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UC-12W NATOPS > Definitions > Flashcards

Definitions Flashcards

(66 cards)

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1
Q

Calibrated airspeed (CAS)

A

Indicated airspeed of an airplane corrected for position and instrument error. CAS is equal to TAS in standard atmosphere at sea level.

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2
Q

Ground Speed (GS)

A

Speed of airplane relative to the ground

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3
Q

Indicated airspeed (IAS)

A

Speed of airplane as shown on airspeed indicator when corrected for instrument error. NATOPS assumes zero error.

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4
Q

KCAS

A

Calibrated airspeed expressed in knots.

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5
Q

KIAS

A

Indicated airspeed expressed in knots

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6
Q

M

A

Mach number is ratio of true airspeed to speed of sound

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7
Q

TAS

A

True airspeed is airspeed of airplane relative to undisturbed air which is CAS corrected for altitude, temperature, and compressibility

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8
Q

V1

A

Take off decision speed

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9
Q

V2

A

Takeoff safety speed is speed at 35 ft AGL assuming engine failure at V1

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10
Q

V35

A

Take off safety speed at 35 AGL with both engines operating

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11
Q

VA

A

Manuevering speed is maximum speed at which application of full available aerodynamic control will not overstress the airplane

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12
Q

VF

A

Design flap speed is the highest speed permissible at which wing flaps maybe actuated

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13
Q

VFE

A

Maximum flap extended speed is the highest speed permissible with Wing flaps in a prescribed

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14
Q

VLE

A

Maximum landing gear extended speed is the maximum speed which an airplane can be safety flown with the Landing gear extended

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15
Q

VLO

A

Maximum landing gear operating speed is the maximum speed at which the Landing gear can be safely extended a retracted

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16
Q

VMCA

A

Air minimum control speed is the minimum flight speed at which the airplane is directionally controllable as determined in accordance with federal aviation regulations. the airplane certification conditions include one engine becoming inoperative with auto feather armed, a 5° bank towards the operative engine, takeoff power on operative engine, landing gear up, flaps in the takeoff position and most rearward CG. for some conditions of weight and altitude stall can be encountered at speeds above the VMCA as established by the certification procedure described above, in which event stall speed must be regarded as the limit of effective directional control

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17
Q

VMO/MMO

A

Maximum operating limit speed is the speed limit that may not be deliberately exceeded in normal flight operations. VMO is expressed in knots and MMO is in Mach number

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18
Q

VR

A

Rotation speed

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19
Q

VREF

A

Reference landing approach speed with the landing gear and flaps down

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20
Q

VS

A

Stalling speed or the minimum steady flight speed at which the airplane is controllable

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21
Q

VS1

A

Stalling speed or the minimum steady flight speed at which the airplane is controllable in a specific configuration

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22
Q

VSO

A

Stalling speed or the minimum steady flight speed at which the airplane is controllable in the landing configuration

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23
Q

VSSE

A

Intentional one engine in operative speed is a speed above both VMCA and stall speed selected to provide a margin of lateral and directional control when one engine is suddenly rendered inoperative

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24
Q

VX

A

Best angle of climb speed is the airspeed which delivers the greatest gain of altitude in the shortest possible horizontal distance

