Aircraft engine rear suspension with thrust recovery

1. A suspension of a turbo engine to an aircraft pylon, including a fitting arranged to be attached to a pylon, a lever fastened in its central portion to the fitting via a linking means with a pivot pin, and two thrust rods each connected by an end to the lever and including at the other end of the fastening means to the engine, wherein said linking means is composed on said central portion of the lever, of two parallel branches apart from one another, to form a biplane, a bore running through said biplane, and on the fitting, of a central fastening tab arranged between both parallel branches, whereas the central fastening tab and both branches are held together by dint of said pivot pin.

2. A suspension according to claim 1 , wherein the lever includes on both sides of its central portion, a fastening tab co-operating with a lateral pivot pin, each with a yoke at the rear end of the rods.

3. A suspension according to claim 2 , wherein the fitting includes on both sides of the central fastening tab, a lateral fastening tab co-operating via a standby connection with the rear end of each rod.

4. A suspension according to claim 3 , wherein the standby connection is formed of a pivot pin installed with a certain clearance in its housing.

5. A suspension according to claim 4 , wherein the lateral pivot pins and the pivot pins of the standby connections are installed on the same yokes at the rear end of the rods.

6. A suspension for a turbo engine, comprising:

a fitting with a tab;

a lever including a central portion with two parallel branches apart from one another so as to form a biplane, said central portion defining a bore running through said biplane, wherein said tab of said fitting is positioned between said two parallel branches;

a pivot pin running through said two parallel branches and said tab so as to mechanically couple said fitting to said lever, and

two rods, each having a first end with a first portion connected to said lever and a second portion connected to said fitting.

7. A suspension according to claim 6 , wherein said tab of said fitting is a central tab positioned between two lateral tabs of said fitting.

8. A suspension according to claim 7 , wherein said central tab and said lateral tabs are drilled perpendicular to a plane of the fitting.

9. A suspension according to claim 7 , wherein said central tab is located on a portion of said fitting that is flat.

10. A suspension according to claim 7 , wherein each of said two rods is configured to be mechanically coupled at a second end to a front of said turbo engine.

11. A suspension according to claim 10 , wherein said lever has a lateral tab on each side of said central portion, each of said rods being connected to one of said lateral tabs of said lever.

12. A suspension according to claim 11 , wherein connections between said rods end said lateral tabs of said lever are active.

13. A suspension according to claim 12 , wherein each of said rods is connected to one of said lateral tabs of said fitting.

14. A suspension according to claim 13 , wherein connections between said rods and said lateral tabs of said fitting are in standby.

15. A suspension according to claim 14 , wherein each of said connections between said rods and said lateral tabs of said fitting include a pin running through an end of each rod and through said one of said lateral tabs of said fittings.

16. A suspension according to claim 15 , wherein said pin is dimensioned so as to leave a clearance between said pin and said one of said lateral tabs of said fittings.