Mounting assembly for connecting aircraft components together

Abstract

An assembly is provided for an aircraft. This aircraft assembly includes a first mount, a second mount, a mounting assembly and a fluid reservoir structure. The mounting assembly connects the first mount to the second mount along an axis while providing controlled intercomponent movement between the first mount and the second mount to reduce internal stress and/or wear. The mounting assembly includes an outer bushing, an inner bushing and a fastener. The fluid reservoir structure includes one of the first mount or the second mount.

What is claimed is: 
     
         1 . An assembly for an aircraft, comprising:
 a first mount comprising a first mount aperture;   a second mount comprising a second mount aperture; and   a mounting assembly connecting the first mount to the second mount along an axis while providing controlled intercomponent movement between the first mount and the second mount to reduce internal stress and/or wear, the mounting assembly including an outer bushing, an inner bushing and a fastener;   the outer bushing comprising an outer bushing bore, the outer bushing projecting partially axially into the first mount aperture, and the outer bushing radially next to the first mount;   the inner bushing including an inner bushing bore, an inner bushing base and an inner bushing rim that projects radially out from the inner bushing base, the inner bushing base projecting axially through the outer bushing bore to axially engage the second mount, the inner bushing base radially between and next to the fastener and the outer bushing, and the inner bushing rim axially next to the first mount with the first mount axially between the inner bushing rim and the second mount;   the fastener projecting axially through the second mount aperture and the inner bushing bore; and   a fluid reservoir structure, the fluid reservoir structure comprising one of the first mount or the second mount.   
     
     
         2 . The assembly of  claim 1 , wherein the second mount is axially between and contacts the inner bushing base and a head of the fastener. 
     
     
         3 . The assembly of  claim 1 , wherein the second mount is clamped axially between the inner bushing base and a head of the fastener. 
     
     
         4 . The assembly of  claim 1 , wherein
 the outer bushing further comprises an outer bushing base and an outer bushing rim that projects radially out from the outer bushing base;   the outer bushing base projects partially axially into the first mount aperture towards the inner bushing rim; and   the outer bushing rim is axially next to the first mount and the second mount.   
     
     
         5 . The assembly of  claim 4 , wherein the outer bushing rim contacts the first mount and is axially spaced from the second mount. 
     
     
         6 . The assembly of  claim 4 , wherein the outer bushing base is fixed to the first mount through a radial interference fit. 
     
     
         7 . The assembly of  claim 6 , wherein a loose fit interface is formed radially between the inner bushing base and the outer bushing base. 
     
     
         8 . The assembly of  claim 1 , wherein the fastener includes
 a head; and   a shank projecting axially out from the head and sequentially through the second mount aperture and the inner bushing bore.   
     
     
         9 . The assembly of  claim 8 , wherein the shank is radially next to the second mount. 
     
     
         10 . The assembly of  claim 8 , wherein
 the shank includes a threaded section and a shoulder section projecting axially through the second mount aperture and the inner bushing bore from the head to the threaded section; and   the mounting assembly further includes a nut threaded onto the threaded section with the inner bushing clamped axially between the nut and the first mount.   
     
     
         11 . The assembly of  claim 10 , wherein the mounting assembly further includes a washer clamped axially between the nut and the inner bushing. 
     
     
         12 . The assembly of  claim 11 , wherein the washer is axially spaced from an axial end of the shoulder section by an air gap. 
     
     
         13 . The assembly of  claim 11 , wherein the washer has a uniform axial thickness extending radially from an inner side of the washer to an outer side of the washer. 
     
     
         14 . The assembly of  claim 1 , further comprising a housing structure for an aircraft engine, the housing structure comprising the other one of the first mount or the second mount. 
     
     
         15 . An aircraft assembly for providing controlled intercomponent movement to reduce internal stress and/or wear, comprising:
 a first mount comprising a first mount aperture that extends axially along an axis through the first mount;   a second mount comprising a second mount aperture that extends axially along the axis through the second mount;   an outer bushing comprising an outer bushing bore, the outer bushing pressed into the first mount aperture;   an inner bushing including an inner bushing bore, an inner bushing base and an inner bushing rim that projects radially out from the inner bushing base, the inner bushing base projecting axially along the axis through the outer bushing bore, and the inner bushing rim axially next to the first mount with the first mount axially between the inner bushing rim and the second mount;   a fastener including a head and a shank projecting axially along the axis out from the head and sequentially through the second mount aperture and the inner bushing bore to a distal end of the fastener;   a washer mounted on the shank; and   a nut threaded onto the shank to clamp the washer, the inner bushing and the second mount in a stack between the nut and the head.   
     
     
         16 . The aircraft assembly of  claim 15 , wherein
 the inner bushing extends axially along the axis from an inner bushing first end to an inner bushing second end;   the inner bushing rim is located at the inner bushing first end; and   an axial distance from the inner bushing rim to the inner bushing second end is larger than an axial thickness of the outer bushing.   
     
     
         17 . The aircraft assembly of  claim 15 , wherein
 the shank includes a threaded section and a shoulder section connected axially between the threaded section and the head;   the second mount and the inner bushing are mounted on the shoulder section;   the nut is threaded onto the threaded section; and   an axial length of the shoulder section is smaller than a sum of an axial thickness of the second mount and an axial thickness of the inner bushing.   
     
     
         18 . The aircraft assembly of  claim 15 , further comprising a fluid reservoir structure comprising the first mount. 
     
     
         19 . The aircraft assembly of  claim 18 , further comprising a housing structure for an aircraft engine, the housing structure comprising the second mount. 
     
     
         20 . An aircraft assembly for providing controlled intercomponent movement to reduce internal stress and/or wear, comprising:
 a shoulder bolt including a head, a threaded section and a shoulder section extending axially along an axis from the head to the threaded section;   an inner bushing including an inner bushing base and an inner bushing rim that projects radially out from the inner bushing base, the inner bushing base mounted on the shoulder section, the inner bushing base extending axially along the axis from an inner bushing first end to an inner bushing second end, the inner bushing second end located closer axially to the head than the inner bushing first end, and the inner bushing rim disposed at the inner bushing first end;   an outer bushing including an outer bushing base and an outer bushing rim that projects radially out from the outer bushing base, the outer bushing base mounted on the inner bushing base, the outer bushing base extending axially along the axis from an outer bushing first end to an outer bushing second end, the outer bushing first end located closer axially to the inner bushing rim than the outer bushing second end, the outer bushing second end axially recessed along the inner bushing base from the inner bushing second end, and the outer bushing rim disposed at the outer bushing second end;   a nut threaded on the threaded section; and   a washer mounted on the shoulder bolt, the washer axially between and contacting the nut and the inner bushing.