TM 1-1520-265-232-14 Change 3NOTEEither probe identified in paragraph 2.7.3.1 may be used depending primarily on theease of accessibility and user friendliness. If the probes are changed, steps 2.7.3.5b. (1), (2), and (3) shall be repeated each time a change is made.2.7.3.7 Marking and Recording of Inspection Results. Mark and record inspection results asrequired by paragraph 1.3.2.7.4 BackupMethod. None required.2.7.5 SystemSecuring. The spindle, if removed, requires installation in accordance with theapplicable technical manuals listed in Table 1-1.2.8 ANTIFLAP BRACKET (ET).2.8.1 Description(Figure2-1,IndexNo.8). The antiflap brackets are installed on each of the fourmain rotor spindle modules next to the hub. The antiflapping assemblies prevent the blades fromflapping when the main rotor head is slowing down or stopped.2.8.2 Defects. The inspection is used to verify crack indications found visually on the antiflapbracket. No cracks are allowed.2.8.3 PrimaryMethod. Eddy Current.2.8.3.1 NDI Equipment and Materials. (Refer to Appendix B.)a. Eddy Current Inspection Unitb. Probe, straight, shielded surface, 2 MHzc. Probe, right angle, shielded surface, 2 MHz, 90_ 1/2 inch dropd. Cable Assemblye. Adapter, probe, 2 MHzf. Reference Block, three-notched titanium (0.008, 0.020, 0.040 EDM notches)g. Teflon Tape, refer to Table 1-8h. Aircraft Marking Pencil, refer to Table 1-82.8.3.2 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.) maybe performed on all exposed surfaces of the installed part using this procedure. If required, theantiflap bracket shall be removed in accordance with the applicable technical manuals listed in Table1-1.2.8.3.3 Access. Access to the antiflap bracket is from the L/R engine cowl (Figure 1-4, Items 3T-7and 4T-8).2.8.3.4 Preparation of Part. The part shall be thoroughly cleaned. Refer to Preparation of Part orArea for NDI, paragraph 1.4.4.
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