Abstract: Air quality sensors are incorporated into an aircraft ventilation system in order to detect the nature and concentration of possible contaminants in the air flow passages. Data from the sensors may also be used to monitor air quality trends, determine corrective measures, and provide maintenance alerts. The sensors are provided at strategic locations throughout the ventilation system, such as before and/or after an air compressor and before and/or after a recirculation system, in order to identify where the problem is occurring.

Abstract: Actuators and methods useful in the operation aircraft flight control surfaces are disclosed. Some of the actuators and methods disclosed may be useful in the operation flight control surfaces when a fault condition such as a jam associated with an actuator is detected. An exemplary electromechanical actuator disclosed comprises: a motor; a first screw configured for translation movement relative to a structure of the aircraft when driven by the motor; a second screw mounted in series with the first screw; and a fuse element coupling the first screw and the second screw together to permit translation movement of the second screw together with the first screw. The fuse element may permit at least partial disengagement of the second screw from the first screw to permit translation of the second screw relative to the first screw. The fuse element may also allow an active flutter damping of the flight control surface. The fuse element may comprise magneto-rheological fluid.

Abstract: A fuel pipe for an aircraft having a wall made of a material including a matrix composed of an epoxy copolymer obtained through the reaction of a resin of the bisphenol A diglycidyl ether type with an amine hardener, and from 3 to 5% of an organically modified nanoclay by weight of the epoxy copolymer, the nanoclay including layered magnesium aluminum silicate platelets, and reinforcing fibers embedded in the matrix. In one example, the resin is a bisphenol A epichlorohydrin based resin, a phenol, 4,40-(1-methylethylidene) bis-polymer with (chloromethyl) oxirane; the nanoclay is provided in a 4% weight proportion to the epoxy copolymer, and is a montmorillonite; the amine hardener is an amidoamine.

Abstract: A cabinet for installation in an aircraft, having a shell (22) defining a load-bearing structure of the cabinet and an outer panel (18) configured to be detachably connected to the shell (22), the outer panel (18) defining at least a part of the visible surfaces of the cabinet. The outer panel (18) is detachably connected to the shell (22) in a stationary position relative to the shell (22) through engagement of complementary attachment members (50, 51) respectively attached to the outer panel (18) and to the shell (22), the complementary attachment members (50, 51) allowing an adjustment of the stationary position of the outer panel (18) relative to the shell (22) when the outer panel (18) is detached from the shell (22). A method of manufacturing a cabinet for an aircraft is also discussed.

Abstract: A skin for an aircraft is configured to be disposed on a first rigid member and on a second rigid member. The second rigid member is movable with respect to the first rigid member and a distance is defined between the first rigid member and the second rigid member. A morphing member of the skin extends between the first rigid member and the second rigid member. The morphing member comprises first segments forming a first portion attached to the first rigid member and second segments forming a second portion attached to the second rigid member. The first and second portions are separated along a substantially linear seam in the absence of change in the distance and an orientation between the first rigid member and the second rigid member.

Abstract: An aircraft includes a fuselage defining a mold line, at least one frame disposed in the fuselage, at least one transparent pane suspended within the frame. The transparent pane is a deformable material that defines a first surface position h1 when not subjected to a differential pressure ?P thereacross and a second surface position h2 when subject to the differential pressure ?P thereacross. The first and second surface positions are defined with reference to the outside mold line. The first surface position h1 defines a reverse curvature. In response to the differential pressure ?P, the second surface position h2 includes bulging of the transparent pane by a predetermined distance ?h. The frame is constructed to be positioned within the aircraft such that the transparent pane presents a surface, when subjected to the pressure differential ?P, that is substantially consistent with the outside mold line of the vehicle.

Abstract: A method of adjusting an interior component to be received in a fuselage of an assembled aircraft, including determining a deformed configuration of a fuselage portion of a test rig, the fuselage portion in the deformed configuration being bent along its longitudinal axis and being representative of at least part of the fuselage of the assembled aircraft, deforming the fuselage portion to the deformed configuration so that the fuselage portion maintains the deformed configuration in a rigid manner, installing the interior component within the fuselage portion in the deformed configuration, determining changes required in a nominal configuration of the interior component based on a fit of the interior component within the fuselage portion in the deformed configuration, and applying the required changes to the nominal configuration of the interior component before installing the interior component within the fuselage of the assembled aircraft. A test rig is also discussed.

Abstract: Systems, methods and computer program products for controlling the movement of a cursor on a display device in an aircraft are disclosed. An exemplary method disclosed comprises the use of a digital representation of a grid defining a plurality of cells overlaying at least a portion of a display area of the display device to control the movement of the cursor over the display area. The grid may be invisible to the user during operation.

Abstract: Composite fasteners, associated blanks and also methods and apparatus for the installation of such fasteners are disclosed. An exemplary composite rivet (10) disclosed comprises an elongated body including braided reinforcement fibers (14) embedded inside the body and supported in a matrix material (16). Also disclosed are structural assemblies comprising composite fasteners and panels or other parts comprising composite and/or other materials.

Abstract: A seat attachable to a floor of a vehicle includes a seat frame movable between a first position and a second position and a mounting assembly attached to the seat frame and configured to be secured to the floor. The mounting assembly and seat frame are configured so that when the seat frame is in the second position first and second sliding assemblies of the mounting assembly are both located in forwardly extended positions and no part of the mounting assembly contacts the floor forward of a front connection of the mounting assembly.

