Abstract: Valves for annular conduits and associated systems and methods are disclosed. A fluid transmission system in accordance with one embodiment of the invention includes a first conduit having a first wall aligned with a flow direction in the first conduit and a second conduit disposed annularly around the first conduit with a second wall aligned with the flow direction. An access channel can be positioned to have an aperture in fluid communication with the first conduit and can be isolated from fluid communication with the second conduit. A valve element can be positioned in fluid communication with the access channel and can be movable between a first position and a second position, with the valve element being positioned to allow a first amount of flow through the access channel when in the first position and being positioned to allow no flow or a second amount of flow less than the first amount of flow through the access channel when in the second position.

Abstract: Adjustable fittings for attaching support members to fluid conduits, including aircraft fuel conduits, are disclosed herein. An aircraft system in accordance with one embodiment of the invention includes a fluid conduit carried by an aircraft and a housing fixedly attached to the fluid conduit. The housing can include a first attachment feature having one of a projection extending outwardly from the housing or an aperture extending at least partially through the housing. The system further includes a support member having an attachment portion positioned proximate to the attachment feature. The attachment portion includes a support member aperture positioned over at least a portion of the first attachment feature. An adjustable fitting couples the support member to the housing. The adjustable fitting can include a first side, a second side opposite the first side, and an engagement portion at the second side positioned within at least a portion of the support member aperture.

Abstract: Systems and methods for distributing loads from fluid conduits, including aircraft fuel conduits, are disclosed. An aircraft configured in accordance with one embodiment of the invention includes a fuselage portion, a wing portion, and a fuel tank carried by least one of the fuselage portion and the wing portion. The aircraft also includes a spar carried by at least one of the fuselage portion and the wing portion. The spar includes a first spar rib and a second spar rib spaced apart from the first spar rib. The aircraft further includes a fluid conduit proximate to the spar and operably coupled to the fuel tank. A support member carrying the fluid conduit is operably coupled to the spar. The support member can be positioned to transfer at least approximately all of the axial loads from the fluid conduit to at least one of the first spar rib and the second spar rib.

Abstract: Fittings with redundant seals for aircraft fuel lines, fuel tanks, and other systems are disclosed. A fitting in accordance with one embodiment can be positioned adjacent to an aperture in a fuel tank wall having an inner surface and an outer surface. The fitting can include a first member having a flange and a barrel. The barrel can further include a passageway. A first flange seal can be positioned at a face of the flange and can be sealably coupled to a surface, for example, the tank wall. A second flange seal can be disposed outwardly from the first flange seal against the surface. The fitting can further include a second member (e.g., a sensor) positioned within the passageway of the barrel. The fitting can further include first and second barrel seals positioned between the barrel and the second member.

Abstract: A shrouded body flow meter assembly includes an inner fluid-conducting conduit disposed in a spaced relation from and within an outer conduit. The shrouded flow meter assembly can be connected to other shrouded fluid-conducting apparatus and/or used to replace sections of a shrouded fluid-conducting apparatus system. The shrouded flow meter assembly maintains the integrity of the inner fluid-conducting conduits and outer conduits of the shrouded fluid-conducting apparatus.

Abstract: A shrouded fluid-conducting apparatus is provided that includes at least one outer conduit and at least one inner conduit disposed within the outer conduit. Preferably, the shrouded fluid-conducting apparatus further includes at least one shrouded end fitting disposed at an end of the shrouded fluid-conducting apparatus and at least one support member engaged with the inner and outer conduits. The shrouded end fitting allows the shrouded fluid-conducting apparatus to be engaged with an additional shrouded fluid-conducting apparatus. The support member allows for the transfer of loads from the inner and/or outer conduits to one or more components external to the shrouded fluid-conducting apparatus. Accordingly, the shrouded fluid-conducting apparatus may be used to transport fuel through an aircraft “ignition zone” in an FAA-compliant manner.

Abstract: A shrouded fluid-conducting apparatus is provided that includes at least one outer conduit and at least one inner conduit disposed within the outer conduit. Preferably, the shrouded fluid-conducting apparatus further includes at least one shrouded end fitting disposed at an end of the shrouded fluid-conducting apparatus and at least one support member engaged with the inner and outer conduits. The shrouded end fitting allows the shrouded fluid-conducting apparatus to be engaged with an additional shrouded fluid-conducting apparatus. The support member allows for the transfer of loads from the inner and/or outer conduits to one or more components external to the shrouded fluid-conducting apparatus. Accordingly, the shrouded-fluid conducting apparatus may be used to transport fuel through an aircraft “ignition zone” in an FAA-compliant manner.

Abstract: A shrouded fluid-conducting apparatus is provided that includes at least one outer conduit and at least one inner conduit disposed within the outer conduit. Preferably, the shrouded fluid-conducting apparatus further includes at least one shrouded end fitting disposed at an end of the shrouded fluid-conducting apparatus and at least one support member engaged with the inner and outer conduits. The shrouded end fitting allows the shrouded fluid-conducting apparatus to be engaged with an additional shrouded fluid-conducting apparatus. The support member allows for the transfer of loads from the inner and/or outer conduits to one or more components external to the shrouded fluid-conducting apparatus. Accordingly, the shrouded-fluid conducting apparatus may be used to transport fuel through an aircraft “ignition zone” in an FAA-compliant manner.