only by the ability of the applied proof test stress conditions to screen the 
critical initial flaw size for operation by causing failure, leak, or other clearly detectible damage to the part during the 
proof test. Just as in the workmanship proof test, the adequacy of a proof test for quantitative flaw screening is likely to 
vary throughout the part. Demonstrating the adequacy of a quantitative proof test is non-trivial and must be coordinated 
intently with the structures and fracture control communities. 
2 Fatigue-critical surfaces are locations where fatigue analysis and surface condition assumptions influence the outcome of 
the structural assessment. 

4.4.1 Quality 
Management 
Systems 
[AMR-13] A QMS compliant to SAE AS9100, Quality Management Systems – Requirements for Aviation, Space, and 
Defense Organizations, or an alternate QMS approved by the CEO and NASA, documented or referenced in the AMCP, shall 
be in place for all entities involved in the design, production, and post-processing of AM hardware. 

4.5 Equipment and 
Facility Control 
Plan (EFCP) 
[AMR-14] All equipment integral to the AM process, and facility-specific processes and procedures, shall be under the control 
of a CEO-approved EFCP developed in accordance with NASA-STD-6033, Additive Manufacturing Requirements for 
Equipment and Facility Control, prior to the production of flight hardware. 

4.6 Fracture Control [AMR-15] All AM parts used in hardware subject to fracture control shall be classified and assessed to NASA-STD-5019 with 
the following limitations: 
a. AM parts are not to be categorized as non-fracture critical low-risk parts, per NASA-STD-5019. 
b. AM parts are not to be categorized as fracture critical lines, fittings, and other pressurized components, per NASA-
STD-5019, section 7.2.4, and instead are to follow the general approach for assessing fracture critical metallic parts 
per NASA-STD-5019, section 7.3. 

4.7 Unplanned 
Interruptions 
[AMR-16] Any unplanned build interruption, including planned interruptions occurring outside approved limits, shall be 
documented as a nonconformance and traceable via a records management system controlled by the QMS.  

4.8.1.1 Quantitative NDE [AMR-17] All Class A parts shall receive quantitative NDE with full coverage of the surface and volume of the part, including 
verifiable detection of critical initial flaw size in fracture critical damage tolerant parts, with any cover age limitations due to 
NDE technique(s) and/or part geometry documented in the PPP per section 7.3 of this NASA Technical Standard.  

4.8.1.2 NASA-STD-5009 
Special NDE 
Approach 
[AMR-18] The NDE approach for Class A parts shall meet the Special NDE requirements of NASA-STD-5009, 
Nondestructive Evaluation Requirements for Fracture Critical Metallic Components, and be documented in the PPP. 

4.8.2.1 Process Control 
NDE 
[AMR-19] All Class B parts shall receive NDE for process control with full coverage of the surface and volume of the part, 
with any coverage limitations due to NDE technique(s) and/or part geometry documented in the PPP.  

4.8.2.2 NASA-STD-5009 
NDE Approach 
[AMR-20] The NDE approach for Class B parts shall meet the requirements of NASA-STD-5009 and be documented in the 
PPP. 

4.9 In-situ Process 
Monitoring 
[AMR-21] Prior to use as a quantitative indicator of part quality for part acceptance, passive in-situ process monitoring 
technologies shall be qualified by the CEO to the satisfaction of NASA in a manner analogous to other NDE techniques.  


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4.10 Repair and 
Rework 
[AMR-22] Explicit provisions controlling any operation used to repair or rework an AM part due to a defect (e.g., short 
feeds/fractures, cracks) or nonconformance (e.g., warping) shall be documented and implemented as follows for Class A and 
B parts: 
a. Repair operations require prior written authorization from the contract authority, as described in the AMCP.  
b. All repair operations require full documentation as a nonconformance record and are included in the production 
engineering record of the part. 
c. Unplanned part operations not part of the QPP that constitute a repair or rework include, but are not limited to, 
bending, blending, sanding, peening, grinding, machining, welding, or brazing for the purposes of defect removal 
and/or part restoration to drawing allowances. 
d. All repair operations require validation on material manufactured using the same QMP.  

4.11.1 Witness Testing 
for Independent 
Builds 
[AMR-23] All AM parts manufactured by an independent build shall include witness specimens integral to the build of the 
types and quantities required in Table 5, Metals Witness Testing Quantities and Acceptance Results for Independent Bu ilds 
(metals), and Table 6, Polymer Witness Testing Quantities and Acceptance Results for Independent Builds (polymers), 
exposed to the same post-processing documented in the QMP, and evaluated per the acceptance methodologies in Tables 5 and 
6, such that any witness test failing to meet the defined acceptance criteria is documented as a nonconformance and traceable 
via a records management system controlled by the QMS. 


