Abstract: A windshield wiper installation system is configured to be used to install a wiper on a windshield of an aircraft. The windshield wiper installation system includes a housing, an installation control unit contained within the housing, at least one positioning member secured to the housing, wherein the installation control unit is operatively coupled to the positioning member(s), and at least one position-setting member secured to the housing, wherein the installation control unit is operatively coupled to the position-setting member(s). The positioning member(s) is configured to be engaged to move the wiper to one or more desired positions on the windshield. The position-setting member is configured to set the desired position(s) when the wiper is at the desired position(s).

Abstract: A windshield wiper installation system is configured to be used to install a wiper on a windshield of an aircraft. The windshield wiper installation system includes a housing, an installation control unit contained within the housing, at least one positioning member secured to the housing, wherein the installation control unit is operatively coupled to the positioning member(s), and at least one position-setting member secured to the housing, wherein the installation control unit is operatively coupled to the position-setting member(s). The positioning member(s) is configured to be engaged to move the wiper to one or more desired positions on the windshield. The position-setting member is configured to set the desired position(s) when the wiper is at the desired position(s).

Abstract: A thermal anti-ice system in an aircraft. A controlled valve receives air from a compressor bleed port of an engine of the aircraft. A self-regulating valve is fluidly connected between the controlled valve and an inlet of the engine. A first pressure sensor senses pressure between the valves. A second pressure sensor senses pressure between the self-regulating valve and the inlet. The system can be used to de-ice aircraft inlet lip skins made of composite materials that have comparatively lower design temperatures than other comparable materials.

Abstract: A thermal anti-ice system in an aircraft. A controlled valve receives air from a compressor bleed port of an engine of the aircraft. A self-regulating valve is fluidly connected between the controlled valve and an inlet of the engine. A first pressure sensor senses pressure between the valves. A second pressure sensor senses pressure between the self-regulating valve and the inlet. The system can be used to de-ice aircraft inlet lip skins made of composite materials that have comparatively lower design temperatures than other comparable materials.