David Lawson

350 West 50th Street, Apt TH-1G

New York, NY 10019

DLawson@LawAero.com

646 541-8767

EXPERIENCE:

  • 2005-
    FAA Structural DER and Analyst, Lawson Aerospace LLC, New York, NY.

    Damage tolerance evaluations, fatigue analysis, static strength analysis of advanced composite and metallic airplane and rotorcraft components, assemblies, and installations. FAA data approval of drawings and structural analysis reports in support of major alterations and major repairs thru Field Approvals, or a Return to Service with FAA approved data on a FAA form 337, one-only or multiple Supplemental Type Certificates of Normal and Transport Category Airplanes and Rotorcraft; or PMAs through identicality, or test and comparability.

  • 2010-
    Unit Member, Dassault FalconJet ODA, Wilmington, DE.
  • 2008-
    Unit Member, Bell Helicopter Textron ODA, Hurst, TX.
  • 2007-2008
    Damage Tolerance Analyst and DER, Adam Aircraft Industries, Denver, CO.

    Structural substantiation of flight control systems and landing gear. Reviewed and approved the damage tolerance and static strength substantiation reports, test reports and test results in support the all composite A700 very light jet Type Certification project.

  • 2006-2007
    MRB Structural Analyst, and Structural DER, Eclipse Aviation Corporation, Albuquerque, NM.

    Reviewed and approved the damage tolerance, fatigue, and static strength analysis reports in support the dispositions of non-conformant parts, assemblies, and installations on the EA500 very light jet prior to Production Certification, and for major repairs of in-service aircraft at the repair stations. Wrote dispositions and substantiations for repairs after Production Certification.

  • 2005-2006
    Fatigue Analyst, Sikorsky Aircraft, Stratford, CT.

    Performed detailed fatigue analyses of the MH-60R and MH-60S Sea Hawk helicopter active vibration control installations, and the MH-60S transmission beams that cracked in service using fine grid PATRAN/NASTRAN models that included fastener free bodies. The AVC installation was 10 percent under projected target weight, two months early, and had a fatigue stress-life of over 300,000 hours. Sized the MH-92 nose electronics bay, composite fairing and access door. Internal loads were obtained from PATRAN/NASTRAN models and free body diagrams. Composite sandwich panels were sized by ply-level open hole strain failure criteria, core shear and compression, and edge band strength. Geometry was obtained from CATIA.

  • 2002-2005
    Aviation Safety and Project Engineer, New York Aircraft Certification Office, FAA, Westbury, NY.

    Reviewed and approved damage tolerance, fatigue, and static strength analysis reports, basic loads reports, issue papers, special conditions, and certification plans for compliance with the requirements in Title 14 of the Code of Federal Regulations for major alterations and repairs to US civil registered airplanes and rotorcraft. Wrote 14 CFR 39 airworthiness directive proposals, and approved AD alternate means of compliance. DER Advisor to around 16 Structural DERs.

  • 1999-2002
    Supervisor, Structural Analysis Dept, EDO Marine and Aircraft Systems, Amityville, NY.

    Partitioned jobs and made work assignments. Sized the carbon fiber weapons bay doors for the Boeing X-32 Joint Strike Fighter. Analyzed the damage tolerance and fatigue resistance, and then redesigned the components of the F-22 Raptor AMRAAM missile launcher that developed cracks and failed during random vibration testing using AFGROW and strain gage data. Built PATRAN/ANSYS finite element models to obtain internal loads, and to determine the locations for strain gages. Wrote computer programs to generate fatigue spectra from F/A-18 flight test accelerometer data that were used to analyze the damage tolerance and fatigue resistance of the bomb release units. Geometry was obtained from CATIA.

  • 1998-1999
    Stress Analyst, Lockheed-Martin Skunk Works, Palmdale, CA.

    Sized wing skins, spars, ribs, and fuselage bulkheads on the F/X-35 Joint Strike Fighter. Carbon fiber sandwich panels were sized by ply-level open hole (damage tolerance) strain failure criteria. Metallic spar and bulkhead webs were sized by shear buckling and checked for maximum principle and shear stresses due to combined shear, biaxial loads, and in-plane moments. Chords were sized by compression crippling or maximum principle stress with strength reduction factors due to elevated temperatures. Frames were sized by Johnson-Euler column buckling. Fuselage skins were sized by shear and compression stability. Skin stiffeners were sized by beam-column strength. Internal loads obtained from PATRAN/NASTRAN finite element models.

  • 1997-1998
    Stress Analyst, Boeing Defense and Space Group, Seattle, WA.

    Analyzed the static strength of the X-32 Joint Strike Fighter aft-fuselage panels. Metallic panels were checked for sonic fatigue due to engine acoustic loads. Carbon fiber solid laminate and sandwich panels were sized by ply-level open hole (damage tolerance) strain failure criteria and checked for shear and compression stability, and edge band joint strength. Sandwich panels were also checked for flat-wise tension and core compression strength. Fasteners were sized by static strength, and joints were checked for fatigue resistance. Internal loads obtained from PATRAN/NASTRAN and femap finite element models. Geometry was obtained from CATIA.

  • 1997-1997
    Durability and Damage Tolerance Analyst, Northrop-Grumman (Vought Aircraft), Dallas, TX.

    Analyzed the damage tolerance of the fracture critical C-17 Globemaster III vertical and horizontal stabilizer skins, spar caps, and splice plates that were damaged during manufacturing operations using MDC crack growth codes. MRB stress analysis.

  • 1996-1997
    Stress Analyst, Lockheed-Martin Tactical Aircraft Systems, Fort Worth, TX.

    Analyzed the damage tolerance and static strength of the F-22 Raptor advanced tactical fighter mid-fuselage bulkheads and weapons bay fittings. Bulkhead webs were sized by shear buckling, and checked for maximum principle and shear stresses due to combined shear and biaxial loads. Stiffeners were sized by moment of inertia requirements and the additional compression loads following web buckling. Typical fitting strength checks included compression crippling, plastic bending, yielding at limit loads, tension fitting, lug, bolt shear, and pin bending strength.

  • 1990-1995
    Damage Tolerance and Stress Analyst, Boeing Commercial Airplane Group, Seattle, WA.

    Analyzed the damage tolerance of the main landing gear and engine strut attachments to the Boeing 737-700/-800 wing to determine mandatory inspection intervals. Analyzed the fatigue resistance and static strength of the 737-700/-800 outboard wing panel attachments to the spar chord, rib and trailing edge panel, the front and rear spar fittings, the 737-700 wing center section rear spar assembly, and the 777-200 main landing gear support fittings. Wrote repairs for 747 Classic SRM. Rotations through Manufacturing Liaison, Primary Structural Design, and Structural Repair engineering groups.

EDUCATION:

  • 1987-1989
    BS in Aerospace Engineering, Polytechnic University, Brooklyn, NY.
  • 1985-1987
    Aeronautical Engineering, University of Texas, Arlington, TX.

FAA DELEGATION AUTHORIZATIONS:

  • Structural DER for all airframe structures including: main and tail rotors, wing, empennage, flight controls, landing gear, fuselage, doors, windows, and antenna installations with no limitations for damage tolerance evaluations, fatigue analysis, static strength analysis, design and construction, service documents, materials and process specifications. Special delegation authorizations in certification project management, major alterations and major repairs, Repair Specification DER, PMA identicality, and Aging Airplane Safety Rule 14 CFR 26 for Part 25 airplanes.