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T-45 > NATOPS CB > Flashcards

NATOPS CB Flashcards

1
Q

Thrust Produced by the F405-RR-401 engine

A

5,527lbs

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2
Q

The BIT display will automatically display upon system power-up. T/F?

A

False

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3
Q

The ___________ is the only portion of the aircraft protected from icing by ducted engine air.

A

The Fan Spinner

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4
Q

The starter is inhibited from cranking the engine above _____%.

A

20%

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5
Q

During engine start the GTS auto shuts down at approx ________% RPM.

A

45%

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6
Q

GTS Duty Interval

A

3min x 3 then 30min

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7
Q

Ingniters On Post GTS Start Button pressed

Weight on Wheels __________
Weight Off Wheels __________

A

WonW: Immediately
WoffW: 30”

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8
Q

Ignition is inhibited when the throttle is advanced past the IDLE position. T/F?

A

False

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9
Q

Yaw dampening function is active at all airspeeds

A

False

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10
Q

The Generator automatically after an AirStart. T/F?

A

False

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11
Q

External electrical power, when used during ground starting, is automatically cut off when the engine reaches 45 percent rpm.

A

True

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12
Q

If both inverters FAIL, the standby attitude indicator becomes the primary attitude instrument. T/F?

A

False

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13
Q

A hand pump is provided to charge the wheel brake accumulator prior to aircraft towing.
True or False

A

True

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14
Q

The HYD FAIL warning light illuminates when HYD 1 and 2 systems drop below 600 psi.
True or False

A

False

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15
Q

Protection circuits within the starting system automatically shut down the GTS if GTS idle speed is not achieved within 30 seconds after the GTS start button is pressed.
True or False

A

True

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16
Q
  1. After start, the closure of the bleed valve is indicated by an approximate 3 percent increase of N2 idle rpm and a 50 °C drop in EGT.
    True or False
A

True

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17
Q

During an airstart using manual fuel control, after the GTS start button is released, the bleed valve remains open for 60 seconds.
True or False

A

True

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18
Q

Manual fuel control, when selected, will provide for automatic fuel scheduling during an airstart.
True or False

A

False

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19
Q

The FIRE warning light illuminates if the engine firewire reaches 300 °C.
True or False

A

True

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20
Q

If flap/slat selection disagrees between the forward and aft cockpit, the flaps/slats will move to the most extended position.
True or False
Mechanically linked

A

False

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21
Q

Following a generator failure the right MFD drops off line and the left MFD shows the ADI display. This is normal.
True or False

A

True

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22
Q

Emergency hydraulic pressure prevents raising the landing gear handle with weight-on-wheels.
True or False

A

False

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23
Q

If the SKID caution light illuminates in flight, the following procedure should be used:
a. Turn anti-skid off.
b. Use normal braking techniques.
True or False

A

False

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24
Q

The launch bar will not extend if the nose wheel angle is greater than 30 degrees from center.
True or False

A

False

25
Q

If the fire warning lights extinguish due to a temperature decrease, an automatic reset may take 45 seconds.
True or False

A

True

26
Q

To ensure there is enough pressure to reset the RAT shuttle valve, the engine rpm should be above 76 percent.
True or False

A

False

27
Q

The HYD caution light illuminates when either HYD 1 or HYD 2 pressure drops below 1,660 ± 110 psi.
True or False

A

True

28
Q

The nominal flap positions are approximately 50 degrees at full down and 25 degrees at 1/2.
True or False

A

True

29
Q

A SP BRK advisory light illuminates when the speed brakes are not fully retracted.
True or False

A

True

30
Q

IFF Mode C altitude reporting works off the forward cockpit altimeter.
True or False

A

True

31
Q

During the VOR/ILS system BIT check, the VOR bearing pointer indicates 90 degrees; VOR/ILS system requires service.
True or False

A

True

32
Q

After pressing the TEST button for 5 seconds during a TACAN BIT check, you observe the following:
a. HSI TACAN bearing pointer indicates 180 ± 2.5 degrees.
b. HSI TACAN range reads 0±1 nm.
c. CDI bar centered.

