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After aircraft has been operated in the environment.
above condition, an entry is required on the b. If icing conditions become unavoidable, the pilot
DA Form 2408-13-1 or 2408-13-1E. should turn on the pitot heat, cabin heater, left and
right defog blowers, and the engine anti-ice system.
4. Radios  Turn volume down on any radio
equipment badly affected by static. c. During flights in icing, the following conditions
may be experienced:
5. At night  Turn interior lights to full bright to
minimize blinding effect of lightning. NOTE
6. Maintain a level attitude and constant power If the windshield defrosters fail to keep the
setting. Airspeed fluctuations should be windshield clear of ice, the side windows
expected and disregarded. may be used for visual reference during
landing.
7. Maintain the original heading, turning only (1) Obscured forward field of view, due to ice
when necessary. accumulation on the windshield and chin bubbles.
(2) Vibrations ranging from mild to severe caused
8. The barometric altimeter is unreliable due to by asymmetrical ice shedding from the main rotor
differential barometric pressures within the system. The severity of the vibration will depend upon
storm. An indicated gain or loss of several the temperatures and the amount of ice accumulation
hundred feet is not uncommon and should be on the blades, when the ice shed occurs. The
allowed for when determining minimum safe possibility of an asymmetric ice shed occurring
altitude. increases as the outside air temperature decreases.
(3) An increase in torque required to maintain a
8-41. LIGHTNING STRIKE. constant airspeed and altitude due to ice accumulation
on the rotor system.
a. Although the possibility of a lightning strike is
remote, the helicopter could sustain lightning damage. (4) Possible degradation of the ability to maintain
autorotational rotor speed within operating limits. If a
torque increase is required above the cruise torque
NOTE setting used prior to entering icing conditions, it may
not be possible to maintain autorotational rotor speed
Avoid flight in or near thunderstorms. within operational limits, should an engine failure occur.
b. Simulated lightning strike tests (on other
helicopters) indicate that lightning strikes may damage WARNING
rotors and/or rotor systems. The degree of damage will
depend on the magnitude of the charge and point of Ice shed from the rotor blades and/or
contact. Catastrophic structural f a i l u r e i s not other rotating components presents a
anticipated; however, evidence of damage to hub hazard to personnel during landing and
bearings, blade aft section, trim tabs, and blade tips shutdown. Ground personnel should
was demonstrated. Also, adhesive bond separations remain well clear of the helicopter during
occurred between the blade spar and aft section landing and shutdown and crewmembers
between the spar and leading edge abrasive strip. Such should not exit the aircraft until the rotor
damage can aerodynamically produce severe structural has stopped turning.
vibration and serious control problems.
d. Control activity cannot be dependent upon to
c. Abnormal operating noises almost always remove ice from the main rotor system. Vigorous
accompany rotor damage. Loudness and pitch of noise control movements should not be made in an attempt to
are not valid indicators of the magnitude of damage. reduce l o w - f r e q u e n c y v i b r a t i o n s caused by
8-21
TM 1-1520-248-10
asymmetrical shedding of ice from the main rotor 8-44. FLIGHT IN VICINITY OF VOLCANIC
blades. These movements may induce a more ACTIVITY.
asymmetrical shedding of ice, further aggravating
helicopter vibration levels. Flight within 200 nautical miles of volcanic activity will
require an entry on DA Form 2408-13-1 or 2408-13-1E
to alert maintenance personnel.
8-43. FLIGHT IN VICINITY OF SALT WATER.
Flight within 10 nautical miles of salt water will require
an entry on DA Form 2408-13-1 or 2408-13-1E to alert
maintenance personnel.
8-22
TM 1-1520-248-10
CHAPTER 9
EMERGENCY PROCEDURES
SECTION I. I. HELICOPTER SYSTEMS
9-1. HELICOPTER SYSTEMS. This section
describes the helicopter systems emergencies that may
reasonably be expected to occur and presents the
procedures to be followed. Emergency operation of
mission equipment is contained in this chapter insofar
as its use affects safety of flight. Emergency
procedures are given in checklist form when applicable.
A condensed version of these procedures is contained
in the condensed checklist, TM 1-1520-248-CL.
Tables 9-1 through 9-3 provide a complete list of
　
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