Abstract: A nacelle cowling for a turbojet, characterized in that it is provided with a fixed part and a mobile part, the mobile part being adapted to slide along the fixed part, from a closed position wherein the mobile part extends in the extension of the fixed part, up to an open position wherein the mobile part is at least partly superimposed to the fixed part. For example, the fixed part is located in the upper part of the cowling, the mobile part being located in the lower part of the cowling.

Abstract: A door apparatus includes a door, actuating mechanism, and tie rod mechanism, the actuating mechanism actuating the tie rod mechanism to impart a substantially translating motion to the door. The actuating mechanism can include a drive yoke coupled to the tie rod mechanism with a one-way coupling. The tie rod mechanism can include a primary tie rod coupled to a secondary tie rod coupled to a latch. In another aspect a door apparatus includes an actuator, a first door, a second door, a first linkage assembly coupling the actuator to the first door, and a second linkage assembly coupling the first door to the second door, the actuator configured to activate the first linkage assembly to move the first door, the first door imparting motion to the second linkage assembly to move the second door in a synchronous and opposite motion with respect to the motion of the first door.

Abstract: A composite panel having a first skin forming the outer wall of the panel, known as the lower face (1), and a second skin forming part of the inner wall of the panel. The second skin is formed hollow such as to produce an inner reinforcing frame (2) in the form of a half-box structure (3) which, together with the first skin, forms box parts. The aforementioned frame is equipped with a rim (4a, 4b) for fixing to the first skin, a face known as the upper face (5) and connecting side walls (6, 6a, 6b, 6c, 6d, 6e, 7) between the rim (4a, 4b) and the upper face (5) the first and second skins forming a monolithic self-stiffened panel. The half-box frame (2) has perforated sections (8) which are defined by hollow beam sections forming the half-box frame (2).

Abstract: An aircraft door is disclosed comprising a first (301), second (302) and third (303) door members pivotably joined and arranged to move from a closed position in which said members are located in a substantially linear arrangement in the aircraft skin to an open position in which said members are located in a relative folded arrangement with the second and third door members situated substantially above the lowest edge of the first door member.

Abstract: A slide door device for an aircraft includes an upper guide roller at a tip end of an upper arm provided at an upper part of a slide door and a lower guide roller at a tip end of a lower arm provided at a lower part of the slide door that are rollably engaged with an upper guide rail and a lower guide rail that are fixed along an upper edge and a lower edge of a door opening frame formed in a fuselage of an aircraft, respectively. An intermediate guide roller, provided at a tip end of an intermediate arm provided in a door opening, is rollably engaged with an intermediate guide rail that is fixed to an inner surface of the slide door, while smoothly guiding the slide door with the upper guide rail, the lower guide rail, and the intermediate guide rail.

Abstract: A door panel that is capable of maintaining the adhering strength of the adhesive is provided. An outer panel and an inner panel are joined together by an adhesive. Adhesive retaining portions, each of which includes an adhesive retaining channel for retaining the adhesive, are provided in adhering portions of the inner panel. Each adhering portion includes vertically extending portions, and the adhesive retaining portions of the inner panel are formed in the shape of an extended raised portion and extend vertically in the respective vertically extending portions of the adhering portions, along ventilation openings, which are formed at locations corresponding to groups of ventilation holes of the outer panel. Each adhesive retaining portion is provided at the middle of each vertically extending portion of the adhering portions so as to be flanked by adhesion margins of identical width.

Abstract: A handle for use in operating a door of an aircraft. The handle is fixed to a shaft and rotates the shaft about an axis. The handle includes multiple separately movable sections, the sections arranged so that each section has a limited range of movement separate from the other. The handle is capable of operating the door when the sections are moved substantially in unison. The handle also provides positive actuation of movable door components.

Abstract: A flexible mounting assembly allows relative movement between a top and a bottom structural member of an air frame, for instance, a helicopter. The flexible mounting assembly comprises a vertical frame member and an isolation frame member where one of the vertical frame member and the isolation frame member has a pin and the other of the vertical frame member and the frame isolation member has an aperture adapted to slidingly receive the pin in a way to accommodate relative vertical motion therebetween while substantially restraining lateral movement therebetween. The flexible mounting assembly may also include a horizontal shear wall assembly extending between adjacent vertical frame members that accommodates relative vertical motion between top and bottom structural members while substantially restraining lateral movement therebetween.

