Abstract: An aircraft includes a fuselage including a plurality of frame members disposed at predetermined intervals in a longitudinal direction of the fuselage and a plurality of stringers extending substantially linearly in the longitudinal direction. The fuselage defines an aircraft interior. A compartment is located in the interior of the fuselage. The compartment defines an interior area. A first one window assembly is mounted to an upper portion of the fuselage for introducing daylight into the interior area. The first window assembly is flanked by adjacent frame members of the plurality of frame members and adjacent stringers of the plurality of stringers. The first window assembly includes a window pane, an inner cover and a retainer. The inner cover introduces daylight from the window pane into the interior area. The retainer secures the window pane and the inner cover to the fuselage.

Abstract: Structures and methods for joining composite fuselage sections and other panel assemblies together. In one embodiment, a shell structure configured in accordance with the present invention includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can further include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion.

Abstract: To easily and inexpensively provide a window of an aircraft having sufficient electromagnetic shielding performance and environment-resistant sealing performance, an aircraft, and an assembly method for a window of an aircraft. A conductive seal member 60 is sandwiched between a conductive film 41 and an outer retainer 22. In the conductive seal member 60, thin wire-like materials 62 made of a conductive material such as aluminum are embedded in a seal member body 61 made of a material, such as silicone rubber, having an electric insulating property, waterproofness and pliability. An electromagnetic shielding effect, and environment-resistant sealing properties such as an electric insulating property and waterproofness can be both ensured by the conductive seal member 60.

Abstract: A window body constituting a window of an aircraft includes an electromagnetic shield film, and a conductive paint is applied to an outer perimeter edge face of the window body. A fixing member secures the window body to an airframe with a gasket seal and a window frame interposed therebetween. The fixing member has a first bonding surface on which a conductive film is formed. The first bonding surface is in direct contact with the gasket seal. An electrical path is formed through the electromagnetic shield film, the conductive paint, the gasket seal, the fixing member, and the window frame.

Abstract: A window for a vehicle includes at least one transparent pane suspendable within a frame. The transparent pane comprises a deformable material. The transparent pane defines a first surface position h1 when not subjected to a pressure differential thereacross and a second surface position h2 when subject to the differential pressure thereacross. The first and second surface positions are defined with reference to an outside mold line. The first surface position h1 defines a reverse curvature with respect to the outside mold line. 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 vehicle 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: The present invention provides polyurethanes including a reaction product of components including: (a) an isocyanate functional urethane prepolymer comprising a reaction product of components including: (i) about 1 equivalent of at least one polyisocyanate; and (ii) about 0.1 to about 0.5 equivalents of at least one diol having 2 to 18 carbon atoms; and (b) about 0.05 to about 0.9 equivalents of at least one branched polyol having 4 to 18 carbon atoms and at least 3 hydroxyl groups; and (c) up to about 0.9 equivalents of at least one polyol different from branched polyol (b) and having 2 to 18 carbon atoms, wherein the reaction product components are essentially free of polyester polyol and polyether polyol; compositions, coatings and articles made therefrom and methods of making the same.

Abstract: An improved vibration damping apparatus is provided for use with window structures, including windows used in vehicles, aircraft, and spacecraft. The vibration damping system includes at least two separate layers of solid material that are typically substantially clear at visible wavelengths, in which the two layers are spaced-apart by a predetermined distance to form a space or gap therebetween. This gap will be of a size and shape to enhance vibration damping when it is filled with a gaseous compound, such as air. The air-film vibration damping system created by the above structure can be applied to an external pane of a window structure, or to the interior pane of a window structure, or perhaps to both an exterior pane and an interior pane of the same window structure, if desired.

Abstract: An assembly for shielding an aircraft from electromagnetic energy may include a window mounting configured to be conductively coupled to an aperture in a fuselage of an aircraft. The window mounting may include a window pane having an electromagnetically-reflective coating for reflecting electromagnetic energy. The window pane may remain electrically isolated from the fuselage prior to the electromagnetic energy exceeding a frequency of approximately 1 GHz. The window mounting may further include a capacitive gasket capcaitively coupling the window pane to the fuselage after the frequency of the electromagnetic energy reflected by the window pane exceeds approximately 1 GHz.

