Latch assemblies and aircraft having latch assemblies

Abstract

To provide a latch assembly for an aircraft, and particularly a decompression latch assembly for a decompression panel.SOLUTION: A latch assembly 10 for a decompression panel includes a base 42 and a swing arm 44 hinged to the base 42 and pivotable relative to the base 42 about a hinge axis 82 between a latched position and an unlatched position. A load pin 40 fixed to the swing arm 44 has a pin axis at a fixed distance from the hinge axis 82. A spring 35 secured to the base 42 is positioned to exert a spring force on the swing arm 44 when the swing arm 44 pivots from the latched position to the unlatched position. A bracket 32 securable to the decompression panel defines a slot 62 retaining the load pin 40 when the swing arm 44 is in the latched position. The load pin 40 is movable in the slot 62, and exits the slot 62 when the swing arm 44 pivots to the unlatched position.SELECTED DRAWING: Figure 1

Description

Technical Field

[0001] The present disclosure relates to a latch assembly for an aircraft, and more particularly to a decompression latch assembly for a decompression panel of an aircraft.

Background Art

[0002] When cruising at high altitudes where the ambient atmospheric pressure is low and the air is thin, the cabin of an aircraft is pressurized to maintain a comfortable oxygen level for passengers and crew. Adjacent compartments such as the crown area and the cargo area are separated from the cabin by aircraft structures such as baggage compartments, ceilings, or floors. In a decompression event in a pressurized area, a larger pressure difference than desired can occur between adjacent compartments. An aircraft may be equipped with a closure panel that automatically opens under a pressure difference to reduce the pressure difference. For example, a latch assembly that releases a panel under a predetermined pressure difference on both sides of the panel is often used.

Summary of the Invention

[0003] A latch assembly for a decompression panel in an aircraft includes a base and a swing arm. The swing arm is hinged to the base and is pivotable relative to the base between a latched position and an unlatched position. A load pin is fixed to the swing arm. A spring is fixed to the base and is arranged to apply a spring force to the swing arm when the swing arm pivots from the latched position to the unlatched position. A bracket is fixable to the decompression panel and defines a slot having an open end. The bracket is configured to hold the load pin within the slot when the swing arm is in the latched position. The load pin is movable within the slot under relative movement between the bracket and the base while the swing arm is in the latched position. Under the force of the bracket on the load pin due to a pressure difference on the decompression panel, the load pin exits the open end of the slot when the swing arm pivots from the latched position to the unlatched position. The force of the bracket on the load pin generates a moment on the swing arm that overcomes the spring force.

[0004] The swing arm may be pivotable around the hinge axis relative to the base between a latched position and an unlocked position. The load pin may have a pin axis located at a certain distance from the hinge axis.

[0005] By fixing the load pin to the moving part of the latch assembly (e.g., the swing arm) and configuring the swing arm and bracket to function as a slip joint, relative motion between the panel and the aircraft structure to which the base is fixed (such as that which may result from normal air turbulence) does not result in variations in the magnitude of the force required to induce the latch assembly. Such relative motion can be referred to as non-induced relative motion. For example, the moment arm of the load pin from the hinge axis to the pin axis remains constant despite any such relative motion.

[0006] In one embodiment, the spring may be a beam spring having one end fixed and the other end supported and free-moving on a support rod fixed to a base. The spring displaces between the fixed end and the supported end when the swing arm pivots from the latched position to the unlocked position. The spring may be a leaf spring, such as a steel leaf spring. The simplicity of a steel leaf spring allows for a highly precise spring force determined by the thickness of the spring, which is independent of the geometric dimensions of bending or other features that can loosen the spring force over time and result in changes in the spring force over time. Furthermore, since the leaf spring may be symmetrical, it can be installed with either side facing the swing arm, simplifying the installation.

[0007] Furthermore, a shim may be placed between the base and the spring. The shim can be used to adjust the spring force exerted on the swingarm by the spring. The sum of the thickness of the shim and the thickness of the spring affects the spring force acting on the swingarm when the swingarm moves from the latched position to the unlocked position.

[0008] The plate may be positioned closer to the fixed end of the spring than to the supported end of the spring, and covering the spring. The plate can be fixed to the base with the spring sandwiched between the base and the plate. The plate helps to evenly distribute the fixing force to the fixed end of the spring.

[0009] In one embodiment, the spring may be made of steel, and the coating may be positioned on the spring. The swing arm may come into contact with the coating as it pivots from the unlocked position to the latched position. The coating reduces wear that would otherwise occur due to friction between the swing arm and the spring when in the latched position, as a result of the relative motion of the components during the aircraft's movement. For similar reasons, the sleeve may be positioned around the load pin, so that the sleeve, rather than the load pin, interacts with the bracket in the slot.

[0010] Furthermore, in order to prevent rattling and wear caused by uninduced relative motion, the spring may preload the swingarm when the swingarm is in the latched position, and / or preload the swingarm when the swingarm is in the unlocked position.

[0011] In one embodiment, the swingarm includes a cam having a profile configured to displace a spring when the swingarm pivots from a latched position to an unlocked position. The cam's profile may be configured such that the maximum spring displacement is between the latched and unlocked positions. Thus, the cam's profile helps to maintain the swingarm in the latched position until the bracket exerts a force of at least a predetermined magnitude on the load pin.

[0012] Furthermore, the base may include a support that prevents the swingarm from pivoting away from the latched position. In other words, the support acts as a stopper that blocks the swingarm from pivoting beyond the latched position. A compressible pad may be placed on the support and may interact with the swingarm when it is in the latched position to dampen any rattle between the parts. Similarly, the base may include a support that prevents the swingarm from pivoting away from the latched position, and a compressible pad may be placed on the support and may interact with the swingarm when it is in the latched position. This support acts as a stopper that blocks the swingarm from pivoting beyond the latched position.

[0013] An aircraft decompression system for an aircraft is disclosed. The aircraft has a fuselage, a first structure within the fuselage, and a second structure within the fuselage, spaced apart from the first structure. The fuselage, the first structure, and the second structure define a first space and a second space within the fuselage. The aircraft decompression system includes a decompression panel rotatably fixed to the first structure, configured to at least partially extend into an opening between the first structure and the second structure in a closed position to at least partially separate the first space from the second space. The aircraft decompression system further includes a base fixed to the second structure, and a swing arm hinged to the base and rotatable relative to the base between a latched position and an unlocked position. The decompression panel is in a closed position when the swing arm is in the latched position. A load pin is fixed to the swing arm. A spring is fixed to the base and is arranged to exert a spring force on the swing arm when the swing arm rotates from the latched position to the unlocked position. A bracket is fixed to the decompression panel. The bracket defines a slot with an open end. The bracket holds the load pin in the slot when the swing arm is in the latched position. The load pin is movable within the slot under relative motion between the bracket and the base while the swing arm is in the latched position. Under a predetermined force on the load pin by the bracket due to a positive pressure difference between the first and second spaces, the load pin exits the open end of the slot and is released from the bracket as the swing arm pivots from the latched position to the unlocked position. The predetermined force on the bracket generates a moment on the swing arm that overcomes the spring force, causing the decompression panel to pivot into the second space away from the opening.

