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INSTALL TUNNEL CONTROL ARMS     (Continued) - TM-55-1520-240-23-9_953
INSTALL TUNNEL CONTROL ARMS     (Continued) - TM-55-1520-240-23-9_955

TM-55-1520-240-23-9 CH-47D Heilcopter Manual
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TM 55-1520-240-23-9 11-241 INSTALL TUNNEL CONTROL ARMS     (Continued) 11-241 INSTALL CONTROL ARMS AT STA 201.00, 241.00, 281.00, 321.00, AND 361.00 WARNING FLIGHT SAFETY PARTS This is an installation critical flight safety part. All aspects of its assembly and installation must be ensured at each joint connection and mounting to the airframe. Ensure that bearings are properly installed and staked at each end of the walking beam. Ensure walking beam hub bearings are serviceable, secure and properly installed. Ensure the locating pads on the walking beam forging are installed facing up at all locations. Ensure the slip bushings are installed when attaching the adjacent control rods at each end of the walking beam assembly. Ensure proper attaching hardware (impedance type bolt, nut, and washers) is installed including verification of bolt head orientation, torque, and installation of cotter pins. Loose attachments within flight control primary linkage will degrade aircraft control.  Missing components will cause loss of control. CAUTION Bellcrank must be positioned as indicated, with side marked TOP facing up; otherwise, serious damage to components can occur. 12. Position control arm (15) on idler (16) with pads (17) and the word TOP up. 13. Install bolt (18), two washers (19 and 20), and nut (21).  Torque nut  85 to 125 inch-pounds. Install cotter pin (22). 14. Check bolt (18).  Bolt shall not rotate with torque less than  10 inch-pounds.  Bolt shall have no axial looseness.  If bolt rotates or is loose, add washer under nut and repeat step 13. 11-938 Change 1







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