DOC AIRBUS | AMM A320FVOR/MARKER - DESCRIPTION AND OPERATION
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** ON A/C NOT FOR ALL
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** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL
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1. General
A. Foreword
The VOR/MARKER comprises two independent systems in a same receiver:
The VOR/MARKER comprises two independent systems in a same receiver:
- a VOR system for the radio navigation phase,
- a MARKER (MKR) system for the landing approach phase.
B. VOR System
The VOR system is a radio aid to medium-range navigation.
The aircraft is equipped with two VOR systems which can accept ground station signals in the frequency range of 108 MHz to 117.95 MHz.
These signals are processed and conditioned to provide the crew with:
The VOR system is a radio aid to medium-range navigation.
The aircraft is equipped with two VOR systems which can accept ground station signals in the frequency range of 108 MHz to 117.95 MHz.
These signals are processed and conditioned to provide the crew with:
- identification of a selected ground station,
- indication of the aircraft position with respect to the station (bearing information),
- indication of the aircraft angular deviation from a selected course.
C. MARKER System
The marker system is a radio navigation aid. It is normally used together with the Instrument Landing System (ILS) portion of the Multi-Mode Receiver (MMR) during an ILS approach. The system determines the distance between the aircraft and the runway threshold. The marker system also marks particular airway and holding points.
The system provides visual and aural indications of the passage of the aircraft over the marker transmitters located on the ground.
The marker system is a radio navigation aid. It is normally used together with the Instrument Landing System (ILS) portion of the Multi-Mode Receiver (MMR) during an ILS approach. The system determines the distance between the aircraft and the runway threshold. The marker system also marks particular airway and holding points.
The system provides visual and aural indications of the passage of the aircraft over the marker transmitters located on the ground.
2. Component Location
VOR/Marker - Component Location ** ON A/C NOT FOR ALL
VOR/Marker - Component Location ** ON A/C NOT FOR ALL
VOR/Marker - Component Location ** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL VOR/Marker - Component Location ** ON A/C NOT FOR ALL VOR/Marker - Component Location ** ON A/C NOT FOR ALL VOR/Marker - Component Location ** ON A/C NOT FOR ALL | FIN | FUNCTIONAL DESIGNATION | PANEL | ZONE | ACCESS DOOR | ATA REF |
|---|---|---|---|---|---|
| ** ON A/C ALL | |||||
| 1RS | ANTENNA-MARKER | 130 | 34-55-18 | ||
| 3RS1 | RECEIVER-VOR/MKR, 1 | 81VU | 127 | 34-55-31 | |
| 3RS2 | RECEIVER-VOR/MKR, 2 | 82VU | 128 | 34-55-31 | |
| ** ON A/C NOT FOR ALL | |||||
| 4RS | ANTENNA-VOR 1/2 | 324AT | 324 | 34-55-11 | |
| ** ON A/C NOT FOR ALL | |||||
| 4RS | ANTENNA-VOR 1/2 | 324 | 34-55-11 | ||
3. System Description
A. Principle
(1) VOR system
The principle of the VOR navigation is a comparison between a reference phase signal and a variable phase signal. The ground station generates these two signals. The phase difference between the reference and the variable phase is a function of the position of the aircraft with respect to the ground station.
Furthermore, the ground station provides a Morse identification.
The principle of the VOR navigation is a comparison between a reference phase signal and a variable phase signal. The ground station generates these two signals. The phase difference between the reference and the variable phase is a function of the position of the aircraft with respect to the ground station.
Furthermore, the ground station provides a Morse identification.
(2) Marker system
There are three marker transmitters positioned on the ground at known distances from the runway threshold :
When the aircraft passes through the beam of a marker, the modulating frequency is detected. Then, the system provides aural and visual indications to the flight crew.
There are three marker transmitters positioned on the ground at known distances from the runway threshold :
- the outer marker at approx. 4 N miles
- the middle marker at 0.6 N miles
- the inner marker at the runway threshold.
When the aircraft passes through the beam of a marker, the modulating frequency is detected. Then, the system provides aural and visual indications to the flight crew.
B. System Architecture
(1) VOR system
The VOR system comprises two independent systems. Each system consists of :
VOR/Marker - Control and Indicating ** ON A/C NOT FOR ALL
VOR/Marker - Control and Indicating ** ON A/C NOT FOR ALL
VOR/Marker - Control and Indicating ** ON A/C NOT FOR ALL
The VOR system comprises two independent systems. Each system consists of :
- one VOR/MKR receiver 1(2) 3RS1 (3RS2)
- one VOR 1/2 antenna 4RS
- one VOR/ADF/DME Radio Magnetic Indicator (VOR/ADF/DME RMI) 21FN.
VOR/Marker - Control and Indicating ** ON A/C NOT FOR ALL VOR/Marker - Control and Indicating ** ON A/C NOT FOR ALL VOR/Marker - Control and Indicating ** ON A/C NOT FOR ALL - the CAPT (F/O) Audio Control Panel (ACP) 2RN1 (2RN2) and the Audio Management Unit (AMU) 1RN for audio control
- the Multipurpose Control and Display Unit 1(2) (MCDU) 3CA1 (3CA2), the Radio Management Panel 1(2) (RMP) 1RG1 (1RG2) and the Flight Management and Guidance Computer 1(2) (FMGC) 1CA1 (1CA2) for frequency/course selection
- the MCDU 1(2) and the Centralized Fault-Display Interface-Unit (CFDIU) 1TW for test purposes.
(2) Marker system
The marker system consists of one system only. The receiver is part of the VOR/MKR receiver 1.
The system comprises :
The marker system consists of one system only. The receiver is part of the VOR/MKR receiver 1.
The system comprises :
- one VOR/MKR receiver 1 3RS1
- one marker antenna 1RS.
(3) VOR system
The VOR system comprises two independent systems. Each system consists of :
VOR/Marker - Control and Indicating ** ON A/C NOT FOR ALL
VOR/Marker - Control and Indicating ** ON A/C NOT FOR ALL
VOR/Marker - Control and Indicating ** ON A/C NOT FOR ALL
The VOR system comprises two independent systems. Each system consists of :
- one VOR/MKR receiver 1(2) 3RS1 (3RS2)
- one VOR 1/2 antenna 4RS
VOR/Marker - Control and Indicating ** ON A/C NOT FOR ALL VOR/Marker - Control and Indicating ** ON A/C NOT FOR ALL VOR/Marker - Control and Indicating ** ON A/C NOT FOR ALL - the CAPT (F/O) Audio Control Panel (ACP) 2RN1 (2RN2) and the Audio Management Unit (AMU) 1RN for audio control
- the Multipurpose Control and Display Unit 1(2) (MCDU) 3CA1 (3CA2), the Radio Management Panel 1(2) (RMP) 1RG1 (1RG2) and the Flight Management and Guidance Computer 1(2) (FMGC) 1CA1 (1CA2) for frequency/course selection
- the MCDU 1(2) and the Centralized Fault-Display Interface-Unit (CFDIU) 1TW for test purposes.