Abstract: A paneled partition assembly is designed to close an opening and collapses to uncover the opening by a movement of at least one panel that initiates the rotation and translation of at least one other panel. When the paneled partition assembly is in a closed or extended position, the plurality of panels covers the opening regardless of the opening's shape, size, or irregularity. When the paneled partition assembly is in an open or retracted position, the plurality of panels collapse to a smaller configuration. In moving between the extended and retracted positions, the panels rotate and translate fluidly with minimum user interaction.

Abstract: An internal swivel door for an aircraft compartment. A door frame for entering the compartment includes a horizontal element and at least one door leaf which is mounted inside the door frame wherein the door leaf is turned about a vertical door rotational axis. The vertical door rotational axis is moved in parallel along a predetermined local curve. In order to take up less space during opening and closing of the door and to be able to operate the door with the least possible force, the door has a rotary sliding joint between the door leaf and the horizontal element. The door leaf has a rotational movement about a momentary rotational axis running through the rotary sliding joint wherein the momentary rotational axis is moved in parallel both in relation to the horizontal element and the door leaf.

Abstract: A door system for an aircraft has a flight deck door hingely coupled to a flight deck bulkhead. A lavatory is adjacent to the flight deck bulkhead and formed of a lavatory bulkhead. A lavatory door is coupled to the lavatory bulkhead. A latching mechanism is attached to the flight deck door. The latching mechanism in a first position engages the flight deck bulkhead and in a second position engages the lavatory bulkhead.

Abstract: A cabin door assembly is provided for use with a pressurized aircraft. The assembly includes two door halves for engaging the fuselage of the aircraft. Structurally, each door half includes a waist section integral with an adjoining tapered section. Further, the assembly includes an activator that is mounted on the fuselage and attached to the door halves. Specifically, the activator is attached to each door half to concertedly move each door half between a closed configuration and an open configuration. In the closed configuration, the door halves are sealed to the fuselage and to each other for pressurization of the aircraft. In the open configuration, the door halves extend outwardly from the fuselage to allow for aircraft ingress and egress.

Abstract: A control device for locking and unlocking a door includes a handle (46) whose movement makes it possible to control the change of state of the locking or unlocking of the door, a hinged flap (54) that can move between a closed position and an open position in which it makes it possible to grip the handle, elements for locking and unlocking the handle that are able to occupy two states, a first locked state in which the handle is immobilized and a second unlocked state in which the handle can be maneuvered, and a stop (64) that makes it possible to control the movement of the hinged flap (54), during the change of state of the locking and unlocking elements, wherein the stop is elastically deformable so as to be able to be deformed by the hinged flap during the change of state of the locking and unlocking elements.

Abstract: Opening and secure-closing system for doors comprising two doors (1,2) for accessing the interior of a chamber, which open towards the outside being hinged around two hinging axes (19,20), both doors (1,2) comprising a set of bolts (17,18) and the opening and closing system comprising additional means of opening/closing operation (26) and an overpressure door (3) located in one of the doors (1,2) which opens towards the outside, in such a way that the means of opening/closing operation (26) comprise a blocking bar (4), a blocking fitting (7) and means of retention (10) between the two doors (1,2) in order to provide a controlled and sequential opening/closing operation of the chamber, and the overpressure door (3) is opened automatically in the event of emergency due to overpressure, and it also participates in the controlled and sequential opening/closing operation of the chamber.

Abstract: A door panel that is light in weight and has sufficient strength is provided. A door panel has an outer panel, an inner panel, and a foamed material filling a space between the outer panel and the inner panel. The inner panel is formed by means of press molding so as to have an uneven surface with adhering portions and a raised portion. The adhering portions are affixed to the inner surface of the outer panel, and the space is formed between the raised portion and the outer panel. The outer panel has a thickness ranging from 1.2 to 5.0 times that of the inner panel. A hemmed portion is formed by folding the peripheral edge of the outer panel so as to curl over the peripheral edge of the inner panel and then pressing down the folded part.

Abstract: An unmanned aerial vehicle (UAV) for making partial deliveries of cargo provisions includes a UAV having one or more ducted fans and a structural interconnect connecting the one or more fans to a cargo pod. The cargo pod has an outer aerodynamic shell and one or more internal drive systems for modifying a relative position of one or more cargo provisions contained within the cargo pod. Control logic is configured to, after delivery of a partial portion of the cargo provisions contained within the cargo pod, vary a position of at least a portion of the remaining cargo provisions to maintain a substantially same center of gravity of the UAV relative to a center of gravity prior to delivery of the partial portion. Other center of gravity compensation mechanisms may also be controlled by the control logic to aid in maintaining the center of gravity of the UAV.

