TM 1-6625-724-13&P0071 000071 00-21TASK 3 - TRACK AND BALANCE MAIN ROTOR IN FLIGHTFigure 9. Polar Chartd. As the caption says in figure 9, if blade 2 was adjusted to bring the aircraft into track that would be a mistakeand would increase the vertical vibration (refer to the AH-64 coefficient polar chart for vertical vibration at theend of this section).e. This information in the displays should not be used to make corrections, this should be used to make changesto the diagnostics to obtain a better solution. After all this information is reviewed, it is time to enterDiagnostics.WARNINGTotal blade balance weight is not to exceed 1017grams, nine -3 weights, on a single blade. WARNINGTotal blade trim tab bends are not to exceed +\- 5degrees in any pocket. Tabs should be bentuniformly at all locations suggested by the AVAdiagnostics.NOTEAVA moves are changes to the adjustable componentsand, as such, are to be added or subtracted to whateverthe component is currently set to. For example, whenthe AVA calls for 1 degree down in pockets 4-10, that 1degree is to be made to any bend already existing inthose pockets. NOTEIf any blade shows a 6-10 or 8-10 tab adjustment of 2degrees or more, it is recommended to Edit Adjustablesto turn off the 2 degree or greater 6-10 or 8-10 tabregion and turn on the next larger tab region for thatblade, then recompute the adjustment. For example, ifthe AVA solution calls for a 2 degree bend in pockets 6-10 on Blade 1, use Edit Adjustables to turn off the Blade1 6-10 tab and turn on Blade 1 4-10 tab and recomputethe adjustments.This is the direction that thevibration readings would moveif the tab or pitch link wasadjusted up on blade 2. All ofthe vibration readings wouldmove away from the center ofthe circle and get worse.
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