[0014] In one embodiment of an aircraft decompression system, the first structure may be an outer box, the second structure may be an inner box, the first space may be a passenger cabin, the second space may be a crown space, and the decompression panel may be a ceiling panel. In such an embodiment, the release of a latch assembly and the associated rotation of the ceiling panel to an open position allow ventilation of the passenger cabin into the crown space through an opening, thereby reducing the pressure difference between the passenger cabin and the crown space.

[0015] A method for installing a decompression latch assembly inside an aircraft is disclosed. The aircraft has a fuselage, a first structure within the fuselage, a second structure, and a decompression panel. The fuselage, the first structure, and the second structure define at least partially a first space and a second space within the fuselage. The decompression panel extends at least partially into an opening between the first structure and the second structure in a closed position to at least partially separate the first space from the second space. The method includes fixing a bracket of a decompression latch assembly to the decompression panel. The bracket defines a slot having an open end that opens toward the second structure. The method includes fixing a base of a decompression latch assembly to the second structure and inserting a load pin into the open end of the slot. The load pin is fixed to a swing arm hinged to the base. The swing arm is pivotable relative to the base between a latched position and an unlocked position when a predetermined force is applied to the load pin by the bracket. The load pin is movable within the slot under relative motion between the bracket and the base when the swingarm is in the latched position.

[0016] In one embodiment, the method may further include fixing a decompression panel to a first structure using a fixed latch assembly. Thereafter, the decompression panel is pivotably fixed to the first structure and pivots relative to the first structure at the fixed latch assembly when the swing arm pivots from a latched position to an unlocked position.

[0017] Furthermore, the method may include inserting a shim between the base of the pressure-reducing latch assembly and the spring to adjust the magnitude of the spring force applied to the swingarm by the spring and the magnitude of a predetermined force applied to the load pin on which the swingarm pivots.

[0018] The features and advantages of this teaching described above, as well as other features and advantages, will become immediately apparent from the following detailed description of some of the best modes and other embodiments for carrying out this disclosure, as set forth in the attached claims, together with the attached drawings.

[0019] The drawings described herein are for illustrative purposes only, are essentially schematic, and are intended to be illustrative rather than limiting the scope of this disclosure. [Brief explanation of the drawing]

[0020] [Figure 1] A perspective view of an exemplary pressure-reducing latch assembly in the latch position. [Figure 2] This is a schematic diagram of a portion of an aircraft, which has a structure that separates adjacent aircraft compartments and includes a decompression latch assembly that latches the ceiling panel to an overhead box. [Figure 3] This is a perspective view of the base of the pressure reducing latch assembly. [Figure 4] This is a perspective view of the swing arm of the pressure relief latch assembly. [Figure 5] A perspective view of the bracket of the pressure reducing latch assembly. [Figure 6] This is a top view of the pressure reducing latch assembly in the latch position. [Figure 7] This is a side view of the pressure reducing latch assembly in the latch position. [Figure 8] This is a cross-sectional view of the pressure-reducing latch assembly cut along line 8-8 in Figure 7. [Figure 9] This is a perspective cross-sectional view of the depressurization latch assembly, cut along line 9-9 in Figure 1. [Figure 10]A perspective cross-sectional view of a vacuum latch assembly cut along line 10-10 of FIG. 1. [Figure 11] A perspective cross-sectional view of the vacuum latch assembly in an intermediate latch release position. [Figure 12] A perspective cross-sectional view of the vacuum latch assembly in a final latch release position. [Figure 13] A perspective view of a sleeve for a load pin of the vacuum latch assembly. [Figure 14] A perspective view of a load pin of the vacuum latch assembly. [Figure 15] A perspective view of a hinge pin of the vacuum latch assembly. [Figure 16] A perspective view of a plate for fixing a spring of the vacuum latch assembly to a base. [Figure 17] A perspective view of a shim for separating a spring from a base. [Figure 18] A perspective view of a spring. [Figure 19] A perspective view of a sleeve for a hinge pin of FIG. 15. [Figure 20] A perspective view of a C-clip for a load pin of FIG. 13 and a hinge pin of FIG. 15. [Figure 21] A perspective view of a screw for a spring of FIG. 18. [Figure 22] A perspective view of a washer for a screw of FIG. 21. [Figure 23] A perspective view of a lock nut for a screw of FIG. 21. [Figure 24] A perspective view of a compressible pad for a base of FIG. 3. [Figure 25] A flowchart showing a method of installing a vacuum latch assembly in an aircraft.

DETAILED DESCRIPTION OF THE INVENTION

[0021] The latch assemblies disclosed herein allow for depressurization of spaces such as aircraft cabins and other spaces by releasing the latch in response to a pressure difference on both sides of a panel, thereby enabling the panel to open to allow ventilation of the space. The design of the latch assembly takes into account the normal relative motion between the panel and the aircraft structure to which the latch assembly latches the panel. In this case, the latch assembly is not unnecessarily induced by its normal relative motion. Furthermore, the latch assembly is configured such that the relative motion does not affect the force that induces the latch assembly to open.

[0022] Referring to the drawings, similar reference numbers refer to similar components, and Figure 1 shows a depressurization latch assembly 10 for an aircraft 12 having an aircraft depressurization system 14 shown in Figure 2. The depressurization latch assembly 10 may be referred to as a depressurization latch assembly or a pressure release latch assembly. The depressurization latch assembly 10 has a latched state shown in Figures 1, 2, 7, 9, and 10, and an unlocked state shown by dashed lines in Figure 2 and in Figure 12.

[0023] Referring to Figure 2, the aircraft 12 has a first structure 16 and a second structure 18 spaced apart from the first structure 16 within the fuselage 20. In one embodiment shown, the first structure 16 is the outer box and the second structure 18 is the central box. The fuselage 20, the first structure 16, and the second structure 18 of the aircraft 12 define and enclose a first space 22, shown as the passenger cabin, and a second space 24, shown as the crown space. The first space 22 may be referred to as the first compartment 22, and the second space 24 may be referred to as the second compartment 24. A portion of the fuselage 20 is shown in Figure 2. It should be understood that the fuselage 20 surrounds the first space 22 and the second space 24, isolating these and other components of the aircraft 12 from the surrounding atmosphere.