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4.11.2 Witness Testing 
for Continuous 
Production Builds 
[AMR-24] All AM parts manufactured by a continuous production build shall include witness specimens integral to the build 
of the types and quantities required in Table 7, Metals Witness Testing Quantities and Acceptance Results for Continuous 
Builds, and Table 8, Polymer Witness Testing Quantities and Acceptance Results for Continuous Builds, exposed to the same 
post-processing as documented in the QMP and evaluated per the acceptance methodologies of Tables 7 and 8.  


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4.11.3 Continuous 
Production Build 
SPC 
Requirements 
[AMR-25] For Class A and B parts, to be eligible for continuous production build witness sampling, the AM machine shall be 
under SPC by meeting each of the following criteria: 
a. Machine maintains an active qualification status per NASA-STD-6033. 
b. Machine operates under the same or equivalent QMPs since the last successful SPC evaluation build or qualification 
build. 
c. Machine has produced an SPC evaluation build within 60 days, using the sample set given in Table 14 or Table 16 
and meeting the requirements of section 5.5 of this NASA Technical Standard.  
d. A minimum of 30 data points are collected from at least 10 of the most recent builds to establish control charts for 
ultimate strength, yield strength, and elongation. 
e. Control charts for ultimate strength, yield strength, and elongation are established according to ASTM E2587 and 
controlled by the QMS, with control limits compatible with the applicable PCRD. 
f. All witness specimens are exposed to the same post-processing as documented in the QMP. 
g. Builds with tensile results that violate control chart acceptance criteria are assigned a nonconformance in the QMS 
that initiates an evaluation of the part and the AM machine’s process history. 
h. Corrective actions are taken for any control chart nonconformance that cannot be specifically isolated to the 
nonconforming build. 
i. Any machine associated with an open SPC nonconformance is given inactive qualification status until the root cause 
evaluation concludes, the necessary corrective actions are complete, and the CEO concurs with the resolution. 
j. The root cause/corrective action record for a nonconformance contains the decision to either return the machine to 
active qualification or requalify the machine, and the bases for that decision. 

4.12 Serialization [AMR-26] For Class A and B parts, serialization (or equivalent) shall be used to provide part traceability to the AM build 
cycle, the location on the build area/platform within the build, all other production records, governing engineering 
documentation, and feedstock lots. 

4.13.1 Maintaining File 
Identity and 
Integrity in the 
Digital Thread 
[AMR-27] All electronic files relevant to the digital thread for an AM part shall be controlled by the QMS within a file 
management system with full version control and appropriate security, with an allowance for files to be removed f rom the file 
management system only if they are fingerprinted with a cryptographic hash to ensure unambiguous identity and integrity of 
the file. 

4.13.2 Part Model 
Integrity 
[AMR-28] For Class A and B parts, a methodology for verifying the integrity of part model(s) throughout all stages of the 
digital part definition associated with the AM process shall be documented and implemented via the AMCP. 

4.13.3 On-Machine 
Execution 
[AMR-29] Any unplanned modifications to the build file on the machine during AM process setup and/or execution shall be 
assigned a nonconformance and traceable via a records management system controlled by the QMS. 

4.14 Production 
Engineering 
Record 
[AMR-30] For Class A and B parts, the AM part production process shall be controlled by a revision-controlled production 
engineering record, consistent with the QPP, that contains, at a minimum and when applicable, records of production for the 
following: 
a. Feedstock removal for any part with geometry precluding line-of-sight confirmation. 


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b. As-built part visual inspections for any indications of build anomalies prior to processes that may alter the as -built 
state of the part. 
c. Platform removal. 
d. Support structure removal. 
e. Machining. 
f. Thermal processing: environmental conditions (times, temperatures, atmosphere/media), process specifications, 
quenching media, surface condition of the part, etc. 
g. Light-activated curing: environmental conditions (times, ambient light, temperature, atmosphere/media), process 
specifications, part orientations, wavelength, intensity, duration, etc.  
h. Joining operations (e.g., welding, brazing, soldering, adhesive bonding) that were developed and qualified to an 
appropriate aerospace standard using representative AM material. 
i. Surface treatments that are influential to the performance of the part, structural or otherwise.  
j. Part marking: part identifiers and serial numbers, including the locations and method for all marking. 
k. Cleaning and part cleanliness. 
l. Inspections, including, but not limited to, dimensional inspections, surface texture measurements, and NDE.  
m. Part handling, packaging, and shipping. 
4.15 Preproduction 
Articles 
[AMR-31] For Class A and B parts, a preproduction article evaluation verifying quality of part and material shall be 
conducted for all AM parts, with the plan for evaluation being approved as part of the PPP.  

