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PC 12 > Limitations > Flashcards

Limitations Flashcards

1
Q

Maximum Demonstrated Crosswind

Flaps 0

PlaneSense imposes a crosswind limitation
equal to the Maximum Demonstrated
Crosswind component of a dry runway. Steady
state values are used, excluding the gust factor

A

30

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2
Q

Maximum Demonstrated Crosswind

Flaps 15

PlaneSense imposes a crosswind limitation
equal to the Maximum Demonstrated
Crosswind component of a dry runway. Steady
state values are used, excluding the gust factor

A

25

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3
Q

Maximum Demonstrated Crosswind

Flaps 30

PlaneSense imposes a crosswind limitation
equal to the Maximum Demonstrated
Crosswind component of a dry runway. Steady
state values are used, excluding the gust factor

A

20

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4
Q

Maximum Demonstrated Crosswind

Flaps 40

PlaneSense imposes a crosswind limitation
equal to the Maximum Demonstrated
Crosswind component of a dry runway. Steady
state values are used, excluding the gust factor

A

15

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5
Q

Maximum Demonstrated Crosswind

Flaps 0

(When Braking Action is reported less than Good (either Medium or
Poor), a limitation of 50% of the dry runway maximum demonstrated
crosswind component will be used

A

15

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6
Q

Maximum Demonstrated Crosswind

Flaps 15

(When Braking Action is reported less than Good (either Medium or
Poor), a limitation of 50% of the dry runway maximum demonstrated
crosswind component will be used

A

12.5

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7
Q

Maximum Demonstrated Crosswind

Flaps 30

(When Braking Action is reported less than Good (either Medium or
Poor), a limitation of 50% of the dry runway maximum demonstrated
crosswind component will be used

A

10

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8
Q

Maximum Demonstrated Crosswind

Flaps 0

(When Braking Action is reported less than Good (either Medium or
Poor), a limitation of 50% of the dry runway maximum demonstrated
crosswind component will be used

A

7.5

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9
Q

Flap Cycle Limitations

-55 to 25 Celsius

A flap cycle is defined as any movement that starts
at 0 and ends at 0

In the event of a balked landing or go around with
residual ice on the airframe, flaps should not be
retracted from 15

A

10 Cycles Per Hour

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10
Q

Flap Cycle Limitations

25 to 50 Celsius

A flap cycle is defined as any movement that starts
at 0 and ends at 0

In the event of a balked landing or go around with
residual ice on the airframe, flaps should not be
retracted from 15

A

8 Cycles Per Hour

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11
Q

Weight Limitations

Maximum Ramp Weight

A

10,495 pounds

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12
Q

Weight Limitations

Maximum Takeoff Weight

A

10,450 pounds

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13
Q

Weight Limitations

Maximum Landing Weight

A

9,921 pounds

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14
Q

Weight Limitations

Maximum Zero Fuel Weight

A

9,039 pounds

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15
Q

Weight Limitations

Maximum Baggage Weight

A

400 pounds

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16
Q

Altitude & Temperature Limitations

Maximum Operating Altitude

A

30,000 ft

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17
Q

Altitude & Temperature Limitations

Minimum Aircraft Operating Temperature

A

-55 Celsius

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18
Q

Altitude & Temperature Limitations

Maximum Aircraft Operating Temperature

A

50 Celsius

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19
Q

Altitude & Temperature Limitations

Minimum Boot Operating Temperature

A

-40 Celsius

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20
Q

Altitude & Temperature Limitations

Maximum Boot Operating Temperature

A

40 Celsius

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21
Q

Engine Starting Limitations

Minimum Voltage to Start on Battery

A

24 Volts

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22
Q

Engine Starting Limitations

Minimum Voltage in which a GPU may be used

A

20 Volts

23
Q

Engine Starting Limitations

Voltage at which no Battery or GPU Start

A

Less than 20 Volts

24
Q

Engine Starting Limitations

Maximum ITT (Turbine Temperature)

A

150 Celsius

25
Q

Engine Starting Limitations

Up to 850 Celsius

A

No Limit

26
Q

Engine Starting Limitations

Time Limit 850 to 870 Celsius

A

20 Seconds

27
Q

Engine Starting Limitations

Time Limit 870° to 1000°
Celsius

A

5 Seconds

28
Q

Engine Starting Limitations

Over 1000°
Celsius

A

Hot Start

29
Q

Engine Takeoff Limitations

Shaft Horsepower

Takeoff ITT is limited to the first 5 minutes of flight.

During steady state operation, a variation of
30 RPM is permitted.

During ground operations, propeller may not be operated between 350 –
950 RPM

A

1200 HP

30
Q

Engine Takeoff Limitations

Torque

Takeoff ITT is limited to the first 5 minutes of flight.

