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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

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
Engine Starting Limitations Up to 850 Celsius
No Limit
26
Engine Starting Limitations Time Limit 850 to 870 Celsius
20 Seconds
27
Engine Starting Limitations Time Limit 870° to 1000° Celsius
5 Seconds
28
Engine Starting Limitations Over 1000° Celsius
Hot Start
29
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
1200 HP
30
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
44.34 PSI
31
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
850 Celsius
32
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
104%
33
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
1730 RPM
34
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
1200 HP
35
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
44.34 PSI
36
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
820 Celsius
37
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
104%
38
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
1700 RPM
39
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.
1000 HP
40
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.
36.9 PSI
41
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.
820 Celsius
42
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.
104%
43
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.
1700 RPM
44
Engine Transient Limitations Torque Transient is defined as 20 seconds
61.0 PSI
45
Engine Transient Limitations ITT (Inter Turbine Temperature) Transient is defined as 20 seconds
870 Celsius
46
Np (Propeller Speed) Transient is defined as 20 seconds
1870 RPM
47
Engine Reverse Limitations Maximum Reverse Horsepower
900 HP
48
Engine Reverse Limitations Torque
43.25 PSI
49
Engine Reverse Limitations ITT (Inter Turbine Temperature)
760 PSI
50
Engine Reverse Limitations Np (Propeller Speed)
1650 RPM
51
Fuel Limitations Total Fuel Capacity PlaneSense requires that the anti-icing additive Prist beadded every time the aircraft is fueled
406.8 Gal
52
Fuel Limitations Total Useable Fuel PlaneSense requires that the anti-icing additive Prist beadded every time the aircraft is fueled
402 Gal
53
Fuel Limitations Total Unusable Fuel PlaneSense requires that the anti-icing additive Prist beadded every time the aircraft is fueled
4.8 Gal
54
Fuel Limitations Fuel Types Allowed PlaneSense requires that the anti-icing additive Prist beadded every time the aircraft is fueled
Jet A Jet A-1 Jet B JP-4

PC 12 (2 decks)

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