Abstract: In the various embodiments, systems and methods are disclosed for determining the location of User Equipment (UE) in a network and for authorizing access to content based on said location. An aspect of the present disclosure is a method including receiving, by a Content Authorization Function (CAF), a request to provide a UE type of a UE and a physical location associated with the UE, the request including a UE Internet Protocol (IP) address associated with the UE; querying, by the CAF, a Network Function (NF), to provide the UE type and associated physical location, the query including the UE IP address; receiving, by the CAF from the NF, the UE type and associated physical location; and transmitting the UE type and associated physical location.

Abstract: A method is provided for disassembling a gas turbine engine. The gas turbine engine includes a compressor section, a combustor section, a turbine section, a static structure and a bypass duct. The static structure houses and supports the compressor section, the combustor section and the turbine section. The static structure includes a turbine support structure. The bypass duct includes an inner duct wall, an outer duct wall and a bypass flowpath formed radially between the inner duct wall and the outer duct wall. The outer duct wall extends axially along the static structure and overlaps the turbine support structure. During the method, the turbine support structure is removed from the gas turbine engine while the outer duct wall remains installed.

Abstract: Methods and tools for facilitating the installation and/or removal of a rotor on a shaft of a gas turbine engine are provided. The tool includes a stabilizer attachable to the shaft and including a first guide counterpart. The tool also includes a holder attachable to the rotor and including a second guide counterpart for engagement with the first guide counterpart of the stabilizer. Engagement of the first and second guide counterparts guides movement of the holder relative to the stabilizer along a guide axis and prevents movement of the holder relative to the stabilizer transverse to the guide axis.

Abstract: In the various embodiments, systems and methods are disclosed for determining the location of User Equipment (UE) in a network and for authorizing access to content based on said location. An aspect of the present disclosure is a method including receiving, by a Content Authorization Function (CAF), a request to provide a UE type of a UE and a physical location associated with the UE, the request including a UE Internet Protocol (IP) address associated with the UE; querying, by the CAF, a Network Function (NF), to provide the UE type and associated physical location, the query including the UE IP address; receiving, by the CAF from the NF, the UE type and associated physical location; and transmitting the UE type and associated physical location.

Abstract: An aircraft engine repair tool for installing and/or removing a mid turbine frame from a gas turbine engine is provided. The tool includes a stabilizer configured to support a shaft via a load path different from a load path provided by the mid turbine frame rotatably supporting the shaft about a rotation axis. The tool includes a holder attachable to the mid turbine frame, and a guide movably engageable with the shaft and attachable to the holder. The guide guides movement of the holder and of the mid turbine frame relative to the shaft along the rotation axis, and prevents movement of the holder and the mid turbine frame relative to the shaft transverse to the rotation axis when the mid turbine frame is released from the support structure and attached to the holder, and when the holder is attached to the guide.

Abstract: A method is provided for disassembling a gas turbine engine. The gas turbine engine includes a compressor section, a combustor section, a turbine section, a static structure and a bypass duct. The static structure houses and supports the compressor section, the combustor section and the turbine section. The static structure includes a turbine support structure. The bypass duct includes an inner duct wall, an outer duct wall and a bypass flowpath formed radially between the inner duct wall and the outer duct wall. The outer duct wall extends axially along the static structure and overlaps the turbine support structure. During the method, the turbine support structure is removed from the gas turbine engine while the outer duct wall remains installed.

Abstract: An aircraft engine repair tool for installing and/or removing a mid turbine frame from a gas turbine engine is provided. The tool includes a stabilizer configured to support a shaft via a load path different from a load path provided by the mid turbine frame rotatably supporting the shaft about a rotation axis. The tool includes a holder attachable to the mid turbine frame, and a guide movably engageable with the shaft and attachable to the holder. The guide guides movement of the holder and of the mid turbine frame relative to the shaft along the rotation axis, and prevents movement of the holder and the mid turbine frame relative to the shaft transverse to the rotation axis when the mid turbine frame is released from the support structure and attached to the holder, and when the holder is attached to the guide.

