TB 1--1520--237--20--232
(a) Depress retaining pin to release the retaining ball mechanism and fill the bolt with CPC.
(b) Apply CPC through one ball hole (while working retaining pin) until excess is seen at the
opposite hole. Rotate the bolt 180 degrees and repeat the procedure.
(c) Spray C PC into both the cotter pin hole and the hole at the end of the bolt. Lightly wipe
excess compound from the threads and retaining ball area.
(d) Apply CPC lightly to the inner cavity of the MS21244-12 and -14 nuts. Do not apply CPC
to nut P/N MS9364-17.
(2) Apply CPC, Item 109, Appendix D, TM 1-1520-237-23-9 or item 126, Appendix D, TM
1-1520-250-23-6, lightly around the outside of the bolt retaining ball area and threads.
NOTE
If CPC (Grade 2), MIL-C-16173, is not available, substitute with MIL-C-16173 (Grade 3), NSN
8030-00-244-1296 for external application on bolt threads and retaining balls.
(3) Reinstall nut IAW TM 1-1520-237-23-6 or TM 1-1520-250-23-5.
WARNING
Except for nut, P/N MS9364-17, NSN 5310-00-946-8342, no nut that is silver in color will
be installed.
WARNING
When torquing nut, slowly approach installation torque. If the customary sharp rise in
torque is not noted, the bolt or nut feels as though the metal is yielding, the bolt and
nut must be replaced.
(4) When all 15 pivot bolts and attaching hardware have been reinstalled, remove protective
bubble wrap from the swashplate links. Using the cargo straps carefully lower swashplate and guide connect-
ing links into position. Re-install expandable pins IAW para 5-4-21, TM 1-1520-237-23-3 or para 5.11, TM
1-1520-250-23-3.
(5) Re-install each lower main rotor pitch change link rod end bearing into respective indexed
swashplate lug IAW para 5-4-17, TM 1-1520-237-23-3 or para 5.10, TM 1-1520-250-23-3.
(6) Re-install RH and LH engine air inlet IAW para 4-4-4, TM 1-1520-237-23-3 or para 4.4.1,
TM 1-1520-250-23-3.
(7) Turn on all electric and hydraulic power IAW para 1-6-13 and 1-6-12, TM 1-1520-237-23-1
or para 1.43.17, TM 1-1520-250-23-1.
(8) Perform flight control hydraulic system check as outlined in applicable maintenance test
flight manual (TM 1-1520-237-MTF, TM 1-1520-250-MTF or TM 1-1520-253-MTF).
(9) Turn off all electric and hydraulic power IAW para 1-6-12 and 1-6-13, TM 1-1520-237-23-1
or para 1.43.17, TM 1-1520-250-23-1.
(10)Re-install main transmission fore and aft covers IAW para 2-4-116, TM 1-1520-237-23-2 or
para 2.37.15, TM 1-1520-250-23-2.
(11) Close the main rotor pylon sliding cover.
a. Parts required. Items cited in paragraph 7 and this paragraph may be required to replace defective
items:
5
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