Mounting arrangement for a gas turbine engine

A mounting arrangement for a gas turbine engine (10) having a casing (15) provided with an at least one annular flange (16) comprising a support member (22) for attachment to an aircraft structure (12) from which the engine (10) is to be mounted, the support member (22) having a first connection means (26) which engages the at least one annular flange (16) on the engine casing (15) to support the engine (10) in a vertical plane, the vertical loads acting peripherally of the engine casing (15) through the annular flange (16), a second connection means:

• (28) which engages the engine casing (15) directly to prevent axial movement of the engine (10) relative to the aircraft structure (12) and a third connection means (30) which in normal operation carries no load unless the first connection means (26) breaks whereby the third connection means (30) engages with a further annular flange (18) on the engine casing (15) to support the engine (10) in a vertical plane, the vertical loads acting peripherally of the engine (15) casing through the further annular flange (18) characterised in that the first (26), second (28) and third (30) connection means are an integral part of the support member (22) and the support member (22) and connection means (26,28 and 30) are split in a direction parallel to the longitudinal axis of the engine (10) to render them damage tolerant.