Abstract: The present invention provides polyurethanes including a reaction product of components including: (a) an isocyanate functional urethane prepolymer comprising a reaction product of components including: (i) about 1 equivalent of at least one polyisocyanate; and (ii) about 0.1 to about 0.5 equivalents of at least one diol having 2 to 18 carbon atoms; and (b) about 0.05 to about 0.9 equivalents of at least one branched polyol having 4 to 18 carbon atoms and at least 3 hydroxyl groups; and (c) up to about 0.9 equivalents of at least one polyol different from branched polyol (b) and having 2 to 18 carbon atoms, wherein the reaction product components are essentially free of polyester polyol and polyether polyol; compositions, coatings and articles made therefrom and methods of making the same.

Abstract: A weatherproof surround, for a jettisonable panel (5) of a vehicle (1) such as a helicopter, possesses four confinement flanges (17-20) integrally formed with a projecting ridge for spring-clipping a corresponding locking strip. Longitudinal foldable shoulders connect the confinement flanges (17-20) to a central trunk (13). Each confinement flange (17-20) can be folded back through pivot angle (31) of at least 90°.

Abstract: Polymerizable liquid compositions of the polyurethane type, consisting of two components (A) and (B), wherein component (A) contains at least one cyclo-aliphatic diisocyanate monomer or a mixture of one cyclo-aliphatic diisocyanate monomer and a pre-polymer obtained by reaction, in the presence of an acid phosphate ester catalyst, between said cyclo-aliphatic diisocyanate monomer and one or more polyols having two or more hydroxy 1 groups per molecule and a molecular weight ranging from 50 to 2,000 g/mole; the second component (B) contains one or more polyols having a molecular weight ranging from 50 to 2,000 g/mole and a functionality between 2 and 5; in the absence of polyalkoxylated tertiary diamines and organometallic catalysts, said components (A) and (B) being present in a weight ratio which varies from 1:1 to 2:1 and the process for the production of organic glass starting from polymerizable liquid compositions of the polyurethane type.

Abstract: A system for shielding an aircraft from electromagnetic energy includes a fuselage, aperture, window mounting, and window plug. The fuselage provides an electrically conductive envelope. The aperture is disposed in the fuselage. The window mounting spans the aperture. The window plug spans the aperture. The window mounting and the window plug are electrically coupled to the fuselage and provide an electrical path spanning the aperture.

Abstract: A window shade assembly for a window includes a first member, a second member, a film, and an actuating device. The second member is disposed apart from the first member. The film has a first end coupled to the first member, a second opposed end coupled to the second member, an opaque portion, and a transparent portion. The actuating device is coupled to the first member or the second member for moving the first member or the second member to move the film between the first and the second members.

Abstract: An observation port (4) in a primary structure (13) of a helicopter cabin (0) is disclosed, which is arranged between a pilot's seat (2) and a co-pilot's seat (3). The observation port (4) is delimited from the interior by an inner screen (15), and from the atmosphere by an outer screen (16), wherein the pilot can observe the space underneath the helicopter cabin (0) through the observation port (4). As a result of the configuration of the observation port (4) the pilot can assume an ergonomic and relaxed seating position at any time, even when he is executing flights with suspended loads. By means of the observation port (4) and the windows (15, 16), which extend laterally between the two pilots' seats (2, 3), a novel unrestricted vertical visual frame of reference onto the suspended load is achieved, wherein the length of the load cable has practically no influence.

Abstract: Methods for attaching a window to an airframe, methods of maintaining structural integrity of an airframe while attaching a window to the airframe, and portions of an aircraft are set forth herein. One method for attaching a window to an airframe comprises the steps of: applying to a bonding surface of a nutplate an adhesive; inserting through an airframe hole a fixture attached to a nut of the nutplate, and applying tension to the fixture to hold the adhesive-coated bonding surface of the nutplate adjacent an interior surface of the airframe; allowing the adhesive to cure; removing the fixture from the nut of the nutplate; and installing a bolt through a hole of a retainer, through the hole in the airframe, and into the nutplate; the retainer being in contact with and securing the window to the airframe. The adhesive is selected such that very specific conditions are met.

