TM 1-1520-265-23
NOTE
Either probe identified in paragraph 4.32.3.1 may be used depending primarily on the ease of
accessibility and user friendliness. If the probes are changed, steps 4.32.3.5 b. (1), (2), and (3)
shall be repeated each time a change is made.
4.32.3.7. Marking and Recording of Inspection Results. Mark and record inspection results as required by paragraph
1.3.
4.32.4. Backup Method. Fluorescent Penetrant, refer to paragraph 1.4.7.
4.32.5. System Securing. The fork, if removed, requires installation in accordance with the applicable technical manuals
listed in Table 1-1.
4.33. TAIL LANDING GEAR LOCK ACTUATOR ASSEMBLY (MT).
4.33.1. Description (Figure 4-1. Index No. 33). The wheel lock and electrically-operated actuator, secured to the yoke
assembly, secures the tail wheel in the trailing position when the helicopter is parked or in flight.
4.33.2. Defects. This inspection is used to verify crack indications found visually on the tail locking gear parts. No
cracks are allowed.
4.33.3. Primary Method. Magnetic Particle.
4.33.3.1. 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.
4.33.3.2. 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 applicable positions of this procedure. If required, the tail landing gear lock mechanism shall be
removed in accordance with the applicable technical manuals listed in Table 1-1.
4.33.3.3. Access. Not applicable.
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