Thrust reverser mounting assembly

Abstract

The invention relates to a thrust reverser mounting assembly. A mounting assembly for supporting a thrust reverser mounted to an engine mount of an aircraft. The mounting assembly includes a support assembly configured to be connected to an engine mount of an aircraft, where the support assembly has a first lateral side and a second lateral side. The first arm is connected to the first lateral side of the support assembly and is configured to be connected to the first section of the thrust reverser. A second arm is connected to a second lateral side of the support assembly and is configured to be connected to a second section of the thrust reverser. The first and second arms are pivotally connected to the support assembly to support the first and second sections of the thrust reverser in different angular positions.

Description

TECHNICAL FIELD

[0001] The present disclosure relates generally to the field of aircraft, and more specifically to a mounting assembly that supports a thrust reverser of an engine. BACKGROUND

[0002] Many aircraft engines are equipped with a thrust reverser. The thrust reverser is configured to be in a stowed position to enable the thrust of the engine to propel the aircraft in a forward direction. The thrust reverser is also configured to be in a deployed position to divert the thrust to counter the forward travel of the aircraft. The thrust reverser is often used to slow the aircraft during landing. The thrust reverser uses the engine thrust to slow the aircraft, which helps to reduce wear on the brakes and enables a shorter landing distance for the aircraft.

[0003] The thrust reverser is mounted to the aircraft and extends around a portion or all of an engine core of the engine. During certain times, such as maintenance work, the thrust reverser is positioned to allow access to the engine core. In one example, the thrust reverser is opened to allow the engine core to be removed from the aircraft. During these times, the thrust reverser is in an open position and remains connected to the aircraft. However, the thrust reverser can be damaged while in the open position.

[0004] The thrust reverser includes one or more seals. In one example, the seals are positioned at joints where different segments of the thrust reverser are connected to the wing. If the thrust reverser is in the closed position and the weight of the thrust reverser compresses the seals against the wing, the seals can be damaged. In one example, the seals are fire seals. If a fire occurs in the engine core, the fire seals contain the fire to the immediate area. In some examples, the seals are configured to prevent oxygen from reaching the fire area, thereby preventing the fire from spreading. If these seals are damaged, they can not function properly to contain and / or suppress the fire.

[0005] The aircraft can need to be towed to a different location with the engine core removed and the thrust reverser still attached to the wing. For example, the aircraft can need to be towed to a maintenance area that is away from an active runway. Towing the aircraft in this situation can cause the thrust reverser to bounce or otherwise move, thereby causing excessive forces to be applied to the thrust reverser. These forces can cause damage to the thrust reverser and / or the seals when the segments are not adequately supported in the open position. SUMMARY

[0006] One aspect relates to a mounting assembly for supporting a thrust reverser mounted to an engine mount of an aircraft. The mounting assembly includes a support assembly configured to connect to the engine mount of the aircraft, where the support assembly includes a first lateral side and a second lateral side. A first arm is connected to the first lateral side of the support assembly and is configured to connect to a first segment of the thrust reverser. A second arm is connected to the second lateral side of the support assembly and is configured to connect to a second segment of the thrust reverser. The first arm and the second arm are pivotably connected to the support assembly to support the first segment and the second segment of the thrust reverser at different angular positions.

[0007] In another aspect, the support assembly includes a first base assembly and a second base assembly mounted adjacent to each other and abutting medially together, and where the first arm is connected to the first base assembly and the second arm is connected to the second base assembly.

[0008] In another aspect, the first base assembly and the second base assembly are aligned in a common plane.

[0009] In another aspect, the first base assembly and the first arm are a mirror image of the second base assembly and the second arm.

[0010] In another aspect, the mounting assembly is configured to support the first segment and the second segment of the thrust reverser at an angular range of 6° to 47°.

[0011] In another aspect, the support assembly, the first arm, and the second arm are aligned in a common plane.

[0012] In another aspect, the first arm pivots about a first pivot axis and the second arm pivots about a second pivot axis, where the first pivot axis and the second pivot axis are spaced apart and parallel.

[0013] One aspect relates to a mounting assembly for supporting a thrust reverser mounted to an engine mount of an aircraft. The mounting assembly includes a beam assembly configured to connect to the engine mount. A first base assembly and a second base assembly are each connected to the beam assembly, where the first base assembly is aligned with the second base assembly in a common plane. A first arm is pivotably connected to the first base assembly and includes a first mount configured to connect to a first segment of the thrust reverser. A second arm is pivotably connected to the second base assembly and includes a second mount configured to connect to a second segment of the thrust reverser. The first arm and the second arm are pivoted between a first position and a second position to selectively position the first segment and the second segment of the thrust reverser at different angular positions.