Abstract: An aircraft window shade assembly is provided. The assembly includes an inboard shade, an outboard shade, a housing and a cover. The inboard and outboard shades each include a plurality of holes disposed along one side. The housing includes a transparent inboard panel, a transparent outboard panel, a pair of inboard guide slots to receive the inboard shade, a pair of outboard guide slots to receive the outboard shade, an inboard motor and an outboard motor. The inboard motor is coupled to a drive gear sprocket having a cylindrical outer surface and a plurality of teeth extending radially therefrom that mesh with the plurality of holes in the inboard shade, and moves the inboard shade between open and closed positions. The outboard motor is coupled to a drive gear sprocket having a cylindrical outer surface and a plurality of teeth extending radially therefrom that mesh with the plurality of holes in the outboard shade, and moves the outboard shade between open and closed positions.

Abstract: An aircraft window arrangement comprising a sidewall lining panel which is provided with a window opening, an inner window attached to the sidewall lining panel and extending across the window opening formed in the sidewall lining panel and an outer window arranged at a distance from the inner window and extending across a window opening formed in an aircraft outer skin. The aircraft window arrangement further comprises a window funnel including an inner rim facing the inner window and extending along a circumference of the window opening formed in the sidewall lining panel, and an outer rim facing the outer window and extending along a circumference of the window opening formed in the aircraft outer skin. The window funnel is formed separate from the sidewall lining panel. The window funnel may be attached to a retainer for retaining the outer window.

Abstract: A window element for a double-shell skin field of an aircraft fuselage cell includes a window frame having a window module disposed in the frame, wherein the frame is disposed in an opening of the double-shell skin field, and wherein the frame is connected to the double-shell skin field by a surrounding embrasure profile positioned against a core structure of the skin field at least in some regions, wherein the core structure includes an inner and an outer covering layer.

Abstract: A hybrid frame is fabricated by initially forming a stack of fibrous layers in an annular pattern. An annular metal trim is separately formed to conform with the annular pattern. The trim is trapped in a lower mold having a complementary lower mold channel. The stacked layers are trapped atop the trim in the lower mold channel. An upper mold is pressed atop the stacked layers for compression co-molding together in the lower mold the stacked layers and trim to co-form the hybrid frame.

Abstract: There is provided a cockpit window of an aircraft and the aircraft in which an electromagnetic shield film for preventing electromagnetic noise can be reliably and easily provided at low cost. An electromagnetic shield film is provided to a window part, and a conductive film is provided between the electromagnetic shield film and an outer retainer made of a conductive material. The conductive film is connected to the electromagnetic shield film via a connecting member is provided so as to be led to an outer perimeter side of the window part along an outer perimeter part of the window part, and is electrically connected to the outer retainer. With this configuration, a film made of a conductive material is formed without a gap at a joint portion between the window part and the outer retainer. Also, the conductive film is assumed to have flexibility.

Abstract: An interior lining interface incorporates a decorative interface ring having a substantially flat flange with multiple bearing ring bosses on an inner surface of the flange for engagement of an inner surface of a rim of a window ring. Multiple friction fit legs extend from the flange and are received within and constrained by the interface ring to the widow ring rim. A window reveal has a mating surface contacting the flange.

Abstract: A window reveal is secured to an aircraft interior sidewall panel by a plurality of clips. Each clip engages a tab on the reveal. A method for removing the reveal includes using a tool to disengage the clips. The tool includes a tapered portion having tips separated by a notch. Using the tool includes inserting the tapered portion into a slot in the reveal with the tab received in the notch, and pressing the tips through the slot until a back of the notch abuts against the tab and stops the movement of the tips. The notch has a depth that allows the tips to press against the clip, yet stops the tips from damaging the clip.

Abstract: A window replacement for filling a window frame in an aircraft is provided, in particular a passenger aircraft, the window replacement being fixable by a retainer in the window frame in place of the window assembly when the window assembly is removed. The window replacement includes a panel-shaped element with at least a single curvature, the panel-shaped element being made of a synthetic material. The window replacement is formed by a monolithic panel-shaped element. The panel-shaped element of the window replacement may also be formed by a sandwich panel. This allows a weight reduction in comparison with a window replacement of a metallic material.

Abstract: The nose section for a flying machine according to the invention comprises an enclosure delimiting a nose cone extending along a longitudinal axis (A-A?), the enclosure delimiting a window, and a glass closing the window extending transversely relative to the longitudinal axis (A-A?). The nose section includes an optical sensor, in particular a camera, positioned in the enclosure behind the glass. The enclosure defines a recess, the window covered by the glass being at least partially positioned in the recess.

