitter, a radio altimeter
indicator, a transmit antenna and a receive antenna. The radio altimeter
display is shown in Figure 3 (Sheet 1).
For aircraft 1021 and subs,
the radio altimeter display is shown in Figure 3 (Sheet 2 ).
The receiver-transmitter transmits a frequency modulated continuous wave
(FM/CW) signal. The receiver receives a ground reflected signal and
produces a signal with a frequency proportional to aircraft altitude.
If the signal is strong enough to provide accurate data, it is translated
into a dc analogue voltage which is fed to the RAD ALT indicator to drive
the pointer display. The indicator sends a validity signal to the flight
director computer. The dc analogue voltage is also fed to altitude trip
circuits in the receiver-transmitter to provide gain programming to the
autopilot during ILS approach (refer to SECTION 4, AUTOMATIC FLIGHT CONTROL
SYSTEM).
If the strength of the signal is not sufficient to provide accurate
altitude data, a bias voltage is sent to the RAD ALT indicator to drive the
pointer off scale, and send a warning signal to the flight director
computer.
A decision height knob, DH, allows the pilot to set a desired altitude.
When the aircraft descends to this height, DH annunciators on the RAD ALT
indicator and both attitude director indicators come on. The system,
excluding the antenna, may be tested with the self-test switch on the
indicator. A simulated 50-feet signal checks the accuracy of the system.
If the DH index is set below 50 feet the DH annunciators come on.
On aircraft 1021 and subs,
the radio altimeter display is included as part of the attitude director
indicator (ADI). The receiver-transmitter and the antennas are the same as
in the basic aircraft.
The four-digit, incandescent display on the ADI indicates the aircraft
radio altitude from -20 to 2500 feet. Resolution above 200 feet of
altitude is 10 feet and below 200 feet resolution is 5 feet. For altitudes
above 2500 feet, the display is blanked. When the radio altitude data is
invalid, the display indicates a dash in each digit.
SECTION 16
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OPERATING MANUAL
DH ANNUNCIATOR
Comes on when aircraft reaches the decision
height.
ALTITUDE POINTER
FLAG
When in view indicates system
malfunction.
DISPLAY SCALE
-20 to 2500 ••*<
SELF TEST
When pressed initiates self test.
RADIO ALTIMETER INDICATOR
DH SET KNOB
To adjust the DH index
EFFECTIVITY: A/C 1004 TO 1020
Radio Altimeter Display
Figure 3 (Sheet 1)
SECTION 16
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OPERATING MANUAL
DECISION HEIGHT
DISPLAY
RADIO ALTITUDE
TEST SWITCH
ATTITUDE DIRECTOR INDICATOR
"RADIO ALTITUDE
DISPLAY
DECISION HEIGHT
SET KNOB AND
DIM CONTROL
EFFECTIVITY: A/C 1021 & SUBS
Radio Altimeter Display
Figure 3 (Sheet 2)
SECTION 16
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OPERATING MANUAL
A composite control knob on the ADI provides for setting decision height
and adjusting display brightness* The inner knob, DH SET, is used to set
an altitude between 0 and 990 feet on the decision height (DH) display.
The outer knob, DIM, controls the brightness of the RAD ALT and DH displays.
Decision height on the ADI is indicated on a three-digit incandescent
display and indicates the preselected radio altitude between 0 and 990 feet
that is set by the DH knob. Display resolution is 10 feet. When the
aircraft is at or below the decision height, the DH annunciator comes on to
warn the pilot.
A radio altitude (RA) test switch is used to initiate a test sequence.
When the RA test switch on the ADI is pressed, the test sequence on the ADI
RAD ALT and DH displays is initiated.
The RAD ALT display, during the test, initially shows four-eights, then
changes to four-dashes and finally changes to the test altitude. The test
altitude remains on the RAD ALT display until the test switch is released,
then the actual altitude is displayed.
The DH display, during the test, initially shows three-eights and then
reverts to the current set DH value for the remainder of the test.
The test sequence is inhibited after the ADI GS mode annunciator comes on
(APR CAP engage).
C. Gyro Compass
The compass system provides a continuous magnetic heading reference for
aircraft navigation. It is a dual system consisting of two flux valves, a
dual compensator, two directional gyros, two control panels and two
synchronizer assemblies.
The flux valves are magnetic azimuth detectors that sense the direction of