[0024] The aircraft decompression system 14 includes a decompression latch assembly 10 and a decompression panel 26. In one illustrated embodiment, the decompression panel 26 is a ceiling panel. The decompression panel 26, the outer box 16, the central box 18, and other aircraft structures separate the first space 22 from the second space 24. It should be understood that the first structure 16 and the second structure 18 are not limited to boxes, the decompression panel 26 is not limited to a ceiling panel, and the first space 22 and the second space 24 are not limited to the passenger cabin and the crown space. In other embodiments, the decompression panel 26 may be a wall or floor panel (instead of a ceiling panel), for example the first compartment may be a cockpit instead of a passenger cabin, and / or, for example the second compartment may be a cargo space.

[0025] The decompression panel 26 is pivotably fixed to the first structure 16 using a fixed latch assembly 28. The fixed latch assembly 28 is referred to as fixed because it is configured such that the decompression panel 26 can pivot relative to the first structure 16 in the fixed latch assembly 28, but remains fixed to the first structure 16 by the fixed latch assembly 28. The fixed latch assembly 28 has a first latch portion 28A fixed to the first structure 16 and a second latch portion 28B fixed to the decompression panel 26. The second latch portion 28B is hinged to the first latch portion 28A, thereby allowing the second latch portion 28B to pivot with the decompression panel 26 relative to the first latch portion 28A. Although only one fixed latch assembly 28 is visible in the side view of Figure 2, there may be two or more fixed latch assemblies 28 spaced apart along the end of the decompression panel 26 closest to the fixed structure 16, and which pivotably secure the decompression panel 26 to the first structure 16.

[0026] The depressurization latch assembly 10 has a bracket 32 ​​that is fixed to the depressurization panel 26 in the second space 24 at the end of the depressurization panel 26 closest to the second structure 18. Although only one depressurization latch assembly 10 is shown in the side view of Figure 2, there may be two or more depressurization latch assemblies 10 spaced apart along the end of the depressurization panel 26 closest to the second structure 18, as well as the latch assembly 28 that is fixed.

[0027] In the opening 30 between the first structure 16 and the second structure 18, the decompression panel 26 extends into the opening 30 when the decompression latch assembly 10 is in the latched position shown in Figure 2, in order to at least partially separate the first space 22 from the second space 24. The edge of the opening 30 is shown in Figure 2, and the opening 30 extends as far as the width and length of the decompression panel 26 (for example, from the latch assembly 28 to which it is fixed to the decompression latch assembly 10). Thus, the air pressure in the first space 22 acts on the first side 34 (lower side in Figure 2) of the decompression panel 26, and the air pressure in the second space 24 acts on the second side 36 (upper side in Figure 2) of the decompression panel 26. The decompression panel 26 is said to extend at least partially into the opening 30 in order to at least partially separate the first space 22 from the second space 24. This is because it is only necessary to separate spaces 22, 24 so as to maintain a pressure difference below a predetermined pressure difference at which the depressurization latch assembly 10 will release the latch.

[0028] Given the thin air of the surrounding atmosphere at high altitude, the air in the first space 22 is pressurized during flight to maintain passenger and crew comfort. The second space 24 does not need to be pressurized to the pressure level of the first space to serve its purpose. Its purpose may include housing electrical wiring systems, gas pressure systems, and other aircraft systems. To help maintain a desired pressure level in the first space, the depressurization latch assembly 10 is configured to remain latched when the pressure difference on the depressurization panel 26 due to the pressurized first space 22 is less than a predetermined magnitude.

[0029] As described herein, a spring 35 (best shown in Figures 8–12 and 18) is fixed to the base 42 and biases the swing arm 44 to the latched position shown in Figure 1, and is positioned to apply a spring force when the swing arm 44 pivots from the latched position to the unlocked position. However, in the event that the pressure difference between the first space 22 and the second space 24 increases such that the net force F acting on the first side surface 34 of the depressurization panel 26 results in at least a predetermined force PF on the bracket 32 ​​onto the load pin 40 of the depressurization latch assembly 10, a moment is generated on the swing arm 44 that can overcome the biasing force of the spring 35. The depressurization latch assembly 10 unlocks, allowing the depressurization panel 26 to pivot from the first space 22 in the direction of arrow A to the open position shown by the dashed line at position 26A and be lifted into the second space 24 by the latch assembly 28 to which it is fixed. By opening the pressure reduction panel 26, the pressure in the first space 22 is vented through the opening 30 into the second space 24, which has a lower pressure, thereby reducing the pressure difference.

[0030] Referring again to Figure 1, in addition to the bracket 32, the depressurization latch assembly 10 includes a base 42 and a swing arm 44. The swing arm 44 is hinged to the base 42 and pivots relative to the base 42 between a latched position and an unlocked position around a hinge axis 46. A load pin 40 is fixed to the swing arm 44 and has a pin axis 48 at a certain distance 50 from the hinge axis 46. The distance 50 may be referred to as the moment arm of the load pin 40. A sleeve 52 may be positioned around the load pin, thereby allowing the load pin 40 to extend through the sleeve 52.

[0031] The bracket 32 ​​can be secured to the decompression panel 26 by bolts, screws, or the like, which may extend through fastener openings 54 in the flange 56 of the bracket 32. Thereafter, the bracket 32 ​​extends prominently from the decompression panel 26 in the second space 24, as shown in Figure 2. The bracket 32 ​​has two elongated bars 58, 60 spaced apart from each other to define a slot 62 between the bars 58, 60. The bars 58, 60 extend outward from the brace portion 57 of the bracket 32 ​​toward the base 42 when the decompression latch assembly 10 is installed in the aircraft 12, as shown in Figure 2. The slot 62 has an open end 64 facing toward the base 42.

[0032] As shown in Figure 1, the bracket 32 ​​is configured to hold the load pin 40 in the slot 62 when the swing arm 44 is in the latched position. As shown in Figure 2, the pressure relief panel 26 is in the closed position when the swing arm 44 is in the latched position. It is the sleeve 52, rather than the load pin 40, that interacts with the bracket 32 ​​in the slot 62. In one embodiment, the bracket 32, base 42, and swing arm 44 may each be made of an aluminum alloy. The load pin 40 may, but is not limited to, stainless steel. The sleeve 52 may be made of nylon and may have an inner diameter 41 (see Figure 13) that fits the outer diameter 43 (see Figure 14) of the load pin 40. Thereafter, the sleeve 52 surrounds the load pin 40. By using a sleeve 52 such as a nylon sleeve, friction with the bars 58, 60 is reduced compared to a stainless steel load pin 40, wear in relative motion is reduced, and the load pin 40 is made more likely to exit the slot 62 during latch release.

