Thrust reverser mounting assembly
A mounting assembly for thrust reversers on aircraft engines stabilizes sections to prevent damage and maintain seal integrity during maintenance and towing, addressing the vulnerability of thrust reversers in open positions.
Patent Information
- Application Number
- JP2025093938
- Authority / Receiving Office
- JP · JP
- Patent Type
- Applications
- Current Assignee / Owner
- Priority Date
- 2024-06-12
- Filing Date
- 2025-06-05
- Publication Date
- 2026-01-14
AI Technical Summary
Thrust reversers on aircraft engines are prone to damage during maintenance operations when in an open position, and towing the aircraft without an engine core can cause further damage due to excessive forces, potentially compromising the integrity of seals that contain engine fires.
A mounting assembly that supports thrust reversers by connecting to the aircraft engine mount, allowing sections of the thrust reverser to pivot between angular positions, providing stable support and preventing damage during engine core removal and towing.
The mounting assembly stabilizes thrust reverser sections, preventing damage and maintaining seal integrity, ensuring safe handling and protection against fire spread during maintenance and towing operations.
Smart Images
Figure 2026004230000001_ABST
Abstract
Description
[Technical Field]
[0001]
[0001] The present disclosure relates generally to the field of aircraft, and more particularly to a mounting assembly that supports a thrust reverser of an engine. [Background technology]
[0002]
[0002] Many aircraft engines are equipped with thrust reversers. The thrust reversers are configured to be in a stowed position to allow the engine's thrust to propel the aircraft forward. The thrust reversers are also configured to be in a deployed position to divert thrust that acts against the forward movement of the aircraft. Thrust reversers are typically used to slow the aircraft during landing. The thrust reversers use the engine's thrust to slow the aircraft, thus helping to reduce brake wear and enabling a shorter landing distance for the aircraft.
[0003]
[0003] A thrust reverser is attached to an aircraft and extends around part or all of the engine core of the engine. During certain times, such as during maintenance operations, the thrust reverser is positioned to allow access to the engine core. In one embodiment, 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 may be damaged when in the open position.
[0004]
[0004] The thrust reverser includes one or more seals. In one example, the seals are located at the joints where various sections of the thrust reverser connect to the wing. The seals can be damaged when the thrust reverser is in a closed position and the weight of the thrust reverser compresses the seal against the wing. In one example, the seals are fire seals. In the event of a fire in the engine core, the fire seals contain the fire within the area directly below. In some examples, the seals are configured to prevent oxygen from reaching the area of the fire, thus preventing the fire from spreading. If these seals are damaged, they may not be able to properly contain or suppress the fire.
[0005]
[0005] With the engine core removed and the thrust reversers still attached to the wings, the aircraft may need to be towed to various locations. For example, the aircraft may need to be towed to a maintenance area away from an active runway. Towing the aircraft in this condition may cause the thrust reversers to bounce or otherwise move, subjecting the thrust reversers to excessive forces. These forces may damage the thrust reversers and / or seals when the sections are not properly supported in the open position. Summary of the Invention
[0006] One aspect is directed to a mounting assembly for supporting a thrust reverser mounted to an aircraft engine mount. The mounting assembly includes a support assembly configured to connect to the aircraft engine mount, the support assembly including a first side and a second side. A first arm is connected to the first side of the support assembly and configured to connect to a first section of the thrust reverser. A second arm is connected to the second side of the support assembly and configured to connect to a second section of the thrust reverser. The first arm and the second arm are pivotally connected to the support assembly to support the first and second sections of the thrust reverser at different angular positions.
[0007] In another aspect, a support assembly includes a first base assembly and a second base assembly mounted adjacent to one another, with their interior surfaces abutting, and a first arm connected to the first base assembly and a second arm 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 mirror images of the second base assembly and the second arm.
[0010] In another aspect, a mounting assembly is configured to support the first and second sections of the thrust reverser within an angular range of 6 degrees to 47 degrees.
[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 is directed 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 with the first base assembly and the second base assembly aligned in a common plane. A first arm is pivotally connected to the first base assembly and includes a first mount configured to connect to a first section of the thrust reverser. A second arm is pivotally connected to the second base assembly and includes a second mount configured to connect to a second section of the thrust reverser. The first arm and the second arm 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.
