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: The invention relates to a device for limiting the deflection of a door (1), particularly a hatch or a freight door, arranged in a fuselage cell (3) of an aircraft, having at least one holding element (5) arranged preferably in the region of a door jamb (4) or in the region of a door leaf edge (7). In order to ensure deflection limitation for doors, hatches and freight doors in aircraft which can be triggered manually independently of an actuation of the normal locking system, it is proposed according to the invention that the at least one holding element (5) can, if there is a sufficient pressure difference ?p between the internal pressure pi prevailing in the fuselage cell (3) and the outside air pressure pa prevailing outside of the fuselage cell (3), be brought into engagement with at least one abutment (6) arranged in the region of the door leaf edge (7) or the door jamb (4).

Abstract: A no touch lavatory has a first sensor outside the lavatory that is operable to cause a motor assembly to open the door of the lavatory in response to a person making a motion in close proximity to the first sensor, a second sensor inside the lavatory that causes the motor assembly to close the door and causes a lock to lock the door in response to the second sensor detecting the person entering the lavatory, and a third sensor inside the lavatory that causes the lock to unlock the door and causes the motor assembly to open the door in response to the third sensor detecting a motion made by the person inside the lavatory.

Abstract: An actuator is configured for transmitting a force or torque to a load. In one example configuration, the actuator includes an input device configured to apply an output force. A backstopping clutch is configured to transmit torque only in the input direction and to prevent back-driving of the input device. An overrunning clutch is configured to include a driven member moved in response to the transmitted torque in the input direction. The load may be moved in response to the driven member, or the load may be moved by a force applied directly to the load.

Abstract: A hingeless door system for a pressure vessel; especially, aeronautic and astronautic crafts. The door system has the following major components: a contour in a pressure vessel wall, a doorway opening, a seal, an upper track, a lower track and a door. The door translocates laterally along the tracks from an open position to a closed position and moves radially along the tracks to a sealed position against the contour which closes the door opening. The problem solved by the invention is to reduce weight, operational volume and complexity and increase durability of a door system for a pressure vessel.

Abstract: An aircraft cabin pressure control system outflow valve includes a frame, a valve element, and a vortex generator structure. The vortex generator structure is coupled to the valve element and is rotatable therewith, and includes a plurality of first vortex generators and a plurality of second vortex generators. The first vortex generators spaced are apart from each other and are configured to generate first vortices when the valve element is in an open position and fluid flows through the flow passage. The second vortex generators are formed in each of the first vortex generators and are spaced apart from each other. The second vortex generators are each configured to generate second vortices, which are smaller than the first vortices, when the valve element is in an open position and fluid flows through the flow passage.

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 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: 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: 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: An aircraft door arrangement having a pivotable door for closing an aperture in the fuselage of an aircraft and selectively movable between closed and open positions by a linear actuating mechanism having a casing and a rod selectively extendable and retractable. An actuator mounting mounts the casing between two elements of the primary structure of the aircraft. The rod is pivotally coupled to the door. The actuator mounting includes a rigid mounting component including three legs extending in a common plane together with the casing and the rotation axis and each having a first and a second longitudinal end. The first and second legs symmetrically extend from the casing at an angle at opposite sides thereof. Each of the second ends of the first and second legs is rotatably coupled on the rotation axis to another one of the spaced elements of the primary structure of the aircraft.

Abstract: A cargo door shield system comprising a cargo door cover movable between a shield position below the fully opened cargo door, and a storage position permitting the cargo door to be moved uninhibited by the cover between the closed and fully opened positions. The system including a pair of spaced apart guide tracks movably supporting the cover for movement between the shield and storage positions, and extending below and spaced apart from the cargo door when the cargo door is in the fully opened position and being spaced apart sufficient to permit passage of the cargo door therebetween when the cargo door is moved between the closed and fully opened positions.

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: 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: The invention relates to a method for fastening an element of airplane interior equipment to a supporting structure in an airplane, comprising the steps of connecting the element of the airplane interior equipment to a first fixing device by using a first locking device, pivoting the element of the airplane interior equipment relative to the supporting structure, and connecting the element of the airplane interior equipment to a second fixing device by using a second locking device. Thus the element of the airplane interior equipment is fastened relative to the supporting structure.

