4.24.3.6. Inspection Procedure

Figure 4-24. Main Landing Gear Shock Strut Upper Cylinder

TM-1-1520-265-23 H-60 Helicopter Series Manual
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TM 1-1520-265-23 4.24.3.6. Inspection Procedure. Refer to Eddy Current Method, paragraph 1.4.11 and Figure 4-24. a. 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. NOTE Either probe identified in paragraph 4.24.3.1 may be used depending primarily on the ease of accessibility and user friendliness. If the probes are changed, steps 4.24.3.5 b. (1), (2), and (3) shall be repeated each time a change is made. 4.24.3.7. Marking and Recording of Inspection Results. Mark and record inspection results as required by paragraph 1.3. 4.24.4. Backup Method. None required. 4.24.5. System Securing. The main landing gear shock strut upper cylinder, if removed, requires installation in accordance with the applicable technical manuals listed in Table 1-1. 4.25. MAIN LANDING GEAR SHOCK STRUT LOWER STAGE PISTON (MT). 4.25.1. Description (Figure 4-1. Index No. 25). The shock strut consists of two pistons. The lower one absorbs the normal landing loads. 4.25.2. Defects. Defects may occur anywhere on the surface of the lower stage piston. Particular attention shall be directed to the bearing bore lug. No cracks are allowed. 4.25.3. Primary Method. Magnetic Particle. 4.25.3.1. NDI Equipment and Materials. (Refer to Appendix B.) a. Magnetic Particle Inspection Probe/Yoke b. Magnetometer c. Black Light d. Fluorescent Magnetic Particles, refer to Table 1-8 e. Consumable Materials, refer to Table 1-8 f. Aircraft Marking Pencil, refer to Table 1-8 NOTE Hand-held magnetic coil may be used. Refer to paragraph 1.4.8.1.2 and Figure 1-6. 4-58

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