BHT-212-MM-1
5-00-00
15 NOV 2018 Rev. 16 Page 125
Export Classification C, ECCN EAR99
DO NOT TO REMOVE ANY PARENT MATERIAL
FROM THE SKIN/DOUBLERS DURING SANDING
OPERATION.
7. If edge voids between grip plate/doublers/skin are found,
determine depth and length by using 0.0015 inch (0.038 mm)
feeler gauge. If edge voids are near outboard tip of grip plate /
doublers, also carefully tap inspect suspect area. Refer to
BHT-212-CR&O, Chapter 62 for void repair limits and
inspection/repair instructions. If no voids are detected, continue
with step 8.
8. Refinish the sanded area as per BHT-212-MM-6,
Chapter 62.
9. Following the inspection, apply a light coat of preservative
oil (C-125) to all surfaces of blade.
Chapter 64 TAIL ROTOR HUB ASSEMBLY
— Detailed Visual Inspection
1. Flapping bearings 212-010-723-001 or 212-010-768-001
exposed outer races for cracks using a 3X magnifying glass.
Any crack is cause for immediate replacement of both bearings.
2. Inspect tail rotor yoke 212-010-704, 212-010-744, or
212-011-702.
TAIL ROTOR STATIC STOP
ASB 212-96-100 and
ASB 212-96-101
1. Inspect flapping stop 212-010-738 or 212-011-713 for
yielding as noted in Chapter 64, to determine if tail rotor yoke
assembly may have been exposed to bending.
If any doubt exists as to the serviceability of these components,
contact Product Support Engineering.
5-22. EACH 25 HOURS OF FLIGHT OPERATION (CONT)
DATA REFERENCE INSPECTION TASK DESCRIPTION
INITIAL
MECH OTHER
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