This disclosure relates to a landing gear system (10) that includes a landing gear strut (14) rotatable between stowed and deployed positions.

The computer/controller calculates the stiction of each landing gear strut and compensates for the pressure distortions caused by landing gear strut stiction.

An oxygen sensor (21) is mounted in relation to each of the landing gear struts as to monitor, recognize, measure and record the identification of oxygen within the telescopic landing gear struts.

The amount of oxygen within each landing gear strut is measured and recorded and downloaded to the responsible aircraft maintenance department.

The method thereby generates relatively low torque loads in the landing gear leg, reducing fatigue damage.

An actuator (18) is connected to the landing gear strut, and includes main and emergency drives housed within a common body and operable independently from one another.

The load on an aircraft component, such as the load on or in a landing gear leg during braking, is measured with an all weather displacement measuring system.

A little deeper, 62 m below sea level, a complete main landing gear assembly lied, alone and devoid of any attachment.

The load on an aircraft component, such as the load on a landing gear leg during braking, is measured with a contactless, all-weather displacement measuring system.

Apparatus for providing information to a pilot about the weight and balance and the flight characteristics of an aircraft (2) includes a weighing pad (4) for each landing gear strut of the aircraft (2).

The assisting means must be usable and self-supporting with one or more landing gear legs collapsed and under a 25-knot wind directed from the most critical angle.

(2) The assisting means must be usable and self-supporting with one or more landing gear legs collapsed and under a 25-knot wind directed from the most critical angle.