TM 1-1520-265-23
2.25.3.6 Inspection Procedure. Refer to Eddy Current Method, paragraph 1.4.11 and Figure 2-25.
a.
Place probe on a good area in the inspection location and null. Adjust phase as required to obtain horizontal lift-
off.
b.
Inspect the part.
c.
Any signal similar to the notches in the test block are cause for rejection.
NOTE
Either probe identified in paragraph 2.25.3.1 may be used depending primarily on the ease of
accessibility and user friendliness. If the probes are changed, steps 2.25.3.5 b. (1), (2), and (3)
shall be repeated each time a change is made.
2.25.3.7 Marking and Recording of Inspection Results. Mark and record inspection results as required by paragraph 1.3.
2.25.4 Backup Method. Fluorescent Penetrant, refer to paragraph 1.4.7.
2.25.5 System Securing. The tail rotor pitch horn, if removed, requires installation in accordance with the applicable
technical manuals listed in Table 1-1.
2.26 TAIL ROTOR PITCH CONTROL ROD ENDS (MT).
2.26.1 Description (Figure P-1. Index No. 96). The pitch control links are installed on the tail rotor I head assembly.
Each link connects an arm of the pitch beam to a pitch control horn on the blade.
2.26.2 Defects. This inspection is used to verify crack indications found visually on the tail rotor pitch control rod ends.
No cracks are allowed.
2.26.3 Primary Method. Magnetic Particle.
2.26.3.1 NDI Equipment and Materials. (Refer to Appendix B.)
a.
Magnetic Particle Inspection Probe/Yoke
b.
Magnetometer
c.
Black Light
d.
Fluorescent Magnetic Particles, refer to Table 1-8
e.
Consumable Materials, refer to Table 1-8
f.
Aircraft Marking Pencil, refer to Table 1-8
NOTE
Hand-held magnetic coil may be used. Refer to paragraph 1.4.8.1.2 and Figure 1-6.
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