TM 1-1520-265-23a.Place probe on a good area in the inspection location and null. Adjust phase as required to obtain horizontal lift-off.b.Inspect the part.c.Any signal similar to the notches in the test block are cause for rejection.NOTEEither probe identified in paragraph 2.16.3.1 may be used depending primarily on the ease ofaccessibility and user friendliness. If the probes are changed, steps 2.16.3.5 b. (1), (2), and (3)shall be repeated each time a change is made.2.16.3.7 Marking and Recording of Inspection Results. Mark and record inspection results as required by paragraph 1.3.2.16.4 BackupMethod. Fluorescent Penetrant, refer to paragraph 1.4.7.2.16.5 SystemSecuring. The lower link, if removed, requires installation in accordance with the applicable technicalmanuals listed in Table 1-1.2.17 BIFILAR VIBRATION ABSORBER (ET).2.17.1 Description(FigureP-1.IndexNo.17). The bifilar vibration absorber absorbs vibrations and stresses. It not onlycontributes to longer life of all components, but to a smoother ride for the crew and passengers.2.17.2 Defects. This inspection is used to verify crack indications found visually on the bifilar vibration absorber. Nocracks are allowed.2.17.3 PrimaryMethod. Eddy Current.2.17.3.1 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 1-82.17.3.2Preparation of Helicopter. The helicopter shall be prepared for safe ground maintenance. A partialinspection for cause (visual indications, sites of mechanical damage, corrosion, etc.) may be performed on all exposedsurfaces of the installed part using this procedure. If required, the bifilar vibration absorber shall be removed inaccordance with the applicable technical manuals listed in Table 1-1.2-35
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