5-35. SEVERE ICING LIMITATIONS.
Severe icing may result from environmental conditions outside of those for which the aircraft is
certiicated. Flight in freezing rain, freezing drizzle, or mixed icing conditions (super-cooled liquid
water and ice crystals) may result in a buildup on protective surfaces exceeding the capability of the
ice protection system, or may result in ice forming aft of these protected surfaces. This ice may not
shed using ice protection systems, and may seriously degrade the performance and controllability
of the aircraft.
All icing detection lights must be operative prior to light into icing conditions at night. This super-
sedes any relief provided by the Master Minimum Equipment List (MMEL) or equivalent.
a. During light, severe icing conditions that exceed those for which the aircraft is certiicated shall be determined
by the following visual cues. If one or more of these visual cues exist, immediately request priority handling from air
trafic control to facilitate a route or an altitude change to exit the icing conditions:
Unusually extensive ice accreted on the frame in areas not normally observed to collect ice.
Accumulation of ice on the upper (or lower, as appropriate) surface of the wing aft of the protected
Accumulation of ice on the propeller spinner farther aft than normally observed.
b. Since the autopilot may mask tactile cues that indicate adverse changes in handling characteristics, use of
the autopilot is prohibited when any of the visual cues speciied above exist, or when unusual lateral trim require-
ments or autopilot trim warnings are encountered while the aircraft is in icing conditions.
5-36. CROSSWIND LIMITATIONS.
Landing with wind conditions in excess of the demonstrated crosswind component may result in
damage to the aircraft. This should only be attempted during emergency situations.
Maximum demonstrated crosswind component for aircraft weighing between 13,000 and 15,675 pounds is 25 knots
at 90° off the nose. Maximum demonstrated crosswind component for aircraft weighing below 13,000 pounds is 20
knots at 90° off the nose. Landing aircraft in a crab will impose side loads on landing gear and should be recorded
on DA Form 2408-13-1. Refer to Chapter 8 for crosswind landing techniques.
5-37. OXYGEN REQUIREMENTS.
a. Oxygen requirements will be in accordance with AR 95-1.
b. Oxygen system data/duration tables are found in Chapter 2.
5-38. CABIN PRESSURE LIMITS.
Maximum cabin differential pressure is 6.5 PSI.
5-39. CRACKED CABIN WINDOW/WINDSHIELD.
If a crack occurs in any side window or windshield, aircraft operation is limited to 25,000 feet or less and cabin pres-
surization of 4.0 PSI or less as required to complete the light. The aircraft shall not be lown again until maintenance
actions are conducted unless proper authorization is obtained for a ferry light to a location where a maintenance ac-
tion can be performed. If a crack develops in any side window or windshield in light, refer to Chapter 9, Emergency