Self-retaining shear pin for blind mount location
View Patent ↗A shear pin connection for use in a difficult to access location has a bolt head to be positioned at an inner end of a bearing. A bushing is received between the bolt and an inner periphery of the bearing. A lock member is positioned between an inner end of the bushing and the bolt head. The lock member is radially expandable, and has a free radially outer dimension that is smaller than an inner dimension of the inner bore. The lock member is expandable to have an expanded radially outer dimension that is greater than the inner dimension of the inner bore. A nut is tightened on the outer end of the bolt. The nut causes the bushing to move relative to the bolt, and causes the lock member to expand radially. A shackle connection for a gas turbine engine and an aircraft are also disclosed.
1. A connection for connecting an aircraft to a gas turbine engine comprising:
a gas turbine engine having an outer casing;
a plurality of shackles each mounted to said outer casing through spherical bearings, and at least one shear pin connection for connecting said outer casing to one of said shackles, said shear pin connection including a bolt having a bolt head to be positioned at an inner end of a bearing, said bolt extending outwardly through an inner bore in the bearing to an outer end, a bushing received radially outwardly of said bolt, and between said bolt and an inner periphery of the bearing, a lock member being positioned between an inner end of said bushing and said bolt head, and said lock member being radially expandable, and having a free radially outer dimension that is smaller than an inner dimension of the inner bore, and said lock member being expandable to have an expanded radially outer dimension which is greater than the inner dimension of the inner bore, and a nut to be tightened on said outer end of said bolt, said nut causing said bushing to move relative to said bolt, and cause said lock member to expand radially.
2. The connection as set forth in claim 1 , wherein said bolt has a ramped surface for causing said lock member to be ramped radially outwardly as said nut is tightened on said bolt, and said bushing and said bolt move relative to each other.
3. The connection as set forth in claim 2 , wherein said bushing has an inner ramped surface which is received in contact with said ramped outer surface of said bolt as said nut is fully tightened on said bolt.
4. The connection as set forth in claim 3 , wherein said lock member is an expandable coil spring.
5. The connection as set forth in claim 4 , wherein said expandable coil spring is received on a cylindrical surface on said bolt axially intermediate said inner end of said bushing and said bolt head.
6. The connection as set forth in claim 1 , wherein said inner end of said bolt will be less accessible than said outer end.
7. An aircraft comprising:
an aircraft body, and a plurality of shackles attached to said aircraft body, said plurality of shackles mounted to a gas turbine engine outer casing through spherical bearings, with shear pins connecting said gas turbine engine casing to said shackles, and at least one said shear connection including a bolt having a bolt head to be positioned at an inner end of a bearing, said bolt extending outwardly through an inner bore in the bearing to an outer end, a bushing received radially outwardly of said bolt, and between said bolt and an inner periphery of the bearing, a lock member being positioned between an inner end of said bushing and said bolt head, and said lock member being radially expandable, and having a free radially outer dimension that is smaller than an inner dimension of the inner bore, and said lock member being expandable to have an expanded radially outer dimension which is greater than the inner dimension of the inner bore, and a nut to be tightened on said outer end of said bolt, said nut causing said bushing to move relative to said bolt, and cause said lock member to expand radially.
8. The aircraft as set forth in claim 7 , wherein said bolt has a ramped surface for causing said lock member to be ramped radially outwardly as said nut is tightened on said bolt, and said bushing and said bolt move relative to each other.
9. The aircraft as set forth in claim 8 , wherein said bushing has an inner ramped surface which is received in contact with said ramped outer surface of said bolt as said nut is fully tightened on said bolt.
10. The aircraft as set forth in claim 9 , wherein said lock member is an expandable coil spring.
11. The aircraft as set forth in claim 10 , wherein said expandable coil spring is received on a cylindrical surface on said bolt axially intermediate said inner end of said bushing and said bolt head.
12. The aircraft as set forth in claim 7 , wherein said shackles are attached to a wing on said aircraft.
13. The aircraft as set forth in claim 7 , wherein said inner end of said bolt will be less accessible than said outer end.