Download SAO-PAS-RS-00001-A - Comisión Nacional de Actividades

SAO-PAS-RS-00001-A
SPECIFICATION
SAFETY AND PRODUCT
ASSURANCE REQUIREMENT
DOCUMENT (S.P.A.R.D)
This document is stored electronically. Printed version might not be the latest.
SAOCOM PROJECT
COMISION NACIONAL DE ACTIVIDADES ESPACIALES
BUENOS AIRES – ARGENTINA
SAOCOM PROJECT
SAO-PAS-RS-00001-A
Number
Title
Summary
SAFETY AND PRODUCT ASSURANCE REQUIREMENT DOCUMENT
(S.P.A.R.D)
Product assurance for the SAOCOM Project is an integrated cost effective
program, covering the disciplines of contamination control, electronics parts
engineering, materials and processes, quality assurance (hardware and
software), reliability assurance, and systems safety.
This is a L2B document. Particular topics, such as Contamination Control,
Materials and Processes Control, Operation Assurance and Configuration
Management, are specifically covered in separated documents
Secondary Reference
Circulation Level
1o2
This document is digitally signed
Workflow Summary
Assignee
State
Action
Completed Date
Changes Record
Issue
Date
23-03-12
Author
PARA
Description
The first requirements were modified to adapt the
structure of the document to the current
requirements. Requirements modified: 01 to 18.
The responsibilities of Mission Product Assurance
area were clarified. Requirements modified: 85,
154, 155, 158. 159, 160, 161, 162, 163, 174, 175,
176, 182
Comisión Nacional de Actividades Espaciales (CONAE) from Argentina owns the copyright of this document which is supplied in confidence and which
shall not be used for any purpose other than that for which it is supplied and shall be only reproduced, copied or communicated, in whole or in part, for
internal use of CONAE, directly or by third parties holding confidentiality agreements with CONAE. Any person other than the authorised holder obtaining
possession of this document by finding or otherwise, should send it, together with his name and address, in a sealed envelope to:
Comisión Nacional de Actividades Espaciales (CONAE) – SAOCOM Project
Av. Paseo Colón 751
(C1063ACH) Capital Federal
ARGENTINA
Letter postage need not be prepaid. Other postage will be refunded.
Page 2 of 28
S.P.A.R.D
SAO-PAS-RS-00001-A
INDEX
INDEX ................................................................................................................................................................. 3
1.
OBJECTIVE ............................................................................................................................................... 4
2.
SCOPE ....................................................................................................................................................... 4
3.
APPLICABLE AND REFERENCE DOCUMENTS .................................................................................... 4
3.1
3.2
4.
APPLICABLE DOCUMENTS ............................................................................................................... 4
REFERENCE DOCUMENTS ............................................................................................................... 5
DEFINITIONS AND ABBREVIATIONS ..................................................................................................... 5
4.1
4.2
DEFINITIONS ...................................................................................................................................... 5
ABBREVIATIONS AND ACRONYMS .................................................................................................. 6
6 DESIGN, VERIFICATION, PROCESS AND SAFETY REQUIREMENTS ..................................................... 7
6.1 RELIABILITY................................................................................................................................................. 7
6.2 PARTS ......................................................................................................................................................13
6.3 QUALITY ASSURANCE (QA) ........................................................................................................................17
6.4 SAFETY REQUIREMENTS ............................................................................................................................21
Comisión Nacional de Actividades Espaciales (CONAE)
Page 3 of 28
S.P.A.R.D
SAO-PAS-RS-00001-A
ID : L2B_SPARD_1
1. OBJECTIVE
ID : L2B_SPARD_2
Product assurance for the SAOCOM Project is an integrated cost effective program, covering the
disciplines of contamination control, electronics parts engineering, materials and processes, quality
assurance (hardware and software), reliability assurance, and systems safety.
This is a L2B document. Particular topics, such as Contamination Control, Materials and
Processes Control, Operation Assurance and Configuration Management, are specifically covered
in separated documents
ID : L2B_SPARD_3
2. SCOPE
ID : L2B_SPARD_4
The requirements listed in this document are applicable to:
(a) Hardware and software supplied by Contractors.
(b) Hardware and software designed and developed by SAOCOM engineers/developers.
(c) Spacecraft, SAR instrument and service platform integration and Test.
(d) SAOCOM launch services and support.
3. APPLICABLE AND REFERENCE DOCUMENTS
ID : L2B_SPARD_6
The following documents of the issue in effect on the date of invitation for bids, or request for
proposal, or product manufacturer, form a part of this document to the extent specified herein. In
case of conflict, the conflicts shall be referred to CONAE
ID : L2B_SPARD_7
3.1
APPLICABLE DOCUMENTS
ID : L2B_SPARD_9
The following documents of the issue in effect on the date of invitation for bids, or request for
proposal, or product manufacturer, form a part of this document to the extent specified herein. In
case of conflict, the conflicts shall be referred to CONAE
JPL D-8091, “JPL Standard for Anomaly Resolution”.
JPL D-560, “JPL Standard for System Safety”.
NASA-STD-8719.9, “NASA Standard for Lifting Devices and Equipment”.
NPSL (NASA Parts Selection List) Level-1.
NPSL (NASA Parts Selection List) Level-2.
MIL-PRF-38534 / QML. “General Specification For Hybrid Microcircuits”.
MIL-PRF-38510 / QPL
MIL-STD-883, “Test Methods and Procedures for Microcircuits”.
MIL-PRF-19500 / QPL, "General Specification for Semiconductor Devices”.
MIL-PRF-38535 / QML, “General Specification for Manufacturing Microcircuits”.
MIL-PRF-55365;”General Specification for Capacitor, Fixed, Electrolytic (tantalum),
Chip, Non-Established Reliability, and Established Reliability”.
[A.D.12] MIL-PRF-39003, “General Specification for Capacitor, Fixed, Electrolytic (Solid
Electrolytic), Chip, Non-Established Reliability, Established Reliability”.
[A.D.1]
[A.D.2]
[A.D.3]
[A.D.4]
[A.D.5]
[A.D.6]
[A.D.7]
[A.D.8]
[A.D.9]
[A.D.10]
[A.D.11]
Comisión Nacional de Actividades Espaciales (CONAE)
Page 4 of 28
S.P.A.R.D
[A.D.13]
[A.D.14]
[A.D.15]
[A.D.16]
[A.D.17]
SAO-PAS-RS-00001-A
MIL-STD-981, “Design, Manufacturing and Quality Standards for Custom
Electromagnetic Devices for Space Applications”.
Military Established Reliability (ER) passive devices, Failure Rate Levels R, S.
MIL-STD-1580 “Destructive Physical Analysis for Electronic, Electromagnetic, and
Electromechanical Parts”
NASA EEE-INST-002. Supersedes 311- INST-001, Rev. A.
NASA GSFC Specification S-311-P-079, “Procurement Specification for Thermo foil
Heaters”
JPL D-19426 “Plastic Encapsulated Microcircuits (PEM's) Reliability. Usage Guidelines
for Space Applications”
[A.D.19] Air Force Space Command Manual 91-710 Volumes 3 and 6
[A.D.18]
ID : L2B_SPARD_10
3.2
REFERENCE DOCUMENTS
ID : L2B_SPARD_11
The following listed documents, are reference documents:
[R.D.1]: SOG-ATP-PL-00100 « Contamination Control Plan ».
[R.D.2]: SOG-ACP-LI-00100 « Preferred Parts List (PPL) ».
[R.D.3]: SOG-ACP-PL-00100 « EEE Parts Control Plan ».
[R.D.4]: SOG-ACM-PL-00100 « Material and Process Control Plan ».
[R.D.5]: SOG-AFE-PL-00100 « Mission Review Plan ».
[R.D.6]: SOG-AQC-PL-00100 « Configuration Management Plan ».
[R.D.7]: SOG-ENV-RQ-00100 “Environmental Requirement Document (ERD)».
[R.D.8]: SOG-SMA-PL-00100 « Mission Assurance Plan (MAP) ».
[R.D.9]: SOG-SMA-PL-00300 « Systems Safety Plan ».