(4) Marker system
The marker system consists of one system only. The receiver is part of the VOR/MKR receiver 1.
The system comprises :
The marker system consists of one system only. The receiver is part of the VOR/MKR receiver 1.
The system comprises :
- one VOR/MKR receiver 1 3RS1
- one marker antenna 1RS.
C. Utilization Technical Data
(a) VOR system
1 On the Navigation Display (ND)
In ROSE and ARC modes.
If you set the ADF/VOR/OFF switch on the EFIS control section of the Flight Control Unit (FCU) to VOR, this causes : display of the characteristics of the VOR 1 and/or VOR 2 stations in the L and/or R lower corner of the ND (item 7) :
If the VOR approach is selected, the VOR APP message comes into view in the center top section of the ND (item 3).
In ROSE NAV and ARC modes, the characteristics and location of the VOR stations which are not already included in the flight plan, can be shown when you push the VOR-D pushbutton switch on the EFIS control section of the FCU:
In ROSE and ARC modes.
If you set the ADF/VOR/OFF switch on the EFIS control section of the Flight Control Unit (FCU) to VOR, this causes : display of the characteristics of the VOR 1 and/or VOR 2 stations in the L and/or R lower corner of the ND (item 7) :
- type of station (VOR 1, VOR 2)
- shape of the associated bearing display
- station identification
- mode of tuning :
nothing : automatically tuned by the FMGC
M : manually tuned through the MCDU
R : tuned through the RMP.
A single pointer on the heading dial shows the bearing of the VOR 1 (item 5), a double pointer that of the VOR 2 (item 1).
All these data are shown in white.
In case of VOR system fault, all the corresponding data go out of view and the VOR indication turns to red.
In ROSE VOR mode, the data below are shown: - a dagger-shaped pointer points to the selected VOR course (cyan) (item 6)
- the lateral deviation bar which represents the VOR deviation is shown with an arrow for the TO FROM indication (cyan) (item 2)
- in the R top corner, the VOR characteristics come into view:
VOR 1 or 2, frequency, selected course (item 4), identification (cyan).
If the VOR approach is selected, the VOR APP message comes into view in the center top section of the ND (item 3).
In ROSE NAV and ARC modes, the characteristics and location of the VOR stations which are not already included in the flight plan, can be shown when you push the VOR-D pushbutton switch on the EFIS control section of the FCU:
- cross symbol for the VOR station (item 8)
- circle plus cross symbol for the VOR/DME station (item 9).
2 On the VOR/ADF/DME RMI
Set the VOR/ADF selector switches to ADF.
The RMI indicates the VOR bearings :
In case of No Computed Data (NCD), no failure flag appears but the corresponding pointer remains in the 3 o'clock position.
Set the VOR/ADF selector switches to ADF.
The RMI indicates the VOR bearings :
- a single pointer indicates the VOR 1 bearing (item 11)
- a double pointer indicates the VOR 2 bearing.
In case of No Computed Data (NCD), no failure flag appears but the corresponding pointer remains in the 3 o'clock position.
(b) Marker system
The MKR data are shown on the PFD, in approach at the intersection of the G/S and LOC scales (item 14).
When the aircraft overflies the corresponding marker, the data given after come into view on the PFD :
The MKR data are shown on the PFD, in approach at the intersection of the G/S and LOC scales (item 14).
When the aircraft overflies the corresponding marker, the data given after come into view on the PFD :
- OM for the outer marker (blue)
- MM for the middle marker (amber)
- AWY or IM for the inner marker (white).
(2) Audio control
(a) VOR system
1 The VOR/MKR receivers apply their VOR audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loud speakers. The AMU controls the audio level through the ACP. On the ACP, the pilot must push the VOR 1 (2) pushbutton switch and adjust the related potentiometer to the correct audio level.
2 In case of ATIS message transmission by the VOR station :
- it is necessary to push the ON VOICE pushbutton switch on one ACP in order to hear clearly this information without Morse signal.
(b) Marker system
The VOR/MKR receiver 1 applies its marker audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loud speakers. The AMU controls the audio level through the ACP. On the ACP, the pilot must push the MKR pushbutton switch and adjust the related potentiometer to the correct audio level.
The VOR/MKR receiver 1 applies its marker audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loud speakers. The AMU controls the audio level through the ACP. On the ACP, the pilot must push the MKR pushbutton switch and adjust the related potentiometer to the correct audio level.
(a) VOR system
1 On the Navigation Display (ND)
In ROSE and ARC modes.
If you set the ADF/VOR/OFF switch on the EFIS control section of the Flight Control Unit (FCU) to VOR, this causes : display of the characteristics of the VOR 1 and/or VOR 2 stations in the L and/or R lower corner of the ND (item 7) :
If the VOR approach is selected, the VOR APP message comes into view in the center top section of the ND (item 3).
In ROSE NAV and ARC modes, the characteristics and location of the VOR stations which are not already included in the flight plan, can be shown when you push the VOR-D pushbutton switch on the EFIS control section of the FCU :
In ROSE and ARC modes.
If you set the ADF/VOR/OFF switch on the EFIS control section of the Flight Control Unit (FCU) to VOR, this causes : display of the characteristics of the VOR 1 and/or VOR 2 stations in the L and/or R lower corner of the ND (item 7) :
- type of station (VOR 1, VOR 2)
- shape of the associated bearing display
- station identification
- mode of tuning :
nothing : automatically tuned by the FMGC
M : manually tuned through the MCDU
R : tuned through the RMP.
A single pointer on the heading dial shows the bearing of the VOR 1 (item 5), a double pointer that of the VOR 2 (item 1).
All these data are shown in white.
In case of VOR system fault, all the corresponding data go out of view and the VOR indication turns to red.
In ROSE VOR mode, the data below are shown : - a dagger-shaped pointer points to the selected VOR course (cyan) (item 6)
- the lateral deviation bar which represents the VOR deviation is shown with an arrow for the TO FROM indication (cyan) (item 2)
- in the R top corner, the VOR characteristics come into view:
VOR 1 or 2, frequency, selected course (item 4), identification (cyan).
If the VOR approach is selected, the VOR APP message comes into view in the center top section of the ND (item 3).
In ROSE NAV and ARC modes, the characteristics and location of the VOR stations which are not already included in the flight plan, can be shown when you push the VOR-D pushbutton switch on the EFIS control section of the FCU :
- cross symbol for the VOR station (item 8)
- circle plus cross symbol for the VOR/DME station (item 9).
(b) Marker system
The MKR data are shown on the PFD, in approach at the intersection of the G/S and LOC scales (item 10).
When the aircraft overflies the corresponding marker, the data given after come into view on the PFD :
The MKR data are shown on the PFD, in approach at the intersection of the G/S and LOC scales (item 10).
When the aircraft overflies the corresponding marker, the data given after come into view on the PFD :
- OM for the outer marker (blue)
- MM for the middle marker (amber)
- AWY or IM for the inner marker (white).
