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T-45A/C TS, E2-C2, ADV & IUT Aero-03
Slow-Speed Flight, Stall and Spin, and AOA System
D. Post-stall gyration
Sg 2, fr 36
80-100 Degree
1.
Defined--Random pitch, roll, and yaw
Departure (5 overlays)
2.
Problems
a.
Control input, especially lateral aggravate
b.
Sideslip
(1) Can cause rudder blowout
(2) Need in excess of 300 pounds force to
Sg 2, fr 38
neutralize
80-100 Degree
Departure
(3) Excessive sideslip can cause yaw and roll,
resulting in inverted spin
c.
To recover, neutralize (squadron will teach
specific procedures)
E. Spins--general
1.
Defined
Sg 2, fr 39
Fig 7: Stall Progression
Departure
a.
Aggravate stall condition with autorotation,
describing helical path
Sg 2, fr 41
Rudder Blowout
b.
Aircraft is in a steady-state, self-sustained mode
which is a combination of roll and yaw
(1) If nose down, pure roll
(2) If flat, pure yaw
Sg 2, fr 42
Fig 7: Stall
Progression Diagram
Sg 2, fr 43-44
Fig 10: Spin
Characteristics
(9-99) Original
Page 3-19


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