Abstract: An exemplary embodiment provides a shrouded conduit joint assembly that includes a joint assembly and a boot shroud. The joint assembly includes a first ferrule having a first seal, and a second ferrule having a second seal. A clamp operatively engages the first ferrule and the second ferrule. The boot shroud surrounds the joint assembly and is spaced from the joint assembly to create a leak detection space between the joint assembly and the boot shroud.

Abstract: A leak detection feature for a fluid conduit. The leak detection feature facilitates the monitoring of fluid leaks at the interface of two adjoining conduit flange fittings. An embodiment of a flange fitting with a leak detection feature for a fluid conduit having an opening. The flange fitting includes a flange body around the opening of the fluid conduit, a leak detection passageway formed in the flange body, and a leak detection port formed in the flange body. The flange body has a sealing face surface configured to mate with a cooperating flange fitting, and the leak detection passageway terminates at the sealing face surface. The leak detection port is in fluid communication with the leak detection passageway, and the leak detection port is configured for fluid communication with a leak sensing apparatus.

Abstract: Fittings with redundant seals for aircraft fuel lines, fuel tanks, and other systems. A representative fitting includes a first member having a flange and a barrel. The barrel further includes a passageway. A first flange seal is positioned at a face of the flange and can be sealably coupled to a surface, for example, a tank wall. A second flange seal is disposed outwardly from the first flange seal to seal against the surface. The fitting further includes a second member positioned within the passageway of the barrel. The fitting further includes first and second barrel seals positioned between the barrel and the second member.

Abstract: A leak detection feature for a fluid conduit. The leak detection feature facilitates the monitoring of fluid leaks at the interface of two adjoining conduit flange fittings. An embodiment of a flange fitting with a leak detection feature for a fluid conduit having an opening. The flange fitting includes a flange body around the opening of the fluid conduit, a leak detection passageway formed in the flange body, and a leak detection port formed in the flange body. The flange body has a sealing face surface configured to mate with a cooperating flange fitting, and the leak detection passageway terminates at the sealing face surface. The leak detection port is in fluid communication with the leak detection passageway, and the leak detection port is configured for fluid communication with a leak sensing apparatus.

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: A leak detection feature for a fluid conduit. The leak detection feature facilitates the monitoring of fluid leaks at the interface of two adjoining conduit flange fittings. An embodiment of a flange fitting with a leak detection feature for a fluid conduit having an opening. The flange fitting includes a flange body around the opening of the fluid conduit, a leak detection passageway formed in the flange body, and a leak detection port formed in the flange body. The flange body has a sealing face surface configured to mate with a cooperating flange fitting, and the leak detection passageway terminates at the sealing face surface. The leak detection port is in fluid communication with the leak detection passageway, and the leak detection port is configured for fluid communication with a leak sensing apparatus.

Abstract: Systems and methods for distributing loads from fluid conduits, including aircraft fuel conduits. 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: 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: 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: 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: 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: A leak detection feature for a fluid conduit is provided. The leak detection feature facilitates the monitoring of fluid leaks at the interface of two adjoining conduit flange fittings. An embodiment of a flange fitting with a leak detection feature for a fluid conduit having an opening is disclosed herein. The flange fitting includes a flange body around the opening of the fluid conduit, a leak detection passageway formed in the flange body, and a leak detection port formed in the flange body. The flange body has a sealing face surface configured to mate with a cooperating flange fitting, and the leak detection passageway terminates at the sealing face surface. The leak detection port is in fluid communication with the leak detection passageway, and the leak detection port is configured for fluid communication with a leak sensing apparatus.

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: An exemplary embodiment provides a shrouded conduit joint assembly that includes a joint assembly and a boot shroud. The joint assembly includes a first ferrule having a first seal, and a second ferrule having a second seal. A clamp operatively engages the first ferrule and the second ferrule. The boot shroud surrounds the joint assembly and is spaced from the joint assembly to create a leak detection space between the joint assembly and the boot shroud.

Abstract: Provided are shrouded adapter assemblies for coupling together a first conduit and a second conduit. The conduits may both be single-walled or one may be shrouded. Thus, the first conduit may include an inner conduit and an outer conduit with a conduit annular space between the inner conduit and the outer conduit. The adapter assembly may include a first adapter body having a first end and a second end. The first end is configured to receive an end of the inner conduit of the first conduit, and to receive an end of the outer conduit of the first conduit. The adapter assembly also includes a second adapter body having a first end and a second end, where the first end of the second adapter body is configured to receive an end of the second conduit. The adapter assembly further includes a clamp operatively engaging and clamping the second end of the first adapter body to the second end of the second adapter body.

Abstract: A shrouded valve apparatus including an outer conduit, an inner conduit disposed within the outer conduit, and a valve member operable to regulate flow through the inner conduit. This apparatus is useful in shrouded aircraft fuel systems.

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: 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: 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: A shrouded valve apparatus including an outer conduit, an inner conduit disposed within the outer conduit, and a valve member operable to regulate flow through the inner conduit. This apparatus is useful in shrouded aircraft fuel systems.