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Global Expresss > Navigation > Flashcards

Navigation Flashcards

1
Q

What is Nav

A

INTRODUCTION Figure 1 The navigation system consists of numerous systems that supply the aircraft navigation data for instrument flight, landing, and other navigation functions.

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2
Q

What are Flight environment data system

A

Flight Environment Data System 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.

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3
Q

What is the Integrated Stby inst syst

A

Integrated Standby Instrument System (Global Express XRS and Global 5000)
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.

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4
Q

What is VHF Nav

A

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

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5
Q

Wat is SSEC

A

Static source error correction

The compensation function for SSE is termed static source error correction (SSEC). During flight SSE is automatically compensated for by the ADC, using programmed SSEC tables stored in the ADC. Since the upper and lower probes are subject to different airflow and surface regime, each is provided with a separate SSEC table. The SSEC table for upper probes is in ADC 1 and lower probes in ADC 2 and 3. Installation strapping of the ADC determines which SSEC table becomes active. Both upper and lower SSEC are functions of AOA and Mach number. The AOA value is received by the ADC from the DAU.

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6
Q

What is Rad Alt

A

Radio Altimeter System
The radio altimeter system gives information about the altitude above ground level (AGL) of the aircraft during the approach phase of the flight. The radio altimeter system has a maximum height of 2550 feet altitude, and is shown on the primary flight displays (PFDs).

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7
Q

What is Air data system

A

Air Data Computer System
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 air data parameters to the other avionics systems.

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8
Q

What is ATC

A

Air Traffic Control Transponder System
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).

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9
Q

What is TCAS

A

Traffic Collision Avoidance System The traffic alert and collision avoidance system (TCAS) is an auxiliary air traffic control (ATC) system. The standard system, TCAS 2000, operates with TCAS I, TCAS II, MODE S, and ATC radar beacon systems (ATCRBS)

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10
Q

What s IRS

A

Inertial Reference System
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 groundspeed, 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).

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11
Q

What is Nav display system

A

Navigation Display Unit System 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.

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12
Q

How many tat probes

A

There are three total air temperature (TAT) probes on the aircraft. The TAT probes transmit total air temperature to the ADCs. TAT probe 1 provides pressure and temperature data to the engine electronic controller (EEC) no. 1. TAT probe 2 provides pressure and temperature data to EEC 2. The TAT probes also have internal heating elements to prevent icing.

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13
Q

Pitot probes, how many

A

Pitot-Static Probes
Figure A1 Static Port S2 Quick Disconnect Pitot-static probes 1 and 3 are mounted on the left side. Pitot-static probe 2 and the standby pitot static probe are mounted on the right side of the fuselage. The pitot-static probes are combination probes containing a single pitot and dual static ports. The contoured shape of the probe compensates for the aircraft aerodynamic characteristics. The probes have a pitot drain hole to provide drainage of moisture. Each probe has a strut that projects it away from the fuselage to isolate it from pressure disturbances close to the fuselage. The probes are mounted far enough apart so that a single bird strike would not damage more than one of the probes. The base plate contains the electrical and pressure fittings. The probes have dual heating elements for protection against icing. The heaters are controlled and monitored by the HBMUs. For more details on the pitot-static heaters, refer to chapter ATA 30.

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14
Q

What is HBMU

A

Two heater and brake temperature monitoring units (HBMUs) control all the probe heaters. If a probe heat failure is detected by the HBMU, it will be annunciated by a CAS message.

All TAT heating elements are controlled by the HBMUs. The heating elements of TAT 1 and TAT 3 are controlled by HBMU 1. The heating element of TAT 2 is controlled by HBMU 2. Circuit breakers for the TAT probe heaters are

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15
Q

How many ADC,s

A

3,

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16
Q

What is STBY system

A

The standby instrument system consists of a standby compass, standby attitude indicator and a combination standby altitude/airspeed indicator. 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 standby instrument system on airplane serial numbers 9002-9158 consists of a standby compass and electromechanical standby attitude and standby altitude/airspeed instruments. On airplane serial numbers 9159 and subs, the system consists of a standby compass and an EFIS type integrated standby instrument (ISI). See section C in this chapter for description of the ISI system

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17
Q

Stby components

A

The standby instrument system consists of the following components: • Standby magnetic compass • Standby attitude indicator • Standby altimeter/airspeed indicator

18
Q

What is ADC

A

The air data computer
system consists of three air data computers (ADCs). Other components/systems associated with the air data computer system are a reversion control panel, two PFD control panels, four pitot-static probes, three total air temperature (TAT) probes and two heater current/brake temperature monitoring units (HBMUs). The ADCs receive pitot pressure, static air pressure and total air temperature from their associated probes, barometric pressure settings from the PFD controllers and aircraft configuration data. The ADCs perform computations, including static source error correction, and transmit the air data information for display to the pilots and to other systems in the aircraft. The reversion control panel allows the pilots to select another ADC as their source of information if an ADC fails or is suspected of supplying unreliable information. ADC failures are indicated as EICAS messages. The ADCs can be monitored and tested through CAIMS.

19
Q

How many ADC,s

A

Air Data Computers
The air data computers (ADCs) are installed in the left and right side consoles in the cockpit. ADC 1 and 3 are on the left side and ADC 2 is on the right side. Inputs to the ADC consist of static and pitot pressure, total air temperature, baro set information and aircraft configuration data. Pitot pressure and static pressure are supplied through quick-disconnect fittings on the front panel. The total air temperature input is from the total air temperature probes. All electrical input/ output is through a multipin connector on the front panel.

20
Q

Speed tape

A

Airspeed Tape
The airspeed tape indicates IAS. The green rolling digits indicate current speed. IAS display range is from 30 to 900 knots. The tape is labeled every 10 knots below 200 knots and every 20 knots above 200 knots.

