This paper presents the implementation of parameter-estimation method on civil aircraft Quick Access Recorder Data. The estimation techniques used are the output error method which works based on maximum likelihood principle and also the classical least square method. The implementation of the algorithm is started by performing data compatibility check or so called flight path reconstruction which aims at determining bias/systematic instrument errors and generating accurate aircraft states. It is found that using the bias corrected measurement data in the parameter estimation process will increase the accuracy of the parameters compare to that of uncorrected measurement data. The results from data compatibility check are then used to estimate the wind component in Earth frame which is not measured or provided in the data recorder. The estimation is also done by computing lift and drag coefficients time-history based in which the parameters are not measured in the data recorder. Estimation of lift and drag coefficients increment due to flap deflection during approach flight is also presented. The last implementation of parameter estimation method in this paper is conducted on the ground-run phase. In this phase, parameters such as lift coefficient, drag coefficient due to spoiler deflection, thrust and friction coefficient are estimated and presented as well. Proof of match is done in order to validate the estimated parameters. It is found that the two estimation methods which used in this paper have succeeded in estimating adequate results. The data used in this paper comes from a flight of Airbus 340-600.
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