During steady state operation, a variation of
30 RPM is permitted.

During ground operations, propeller may not be operated between 350 –
950 RPM

A

44.34 PSI

31
Q

Engine Takeoff Limitations

ITT (Inter Turbine Temperature)

Takeoff ITT is limited to the first 5 minutes of flight.

During steady state operation, a variation of
30 RPM is permitted.

During ground operations, propeller may not be operated between 350 –
950 RPM

A

850 Celsius

32
Q

Engine Takeoff Limitations

Ng (Gas Generator Speed)

Takeoff ITT is limited to the first 5 minutes of flight.

During steady state operation, a variation of
30 RPM is permitted.

During ground operations, propeller may not be operated between 350 –
950 RPM

A

104%

33
Q

Engine Takeoff Limitations

Np (Propeller Speed)

Takeoff ITT is limited to the first 5 minutes of flight.

During steady state operation, a variation of
30 RPM is permitted.

During ground operations, propeller may not be operated between 350 –
950 RPM

A

1730 RPM

34
Q

Engine Climb Limitations

Maximum Continuous Climb Horsepower

PlaneSense imposes an ITT limitation of 780 during the climb segment.

During steady state operation, a variation of
30 RPM is permitted

A

1200 HP

35
Q

Engine Climb Limitations

Torque

PlaneSense imposes an ITT limitation of 780 during the climb segment.

During steady state operation, a variation of
30 RPM is permitted

A

44.34 PSI

36
Q

Engine Climb Limitations

ITT (Inner Turbine Temperature)

PlaneSense imposes an ITT limitation of 780 during the climb segment.

During steady state operation, a variation of
30 RPM is permitted

A

820 Celsius

37
Q

Engine Climb Limitations

Ng (Gas Generator Speed)

PlaneSense imposes an ITT limitation of 780 during the climb segment.

During steady state operation, a variation of
30 RPM is permitted

A

104%

38
Q

Engine Climb Limitations

Np (Propeller Speed)

PlaneSense imposes an ITT limitation of 780 during the climb segment.

During steady state operation, a variation of
30 RPM is permitted

A

1700 RPM

39
Q

Engine Cruise Limitations

Maximum Continuous Cruise Horsepower

PlaneSense imposes
an ITT limitation of 820 Celsius during the cruise segment.

During steady state operation, a variation of
30 RPM is permitted.

A

1000 HP

40
Q

Engine Cruise Limitations

Torque

PlaneSense imposes
an ITT limitation of 820 Celsius during the cruise segment.

During steady state operation, a variation of
30 RPM is permitted.

A

36.9 PSI

41
Q

Engine Cruise Limitations

ITT (Inter Turbine Temperature)

PlaneSense imposes
an ITT limitation of 820 Celsius during the cruise segment.

During steady state operation, a variation of
30 RPM is permitted.

A

820 Celsius

42
Q

Engine Cruise Limitations

Ng (Gas Generator Speed)

PlaneSense imposes
an ITT limitation of 820 Celsius during the cruise segment.

During steady state operation, a variation of
30 RPM is permitted.

A

104%

43
Q

Engine Cruise Limitations

Np (Propeller Speed)

PlaneSense imposes
an ITT limitation of 820 Celsius during the cruise segment.

During steady state operation, a variation of
30 RPM is permitted.

A

1700 RPM

44
Q

Engine Transient Limitations

Torque

Transient is defined as 20 seconds

A

61.0 PSI

45
Q

Engine Transient Limitations

ITT (Inter Turbine Temperature)

Transient is defined as 20 seconds

A

870 Celsius

46
Q

Np (Propeller Speed)

Transient is defined as 20 seconds

A

1870 RPM

47
Q

Engine Reverse Limitations

Maximum Reverse Horsepower

A

900 HP

48
Q

Engine Reverse Limitations

Torque

A

43.25 PSI

49
Q

Engine Reverse Limitations

ITT (Inter Turbine Temperature)

A

760 PSI

50
Q

Engine Reverse Limitations

Np (Propeller Speed)

A

1650 RPM

51
Q

Fuel Limitations

Total Fuel Capacity

PlaneSense requires that the anti-icing additive Prist beadded every time the aircraft is fueled

A

406.8 Gal

52
Q

Fuel Limitations

Total Useable Fuel

PlaneSense requires that the anti-icing additive Prist beadded every time the aircraft is fueled

A

402 Gal

53
Q

Fuel Limitations

Total Unusable Fuel

PlaneSense requires that the anti-icing additive Prist beadded every time the aircraft is fueled

A

4.8 Gal

54
Q

Fuel Limitations

Fuel Types Allowed

PlaneSense requires that the anti-icing additive Prist beadded every time the aircraft is fueled

A

Jet A
Jet A-1
Jet B
JP-4

PC 12 (2 decks)

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