[0014] In another aspect, each of the first base assembly and the second base assembly includes an inner edge abutting together and an outer edge facing outward in an opposite lateral direction, where the first arm is connected at the outer edge of the first base assembly and the second arm is connected at the outer edge of the second base assembly.

[0015] In another aspect, the beam assembly includes a beam and a U-shaped joint extending outward from the beam and configured to connect to the first base assembly and the second base assembly.

[0016] In another aspect, the beam assembly, the first base assembly, the second base assembly, the first arm, and the second arm are aligned in a common plane.

[0017] In another aspect, the first arm and the second arm are configured to pivot in a range of 6°-47° relative to the respective pivot axis.

[0018] In another aspect, a first block is positioned between the first base assembly and the first arm to support the first arm in the first position, and a second block is positioned between the second base assembly and the second arm to support the second arm in the first position.

[0019] One aspect relates to a method of supporting a thrust reverser on an engine mount of an aircraft. The method includes connecting a support assembly to the engine mount; connecting a first arm extending from the support assembly to a first segment of the thrust reverser; connecting a second arm extending from the support assembly to a second segment of the thrust reverser; positioning the first arm and the second arm in a first angular position relative to the support assembly and supporting the first segment and the second segment of the thrust reverser in a first position; and positioning the first arm and the second arm in a second angular position relative to the support assembly and supporting the first segment and the second segment of the thrust reverser in a second position.

[0020] In another aspect, the method further includes pivoting the first arm and the second arm about a pivot axis extending through the support assembly and pivoting the first segment and the second segment of the thrust reverser about a thrust reverser axis, where the pivot axis and the thrust reverser axis coincide.

[0021] In another aspect, the method further includes connecting a first power door opening system (PDOS) bracket on the first arm to the first segment and connecting a second PDOS bracket on the second arm to the second segment.

[0022] In another aspect, the method further includes positioning the first arm and the second arm forward of a forward edge of the thrust reverser.

[0023] In another aspect, the method further includes moving the first segment and the second segment of the thrust reverser through a range of angles of 6°-47°.

[0024] In another aspect, supporting the first segment and the second segment in the first position includes positioning the first segment and the second segment in a fully open position.

[0025] In another aspect, supporting the first segment and the second segment in the second position includes supporting the first segment and the second segment in a near closed position.

[0026] In embodiments of the mounting assembly, wherein the beam assembly (53), the first pedestal assembly (54a), the second pedestal assembly (54b), the first arm (52), and the second arm (52) are aligned in a common plane.

[0027] In embodiments of the mounting assembly, wherein the first arm (52) and the second arm (52) are configured to pivot in a range of 6°-47° relative to the respective pivot axis.

[0028] In embodiments of the mounting assembly, further comprising a first block (96) positioned between the first pedestal assembly (54a) and the first arm (52) to support the first arm (52) in the first position, and a second block (98) positioned between the second pedestal assembly (54b) and the second arm (52) to support the second arm (52) in the first position.

[0029] A method of supporting a thrust reverser on an engine mount of an aircraft, the method comprising: connecting a support assembly (51) to the engine mount; connecting a first arm (52) extending from the support assembly (51) to a first segment of the thrust reverser; connecting a second arm (52) extending from the support assembly (51) to a second segment of the thrust reverser; positioning the first arm (52) and the second arm (52) in a first angular position relative to the support assembly (51) and supporting the first segment and the second segment of the thrust reverser in a first position; and positioning the first arm (52) and the second arm (52) in a second angular position relative to the support assembly (51) and supporting the first segment and the second segment of the thrust reverser in a second position.

[0030] The method further comprises pivoting the first arm (52) and the second arm (52) about a pivot axis extending through the support assembly (51) and pivoting the first segment and the second segment of the thrust reverser about a thrust reverser axis, wherein the pivot axis and the thrust reverser axis coincide.

[0031] The method further includes connecting the first arm (52) to the first electric door opening system bracket, i.e., the first PDOS bracket, on the first section, and connecting the second arm (52) to the second electric door opening system bracket, i.e., the second PDOS bracket, on the second section.

[0032] The method further includes positioning the first arm (52) and the second arm (52) in front of the front edge of the thrust reverser.

[0033] The method further includes moving the first and second sections of the thrust reverser through an angular range of 6° to 47°.