[0014] In another aspect, the first base assembly and the second base assembly each include abutting inner edges and opposite laterally outwardly facing outer edges, wherein the first arm is connected to the outer edge of the first base assembly and the second arm is connected to the outer edge of the second base assembly.
[0015]
[0015] In another aspect, a beam assembly includes a beam and a clevis joint extending outward from the beam and configured to connect to a first base assembly and a 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]
[0017] In another aspect, the first arm and the second arm are configured to rotate within a range of 6 degrees to 47 degrees about their respective rotation axes.
[0018]
[0018] In another aspect, a first block is positioned between the first base assembly and the first arm to support the first arm at a first position, and a second block is positioned between the second base assembly and the second arm to support the second arm at the first position.
[0019] One aspect is directed to a method of supporting a thrust reverser on an engine mount of an aircraft, the method including connecting a support assembly to the engine mount, connecting a first arm extending from the support assembly to a first section of the thrust reverser, connecting a second arm extending from the support assembly to a second section of the thrust reverser, positioning the first and second arms at a first angular position relative to the support assembly to support the first and second sections of the thrust reverser at a first location, and positioning the first and second arms at a second angular position relative to the support assembly to support the first and second sections of the thrust reverser at a second location.
[0020]
[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 section and the second section of the thrust reverser about a thrust reverser axis coincident with the pivot axis.
[0021]
[0021] In another aspect, the method further includes connecting a first arm to a first power door opening system (PDOS) bracket on the first section, and connecting a second arm to a second PDOS bracket on the second section.
[0022] In another aspect, the method further includes positioning the first arm and the second arm forward of a leading edge of the thrust reverser.
[0023] In another aspect, the method further includes moving the first section and the second section of the thrust reverser through an angular range of 6 degrees to 47 degrees.
[0024]
[0024] In another aspect, supporting the first section and the second section in the first position includes placing the first section and the second section in a fully open position.
[0025] In another aspect, supporting the first section and the second section in the second position includes supporting the first section and the second section in a substantially closed position.
[0026]
[0026] The above-described features, functions, and advantages can be realized alone in various aspects or can be combined in further multiple aspects, details of which can be confirmed by referring to the following description and accompanying drawings. [Brief explanation of the drawings]
[0027] [Figure 1]
[0027] FIG. 1 is an isometric view of an aircraft. [Figure 2]
[0028] FIG. 10 is a schematic top view of the thrust reverser in a first position to allow air to pass through the fan duct and out the aft end. [Figure 3]
[0029] FIG. 3 is a schematic top view of the thrust reverser of FIG. 2 in a deployed position for directing air out of the fan duct and through an opening. [Figure 4]
[0030] FIG. 1 is a schematic diagram of a thrust reverser including a first section and a second section. [Figure 5A]
[0031] FIG. 2 is a schematic diagram of a thrust reverser in an open position. [Figure 5B]
[0032] FIG. 5B is a schematic diagram of the thrust reverser of FIG. 5A in a substantially closed position. [Figure 6]
[0033] FIG. 1 is an isometric view of a mounting assembly connected to the first and second sections of the thrust reverser. [Figure 7A]
[0034] FIG. 1 is a schematic diagram of a mounting assembly in a first angular orientation. [Figure 7B]
[0035] FIG. 7B is a schematic diagram of the mounting assembly of FIG. 7A in a second angular orientation. [Figure 8]
[0036] FIG. 2 is a schematic diagram of a thrust reverser in a substantially closed position. [Figure 9]
[0037] FIG. 1 is an isometric view of a mounting assembly supporting the thrust reverser in an open position. [Figure 10]
[0038] FIG. 1 is an isometric view of a mounting assembly supporting a thrust reverser in a substantially closed position. [Figure 11]
[0039] 1 is a flowchart of a method for supporting a thrust reverser on an aircraft wing in the absence of an engine core. DETAILED DESCRIPTION OF THE INVENTION
[0028]
[0040] 1 shows an aircraft 100 configured to transport passengers and / or cargo. The aircraft 100 generally includes a fuselage 101 having an interior space configured to accommodate passengers and / or cargo. The interior space of the fuselage 101 also includes a cockpit 102 having various controls that enable flight personnel to control the aircraft 100. Engines 104 are mounted on wings 103 on either side of the fuselage 101.
