Resilient aircraft engine mounts and aircraft engine mounting systems including the same

An aircraft engine mounting system comprising:

• a pair of resilient aircraft engine mounts, each resilient aircraft engine mount comprising:
• a base for attaching to a mount location on an aircraft engine;
• a pair of opposed spiral springs in parallel forming a clevis with the base, a first spiral spring of the pair of opposed spiral springs having a first center opening extending therethrough and a second spiral spring of the pair of opposed spiral springs having a second center opening extending therethrough that is concentric with the first center opening for accepting a clevis pin, each resilient aircraft engine mount independently tunable in three translational axes;
• and
• a pair of clevis pins, the clevis pin comprising one clevis pin of the pair of clevis pins.

An aircraft engine mounting system for isolating aircraft engine-produced vibratory forces from a fuselage of an aircraft and for attaching an aircraft engine to a pylon structure comprising a yoke having a first mounting portion and a second mounting portion, each of the first and second mounting portions having a mount opening therethrough, the aircraft engine mounting system comprising:

• a first resilient aircraft engine mount attached to a first mount location of the aircraft engine and a second resilient aircraft engine mount attached to a second mount location of the aircraft engine, each of the first and second resilient aircraft engine mounts comprising:
• a base for attaching to the respective mount location of the aircraft engine;
• a pair of opposed spiral springs in parallel forming a clevis, a first spiral spring of the pair of opposed spiral springs having a first opening extending therethrough, a second spiral spring of the pair of opposed spiral springs having a second opening extending therethrough that is concentric with the first opening for accepting a clevis pin, each resilient aircraft engine mount independently tunable in three translational axes;
• and
• wherein the first mounting portion of the yoke is disposed between the first and second spiral springs of the first resilient aircraft engine mount with a first clevis pin extending and secured through the first opening, the mount opening, and the second opening and the second mounting portion is disposed between the first and second spiral springs of the second resilient aircraft engine mount with a second clevis pin extending and secured through the first opening, the second opening, and the mount opening.