[0034] In an embodiment of the method, supporting the first segment (48) and the second segment (49) in a first position includes positioning the first segment (48) and the second segment (49) in a fully open position.

[0035] In an embodiment of the method, supporting the first segment (48) and the second segment (49) in the second position includes supporting the first segment (48) and the second segment (49) in a near-closed position.

[0036] The features, functions, and advantages already discussed can be implemented independently in each aspect or combined in other aspects, and further details can be seen in the following description and figures. Attached Figure Description

[0037] Figure 1 It is an isometric view of the aircraft.

[0038] Figure 2 This is a schematic top view showing the thrust reverser in the first position, allowing air to move through the fan duct and be discharged at the rear.

[0039] Figure 3 yes Figure 2 A schematic top view of the thrust reverser in the deployed position to direct air from the fan duct through the opening for discharge.

[0040] Figure 4 This is a schematic diagram of a thrust reverser including the first and second sections.

[0041] Figure 5A This is a schematic diagram of the thrust reverser in the open position.

[0042] Figure 5B yes Figure 5A A schematic diagram of the thrust reverser in a near-closed position.

[0043] Figure 6This is an isometric view of the mounting components connected to the first and second sections of the thrust reverser.

[0044] Figure 7A This is a schematic diagram of the mounting components in the first-angle orientation.

[0045] Figure 7B yes Figure 7A A schematic diagram of the mounting components in a second-angle orientation.

[0046] Figure 8 This is a schematic diagram of the thrust reverser in a near-closed position.

[0047] Figure 9 This is an isometric view of the mounting assembly that supports the thrust reverser in the open position.

[0048] Figure 10 It is an isometric view of the mounting assembly that supports the thrust reverser in a near-closed position.

[0049] Figure 11 This is a flowchart of a method for supporting a thrust reverser on an aircraft wing without an engine core. Detailed Implementation

[0050] Figure 1 An aircraft 100 configured to transport passengers and / or cargo is shown. The aircraft 100 generally includes a fuselage 101 having internal space configured to accommodate passengers and / or cargo. The internal space of the fuselage 101 also includes a flight deck 102 with various control devices to enable flight personnel to control the aircraft 100. Engines 104 are mounted on wings 103 on the opposite side of the fuselage 101.

[0051] Figure 2 An engine 104 with certain features is schematically shown; these features will be obscured in the view and indicated by dashed lines. Engine 104 typically includes an engine core 21 and a nacelle 30. The engine core 21 can include various different configurations, including but not limited to a gas turbine engine. In some examples, the engine core 21 includes a fan 22 to draw air into the engine core 21. The nacelle 30 extends around and protects the engine core 21 and the fan 22. The nacelle 30 includes a forward section 31 formed by one or more of an air intake cowl and a fan cowl. The forward section 31 is fixed relative to the engine core 21. The nacelle 30 also includes a thrust reverser 40 with a sleeve that translates relative to the engine core 21 along a longitudinal axis L.

[0052] The thrust reverser 40 is configured to move between a first position and an extended position, the first position allowing air to move through the fan duct 23 and be discharged through the nozzle outlet 24, and the extended position reversing the air moving through the fan duct 23. Figure 2 The thrust reverser 40 is shown in a first position (e.g., during flight). Air is drawn into engine 104, and the first portion, indicated by arrow A, is directed to engine core 21, while the second portion, indicated by arrow B, is directed to fan duct 23. Figure 2 In the retracted position shown, the thrust reverser 40 is positioned forward against the front section 31. The choke 33 is positioned to allow airflow across the length of the fan duct 23 and exit through the nozzle outlet 24 at the rear end. One or more cable chains 34 are attached to the choke 33. The cable chains 34 are in a first orientation that extends across the fan duct 23 and positions the choke 33 in the open position.

[0053] Figure 3 The thrust reverser 40 is shown in its deployed position. The thrust reverser 40 is translated rearward to form an opening 35 between the fixed front section 31 and the thrust reverser 40. The cable chain 34 is actuated to a second orientation to position the baffle 33 across the fan duct 23. This position forces air entering the fan duct 23 through the opening 35. The air flows over the cascading member 36 (e.g., in the form of cascading blades) and exits as a reversed external exhaust flow.

