During Air Data Inertial Reference Unit alignment, why can the Primary Flight Display continue to show valid airspeed and altitude while attitude, heading, track and vertical-speed information show no computed data?, The Air Data Reference function continues operating independently of the Inertial Reference alignment mode, while the inertial-derived parameters remain unavailable until alignment is complete., The Air Data Modules temporarily calculate airspeed and altitude independently and send them directly to the Display Processing Computers., The Integrated Standby Flight Display supplies substitute airspeed and altitude to the Primary Flight Display until Inertial Reference alignment is complete., The Integrated Standby Flight Display loses normal aircraft battery-bus voltage but its dedicated battery/charger remains serviceable. Which combination of standby information can continue to be generated independently of the main Air Data Inertial Reference System?, Pitch, roll, indicated airspeed and barometric altitude can continue using internal inertial sensors and the alternate pitot-static system, but heading still depends on the left Air Data Inertial Reference Unit., All standby parameters, including heading, remain completely independent because the Integrated Standby Flight Display contains its own magnetic heading sensor., Only pitch and roll remain available because airspeed and altitude require electrical data from the Air Data Inertial Reference Units., During an Integrated Multi-Mode Receiver Built-In Test Equipment test, the Multi-Mode Receiver STATUS indicator finishes red while the CONTROL FAULT and ANTENNA FAULT indicators flash amber. What fault category is specifically identified in the training material as capable of producing this pattern?, A simultaneous localizer and glideslope antenna open circuit., A failure of the Navigation Control Panel active/standby transfer switch., An Operational Program Software fault within the Integrated Multi-Mode Receiver., During an AIII Head-Up Display approach below 500 feet Above Ground Level, the approach monitor detects that localizer deviation has exceeded the permitted tolerance. What is the expected system response?, The FLARE annunciation appears immediately and flare guidance replaces the lateral guidance commands., The APCH WARN annunciation appears and NO AIII is displayed on the combiner, indicating that the AIII approach should not continue., The Head-Up Display removes only the localizer symbol while AIII approach capability remains valid., A Predictive Windshear warning occurs while the Traffic Alert and Collision Avoidance System is generating a Resolution Advisory. What does the weather-radar interface command the Traffic Alert and Collision Avoidance System to do?, Resolution Advisories are changed to Traffic Advisories and Traffic Alert and Collision Avoidance System audio alerts are inhibited., The Resolution Advisory remains active, but all Predictive Windshear audio is inhibited until the traffic conflict clears., Both systems continue issuing their normal alerts simultaneously because neither system has priority over the other., The Predictive Windshear system detects a windshear threat, but the Navigation Display is currently in a display mode that does not permit the windshear icon. What remains available to the flight crew?, The entire Predictive Windshear warning is inhibited until the crew selects Expanded Approach, Expanded VOR, Expanded Map or Centered Map., Predictive Windshear remains active and its aural and text alerts can still occur, but the icon and attention bars will not appear until an allowable display mode is selected., Only the aural warning remains available; all textual annunciations are inhibited in a non-allowable display mode., A Terrain Awareness display shows high-density red terrain ahead of the aircraft. What relative terrain condition does this represent before any terrain-warning logic converts the threat area to solid red?, Terrain between 500 feet below and 1,000 feet above aircraft altitude., Terrain more than 2,000 feet above aircraft altitude., Terrain between 1,000 and 2,000 feet above aircraft altitude., Air Traffic Control transponder 2 is selected as the active transponder. What additional system action is required beyond placing transponder 1 into standby?, Air Data Inertial Reference Unit 2 automatically becomes the mandatory altitude source regardless of the altitude-source switch position., The Traffic Alert and Collision Avoidance System transfers to its lower directional antenna only., An antenna-transfer discrete operates the Air Traffic Control coaxial switches so the Air Traffic Control antennas connect to transponder 2., The Navigation Control Panel fails while the Distance Measuring Equipment system was previously receiving automatic tuning commands through it. How can automatic Distance Measuring Equipment tuning continue?, The Display Processing Computer substitutes for the Navigation Control Panel and generates the automatic tuning frequencies., The VHF Omnidirectional Range receiver retransmits the last valid automatic tuning command to the Distance Measuring Equipment interrogator., The Flight Management Computer can send automatic tuning signals directly to the Distance Measuring Equipment interrogator when the Navigation Control Panel has failed., During Flight Management Computer System ground power-up, the Operational Flight Programs in the primary and secondary Flight Management Computers match, but an analog discrete mismatch exists between the computers. What maintenance page takes priority over a database mismatch?, The DATABASE CROSSLOAD page showing all database differences., The ANALOG DISCRETE page showing the specific mismatch., The SENSOR STATUS page showing the Line Replaceable Unit associated with the discrete.

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