Aircraft Fatigue & Damage Tolerance Engineer

Innova Solutions•Waco, TX

13h•Onsite

About The Position

Innova Solutions has a client that is immediately hiring for an Aircraft Fatigue and Damage Tolerance Engineer. This is a Full-Time Contract position with a duration of 12 months, located in Waco, TX. As an Aircraft Fatigue and Damage Tolerance Engineer, you 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 the determination of critical load paths in primary aircraft structure resulting from applied and induced operational loads, as well as determining local stress concentrations, internal fastener load distributions, operational usage environments, and design allowables. You will also be responsible for the development of tailored mission profiles and usage spectra for modified aircraft for use in calculation of service life.

Requirements

BSME, BSAE, BSCE and minimum 10 years of relevant work experience OR MSME, MSAE, MSCE and minimum 9 years of relevant work experience.
Proficient in Microsoft Office, and have general computer knowledge.
Good verbal and written communication skills.
Willingness to mentor younger engineers.
Effective leadership qualities.

Nice To Haves

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.

Responsibilities

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.
Generate free body diagrams, determine reaction forces, and calculate internal load distributions, local stress concentrations, and operational usage environments.
Travel as necessary.
Obtain a security clearance.