(4) Audio control
(a) VOR system
1 The VOR/MKR receivers apply their VOR audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loud speakers. The AMU controls the audio level through the ACP. On the ACP, the pilot must push the VOR 1 (2) pushbutton switch and adjust the related potentiometer to the correct audio level.
2 In case of ATIS message transmission by the VOR station :
- it is necessary to push the ON VOICE pushbutton switch on one ACP in order to hear clearly this information without Morse signal.
(b) Marker system
The VOR/MKR receiver 1 applies its marker audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loud speakers. The AMU controls the audio level through the ACP. On the ACP, the pilot must push the MKR pushbutton switch and adjust the related potentiometer to the correct audio level.
The VOR/MKR receiver 1 applies its marker audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loud speakers. The AMU controls the audio level through the ACP. On the ACP, the pilot must push the MKR pushbutton switch and adjust the related potentiometer to the correct audio level.
(a) VOR system
1 On the Navigation Display (ND)
In ROSE and ARC modes.
If you set the ADF/VOR/OFF switch on the EFIS control section of the Flight Control Unit (FCU) to VOR, this causes : display of the characteristics of the VOR 1 and/or VOR 2 stations in the L and/or R lower corner of the ND (item 7) :
If the VOR approach is selected, the VOR APP message comes into view in the center top section of the ND (item 3).
In ROSE NAV and ARC modes, the characteristics and location of the VOR stations which are not already included in the flight plan, can be shown when you push the VOR-D pushbutton switch on the EFIS control section of the FCU:
In ROSE and ARC modes.
If you set the ADF/VOR/OFF switch on the EFIS control section of the Flight Control Unit (FCU) to VOR, this causes : display of the characteristics of the VOR 1 and/or VOR 2 stations in the L and/or R lower corner of the ND (item 7) :
- type of station (VOR 1, VOR 2)
- shape of the associated bearing display
- station identification
- mode of tuning :
nothing : automatically tuned by the FMGC
M : manually tuned through the MCDU
R : tuned through the RMP.
A single pointer on the heading dial shows the bearing of the VOR 1 (item 5), a double pointer that of the VOR 2 (item 1).
All these data are shown in white.
In case of VOR system fault, all the corresponding data go out of view and the VOR indication turns to red.
In ROSE VOR mode, the data below are shown: - a dagger-shaped pointer points to the selected VOR course (cyan) (item 6)
- the lateral deviation bar which represents the VOR deviation is shown with an arrow for the TO FROM indication (cyan) (item 2)
- in the R top corner, the VOR characteristics come into view:
VOR 1 or 2, frequency, selected course (item 4), identification (cyan).
If the VOR approach is selected, the VOR APP message comes into view in the center top section of the ND (item 3).
In ROSE NAV and ARC modes, the characteristics and location of the VOR stations which are not already included in the flight plan, can be shown when you push the VOR-D pushbutton switch on the EFIS control section of the FCU:
- cross symbol for the VOR station (item 8)
- circle plus cross symbol for the VOR/DME station (item 9).
2 On the VOR/ADF/DME RMI
Set the VOR/ADF selector switches to ADF.
The RMI indicates the VOR bearings :
If No Computed Data (NCD), the warning flag comes into view and the related pointer stays at the position corresponding to the last correct data.
Set the VOR/ADF selector switches to ADF.
The RMI indicates the VOR bearings :
- a single pointer indicates the VOR 1 bearing (item 11)
- a double pointer indicates the VOR 2 bearing.
If No Computed Data (NCD), the warning flag comes into view and the related pointer stays at the position corresponding to the last correct data.
(b) Marker system
The MKR data are shown on the PFD, in approach at the intersection of the G/S and LOC scales (item 14).
When the aircraft overflies the corresponding marker, the data given after come into view on the PFD :
The MKR data are shown on the PFD, in approach at the intersection of the G/S and LOC scales (item 14).
When the aircraft overflies the corresponding marker, the data given after come into view on the PFD :
- OM for the outer marker (blue)
- MM for the middle marker (amber)
- AWY or IM for the inner marker (white).
(6) Audio control
(a) VOR system
1 The VOR/MKR receivers apply their VOR audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loud speakers. The AMU controls the audio level through the ACP. On the ACP, the pilot must push the VOR 1 (2) pushbutton switch and adjust the related potentiometer to the correct audio level.
2 In case of ATIS message transmission by the VOR station :
- it is necessary to push the ON VOICE pushbutton switch on one ACP in order to hear clearly this information without Morse signal.
(b) Marker system
The VOR/MKR receiver 1 applies its marker audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loud speakers. The AMU controls the audio level through the ACP. On the ACP, the pilot must push the MKR pushbutton switch and adjust the related potentiometer to the correct audio level.
The VOR/MKR receiver 1 applies its marker audio output to the audio integrating system. This system controls and directs the output to the headsets and/or the loud speakers. The AMU controls the audio level through the ACP. On the ACP, the pilot must push the MKR pushbutton switch and adjust the related potentiometer to the correct audio level.
D. Warning
VOR/Marker - Data and Warning Displays ** ON A/C NOT FOR ALL
VOR/Marker - Data and Warning Displays ** ON A/C NOT FOR ALL
The warning related to the VOR is the local warning shown on the VOR/ADF/DME RMI.
In case of VOR fault, a flag comes into view on the VOR/ADF/DME RMI.
VOR/Marker - Data and Warning Displays ** ON A/C NOT FOR ALL VOR/Marker - Data and Warning Displays ** ON A/C NOT FOR ALL In case of VOR fault, a flag comes into view on the VOR/ADF/DME RMI.
4. Power Supply
Energization of each system is through 115VAC 400Hz buses :
Energization of each system is through 115VAC 400Hz buses :
** ON A/C NOT FOR ALL Energization of each system is through 115VAC 400Hz buses :
- 115VAC ESS BUS 401XP via circuit breaker 2RS1 for system 1
- 115VAC BUS 2 204XP via circuit breaker 2RS2 for system 2.
Energization of each system is through 115VAC 400Hz buses :
- 115VAC ESS BUS 401XP via circuit breaker 2RS1 for system 1
- 115VAC BUS 2 204XP via circuit breaker 2RS2 for system 2.
5. Component Description
A. VOR/MKR Receiver FIN: 3-RS-1 FIN: 3-RS-2
(1) External description
The face of the receiver is fitted with a handle, two lugs, a TEST pushbutton switch and test LEDs.
The name, color and function of the LEDs are as follows:
Contact grouping is as follows:
The face of the receiver is fitted with a handle, two lugs, a TEST pushbutton switch and test LEDs.
The name, color and function of the LEDs are as follows:
- CONTROL FAIL (red) indicates that the control input data are faulty
- LRU STATUS (green) indicates that no faults are detected during the self-test sequence
- LRU STATUS (red) indicates that a fault is detected during the self-test sequence.
Contact grouping is as follows:
- Top plug (TP): connection with the automatic test circuit
- Middle plug (MP): connection with the peripheral circuits
- Bottom plug (BP): connection with the power supply circuit and the antennas.