[R.D.10]: SOG-SMA-PL-00200 « Problem & Failure Reporting Plan (PFRP) »
ID : L2B_SPARD_12
4. DEFINITIONS AND ABBREVIATIONS
ID : L2B_SPARD_13
4.1
DEFINITIONS
ID : L2B_SPARD_14
Critical Hardware: flight hardware, flight spare, engineering model, ground support equipment and
other critical equipment that interface with flight hardware.
ID : L2B_SPARD_15
Critical Processes: are identified as those which affect the functionality, performance, or quality of
the hardware and that failure to control these processes will result in significant risk to the end
product.
ID : L2B_SPARD_16
Quality Records: are those records, which furnish objective evidence of performed activities, or
results achieved, relating to the fabrication, assembly, integration and test of parts/hardware.
Quality records include manufacturing planning records detailing specific steps performed, and
inspection points; test logs and/or test documents detailing the test set up (temperature setting,
dwell time, etc), test duration, and results achieved; records documenting non-conformances and
the respective dispositions; corrective action records; calibration records; parts list for configuration
management; and engineering and specification changes.
ID : L2B_SPARD_17
efinitions for the present document.
Comisión Nacional de Actividades Espaciales (CONAE)
Page 5 of 28
S.P.A.R.D
4.2
SAO-PAS-RS-00001-A
ABBREVIATIONS AND ACRONYMS
ID : L2B_SPARD_18
CONAE-C: part of the organization of CONAR acting as “customer” of the SAOCOM Project
CONAE-PC: part of the organization of CONAE acting as principal contractor of the SAOCOM
Project
PA: Product Assurance
Comisión Nacional de Actividades Espaciales (CONAE)
Page 6 of 28
S.P.A.R.D
SAO-PAS-RS-00001-A
ID : L2B_SPARD_19
5 DESIGN, VERIFICATION, PROCESS AND SAFETY
REQUIREMENTS
ID : L2B_SPARD_20
5.1 Reliability
ID : L2B_SPARD_21
Information: Assurance of SAOCOM reliability for required on-orbit operational period will be
achieved through the implementation of the integrated product assurance program described in
product assurance plan and high reliability design and development requirements/ practices,
identified below. These include:
(a) Successful completion of a comprehensive test program, involving large margins over the
expected environment, and full compliance with imposed requirements.
(b) Verification of design robustness for end of life conditions, detailed in a complete set of
reliability analyses, such as worst case and parts stress analysis.
(c) Assurance of fault tolerance and protective measures, verified by Failure Modes and Effect
Analyses (FMEA) s.
(d) Application of high reliability standards for design, fabrication, inspection and testing.
(e) Selection of Grade Level 2 or better electronic components and flight proven materials and
processes.
(f) Extensive burn-in and operational testing of electronic assemblies.
ID : L2B_SPARD_22
5.1.1 Lifetime
ID : L2B_SPARD_23
Requirement: The satellite shall be designed for 12 months of unpowered ground storage.
ID : L2B_SPARD_24
Requirement: During storage, the satellite shall be powered on and tested at a minimum
frequency of every 3 months for a maximum total test time of 240 hours.
ID : L2B_SPARD_25
Requirement: Flight hardware shall be designed to operate over two times the expected
mechanical cycles and three times electrical power cycles. Total cycle number is the sum of cycles
during assembly, integration, testing & flight operations.
ID : L2B_SPARD_26
Requirement: For qual program, single actuation mechanisms (i.e. deployment mechanisms)
shall be designed to be able to withstand successful ground test at a minimum of 10 deployments
before lunch.
ID : L2B_SPARD_27
Requirement: For a protofligth program and flight model acceptance test a single actuation
mechanism shall be designed to withstand successful ground test of 3 to 10 deployment before
launch.
ID : L2B_SPARD_28
Requirement: Life limited hardware shall be identified along with the mitigation approach and
method(s) for tracking usage.
ID : L2B_SPARD_29
5.1.2 Single point failure (SPF)
ID : L2B_SPARD_30
Requirement: Single Point Failure not listed in the project approved exception list shall require a
waiver. The waiver shall include:
Comisión Nacional de Actividades Espaciales (CONAE)
Page 7 of 28
S.P.A.R.D
SAO-PAS-RS-00001-A
(a) Rationale for the acceptance.
(b) Risk impact on the mission.
(c) Mitigation approach.
ID : L2B_SPARD_31
5.1.3 Operating hours
ID : L2B_SPARD_32
Requirement: Flight electronics shall accumulate a minimum power-on operating time of 200
hours at the unit level prior to SAR Instrument/Service platform installation.
ID : L2B_SPARD_33
Information: This requirement can be satisfied by:
(a) Operating the hardware at ambient temperature,
(b) During environmental test or,
(c) Sum of operating time at (a) and (b).
ID : L2B_SPARD_34
Requirement: Each side of a block redundant flight electronic unit shall accumulate a minimum
power-on operating time of 200 hours at the satellite level (plus 100 hours at unit level) for a total of
300 hours prior to launch.
ID : L2B_SPARD_35
Requirement: Single string flight electronic units shall accumulate a minimum power - on
operating time of 300 hours at satellite level (plus 200 hours at unit level) for a total of 500 hours
prior to launch.
ID : L2B_SPARD_36
Requirement: As a minimum the last 50 hours of operating time prior to delivery to the next level
of integration shall be failure-free and without configuration change.
ID : L2B_SPARD_37
Information: The intent of this requirement is to require that the last 50 hours of testing of a
particular component be failure free and done in the final flight configuration.
ID : L2B_SPARD_38
Requirement: Flight spare hardware, if any, shall meet operating hours requirements listed
above. This requirement applies to assemblies and not parts.
ID : L2B_SPARD_39
Requirement: All heaters used in the satellite shall meet the 168 hours of operation as specified
in paragraph 4.7.2 in [A.D.17].
ID : L2B_SPARD_40
Information: Note that the heater foil burn-in duration required in requirement above may occur
either at the manufacturer (assuming appropriate documentation is delivered with the components)
or after delivery.
ID : L2B_SPARD_41
5.1.4 Design/Reliability Analyses
ID : L2B_SPARD_42
Requirement: The SAR Instrument and satellite design robustness shall be assessed through the
use of the following analyses:
(a) Satellite level Failure Modes, Effects and Criticality Analysis (FMECA).
(b) Interface FMECA: Flight Hardware to Flight Hardware.
(c) Interface Failure Modes and Effect Analysis (FMEA): flight hardware to Support equipment.
(d) Fault Tree Analysis (FTA).
(e) Worst Case Analysis, including power supply transient analysis.
(f) Electronic Parts Stress Analysis.
(g) Single Event Effects Analysis.
(h) Thermal and Structural Analyses.
ID : L2B_SPARD_43
Comisión Nacional de Actividades Espaciales (CONAE)
Page 8 of 28
S.P.A.R.D
SAO-PAS-RS-00001-A
5.1.4.1 System FMECA
ID : L2B_SPARD_44
Information: FMECA analysis starts during formulation and is updated throughout implementation
phase for review at the system level PDR and CDR and project risk assessment reviews.
ID : L2B_SPARD_45
Requirement: Functional FMECA shall be performed and documented for the SAR Instrument and
for the Service Platform subsystems, indicating criticality levels without probability of occurrence.
ID : L2B_SPARD_46
Requirement: Satellite functional FMECA down through the subsystem level shall be performed to
determine possible modes of failures and their effects on mission objectives.
ID : L2B_SPARD_47
Information: Satellite level FMECA starts during conceptual design and trade studies to establish
boundaries within which the fault is contained and the SAR instrument is capable of meeting its
mission objectives.
ID : L2B_SPARD_48
Requirement: Satellite level FMECA (or equivalent analysis method) shall:
(a) Identify failure modes of each unit.
(b) Identify how the failure mode is detected.
(c Identify the effects of the failure on mission objectives.
(d) Create a list of candidates for fault protection and the mitigation approach.
(e) Consider all phases of the mission
ID : L2B_SPARD_49
5.1.4.2 Interface FMECA
ID : L2B_SPARD_50
Requirement: Interface FMECA shall be performed and documented:
(a) At the fault containment boundaries identified in satellite level FMECA.
(b) SAR Instrument to service platform interfaces.
(c) Flight hardware to ground support equipment interface (FMEA).