Abstract: A door assembly, in particular for a helicopter, has a post; a door fitted to the post by a first and second hinge arranged on an outer wall of the post, so as to rotate about a hinge axis to open and close a door opening; and an emergency release device having a release handle, and a stem which extends through the post along a release axis substantially perpendicular to the hinge axis, rotates axially, in response to operation of the release handle, from a first to a second angular position to detach the door from the post, and is fixed at one axial end to the first hinge; the release handle being connected to the stem to rotate together with the stem about its release axis.

Abstract: A door assembly, in particular for a helicopter, has a post; a door fitted to the post by a first and second hinge arranged on an outer wall of the post, so as to rotate about a hinge axis to open and close a door opening; and an emergency release device having a release handle, and a stem which extends through the post along a release axis substantially perpendicular to the hinge axis, rotates axially, in response to operation of the release handle, from a first to a second angular position to detach the door from the post, and is fixed at one axial end to the first hinge; the release handle being connected to the stem to rotate together with the stem about its release axis.

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: The invention relates to a device for limiting the deflection of a door (1), particularly a hatch or a freight door, arranged in a fuselage cell (3) of an aircraft, having at least one holding element (5) arranged preferably in the region of a door jamb (4) or in the region of a door leaf edge (7). In order to ensure deflection limitation for doors, hatches and freight doors in aircraft which can be triggered manually independently of an actuation of the normal locking system, it is proposed according to the invention that the at least one holding element (5) can, if there is a sufficient pressure difference ?p between the internal pressure pi prevailing in the fuselage cell (3) and the outside air pressure pa prevailing outside of the fuselage cell (3), be brought into engagement with at least one abutment (6) arranged in the region of the door leaf edge (7) or the door jamb (4).

Abstract: An attachment assembly for securing a secondary door to a mating structure may include a door frame and at least one telescoping structural pin disposable within a side of the door frame. The structural pin may be extendable from a retracted position to a deployed position into the mating structure.

Abstract: A counterbalance mechanism for counterbalancing weight of a bottom-hinged door (such as a clamshell-type airstair door of an aircraft) includes an operator handle, a hoist rod pivotally connected at one end to the operator handle and at an opposite end thereof to the door near a bottom region thereof. A force accumulator assembly is provided which includes a force biasing member which accumulates and dissipates a bias force when opening and closing the door, respectively, to provide mechanical counterbalance to the weight of the door. A bellcrank assembly operatively connects the operator handle to the force accumulator. In such a manner, weight counterbalancing of the door is achieved.

Abstract: A dual function lavatory door and methods are presented. A hinged door panel comprises a doorway hinge coupled to a first side of a lavatory doorway of a lavatory. The doorway hinge positions the hinged door panel to couple to a first interior side-wall of the lavatory in a deployed position. An extendable door panel is coupled to the hinged door panel by a vertical hinge and can couple to a second side of the lavatory doorway opposite to the first side. The extendable door panel folds along the vertical hinge into an interior space of the lavatory in the deployed position. An extension panel is coupled to the extendable door panel and extends from the extendable door panel to couple to a second interior side-wall of the lavatory opposite to the first interior side-wall in the deployed position.

Abstract: A door assembly for an aircraft includes a partition panel disposed laterally within a fuselage of the aircraft and a descender panel moveably secured to a lower end of the partition panel for selectively closing an aisle opening defined below the partition panel. The door assembly further includes a handle disposed on the partition panel that is operatively connected to the descender panel through a link mechanism such that rotation of the handle is translated into movement of the descender panel to move the descender panel between a retracted position and a deployed position.

Abstract: The invention relates to an aircraft including a cabin and a door panel (6) comprising, facing the lintel (5) of the opening (3), a sealing strip (13) having a heel piece (14) secured to the internal face of the door panel (6) and a flexible flap (15) that can deform elastically. In addition, the lintel (5) comprises a supporting face (21) for supporting the flexible flap (15), which face is set back from the profile of the fuselage (2) at the junction between the fuselage and the supporting face, such that, when the door panel (6) is in the closed position, the flexible flap (15) extends over the supporting face and matches the profile of the fuselage.

