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PHA or other hazard analysis techniques may include, but are not limited to:
·  Structure/integrity of main structure
·  Thermal Protection System (e.g., ablative coating)
·  Temperature Control System (if needed to control environment for other critical systems)
·  Main Propulsion System
·  Propellant Tanks
·  Power Systems
·  Propellant Dumping System
FAA System Safety Handbook, Chapter 13: Launch Safety
December 30, 2000
13 -6
·  Landing Systems
·  Reentry Propulsion System
·  Guidance, Navigation and Control System(s), Critical Avionics (Hardware and Software) -
includes Attitude, Thrust and Aerodynamic Control Systems
·  Health Monitoring System (hardware and software)
·  Flight Safety System (FSS)
·  Flight Dynamics (ascent and reentry) for stability (including separation dynamics) and
maneuverability
·  Ground Based Flight Safety Systems (if any) including telemetry, tracking and command and
control systems
·  Depending on the concept, additional “systems” might include pilot and life support systems
and landing systems if they materially affect public health and safety
·  Others identified through hazard analysis
13.4.2 Validation of Safety Critical Systems
Through the system safety process, the applicant demonstrates that the proposed vehicle design and
operations satisfy regulatory requirements and that the system is capable of surviving and performing
safely in all operating environments including launch, orbit, reentry and recovery. Documentation must
show adequate design, proper assembly, and vehicle control during all flight phases. Documentation is
expected to consist of design information and drawings, analyses, test reports, previous program
experience, and quality assurance plans and records.
AST uses a pre-application consultation process to help a potential applicant to understand what must be
documented and to help identify potential issues with an applicant’s proposed activities that could
preclude its obtaining a license. The pre-application process should be initiated by the applicant early in
their system development (if possible during the operations concept definition phase) and maintained
until their formal license application is completed. This pre-application process should be used to provide
AST with an understanding of the safety processes to be used, the safety critical systems identified,
analysis and test plan development, analysis and test results, operations planning and flight rules
development.
Analyses may be acceptable as the primary validation methodology in those instances where the flight
regime cannot be simulated by tests, provided there is appropriate technical rationale and justification.
Qualification tests, as referenced in the safety demonstration process and the System Safety Program
Plan, are normally conducted to environments higher than expected. For example, expendable launch
vehicle (ELV) Flight Safety Systems (FSS) are qualified to environments a factor of two or higher than
expected. (See Figure 13-2) These tests are conducted to demonstrate performance and adequate design
margins and may be in the form of multi-environmental ground tests, tests to failure, and special flight
tests. Such tests are normally preceded with detailed test plans and followed by test reports.3
3 Test plans are important elements of the ground and flight test programs. Such plans define, in advance, the nature of the test (what
is being tested and what the test is intended to demonstrate with respect to system functioning, system performance and system
reliability). The test plan should be consistent with the claims and purpose of the test and wherever appropriate, depending on the
purpose of the test, clearly defined criteria for pass and fail should be identified. A well-defined test plan and accompanying test
report may replace observation by the FAA.
FAA System Safety Handbook, Chapter 13: Launch Safety
December 30, 2000
13 -7
Figure 13-2: Relationship of Use Environment to Qualification Test
Use Environment
Qualification
Test Environment
Vibration
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p
e
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a
t
u
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e
In addition, Quality assurance (QA) records are useful in establishing verification of both design
adequacy and vehicle assembly and checkout (workmanship).
Table 13-1, Validation Acceptance Matrix, identifies sample approaches that may be employed to
validate acceptance for critical systems. Examples of types of analyses, ground tests, and flight tests are
　
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