the horizontal component of the earth's magnetic field relative to the
longitudinal axis of the aircraft.
The dual compensator electrically compensates for single-cycle error. The
two gyros and amplifier assemblies provide gyro stabilized heading
references for the horizontal situation indicators (HSI), the radio
magnetic indicators (RMI), navigation receivers and the autopilot.
Both control panels contain a mode switch, a slew switch and a null meter.
Operation of the compass controls is described in Figure 4.
SECTION 16
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OPERATING MANUAL
DG/SLAVED SWITCH
Controls mode of operation of the system.
DG —Directional gyro in free mode.
SLAVED—Directional gyro controlled by flux
valve.
Displays synchronization error between the
flux valve heading and the gyro heading.
When system is synchronized, the pointer is
in the central position.
SYNCH SWITCH
Switch is slewed to synchronize gyro with the flux valve.
EFFECTIVtTY: A/C 1004 TO 1020
Compass Control Panel
Figure 4 (Sheet 1)
SECTION 16
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OPERATING MANUAL
MODE SWITCH
Controls mode of operation of the system.
DG - Directional gyro in free mode.
SLAVED - Directional gyro controlled by flux valve.
COMPASS CONTROLS
DG
SLAVED
SYNCH SWITCH
Switch is slewed to synchronize gyro
with the flux valve.
EFFECTIVITY : A/C 1021 & SUBS
Compass Control Panel SECTION 16
Figure 4 (Sheet 2) page 10
Oct 03/83
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OPERATING MANUAL
DEPENDENT POSITION DETERMINING SYSTEMS
A. VHF Navigation (Figures 5, 6, 7 and 8)
The VHF navigation system is a dual receiving system (NAV-1 and NAV-2) and
operates in two modes, VHF omnirange (VOR) for enroute navigational
guidance, and instrument landing system (ILS) for terminal guidance. The
ILS consists of a localiser (LOC) receiver and a glidescope (GS) receiver.
A marker beacon receiver is provided for distance-to-runway threshold
information.
The VOR mode is operational when a VOR frequency is set on the navigation
control unit and ILS is operational when a LOC frequency is set on the
navigation control unit. The GS frequency is paired to the LOC frequency
and is automatically tuned. The marker beacon receiver is operational in
both modes.
(1) VOR Mode
NOTE: The following description applies to both systems. Only NAV-1
is described.
When the navigation receiver is tuned to a VOR frequency, the received
signal is processed to produce an aural signal to identify the station
received, a deviation signal and a bearing signal. The aural signal
is fed to the intercom system and the bearing signal is fed to the
pilots1 HSI and RMI to drive the bearing pointer. A deviation signal
is fed to the HSI and the flight director computer, and a TO/FROM
signal to the HSI. A flag circuit monitors the output of the receiver
and provides a validity signal.
(2) ILS Mode
The ILS mode provides terminal guidance using ground station localiser
and glideslope transmitters. The received LOC deviation signal is fed
to the course deviation bar on the pilot's HSI and the received GS
deviation signal is fed to the vertical deviation pointer on the ADI.
The receiver also provides LOC validity and GS validity signals which
are fed to the flight director computer and to the HSI and ADI warning
flags.
(3) Marker Beacon Receiver (Figure 9)
The marker beacon receiver provides visual and aural indication of the
position of the aircraft when flying over the marker beacon radio
SECTION 16
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OPERATING MANUAL
stations. As the aircraft passes the markers, an aural tone and an
indicator light signal are produced as follows:
MARKER LIGHT
Outer OUTER (blue)
Middle MIDDLE (amber)
Inner AIRWAY (white)
A HIGH/LOW switch adjacent to the lights controls the sensitivity of
the marker beacon receiver.
VOR Test Mode
NOTE: The receiver is set to a VOR frequency and the course selector
to approximately five degrees prior to testing.
When the TEST switch on the NAV control unit is held in the NAV
position and a VOR signal is present the following occurs: the HSI NAV
mode flag remains out of view, the TO/FROM flag indicates TO and the
course deviation bar centres. The RMI pointer indicates between 0 and
5 degrees magnetic bearing. The three marker lights flash and an
aural tone is heard through the headphones/speaker.
When the TEST switch is released, the HSI NAV mode flag comes into
