Abstract: The present invention relates to a paper towel that can be provided with dry crepes with no need for involving a large equipment investment. The paper towel contains one or more of chemical pulp, mechanical pulp, de-inked pulp, and recycled pulp, being provided with crepes in an off-machine process by use of a microcreper, such as a MICREX®/Microcreper™ system, and having a basis weight of 32.2 to 64.3 gsm, a density of 0.130 to 0.150 g/cm3, which is obtained by dividing the basis weight by the caliper (?m), and the number of crepes (cpi) of 12 to 30.

Abstract: Roadway barrier bicycle safety apparatus for attachment to an upper portion of a roadway barrier segment for topping the upper portion to prevent a bicycle from extending over the upper portion. The apparatus includes a shell having a curved upper surface and configured to prevent snagging of a bicycle or bicycle rider.

Abstract: The normalization of data originating from endpoints within low power wide area networks (LPWANs) is contemplated. The normalization may be beneficial to facilitate normalizing data when collected and/or communicated according to disparate protocols, languages, formats, syntaxes, structures, etc. of the endpoints and/or the LPWANs so as to enable commonization of the data prior to being interfaced with applications or other entities intending to make use thereof.

Abstract: A system and method are provided that improve upon existing aircraft display systems by generating and updating an overrun image that may be overlaid on a variety of panoramic and landscape images on a display device. The overrun image displays stopping locations for all relevant available stopping devices, as determined from the far end of the selected runway. In addition, the aircraft display system determines an advisory zone on the selected runway and presents limited symbols and images in and near the advisory zone that indicate distances and relevant information.

Abstract: Methods and systems are provided for a boosted engine system having an engine arranged to receive boosted air from a variable geometry turbocharger and an electrically powered compressor arranged in parallel with the turbocharger. During temporary high torque demands above a predefined level, the electrically powered compressor may be used to supplement the flow of boosted air from the turbocharger. Additionally, a recirculation circuit around the electrically powered compressor may be provided to build up pressure in the electrically powered compressor before it is connected to the engine so as to minimize fluctuations in engine boost pressure upon start-up of the electrically powered compressor.

Abstract: A bezel assembly for data reception is provided for use in a transactional device that comprises a door attached to open and close. The bezel assembly comprises: a casing secured to the door, an interior insertion/dispensing slot formed in the casing, a hollow tongue or protrusion forward-extending from the casing to define a bottom surface of the interior insertion/dispensing slot, and a wireless communication module arranged in the hollow tongue or protrusion for communication with a built-in NFC chip in an identification card when put in the interior insertion/dispensing slot to identify a user of the identification card.

Abstract: A method of predicting a parameter for an aircraft includes detecting an actual approach profile of the aircraft. The actual approach profile includes an actual approach angle. The method also includes comparing, by a processor, the actual approach profile to a predetermined approach profile to determine a difference between the actual and predetermined approach profiles. The predetermined approach profile includes a predetermined approach angle. The method further includes determining, by the processor, an effective approach angle by combining the actual approach angle and the predetermined approach angle according to a factor that varies based on the difference between the actual and predetermined approach profiles. Moreover, the method includes determining, by the processor, the predicted parameter based on the effective approach angle.

Abstract: A wheelbarrow having a load carrying body supported on a chassis. An electrically powered axle assembly is located at one end of the chassis and has a pair of wheels disposed at opposite sides of the axle assembly. The chassis includes a pair of side plates that extend downwardly to provide legs and a cross member extending between the side plates to maintain them in spaced relationship. A shelf extends between the side plates and is spaced below the underside of the body to provide a cavity to receive a battery. A pair of handles is secured to the side plates, one on each side of the body to transfer loads from the handles in to the chassis and the body is secured to the handles and side plates at a common connection.

Abstract: A method is provided for monitoring a landing approach of an aircraft. The method includes receiving instrument landing system (ILS) signals; determining a glideslope deviation from the ILS signals; disabling, when the glideslope deviation is less than a first predetermined threshold, at least one glideslope alert function; evaluating a current glideslope condition by comparing a designated glideslope angle to a glideslope check value; and re-enabling the at least one glideslope alert function when the glideslope check value differs from the designated glideslope angle by more than a second predetermined threshold.

Abstract: A system and method for selecting a runway, comprises retrieving runway feature data and aircraft data including aircraft heading with respect to the bearing of first and second runways. Runway boundary envelopes are created for each of the first and second runways, each having a predetermined score. A total score for each of the first and second runways is compared to determine which of the runways is selected.

