An avionics power management panel and door assembly where the panel includes a cabinet including a set of walls at least partially defining an interior with an open face and door assembly includes a central panel a front panel that includes a set of rows with apertures formed between two adjacent rows and where the set of rows have a crimped profile.

A lever assembly for mounting to a removable plug-in module for selectively engaging a lip of a rack for effecting an injection of the plug-in module into the rack, and related kit(s) and method(s). The lever assembly includes a lever handle, an elastic bias element mounted to the lever handle, a pivot arm pivotally mounted to the lever handle, a pawl pivotally mounted to the lever handle, and a pivot axle. The pivot arm and the pawl abut one another so that a rotational force applied to a forward free end of the pivot arm, urging the pivot arm to rotate away from a lower interior surface of the lever handle, is transmitted to the pawl so that a rearward tip of the pawl is urged to rotate upward.

The present invention concerns a backplane electronic board (20) having on inner face (142) suitable for being connected to electronic board connectors (12) and an outer face (143) suitable for being connected to an outer connector (15), the backplane board (20) being characterized in that it has blind holes opening on the inner face (142) of same, and holes opening on the outer face (143) of same, the holes being suitable for receiving press-fit connection elements and forming therewith an electrical connection point.

An aircraft comprising a fuselage (1) subdivided by a floor (2) into a top volume (3) and a bottom value (4) in which girders (5) extend supporting the floor and co-operating with the fuselage and the floor to define two lateral housings (6) that are of substantially triangular cross-section and that extend parallel to a longitudinal axis of the fuselage. Calculation units (100) are arranged in the lateral housings and each comprises a box (101) defining a main compartment containing calculation modules (122) insertable into the main compartment along an insertion axis through an opening in the compartment and connectable to the connectors (115) carried by a back wall (116) of the compartment so as to extend into the main compartment opposite from the opening, the insertion axis being substantially parallel to the longitudinal axis of the fuselage.

An avionics power management panel and door assembly where the panel includes a cabinet including a set of walls at least partially defining an interior with an open face and door assembly includes a central panel a front panel that includes a set of rows with apertures formed between two adjacent rows and where the set of rows have a crimped profile.

A magnetically latched installation and extraction mechanism for an avionics display unit or other Line Replaceable Unit (LRU) installable in, and extractable from, a vehicle instrument panel includes a bezel attachable to the LRU, the paddle or the bezel including magnets embedded into opposing corners configured to attract the magnetic surfaces of, or the embedded magnets in, the opposing bezel or paddle. The LRU may include hinged paddles having an open position for installing/extracting the LRU from the instrument panel and a stowed position substantially flush with the surface of the bezel, the paddles corresponding to the embedded bezel magnets. Magnets embedded in the hinged paddles may secure the paddles in the stowed position via attraction to the bezel magnets.

A supporting structure of optimized volume includes at least two vertical structural elements having a front face and a rear face. Modules including electronic equipment items are fixed onto the front face of the vertical structural elements. Use in particular can be for the integration of avionics modules on aircraft.

An aircraft seating assembly including a replaceable underseat passenger accommodation feature tray includes passenger seats incorporating in-flight entertainment (IFE) system components for the use of the occupying passengers or neighboring passengers in the seats immediately behind. The IFE system components are connected by internal cabling paths within the seating assembly to contact points, and seat electronic boxes (SEB) mounted to a replaceable passenger accommodation feature tray provide IFE services to the system components. The SEB is connected to a second set of contact points on the feature tray by cabling paths that circumvent the spreader and leg structures of the seating assembly. When the feature tray is fully mounted to the seating assembly, the SEB is connected to the IFE system components through the cabling paths and contact points at which the cabling paths terminate, each contact point on the feature tray having a counterpart in the seating assembly.

Internal interchangeable modular avionics platform assemblies and methods for removably mounting and interchanging modular avionics platforms within an aircraft. In some embodiments, modular avionics platform assemblies may include a modular avionics platform configured to support various avionics equipment, suitable for removable mounting within a forward fuselage, and interchangeable with a number of alternate platforms. A platform may include a frame structure, and mounting pins and a connector assembly disposed on the frame structure. The mounting pins may project outwardly from the frame structure to align with and detachably secure to corresponding airframe members of an aircraft when the frame structure is in a mounted position. The connector assembly may be disposed on the frame structure and have a plurality of connectors, including connectors for alternating current, direct current, and data. In some embodiments, the platform may also include an environmental cooling system disposed on the frame structure.

A guard for a backshell of an aircraft avionics unit is disclosed herein. The guard includes a guard body having a first feature formed therein to slidably receive a first portion of the backshell, a second feature formed therein to slidably receive a second portion of the backshell and a third feature formed therein to protectively cover a mating connector area when the backshell has been slid into the guard body.