TM 1-1520-264-23
NOTE
Either probe identified in paragraph 4.33.3.1 may be used depending primarily on the ease of accessibility
and user friendliness. If the probes are changed, steps 4.33.3.5 b. (1), (2), and (3) shall be repeated each
time a change is made.
4.33.3.7 Marking and Recording of Inspection Results. Mark and record the inspection results as required by paragraph
1.3.
4.33.4
Backup Method. None required.
4.33.5
System Securing. The tail wheel, if removed, requires assembly and installation in accordance with the
applicable technical manuals listed in Table 1-1.
4.34
TAIL LANDING GEAR SHOCK STRUT (MT).
4.34.1
Description (Figure 4-1. Index No. 34).
The tail landing gear shock strut is attached to the aft end of the
trailing arm to the aft upper area of the empennage. It absorbs shock generated by the tail landing gear.
4.34.2
Defects. This inspection is used to verify crack indications found visually on the tail landing gear shock strut.
No cracks are allowed.
4.34.3
Primary Method. Magnetic Particle.
4.34.3.1 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.
4.34.3.2 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 shock strut shall be
removed in accordance with the applicable technical manuals listed in Table 1-1.
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