view within one second and goes out of view within 5 seconds. The
marker lights stop flashing and the system returns to the pretest
condition.
If there is no VOR signal present when the test switch is set to NAV,
the HSI NAV mode flag goes out of view after three seconds and the
TO/FROM flag indicates TO. The RMI indicates between 0 and
5 degrees magnetic bearing. The marker lights flash and an aural tone
is heard through the headphones/speaker. When the TEST switch is
released, the HSI NAV mode flag comes into view, the RMI pointer parks
and the marker lights go out within one second.
ILS Test Mode
When the TEST switch is in the NAV position with a LOC signal present
the following occurs; the HSI NAV mode flag stays out of view, the
lateral deviation bar deflects one dot to the right and the GS
deviation bar moves down one dot. The ADI GS deviation pointer moves
down one dot and the expanded localizer pointer moves out of view to
the right. The three marker lights flash and an aural tone is heard
through the headphones/speaker.
SECTION 16
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OPERATING MANUAL
NAV-1 FREQUENCY DISPLAY
Displays frequency chosen for the NAV-1
system. The DME-1 operates on the same frequency
unless DME HOLD has been set prior
to altering the NAV-1 frequency.
DME-1 HOLD PUSH SWITCH
When set to HOLD, the amber light comes on
and the DME-1 frequency holds to enable the
NAV-1 frequency to be altered without affecting
the DME frequency.
NAV-1 DME-1
FREQUENCY SELECTOR
Controls NAV-1 and DME-1 operating
frequency.
Selector for tenths and hundreths of MHz
Selector for tenths and units of MHz.
VOLUME CONTROL ON/OFF SWITCH
Switches NAV-1 and DME-1 on/off and
controls volume of the audio signal to the
headphones.
TEST SWITCH
Selects self test of NAV-1 or DME-1 system.
DME-1 STATUS SWITCH
In STBY power is applied to the DME-1
system but no transmission takes place. In
the NORM position the DME-1 system is fully
operational.
NAV-1 Control Panel
Figure 5
SECTION 16
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OPERATING MANUAL
DME-2 HOLD PUSH SWITCH
When set to HOLD the amber light comes on
and the DME-2 frequency holds to enable the
NAV-2 frequency to be altered without affecting
the DME frequency.
NAV-2 FREQUENCY DISPLAY
Displays frequency chosen for NAV-2
system. The DME-2 system operates on the
same frequency unless DME HOLD has been
set prior to altering the NAV-2 frequency.
NOTE
The COMM-2 controls are described
in Section 6.
DME-2 STATUS SWITCH
In STBY, power is applied to the DME-2
system but no transmission takes place.
In the NORM position the DME-2 is fully
operational.
NAV-2 DME-2
FREQUENCY SELECTOR
Selector for tenths and units of MHz.
tenths and hundreths of MHz.
VOLUME CONTROL ON/OFF SWITCH
Switches NAV-2 and DME-2 on/off and
controls volume of the audio signal to the
headphones.
TEST SWITCH
.Self test NAV-2 or DME-2 systems.
NAV-2 Control Panel
Figure 6
SECTION 16
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OPERATING MANUAL
. O k \ i /ilCD
SINGLE BAR POINTER
Indicates VOR or ADF bearing.
COMPASS CARD
Indicates aircraft
magnetic heading.
FORE LUBBER LINE
DOUBLE BAR POINTER
indicates VOR or ADF bearing.
SINGLE BAR SWITCH
Selects ADF or VOR on single
bar pointer.
AFT LUBBER LINE
OFF FLAG
When in view indicates
system malfunction.
DOUBLE BAR SWITCH
Selects ADF or VOR on double
bar pointer.
Radio Magnetic Indicator
Figure 7
SECTION 16
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OPERATING MANUAL
COURSE
DEVIATION BAR
VERTICAL
WARNING FLAG
HEADING DIAL
RECIPROCAL
COURSE
POINTER
EFFECTIVITY: A/C 1004 TO 1020
DME
SWITCH
BEARING SELECT
PUSHBUTTONS
Horizontal Situation Indicator
Figure 8 (Sheet 1)
SECTION 16
Page 16
Oct 03/83
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OPERATING MANUAL
,0\t
&=S
COURSE FORE
SELECT LUBBER
POINTER LINE
TRUE HEADING
HEADING WARNING
ANNUNCIATOR FLAG
DISTANCE
DISPLAY
NAVIGATION
SOURCE
ANNUNCIATORS'
WAYPOINT
ANNUNCIATOR"
VERTICAL
DEVIATION .
POINTER
COURSE
DEVIATION
BEARING
' SELECT
PUSHBUTTON
' NAVIGATION
WARNING FLAG
* COMPASS
SYNC
ANNUNCIATOR
AIRCRAFT RECIPROCAL AFT RECIPROCAL
SYMBOL BEARING LUBBER COURSE
POINTER LINE POINTER
TO-FROM
ANNUNCIATOR
EFFECTIVITY: A/C 1021 & SUBS
Horizontal Situation Indicator SECTION 16
Figure 8 (Sheet 2) Page 17
Oct 03/83
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OPERATING MANUAL
AIRWAY MIDDLE OUTER
HIGH
LOW
Marker Lights with High/Low Switch