Abstract: A mechanism including a hinge and movement assembly having a first fastening region, a second fastening region, and a hinge defining an axis of rotation of the second fastening region relative to the first fastening region is provided. The mechanism further comprises an assembly for maintaining a releasable portion of the partition relative to a stationary portion of the partition, the maintenance assembly having at least one frangible connection that can be broken to rotationally free the second fastening region relative to the first fastening region. The hinge and movement assembly includes relative movement means for the second fastening region relative to the first fastening region at least in a direction parallel to the axis of rotation.

Abstract: A gutter profile for draining liquids on an aircraft, comprising a connecting section for connecting the gutter profile to an outer skin of the aircraft and comprising a drain section for forming a drain cross-section of the gutter profile. The drain section is pre-tensioned into a ground position which opens the drain cross-section and has a flow guiding device for transferring the drain section into a flight position which closes the drain cross-section. An aircraft having such a gutter profile is also disclosed.

Abstract: A door assembly, in particular for a helicopter, has a post; a door fitted to the post by a first and second hinge arranged on an outer wall of the post, so as to rotate about a hinge axis to open and close a door opening; and an emergency release device having a release handle, and a stem which extends through the post along a release axis substantially perpendicular to the hinge axis, rotates axially, in response to operation of the release handle, from a first to a second angular position to detach the door from the post, and is fixed at one axial end to the first hinge; the release handle being connected to the stem to rotate together with the stem about its release axis.

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: Particular embodiments comprise a non-dedicated, temporarily installed, airborne special mission payload mounting system which is mechanically interfaced to the Air Deployment System (ADS) rails of a host cargo aircraft. An Adaptive Mounting Plate (AMP) is placed over an ADS rail section and restrained in position. Once the AMP is secured, an articulated or fixed position strut can be attached to it through the opened side doorway without removing the original door. Once the fixed position or articulated strut is bolted to the AMP, a one piece or segmented two piece pressurized door plug indented along its lower periphery to accommodate the protruding form factor of the fixed position or articulated strut is installed within the vacant doorway above the strut providing an airtight seal and thereby permitting pressurization of the aircraft.

Abstract: Overhead stowage compartments are provided for an aircraft. The stowage compartments feature an opening device that can be displaced or rolled up. This may make it possible to prevent lights or air outlets from being covered by pivoting a door upward, as well as to preserve the headroom during the opening process and to prevent collisions between the doors. The architecture of the aircraft may be optimized in this fashion.

Abstract: A door assembly, in particular for a helicopter, has a post; a door fitted to the post by a first and second hinge arranged on an outer wall of the post, so as to rotate about a hinge axis to open and close a door opening; and an emergency release device having a release handle, and a stem which extends through the post along a release axis substantially perpendicular to the hinge axis, rotates axially, in response to operation of the release handle, from a first to a second angular position to detach the door from the post, and is fixed at one axial end to the first hinge; the release handle being connected to the stem to rotate together with the stem about its release axis.

Abstract: An aircraft cabin pressure control system outflow thrust recovery valve includes a frame, a valve element, and actuation hardware. The frame, valve element, and at least a portion of the actuation hardware are made of composite material. The actuation hardware is disposed external to the frame.

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 airship for facilitating transportation to and from one or more locations which are difficult to access or operate such as high above the ground level is disclosed. The airship can also be used in surface missions, The airship includes a cabin and a platform. The cabin is configured on a top portion of the airship. The platform is operatively connected to the cabin. The platform facilitates easy access to the cabin.

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: The overpressure door, of axial type, includes a hatch configured to pivot about an axis between a closed position and an open position and an aerodynamic appendage securely attached to the hatch. The aerodynamic appendage makes it possible to produce a deflection of the external flow in the open position of the hatch of the door.

Abstract: A guiding mechanism is disclosed for moving a cargo door into extended cargo door positions to open and into a retracted cargo door position to close at least one section of an opening of a loading hatch on a fuselage of an aircraft. A first structural component in the form of the cargo door is pivotably supported on a second structural component on a front lateral edge by a pivot joint arranged in a pivoting axis in order to assume the extended cargo door positions on the loading hatch. The guiding mechanism features at least one actuator for moving the cargo door, a supporting device arranged on an actuating element, and a spring mechanism on the actuator for exerting a compressive force.