Abstract: A method for providing alerts or indications to an aircrew of an aircraft that is in-flight and approaching a destination airport includes receiving an aircrew runway selection from the aircrew of the aircraft, automatically generating a probable runway selection by the aircraft, and determining a position of the in-flight aircraft with reference to a threshold point. If the aircraft is prior to the threshold point, the method includes generating alerts and indications to the aircrew based solely on the received runway selection into the FMS from the aircrew of the aircraft and not on the automatically-generated probable runway selection from the aircraft. Alternatively, if the aircraft is past the threshold point, the method includes generating alerts and indications to the aircrew based solely on the automatically-generated probable runway selection from the aircraft and not on the received runway selection into the FMS from the aircrew of the aircraft.

Abstract: An exemplary method of providing torque-assist to a crankshaft of an internal combustion engine includes, among other things, assisting a rotation of the crankshaft using an electric machine during the transition between stages of a multi-stage forced induction system.

Abstract: Systems and methods for improving sink rate alerting for rotary wing aircraft. In one example, the system includes a radio altimeter that produces an altitude value, a processor that is in signal communication with the user interface device and the radio altimeter. The processor receives an altitude value, a position value for the aircraft and landing zone (LZ) information. The processor determines if the aircraft is on an approach to land at an LZ that is raised above surrounding terrain based on the received position value and LZ information. The processor receives sink rate information for the aircraft and generates a sink rate alert based on the received sink rate information and the aircraft altitude value if the sink rate information is greater than a sink rate value adjusted according to the LZ information. An output device outputs the generated sink rate alert. The LZ information includes an altitude value.

Abstract: A method for managing a premature descent envelope during descent of an aircraft is provided. The method receives glideslope deviation data by an instrument landing system (ILS) onboard the aircraft; compares, by the ILS, the glideslope deviation data to an acceptable band of glideslope deviation values; and when the glideslope deviation data is within the acceptable band, expands, by a terrain awareness and warning system (TAWS), the premature descent envelope to produce an increased premature descent envelope for the aircraft.

Abstract: A method is provided for monitoring a landing approach of an aircraft. The method includes receiving instrument landing system (ILS) signals; determining a glideslope deviation from the ILS signals; disabling, when the glideslope deviation is less than a first predetermined threshold, at least one glideslope alert function; evaluating a current glideslope condition by comparing a designated glideslope angle to a glideslope check value; and re-enabling the at least one glideslope alert function when the glideslope check value differs from the designated glideslope angle by more than a second predetermined threshold.

Abstract: A method for managing a premature descent envelope during descent of an aircraft is provided. The method receives glideslope deviation data by an instrument landing system (ILS) onboard the aircraft; compares, by the ILS, the glideslope deviation data to an acceptable band of glideslope deviation values; and when the glideslope deviation data is within the acceptable band, expands, by a terrain awareness and warning system (TAWS), the premature descent envelope to produce an increased premature descent envelope for the aircraft.

Abstract: An electrical box assembly includes an electrical box and a bracket. The electrical box includes a plurality of walls, one of the walls including at least one hole for receiving a conduit. The bracket includes a first portion and a second portion. The first portion is coupled to the electrical box, and the second portion includes at least one finger for extending at least partially around and gripping an outer surface of the conduit. The second portion is pivotable relative to the first portion.

Abstract: A method for providing alerts or indications to an aircrew of an aircraft that is in-flight and approaching a destination airport includes receiving an aircrew runway selection from the aircrew of the aircraft, automatically generating a probable runway selection by the aircraft, and determining a position of the in-flight aircraft with reference to a threshold point. If the aircraft is prior to the threshold point, the method includes generating alerts and indications to the aircrew based solely on the received runway selection into the FMS from the aircrew of the aircraft and not on the automatically-generated probable runway selection from the aircraft. Alternatively, if the aircraft is past the threshold point, the method includes generating alerts and indications to the aircrew based solely on the automatically-generated probable runway selection from the aircraft and not on the received runway selection into the FMS from the aircrew of the aircraft.

Abstract: Embodiments of a flight deck display system deployed onboard an aircraft are provided, as are embodiments of a method carried-out by a flight deck display system. In one embodiment, the flight deck display system includes a cockpit display device and a controller. The controller is configured to: (i) establish the speed trend of the aircraft over a predetermined time period; (ii) generate a primary flight display on the cockpit display device including a speed trend vector graphic representative of the established speed trend; and (iii) alter the appearance of the speed trend vector graphic in a first predetermined manner if a low speed change condition is detected during at least one of aircraft takeoff and landing.

Abstract: A system and method are disclosed for indicating to an aircrew of an aircraft an unstable approach to a desired landing. When the energy state of the aircraft exceeds a threshold, a suggested airspeed in consideration of the energy state is displayed. Additionally, a landing spots on a displayed runway are shown indicating where the aircraft would land in view of the energy state and where the aircraft is recommended to land in view of the current aircraft type and weight. A text message may also be displayed that conveys the ability of the aircraft to land.