TM 1-1520-265-234.31.3.7. Marking and Recording of Inspection Results. Mark and record inspection results as required by paragraph1.3.4.31.4. BackupMethod. Fluorescent Penetrant, refer to paragraph 1.4.7.4.31.5. SystemSecuring. The yoke, if removed, requires installation in accordance with the applicable technicalmanuals listed in Table 1-1.4.32. TAIL LANDING GEAR FORK (ET).4.32.1. Description(Figure4-1.IndexNo.32). The fork assembly, secured to the yoke assembly is the attachmentpoint for the tail wheel and allows the wheel to swivel through 360° for ground control.4.32.2. Defects. Defects may occur anywhere on the surface of the tail landing gear fork. No cracks are allowed.4.32.3. PrimaryMethod. Eddy Current.4.32.3.1. NDI Equipment and Materials. (Refer to Appendix B.)a.Eddy Current Inspection Unitb.Probe, straight, shielded surface, 100 KHz-500 KHzc.Probe, right angle, shielded surface, 100 KHz-500 KHz, 90" 1/2 inch dropd.Cable Assemblye.Reference Block, three-notched aluminum (0.008, 0.020, 0.040 EDM notches)f.Teflon Tape, refer to Table 1-8g.Aircraft Marking Pencil, refer to Table 1-84.32.3.2. Preparation of Helicopter. The helicopter shall be prepared for safe ground maintenance. A partial inspectionfor cause (visual indications, sites of mechanical damage, corrosion, etc.) may be performed on all exposed surfaces ofthe installed part using this procedure. If required, the tail landing gear fork shall be removed in accordance with theapplicable technical manuals listed in Table 1-1.4.32.3.3. Access. Not applicable.4.32.3.4. Preparation of Part. The part shall be thoroughly cleaned. Refer to Preparation of Part or Area for NDI,paragraph 1.4.4.4.32.3.5. NDI Equipment Settings.a.Make the following initial settings on the Eddy Current Inspection Unit, NORTEC-19eII.Frequency F1- 200 KHzF2- offHdB- 57.0VdB- 69.0Rot- 560Probe drive- mid4-74
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