[0033] Referring to Figure 5, each of the bars 58 and 60 has straight sections 58A and 60A, and curved ends 58B and 60B, respectively. The curved ends 58B and 60B spread apart from each other. The slot 62 has a length 66 along the straight sections 58A and 60A that is sufficient to allow the expected relative motion in the direction along the slot 62. This relative motion may occur between the decompression panel 26 and the second structure 18 during flight. Thereafter, the load pin 40 remains in the slot 62 and the swing arm 44 remains in the latched position until a predetermined force PF induced on the load pin 40 causes the latch to be released.

[0034] The load pin 40 will exit the open end 64 of the slot 62 during latch release. The load pin 40 and sleeve 52 will move along the convex surface 68 at the curved end 60B of the bar 60 as they exit the open end 64, allowing the bar 60 to continue transmitting force PF to the swing arm 44 as the swing arm 44 pivots toward the latch release position, ensuring that the swing arm 44 overcomes the biasing force of the spring 35 and is pushed by the bracket 32 ​​toward the latch release position.

[0035] Therefore, the ability of the load pin 40 to move within the slot 62 without leaving the slot 62 until a predetermined force PF to be induced is applied by the bracket 32 ​​causes the swing arm 44 and the bracket 32 ​​to function as a slip joint. By fixing the load pin 40 to the moving part of the decompression latch assembly 10 (e.g., the swing arm 44) and configuring the swing arm 44 and the bracket 32 ​​to function as a slip joint, the magnitude of the predetermined force required to induce the latch assembly 10 does not change due to the relative motion, thereby allowing relative motion between the decompression panel 26 and the second structure 18 to which the base 42 is fixed. This would not be the case if the load pin 40 were instead fixed to the bracket 32. In that case, the moment arm of the load pin 40 with respect to the hinge axis 46 could change due to the relative motion. Instead, the moment arm of the load pin 40 from the hinge axis 46 to the pin axis 48 (a constant distance 50) remains constant despite such relative motion.

[0036] Referring to Figure 3, the base 42 includes a flange 70 having a plurality of fastener openings 72. Fasteners extend through the openings 72 to fasten the base 42 to the second structure 18. Fasteners 74 are shown in Figure 1. The base 42 includes outer supports 76 and inner supports 78 extending outward from the flange 70. The inner supports 78 are spaced apart from each other by sufficient spacing 77 to allow one end 35A to which the spring 35 is fixed to be positioned on the surface 81 of the flange 70 at the fastener opening 79 (see Figure 9). Each support 76, 78 includes a hinge pin opening 80, which is aligned with each other and together defines a hinge axis 46.

[0037] The spring 35 is shown in Figure 18 as a flat spring of uniform thickness T having one end 35A fixed and the other end 35B supported. The spring 35 has an opening 37 spaced apart to align with an opening 79 when fixed to the base 42 in Figure 3. The fixed end 35A is referred to as fixed because it is fixed to the base 42 as described herein and does not displace when the swing arm 44 pivots. The supported end 35B is free to move on a support rod 39 fixed to the base 42. The surface 81 of the flange 70 is angled outward to create a recess 83 within the spacing 77. The recess 83 gives the spring 35 room to bend between the fixed end 35A and the supported end 35B when the spring 35 is moved by the swing arm 44. The supported end 35B is referred to as free to move. This is because the spring 35, while resting on the support rod 39, is not fixed and slides relative to the support rod 39 when it is displaced (bent) in order to allow the swing arm 44 to move from the latched position to the unlocked position.

[0038] As illustrated, the support rod 39 may include an outer sleeve 39A in contact with the other end 35B that is supported, and an inner pin 39B. Similar to the sleeve 52 on the load pin 40, the outer sleeve 39A may be made of nylon and may have an inner diameter that fits the outer diameter of the inner pin 39B. Thereafter, the outer sleeve 39A surrounds the inner pin 39B. The inner pin 39B may extend through an opening in the inner support 78 and may be fixed to the support, for example, via a screw 45 integral with the inner pin 39B or a screw 45 and lock nut 47 extending through the inner pin 39B. By using an outer sleeve 39A such as a nylon sleeve, friction at the other end 35B that is supported is reduced, and wear is reduced compared to the inner pin 39B (which may be made of steel, for example).

[0039] The spring force of spring 35 on the swing arm 44 depends on the material and thickness T of spring 35. They are selected to provide spring stiffness such that when a predetermined force PF, designed to cause the aircraft decompression system 14 to open the decompression panel 26, acts on the load pin 40, the spring 35 is displaced sufficiently to release the latch on the swing arm 44.

[0040] Referring to Figure 4, the swing arm 44 includes two spaced-apart knuckle joints 84. Each of them defines a hinge pin opening 86. The hinge pin opening 86 aligns with a hinge pin opening 80 along the hinge axis 46. As best seen in Figure 8, two hinge pins 82 are used to connect the swing arm 44 (only the knuckle 84 is shown in Figure 8) to the base 42. Each hinge pin 82 extends through openings 80 in one inner support 78 and one outer support 76. One of the hinge pin openings 86 of the knuckle 84 is located between the inner support 76 and the outer support 78.

[0041] A clip 88, referred to herein as a C-clip 88, fits into a groove 90 of a hinge pin 82 to hold the hinge pin 82 within openings 80, 86. When used herein, a C-clip is a retaining ring having an open end that can be secured in place within a pin, rod, or shaft, such as within a groove 90 in a hinge pin 82, allowing rotation but acting as a barrier to prevent lateral movement of an object adjacent to the C-clip on the pin. One C-clip 88 is shown in Figure 20, and one hinge pin 82 having a groove 90 is shown in Figure 15.

[0042] The hinge pin 82 may, but is not limited to, stainless steel. Two hinge sleeves 85 may be used. Each of them extends around the outer diameter of each hinge pin 82 between the grooves 90 of the hinge pin 82. Thereafter, the hinge sleeves 85 interact with the swing arm 44 at the opening 86 and with the supports 76, 78 at the opening 80 to reduce friction and wear on the hinge pin 82. The hinge sleeves 85 are also shown in Figure 19. The hinge sleeves 85 may, but is not limited to, nylon.

