• 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.

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