Spinning Flashcards

1
Q

What is spinning

A

Pitching/Rolling/Yawing around vertical axis without input

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2
Q

Stages to a spin

A

Incipient
Fully developed spin
Recovery phase.

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3
Q

Incipient Spin

A

Aircraft stalls and autorotates.
Initial roll and settle nose down

Recovery:
- Centralise the controls

Starts - When ac begins to autorotate
Ends - First full turn through 360 degrees

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4
Q

Autorotation

A

After the stall but prior to the spin

Definition: Occurs after the stall but before the spin fully develops. Ac pitches/roll/yaws around a vertical axis without control inputs

Both wings are stalled but one is more deeply stalled than the other

Inside wing has less lift and more form drag
Ac roll and yaw towards the drag
Due to yawing cp behind CG nose will rise
One wing is stalled more than the other - both are stalled

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5
Q

Fully developed spin

A

Stable flight conditions no control inputs needed to maintain
Steady yawing rolling pitching flight

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6
Q

Recovery Phase from fully developed spin

A

Close power (remove torque forces from propeller)
Apply full opposite rudder in opposite direction
Push control column central forward

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7
Q

Spiral Diver (Difference from spin)

A

Airspeed increasing/ G force increasing/Nose further below horizon
Forgetting to level wings before trying to pull out of a dive

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8
Q

CG Position on Spinning

A

Forward CG - Steeper spin (easier to recover from)
Aft CG - Flatter spin (relative airflow is vertical)

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9
Q

AC characters for a flat spin

A

Low aspect ratio wings
Inboard engines
Mass concentrated on longitudinal axis

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10
Q

Pro Spin Controls

A

Forced autorotation from pilot

Full up elevator and full rudder at the stall

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11
Q

Buffet (Aerodynamic Warning)

A

Turbulent wake from air flow over TE over elevators
Reliable indicator on approach to stall

Stall strips on LE to encourage earlier flow separation

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12
Q

Aerodynamic symptoms at the stall

A

Intense buffet
Increase aerodynamic noise
Wing drop
Abrupt nose down pitch (Rapid forward CP)

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13
Q

Flapper Switch (Artificial stall warning system)

A

Mounted on LE
Stagnation point moves down and aft
Once stagnation point behind flapper airflow pushes on it
Horn alarm in cockpit

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14
Q

AOA Vane (Artificial Stall warning system)

A

Rotates around own axis and measure relative to ac longitudinal axis

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15
Q

Fixed Probe (Artificial Stall Warning)

A

2 ports which detect angle
Pressure differences sensed at each port and fed back to determine AOA

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16
Q

Rotating probe (artificial stall warning)

A

Servo motor drives probe around until 2 pressures equal and then calculates wings AOA

17
Q

“Pitch Eyebrow”

A

Max safe pitch up angle on PFD

18
Q

Advantage of Artificial warners

A

Independent of pitot systems so any blockage in pitot system does not impact warning systems

19
Q

Power on vs Power off stall

A

Propeller AC:
High pitch angle means thrust vector pointing downwards contributing to lift reducing the stall speed
Slipstream from propeller increases lift reducing stall speed

Jets:
Under wing engines thrust line below ac CG full power pitch up couple

20
Q

Recovery of stick pusher

A

Announce
Disengage autopilot
Apply nose down elevator
Nose down trim
Reduce thrust
Roll

21
Q

Autorotation cause of roll and yaw

A

Difference in values of CL and CD for each wing that causes roll and yaw

22
Q

Effect of CG position on spin

A

Further forward CG = steeper spin
Further aft CG = flatter spin (difficult to recover)

23
Q

Mass along lateral axis will….

A

Spin with large amount of roll
Less yaw and a steeper pitch attitude

(Less sweepback/full tanks/engines mounted outboard)

24
Q

Mass along longitudinal axis

A

Will spin flatter

(High aspect ratio/inboard engines)

25
Q

Spiral Dive Recovery

A

Close power level/air brakes/level wings and ease out of dive

26
Q

Incipient Spin Recovery Action

A

Retard the throttle to idle
Ailerons neutral
Apply full opposite rudder to rotation of spin (look at turn needle)
Apply forward elevator
Recover from dive

27
Q

Spiral Dive

A

High static directional stability but low lateral stability

Small sideslip directional stability restore but weak dihedral effect lags behind

28
Q

Possible cause for auto recovery of aeroplane after the stall

A

The angle of incidence of the wing is larger than the angle of incidence of the horizontal stabiliser (negative)