Abstract: An engine thrust rating process and system for controlling engine thrust during flight of an aircraft and/or to support an airplane development program (including design, validation testing, and production of airplane systems, airplane dispatch and operation tools). The thrust rating process uses thrust ratios derived from thrust expressed in power rather than engine rotor speed (N1). In one or more examples, the thrust rating architecture is based on “Max Rated Thrust” tables and the power setting parameter “PSP” being calculated at the end of the process instead of at the beginning of the process (unlike conventional procedures), thereby enabling the system software development early as needed to support the airplane development phase. This concept also yields improvements such as simplified control logic, optimized engine performance and engine life.

Abstract: An engine thrust rating process and system for controlling engine thrust during flight of an aircraft and/or to support an airplane development program (including design, validation testing, and production of airplane systems, airplane dispatch and operation tools). The thrust rating process uses thrust ratios derived from thrust expressed in power rather than engine rotor speed (N1). In one or more examples, the thrust rating architecture is based on “Max Rated Thrust” tables and the power setting parameter “PSP” being calculated at the end of the process instead of at the beginning of the process (unlike conventional procedures), thereby enabling the system software development early as needed to support the airplane development phase. This concept also yields improvements such as simplified control logic, optimized engine performance and engine life.

Abstract: Systems and methods for displaying N1 speed on a flight deck display in a manner that provides increased resolution at the upper end of the operating range. This is accomplished by a variable scale(s) which improves the functionality of the N1 gauge (serving as an indication of thrust) in the desired region. Also, there is visual indication to provide pilots the ability to discern if the current thrust is within a specific tolerance to the desired value within the takeoff region. This additional indication is based on color changes associated with the N1 display structure.

Abstract: Methods and apparatus to increase a payload capacity of an aircraft are disclosed herein. An example method includes receiving a selection via a control display unit to employ a fluid delivery system during takeoff of an aircraft. The fluid delivery system includes a tank disposed on the aircraft. The example method also includes automatically controlling, via a fluid management system including a processor, a flow of the water from the tank during takeoff in response to the selection. The water is to cool an engine heat source of the aircraft.

Abstract: Systems and methods for displaying N1 speed on a flight deck display in a manner that provides increased resolution at the upper end of the operating range. This is accomplished by a variable scale(s) which improves the functionality of the N1 gauge (serving as an indication of thrust) in the desired region. Also, there is visual indication to provide pilots the ability to discern if the current thrust is within a specific tolerance to the desired value within the takeoff region. This additional indication is based on color changes associated with the N1 display structure.

Abstract: Methods and apparatus to increase a payload capacity of an aircraft are disclosed herein. An example method includes receiving a selection via a control display unit to employ a fluid delivery system during takeoff of an aircraft. The fluid delivery system includes a tank disposed on the aircraft. The example method also includes automatically controlling, via a fluid management system including a processor, a flow of the water from the tank during takeoff in response to the selection. The water is to cool an engine heat source of the aircraft.

Abstract: A system for detecting and correcting a thrust control malfunction in an aircraft engine. The system includes an electronic engine control (EEC) unit that includes a first processing subsystem and a second processing subsystem, and a thrust control malfunction accommodation (TCMA) circuit included in the first processing subsystem and the second processing subsystem. Additionally, the system includes a TCMA software package executed by the first processing subsystem and the second processing subsystem, thereby providing redundant execution of the TCMA software package.

Abstract: A system for detecting and correcting a thrust control malfunction in an aircraft engine. The system includes an electronic engine control (EEC) unit that includes a first processing subsystem and a second processing subsystem, and a thrust control malfunction accommodation (TCMA) circuit included in the first processing subsystem and the second processing subsystem. Additionally, the system includes a TCMA software package executed by the first processing subsystem and the second processing subsystem, thereby providing redundant execution of the TCMA software package.