Abstract: A method of and a system for presenting an operating status of an aircraft engine. The method comprises accessing a first indication indicative of a position of an aircraft engine start switch and accessing a second indication indicative of an aircraft engine start operating mode, the second indication having been generated based on an analysis of a parameter associated with an operating condition of the aircraft engine. The method, upon determining that the position of the aircraft engine start switch is an “on” position and the aircraft engine start operating mode is a healthy start causes the display of a visual indication indicative of the healthy start. The method upon determining that the position of the aircraft engine start switch is an “on” position and the aircraft engine start operating mode is an abnormal start causes the display of a visual indication indicative of the abnormal start.

Abstract: A device (10, 40, 50, 60) and a related method for selectively applying pressure to a fiber impregnated resin, where the device includes a thermally expansive material having a body (12) which extends in an axial direction from an upper terminal surface (14) to an opposite lower terminal surface (16), a first retaining member (18) affixed to one of the upper terminal surface and the lower terminal surface, wherein the first retaining member is configured to limit expansion of the thermally expansive material in a direction substantially perpendicular to the axial direction when the thermally expansive material is subjected to an increase in temperature.

Abstract: An outlet door is provided for covering an outlet defining an outlet area in a skin (24) of an aircraft component to exhaust a flow of heated air to an outside of the aircraft. The outlet door includes a body defining a door area and extending between a leading edge and a trailing edge and a linkage (38) connecting the body to the aircraft, permitting the body to transition between at least one of an open position and a closed position. In the closed position, the body at least partially occupies the outlet area. In the open position, the body forms an angle with the skin of the aircraft. The leading edge of the body and the skin of the aircraft define a separation (202) therebetween when the body is in the open position. The separation defines and air flow for mixing cold air with the flow of heated air.

Abstract: A partition assembly (16) for an aircraft cabin, including a bulkhead (18) with first (28) and second (30) internal compartments having respective first (32) and second (34) open ends defined in a same side of the bulkhead (18), one of the compartments being located aft of the other, a sliding door (36) slidingly supported within the first compartment (28) and slidable out of the first compartment (28) through the first open end (32), and a curtain (42) slidingly engaged to a curtain rail (40), the curtain receivable in the second compartment (30) and slidable along the curtain rail (40) out of the second compartment (30) through the second open end (34). An aircraft curtain rail is also described where the curtain rail and curtain track each have a non-rectilinear profile when viewed in a first plane and when viewed in a second plane perpendicular to the first plane. A method of manufacturing a curtain rail is also discussed.

Abstract: A support assembly (10) having a structural element (12) having first and second non-parallel adjoining surfaces (18), a bracket (14) attached to the structural element (12), and a component support (16). The bracket (14) has a first flange (20) including a first attachment surface (24) adhesively bonded to the first surface (18) of the structural element (12), a second flange (20) including a second attachment surface (24) adhesively bonded to the second surface (18) of the structural element (12), and a connection portion (48) interconnecting the first and second flanges (20), the connection portion (48) extending spaced from the structural element (12) such that a gap (52) is defined therebetween. The component support (16) is engaged to the first flange (20). The connection portion (48) may have a lower resistance to rupture than that of the first and second flanges (20). A method of removably securing a component to a structural element is also discussed.

Abstract: Systems, devices and methods a for assisting a pilot with aircraft landing are disclosed. One exemplary method comprises receiving data representative of a current approach/landing capability of the aircraft and data representative of an approach/landing intent of the pilot; and showing a combined indicator graphically and simultaneously indicating the current approach/landing capability of the aircraft and the approach/landing intent of the pilot on a display device of the aircraft. The approach/landing intent of the pilot may be graphically indicated via cooperation between a first graphical object of the indicator and a second graphical object of the indicator. The method may graphically indicate a system degradation affecting the current approach/landing capability of the aircraft with the same indicator.

Abstract: Apparatus and methods for assisting with maintenance and design of one or more structural elements of an aircraft are disclosed. One exemplary method comprises receiving actual utilization data for the aircraft and evaluating the actual utilization data with respect to at least one of a plurality of utilization criteria respectively associated with a plurality of utilization categories for the aircraft where the utilization categories are associated with respective predetermined maintenance programs for the structural element or for the aircraft as a whole. Based on the evaluation of the actual utilization data with respect to the at least one utilization criterion, one of the utilization categories is assigned to the aircraft. Based on the utilization category assigned to the aircraft, one of the predetermined maintenance programs is assigned to the structural element or to the aircraft as a whole.

Abstract: A vehicle seat includes a seat pan and a backrest. The seat pan and the backrest are positionable with respect to one another such that the seat is configurable into at least one of a taxi, takeoff and landing position, a napping position, and a sleeping position. A swivel is disposed beneath and supporting the seat, permitting the seat to rotate about a pivotal axis. Base tracking is disposed beneath and supporting the seat, permitting the seat to move in a lateral and a longitudinal direction. A first control is provided to lock and unlock movement of the seat in at least one of the lateral and the longitudinal directions. A second control is provided to lock and unlock the swivel. The swivel is permitted to be unlocked while movement of the seat in the lateral and the longitudinal direction is locked.

Abstract: Systems, devices and methods a for use with one or more high-lift flight control surfaces (24) of aircraft are disclosed. One exemplary method comprises receiving data representative of a commanded configuration (48) for a high-lift flight control surface (24); and on a display device (14) of the aircraft, showing an indicator (30) indicating the commanded configuration and a corresponding commanded position (50) for the high-lift flight control surface (24). The indicator (30) graphically indicates a correlation between the commanded configuration (48) and the corresponding commanded position (50) for the high-lift flight control surface (24).