ID : L2B_SPARD_51
Requirement: The interface FMECA shall as a minimum:
(a) Consider all phases of the mission;
(b) Verify that failures in SAR instrument interface circuitry will not propagate to and potentially
damage the satellite;
(c) Verify that failures cannot propagate through an interface to disable or damage: (1) redundant
hardware and (2) redundancy switching hardware;
(d) Verify that failures in any test equipment interface circuitry will not propagate to and
damage/degrade the flight hardware.
ID : L2B_SPARD_52
5.1.4.3 Fault Tree analysis (FTA)
ID : L2B_SPARD_53
Requirement: FTA shall be performed on mechanisms and electromechanical hardware by
addressing:
(a) Failure modes capable of occurring down to the lowest point at which corrective action could be
implemented.
(b) Generate a matrix of potential corrective action.
ID : L2B_SPARD_54
Information: Mechanical FMECAS in lieu of FTAS is an acceptable method on a case-by-case
basis. Reliability approval is required.
ID : L2B_SPARD_55
5.1.4.4 Worst Case analysis (WCA)
ID : L2B_SPARD_56
Comisión Nacional de Actividades Espaciales (CONAE)
Page 9 of 28
S.P.A.R.D
SAO-PAS-RS-00001-A
Requirement: A WCA shall be performed and documented for all circuit designs determined to be
critical by the project reliability engineer or contractor/supplier equivalent
ID : L2B_SPARD_57
Requirement: For non critical circuits where WCA is not required, analysis shall be performed to
demonstrate that the hardware end of life performance is not affected.
ID : L2B_SPARD_58
Requirement: The analysis shall demonstrate that appropriate operating margins as defined by
the project reliability engineer exist under all operating conditions and performance requirements
by considering the cumulative effects of the following:
(a) Part case temperature obtained from thermal analysis.
(b) Piece part initial tolerance.
(c) Part aging for the operating life of the mission including ground test time.
(d) Radiation effects (TID).
ID : L2B_SPARD_59
Information: If part case temperature is not available from thermal analysis, use 20°C plus base
plate.
ID : L2B_SPARD_60
Requirement: Worst case analysis shall include all environmental factors including shock,
vibration and vacuum where those conditions will contribute to variation in circuit parameters,
voltage, frequency and load variations.
ID : L2B_SPARD_61
Requirement: The WCA shall:
(a) Be an Extreme Value Analysis (EVA).
(b) Include the protective circuitry to ensure proper operation if a fault were to occur.
(c) Consider electrical noise on power lines, including ground differences, and interface signal
lines.
(d) Consider transient conditions.
ID : L2B_SPARD_62
Information: On a case by case basis, one of the following is an acceptable method in lieu of EVA
without a need for a waiver:
(1) Temperature-voltage-frequency margin test.
(2) Root Sum Square (RSS).
(3) Monte Carlo.
ID : L2B_SPARD_63
Requirement: the radiation and temperature used in WCA shall be:
(a) Radiation: per [R.D.7] document.
(b) Temperature: per [R.D.7] document.
ID : L2B_SPARD_64
Information: If a temperature rise of +20° C is assumed in the worst case analysis the result of
thermal analysis indicates a part temperature outside of the range used in the analysis, the WCA
must be amended to take into account the thermal analysis predicted temperature.
ID : L2B_SPARD_65
5.1.4.5 Electronic part test analysis (PSA)
ID : L2B_SPARD_66
Requirement: PSA shall be performed to verify that the applied stress on each piece part does not
exceed the derating values established: [A.D.16] for all hardware.
ID : L2B_SPARD_67
Requirement: The voltages and temperatures used in the analysis shall be:
(a) Voltage: Maximum and minimum operating voltage.
(b)Temperature: per [R.D.7].
ID : L2B_SPARD_68
Information: If thermal analysis indicates a part temperature outside of the range used in the
analysis, the PSA must be amended to take into account the thermal analysis predicted
temperature.
Comisión Nacional de Actividades Espaciales (CONAE)
Page 10 of 28
S.P.A.R.D
SAO-PAS-RS-00001-A
ID : L2B_SPARD_69
5.1.4.6 Single event effects analysis (SEE)
ID : L2B_SPARD_70
Requirement: Circuits containing SEE sensitive electronic parts shall be analyzed to determine
the effects of SEE and to assure compliance with subsystem level requirements (see radiation
requirements).
ID : L2B_SPARD_71
Requirement: Irreversible SEE shall not be permitted for the life of the mission.
ID : L2B_SPARD_72
Requirement: Temporary loss of function or data due to SEE shall not compromise the satellite,
nor impact mission science requirements, nor prevent rapid recovery to full performance
conditions.
ID : L2B_SPARD_73
5.1.4.7
Thermal and Structural Analysis
ID : L2B_SPARD_74
Requirement: Thermal and structural analyses shall be performed and documented. The analysis
shall:
(a) Address the effect of the thermal environment, including worst case estimate.
(b) Generate piece part and junction temperatures for electrical parts.
(c) Demonstrate structural design margin exists.
ID : L2B_SPARD_75
5.1.5 Problem/Failure Reporting (P/FR)
ID : L2B_SPARD_76
Requirement: A closed-loop Failure Reporting, Analysis, and Corrective Action System shall be
implemented to assure anomalies are thoroughly investigated, properly documented and that
corrective actions are implemented in a timely fashion. Contractor Non conformance (NC) Closed
Loop System is also acceptable. All NCs that affect / impact other subsystems or the mission shall
be reported to the Project Mission Assurance and Mission System Engineering. The following
requirements regarding PFR system shall apply only to CONAE and those contractors/suppliers
which adopt this system for the SAOCOM Project
ID : L2B_SPARD_77
Requirement: Problem/ Failure Reports (P/FR) shall be used for:
(a) Flight (FLT) hardware.
(b) Software in acceptance test and all subsequent tests.
(c) Support equipment (hardware and software) when testing with item (a) or (b).
ID : L2B_SPARD_78
Requirement: Formal P/FR shall begin with:
(a) QEM or FLT Electronic hardware at the board level beginning at first application of power.
(b) Mechanical or electromechanical, the first functional /performance test of the hardware,
qualification model, flight model or protofligth model.
(c) Software to begin at acceptance testing.
(d) Support equipment hardware and software (including test and facility equipment) while testing
items listed in (a) and/or (b) above.
(e) Hardware damage or safety violations to QEM or flight hardware, facilities or personnel.
(f) Test software while testing the items listed in (a) or (b) above.
ID : L2B_SPARD_79
Requirement: P/FR shall be written for any of the following:
(a) All hardware failure, damage, problems, malfunctions, anomalies, nonstandard or unexpected
results, and incidents of performance outside specification limits; also incidents of anomalous
dynamic performance such as glitches, drifts, transients, stepping, oscillation, etc within
specification.
(b) All software and procedure problems, errors, ambiguities encountered with software while
utilized with SAOCOM hardware or while being checked in preparation for operation with
Comisión Nacional de Actividades Espaciales (CONAE)
Page 11 of 28
S.P.A.R.D
SAO-PAS-RS-00001-A
SAOCOM hardware or while in the workstation environment.
(c) All Support equipment, test equipment, or test facilities problem, failure, and anomalous
performance, including procedure and operator actions, while being utilized in conjunction with
SAOCOM hardware or while being checked in preparation for operation with SAOCOM hardware.
(d) All incidents involving actual or potential damage to hardware, software, or injury to personnel.
ID : L2B_SPARD_80
Requirement: The individual in charge of the activity, the SAOCOM hardware, software, test
equipment, or support equipment at the time when a reportable incident occurs shall have the
primary responsibility to originate the P/FR; however any individual observing a reportable incident
is responsible to originate a P/FR.
ID : L2B_SPARD_81
Requirement: Each problem/failure report shall be assigned two factored assessment which leads
to a statement of risk as follows:
(a) “Failure Effect Rating”, the first factor, is an assessment of the consequence or impact of the
problem or failure if it had occurred in flight. Redundancy shall not be considered in making this
assessment.
(b) “Failure Cause /Corrective Action Rating”, the second factor is an assessment of the certainty
that the exact failure cause has been determined and that the corrective action will mitigate the risk
of recurrence of the problem/failure in flight.
ID : L2B_SPARD_82
Requirement: definition of risk ratings in [A.D. 1] or equivalent, shall be used to risk rate PFRs.
