Abstract: Devices, systems, and methods for anchoring a drill rig at a borehole are disclosed. An anchor assembly includes a rod mountable within a borehole, an adapter positioned on an end of the rod, an anchor face unit having a plurality of drill rig assembly mounting features, and an anchor clamp mounted to the anchor face unit. The anchor clamp has a plurality of jaws movable from an engagement position wherein said plurality of jaws are positioned within an adapter groove to a disengagement position wherein said plurality of jaws are positioned away from said adapter groove.

Abstract: Auxiliary power systems, aircraft including the same, and related methods are disclosed herein. In one embodiment, the aircraft includes an airframe and an auxiliary power system that includes an auxiliary power unit (APU), an APU controller, and a bleed air temperature (BAT) sensor. The APU defines a bleed air outlet and is configured to regulate a BAT of a bleed air flow generated by the auxiliary power unit. The BAT sensor is positioned at a remote BAT location that is outside the bleed air outlet of the APU. In another embodiment, the auxiliary power system includes an APU configured to generate a bleed air flow, an APU controller configured to receive and transmit signals, and a BAT sensor suite configured to measure the BAT of the bleed air flow and to generate a BAT signal that is based, at least in part, on the BAT.

Abstract: Auxiliary power systems, aircraft including the same, and related methods are disclosed herein. In one embodiment, the aircraft includes an airframe and an auxiliary power system that includes an auxiliary power unit (APU), an APU controller, and a bleed air temperature (BAT) sensor. The APU defines a bleed air outlet and is configured to regulate a BAT of a bleed air flow generated by the auxiliary power unit. The BAT sensor is positioned at a remote BAT location that is outside the bleed air outlet of the APU. In another embodiment, the auxiliary power system includes an APU configured to generate a bleed air flow, an APU controller configured to receive and transmit signals, and a BAT sensor suite configured to measure the BAT of the bleed air flow and to generate a BAT signal that is based, at least in part, on the BAT.

Abstract: Auxiliary power systems, aircraft including the same, and related methods. An auxiliary power system comprises an auxiliary power unit (APU) controller and an APU with an air intake, a powerhead, and a load compressor stage. The load compressor stage includes a flow regulator assembly, a load compressor, and a bleed air temperature (BAT) sensor for generating a BAT signal. The APU controller regulates a flow rate of a load compressor airflow through the load compressor based on the BAT signal. A method of utilizing an auxiliary power system includes compressing a load compressor airflow to generate a bleed air flow, measuring the BAT with a BAT sensor, generating a BAT signal based on the BAT, transmitting the BAT signal to an APU controller, generating a flow regulator command with the APU controller, transmitting the flow regulator command to a flow regulator assembly, and controlling a flow regulator assembly.

Abstract: Auxiliary power systems, aircraft including the same, and related methods. An auxiliary power system comprises an auxiliary power unit (APU) controller and an APU with an air intake, a powerhead, and a load compressor stage. The load compressor stage includes a flow regulator assembly, a load compressor, and a bleed air temperature (BAT) sensor for generating a BAT signal. The APU controller regulates a flow rate of a load compressor airflow through the load compressor based on the BAT signal. A method of utilizing an auxiliary power system includes compressing a load compressor airflow to generate a bleed air flow, measuring the BAT with a BAT sensor, generating a BAT signal based on the BAT, transmitting the BAT signal to an APU controller, generating a flow regulator command with the APU controller, transmitting the flow regulator command to a flow regulator assembly, and controlling a flow regulator assembly.

Abstract: A lubrication distribution system for an engine is disclosed. The system includes a source of lubricant for the engine and at least one feed line fluidly connected to the source of lubricant. The feed line includes a wall defining a passageway and an orifice. The feed line terminates at the orifice, and lubricant flows through the passageway and exits the feed line through the orifice. The feed line also includes a heating element contained substantially within the wall of the feed line and located at or directly upstream of the orifice. The heating element is selectively activated to heat the lubrication flowing through the passageway and exiting the orifice.

Abstract: A lubrication distribution system for an engine is disclosed. The system includes a source of lubricant for the engine and at least one feed line fluidly connected to the source of lubricant. The feed line includes a wall defining a passageway and an orifice. The feed line terminates at the orifice, and lubricant flows through the passageway and exits the feed line through the orifice. The feed line also includes a heating element contained substantially within the wall of the feed line and located at or directly upstream of the orifice. The heating element is selectively activated to heat the lubrication flowing through the passageway and exiting the orifice.

Abstract: A method and apparatus comprising a tube, an opening in the tube, and a valve associated with the opening. The tube is configured to carry an inert gas in a fuel tank. The valve is configured to control an amount of the inert gas that exits the opening based on a level of fuel relative to the opening.

Abstract: A fuel system for an aircraft has a vent system. The system has a conduit opening into the fuel section. The system has a member connected to the conduit at a proximal end. The member has a seal plate within the conduit sealing the opening into the fuel section when a buoyant section at a distal end rises along with the seal plate through the member with a rise in fluid level within the fuel section.

Abstract: A fuel system for an aircraft has a vent system. The system has a conduit opening into the fuel section. The system has a member connected to the conduit at a proximal end. The member has a seal plate within the conduit sealing the opening into the fuel section when a buoyant section at a distal end rises along with the seal plate through the member with a rise in fluid level within the fuel section.

Abstract: A method and apparatus comprising a tube, an opening in the tube, and a valve associated with the opening. The tube is configured to carry an inert gas in a fuel tank. The valve is configured to control an amount of the inert gas that exits the opening based on a level of fuel relative to the opening.