T-6B Closed Book MQF Flashcards
____altitude is the altitude at which 100% torque is no longer available.
A. Maximum
B. Minimum
C. Critical
D. Flight
C. Critical
Although there is no limit for operation at maximum continuous power, sustained operation at maximum power may significantly reduce engine service life.
A. True
B. False
A. True
Maximum _______ speed is the maximum speed at which an abort may be started and the aircraft stopped within the remaining runway length.
A. Braking
B. Abort
C. Engine failure
D. Rotation
B. Abort
Increase takeoff speeds by ____% of the gust increment up to a maximum of 10 knots.
A. 25
B. 50
C. 75
D. 100
B. 50
The engine has been flat rated to produce _______ shaft horsepower.
A. 900
B. 1100
C. 1300
D. 1500
B. 1100
The sight glass is ___ to be used for checking oil level; only the ___ is to be used for correct indication of oil level in the tank.
A. required, sight glass
B. authorized, low oil px light
C. not, dipstick
D. not, low oil px light
C. not, dipstick
The SCU activates the red OIL PX warning if oil pressure drops to ____ psi or below when above ____ power.
A. 15, IDLE
B. 15, 60%
C. 40, 60%
D. 40, IDLE
D. 40, IDLE
The SCU activates the red OIL PX warning if oil pressure drops ___ psi or below at idle power.
A. 15
B. 29
C. 40
D. 65
A. 15
9) During an auto start or normal operation with the ignition switch set to ____, the PMU will energize and de-energize the igniters as required.
A. ON
B. NORM
C. AUTO
D. AUTO/RESET
B. NORM
When the IGNITION switch is set to ON or when the igniters are activated for an auto start, a green IGN SEL annunciator is illuminated.
A. True
B. False
A. True
Power for the start control is provided through a circuit breaker, placarded START, located on the ____ bus circuit breaker panel in the front cockpit.
A. battery
B. generator
C. aux battery
D. AC
A. battery
Power for the ignition system is provided through a circuit breaker, placarded IGN, located on the ____ bus circuit breaker panel in the front cockpit.
A. battery
B. generator
C. aux batter
D. AC
A. battery
A chip detector is mounted in the ____ to detect ferrous material in the oil.
A. RGB
B. PCL
C. PMU
D. PIU
A. RGB
The ____ and the ____ automatically control the propeller blade angle (pitch) and propeller speed (NP).
A. RGB, PMU
B. PMU, PCL
C. PMU, PIU
D. PCL, PIU
C. PMU, PIU
The propeller system is designed to maintain a constant speed of _____ rpm (100% NP) during most flight conditions.
A. 30,000
B. 3000-5000
C. 2000
D. None of the above
C. 2000
If PMU function is lost or deactivated, NP may peak above 100% during power changes and then return to the governed range.
A. True
B. False
A. True
If the PCL is inadvertently moved to cutoff and the engine is shutting down, do not attempt to relight the engine by moving the PCL to idle or severe damage could occur to the engine
A. True
B. False
A. True
The PMU operates in either flight or ground mode. The aircraft _____ control these modes.
A. radar altimeter
B. PCL position
C. Landing gear position
D. weight-on-wheels switches on the main gear struts.
D. weight-on-wheels switches on the main gear struts.
In ground mode, idle is ____% N1 and in flight mode, idle is ____% N1 (min).
A. 60, 67
B. 60-61, 67
C. 40-41, 60
D. 67, 60-61
B. 60-61, 67
Above _____ feet PA, the PMU raises N1 to maintain NP above __ % to avoid the stress on the propeller during spins.
A. 18,000, 40-50
B. 18,069, 67
C. 10,000, 80
D. None of the above
C. 10,000, 80
Illumination of both the ____ warning and ____ caution on the EICAS indicates the system is in manual mode.
A. PMU OFF, PMU FAIL
B. PMU FAIL, PMU STATUS
C. PMU OFF, PMU STATUS
D. None of the above
B. PMU FAIL, PMU STATUS
Engine starts are not recommended with the PMU in the manual mode.
