A fixed wing unmanned aircraft and a method for operating the same are provided. The fixed wing unmanned aircraft may include, but is not limited to, a failure detection system configured to detect faults in one or more of the plurality of components, a capability evaluation system communicatively coupled to the failure detection system, the capability evaluation system configured to determine a capability level of the fixed wing unmanned aerial vehicle based upon the faults in the one or more of the plurality of components, and a trajectory generation system communicatively coupled to the failure detection system and the capability evaluation system, the trajectory generation system configured to generate a touch down trajectory for the fixed wing unmanned aerial vehicle based upon the determined capability level of the fixed wing unmanned aerial vehicle, wherein when the determined capability level is below a predetermined threshold, the touch down trajectory comprising a stall maneuver configured to minimize a lateral energy of the fixed wing unmanned aerial vehicle.

Disclosed herein is a method that comprises detecting that a rate of decrease in fuel quantity for an aircraft exceeds a previously-determined baseline rate of decrease in fuel quantity for the aircraft by a threshold rate during a corresponding segment of flight of the aircraft. The method also comprises determining that a fuel jettison setting for the aircraft is enabled in response to the detected increase in the rate of decrease in fuel quantity. The method further comprises determining that an angle of one or more flaps of the aircraft satisfies a threshold angle. The method additionally comprises generating an alert indicating possible fuel contamination of the one or more flaps due to jettisoned fuel.

Disclosed herein is a method that comprises detecting that a rate of decrease in fuel quantity for an aircraft exceeds a previously-determined baseline rate of decrease in fuel quantity for the aircraft by a threshold rate during a corresponding segment of flight of the aircraft. The method also comprises determining that a fuel jettison setting for the aircraft is enabled in response to the detected increase in the rate of decrease in fuel quantity. The method further comprises determining that an angle of one or more flaps of the aircraft satisfies a threshold angle. The method additionally comprises generating an alert indicating possible fuel contamination of the one or more flaps due to jettisoned fuel.

Device for draining liquids for an aircraft engine, comprising a collector designed to collect liquids drained from the engine, said device comprising means for pumping the liquids held in the collector and for discharging said liquids, and monitoring means designed to indicate when the liquids have been collected by the collector in an anomalous manner, said monitoring means being designed to be activated when the flow rate of collected liquids is greater than the delivery of the pumping means.

Device for draining liquids for an aircraft engine, comprising a collector designed to collect liquids drained from the engine, said device comprising means for pumping the liquids held in the collector and for discharging said liquids, and monitoring means designed to indicate when the liquids have been collected by the collector in an anomalous manner, said monitoring means being designed to be activated when the flow rate of collected liquids is greater than the delivery of the pumping means.

A fuel tank comprises an interior wall, a sump, and a baffle that comprises a center fitting, a full-length containment petal, a partial-length containment petal, a dump tube. The full-length containment petal comprises a full-length side edge, extending radially outward from the center fitting. The partial-length containment petal comprises a partial-length side edge, extending radially outward from the center fitting. The dump tube is connected to the sump. The full-length side edge of the full-length containment petal is longer than the partial-length side edge of the partial-length containment petal. All of the partial-length side edge of the partial-length containment petal is attached to a linear portion of the full-length side edge of the full-length containment petal.

A method includes displaying, on an electronic display, an electronic checklist. The method further includes determining whether the electronic checklist includes a checklist item associated with states of multiple components of a subsystem associated with the electronic checklist. The method further includes, based on determining that the electronic checklist includes the checklist item associated with the states of the multiple components, displaying, on the electronic display, a single option that is selectable to send control commands to the multiple components.

A method includes displaying, on an electronic display, an electronic checklist. The method further includes determining whether the electronic checklist includes a checklist item associated with states of multiple components of a subsystem associated with the electronic checklist. The method further includes, based on determining that the electronic checklist includes the checklist item associated with the states of the multiple components, displaying, on the electronic display, a single option that is selectable to send control commands to the multiple components.

An aircraft, the aircraft including a whole-aircraft ballistic parachute that is coupled to the aircraft. The aircraft determines if a pre-activation action needs to be performed before activation of the whole-aircraft ballistic parachute. The aircraft also receives a whole-aircraft ballistic parachute activation request. The aircraft then issues a command to perform the pre-activation action and then activates the deployment of the whole-aircraft ballistic parachute. The aircraft then issues a command to perform a post-activation action.

A system includes display equipment and a processor coupled to the display equipment. The processor is configured to cause the display equipment to display an electronic checklist associated with an aircraft. The processor is configured determine whether the electronic checklist includes a checklist item associated with a particular control page of a plurality of control pages. The processor is configured to, based on determining that the electronic checklist includes the checklist item associated with the particular control page, cause the display equipment to display the particular control page that includes a control element that is selectable to cause a control command to be sent to one or more components.