The navigation systems supply the aircraft navigation data for instrument flight, landing, and other navigation functions.

The flight environment data systems sense environmental conditions such as total and static pressure via the pitot-static probes, and outside air temperature via the total air temperature probes (TATs). 

Flight environment sensors supply the air data to the air data computer system, the standby instruments and the stall protection system.

The standby instrument system is installed to provide the flight crew with an independent source of heading, attitude, altitude and airspeed required to meet safety requirements. These stand-alone instruments provide the necessary minimum flight environment information in the event of a serious system failure.

The integrated standby instrument system (ISIS) consists of a single self-contained integrated standby instrument (ISI), installed to provide standby attitude, altitude and airspeed information to the flight crew. The integrated standby instrument is installed on the Global Express/XRS and Global 5000. It replaces the standby attitude indicator and standby altimeter/airspeed indicator, installed on the Global Express.

The air data computer system is the primary source of air data. The air data computer system uses the flight environment system to monitor the external atmospheric conditions and sends the digital air data to the other avionics systems.

The aircraft is certified for operation under reduced vertical separation minimum (RVSM). The radio altimeter system gives information about altitude above ground level (AGL) of the aircraft during the approach phase of the flight. The radio altimeter system has a maximum height of 2,550 feet altitude, and is shown on the primary flight displays (PFDs).

The weather radar (WXR) system identifies the location and intensity of the rain or hail in the flight path of the aircraft. It also identifies the contour of the ground (terrain) with a ground-map (GMAP) function.

The lightning sensor system is a system in the aircraft to detect and advise the pilots of lighting activity that may be a threat to the aircraft. The system detects and displays regions of significant lightning activity within 100 nm of an aircraft on the MFDs. The lightning sensor system is available on the Global 5000 and on Global Express/XRS as optional.

The VHF navigation (VHF NAV) system is a remote-controlled integrated radio system. The VHF NAV system operates as a conventional VHFomnidirectional radio/instrument landing system (VOR/ILS). It receives the approach and landing data used to correctly align the aircraft with a runway.

The air traffic control (ATC) transponder system transmits and receives an aircraft identification code and barometric altitude data. The aircraft and ATC ground stations use this data to prevent midair collisions with other aircraft. This system operates with the traffic collision avoidance system (TCAS).

The TCAS is an auxiliary air traffic control (ATC) system. It provides aural and visual alerts to avoid midair collision with other aircraft. The standard system, TCAS 2000, operates with TCAS I, TCAS II, MODE S, and ATC radar beacon systems (ATCRBS).

The head-up display (HUD) system is an electronic and optical device. It displays information (flight director guidance cues, flight monitoring and situational data) superimposed on a transparent window (combiner) in the forward field of view of the pilot. The HUD provides information to ease flight operations in adverse operating and emergency conditions with an improvement of pilot reaction time to unexpected events and decision-making process in all phases of flight.

The enhanced vision system (EVS) enhances pilot situational awareness by augmenting his ability to make visual contact with the ground or to detect obstacles. EVS is based on an infrared camera that provides a video image of the aircraft front scene.The infrared image is displayed on the HUD combiner along with other HUD data. The infrared image may also be displayed on FMS CDU 2.

The enhanced ground proximity warning system(GPWS) is a system that gives the flight crew aural and visual indications of dangerous flight conditions. The dangerous flight conditions include controlled flight into terrain and windshear.

The global positioning system (GPS) is a remote controlled navigation system. It operates independently of the aircraft´s primary navigation system, and is the primary source of navigation data used by the flight management system (FMS). GPS has sensor unit and GPS antenna. GPS antenna 2 is available as optional.

The GPS uses orbital satellites to give the continuous position and velocity data of the aircraft. It supplies the universal time coordinate(UTC) used by the other avionics systems.

The inertial reference system (IRS) is a three-axis inertial sensor system. The IRS uses sensor output data to calculate attitude, true/magnetic heading, angular/linear accelerations, and velocity. The IRS supplies ground speed, position/track, wind speed/direction, and attitude data to the electronic flight instrument system (EFIS). The EFIS shows this data on the primary flight display (PFD) and multifunction display (MFD).

The navigation display unit (NDU) system is a backup navigation system that calculates and shows navigation data. The NDU system is an integrated navigation computer and display system. It receives navigation data from the inertial reference system (IRS) and from pilot inputs, and provides outputs that are displayed on the EFIS, PFD and MFD displays.

The flight management system (FMS) is an integrated navigation system. It provides the pilots with navigation and performance data to fly the lateral and vertical modes of a programmed flight plan. The FMS also performs radio tuning function.

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