(2) Description
The back of the VOR/MKR receiver contains an ARINC 600, shell size connector to provide electrical connections to the aircraft wiring via mount.
Contact grouping is as follows:
The back of the VOR/MKR receiver contains an ARINC 600, shell size connector to provide electrical connections to the aircraft wiring via mount.
Contact grouping is as follows:
- Top Plug (TP): connection with the automatic test circuit
- Middle Plug (MP): connection with the peripheral circuits
- Bottom Plug (BP): connection with the power supply circuit and the antennas.
The face of the receiver is fitted with a handle, two attaching parts, a TEST pushbutton switch and three LEDs.
The names, colors and functions of the three LEDs are as follows:
(a) VOR STATUS:
- amber: indicates that the test is in progress
- green: indicates that no faults are detected during the self-test sequence.
- red: indicates that a fault is detected during the self-test sequence.
(b) CONTROL FAULT:
- amber: indicates that the test is in progress
- red: indicates invalid frequency input tuning words or no transmission
- off: indicates that no faults are detected during the self-test sequence.
(c) ANTENNA FAULT:
- amber: indicates that the test is in progress
- red: indicates a failure of the antenna (discontinuity)
- off: indicates that no faults are detected during the self-test sequence.
(3) Internal description
VOR/MKR Receiver - General Architecture ** ON A/C NOT FOR ALL
VOR/MKR Receiver - General Architecture ** ON A/C NOT FOR ALL
The microprocessor-based receiver processes and conditions signals within the frequency range of 108 MHz to 117.95 MHz, to produce digital bearing and identification word outputs and an audio output.
The receiver comprises:
VOR/MKR Receiver - General Architecture ** ON A/C NOT FOR ALL VOR/MKR Receiver - General Architecture ** ON A/C NOT FOR ALL The receiver comprises:
(a) A VOR RF receiver module which converts, conditions, filters and amplifies the received VOR signal.
(b) A marker beacon receiver module which converts, conditions, filters and amplifies the received marker beacon signal.
(c) A digital instrumentation module which processes VOR and marker beacon detector signals into ARINC-711 NAV receiver outputs.
This module contains a signal processor and system processor. The signal processor is used in computing VOR bearing information. The system processor is used in interfacing with the aircraft and also communicates with the maintenance processor.
This module contains a signal processor and system processor. The signal processor is used in computing VOR bearing information. The system processor is used in interfacing with the aircraft and also communicates with the maintenance processor.
(d) A maintenance processor module which monitors the health of the VOR and marker beacon receivers, power supply and signal and system processor faults.
(e) A power supply module which converts aircraft 115VAC, 400 Hz power to supplies used by the internal circuits.
(4) Operation
(a) VOR operation
The antenna applies the composite signal transmitted by the ground station to a Radio Frequency (RF) receiver. In the receiver, the signal passes through a low-pass filter, a bandpass filter (preselector) and a RF switch to a RF amplifier. The output of the amplifier passes through one of two bandpass filters, depending on the RF frequency of the station being received, to the first mixer. The mixer combines the RF signal with a Local Oscillator (LO) to produce a first Intermediate Frequency (IF) of 20.05 MHz. The first LO inputs a frequency 20.05 MHz below the desired RF frequency. The mixer output is filtered by a crystal filter and passed through a two-stage IF amplifier. Following the IF amplifier, the signal is mixed with a 20.505 MHz second LO to produce a second IF of 455 kHz. The second IF signal is demodulated using a precision Amplitude Modulation (AM) peak detector. The VOR detector signal is processed by the signal processor on the instrumentation module. The filtered VOR detector signal is output to the rear interconnect module where it is amplified and output to the aircraft.
The antenna applies the composite signal transmitted by the ground station to a Radio Frequency (RF) receiver. In the receiver, the signal passes through a low-pass filter, a bandpass filter (preselector) and a RF switch to a RF amplifier. The output of the amplifier passes through one of two bandpass filters, depending on the RF frequency of the station being received, to the first mixer. The mixer combines the RF signal with a Local Oscillator (LO) to produce a first Intermediate Frequency (IF) of 20.05 MHz. The first LO inputs a frequency 20.05 MHz below the desired RF frequency. The mixer output is filtered by a crystal filter and passed through a two-stage IF amplifier. Following the IF amplifier, the signal is mixed with a 20.505 MHz second LO to produce a second IF of 455 kHz. The second IF signal is demodulated using a precision Amplitude Modulation (AM) peak detector. The VOR detector signal is processed by the signal processor on the instrumentation module. The filtered VOR detector signal is output to the rear interconnect module where it is amplified and output to the aircraft.
(b) MARKER operation
The RF signal is filtered through a low-pass and a 75 MHz bandpass filter. Following the bandpass filter, the signal passes through a RF switch. This switch selects the incoming signal or the functional test signal. After the switch, a RF amplifier provides 12 dB of gain. Following the RF amplifier, the signal is further filtered by another 75 MHz bandpass filter. The output of the second filter goes to a mixer, where it is mixed with a 85.700 MHz LO signal to produce an IF of 10.7 MHz. This IF signal is filtered, amplified and demodulated. The detector output is applied to three tone filters. The filter outputs are rectified and checked against a reference level by a comparator. Each comparator output is sent to the instrumentation module.
The marker-beacon receiver module also contains the functional-test generator circuits. These circuits generate the 75 MHz test signal for the marker beacon receiver and VOR test signal for the VOR receiver.
The RF signal is filtered through a low-pass and a 75 MHz bandpass filter. Following the bandpass filter, the signal passes through a RF switch. This switch selects the incoming signal or the functional test signal. After the switch, a RF amplifier provides 12 dB of gain. Following the RF amplifier, the signal is further filtered by another 75 MHz bandpass filter. The output of the second filter goes to a mixer, where it is mixed with a 85.700 MHz LO signal to produce an IF of 10.7 MHz. This IF signal is filtered, amplified and demodulated. The detector output is applied to three tone filters. The filter outputs are rectified and checked against a reference level by a comparator. Each comparator output is sent to the instrumentation module.
The marker-beacon receiver module also contains the functional-test generator circuits. These circuits generate the 75 MHz test signal for the marker beacon receiver and VOR test signal for the VOR receiver.
(c) Instrumentation
The instrumentation module contains two processors. The signal processor, takes the VOR detector signal and separates the two 30 Hz signals (variable and reference). From these two signals, the signal processor computes the station bearing. The second processor on the module, the system processor, is used to communicate the bearing information to the aircraft. The system processor handles the signal interface with the aircraft.
The instrumentation module contains two processors. The signal processor, takes the VOR detector signal and separates the two 30 Hz signals (variable and reference). From these two signals, the signal processor computes the station bearing. The second processor on the module, the system processor, is used to communicate the bearing information to the aircraft. The system processor handles the signal interface with the aircraft.