Figure 9
SECTION 16
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OPERATING MANUAL
When the TEST switch is released the HSI NAV mode flag comes into view
within one second goes and out of view within five seconds. The
marker lights go out and the system returns to the pretest condition.
If there is no LOC signal present when the TEST switch is in the NAV
position, the HSI NAV mode flag goes out of view after three seconds,
the lateral deviation bar moves one dot and the expanded localizer
pointer moves out of sight to the right. The marker lights flash and
an aural tone is heard through the headphones/speaker.
When the TEST switch is released the HSI NAV mode flag comes into view
within one second, the lateral bar centres, the ADI GS deviation
pointer parks and the expanded localizer pointer centres. The marker
lights go out.
(6) Flight Director Switching
A two position switch on the flight director switching panel labeled
CAPT FLT DIR, switches the pilot's flight director navigational
information from NAV 1 in the normal position, to NAV 2.
(7) Automatic Flight Control System Interface
The navigation system is interfaced with the automatic flight control
system through the NAV, APR and VORAPR switch/lights on the flight
director mode selector (refer to Section 4).
(8) Instrument Comparator
The instrument comparator monitors compass heading information used by
NAV-1 and NAV-2 system, localiser signals and glidescope signals.
Should a predetermined difference be exceeded, individual
annunciators, HD6, GS and LOC come on (refer to Section 4).
Automatic Direction Finder (Figure 10)
The ADF provides aural reception from selected ground stations and
indicates relative bearing to that station. The station selected may be a
non-directional beacon or standard AM broadcast station in the frequency
range 190 to 1749.5 kHz.
The major units in the system are the combined sense and loop antenna, a
receiver, and two radio magnetic indicators. There are three selectable
switch positions:
ANT - Audio reception with RMI parked
ADF - Audio reception with RMI providing bearing
Tone - Beat frequency oscillator (BFO) in addition to ANT or ADF to
enable CW reception.
SECTION 16
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OPERATING MANUAL
ADF
FREQUENCY
DISPLAY
FREQUENCY
CONTROL
VOLUME
CONTROL
BFO
CONTROL
SWITCH
ADF
ON/OFF
SWITCH
TEST SWITCH
Operates in ADF only
MODE SWITCH
ADF — provides audio
and directional
data.
ANT — provides audio
only.
ADF Control Unit
Figure 10
SECTION 16
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OPERATING MANUAL
With the ADF switched on and the frequency tuned to the desired station the
system functions as follows:
In the ANT mode, the mode switch is in the ANT position to disable the
loop antenna circuits and the BFO switch is set to OFF. The signal
received by the sense antenna is fed to the receiver as an RF signal
with no bearing information. The receiver processes the signal and
passes it as an audio signal to the intercom system. As there is no
bearing information the RMI pointer is parked in the horizontal
position.
In the ADF mode, the mode switch is in the ADF position and the BFO is
off. Signals from the sense and loop antenna are sent to the receiver
as radio frequency signals carrying bearing information. This is
processed by the receiver which sends an audio output to the intercom
system and bearing information to the pilot!s RMI, the pilot's HSI.
the copilot's RMI and the copilot's HSI.
In the tone mode, the BFO is included in the ADF or ANT mode to
receive CW signals for station identification.
The self-test facilities can only be operated in the ADF mode. When the
test switch is operated the pointer rotates 90 degrees counter-clockwise
from the existing position and returns when the test switch is released.
A 1000-Hz tone is sent to the intercom system.
(1) VOR Interface
When the VHF NAV system is in the NAV mode the VOR sends a bearing
signal to the RMIs. Two VOR/ADF switches mounted on the front of the
indicator permit VOR or ADF bearing information to be displayed on the
single bar and double bar pointers.
(2) Compass System Interface
When the compass system is valid, a validity signal is sent to the RMI
and the heading flag is cleared. Magnetic heading is also fed to the
RMI compass card which displays the aircraft heading against a fixed
lubber line.
Distance Measuring Equipment
