A method for determining a status of fluids in an oleopneumatic pitch trim actuator of an aircraft landing gear, the pitch trim actuator comprising a main actuator fluidly connected to an accumulator, wherein a gas chamber is positioned entirely within the accumulator and an oil chamber is continuous within the main actuator and accumulator, and wherein a separator piston is positioned between gas chamber and oil chamber, the pitch trim actuator comprising nominal values for a volume of oil, a pressure of gas, a volume of gas, a temperature of gas and a position of the separator piston; the method comprising: detecting, by a position sensor, a first position measurement of the separator piston before a landing of the aircraft; detecting, by a pressure sensor, a first pressure measurement of the gas within the gas chamber of the pitch trim actuator before the landing of the aircraft; detecting, by a temperature sensor, a first temperature measurement of the gas within the gas chamber of the pitch trim actuator before the landing of the aircraft; storing, in a memory, a first position value based on the first position measurement of the separator piston, a first pressure value based on the first pressure measurement of the gas and a first temperature value based on the at least one first temperature measurement of the gas; moving the separator position from a first position before the landing of the aircraft to a second position during the landing of the aircraft; detecting, by the position sensor, a second position measurement of the separator piston during the landing of the aircraft; detecting, by the pressure sensor, a second pressure measurement of the gas within the gas chamber of the pitch trim actuator during the landing of the aircraft; detecting, by the temperature sensor, a second temperature measurement of the gas within the gas chamber of the pitch trim actuator during the landing of the aircraft; storing, in a memory, a second position value based on the second position measurement of the separator piston, a second pressure value based on the second pressure measurement of the gas and a second temperature value based on the second temperature measurement of the gas; determining, by the processor, a loss volume of the oil that has leaked from the oil chamber to a location other than the gas chamber based on the first and second position value, the first and second pressure value and the first and second temperature value; determining, by the processor, a leakage volume of oil that has leaked from the oil chamber into the gas chamber based on the first and second position value, the first and second pressure value and the first and second temperature value; determining, by the processor, a gas leakage from the gas chamber based on the first position value, the volume of oil that has leaked into the gas chamber, the first pressure value, the first temperature value, the nominal values for the pressure of gas, the volume of gas and the temperature of gas, and the ideal gas constant. detecting, by a position sensor, a first position measurement of the separator piston before a landing of the aircraft; detecting, by a pressure sensor, a first pressure measurement of the gas within the gas chamber of the pitch trim actuator before the landing of the aircraft; detecting, by a temperature sensor, a first temperature measurement of the gas within the gas chamber of the pitch trim actuator before the landing of the aircraft; storing, in a memory, a first position value based on the first position measurement of the separator piston, a first pressure value based on the first pressure measurement of the gas and a first temperature value based on the at least one first temperature measurement of the gas; moving the separator position from a first position before the landing of the aircraft to a second position during the landing of the aircraft; detecting, by the position sensor, a second position measurement of the separator piston during the landing of the aircraft; detecting, by the pressure sensor, a second pressure measurement of the gas within the gas chamber of the pitch trim actuator during the landing of the aircraft; detecting, by the temperature sensor, a second temperature measurement of the gas within the gas chamber of the pitch trim actuator during the landing of the aircraft; storing, in a memory, a second position value based on the second position measurement of the separator piston, a second pressure value based on the second pressure measurement of the gas and a second temperature value based on the second temperature measurement of the gas; determining, by the processor, a loss volume of the oil that has leaked from the oil chamber to a location other than the gas chamber based on the first and second position value, the first and second pressure value and the first and second temperature value; determining, by the processor, a leakage volume of oil that has leaked from the oil chamber into the gas chamber based on the first and second position value, the first and second pressure value and the first and second temperature value; determining, by the processor, a gas leakage from the gas chamber based on the first position value, the volume of oil that has leaked into the gas chamber, the first pressure value, the first temperature value, the nominal values for the pressure of gas, the volume of gas and the temperature of gas, and the ideal gas constant.