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 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: Control systems, controllers, systems, and methods of stabilizing a light aircraft during flight and/or ground maneuvers, such as by detecting and/or correcting undesired yaw characteristic, such as, for example, yaw angle, yaw rate, and/or yaw fluctuations.

Abstract: A method and apparatus for a fully integrated Information System (IS) with modules for each business activity, that can be used individually or grouped in a suite of modules, each module containing its own individual database, and connected via a middleware-like integration device, or Enterprise Service Bus, for network based data synchronization and communications, that connect the modules to each other and to existing ERP, CRM, data warehouse and custom legacy systems. Each module therefore acts more efficiently since it is not burdened by the tasks of interfacing with the hardware platforms and operating systems, which are assigned to the programs in the integration server. These smaller and more flexible modules work together and automatically update all related applications, databases and users, when data is entered into one.

Abstract: A middleware product suitable for retrofitting to an existing network environment to perform the functions of data synchronization, transfer and validation while providing a secondary channel to remove workload from the primary database thereby performing the functions of middleware without its associated disadvantages, for example, cost and labor intensive maintenance. The unique feature of this technology is a network-based data communication, validation, and transfer system known as the Harmonizer™, which is employed to interface a plurality of modules used in an Information System application.