B767/34/307 ADFS
Boeing 767-200/300
Automatic Direction Finder System Training manual For training purposes only LEVEL 3
ATA 34
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This publication was created by Sabena technics training department, Brussels-Belgium, following ATA 104 specifications. The information in this publication is furnished for informational and training use only, and is subject to change without notice. Sabena technics training assumes no responsibility for any errors or inaccuracies that may appear in this publication. No part of this publication may be reproduced, stored in a retrieval system, or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without the prior written permission of Sabena technics training.
Contact address for course registrations course schedule information Sabena technics training
[email protected]
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LIST OF EFFECTIVE PAGES 1.......................... 04 - 09 - 2012 2.......................... 04 - 09 - 2012 3.......................... 04 - 09 - 2012 4.......................... 04 - 09 - 2012 5.......................... 04 - 09 - 2012 6.......................... 04 - 09 - 2012 7.......................... 04 - 09 - 2012 8.......................... 04 - 09 - 2012 9.......................... 04 - 09 - 2012 10........................ 04 - 09 - 2012 11........................ 04 - 09 - 2012 12........................ 04 - 09 - 2012 13........................ 04 - 09 - 2012 14........................ 04 - 09 - 2012 15........................ 04 - 09 - 2012 16........................ 04 - 09 - 2012 17........................ 04 - 09 - 2012 18........................ 04 - 09 - 2012 19........................ 04 - 09 - 2012 20........................ 04 - 09 - 2012 21........................ 04 - 09 - 2012 22........................ 04 - 09 - 2012
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TABLE OF CONTENTS 1. GENERAL..................................................................................................6 2. COMPONENT LOCATION.........................................................................8 3. COMPONENT DESCRIPTION..................................................................10 3.1. Dual ADF Control Panel........................................................................10 3.2. ADF Receiver.........................................................................................10 3.3. ADF Antennas......................................................................................12 3.4. Audio Selector Panels...........................................................................12 3.5. Radio Distance Magnetic Indicator........................................................14 3.6. EHSI - ADF Display.................................................................................14 4. DETAILED DESCRIPTION........................................................................16 5. SELF-TEST...............................................................................................20 5.1. Automatic Self-Test...............................................................................20 5.2. Manual Self-test...................................................................................20
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LIST OF ILLUSTRATIONS ADF FUNCTIONAL BLOCK DIAGRAM...................................................................................... 19 AUDIO SELECTOR PANEL........................................................................................................ 13 AUTOMATIC DIRECTION FINDER RECEIVER............................................................................. 11 AUTOMATIC DIRECTION FINDER SYSTEM................................................................................. 7 AUTOMATIC DIRECTION FINDER SYSTEM ANTENNA............................................................... 13 AUTOMATIC DIRECTION FINDER SYSTEM - COMPONENT LOCATION........................................ 9 AUTOMATIC DIRECTION FINDER SYSTEM - SELF TEST............................................................. 21 DUAL ADF CONTROL PANEL................................................................................................... 11 RADIO DISTANCE MAGNETIC INDICATOR............................................................................... 15
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ABBREVIATIONS AND ACRONYMS ADF BFO CW DME EFIS EHSI FT ILS LRU NCD NDB QEC RDMI RF RMI
Automatic Direction Finder Beat Frequency Oscillator Continuous Wave Distance Measuring Equipment Electronic Flight Instrument System Electronic Horizontal Situation Indicator Feet Instrument Landing System Line Replaceable Unit No Computed Data Non-Directional Beacon Quadrantal Error Correction Radio Distance Magnetic Indicator Radio Frequency Radio Magnetic Indicator
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1. GENERAL. The automatic direction finder (ADF) system serves as a navigational aid to determine the relative bearing to a selected ground station with respect to the airplane center line, and to provide audio reception to the flight crew. The ADF system is normally used with standard a/m broadcast stations. To operate the system, it must be tuned to a ground station in the 190 to 1750 kHz radio frequency band. A tuning capability and ADF bearing displays are provided in the flight compartment. Received audio is transmitted to the flight interphone system. The dual ADF system consists of two independent ADF receivers, each receiving its input from a dedicated antenna. Both receivers can operate simultaneously and be tuned to different ground stations. Each receiver sends its computed relative bearing to both RDMI’s, and all three EFIS symbol generators. The audio is sent to the flight interphone system : it may be the audio identifier of a non-directional beacon (NDB) station or the program of a commercial broadcast station. Actuation of the BFO (Beat Frequency Oscillator) switch to the ON position will cause a 1020 Hz tone to be injected for CW (Continuous Wave) RF reception. Frequency selection is accomplished from the dual ADF control panel.
