More explanations are given in the GPWS system (Ref. 34-48).
E. Dependent Position Determining This part of the navigation system comprises :
(1)
Distance Measuring Equipment (DME) The DME enables the distance separating the aircraft from one or two DME station being received to be known. The DME is made up of two systems comprising respectively :
-
a DME interrogator
-
a transmission/reception antenna.
The system receives frequency information from FMGCs or RMPs.
The slant range distance is displayed on NDs and PFDs.
More explanations are given in the DME system (Ref. 34-51).
The slant range distance is displayed also on a VOR/DME Radio
Magnetic Indicator (RMI) or a VOR/ADF/DME RMI (optional) (Ref.
34-57).
(2)
Air Traffic Control (ATC) The ATC allows an operator of the corresponding equipment on the ground to locate and identify the aircraft in flight without having to communicate with the crew. The system is made up of the following components :
-two ATC transponders
-a ATC/TCAS control unit
-four ATC antennas: two bottom antennas and two top antennas
(optional). More explanations are given in the ATC system (Ref. 34-52).
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(3)
Automatic Direction Finder (ADF) The ADF enables the bearings of one or two ADF ground transmitter stations to be permanently indicated with respect to the aircraft heading. The system is made up of the following components : - one or two transceivers (transceiver 2 is optional)
-
two ADF loop and sense antennas.
The system receives frequency information from FMGCs or RMPs.
The ADF bearings are displayed on:
-
two EFIS Navigation Displays (in Rose mode).
-a Radio Magnetic Indicator (RMI) (optional) (Ref. 34-57).
More explanations are given in the ADF system (Ref. 34-53).
(4)
VHF Omni-Range (VOR) The VOR firstly enables the bearings of one or two VOR ground transmitter stations to be permanently indicated with respect to the aircraft heading, and secondly it indicates the aircraft course deviation with respect to a preselected course. The system is made up of the following components :
-two VOR/MKR receivers
-
a VOR antenna to supply the two VOR/MKR receivers
-
a MARKER antenna to supply the VOR/MKR receiver 1 which is the only
one to ensure the MARKER function.
The system receives frequency information from FMGCs or RMPs.
VOR data are displayed on:
-
two EFIS PFDs
-
two EFIS NDs
-a VOR/DME Radio magnetic Indicator (RMI) or a VOR/ADF/DME RMI
(optional) (Ref. 34-57). Marker data are displayed on CAPT and F/O PFDs and NDs. More explanations are given in the VOR/MARKER system (Ref. 34-55).
(5) Global Positioning System (GPS) (optional system) The GPS system is a radio aid to worldwide navigation which provides:
-
the crew with a readout of accurate navigation information, e.g. position, track and speed.
-
the Flight Management and Guidance Computer (FMGC) with position
information for accurate position fixing. To this end, the GPS system uses signals broadcast by a constellation of 24 satellites at a frequency of 1575.42 MHz. The GPS system is composed of:
-
two GPS Sensor Units (GPSSUs)
-
two GPS antennas.
More explanations are given in the GPS system (Ref. 34-58).
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AIR DATA/INERTIAL REFERENCE SYSTEM (ADIRS) - DESCRIPTION AND OPERATION
______________________________________________________________________
1. General
_______
R The main air data and heading/attitude data are provided by a three-channel Air Data Inertial Reference System (ADIRS). This configuration provides for triple redundant information for all inertial and air data functions. Each channel is isolated from the others and provides independent information as defined by ARINC Characteristic 738. The ADIRS comprises:
-Three Air Data/Inertial Reference Units (ADIRU(s)) (ATA 34-12)
-A control and Display Unit (CDU) (ATA 34-12)
-Three pitot probes (ATA 34-11)
-Six static probes (ATA 34-11)
-Eight Air Data Modules (ADMs) Linked to the pitot and static probes (ATA 34-11)
-Two Total Air Temperature (TAT) sensors (ATA 34-11)
-Three Angle of Attack (AOA) sensors (ATA 34-11)
Each of the ADIRUs contains two portions:
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