-
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.
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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:
-LAST LEG REPORT
**ON A/C 001-049, 101-105, 151-199,
(Ref. Fig. 013)
R **ON A/C 051-099, 106-149, 201-299, 301-399, 401-499,
(Ref. Fig. 013A)
**ON A/C ALL
This menu permits to display two failures per page. These may
be any combination of class 1 and /or class 2 faults.
-PREVIOUS LEGS REPORT
**ON A/C 001-049, 101-105, 151-199,
(Ref. Fig. 013)
R **ON A/C 051-099, 106-149, 201-299, 301-399, 401-499,
(Ref. Fig. 013A)
**ON A/C ALL
This report contains the fault messages related to the external or internal failures (class 1 and 2) recorded during the previous 63 flight legs.
-LRU IDENTIFICATION
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VOR - Maintenance Test Procedure - VOR Menu (Sheet 1/6)
Figure 013
R 1EFF : 001-049, 101-105, 151-199, 1 34-55-00Page 49 1 1 May 01/05 1 1 1CES 1
VOR - Maintenance Test Procedure - VOR Menu (Sheet 1/6)
Figure 013A
R 1EFF : 051-099, 106-149, 201-299, 301-399, 1 34-55-00Page 50 1401-499, 1Aug 01/05 1 1 1CES 1 **ON A/C 001-049, 101-105, 151-199,
(Ref. Fig. 013)
R **ON A/C 051-099, 106-149, 201-299, 301-399, 401-499,
(Ref. Fig. 013A)
**ON A/C ALL
Allows to display the P/N and S/N of the equipment.
-GROUND SCANNING (Ref. Fig. 014) Based on the monitoring and fault analysis during flight, provides information of the failures detected while using this function.
-TROUBLE SHOOTING DATA (Ref. Fig. 014) Provides correlation parameters and snapshot data concerning the failure displayed in the LAST LEG REPORT and PREVIOUS LEG REPORT.
-CLASS 3 FAULT (Ref. Fig. 015) Allows to display the class 3 faults recorded during the last flight leg.
-GROUND REPORT (Ref. Fig. 015) 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 (Ref. Fig. 016, 017, 018) 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
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VOR - Maintenance Test Procedure - VOR Menu (Sheet 2/6) Figure 014
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VOR - Maintenance Test Procedure - VOR Menu (Sheet 3/6) Figure 015
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VOR - Maintenance Test Procedure - VOR Menu (Sheet 4/6) Figure 016
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VOR - Maintenance Test Procedure - VOR Menu (Sheet 5/6) Figure 017
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VOR - Maintenance Test Procedure - VOR Menu (Sheet 6/6) Figure 018
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(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.
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