TM 1-1520-265-234-50 Change 24.21 STABILATOR ACTUATOR HOUSING (PT).4.21.1 Description(Figure4-1,IndexNo.21). The hydraulically-operated actuator is mounted tothe pylon and the horizontal stabilator. It reacts to commands from the cockpit and moves thehorizontal stabilator in an up or down direction.4.21.2 Defects. This inspection is used to verify crack indications found visually on the actuatorhousing. No cracks are allowed.4.21.3 PrimaryMethod. Fluorescent Penetrant.4.21.3.1 NDI Equipment and Materials. (Refer to Appendix B.) Inspection equipment is listed inTable 1-7. AMS 2644 level 3 penetrant materials shall be selected from the approved list in Table1-8. Parts requiring flourescent penetrant inspection shall be cleaned prior to inspection withn--Propyl Bromide (vapor degreasing only)(Table 1--8), DS--108 (Table 1--8), Electron (Table 1--8),Positron (Table 1--8). DS--108, Electron, Positron must be followed by an acetone (Table 1--8) rinseor wipe: or drying until there is no visible solvent residue left on parts..4.21.3.2 Preparation of Helicopter. The helicopter shall be prepared for safe ground maintenanceand the actuator removed in accordance with the applicable technical manuals listed in Table 1-1.4.21.3.3 Access. Not applicable.4.21.3.4 Preparation of Part. Refer to Preparation of Part or Area for NDI, paragraph 1.4.4.4.21.3.6 Inspection Procedure. Perform fluorescent penetrant inspection. Refer to FluorescentPenetrant Method, paragraph 1.4.7 and Table 1-5. Inspect area of concern. See Figure 4-21.4.21.3.7 Marking and Recording of Inspection Results. Mark and record inspection results asrequired by paragraph 1.3.4.21.4 BackupMethod. None required.4.21.5 SystemSecuring. Clean the actuator to remove inspection media. Refer to Post Cleaningand Restoration of Part or Area After NDI, paragraph 1.4.16. The actuator requires installation inaccordance with the applicable technical manuals listed in Table 1-1.4.22 DRAG BEAM SUPPORT FITTING (ET).4.22.1 Description(Figure4-1,IndexNo.22). The drag beam support fitting connects the mainlanding gear drag beam to each side of the fuselage midsection.4.22.2 Defects. This inspection is used to verify crack indications found visually on the supportfitting, especially at the lug areas and bearing bores. No cracks are allowed.4.22.3 PrimaryMethod. Eddy Current.
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