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25
VXSE
One engine inoperative best angle of climb speed is the airspeed which delivers the greatest gain in altitude in the shortest possible horizontal distance with one engine inoperative
26
VY
Best rate of climb speed is the airspeed which delivers the greatest gain in altitude in the shortest possible time
27
VYSE
One engine inoperative best rate of climb speed - the airspeed which delivers the Greatest gain in altitude in the shortest possible time with one engine inoperative
28
Indicated pressure altitude
The number actually read from an altimeter when the barometric subscscale has been set to 29. 92 inches of mercury
29
ISA
International standard atmosphere in which 1 the air is a dry perfect gas 2 the temperature at sea level is 15°C 3 the pressure at sea level is 29.92 inches of mercury 4 the temperature gradient from sea level to the altitude it was the temperature is -56.5°C is -.00198 Celsius per foot and zero above that altitude
30
Pressure altitude
Altitude measured from standard sea level pressure altimeter. 29.92 it is the indicated pressure altitude corrected for position and instrument error
31
Temperature compressibility affects
An error in indication of temperature caused by airflow over the temperature probe
32
Beta range
The region of the power leaver control which is aft of the idle gate and forward of reversing range were blade pitch angle can be changed without a change of gas generator RPM
33
Cruise climb power
The maximum power approved for Cruise climb. | these powers are torque our temperature
34
Cycle
```  A normal or full cycle includes the following Engine start Idle takeoff flight landing idle shut down ```
35
High idle
Obtained by placing the condition lever in the high idle position. this limits the power operation to a minimum of 70% of N1 rpm
36
Low idle
Obtained by placing the condition lever in the low idle position. this limits the power operation to a minimum of 62% of N1 rpm
37
Maximum continuous power
The highest power rating not limited by time
38
Maximum cruise power
The highest power rating for cruise and is not time limited
39
Propeller ground fine
Propeller ground fine operation is used to provide deceleration on the ground during landing and accelerate-stop conditions by taking advantage of the maximum available propeller drag without creating negative thrust
40
Reverse
Rivers thrust is obtained by lifting the power leavers and moving them after the beta and ground fine range
41
Static takeoff power
Static power which must be available for takeoff without exceeding the engine limitations
42
Takeoff power
Maximum power rating. | use of this rating should be limited to normal take off operations and other operations at the discretion of the pilot
43
Condition lever
Also called the fuel shut off lever. the fuel shut off the lever actuates valve in the fuel control unit which controls the flow at the fuel control outlet and regulates the idle range from low to high idle
44
ITT
Interstage turbine temperature. | eight probes wired in parallel indicate the temperature between the compressor and power turbines
45
N1 tachometer
Gas generator RPM. | the tachometer registers the rpm of the gas generator with 100% representing a gas generator speed of 37,500 RPM
46
Power lever
Gas generator N1 RPM. this lever serves to modulate engine power from full reverse thrust to takeoff. the position for idle represents the lowest recommended level of power for flight operation
47
Propeller control lever
N2 RPM . this lever is used to control the RPM setting of the propeller governor. movement of the lever results in an increase or decrease in propeller RPM. propeller feathering is the result of lever movement beyond the detents at the low rpm ( high pitch ) end of the lever travel
48
Propeller governor
The propeller governor senses changes in RPM and hydraulically changes propeller blade angle to compensate for the changes in RPM. constant propeller RPM is there by maintained at the selected RPM setting
49
Torquemeter
Indicates shaft output torque
50
Demonstrated crosswind
Max 90 degree crosswind component for which adequate control during takeoff and landing was actually demonstrated during certification
51
Landing distance
Distance from point 50 feet above runway surface to the point at which the air plane would come to a complete ratio stop . These distances don’t include landing factors which may be required by operating regulations for destination or alternate airports
52
Net gradient of climb
Gradient of climb with flaps in takeoff position and landing gear retracted. Net indicates actual gradients have been reduced by regulatory increment to allow for turbulence and pilot technique. Values using outside air temp and pressure altitude will be average gradient from 35 ft to 1500 ft
53
TOFL
Takeoff field length. Min length required for departure. Distance is longest of 1 distance to accelerate and recognize engine failure so V1, accelerate to and rotate VR,then climb and accelerate IOT achieve V2 at 35 ft above runway 2 distance to accelerate and recognize engine failure at V1 and bring plane to stop 3 all engines operating distance to accelerate and rotate at VR then climb and accelerate IOT achieve V35 at 35 ft above runway increases by 15%
54
Take off flight path
Min gradient of climb required to clear obstacles in excess of 35 ft measured horizontally from reference zero and vertically at altitude above runaway.
55
Reference zero
Point where airplane has reached 35 ft above runway from takeoff field length graphs
56
Basic empty weight
Weight of empty airplane including full engine oil and unusable fuel
57
Empty weight
Weight of empty airplane before any oil and fuel are added
58
Payload
Weigh of occupants and cargo and baggage
59
Ramp weight
Airplane weight at engine start assuming all loading complete
60
Useful load
Difference between ramp weight and basic empty weight
61
Warning
Explanatory information about operating procedure or practice or condition that may result in injury or death or loss of aircraft if not carefully observed or followed
62
Caution
Explanatory information about operating procedure or practice or condition that may result in damage to equipment is not carefully observed or followed
63
Note
Explanatory information about operating procedure or practice or condition that must be emphasized
64
Land immediately
Land without delay
65
Land as soon as possible
Land at first site where safe landing can be made
66
Land as soon as practicable
Extended flight not recommended. | Landing site and duration at discretion of pilot in command

UC-12W NATOPS (5 decks)

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