Abstract: A pressure relief assembly (24) includes an aircraft engine cowl (26) having radially outer and inner skins (28,30) having an opening. A door frame (32) is joined around the perimeter of the opening and defines a door seat (34) surrounding a central portal (36). A pressure relief door (38) is joined to the cowl (26) to cover the portal (36). The door (38) has inner and outer surfaces (40,42) terminating in a perimeter rim (44), with the inner surface (40) of the rim (44) overlapping the door seat (34) to define a primary seal (46) with the door stowed closed. A fireproof secondary seal (48) bridges the door inner surface (40) and frame (32) around the inner perimeter of the primary seal (46) to pre-seal flow to the primary seal (46).

Abstract: Cable retainer apparatuses for retaining a cable, and aircraft and methods including such apparatuses are provided. In one example, a cable retainer for retaining a cable proximate a surface of an aircraft includes a cable retainer. The cable retainer is configured to retain the cable. A fairing is disposed about the cable retainer and is configured to couple to the aircraft to support the cable retainer adjacent to the surface of the aircraft.

Abstract: An avionics system for an aircraft includes a threat data structure and a processor. The threat data structure stores an alert threshold and a margin threshold. The processor is programmed to: predict an aircraft state at a plurality of positions along a potential future trajectory; calculate a margin value at each of the plurality of positions as a difference between the predicted future condition and the threat value at each respective one of the plurality of positions; calculate a margin rate of change at each of the plurality of positions based on a change in the margin value along the potential future trajectory; estimate a time to go value based on a minimum calculated margin value and a maximum calculated margin rate of change among the plurality of positions; and command an indicator to alert the pilot in response to the time to go value reaching the alert threshold.

Abstract: The processor supplies flight commands to the flight control system by selectively blending pilot input with control signals from the autopilot. The processor generates a projected recovery trajectory through successive iterations, each beginning at the current aircraft location and using a recovery constraint selectable by the processor to influences a degree of flight aggressiveness. A detection system that identifies and invokes a state of threat existence if a threat exists along the projected recovery trajectory. The processor during threat existence in a first iteration commands an initial soft recovery, with permitted blended pilot input. If the threat exists on subsequent iteration, the processor commands a more aggressive recovery while attenuating blended pilot input.

Abstract: The aircraft threat envelope protection system employs a threat envelope data structure in a computer-readable medium that stores at least one trigger condition for each of a plurality of different types of threats associated with the aircraft, and modeled using a common schema. A processor computes plural different projected trajectories representing different possible aircraft paths through spacetime. The processor associates at least some of the plurality of the threats to specific trigger points in spacetime along each of the projected trajectories. The processor will deprecate ones of the projected trajectories when they are deemed not viable to recover from a threat. The processor initiates an aircraft protective response when all projected trajectories but one have been deprecated and the aircraft is within a predetermined proximity to the closest trigger point in spacetime along the non-deprecated trajectory.

Abstract: Avionics systems, aircraft, and methods are provided. An avionics system for a subject aircraft includes an intruder aircraft detection device and a processor. The processor is programmed to: identify an intruder aircraft using the intruder aircraft detection device; predict a future path of the intruder aircraft; estimate strength, size, and location characteristics of a wake vortex created by the intruder aircraft at future points in time along the future path; calculate a potential trajectory with potential positions of the subject aircraft at each of the future points in time; compare the potential positions with the strength, size, and location characteristics of the wake vortex at each of the future points in time to identify a wake conflict; and maneuver the subject aircraft based on the wake conflict.

Abstract: A projected recovery trajectory for an aircraft autopilot system is precomputed by providing a stored set of predefined recovery mode segments, including: a mode 1 segment that models the aircraft coasting; a mode 2 segment that models the aircraft executing a nose high recovery; a mode 3 segment that models the aircraft executing a nose low recovery; a mode 4 segment that models the aircraft executing a throttle only recovery; and a mode 5 segment that models the aircraft executing a terrain avoidance recovery. A processor generates at least one projected recovery trajectory based on a current state of the aircraft, where the processor selectively concatenates selected ones of the predefined recovery mode segments into a sequence and uses that sequence to generate the projected trajectory.

Abstract: Drilling aid apparatuses and methods for drilling a structure are provided. In one example, a drilling aid apparatus includes a bushing holder portion. The bushing holder portion has a first surface for facing a first structure portion, a second surface on a side opposite the first surface, and an opening formed through the bushing holder portion extending from the first surface to the second surface. The opening is configured to receive a bushing that is sized for guiding a drill bit for drilling into the first structure portion. A first coupling member is coupled to the bushing holder portion and is configured to couple to a second structure portion for supporting the bushing holder portion in a fixed position relative to the first structure portion.