A. True
B. False
A. True
A PMU STATUS caution in flight indicates:
A. Imminent engine failure
B. Weight-on-wheels switches fault and/or mismatch
C. PMU has experienced a fault not serious enough to revert to manual mode.
D. PCL retard is required
B. Weight-on-wheels switches fault and/or mismatch
24) The ______ powers the PMU when propeller RPM is above 40-50 % NP.
A. generator bus
B. permanent magnet alternator (PMA)
C. aux battery
D. battery bus
B. permanent magnet alternator (PMA)
25) If the auto balance system shuts off without reducing the fuel imbalance to ___ pounds or less, the auto balance system may be reset to provide an additional ___ minutes to balance the fuel load.
A. 20, 2
B. 50, 3
C. 110, 5
D. 30, 2
D. 30, 2
During inverted flight, a weighted rod in the pickup valve closes off the normal fuel pickup, and opens the inverted flight fuel pickup. This provides ____ of fuel regardless of orientation, and prevents air ingestion into the fuel system.
A. a minimum of 15 seconds
B. a minimum of 60 seconds
C. a maximum of 30 seconds
D. an unlimited
B. a minimum of 60 seconds
When correcting a fuel imbalance, set the MANUAL FUEL BAL switch to the low tank.
A. True
B. False
A. True
If a fuel probe fails, ____ will continue to provide an accurate indication of minimum fuel level.
A. the fuel gage
B. the auto balance
C. backup fuel indication system
D. the low fuel warning lights
D. the low fuel warning lights
The pilot applying the most pedal force determines the amount of braking being used.
A. True
B. False
A. True
If the hydraulic pressure in the emergency accumulator drops below ____ psi, an amber EHYD PX LO caution will illuminate.
A. 3000 (+/- 150)
B. 1790 (+/- 150)
C. 3250 (+/- 150)
D. 2400 (+/- 150)
D. 2400 (+/- 150)
A normal gear extension/retraction sequence takes approximately ____ seconds.
A. 5
B. 6
C. 10-15
D. 30
B. 6
Pulling the emergency landing gear extension handle will extend the gear and flaps.
A. True
B. False
B. False
Cockpit indications when the emergency extension system is used are:
A. three green gear lights
B. three red gear lights, red light in the gear handle
C. two red main gear lights, red light in the gear handle
D. A and C
D. A and C
The brake system ____ affected by a failure of the aircraft hydraulic system.
A. is
B. is not
C. could be
D. should be
B. is not
Normal flap operation and position indication is unavailable anytime:
A. the battery bus has failed
B. when the aux battery is the only source of electrical power
C. the generator bus has failed
D. either A or B
D. either A or B
The trim system control circuits give ____ priority if trim selection conflicts between cockpits.
A. the rear cockpit
B. the forward cockpit
C. the first actuation
D. whoever is in norm
A. the rear cockpit
The ____ senses engine torque, altitude, airspeed, and pitch rate, and computes a desired rudder trim tab position.
A. trim computer
B. PMU
C. TAT
D. Trim Aid Device (TAD)
D. Trim Aid Device (TAD)
If the hydraulic reservoir fluid level indicator shows in the area labeled FULL AC or FULL AD:
A. have maintenance personnel service the system
B. the system requires servicing after the flight
C. the system is fully serviced
D. get another aircraft
C. the system is fully serviced
When flying solo, failure to secure the rear seat oxygen regulator will result in the loss of ability to:
A. deactivate OBOGS from the front seat
B. activate OBOGS from the front seat
C. eject from the front seat
D. select EMER oxygen from the front seat
A. deactivate OBOGS from the front seat
To preclude unnecessary wear to nose wheel steering and tire, ____ nose wheel steering prior to executing sharp turns with differential braking.
A. disengage
B. engage
C. fully deflect
D. none of the above
A. disengage
Do not delay ejection while attempting air-start at low altitude if below ____ feet AGL.