ID : L2B_SPARD_83
Requirement: All reportable incidents:
(a) Shall be documented within one working day of incident/ observation and risk rated within sixty
days of occurrence of the incident.
(b) For contractor generated P/FR:
1. Initial contactor notification and coordination with its customer shall be within one working day of
the incident and
2. Initial contractor submittal shall consist of a form defined by the SAOCOM Mission Assurance &
Safety Manager (MAM), and/or his designee’s, on a contractor form. The form shall be submitted
to the customer within two working days of the incident.
3. Final Submittal shall consist of updated releases of contractor's closed report, signed by
contractor product Assurance manager with copies of all referenced supplemental data/ document
not previously submitted.
ID : L2B_SPARD_84
Requirement: Each P/FR shall be subjected to a review, approval, and closure process as follows:
(a) The cognizant engineer and the reliability engineer, shall perform a preliminary review of each
P/FR.
(b) Each P/FR shall be assessed and rated for safety concerns, assigned a cause code, and a
cause/corrective action rating.
(c) Electronic parts and environmental test technical specialist shall review and approve P/FRs
related to their disciplines for closure.
(d) Closure of a P/FR requires that all signatures are on P/FR in the following order:
1. Cognizant engineer and Project Element Manager (PEM), or equivalent position at CONAE, for
and Individual Responsible for the item for all P/FRs.
2. Reliability Engineer, for all P/FRs.
3. System Engineer, or his designee’s, for P/FRs which:
i. Results in Engineering Change Request (ECR) to hardware or software
ii. Results in waiver to level 4 or higher functional requirements.
iii. Have an unknown cause
iv. Have a cause / corrective action rating of 3 or 4.
4. Safety Engineer, shall review all P/FRs to assess for hardware or personnel safety.
In general, the designee’s are called “Safety Engineers” and are designed by SMASM.
5. Mission Assurance manager, for all P/FRs with a risk rating grater than 1 / 1.
6. Project Manager (PM) for Red Flag P/FRs.
(e) Closure of Contractor P/FR risk rated greater than 1 / 1 requires CONAE reliability signature
Comisión Nacional de Actividades Espaciales (CONAE)
Page 12 of 28
S.P.A.R.D
SAO-PAS-RS-00001-A
ID : L2B_SPARD_85
Requirement: Contractor generated P/FR risk rated as red flag requires contractor project
manager and contractor Product Assurance Manager approval and signature.
ID : L2B_SPARD_86
Requirement:Each contractor organization external to CONAE that is providing SAOCOM
hardware and/or software shall:
(a) Establish a system for controlling and monitoring the status of P/FR generated under its
cognizant.
(b) Meet the requirements of this document.
(c) Impose these requirements down to the subcontractors and suppliers.
ID : L2B_SPARD_87
Information: For SAOCOM H/W and SW, SAOCOM personnel/designee will review and approve
the PFRs.
ID : L2B_SPARD_88
Information: Each partner will use its own P/FR form as defined in their respective Mission
Assurance or Product Assurance Implementation Plan.
ID : L2B_SPARD_89
5.2 Parts
ID : L2B_SPARD_90
Requirement: All parts shall satisfy the SAOCOM environmental requirements as specified in
[R.D.7].
ID : L2B_SPARD_91
5.2.1 EEE Parts
ID : L2B_SPARD_92
Requirement: EEE parts shall meet at least NASA level 2 parts requirements.
ID : L2B_SPARD_93
Requirement: Level 1 parts shall be used where available and within cost and schedule
constraints.
ID : L2B_SPARD_94
6.2.1.1 Standard Parts
ID : L2B_SPARD_95
Definition: Standard parts are defined as those that meet or exceed the following reliability
standards: (a) [A.D.4]; (b) [A.D.6], Class K; (c) [A.D.10], Class V;
(d) [A.D.9] JANS; (e) [A.D.5]; (f) [A.D.6], Class H; (g) [A.D.7], Class B;
(h) [A.D.10], Class Q; (i) [A.D.9], JANTXV; (j)[A.D.14];
ID : L2B_SPARD_96
5.2.1.2 Non Standard Parts
ID : L2B_SPARD_97
Definition: A Non-Standard Part is defined to be a part that does not meet the minimum quality
and reliability criteria of standard parts in descripted above.
ID : L2B_SPARD_98
Requirement: A list of non-standard parts proposed for up screening shall be generated by the
contractor and approved by the procuring agency.
ID : L2B_SPARD_100
Requirement: All non-standard parts approved by the procuring agency shall be upgraded /
screened according to the standard part definitions.
ID : L2B_SPARD_101
Requirement: Plastic parts, which are non-standard by default, shall be screened in accordance
with [A.D.18], or equivalent.
ID : L2B_SPARD_102
Comisión Nacional de Actividades Espaciales (CONAE)
Page 13 of 28
S.P.A.R.D
SAO-PAS-RS-00001-A
Information: Unique, custom parts (e.g., ASICs and Custom Hybrids) and commercial parts
(COTS, PEM's, etc.) are also considered nonstandard parts.
ID : L2B_SPARD_103
5.2.2 Application Specific Integrated circuit (ASIC) Requirements
ID : L2B_SPARD_104
5.2.2.1 Digital ASIC Test
ID : L2B_SPARD_105
Requirement: Digital logic circuitry in ASICs (including microprocessor, micro-controller and all
custom designs) shall be tested to at least 95% stuck-at fault coverage as is defined by [A.D.8],
Method 5012.
ID : L2B_SPARD_106
Requirement: Quiescent current (all vector IDDQ method) tests shall be based on a set of vectors
that will toggle 99% of the nodes.
ID : L2B_SPARD_107
Requirement: As a minimum, the following additional tests shall be conducted on Digital ASICs:
(a) Operating speed (or maximum testable speed) functional test to verify all functions of the
design.
(b) DC and AC parametric test vectors.
ID : L2B_SPARD_108
5.2.2.2 Mixed Signal ASIC Test
ID : L2B_SPARD_109
Requirement: For mixed-signal ASICs, the digital portions shall be tested as above, digital ASIC
tests. The analog portions shall be modeled and tests performed to measure the correspondence
of the actual part performance to the models.
ID : L2B_SPARD_110
5.2.3 Custom Hybrid, MCM and HDI Microcircuits
ID : L2B_SPARD_111
Requirement: Custom hybrid devices designed and fabricated by non-QML sources shall be in
conformance with requirements of Class K reliability level of [A.D.6].
ID : L2B_SPARD_112
Requirement: Custom hybrid QML sources shall be in conformance with Class H reliability level of
[A.D.6].
ID : L2B_SPARD_113
Requirement: Document review and pre-cap inspection shall be performed for all hybrids prior to
seal.
ID : L2B_SPARD_114
Requirement: All substrates for use in custom hybrids or MCM, shall be subjected to [A.D.6]
substrate element evaluation.
ID : L2B_SPARD_115
Requirement: All Low Temperature Co-fired ceramic (LTCC) substrates shall be qualified and
screened through a Project approved screening and qualification program.
ID : L2B_SPARD_116
5.2.4 Destructive Physiscal analysis (DPA)
ID : L2B_SPARD_117
Requirement: Non Standard Parts shall be subjected to DPAs and RGA (cavity devices) per the
requirements of [A.D.15] for each manufacturing lot date code. DPA/RGA is not required when
approved by the parts specialist (i.e. for parts subjected to SCSI or full visual inspections)
ID : L2B_SPARD_118
Comisión Nacional de Actividades Espaciales (CONAE)
Page 14 of 28
S.P.A.R.D
SAO-PAS-RS-00001-A
Requirement: Ceramic capacitors rate to 100V or less and used in 10V or less applications shall
be subjected to DPA and proven to have a dielectric thickness of at least 20 microns (0.8 mils)
before being approved for use.
ID : L2B_SPARD_119
5.2.5 Particle Impact Noise Detection (PIND)
ID : L2B_SPARD_120
Requirement: Non Standard cavity devices shall require PIND testing in accordance with [A.D.8],
Method 2020, Condition “A”. Parts being PIND tested will be subject to one pass only. Rejects will
be removed from the lot and reminder of the parts will be considered acceptable.
ID : L2B_SPARD_121
5.2.6 Solid Tantalum Style Capacitor Additional Screening
ID : L2B_SPARD_122
Requirement: All solid tantalum capacitors shall be subjected to 100% surge current testing.