[0054] The thrust reverser 40 has a generally cylindrical shape, with a hollow internal dimension suitable for receiving the engine core 21. For example... Figure 4 As shown, the thrust reverser 40 includes a length X measured between a front end 41 and a rear end 42. In some examples, the thrust reverser 40 extends entirely around the engine core 21. In other examples, the thrust reverser 40 extends partially around the engine core 21. The thrust reverser 40 is divided along the length X into segments including a first segment 48 and a second segment 49. Each segment 48, 49 includes a semi-cylindrical shape with edges 45, 46 extending along the length X. In some examples, segments 48, 49 include the same shape and dimensions. In other examples, segments 48, 49 include different shapes and / or dimensions.

[0055] like Figure 5A and Figure 5BAs shown, the mounting assembly 50 connects the thrust reverser 40 to the engine mount 105 on the wing 103. The mounting assembly 50 provides support when the engine core 21 is removed from the internal space 44 of the thrust reverser 40. The mounting assembly 50 generally includes a support assembly 51 connected to the engine mount 105 in the wing 103. Arms 52 extend from the support assembly 51 and are configured to be connected to the first section 48 and the second section 49 respectively. The arms 52 enable the first section 48 and the second section 49 to move to different angular positions. The first section 48 is configured to pivot about a pivot axis A. The second section 49 is configured to pivot about a pivot axis B.

[0056] Figure 5A The sections 48, 49 are shown in a first position. In some examples, the first position is a fully open position, i.e., the range of the pivotal movement of the sections 48, 49. In other examples, the first position is not a fully open position. The sections 48, 49 are positioned at an angle α measured from the thrust reverser pivot axes A, B and the latch beam edge 46 to the center plane Y between the first section 48 and the second section 49 of the thrust reverser 40. The sections 48, 49 pivot outwardly about the respective pivot axes A, B near the hinge beam edge 45, where the opposing latch beam edges 46 are spaced a greater distance apart. The range of the pivot can vary. In some examples, the angle α is in the range between 40° and 50°. In a specific example, the angle α is 47°.

[0057] Figure 5B The thrust reverser 40 is shown in a second position. In some examples, the second position is a near-closed position, where the first section 48 and the second section 49 pivot such that the latch beam edges 46 are close but still spaced apart. The mounting assembly 50 is configured to prevent the latch beam edges 46 from contacting. The angle α can vary, and one specific example includes an angle of 6°.

[0058] The mounting assembly 50 enables the different sections 48, 49 to move and supports the sections 48, 49 at different angular positions. In some examples as shown in Figure 5A and Figure 5B , the sections 48, 49 are moved an equal distance and positioned at corresponding angles. In other examples, the sections 48, 49 are moved different amounts such that the two angles are different. In some examples as shown in Figure 5A and Figure 5B , the sections 48, 49 are symmetrically positioned with respect to the center plane Y. In other examples, the thrust reverser 40 is aligned at different rotational angles with respect to the center plane Y. In some examples, the mounting assembly 50 enables the first section 48 and the second section 49 to pivot within an angular range of 6° to 47°.

[0059] Overall, mounting assembly 50 enables segments 48 and 49 to pivot between a first position and a second position through a certain range of motion. Mounting assembly 50 supports the segments in various angular positions. In some examples, the range of motion for each segment is 40°. A specific range of motion for each of segments 48 and 49 is an angle α of 47° in the first position and 6° in the second position.

[0060] When the engine core 21 is removed from the internal space 44, the mounting assembly 50 is able to move and support sections 48, 49. In some examples, the mounting assembly 50 supports sections 48, 49 to prevent damage to one or more seals 43 positioned abutting the edges 45 and to the tower structure including the engine mount 105 and positioned in front of the thrust reverser 40. In one example, the seal 43 is a fire-resistant seal positioned between the edges 45 of sections 48, 49.

[0061] Figure 6 A mounting assembly 50, including a support assembly 51 and an arm 52, is shown. The support assembly 51 includes a beam assembly 53 configured to connect to an engine mount 105. In some examples, the beam assembly 53 includes a beam and one or more U-joints. The beam is configured to connect to the engine mount 105 and to position the U-joints outwardly under the wing. The support assembly 51 also includes a base assembly 54. The base assembly 54 is connected to the U-joints of the beam assembly 53. In some examples, the base assembly 54 includes multiple plates arranged in an overlapping manner, joined together, and secured together with fasteners.

[0062] The base assembly 54 can be formed as a single segment or multiple segments. Figure 6 In one example, base assembly 54 includes a first base assembly 54a and a second base assembly 54b. Components 54a and 54b are positioned adjacent to each other and are respectively connected to beam assembly 53. Components 54a and 54b include adjacent inner edges. In one example, the inner edges are aligned along the vertical centerline of thrust reverser 40. Contact along the inner edges between the different components 54a and 54b provides additional strength. In some examples, the separate components 54a and 54b are mirror images of each other.

