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.

Abstract: A secure flat wall mounting rack for network service provider equipment and cabling is provided. The mounting rack not only restricts unauthorized access to network communication equipment, but is also properly labeled for authorized user. The rack is especially suitable for service demarcation applications involving patch panels. The flat wall mounting rack has a securing bar with a movable plate which, when extended, only allows authorized users to remove and/or access cabling connected to the service ports of an Ethernet service delivery switch. The securing bar also allows for securing service handoff modules to be secured to the same.

Abstract: A method and system are provided for generating a low airspeed warning in an aircraft. This method creates a scale factor that is a factor of engine thrust and aircraft altitude. A low airspeed threshold is determined that varies according to the aircraft altitude with respect to a predetermined altitude band and the engine thrust with respect to a predetermined engine thrust band. A low airspeed alert is generated in response to the determination of the low airspeed threshold. This method provides a pilot with earlier knowledge of low airspeed conditions when the aircraft is in a target altitude band, increasing the pilot's response time and thereby enhancing overall aircraft safety.

Abstract: A system and method for alerting a helicopter pilot to an undesirable operating condition during landing operations are provided. Avionics data are supplied from an avionics data source. A controller coupled to receive at least a portion of the avionics data from the avionics data source is configured, upon receipt of the avionics data, to determine when the undesirable operating condition exists and, upon determining that the undesirable operating condition exists, to generate an alert signal that provides notification to the helicopter pilot to increase helicopter airspeed.

Abstract: A system and method are disclosed for indicating to an aircrew of an aircraft a normalized runway icon to ensure visualization of a predicted touchdown point, runway length, stopping distance, energy state marking, and threat conditions, where normalization is referenced to typically available length for landing. Indications of present aircraft locations relative to the icons as well as alerts when thresholds are exceeded are provided.

Abstract: An exhaust gas recirculation system may include a header located at an end of a cooler, and a mixer for mixing exhaust gases and intake air within the header. The mixer may include a passage for receiving exhaust gases and an inlet for receiving intake air. The exhaust gases and intake air may collide at a substantially perpendicular angle within the mixer, and the mixer may further include an outlet for emitting mixed exhaust gases and intake air.

Abstract: A system and method are disclosed for indicating to an aircrew of an aircraft a normalized runway icon to ensure visualization of a predicted touchdown point, runway length, stopping distance, energy state marking, and threat conditions, where normalization is referenced to typically available length for landing. Indications of present aircraft locations relative to the icons as well as alerts when thresholds are exceeded are provided.

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.

Abstract: A system and method provide an alert to a pilot of an aircraft aurally with a given volume and inflection, and/or visually with a text message which includes color, font, and pitch (size). The alert is rendered in distinct fashion for the expected and unexpected cases, e.g., an intended runway and an unintended runway. In a preferred embodiment, the alert for the intended runway is changed to a confirmation level, or one that is less likely to interfere with other information flow, while the alert for the unintended runway would be provided in a more conspicuous manner.

Abstract: Systems and methods that alert the pilot of the unusual negative pitch attitude. Additionally, the system can bias a “sink rate” envelope toward a more sensitive direction, such that the pilot can be alerted while (or before) a large sink rate is built up during an unusual negative pitch attitude condition.

Abstract: A system and method monitor aircraft state parameters, for example, aircraft movement and flight parameters, applies those inputs to a spatial disorientation model, and makes a prediction of when pilot may become spatially disoriented. Once the system predicts a potentially disoriented pilot, the sensitivity for alerting the pilot to conditions exceeding a threshold can be increased and allow for an earlier alert to mitigate the possibility of an incorrect control input.

Abstract: A secure flat wall mounting rack for network service provider equipment and cabling is provided. The mounting rack not only restricts unauthorized access to network communication equipment, but is also properly labeled for authorized user. The rack is especially suitable for service demarcation applications involving patch panels. The flat wall mounting rack has a securing bar with a movable plate which, when extended, only allows authorized users to remove and/or access cabling connected to the service ports of an Ethernet service delivery switch. The securing bar also allows for securing service handoff modules to be secured to the same.

Abstract: A system and method is provided for controlling the speed of an aircraft with a speed brake during landing. The system includes a speed brake control system and a speed brake controller coupled to the speed brake control system for arming the speed brake. An alert generator is coupled to the speed brake controller for generating an alert when the speed brake is not armed.

Abstract: A method and system are provided for generating a low airspeed warning in an aircraft. This method creates a scale factor that is a factor of engine thrust and aircraft altitude. A low airspeed threshold is determined that varies according to the aircraft altitude with respect to a predetermined altitude band and the engine thrust with respect to a predetermined engine thrust band. A low airspeed alert is generated in response to the determination of the low airspeed threshold. This method provides a pilot with earlier knowledge of low airspeed conditions when the aircraft is in a target altitude band, increasing the pilot's response time and thereby enhancing overall aircraft safety.

Abstract: A system and method are provided for modifying the position or shape of a premature descent protection envelope with regard to a runway when an aircraft making an approach to the runway is below the nominal approach path and has a flight path angle greater than the nominal approach path angle.

Abstract: A method of dynamically analyzing source code for generating usage hints while editing the source code is disclosed. A parse tree data structure is generated for each function called. The incoming and outgoing arguments in the parse tree are identified. A user calls the function by entering arguments as part of the function-call. The user's input arguments are associated with the corresponding argument in the parse tree. Relevant preconditions and post-conditions of the nodes surrounding the current location in the parse tree are analyzed to provide usage hints for the completion of the function call. In the case of a completed function call argument entered by the user, the type and number of arguments in the completed function call are compared to the required type and number of arguments of the function to validate the function call. Error messages are provided in the event of an invalid call.