0075 00
TM 1-6625-724-13&P
0075 00-20
NOTE
If a blade requires more than a 15-degree tab bend from
0 in either direction, refer to the manufacturer’s
procedure for isolation of a defective blade.
i. If any adjustments have been made, perform the flight test again and verify the corrections.
j. Remove the AVA equipment from the aircraft.
k. Inventory AVA kit and adapter kit to ensure all parts are removed from the aircraft.
Figure 13. FLIGHT Flow Chart
FLIGHT MEASUREMENTS
Within
Limits?
YES
Exit Vibration Analysis
NO
Make AVA-recommended
adjustments
Use Edit Adjustables to turn on trim
tab for hub with >12 mark pitch link
adjustment
YES
NO
AVA Default
solution >12
marks for
pitch link?
