TB1--1520--238--20--124
IAW TB 1--1520--238--20--124." Inspect the bellcrank support bracket IAW paragraph 8c of this TB at each
10 hour/14 day MPG--1 until the AVIM level permanent repair is completed IAW paragraph 9b. ULLS--A units
will use an "800" inspection number for the recurring 10 hour/14 day PMS--1 inspection.
b. At the next 250 hour phase,
NOTE
AH--64A only-- schedule an AVIM level repair of the bellcrank support bracket.
NOTE
AH--64D only-- Contact the LOG POC IAW paragraph 16b for a replacement bellcrank
support bracket. A new or reworked bracket will be provided at no cost to the unit.
(1) Install rig pins at tail rotor control bellcranks P/N 7--311517052 (FS 164.33) and P/N
7--311524010 (FS 347.96).
(2) Disconnect push rod assemblies P/N 7--211524001--7 and P/N 7--211524001--9 from the tail
rotor control bellcrank (FS 216.25). Retain hardware for reinstallation.
(3) Remove the bellcrank by removing two cotter pins (P/N MS24665--153), two nuts (P/N
21224--4) and two bolts (P/N MS27576--4--17) from top of bellcrank. Remove cotter pin (P/N MS24665--153),
nut (P/N MS1224--4), and bolt (P/N MS27576--4--45) from bottom of bellcrank.
(4) Remove the bellcrank support bracket from aircraft by removing four bolts (2 each P/N
NAS6604H9 and 2 each P/N NAS6604H10) from bellcrank support bracket.
NOTE
AH--64A only-- completion of steps 9b(5) and 9b(6) will be performed by AVIM level re-
pair of the bellcrank support bracket.
NOTE
AH--64D only-- completion of steps 9b(5) and 9b(6) are note required if a new or repaired
bellcrank support bracket has been provided by the log PM for installation.
(5) Clamp the bellcrank support bracket securely to a wood 2x4 and install the 2x4 in bench vise.
Referencing the procedures received from the LAR or safety website, use a pin router or half--round hand
file to remove metal as required.
(6) Touch--up repaired area using MIL--C--5541 Class A (corrosion resistant coating) and MIL--
PRF--85582 Type 1/Class 2 (epoxy primer).
(7) Reinstall bellcrank support bracket in aircraft IAW TM 1--1520--238--23 or the IETM.
c. At the next 250 hour phase, perform the following AVIM/OLR level repair of the bellcrank.
(1) Install rig pins at tail rotor control bellcranks P/N 7--311517052 (FS 164.33) and P/N
7--311524010 (FS 347.96).
(2) Disconnect push rod assemblies P/N 7--211524001--7 and P/N 7--211524001--9 from the tail
rotor control bellcrank (FS 216.25). Remove bellcrank from the bellcrank support bracket. Retain hardware
for reinstallation.
(3) Referencing the rework procedures provided by the LAR, the bellcrank may be repaired to
a maximum depth of 0.060 inch and blended out approximately 12 to 1 in each direction. Bellcranks damaged
beyond these limits must be replaced.
(4) Conduct a dye penetrant inspection of the area and touch up the finish.
(5) Reinstall bellcrank IAW TM 1--1520--238--23 or the IETM.
(6) Reinstall the push rods P/N 7--211524001--7 and P/N 7--211524001--9 onto the tail rotor bell-
crank.
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