3272-5 (9) Tec Dig

HIRF protection of LRUs is provided by. internally shielded cables. built in filters and overvoltage circuits. built in filters only.

To stop earth loops forming, you would. earth both ends of the cable screen. leave both ends of the cable screen open circuit. earth only one end of the cable screen.

An aircraft may have been HIRF affected. Test all radio frequencies for interference. A static wick check is required. A bonding load check is required.

Testing of HIRF on aircraft systems is done. by periodically listening for interference on all systems. at and during production and testing (initial certification). only after a report of radio interference.

When carrying out a bonding check on a surface protected by anodic film. the film is conductive so no preparations are required. the anodic film should be removed locally to ensure a good contact. add a bonding factor to the result of the test to account for the resistance of the anodic film.

When clamping cable looms containing co-axial cables. avoid distortion to the co-axial cable to maintain the dielectric constant. the clamps must be no more than 1 metre apart. distortion of the outer sheath is allowed providing the inner cable is not affected.

When incorporating an aerial cable it must be. in the centre of the other wires. outside the other wires for easy access. positioned separately from the loom.

When carrying out airframe bonding checks as part of a program of HIRF prevention the airframe bonding resistance should be less than. 100 milliohms. 1 ohm. 50 milliohms.

Electromagnetic compatibility is achieved by. shielding, screening, earthing, bonding and interference filters. coating in a conductive paint. enclosing the system with same frequency and strength of which screening is done.

To reduce HIRF on radio equipment. ensure all static wicks are in place. periodically check bonding leads for condition. transmit on all radio frequencies to determine which frequencies are causing the interference.

For braided cables, the amount of braiding. must conform to the requirement for the shielding to cover at least 50% of the surface of the cable. keeps radiated power inside the emitting assembly or away from the susceptible circuit. is a trade-off design feature.

HIRF is acronym for. Heavily Ionised Radio Frequencies. High Intensity Radiated Field. High Intensity Radio Frequencies.

HF aerials are protected against lightning strike by. current mode coupler. bus terminal. spark gap.

An FMS system, besides controlling navigation, thrust and auto-nav, also provides. GPWS warnings. dedicated status and warnings. take-off and landing warnings.

The minimum standards for aircraft instrumentation is set by. CAA. ICAO. JAA.

EADI sky and ground display is provided by. raster scan. stroke pulse. synthetic TV signals.

HSI heading is valid if the heading flag is. in view. green. out of view.

MFD is the abbreviation for. Multi function display. Mandatory flight display. Master flight display.

A TCAS uses the radar mile definition in its calculations, which is. 36 microsecond. 18 microsecond. 72 microsecond.

GPS navigation uses a constellation of satellites that is made up of. 21 active and 3 spare. 28 active and 7 spare. 23 active and 5 spare.

An IRS is only certifed for alingment up to. +88. 45 and -88.45 degrees. +78. 25 and -78.25 degrees. +60 and -60 degrees.

The command bars on an ADI relate to. roll indications. path being followed. path required.

ECAM has at its heart. a multi function symbol generator. a central maintenance computer. ACARS.

The recording medium in an FDR is. copper foil coated with ferrite. a high density floppy disc. magnetic tape coated with ferrite.

The recording medium in an FDR is. copper foil coated with ferrite. a high density floppy disc. magnetic tape coated with ferrite.

An FMS databank memory is updated. every 365 days. every 28 days. every 32 days.

What does the CADC feed?. cabin pressure controller sensor / machmeter / altimeter. Altimeter / FMS / secondary radar. standby altimeter / machmeter.

In a Flight Management System (FMS), data is input manually to the computing system through the. Data Acquisition Unit. Electronic Centralised Aircraft Monitoring control panel. Control and Display Unit.

In a Global Positioning System (GPS), the number of satellites required to achieve a 3 dimensional fix is. 2. 3. 4.

In a Global Positioning System (GPS), each satellite transmission identifies the satellite using a. different channel frequency. pseudo random code. whisper shout method.

In a Global Positioning System (GPS) satellites below the Mask Angle are ignored as these may cause. range errors. clock errors. ephemeris errors.

Information required by a Flight Management System (FMS) to function correctly is indicated on the display by. dashes. a flashing cursor. boxes.

A flight data recorder can obtain information from aircraft instruments. provided there is adequate damping. provided there is adequate isolation. by direct connection to the instruments.

The inputs and outputs of a CADC are. pitot and static in; altitude, attitude, CAS and VS out. pitot and static in; altitude, CAS, mach and VS out. pitot in; static, altitude, mach, CAS and VS out.

EICAS provides the following: Engine parameters and engine warnings only. Engine parameters and system warnings only. Engine parameters only.

A central maintenance computer provides. ground and flight monitoring and testing on an on-board computer. ground and BITE testing using a portable control panel. display of system warnings and cautions.

The rising runway is positioned from information derived from. barometric height. radio altimeter. vertical speed.

Where are the Digital Flight Data Recorder outputs supplied to?. The recording unit. There are no outputs. Flight instruments.

FMS failure and warnings are. EFIS warnings only. displayed on EICAS. engine warnings only.

Flight director command bars are moved to the correct position by. calibration. position feedback. amplifier gain.

What information is required before completion of the alignment of an Inertial Navigation System?. Aircraft present position. Heading and attitude. Aircraft present position and heading.

IRS accelerometers are mounted. 90° to each other. 45° to each other. 60° to each other.

An FMS navigation database is updated. once a month. every 28 days. at the operators request.