TB 1
15
6. Assembly Components to be inspected.
Part No.
Nomenclature
7-311421036
1615-01-l 54-7080
Head, Rotary Wing
7-311421036-7
Head, Rotary Wing
l/-l 3
Head, Rotary Wing
7-311340001-3
1615-01-l 55-6583
T/R Gearbox
T/R Gearbox
T/R Output Shouldered Shaft
7-311340092
3040-01-l 72-8192
7.
Parts to be Inspected.
Nomenclature
Part No.
Fork Assembly
1
7-511421008
Fork Assembly
5307-01-l 77-5805
Stud, Locking
Nut, Self-Locking
Nut, Self-Locking
531 O-01 -440-4438
8. Inspection Procedures.
NOTE
Inspection 8.a. is performed on the aircraft with nothing
disassembled. The following 600 inch-pound torque check
is only used to determine if the studs are in a loose
condition.
a. No later than next 10 hour/l4 day inspection, perform torque check of three nuts, P/N
securing the T/R Fork to the T/R Gearbox Output Shaft (item 5, paragraph
of reference 13).
Using a torque wrench set to 600 inch-pounds, attempt to turn each nut in a clockwise direction. Any
rotation of the nut before 600 inch-pounds is unacceptable.
b. If nut rotation does not occur before 600 inch-pounds, verify proper indexing of tail rotor fork using
paragraphs 8.d. through
no later than next 250 hour phase inspection.
c. If rotation of any of the nuts occurs before 600 inch-pounds, verify proper indexing of tail rotor fork
using paragraphs 8.d. through
prior to the next flight.
NOTE
Task 5.61 of reference 13 refers to a single stud marked
with an
on the end. An
on the stud may be unreliable
and should be ignored. Positive verification of alignment
shall be accomplished prior to each T/R Head installation.
d. Locate the number 1 hole in the T/R Fork. The number 1 hole is the hole adjacent to the Teeter
Stop Arm. For clarification, refer to item 3 in paragraph 5.61.3(a) of reference 13. Apply torque stripe
paint around this hole (not the stud).
3