[0043] The outer support 76 includes a retainer 92 that prevents the swing arm 44 from pivoting away from the latched position. In other words, each outer support 76 acts as a retainer that blocks the swing arm 44 from pivoting beyond the latched position. When the swing arm 44 is in the latched position, a compressible pad 94 may be positioned on the surface of the retainer 92, may be bonded to the surface of the retainer 92, may interact with the swing arm 44, and dampen any rattle between the swing arm 44 and the retainer 92. Figures 7, 9, and 10 best illustrate the swing arm 44 interacting with the compressible pad 94 while the retainer 92 is blocking the swing arm 44 from pivoting further away from the latched position. One compressible pad 94 is shown in Figure 24. The compressible pad 94 may, but is not limited to, silicone.

[0044] Similarly, as shown in Figure 3, the inner support 78 includes a retainer 96 that prevents the swing arm 44 from pivoting away from the unlocked position. Each support 78 acts as a retainer that blocks the swing arm 44 from pivoting beyond the unlocked position. A compressible pad 94 may be positioned on the surface of the retainer 96, or bonded to the surface of the retainer 96, and may interact with the swing arm 44 when the swing arm 44 is in the unlocked position, and may dampen any rattle between the swing arm 44 and the retainer 92. Figure 12 best illustrates the swing arm 44 interacting with the compressible pad 94 with the retainer 96 blocking the swing arm 44 from pivoting further away from the unlocked position.

[0045] Referring to Figure 4, the swing arm 44 includes two arm portions 44A and 44B spaced apart from each other. Each arm portion 44A, 44B has an opening 98. The opening 98 is aligned to define a pin shaft 48. As shown in Figure 1, the load pin 40 extends through the opening 98. The opening 98 is sized to allow the load pin 40, rather than the sleeve 52, to extend through it, as shown in Figures 6 and 11. Referring to Figure 14, the load pin 40 has a circumferential groove 90 similar to that of the hinge pin 82 to receive a C-clip 88, as shown in Figures 1 and 7, for example.

[0046] Referring again to Figure 4, the swing arm 44 includes a cam 100 positioned between two spaced knuckles 84, which extends further than the knuckles 84 away from the ends of the arm portions 44A and 44B that support the load pin 40. The cam 100 has a cam surface 102 with a contour 104 configured to displace the spring 35 when the swing arm 44 pivots from a latched position to an unlocked position. The contour 104 of the cam 100 may be configured such that the maximum displacement of the spring 35 is between the latched position and the unlocked position. For example, referring to Figure 4, the cam surface 102 includes a first surface portion 102A, a second surface portion 102B, and a tip portion 102C between the first surface portion 102A and the second surface portion 102B. As shown in Figures 9 and 10, when in the latched position, the first surface portion 102A is leaning against the spring 35. To help maintain the swing arm 44 in the latched position and to prevent rattling and wear of the spring 35 of the cam 100 due to the non-induced relative motion described herein, the cam 100 is configured to preload the spring 35 so that it is slightly displaced (for example, the spring 35 is slightly pushed toward the base 42 between the supported other end 35B and the fixed one end 35A).

[0047] As shown in Figure 12, when in the unlocked position, the second surface portion 102B is resting on the spring 35. To help maintain the swing arm 44 in the unlocked position and to prevent rattling and wear due to uninduced relative motion, the cam 100 is configured to preload the spring 35 so that the spring 35 is slightly displaced (for example, the spring 35 is slightly pushed toward the base 42 between the supported other end 35B and the fixed one end 35A).

[0048] To move the swing arm 44 from the latched position to the unlocked position, and vice versa, the tip portion 102C of the cam 100 moves across and against the spring 35 (for example, against the coating 110 on the spring 35). Since the tip portion 102C is the furthest part of the cam 100 in the opposite direction to the direction from the hinge axis 46 to the pin axis 48 (for example, opposite to the moment arm), the spring 35 will experience the maximum displacement by the swing arm 44 at an intermediate position between the latched position and the unlocked position, as shown in Figure 11. The cam contour 104 may be configured such that a predetermined force PF is the force that causes the displacement of the spring 35 by the amount by which the tip portion 102C contacts the spring 35 (for example, displacing the spring 35 to the intermediate position in Figure 11). Therefore, the cam contour 104 helps to maintain the swing arm 44 in the latched position until a force of at least a predetermined force PF acts on the load pin 40.

[0049] The cam contour 104 is asymmetrical in that the first surface portion 102A is slightly longer than the second surface portion 102B. As a result, the tip portion 102C is slightly distorted in one direction. An asymmetrical marker 106 (see Figure 4) is provided on one or both of the arm portions 44A, B and indicates the direction in which the swing arm 44 should be oriented so that the second surface portion 102B interacts with the spring 35 in the unlocked position. In one illustrated embodiment, the asymmetrical marker 106 is a triangle with a vertex indicating the upward direction in which the swing arm 44 should be oriented before the hinge pin 82 is inserted through the opening 80.

[0050] Referring to Figure 7, relative motion between the bracket 32 ​​and the base 42 can occur in the horizontal direction X in Figure 7 along the length 66 of the straight sections 58A, 60A without the load pin 40 exiting the slot 62. Thus, the load pin 40 can slide between the closed end 63 of the slot 62 and the inflection of the bars 58, 60 at the end of the straight section where the bars 58, 60 begin to curve at the curved ends 58B, 60B. Relative motion can also occur in the vertical direction Y in Figure 7 by any amount that results in a force on the load pin 40 by the bracket 32 ​​less than a given force PF. This is because the spring 35 can prevent the swing arm 44 from passing the tip portion 102C of the cam contour 104 at such relatively low forces. Thus, pressure differences between sections 22, 24 on the pressure reduction panel 26 less than a given pressure difference will not unlock the pressure reduction latch assembly.

[0051] Referring to Figures 8 to 10, the spring 35 is shown as a beam spring having one fixed end 35A and the other supported end 35B. In one illustrated embodiment, the spring 35 is a steel plate spring, and in other embodiments, it may be made of a different material and does not need to be flat. The simplicity of the steel plate spring allows for a highly precise spring force determined by the thickness of the spring 35, which is independent of the geometric dimensions of bending or other features that can loosen the spring force over time and result in changes in the spring force over time. Although the spring 35 is depicted as a beam spring with the other supported end 35B, in other embodiments, the spring 35 may instead be a cantilever beam having, for example, a free end (without a support rod 39). As described, by configuring the spring 35 as a beam spring having one fixed end 35A and the other supported end 35B free on the rod 39, the desired release of the latch at a given force PF can be achieved more easily than, for example, with a cantilever spring. The thickness T may be reduced, for example, compared to a cantilever spring with a free end.

