Abstract: An aircraft fuselage element (26) with a fuselage body (30) which forms an internal cavity (40) and which includes a viewing window (32, 34). To provide for taking substantially distortion-free high-resolution pictures in the infrared wavelength range and from a large angular range the fuselage body (30) is mounted for rotation about an axis of rotation (36).

Abstract: For use on board a mobile means of transport (eg. aircraft, bus, ship), a heating system and method are described which lead to a reduction of peak demand in the on-board kitchen energy supply system relating to the integrated heating appliances for the warming or heating of food. For this, latent or thermochemical heat storage units are used which are fully integrated into the structural elements of the heating appliance in question and heats the product in such a way that there is sufficient heat output, while at the same time, the absolute temperature is limited by means of an appropriate choice of heat storage material for product enhancement.

Abstract: A window assembly for an aircraft fuselage comprises an exterior transparent panel and an interior transparent panel positioned in an opening of the fuselage. At least one of the transparent panels may be relatively lightweight and the exterior transparent panel may be spaced apart from and in overlying relationship with the interior transparent panel. To ameliorate pressure build up in the spaced apart area, a pressure modulator, such as a vent, may be provided.

Abstract: An acoustical and thermal insulation product suitable for use in an aircraft is provided, comprising: an insulation layer formed from at least one sheet of insulation material, and a plurality of elongated reinforcing members for reinforcing the insulation product, wherein the plurality of elongated reinforcing members comprises fiber glass and a resin.

Abstract: An aircraft cabin module of an elongated rectangular shape and that includes two large walls connected by two small walls, a service module arranged along a wall separating the module from an aisle, a door mounted in an opening implemented in a small wall, and at least one seat having at least one configuration in which it is positioned longitudinally in relation to the direction of movement of the airplane. Each module includes elements configured to form a bedding surface for at least one passenger.

Abstract: A mobile aircrew restraint system includes a track system and a trolley which runs along the track and carries a retractor which releases a webbing strap attached to a harness. The track is preferably an extruded or sectioned track which follows contours of an aircraft interior and may be removable and/or retractable to allow additional room for oversize cargo. The trolley includes an interlock pin which cooperates with interlock holes spaced one to two feet apart along the track, and includes a release handle for disengaging the interlocking pin. The strap retractor is attached to the trolley and is controllable to limit the payout of the webbing strap. The harness is worn by an aircrew member and is attached to the webbing strap by releasable buckles.

Abstract: A modular communication fixture is installed in a passenger aircraft adjacent to an entrance and exit area adjoining a passenger boarding door. The fixture includes a housing, at least one access door that is selectively movable to an open position and a closed position relative to the housing, an information and communication terminal arrangement that is installed at least partly in the housing and that includes a control section, and a seat that is adapted to support a person seated thereon and that is arranged movable into and out of the housing. In the open position, the at least one access door permits access to the control section and the seat, and extends into the entrance and exit area. In the closed position, the at least one access door prohibits access to the control section and the seat, and does not obstruct the entrance and exit area.

Abstract: One advantageous embodiment of the present invention is a variable-duct support assembly (14) for mounting one or more ducts (12a-12c) thereon. This variable-duct support assembly (14) includes one or more rails (18) each having a groove (40). Each groove (40) has one or more pairs of support brackets (20) positioned therein for supporting a proximal surface (22) of the ducts (12a-12c). The support brackets (20) are coupled to one or more flexible bands (24) and utilized for clamping the duct (12a-12c) between the support brackets (20) and the flexible bands (24). The flexible bands (24) are intended to contact and wrap around a distal surface (26) of the duct (12a-12c) so as to distribute a load substantially across the distal surface (26). Likewise, the support brackets (20) each include support portions (28) for distributing the load substantially across the proximal surface (22) of each duct (12a-12c).

Abstract: The present invention is directed toward clamping apparatus and methods for holding an item to an electrically conductive structure. In one embodiment, the clamp includes a strap, a fastener, a cushion, and a conductive material. The strap provides the structural strength for holding the item. The fastener is coupled to the strap for securing the strap to the structure. The cushion is disposed within the strap to at least partially isolate the item from shock and vibration transmitted through the strap. The conductive material is held by the cushioning material at least at a portion of the interior surface of the cushioning material. The conductive material is electrically coupled to the strap.

