Abstract: A magnetic fastener assembly for securing an access panel to an aircraft structure. A panel magnetic foundation member is rigidly secured to a surface of the panel facing the aircraft structure and a land magnetic foundation member is rigidly secured to a surface of the aircraft structure facing the panel. A planar magnet is positioned between the panel magnetic foundation member and the land magnetic foundation member and being magnetically coupled thereto so as to secure the panel to the aircraft structure. A separation device, such as a pneumatic bladder, is positioned between the panel and the land structure and adjacent to the magnet, and is rigidly secured to the aircraft structure. The separation device is actuated to apply pressure to the panel and break the magnetic attraction between one or both of the panel magnetic foundation member and the magnet or the land magnetic foundation member and the magnet.

Abstract: A rack-based information handling system (RIHS) includes a rack chassis having at least two opposing side panels which are structurally held in place by one or more segments spanning between the two opposing side panels to generate an internal volume between the at least two opposing side panels. The internal volume has structures that enable insertion and retention of information technology (IT) gear and other components of the IHS at one of a front access space and a rear access space of the rack chassis that extend between the two opposing side panels. The RIHS also includes at least one security screen that is removably affixed to opposing edges of the two opposing side panels and span across a first segment of an access space to prevent direct physical access to the IT gear or other components that are inserted within the rack chassis behind the security screen.

Abstract: A nacelle for an engine has outer and inner cowl doors that are independently rotatable about offset hinge lines. A connection device is provided for selectively connecting the outer and inner cowl doors so as to cause them to open simultaneously. The inner cowl door is arranged to rotate by a greater angle than the outer cowl door so as to improve access to the engine for maintenance purposes.

Abstract: A magnetic latching system is provided for removably latching a panel to an aircraft surface portion. The latching system includes a removable axis panel engageable to a latching land. The panel and land define opposing magnetically attractive surface portions, with a body of magnetic material disposed there between. An inflatable seal is also disposed intermediate the panel and the land. Upon inflation, the inflatable seal is operative to urge the panel away from the land far enough to reconnect magnetic engagement between the panel and the land, sufficient to permit disengagement of the panel from the land.

Abstract: The track lock assembly may comprise a translating sleeve, a track beam, a pivoting lock assembly, and a ramp. The pivoting lock assembly may be mounted to the translating sleeve, wherein in response to the pivoting lock being mounted to the translating sleeve, the ramp is mounted to the track beam. The pivoting lock assembly may be mounted to the track beam, wherein in response to the pivoting lock being mounted to the track beam, the ramp is mounted to the translating sleeve.

Abstract: A method and apparatus comprising a sealing member, an integral structure associated with the sealing member, and an engagement section extending from the sealing member. The sealing member is configured to be attached to a surface of an object. The sealing member is consolidated with the integral structure. The engagement section is deformable and configured to engage a receiving structure in the object.

Abstract: Structures and methods for access panels. Some include a panel member having an inner side; a mounting member having a portion extending from the inner side at an angle to the inner side; and a retaining member coupled to the mounting member, the retaining member having a length and being biased to be in contact with the inner side along a portion of the length, the retaining member also being capable of flexing away from the inner side.

Abstract: An aircraft pressurized cabin door includes an integral door structure unit made of fiber composite, the unit including an outer skin and a door framework arranged on an inner side of the outer skin. The framework includes a plurality of edge supports and a plurality of longitudinal supports extending in a width direction between the edge supports so as to form door framework interstices delimited by the inner side of the outer skin, by the edge supports and by the longitudinal supports. The door framework interstices are configured in a manner open toward the inner side of the door.

Abstract: An access door is provided in a housing for a gas turbine engine, with the access door being movable to an access position independent of any required movement of any cowl door or a fan duct door.

Abstract: A door frame is provided at an opening made in a fuselage of an aircraft that is delimited by a skin. The frame includes an upper longitudinal stiffener and a lower longitudinal stiffener and two vertical substructures, each arranged on one side of the opening, connected by the upper and lower longitudinal stiffeners. The frame also comprises at least one stop provided at the level of the opening that uptakes radial forces exerted by the door. Each vertical substructure comprises at least three walls made of composite material that are connected to one another to form a box substructure having a closed and hollow cross-section in a sectional plane perpendicular to an axis of the length of the vertical substructure.