A. 500
B. 2000
C. 6000
D. 10,000
B. 2000
If the airstart is successful, useful power will be available after ____ seconds from starter engagement.
A. 10
B. 30
C. 40
D. 60
C. 40
The emergency oxygen bottle provides approximately ____ minutes of oxygen.
A. 5
B. 10
C. 15
D. 20
B. 10
Illumination of the L or R FUEL LO caution indicates that approximately ____ pounds of usable fuel remains in the affected wing tank.
A. 150
B. 370
C. 110
D. 16
C. 110
Recommend minimum altitudes for ejection are ____ feet AGL for controlled ejection and ____ feet AGL for uncontrolled ejection.
A. 2,000, 10,000
B. 2,000, 6,000
C. 6,000, 10,000
D. None of the above
B. 2,000, 6,000
Maximum oil pressure during start is ____ psi.
A. 3
B. 45-65
C. 105
D. 200
D. 200
Do not connect external power if battery voltage is below ____ volts.
A. 20
B. 23.5
C. 28
D. 22
D. 22
Maximum airspeed for flying through turbulence is ____ KIAS.
A. 150
B. 207
C. 227
D. 316
B. 207
The maximum permissible crosswind for a wet runway is ____ knots.
A. 10
B. 15
C. 20
D. 25
A. 10
Taxi over arresting cables at ____. Steer to avoid nose and main gear contact with cable support donuts.
A. 5 knots
B. Less than 20
C. as slow a speed as possible
D. 40 knots
C. as slow a speed as possible
The canopy shall not be opened on the ground when the surface winds exceed ____ knots.
A. 17
B. 25
C. 40
D. 50
C. 40
If the flaps are set to any position other than UP, the speed brake will:
A. remain extended if already extended
B. retract if already extended
C. remain retracted if the pilot attempts to extend it after the flaps are extended
D. B and C above
D. B and C above
Best glide speed in clean configuration is approximately ____ KIAS with a sink rate of ____ feet per minute and a glide ratio of 2.0 NM/1000 feet.
A. 125, 1350
B. 105, 1350
C. 125, 2000
D. 227, 600-800
A. 125, 1350
A stick shaker, activated by the angle-of-attack system, provides artificial stall warning in each cockpit a minimum of ____ knots before the stall is reached.
A. 5
B. 10
C. 15
D. 20
A. 5
While landing gear position has little effect on the stall characteristics, extending the ____ aggravates the roll-off tendency at the stall.
A. speed brake
B. flaps
C. slats
D. student
B. flaps
Above ____ % torque, full right rudder and full right aileron may not prevent a left roll-off at stall.
A. 60
B. 6-8
C. 50
D. 33
A. 60
____ are the motions of the aircraft about one or more axes immediately following a stall and prior to the incipient spin.
A. steady-state spin
B. accelerated spin
C. post-stall gyrations
D. out of control flight
C. post-stall gyrations
A(n) ____ is characterized by oscillations in pitch, roll, and yaw attitudes and rates.
A. spiral
B. incipient spin
C. steady-state spin
D. post-stall gyrations
B. incipient spin
The incipient spin phase of the aircraft lasts approximately ____ turns.
A. 1
B. 2
C. 3
D. 4
B. 2
A spiral is a rolling and/or yawing motion of the aircraft that is often mistaken for a spin, but is not steady-steady in that airspeed is ____ through 160 KIAS and motions are oscillatory.
A. increasing
B. decreasing
C. constant
A. increasing
Spins below 10,000 feet MSL are prohibited due to high stresses on the ____ which occur during the spin maneuver with the ____.
A. PMU, PCL above idle
B. propeller, propeller RPM below 80%
C. rudder, propeller RPM below 80%
D. propeller, propeller RPM above 80%
B. propeller, propeller RPM below 80%
Ailerons have a pronounced effect on spin characteristics.
A. True
B. False
A. True
With ailerons held in the direction of spin rotation, roll and yaw become noticeably oscillatory.
A. True
B. False
A. True