Aircraft Fatigue & Damage Tolerance Engineer

Aircraft Fatigue and Damage Tolerance Engineer responsible for performing structural fatigue and damage tolerance analysis of aircraft modifications, including design support, and preparation of technical documentation necessary to ensure airworthiness.
Determination of critical load paths in primary aircraft structure resulting from applied and induced operational loads, as well as the determining the local stress concentrations, internal fastener load distributions, operational usage environments and design allowables.
Development of tailored mission profiles and usage spectra for modified aircraft for use in calculation of service life

Skills/Experience:
Qualifications:
BSME, BSAE, BSCE and minimum 10 years of relevant work experience
MSME, MSAE, MSCE and minimum 9 years of relevant work experience.
Must be able to generate free body diagrams, determine reaction forces, and calculate internal load distributions, local stress concentrations, and operational usage environments
Must be able to travel as necessary.
Must be able to obtain a security clearance.
Must be proficient in Microsoft Office, and have general computer knowledge.
Must be able to work any shift, weekends, and overtime as required.
Good verbal and written communication skills
Willingness to mentor younger engineers
Effective leadership qualities

Preferred Skills:
Experience with predicting crack initiation lives and running standard crack growth programs; e.g., AFGROW, NASGRO
Working knowledge of one programming language
CAD or analysis (FEA) tools exposure, and/or experience in mechanical design or analysis structures and mechanisms
Working knowledge of both military (Mil Standard) and civilian (14 CFRs) certification regulations and generating substantiation data to demonstrate compliance
Familiarity with transducer instrumentation, data collection and or automation and software programming for numerical analysis
Working knowledge on how to develop the Airworthiness Limitations section of the Instructions for Continued Airworthiness for a structural modification
Experience with standard Nondestructive Inspection (NDI) methods and corresponding crack growth detectable flaw sizes