FAA AC 20-107B Certification Cost Reduction — PatSnap Eureka
Reduce Aircraft Composite Certification Costs Under FAA AC 20-107B
More than 60 patents and literature sources reveal four proven strategies—shared material databases, virtual FEM testing, supplier equivalency frameworks, and design-for-certification—that together slash the physical test burden for novel aircraft composite structures.
Shared Qualification Databases: The Highest-Leverage Mechanism
The FAA's Building Block Approach, complemented by NCAMP and AGATE shared databases, distributes coupon test costs across multiple certification programs—eliminating the need to regenerate hundreds of material allowables.
Structured Verification from Coupons to Full-Scale
The Building Block Approach structures verification evidence from coupons through sub-components to full-scale articles. Each tier validates computational assumptions made at a lower tier, so that the number of expensive full-scale tests can be justified and minimized. The Aircraft Airworthiness Institute (China, 2011) established that the BBA is built on residual-strength-versus-damage-size relationships, allowable ultimate load damage limits, and limit-load-capability damage thresholds.
Reduces full-scale test countAccept Pre-Qualified Allowables Without Repeating Coupon Campaigns
Because NCAMP places fully documented qualification data in the public domain, a new applicant can accept previously generated A-basis and B-basis allowables if their material and process controls match the qualified specification, eliminating the need to repeat hundreds of coupon tests. The Aircraft Airworthiness Institute (2011) frames this as the principal mechanism for cost reduction under FAA AC 20-107B.
Eliminates coupon repetitionStructure-Specific Allowables Reduce Unnecessary Conservatism
Beihang University (2021) proposed an algorithm that assigns structure-specific compression allowables based on measured initial delamination statistics and damage factor models, rather than applying a single conservative blanket allowable to all structural locations. This targeted approach can raise permissible stress levels for lightly damaged regions, reducing the degree of structural conservatism that would otherwise drive additional weight, redesign, and re-test cycles. Access PatSnap analytics to explore related patent landscapes.
Targeted allowables per locationProgram-Level Damage Thresholds Avoid Per-Location Revisits
Maintenance-relevant damage thresholds defined once at the program level—rather than revisited for each structural location—represent a significant cost-reduction mechanism. The BBA framework ensures that allowable ultimate load damage limits and limit-load-capability damage thresholds are established systematically, preventing the costly repetition of threshold determination for each new structural region.
One-time program-level definitionCertification Cost Drivers: What the Patent Data Shows
Analysis of 60+ patents and literature sources reveals where the largest cost-reduction opportunities lie across the BBA pyramid and supplier qualification lifecycle.
AVIC Xi'an Equivalency Scoring Dimensions
Four evaluation dimensions used to score material equivalency for aviation composite supplier changes, replacing expert judgment with a documented, technically defensible scoring system (AVIC Xi'an, 2023).
BBA Pyramid: Physical Tests vs. Analytical Substitution
FAA AC 20-107B accepts validated analysis as compliance evidence. The proportion of tests addressable by FEM simulation increases at lower BBA tiers, concentrating physical test effort where analytical uncertainty is highest.
Virtual FEM Testing as a Substitute for Physical Certification Tests
A central cost-reduction lever permitted under FAA AC 20-107B is the substitution of validated analytical models for certain categories of physical tests. The Moscow Aviation Institute (2021) formalized a "computational and experimental research pyramid" that mirrors BBA levels, explicitly stating that this integrated approach allows replacement of part of the certification tests with numerical modelling. Effects of manufacturing cycle parameters on final structural performance are captured within the model, avoiding the need for separate manufacturing-variation test campaigns.
The University of Patras (2022) demonstrated that computer-aided FEA can simulate different seat configuration concepts, identifying whether a preliminary design will pass structural and biomechanical requirements before any physical article is manufactured, saving development time and certification cost. PatSnap's life sciences and engineering solutions support similar analytical substitution workflows.
Post-buckling numerical simulation provides another avenue for reducing conservatism and test count. Magnaghi Aeronautica (2023) illustrated a methodology that abandons the conservative no-buckling-up-to-ultimate-load assumption, directly simulating the post-buckling non-linear regime. Because more realistic structural behavior is captured analytically, compliance demonstration can be documented computationally at a fraction of the cost of a dedicated post-buckling test article.
Boeing Research and Technology (2019) identified inaccurate three-dimensional property measurement—particularly interlaminar tensile strength—as a source of model conservatism that inflates test count requirements. Accurate through-thickness property measurement via digital image correlation reduces scatter in the model, narrowing the confidence intervals that must be bracketed by physical tests. Korean airworthiness standards, as confirmed by Hankyong National University (2021), explicitly recommend that analytical methods be used to verify structural safety where analysis technology is sufficiently developed.
