Abstract: A tube fitting including a first coupling member having at least a snap coupling, and a second coupling member having a first quick-connect side having a mating snap coupling disposed at a first end of the second coupling member, and a second quick-connect side configured for threaded engagement disposed at a second end of the second coupling member, the second end being opposite the first end, wherein the mating snap coupling is configured to engage the snap coupling to effect coupling of the first and second coupling member.

Abstract: A tube fitting including a first coupling member having at least a snap coupling, and a second coupling member having a first quick-connect side having a mating snap coupling disposed at a first end of the second coupling member, and a second quick-connect side configured for threaded engagement disposed at a second end of the second coupling member, the second end being opposite the first end, wherein the mating snap coupling is configured to engage the snap coupling to effect coupling of the first and second coupling member.

Abstract: An exhaust vane disposed in a divergent section of an aircraft gas turbine engine exhaust nozzle is sideways pivotable about a vane pivot axis. The nozzle vane pivot axis may be centrally located at an unvectored nozzle throat. Transversely spaced apart upper and lower tips of the exhaust vane may be incorporated to sealingly engage a nozzle outer wall along upper and lower surfaces of the outer wall of the nozzle. The exhaust vane has flat or contoured vane sidewalls and contoured vane sidewalls may be concave. The exhaust vane may have transversely biased apart upper and lower vane sections extending transversely inwardly from the upper and lower tips of the exhaust vane respectively. The exhaust vane may be articulated having upstream and downstream sections separately sideways pivotable about the vane pivot axis and a second pivot axis downstream of and parallel to the vane pivot axis respectively.

Abstract: An exhaust vane disposed in a divergent section of an aircraft gas turbine engine exhaust nozzle is sideways pivotable about a vane pivot axis. The nozzle vane pivot axis may be centrally located at an unvectored nozzle throat. Transversely spaced apart upper and lower tips of the exhaust vane may be incorporated to sealingly engage a nozzle outer wall along upper and lower surfaces of the outer wall of the nozzle. The exhaust vane has flat or contoured vane sidewalls and contoured vane sidewalls may be concave. The exhaust vane may have transversely biased apart upper and lower vane sections extending transversely inwardly from the upper and lower tips of the exhaust vane respectively. The exhaust vane may be articulated having upstream and downstream sections separately sideways pivotable about the vane pivot axis and a second pivot axis downstream of and parallel to the vane pivot axis respectively.