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BEARING DATA TO L & R RDMI AND L, R & C EFIS SG’S LEFT ADF ANTENNA
LEFT ADF RECEIVER AUDIO TO FLIGHT INTERPHONE SYSTEM
BEARING DATA TO L & R RDMI AND L, R & C EFIS SG’S DUAL ADF CONTROL PANEL
RIGHT ADF ANTENNA
RIGHT ADF RECEIVER
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2. COMPONENT LOCATION. Left and right ADF circuit breakers are located on the overhead circuit breaker panel (P11) in the flight compartment. The left ADF antenna is located on the top of the aft fuselage, at station 1122. The right ADF antenna is located on the top of the aft fuselage at station 1165. The left and right ADF receivers are located on rack E5-1 in the mid equipment center. The ADF control panel is located on the aft electronics panel (P8) in the flight compartment. The left radio distance magnetic indicator is located on the captain’s instrument panel (P1-1). The right radio distance magnetic indicator is located on the first officer’s instrument panel (P3-1). The SYS No. 1 air/ground relay K124 is located in the left miscellaneous electronic equipment panel (P36). The SYS No. 2 air/ground relay K214 is located in the right miscellaneous electronic equipment panel (P37). The left horizontal situation indicator is located on captains instrument panel (P1-2). The right horizontal situation indicator is located on first officers instrument panel (P3-2).
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CAPTAIN’S INSTRUMENT PANEL (P1) • LEFT RDMI • LEFT EHSI
R ADF ANTENNA STA 1165 L ADF ANTENNA STA 1122
FIRST OFFICER’S INSTRUMENT PANEL (P3) • RIGHT RDMI • RIGHT EHSI AFT ELECTRONICS PANEL (P8) • ADF CONTROL PANEL OVERHEAD CIRCUIT BREAKER PANEL (P11) • LEFT AND RIGHT ADF CIRCUIT BREAKER RIGHT MISC ELEC EQUIP PNL (P37) • SYS N° 2 AIR/GND RELAY K214
MID EQUIPMENT CENTER RACK E5-1 • LEFT AND RIGHT ADF RECEIVERS
LEFT MISC ELEC EQUIP PANEL (P36) • SYS N° 1 AIR/GROUND RELAY K124
AUTOMATIC DIRECTION FINDER SYSTEM - COMPONENT LOCATION EFFECTIVITY ALL
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3. COMPONENT DESCRIPTION. 3.1. Dual ADF Control Panel.
3.2. ADF Receiver.
The purpose of the ADF control panel is to select the frequencies and the BFO tone.
The purpose of the ADF receiver is to receive directional and non-directional rf signals in the 190-1750KHz frequency range from the ADF antenna, to process them, to compute the bearing and to transmit bearing information to the RDMI’s and audio output to the flight interphone system.
- Frequency selector : Two frequency selectors are provided, one for each ADF receiver. Each frequency selector consists of three concentric knobs. The outer knob selects the thousands and hundreds of kHz ; - the center knob the tens of kHz; - and the inner knob the units and - 0.5 of kHz.
- Status indicators : Three LED status indicators are provided on the front panel. A red light CONTROL INPUT FAIL indicates control input fault. A green light LRU STATUS - PASS indicates proper receiver operation, and a red light LRU STATUS - FAIL indicates receiver failure. These indicators illuminate only when the front panel test switch is actuated.
- Selected frequency display : Two five-digit LCD displays are provided to indicate the selected frequencies; one for the frequency selected by the left selector and the other one for the frequency selected by the right selector.
- Self-test switch : The momentary pushbutton switch test is provided to initiate a self-test. - Fault Memory (Optional) :
- BFO tone selector : A switch is provided for each ADF receiver to activate the BFO tone generator.
A fault memory is provided to record faults. Fault recording is done by flight segments. Recorded fault readout is done during bench testing to external test equipment through the ATE connector.
NOTE : The ADF control panel assembly contains electrostatically sensitive parts and must be handled accordingly.