[0052] Furthermore, the leaf spring may be symmetrical and may be positioned so that either side faces the cam 100. In one embodiment, as shown in Figure 10, the coating 110 is placed on the outer surface of the spring 35. As previously described, the coating 110 reduces frictional wear (which may occur without the coating 110) of the cam 100 of the swing arm 44 against the spring 35 when in the latched position, as a result of the normal relative motion of the components of the latch assembly during flight (e.g., the bracket 32 ​​and the base 42). Since the spring 35 is symmetrical and may be positioned so that either side faces the cam 100, both sides of the spring 35 are coated. The spring 35 may, but is not limited to, a plate of stainless steel finished with a zinc-nickel alloy, coated with a primer, and then coated with polytetrafluoroethylene (PTFE) polyester 110.

[0053] Furthermore, a shim 112 may be used and is shown to be positioned between the base 42 and the spring 35. A shim 112 having a fastener opening 114 is shown in Figure 17 to allow a screw, such as the screw 120 shown in Figure 21, to extend through the shim 112 when fastening the shim 112 and the spring 35 to the base 42. The shim 112 is used to adjust the spring force applied to the swingarm 44 by the spring 35. The combined thickness of the shim 112 and the spring 35 affects the spring force of the spring 35 acting on the swingarm 44 when the swingarm 44 moves from the latched position to the unlocked position. The shim 112 may be made of machined aluminum alloy.

[0054] A plate 116, referred to as a clamping plate 116, is positioned closer to the fixed end 35A of the spring 35 than to the supported end 35B of the spring 35, and covers the spring 35. Figure 16 shows a plate 116 having fastener openings 118 aligned with the opening 37 of the spring 35 and the opening 114 of the shim 112. The plate 116 can be fixed to the base 42 with the spring 35 sandwiched between the base 42 and the plate 116. The plate 116 may be made of an aluminum alloy. The plate 116 helps to evenly distribute the fixing force to the fixed end 35A of the spring 35. The screw 120 shown in Figures 10 and 21 extends through the aligned openings 118, 37, 114, and 79 and is secured to a washer 124 (also shown in Figure 22) with a lock nut 122 (shown in Figure 23) to fasten one end 35A which is fixed in place on the base 42. The spring 35 is of such length that when the swing arm 44 moves from the latched position to the unlocked position, and vice versa, the supported other end 35B moves along the outer surface of the support rod 39 and comes into contact with its outer surface.

[0055] A method 200 for installing a decompression latch assembly inside an aircraft is disclosed and described in relation to a decompression latch assembly 10 and an aircraft 12. Figure 25 is a flowchart of the method 200. In one embodiment, the method 200 may include step 202, which is to secure a decompression panel 26 to a first structure 16 (e.g., an outer box 16) using a latch assembly 28 to be fixed. Thereafter, the decompression panel 26 is pivotably fixed to the first structure 16 and pivots relative to the first structure 16 at the latch assembly 28 to be fixed. Alternatively, the decompression panel 26 may already be fixed to the first structure 16 using the latch assembly 28 to be fixed when the method 200 is started.

[0056] Method 200 includes step 204, which is to fasten the bracket 32 ​​of the latch assembly 10 to the decompression panel 26. The bracket 32 ​​defines a slot 62 having an open end 64 that opens toward a second structure 18 (e.g., a central box 18). In other words, when the bracket 32 ​​is fastened to the decompression panel 26, the installer orients the open end 64 toward the second structure 18 rather than toward the first structure 16 (e.g., an outer box 16).

[0057] Method 200 includes step 206, which is to secure the base 42 of the latch assembly 10 to the second structure 18. Step 206 may be completed either before or after step 204 is completed. Method 200 further includes step 208, which is to insert a load pin 40 into the open end 64 of the slot 62. The load pin 40 is secured to a swing arm 44 that is hinged to the base 42. The load pin 40 may already be secured to the swing arm 44 when it is inserted into the slot 62, and the swing arm 44 may already be hinged to the base 42. The swing arm 44 is pivotable relative to the base 42 between a latched position and an unlocked position when a predetermined force is applied to the load pin by a bracket, and the depressurization panel 26 pivots relative to the first structure 16 in the latch assembly 28 to which it is secured when the swing arm 44 pivots from the latched position to the unlocked position. The load pin 40 is movable within the slot 62 under the relative motion between the bracket 32 ​​and the base 42 while the swing arm 44 is in the latched position.

[0058] Furthermore, method 200 may include step 210, which is the step of inserting a shim 112 between the base 42 of the latch assembly 10 and the spring 35 in order to adjust the magnitude of the spring force applied to the swing arm 44 by the spring 35 and the magnitude of a predetermined force PF applied to the load pin 40 on which the swing arm 44 pivots. For example, step 210 may be performed if it is determined that the spring force needs to be adjusted to achieve a desired predetermined force PF that induces the latching of the latch assembly 10. Alternatively, the shim 112 may already be inserted as described when method 200 begins, or the shim 112 may not be included in the latch assembly.

[0059] Accordingly, the decompression latch assembly 10 disclosed herein can accommodate relative motion between components of the aircraft 12, for example, caused by turbulence, without the force fluctuations required to unlatch the decompression latch assembly 10. The decompression latch assembly 10 opens at a predetermined pressure difference between two components in the aircraft 12 that brings a predetermined force PF onto the load pin 40 by unlatching regardless of the relative position of the load pin 40 in the slot 62 of the bracket 32, allowing the decompression panel 26 to pivot into the second compartment 24 and ventilate the first compartment 22.

[0060] Further exemplary and non-exclusive embodiments of this disclosure are described in the following paragraphs.

[0061] In one embodiment of the present disclosure, a latch assembly (10) for a decompression panel (26) in an aircraft (12) comprises a base (42), a swing arm (44) hinged to the base (42) and pivotable relative to the base (42) between a latched position and an unlocked position, a load pin (40) fixed to the swing arm (44), a spring (35) fixed to the base (42) and arranged to apply a spring force to the swing arm (44) when the swing arm (44) pivots from the latched position to the unlocked position, and a bracket (32) fixable to the decompression panel (26) defining a slot (62) having an open end (64), and when the swing arm (44) is in the latched position, the load The bracket (32) is configured to hold the pin (40) within the slot (62), and the load pin (40) is movable within the slot (62) under the relative motion between the bracket (32) and the base (42) when the swing arm (44) is in the latched position, and the load pin (40) exits the open end (64) of the slot (62) under the force of the bracket (32) on the load pin (40) due to the pressure difference on the depressurization panel (26), when the swing arm (44) pivots from the latched position to the unlocked position, and the force of the bracket (32) on the load pin (40) generates a moment on the swing arm (44) that overcomes the spring force.

