TM 1-1520-264-23
4.32.3.7
Marking and Recording of Inspection Results. Mark and record the inspection results as required by
paragraph 1.3.
4.32.4
Backup Method. None required.
4.32.5
System Securing. The tail landing gear fork, if removed, requires installation in accordance with the
applicable technical manuals listed in Table 1-1.
4.33 TAIL WHEEL (ET).
4.33.1
Description (Figure 4-1. Index No. 33)
. The tail wheel comes either with or without a grease fitting. The
wheels are the same for inspection purposes. The wheel assembly consists of male and female wheel halves.
4.33.2
Defects. This inspection is used to verify crack indications found visually on the tail wheel. No cracks are
allowed.
4.33.3
Primary Method. Eddy Current.
4.33.3.1
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
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 this procedure. If required, the tail wheel assembly shall be removed and disassembled in
accordance with the applicable technical manuals listed in Table 1-1.
4.33.3.3
Access. Not applicable.
4.33.3.4
Preparation of Part. The part shall be thoroughly cleaned. Refer to Preparation of Part or Area for NDI,
paragraph 1.4.4.
4.33.3.5
NDI Equipment Settings.
a.
Make the following initial settings on the Eddy Current Inspection Unit, NORTEC-19e
”
Frequency F1
- 200 KHz
F2
- off
HdB
- 57.0
VdB
- 69.0
Rot
- 56
Probe drive
- mid
4-74
