Either probe identified in paragraph 22.214.171.124 may be used depending primarily on the
ease of accessibility and user friendliness. If the probes are changed, steps 126.96.36.199
b. (1), (2), and (3) shall be repeated each time a change is made.
188.8.131.52 Marking and Recording of Inspection Results. Mark and record inspection results as
required by paragraph 1.3.
Backup Method. None required.
System Securing. The spindle, if removed, requires installation in accordance with the
applicable technical manuals listed in Table 1-1.
2.8 ANTIFLAP BRACKET (ET).
Description (Figure 2-1, Index No. 8). The antiflap brackets are installed on each of the four
main rotor spindle modules next to the hub. The antiflapping assemblies prevent the blades from
flapping when the main rotor head is slowing down or stopped.
Defects. The inspection is used to verify crack indications found visually on the antiflap
bracket. No cracks are allowed.
Primary Method. Eddy Current.
184.108.40.206 NDI Equipment and Materials. (Refer to Appendix B.)
a. Eddy Current Inspection Unit
b. Probe, straight, shielded surface, 2 MHz
c. Probe, right angle, shielded surface, 2 MHz, 90_ 1/2 inch drop
d. Cable Assembly
e. Adapter, probe, 2 MHz
f. Reference Block, three-notched titanium (0.008, 0.020, 0.040 EDM notches)
g. Teflon Tape, refer to Table 1-8
h. Aircraft Marking Pencil, refer to Table 1-8
220.127.116.11 Preparation of Helicopter. The helicopter shall be prepared for safe ground maintenance.
A 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
antiflap bracket shall be removed in accordance with the applicable technical manuals listed in Table
18.104.22.168 Access. Access to the antiflap bracket is from the L/R engine cowl (Figure 1-4, Items 3T-7
22.214.171.124 Preparation of Part. The part shall be thoroughly cleaned. Refer to Preparation of Part or
Area for NDI, paragraph 1.4.4.