MIL-T-18607(Aer)
3.4.1.1.1 Normal rated power. - The aircraft shall be in a Ievel flight in
clear air with the engines operating at normal rated power.
3.4.1.1.2 Ambient temperature.- The ambient air temperature shall be 15
degrees Fahrenheit*
3.4.1.1.3 Solar radiation.- The specified temperatures shall be obtained
independently of the effect of solar radiation.
3.4.1.2 Spar at 20 percent chord point. - When the spar is located immediately
aft of the 20 percent chord point, temperature of the leading edge skin forward of
the spar shall be not less than 50 degrees Fahrenheit.
3.4.1.3 Spar at 15 percent chord point. - When the spar is located immediately
aft of 15 percent chord point, the temperature of the leading edge skin forward of the
spar shall be net less than 85. degrees Fahrenheit.
3.4.1.4 Spar at 10 percent chord point. - When the spar is located immediately
aft of the 10 percent chord point, the temperature of the leading edge skin forward of
the spar shall be not less than 120 degrees Fahrenheit.
3.4.2 Tempe rature Distribution. -The maximum variation in skin temperate
between any two points along the surface span at a given percentage of chord shhall not
exceed 20 degrees Fahrenheit.
3.4.3 Fuel temperature. - Operating of the anti-icing system under any flight
condition shall not raise the temperature of the fuel in any portion of the fuel system
more than 10 degrees Fahrenheit.
3.4.4 Temperature of structure. -Operation of the anti-icing system shall
not result in raising the temperature of any structural member of the aircraft to a
value in excess of 250 degrees Fahrenheit.
3.5 General requirements.
3.5.1 Weight. - The airplane weight empty shall not be increased more than
one percent (1.0 percent) due to installation. of the thermal anti-icing system. The
weight of the anti-icing system shall be included in the weight empty of the airplane.
3.5.2 Accessibility.- All operating components of the anti-icing instal-
lation shall be readily accessible for inspection, adjustment and repair.
3.5.3 Removability.
3.5.3.1 heaters,heat exchangers and accessories. - All heaters, heat ex-
changers and accessories used there with shall be readily removable. It shall not re-
quire more than 8 man-hours to remove and replace each heat exchanger or heaters
3.5.3.2 Ducts. - It is desired that major components of the anti-icing system
such as ducts be removed for flight operations where-anti-icing equipment will not
be required. Provisions shall be made in the aircraft for securing cables, etc.,
which will "be loose when equipment is removed.
3.5.4 Operation of' anti-icing system.
3.5.4.1 Cockpit.-The following items shall be grouped together in a
position convenient to the pilot, copilot or fliight engineer.
Control. -For normal operation, the anti-icing system shall be
3.5.4.1
operated by a single control.
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3.5.4.l.2 Temperature indicator, -A temperature indicator shall be provided
which indicates in degrees Fahrenheit the temperature of one typical point on each
protected semi-span wing panel and on each protected stabilizing surface (semi-
stabilizer and fin), that is most responsive to icing condition.
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