| 2.3.3-4-1 Ensure parts and material temperature and stress derating analyses performed before design release |
Phase B |
Phase C |
|
Ensure that part and circuit stress analysis is completed prior to design release.
|
SFWC 2.3
|
NA
|
Mission Assurance Guide, TOR-2007(8546)-6018, Rev B, PMP Chapter; Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494; TOR-2006(8583)-5235 Rev A, Parts, Materials, and Processes Control Program for Space and Launch Vehicles
|
| 2.3.3-4-2 Ensure electrical, electronic, electromechanical and electro-optical part parameter derating policy is established and implemented |
Phase B |
Phase C |
|
Ensure that a uniform derating policy is established that meets the system technical requirements and the derating requirements of the mission life of the program. Implement this policy on all parts and materials used by the contractor and subcontractors alike for all flight, qualification and/or proto-qualification hardware. The Parts Materials and Processes Control Board should review and approve the derating policy used on the program, and any exceptions requested thereafter.
|
SFWC 2.3
|
NA
|
Mission Assurance Guide, TOR-2007(8546)-6018, Rev B, PMP Chapter; Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494; TOR-2006(8583)-5235 Rev A, Parts, Materials, and Processes Control Program for Space and Launch Vehicles
|
| 2.3.3-4-3 Ensure radiation hardness assurance program is developed and implemented |
Phase B |
Phase C |
Phase D1 |
|
Ensure that a radiation hardness assurance (RHA) program applicable to radiation sensitive Electrical, Electronic, Electromagnetic and Electro-optical parts is developed and implemented.
|
SFWC 2.3
|
NA
|
Mission Assurance Guide, TOR-2007(8546)-6018, Rev B, PMP Chapter; Space Vehicle Systems Engineering Handbook; TOR-2006(8583)-5235A
|
| 2.3.3-4-4 Ensure all Parts, Materials & Processes Control Board requirements flowed down to subcontractors |
Phase B |
Phase C |
Phase D1 |
|
Ensure the implementation of procedures and processes for the generation, analysis, flow down, and verification of PMP requirements from the contract statement of work, top level system specification, the system environmental requirement specification(s), and other contractual documents as required, to lower level systems / segments / product specifications, subcontractor statement of work, and PMP specifications. Ensure radiation hardness assurance requirements of semiconductor parts requirements are included
|
SFWC 2.3
|
NA
|
Mission Assurance Guide, TOR-2007(8546)-6018, Rev B, PMP Chapter; Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494; TOR-2006(8583)-5235 Rev A, Parts, Materials, and Processes Control Program for Space and Launch Vehicles
|
| 2.3.3-4-5 Ensure parts stress derating requirements are developed and applied across the program uniformly |
Phase B |
Phase C |
Phase D1 |
|
Ensure derating requirements in compliance per task 206.1 of MIL-STD-1543. Circuits should be designed with the parts derated as specified in TOR-2006(8583)-5236A.
|
SFWC 2.3
|
NA
|
Mission Assurance Guide, TOR-2007(8546)-6018, Rev B, PMP Chapter; Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494; TOR-2006(8583)-5235 Rev A, Parts, Materials, and Processes Control Program for Space and Launch Vehicles
|
| 2.3.3-4-6 Ensure worst-case circuit analysis performed as required |
Phase B |
Phase C |
|
Ensure worse case circuit analysis is conducted as specified in Mil-STD-1542, or to equivalent requirements. Circuits should be designed with the parts derated as specified in TOR-2006(8583)-5236A.
|
SFWC 2.3
|
NA
|
Mission Assurance Guide, TOR-2007(8546)-6018, Rev B, PMP Chapter; Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494; TOR-2006(8583)-5235 Rev A, Parts, Materials, and Processes Control Program for Space and Launch Vehicles; Mil-STD-1543B, Reliability Program Requirements
|
| 2.3.3-4-7 Ensure Single Event Effects (SEE) analysis performed |
Phase B |
Phase C |
|
Ensure validation of SEE analyses at box/system level demonstrating compliance to allocated outages and system level availability/dependability requirements. Validation consists of verification that the SEE rates used in the analyses are endorsed/sanctioned from the cognizant hardness assurance engineer.
|
SFWC 2.3
|
NA
|
Mission Assurance Guide, TOR-2007(8546)-6018, Rev B, PMP Chapter; Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494; TOR-2006(8583)-5235 Rev A, Parts, Materials, and Processes Control Program for Space and Launch Vehicles
|
| 2.3.3-4-8 Ensure Electrical, Electronic, Electromagnetic and Electro-optical parts have completed quality conformance inspections/test |
Phase B |
Phase C |
|
Ensure lot conformance testing (or quality conformance inspection) is performed as a basis for final lot acceptance on each production lot of parts.
|
SFWC 2.3
|
NA
|
Mission Assurance Guide, TOR-2007(8546)-6018, Rev B, PMP Chapter; Space Vehicle Systems Engineering Handbook, TOR-2006(8506)-4494; TOR-2006(8583)-5235 Rev A, Parts, Materials, and Processes Control Program for Space and Launch Vehicles
|