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 capacitively coupling the window pane to the fuselage after the frequency of the electromagnetic energy reflected by the window pane exceeds approximately 1 GHz.

Abstract: A deployable barrier arrangement for selectively blocking a passage in an aircraft cabin, wherein the barrier arrangement comprises a substantially longitudinal barrier member and a joint unit for fixing the barrier member to an inner wall of the aircraft cabin. The joint unit is configured to allow for a movement of the barrier member between a stowed position in which the barrier member extends substantially parallel to the inner wall of the aircraft cabin and a deployed position in which the barrier member extends at an angle of approximately 60° to 120° to the inner wall of the aircraft cabin. The joint unit is further configured to allow for a rotational movement of the barrier member about a longitudinal axis of the barrier member.

Abstract: The present invention prevents misassembly of access doors while reducing stress concentrations. A hole-side convex portion 80 is formed in each opening 12 at one or more locations in a circumferential direction, and a door-side rib 70 is formed on each door body 30. The hole-side convex portions 80 formed in the openings 12A to 12C differ in location in the circumferential direction among the plural openings 12A to 12C. The door-side ribs 70 formed on the respective door bodies 30A to 30C are provided in such locations as not to interfere with the hole-side convex portions 80 provided in the openings 12A to 12C in correct combination with the door bodies 30A to 30C.

Abstract: This maintenance trolley (17) for the air intake (9) of the nacelle of an aircraft turbojet engine is notable in that it comprises a base (19) and a platform (23) cantilever-mounted on this base (19) and designed to enter said air intake (9) without contact therewith.

Abstract: A decompression arrangement includes first and second cabin lining elements each with an edge region, the edge region of the second being arranged at a smaller distance from an aircraft outer skin than the edge region of the first, an air discharge opening arranged between the first edge region and second edge region and which is adapted to discharge air from an inner region of the cabin delimited by the cabin lining elements into a region of the aircraft lying between the cabin lining elements and the aircraft outer skin, and a decompression element integrated in the second cabin lining element having a flap pivotable about an axis from a closed position, in which it closes a pressure equalizing opening formed in the decompression element, into a first open position, in which it opens the pressure equalizing opening if a first predetermined differential pressure acts on the decompression element.

Abstract: Decompression panel assemblies and methods of equalizing air pressure differential are provided. The decompression panel assembly includes a panel comprising an opening defined therein, a vent cover coupled across the opening, and a latching mechanism. The vent cover is configured to move between a first position and a second position. The latching mechanism is configured to maintain the vent cover in the first position when a pressure differential across the panel is below a predetermined value and facilitate the vent cover moving to the second position when the pressure differential across the panel exceeds the predetermined value.

Abstract: The invention relates to a nacelle rear assembly for a turbojet engine, that comprises: a hood, an inner structure in the shape of a sheath in which at least the rear portion (15) is of the O-duct type and is capable of axial sliding between an operational position in which it covers the gas generator (3) of said turbojet engine and defines an annular cold-air jet with said hood, and a maintenance position downstream from said operational position. The downstream portion (15) is conformed so as to be capable of sliding without blocking relative to said gas generator (3), and the inner structure includes an upstream portion (13) that can be separated from the downstream portion (15) and that includes at least two doors (13a, 13b) capable of opening towards the outside.

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: The invention is based on a partition wall in an aircraft, wherein the partition wall comprises a support element and a tension-mounted material. According to the invention, the support element is composed of individually formed system components, and the tension-mounted material is supported by the support element such that an area-shaped partition wall is created in the aircraft.

Abstract: A decompression assembly (10; 10?) for an aircraft comprises a first cabin lining element (12; 12?) having a boundary area (14; 14?) and a second cabin lining element (20; 20?) having a boundary area (22; 22?), wherein the boundary area (22; 22?) of the second cabin lining element (20; 20?) is disposed at a smaller distance from an aircraft outer skin (24; 24?) than the boundary area (14; 14?) of the first cabin lining element (12; 12?). An air discharge opening (28; 28?) is disposed between the boundary area (14; 14?) of the first cabin lining element (12; 12?) and the boundary area (22; 22?) of the second cabin lining element (20; 20?) for discharging air from a cabin (18; 18?) of the aircraft into an area (30; 30?) of the aircraft located between the cabin lining elements (12, 20; 12?, 20?) and the aircraft outer skin (24; 24?).