[0029]
[0041] FIG. 2 illustrates the engine 104 in a schematic manner, with certain features that may be obscured from view indicated by dashed lines. The engine 104 generally includes an engine core 21 and a nacelle 30. The engine core 21 may include a variety of different configurations, including, but not limited to, a gas turbine engine. In some embodiments, the engine core 21 includes a fan 22 that draws 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 inlet 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 having a sleeve that translates along a longitudinal axis L relative to the engine core 21.
[0030]
[0042] The thrust reverser 40 is configured to move between a first position and a deployed position. The first position allows air to travel through the fan duct 23 and exit through the nozzle outlet 24. The deployed position diverts air traveling through the fan duct 23. FIG. 2 shows the thrust reverser 40 in the first position, such as during flight. A first portion, illustrated by arrow A, of air drawn into the engine 104 is directed toward the engine core 21, and a second portion, illustrated by arrow B, is directed toward the fan duct 23. In the retracted position, as shown in FIG. 2, the thrust reverser 40 is positioned forward to contact the forward section 31. A blocker door 33 is positioned to allow airflow through the length of the fan duct 23 and exit through the nozzle outlet 24 at the aft end. One or more pull rods 34 are connected to the blocker door 33. The pull rods 34 extend across the fan duct 23 and are in a first orientation that places the blocker door 33 in an open position.
[0031]
[0043] 3 shows the thrust reverser 40 in a deployed position. The thrust reverser 40 is translated aft to create an opening 35 between the fixed forward section 31 and the thrust reverser 40. The pull rod 34 is actuated in a second direction to position the blocker door 33 across the fan duct 23. This position forces air entering the fan duct 23 through the opening 35. The air flows through cascade members 36, such as in the form of cascade vanes, and exits as a counterflow airflow.
[0032]
[0044] The thrust reverser 40 is substantially cylindrical in shape and has a hollow interior sized to receive the engine core 21. As shown in FIG. 4 , the thrust reverser 40 includes a length X measured between a forward end 41 and an aft end 42. In some embodiments, the thrust reverser 40 extends completely around the engine core 21. In other embodiments, the thrust reverser 40 extends partially around the engine core 21. The thrust reverser 40 is divided along the length X into sections, including a first section 48 and a second section 49. Each section 48, 49 includes a semi-cylindrical shape having edges 45, 46. The edges 45, 46 extend along the length X. In some embodiments, the sections 48, 49 include the same shape and size. In other embodiments, the sections 48, 49 include different shapes and / or sizes.
[0033]
[0045] As shown in Figures 5A and 5B, a mounting assembly 50 connects the thrust reverser 40 to an engine mount 105 in a wing 103. The mounting assembly 50 provides support when the engine core 21 is removed from the interior space 44 of the thrust reverser 40. The mounting assembly 50 generally includes a support assembly 51 that connects to the engine mount 105 in the wing 103. An arm 52 extends from the support assembly 51 and is configured to connect to the first section 48 and the second section 49, respectively. The arm 52 allows 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.
[0034]
[0046] FIG. 5A shows sections 48, 49 in a first position. In some embodiments, the first position is a fully open position. This fully open position is the range of pivot travel of sections 48, 49. In other embodiments, the first position is not a fully open position. Sections 48, 49 are disposed at an angle α measured from thrust reverser pivot axes A, B and latch beam edge 46 to a center plane Y between first section 48 and second section 49 of thrust reverser 40. Sections 48, 49 are pivoted outward about their respective pivot axes A, B near hinge beam edge 45, with the opposite latch beam edge 46 spaced a greater distance apart. The range of pivot can vary. In some embodiments, angle α is in the range of 40 degrees to 50 degrees. In one specific example, angle α is 47 degrees.
[0035]
[0047] 5B shows the thrust reverser 40 in a second position. In some embodiments, the second position is a substantially closed position, in which the first section 48 and the second section 49 are pivoted so that the latch beam edges 46 are close together but still spaced apart. The mounting assembly 50 is configured to prevent the latch beam edges 46 from touching. The angle α can vary, with one particular embodiment including an angle of 6 degrees.
[0036]
[0048] The mounting assembly 50 allows movement of the different sections 48, 49 and supports the sections 48, 49 at different angular positions. In some embodiments, such as shown in FIGS. 5A and 5B, the sections 48, 49 are moved an equal distance and positioned at a corresponding angle. In other embodiments, the sections 48, 49 are moved by different amounts so that the two angles are different. In some embodiments, such as shown in FIGS. 5A and 5B, the sections 48, 49 are positioned symmetrically about the central plane Y. In other embodiments, the thrust reverser 40 is aligned at different rotational angles about the central plane Y. In some embodiments, the mounting assembly 50 allows pivotal movement of the first section 48 and the second section 49 through an angular range of 6 to 47 degrees.
