Closed Book Flashcards

1
Q

____altitude is the altitude at which 100% torque is no longer available

A

Critical

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2
Q

(T/F) Although there is no limit for operation at maximum continuous power, sustained operation at maximum power may significantly reduce engine service life.

A

True

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3
Q

Maximum _______ speed is the maximum speed at which an abort may be started and the aircraft stopped within the remaining runway length.

A

Abort

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4
Q

Increase takeoff speeds by ____% of the gust increment up to a maximum of 10 knots.

A

50%

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5
Q

The engine has been flat-rated to produce _______ shaft horsepower.

A

1100

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6
Q

The SCU will activate the red Oil PX annunciator if oil pressure falls below ____ psi when the engine is above ____ idle power.

A

40 / Idle

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7
Q

The SCU will activate the OIL PX annunciator if the oil pressure drops below ___ psi at idle power.

A

15

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8
Q

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

NORM

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9
Q

(T/F) When the ignition control toggle switch is set to ON, or when the igniters are activated in the AUTO mode, a green IGN SEL annunciator is illuminated.

A

True

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10
Q

Power for the starter control (START) is provided through the ____ bus.

A

Battery

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11
Q

Power for the ignition system (IGN) is provided through the ____ bus.

A

Battery

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12
Q

The chip detector is mounted in the ____ to detect metal contamination in the oil.

A

RGB

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13
Q

The ____ and the ____ automatically control the propeller blade angle (pitch) and propeller speed (Np).

A

PMU, PIU

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14
Q

The propeller system is designed to maintain a constant speed of _____ rpm (100% Np) during most flight conditions.

A

2000

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15
Q

(T/F) With the PMU not functioning, Np may peak above 100% during power changes and then return to the governed range.

A

True

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16
Q

The PMU provides two operating modes, ground and flight, which are controlled by the ____.

A

Weight-on-wheels switch on the main landing gear struts

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17
Q

In the ground mode, the engine idle N1 is ____% and in the flight mode, idle is normally ____%.

A

60, 67

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18
Q

illumination of both the ____ and ____ annunciators indicates the system is in the manual mode.

A

PMU FAIL, PMU STATUS

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19
Q

(T/F) Engine starts are recommended with the PMU in the manual mode.

A

False

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20
Q

A PMU STATUS light in flight indicates

A

Weight-on-wheels switch fault and/or mismatch

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21
Q

The PMU is normally powered by ____.

A

PMA

22
Q

During inverted flight, the inverted flight fuel pickup provides ____ of fuel supply, and prevents air ingestion into the fuel system.

A

Min of 15 seconds

23
Q

(T/F) When correcting a fuel imbalance, set the MANUAL FUEL BAL switch to whichever wing tank is “lighter”.

A

True

24
Q

If a fuel probe fails, ____ will continue to provide an accurate indication of minimum fuel level.

A

the low fuel warning lights

25
Q

If the hydraulic pressure in the emergency accumulator drops below ____ psi, an amber EHYD PX LO annunciator will illuminate.

A

2400 (+/- 150)

26
Q

A normal gear extension/retraction sequence takes approximately ____ seconds.

A

6

27
Q

(T/F) Pulling the emergency landing gear extension handle will extend the gear and flaps.

A

False

28
Q

Normal cockpit indications when the emergency extension system is used are:

A

three green gear lights

red main gear lights, red light in the gear handle

29
Q

The wheel brake system ____ affected by a failure of the aircraft hydraulic system.

A

is not

30
Q

Normal flap operation and indications are 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

A

D. either a or b

31
Q

The trim system control circuits give ____ priority if trim selection conflicts between cockpits.

A

the rear cockpit

32
Q

The ____ senses torque, altitude, airspeed, and pitch rate and computes a desired rudder trim tab position.

A

TAD

33
Q

If the hydraulic reservoir fluid level indicator shows in the area labeled FULL AC or FULL AD:

A

the system is fully serviced

34
Q

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

35
Q

To preclude unnecessary wear to nose wheel steering and tire, ____ nose wheel steering prior to executing sharp turns with differential braking.

A

disengage

36
Q

Any fault discovered during the ____ check is reason for a ground abort.

A

OVERSPEED GOVERNOR

37
Q

Do not delay ejection while attempting airstart below ____ feet AGL.

A

2000

38
Q

If an airstart is successful, useful power will be available after approximately ____ seconds from starter engagement.

A

40

39
Q

The emergency oxygen bottle provides approximately ____ minutes of oxygen.

A

10

40
Q

Illumination of the L FUEL LO annunciator indicates that approximately ____ pounds of usable fuel remains in the left wing tank.

A

110

41
Q

Recommend minimum altitudes for ejection are ____ feet AGL for controlled ejection, and ____ feet AGL for uncontrolled ejection.

A

2000, 6000

42
Q

Maximum oil pressure during start is ____ psi.

A

200

43
Q

Do not connect external power if the battery voltage is below ____ volts.

A

22

44
Q

Maximum airspeed for flying through turbulence is ____ KIAS.

A

207

45
Q

The maximum permissible crosswind for a wet runway is ____ knots.

A

10

46
Q

Taxi over arresting cables at ____. Steer to avoid nose and main gear contact with cable support donuts.

A

as slow as possible

47
Q

The canopy shall not be opened in the ground when the surface winds exceed ____ knots.

A

40

48
Q

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

A

D. b and c above

49
Q

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

50
Q

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