Suspension for suspending a jet engine on an aircraft strut

1. A suspension for suspending a jet engine on an aircraft strut, comprising:

a beam having a platform provided with fasteners for fastening the beam to said aircraft strut and arranged transversely with respect to a longitudinal axis of the jet engine,

first and second lateral links each connected by a first pin to the beam and by a second pin to an engine casing, the second lateral link being prolonged by a finger extending from the first pin of said second lateral link and housed with clearance in a cavity provided in the beam so as to form a standby safety connection and

a central link arranged between the first and second lateral links and connected by a first pin to the beam and by a second pin to said engine casing,

wherein the beam comprises a clevis for housing the first connecting pin of the central link, and said first pin of the central link is distant from the platform so that a space is provided between the platform and the central link, this space forming said cavity in which the finger of the second lateral link is housed with clearance in normal operation such that said finger, in said normal operation, extends between said platform and said first pin of the central link and across a plane passing through said first pin of the central link and perpendicular to the platform, and

wherein said clearance is eliminated when the transmission of the forces by the second pin of the central link is interrupted.

2. A suspension according to claim 1 , wherein the central link is connected by a third pin to the beam so as to form a second standby connection with a clearance.

3. A suspension according to claim 2 , wherein the clearance of the second standby connection is eliminated when the transmission of the forces by the first lateral link or the second lateral link is interrupted.

4. A suspension according to claim 2 , wherein the clearance of the second standby connection is eliminated when the transmission of the forces by the first pin of the central link is interrupted.

5. A suspension according to claim 1 , wherein the clevis supports the first connecting pins of the two lateral links and of the central link together to form a piece of a U-shaped cross section with the platform.

6. A suspension according to claim 1 , wherein the connections of the links with the beam or the casing are swivel-type connections.

7. A suspension according to claim 1 , wherein said clevis has upstream lugs and downstream lugs relative to a gas-flow direction in said jet engine, wherein said upstream and downstream lugs house the first connecting pins of the first and second lateral links and of the central link, and wherein said upstream lugs are in a plane perpendicular to a plane of said platform, and said downstream lugs are in a plane parallel to the plane of the upstream lugs.

8. A suspension according to claim 1 , wherein said finger forms an angle with a portion of said second lateral link extending between the first and second pins of the second lateral link.

9. A suspension according to claim 8 , wherein said clearance, during said normal operation, includes a first clearance between said central link and said finger and a second clearance between said finger and said platform.

10. A suspension according to claim 9 , wherein said finger and said central link are configured such that a relative angular position between said finger and said central link is variable during said normal operation without eliminating said first and second clearances.

11. A suspension according to claim 1 , wherein said first connecting pins of the first and second lateral links and of the central link are arranged on a same plane parallel to a plane of said platform.

12. A suspension according to claim 1 , wherein said central link is connected by a third pin to the beam, and wherein said first connecting pins of the first and second lateral links and of the central link and said third pin are arranged on a same plane parallel to a plane of said platform.