Structured Equivalency Frameworks Avoid Full Re-Qualification
Two patent applications from Chinese aerospace institutions directly address the highest-impact supplier-change cost problem with frameworks that classify what must genuinely be re-tested versus what can be credited from prior data.
| Strategy | Source / Year | Mechanism | Cost Impact | Key Differentiator |
|---|---|---|---|---|
| Supplier Change Classification | Shanghai Aircraft Mfg, 2025 | Differentiates type-design vs. non-type-design changes; only genuinely changed verification activities are repeated | High reduction | Eliminates automatic full re-qualification trigger |
| 4-Dimension Equivalency Scoring | AVIC Xi'an, 2023 | Scores basic performance, design allowables, process performance, and typical element performance with pre-weighted coefficients | High reduction | Replaces unstructured expert judgment with documented scoring |
| NCAMP Shared Allowables | Aircraft Airworthiness Institute, 2011 | Accept publicly documented A/B-basis allowables if material and process controls match qualified specification | Highest reduction | Eliminates hundreds of coupon tests per program |
| Static Test Rationalization | COMAC Composite Center, 2021 | Strain coverage principles screen load cases before test setup design, reducing number of configurations on expensive full-scale articles | Significant | Structured aerodynamic-to-test load transformation |
| Delamination-Based Allowables | Beihang University, 2021 | Structure-specific allowables from measured delamination statistics eliminate blanket conservatism | Significant | Raises permissible stress for lightly damaged regions |
Monitor Supplier Equivalency Patent Activity in Real Time
Set alerts for new filings from Shanghai Aircraft Manufacturing, AVIC Xi'an, and COMAC.
Certification Cost Begins at the Design Stage
Structural configuration, manufacturing process, and repair strategy each carry implicit certification liabilities that can be anticipated and managed before design freeze, preventing costly late-stage redesigns.
Reliability-Based Manufacturing Cost Optimisation
The University of Ferrara (2022) presents a methodology coupling a bottom-up cost model with a genetic algorithm and deep neural network to optimize ply stacking sequence simultaneously for manufacturing cost and buckling reliability. Certification-unfriendly configurations—those with high variability or poor damage tolerance—can be eliminated before any physical article is built, reducing the probability of test failures that force expensive redesign and re-certification loops.
Modular Architecture Lowers Repair Certification Burden
Dronamics (2016) demonstrated that designing fuselage or wing panels as assemblies of identical, replaceable modules rather than monolithic parts can reduce both fabrication cost and repair cost. For certification purposes, the smaller, repeated modules can be individually qualified at lower cost, and replace-and-requalify strategies for damaged modules avoid the need for special-purpose repair qualification data for every damage size combination.
Key Players in AC 20-107B Cost-Reduction Innovation
Analysis of assignee frequency across 60+ patents and literature sources reveals four distinct clusters of sustained innovation relevant to composite certification cost reduction. Explore the full landscape on PatSnap Analytics.
Chinese Civil Aviation & Defense Institutions
CAAC, Aircraft Airworthiness Institute, COMAC Composite Center, Shanghai Aircraft Design and Research Institute, Shanghai Aircraft Manufacturing, and AVIC Xi'an together produce the densest body of directly relevant certification methodology work. Their output covers BBA/NCAMP analysis (2011), full-scale static test rationalization (2021), supplier change equivalency patents (2023, 2025), and design allowable algorithms (2021). This reflects China's active effort to develop indigenous regulatory expertise aligned with FAA AC 20-107B as COMAC aircraft seek international certification. See how aerospace teams use PatSnap.
BBA · NCAMP · Supplier equivalencyEuropean Aerospace Research Bodies & Universities
Moscow Aviation Institute (computational pyramid, 2021), University of Ferrara (cost-optimized stacking sequence, 2022), Cranfield University (multidisciplinary cost modelling, 2019), VZLU Czech Aerospace Research Centre (NDT fatigue test protocols, 2021), Magnaghi Aeronautica (post-buckling simulation, 2023), and SAAB/Linköping University (DFM strategy, 2014) collectively provide the methods-development underpinning for virtual test substitution and design-for-certification. Their work operationalizes the analytical substitution provisions of AC 20-107B. Explore their patents via PatSnap Open API.
