Lead, Aircraft Fatigue and Damage Tolerance Engineer

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Job Title:
Lead, Aircraft Stress Engineer
Job Code: 32080
Job Location:
Waco, TX (Onsite)
Job Schedule: 9/80

Job Description:

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Harris MMG Division is seeking an experienced Aircraft Fatigue and Damage Tolerance Engineer for our onsite aircraft modification facility located in Waco, TX. We offer competitive benefits and a generous relocation package for those who qualify.

The Aircraft Fatigue and Damage Tolerance Engineer will be responsible for performing structural fatigue and damage tolerance analysis of aircraft modifications, including design support, and preparation of technical documentation necessary to ensure airworthiness. This includes identification of critical load paths in primary aircraft structure resulting from applied and induced operational loads, as well as determining the local stress concentrations, internal fastener load distributions, operational usage environments and design allowables.

Additional responsibilities include development of tailored mission profiles and usage spectra for modified aircraft for use in calculation of service life.

• Fatigue analysis of aircraft structures.
• Crack growth analysis of aircraft structures.
• Development of specific mission profiles and usage spectrum for modified aircraft.
• Determination of inspection intervals for delivered aircraft.
• Design support and drawing review.
• Ability to generate free body diagrams, determine reaction forces, calculate internal load distributions, local stress concentrations, and operational usage environments.
• Willingness and ability to travel as necessary.
• Ability to obtain and maintain a SECRET security clearance.
• Must be able to work any shift, weekends, and overtime as required.
• Willingness to mentor less experienced engineers.
• Effective and demonstrated leadership qualities.

• Bachelor’s Degree in Mechanical Engineering, Aerospace Engineering, Civil Engineering and minimum 9 years of prior relevant experience. Graduate Degree (MSME, MSAE) and a minimum of 7 years of prior aircraft structural dynamics related experience. In lieu of a degree, minimum of 13 years of prior related experience.
• Must be a U.S. citizen.

• Experience with predicting crack initiation lives and running industry‑standard crack growth programs; e.g., AFGROW, NASGRO.
• Working knowledge of one programming language.
• Working knowledge of both military (Mil Standard) and civilian (14 CFRs) certification regulations and generating substantiation data to demonstrate compliance.
• 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.
• Experience with Dynamic Response Fatigue Analysis (High‑Cycle Fatigue) due to high vibration environments and/or acoustic fatigue stresses.
• CAD or analysis (FEA) tools exposure, and/or experience in mechanical design or analysis structures and mechanisms.
• Familiarity with transducer instrumentation, data collection and or automation and software programming for numerical analysis.
• Proficient in Microsoft Office, and have general computer knowledge.
• Excellent verbal and written communication skills.

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