The report details the position of the trim as near full "nose up" this is exactly opposite to what i would expect to see considering the CofG location also the trim failure light was illuminated?
The stabilizer trim aft jackscrew was examined, and about 14 exposed threads were noted. According to Mooney documentation, this is consistent with a nose-up trim setting, with 16 exposed threads corresponding to full nose-up, and 7 exposed threads for takeoff.
The trim position was further corroborated by examination of the stabilizer trim control system assembly, located in cabin floor area. The dimension of the trim stop from the forward jam nuts was measured. The dimension was 0.9 inches, which according to Mooney documentation, was consistent with a nose-up trim setting, with 0.7 inches correlating to full nose-up. Rotation of the assemblies' output shaft resulted in smooth rotation of the drive sprocket. The trim assembly chain appeared intact, and no damage was noted to the sprockets. The plastic trim wheel had become fragmented, with the center hub still in place. Rotation of the trim wheel hub resulted in rotation of output drive shaft at the trim assembly.
The remaining sections of the elevator trim system were examined and exhibited varying degrees of crush and fragmentation damage. No anomalies were noted to the trim system.
During the examination, the lamp filaments from the indicator panel of the KC-191 Flight Computer were examined. All lamp filaments with the exception of the trim failure warning lamp, were either intact and upright, or broken midspan. The trim failure warning lamp filament remained intact, but exhibited stretching to its filament, and was bent in the downwards direction relative to the airplanes vertical axis.
According to the autopilot operating instructions, the illumination of only the trim failure warning lamp indicated that the unit had either been powered-up, and no system self-test had been performed, or that a test was performed but the system failed. Additionally, the illumination could indicate a trim failure during flight. Under all of these conditions, the autopilot is inoperative.