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OBSERVE PRECAUTIONS FOR HANDLING ELECTROSTATIC SENSITIVE DEVICES
SELECTED FREQUENCY (TYP) FREQUENCY SELECTOR (TYP)
STATUS LIGHTS SELF-TEST PUSHBUTTON SWITCH
DUAL ADF CONTROL PANEL FOLD-AWAY HANDLE
HOLD DOWN HOOK
AUTOMATIC DIRECTION FINDER RECEIVER
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3.3. ADF Antennas. The purpose of the ADF antenna is to receive rf signals from a ground station, to amplify them and to transmit them to the ADF receiver. Enclosed in a tear-drop shaped shell, the ADF antenna contains the loop and the sense antennas, and an electronics assembly with amplifiers for each antenna. Loop Antenna. The loop antenna provides the directional signals. It consists of two mutually perpendicular loops (one sine loop and one cosine loop) mounted on a rectangular ferrite core. The sine loop is mounted parallel to the longitudinal axis of the airplane. The cosine loop is perpendicular to it. Sense Antenna. RF input is provided by the non-directional sense antenna. It consists of a printed circuit mounted beneath the top surface of the unit. Transmission Line & Connector. The transmission line is connected to the antenna by means of a 16-pin circular connector. Each of the loop and the sense antennas is connected to the ADF receiver through a shielded 78 ohm 2-wire cable. Power is supplied over three wires. The power wires are a twisted pair. The third wire is a ground wire. All cables and wires form one integral shielded bundle. The length of the interconnecting cables is not critical.
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Precipitation-Static Protection. The top surface of the antenna is covered with conductive antistatic paint for the purpose of providing precipitation-static protection. To enable the precipitation-static charge to drain off, a good bond between the precipitation-static coating and the fuselage skin through the mounting screws is required. Additionally, a conductive gasket is used between the antenna and the fuselage. The bonding resistance measured between the indicated measuring point and the airplane skin should be less than the allowable maximum value of 0.0015 ohm.
3.4. Audio Selector Panels. The audio selector panel permits the flight crew to select an audio system for transmission or reception. The listen switches are used to select the source and control the volume of audio connected to a flight compartment speaker and headset. They are momentary switches which are rotated clockwise for maximum volume. Each press of a listen switch changes the audio status of that system (off or on). When a microphone switch is selected, the corresponding listen circuit is automatically connected. The voice toggle switch selects a filter which attenuates the range audio (Morse identifier) of radio navigation signals (ADF, VOR, DME, or ILS).
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CONDUCTIVE GASKET OBSERVE PRECAUTIONS FOR HANDLING ELECTROSTATIC SENSITIVE DEVICES
CAPTIVE MOUNTING SCREWS (TYP)
TOP VIEW
SENSE ANTENNA TOP SURFACE COVERED WITH PRECIPITATION-STATIC COATING LOOP ANTENNAS ELECTRONICS ASSEMBLY MOUNTING SCREW WITH TAB FOR RESISTANCE MEASUREMENT
FWD
O-RING
ELECTRICAL CONNECTOR
ANTENNA INSTALLATION
AUTOMATIC DIRECTION FINDER SYSTEM ANTENNA
LISTEN SWITCHES (15) FILTER SWITCH
AUDIO SELECTOR PANEL
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3.5. Radio Distance Magnetic Indicator. The RDMI’s display magnetic heading, VOR or ADF bearing, and DME distance. Flags are displayed for non-computed or invalid data. See brochure RMI B767/34/105 for a detailed description of the RMI.
3.6. EHSI - ADF Display. In addition to various other navigational displays, the EHSI’s also display ADF bearing data received from the ADF receivers via the EFIS symbol generators. ADF bearing data from the left and right ADF receivers is displayed on the EHSI’s in all EFIS modes, as well as a test value during ADF test. Left & right ADF failure flags indicate failures of the respective ADF bearing data sources. During a non-computed-data condition, the respective pointer is removed, and no flag is displayed.
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NORMAL DISPLAY
FAIL/NCD DISPLAY
RADIO DISTANCE MAGNETIC INDICATOR
LEFT ADF FLAG
L-ADF BEARING POINTER
RIGHT ADF FLAG
R-ADF BEARING POINTER
R (RECIPR.) L (RECIPROCAL)
NORMAL DISPLAY
FAULT DISPLAY
ELECTRONIC HORIZONTAL SITUATION INDICATOR -ADF DISPLAYS EFFECTIVITY ALL
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4. DETAILED DESCRIPTION. ADF Receiver Power. The dual ADF system receives 115 Vac 400 Hz power from the 115 Vac left bus for the left ADF system, and from the 115 Vac standby bus for the right ADF system, via the left or the right ADF circuit breaker, respectively. Each one of the systems (left & right) becomes operational when the respective circuit breaker is closed. Both systems can be operated simultaneously.
