Gas turbine engine mounting arrangement

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 extends 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;
• the main mounting arrangement comprising a main bracket and a main interconnection means, the main bracket being attached to and extending in an axial direction of the engine from the pylon, and main interconnection means attached to the main bracket to interconnect the main bracket with the engine, one of the main interconnection means extending from the main bracket to interconnect with the engine comprising at least one thrust link, one end of the thrust link being attached to the main bracket with the opposite end of the thrust link attached to the engine, the thrust link extending between and connecting the main bracket and the engine;
• wherein the auxiliary interconnection means extending from the safety bracket comprise at least one ear, the at least one the ear is connected to the at least one thrust link in order to connect the safety bracket with the engine, the ear connected to the thrust link so that it will only engage with the thrust link in the event of failure of the main mounting.

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 to 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 main mounting means comprises a main bracket, a pair of thrust links, a pin and corresponding socket, the pair of thrust links disposed laterally on either side of the main bracket, the pin and corresponding socket within which the pin is engaged, is disposed at a distil end of the main bracket, the pin and socket and the thrust links interconnecting the main bracket to the engine, the auxiliary mounting structure comprises an independent safety bracket, a pair of safety links, and pair of ears, the pair of ears extending from the safety bracket, the safety bracket is connected to the pylon and is disposed between the main bracket and the pylon, the safety links extending between the safety bracket and engine are pivotally connected to the safety bracket and engine, and the ears are connected to the respective thrust link, the connection between the ears and thrust link and the safety link connections are arranged to connect the engine to the safety bracket via a pin mounted within a clearance hole so that the safety bracket only engages with the engine and carries substantial engine loads in the event of failure of the main mounting means.