Inspection Procedure. Refer to Eddy Current Method, paragraph 1.4.11 and Figure 4-24.
Place probe on a good area in the inspection location and null. Adjust phase as required to obtain horizontal
Inspect the part.
Any signal similar to the notches in the test block is cause for rejection.
Either probe identified in paragraph 220.127.116.11 may be used depending primarily on the
ease of accessibility and user friendliness. If the probes are changed, steps 18.104.22.168 b.
(1), (2), and (3) shall be repeated each time a change is made.
Marking and Recording of Inspection Results. Mark and record the inspection results as required by
Backup Method. None required.
System Securing. The engine nacelle strut, if removed, requires installation in accordance with the applicable
technical manuals listed in Table 1-1.
4.25 MAIN LANDING GEAR TRAILING ARMS (MT).
Description (Figure 4-1. Index No. 25)
. The left and right main landing gear trailing arms are the largest
tubular portion of each of the landing gear assemblies. The upper end attaches to the cross tube and the lower end is the
Defects. This inspection is used to verify crack indications found visually on the main landing gear trailing
arms. No cracks are allowed.
Primary Method. Magnetic Particle.
NDI Equipment and Materials. (Refer to Appendix B.)
Magnetic Particle Inspection Probe/Yoke
Fluorescent Magnetic Particles, refer to Table 1-8
Consumable Materials, refer to Table 1-8
Aircraft Marking Pencil, refer to Table 1-8
Hand-held magnetic coil may be used. Refer to paragraph 22.214.171.124.2 and Figure 1-6.