I am working on antenna (with 20 Kg mass) Installation at non-pressurised fuselage, after pressure bulk head. The antenna is installed directly on Stringer with Stringer coupling, and there is 2" x 2" square hole on fusealge skin for ELECTRICAL Provision. This hole is reinforced as per OEM SRM Skin repair. As per SRM, there is no inspection interval mentioned for Skin repair and Stringer repair. Do I Need to DTA and calculate the inspection interval? or only the static calculation is enough?
If I Need to do DTA, what load is to be considered?
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