Abstract: A locking device for an aircraft door in a fuselage section of an aircraft includes at least one fuselage fitting disposed in a region of a sill of the fuselage section and at least one door fitting disposed in a region of a lower edge of the aircraft door and corresponding in number to the at least one fuselage fitting. The at least one fuselage fitting and the at least one door fitting are each configured to transfer at least one of a circumferential load and a radial load.

Abstract: A locking system is disclosed for locking and unlocking a door such as a cockpit door between the cockpit and cabin of an aircraft. The locking system has a door held by hinges on a door frame and movable between an open position and closed position, and at least one closing means that can lock the door when it is in the closed position. The locking system includes a compressed air source that can be coupled to the closing means to move the closing means from an unlocking position to a locking position by supplying compressed air, and at least one venting valve coupled to each of the closing means in order to conduct compressed air away from each closing means when in the open state, in order to move the at least one closing means from the unlocking position to the locking position.

Abstract: An aircraft exterior door installation with a door attached to an airframe. A damper is arranged to damp motion of the door as it is opened by rotating it away from the airframe. A coupling mechanism couples the damper with the door over an opening damping range and decouples the damper from the door at the end of the opening damping range. The damper does not damp the motion of the door as it opens beyond the opening damping range. Instead of damping the door over its full range of motion, it is only damped over a limited inner range of its motion. A further advantage of decoupling the door and the damper is that the damper does not need to extend into the airflow to the same extent as the door, thus minimising aerodynamic drag.

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 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: 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 jettisonable door system for an aircraft includes an upper hinge having a forward portion that is hingedly coupled to an airframe of the aircraft, the upper hinge having an aft portion that is releasably secured to an upper outboard plate with an upper pin. The jettisonable door system further includes a lower hinge having a forward portion that is hingedly coupled to the airframe of the aircraft, the upper hinge having an aft portion that is releasably secured to a lower outboard plate with a lower pin. A rotation of the upper pin releases the upper hinge from the upper outboard plate and a rotation of the lower pin releases the lower hinge from the lower outboard plate.

Abstract: An aircraft-conversion method of converting a passenger aircraft to a cargo aircraft, includes selecting a passenger aircraft, and converting the aircraft to a cargo aircraft by changing a door of the aircraft to accommodate loading and unloading of cargo. The selecting step may involve an all-passenger aircraft, and the converting step may include removing all seats from the aircraft. A system for converting a passenger aircraft with a passenger door for passenger entry and exit to a cargo aircraft includes aircraft-door conversion structure constructed to replace the passenger door with a cargo door that allows loading and unloading of cargo on the aircraft via the cargo door. A converted cargo aircraft includes an aircraft body, and aircraft-door conversion structure constructed to replace the passenger door with a cargo door that allows loading and unloading of cargo on the aircraft via the cargo door.

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: The present invention provides a double hook door mechanism for use in opening and closing aircraft landing gear bay doors.

Abstract: A system for announcing failure of a mechanically actuated arrangement employs a first coupler arrangement that couples an actuator to a structural element that is desired to be controlled, and a first force sensor is coupled to the first coupler arrangement. The first coupler arrangement and the first force sensor constitute a primary load path. Similarly, a second coupler arrangement is coupled to the actuator to the structural element and constitutes a secondary load path. Changes in the forces experienced by one or both of first and second force sensors are monitored by a controller/monitor system. A connector has a screw shaft in the primary load path and a preloaded tie rod in the secondary load path. Axial forces are generated by a drive motor, which can include a ball screw arrangement. Operating impulses generated by the ball screw arrangement are monitored during a predetermined interval of operation.

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 aircraft nacelle includes an air intake followed at the upper part by a part that is integral with the mast, called a cap, and at least one door with a curved profile that includes a stiffening device arranged at the edge upstream from the door and which includes: a flexible element that follows the curved profile of the door between two remote anchoring points, at least one safety index including a latch pivotable around an axis of rotation, and connected to the door so as to occupy a locked position in which the end of the latch rests against the inside surface of an edge upstream from the door, and an unlocked position in which the end of the latch is offset relative to the edge, whereby in the locked position, the latch prevents the scooping phenomena by limiting movements of the door in the radial direction toward the outside of the nacelle, and elements for stretching the flexible element between the two anchoring points and for controlling the pivoting in the locked position of the latch.