Frequency Selection and Display. Two sets of frequency selectors are provided for frequency selection; one for the left system and the other for the right system.
In the ADF receiver, the 115 Vac input is used to power the internal power supply which generates the required dc voltages. The ADF receiver power supply also provides power for the onside ADF antenna.
Mode and BFO Selection. The ADF mode selector is hard wired internally in the control panel. No antenna (ANT) mode selection is provided.
Dual ADF Control Panel Power. In the dual ADF control panel, the received 115 Vac is used to power the internal left and/or right power supplies which in turn generate the required dc voltages. A 115 Vac connection from each 115 Vac power input branches off into the respective ADF receiver. ADF Antenna Power. Antenna +12 Vdc and -12 Vdc power is received from the ADF receiver power supply. During self-test, antenna power is switched off in the receiver by switch S1, to prevent antenna output signals from interfering with test signals generated in the receiver. Dual ADF Control Panel Function. The control panel has two identical sets of electronics, one for the left system, and the other for the right system. The left set of electronics is powered by the left power supply; the right set of electronics is powered by the right power supply.
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Each one of the frequency selector knobs activates an encoder which transmits the selected frequency to the microprocessor, and to the display drivers for display.
For BFO tone selection, a ground-level discrete is routed to the respective (left or right) microprocessor. Control Data. The microprocessor processes the received frequency and BFO tone information and transmits it, via the ARINC 429 transmitter, to the respective ADF receiver. Antenna Functions. The received radio signal is received by the three elements of the ADF antenna: the sense antenna and the two loop antennas. The electric (E) field component of the rf signal is received by the sense antenna. The magnetic (H) field component is received by the two loop antennas. The signal received by the longitudinal loop antenna is proportional to the sine of the signal bearing relative the airplane heading. The one received by the lateral loop antenna is proportional to the cosine. Each of the antenna signals is pre-amplified and then transmitted to the ADF receiver through the coupling circuits.
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Antenna Identification. Top antenna installation is recognized by jumpering designated pins in the receiver mating connector. This information is transmitted to the microprocessor . Generation of Composite RF Signals. The received sine and cosine signals are each amplitude modulated by a 96 Hz modulation signal generated in the modulation frequency generator. The modulation signal that is applied to the cosine signal modulator is shifted 90 ° with respect to the other modulation signal. The modulation frequency generator is enabled through OR gate 2 during normal operation (always ADF mode in this configuration) and in test. The two modulator outputs are first summed in summing point SP1 to produce a composite signal. Subsequently, this composite signal is summed in summing point SP2 with the nondirectional sense rf signal, to remove 180 ° ambiguity. The resultant composite rf signal contains the desired bearing information. Composite RF Signal Processing. The composite rf signal is now applied to the receive circuits (RF/IF/DETECTOR). RF band selection is provided by the microprocessor. Local oscillator frequencies are supplied by the frequency synthesizer. In the receive circuits, the audio modulation is extracted. The audio output is either an audio signal or the keyed 1020 Hz identifier. Bearing information is contained in the 96 Hz bearing signal. Its phase angle contains this information.
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Bearing Signal Processing. The 96 Hz bearing output from the detector is phase-compared with the 96 Hz reference signal from the modulation frequency generator. The phase relation between these two signals contains the desired bearing information. This data is transmitted in digital format to the microprocessor where the bearing is computed. Quadrantal error correction (QEC) is included to compensate for airplaneinduced rf field distortions. The QEC is made by jumpering designated pins in the receiver mating connector. The computed bearing is now sent in digital format to the ARINC 429 transmitter. Bearing Output. The computed bearing is transmitted to the left and the right RDMI’s over an ARINC 429 data bus. Audio from Ground Station. Audio output from the ADF receiver is routed to the captain’s, the first officer’s and the first observer’s audio selector panels. In normal operation, the audio emanates from the detector circuit and consists either of the 1020 Hz keyed identifier from a non-directional continuous-wave homing beacon station, or of transmissions from a commercial am broadcast station.
