PITCH BEAM WASHER (MT).

Figure 2-26. Tail Rotor Pitch Control Rod Ends

TM-1-1520-265-23 H-60 Helicopter Series Manual
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TM 1-1520-265-23 2.27 PITCH BEAM WASHER (MT). 2.27.1 Description (Figure 2-1. Index No.27). The pitch beam washer is installed between the pitch beam retaining nut and pitch beam. 2.27.2 Defects. This inspection is used to verify crack indications found visually on the pitch beam washer. No cracks are allowed. 2.27.3 Primary Method. Magnetic Particle. 2.27.3.1 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. 2.27.3.2 Preparation of Helicopter. The helicopter shall be prepared for safe ground maintenance and the pitch beam washer removed in accordance with the applicable technical manuals listed in Table 1-1. 2.27.3.3 Access. Not applicable. 2.27.3.4 Preparation of Part. The part shall be thoroughly cleaned. Refer to Preparation of Part or Area for NDI, paragraph 1.4.4. 2.27.3.5 NDI Equipment Settings. Refer to Magnetic Particle Method, paragraph 1.4.8. 2.27.3.6 Inspection Procedure. A magnetic field shall be applied to the part perpendicular to the orientation of possible cracks. Positions required for this inspection are illustrated in Figure 2-27. a. Select AC on the AC/DC power switch. b. Place probe/yoke on part in position 1 as shown. c. Press the test switch and apply a light coat of magnetic particle media at the same time. Remove the media momentarily before removing the current. Current should be applied for no more than five seconds. d. Inspect for cracks using the black light. e. Demagnetize before moving to the next position. Refer to paragraph 2.27.3.8. f. Repeat steps a. through e. for position 2. 2-65

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