ID : L2B_SPARD_123
Requirement: CWR type capacitors shall be tested in accordance with test option B of [A.D.11]
ID : L2B_SPARD_124
Requirement: CSR type capacitors shall be tested in accordance with the appropriate slash sheet
of [A.D.12].
ID : L2B_SPARD_125
5.2.7 Radiation
ID : L2B_SPARD_126
Information: References to "Part Specialists" or "Radiation Specialists" below, refer to the
"Procuring Agency's Specialists".
ID : L2B_SPARD_127
Requirement: All parts shall be evaluated for radiation Total Ionizing Dose (TID), Displacement
Damage (DD) and Single Event Effect (SEE) sensitivity in accordance to the radiation levels
specified in the [R.D.7].
ID : L2B_SPARD_128
Requirement: All parts evaluated to be radiation sensitive:
(a) Shall undergo characterization testing and /or lot acceptance testing in accordance with
CONAE, or
(b) Shall demonstrate by analysis based on test data to be compatible with the SAOCOM radiation
levels.
ID : L2B_SPARD_129
Requirement: Device types that are not fabricated using a radiation hardened process shall be
subjected to Radiation Lot Acceptance Testing (RLAT).
ID : L2B_SPARD_130
Requirement: All linear bipolar and BiCMOS ICs shall be evaluated for susceptibility to Enhanced
Low Dose Rate Sensitivity (ELDRS). Radiation specialist shall review and approve these parts for
use.
ID : L2B_SPARD_131
Requirement: ELDRS test plan and procedure shall be approved by radiation specialist.
ID : L2B_SPARD_132
Requirement: All flight parts shall operate within post-irradiation specification limits following
exposure to twice the expected total dose environment (i.e., RDF of 2) specified in [R.D.7].
ID : L2B_SPARD_134
Requirement: All devices shall operate within specification limits following exposure to twice the
expected environment (i.e., RDF of 2) specified in [R.D.7].
ID : L2B_SPARD_135
Comisión Nacional de Actividades Espaciales (CONAE)
Page 15 of 28
S.P.A.R.D
SAO-PAS-RS-00001-A
Requirement: All microcircuits containing bistable elements (e.g. flip-flops, counters, RAMs,
microprocessors, etc.) shall be characterized to a fluency of 10E7 ions/cm² so that an upset rate
calculation can be performed.
ID : L2B_SPARD_136
Requirement: The criteria for evaluating part Single Event Upset (SEU) acceptability shall be:
(a) No upsets observed during SEU testing with LET of 75 MeV-cm2/mg, or
(b) Verification of device bit error rate of 10E-10 per day or better in the galactic cosmic ray
environment, or
(c) Calculation of a device's upset rate shall be equal to or less than the required circuit upset rate,
as determined by circuit SEU analysis.
Note: in those cases where the component is not according with part (b) of this requirement, e.g.
mass memories, it is necessary (obligatory) to implement detection and correction error system, in
order to comply with part (b).
ID : L2B_SPARD_137
Requirement: All devices (including those with epitaxial layers) shall be subject to latch-up
evaluation.
ID : L2B_SPARD_138
Requirement: The criteria for evaluating part Latch-up acceptability shall be:
(a) part does not exhibit latch-up to an LET of 75 MeV-cm2 /mg, or
(b) verification confirms the device latch up probability in the mission environment to be < 10E-4
/device-year for parts that exhibit latch up between 35 Mev-cm2/mg and 75 MeV-cm2/mg, or
(c) the device passes a radiation test to a fluency of 10E7 ions/cm2. Test plan and procedure shall
be reviewed and approved by designated radiation specialist prior to testing.
ID : L2B_SPARD_139
Requirement: A waiver is required for LET sensitive devices used in the circuits with latch up
protection circuitry.
ID : L2B_SPARD_140
Requirement: All power MOSFETs operated in the off-mode shall be evaluated for, single event
gate rupture (SEGR) at the worst-case application VGS. The survival voltage (VDS) shall be
based on exposure to a minimum fluency of 10E6 ions/cm² of an ion with a minimum LET of 37
MeV-cm2/mg and with a range greater than 100 microns. The application voltage shall be derated
to 75% of the established survival voltage.
ID : L2B_SPARD_141
Requirement: All power transistors operated in the off-mode shall be evaluated for, single event
burnout (SEB) at the worst-case application VBE (for bipolar devices) or VGS (for MOS devices).
The survival voltage (VCE or VDS) shall be based on exposure to a minimum fluency of 10E6
ions/cm² of an ion with a minimum LET of 37 MeV-cm2/mg and with a range greater than 100
microns. Testing shall be performed with normal beam incidence and at room ambient
temperature. Test requirements for single event burnout shall be identical to those for SEGR
except that the drain current (or collector current for bipolar transistor) shall be measured to
determine if burnout occurs. The application voltage shall be derated to 75% of the established
survival voltage.
ID : L2B_SPARD_142
Requirement: Parts for which a SET would unacceptably impact system operation shall be
evaluated for SET.
ID : L2B_SPARD_143
5.2.8 Implementation requirements
ID : L2B_SPARD_144
Requirement: All non-standard parts shall be approved by MRB.
ID : L2B_SPARD_145
Requirement: Part specialist shall be a member of the Application Specific Integrated Circuit
(ASIC) design team and attend ASIC design meetings.
ID : L2B_SPARD_146
Requirement: All ASIC developments shall have PDR, CDR and manufacturing Readiness
Review.
Comisión Nacional de Actividades Espaciales (CONAE)
Page 16 of 28
S.P.A.R.D
SAO-PAS-RS-00001-A
ID : L2B_SPARD_147
Requirement: Part specialist shall be a member of the Custom Hybrid, MCM and HDI
Microcircuits design team and attend the design meetings.
ID : L2B_SPARD_148
Requirement: All hybrid, MCM and HDI developments shall have PDR, CDR and manufacturing
Readiness Review.
ID : L2B_SPARD_149
Requirement: A list of part types used by the design organization shall be reviewed against
available alerts from space organizations or similar through the project life cycle.
ID : L2B_SPARD_150
Requirement: A final "as-designed" parts list shall be reviewed by part specialist prior to CDR.
ID : L2B_SPARD_151
Requirement: Failure analysis shall be performed on all parts that failed during or subsequent to
screening to determine if failure was lot dependent.
ID : L2B_SPARD_152
5.3 Quality assurance (QA)
ID : L2B_SPARD_153
5.3.1 Quality Management System (QMS)
ID : L2B_SPARD_154
Requirement: CONAE-PC shall implement a Mission Assurance Plan in accordance to ESA
requirements.
All sub-tier contractors shall implement a Product Assurance Plan in accordance to the
requirements of SAO-PAS-RS-00002 “PA Plan for subcontractors” and submit it for approval to
CONAE-PC.
Those subcontractors that are ISO 9001 certified, may issue the required PA Plan as part of their
quality management system and make reference to relevant documentation.
ID : L2B_SPARD_155
Requirement: CONAE-C PA area shall audit the contractors PA Plans.
ID : L2B_SPARD_156
Requirement: Contractors shall flow down SAOCOM requirements to sub-tier vendors and ensure
that sub-tier vendors supporting the SAOCOM Project produce hardware and services that meet
the requirements.
ID : L2B_SPARD_157
Requirement: Contractors shall qualify their sub-tiers prior to contract award and for the
monitoring and quality of parts produced by sub-tier vendors.
ID : L2B_SPARD_158
Requirement: Upon request, the contractors shall make available to CONAE-PC PA area the
records of their activities related to the implementation of their PA Plans.
ID : L2B_SPARD_159
Requirement: Contractor shall designate at least one person as the manager or lead dedicated to
the SAOCOM Project representing the contractor's Product Assurance organization.
ID : L2B_SPARD_160
Requirement: Contractors shall identify Mandatory Inspection Points (MIPS) and inform CONAEPC in advance of the schedule for MIPs.
ID : L2B_SPARD_161
Requirement: CONAE-PC PA representative shall have access to appropriate areas of the
contractors facilities.
ID : L2B_SPARD_162
Requirement: CONAE-PC PA representative shall be notified of meetings, reviews, testing, test
set-ups, inspection points, and other activities in advance
ID : L2B_SPARD_163
Requirement: A minimum of three working days notice to CONAE -PC PA for itinerant source
inspections is required.
