TB 1--1520--210--20--46
8.
a. Inspect aircraft DA Form 2408--16 to determine the current time since new of the tail rotor blades,
part number 204--011--702--15. Complete and submit DA Form 2410 copy 3 (use failure code 999) reporting
the current time since new and next higher assembly (NHA) information for each tail rotor blade installed. If
in local supply leave the current DA Form 2410 with the tail rotor blade, copy data from current DA Form 2410
to a new DA Form 2410 copy 3 (use failure code 999) by entering uninstalled in block 50 and completing the
remainder of the form per DA PAM 738--751 dated Mar 99.
NOTE
Temporary life extension is not authorized on part number 204--011--702--17
(NSN 1615--00--907--0842) tail rotor blades. The retirement life on these
blades remains at 1200 hours.
b. For those tail rotor blades that subsequently reach the normal 1200 hour retirement life, perform the
inspections in paragraphs 8.c and 8.d to determine if the retirement life can be temporarily extended to 1500
hours.
NOTE
Tail rotor hub removal is not required to perform the initial and recurring 75
hour blade inspections. IAW TM 55--1520--210--23--1 paragraph 5--96, tail
rotor balancing is not required if blades are removed and re--installed in the
same hub assembly. If reinstalling blades in the same hub, follow the proce-
dures in paragraph 5--93 to ensure that the blades and hardware are
installed in the same location. A maintenance test flight is required prior to
releasing aircraft for flight.
NOTE
In accordance with TM 55--1520--210--23 (para 5--117d), any crack de-
tected in any location on the blade is cause for replacement.
c. Initial inspection: When a blade reaches 1200 hours TSN, remove the part from the aircraft. Clean
blade IAW TM 55--1520--210--23, paragraph 5--116, and inspect IAW paragraph 5--117. In addition to the in-
spections in para 5--117, inspect the grip plate area around the bushing bolt holes for cracks using Eddy Cur-
rent (TM 1--1520--256--23, paragraph 2.41). Perform recurring inspections IAW the following:
(1) At each 50 hour interval, clean blades IAW TM 55--1520--210--23 (paragraph 1--19) and in-
spect IAW paragraph 5--117 (excluding paragraph 5--117f).
(2) At each 75 hour interval, remove the blade from the aircraft and inspect the retention bolt
holes IAW paragraph 5--117f. Inspect the grip plate area around the bushing bolt holes for cracks using Eddy
Current (TM 1--1520--256--23, paragraph 2.41).
NOTE
A plus 10% time variance is not authorized for the 50 or 75 hour recurring
inspections.
d. After the last flight of each mission day -- inspect blades as follows:
(1) Using a 10X magnifying glass, inspect the exposed area of the tail rotor blade grip plate for
cracks. Pay particular attention for cracks emanating from the area under the tail rotor grip flanges.
(2) Visually inspect the entire surface of the tail rotor blade for cracks, skin separation or other
damage. Pay particular attention to the area from the blade doublers (includes doublers) outward to station
25.
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