Abstract: An aircraft engine repair tool for installing and/or removing a mid turbine frame from a gas turbine engine is provided. The tool includes a stabilizer configured to support a shaft via a load path different from a load path provided by the mid turbine frame rotatably supporting the shaft about a rotation axis. The tool includes a holder attachable to the mid turbine frame, and a guide movably engageable with the shaft and attachable to the holder. The guide guides movement of the holder and of the mid turbine frame relative to the shaft along the rotation axis, and prevents movement of the holder and the mid turbine frame relative to the shaft transverse to the rotation axis when the mid turbine frame is released from the support structure and attached to the holder, and when the holder is attached to the guide.

Abstract: Methods and tools for facilitating the installation and/or removal of a rotor on a shaft of a gas turbine engine are provided. The tool includes a stabilizer attachable to the shaft and including a first guide counterpart. The tool also includes a holder attachable to the rotor and including a second guide counterpart for engagement with the first guide counterpart of the stabilizer. Engagement of the first and second guide counterparts guides movement of the holder relative to the stabilizer along a guide axis and prevents movement of the holder relative to the stabilizer transverse to the guide axis.

Abstract: A packet destined for a Multi-access Edge Computing (MEC) network is received at a wireless station from a user device. A serving gateway (SGW) receives the packet from the wireless station via an S1U GTP tunnel and assigns an uplink S1U General Packet Radio Service (GPRS) Tunneling Protocol (GTP) tunnel endpoint identifier (TEID) to the packet. The SGW performs a network address translation (NAT) function on the packet based on the uplink S1U GTP TEID assigned to the packet to form a translated packet. The SGW transmits the translated packet to the MEC network.

Abstract: A method is provided for disassembling a gas turbine engine. The gas turbine engine includes a compressor section, a combustor section, a turbine section, a static structure and a bypass duct. The static structure houses and supports the compressor section, the combustor section and the turbine section. The static structure includes a turbine support structure. The bypass duct includes an inner duct wall, an outer duct wall and a bypass flowpath formed radially between the inner duct wall and the outer duct wall. The outer duct wall extends axially along the static structure and overlaps the turbine support structure. During the method, the turbine support structure is removed from the gas turbine engine while the outer duct wall remains installed.

Abstract: Methods and tools for facilitating the installation and/or removal of a rotor on a shaft of a gas turbine engine are provided. The tool includes a stabilizer attachable to the shaft and including a first guide counterpart. The tool also includes a holder attachable to the rotor and including a second guide counterpart for engagement with the first guide counterpart of the stabilizer. Engagement of the first and second guide counterparts guides movement of the holder relative to the stabilizer along a guide axis and prevents movement of the holder relative to the stabilizer transverse to the guide axis.

Abstract: Methods and tools for facilitating the installation and/or removal of a rotor on a shaft of a gas turbine engine are provided. The tool includes a stabilizer attachable to the shaft and including a first guide counterpart. The tool also includes a holder attachable to the rotor and including a second guide counterpart for engagement with the first guide counterpart of the stabilizer. Engagement of the first and second guide counterparts guides movement of the holder relative to the stabilizer along a guide axis and prevents movement of the holder relative to the stabilizer transverse to the guide axis.

Abstract: A gas turbine engine yoke includes an arcuate body mountable to a stand and rotatable between an upright orientation and a horizontal orientation. The body has an inner wall spaced apart from an outer wall and first and second side walls extending between the inner and outer walls. A mounting plane of the yoke extends through the inner and outer walls and is positioned between the first and second side walls. Engine attachments are spaced apart along the inner wall and lie in the mounting plane. A method of assembling the gas turbine engine is also disclosed.

Abstract: A packet destined for a Multi-access Edge Computing (MEC) network is received at a wireless station from a user device. A serving gateway (SGW) receives the packet from the wireless station via an S1U GTP tunnel and assigns an uplink S1U General Packet Radio Service (GPRS) Tunneling Protocol (GTP) tunnel endpoint identifier (TEID) to the packet. The SGW performs a network address translation (NAT) function on the packet based on the uplink S1U GTP TEID assigned to the packet to form a translated packet. The SGW transmits the translated packet to the MEC network.

Abstract: A gas turbine engine yoke includes an arcuate body mountable to a stand and rotatable between an upright orientation and a horizontal orientation. The body has an inner wall spaced apart from an outer wall and first and second side walls extending between the inner and outer walls. A mounting plane of the yoke extends through the inner and outer walls and is positioned between the first and second side walls. Engine attachments are spaced apart along the inner wall and lie in the mounting plane. A method of assembling the gas turbine engine is also disclosed.