F&DT Analysis Engineer

Job Description: Experience Range: 5-7 Years Only - Knowledge Fatigue and Damage Tolerance analysis - Theoretical knowledge in aircraft crack propagation analysis - Knowledge of aircraft loads and experienced in spectrum generation - Calculation of Seq stresses (fatigue and crack propagation), understanding of mission profiles, rainflow counting, Miner's rule, stress files, FESPS databases. - Calculation of Stress concentration (Kt) values using Petersons' or DFEM or ISAMI modules. - Analysis of metallic and composite structures (Plain Strength checks, Buckling, Bolted joint analysis) - Knowledge of static and fatigue design values (Ftu, Fty, Fcy, AFI parameters, S-N curve parameters, fracture toughness etc.,) - Static and Fatigue calculations (Hand calculations, DFEM, ISAMI, GFEM load redistribution) - Ability to read the drawings and interpret fastener diameter, fastener fit, fastener spec & type, surface protection treatment to be useful for fatigue calculations. - Possess strong foundation in the area of load/stress analysis with abilities to formulate "free body diagrams" and identify load path of structures - ISAMI modules (Metallic Filled Hole, Composite Filled Hole, Lug analysis, Corin Analysis, Notch Sensitivity, Damage Tolerance, Tension Fitting, Fatigue Spectrum Analysis (1D & 2D), Fatigue DFEM Initiation Modules, etc.,) - Experienced in documents (like PDR/CDR/Certification reports, Concessions, Repairs) and report creation and getting validated. This job requires an awareness of any potential compliance risks and a commitment to act with integrity, as the foundation for the Company’s success, reputation and sustainable growth.

Responsibilities

Calculation of Seq stresses (fatigue and crack propagation), understanding of mission profiles, rainflow counting, Miner's rule, stress files, FESPS databases; Calculation of Stress concentration (Kt) values using Petersons' or DFEM or ISAMI modules; Analysis of metallic and composite structures (Plain Strength checks, Buckling, Bolted joint analysis); Static and Fatigue calculations (Hand calculations, DFEM, ISAMI, GFEM load redistribution); Report creation and getting validated

Requirements

Experience Range: 5-7 Years Only; Knowledge Fatigue and Damage Tolerance analysis; Theoretical knowledge in aircraft crack propagation analysis; Knowledge of aircraft loads and experienced in spectrum generation; Calculation of Seq stresses (fatigue and crack propagation), understanding of mission profiles, rainflow counting, Miner's rule, stress files, FESPS databases; Calculation of Stress concentration (Kt) values using Petersons' or DFEM or ISAMI modules; Analysis of metallic and composite structures (Plain Strength checks, Buckling, Bolted joint analysis); Knowledge of static and fatigue design values (Ftu, Fty, Fcy, AFI parameters, S-N curve parameters, fracture toughness etc.,); Static and Fatigue calculations (Hand calculations, DFEM, ISAMI, GFEM load redistribution); Ability to read the drawings and interpret fastener diameter, fastener fit, fastener spec & type, surface protection treatment to be useful for fatigue calculations; Possess strong foundation in the area of load/stress analysis with abilities to formulate "free body diagrams" and identify load path of structures; ISAMI modules (Metallic Filled Hole, Composite Filled Hole, Lug analysis, Corin Analysis, Notch Sensitivity, Damage Tolerance, Tension Fitting, Fatigue Spectrum Analysis (1D & 2D), Fatigue DFEM Initiation Modules, etc.,); Experienced in documents (like PDR/CDR/Certification reports, Concessions, Repairs) and report creation and getting validated; Awareness of potential compliance risks and commitment to act with integrity

Benefits

Flexible working arrangements