Abstract: A fire retardant, transparent panel and method of making the panel, that is especially well suited for use on mobile platforms, and particularly on aircrafts. The panel is a composite of a transparent matrix and a plurality of fire-retardant nanoparticles. The nanoparticles have a diameter less than the visible spectrum of light, and in one form between about 0.1 nm to about 400 nm in diameter. The nanoparticles may be arranged randomly or in predetermined patterns within the matrix during manufacturing of the panel. The panel is lightweight, transparent and yet highly fire retardant.

Abstract: The invention relates to an aircraft opening window comprising at least one pane (2) equipped with a movable frame (3), the assembly comprising the said movable frame (3) and the said at least one pane (2) being movable relative to a fixed frame (1), an element (4) for maneuvering the said movable assembly, a device for locking/unlocking and opening/closing the said movable assembly actuated by the said maneuvering element (4) and means for guiding and supporting the said movable assembly.

Abstract: An aircraft window includes a microstructure so that light rays with a correspondingly large angle of incidence are reflected back to the exterior region. By contrast, light rays with another, i.e. smaller, angle of incidence are allowed to pass almost without hindrance. The microstructures are designed as optical prisms, wherein the order of magnitude of the prisms is in the region of light wave lengths.

Abstract: An electrically controlled dimmable window for aircraft includes a controller and power that eliminates the need for wiring connections to on-board systems. The controller is integrated into the sidewall in which the window is mounted. Power for controlling the window is derived from an energy harvesting device that generates power by converting thermal gradients, motion/vibration or light energy present near the window. The integrated controller includes passenger controls for adjusting the opacity of the window, power conditioning circuitry, an electrical power storage device such as a battery, a processor and a radio receiver. The window can be remotely controlled by a cabin attendant from a central controller that transmits window control signals to the radio receiver.

Abstract: An aircraft fuselage may include a barrel section having a side region. The fuselage may include a first cutout and a second cutout formed in the side region in side-by-side relation to one another. The fuselage may provide a direct load path extending along the barrel section. The load path may extend substantially continuously from a lower portion of the side region generally under the first cutout to an upper portion of the side region generally over the second cutout.

Abstract: The present invention relates to an aircraft window, of the type including a holding frame for securing the window to the fuselage of an aircraft and at least one pane mounted in the holding frame by a sealing system, the at least one pane having an inner surface and an outer surface, characterized in that: the pane includes, in a first state called the rest state, at least one concavity in its outer surface when there is no pressure difference between the outer surface and the inner surface of the pane, and the at least one concavity of the pane is at least partially eradicated in a second state in which there is a pressure difference between the outer surface and the inner surface of the pane.

Abstract: A low drag passenger-cabin window for use on an aircraft fuselage having a generally cylindrical shape, in which the as-manufactured geometry of the window is modified so that the shape of the window at cruise altitudes is aerodynamically optimized. The window comprises a pane of transparent material. The inner and outer surfaces of the peripheral portion of the pane as manufactured conform to a generally cylindrical shape, while the inner and outer surfaces of the medial portion of the pane as manufactured are depressed inwardly in a prescribed manner relative to the peripheral portion. The surfaces of the medial portion are adapted to deflect outwardly to conform to a generally cylindrical shape in response to a predetermined air pressure differential and/or a predetermined temperature gradient experienced at cruise altitude.

Abstract: A mechanism for operating a dual shade covering a window with a single handle. The mechanism provides a first glide attached by a pulley system to the first shade of the dual shade, and a second glide attached by a pulley system to the second shade of the dual shade. The first glide and the second glide are slidably disposed within a track assembly, and a master glide is disposed in the track assembly between the first glide and the second glide. The master glide engages the first glide to lower the first shade, and is detached from the first glide along the track assembly by a disengaging plate. The master glide engages the second glide to lower the second shade, and is detached from the second glide along the track assembly by a disengaging plate.

Abstract: A mechanism for operating a dual shade covering a window with a single handle. The mechanism provides a first glide attached by a pulley system to the first shade of the dual shade, and a second glide attached by a pulley system to the second shade of the dual shade. The first glide and the second glide are slidably disposed within a track assembly, and a master glide is disposed in the track assembly between the first glide and the second glide. The master glide engages the first glide to lower the first shade, and is detached from the first glide along the track assembly by a disengaging plate. The master glide engages the second glide to lower the second shade, and is detached from the second glide along the track assembly by a disengaging plate.

