Office Action 1: Notice of Allowance (2025-03-18)

CLAIMS:
CLAIMS
1\. An engine pylon for fastening an engine of an aircraft, the engine pylon having: a structure configured to be fastened beneath a wing of the aircraft and having two lateral faces, wherein the structure has a tunnel with two ends passing therethrough, wherein each of the two ends of the tunnel emerges at one of the two lateral faces, a spreader housed in the tunnel and fastened in an articulated manner to each lateral face by a first connection point, wherein a first end of the spreader has a first bore, and wherein a second end of the spreader has two second bores each configured to form a second connection point with the engine, and a rod fastened in an articulated manner to said first bore and having two third bores each configured to form a third connection point with the engine.
2\. The engine pylon according to claim 1, wherein each first connection point is constituted of a first female clevis fastened to an outside of a corresponding lateral face, a single male clevis being constituted by the spreader, wherein the spreader is disposed inside each first female clevis, a first connection pin and a first ball joint ring being inserted and fastened in a bore of the spreader provided for such insertion, and wherein the first connection pin is housed and fastened in the first ball joint ring and housed free to rotate in bores of the first female clevis provided for such rotatable housing.
3\. The engine pylon according to claim 1, wherein the rod is constituted of two shackles disposed on either side of the first end of the spreader, wherein each of the third bores is constituted of a third sub-bore made in one of the shackles and a third sub-bore made in the other of the shackles, wherein a third ball joint ring is inserted and fastened in the first bore of the spreader, and wherein a third connection pin is housed and fastened in the third ball joint ring and housed free to rotate in a fourth sub-bore provided for such rotatable housing in each shackle.
4\. An aircraft comprising: a wing, an engine having a structure and an engine pylon according to claim 1, wherein the structure of the engine pylon is fastened beneath the wing, wherein the two second bores each form a second connection point with the structure of the engine, and wherein the two third bores each form a third connection point with the structure of the engine.
5\. The aircraft according to claim 4, wherein each second connection point is constituted of a second female clevis as one with the structure of the engine, a single male clevis being constituted by the second end of the spreader, wherein the spreader is disposed inside each second female clevis, a second connection pin and a second ball joint ring being inserted and fastened in the second bore of the spreader, and wherein the second connection pin is housed and fastened in the second ball joint ring and housed free to rotate in bores provided for such rotatable housing in the second female clevis.
6\. The aircraft according to claim 4, wherein the rod is constituted of two shackles disposed on either side of the first end of the spreader, wherein each of the third bores is constituted of a third sub-bore made in one of the shackles and a third sub-bore made in the other of the shackles, wherein a third ball joint ring is inserted and fastened in the first bore of the spreader, wherein a third connection pin is housed and fastened in the third ball joint ring and housed free to rotate in a fourth sub-bore provided for such rotatable housing in each shackle, wherein each third connection point is constituted of a pair of third female clevises as one with the structure of the engine, for each third female clevis of the pair of third female clevises, a male clevis being constituted by one of the rods disposed inside said third female clevis, a fourth connection pin and a fourth ball joint ring being inserted and fastened in the third sub-bores of each shackle, and wherein the fourth connection pin is housed fastened in the fourth ball joint ring and housed free to rotate in the third sub-bores.

OFFICE ACTION:
Notice of Pre-AIA  or AIA  Status
The present application, filed on or after March 16, 2013, is being examined under the first inventor to file provisions of the AIA .
Reasons for Allowance
The following is an examiner’s reasons for allowance:
Regarding Claim 1, there is no prior art nor any reasons to modify any prior art to have the structure has a tunnel with two ends passing therethrough, wherein each of the two ends of the tunnel emerges at one of the two lateral faces, a spreader housed in the tunnel and fastened in an articulated manner to each lateral face by a first connection point, wherein a first end of the spreader has a first bore, and wherein a second end of the spreader has two second bores each configured to form a second connection point with the engine. The limitations stated along with the other limitations of the independent claim give reason for allowance. Claims 2-6 are allowable as being dependent on Claim 1.
Any comments considered necessary by applicant must be submitted no later than the payment of the
issue fee and, to avoid processing delays, should preferably accompany the issue fee. Such submissions
should be clearly labeled “Comments on Statement of Reasons for Allowance.”
Conclusion