Comisión Nacional de Actividades Espaciales (CONAE)
Page 17 of 28
S.P.A.R.D
SAO-PAS-RS-00001-A
ID : L2B_SPARD_164
5.3.2 Critical Processes
ID : L2B_SPARD_165
Requirement: Contractors shall successfully demonstrate the capability to conduct critical
processes that affect the quality of the parts or hardware being built.
ID : L2B_SPARD_166
Information:
(1) Contractors' capabilities can be demonstrated using various methods including metrics and
process control charts.
(2) Critical processes include but are not limited to the following:
(a) Plating,
(b) Anodizing,
(c) Heat treating,
(d) Welding,
(e) Soldering,
(f) Polymeric applications,
(g) Cleaning,
(h) Die attachment,
(i) Wire bonding,
(j) Magnetic Particle inspection,
(k) Radiographic inspection,
(l) Ultrasonic inspection,
(m) Liquid penetration inspection
ID : L2B_SPARD_167
Requirement: All quality control processes used such as Electro-Static Discharge control plan,
workmanship standards; contamination control shall meet or exceed requirements contemplated
on the corresponding document (e.g. for Contamination control, corresponds [R.D.1]).
ID : L2B_SPARD_168
5.3.3 Quality Records and Controlled Documents
ID : L2B_SPARD_169
Requirement: Hardware provider shall retain quality Records and furnish them to SAOCOM
project upon request or delivery of the component to the project.
ID : L2B_SPARD_170
Requirement: Hardware provider shall maintain full traceability on all hardware designed as flight,
flight spare, engineering model, ground support equipment and other critical equipment that
interfaces with flight hardware.
ID : L2B_SPARD_171
Requirement: Hardware provider shall maintain and deliver records of S/W Requirements, Users
Guides and S/W Acceptance Tests results.
ID : L2B_SPARD_172
Requirement: Hardware provider shall include a data package sufficient enough to validate a
component's pedigree as flight worthy and to support a failure investigation, if necessary.
Requirement for EIDP and as-Built-Data will be defined in the Purchase Order or Contract
Statement of Work (SOW).
ID : L2B_SPARD_173
5.3.4 Non conformance reporting
ID : L2B_SPARD_174
Requirement: Contractors shall have a closed loop reporting system for the handling of nonconformances with a means to measure the effectiveness of any corrective action taken, in
accordance to SAO-PAS-PR-00001 subcontractors non conformance control
ID : L2B_SPARD_175
Comisión Nacional de Actividades Espaciales (CONAE)
Page 18 of 28
S.P.A.R.D
SAO-PAS-RS-00001-A
Requirement: Non-conformances Review Board activities occurring at CONAE-PC shall be
reviewed and approved by CONAE-C PA area. .
ID : L2B_SPARD_176
Requirement: Similarly, Material Review Board activities occurring at the sub-tiers shall be
reviewed and approved by SAOCOM project management.
ID : L2B_SPARD_177
5.3.5 Handling, Packaging, Shipping, and Storage Control
ID : L2B_SPARD_178
Requirement: Hardware provider shall have documented and approved processes for handling,
packaging, shipping, and storage of critical hardware.
ID : L2B_SPARD_179
Requirement: Non-conforming hardware shall be kept (segregated) in areas only designated for
non-conforming hardware with precautions made to prevent the co-mingling of these parts with
other acceptable hardware.
ID : L2B_SPARD_180
Requirement: All EEE parts and materials procured for SAOCOM shall be segregated and stored
in a dedicated store space.
ID : L2B_SPARD_181
5.3.6 Control Assembly, Test, and Launch Operation Support
ID : L2B_SPARD_182
Requirement: QA shall provide the necessary support, as determined by Mission Assurance
Management, to ensure correct and safe integration of hardware deliverables. QA activities shall
include, but not be limited to:
(a) Review and certification of transportation vehicles.
(b) Receiving inspection.
(c) Surveillance and monitoring to assure compliance to satellite processing and testing
procedures.
(d) Performing and documenting necessary inspections.
(e) Monitoring and verification of satellite closeout procedures.
(f) Verification of flight ready status prior to LV integration.
(g) Verification of compliance to procedures and requirements regarding satellite processing in
preparation for Launch Vehicle integration.
(h) Participation in Launch Vehicle Integration Readiness Reviews.
(i) Ensure Project Handling Constraints are clearly identified and that integration procedures are in
compliance.
(j) Monitoring and ensuring contamination control procedures are followed.
ID : L2B_SPARD_183
5.3.7 Training
ID : L2B_SPARD_184
Requirement: Hardware provider shall provide adequate training and certification to personnel to
insure they are qualified to perform critical processes.
ID : L2B_SPARD_185
Requirement: Hardware providers shall ensure that sub-tier contractor personnel are
appropriately qualified and certified.
ID : L2B_SPARD_186
5.3.8 Software (S/W) Quality Assurance
ID : L2B_SPARD_187
Information: S/W quality assurance applies to both, SAOCOM Service-Platform and SAR
instrument.
ID : L2B_SPARD_188
Comisión Nacional de Actividades Espaciales (CONAE)
Page 19 of 28
S.P.A.R.D
SAO-PAS-RS-00001-A
5.3.8.1 S/W Development Process
ID : L2B_SPARD_189
Requirement: Equipment providers shall follow the established processes and standards specified
in the contractor developed S/W Management Plan (SMP).
ID : L2B_SPARD_190
5.3.8.2 Requirement Traceability
ID : L2B_SPARD_191
Requirement: Two-way requirement traceability shall be established:
(a) SAOCOM Specification/ Contactor Developed Functional Requirements to S/W Requirements.
(b) S/W Requirements to S/W Design/Implementation.
(c) S/W Requirements to S/W Acceptance Tests.
ID : L2B_SPARD_192
5.3.8.3 S/W Reviews
ID : L2B_SPARD_193
Requirement: Contractor SQAE shall participate in the following S/W related reviews to assure
adequacy, consistency and completeness of the Contractor Implementation Plan:
• Software Architecture Design Review.
• Software Detailed Design Review.
• Software Test Readiness Review.
ID : L2B_SPARD_194
Requirement: A SQAE from each software development organization shall assure that the action
items/defects resulting from the S/W reviews are tracked and resolved.
ID : L2B_SPARD_195
Requirement: A S/W inheritance review shall be performed for inherited S/W to ensure that the
inherited S/W meets project requirements
ID : L2B_SPARD_196
Requirement: SQAE shall ensure that all S/W deliverables as specified in the SMP, CDRLs, and
DRDs are verified and validated prior to any S/W delivery review or S/W Review/Certification
Requirement review (SRCR).
ID : L2B_SPARD_197
5.3.8.4 S/W Verification and Validation (V&V)
ID : L2B_SPARD_198
Requirement: Software development organization shall report test coverage matrix to ensure
adequate S/W test coverage.
ID : L2B_SPARD_199
Requirement: All software development review shall have a defined scope and pass/fail criteria.
ID : L2B_SPARD_200
Requirement: Contractor shall have an independent review process that assures the S/W
Acceptance Test shall cover the following:
(a) Stress testing
(b) Reused S/W tested in the operating environment.
(c) Fault Protection functions
ID : L2B_SPARD_201
Requirement: All the following items of the S/W and firmware destined for Qualification,
Protofligth, Flight, Flight Spares, shall be subjected to Contractor SQA evaluations:
(a) Accuracy of as-built product identification
(b) Proper Test Plan/Procedures/Reports have been released
(c) Installation Manual
(d) List of open/closed PFR or liens against this delivery.
ID : L2B_SPARD_202
Comisión Nacional de Actividades Espaciales (CONAE)
Page 20 of 28
S.P.A.R.D
SAO-PAS-RS-00001-A
5.3.8.5 S/W Configuration Management
ID : L2B_SPARD_203
Requirement: SQAE shall ensure that the project follows S/W configuration management
procedures in accordance with the Project Information, IT and Configuration Management Plan.
ID : L2B_SPARD_204
5.3.8.6 S/W Engineering Change Request
ID : L2B_SPARD_205
Requirement: SQAE shall participate in assessing the impact of the S/W ECRs. Prior to S/W
SRCR, contractor SQAE shall perform this function.
