FLIGHT ENGINEER PRACTICE EXAM

Click the appropriate answer and at the end of your exam click on the done button.

724 "IN ORDER TO OPTIMIZE RANGE WITH A PROPELLER THAT IS PITCHLOCKED AT A LOWER BLADE ANGLE, THE AIRCRAFT SHOULD BE FLOWN AT AIRSPEEDS APPROXIMATING MAXIMUM ENDURANCE. THAT IS….."
12 UNITS AOA or 1.52 Vs
16 UNITS AOA or 1.52 Vs
12 UNITS AOA or 1.2 Vs
9 UNITS AOA or 1.2 Vs

204 THE APU FIRE DETECTION SYSTEM IS POWERED BY THE:
MEDC BUS.
MDC BUS.
APU ESS BUS.
GOB BUS.

589 THE ENGINE HAS A FRICTION-CONE TYPE PROPELLER BRAKE WHICH OPERATES AUTOMATICALLY AND:
IS ALWAYS LOCKED WHEN THE ENGINE IS NOT RUNNING.
IS HELD RELEASED BY PROPELLER CONTROLING OIL PRESSURE ABOVE 21% RPM.
REMAINS IN THE APPLIED POSITION UNTIL RPM REACHES 21% DURING AN INFLIGHT RESTART.
ALL OF THE ABOVE

616 "IN FLIGHT, THE PROPELLER SHOULD NOT BE ALLOWED TO ROTATE UNNECESSARILY BELOW 21% RPM FOR EXTENDED PERIODS BECAUSE:"
SEVERE BUFFETING WILL OCCUR.
EXCESSIVE OIL MAY BE LOST FROM THE ENGINE LAB SEALS.
THE GENERATOR WILL NOT RECEIVE SUFFICENT COOLING AIR.
DAMAGE TO THE PROPELLER BRAKE CAN RESULT.

480 THE MAXIMUM CONTINUOUS EXHAUST TEMPERATURE FOR THE GTCP95-3 APU IS:
704 DEGREES C
649 DEGREES C
688 DEGREES C
715 DEGREES C

578 THE ENGINE ANTI-ICING SOLENOID VALVE:
MUST RECEIVE POWER FROM THE MON ESSENTIAL DC BUS TO ALLOW ANTI-ICING AIR FLOW TO THE ENGINE.
IS SPRING LOADED OPEN SO AS TO ENSURE ANTI-ICING AIR FLOW IN THE EVENT ELECTRICAL POWER IS LOST.
MODULATES 14TH STAGE AIR TO THE INLET SCOOP TO MAINTAIN THE PROPER DEICING TEMP.
MODULATES 5TH AND 10TH STAGE AIR TO THE SCOOP FOR DEICING.

25 THE RADOME EXTENSION AND RETRACTION CIRCUITS ARE CONTROLLED BY THE ______ BUS.
EMDC
SEDC
MDC
NONE OF THE ABOVE

628 "WITH A LOSS OF MON ESS DC, WHICH PROPELLERS WILL FULLY FEATHER ELECTRICALLY WHEN THE E-HANDLE IS PULLED?"
ALL
ONLY 2 OR 3
ONLY 3
NONE

289 "WITH THE NO.2 ENGINE IN NORMAL RPM, YOU SHIFT DOWN ENGINES NO.1, 3 AND 4 AND LOSE MAIN AC BUS B. THE PROBABLE CAUSE WOULD BE:"
TRANSFER RELAY NO.6 FAILURE
GENERATOR NO.4 CONTROL AUX. RELAY DE-ENERGIZED
GENERATOR NO.4 AUXILARY CONTROL CIRCUIT BREAKER OUT
"TRANSFER RELAY NO.4 FAILURE, NOT ALLOWING GENERATORS NO.2 AND 3 TO BACK EACH OTHER UP"

491 "ON TAKEOFF POWER APPLICATION, THE RPM OF NO.1 ENGINE OVERSHOOTS TO 107% AND IMMEDIATELY RETURNS TO 100%, WHAT ACTION IS REQUIRED?"
FEATHER AND ABORT THE TAKEOFF.
ABORT FOR MAINTENANCE ACTION.
CONTINUE THE TAKEOFF.
CONTINUE THE TAKEOFF BUT MAINTENANCE ACTION IS REQUIRED PRIOR TO THE NEXT FLIGHT.