Abstract: A lavatory complex for an aircraft. The lavatory complex includes a male lavatory facility and a female lavatory facility. The male lavatory facility includes stall units and may include urinals. The female lavatory facility includes stall units. Each stall unit suitably includes a single commode. The male and female lavatory facilities include at least one sink separated from the stall units by stall unit doors. The lavatory complex may include sinks that are not located within either the male or female lavatory facilities. A lavatory may include illuminating indicators; an illuminated, folding, baby changing station; a vanity; a self-cleaning toilet; and/or an illuminated faucet.

Abstract: A method and system for controlling a movable appendage on an aerospace vehicle independent from the position of the aerospace vehicle. First and second beacons containing actual position information for the movable appendage are tracked and acquired by first and second beacon tracking sites. The beacon tracking sites report the azimuth and elevation data relating to the position of the movable appendage to a processor where a correction command is determined based on an error calculated from the position data and a desired position. The correction command is communicated to the movable appendage so that appropriate correction to the desired position can be made.

Abstract: A seat track cover for transferring at least one of electrical power and data between two seats. The cover has a housing and a cable. The housing is sized to extend between a first seat leg assembly of a first seat and a second seat leg assembly of a second seat. The housing comprises a channel forming a first aperture at one end and a second aperture at a second end opposite the first aperture. The cable is seated within the housing and has a length at least equal to the length of the housing. The cable comprises a first connector and a second connector. The cable is seated within the housing such that the first connector is at the first aperture of the housing and the second connector is at the second aperture of the housing. The first connector couples with the first seat leg assembly and the second connector couples with the second seat leg assembly when the housing is positioned between the first seat leg and the second seat leg.

Abstract: A drain, for example for an aircraft engine support strut, arranged on the trailing edge of the rear secondary structure of the strut. The drain includes a conduit with a substantially horizontal axis and a substantially rectangular cross-section, taken in a plane parallel to the trailing edge, the conduit closed at an outer extremity by a terminal portion with a substantially ogival cross-section taken in the axis of the conduit and including at least one opening for drainage with an elongated shape on at least one of the opposing lateral walls.

Abstract: The invention includes a method of mounting a component to the skin of an aircraft. The component can include a drain valve, a gas cap, other external fuel instrumentation such as sensors, and antennae. One aspect of the invention includes a new method of mounting a drain valve to an aircraft fuel tank. The drain valve in the method includes any conventional drain valve having a stem and a flange that surrounds the stem. The method includes applying a material around a drain opening of the fuel tank; the material directs an electric charge away from the drain valve.

Abstract: An apparatus for supporting an aircraft system interconnect member between a strut and an engine of the aircraft. The apparatus includes a disconnect panel near the engine through which the interconnect member is connected with the engine, and a support structure movably attached to the strut and that supports the interconnect member near the strut.

Abstract: A cable raceway assembly includes an elongated raceway adapted for being mounted to a supporting structure. The raceway defines an open, upward-facing trough for receiving a cable and includes a mounting structure for attaching the raceway to the supporting structure. A fluid-resistant cover is attached to the raceway. The cover encloses at least a portion of the trough and forms a flowpath for directing fluid over and away from the trough.

Abstract: The invention relates to a device for fastening an in-fill panel element to a plane panel element of a covering for an aircraft, the in-fill panel element and the panel element being releasably interconnected at longitudinal sides facing each other, a transverse pin being arranged at least in the end portion of a longitudinal side so that a hook element arranged in the corresponding end portion of the other longitudinal side is able to clampingly engage with a hook opening, in such a manner that a covering surface of the in-fill panel element is arranged so as to be even with a covering surface of the panel element.

Abstract: A pivoting aircraft wing and associated system and method are provided. The pivoting aircraft wing includes a wing member, a carry-through structure, and a spar box assembly pivotally connected to the carry-through structure. The spar box assembly extends longitudinally within the wing member. The spar box assembly comprises a spar box and a bearing support structure attached to the spar box. The aircraft wing further includes a plurality of bearings disposed within a plurality of bearing races defined by the bearing support structure and carry-through structure. The plurality of bearing races advantageously define an arcuate path of rotation such that the wing member is capable of rotating about a virtual axis of rotation.

