The Electronic Engine Controls lose electrical power in flight. Which engine indications can the Display Processing Computers still generate using their auxiliary analog inputs?, N1 and N2 only., N1, N2 and Exhaust Gas Temperature., N1, N2 and engine vibration., Why does the N1 speed sensor contain three electrically isolated sensing elements rather than a single common output?, One element supplies the Display Processing Computers and the other two independently supply Electronic Engine Control channels A and B., One element measures fan speed, one measures Low Pressure Turbine speed, and one provides vibration phase information., Two elements supply the Electronic Engine Controls while the third is reserved exclusively for fan trim balance calculations., Which additional function distinguishes the N2 speed sensor from the N1 speed sensor in the engine indicating system?, The N2 signal is also used for engine overspeed detection., The N2 signal is also used for fan trim balance calculations., The N2 signal is also used as the primary input for Exhaust Gas Temperature averaging., The commanded N1 is greater than the actual N1. How is this shown on the Engine Indication display?, The commanded N1 appears at the lower edge of the command sector., The commanded N1 appears at the upper edge of the command sector., The N1 reference bug replaces the command sector until actual N1 reaches the target., An N2 redline exceedance occurred during the previous engine operation. After N2 falls back below the redline during operation, what happens to the normal flight-deck indication?, The N2 indications remain red continuously until maintenance resets the exceedance., The indications return to their normal colour, but the red exceedance box becomes apparent after both engines are shut down., The N2 indication changes to amber until the next successful engine start., During cruise, actual fuel flow differs from the Flight Management Computer expected fuel flow beyond the applicable threshold for more than five minutes. What indication is expected?, A FUEL FLOW alert flashes for 10 seconds and then remains steady., A THRUST alert flashes until the expected and actual fuel flows agree., An ENG FAIL message appears on the Exhaust Gas Temperature display., During takeoff, Exhaust Gas Temperature rises above the normal maximum continuous limit but remains below the redline. Why might the normal amber colour change not appear immediately?, The amber caution-range colour change is inhibited for up to five minutes during takeoff., The maximum continuous limit is automatically increased to the redline during every takeoff., The Display Processing Computers suppress all Exhaust Gas Temperature colour changes until climb thrust is selected., What is the maintenance value of Exhaust Gas Temperature margin rather than simply monitoring the highest Exhaust Gas Temperature reached during takeoff?, It indicates the difference between maximum permitted Exhaust Gas Temperature and the highest takeoff Exhaust Gas Temperature, providing an indication of engine performance deterioration., It identifies the difference between the two Electronic Engine Control channel temperature calculations and therefore detects sensor disagreement., It shows the difference between start redline and maximum continuous Exhaust Gas Temperature and is used primarily for hot-start detection., The Airborne Vibration Monitoring system cannot determine whether the N1 or N2 vibration component is dominant. What type of vibration information is sent for display?, The vibration indication is removed because rotor identification is required before any value can be displayed., Broadband vibration is displayed as an indication of unfiltered overall engine vibration., The system displays the average of the N1 and N2 narrow-band vibration values., A high vibration level greater than 4.0 Cockpit Units occurs during a ground engine start while the rotor is passing through a bowed-rotor condition. What is the expected alert behaviour?, The high-vibration alert is inhibited during the ground start and becomes available again after the engine reaches idle., The alert appears immediately because any vibration above 4.0 Cockpit Units requires crew action., The vibration indication is removed completely until N2 reaches idle.

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