TABLE 2-1.3. NORMAL ONE/REV VIBRATION LEVELS FWD AND AFT ROTOR A T 225 RPM

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
Page Navigation
125

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

Privacy Statement
Press Release
Contact