VIBRATION ABSORBER SPRINGS (MT)

Figure 4-4. Fluid in Honeycomb Core Panels and Structures (Sheet 2 of 2)

TM-1-1520-265-23 H-60 Helicopter Series Manual
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TM 1-1520-265-23 4.4.3.6 Inspection Procedure. Inspect designated areas, refer to Figure 4-4 for typical fluid entrapment and source/film placement. a. Position film and desired nameplate data for exposure number 1. b. Position X-ray tubehead for exposure number 1. c. Set X-ray unit to the values given in the Radiographic Inspection Data chart for exposure number 1. d. Make exposure number 1. e. Remove exposed film. f. Repeat inspection procedure (steps a. through e. above) for each exposure. g. Process and interpret film for defects as noted in paragraph 4.4.2 and as shown in Figure 4-4. 4.4.4 Backup Method. None required. 4.4.5 System Securing. The inspected area shall be cleaned as necessary. Refer to Post Cleaning and Restoration of Part or Area after NDI, paragraph 1.4.16. 4.5 VIBRATION ABSORBER SPRINGS (MT). 4.5.1 Description (Figure 4-1. Index No. 5). Vibration absorbers are installed in the nose section, cabin overhead, and under each of the drag beam support fairings. The other vibration absorber, located at the rear of the pylon, is not included in this inspection. This inspection is applicable to the steel spring elements which are included above. 4.5.2 Defects. This inspection is used to verify crack indications found visually on the vibration absorber springs. No cracks are allowed. 4.5.3 Primary Method. Magnetic Particle. 4.5.3.1 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 4-13

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