Abstract: A fairing arrangement for bridging an aircraft fixed structure (14) and a control surface (10) hingedly mounted on and angularly displaceable with respect to the aircraft structure is provided, together with a method of producing a flexible seal member for such an arrangement. The fairing arrangement includes first and second fairing portions (22, 24) on the fixed aircraft structure (14) and control surface (10) respectively with an intermediate flexible seal (26) disposed between them. The flexible seal (26) is of composite construction being made of rubber-like material with a series of reinforcing plies (341 to 345). The plies are of fabric construction and the seal is deformable to accommodate differential movement between the first and second fairing portions (22, 24) to provide a continuous seal therebetween.

Abstract: A mounting bar system permitting infinite adjustability in mounting avionics-components trays and Dzus-mounted avionics in at least one aircraft cockpit instrument panel assembly. Each mounting bar is slotted along its longitudinal axis. The slot is made to include the shape of a T such that a wider channel exists below the opening of the slot. Spring-loaded nut assemblies set to receive mounting screws from the avionics-components trays are fit within the T slot. Friction provided by the spring holds the nut assembly at any desired location within the T slot. As the nut assembly can be positioned at any location within the T slot, the mounting bar can readily be adjusted to support any avionics-components tray intended for at least one aircraft cockpit instrument panel assembly.

Abstract: A gas turbine engine (10) includes a first fire zone (Zone 3) in the region of a core of the engine and a second fire zone (Zone 1) in the region of a fan case of the engine, the first and second fire zones being separated by fire walls. The first fire zone is located generally radially inwardly of the second fire zone but includes a bifurcation part which extends radially outwardly of the remainder of the zone for limited circumferential extent. The engine further includes a disconnect panel (52) mounted on the fan case (32) to extend radially outwardly therefrom, the disconnect panel (52) forming a fire wall and providing means for pipes and harnesses (44) to be routed therethrough.

Abstract: An insulation baffle for a mobile platform. The baffle is secured to a structure separating different lobes of the mobile platform. The baffle includes a main body portion and at least one blow out portion. A perimeter of the blow out portion is defined by at least one recess. The recess also forms a web portion that connects the blow out portion with the main body portion. A depth of the recess is predetermined such that the web portion formed by the recess will sever when a pressure differential between the different lobes exceeds a predetermined threshold. When the web portion severs at least a section of the blow out portion separates from the main body portion to air to pass between the lobes so that the pressure differential is reduced to approximately zero.

Abstract: A detachable tray of the type usually pivotally attached to the seat back of a conventional airliner includes a layer of threat-resistant material for precluding penetration of a projectile from a firearm or sharp edged or sharp pointed weapon and serves in the manner of a shield to prevent injury to a person's shielded body parts. Where the economics of manufactur permit, the whole tray may be made of threat-resistant material. One or more handles or straps may be disposed on the bottom side of the tray to facilitate manipulation in positioning the tray to render it most effective to ward off an attack.

Abstract: Methods and systems for removing material from aircraft flight surfaces are disclosed herein. In one embodiment, an aircraft nacelle includes an inlet housing having a lip, a wiper positioned at the lip and movable relative to the lip, and a drive assembly positioned at least partially within the inlet housing and operably coupled to the wiper. The drive assembly is configured to move the wiper relative to the inlet housing to remove insect buildup and/or other material from at least a portion of the lip. The inlet housing can further include an interior surface and an exterior surface radially outward of the interior surface. The wiper can include a first end portion proximate to the interior surface and a second end portion proximate to the exterior surface.

Abstract: A locking device with a solenoid release actuator includes a housing, a plunger axially slidable within the housing, a biasing member for biasing the plunger in a first direction, one or more locking balls, and the locking balls disposed in an aperture in the housing, the plunger having a portion thereof containing at least one recess for receiving the balls, a member to be locked being held in a first locked position with the plunger in a first locking position and the balls in a radially outward position, the plunger being positioned axially such that the recesses therein are not in alignment with the apertures, and a solenoid coil disposed in the housing around the plunger, for inducing a magnetic force to move the plunger against the biasing member such that the recesses align with the apertures and the balls are movable radially inward into the recesses thereby releasing the locked member.

Abstract: A conformal air defense (CAD) system is provided which is adapted to be attached externally to an aircraft as an appendage. The CAD system includes a conformal mounting adapter having an aircraft-to-adapter interface and upper adapter side. A mounting structure is provided which has an adapter interface and a mounting side, wherein the adapter interface is attached to the upper adapter side. A missile countermeasures system is mounted on the mounting side of the mounting structure. And a cover substantially encloses the countermeasures system, wherein the cover is removably fastened to the mounting side of the mounting structure.

