Aircraft Damage Tolerance Engineer -- KUMDC5868304

Position: Aircraft Fatigue and 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