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1500
H
2400FT
MULTIFUNCTION DISPLAY
(NAV SECTOR PAGE)
PRIMARY FLIGHT DISPLAY
PILOT'S AND COPILOT'S INSTRUMENT PANELS
Distance Readout
Indicates DME distance (slant
range maximum 300 NM) to
tuned navigation aid.
DME HOLD (H) Symbol
When DME-H is selected, H
replaces NM legend on distance
readout.
(yellow)
Distance Display
Navigation
Source Indicator
Station Identifier
Time-To-Go Display
Nautical Miles (NM)
DME Hold (H) Symbol
Ground Speed Readout (white)
When VOR is navigation source, readout indicates
DME ground speed.
When DME failed, readout and label blanked.
Cross-Side
Course
Displays
VOR 1
LOC 1
FMS 1
FMS 3
VOR 2
LOC 2
FMS 2
FMS 3
VOR 1
LOC 1
FMS 1
FMS 3
VOR 2
LOC 2
FMS 2
FMS 3
PFD 1 PFD 2
P604_17_034
YUL
LX/RADAR OFF G+3 USTB T+10.7
TAS 345 345
YUL
THURO
CYOW
HOKKE
15NM
26NM
66NM
9NM
0:05
0:15
0:02
:
:
:
:
DIRECT
TEXEN
3.3°
2600A
0:11/
2000
56NM
DME1
YUL
15.6
5.0
UTC01: 06 GS SAT-29C TAT-13C
VOR1 ADF2
HOKKE
THURO
25
50
280
26000A
DME2
YUL
15.6
ABOVE
BELOW
MULTIFUNCTION DISPLAY
(FMS MAP PAGE)
NAVIGATION SYSTEMS
17-68 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
Automatic Direction Finder (ADF) System
Description
The Automatic Direction Finder (ADF) system is a dual low-frequency radio
navigation system (ADF 1 and ADF 2). The receivers are independently tunable in
0.5-kHz increments, in the frequency ranges of 190.0 to 1799.5 kHz and 2179 to 2185
kHz. The transmitting stations can be non-directional beacons (NDBs) or standard AM
broadcasting stations.
Components and Operation
ADF Receivers
The ADF receivers supply bearing-to-station and audio outputs to the navigation and
audio systems, and digital bus outputs to the Integrated Avionics Processor System
(IAPS) and Electronic Flight Instrument System (EFIS).
ADF 1 is powered by the DC essential bus, and ADF 2 is powered by the DC bus 2.
ADF Antenna
The ADF Antenna contains one sense antenna and two loop antennas mounted 90°
relative to each other.
ADF Tuning
The ADF receiver is normally tuned by the on-side RTU, but may also be tuned by the
cross-side RTU or by the FMS. The audio is controlled by ADF 1 and ADF 2 switches
on the audio control panel. A VOICE/BOTH switch filters out the station
identification or selects both identification and voice.
When the 1/2 switch on the RTU is pushed, each RTU can control the on-side and
cross-side ADF receivers.
ADF Bearing Pointer Selection and Navigation
The BRG pushbuttons on the DCPs allow selection of pilot's side or copilot's side
ADF information in the form of bearing pointers. The magenta single bearing pointer
displays the direct bearing to the ADF 1 station. The cyan double bearing pointer
displays the direct bearing to the ADF 2 station.
Both pointers may be displayed simultaneously on either PFD’s HSI, and on the HSI,
NAV SECTOR, and FMS MAP formats of the MFD.
NAVIGATION SYSTEMS
For Training Purposes Only
May 03
17-69
P I LOT T R A I N I N G GU I D E
ADF bearings cannot be coupled to course tracking or flight guidance systems. If
navigation is being conducted using ADF information, the pilot is responsible to
assign heading or course commands using the airplane’s other navigational systems.
ADF Operation Modes
The ADF system has two selectable modes of operation: ANT and ADF.
• when ANT is selected on the ADF page of the RTU, the NDB station signal may
be received at long range, but no bearing information is available
• when ADF is selected, the reception range for the NDB signal is reduced, but
bearing to the station is available
ADF Failure Indication
An ADF system failure is displayed as follows:
• the ADF frequency display on the RTU top level page is replaced with dashes
• on the pilot’s and copilot’s PFDs and MFDs, the applicable bearing pointer is
removed
• the applicable magenta or cyan bearing source indicator is replaced with a red
boxed bearing source indicator
ADF Self-test
To conduct the self-test, the ADF receiver must be in the ADF mode with a valid NDB
frequency tuned in. The self-test is started by pushing the ADF TEST key on the RTU
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