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Engine anti-ice valves control anti-icing of the engine inlet compressor guide vanes, bullet, and the engine nose cowl.   Engine bleed air for engine anti-ice is supplied by the respective engine.
Electrical resistance heating elements and appropriate coatings provide heat for anti-icing and anti-fogging the pilot’s three windshields and for anti-fogging the clearview and overhead windows.  The windshield anti-ice system also provides heating required for bird impact resistance.
Electrical resistance heating elements are used for anti-icing the pitot tubes, static port areas, stall angle of attack vanes, and ram air temperatures probe.
Airfoil Ice Protection
The airfoil ice protection system will either have one switch labeled AIR FOIL or two switches labeled AIR FOIL L SYS / R SYS.
One Switch System
Wing and fuselage strake anti-icing and horizontal stabilizer de-icing are activated by the AIR FOIL switch and the pneumatic crossfeed valves which provide alternating cycles of 15 minutes of wing anti-icing and 2.5 minutes of horizontal stabilizer de-icing.  The ram air scoop is anti-iced in both cycles. Any part of the automatic cycle can be overridden by means of a manual override TAIL button which, when pushed, provides for 2.5 minutes of horizontal stabilizer de-icing after which a new wing/tail cycle starts.  Placing the AIR FOIL anti-ice switch on OFF position with the pneumatic crossfeed valve(s) open, causes the horizontal stabilizer de-icing cycle to be activated for 2.5 minutes.  Closing the pneumatic crossfeed valves during this cycle will cause the de-icing cycle to be deactivated.
Sec. 15 Page 2
MD-80 Rev. 12/01/00  #29 Continental Flight Manual
Two Switch System
Wing and fuselage strake anti-icing are activated when one or both of the AIR FOIL L SYS / R SYS switches and associated pneumatic crossfeed valves are actuated.  De-icing is provided to the horizontal stabilizer leading edge by pushing the TAIL button, which diverts the flow of heated air from the wing ducts to the stabilizer.  After 2.5 minutes, heated airflow reverts to the wing ducts.  The ram air scoop is anti-iced during both wing and tail operation.
Both Systems
Fuselage strakes anti-icing is accomplished through a wye duct connected to the wing leading edge ducting and controlled by the same switches used for wing slat anti-icing.  Interlock of the airfoil ice protection control valves through the ground control relays prevents flow of heated air in the airfoil ice protection systems until the aircraft becomes airborne.
Engine Ice Protection
Engine anti-ice protection is provided by independent systems, controlled by individual switches, located on the ice protection panel.  Each system (left and right) provides ice protection for the respective engine’s nose cowl, inlet bullet, and compressor inlet guide vanes.
If engine anti-ice is on for takeoff or go-around, there is no EPR penalty to be applied.  If it is on for Climb, Cruise, or Maximum Continuous Thrust conditions, the TRI will automatically compute and display the appropriate EPR penalty.
UWAI System Description
Two amber lights on the upper instrument panel (located to the left of the ASSUMED TEMP selector) indicate status of the UWAI system:
WING ICE  Indicates the temperature in one or more sensors has fallen 
ALERT  below 38°F and there is the possibility of ice formation. 
WING HTR  Indicates failure of a heater segment or internal controller 
INOP  failure.  The UWAI system is inoperative. 

The UWAI system is a very thin electric heater blanket assembly which is bonded to the upper wing surface over the affected area (cold corner).  The UWAI system electrically heats the blanket assemblies in essentially the same manner as windshield heat.  Temperature sensors embedded in the heater blanket assemblies send upper wing temperature signals to their respective controller unit.  The left and right wing controller units (mounted in the fuselage just forward of the slat drive mechanism), regulate electrical power to the heater blanket assemblies to maintain upper wing surface temperature above freezing.  The UWAI system does not require any input or control from the flight crew to function.
Electrical bus protection for the UWAI main power circuits is through the #3 galley 35 AMP three phase circuit breakers located on the right generator bus circuit breaker panel, labeled #3 GALLEY POWER AND UPPERWING ANTI-ICE. Electrical bus protection for the UWAI control circuits is through a 1 AMP circuit breaker located at H-26, labeled UPPER WING ANTI-ICE.
Three phase power that is normally routed to galleys #2 and #3, is now routed through an air/ground sense relay.  When the aircraft is on the ground, electrical power is removed from galleys #2 and #3 and is applied to the UWAI system.  When the aircraft is airborne, electrical power is completely removed from the UWAI system and electrical power to galleys #2 and #3 is restored.  During AC crosstie operation, UWAI power along with galley power will load shed automatically.  This is done so that aircraft electrical bus limitations are not exceeded.  Pulling the 1 AMP UWAI control circuit breaker, (H-26) labeled UPPER WING ANTI-ICE, will remove all power to the UWAI system and will restore power to galleys #2 and #3.  Galley power switch position has no effect on UWAI operation.
　
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