The green airspeed digital readout in the current value window of the airspeed tape will roll. The digital readout will freeze at 30 knots and the digits are removed from the lower portion of the airspeed tape. When the airspeed trend vector exceeds VMO or less than calculated stall warning speed by 1 knot, the digits turn amber. When IAS is equal or exceeds VMO or less than the calculated stall warning speed, the digits turn red.

21
Q

Sat-tat

A

Static air temp and total air temp

22
Q

If ADC,s are miscompared

A

Yaw damper will not engage
Miscompare will be an advisory

23
Q

What is RVSM

A

RVSM refers to the reduction of aircraft vertical altitude separation by air traffic control (ATC) from 2000 feet to 1000 feet between FL 290 (29,000 feet) and FL 410 (41,000 feet). Air traffic vertical separation was traditionally 1000 feet. At the lower altitudes and above FL 290 (29,000 feet), air traffic separation was 2000 feet as a result of the known inaccuracy of altimeters at high altitudes. Due to increasing air traffic in the 1980s, and the development of more accurate altimeter systems and test equipment, RVSM was introduced to reduce the vertical separation above FL 290 from 2000 feet to 1000 fee

24
Q

What is skin Waviness insp

A

Skin Waviness Inspection
For continued RVSM certification, a remeasure of the skin waviness is required after all repairs, rework or panel(s) replacement in the RVSM critical area (zone 4). If repair, rework or panel(s) replacement was carried out, use qualified personnel and do a skin mapping of the entire zone. The results are then sent to Bombardier Business Aircraft Customer Support, Customer Support Engineering, Montreal. Analysis of the data indicate that the overall repeatability of the surface fitting is measured within 0.015-0.020 inches. A geometric contour approval (GCA) certificate is issued to confirm that a skin waviness inspection has been carried out and the aircraft meets allowable waviness requirements for certification.

25
Q

What is rad alt system

A

The radio altimeter system consists of two radio altimeter transceivers and four antennas. The dual radio altimeter system, Collins model ALT-4000, measures altitude between the aircraft and the ground (AGL). It provides aircraft height from 0 to 2550 feet. The dual radio altimeter systems are operation independent. Radio altimeter (Rad Alt) 1 provides information to the pilot and Rad Alt 2 provides information to the copilot. Radio altitude is also supplied to other aircraft systems.

26
Q

How many transceivers

A

Radio Altimeter Transceivers The two Rad Alt transceivers are installed in the aft equipment compartment. The Rad Alt transceiver transmits radio signals and processes reflections from ground to determine altitude. The altitude data is distributed to other aircraft systems via ARINC 429 bus.

27
Q

What does Rad alt 1 supply

A

The transmitter output signal is applied to the transmit antenna. The reflected signal from the ground is picked up by the receive antenna and compared in the receiver to the transmitted signal. The difference in frequency is proportional to height above ground level (AGL) and is converted to altitude readout. The two RAs use different modulation frequencies to identify their respective signals. The radio altimeters transmit radio altitude via ARINC 429 to: • The TCAS computer for intruder advisory calculations • EGPWS for its ground proximity alert and warning logic calculations • The FCU uses side specific radio altitude for spoiler autodeploy logic during approach and landing • DAUs 3 and 4 receive radio altitude information from the Rad Alts via ARINC 429. The DAUs format this information and place it on the ASCB to the IACs for display purposes and fault reporting in CAIMS

28
Q

What hz does rad alt 1 use

A

50hz
Rad alt 2 uses 51hz

29
Q

What is GPS

A

The global positioning system (GPS) is a remotecontrolled navigation system. It operates independently of the primary navigation system of the aircraft, and is the primary source of navigation data used by the flight management system (FMS). 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.

30
Q

What is the IRS system

A

Inertial Reference System
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 groundspeed, 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).

31
Q

What is attitude mode

A

Heading, straight level flight on IRS

32
Q

Amber info light on source

A

Using same source, ie; both pilots using IRS 1

33
Q

What is the weather radar system

A

The weather radar system consists of a receivertransmitter antenna (RTA) assembly and two weather radar controllers. The weather radar system (WX) detects significant weather along the flightpath of the aircraft and gives a visual indication of its intensity. The WX system is capable of detecting storms and turbulence at ranges up to 300 nm. The radar operating modes are controlled by two weather radar controllers. Operating range is selected from the MFD controllers. Radar information is displayed on the multifunction displays (MFDs). The WX indicates failures on the MFDs and in CAIMS.

34
Q

Weather radar components

A

The weather radar system consists of the following components: • Receiver-transmitter antenna (RTA) • Weather radar controllers

35
Q

Is there an off switch

A

Yes on radar scanner

36
Q

Do i have to check flight deck select for off position

A

Yes check for of

37
Q

Where is lightning sensor panel

A

L/h side only

38
Q

What is react mode

A

Compensates when looking at big thunderstorms,gives cyan pointer for weather behind raster

39
Q

What is dia of radar flat plate

A

18 inches

40
Q

What is lightning sensor

A

The lightning sensor system (LSS) consists of a lightning sensor processor, a lightning sensor antenna and one weather radar controller. The lightning sensor system is a lightweight system. It is installed 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. There are two types of symbols. The rate symbols show the location and intensity of the lightning, and an alert symbol annunciates new rate symbols and their bearing. The modes of operation and fault codes are also displayed on the MFDs. The lightning symbols remain on the display for several minutes. They must be compensated for aircraft motion and course changes. The FMS system provides the required information to support the lightning sensor system displays.

41
Q

What can i mute on EGPWS

A

Yes

42
Q

Is glide slope dual

A

Yes, 1 antenna(diplexer)serving 2 GS recievers
Diplexer - meaning 2

Global Expresss (28 decks)

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