[0037]
[0049] Overall, the mounting assembly 50 allows the sections 48, 49 to pivot through a range of motion between a first position and a second position. The mounting assembly 50 supports the sections at various angular positions. In some embodiments, the range of motion for each section is 40 degrees. One specific range of motion for each of the sections 48, 49 is an angle α of 47 degrees in the first position and an angle α of 6 degrees in the second position.
[0038]
[0050] The mounting assembly 50 allows movement and supports the sections 48, 49 when the engine core 21 is removed from the interior space 44. In some embodiments, the mounting assembly 50 supports the sections 48, 49 to prevent damage to the seals 43 disposed against one or more of the edges 45 and the pylon structure. The pylon structure includes the engine mounts 105 and is disposed forward of the thrust reverser 40. In one embodiment, the seals 43 are fire seals disposed between the edges 45 of the sections 48, 49.
[0039]
[0051] FIG. 6 illustrates a mounting assembly 50 including a support assembly 51 and an arm 52. The support assembly 51 includes a beam assembly 53 configured to connect to an engine mount 105. In some embodiments, the beam assembly 53 includes a beam and one or more clevis joints. The beam is configured to connect to the engine mount 105 and to position the clevis joints below and outward from the wing. The support assembly 51 also includes a base assembly 54. The base assembly 54 is connected to the clevis joints of the beam assembly 53. In some embodiments, the base assembly 54 includes multiple plates connected together in an overlapping arrangement and secured together using fasteners.
[0040]
[0052] The base assembly 54 can be formed in a single section or in multiple sections. In the embodiment of FIG. 6, the base assembly 54 includes a first base assembly 54a and a second base assembly 54b. The assemblies 54a, 54b are positioned adjacent to one another and individually connected to the beam assembly 53. The assemblies 54a, 54b include abutting inner edges. In one embodiment, the inner edges are aligned along the vertical centerline of the thrust reverser 40. The contact between the different assemblies 54a, 54b along the inner edges provides additional strength. In some embodiments, the individual assemblies 54a, 54b are mirror images of one another.
[0041]
[0053] The arms 52 are connected to the base assembly 54. The arms 52 include an elongated shape, with a first end connecting to the base assembly 54 and a second end connecting to the thrust reverser 40. In some embodiments, the arms 52 include a single piece. In other embodiments, such as shown in FIG. 6, the arms 52 are formed by two or more separate pieces connected together. In the embodiment of FIG. 6, the arms 52 include a support assembly 55 and an arm 56. Each support assembly 55 is connected to the outer edge of the base assembly 54 using fasteners. The fasteners secure the support assembly 55 to the base assembly 54 and also provide for positioning the support assembly 55 at different angular positions relative to the base assembly 54. Each support assembly 55 also includes a receptacle 57 on an opposing end sized to receive the arm 56.
[0042]
[0054] Each arm 56 includes an elongated shape, with a first section configured to be inserted into a receptacle 57. A fastener extends through the arm 56 within the receptacle 57, connecting the arms 56. A mount 58 is disposed at the second end and configured to engage the thrust reverser 40. In some embodiments, the mount 58 is configured to connect to a power door opening system (PDOS) bracket 110 on the thrust reverser 40. The PDOS bracket 110 is disposed along the forward end 41 of the thrust reverser 40 and spaced from the inner edge 45.
[0043]
[0055] In some embodiments, the mounting assembly 50 is divided into two sections about the central axis Y of the thrust reverser 40. Each of the sections has the same shape and size and is arranged in an inverted configuration (i.e., mirror image about the central axis Y). This configuration may be easier to manufacture and use because the mounting assembly 50 has fewer overall parts.
[0044]
[0056] The mounting assembly 50 allows the sections 48, 49 of the thrust reverser 40 to be positioned at different angular positions. The angular positions are achieved between the base assembly 54 and the support assembly 55. FIG. 7A shows the arm 52 attached to the support assembly 51 in a first position. The arm 52 is attached to the support assembly 51 at a pivot 95. In some embodiments, a fastener 90 extends through each of the support assembly 51 and the arm 52 at the pivot 95. In some embodiments, the pivots 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. FIG. 7B shows the mounting assembly 50 in a second position. The arm 52 is pivoted inward relative to the support assembly 51 to close the thrust reverser sections. The arm 52 is connected using multiple fasteners 90 spaced along the joint.
