Aircraft engine rear suspension with thrust recovery

Details Aircraft engine rear suspension with thrust recovery Aircraft engine rear suspension with thrust recovery

2006-09-19

2006-09-19

Collins, Timothy D. (Department: 3643)

Aeronautics and astronautics

Aircraft power plants

Mounting

C060S797000

Reexamination Certificate

active

07108224

ABSTRACT:
A suspension of the turbo fan engine to an aircraft pylon, includes a fitting arranged to be attached to a pylon, a lever fastened in its central portion to the fitting via a linking device with a pivot pin. Two thrust rods are each connected by an end to the lever and including at the other end of the fastening device to the engine. The linking device is composed on the central portion of the lever, of two parallel branches apart from one another, and on the fitting, of a central fastening tab, whereas the fastening tab and both branches are held together by dint of the pivot pin.

REFERENCES:
patent: 2003/0066928 (2003-04-01), Brefort et al.
patent: 1 136 355 (2001-09-01), None
patent: 001136355 (2001-09-01), None
patent: 2 830 515 (2003-04-01), None
patent: 2830515 (2003-04-01), None
U.S. Appl. No. 10/838,243, filed May 5, 2004, Pasquer et al.
U.S. Appl. No. 10/839,133, filed May 6, 2004, Pasquer et al.
U.S. Appl. No. 10/843,306, filed May 12, 2004, Pasqier et al.

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