Patent attributes
A drive system for an aircraft such as a tiltrotor aircraft. The drive system includes first and second gearbox assemblies in mechanical communication with each other. A first lubrication system is associated with the first gearbox assembly and includes a bifurcated tank configured to contain a lubricant in an operating chamber including a lower sump and in an emergency chamber including an upper sump. A second lubrication system is associated with the second gearbox assembly. An emergency pump is in fluid communication with the emergency chamber. The emergency pump is configured to supply the lubricant to the first gearbox assembly from the emergency chamber responsive to a failure in the first lubrication system. In addition, the emergency pump is configured to supply the lubricant to the second gearbox assembly and to the operating chamber from the emergency chamber responsive to a failure in the second lubrication system.
