Patent ID: 8444084
Filing Date: 2013-05-21
Classification: B64D

Abstract:
1. A gas turbine engine mounting arrangement comprising: a pylon; a gas turbine engine comprising a core engine casing, a fan casing comprising a rigid containment casing, a tail bearing housing and a nacelle comprising a structurally stiff inner wall; a front mount directly connected to the fan casing or to the core engine casing, the front mount being connected to the pylon by a first pylon connector; a rear mount directly connected to the tail bearing housing or the structurally stiff inner wall, the rear mount being connected to the pylon by a second pylon connector, wherein the front and rear mounts are axially separated from one another; and a fail-safe mount directly connected to the structurally stiff inner wall or the rigid containment casing, the fail-safe mount being connected to the pylon by a third pylon connector, wherein said fail-safe mount is axially spaced from the front and rear mounts, wherein the fail-safe mount does not transmit loads between the engine and the pylon except in the event of failure to either the front or rear mounts so that any load combination on the front and rear mounts may be transferred to the fail-safe mount.