TM 1-1520-265-233.3.3.7 Marking and Recording of Inspection Results. Mark and record inspection results as required by paragraph 1.3.3.3.4 BackupMethod. Fluorescent Penetrant, refer to paragraph 1.4.7.3.3.5 SystemSecuring. The intermediate gearbox, if removed, requires installation in accordance with the applicabletechnical manuals listed in Table 1-1.3.4 TAIL ROTOR DRIVE SHAFT (ET).3.4.1 Description(Figure3-1.IndexNo.4). The tail rotor is driven by a series of seven shafts. The shafts run from thetail take off flange on the rear of the main transmission to the intermediate gearbox. The tail rotor drive shaft then runsfrom the intermediate gearbox to the tail gearbox.3.4.2 Defects. This inspection is used to verify crack indications found visually on the tail rotor drive shaft. No cracksare allowed.3.4.3 PrimaryMethod. Eddy Current.3.4.3.1 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 1-83.4.3.2 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 rotor drive shaft shall be removed in accordance with theapplicable technical manuals listed in Table 1-1.3.4.3.3 Access. Accessibility of the tail rotor drive shaft varies considerably. Refer to Figure 1-4 and Table 1-2 to locateapplicable access provisions.3.4.3.4 Preparation of Part. The part shall be thoroughly cleaned. Refer to Preparation of Part or Area for NDI,paragraph 1.4.4.3-8
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