TM 1-1520-265-234.3HONEYCOMB AND COMPOSITE STRUCTURES (BT).4.3.1 Description(Figure4-1.IndexNo.3). This inspection is applicable to parts or components made ofmetallic/nonmetallic skins bonded to metallic/ nonmetallic cores and laminations of facings of metal or fiberglass panels.The structural assembly components identified for inspection are: honeycomb panels, cabin floors, drive shaft covers,access doors and covers, cowlings, and work platforms.4.3.2 Defects. Perform the NDI method contained herein on the components listed above for the purpose of verificationof void damage identified by visual inspection. Void damage may occur anywhere on either side of bonded panels as aresult of mechanical damage (dents, punctures, scratches, etc.) or fluid intrusion/corrosion.NOTEA void is defined as an unbonded area that is suppose to be bonded. Many sub-definitions aregiven such as bond separation, delamination, lack of adhesive, gas pocket, misfit, etc. Thisprocedure makes no distinction among these instead grouping under the general term "void."4.3.3 PrimaryMethod. Bond Testing.4.3.3.1NDI Equipment and Materials. (Refer to Appendix B.)a.Bond Test Unitb.Probe Mechanical Impedance Analysisc.Probe Holderd.Cable Assemblye.Test Block, metal honeycomb with skin thickness closest to that of the panel to be inspected (refer to AppendixC)f.Test Block, Composite Defect Standard #1g.Test Block, Composite Defect Standard #3h.Teflon Tape, consumable material, refer to Table 1-8i.Aircraft Marking Pencil, refer to Table 1-84.3.3.2Preparation of Helicopter. The helicopter shall be prepared for safe ground maintenance in accordance withapplicable technical manuals listed in Table 1-1.4.3.3.3Access. Not applicable.4.3.3.4Preparation of Part. The components shall be thoroughly cleaned. Refer to Preparation of Part or Area forNDI, paragraph 1.4.4.4-7
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