Abstract: An aircraft vent door system includes a vent door for a vent on an aircraft door. A cam, having a groove, is disposed on the vent door. The system also includes a movement assembly, which includes a roller disposed within the groove, and a lever coupled to the movement assembly. A portion of the lever extends beyond and proximate to the perimeter of the vent door. A second lever may also be attached to the aircraft door. The first lever pivots in response to the movement of the movement assembly, and urges the second lever to pivot. The second lever, in turn, urges the vent door open, thereby overcoming the sticking effect of, for example, built up ice or other obstructions.

Abstract: Disclosed is an aircraft door including a handle-activated pressure relief system that avoids potentially dangerous pressure differences between the cabin and the atmosphere outside the aircraft. A flow path is created between the inboard and outboard handles on the door. A pressure vent door is located in the flow path. The vent door being is opened when either of the inboard and outboard handle assemblies are activated. Once either handle is rotated beyond a particular point, a spring in the supporting mechanics becomes over-center. At the same time, the vent door comes under the influence of a magnet, snapping the vent open. After the door has been opened, it can be relatched by operating the handles in the reverse direction. The magnet and spring hold the vent door open until the aircraft door is fully latched, sealed, and secured. Only then does the vent door sealingly close.

Abstract: A latch device for detecting pressure reduction of a cockpit in an aircraft and releasing a bolt and a stopper device are provided so as to prevent a cockpit door from unexpectedly opening by an impact. A main latch device 100 of the cockpit door has a frame 112 fixed to a door panel, and a latch base 120 is mounted to the frame 112 capable of pivotal rotation with a pin 122 as a fulcrum. A bolt 132 is inserted into a catch in conjunction with a door handle 130. A holding/releasing portion 150 holds the latch base 120. When a pressure difference occurs between a cockpit 4 and a cabin 5, a pressure-sensing piston 160 is pushed in, a trigger 170 and a flapper 180 are rotated and the latch base 120 is released. A stopper device 190 regulates movement of the trigger 170 by movement of an inertial piston 192 when an impact force is applied from the cabin 5 side.

Abstract: An aircraft fuselage section is provided in which an outer skin construction provides at least one door opening having a width, such that it is divided by at least one rib of the fuselage skeleton of the aircraft fuselage section into multiple opening areas.

Abstract: An aircraft door closing device, and an aircraft incorporating such a device. The door includes a leaf and, connected to the aircraft fuselage, a frame including an opening configured to take the leaf, the leaf adopting a closed position to block the opening and another position to reveal the opening. The device includes a bearing mechanism, some on the leaf and some on the frame, each formed by a crenelated structure, two crenelated structures being arranged such that the teeth of one pass through notches of the other as the leaf moves from one position to the other, and such that the teeth of the leaf structure bear, in the closed position, on the inside face of the corresponding teeth of the frame structure.

Abstract: The present invention relates to a specially designed hinge mechanism, which makes it possible to construct an aircraft door that can be fitted in a fuselage so as to be displaceable and swivellable on the fuselage. Furthermore, the invention relates to an aircraft door comprising at least one such hinge mechanism designed in this way, to a fuselage with at least one aircraft door that is linked to at least one hinge mechanism, designed in this way, on the fuselage, as well as to the use of at least one hinge mechanism for installation of an aircraft door at a fuselage.

Abstract: The invention relates to a guard for the upper part of a door (2) of an aircraft, consisting of: a composite comprising a composite and/or stainless steel strip (14) which forms the core of the guard (1) and which renders same flexible and resistant, a silicon which is optionally reinforced with fibres and a polyester.

Abstract: A system for opening and closing an aircraft landing-gear compartment is described. The landing-gear compartment includes a plurality of hatches mounted on a fairing of the aircraft and has main hatches with crosswise openings and at least one secondary hatch with a longitudinal opening.

Abstract: The invention relates to a panel pivoting about an axis parallel to a side of the panel, which comprises a first continuous coating (1),a main structural frame of a composite stiffener (2, 3, 4, 5, 6) connected to the coating (1) and including a stiffening mesh (2, 3) with at least one pair of cross-shaped stiffeners each oriented in one of two directions, respectively, not parallel or perpendicular to the rotation axis. The two parts (3a, 3b) of each stiffener (3, 2) extending on either side of the centre of the cross are in structural continuity, and the two stiffeners (2, 3) each have an end located at one point (A, B, C) on the side of the panel parallel to the rotation axis, wherein the end is connected to a rigid member for connection to the rotation axis, the opposite end of at least one stiffener being blocked in rotation on a bearing point on the opposite side of the panel.