Abstract: A method and system for controlling a movable appendage on an aerospace vehicle independent from the position of the aerospace vehicle. First and second beacons containing actual position information for the movable appendage are tracked and acquired by first and second beacon tracking sites. The beacon tracking sites report the azimuth and elevation data relating to the position of the movable appendage to a processor where a correction command is determined based on an error calculated from the position data and a desired position. The correction command is communicated to the movable appendage so that appropriate correction to the desired position can be made.

Abstract: Device for attachment of an aircraft windshield. The device comprises a monoblock flange (14). The flange is fixed to the structure (12) of the aircraft by screws (16), so as to trap a peripheral edge of the windshield glass (10) between the flange and the structure. A dry monoblock seal (18) surrounds the peripheral edge of the windshield, such that the seal alone provides leak tightness between the inside and the outside of the aircraft. Preferably, the screws (16) are in contact with the flange (14) through plane surfaces perpendicular to the center lines of the screws. At least one second dry monoblock seal (20) may also be placed between the flange (14) and the structure (12).

Abstract: An air intake of a turbofan engine, capable of being fixed at the front of an engine casing enclosing the fan. The air intake includes an annular inner wall, an annular outer cowl radially spaced apart from the inner wall and of the outer cowl, a front annular partition linking downstream ends of the inner wall and of the outer cowl, a rear annular flange located in an extension of the inner wall to fix the air intake in front of the engine casing, and a front annular lip that forms with the front partition an annular de-icing chamber capable of being connected to a defrosting system. The air intake is made in at least two separable parts. The separation plane of the two parts passes outside the de-icing chamber, the inner wall, and the rear flange, and cuts out a dome in the outer cowl and a crescent with rectilinear edge in the rear partition.

Abstract: An aircraft floor panel (10) comprising a plurality of layers (18) cured together to form a lower support level (20) and an upper heater level (22), and a metal face sheet (16) for protecting the underlying layers (18) from floor-traffic related damage. A pressure sensitive adhesive (32) (or other adhesive which retains elasticity after bonding) is used to bond the metal face sheet (16) to the underlying support/heater layers (18) so that the different rates of thermal expansion can be accommodated during curing and cooling steps of the manufacturing process.

Abstract: A method for positioning a cable in a recess behind a fixed structure, e.g. a storage bin, in an aircraft. A portion of the cable is enclosed in a conduit. Panels adjacent the structure are removed to partially expose the recess and at least one stringer. The conduit is directed into the recess from adjacent one end of the structure until the conduit passes another end of the structure, and the conduit is fastened to the stringer(s). The method provides an easy way to route cable behind a fixed structure without removing the structure and without having to make holes in the aircraft.

Abstract: A method and apparatus contains and drains leakage from fluid system piping on a mobile platform such as an aircraft. A generally U-shaped channel is formed having outwardly oriented edge flanges and either integral or attached end plates. A pair of drain connections is disposed adjacent to each end plate. A group of fluid lines including at least one flammable fluid line is loaded within the U-shaped channel. A cover plate having outwardly oriented edge flanges aligning with the U-shaped channel edge flanges is positioned over the U-shaped channel. The edge flanges of both the cover plate and the U-shaped channel are joined with a seal such that a fluid-tight assembly results. Fluid leakage from any of the group of enclosed fluid lines discharges through the pair of drain connections. One of the end plates forms a firewall connectable to an engine firewall boundary.

Abstract: An interactive kiosk that permits the user to create custom postcards composed of photographs taken with the user's own digital camera. The postcards will be printed instantly by reading the memory (via camera's memory card or by wire transfer or infrared transfer of images) of the user's digital still or video camera. The kiosk contains a programmed computer that guides the user through the transfer and postcard creation process. The photograph/s will be printed in high quality color or black and white on one side with various options for borders and text messages. The back of the postcard will resemble a traditional postcard with space for a message to the recipient and the recipient's address.

Abstract: An armrest assembly for an aircraft. The armrest assembly includes an insert. The insert includes a flange for coupling to an aircraft interior panel. The insert also includes a protruding portion. The protruding portion includes a cavity. The cavity has a length greater than 12 inches and has a width greater than 2 inches. The armrest assembly also includes an armrest. The armrest is attached to the cavity. The armrest includes an upper surface for supporting the arm of an aircraft pilot or passenger. The armrest's upper surface has a length that is greater than 12 inches and has a width that is greater than 2 inches.