(d) LRU monitoring
The maintenance processor, monitors the health of the VOR and marker beacon receivers. The maintenance processor provides all the BITE functions for the LRU. BITE information is transferred to the system processor for communications to the aircraft. Maintenance functions include:
The maintenance processor, monitors the health of the VOR and marker beacon receivers. The maintenance processor provides all the BITE functions for the LRU. BITE information is transferred to the system processor for communications to the aircraft. Maintenance functions include:
1 Receive data from the ARINC maintenance bus and store the time, data, aircraft IDENT, aircraft configuration and process the maintenance control word.
2 Process data received from the system processor for storage in the non-volatile fault memory.
3 Monitor discrete inputs.
4 Determine the validity of the maintenance input-control word.
5 Format the fault summary word and transfer it to the system processor.
6 Transfer all Onboard Maintenance Terminal (OMS) interactive mode data and normal-mode data words to the system processor.
7 Provide maintenance menus in the aircraft.
8 Provide extended interactive-mode support for troubleshooting when the LRU is in the maintenance mode.
(a) VOR operation
The VOR receiver is a single-conversion superheterodyne design. The receiver frequency and gain are controlled by the DSP section of the main processor board. The VOR antenna receives signals transmitted by the VOR ground station in the 108.00 MHz to 117.95 MHz frequency range. The received VOR signal is modulated with audio tones, which provide a digital bearing word output in accordance with ARINC specification format. The signal from the antenna is applied to the preselector, which is tuned to the selected VOR channel by a tuning voltage provided by the digital signal processor (DSP).
A frequency synthesizer, which is tuned by the DSP, supplies the local oscillator signal for injection into a balanced mixer. The mixer subtracts the local oscillator frequency from the preselector localizer signal to produce an 18.1 MHz intermediate frequency (i-f) signal. The preselector, in conjunction with the balanced mixer, provides rejection of undesired signals and immunity to cross-modulation and inter-modulation effects.
The 18.1 MHz i-f signal from the mixer is amplified, and then filtered by a highly selective 18.1 MHz crystal filter prior to additional amplification and filtering. The amplified and filtered i-f signal is then applied to a detector stage where the audio signals are recovered as composite audio output levels for processing.
A carrier-proportional dc voltage is also provided for Automatic Gain Control (AGC) operation. The DSP removes all audio information and provides the AGC control signals to the i-f amplifiers. AGC is used to provide a constant receiver output level over a carrier input level range of less than 5 microvolts to greater than 100 millivolts.
Functional test is accomplished by injecting a test oscillator signal into the receiver and modulating the signal by the BITE. During normal operation, signals from the local oscillator, synthesizer, and AGC are monitored by the DSP.
The VOR receiver is a single-conversion superheterodyne design. The receiver frequency and gain are controlled by the DSP section of the main processor board. The VOR antenna receives signals transmitted by the VOR ground station in the 108.00 MHz to 117.95 MHz frequency range. The received VOR signal is modulated with audio tones, which provide a digital bearing word output in accordance with ARINC specification format. The signal from the antenna is applied to the preselector, which is tuned to the selected VOR channel by a tuning voltage provided by the digital signal processor (DSP).
A frequency synthesizer, which is tuned by the DSP, supplies the local oscillator signal for injection into a balanced mixer. The mixer subtracts the local oscillator frequency from the preselector localizer signal to produce an 18.1 MHz intermediate frequency (i-f) signal. The preselector, in conjunction with the balanced mixer, provides rejection of undesired signals and immunity to cross-modulation and inter-modulation effects.
The 18.1 MHz i-f signal from the mixer is amplified, and then filtered by a highly selective 18.1 MHz crystal filter prior to additional amplification and filtering. The amplified and filtered i-f signal is then applied to a detector stage where the audio signals are recovered as composite audio output levels for processing.
A carrier-proportional dc voltage is also provided for Automatic Gain Control (AGC) operation. The DSP removes all audio information and provides the AGC control signals to the i-f amplifiers. AGC is used to provide a constant receiver output level over a carrier input level range of less than 5 microvolts to greater than 100 millivolts.
Functional test is accomplished by injecting a test oscillator signal into the receiver and modulating the signal by the BITE. During normal operation, signals from the local oscillator, synthesizer, and AGC are monitored by the DSP.
(b) MARKER operation
The marker antenna receives a 75 MHz signal from one of the three marker beacon transmitters. The received signal is modulated with a 400 Hz, 1300 Hz, or 3000 Hz tone, depending upon whether the outer, middle, or inner marker is being crossed. The received 75 MHz signal is applied to a 4-pole crystal filter through an antenna monitor circuit which determines whether or not the antenna is connected to the receiver. The crystal filter provides the necessary selectivity and rejection of spurious or undesired frequencies.
The output from the 4-pole 75 MHz crystal filter is applied to a variable gain rf amplifier through a switchable attenuator which either adds or does not add 14 dB of attenuation, as determined by the presence of absence of a buffered sensitivity select signal from the main processor. The main processor through a temperature compensated AGC amplifier. AGC is used to provide a constant receiver output level during variations in carrier input level.
The output from the variable gain rf amplifier is applied to a 2-pole crystal filter through a cascode amplifier which provides the required impedance match between the RF amplifier and the filter. The output of the filter is then applied to the audio detector through a buffer amplifier which presents a constant load to the filter and isolates the varying input impedance of the detector circuit.
The recovered marker audio is then amplified and passed through an anti-alias (low-pass) filter to reduce harmonics before it is output to the main processor for analog-to-digital conversion. Functional testing is accomplished by applying a test enable signal through a buffer which provides a constant voltage to the base of the test oscillator transistors to prevent variation in the power levels of the test oscillators. The test oscillator injects a 75 MHz signal into the receiver through an adjustable pad which is used to set the output power level for maximum receiver sensitivity.
The marker antenna receives a 75 MHz signal from one of the three marker beacon transmitters. The received signal is modulated with a 400 Hz, 1300 Hz, or 3000 Hz tone, depending upon whether the outer, middle, or inner marker is being crossed. The received 75 MHz signal is applied to a 4-pole crystal filter through an antenna monitor circuit which determines whether or not the antenna is connected to the receiver. The crystal filter provides the necessary selectivity and rejection of spurious or undesired frequencies.
The output from the 4-pole 75 MHz crystal filter is applied to a variable gain rf amplifier through a switchable attenuator which either adds or does not add 14 dB of attenuation, as determined by the presence of absence of a buffered sensitivity select signal from the main processor. The main processor through a temperature compensated AGC amplifier. AGC is used to provide a constant receiver output level during variations in carrier input level.
The output from the variable gain rf amplifier is applied to a 2-pole crystal filter through a cascode amplifier which provides the required impedance match between the RF amplifier and the filter. The output of the filter is then applied to the audio detector through a buffer amplifier which presents a constant load to the filter and isolates the varying input impedance of the detector circuit.
The recovered marker audio is then amplified and passed through an anti-alias (low-pass) filter to reduce harmonics before it is output to the main processor for analog-to-digital conversion. Functional testing is accomplished by applying a test enable signal through a buffer which provides a constant voltage to the base of the test oscillator transistors to prevent variation in the power levels of the test oscillators. The test oscillator injects a 75 MHz signal into the receiver through an adjustable pad which is used to set the output power level for maximum receiver sensitivity.