Abstract: A method for mounting an aircraft component, which in the mounted state is movable between a first and a second operating position and is taken up in its first operating position in a mounting area, comprises the measuring of the mounting area, in order to obtain data characteristic of the shape and/or the dimensions of the mounting area. The data characteristic of the shape and/or the dimensions of the mounting area are projected onto the aircraft component arranged in its second operating position. Finally, the aircraft component arranged in its second operating position is adjusted with reference to the projection of the data characteristic of the shape and/or the dimensions of the mounting area.

Abstract: A protective cover (10) for an instrument dome (12) extending from a body (20) of a vehicle, such as a missile. The cover (10) includes multiple segments (14 and 16) having trailing ends (18) connectable to the body (20) at joints (22) that allow for rotational movement. The cover (10) further includes a releasable holder (26) that includes a retention device (28) that holds leading ends (24) of the segments (14 and 16) together, and a release mechanism (30) for causing the retention device (28) to release the leading ends (24). The joints (22) hold the trailing ends (18) of the segments (14 and 16) to the body (20) through a predetermined range of motion beyond which the segments (14 and 16) will be released to separate from the body (20) when the segments (14 and 16) rotate beyond the predetermined range.

Abstract: An emergency opening system (1) of an aircraft cabin door (3) mounted in an aircraft fuselage structure (4) by means of a hinge arm (2). An actuator (7), designed to assist the opening of the aircraft cabin door (3) against the force of gravity by means of a gas operated actuating rod (8) is mounted with its fix end (9) to said hinge arm (2) and said actuating rod (8) is connected to an actuator joint (10). A fork lever (24) is linked to said actuator joint (10). A bell crank (13) is respectively pivotable mounted to said hinge arm (2) and to said actuator joint (10) for the fork lever (24). At least one coupling lever (12) is pivotable joint to said fork lever (24) at at least one coupling joint (14). Said at least one coupling lever (12) is mounted in at least one hinge (18) of the hinge arm (2) by means of a respective bolt (26), said bolt (26) being drivingly connected to said aircraft cabin door (3) for rotation of said aircraft cabin door (3).

Abstract: An aircraft door 18 which closes an opening of a storage space 16 for storing a RAT 13 as an accessory and which is opened in association with deployment of the RAT 13 from the storage space 16, the door including: a door body 20 that opens and closes the opening, and whose front surface faces an outside and whose rear surface faces the storage space 16 in a closed state; and a fence 24 that rises from the rear surface of the door body 20. In a traveling direction of the aircraft, the fence 24 is located anterior to a position where the RAT 13 is stored. The fence 24 prevents an airflow Air from passing through between the RAT 13 and the door body 20 in an initial stage where the door 18 starts to be opened, thereby suppressing the aerodynamic force in the closing direction acting on the door body 20.

Abstract: A turbojet engine nacelle, including an air intake structure for directing an airflow towards a fan of the turbojet engine, a middle structure attached to the air intake structure for surrounding the fan of the turbojet engine, the air intake structure including an inner panel attached to the middle structure and defining a fixed structure with the middle structure, and an outer panel including an air intake lip at the end thereof opposite the middle structure, the outer panel being longitudinally translatably movable relative to the inner panel. The nacelle further includes at least one rod having one end attached onto a flange of the air intake lip and a mechanism rigidly connected to the middle structure for securing and locking the other end of each rod by applying a traction force thereon.

Abstract: An aircraft nacelle includes, on its outside surface, at least one opening that is blocked by at least one movable part (16) that is kept in closed position by at least one locking mechanism that connects the movable part (16) to another part of the nacelle (16?), characterized in that it includes an anchoring point (32) on one of the two parts (16?) that are to be connected, and a detachable link (34) that is connected to a traction element (36) that is integral with the other part (16) that is to be connected.

Abstract: A method and apparatus for a hierarchical access system for a compartment. The hierarchical access system comprises a moveable barrier, a locking mechanism, and a control unit. The moveable barrier is capable of preventing access to at least one of a first space and a second space in the compartment in the lavatory when the moveable barrier is in a closed position. The locking mechanism is capable of securing the moveable barrier in the closed position. The control unit is capable of unlocking the locking mechanism in a manner that provides different levels of access to the first space and the second space in the compartment in response to receiving an access request.