Abstract: An aircraft includes a cover wall without a door so that passengers cannot go back and forth between a flight deck and a cabin. A device for indicating urgent closing is provided in one of the flight deck and cabin, and a closing control part which closes information machines and equipment so that information regarding activity of the passengers in the cabin does not transmit to the flight deck when the urgent closing indication means indicates an urgent closing state. A device for communicating outside of the aircraft is provided at the cabin, allowing communication with the outside, so that suicidal-explosion terrorism can be prevented.

Abstract: Structural assembly of part of an aircraft and aircraft, particularly a rotary-wing aircraft, comprising such a structural assembly. The structural assembly comprises an outer structure (3) equipped with a floor (4), a cladding assembly (5) comprising cladding panels (6) forming a self-supporting envelope (7) which is arranged inside (9) the outer structure (3) and mounted on the floor (4), and a connecting system (10) for connecting the self-supporting envelope (7) to the outer structure (3). The connecting system (10) comprises a number of connecting means (11) which, by rigid and permanent connections, fix the self-supporting envelope (7) to the outer structure (3) and perform this rigid and permanent fixing only between the floor (4) of the outer structure (3) and ends (12) of cladding panels (6) of the self-supporting envelope (7).

Abstract: An electromechanical flight deck door locking system capable of functioning to keep a cockpit door locked in the event of an interruption in electrical power to the system. The flight deck door locking system includes a locking assembly including a locking component and a manually graspable handle for displacing the locking component. Further, the locking system includes an electronic control panel configured to receive data from an individual seeking access to the cockpit and for electrically locking and unlocking the locking assembly. The locking system also includes a mechanical locking assembly, such as a key lock, whereby a user can use a key to lock and unlock the door if electrical power to the system is unavailable.

Abstract: An airborne platform comprising: (a) an aerodynamic body; (b) a protected element within the aerodynamic body; and (c) a cover, reversibly secured to the aerodynamic body, for protecting the protected element from an external atmosphere. The present invention is particularly suited for an electro-optical detection system equipped with an optical dome or window. Optical windows carried on airborne platforms are known to be particularly sensitive to the high temperatures generated by air friction at super-sonic speeds. By covering such a window when the airborne platform is in flight, and releasing the cover just before use, the electro-optical detection system equipped with the optical window can be made operative, even at airborne platform speeds of several Mach and higher.

Abstract: A dual stage hybrid inflation device includes a pressure switch that prevents the second stage pyrotechnic gas generator from being initiated when the additional heat and gas would overpressurize the first stage pressure vessel. As the pressurized gas stored in the first stage pressure vessel escapes the first stage pressure vessel, the pressure in the first stage pressure vessel drops. If the pressure in the first stage pressure vessel drops below the threshold pressure of the pressure switch, the pressure switch closes allowing the voltage signal to reach the pyrotechnic gas generator thereby initiating the second stage gas source. In an alternative embodiment, the pressure transducer is replaced by a pressure transducer or a temperature transducer and timing circuit.

Abstract: A detachable tray of the type usually pivotally attached to the seat back of a conventional airliner includes a layer of threat-resistant material for precluding penetration of a projectile from a firearm or sharp edged or sharp pointed weapon and serves in the manner of a shield to prevent injury to a person's shielded body parts. Where the economics of manufactur permit, the whole tray may be made of threat-resistant material. One or more handles or straps may be disposed on the bottom side of the tray to facilitate manipulation in positioning the tray to render it most effective to ward off an attack.

Abstract: The invention relates to a decompression unit for equalizing an explosive air pressure between pressurized areas of an aircraft, which have different air pressure conditions and are separated by a wall structure. An air chamber, whose shape alters by contraction (1), is located inside an exterior zone of the cabin (6) and is subjected to an ambient air pressure (p1), said chamber constituting the decompression unit in concrete terms. The wall of the air chamber (1) is perforated. The air chamber is mounted in the vicinity of the periphery of an air pressure equalization flap (2), which is fixed inside an air equalization cavity (9). Said air chamber is connected to a locking device (4), which likewise fixes the air pressure equalization flap in the air equalization cavity.

Abstract: A method and system for controlling a movable appendage on an aerospace vehicle independent from the position of the aerospace vehicle. First and second beacons containing actual position information for the movable appendage are tracked and acquired by first and second beacon tracking sites. The beacon tracking sites report the azimuth and elevation data relating to the position of the movable appendage to a processor where a correction command is determined based on an error calculated from the position data and a desired position. The correction command is communicated to the movable appendage so that appropriate correction to the desired position can be made.