[0062] Optionally, in the latch assembly (10) of the previous paragraph, the swing arm (44) is pivotable relative to the base (42) around the hinge axis (46) between the latched position and the unlocked position, and the load pin (40) has a pin axis (48) at a certain distance from the hinge axis (46).

[0063] Optionally, one of the latch assemblies (10) in the preceding paragraph further comprises a support rod (39) fixed to the base (42), the spring (35) being a beam spring having a fixed end (35A) and a supported end (35B) that is free-moving on the support rod (39), the spring (35) being displaced between the fixed end and the supported end when the swing arm (44) pivots from the latched position to the unlocked position.

[0064] Optionally, in the latch assembly (10) of one of the preceding paragraphs, the spring (35) is a leaf spring.

[0065] Optionally, in one of the latch assemblies (10) in the preceding paragraph, the spring (35) is made of steel, and the latch assembly (10) further includes a coating (110) positioned on the spring (35), and the swing arm (44) comes into contact with the coating (110) when it pivots from the unlocked position to the latched position.

[0066] Optionally, one of the latch assemblies (10) in the preceding paragraph further comprises a shim (112) positioned between the base (42) and the spring (35).

[0067] Optionally, one of the latch assemblies (10) in the preceding paragraph further comprises a plate (116) positioned to cover the spring (35) closer to the fixed end of the spring (35) than the other supported end of the spring (35), wherein the plate (116) can be fixed to the base (42) with the spring (35) sandwiched between the base (42) and the plate (116).

[0068] Optionally, in one of the latch assemblies (10) in the preceding paragraph, the spring (35) preloads the swing arm (44) when the swing arm (44) is in the latched position or when the swing arm (44) is in the unlocked position.

[0069] Optionally, one of the latch assemblies (10) in the preceding paragraph includes a cam (100) having a contour (104) configured to displace the spring (35) when the swing arm (44) pivots from the latched position to the unlocked position.

[0070] Optionally, in one of the latch assemblies (10) in the preceding paragraph, the contour (104) of the cam (100) is configured such that the maximum displacement of the spring (35) lies between the latch position and the unlocked position.

[0071] Optionally, one of the latch assemblies (10) in the preceding paragraph further comprises the sleeve (52) positioned around the load pin (40) such that the sleeve (52) interacts with the bracket (32) in the slot (62).

[0072] Optionally, in one of the latch assemblies (10) in the preceding paragraph, the base (42) includes supports (76, 78) that prevent the swing arm (44) from pivoting away from the latch position or away from the latch position.

[0073] Optionally, one of the latch assemblies (10) from the previous paragraph further comprises a compressible pad (94) positioned on the support (76, 78) and configured to interact with the swing arm (44).

[0074] In another embodiment of the present disclosure, an aircraft decompression system for an aircraft (12), the aircraft (12) having a fuselage (20), a first structure (16) within the fuselage (20), and a second structure (18) within the fuselage (20) spaced apart from the first structure (16), the fuselage (20), the first structure (16), and the second structure (18) defining a first space (22) and a second space (24), the aircraft decompression system being rotatably fixed to the first structure (16), and the first space To at least partially separate the space (22) from the second space (24), the system includes a pressure relief panel (26) configured to at least partially extend into the opening between the first structure (16) and the second structure (18) in the closed position, and a latch assembly (10), the latch assembly (10) comprising a base (42) fixed to the second structure (18), a swing arm (44) hinged to the base (42) and pivotable relative to the base (42) between a latched position and an unlocked position, wherein the swing arm (44) When the pressure reducing panel (26) is in the latched position, the pressure reducing panel (26) is in the closed position, and the swing arm (44), load pin (40) fixed to the swing arm (44), spring (35) fixed to the base (42) and arranged to apply a spring force to the swing arm (44) when the swing arm (44) rotates from the latched position to the unlocked position, and bracket (32) fixed to the pressure reducing panel (26), defining a slot (62) having an open end (64), and when the swing arm (44) is in the latched position When the swing arm (44) is in the latched position, the load pin (40) is held in the slot (62), and the load pin (40) is movable in the slot (62) under the relative movement between the bracket (32) and the base (42) when the swing arm (44) pivots from the latched position to the unlocked position under a predetermined force on the load pin (40) of the bracket (32) due to the positive pressure difference between the first space (22) and the second space (24),The bracket (32) is included, which exits the open end (64) of the slot (62) and is released from the bracket (32), and the predetermined force of the bracket (32) on the load pin (40) generates a moment on the swing arm (44) that overcomes the spring force, and the decompression panel (26) pivots into the space (24) so ​​as to move away from the opening.

[0075] Optionally, in the aircraft decompression system of the previous paragraph, the latch assembly (10) is located in the second space (24) both when the latch assembly (10) is in the latched position and when the latch assembly (10) is in the unlocked position.

[0076] Optionally, one of the aircraft decompression systems in the preceding paragraph further comprises a fixed latch assembly (28) that pivotably secures the decompression panel (26) to the first structure (16), the decompression panel (26) pivoting in the fixed latch assembly (28) when the decompression panel (26) pivots into the second space (24) so ​​as to move away from the opening.

[0077] Optionally, in the aircraft decompression system of the previous paragraph, the first structure (16) is an outer box, the second structure (18) is an inner box, the first space (22) is the passenger cabin, the second space (24) is the crown space, and the decompression panel (26) is the ceiling panel.

[0078] In another embodiment of the present disclosure, a method for installing a decompression latch assembly (10) in an aircraft (12), the aircraft (12) having a fuselage (20), a first structure (16), a second structure (18) within the fuselage (20), and a decompression panel (26), wherein the fuselage (20), the first structure (16), and the second structure (18) at least partially define a first space (22) and a second space (24) within the fuselage (20), and the decompression panel (26) at least partially extends into an opening (30) between the first structure (16) and the second structure (18) in the closed position of the decompression panel (26) to at least partially separate the first space (22) from the second space (24), the method comprising fixing a bracket (32) of the latch assembly (10) to the decompression panel (26), wherein the bracket (32) is the The method includes fixing a bracket (32) to the decompression panel (26), fixing the base (42) of the latch assembly (10) to the second structure (18), and inserting a load pin (40) into the open end (64) of the slot (62), wherein the load pin (40) is fixed to a swing arm (44) hinged to the base (42), and the swing arm (44) is pivotable relative to the base (42) between a latched position and an unlocked position when a predetermined force is applied to the load pin (40) by the bracket (32), and the load pin (40) is movable within the slot (62) under the relative motion between the bracket (32) and the base (42) when the swing arm (44) is in the latched position.