The TACAN system requires service. T/F?

A

False

33
Q

If cockpit pressure is lost, a warning is provided when the cockpit altitude exceeds 24,500 ±500 feet.
True or False

A

True

34
Q

Pressing the ADR pushbutton initiates a 10-second parameter record.
True or False

A

True

35
Q

On the ground (weight-on-wheels), inadvertently moving the landing gear handle from DN to UP will cause the landing gear to retract.
True or False

A

False

36
Q

The FUEL caution light illuminates when the usable fuel remaining is less than approximately 350 pounds.
True or False

A

True

37
Q

The speed brakes may not extend fully above 340 knots.
True or False

A

True

38
Q

In the event of a HYD 1 system failure, power to the flaps is available from the wheel brake/emergency flap accumulator.
True or False

A

True

39
Q

A valid BIT check for the VOR/ILS is as follows:
a. The VOR bearing pointer indicates 315 ±3.0 degrees.
b. The course deviation line moves to the left 2 dots maximum.
c. The marker beacon lights illuminate.
True or False

A

True

40
Q

The engine bleed valve is:

A

Open during engine starting to prevent N2 compressor stalling.

41
Q

Operation of the emergency jettison switch is inhibited by:

A

Weight-on-wheels.

42
Q

NWS is ______ controlled and ________ operated.

A

Electrically / hydraulically

43
Q

Select all that apply. In flight, the FIRE light illuminates but then goes out. What indications would verify that you do have an engine fire?

A

a. EGT indicates 710 °C and TP HOT caution light is on.
b. EGT/RPM warning light is on and HYD 1 caution is on.

44
Q

The major components of the display system consist of.

A

FOUR MFDs, a DEU, TWO DEPs, and a HUD

45
Q

IFF MODE C coded transmissions contai

A

Altitude information from the main altimeter in the fwd cockpit.

46
Q

You are starting the engine and the rpm has stabilized. You advance the throttle through 65 percent and return it to IDLE. Checking your rpm and EGT, you find that they have not changed from their original position. What malfunction would give you these indications?

A

Bleed valve failure.

47
Q

Anti-Skid deactivates

A

Decelerating through 13-10 kts

48
Q

while in manual fuel control is that when in manual fuel control,

A

Throttle movements must be made judiciously.

49
Q

The OBOGS heat exchanger:

A

Reduces the temperature of engine bleed air.

50
Q

Select all that apply. Under what conditions may a safe ejection be initiated?

A
  • Canopy closed and locked.
  • After MDC firing handle shatters canopy.
51
Q

Select all that apply. When the eject mode selector is set in the FWD-BOTH/AFT SELF position and the forward seat initiates ejection:

A

a. The aft seat fires first.
b. Both cockpits fire.

52
Q

The Display Electronics Unit (DEU) acts as a ___________ computer.

A

display and mission

53
Q

During a high altitude ejection, which of the following occurs immediately after the drogue chute is deployed?

A

a. The seat is stabilized by the drogue during descent.

54
Q

The LP fuel pump is powered by the:

A

Engine-driven gearbox.

55
Q

While starting the engine, you receive no rise in EGT within 15 seconds after advancing the throttle, and the plane captain is pinching their nose and pointing at the tail pipe. What malfunction are you experiencing?

A

Wet start

56
Q

HEFOE

A
  1. HYDRAULIC SYSTEM
  2. _ELECTRICAL SYSTEM
  3. _FUEL SYSTEM______
  4. _OXYGEN SYSTEM_____
  5. _ENGINE______________
57
Q

The four basic steps of preparation for thunderstorm penetration are

A

HEAT
AIRSPEED/ATTITUDE
LIGHT
TIGHT

58
Q

Max EGT Limits
MRT ______
Trans _____
Contin ____

A

MRT: 610
Trans: 645
Cont: 550

59
Q

Max RPM Limits:
MRT _____
Trans ____
Cont _____

A

MRT: 104
Trans: 106
Cont: 100

T-45 (5 decks)

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