Abstract: The invention relates to a section of fuselage for an aircraft, including frames and bays for receiving cabin windows. According the disclosed embodiments, at least some of the frames include at least one frame segment that surrounds at least one bay, the frame segment having two branches that are disposed to the side of the bay. The ends of the branches are attached to each of the ends of the frame segment such as to form a Y.

Abstract: A window replacement for filling a window frame in an aircraft is provided, in particular a passenger aircraft, the window replacement being fixable by a retainer in the window frame in place of the window assembly when the window assembly is removed. The window replacement comprises a panel-shaped element with at least a single curvature, the panel-shaped element being made of a synthetic material. The window replacement is formed by a monolithic panel-shaped element. The panel-shaped element of the window replacement may also be formed by a sandwich panel. This allows a weight reduction in comparison with a window replacement of a metallic material.

Abstract: A method of fitting a fuselage shell of an aircraft with at least one window frame of a cabin window includes positioning an uncured laminate including a fiber-reinforced plastic-based composite material configured to form a fuselage shell on a mold surface. A window aperture is introduced into the laminate. A window frame including a fiber-reinforced plastic-based composite material is positioned on the laminate in a region of the window aperture. The laminate is cured under the action of pressure and temperature so as to connect the window frame with the laminate by a material bond.

Abstract: A compression mounted window assembly is disclosed that includes a circular window having opposed front and rear planar surfaces and an outer periphery having forward and rearward chamfered edge surfaces, a compressible gasket circumscribing the outer periphery of the window, a housing with a portal having an annular seat for accommodating the window circumscribed by the gasket, wherein the annular seat has a first chamfered abutment surface corresponding to the forward chamfered edge surface of the window, an annular bezel operatively associated with the housing for compressively retaining the window assembly within the annular seat of the portal, and structure for securing the bezel to the housing, wherein the bezel has a second chamfered abutment surface corresponding to the rearward chamfered edge surface of the window.

Abstract: A window funnel for an aircraft is provided, which has a ring made of an elastic material, which is arranged by means of an adhesive layer on an outer side of the window funnel, the ring having a hollow profile. The ring serves as a sight screen, light screen and dust screen for the rear side of the window funnel.

Abstract: A vehicle window with a primary window pane arrangement, a secondary window pane that is spaced apart from the primary window pane arrangement and a window funnel that extends between the secondary window pane and the primary window pane arrangement is provided. The vehicle window includes an intermediate space that is formed by the window funnel, the secondary window pane and the primary window pane arrangement, and the intermediate space is sealed and equipped with an air inlet for introducing dehumidified air into the intermediate space. Due to the seal, humid air leading to condensation and frost in the intermediate space is prevented from flowing into the intermediate space during a pressure compensation flow. The passenger comfort is enhanced due to the improved view through the window.

Abstract: Fiber reinforced composite structures having curved stepped surfaces are fabricated by laying up plies of fiber reinforced material over a tool having a stepped tool feature. The plies are rotated about a fixed axis as they are laid up to substantially form a fixed axis rosette pattern. The plies are angularly oriented such that at least certain of the plies have fiber orientations other than 0, +45, ?45 and 90 degrees. Potential bridging of the fibers over the stepped tool features is reduced or eliminated by cutting slits in the plies in the area of the stepped features, so that the plies can be fully compacted.

Abstract: The present invention provides a method for the production of a fuselage structure, and a fuselage structure, in particular of an aircraft or spacecraft, with an inner shell arrangement which has an upper inner shell and a lower inner shell, the upper inner shell being spaced apart at least in some sections from the lower inner shell by a first gap in order to form a window region; and a window band which is arranged at least in the window region and has a pane device which comprises a grid structure which absorbs fuselage forces.

Abstract: A door for an aircraft wing fuel tank access opening includes an outer impact resistant composite door panel, and an inner composite door panel. Double seals on the inner door panel prevent fuel leakage, and a chamfered outer edge on the outer door panel transfers a component of impact loads laterally into the wing skin to increase kinetic energy absorption.

Abstract: An improved vibration damping apparatus is provided for use with window structures, including windows used in vehicles, aircraft, and spacecraft. The vibration damping system includes at least two separate layers of solid material that are typically substantially clear at visible wavelengths, in which the two layers are spaced-apart by a predetermined distance to form a space or gap therebetween. This gap will be of a size and shape to enhance vibration damping when it is filled with a gaseous compound, such as air. The air-film vibration damping system created by the above structure can be applied to an external pane of a window structure, or to the interior pane of a window structure, or perhaps to both an exterior pane and an interior pane of the same window structure, if desired.

