A fuel characteristic determination system and method for determining one or more fuel characteristics of an aviation fuel for powering a gas turbine engine of an aircraft. The system includes a sensor component that is formed from a nitrile seal material and includes a surface that can be exposed to the fuel; a sensor for measuring a swell parameter of the seal material; and a fuel characteristics determination module for determining one or more fuel characteristics of the fuel based on the swell parameter. The method includes: exposing one or more seals of a fuel system of an aircraft to fuel within the fuel system; exposing a sensor component, made from the same material as the one or more seals, to the fuel; and measuring a swell parameter of the seal material.

A method for validating a capacitance measurement device including, sending a first drive signal from a capacitance measurement device to a capacitor emulator, modifying the first drive signal by an four quadrant analog multiplier, directing the modified signal across a capacitor to produce a return signal, sending the return signal to the capacitance measurement device to validate the capacitor, and validating the return signal against an expected return signal by the capacitance measurement device.

An isolator for an aircraft fuel tank configured to separate an electrically conductive internal panel of the fuel tank from an electrically conductive pipe that passes through the panel. The isolator includes: a plurality of first attachment points for attaching the isolator to the panel, a plurality of second attachment points for attaching the isolator to the pipe, and an aperture defined by an outer wall and extending from a first side of the isolator to a second side of the isolator. The aperture is configured to receive the pipe in use, wherein the isolator is formed of a non-electrically conductive material.

A passive lockable strut is presented. The passive lockable strut comprises a first end; a second end; a fluid chamber between and connected to the first end and the second end; and a fluid within the fluid chamber, wherein the fluid is configured to activate the passive lockable strut to place the passive lockable strut in a locked condition in response to a change in an operating condition applied to the passive lockable strut.

A rotodynamic pump for pumping a fluid includes an impeller, a housing surrounding the impeller, and a pressure regulating mechanism. The pressure regulating mechanism is configured to adjust the clearance between the impeller and the impeller housing to regulate pressure of the fluid downstream of the impeller. A method of regulating the delivery pressure is also disclosed.

A fluid conduit includes, a body, a first conduit portion connected to the body, a second conduit portion connected to the body, and a base connected to the second conduit portion. The body, the first conduit portion, the second conduit portion, and the base may be formed as a monolithic component via additive manufacturing. A method of making a fluid conduit may include forming sets of layers. The set of layers may include parts or portions of the fluid conduit and/or supports.

An aircraft includes a fuselage, a wing connected to and extending from the fuselage, a pylon mounted to a portion of the wing, an engine attached to the pylon, and an accessory system. The accessory system is mounted remotely from the engine and includes at least one of a fuel pump and a lubrication system. The fuel pump is disposed to supply fuel to portions of the engine and is the downstream-most fuel pump in fluid communication with the combustion section. The lubrication system is disposed to provide oil to portions of the engine.

A touchscreen fuel panel with checklist automation is disclosed. In embodiments, the fuel panel includes a touchscreen display and a controller coupled to the touchscreen display. The controller is configured to generate a graphical user interface at the touchscreen display and receive user inputs via the touchscreen display. The controller is further configured to execute an automated set of fuel management checklist procedures in response to a user input. In some embodiments, the controller can be alternatively or additionally configured to execute other automated sets of checklist procedures, for example, pre-flight, in-flight, taxi/takeoff/landing (TTL), and/or post-flight procedures.

A flapper valve comprising a generally rigid flap which is mounted within a flexible body coating. The hinge in the flexible body is formed by using an internal reinforcement material having a permeated structure which allows for the body material to penetrate through the reinforcement material during the valve formation. This provides for a more sturdy hinge which better resists wear.

An aircraft with a fuselage that accommodates a floor panel and a fuel storage system, wherein the fuel storage system comprises a tank system with at least one main tank 5a that is arranged underneath the floor panel; a cross ventilation system with a plurality of ventilation lines for venting the tank system, wherein the plurality of ventilation lines comprises at least one crossing ventilation line 11a that is routed from a first lateral side of the tank system to an opposite second lateral side of the tank system; and wherein the at least one crossing ventilation line is routed underneath or in the floor panel from the first lateral side of the tank system to the second lateral side of the tank system.