T-45 STALL CHARACTERISTICS
In the T-45, impending stall is announced by light buffeting which increases in intensity as you approach
stall. Depending on the aircraft configuration and the rate of deceleration, the stall may be signified by a
yaw, wing drop, or development of high sink rate in pronounced buffet. If the deceleration is rapid, you can
penetrate the stall until the control stick is fully aft. The controls remain effective throughout, and you can
terminate the stall by relaxing back stick pressure, maintaining wings level with rudder, and simultaneously
advancing throttle. Check engine EGT and RPM after any stall to ensure engine is stall free.
With flaps/slats and gear up, idle, and without external stores, the onset of light buffet is at about 22 units
AOA. If you increase the AOA beyond buffet, the aircraft will remain controllable until a wing drop occurs
at about 26 units. The aircraft then descends at a high rate and in a flat attitude with wing rock and yaw
With 1/2 flaps and landing gear down, idle, and without external stores, the onset of buffet is at about
26-27 units AOA. As you approach the stall, buffet increases but the aircraft displays no tendency to yaw.
The stall is usually announced by a gentle wing drop at 29-30 units AOA. You can fly the aircraft beyond
stall AOA, controlling any roll activity with rudder, until the stick is fully aft.
With flaps/slats fully extended, landing gear down, idle, and without external stores, the stall characteristics
are similar to those with 1/2 flaps. The prestall buffet begins at about 26-27 units AOA, and the stall
occurs at 29-30 units AOA.
WARNING: If you continue the stall in the landing configuration until the stick is fully aft, the
aircraft may develop pitch and roll oscillations which you cannot control, and recovery is likely to
result in a large altitude loss.
EMERGENCY FLAP CONFIGURATION
With flaps extended and slats retracted (emergency flap extension or slat failure), the aircraft will exhibit no
natural stall warning during the approach to stall. Stall warning rudder pedal shaker comes on at 21.5 units
AOA, closely followed by the stall at 23-25 units AOA. (Stall airspeed is 9-11 KIAS greater than landing
configuration at the same gross weight.) The stall is very disorienting and is characterized by a slight
pitchup of 4-5 degrees followed by an abrupt roll-off of 60-80 degrees AOB. Following roll-off, the aircraft
is left in a 30-degree nosedown pitch attitude. If recovery is initiated immediately upon roll-off, altitude loss
can be minimized to 700-1,000 ft.
The centerline store (baggage container) has little effect on the stall characteristics of the T-45. Wing
stores, including bar pylons, have a slightly destabilizing effect on pitch but a negligible effect on stall
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