[0063] Arm 52 is connected to base assembly 54. Arm 52 includes an elongated shape, with a first end connected to base assembly 54 and a second end connected to thrust reverser 40. In some examples, arm 52 comprises a single piece. Figure 6 In other examples shown, arm 52 is formed by two or more separate pieces connected together. Figure 6In the example, arm 52 includes support components 55 and arm 56. Each support component 55 is connected to the outer edge of base component 54 by fasteners. The fasteners secure the support component 55 to the base component 54 and also position the support component 55 at different angular positions relative to the base component 54. Each support component 55 also includes a receptacle 57 on the opposite end, which is sized to receive arm 56.

[0064] Each of the arms 56 includes an elongated shape, the first section of which is configured to insert into a bracket 57. Fasteners extend through and connect the arm 56 to the bracket 57. A mounting member 58 is positioned at a second end and configured to engage with a thrust reverser 40. In some examples, the mounting member 58 is configured to connect to a Power Door Opening System (PDOS) bracket 110 on the thrust reverser 40. The PDOS bracket 110 is positioned along the front end 41 of the thrust reverser 40 and spaced apart from the inner edge 45.

[0065] In some examples, the mounting assembly 50 is divided into two sections around the central axis Y of the thrust reverser 40. Each of the sections has the same shape and dimensions and is positioned in an inverted configuration (i.e., a mirror image around the central axis Y). This configuration facilitates manufacture and use because the mounting assembly 50 has fewer integral parts.

[0066] Mounting assembly 50 can position sections 48 and 49 of thrust reverser 40 at different angular positions. Angular positioning occurs between base assembly 54 and support assembly 55. Figure 7A An arm 52 is shown mounted to a support assembly 51 in a first position. The arm 52 is attached to the support assembly 51 at a pivot axis 95. In some examples, a fastener 90 extends through each of the support assembly 51 and the arm 52 at the pivot axis 95. In some examples, the pivot axes 95 are parallel. A block 96 is positioned in the gap between the support assembly 51 and the arm 52 to support the arm 52. Figure 7B The mounting assembly 50 is shown in the second position. Arm 52 pivots inward relative to support assembly 51 to close the section of the thrust reverser. Arm 52 is connected by a plurality of fasteners 90 spaced apart along the joint.

[0067] exist Figure 8In some of the examples shown, segments 48, 49 of the thrust reverser 40 pivot about one or more axes. In other examples, segments 48, 49 are separate / individual and pivot about individual axes. Furthermore, mounting assembly 50 enables arm 52 to pivot relative to support assembly 51 at an axis at pivot point 95 to move between different angular positions. In some examples with multiple pivot axes, these axes coincide to allow segments 48, 49 to pivot without constraining or otherwise preventing pivoting movement between different angular positions.

[0068] Figure 9 A mounting assembly 50 is shown that positions sections 48, 49 of the thrust reverser 40 in the open position. The mounting assembly 50 is mounted to the engine mount. In some examples, the open position allows an engine core removal / installation device (not shown) to be removed and / or installed onto the tower. An arm 52 is pivoted outward and supports sections 48, 49 to maintain the pivot open position, thereby providing access to the interior space 44.

[0069] Figure 10 Mounting assembly 50 is shown positioning sections 48 and 49 in a near-closed position. In some examples, this positioning is maintained for an extended period before the engine core 21 is reinstalled into the aircraft 100. Mounting assembly 50 supports sections 48 and 49 and maintains their positioning. In some examples, mounting assembly 50 supports sections 48 and 49 and prevents and / or reduces movement, such as when the aircraft is towed. This support prevents damage to the thrust reverser 40.

[0070] like Figure 9 and Figure 10 As shown, the mounting assembly 50 is positioned in front of the front end 41 of sections 48, 49 of the thrust reverser 40. This positioning facilitates the attachment of the mounting assembly 50 and the transition between the open and near-closed positions. In some examples, when mounted on aircraft 100, the components of the mounting assembly 50 are aligned in a common plane that is vertically aligned. This common vertical plane is positioned in front of the front end 41 of sections 48, 49.