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1020 Hz BFO Tone. When the TONE OFF/ON switch on the ADF control panel is in the ON position, a 1020 Hz BFO tone is injected into the audio output circuit through switch S2. This tone is generated by the frequency synthesizer. Switch S2 is controlled by the AND gate. The output of the AND gate is a logic 1 when the BFO ON signal from the microprocessor is 1, and when a signal is received from a ground station (TUNER LOCK = 1). The BFO function mainly is used overseas, to produce a keyed audio output from a morse-coded carrier frequency received from a ground station.
B767/34/307 ADFS
Fault Recording. Detected faults on at least 49 flights can be stored in the fault memory by flight segments. Flight segments are separated by air/ground relay inputs. During bench tests only, the fault memory can be accessed on the ground through the ATE connector on the rear interconnect panel. Front Panel Status Indicator Functions. Status indicators on the ADF receiver front panel indicate ADF receiver and control panel data status during manually initiated self-test only.
BITE Function. The purpose of the BITE circuit is to monitor the operation of ADF receiver circuits, to initiate the test function, to transmit fault information to the fault memory for storage, and to control the status indicators on the ADF receiver’s front panel. Circuits Monitored. The operation of the receive circuits, the frequency synthesizer, the modulation frequency generator, the microprocessor and the power supply as well as the control input and the output words are continuously monitored, and faults are stored in the fault memory.
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ADF FUNCTIONAL BLOCK DIAGRAM
B767/34/307 ADFS
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5. SELF-TEST. 5.1. Automatic Self-Test. An automatic self-test is initiated at power on. No special test indications are associated with the automatic self-test at power on, if no failures are detected. If a fault is detected, the fault is indicated by the bearing fault flag.
5.2. Manual Self-test. Manual self-test is initiated by pushing the TEST switch on the front panel of the ADF receiver to be tested. During self-test, the antenna signals are inhibited by antenna power cut-off through S1. For a complete test, the test switch must be held in the test position for the duration of the test. The test function times out after 16 seconds if the receiver’s test switch is held that long.
To have ADF indications on the RDMI’s, the respective left or right VOR/ADF select switch must be in the ADF position. At self-test initiation, the respective left or right bearing fault flag appears for six seconds. The flag will remain if there is a system fault. Six seconds after the self-test has been initiated, the respective bearing pointer is driven to 135 ° with respect to the lubber line for a duration of up to 10 seconds. Select full VOR or ILS on the EFIS control panel to control EHSI indications. This provides the most easily read display of the ADF test. Also at self-test initiation, the respective left or right ADF fail flag will appear for 3 seconds. Six seconds after the self-test has been initiated, the respective green pointer will indicate 135. A steady 1020 Hz tone is transmitted from the beginning of the manual self-test for a duration of 16 seconds.
At self-test initiation, the ARINC 429 bearing word changes. The data field for bearing changes to a value of 135°. The sign status matrix flags failure warning for three seconds, NCD for three seconds, then FT (functional test) for the duration of the test. All three panel status indicators are illuminated for three seconds. All status indicators then extinguish for a three-second interval. Subsequently, the green LED labeled LRU STATUS PASS illuminates for proper receiver operation. In the event of a fault, the respective red LED, labeled CONTROL INPUT FAIL or LRU STATUS FAIL illuminates.
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YELLOW
ALL THREE STATUS INDICATORS ILLUMINATE
RED
GREEN “LRU STATUS - PASS” LED IS ON FOR RCVR OK. RED “LRU STAUS - FAIL” LED IS ON FOR ADF RCVR FAULT. RED “CONTROL INPUT FAIL
GREEN
STATUS INDICATORS
RED SELF-TEST PUSHBUTTON SWITCH (PRESS AND HOLD)
ADF RECEIVER STATUS INDICATORS ADF RECEIVER 1020 Hz TONE ON
1020 Hz BFO TONE ADF (EHSI) FAIL DISPLAY - LEFT/RIGHT ADF TEST (3 SECONDS)
FAIL FLAG IN VIEW (EHSI)
RIGHT BEARING FAILURE FLAG BEARING FLAG IN VIEW (RDMI)
BEARING FLAG STAYS IN VIEW IF THERE IS A FAULT
LEFT BEARING FAILURE FLAG
TEST SEQUENCE ANNUNCIATIONS
ADF (EHSI) 135° BEARING INDICATION - LEFT/RIGHT ADF TEST (10 SECONDS)
135° BEARING INDICATED (EHSI AND RDMI)
LEFT & RIGHT ADF POINTERS AT 135° ADF SELECTED RDMI DISPLAY
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135° BEARING INDICATION
ADF SYSTEM - SELF TEST
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