184.108.40.206 Preparation of Helicopter. The helicopter shall be prepared for safe ground maintenance and the cargo hook
removed in accordance with the applicable technical manuals listed in Table 1-1.
220.127.116.11 Access. Not applicable.
18.104.22.168 Preparation of Part. The part shall be thoroughly cleaned. Refer to Preparation of Part or Area for NDI,
22.214.171.124 NDI Equipment Settings. Refer to Magnetic Particle Method, paragraph 1.4.8.
126.96.36.199 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 4-35.
Select AC on the AC/DC power switch.
Place probe/yoke on part in position 1 as shown.
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.
Inspect for cracks using the black light.
Demagnetize before moving to the next position. Refer to paragraph 188.8.131.52.
Repeat steps a. through e. for position 2.
184.108.40.206 Marking and Recording of Inspection Results. Mark and record inspection results as required by paragraph 1.3.
220.127.116.11 Demagnetization. With the switch remaining in the AC position, place the probe/yoke legs in the same position
used for magnetizing. Press the test switch and withdraw the probe/yoke from the part for a distance of two feet before
releasing the switch.
4.35.4 Backup Method. None required.
4.35.5 System Securing. Clean the cargo hook thoroughly to remove all residual magnetic particle media. Refer to Post
Cleaning and Restoration of Part or Area After NDI, paragraph 1.4.16. The cargo hook requires installation in
accordance with the applicable technical manuals listed in Table 1-1.
4.36 FERROUS BOLTS AND PINS CONTAINED WITHIN THE AIRFRAME AND LANDING GEAR SYSTEM (MT).
4.36.1 Description (Figure 4-1. Index No. 36). Refer to paragraph 2.3 for inspection procedure.
4.37 NONFERROUS BOLTS AND PINS CONTAINED WITHIN THE AIRFRAME AND LANDING GEAR SYSTEM (PT).
4.37.1 Description (Figure 4-1. Index No. 37). Refer to paragraph 2.4 for inspection procedure.