Abstract: A stairway used for gaining access from a theoretically horizontal lower level to a theoretically horizontal higher level, and including a succession of intermediate steps between these two levels. A subassembly of intermediate steps corresponding to the steps closest to the lower level is mobile between a first deployed position at which the lower intermediate steps are in the extension of other intermediate steps, and a raised position at which the lower intermediate steps are in a substantially vertical position.

Abstract: The invention relates to a pressurised aircraft door that minimises risk of ingress of precipitation inside the aircraft, while maintaining venting of the aircraft before unlocking the door. The purpose of the invention is achieved using a vent flap (15) controlled by a door control member (14) and designed such that the flap (15) successively occupies the following positions during the opening movement of the control member (14): a closed position when the control member (14) occupies a first end position putting the door in a closed/locked position; at least one partially open position before the door is in a closed/unlocked position; then once again in the closed position when the control member (14) occupies a second end position putting the door in an open position.

Abstract: A panel (1) includes a plurality of retainers (7) along its lateral sides, these being intended to engage, in the closure position of the panel, with corresponding retainers located on the frame structure of this panel. The panel includes at least one beam (3), a longitudinal end portion of which has a slot (15) emerging in the end face of the beam and located at a suitable position for mounting a retainer (6) directly on this beam. The retainer includes a retaining part (7) and a mounting part (8) formed by a base, the mounting part forming one body with the retaining part. The mounting part and the slot (15) are shaped such that the mounting part engages tightly in the slot and the mounting part is fastened to the beam by fastening members, particularly nuts and bolts, which are positioned approximately perpendicular to the principal direction of the beam.

Abstract: The present application relates to a specially designed hinge mechanism (4) which makes it possible to construct an aircraft door (2) that can be fitted in a fuselage (3) so as to be displaceable and swivellable on the fuselage (3). Furthermore, the invention relates to an aircraft door (2) comprising at least one such hinge mechanism (4) designed in this way, to a fuselage (3) with at least one aircraft door (2) that is linked to at least one hinge mechanism (4), designed in this way, on the fuselage (3), as well as to the use of at least one hinge mechanism (4) for installation of an aircraft door (2) on a fuselage (3). The hinge mechanism (4) essentially comprises a displacement mechanism (5, 6) as well as a telescopic scissor-type mechanism (7-12). The displacement mechanism (5, 6) can be linked to an aircraft door (2) and is kinematically designed such that as a result of its activation the aircraft door (2) can be displaced from its home position in the direction of the fuselage (3).

Abstract: An aircraft door includes an outer skin configured as a panel structure; and a rear body structure configured as an integral cast structure and operatively connected to the panel structure so as to provide rigidity.

Abstract: This door includes a device that permits air to flow through the door in one direction but prevents this flow of air in the opposite direction. On the attached illustration, the door includes at least a window (74), that less air pass through as well as an elastic membrane (76) covering window (74). Elastic membrane (76) includes on the one hand an area that is airtight facing window (74) and capable of fully covering it and on the other hand, an area that is pervious to air near the impervious area.

Abstract: A door pod assembly includes a housing that defines a cavity for emergency equipment, a pod door, and a latch retaining the pod door in a closed position relative to the housing. The assembly is configured such that the latches, upon activation free the release door thereby exposing the emergency equipment and allowing it to be deployed. The door pod assembly maybe coupled to an interior surface of a baggage compartment door and is configured so that the baggage compartment may continue to be used for its originally intended purpose.

Abstract: The invention relates to an emergency exit hatch for exiting a cabin module for an aircraft in an emergency and entering the cabin module. Said emergency exit hatch comprises a first mechanism for visually inspecting a zone below the emergency exit hatch by at least partly opening the emergency exit hatch by means of the first mechanism, and a second mechanism for entirely opening the emergency exit hatch . The first mechanism is not the same as the second mechanism.

Abstract: The present invention relates to a fuselage nose door for sealing an opening in the hull of an aircraft. In order to make loading and unloading as efficient as possible, a door shell is proposed that is movably held between a closed setting and an open setting by a bearing device, wherein the door shell can be pivoted and shifted in relation to the bearing device. The invention also relates to an aircraft with such fuselage nose door. In addition, the invention also relates to a method for opening and closing an opening in the hull of an aircraft with a fuselage nose door, which has a door shell that is movably held by a bearing device between the closed setting and open setting, wherein the door shell is pivoted and shifted in relation to the bearing device in the opening and closing process.

