Correction Procedures

TB 1-1520-238-20-77

9. Correction Procedures.

a. Safe Helicopter per paragraph 1.57 of reference 13.a.

NOTE

To prevent unnecessary damage to screw, use of proper procedures and tools is

required during removal of tip cap. After removing tip cap screws, visually inspect

for any cracks, thread damage, obvious wear or physical damage. Apply thread

anti-seize compound, MIL-T-83483, to screw threads before reinstalling tip cap.

b. Remove main rotor blade leading edge tip cap per paragraph 5.13 of reference 13.a. Retain all

undamaged screws for reuse during re-assembly. Replace all damaged screws using standard ordering

procedures.

NOTE

Task is to be completed for each individual weight assembly before beginning task

on next weight assembly. Visually inspect studs for cracks, thread damage,

obvious wear, or physical damage. Do not remove weights from blade assembly.

c. Remove the two (2) nuts (MS21042-6) that secure the aft weight support fitting and discard. Apply

corrosion preventative compound (CPC) MIL-C-16173, Class 1, Grade 2 (soft film) to the threaded as well as

shank portion of both AFT studs during assembly. Reuse the existing washers (AN960C616L). Install two (2)

new nuts (NAS1 291 C6M) listed in paragraph 10 and torque the nuts to 205-225 inch-pounds. Use torque

wrench.

d. Remove the three (3) nuts (MS21042L5) that secure the forward weight support fitting and discard.

Apply corrosion preventative compound (CPC) MIL-C-16173, Class 1, Grade 2 (soft film) to the threaded as

well as shank portion of the three FWD studs during assembly. Reuse the two (2) existing washers

(AN960C516L) and the one (1) washer (HS5415-0001) on the leading edge stud. Position the HS5415-0001

washer to match the contour of the leading edge. Install three (3) new nuts (NAS1291 C5M) listed in paragraph

10. Torque the nuts to 160-180 inch-pounds. Use torque wrench.

NOTE

The HS541 5-0001 washer may be trimmed, if necessary, to match the contour of

the leading edge. This is to ensure proper fit of the leading edge tip cap.

e. Reinstall the leading edge tip cap per paragraph 5.13 of reference 13.a.

10. Supply/Pans and Disposition.

a. Parts Required.

NOMENCLATURE

PART NUMBER

NSN

Nut, Self-Locking, AFT Fitting

NAS1291 C6M

5310-00-879-0669

Nut, Self-Locking, FWD Fitting

NAS1291C5M

5310-00-882-6479

Screw, Close Tolerance

HS4396-3T4

5305-01-224-6693

Screw, Close Tolerance

HS4396-3T5

5305-01 -219-8718

b. Requisitioning Instructions. Requisition replacement parts through normal supply channels using

normal supply procedures. All requisitions shall use project code " XB8 " per this TB.