TM 1-1520-265-23NOTEEither probe identified in paragraph 4.32.3.1 may be used depending primarily on the ease ofaccessibility and user friendliness. If the probes are changed, steps 4.32.3.5 b. (1), (2), and (3)shall be repeated each time a change is made.4.32.3.7. Marking and Recording of Inspection Results. Mark and record inspection results as required by paragraph1.3.4.32.4. BackupMethod. Fluorescent Penetrant, refer to paragraph 1.4.7.4.32.5. SystemSecuring. The fork, if removed, requires installation in accordance with the applicable technical manualslisted in Table 1-1.4.33. TAIL LANDING GEAR LOCK ACTUATOR ASSEMBLY (MT).4.33.1. Description(Figure4-1.IndexNo.33). The wheel lock and electrically-operated actuator, secured to the yokeassembly, secures the tail wheel in the trailing position when the helicopter is parked or in flight.4.33.2. Defects. This inspection is used to verify crack indications found visually on the tail locking gear parts. Nocracks are allowed.4.33.3. PrimaryMethod. Magnetic Particle.4.33.3.1. NDI Equipment and Materials. (Refer to Appendix B.)a.Magnetic Particle Inspection Probe/Yokeb.Magnetometerc.Black Lightd.Fluorescent Magnetic Particles, refer to Table 1-8e.Consumable Materials, refer to Table 1-8f.Aircraft Marking Pencil, refer to Table 1-8NOTEHand-held magnetic coil may be used. Refer to paragraph 1.4.8.1.2 and Figure 1-6.4.33.3.2. 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 applicable positions of this procedure. If required, the tail landing gear lock mechanism shall beremoved in accordance with the applicable technical manuals listed in Table 1-1.4.33.3.3. Access. Not applicable.4-76
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