[0071] Figure 11A method for supporting a thrust reverser 40 on a wing 103 of an aircraft 100 is illustrated. The method includes connecting a support assembly 51 to the wing 103 (box 300). A first arm 52 extending from the support assembly 51 is connected to a first segment 48 of the thrust reverser 40 (box 302). A second arm 52 extending from the support assembly 51 is connected to a second segment of the thrust reverser (box 304). The first and second arms 52 are positioned at a first angular position relative to the support assembly 51 to support the first segment 48 and the second segment 49 of the thrust reverser 40 in a first position (box 306). The first and second arms 52 are positioned at a second angular position relative to the support assembly 51 to support the first segment 48 and the second segment 49 in the second position (box 308). The first and second positions can be at various angular positions.

[0072] While the aircraft 100 is on the ground, mounting assembly 50 is attached to engine mount 105 on wing 103. Mounting assembly 50 is then attached to thrust reverser 40. Mounting assembly 50 is manipulated to position sections 48, 49 of thrust reverser 40 at various angular positions required for maintenance. Mounting assembly 50 is removed before core engine 21 is installed.

[0073] Regarding quantities or measurements, the term "approximately" means that the characteristic, parameter, or value does not need to be precisely achieved. Instead, deviations or variations, including, for example, tolerances, measurement errors, measurement accuracy limitations, and other factors known to those skilled in the art, may occur in quantities that do not preclude the effects the characteristic is intended to provide.

[0074] Of course, the invention may be practiced in ways other than those specifically set forth herein without departing from its essential characteristics. This embodiment should be considered illustrative rather than restrictive in all respects, and all variations within the meaning and equivalence of the appended claims are intended to be included therein.

Claims

1. A mounting assembly for supporting a thrust reverser mounted to an engine mount of an aircraft, the mounting assembly comprising: A support assembly (51) configured to be connected to the engine mount of the aircraft, the support assembly (51) including a first lateral side and a second lateral side; The first arm (52) is connected to the first lateral side of the support assembly (51) and is configured to be connected to the first section of the thrust reverser; The second arm (52), which is connected to the second lateral side of the support assembly (51) and configured to connect to the second section of the thrust reverser; and The first arm (52) and the second arm (52) are pivotally connected to the support assembly (51) to support the first and second sections of the thrust reverser at different angular positions.

2. The mounting assembly according to claim 1, wherein the support assembly (51) includes a first base assembly (54a) and a second base assembly (54b) mounted adjacent to each other, and the inner sides of the first base assembly (54a) and the second base assembly (54b) are adjacent to each other, and the first arm (52) is connected to the first base assembly (54a) and the second arm (52) is connected to the second base assembly (54b).

3. The mounting assembly according to claim 2, wherein the first base assembly (54a) and the second base assembly (54b) are aligned in a common plane.

4. The mounting assembly according to claim 2, wherein the first base assembly (54a) and the first arm (52) are mirror images of the second base assembly (54b) and the second arm (52).

5. The mounting assembly of claim 1, wherein the mounting assembly is configured to support the first and second sections of the thrust reverser within an angular range of 6° to 47°.

6. The mounting assembly according to claim 1, wherein the support assembly (51), the first arm (52) and the second arm (52) are aligned in a common plane.

7. The mounting assembly of claim 1, wherein the first arm (52) pivots about a first pivot axis and the second arm (52) pivots about a second pivot axis, wherein the first pivot axis and the second pivot axis are spaced apart and parallel.

8. A mounting assembly for supporting a thrust reverser mounted to an engine mount of an aircraft, the mounting assembly comprising: A beam assembly (53) is configured to be connected to the engine mount; A first base assembly (54a) and a second base assembly (54b), both of which are connected to the beam assembly (53), are aligned in a common plane. A first arm (52), which is pivotally connected to the first base assembly (54a) and includes a first mounting (58) configured to connect to a first section of the thrust reverser; The second arm (52), which is pivotally connected to the second base assembly (54b) and includes a second mounting (58) configured to connect to a second section of the thrust reverser; and The first arm (52) and the second arm (52) pivot between a first position and a second position to selectively position the first section and the second section of the thrust reverser at different angular positions.

9. The mounting assembly of claim 8, wherein each of the first base assembly (54a) and the second base assembly (54b) includes adjacent inner edges and outer edges facing outward in opposite lateral directions, wherein a first arm (52) is connected to the outer edge of the first base assembly (54a) and a second arm (52) is connected to the outer edge of the second base assembly (54b).

10. The mounting assembly of claim 9, wherein the beam assembly (53) comprises: Liang; and A U-shaped connector extends outward from the beam and is configured to connect to the first base assembly (54a) and the second base assembly (54b).

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