Patent ID: 8684316
Filing Date: 2014-04-01
Classification: B64C,Y02T

Abstract:
1. A trailing edge flap mechanism for an aircraft comprising: a support beam having a first portion with a first rotation axis and a fourth rotation axis aft of the first rotation axis; a flap carrier beam supporting an aerodynamic flap, said carrier beam having a second rotation axis at a forward end and a third rotation axis within a nose contour of the flap aft of the second rotation axis; a first link interconnecting the first rotation axis and second rotation axis; a second link interconnecting the third rotation axis and fourth rotation axis; said support beam having a second portion extending angularly forward from the first portion and having a fifth rotation axis at a forward end for connection on a first fixed hinge axis; a connection link having a sixth rotation axis at a forward end for connection on a second fixed hinge axis and a seventh rotation axis connected to the first link intermediate the first and second rotation axes; and an actuator operably connected with a drive link pivotally engaged to the first link.