Assembly Components to be inspected

TB 1

6. Assembly Components to be inspected.

Part No.

Nomenclature

7-311421036

1615-01-l 54-7080

Head, Rotary Wing

1615-01-224-6951

7-311421036-7

Head, Rotary Wing

1615-01-307-0156

l/-l 3

Head, Rotary Wing

7-311340001-3

1615-01-l 55-6583

T/R Gearbox

1615-01-254-7793

T/R Gearbox

T/R Output Shouldered Shaft

7-311340092

3040-01-l 72-8192

Parts to be Inspected.

Nomenclature

Part No.

Fork Assembly

1615-01-221-2932

7-511421008

1615-01-461-5084

Fork Assembly

5307-01-l 77-5805

Stud, Locking

5310-01-184-0357

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).