Abstract: A method and system of controlling data collection and use, the method for use with at least a first sensor designed to sense at least a first parameter and an interface device, the method comprising the steps of receiving data values from the sensor, storing the received data values in a temporary private database that is inaccessible by at least a first application program, tracking time since collection for collected data values, presenting at least a first redaction option via the interface, upon selection of the first redaction option, rendering the at least a first data subset stored in the temporary database permanently inaccessible to the at least one application program and upon the tracked time since collection of stored data values reaching a threshold period, releasing the stored data values for use by the at least a first application program.

Abstract: A water heater (10) is suitable for point-of-use applications. The water heater includes a tank housing (12) and one or more electrically powered heating elements (18). A water inlet line (20) and a water outlet line (24) may be molded as a unitary structure with the tank housing. The water outlet line includes a lower port (68) and an upper port (70) for mixing water in the outlet line. The housing may be mounted such that its axis is either vertical or horizontal.

Abstract: An airborne vehicle lighting control apparatus and method for automatically controlling activation and deactivation of an airborne vehicle lighting system. A processor for automatically controlling the lighting system can be employed and having one or more sensors operatively connected to the processor for sensing the current flight operating mode and geographical position of an airborne vehicle. The processor can activate or deactivate lighting based on the current flight operating mode and position.

Abstract: An automatic trim system and method is disclosed for automatically trimming a flight control surface of an aircraft. A force sensor measures a force applied by a pilot to a flight control system actuator. The length of time that the force is applied by the pilot is then timed by a timer. A trim system to reduce the applied force is included on the flight control surfaces. A processor determines if trim is required if a predetermined amount of time is exceeded based on the force sensor measurement. The processor can set the trim system to the trim required therein. An airspeed sensor is used to verify that the aircraft has sufficient speed for flight. A force sensor can be utilized to measure the input force being applied by the pilot. If a pilot input force is applied to the controls and the aircraft is in a steady state, a timer can be activated.

Abstract: A water heater (10) is suitable for point-of-use applications. The water heater includes a tank housing (12) and one or more electrically powered heating elements (18). A water inlet line (20) and a water outlet line (24) may be molded as a unitary structure with the tank housing. The water outlet line includes a lower port (68) and an upper port (70) for mixing water in the outlet line. The housing may be mounted such that its axis is either vertical or horizontal.

Abstract: A fuel pump system for an aircraft engine having a booster pump that is always on during maneuvers and malfunction of primary fuel pump is disclosed. During fuel pressure loss, the boost pump and warning systems for the pilot are activated. The booster pump off and on up process are continued up to a maximum of a predefined number of times at a predetermined time interval in order to confirm that the low pressure was not due to an air bubble, or sensor glitch. The cyclic on and off process is performed only when the aircraft is at a safe altitude above ground level. If the aircraft is in close proximity to the ground and the pressure drops, the boost pump will be activated and remain on without cycling until the aircraft is at a safe altitude, or the aircraft is parked and the engine has been turned off.

Abstract: An airborne vehicle lighting control apparatus and method for automatically controlling activation and deactivation of an airborne vehicle lighting system. A processor for automatically controlling the lighting system can be employed and having one or more sensors operatively connected to the processor for sensing the current flight operating mode and geographical position of an airborne vehicle. The processor can activate or deactivate lighting based on the current flight operating mode and position.

Abstract: An automatic trim system and method is disclosed for automatically trimming a flight control surface of an aircraft. A force sensor measures a force applied by a pilot to a flight control system actuator. The length of time that the force is applied by the pilot is then timed by a tinier. A trim system to reduce the applied force is included on the flight control surfaces. A processor determines if trim is required if a predetermined amount of time is exceeded based on the force sensor measurement. The processor can set the trim system to the trim required therein. An airspeed sensor is used to verify that the aircraft has sufficient speed for flight. A force sensor can be utilized to measure the input force being applied by the pilot. If a pilot input force is applied to the controls and the aircraft is in a steady state, a timer can be activated.

Abstract: A method of improving the adhesion of processing materials on a ceramic component is described. The method includes the steps of forming a green ceramic component and texturing the surface of the green ceramic component. The as-textured component is then fired to harden the ceramic material. In an alternative embodiment of the method, a coating is applied to the surface of the as-fired ceramic component to provide a secondary adhesion layer. A ceramic component for use in an etching or deposition reactor chamber is also described. The ceramic component includes a substrate formed of a ceramic material and has a textured surface formed thereon such that the textured surface has a roughness of about 100 to 1000 ?in Ra.