18.104.22.168 Preparation of Helicopter. The helicopter shall be prepared for safe ground maintenance. Partial inspection for
cause (visual indications, sites of mechanical damage, corrosion, etc.) may be performed on all exposed surfaces of the
installed part using this procedure. if required, the connecting link shall be removed in accordance with the applicable
22.214.171.124 Access. Access is obtained through transmission work platforms, flight controls closet panel, or cockpit. See
9, 27, 34, and/or 47; MH-47: 16, 17, and 32.
126.96.36.199 Preparation of Part. The part shall be thoroughly cleaned. Refer to Preparation of Part or Area for NDI,
188.8.131.52 NDI Equipment Settings. Refer to Magnetic Particle Method, paragraph 1.4.8.
184.108.40.206 Inspection Procedure. A magnetic field shall be applied to the part perpendicular to the orientation of possible
cracks. Positions for this inspection are illustrated in Figure 6-3.
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.
f. Repeat steps a. through e. for Positions 2 and 3.
220.127.116.11 Marking and Recording of Inspection Results. Mark and record the inspection results as required by paragraph
18.104.22.168 Demagnetization. With the switch remaining
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.
6.3.4 Backup Method. None required.
6.3.5 System Securing. Clean the connecting link 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 connecting link, if removed, requires
installation in accordance with the applicable technical manuals listed in Table 1-1. Secure applicable work platform and
6.4 STAINLESS STEEL FLIGHT CONTROL SYSTEM CONNECTING LINKS (PT).
6.4.1 Description (Figure 6-1. Index No. 4). Control inputs from the cockpit are transmitted through mechanical linkage
to the Integrated Lower Control Actuator (ILCA). The ILCA then transmits individual control motions to the first and
second stage mixing units. The mixed outputs are then transmitted through a series of push-pull tubes to the upper dual-
boost actuators attached to the forward and aft swashplates.
6.4.2 Defects. This inspection is to verify cracks found visually. No cracks are allowed.
6.4.3 Primary Method. Fluorescent Penetrant.