Embedded Software Engineer

Basic Qualifications:

• At least 10 years of safety critical Computing System/Software/Hardware development, verification, or certification experience, in one or more of the following areas:
• Processing Hardware / Electronics, including Programmable Logic for FPGA or ASIC
• Software (SW) Development including Architecture, Design, and Qualifications
o Experience designing, developing, verifying and/or certifying safety critical SW
o Experience designing, developing, verifying and/or certifying SW for Multicore processors
o Experience with SW Partitioning (e.g. ARINC653)
o Experience with SW build, load & CM process for airborne equipment
o Experience conducting MIL-HBK-516C and/or DO-178B/C (SOI) audits on SW
o Experience with Standards: RTCA DO-178C, Emerging Mil Standard, FAA CAST-32A, RTCA DO-331, RTCA DO-330, RTCA DO-332, ARINC Specification 653, RTCA DO-278A, FAA CAST-2, FAA CATS-12, FAA CAST-17, FAA CAST-19, FAA Order 8110.49 CHG2, RTCA DO-248C, Joint Software Systems Safety Engineering Handbook, FAA AC 20-115C

Processing Hardware / Electronics:

o Experience designing, developing, verifying and/or certifying safety critical Electronic hardware & Firmware
o Experience with Programmable Logic Devices (PLDs) such as Field Programmable Gate Arrays (FPGAs) or Application Specific Integrated Circuits (ASICS).
o Experience conducting MIL-HBK-516C Airworthiness Assessments or DO-254 Stage of Involvement (SOI) audits on Complex (CEH) or Simple (SEH) Electronic Hardware
o Experience with Standards: RTCA DO-254, FAA Order 8110.105A, EASA-CM-SWCEH-001, MIL-STD-704F, RTCA DO-160E, MIL-STD-461, FAA AC 20-152, FAA CAST-30, FAA CAST-31
• System Processing Architecture (SPA)
o Architecture and Design of Safety Critical Systems & Subsystems for aircraft
o Development of Physical and Functional ICDs between Elements of the System
o Development of Safety Critical Thread Analysis (SCFTA) and Safety Interlocks (SI) Analysis
o Understanding of Computer Software Integrity Level CSIL used in MIL-HBK-516C and its relationship to Design Assurance Level (DAL) used in DO-178C and DO-254.
o Experience/familiarity with PLOC (Probability of Loss of Control) and PLOA (Probability of Loss of Aircraft) analyses
o Experience conducting MIL-HBK-516C Airworthiness Assessments or FAA/EASA Audits on systems and subsystems and associated System, Safety & Reliability artifacts
o Experience with Standards: MIL-HDBK-516C, AC-17-01, SAE ARP 4754A, MIL-STD-882E, MIL-NDBK-217, and JSSG-2008.