TASK 3 - BALANCE MAIN ROTOR

TASK 2 - FLAT TRACK MAIN ROTOR ON THE GROUND - TM-1-6625-724-13P_425

TM-1-6625-724-13P Aviation Vibration Analyzer Manual
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0070 00 TM 1-6625-724-13&P 0070 00-12 TASK 3 - BALANCE MAIN ROTOR - INITIAL PROCEDURE 1: PREPARATION Perform task 2, Flat Track Main Rotor on the Ground. PROCEDURE 2: PERFORM INITIAL MEASUREMENT a. Use cursor keys to highlight Aircraft Type, then press DO. b. Use cursor keys to highlight aircraft type based on table 2, then press DO. c. Tail Number is highlighted. Press DO. d. Use cursor keys to highlight a tail number used in task 2, then press DO. e. Flight Plan is highlighted. Press DO. f. Use cursor keys to highlight INITIAL. Press DO. g. Enter the Measure mode by pressing F1. Verify that Test State IDLE is highlighted. h. Press DO when the aircraft is stable at the highlighted selection. Re-verify that the aircraft is at the required Test State (IDLE, FPG100, or Hover) and press DO again. Perform this operation each time a measurement is completed and another Test State is highlighted. The AVA will acquire track and vibration data at each Test State and then return to the selection menu. i. After the last measurement is completed, press DO on Finish, then press DO on Diagnostics. If measurements are within specified limits, press QUIT to Main Menu and perform task 4, Track Main Rotor In Flight. j. If measured values exceed specifications, press DO to calculate a solution. Evaluate the improvements obtainable through recommended corrections. Perform all corrections as shown, ensuring that you display all screens of a multiple screen solution. k. Do not use a partial set of adjustments. If changes to the recommended corrections are desired, use the Edit Adjustables and Edit Defaults options. The AVA will calculate a new set of corrections, use view predictions to compare the new set of adjustments to the default solution to ensure the vibration is being reduced. Use all of the new corrections. l. After corrections are installed, take the measurements again to verify improvements. m. After more than one measurement has been taken, trend flights to verify if the hover lateral vibration is being reduced. PROCEDURE 3: PITCH LINK ADJUSTMENTS NOTE When adjusting the pitch link on the AH-1SS, turn as shown in figure 8 and count flats/turn at the specified location. a. Turn barrel the specified amount displayed on the CADU. b. Verify corrections by completing another ground run at 100% Nr, flat pitch. c. Make appropriate logbook entry on the pitch control links and balance weighs that were changed, if any. Figure 8. Pitch Link

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