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.
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VOR/Marker - Block Diagram
Figure 002A
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INTENTIONALLY BLANK
1 1
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VOR/Marker - Control and Indicating
Figure 003
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VOR/Marker - Control and Indicating
Figure 003A
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VOR/Marker - Data and Warning Displays
Figure 004
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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).
In case of VOR system fault ,all these data go out of view and the VOR 1 or 2 indication turns to red. 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/DME RMI
_
The RMI indicates the VOR bearings :
-
a single pointer indicates the VOR 1 bearing (item 11)
-
a double pointer indicates the VOR 2 bearing.
A warning flag comes into view to indicate system malfunction
(item 12). In this case, the corresponding pointer is in the 3
o'clock position (item 13).
In case of No Computed Data (NCD), no warning 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 :
-OM for the outer marker (blue)
-MM for the middle marker (amber)
-AWY 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
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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.
D. Warning (Ref. Fig. 004) The warning related to the VOR is the local warning shown on the VOR/DME RMI. In case of VOR fault, a corresponding VOR flag comes into view on the VOR/DME RMI.
R **ON A/C 106-149, 201-299, 301-399, 401-499,
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.
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