We present a fault detection and isolation (FDI) filter design using a linear parameter-varying (LPV) model of the longitudinal dynamics of a Boeing 747 series 100/200. The LPV FDI filter design is based on an extension of the fundamental problem of residual generation concepts elaborated for linear, time-invariant systems. Typically, the FDI filters are designed for open-loop models, and applied in closed loop. An application is shown of an LPV FDI filter for actuator failure detection and isolation in the closed-loop longitudinal LPV system to the full nonlinear Boeing 747 aircraft simulation, which represents the "true" system. Nomenclaturē c = wing chord, m c 7 = inertia coefficient, kg −1 m −2 (1/I yy) q = dynamic pressure, N/m 2 S = reference surface area, m 2 s α , c α = sine and cosine of AOA, rad T n = trust force, N z eng = engine position z axis, m α = angle of attack (AOA), rad α w = wing design plane, α w = α(180/ pi) + 2 deg

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