Originally Posted by
Snyggapa
In amongst the pedantry of whether failure to meet a "stick force gradient (or stick force stable slope) and its title is "§25.175 Demonstration of static longitudinal stability" means that we can call the aircraft unstable or not, I am surprised that there is so little comment about the potential wiring bundle chafing problem identified above, where if I understand it correctly it seems that a live wire could short to the to stab trim control and drive the stab trim to the stops - without the cutoff switches doing anything about it.
Coupled with the inability to stop it or to use the now tiny manual trim wheel , how many people fancy their chances of winning that argument with the aircraft ?
Just because it hasn't happened yet (205 million safe hours) doesn't mean that it won't happen as things age and fatigue (think pickle forks)
If the FAA has the same view of the risk, what might that mean for all those NGs?