(c) Instrumentation
The CPU section is used to process the data from the DSP section, to provide information to the front panel display and to provide the data and control signals to the I/O section.
The microprocessor in the CPU section controls all major functions of the VOR Receiver. ASICs an PLDs serve as the microprocessor controller and provides the interfaces with the memory devices (boot routine, program, fault and data), the data loader/recorder card, and the front panel display driver.
Data is exchanged with the DSP section through a dual-port RAM.
The CPU section is used to process the data from the DSP section, to provide information to the front panel display and to provide the data and control signals to the I/O section.
The microprocessor in the CPU section controls all major functions of the VOR Receiver. ASICs an PLDs serve as the microprocessor controller and provides the interfaces with the memory devices (boot routine, program, fault and data), the data loader/recorder card, and the front panel display driver.
Data is exchanged with the DSP section through a dual-port RAM.
(d) LRU monitoring
The maintenance processor, monitors the health of the VOR and marker beacon receivers. The maintenance processor provides all the BITE functions for the LRU. BITE information is transferred to the system processor for communications to the aircraft maintenance functions include:
The maintenance processor, monitors the health of the VOR and marker beacon receivers. The maintenance processor provides all the BITE functions for the LRU. BITE information is transferred to the system processor for communications to the aircraft maintenance functions include:
1 Receive data from the ARINC maintenance bus and store the time, data, aircraft IDENT, aircraft configuration and process the maintenance control word.
2 Process data received from the system processor for storage in the Non-Volatile fault Memory (NVM).
3 Monitor discrete inputs.
4 Determine the validity of the maintenance input control word.
5 Format the fault summary word and transfer it to the system processor.
6 Transfer all OMS interactive mode data and normal mode data words to the system processor.
7 Provide maintenance menus in the aircraft.
8 Provide extended interactive mode support for troubleshooting when the LRU is in the maintenance mode.
(6) Digital outputs
This table contains all the output parameters in the digital form.
They are sorted as per the numerical order of their output label.
The following table gives :
This table contains all the output parameters in the digital form.
They are sorted as per the numerical order of their output label.
The following table gives :
- EQ.SYS.LAB.SDI: (SDAC,FWC,DMC...) output label for which the parameter is available
- PARAMETER DEFINITION: parameter name
- WORD RANGE OPER RANGE RESOLUTION ACCURACY: measurement range. Maximum value transmitted. When the digital value changes, the change step is equal to the accuracy
- UNIT: unit in which the digital value is transmitted
- SIG BIT: indicates whether a sign bit is available
- BITS: number of bits used by the parameter in the label
- XMSN/INTV: output transmission interval. The refresh rate is given in milliseconds
- CODE :
BNR: binary data word
BCD: binary coded decimal data word
ISO: data word coded in ISO5 code
DIS: discrete data word
HEX: hexadecimal coded
HYB: mixed code - ALPHA CODE: indicates the parameter mnemonic code
- SOURCE ORIGIN: parameter source computer or system.
| ------------------------------------------------------------------------------- |
| | PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | |
| ------------------------------------------------------------------------------- |
| |EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | |
| | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | |
| | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| |
| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| |
| | | | | | | | | | |CONV | |
| ------------------------------------------------------------------------------- |
| ! .034. !VOR 1 FREQ! 108/117.95 !MHZ ! ! 4 !2560!BCD ! ! ! |
| ! ! ! 0.01 ! ! ! ! ! ! ! ! |
| ! !VOR 2 FREQ! ! ! ! ! ! ! ! ! |
| !--------------!----------!------------!----!----!----!----!----!-----!-------! |
| ! .100. !SEL ! 180 !DEG ! ! 12 ! !BNR ! ! ! |
| ! !COURSE 1 ! 0.0439 ! ! ! ! ! ! ! ! |
| ! ! ! ! ! ! ! ! ! ! ! |
| !--------------!----------!------------!----!----!----!----!----!-----!-------! |
| ! .222. !OMNI ! 180 !DEG ! ! 12 ! !HYB ! ! ! |
| ! !BEARING ! 0.0439 ! ! ! ! ! ! ! ! |
| ! ! ! ! ! ! ! ! ! ! ! |
| !--------------!----------!------------!----!----!----!----!----!-----!-------! |
| ! .242. !VOR 1 ! ! ! ! ! !HYB ! ! ! |
| ! !IDENT ! ! ! ! ! ! ! ! ! |
| ! !WORD 1 ! ! ! ! ! ! ! ! ! |
| ! ! ! ! ! ! ! ! ! ! ! |
| ! !VOR 2 ! ! ! ! ! ! ! ! ! |
| ! !IDENT ! ! ! ! ! ! ! ! ! |
| ! !WORD 1 ! ! ! ! ! ! ! ! ! |
| !--------------!----------!------------!----!----!----!----!----!-----!-------! |
| ! .244. !VOR 1 ! ! ! ! ! !HYB ! ! ! |
| ! !IDENT ! ! ! ! ! ! ! ! ! |
| ! !WORD 2 ! ! ! ! ! ! ! ! ! |
| ! ! ! ! ! ! ! ! ! ! ! |
| ! !VOR 2 ! ! ! ! ! ! ! ! ! |
| ! !IDENT ! ! ! ! ! ! ! ! ! |
| ! !WORD 2 ! ! ! ! ! ! ! ! ! |
| ------------------------------------------------------------------------------- |
(7) Digital outputs
This table contains all the output parameters in the digital form.
They are sorted as per the numerical order of their output label.
The following table gives:
This table contains all the output parameters in the digital form.
They are sorted as per the numerical order of their output label.
The following table gives:
- EQ.SYS.LAB.SDI: (SDAC,FWC,DMC...) output label for which the parameter is available
- PARAMETER DEFINITION: parameter name
- WORD RANGE OPER RANGE RESOLUTION ACCURACY: measurement range. Maximum value transmitted. When the digital value changes, the change step is equal to the accuracy
- UNIT: unit in which the digital value is transmitted
- SIG BIT: indicates whether a sign bit is available
- BITS: number of bits used by the parameter in the label
- XMSN/INTV: output transmission interval. The refresh rate is given in milliseconds
- CODE :
BNR: binary data word
BCD: binary coded decimal data word
ISO: data word coded in ISO5 code
DIS: discrete data word
HEX: hexadecimal coded
HYB: mixed code - ALPHA CODE: indicates the parameter mnemonic code
- SOURCE ORIGIN: parameter source computer or system.