Abstract: A method for manufacturing a fiber-composite component with a cladding field and a primary component for reinforcing the fiber-composite component includes the steps of: applying a prepreg semifinished product to a mold to form the cladding field, where in the prepreg semifinished product fibers extend in some sections in a curved manner according to an assumed flow force path in the cladding field of the component to be manufactured; curing the prepreg semifinished product; applying layers of a semifinished textile product to the cured prepreg semifinished product to form the primary component; impregnating the semifinished textile product with matrix material; and curing the assembly comprising pre-cured prepreg semifinished product and semifinished textile product; a fiber-composite component with at least one structural component and a skin section connected to said structural component with a recess as well as a fiber-composite fuselage component of an aircraft with a shell component with at least one re

Abstract: An ejection system for a window pane or panel which is affixed to a frame structure with at least one clamping seal. The system has means for ejecting the panel or window pane from the clamping seal and (a) a frame part with a housing which surrounds the inner face of the window pane or panel along a peripheral path, wherein the housing has an open end facing the window pane or panel; (b) an inflatable seal arranged in the housing; (c) a pressure source which is joined to the inflatable seal; and (d) an emergency actuation means to release pressure from the gas pressure source. The released air or gas expands the inflatable seal which pushes the window pane or panel out of the clamping seal.

Abstract: The present invention provides polyurethanes including a reaction product of components including: (a) at least one polyisocyanate; (b) at least one branched polyol having 4 to 18 carbon atoms and at least 3 hydroxyl groups; and (c) at least one polyol having one or more bromine atoms, one or more phosphorus atoms or combinations thereof; compositions, coatings and articles made therefrom and methods of making the same.

Abstract: An electromagnetic shield mesh 25 is provided on a window part 21, and a gasket seal 50 is provided between the electromagnetic shield mesh 25 and a window frame 30 made of a conductive material. The first seal part 51 of the gasket seal 50 has a low volume resistivity, and makes it possible to prevent electromagnetic noise from entering the inside of an airframe between the window part 21 and a window frame 30. Moreover, the second seal part 52 of the gasket seal 50, which is made in contact with the electromagnetic shield mesh 25 of the window part 21 on the outer perimeter side of window panels 23A and 23B, has a volume resistivity of, for example, 300 ?cm or more, so that it becomes possible to prevent corrosion from occurring at contact portions with a clamp 28, a clip 29 or the like.

Abstract: Electrically dimmable windows for aircraft are powered by energy harvesting devices on-board the aircraft. The harvested energy is stored and used to control the opacity of the windows based on individual window opacity settings selected either by passengers or a cabin attendant. Each window has an associated control circuit that controls the electrical power applied to the window based on the selected opacity setting. The control circuit includes a low energy usage processor that remains in a sleep mode until a change in the opacity setting is detected. Each control circuit may include a radio transceiver that receives control signals from a transmitter operated by the cabin attendant in order to simultaneously remotely control the opacity settings of multiple windows.

Abstract: A reduction of the multiple costs of manufacture, assembly use, and upkeep connected with the assembly of window frames on aircraft fuselages. To this end, the invention provides a particular shape for the frames connected to the fuselage skin according to a specific assembly method. The shape enables, among other things, the window frames to be fitted onto the skin by means of adhesion and also frames to be dispensed with between the fuselage and the window. In one embodiment, composite material window frame has a wall totally in the shape of a crown that is connected, through co-adhesion, to the inner surface of the fuselage skin, also made of composite material. The skin is cut into a window-receiving opening, and the frame has a T-shaped cross section, wherein the bar of the “T” that forms the crown includes two portions having substantially equal lengths “T.

Abstract: A method for assembling a cabin window to a bay in a side wall of an aircraft fuselage, where the cabin window including an outer transparent element and at least one inner transparent element, includes making a non-through hole in a portion of the side wall. The outer transparent element includes a first part having a diameter greater than that of the bay and which is shaped to co-operate with the portion of the side wall to block the outer transparent element in the bay both laterally and longitudinally. A second part of the outer transparent element has a groove that projects into the fuselage. The outer transparent element and the at least one inner transparent element are welded to the fuselage using a strap which presses a seal against at least the fuselage and the inner wall of the groove.