Abstract: An actuating device is provided for a locking system which locks one of half-shells of a jet engine nacelle with respect to the other half-shell. The actuating device includes a fixed body in which an actuating rod is translationally and rotationally mounted with respect to the rod's longitudinal axis, and the fixed body has a track cooperating with a follower projecting from the actuating rod. In particular, the actuating rod includes a first end equipped with a handle and a second end connected to the locking system. The track has a middle part running parallel to the longitudinal axis, a first end part and a second end part formed on each side of the middle part, each of the end parts running perpendicular to the longitudinal axis.

Abstract: An object of the invention is to provide a low-cost closing member for an opening having an excellent lightning protection capability. In a door body 30, an outer surface 31a of a plate part 31 is formed by a composite material layer 60, and a side of an inner surface 31b and a flange part 32 are formed by a metallic material layer 61. The door body 30, a clamp ring 40, and an opening 12 of a wing panel 11 are electrically connected by surface bonding of conductive materials in a butt section of an abutment surface 34 of the door body 30 and a tapered surface 40c of the clamp ring 40 and a butt section of a tapered surface 40d of the clamp ring 40 and an abutment surface 14 of the opening 12.

Abstract: The present invention provides a cover plate for covering at least portions of a door gap formed between a door covering and a fuselage cell of an aircraft or spacecraft, comprising: a fastening portion by which the cover plate can be mounted on an outer surface of the door covering; a contact portion which rests in a contacting manner against an outer skin of the fuselage cell when the door covering is closed; at least one corner portion associated with a corner of the door covering; and a side portion associated with a side of the door covering, the at least one corner portion and the side portion being configured to press the contact portion with a constant contact pressure against the outer skin of the fuselage cell when the door covering is closed.

Abstract: A vehicle has a passenger section, a control section and a door positioned between the passenger section and the control section. The door has an indented region on a side of the door facing the control section when the door is in a closed position, where the indented region has a surface. The vehicle also includes a second surface. A locking mechanism has a first locking portion, a second locking portion and a connecting portion connecting the first locking portion and the second locking portion. The locking mechanism locks the door in the closed position when the first locking portion engages the surface of the indented region and the second locking portion engages the second surface.

Abstract: A locking mechanism includes a hydraulic actuator component and an electronic actuator component that are arranged coaxially, each of the actuator components being arranged to control a locking member that retains a movable component. In one version, each of the actuator components can individually engage a mechanical detent to enable unlocking of the movable component, for use, for example, in an uplock mechanism for aircraft.

Abstract: The system and apparatus of the present invention is generally comprised of a non-dedicated, temporarily-installed, aircraft observer bubble door, chair, sonotube ejection system, mission electronics LRU rack and workstation assembly which are affixed to the Air Deployment System (ADS) rails, cargo tie down “D” rings, seat belt restraint ring bolt sockets, and litter bar of a host aircraft, thereby precluding the requirement for dedicated airframe modifications. One embodiment of the present invention also utilizes a multi-axis, articulated, foldable chair temporarily-installed in conjunction with a segmented or one piece pressurized observer bubble door plug and door retraction system. Once installed the subject apparatus can be stowed outboard of the fuselage cargo transit envelope to permit use of the ADS rail system in-flight, without affecting normal air drop operations, crew egress, the flight performance envelope, or emergency procedures of the host aircraft.

Abstract: A loads interface (1) of an aircraft structure with an edge member (6) and a background structure both preferably made from fiber reinforced plastics. A loads transferring flange (2) is adapted and mounted to said edge member (6) to transmit bending moments into the background structure. Said loads transferring flange (2) is provided with two angled upper and lower planes (8, 9). Said edge member (6) is provided with two angled edge member's upper and lower transfer planes (10, 11). The two angled upper and lower planes (8, 9) and the two angled edge member's upper and lower transfer planes (10, 11) are paired essentially parallel and respectively oriented to each other with an angle of approximately 90°. The invention relates as well to applications of such a loads interface (1).

Abstract: A loads interface (1), particularly a loads interface (1) of an aircraft door with an edge frame (13), an outer skin (15) and a beam (14). A loads transferring flange (11) is designed to transmit transverse, circumferential and/or longitudinal forces, is provided with at least three flanges (18, 19, 20) for distribution of the loads in the edge frame (13), the outer skin (15) and the beam (14).