[0045]
[0057] In some embodiments, such as shown in FIG. 8, sections 48, 49 of thrust reverser 40 pivot about one or more axes. In other embodiments, sections 48, 49 pivot about separate axes. Additionally, mounting assembly 50 allows arm 52 to pivot relative to support assembly 51 about an axis at pivot point 95 to move between different angular positions. In some embodiments with multiple pivot axes, the axes coincide to allow pivotal movement of sections 48, 49 without constraining or otherwise preventing pivotal movement between different angular positions.
[0046]
[0058] 9 shows a mounting assembly 50 that positions sections 48, 49 of thrust reverser 40 in an open position. Mounting assembly 50 is attached to an engine mount. In some embodiments, the open position allows an engine core removal / installation device (not shown) to remove and / or install the engine core from and / or onto the pylon. Arms 52 pivot outward and support sections 48, 49 to maintain the pivoted open position to provide access to interior space 44.
[0047]
[0059] 10 shows the mounting assembly 50 positioning the sections 48, 49 in a generally closed position. In some embodiments, this positioning is maintained for an extended period of time before the engine core 21 is reinstalled on the aircraft 100. The mounting assembly 50 supports the sections 48, 49 and maintains their positioning. In some embodiments, the mounting assembly 50 supports the sections 48, 49 and prevents and / or reduces movement, such as when the aircraft is being towed. This support protects the thrust reverser 40 from damage.
[0048]
[0060] 9 and 10 , the mounting assembly 50 is positioned forward of the forward ends 41 of the sections 48, 49 of the thrust reverser 40. This positioning facilitates installation of the mounting assembly 50 and transition between the open and substantially closed positions. In some embodiments, the components of the mounting assembly 50 are aligned in a common plane that is vertically aligned when installed on the aircraft 100. The common vertical plane is positioned forward of the forward ends 41 of the sections 48, 49.
[0049]
[0061] 11 illustrates a method of supporting a thrust reverser 40 on a wing 103 of an aircraft 100. The method includes connecting a support assembly 51 to the wing 103 (block 300). A first arm 52 extending from the support assembly 51 is connected to a first section 48 of the thrust reverser 40 (block 302). A second arm 52 extending from the support assembly 51 is connected to a second section of the thrust reverser (block 304). The first arm 52 and the second arm 52 are positioned at a first angular position relative to the support assembly 51 to support the first section 48 and the second section 49 of the thrust reverser 40 in a first position (block 306). The first arm 52 and the second arm 52 are positioned at a second angular position relative to the support assembly 51 to support the first section 48 and the second section 49 in a second position (block 308). The first and second positions can be at various angular positions.
[0050]
[0062] The mounting assembly 50 is attached to engine mounts 105 on the wing 103 while the aircraft 100 is on the ground. The mounting assembly 50 is then attached to the thrust reverser 40. The mounting assembly 50 is manipulated to position the sections 48, 49 of the thrust reverser 40 in various angular positions as needed to perform maintenance. The mounting assembly 50 is removed prior to installation of the core engine 21.
[0051]
[0063] The term "substantially" in connection with a quantity or measurement means that the recited characteristic, parameter, or value need not be achieved exactly. Rather, deviations or variations (including, for example, tolerances, measurement errors, measurement accuracy limits, and other factors known to those skilled in the art) may occur to the extent that they do not eliminate the effect intended to be produced by the feature.
[0052]
[0064] The present invention may, of course, be practiced otherwise than as specifically set forth herein without departing from the essential characteristics thereof. The present embodiments are to be considered in all respects as illustrative and not restrictive, and all changes which come within the meaning and range of equivalency of the claims are intended to be embraced within their scope.
Claims
1. 1. A mounting assembly for supporting a thrust reverser mounted to an engine mount of an aircraft, comprising: a support assembly (51) configured to connect to the engine mount of the aircraft, the support assembly (51) including a first side and a second side; a first arm (52) connected to the first side of the support assembly (51) and configured to connect to a first section of the thrust reverser; and a second arm (52) connected to the second side of the support assembly (51) and configured to be connected to a second section of the thrust reverser; a mounting assembly, wherein the first arm (52) and the second arm (52) are pivotally connected to the support assembly (51) for supporting the first section and the second section of the thrust reverser at different angular positions.
