TASK 3 - TRACK AND BALANCE MAIN ROTOR IN FLIGHT

TASK 3 - TRACK AND BALANCE MAIN ROTOR IN FLIGHT - TM-1-6625-724-13P_450

TM-1-6625-724-13P Aviation Vibration Analyzer Manual
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TM 1-6625-724-13&P 0071 00 0071 00-19 TASK 3 - TRACK AND BALANCE MAIN ROTOR IN FLIGHT e. On the measurement screen, highlight the desired flight condition (FPG100 for AH-64A or FPG101 for AH-64D, Hover, 60, 80, 100, 120, or 140 Knots). Press DO. Verify that the aircraft is steady in selected condition and press DO to initiate measurement. f. The next screen will indicate that measurement is in progress. g. Following successful measurement, the limits screen will appear to display all measurements that exceed limits. This information can be useful in determining whether or not to proceed to the next flight condition. Use the up cursor to display all measurements relative to limits. h. Press QUIT to exit the limits screen and return to the measurement screen. The next Test State will be highlighted. Press DO twice to start measurement and repeat until all flight conditions have been obtained, or until vibration and/or track precludes advancing to the next higher speed. WARNING If main rotor 1/REV vibration becomes objectionable, acquire data normally through the highest airspeed at which vibration can be tolerated. Do not skip test conditions, data should be taken from ground to the highest airspeed possible. After data is taken at the highest airspeed achieved, press QUIT then highlight Save and Exit and then press DO. Land the aircraft and perform corrections suggested by the CADU prior to further flight. NOTE Autorotation RPM verification should be done as soon as the aircraft is capable of a forward airspeed of 80 to 100 knots. Autorotation adjustments may disturb track and balance. NOTE If any Test State has a “failed” or “partial” message next to the prompt or the AVA did not get a complete set of data for this Test State. Arrow back to the Test State and repeat the measurement until all Test States have “done” next to them. NOTE If the tracker is pointed towards the sun, the AVA may give a tracker error and may indicate “partial” next to the measurement condition. Re-orient the aircraft away from the sun, and repeat the measurement for that condition. NOTE Prior to initiating diagnostics, it may be helpful to review the measured data so that the diagnostic solution can be better interpreted and adjusted (see procedure 3 below). g. Exit measurement mode: a.) If measurements have been acquired for all seven flight conditions, the measurement screen will automatically exit. Highlight Finish and press DO. Highlight Diagnostics and press DO.

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