MIL-T-18607(Aer)
Wing Thermal Ice Prevention in Specified
Icing Conditions.
Carr B. Neal, Jr., Norman R. Bergum, David
Sukoff, and Bernard A. Schloff, December
1947 l
(Application for copies should be addressed to the Superintendent of
Documents, Government Printing Office, Washington 25, D. C.)
REQUIREMENTS
3.
3.1 Surfaces to be protected.-The anti-icing system shall protect the
surfaces of the aircraft against the accumulation of ice as outlined in the following
paragraphs.
3.1.2 All portions of the wing(s) and stabilizing surfaces which are
exposed to ice accumulations during flight under the conditions specified in 3.2, 3.3,
3.3.1, 3.3.2 and 3.3.3 shall be protected by the anti-icing system.
3.2.1.1 Wing areas adjacent to fuel cells. -Wing areas adjacent to integral
fuel cells need not be heated.
3.1.2 Stabilizing surfaces.-Ali parts of the aircraft stabilizing surfaces
which are exposed to ice accumulation during flight shall be protected by the anti-
icing system.
3.1.3 The entrance to each air scoop which must function during icing
conditions shall be protected against ice accumulations. Protection shall also be
provided for the guide vanes or at abrupt changes in direction of ducts leading from
these scoops to permit unrestricted airflow in these ducts.
3.1.4 Protection of antenna masts, hinge fairings, spoilers, dive brakes,
struts, and other miscellaneous ice accreting parts shall depend upon the effects of':
(1) ice accumulation on the normal functioning of the individual part, and (2)
increased drag on aircraft performance.
3.2 Icing conditions. - The thermal anti-icing system shall be designed to
preclude the forming of ice on the protected surfaces of the aircraft in atmospheric
conditions at least as severe as to those in which the free air temperature is not
over 15 degrees Fahrenheit, the moisture content is at lease 0.5 grams per cubic meter,
and the average size of the water droplets is at least 25 microns in diameter.
3.3 Flight Conditions. - The thermal anti-icing system shall be designed to
preclude the forming of ice on the protected surfaces of the aircraft during the
following conditions:
3.3.1 Altitude. - The anti-icing system shall function satisfactorily from
sea level to 20,000 feet or to the ceiling of the airplane, whichever is lower.
3.3.2 Attitude. - The anti-icing system shall function satisfactorily with
the aircraft in any permissible flight attitude.
3.3.3 Speed. - The anti-icing system shall function satisfactorily at any
speed between design stalling and the design level flight speeds of the aircraft.
3.3.4 Vibration and acceleration. - The functioning of the anti-icing system
shall not be adversely affected by acceleration or vibration of the aircraft.
3.4 Thermal requirements
3.4.1 Flight temperatures. - The anti-icing system shall be capable of main-
taining the skin of the protected surface as outlined herein.
3.4.1.1 Conditions. - Readings shall be made under the following conditions:
3
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