| ------------------------------------------------------------------------------- |
| | PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) | |
| ------------------------------------------------------------------------------- |
| |EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE | |
| | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN | |
| | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.| |
| | |(X=NOTE) | ACCURACY | | | | | | |ATA REF| |
| | | | | | | | | | |CONV | |
| ------------------------------------------------------------------------------- |
| ! .034. !VOR 1 FREQ! 108/117.95 !MHZ ! ! 4 !2560!BCD ! ! ! |
| ! ! ! 0.01 ! ! ! ! ! ! ! ! |
| ! !VOR 2 FREQ! ! ! ! ! ! ! ! ! |
| !--------------!----------!------------!----!----!----!----!----!-----!-------! |
| ! .100. !SEL ! 180 !DEG ! ! 10 ! !BNR ! ! ! |
| ! !COURSE 1 ! 0.0439 ! ! ! ! ! ! ! ! |
| ! ! ! ! ! ! ! ! ! ! ! |
| !--------------!----------!------------!----!----!----!----!----!-----!-------! |
| ! .222. !OMNI ! 180 !DEG ! ! 13 ! !HYB ! ! ! |
| ! !BEARING ! 0.0439 ! ! ! ! ! ! ! ! |
| ! ! ! ! ! ! ! ! ! ! ! |
| !--------------!----------!------------!----!----!----!----!----!-----!-------! |
| ! .242. !VOR 1 ! ! ! ! ! !HYB ! ! ! |
| ! !IDENT ! ! ! ! ! ! ! ! ! |
| ! !WORD 1 ! ! ! ! ! ! ! ! ! |
| ! ! ! ! ! ! ! ! ! ! ! |
| ! !VOR 2 ! ! ! ! ! ! ! ! ! |
| ! !IDENT ! ! ! ! ! ! ! ! ! |
| ! !WORD 1 ! ! ! ! ! ! ! ! ! |
| !--------------!----------!------------!----!----!----!----!----!-----!-------! |
| ! .244. !VOR 1 ! ! ! ! ! !HYB ! ! ! |
| ! !IDENT ! ! ! ! ! ! ! ! ! |
| ! !WORD 2 ! ! ! ! ! ! ! ! ! |
| ! ! ! ! ! ! ! ! ! ! ! |
| ! !VOR 2 ! ! ! ! ! ! ! ! ! |
| ! !IDENT ! ! ! ! ! ! ! ! ! |
| ! !WORD 2 ! ! ! ! ! ! ! ! ! |
| ------------------------------------------------------------------------------- |
B. Antennas
(1) MARKER antenna
A low-drag, lightweight antenna, located in the longitudinal axis of the aircraft below the fuselage, is provided for the reception of the 75 MHz marker signals. The dielectric, foam-filled, white polyester fiberglass housing, fitted with a metal leading edge, protects against moisture and erosion. The antenna is horizontally polarized, has an impedance of 50 ohms.
A low-drag, lightweight antenna, located in the longitudinal axis of the aircraft below the fuselage, is provided for the reception of the 75 MHz marker signals. The dielectric, foam-filled, white polyester fiberglass housing, fitted with a metal leading edge, protects against moisture and erosion. The antenna is horizontally polarized, has an impedance of 50 ohms.
(2) VOR antenna
The VOR antenna is an airborne antenna sunk into the fin and used to receive VOR signals in the 108-118 MHz range. It is a small-sized half-wave folded dipole type.
The antenna has two independent RF connectors used to feed two items of equipment. The antenna is horizontally polarized, has an impedance of 50 ohms.
The VOR antenna is an airborne antenna sunk into the fin and used to receive VOR signals in the 108-118 MHz range. It is a small-sized half-wave folded dipole type.
The antenna has two independent RF connectors used to feed two items of equipment. The antenna is horizontally polarized, has an impedance of 50 ohms.
6. Operation
A. Control
(1) VOR system
VOR - Frequency Selection in Emergency Mode ** ON A/C NOT FOR ALL
VOR - Frequency Selection in Emergency Mode ** ON A/C NOT FOR ALL
VOR - Frequency Selection in Emergency Mode ** ON A/C NOT FOR ALL
- Each VOR/MKR receiver is connected to one RMP. The VOR/MKR receiver 1 is connected to the RMP 1, (the VOR/MKR receiver 2 to the RMP 2). The RMP 1 also receives the management bus from the FMGC 1 (the RMP 2 from the FMGC 2).
- In normal operation, the FMGC 1(2) tunes the VOR/MKR receiver 1(2) either automatically or manually by means of the MCDU 1(2). In this case the RMP 1(2) operates as a relay which sends the frequency and course information from the FMGC 1(2) to the VOR/MKR receiver 1(2).
- By a second port, the VOR/MKR receiver 1(2) receives a second management bus directly from the FMGC 2(1). The receiver selects one of the two port functions by a discrete signal from the FMGC 1(2) through the RMP 1(2).
- In case of one FMGC fault, the other FMGC can control the two VOR/MKR receivers, one directly, the other through its RMP.
- In case of the RMP 1(2) or two RMPs fault, the concerned RMP is transparent to data and discrete from the FMGC.
- In emergency configuration (in case of two FMGCs fault) the RMP 1 can control the VOR/MKR receiver 1 after ON NAV mode selection. Same possibility for the RMP 2 (VOR/MKR receiver 2).
VOR - Frequency Selection in Emergency Mode ** ON A/C NOT FOR ALL VOR - Frequency Selection in Emergency Mode ** ON A/C NOT FOR ALL VOR - Frequency Selection in Emergency Mode ** ON A/C NOT FOR ALL (2) Marker system
The marker receiver is contained in the VOR/MKR receiver.
In normal operation, the VOR/MKR receiver receives a signal when the aircraft overflies the corresponding marker.
The marker receiver is contained in the VOR/MKR receiver.
In normal operation, the VOR/MKR receiver receives a signal when the aircraft overflies the corresponding marker.
B. Reconfiguration Switching
In normal utilization, both VOR 1 and 2 data are shown on the CAPT (F/O) ND through their respective Display Management Computer (DMC 1(2)). The marker data are shown on the CAPT (F/O) PFD through the DMC 1(2).
In case of the DMC 1(2) fault, it is possible to switch over to the DMC 3 with the EIS DMC selector switch. This selector switch is located on panel 8VU on the center pedestal. In this case the DMC 3 totally replaces the DMC 1(2) through the stage of the output switching relay of the failed DMC. In case of PFD fault, there is an automatic transfer of the PFD image into the ND.
In case of ND fault:
In normal utilization, both VOR 1 and 2 data are shown on the CAPT (F/O) ND through their respective Display Management Computer (DMC 1(2)). The marker data are shown on the CAPT (F/O) PFD through the DMC 1(2).
In case of the DMC 1(2) fault, it is possible to switch over to the DMC 3 with the EIS DMC selector switch. This selector switch is located on panel 8VU on the center pedestal. In this case the DMC 3 totally replaces the DMC 1(2) through the stage of the output switching relay of the failed DMC. In case of PFD fault, there is an automatic transfer of the PFD image into the ND.
In case of ND fault:
- you obtain the transfer of the ND image onto the PFD when you push the PFD/ND XFR pushbutton switch on panel 301VU (500VU).
- deactivation of the PFD
- transfer of the PFD image onto the ND.
7. BITE Function
A. Access to the VOR/MKR Sub-menu Functions
It is possible to select the maintenance functions of the VOR/MKR receiver 1 (2) on the MCDU1 (2) by pressing the line key adjacent to the SYSTEM REPORT/TEST indication on the CFDS menu, and then selecting the relevant VOR on the NAV menu.