ID : L2B_SPARD_206
5.4 Safety Requirements
ID : L2B_SPARD_207
5.4.1 General Safety Design Requirements
ID : L2B_SPARD_208
Information: The number of design inhibits required to prevent an overall system failure or mishap
is based on the failure or mishap result.
ID : L2B_SPARD_209
5.4.1.1 Catastrophic Hazard
ID : L2B_SPARD_210
Information: A catastrophic hazard can result in the potential for a disabling or fatal personnel
injury or for loss of facilities or equipment (e.g., ground processing facility, launch vehicle, other
payload).
ID : L2B_SPARD_211
Requirement: If a system failure may lead to a catastrophic hazard, the system shall have at least
three inhibits (dual fault tolerant).
ID : L2B_SPARD_212
5.4.1.2 Critical Hazard
ID : L2B_SPARD_213
Information: A critical hazard can result in damage to equipment, a personnel injury or in the
unscheduled use of saving procedures, that affect operators/operation of the SAOCOM.
ID : L2B_SPARD_214
Requirement: If a system failure may lead to a critical hazard, the system shall have at least two
inhibits (single fault tolerant).
ID : L2B_SPARD_215
5.4.1.3 Marginal Hazard
ID : L2B_SPARD_216
Requirement: If a system failure may lead to a marginal hazard, the system shall have at least a
single inhibit (no fault tolerant).
ID : L2B_SPARD_217
5.4.1.4 Return to Safe State
ID : L2B_SPARD_218
Requirement: Systems shall be able to be brought to a safe state with the loss of an inhibit.
ID : L2B_SPARD_219
Comisión Nacional de Actividades Espaciales (CONAE)
Page 21 of 28
S.P.A.R.D
SAO-PAS-RS-00001-A
5.4.1.5 Independent and Verifiable
ID : L2B_SPARD_220
Requirement: All inhibits shall be independent and verifiable, common cause failures shall be
considered.
ID : L2B_SPARD_221
5.4.1.6 Electrical and mechanical hardware
ID : L2B_SPARD_222
Requirement: Design inhibits shall consist of electrical and/or mechanical hardware.
ID : L2B_SPARD_223
5.4.1.7 Operator Controls
ID : L2B_SPARD_224
Requirement: Operator controls shall not be considered a design inhibit.
ID : L2B_SPARD_225
Information: Operator controls are considered an inhibition control.
ID : L2B_SPARD_226
5.4.2 Documentation Requirements
ID : L2B_SPARD_227
Requirement: SAOCOM shall comply with Launch Safety Package (LSP) submittal, reviews, and
approval process as defined in launch site safety requirement document.
ID : L2B_SPARD_228
5.4.3 Flight System Design Requirements
ID : L2B_SPARD_229
Requirement:SAOCOM Flight System Design requirements shall be in accordance with what it
has been defined in [A.D.19].
ID : L2B_SPARD_230
5.4.3.1 Material Handling Equipment
ID : L2B_SPARD_231
Requirement: SAOCOM shall comply with general requirements for Material Handling Equipment
(MHE) as defined in [A.D.19].
ID : L2B_SPARD_232
6.4.3.2 Cranes and Hoists
ID : L2B_SPARD_233
Requirement: SAOCOM shall comply with Cranes and Hoists requirements as defined in
[A.D.19].
ID : L2B_SPARD_234
5.4.3.3 Removable, Extendable, and Hinged Personnel Work Platforms
ID : L2B_SPARD_235
Requirement: SAOCOM shall comply with requirements for the design, inspection, and test of
personnel work platforms as defined in [A.D.19].
ID : L2B_SPARD_236
5.4.3.4 Man-Rated Baskets
ID : L2B_SPARD_237
Requirement: SAOCOM shall comply with man-rated baskets requirement as defined in [A.D.19].
Comisión Nacional de Actividades Espaciales (CONAE)
Page 22 of 28
S.P.A.R.D
SAO-PAS-RS-00001-A
ID : L2B_SPARD_238
5.4.3.5 Acoustic Hazards
ID : L2B_SPARD_239
Requirement: SAOCOM shall comply with acoustic design standards and acoustics data
requirements as defined in [A.D.19].
ID : L2B_SPARD_240
5.4.3.6 Non-Ionizing Radiation Sources
ID : L2B_SPARD_241
5.4.3.6.1 Radio Frequency Emitter
ID : L2B_SPARD_242
Requirement: SAOCOM shall comply with radio frequency emitter design standards as defined in
[A.D.19].
ID : L2B_SPARD_243
5.4.3.6.2 Laser System
ID : L2B_SPARD_244
Requirement: SAOCOM shall comply with laser system design standards as defined in [A.D.19].
ID : L2B_SPARD_245
5.4.3.7 Radioactive (Ionizing Radiation) Sources
ID : L2B_SPARD_246
Requirement: SAOCOM shall comply with radioactive sources design, standards as defined in
[A.D.19].
ID : L2B_SPARD_247
5.4.3.8 Hazardous Materials
ID : L2B_SPARD_248
Requirement: SAOCOM shall comply with hazardous materials selection criteria, test
requirements, hazardous materials environmental requirements, and data requirements as defined
[A.D.19].
ID : L2B_SPARD_249
5.4.3.9 Ground Support Pressure, Vacuum, and Hazardous Storage Systems
ID : L2B_SPARD_250
5.4.3.9.1 Definition of Ground Support Hazardous Pressure Systems
ID : L2B_SPARD_251
Information: These requirements establish minimum safety design, fabrication, installation,
testing, inspection, recertification, and data requirements for fixed, portable, or mobile ground
support hazardous pressure systems. Ground support systems include aerospace ground
equipment (AGE), ground support equipment (GSE), missile support systems, real property
installed equipment (RPIE), and industrial property. Ground support hazardous pressure systems
are defined as follows: (1) systems used to store and transfer hazardous fluids such as cryogens,
flammables, combustibles, and hypergols; (2) systems with operating pressures that exceed 250
psig; (3) systems with stored energy levels exceeding 14,240 ft lb; (4) systems that are identified
by Range Safety as safety critical.
ID : L2B_SPARD_252
5.4.3.9.1.1 Ground Support Pressure System Requirements
ID : L2B_SPARD_253
Comisión Nacional de Actividades Espaciales (CONAE)
Page 23 of 28
S.P.A.R.D
SAO-PAS-RS-00001-A
Requirement: SAOCOM shall comply with ground support pressure vacuum and storage systems
requirements as defined in [A.D.19].
ID : L2B_SPARD_256
5.4.3.9.1.2 Ground Support Pressure Systems Certification
and Recertification
ID : L2B_SPARD_257
Requirement: SAOCOM shall comply with requirements as defined in [A.D.19] for all ground
support pressure systems certification and recertification.
ID : L2B_SPARD_258
5.4.3.10 Flight Hardware Pressure System and Pressurized Structure General
Requirements
ID : L2B_SPARD_259
Requirement: SAOCOM shall comply with requirements as defined in [A.D.19] for flight hardware
pressure system and pressurized structure.
ID : L2B_SPARD_260
5.4.3.11 Flight Hardware Pressure Vessel Design, Analysis, and Test
Requirements
ID : L2B_SPARD_261
Requirement: SAOCOM shall comply with requirements as defined in [A.D.19] for flight hardware
pressure vessel design, analysis, and test.
ID : L2B_SPARD_262
5.4.3.12 Flight Hardware Metallic Pressurized Structure Analysis and Test
Requirements
ID : L2B_SPARD_263
Requirement: SAOCOM shall comply with flight hardware metallic pressurized structure analysis
and test requirements as defined in [A.D.19].
ID : L2B_SPARD_264
5.4.3.13 Flight Hardware Special Pressurized Equipment Design, Analysis,
and Test Requirements
ID : L2B_SPARD_265
Requirement: SAOCOM shall comply with flight hardware special pressurized equipment design,
analysis, and test requirements as defined in [A.D.19].
ID : L2B_SPARD_266
5.4.3.14 Flight Hardware Pressure System Component Design and Test
Requirements
ID : L2B_SPARD_267
Requirement: SAOCOM shall comply with flight hardware pressure system component design
and test requirements as defined in [A.D.19]. Included are hydraulic, pneumatic, hypergolic, and
cryogenic system components.
