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VIBRATION FREQUENCY IDENTIFIED AS 225 RPM (1 /REV) (Continued)
2-1.4   VIBRATION   FREQUENCY   IDENTIFIED   AS   675   CYCLES/MIN   (3/REV)

TM-55-1520-240-T-1 CH-47D Heilcopter Manual
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TM  55-1520-240-T 2-1.3   VIBRATION   FREQUENCY   IDENTIFIED   AS   225   RPM   (1/REV)   (Continued) 2-1.31 USE “0” MARKS PITCH LINK ADJUSTMENT AS INPUT TO PITCH  LINK-LATERAL  PRO- GRAM. USING  THE  PITCH  LINK-LATERAL  PROGRAM,  DETERMINE  VIBREX  TIP WEIGHT  CORRECTION  TO  COMPENSATE  FOR  ANY  PITCH  LINK  ADJUST- MENT AND THE RECORDED LATERAL IMBALANCE AT 130 KNOTS. ADJUST VIBREX  TIP  WEIGHTS  (TM  55-1520-240-23).  HAVE  PILOT  ESTABLISH  130 KNOT  CRUISE  PROFILE  RECORD  BLADE  TRACK  AND  MEASURE  VIBRATION. ARE VERTICAL AND LATERAL VIBRATIONS WITHIN RANGE OF TABLE 2- 1.3? ARE RECORDED VERTICAL Vl- BRATION  LEVELS  WITHIN RANGE  OF  TABLE  2-1.3? ADJUST  VIBREX  BLADE  TIP WEIGHTS (TM 55-1520-240-23) TO  CORRECT  LATERAL  VIBRA- TION, USING LATEST 130 KNOT VIB INPUT DATA IN PC PITCH LINK-LATERAL PRO- GRAM. MAKE NECESSARY AD- JUSTMENTS  AND  PERFORM THIS  TASK  AGAIN  BEGINNING AT 130 KNOT CRUISE. LAND  HELlCOPTER  AND  SHUT DOWN ENGINES. OBSERVE RE- CORDED BLADE TRACK AT 130 KNOTS. DID ANY BLADE CLIMB OR DIVE? CHECK  TRIM  TAB  SETTING  ON CLIMBING OR DIVING BLADE (TM 55-1520-240-23). IF TRIM TAB  IS  SET  CORRECTLY  AS STENCILED, REPLACE BLADE. IF TRIM  TAB  SETTING  IS  lNCOR- RECT,  RESET  TRIM  TAB  WITH TAB  BENDING  TOOL  AND  PER- FORM THIS TASK AGAIN BE- GINNING  AT  130  KNOT  CRUISE. 1/REV  VIBRATION  LEVELS  ARE SATISFACTORY. INSPECT  ROTOR  HEAD  ASSY. REF TM 55-1520-240-23. TABLE 2-1.3. NORMAL ONE/REV VIBRATION LEVELS FWD AND AFT ROTOR A T 225 RPM FLIGHT  PROFILE ACCELEROMETER LOCATION HOVER 130 KT 155 KT FWD  VERTICAL 0 TO 0.2 0.2 TO 0.4 0.2 TO 0.6 FWD LATERAL 0.1 TO 0.3 0.2 TO 0.4 0.3 TO 0.5 AFT   VERTICAL 0 TO 0.2 0.2 TO 0 4 0.2 TO 0.6 AFT LATERAL 0.1 TO 0.3 0.2 TO 0.4 0.3 TO 0.5 END OF TASK Change  5      2-7







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