Abstract: The invention relates to a jet engine nacelle intended to equip an aircraft, comprising a forward air inlet section, a mid-section intended to surround a fan of the jet engine, and an aft section formed from at least first and second hath-shells rotatably mounted about an axis such that they can each be deployed between a working position in which the half-shells are drawn towards one another and a maintenance position in which the half-shells are spaced apart, at least the first half-shell (11) being equipped with a first follower element (19) in a region situated at a distance from the axis of rotation, the nacelle being equipped with a first fixed guide element (28), the first follower element (19) being designed to bear against a first guide element (28) which is fixed with respect to the jet engine during the rotation of the first half-shell (11).

Abstract: An aircraft nacelle includes an air intake (12) followed at the upper part by a part (14) integral with the mast, called a cap, and at least one door (16) with a curved profile, and a device for encircling it in the form of at least one flexible element (38), guide elements (40) for allowing the at least one flexible element (38) to follow the curved profile of the at least one door, a first anchoring point (42) of the at least one flexible element (38) integral with a first edge (78) of the cap and another anchoring point of the at least one flexible element (38) integral with a second edge (80) of the cap, whereby the anchoring points (42) allow a relative translational movement, in a direction that is parallel to the longitudinal axis of the nacelle, between the cap (14) and the at least one door (16).

Abstract: An object of the invention is to provide a low-cost closing member for an opening having an excellent lightning protection capability. A door body 30, a clamp ring 40 made of a composite material, and an opening 12 of a wing panel 11 made of the composite material are electrically connected by surface bonding of conductive materials in a butt section of an abutment surface 34 of the door body 30 and a tapered surface 40c of the clamp ring 40 and a butt section of a tapered surface 40d of the clamp ring 40 and an abutment surface 14 of the opening 12.

Abstract: The invention relates to a cover panel for a landing gear for an aircraft with at least one pivotal closable flap 6, 7. According to the invention the at least one flap 6, 7 is attached for swivel movement to the fuselage cell 2 of the aircraft by means of at least one multi-articulated joint 8, 9, 13 wherein the multi-articulated joint 8, 9, 13 is constructed with a number of individual joints seated on a shaft 17, similar to a piano hinge, and a mechanical play increases preferably uniformly starting from a middle individual joint 14 towards the outer individual joints 15, 16. As a result of the mechanical play which increases within the multi-articulated joint 8, 9, 13 from the middle individual joint 14 to the two outer individual joints 15, 16 in the direction of the x-axis or aircraft longitudinal axis, a substantial mechanical isolation of the cover panel from any possible fuselage cell movements is provided.

Abstract: The invention relates to a pressure relief latch for aircraft, able to absorb vibrations and shocks without inopportune opening, as well as to adapt to dimensional stresses during its assembly. The latch includes: a console, a lever mounted on the console, and an opening effort exerted on a fulcrum of the lever causing an angular displacement of the fulcrum between a closing position and an opening position. The latch also includes a roller able to roll against a profile of the lever and connected to an elastic return device. The latch further being provided with means able to vary the angular displacement of the fulcrum of the lever according to the opening effort, with two different slopes according to an opening effort E1.

Abstract: An aircraft auxiliary power unit assembly includes an aircraft skin that provides a cavity. It is secured to a structure in an assembled condition and it provides an opening. An auxiliary power unit is arranged within the cavity and is secured to the structure. The aircraft skin substantially covers the auxiliary power unit in the assembled condition. An inlet duct that is removable is secured within the opening and is selectively connected to the auxiliary power unit between the installed and service positions. The installed and service positions are with the aircraft skin in the assembled condition.

Abstract: A translating sleeve assembly for use with an aircraft engine thrust reverser broadly comprises a slider track, a lifting bolt, and a hinge. The slider track may include a tubular sidewall and a guide channel formed therein that follows a curved path along a length thereof. The lifting bolt may be slidably positioned within the slider track. The hinge may include a first hinge element with a base coupled to an outer cowl shroud, a second hinge element with a hinge rod slidably positioned within the guide channel, and a pin about which the first hinge element and the second hinge element pivot. During deployment of the thrust reverser, the lifting bolt slides aftward and the hinge rod slides within the guide channel, urging the lifting bolt to pivot and the hinge to open, thereby lifting the outer cowl shroud away from the center of the aircraft engine.

