Abstract: Herein provided are methods and systems for assessing a fuel burn level of an aircraft for a planned mission. Flight information relating to the planned mission is obtained via a graphical user interface, the flight information comprising configurable number of passengers for the aircraft. A requisite engine bleed level for the planned mission is determined based on the flight information. The fuel burn level is assessed based on the requisite engine bleed level.

Abstract: The present disclosure provides systems and methods for controlling thrust produced at takeoff by at least one engine (114, 116) of an aircraft (100). At least one input signal comprising input data indicative of a speed of the aircraft is received (202). The speed of the aircraft is compared to a first pre-determined threshold. Responsive to determining that the speed is below the first threshold, a thrust limit for the at least one engine is determined (204) from the input data and output to the at least one engine a thrust limitation signal for causing the thrust to be limited according to the thrust limit (210).

Abstract: The present disclosure provides systems and methods for controlling thrust produced at takeoff by at least one engine (114, 116) of an aircraft (100). At least one input signal comprising input data indicative of a speed of the aircraft is received (202). The speed of the aircraft is compared to a first pre-determined threshold. Responsive to determining that the speed is below the first threshold, a thrust limit for the at least one engine is determined (204) from the input data and output to the at least one engine a thrust limitation signal for causing the thrust to be limited according to the thrust limit (210).

Abstract: Herein provided are methods and systems for assessing a fuel burn level of an aircraft for a planned mission. Flight information relating to the planned mission is obtained via a graphical user interface, the flight information comprising configurable number of passengers for the aircraft. A requisite engine bleed level for the planned mission is determined based on the flight information. The fuel burn level is assessed based on the requisite engine bleed level.

Abstract: Systems and methods to facilitate a steep final approach phase of flight of an aircraft are disclosed. In one embodiment, a method for operating an aircraft during a steep approach phase of flight of the aircraft comprises operating an engine of the aircraft at an idle speed associated with the steep approach type that is lower than an idle speed associated with a non-steep approach type capable of being executed by the aircraft. The method also comprises operating an ice protection system of the aircraft during the steep approach phase of flight of the aircraft.

Abstract: A method for controlling a pressure control mechanism in a turbofan engine having a precooler permitting heat exchange between ambient air and bleed air includes detecting at least one of an engine failure or a bleed system failure, detecting at least one of an ice condition or an activation of an anti-ice system, and actuating the pressure control mechanism, thereby altering the heat exchange between the ambient air and the bleed air.

Abstract: An aircraft engine includes a precooler disposed within a nacelle. The precooler defines an ambient air passage and a bleed air passage. Air passes through the precooler from an ambient air inlet to an ambient air outlet. Bleed air passes through the precooler from a bleed air inlet to a bleed air outlet. Heat is transferred between the air and the bleed air via heat exchange within the precooler. At least one pressure relief door disposed proximate to the air outlet of the engine. A controller is operatively connected to the pressure relief door. The controller at least opens the pressure relief door based on a demand for increased flow of air through the ambient air passage.

Abstract: An aircraft engine includes a precooler disposed within a nacelle. The precooler defines an ambient air passage and a bleed air passage. Air passes through the precooler from an ambient air inlet to an ambient air outlet. Bleed air passes through the precooler from a bleed air inlet to a bleed air outlet. Heat is transferred between the air and the bleed air via heat exchange within the precooler. At least one pressure relief door disposed proximate to the air outlet of the engine. A controller is operatively connected to the pressure relief door. The controller at least opens the pressure relief door based on a demand for increased flow of air through the ambient air passage.