Abstract: A method and apparatus contains and drains leakage from fluid system piping on a mobile platform such as an aircraft. A generally U-shaped channel is formed having outwardly oriented edge flanges and either integral or attached end plates. A pair of drain connections is disposed adjacent to each end plate. A group of fluid lines including at least one flammable fluid line is loaded within the U-shaped channel. A cover plate having outwardly oriented edge flanges aligning with the U-shaped channel edge flanges is positioned over the U-shaped channel. The edge flanges of both the cover plate and the U-shaped channel are joined with a seal such that a fluid-tight assembly results. Fluid leakage from any of the group of enclosed fluid lines discharges through the pair of drain connections. One of the end plates forms a firewall connectable to an engine firewall boundary.

Abstract: A method and system for controlling a movable appendage on an aerospace vehicle independent from the position of the aerospace vehicle. First and second beacons containing actual position information for the movable appendage are tracked and acquired by first and second beacon tracking sites. The beacon tracking sites report the azimuth and elevation data relating to the position of the movable appendage to a processor where a correction command is determined based on an error calculated from the position data and a desired position. The correction command is communicated to the movable appendage so that appropriate correction to the desired position can be made.

Abstract: A method and an arrangement for adjusting a door-side safety device of an airplane door is provided to further improve the ergonomics for the operation of the door. A safety shaft of a safety device arranged on the door side can be adjusted by a coupling device by a driving device arranged on the frame side between the locked condition and the secured locked condition. The safety shaft arranged on the door side is coupled by way of a coupling device arranged between the door and the frame with the driving device arranged on the frame side and connected by way of the operating shaft. This arrangement allows an operation of the door in the cabin interior by an operating element which is arranged on the frame side next to the door opening.

Abstract: The invention relates to a decompression unit for equalizing an explosive air pressure between pressurized areas of an aircraft, which have different air pressure conditions and are separated by a wall structure. An air chamber, whose shape alters by contraction (1), is located inside an exterior zone of the cabin (6) and is subjected to an ambient air pressure (p1), said chamber constituting the decompression unit in concrete terms. The wall of the air chamber (1) is perforated. The air chamber is mounted in the vicinity of the periphery of an air pressure equalization flap (2), which is fixed inside an air equalization cavity (9). Said air chamber is connected to a locking device (4), which likewise fixes the air pressure equalization flap in the air equalization cavity.

Abstract: An aircraft floor heating panel is constructed for mechanical strength and to meet special heating requirements next to a door in an aircraft. The panel has a lightweight core. Each surface of the core is first covered with at least one carbon-fiber reinforced composite layer for protection against deterioration. Each carbon fiber layer in turn is covered by a glass fiber reinforced composite layer for mechanical strength. A foil heater is arranged inside the composite panel coextensive with at least a portion of the panel area. A heat distributing metal plate covers the panel as an upper step-on surface. A heat insulating layer is bonded to the panel opposite the heat distributing metal plate. A triple heat control is provided for an increased safety against fire hazards.

Abstract: A differential pressure sensing release system and apparatus specifically adapted for use with an aircraft or spacecraft compartment panel. The apparatus utilizes a mechanism activated by a pressure differential acting on a diaphragm(s) to trigger a single latch bolt or series of latch bolts or other retention mechanisms, thereby releasing the panel. The apparatus thus provides a means of equalizing the pressure differential between adjacent compartments, eliminating potential damage due to forces created by the pressure differential.

Abstract: A method and system for controlling a movable appendage on an aerospace vehicle independent from the position of the aerospace vehicle. First and second beacons containing actual position information for the movable appendage are tracked and acquired by first and second beacon tracking sites. The beacon tracking sites report the azimuth and elevation data relating to the position of the movable appendage to a processor where a correction command is determined based on an error calculated from the position data and a desired position. The correction command is communicated to the movable appendage so that appropriate correction to the desired position can be made.

Abstract: The present invention provides a replacement cover or faceplate for use with an existing power port assembly on a commercial aircraft that provides additional connectivity to on-board systems using portable electronic devices, while minimizing the need for recertification for installation. The replacement cover or faceplate is installed within the existing structure of the power port assembly using existing bracketing and attachment points. The cover allows access to an existing power port while providing a plurality of connectors for connection to on-board systems.