Abstract: An object is to provide a closing member for an opening, the closing member capable of more reliably maintaining a lightning-protective function. In addition to a first insulator 63, a second insulator 65 is provided between a door body 30 and a wing inner surface 11b around an opening 12. When the first insulator 63 falls off, the second insulator 65 becomes interposed between an inner peripheral planar part 64 and the wing inner surface 11b. With the first insulator 63 being tightly interposed between an outer peripheral planar part 62 and the wing inner surface 11b, the second insulator 65 faces the wing inner surface 11b with a predetermined clearance C therebetween. The outer peripheral planar part 62 is formed at a position further away from the wing inner surface 11b than an apical surface 65a of the second insulator 65 mounted on the inner peripheral planar part 64.

Abstract: A manhole assembly in the lower skin (37) of an aircraft wing made of a composite material for giving access to an installation placed inside said aircraft wing such as a fuel tank, comprising an inner cover (31) and an outer cover (33) joined by first fastener means (35); the lower skin (37) being configured with a rebated edge (45) around the manhole so that the outer cover (33) can be mounted over the lower skin (37) maintaining the aerodynamic continuity in the aircraft wing surface; the inner cover (31) being mounted over the lower skin (37) by its inner surface with a sealing profile (41) between them and being joined to the lower skin (37) by second fastener means (47).

Abstract: A door for an aircraft engine nacelle, comprising an opening leaf, locking device with which the opening leaf may be locked in the closed position, as well a device for setting the opening leaf into motion with which the latter may be displaced from the closed position to the open position. The locking device has a mechanical fuse intended to break under the effect of a force exerted by the opening leaf and resulting from an opening gas pressure being applied on the opening leaf, with a value greater than or equal to a predetermined value and causing displacement of the opening leaf from the closed position to the open position after breakage of the mechanical fuse.

Abstract: A tail-cone of an aircraft includes a skin provided with a movable fairing which, by a swing articulated mechanism, is supported on the skin in order to allow the opening/closing of the movable fairing and gain access to the inside of the tail-cone. The tail-cone includes actuators for operating the swing articulated mechanism in order to permit the automatic opening and closing of the movable fairing to be carried out.

Abstract: A fuselage structure, particularly an aircraft door (1) of composite material comprising at least one panel (2) and at least one beam (3) mounted to each other and the panel (2) with the panel (2) being formed of at least one group of composite layers (5, 6, 20). The at least one beam (3) is provided at least at one of its respective ends (10, 11) with a flange (13) suitable for adhesive engagement with the at least one panel (2). The at least one group of composite layers (5, 6, 20) of the panel (2) is in form locking engagement with this flange (13) of the beam (3).

Abstract: An aircraft includes a part defining an aerodynamic surface against which flows an air stream, with at least one hood able to block an opening made at the aerodynamic surface, kept in the closed position by at least one locking mechanism, and an access flap for the locking mechanism, pivoting relative to the hood around an axis substantially parallel to the flow direction of the air stream and including elements for keeping it flattened against the hood, characterized in that it includes a device for protection of the access flap that includes a coverage plate that pivots around an axis of rotation, and which is able to occupy a first position in which it projects relative to the aerodynamic surface and another position in which after pivoting around the axis of rotation, it is flattened against the outside surface of the access flap such that the protective device limits the appearance of a scoop phenomenon.

Abstract: The invention relates to a locking device (9) designed to be arranged in a junction region of a nacelle, comprising a locking system (10), intended to be mounted on a first half-shell of the nacelle, engaging with a retention member (11) intended to be mounted on a second half-shell, the locking system (10) being actuable between a locked state and an unlocked state with respect to the retention number (11), the locking system (10) and the retention member (11) being movable with respect to one another between a drawn-together position in which they can be locked with respect to one another and a spaced-apart position. The locking system (10) and/or the retention member (11) comprise locking means (25) designed to allow the locking system (10) to be locked with respect to the retention member (11) when they are in the drawn-together position and to prevent them from being locked when they are in the spaced-apart position.

Abstract: The invention relates to a cover panel for an aircraft, comprising a decompression opening that can be closed by a decompression flap that comprises a membrane, and a ventilation opening that is provided separately in the cover panel and that is permanently open. Furthermore, the invention relates to an aircraft fuselage comprising such a cover panel.