Abstract: A method comprising: inspecting an engine during a first period of time to identify damage, the engine being associated with an aircraft; receiving three-dimensional data of one or more components of the engine, the three-dimensional data being generated during the first period of time; determining, during the first period of time, whether the identified damage exceeds a threshold; providing instructions to release the aircraft for operation in a second period of time, subsequent to the first period of time, if the identified damage does not exceed the threshold; and inspecting the received three-dimensional data during the second period of time to measure damage.

Abstract: A computer-implemented method comprising: receiving data comprising two-dimensional data and three-dimensional data of a component of an engine; identifying a feature of the component using the two-dimensional data; determining coordinates of the feature in the two-dimensional data; determining coordinates of the feature in the three-dimensional data using: the determined coordinates of the feature in the two-dimensional data; and a pre-determined transformation between coordinates in two-dimensional data and coordinates in three-dimensional data; and measuring a parameter of the feature of the component using the determined coordinates of the feature in the three-dimensional data.

Abstract: A computer-implemented method comprising: receiving data comprising two-dimensional data and three-dimensional data of a component of an engine; identifying a feature of the component using the two-dimensional data; determining coordinates of the feature in the two-dimensional data; determining coordinates of the feature in the three-dimensional data using: the determined coordinates of the feature in the two-dimensional data; and a pre-determined transformation between coordinates in two-dimensional data and coordinates in three-dimensional data; and measuring a parameter of the feature of the component using the determined coordinates of the feature in the three-dimensional data.

Abstract: A method comprising: inspecting an engine during a first period of time to identify damage, the engine being associated with an aircraft; receiving three-dimensional data of one or more components of the engine, the three-dimensional data being generated during the first period of time; determining, during the first period of time, whether the identified damage exceeds a threshold; providing instructions to release the aircraft for operation in a second period of time, subsequent to the first period of time, if the identified damage does not exceed the threshold; and inspecting the received three-dimensional data during the second period of time to measure damage.

Abstract: An asset operational health monitoring system, in which a plurality of sensors are arranged to determine values of asset operation parameters pertaining to an instance of asset operation. One or more processing unit receives data corresponding to said asset operation values and determine a plurality of asset locations at a corresponding plurality of points in time. The one or more processing unit is arranged to receive data indicative of the location of a region of adverse environmental conditions which may impact on the operation of the asset and to compare the determined locations of the asset with the location of said region so as to determine whether one or more of said asset locations fall within said region. An indicator of operational risk associated with the presence of said asset in said region is output which can drive asset operation or maintenance decision making. The system may be used for ash cloud impact monitoring for aircraft, a fleet of aircraft or aircraft engines.

Abstract: An asset operational health monitoring system, in which a plurality of sensors are arranged to determine values of asset operation parameters pertaining to an instance of asset operation. One or more processing unit receives data corresponding to said asset operation values and determine a plurality of asset locations at a corresponding plurality of points in time. The one or more processing unit is arranged to receive data indicative of the location of a region of adverse environmental conditions which may impact on the operation of the asset and to compare the determined locations of the asset with the location of said region so as to determine whether one or more of said asset locations fall within said region. An indicator of operational risk associated with the presence of said asset in said region is output which can drive asset operation or maintenance decision making. The system may be used for ash cloud impact monitoring for aircraft, a fleet of aircraft or aircraft engines.

Abstract: A method of monitoring the health of a gas turbine engine 10 comprising a fuel system 30 having a fuel metering valve 36 and a fuel pump 40 for supplying fuel to a combustor apparatus 15. The method comprising the steps of: monitoring the fuel metering valve percentage open, detecting and sending a warning message when the fuel metering valve percentage open is at 97% or greater and within a predetermined time from when the first percentage open is at 97% or greater, replacing the fuel pump 40. In this way scheduling of servicing and replacement of the fuel pump may be made without disruption to the aircraft operator particularly where the operator has a fleet of aircraft.

Abstract: The present invention is a method of monitoring the health of a fuel system 30 of a gas turbine engine 10. The fuel system 30 comprising a fuel-metering valve 36, a hydraulic control valve servo pressure line 40 and a control pressure line 39. The fuel-metering valve comprises a hydraulic control valve solenoid 36 for metering the flow of fuel and a fuel filter 38 and, in use, a current is applied to the solenoid 38 to control the required fuel demand to fuel nozzles 25. The method comprises the steps of; measuring either the percentage difference between fuel metering valve demand and actual positions or the percentage difference in pressure between the servo pressure line 40 and the control pressure line 39, comparing the differential to a predetermined level, when that predetermined level is reached a warning is given. Thereby the engine may be scheduled for service before unsatisfactory performance of the fuel system is experienced.

Abstract: The present invention is a method of monitoring the health of a fuel system 30 of a gas turbine engine 10. The fuel system 30 comprising a fuel-metering valve 36, a hydraulic control valve servo pressure line 40 and a control pressure line 39. The fuel-metering valve comprises a hydraulic control valve solenoid 36 for metering the flow of fuel and a fuel filter 38 and, in use, a current is applied to the solenoid 38 to control the required fuel demand to fuel nozzles 25. The method comprises the steps of; measuring either the percentage difference between fuel metering valve demand and actual positions or the percentage difference in pressure between the servo pressure line 40 and the control pressure line 39, comparing the differential to a predetermined level, when that predetermined level is reached a warning is given. Thereby the engine may be scheduled for service before unsatisfactory performance of the fuel system is experienced.