2. 2. The mounting assembly of claim 1, wherein the support assembly (51) comprises a first base assembly (54a) and a second base assembly (54b) mounted adjacent to each other, the inner sides of the first base assembly (54a) and the second base assembly (54b) abutting against 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 of claim 2 , wherein the first base assembly (54 a) and the second base assembly (54 b) are aligned in a common plane.
4. The mounting assembly of 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. 10. The mounting assembly of claim 1, wherein the mounting assembly is configured to support the first section and the second section of the thrust reverser within an angular range of 6 degrees to 47 degrees.
6. The mounting assembly of claim 1, wherein the support assembly (51), the first arm (52), and the second arm (52) are aligned in a common plane.
7. 2. 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, the first pivot axis and the second pivot axis being spaced apart and parallel.
8. 1. A mounting assembly for supporting a thrust reverser mounted to an engine mount of an aircraft, comprising: a beam assembly (53) configured to connect to the engine mount; a first base assembly (54a) and a second base assembly (54b), each connected to the beam assembly (53), the first base assembly (54a) and the second base assembly (54b) aligned in a common plane; a first arm (52) pivotally connected to the first base assembly (54a) and including a first mount (58) configured to be connected to a first section of the thrust reverser; and a second arm (52) pivotally connected to the second base assembly (54b) and including a second mount (58) configured to be connected to a second section of the thrust reverser; a mounting assembly, wherein 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. 9. The mounting assembly of claim 8, wherein the first base assembly (54a) and the second base assembly (54b) each have abutting inner edges and opposite laterally outwardly facing outer edges, the first arm (52) being connected to the outer edge of the first base assembly (54a) and the second arm (52) being connected to the outer edge of the second base assembly (54b).
10. The beam assembly (53) beam, and The mounting assembly of claim 9, comprising a clevis joint extending outward from the beam and configured to connect to the first base assembly (54a) and the second base assembly (54b).
11. 9. The mounting assembly of claim 8, wherein the beam assembly (53), the first base assembly (54a), the second base assembly (54b), the first arm (52), and the second arm (52) are aligned in a common plane.
12. The mounting assembly of claim 8, wherein the first arm (52) and the second arm (52) are configured to pivot within a range of 6 degrees to 47 degrees about their respective pivot axes.
13. 9. The mounting assembly of claim 8, further comprising: a first block (96) disposed between the first base assembly (54a) and the first arm (52) to support the first arm (52) at the first position; and a second block (96) disposed between the second base assembly (54b) and the second arm (52) to support the second arm (52) at the first position.
14. 1. A method for supporting a thrust reverser on an aircraft engine mount, comprising: connecting a support assembly (51) to said engine mount; connecting a first arm (52) extending from said support assembly (51) to a first section of said thrust reverser; connecting a second arm (52) extending from said support assembly (51) to a second section of said thrust reverser; disposing the first arm (52) and the second arm (52) at a first angular position relative to the support assembly (51) to support the first section and the second section of the thrust reverser at a first position; and and positioning the first arm (52) and the second arm (52) at a second angular position relative to the support assembly (51) to support the first section and the second section of the thrust reverser at a second position.
15. 15. The method of claim 14, further comprising: pivoting the first arm (52) and the second arm (52) about a pivot axis extending through the support assembly (51), and pivoting the first section and the second section of the thrust reverser about a thrust reverser axis coincident with the pivot axis.
16. 15. The method of claim 14, further comprising connecting the first arm (52) to a first power door opening system (PDOS) bracket on the first section, and connecting the second arm (52) to a second PDOS bracket on the second section.
17. The method of claim 14, further comprising positioning the first arm (52) and the second arm (52) forward of a leading edge of the thrust reverser.
18. 15. The method of claim 14, further comprising moving the first section and the second section of the thrust reverser through an angular range of 6 degrees to 47 degrees.
19. 15. The method of claim 14, wherein supporting the first section (48) and the second section (49) in a first position comprises placing the first section (48) and the second section (49) in a fully open position.
20. 15. The method of claim 14, wherein supporting the first section (48) and the second section (49) in a second position comprises supporting the first section (48) and the second section (49) in a substantially closed position.