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B1900 Technical Exam > 1900 Tech Exam > Flashcards

1900 Tech Exam Flashcards

1
Q

Maximum ITT for takeoff is

A

800 degrees for 5 minutes.

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2
Q

Minimum battery voltage for an external power start is

A

20 VDC.

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3
Q

In cruise flight at 3200 ft/lbs and 1550 RPM a propeller lever cable break will result in

A

the propeller governing at 1700 RPM.

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4
Q

During an engine start if no ITT is observed

A

a clearing start is required.

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5
Q

With respect to certification, the maximum landing weight may be limited by

A

brake energy.

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6
Q

Moving the pressurization switch to the dump position does what?

A

It energizes the dump solenoid and de-energizes the ram air vent lock, to allow vacuum air to open the valve.

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7
Q

Engine anti ice is required

A

before entering visible moisture with an OAT of 10 degrees Celsius or less.

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8
Q

Asymmetric flap protection is provided by

A

a switch between adjacent flap segments.

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9
Q

Maximum pressure differential is

A

5.0 to 5.2 psi.

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10
Q

The landing gear safety switch

A

interrupts power to the landing gear motor on the ground.

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11
Q

The vacuum/pneumatic system is driven by

A

P3 air from the compressor regulated to 18 psi.

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12
Q

When the engine auto ignition is armed the

A

igniters operate when torque falls below 750 ft/lbs.

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13
Q

After starting the engine, the condition lever should be moved to high,

A

after the engine has stabilized and N1 is 65%.

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14
Q

With the gen ties switch in NORM,

A

both ties close when the line contactor closes.

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15
Q

The ram vent air is

A

available only when the dump solenoid is engaged.

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16
Q

The minimum N1 allowed for putting a generator online is

A

72%.

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17
Q

Annunciators associated with a loss of power to the left generator bus are,

A

L DC GEN, L GEN TIE OPEN and

R ENVIRO FAIL.

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18
Q

Va is

A

178 knots.

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19
Q

The primary governor’s operating range is

A

1200-1700 RPM.

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20
Q

The stand by boost pump is energized

A

when the IGNITION AND ENGINE START switches are in the ON position and/or fuel is being transferred.

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21
Q

If the engine driven high pressure fuel pump fails

A

the engine will fail.

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22
Q

The fuel topping governor

A

utilizes inputs from fly weights and pneumatic bellows to meter fuel.

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23
Q

With an oil pressure indication of less than 90 psi

A

a maximum torques of 2000 ft/lbs must be observed.

24
Q

ITT limits for engine start are

A

not more than 870-1000 degrees for more than 5 seconds.

25
Q

Failure of the stand by pump results in

A

a loss of fuel transfer capability.

26
Q

26) The R ENVIR FAIL annunciator illuminated means

A

the pre cooler and shut off valve regulator valves are closed and the switch is OPEN.

27
Q

27) Vacuum for the wing de ice system is provided by

A

a bleed air ejector.

28
Q

28) Maximum N1 for the PT6-67D is

A

104%.

29
Q

29) The engine intake lip is heated

A

continuously by exhaust air.

30
Q

With 17,000 set on the aircraft scale of the pressure controller, you begin a descent to 15,000 feet.

A

The cabin differential will decrease.

31
Q

Fault protection for the triple fed bus is provided by

A

three 60 amp current limiters.

32
Q

Min Flow is

A

50% N1.

33
Q

The fuel control units receive inputs from

A

a pneumatic bellows, N1 governor, the power lever and the condition lever.

34
Q

A completely blank or black EFIS tube is most likely

A

a failure of the tube.

35
Q

When the IGNITION AND ENGINE START switches are in the full ON position

A

the starter turns the engine, the ignitors are on and the stand by pump is on.

36
Q

The starter limits are

A

20 seconds on, 30 seconds off, 20 seconds on, 60 seconds off, 20 seconds on, 5 minutes off.

37
Q

After a failure of the triple fed bus

A

the pilot will notice that COM 1 and the engine instruments will lose power

38
Q

) A vacuum source failure will be indicated by

A

zero or very low suction, and a pressurization loss/cabin descent.

39
Q

The 0 flap Vref at 14,000 lbs is

A

124 knots

40
Q

The HED’s protect their respective buses by

A

opening its associated bus tie if excessive current is sensed.

41
Q

The L DC GEN annunciator will illuminate when

A

the line contactor is open and the starter switch is in the STARTER ONLY position.

42
Q

The balked landing climb gradient is

A

3.3%

43
Q

A compressor bleed valve that is stuck open will result in

A

high ITT and low torque.

44
Q

A wet runway

A

has no effect on V1 for the Beech 1900

45
Q

The hydraulic power pack shuts off

A

during gear extension when the 3 actuator down lock pins are engaged or the 16 second switch is energized.

46
Q

With the landing gear up

A

the hydraulic power pack comes on at 2320 psi and cuts out when the pressure switch detects 2775 psi or the timer switch hits 16 seconds.

47
Q

For the MAN COOL mode to function,

A

the ACM bypass valve must be closed and the OAT must be 45 degrees Fahrenheit or greater

48
Q

A XDTA annunciator on the first officer’s side means

A

the f/o can not receive data from the captains side.

49
Q

Placing bleed air switches in the ENVIR OFF position

A

de-energizes the enviro valves closed but the pneumatic valve stays open.

50
Q

A squat switch

A

energizes the dump solenoid open and prevents aircraft pressurization on the ground.

51
Q

While taxiing, the firewall fuel valve light comes on

A

The pilots should visually confirm the fire, and then blow the extinguisher bottle.

52
Q

The hydraulic accumulator

A

assists in maintaining system pressure to hold the landing gear up

53
Q

A squat switch

A

energizes the dump solenoid open and prevents aircraft pressurization on the ground.

54
Q

While taxiing, the firewall fuel valve light comes on

A

The pilots should visually confirm the fire, and then blow the extinguisher bottle.

55
Q

The hydraulic accumulator

A

assists in maintaining system pressure to hold the landing gear up

B1900 Technical Exam (1 decks)

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