The DME is a dual system consisting of two DME receiver-transmitters and
two antennas. When the DME is on in the NORM position, a coded
interrogation signal is transmitted to the ground station, the ground
station sends back a coded reply. The DME receives the signal and
calculates the slant distance to the ground station from the time between
the transmitted signal and the received signal. An analogue voltage
SECTION 16
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OPERATING MANUAL
proportional to the slant distance is fed to the HSI as distance in
nautical miles, to the flight director computer for gain programming and to
the VNAV computer/controller for vertical navigation computations. The
receiver section also uses the analogue voltage to produce a DME valid
signal when the system is functioning correctly and the ground station is
in range. If a valid signal is not available, dashes appear on the
distance display on the HSI.
A DME-l/DME-2 switch, on the pilot's instrument panel, permits the pilot to
select which system feeds the pilot's HSI, the flight director computers
and the VNAV computer. The copilot does not have this facility.
A test switch, NAV/DME, on the NAV-1 and NAV-2 control units, allows the
associated DME to be tested. When the test switch is set to DME, the
distance display on the HSI reads either 000.0 or 000.1.
D. ATC Transponder (Figure 11)
The transponder (TRP) provides air traffic control (ATC) with coded
identification and altitude data.. The system consists of two
transponders, two antennas and one control unit. When the transponder is
selected to operate in mode A, only the selected code identification signal
is transmitted. When mode C is selected, aircraft altitude is added to the
identification signal. The identification code is set on the control unit
and the altitude data is fed to the transponder when the ALT/OFF switch is
in the ALT position.
On receipt of an interrogation signal the TRP tests the validity of the
received signal. If it is in mode A or mode C, it responds with the
appropriate coded information. Each time the TRP replies the REPLY lamp
comes on for one second. If requested by ATC the pilot can momentarily
press the IDENT push switch, to extend the transmitted reply to 20 seconds.
The TEST push-button switch tests mode A if the ALT/OFF switch is in the
OFF position and mode C if in the ALT position. The REPLY lamp will come
on to indicate the system is functioning correctly.
MISCELLANEOUS INSTRUMENTS
A. Digital Clock
The digital clock is described in Figure 12.
SECTION 16
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OPERATING MANUAL
IDENTIFICATION CODE WINDOW
Displays identification code.
IDENTIFICATION CODE SWtTCHES
Outer switch sets first digit, inner switch sets
second digit.
IDNT PUSH-BUTTON SWITCH
When pressed transmits identification code for 20-seconds.
REPLY LIGHT
Comes on for one second when reply signal is transmitted or
on completion of test.
IDENTIFICATION CODE SWITCHES
Outer switch sets fourth digit, inner switch
sets third digit.
^ ^
TEST PUSH-BUTTON SWITCH
Tests mode A when ALT/OFF switch is in
OFF position. Tests mode C when ALT/OFF
switch is in ALT position.
TRANSFER SWITCH
In position 1 No 1 system is on and No 2 system is in standby.
In position 2, No 2 system is on and No 1 system is in stand-
ALTITUDE DATA CONTROL
ALT-provides altitude data for mode C reply
signal.
STATUS SWITCH
OFF - both systems off.
STBY - both systems in standby.
ON - system selected by transfer
switch on,other system in standby.
Transponder Control Unit SECTION 16
Figure 11 Page 23
Oct 03/83
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OPERATING MANUAL
SET SWITCH
UP - advances clock one second for each
second held.
D - retards clock one second for each second
held.
BRIGHT/DIM SWITCH
B - brightens display.
DIM - dims display.
1 HR UP - advances time one hour when held
and released.
@XUP(0)D B(Q)1HR
SET niMUK
l LP i
ZERO /T^
HOURS AND MINUTES DISPLAY
TIME SWITCH
TIME - displays selected standard time.
F.T. - displays flight time.
E.T. - displays elapsed time.
SECONDS DISPLAY ELAPSED TIME SWITCH
RUN - starts elapsed time meter.
STOP - stops elapsed time meter.
ZERO - returns elapsed time meter to zero when held
and released. Also returns flight time meter to zero
when the aircraft is on the ground.
Digital Clock
Figure 12
SECTION 16
Page 24
Oct 03/83

17party

很好的资料！

dul

本帖隐藏的内容需要回复才可以浏览

bocome

庞巴迪挑战者导航

autofannuaa

偶然经过，学习一下

liu5031

导航都要看