R Navigation Display - Interface with DME Figure 080
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---------------------------------------. | | OCTAL | | | SIGNAL | LABEL | FORMAT | |------------------|---------|--------| | DME FREQUENCY | 035 | BCD | |------------------|---------|--------| | DME DISTANCE | 202 | BNR | | (DISPLAY) | | | |------------------|---------|--------| | DME AUDIO IDENT | 246 | | | WORD * 1 | | | |------------------|---------|--------| | DME AUDIO IDENT | 247 | | | WORD * 2 | | |
G. ILS
R (Ref. Fig. 081) All 3 DMCs receive ILS1 and ILS2 data. The ILS1 data are displayed on the CAPT PFD and F/O ND, and the ILS2 data on the F/O PFD and CAPT ND.
---------------------------------------. | | OCTAL | | | SIGNAL | LABEL | FORMAT | |------------------|---------|--------| | ILS FREQUENCY | 033 | BCD | |------------------|---------|--------| | SELECTED RUNWAY | 017 | BCD | | HEADING | | | |------------------|---------|--------| | SELECTED RUNWAY | 105 | BNR | | HEADING | | | |------------------|---------|--------| | LOCALIZER | 173 | BNR | | DEVIATION | | | |------------------|---------|--------| | GLIDE SLOPE | 174 | BNR | | DEVIATION | | | |------------------|---------|--------| | ILS AUDIO IDENT | 263 | | | WORD * 1 | | | |------------------|---------|--------| | ILS AUDIO IDENT | 264 | | | WORD * 2 | | |
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R Navigation Display - Interface with ILS Figure 081
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H. TCAS (Ref. Fig. 082) The TCAS computer comprises 2 redundant sections which utilize a bi-processor structure. The DMCs 1 and 3 receive data from processor 1 and the DMC 2 receives data from processor 2.
_______________________________________________ | SIGNAL | LABEL | FORMAT | |________________________|_________|__________| | VERTICAL RESOLUTION | 270 | HYB | | ADVISORY | | | |________________________|_________|__________| | SENSITIVITY LEVEL | 016 | HYB | |------------------------|---------|----------| | SELECTED ALTITUDE | 015 | HYB | | LIMITS (Optional) | | | |------------------------|---------|----------| | SELECTED ALTITUDE | 013 | HYB | | (Optional) | | | |------------------------|---------|----------| | REQUEST TO SEND | 357 | HYB | |------------------------|---------|----------| | INTRUDER RANGE | 130 | HYB | |------------------------|---------|----------| | INTRUDER ALTITUDE | 131 | HYB | |------------------------|---------|----------| | INTRUDER BEARING | 132 | HYB | |------------------------|---------|----------| | END OF TEXT | 357 | HYB | |------------------------|---------|----------| | TCAS PROCESSOR MADE | 274 | HYB | |------------------------|---------|----------| | MAINTENANCE WORD | 350 | HYB |
R **ON A/C 001-049, 101-149, 151-199, 201-299, 301-399, 401-499,
J. Weather Radar Each DMC receives from the transceiver unit its 2 data buses, D1 and D2. The DMC processes the information from the in service transceiver unit. The DMCs which operate on side 1 normally work with the data 1 bus, which corresponds to the CAPT range selection. However, they can operate with a data 2 bus, i.e. using the data corresponding to the range selected by the F/O, in case of an FMGC1 failure which leads to an automatic change-over to the FMGC2 data in the DMC1. (SET OFFSIDE RANG/MODE message on the CAPT ND).
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R Navigation Display - Interface with TCAS Figure 082
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The same applies for the DMCs working on side 2, which normally use the
D2 bus, but which use the D1 bus in case of FMGC2 failure.
**ON A/C 051-099,
J. Weather Radar (Ref. Fig. 083) Each DMC receives from the WXR T/R units their 2 data buses, D1 and D2. The DMC processes information from the in service WXR T/R Unit. The DMCs which operate on side 1 normally work with the data 1 buses, which correspond to the CAPT range selection. However, they can operate with a data 2 bus, i.e. using the data corresponding to the range selected by the F/O, in case of an FMGC1 failure which leads to an automatic change-over to the FMGC2 data in the DMC1. (message "SET OFFSIDE RANG/MODE" on the CAPT ND).
The same applies for the DMCs working on side 2, which normally use the
D2 buses, but which use the D1 buses in case of FMGC2 failure.
**ON A/C ALL
5. Flags Test__________
**ON A/C 001-049, 051-099, 101-105, 151-199, 201-299, 301-302,
(Ref. Fig. 084)
**ON A/C ALL
When performing a cockpit light test all the EIS DUs display fixed flags test patterns showing flags and annunciators at their proper locations. This mode is inhibited in flight. This test is activated by the DMCs on reception of a ground discrete signal coming through contacts of a relay. This relay is controlled by a signal coming from the ALTU (annunciator light test unit) in series with a flight/ground switch contact.
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