Aircraft engine thrust mount

A thrust mount for supporting a gas turbine engine to a pylon of an aircraft comprising:

• an annular first frame in said engine disposed coaxially about a longitudinal centerline axis of said engine;
• first and second spaced apart thrust links, each having a distal end pivotally joined to said first frame, and each further including an opposite, proximal end;
• a lever including first and second ends and a center therebetween, said first and second ends being pivotally joined to said first and second thrust link proximal ends, respectively, by first and second lever pins, respectively;
• a platform fixedly joined to said pylon and including first and second spaced apart clevises and a center clevis therebetween;
• said lever center being pivotally joined to said platform center clevis for carrying thrust force from said first frame through both said first and second thrust links and said platform to said pylon;
• said platform first and second clevises each including top and bottom spaced apart legs defining therebetween a slot, and each of said top and bottom legs including coaxially aligned apertures;
• said first thrust link proximal end and said lever first end being disposed in said platform first clevis slot with said first pin being disposed through said first clevis top and bottom leg apertures and defining therebetween a predetermined first gap for allowing said lever to rotate relative to said platform center clevis up to a predetermined angular rotation;
• and
• said second thrust link proximal end and said lever second end being disposed in said platform second clevis slot with said second pin being disposed through said second clevis top and bottom leg apertures and defining therebetween a predetermined second gap for allowing said lever to rotate relative to said platform center clevis up to said predetermined angular rotation.