(2) Attitude, heading and position function Attitude, heading and position data are provided by four independent sources:
 (a)
 Three main systems The three main systems are made up of the following components :

 -three IR portions

 -a Control and Display Unit (CDU).
 They provide inertial reference information, attitude (pitch,
 roll and yaw), heading, ground speed and present position.
 The primary information of rotation rates and linear acceleration
 measured by the IR portions are directly used by the Auto Flight
 System (AFS), by the Flight Augmentation Computer (FAC) and the
 Flight Management and Guidance Computer (FMGC).
 The IR data are transmitted to the indicators (PFD, ND and RMI)
 and to the various aircraft systems.

 (b)
 A standby system

 1_ The standby system includes a standby horizon indicator and a
 standby compass (Ref. 34-22).
 More explanations are given in the ADIRU system (Ref. 34-14).

 B. Integrated Standby Instrument System (ISIS) (optional system) The Integrated Standby Instrument System (ISIS) indicator replaces the three conventional standby instruments i.e.:
 -
the standby altimeter (and standby altimeter in meters -optional-)

 -
the standby airspeed indicator

 -
the standby horizon indicator. The standby heading is given by a magnetic compass, which is an independent instrument.

 (1) The ISIS indicator, provides the following standby data on a Liquid Crystal Display (LCD) installed in place of the standby horizon:
 -Attitude,
 -Standard or baro-corrected altitude and related barometric pressure
 -Indicated airspeed and Mach number
 -Lateral acceleration and the following optional parameters:
 -ILS deviation
 -V-bar aircraft symbol
 -Barometric pressure in hPa or in hPa and in.Hg
 -Altitude in meters. In addition, two specific functions are available:
 -Display and adjustment of four airspeed bugs and four airspeed altitude bugs
 -Automatic test procedure.
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 More explanations are given in the ISIS system (Ref. 34-22).
 C. Landing and Taxiing Aids This part of the navigation system comprises :
 (1)
 Paravisual Indicator (PVI) (optional system) The aircraft is equipped with one PVI installed on the glareshield panel 131VU, Captain's side. This system provides the Captain with an image which serves as a piloting aid for take-off and landing in reduced visibility conditions. The system receives parameters from the DMC1 which can be switched to the DMC3, and generates the image. More explanations are given in the PVI system (Ref. 34-34).

 (2)
 Head Up Display (HUD) (optional system)
 The aircraft is equipped with :

 -
a HUDC (Head Up Display Computer)

 -
a OHU (Optical Head Unit).
 This system provides the Captain with an image superimposed on the
 outside world in his field of view. This image gives the guidance
 information in take-off, landing or approach configurations.
 The HUDC processes the input parameters received from the Display
 Management Computer 1 (DMC1), which can be switched to the DMC3, and
 sends them to the OHU after transformation.
 More explanations are given in the HUD system (Ref. 34-35).

 (3)
 Instrument Landing System (ILS) or Multi-Mode Receiver (MMR) (optional system) Both ILS or MMR receivers are controlled from FMGCs and Radio Management Panels (RMPs) featuring two output channels, one command output and one dialog output. All data are shown on the EFIS displays. More explanations are given in the ILS system (Ref. 34-36).

 (a)
 The ILS system enables to know the aircraft position during the landing phase with respect to a predetermined descent path. This system is composed of:

 -two ILS receivers
 -
a Localizer antenna

 -
a Glide/Slope antenna.

 (b)
 The MMR system is a navigation system with two internal receivers, the Instrument Landing System (ILS) and the Global Positioning System (GPS).

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 1_ The ILS function is to provide the crew and the airborne
 system users with lateral (LOC) and vertical (Glide/Slope)
 deviations signals, with respect to the approach ILS radio
　
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