Abstract: A roll-on/roll-off, aircraft-borne sensor pod deployment system having an operator station and a sensor pallet system and method of using same. The operator station has a base platform, a shelter box mounted on the base platform for accommodating a human operator, and a computer installed inside the shelter box. The sensor pallet system has a base platform, a linear system mounted on the base platform, a rotational system mounted on the linear system, a mechanical arm attached to the rotational system, a sensor pod attached to the mechanical arm, and an electrical control system that provides power to the deployment system and controls movements of the sensor pallet system. In operation, the sensor pod can be retracted into a compact, stowing position, or extended out an opening in the aircraft for an unobstructed field of view. The deployment system optionally includes an apparatus and method for sealing the aircraft opening.

Abstract: There is provided a space-saving and compact swing type door structure of an aircraft restroom, in which a door is automatically closed and which is easy to use for a passenger using the restroom. The swing type door (40) is slidably hung at its upper end edge (44) from a rail disposed at an upper portion of a door frame by a guide structure including a slide pin (46) and is turnably connected in a predetermined position different from the hung position to the door frame by a linkage (60). Swinging operation in opening the door (40) deforms a spring provided in an automatic closing device (50). When a hand is released from the door (40), the door (40) is constantly biased in a closing direction by spring resilience through the linkage (60) and automatically returns to a closed position. Therefore, the restroom becomes easy to use, an aisle in front of the restroom can be used in an emergency, and it is possible to avoid contingencies caused by false recognition of an escape hatch.

Abstract: A door hinge (10) according to the invention comprises a first hinge element (12) which is fastenable to a door frame (24) and a second hinge element (14) which is fastenable to a door leaf (28) and has a first hinge blade (20) and a second hinge blade (22). A first pivot axis (32) is connected, when the door hinge (10) is in a first operating condition, to the first and second hinge elements (12, 14) in such a way that the second hinge blade (22) of the second hinge element (14) is pivotable, when the door hinge (10) is in said first operating condition, about said first pivot axis (32), relative to the first hinge element (12), in a first pivot direction (Px), for the purpose of unblocking a door aperture which is bounded by the door frame (24). The first pivot axis (32) is decoupled from the first or the second hinge element (12, 14) when the door hinge (10) is in a second operating condition.

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. The door plug assembly is designed to accommodate the simultaneous use of a sonotube stores launch system, a missile defense system, and an observer bubble window.

Abstract: The invention is directed to a device for heating lock elements in aircraft, in particular to prevent icing up of door locks and emergency slide locks. The object of the invention, to find a novel possibility for heating lock elements in aircraft, particularly for preventing icing of door locks and emergency slide locks, which reliably eliminates icing of the lock elements without requiring frequent maintenance and repair due to high mechanical, chemical and thermal stresses, is met according to the invention in that a base body which is mounted in the floor of the aircraft and contains an insert profile has an integrated, inserted sliding plate and in that the sliding plate is hollowed out from the bottom over a large surface to receive a heating foil, wherein the heating foil is embedded in the hollowed out recess in a sandwich-type construction, and the sliding plate is hermetically sealed from the bottom.

Abstract: A door assembly has a first door integrated with a second door. The first door has a first door cowl. The second door is pivotably mounted to the first door and has a second door cowl forming at least a portion of the first door cowl. The door assembly includes at least one actuator coupled to the first and second doors. Each one of the first and second doors is pivotable between open and closed positions and defines an opening when moved to the open position. The openings of the first and second doors face in opposite directions. The actuator is operative to pivotably move at least one of the first and second doors between the open and closed positions.

Abstract: A device intended for a hold that can receive containers and luggage simultaneously. The hold includes a freight loading system including rollers defining a rolling surface on which a container can move with the movement of the rollers. The device includes a unit including conveyor belts disposed longitudinally in the hold one after the other such as to extend over at least part of the length of the hold. Each conveyor belt includes an upper section configured to receive an object to be moved and each conveyor belt can move between a first raised position in which the upper section of the belt is located above the rolling surface defined by the rollers of the freight loading system and a second position in which the upper section of the belt is located below the rolling surface.

