A method for calculation and consolidation of a first plurality of flight parameters of an aircraft including a second plurality, equal to or greater than said first plurality, of pressure sensors (S 1 -S N) arranged at respective locations (i 1 -i N) on the aircraft, each pressure sensor being configured to provide a transduced pressure value (X 1 -X N) on the basis of a respective detected static pressure value, the method comprising the step of acquiring said transduced pressure values (X 1 -X N) from the pressure sensors, and being characterized by further comprising the steps of: a- defining a system of equations by associating with each transduced pressure value (X 1 -X N) a respective non-linear mathematical model that is a function of said flight parameters and which defines a mathematical relationship between each transduced pressure value and the aerodynamic behaviour of the aircraft at the location (i 1 -i N) of the pressure sensor (S 1 -S N) that has generated this transduced pressure value; b- iteratively solving said system of equations, obtaining a current value of each of said flight parameters at each respective location (i 1 -i N); c- calculating, for each respective location (i 1 -i N), a respective estimated pressure value (Y 1 -Y N) by applying the current values of said flight parameters calculated for the respective location (i 1 -i N) to each mathematical model; d- comparing (30, 40) each transduced pressure value (X 1 -X N) with the respective estimated pressure value (Y 1 -Y N), obtaining a result value; and e- detecting an operation state of said pressure sensors (S 1 -S N) on the basis of said result value by performing statistical analysis on said result values, wherein said statistical analysis comprises: defining a plurality of subgroups of said pressure sensors (S 1 -S N) different from each other, each subgroup comprising a number of sensors equal to the total number of said pressure sensors (S 1 -S N) minus one; repeating steps a- to d- for each subgroup of said pressure sensors (S 1 -S N); calculating a value of standard deviation of said result value for each subgroup; and comparing said values of standard deviation of each subgroup with each other. a- defining a system of equations by associating with each transduced pressure value (X 1 -X N) a respective non-linear mathematical model that is a function of said flight parameters and which defines a mathematical relationship between each transduced pressure value and the aerodynamic behaviour of the aircraft at the location (i 1 -i N) of the pressure sensor (S 1 -S N) that has generated this transduced pressure value; b- iteratively solving said system of equations, obtaining a current value of each of said flight parameters at each respective location (i 1 -i N); c- calculating, for each respective location (i 1 -i N), a respective estimated pressure value (Y 1 -Y N) by applying the current values of said flight parameters calculated for the respective location (i 1 -i N) to each mathematical model; d- comparing (30, 40) each transduced pressure value (X 1 -X N) with the respective estimated pressure value (Y 1 -Y N), obtaining a result value; and e- detecting an operation state of said pressure sensors (S 1 -S N) on the basis of said result value by performing statistical analysis on said result values, wherein said statistical analysis comprises: defining a plurality of subgroups of said pressure sensors (S 1 -S N) different from each other, each subgroup comprising a number of sensors equal to the total number of said pressure sensors (S 1 -S N) minus one; repeating steps a- to d- for each subgroup of said pressure sensors (S 1 -S N); calculating a value of standard deviation of said result value for each subgroup; and comparing said values of standard deviation of each subgroup with each other. defining a plurality of subgroups of said pressure sensors (S 1 -S N) different from each other, each subgroup comprising a number of sensors equal to the total number of said pressure sensors (S 1 -S N) minus one; repeating steps a- to d- for each subgroup of said pressure sensors (S 1 -S N); calculating a value of standard deviation of said result value for each subgroup; and comparing said values of standard deviation of each subgroup with each other.