Patent ID: 6474597
Filing Date: 2002-11-05
Classification: B64D

Abstract:
A gas turbine engine mounting arrangement for attaching a gas turbine engine to an aircraft via a pylon, the arrangement comprising a main mounting means and an auxiliary mounting structure, wherein the main mounting means interconnects the engine with the pylon and carries the engine loads under normal operating conditions, the auxiliary mounting structure is capable of interconnecting the engine with the pylon and is arranged to be substantially unloaded under normal operating conditions;wherein the auxiliary mounting structure comprises a safety bracket and an auxiliary interconnection means, bracket is independent of the main mounting means and is attached to the pylon, the auxiliary interconnection means comprises at least one safety link, the at least one safety link being pivotally attached to and extending from the safety bracket and extending from the safety bracket to connect the safety bracket to the engine, the auxiliary interconnection means and the safety bracket only engaging with the engine and carrying substantial engine loads in the event of failure of the main mounting means.