TM 55-1510-221-10
Section VI. MANUEVERING LIMITS
5-26. MANEUVERS.
For abrupt maneuvers above 168 KIAS. refer to Flight
Envelope (tip. 5-2).
a.
The following maneuvers are prohibited.
1. Spins.
4. Any maneuver which results in a positive load
factor of 3.06G's or a negative load factor of
1.224G’s with wing flaps up, or a positive load
factor of 2.0G’s or a negative 1224G’s with
wing flaps down.
b. Recommended turbulent air penetration airspeed is
158 KIAS.
3. Aerobatics of any kind.
5-27. BANK AND PITCH LIMITS.
3. Abrupt maneuvers above 168 KIAS.
a. Bank limits are 60° left or right.
b. Pitch limits are 30° above or below the horizon.
Section VII. ENVIRONMENTAL RESTRICTIONS
5-28. ALTITUDE LIMITATIONS.
The maximum altitude that the aircraft may be operated
at is 31,000. When operating with inoperative yaw damp,
the altitude limit is 17,000 feet.
5-29. TEMPERATURE LIMITS.
a. The aircraft shall not be operated when the ambient
temperatures are warmer than ISA 37°C at SL to 25,000
feet. ISA 31°C above 25,000 feet.
b. Engine ice vanes shall be retracted at 1°C and above.
5-30. FLIGHT UNDER IMC (INSTRUMENT
METEOROLOGICAL CONDITIONS).
This aircraft is qualified for operation in instrument
meteorological
conditions.
5-30A. ICING LlMlTATlONS (TYPICAL).
While in icing conditions, if there is an
unexplained 30% increase of torque needed
to maintain airspeed in level flight, a
cumulative total of two or more inches of ice
accumulation on the wing, an unexplained
decrease of 15 knots IAS, or an unexplained
deviation between pilot’s and copilot’s
airspeed indicators, the icing environment
should be exited as soon as practicable. Ice
accumulation on the pitot tube assemblies
could cause a complete loss of airspeed
indication.
The following conditions indicate a possible
accumulation of ice on the pitot tube assemblies and
unprotected airplane surfaces. If any of these conditions
are observed, the icing environment should be exited as
soon as practicable.
1. Total ice accumulation of two inches or more on the
wing surfaces.
Determination of ice thickness can be
accomplished by summing the estimated ice thickness on
the wing prior to each pneumatic boot deice cycle (e.g. four
cycles of minimum recommended 1/2-inch accumulation.
2. A 30 percent increase in torque per engine required
to maintain a desired airspeed in level flight (not to exceed
85 percent torque) when operating at recommended
holding speed.
3. A decrease in indicated airspeed of 15 knots after
entering the icing condition (not slower than 1.4 power off
stall speed) if maintaining original power setting in level
flight. This can be determined by comparing pre-icing
condition entry speed to the indicated speed after a surface
and antenna deice cycle is completed.
4. Any variations from normal indicated airspeed
between the pilot’s and copilot’s airspeed indicators.
5-10
Change 5