ID : L2B_SPARD_268
5.4.3.15 Flight Hardware Pneumatic System Design Requirements
ID : L2B_SPARD_269
Requirement: SAOCOM shall comply with flight hardware pneumatic system design requirements
as defined in [A.D.19].
ID : L2B_SPARD_270
Comisión Nacional de Actividades Espaciales (CONAE)
Page 24 of 28
S.P.A.R.D
SAO-PAS-RS-00001-A
5.4.3.16 Flight Hardware Hydraulic system Design, and Test Requirements
ID : L2B_SPARD_271
Requirement: SAOCOM shall comply with flight hardware hydraulic system design and test
requirements as defined in [A.D.19].
ID : L2B_SPARD_272
5.4.3.17 Flight Hardware Hypergolic Propellant System Design and Test
Requirements
ID : L2B_SPARD_273
Requirement: SAOCOM shall comply with flight hardware hypergolic propellant system design
and test requirements as defined in [A.D.19].
ID : L2B_SPARD_274
5.4.3.18 Flight Hardware Cryogenic Systems Design and Test Requirements
ID : L2B_SPARD_275
Requirement: SAOCOM shall comply with flight hardware cryogenic systems design and test
requirements as defined in [A.D.19].
ID : L2B_SPARD_276
5.4.3.19 Flight Hardware Pressure Systems Data Requirements
ID : L2B_SPARD_277
Requirement: SAOCOM shall comply with flight hardware pressure systems data requirements
as defined in [A.D.19].
ID : L2B_SPARD_278
5.4.3.20 Ordnance System
ID : L2B_SPARD_279
Requirement: SAOCOM shall comply with ordinance hazard classification requirements as
defined in [A.D.19].
ID : L2B_SPARD_280
5.4.3.21 Ordnance System General Requirements
ID : L2B_SPARD_281
Requirement: SAOCOM shall comply with ordinance system general requirements as defined in
[A.D.19].
ID : L2B_SPARD_282
5.4.3.22 Ordnance Electrical and Optical Circuits
ID : L2B_SPARD_283
Requirement: SAOCOM shall comply with ordnance electrical and optical circuits requirement as
defined in [A.D.19].
ID : L2B_SPARD_284
5.4.3.23 Initiator Electrical and Optical Circuits
ID : L2B_SPARD_285
Requirement: SAOCOM shall comply with initiator electrical and optical circuits requirements as
defined in [A.D.19].
ID : L2B_SPARD_286
5.4.3.24 Ordnance Safety Devices
ID : L2B_SPARD_287
Comisión Nacional de Actividades Espaciales (CONAE)
Page 25 of 28
S.P.A.R.D
SAO-PAS-RS-00001-A
Requirement: SAOCOM shall comply with ordnance safety devices requirements as defined in
[A.D.19].
ID : L2B_SPARD_288
5.4.3.25 Ordnance Initiating Devices
ID : L2B_SPARD_289
Requirement: SAOCOM shall comply with ordnance initiating devices requirements as defined in
[A.D.19].
ID : L2B_SPARD_290
5.4.3.26 Explosive Transfer Systems and Receptor Ordnance
ID : L2B_SPARD_291
Requirement: SAOCOM shall comply with explosive transfer systems and receptor ordnance
requirements as defined in [A.D.19].
ID : L2B_SPARD_292
5.4.3.27 Ordnance Test Equipment
ID : L2B_SPARD_293
Requirement: SAOCOM shall comply with ordnance test equipment requirements as defined in
[A.D.19].
ID : L2B_SPARD_294
5.4.3.28 Ordnance Data Requirements
ID : L2B_SPARD_295
Requirement: SAOCOM shall comply with ordnance data requirements as defined in [A.D.19].
ID : L2B_SPARD_296
5.4.3.29 Electrical and Electronic Ground Support Equipment and Flight
Hardware General Design Requirements and Standards
ID : L2B_SPARD_297
Requirement: SAOCOM shall comply with electrical and electronic ground support equipment
and flight hardware general design requirements and standards as defined in [A.D.19].
ID : L2B_SPARD_298
5.4.3.30 EGSE Design Requirements
ID : L2B_SPARD_299
Requirement: SAOCOM shall comply with EGSE design requirements as defined in [A.D.19].
ID : L2B_SPARD_300
5.4.3.31 Electrical and Electronic Flight Hardware
ID : L2B_SPARD_301
Requirement: SAOCOM shall comply with electrical and electronic flight hardware requirements
as defined in [A.D.19].
ID : L2B_SPARD_302
5.4.3.32 Computer Systems and Software General Requirements
ID : L2B_SPARD_303
Requirement: SAOCOM shall comply with computer systems and software general requirements
as defined in [A.D.19].
ID : L2B_SPARD_304
Comisión Nacional de Actividades Espaciales (CONAE)
Page 26 of 28
S.P.A.R.D
SAO-PAS-RS-00001-A
5.4.3.33 Determination of Safety Critical Computer System Functions
ID : L2B_SPARD_305
Requirement: SAOCOM shall identify all safety critical computer system functions (SCCSFs).
These functions are defined as any computer system function that, (1) if not performed, (2) if
performed out of sequence, or (3) if performed incorrectly, may directly or indirectly cause a safety
hazard to exist. Safety critical computer system functions include, but are not necessarily limited
to: (a) software used to control and/or monitor safety critical systems, (b) software used for fault
detection in safety critical computer hardware or software, (c) software used to transmit safety
critical data, including time-critical data and data about hazardous conditions, (d) software that
responds to the detection of a safety critical fault, (e) FTS software, (f) software that computes
safety critical data, (g) software used to access safety critical data, (h) processor interrupt software
associated with previously designated safety critical computer system functions. [A.D.19].
ID : L2B_SPARD_306
5.4.3.34 Hardware and Software Safety Design Requirements
ID : L2B_SPARD_307
Requirement: SAOCOM shall comply with hardware and software safety design requirements as
defined in [A.D.19].
ID : L2B_SPARD_308
5.4.3.35 Software Requirements
ID : L2B_SPARD_309
Requirement: SAOCOM shall comply with software requirements as defined in [A.D.19].
ID : L2B_SPARD_310
5.4.3.36 Computer System and software Data Requirements
ID : L2B_SPARD_311
Requirement: SAOCOM shall comply with computer system and software data requirements as
defined in [A.D.19].
ID : L2B_SPARD_312
5.4.3.37 Seismic Design
ID : L2B_SPARD_313
Requirement: SAOCOM shall comply with anchorage or restraint requirements as defined in
[A.D.19].
ID : L2B_SPARD_314
5.4.3.38 Basic Seismic Design
ID : L2B_SPARD_315
Requirement: SAOCOM shall comply with basic seismic design requirement as defined in
[A.D.19].
ID : L2B_SPARD_316
5.4.3.39 Seismic Data Requirements
ID : L2B_SPARD_317
Requirement: SAOCOM shall comply with seismic data requirements as defined in [A.D.19].
ID : L2B_SPARD_318
5.4.4 Ground Support Personnel, Equipment, Systems, and Material
Operations Safety Requirements
ID : L2B_SPARD_319
Comisión Nacional de Actividades Espaciales (CONAE)
Page 27 of 28
S.P.A.R.D
SAO-PAS-RS-00001-A
Requirement: SAOCOM shall comply with safety requirements for ground personnel and
equipment, systems, and material operations on the ranges as defined in [A.D.19].
ID : L2B_SPARD_320
5.4.5 Mishap Reporting
ID : L2B_SPARD_321
Requirement: all Contractor employees are responsible for reporting mishaps immediately. In the
event that a mishap is serious (defined above), the Contractor shall immediately notify Project
Management. All mishaps shall be documented on a Mishap Report and forwarded to Project
Management.
ID : L2B_SPARD_322
Requirement: When a mishap reporting occurs, an Initial Mishap Report shall be sent to
SAOCOM Systems Safety Engineer within 24 hours of the mishap.
ID : L2B_SPARD_323
5.4.6 Lifting Device
ID : L2B_SPARD_324
Requirement: The testing, inspection, maintenance, operational, and operator and rigger
certification/ re-certification / licensing requirements apply to new and existing lifting devices and
equipment. All lifting devices and equipment shall comply with NASA Standards, [A.D.3]. or
equivalent defined by CONAE.
Comisión Nacional de Actividades Espaciales (CONAE)
Page 28 of 28