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DEICE AND ANTI-ICING SYSTEMS FOR THE S-3 AIRCRAFT
DEICE AND ANTI-ICING SYSTEMS FOR THE S-3 AIRCRAFT-Cont.

Aviation Structural Mechanic E2 - How airplanes are built and how to maintain them
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supply subsystem, in addition to supplying deice air, is to control the temperature of that supply. The high-stage bleed-air regulator valve primarily maintains a set pressure schedule in the bleed-air manifold. During deice operations this function is expanded to maintain a temperature of 500°±25°F (260°±14°C) (or maximum 14th stage temperature, if less than 500°F). Pneumatic signals from the bleed-air control temperature thermostat and anticipator are fed to the deice temperature control regulator valve (fig. 1-10), which, in turn, signals the high-stage bleed-air regulator valve to open, as necessary, to satisfy either the pressure schedule or the 500°F requirement, whichever needs the larger amount of 14th stage bleed air. Both engines are connected by the cross-bleed manifold, which provides a flow path for bleed air from either one or both engines. The total deice system is controlled by the timing control, which uses pressure regulator valves and cyclic valves to direct bleed air in the proper sequence to each of the eight deice segments. Sequencing minimizes bleed-air con- sumption. Bleed air is ported from the cross-bleed manifold to each of the pressure regulator valves. The pressure regulator valves are energized by setting the DEICING switch on the environmental panel on the center console to WING EMP (wing and empennage). Setting this switch energizes a solenoid that ports pressure from the bleed-air supply to open the pressure regulator valve. Duct pressure is regulated by the pressure regulator valve to 26 ±2 psi. In the de-energized position, the pressure regulator valves are pneumatically Figure 1-10.—Ice protection system. 1-12







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