Support for your major and minor repair or alteration projects that require a Return to Service with FAA approved data or a coordinated Field Approval on a FAA form 337, one-only or multiple Supplemental Type Certificates of Normal and Transport Category Airplanes and Rotorcraft. Support for both domestic and foreign repair stations.
FAA data approval of drawings and structural analysis reports for major repairs or major alterations that show compliance with Code of Federal (Aviation) Regulations 23, 25, 27, 29, & Car 3, 4b, 6, 7.
Structural analysis reports and/or drawings prepared to substantiate major repairs or alterations to install equipment on military, public use, or civil registered aircraft.
Data approvals for the extension of repair limits beyond the manufacturer’s Structural Repair Manual, in lieu of AC 43.13-1B, or for multiple-use Repair Specifications.
FAA certification projects (STC, RS, or PMA) can be conducted on behalf of your company.
Static strength of aircraft components and installations is analyzed by obtaining internal loads through free-body, shear and bending moment diagrams or numerical methods, and then performing structural analysis using classical handbook solutions.
Damage tolerance (crack growth) is analyzed to determine the NDI inspection intervals per 14 CFR 25.571, and 26.43 for repairs or alterations to pressurized fuselage, wings, and empennage.
Advanced composite sandwich and solid laminate panels are analyzed using classical laminated plate theory for ply-level tension and compression failure modes, core shear and compression, insert pull out, and edge band (bearing) strength.
High cycle fatigue due to flight, acoustic, and random vibration loads is analyzed using stress-life methods. Low cycle fatigue due to mechanical or thermal loads is analyzed using strain-life methods.
Two aircraft structural analysts and one primary structural design engineer on staff.