Abstract: An aircraft structure is provided. The aircraft structure for an aircraft includes a fuselage, front wings, rear small wings, vertical winglets, and four levels. The fuselage has a cross-section of substantially a half circle fuselage shape. Being is wide enough to provide lifting force, and includes four levels separated by multi partition structure. The front wings are disposed horizontally in front portions of the fuselage. The rear small wings are disposed horizontally in rear portions of the fuselage. The vertical winglets are disposed at the wingtips of the rear small wings. The first level disposed at a bottom of the four levels includes a fuel tank storages and a plurality of landing gear bays. The second level disposed at a middle of the four levels includes cargo bay. The third level may comprise a top cockpit and a plurality of passenger cabins. The fuselage provides major portion of lifting force and the wings provides steering force, and lifting force.

Abstract: This door is intended for a compartment, such as an aircraft baggage compartment. The door can be moved between a first position, in which it closes an opening of the compartment, and a second position, in which the opening is accessible. This door is provided with a guide system on both sides of the opening of the compartment to guide the door in a substantially vertical translational movement.

Abstract: The invention relates to floor heating for an aircraft which has a floor (20) made up of heatable panels (18). In order to be able to heat up the panels (18) in an energy-saving way, the same are provided with hollow chambers (26) which pass through them, wherein a feed line (28) for warm waste air originating from the cooling of the aircraft's electronic equipment which is connected to the first hollow chambers (26), conveys hot air to the first hollow chambers (26) when the floor heating system is in operation.

Abstract: Embodiments relate to a locking and unlocking system of a separation door separating a cockpit from a cabin of an aircraft. In one embodiment, a system comprises a set of electrically controlled bolts configured to lock the door, a control unit configured to electrically control the set of bolts, a first manual control connected to the control unit, installed in the cockpit and configured to unlock the door, a second manual control connected to the control unit, installed in the cabin and configured to unlock the door, an accelerometer to detect a crash, and a switching relay to control automatic unlocking of the door when a crash of the aircraft is detected, the relay connected to the accelerometer, the control unit and the set of bolts.

Abstract: A method and apparatus comprising a frame and a door. The door may be moveably connected to the frame. The door may be capable of being rotated in the frame between a closed position and an open position to provide access to an opening of a vehicle body without moving the door outside of a mold line of the vehicle body.

Abstract: A door opening and closing mechanism for opening and closing the door from the inside of a fuselage. A door pivotally supported at an opening portion of the fuselage includes first and second position restricting links each having one end pivotally supported on the fuselage with a door driving link having one end pivotally supported on the door. The other end of the second position restricting link is pivotally supported on a middle portion of the door driving link. The door opening/closing operation lever is provided at one end with a grip with the other end pivotally supported on the other end of the door driving link. The middle portion of the door opening/closing operation lever is pivotally supported on the other end of the first position restricting link. By pulling the grip toward the inside of the fuselage and thereafter pushing downward, the door can be closed.

Abstract: A deceleration device adapted for gradual dissipation of kinetic energy comprises a spool reel carrying a belt being wound up on the spool reel; an elevating spindle being driven by the spool reel when the belt is being retracted from the spool reel; at least one collet screwed to the elevating spindle; and at least one spring assembly being installed between the collet and a fixed bearing portion of the deceleration device. The at least one collet is screwed towards the fixed bearing portion by retraction of the belt from the spool reel thereby compressing the spring assembly, whereby a reaction load is generated by the spring assembly counteracting the retraction of the belt.

Abstract: The invention relates to a device for supporting a door which is pivotably received in a fuselage airframe of an aircraft, with a counter bearing arranged in the region of a doorframe and a thrust bearing located opposite in the region of the door. According to the invention, the counter bearing has a planar counter bearing surface and the thrust bearing has a mounting in which a planar thrust bearing surface which can tilt about at least one spatial axis is received, the counter bearing surface lying against the thrust bearing surface at least in some regions when the door is closed. Because of the thrust bearing surface which can be tilted in at least one spatial direction, the counter bearing always lies against the thrust bearing over the entire surface areas thereof, irrespective of any manufacturing tolerance deviations between the doorframe and the door or the bearing on the fuselage airframe, in such a way that optimal force transfer is ensured.

Abstract: Attachment bolts and tensioned support systems (e.g., aircraft access systems) are set forth herein. According to one embodiment, an attachment bolt for use in a tensioned support system includes a head portion and a shaft portion extending from the head portion. The head portion has an end face, and the shaft portion has at least one thread and a tip distal to the head portion. A cavity extends entirely through the head and shaft portions and has a linearly extruded segment, an extended diameter at the end face, and an enlarged diameter at the tip. The extended diameter is larger than a diameter of the linearly extruded segment, and the enlarged diameter is larger than the diameter of the linearly extruded segment.