Abstract: An engine mount system having failsafe securement points. The engine mount system includes a forward mount carrying a coat hanger shackle having a spherical bearing and a cylindrical bearing. Securement of the engine mount to a support utilizes pins and bolts with a retaining double wrench washer incorporated into the final mounting structure. The engine mount system additionally includes an aft mount.

Abstract: An engine mount system having failsafe securement points. The engine mount system includes a forward mount carrying a coat hanger shackle having a spherical bearing and a cylindrical bearing. Securement of the engine mount to a support utilizes pins and bolts with a retaining double wrench washer incorporated into the final mounting structure. The engine mount system additionally includes an aft mount.

Abstract: An engine mount system having failsafe securement points. The engine mount system includes a forward mount carrying a coat hanger shackle having a spherical bearing and a cylindrical hearing. Securement of the engine mount to a support utilizes pins and bolts with a retaining double wrench washer incorporated into the final mounting structure. The engine mount system additionally includes an aft mount.

Abstract: An engine mount system having failsafe securement points. The engine mount system includes a forward mount carrying a coat hanger shackle having a spherical bearing and a cylindrical hearing. Securement of the engine mount to a support utilizes pins and bolts with a retaining double wrench washer incorporated into the final mounting structure. The engine mount system additionally includes an aft mount.

Abstract: The present invention broadly comprises an aircraft motion control auxiliary power unit suspension system device, the aircraft motion control auxiliary power unit suspension system device comprising a first motion control nonelastomeric member and a second motion control nonelastomeric member, a first motion control elastomer member disposed to operatively interconnect the first motion control nonelastomeric member and the second motion control nonelastomeric member. The first motion control elastomer member includes an exterior surface coating formed from an elastomeric polymer dissolved in an organic solvent and the elastomeric polymer dissolved in the solvent is applied to an exterior surface of the first motion control elastomer member, the solvent evaporates, and the elastomeric polymer crosslinks.

Abstract: The present invention broadly comprises an aircraft motion control auxiliary power unit suspension system device, the aircraft motion control auxiliary power unit suspension system device comprising a first motion control nonelastomeric member and a second motion control nonelastomeric member, a first motion control elastomer member disposed to operatively interconnect the first motion control nonelastomeric member and the second motion control nonelastomeric member. The first motion control elastomer member includes an exterior surface coating formed from an elastomeric polymer dissolved in an organic solvent and the elastomeric polymer dissolved in the solvent is applied to an exterior surface of the first motion control elastomer member, the solvent evaporates, and the elastomeric polymer crosslinks.

Abstract: The invention provides an aircraft with an auxiliary power unit isolated from the aircraft. An auxiliary power unit suspension system includes at least one suspension linkage. The suspension linkage terminates with a first low stiffness elastomeric rod end. The low stiffness elastomeric rod end has a low spring rate with the aircraft auxiliary power unit suspension system providing the aircraft auxiliary power unit with a suspended auxiliary power unit natural frequency, the suspended auxiliary power unit natural frequency below the aircraft auxiliary power unit operation frequency.

Abstract: The invention provides an aircraft with an auxiliary power unit isolated from the aircraft. An auxiliary power unit suspension system includes at least one suspension linkage. The suspension linkage terminates with a first low stiffness elastomeric rod end. The low stiffness elastomeric rod end has a low spring rate with the aircraft auxiliary power unit suspension system providing the aircraft auxiliary power unit with a suspended auxiliary power unit natural frequency, the suspended auxiliary power unit natural frequency below the aircraft auxiliary power unit operation frequency.

Abstract: The invention provides an aircraft with an auxiliary power unit isolated from the aircraft. An auxiliary power unit suspension system includes at least one suspension linkage. The suspension linkage terminates with a first low stiffness elastomeric rod end. The low stiffness elastomeric rod end has a low spring rate with the aircraft auxiliary power unit suspension system providing the aircraft auxiliary power unit with a suspended auxiliary power unit natural frequency, the suspended auxiliary power unit natural frequency below the aircraft auxiliary power unit operation frequency.

Abstract: The present invention broadly comprises an aircraft motion control auxiliary power unit suspension system device, the aircraft motion control auxiliary power unit suspension system device comprising a first motion control nonelastomeric member and a second motion control nonelastomeric member, a first motion control elastomer member disposed to operatively interconnect the first motion control nonelastomeric member and the second motion control nonelastomeric member. The first motion control elastomer member includes an exterior surface coating formed from an elastomeric polymer dissolved in an organic solvent and the elastomeric polymer dissolved in the solvent is applied to an exterior surface of the first motion control elastomer member, the solvent evaporates, and the elastomeric polymer crosslinks.

Abstract: A system for supporting an auxiliary power unit in an aircraft tailcone wherein the auxiliary power unit is supported by a focalized suspension system supporting the power unit, the focalized suspension system having a plurality of support means each having a line of action, the lines of action intersecting at the focal point. The support system simplifies removal and installation of the auxiliary power unit from and into the aircraft's tailcone.

Abstract: A system for supporting an auxiliary power unit in an aircraft tailcone wherein the auxiliary power unit is supported by a focalized suspension system supporting the power unit, the focalized suspension system having a plurality of support means each having a line of action, the lines of action intersecting at the focal point. The support system simplifies removal and installation of the auxiliary power unit from and into the aircraft's tailcone.

Abstract: A multi-linkage suspension system (20) including isolators (32) positioned at the outboard ends of the linkages (26) for suspending and isolating an engine (22), such as an Auxiliary Power Unit (APU), from a structure (24), such as an aircraft fuselage. The system (20) has a plurality of linkages (26) extending from the engine (22) towards the structure (24); each linkages (26) including an inboard (28) and outboard (30) end, a plurality of outboard isolators (32) attached at the outboard ends (30), a bracket (27) for connecting the outboard isolators (32) to the structure (24), a rod end (34), which is preferably elastomeric and includes an elastomer layer (36), for connecting the plurality of linkages (26) to the engine (22). The system (20) is easily tuned and provides for common components and the location of the isolators (32) minimizes direct exposure to heat and aggressive fluids.