Abstract: A gas turbine engine 10 is suspended via a casing 15 from a pylon 12 by a front mount 20 and a rear mount 40. The front mount 20 comprises a bracket 22, having a plurality of pins 26,28 and 30 integral therewith, which is bolted to the underside 11 of the pylon 12. The first pin 26 engages an annular flange 16 around the casing 15 to support the engine 10 in a vertical plane. Any vertical loads act peripherally of the casing 15 through the annular flange 16 to minimise the distortion of the casing 15. The second pin 28 engages with the casing 15 directly to prevent axial and lateral movement of the engine 10 relative to the pylon 12. The third pin 30 is provided as a failsafe. In normal operation the third pin 30 carries no load, however if the first pin 26 should break the third pin 30 then supports the engine 10 in a vertical plane. Any vertical loads then act peripherally of the engine casing 15 through an annular flange 18.