TM 1-1520-264-23
2.13
MAIN ROTOR DAMPER (ET).
2.13.1
Description (Figure 2-1. Index No. 13). Two dampers are attached between each pitch housing and its lead lag
link. The dampers are used to control the lead lag movement of the rotor blades and to prevent mass imbalance
(unequal blade spacing) and for main rotor blade phase adjustment.
2.13.2
Defects. This inspection is used to verify crack indications found visually on the main rotor damper. No cracks
are allowed.
2.13.3
Primary Method. Eddy Current.
2.13.3.1
NDI Equipment and Materials. (Refer to Appendix B.)
a.
Eddy Current Inspection Unit
b.
Probe, straight, shielded surface, 100 KHz-500 KHz
c.
Probe, right angle, shielded surface, 100 KHz-500 KHz, 90 °
1/2 inch drop
d.
Cable Assembly
e.
Reference Block, three-notched aluminum (0.008, 0.020, and 0.040 EDM notches)
f.
Teflon Tape, refer to Table 1-8
g.
Aircraft Marking Pencil, refer to Table 1-8
2.13.3.2
Preparation of Helicopter. The helicopter shall be prepared for safe ground maintenance. A partial inspection
for cause (visual indications, sites of mechanical damage, corrosion, etc.) may be performed on all exposed surfaces of
the installed part using this procedure. If required, the main rotor damper shall be removed in accordance with the
applicable technical manuals listed in Table 1-1.
2.13.3.3
Access. Not applicable.
2.13.3.4
Preparation of Part. The part shall be thoroughly cleaned. Refer to Preparation of Part or Area for NDI,
paragraph 1.4.4.
2.13.3.5
NDI Equipment Settings.
a.
Make the following initial settings on the Eddy Current Inspection Unit, NORTEC-19e11.
Frequency F1
- 200 KHz
F2
- off
HdB
- 57.0
VdB
- 69.0
Rot
- 56°
Probe drive - mid
LPF
- 100
HPF
-0
H Pos
- 80%
V Pos
- 20%
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