4.16 Proof Testing [AMR-32] All Class A and B AM parts shall be proof tested as part of acceptance testing unless otherwise substantiated as 
part of the Integrated Structural Integrity Rationale in an approved PPP. 

4.17 Qualification 
Testing 
[AMR-33] All AM parts in Classes A1 through B2 shall be subject to a qualification test program that demonstrates that part 
performance and functionality meet the mission design requirements, life factors, and life -cycle capability, given the following 
stipulations: 
a. Parts for qualification testing are produced to a QPP. 
b. Any AM part that functions as part of a mechanism is subject to the qualification, design life verification, and 
acceptance testing defined by NASA-STD-5017, Design and Development Requirements for Mechanisms. 
c. The protoflight approach to qualification of hardware as defined in NASA-STD-5001 or JSC 65828, Structural 
Design Requirements and Factors of Safety for Spaceflight Hardware, which does not include a dedicated test article, 
is not considered applicable to AM hardware of Classes A1 through B2, nor is the “no test” option for verification by 
analysis only. 

4.18.1 Part Acceptance, 
Class A and B 
Parts 
[AMR-34] For Class A and B parts, data that are objective evidence of part conformance shall be a prerequisite for acceptance 
of the part by the CEO and made available to NASA upon request, including, but not limited to, information showing 
compliance to all part acceptance items listed in an approved PPP (see section 7.6 of this NASA Technical Standard).  

4.18.2 Part Acceptance, 
Class C Parts 
[AMR-35] For Class C parts, a certificate of conformance (CoC) shall be a prerequisite for acceptance of the part by the CEO 
and made available to NASA upon request 


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5.2 Unique QMPs, 
Minimum Control 
Categories 
[AMR-36] Each AM machine used to fabricate hardware shall have at least one QMP for each unique combination of the 
following control categories that affect the material condition: 
a. Feedstock specification and associated controls per section 5.4.1 of this NASA Technical Standard. 
b. Associated machine, build process controls, and restart procedures per section 5.4.2 of this NASA Technical 
Standard. 
c. Post-processing requirements per section 5.4.3 of this NASA Technical Standard.  

5.3 Configuration 
Management 
[AMR-37] Each QMP shall be controlled by the QMS and subject to configuration control.   
5.4.1.1 Virgin Feedstock 
Procurement 
[AMR-38] Feedstock to be used for a Candidate QMP shall be controlled by industry standard specifications or configuration-
controlled material specifications that levy requirements, including tolerances when applicable, to ensure consistent 
performance in the process and govern, at a minimum, the aspects of virgin feedstock production and procurement defined in 
Table 9, Virgin Powder Feedstock Controls, for powders; Table 10, Wire Feedstock Controls, for wire; Table 11, Filament 
Feedstock Controls, for filament; and Table 12, Liquid Feedstock Controls, for liquid feedstock. 


Table 9—Virgin Powder Feedstock Controls 

Powders 
a 
Requiring powder producers and distributors to operate under a QMS conforming to SAE 
AS9100, SAE AS9120, Quality Management Systems – Requirements for Aviation, Space, and 
Defense Distributors, or an equivalent approved by the CEO. 
b Specifying unambiguously the method of powder manufacture. 
c Specifying powder chemistry requirements, including acceptable methods of measurement and 
tolerance. 
d 
Specifying particle size distribution (PSD) requirements and the acceptable methods for powder 
sampling and determining the PSD, including explicit limits in weight percent on the quantity of 
coarse and fine particles outside the PSD range. 
e Specifying, at least qualitatively, the mean particle shape (powder morphology) and limits on 
satellite/agglomerated particles using standardized terminology/methodology.*   
f Controlling the blending of virgin powder heats/batches into powder lots by requiring that each 
blended powder heat/batch individually meets all requirements of the feedstock specification.  
g Prohibiting post-production additions to the powder lot for control of PSD or chemistry (doping).  
h Providing requirements for powder cleanliness and contamination control, including moisture 
content for sensitive materials. 
i Providing requirements for powder packaging, labeling, and environmental controls.  
j Specifying rheological (flow and spreading) behavior of the powder and associated method of 
verification. 
k 
Specifying a certificate of compliance be provided for all levied requirements along with 
identifiers for each powder heat and blended lot and the date(s) and location(s) of powder 
production. 
l Specifying powder crystallinity morphology control, such as solvent processing procedures and 
heat treatments, if applicable. 
* Description of powder morphology requirements should use standardized terminology to the greatest 
extent possible by following powder standards such as ASTM F1877, Standard Practice for Characterization 
of Particles, and ASTM B243, Standard Terminology of Powder Metallurgy.   


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Table 10—Wire Feedstock Controls 
Wire 
a Requiring wire producers and distributors to operate under