Backup Method. None required.
System Securing. The main rotor damper trunnion, if removed, requires installation in accordance with the
applicable technical manuals listed in Table 1-1.
MAIN ROTOR DAMPER ROD END (MT).
Description (Figure 2-1. Index No. 15). The main rotor damper rod end provides for attachment of the damper
assembly to the lead lag link.
Defects. This inspection is used to verify crack indications found visually on the main rotor damper rod end. No
cracks are allowed.
Primary Method. Magnetic Particle.
NDI Equipment and Materials. (Refer to Appendix B.)
Magnetic Particle Inspection Probe/Yoke
Fluorescent Magnetic Particles, refer to Table 1-8
Consumable Materials, refer to Table 1-8
Aircraft Marking Pencil, refer to Table 1-8
Hand-held magnetic coil may be used. Refer to paragraph 22.214.171.124.2 and Figure 1-6.
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 applicable positions of this procedure. If required, the main rotor damper rod end shall be
removed in accordance with the applicable technical manuals listed in Table 1-1.
Access. Not applicable.
Preparation of Part. The part shall be thoroughly cleaned. Refer to Preparation of Part or Area for NDI,
NDI Equipment Settings. Refer to Magnetic Particle Method, paragraph 1.4.8.
Inspection Procedure. A magnetic field shall be applied to the part perpendicular to the orientation of
possible cracks. The position required for this inspection is illustrated in Figure 2-15.
Select AC on the AC/DC power switch.
Place probe/yoke on part in position 1 as shown.