Engineer Software 3
Job Description
Engineer Software 3
Location: Melbourne, FL
Description
Individuals will work with, and auditing our Suppliers, to assess compliance to airworthiness criteria for Flight Critical Computing Systems (software and hardware) used in military aircraft.
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
Experience designing, developing, verifying and/or certifying safety critical SW
Experience designing, developing, verifying and/or certifying SW for Multicore processors
Experience with SW Partitioning (e.g. ARINC653)
Experience with SW build, load & CM process for airborne equipment
Experience conducting MIL-HBK-516C and/or DO-178B/C (SOI) audits on SW
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:
Experience designing, developing, verifying and/or certifying safety critical Electronic hardware & Firmware
Experience with Programmable Logic Devices (PLDs) such as Field Programmable Gate Arrays (FPGAs) or Application Specific Integrated Circuits (ASICS).
Experience conducting MIL-HBK-516C Airworthiness Assessments or DO-254 Stage of Involvement (SOI) audits on Complex (CEH) or Simple (SEH) Electronic Hardware
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)
Architecture and Design of Safety Critical Systems & Subsystems for aircraft
Development of Physical and Functional ICDs between Elements of the System
Development of Safety Critical Thread Analysis (SCFTA) and Safety Interlocks (SI) Analysis
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.
Experience/familiarity with PLOC (Probability of Loss of Control) and PLOA (Probability of Loss of Aircraft) analyses
Experience conducting MIL-HBK-516C Airworthiness Assessments or FAA/EASA Audits on systems and subsystems and associated System, Safety & Reliability artifacts
Experience with Standards: MIL-HDBK-516C, AC-17-01, SAE ARP 4754A, MIL-STD-882E, MIL-NDBK-217, and JSSG-2008\