[0079] Optionally, the method of the preceding paragraph further includes fixing the decompression panel (26) to the first structure (16) using the fixed latch assembly (28) such that the decompression panel (26) is pivotably fixed to the first structure (16) and the fixed latch assembly (28) pivots relative to the first structure (16) when the swing arm (44) pivots from the latched position to the unlocked position.

[0080] Optionally, the method of the preceding paragraph further includes inserting a shim (112) between the base (42) of the latch assembly (10) and the spring (35) to adjust the magnitude of the spring force applied to the swing arm (44) by the spring (35) and the magnitude of the predetermined force applied to the load pin (40) on which the swing arm (44) pivots.

[0081] Detailed descriptions and drawings or figures support and illustrate this teaching, but the scope of this teaching is defined solely by the claims. While some of the best modes and other embodiments for carrying out this teaching have been described in detail, various alternative designs and embodiments exist for carrying out this teaching as defined in the attached claims.

Claims

1. A latch assembly (10) for a decompression panel (26) inside an aircraft (12), Bass (42), A swing arm (44) is hinged to the base (42) and is rotatable relative to the base (42) between a latched position and a released position. A load pin (40) fixed to the swing arm (44), A spring (35) is fixed to the base (42) and is arranged to apply a spring force to the swing arm (44) when the swing arm (44) rotates from the latched position to the unlocked position, and A bracket (32) that can be fixed to the pressure reducing panel (26) defines a slot (62) having an open end (64) and is configured to hold the load pin (40) in the slot (62) when the swing arm (44) is in the latch position, and the load pin (40) is movable in the slot (62) under the relative movement between the bracket (32) and the base (42) when the swing arm (44) is in the latch position, and the load A latch assembly (10) comprising a bracket (32), wherein the pin (40) exits the open end (64) of the slot (62) as the swing arm (44) pivots from the latched position to the unlocked position under the force of the bracket (32) on the load pin (40) due to the pressure difference on the depressurizing panel (26), and the force of the bracket (32) on the load pin (40) generates a moment on the swing arm (44) that overcomes the spring force.

2. The swing arm (44) is pivotable around the hinge axis (46) relative to the base (42) between the latched position and the unlocked position. The latch assembly (10) according to claim 1, wherein the load pin (40) has a pin axis (48) located at a certain distance from the hinge axis (46).

3. The base (42) is further equipped with a support rod (39) fixed to it. The latch assembly (10) according to claim 1 or 2, wherein the spring (35) is a beam spring having one fixed end (35A) and the other supported end (35B) that is free to move on the support rod (39), and the spring (35) is displaced between the fixed end and the other supported end when the swing arm (44) rotates from the latch position to the latch release position.

4. The latch assembly (10) according to claim 3, wherein the spring (35) is a leaf spring.

5. The spring (35) is made of steel, and the latch assembly (10) is further made of steel. The coating (110) is disposed on the spring (35), The latch assembly (10) according to claim 4, wherein the swing arm (44) contacts the coating (110) when it pivots from the latch release position to the latch position.

6. The latch assembly (10) according to claim 4 or 5, further comprising a shim (112) disposed between the base (42) and the spring (35).

7. The latch assembly (10) according to claim 4, further comprising a plate (116) positioned to cover the spring (35) closer to the fixed end of the spring (35) than the other supported end of the spring (35), wherein the plate (116) is fixable to the base (42) with the spring (35) sandwiched between the base (42) and the plate (116).

8. The latch assembly (10) according to any one of claims 1 to 7, wherein the spring (35) preloads the swing arm (44) when the swing arm (44) is in the latch position or when the swing arm (44) is in the unlock position.

9. A latch assembly (10) according to any one of claims 1 to 8, comprising a cam (100) having a contour (104) configured to displace the spring (35) when the swing arm (44) pivots from the latch position to the unlocked position.

10. The latch assembly (10) according to claim 9, wherein the contour (104) of the cam (100) is configured such that the maximum displacement of the spring (35) is between the latch position and the latch release position.

11. The latch assembly (10) according to any one of claims 1 to 10, further comprising the sleeve (52) positioned around the load pin (40) such that the sleeve (52) interacts with the bracket (32) within the slot (62).

12. The latch assembly (10) according to any one of claims 1 to 11, wherein the base (42) includes support members (76, 78) that prevent the swing arm (44) from pivoting away from the latch position or away from the latch position.

13. The latch assembly (10) according to claim 12, further comprising a compressible pad (94) disposed on the support (76, 78) and configured to interact with the swing arm (44).

14. A method for installing a decompression latch assembly (10) inside an aircraft (12), the aircraft (12) having a fuselage (20), a first structure (16), a second structure (18) inside the fuselage (20), and a decompression panel (26), wherein the fuselage (20), the first structure (16), and the second structure (18) at least partially define a first space (22) and a second space (24) inside the fuselage (20), and the decompression panel (26) at least partially extends into an opening (30) between the first structure (16) and the second structure (18) in the closed position of the decompression panel (26) to at least partially separate the first space (22) from the second space (24), and the method is as follows: Fixing the bracket (32) of the latch assembly (10) to the pressure reducing panel (26), wherein the bracket (32) defines a slot (62) having an open end (64) that opens toward the second structure (18), and fixing the bracket (32) to the pressure reducing panel (26), The base (42) of the latch assembly (10) is fixed to the second structure (18), This includes inserting the load pin (40) into the open end (64) of the slot (62), The load pin (40) is fixed to a swing arm (44) hinged to the base (42), and the swing arm (44) is pivotable relative to the base (42) between a latched position and a released position when a predetermined force is applied to the load pin (40) by the bracket (32). A method wherein the load pin (40) is movable within the slot (62) under the relative movement between the bracket (32) and the base (42) while the swing arm (44) is in the latch position.

15. The pressure reducing panel (26) is fixed to the first structure (16) so as to be rotatable, and the pressure reducing panel (26) is fixed to the first structure (16) using the fixed latch assembly (28) so as to rotate relative to the first structure (16) when the swing arm (44) rotates from the latch position to the unlocked position, and The method according to claim 14, further comprising inserting a shim (112) between the base (42) of the latch assembly (10) and the spring (35) in order to adjust the magnitude of the spring force applied to the swing arm (44) by the spring (35) and the magnitude of the predetermined force applied to the load pin (40) on which the swing arm (44) pivots.

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