MIL-T-18607 Thermal Anti-Icing Equipment, Wing And Empennage \(S/S By Sae-As18607\)

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3.5.4.1.3 Warning signal.-A suitable warning signal shall be provided to

indicate when actuation of any safety device has stopped the operation of the anti-

icing system.

3.5.4.1.4 Operating instructions.-A suitable instruction plate shall be

provided containing necessary instructions for the operation of the anti-icing system.

3.5.4.2 Temperature control. -The temperature of the hot air being supplied

to the protected surfaces shall be automatically controlled to prevent overheating of

the surfaces.

3.6 Hot air distribution system.

3.6.1 Distribution. -The hot air shall be distributed to the leading edges

of the protected surfaces by means of suitable ducts. The system shall be designed

so that the hot air, after leaving the heat source, may be directed through the system

or it may be dumped overboard.

3.6.2 Exhaust gases. - Whenever the anti-icing system contains gases from the

engine exhaust. or the combustion heaters, the system shall be designed to preclude the

possibility of toxic gases escaping into occupied compartments in the event of leaks

in the heater or heat exchanger, or of corroding my part of the aircraft structure.

3.6.3 Water drains. - Provision shall be made to insure the free drainage of'

any water that may enter the system.

3.7 Heat sources.

3.7.1 Heat exchangers .-When heat is to be obtained from engine exhaust, it

shall be extracted by one or more heat exchangers.

3.7.1.1 Exhaust back pressure. - With heat exchangers installed, the exhaust

`back pressure shall conform to the requirements of Specification AN-9500.

3.7.2 Combustion heaters. - Combustion heaters shall conform with the require-

ments of Specification MIL-H-5484.

3.7.2.1 Fuel supply.-Fue2 for the combustion heaters may be obtained from

the engine fuel pumps or pumped directly from the aircraft fuel system by electrically-

driven pumps.

3.7.2.2 Shut-off valves.- Positive Shut-off valves shall be Incorporated as

near as practicable to the fuel sources (engine-driven pumps or fuel tanks).

3.7.2.3 . Fuel lines. - All lines carrying fuel to the heaters shall be either

AN-6264 hose assemblies or aluminum alloy tubing in conformity with the requirements

of Specification WW-T-787. Fuel lines shall be marked in accordance with Standard

AND-20375.

3.7.2.4 Drain lines. - Each heater shall be provided with drain lines to in-

sure that in the event of nonignition, all fuel pumped to the heater will be drained

overboard.

3.7.3 Bleed air.- In turbo prop and jet aircraft, bleed air from the

compressor may be utilized.

3.8 Electrical equipment.

3.8.1 Installation. - The electrical installation shall conform to Specifi-

cation MIL-W-5088 and Specification MIL-E-7080.

3.8.1.1 Quick disconnect connectors. -Where equipment is subjected to re-

moval for inspection and servicing, quick disconnect electrical connectors in confor-

mance with Specification MIL-C-5015 shall be provided.