Abstract: An apparatus for wheel maintenance includes a base configured to rotate about a vertical rotational axis and a frame mounted to the base that has a pair of opposing longitudinal members and a pair of opposing transverse members. First and second rollers are spaced apart from one another and coupled to the pair of opposing transverse members. Both the first and second rollers rotate about a longitudinal rotational axis orthogonal to the vertical rotational axis. In this way, when a wheel is positioned on the first and second rollers, the wheel may be rotated about the vertical rotational axis and a wheel rotational axis during a maintenance procedure.

Abstract: A system and a method for drone detection and collision avoidance, particularly for use in an aircraft, is provided. The system includes, but is not limited to a sensor, a processor, and an avoidance unit comprising a control unit. The sensor is configured to detect a drone signal in a predetermined space and to transmit the drone signal to the processor. The processor is configured to determine the presence of a drone in the predetermined space based on the drone signal. The processor is configured to transmit a command to the avoidance unit when the processor determines the presence of a drone. The control unit is configured to receive the command and to generate a warning signal in response to receiving the command.

Abstract: A device, a system and a method for dispensing adhesive elements are provided. The device comprising a first holder, a second holder, and an alignment element. The first holder is configured to rotatably hold a film having adhesive elements and a protective layer attached on adhesive areas of the adhesive elements. The second holder is configured to receive the protective layer as the protective layer is peeled off the adhesive areas of the adhesive elements while the adhesive elements are moved towards an alignment element. The alignment element is arranged in a direction of movement of the adhesive elements and configured to receive and align the adhesive elements at a predetermined position on the alignment element.

Abstract: Methods for characterizing shape changes of an aircraft due to flight loads are provided. In one example, a method for characterizing shape changes of an interior portion of an aircraft from flight loads includes positioning one or more 3D scanners within the interior portion of the aircraft. A reference scan of the interior portion is created with the one or more 3D scanners while the aircraft is substantially stationary and/or on the ground. A deformed scan of the interior portion is created with the one or more 3D scanners while the aircraft is in flight subject to substantial flight loads. The reference scan and the deformed scan are postprocessed and analyzed to characterize the shape changes of the interior portion of the aircraft from the substantial flight loads.

Abstract: Aircraft instrumentation systems, aircraft, and controllers are provided for transcribing radio communications. An aircraft instrumentation system and an aircraft include a radio device, a display device, and a controller. The controller is communicatively coupled with the radio device and the display device. The controller is configured to monitor the radio device and recognize a voice communication received over the radio device. The controller is further configured to generate an electronic transcript of the voice communication and control the display device to display a transcript of the voice communication.

Abstract: An airfoil is provided having reduced noise generation for use with an aircraft. The airfoil includes a body and a cover. The body has a leading edge spaced from a trailing edge and a side surface disposed between the leading edge and the trailing edge. The body defines an inlet proximate the leading edge and configured to receive air. The side surface defines an outlet in fluid communication with the inlet. The outlet is configured to exhaust air away from the side surface. The cover overlies the inlet and is movable between a first and a second cover position. The cover is configured to prevent movement of air through the inlet when the cover is in the first cover position and configured to permit movement of air through the inlet when the cover is in the second cover position.

Abstract: Seat assemblies and methods for fabricating seat assemblies are provided. In one example, a seat assembly includes a seat frame and a seat cushion that is supported by the seat frame. The seat cushion includes a modular foam arrangement having an interior surface disposed therein. The modular foam arrangement includes a venting modular section in fluid communication with the interior surface. An outer covering at least partially covers the modular foam arrangement. An air movement device is in fluid communication with the venting modular section for advancing air between the interior surface and the air movement device.

Abstract: Seat assemblies are provided. In one example, a seat assembly includes a seat base portion and a seat backrest portion. An armrest is disposed adjacent to the seat base portion and forward of the backrest portion. The armrest includes a fixed armrest portion that is coupled to the seat frame. An armrest lid is configured to move relative to the fixed armrest portion between a closed position overlying an upper section of the fixed armrest portion and an open position allowing access to the upper section of the fixed armrest portion. A hinge arrangement is pivotally couples the armrest lid to the fixed armrest portion. The hinge arrangement includes a damper and a damper gear that meshes with the damper to dampen movement of the armrest lid between the closed and open positions.

Abstract: Fuselage assemblies, over-frame blanket assemblies, and methods of installing over-frame blanket assemblies are provided. A fuselage assembly for an aircraft includes a fuselage skin, a cabin liner, and an over-frame blanket assembly. The cabin liner has an outer side facing the fuselage skin. The over-frame blanket assembly is disposed between the fuselage skin and the cabin liner and has a first blanket piece. The first blanket piece includes a first sound barrier layer that defines a first outer surface of the over-frame blanket assembly and a first sound absorbing layer that defines a second outer surface of the over-frame blanket assembly facing the fuselage skin. A method of installing the over-frame blanket assembly includes positioning the first blanket piece in an orientation such that the first sound barrier layer is directly adjacent the cabin liner.