After these actions, the VOR 1 (2) provides its own menu page and the sub-menu functions can then be chosen by the operator.
It is possible to select the maintenance functions of the VOR/MKR receiver 1 (2) on the MCDU1 (2) by pressing the line key adjacent to the SYSTEM REPORT/TEST indication on the CFDS menu, and then selecting the relevant VOR on the NAV menu.
After these actions, the VOR 1 (2) provides its own menu page and the sub-menu functions can then be chosen by the operator.
It is possible to select the maintenance functions of the VOR/MKR receiver 1 (2) on the MCDU1 (2) by pressing the line key adjacent to the SYSTEM REPORT/TEST indication on the CFDS menu, and then selecting the relevant VOR on the NAV menu.
After these actions, the VOR 1 (2) provides its own menu page and the sub-menu functions can then be chosen by the operator.
It is possible to select the maintenance functions of the VOR/MKR receiver 1 (2) on the MCDU1 (2) by pressing the line key adjacent to the SYSTEM REPORT/TEST indication on the CFDS menu, and then selecting the relevant VOR on the NAV menu.
After these actions, the VOR 1 (2) provides its own menu page and the sub-menu functions can then be chosen by the operator.
B. Activation of the Test Function
The test function can be activated in ground conditions only.
The test function can be activated in ground conditions only.
The VOR/MARKER test can be activated from any of the following sources:
The test function can be activated in ground conditions only.
The test function can be activated in ground conditions only.
The VOR/MARKER test can be activated from any of the following sources:
- the tuning frequency word's SSM set to "TEST"
- the front panel pushbutton
- via the ARINC 429 CFDIU Data Bus (on the ground only)
- the CFDS interactive menu.
(1) Marker test
The marker test can be activated by pressing the line key adjacent to the TEST indication on the VOR 1 maintenance sub-menu or by pressing the pushbutton switch on the face of the receiver.
The marker test can be activated by pressing the line key adjacent to the TEST indication on the VOR 1 maintenance sub-menu or by pressing the pushbutton switch on the face of the receiver.
(2) VOR test
The VOR test can be activated by pressing the line key adjacent to the TEST indication on the VOR 1(2) maintenance sub-menu or by pressing the pushbutton switch on the face of the receiver.
The VOR test can be activated by pressing the line key adjacent to the TEST indication on the VOR 1(2) maintenance sub-menu or by pressing the pushbutton switch on the face of the receiver.
(3) The SSM must be continuously updated and must reflect the current states of the BITE. If any failures are present the SMM must be set to "FAIL". If no failures are present, then the SMM must be set to "TEST".
8. BITE Test
A. CFDIU Interface
(1) BITE description
The BITE facilitates maintenance on in-service aircraft. It detects and identifies a failure related to the VOR system.
The BITE of the VOR receiver is connected to the CFDIU (Ref. AMM D/O 31-32-00-00).
The unit tested is the VOR receiver.
The BITE:
The BITE facilitates maintenance on in-service aircraft. It detects and identifies a failure related to the VOR system.
The BITE of the VOR receiver is connected to the CFDIU (Ref. AMM D/O 31-32-00-00).
The unit tested is the VOR receiver.
The BITE:
- transmits permanently VOR system status and its identification message to the CFDIU
- memorizes the failures which occurred during the last 63 flight segments
- monitors data inputs from the various peripherals (FMGC, RMP and CFDIU)
- transmits to the CFDIU the result of the tests performed and self-tests
- can communicate with the CFDIU through the menus.
- the normal mode
- the menu mode.
(a) Normal mode
During the normal mode the BITE monitors cyclically the status of the VOR system. It transmits its information to the CFDIU during the concerned flight.
In case of fault detection the BITE stores the information in the fault memories.
These items of information are transmitted to the CFDIU every 50 to 250 ms by an ARINC 429 message with label 356.
During the normal mode the BITE monitors cyclically the status of the VOR system. It transmits its information to the CFDIU during the concerned flight.
In case of fault detection the BITE stores the information in the fault memories.
These items of information are transmitted to the CFDIU every 50 to 250 ms by an ARINC 429 message with label 356.
(b) Menu mode:
The menu mode can only be activated on the ground.
This mode enables communication between the CFDIU and the VOR receiver BITE by means of the MCDU.
The VOR menu mode is composed of:
The menu mode can only be activated on the ground.
This mode enables communication between the CFDIU and the VOR receiver BITE by means of the MCDU.
The VOR menu mode is composed of:
- LAST LEG REPORT This menu permits to display two failures per page. These may be any combination of class 1 and /or class 2 faults. VOR - Maintenance Test Procedure - VOR Menu ** ON A/C NOT FOR ALL VOR - Maintenance Test Procedure - VOR Menu ** ON A/C NOT FOR ALL
- PREVIOUS LEGS REPORT This report contains the fault messages related to the external or internal failures (class 1 and 2) recorded during the previous 63 flight legs. VOR - Maintenance Test Procedure - VOR Menu ** ON A/C NOT FOR ALL VOR - Maintenance Test Procedure - VOR Menu ** ON A/C NOT FOR ALL
- LRU IDENTIFICATION Allows to display the P/N and S/N of the equipment. VOR - Maintenance Test Procedure - VOR Menu ** ON A/C NOT FOR ALL VOR - Maintenance Test Procedure - VOR Menu ** ON A/C NOT FOR ALL
- GROUND SCANNING
Based on the monitoring and fault analysis during flight, provides information of the failures detected while using this function. - TROUBLE SHOOTING DATA
Provides correlation parameters and snapshot data concerning the failure displayed in the LAST LEG REPORT and PREVIOUS LEG REPORT. - CLASS 3 FAULT
Allows to display the class 3 faults recorded during the last flight leg. - GROUND REPORT
Allows to present the class 1, 2 or 3 internal failures detected on ground.
These failures differ from those displayed on the LAST LEG REPORT and CLASS 3 FAULTS. - TEST
Allows a check of the correct operation of the VOR/MKR on ground.
B. Power-up Tests Initialization and Cockpit Repercussions
(1) Conditions of power-up tests initialization
- How long the computer must be de-energized: 3 s.
- A/C configuration:
- whatever the A/C configuration on ground
(2) Progress of power-up tests
(a) Duration: 3 s.
(b) Cockpit repercussions directly linked to power-up test accomplishment (some other repercussions may occur depending on the A/C configuration but these can be disregarded):
- if VOR selected on FCU
- ND
VOR 1 or 2 in red
Bearing of VOR 1 or VOR 2 rotates to 360 deg.
(3) Results of power-up tests
(cockpit repercussions, if any, in case of tests pass/tests failed).
(cockpit repercussions, if any, in case of tests pass/tests failed).
(a) Tests pass:
- if VOR selected on FCU
- ND
VOR 1 or 2 in white
(b) Tests failed:
- if VOR selected on FCU
- ND
VOR 1 or 2 in red
VOR 1 or 2 bearing in red