FEM substitution · DFM · Cost modellingBoeing Research & Technology
Boeing's contribution on three-dimensional property measurement (2019) addresses a persistent accuracy gap in composite material characterization that constrains the reliability of analytical substitution. Accurate through-thickness interlaminar tensile strength measurement via digital image correlation reduces scatter in FEM models, directly enabling leaner test pyramids by narrowing the confidence intervals that must be bracketed by physical tests. The EASA and FAA both accept this approach as compliance evidence.
DIC · Interlaminar strength · Model accuracyANH Structures — GUI-Based BBA Compliance Tools
Two active Korean patents (2023, 2025) on GUI-based composite strength analysis systems from ANH Structures indicate a commercial product market forming around automated BBA compliance documentation tools. Their systems evaluate fastener stability, joint stability, and buckling stability of certified composite materials, covering in-plane failure rate, buckling failure rate, joint failure rate, and adhesive failure rate—automating the analyst-hours required to produce compliance documentation for joint-critical BBA pyramid portions. Access PatSnap materials solutions for related analysis.
GUI automation · BBA documentationCertification Cost-Reduction Workflow and Supplier Scoring Breakdown
How structured equivalency evaluation and the computational pyramid interact to reduce total certification expenditure under FAA AC 20-107B.
AC 20-107B Cost-Reduction Decision Pathway
Sequential decision pathway from design concept to certification compliance, identifying where each cost-reduction strategy applies within the BBA framework.
Assignee Cluster Distribution Across 60+ Sources
Distribution of patent and literature sources by institutional origin, reflecting China's dominant output volume in AC 20-107B certification methodology alongside European and US contributions.
FAA AC 20-107B Composite Certification Cost — key questions answered
The Building Block Approach (BBA) structures verification evidence from coupons through sub-components to full-scale articles. Each tier in the BBA is designed to validate computational assumptions made at a lower tier, so that the number of expensive full-scale tests can be justified and minimized. It is complemented by the AGATE and NCAMP programs, which allow sharing of material databases furnished by suppliers across multiple certification programs, thereby distributing qualification costs among many users.
Shared databases directly reduce the single largest cost component in composite certification: generating statistically valid material allowables (A-basis and B-basis values). Because NCAMP places fully documented qualification data in the public domain, a new applicant can accept previously generated allowables if their material and process controls match the qualified specification, eliminating the need to repeat hundreds of coupon tests.
Yes. FAA AC 20-107B accepts validated analysis as compliance evidence across the BBA pyramid. The Moscow Aviation Institute (2021) formalized a computational and experimental research pyramid that mirrors BBA levels, explicitly stating that this integrated approach allows replacement of part of the certification tests with numerical modelling. Korean airworthiness standards also explicitly recommend that analytical methods be used to verify structural safety where analysis technology is sufficiently developed, with the numerical method serving as the primary verification tool and test results used for validation rather than primary evidence.
Not necessarily. Structured equivalency frameworks can dramatically reduce repeat test scope. Shanghai Aircraft Manufacturing (2025) patented a methodology that differentiates between type-design-data changes and non-type-design-data changes caused by a supplier transition, identifying only those verification activities that must genuinely be repeated. AVIC Xi'an (2023) proposed a scored material comparison system evaluating four dimensions—basic performance, design allowables, process performance, and typical element performance—to provide a documented, technically defensible basis for the equivalency determination.
Modular structural architecture—designing fuselage or wing panels as assemblies of identical, replaceable modules rather than monolithic parts—can reduce both fabrication cost and repair cost compared to large single-piece structures. For certification purposes, the smaller, repeated modules can be individually qualified at lower cost, and replace-and-requalify strategies for damaged modules avoid the need for special-purpose repair qualification data for every damage size combination, as demonstrated by the Dronamics repair cost analysis (2016).
Early-stage multidisciplinary cost modelling anchored to certification-relevant design attributes is essential for preventing costly late redesigns. By incorporating certification-relevant attributes—structural concept, damage tolerance classification, inspection accessibility—into the cost model at the concept stage, program managers can compare certification-friendly and certification-unfriendly configurations before design decisions become locked, avoiding the costly late-stage redesigns that inflate total program certification expenditure, as described by Cranfield University (2019).
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References
- Study on Airworthiness Requirements of Composite Aircraft Structure for Transport Category Aircraft in FAA — Aircraft Airworthiness Institute, China Academy of Civil Aviation Science and Technology, Civil Aviation Administration of China, 2011
- Aircraft Composite Structures Integrated Approach: A Review — Moscow Aviation Institute (National Research University), 2021
- Structural Analysis of a Composite Passenger Seat for the Case of an Aircraft Emergency Landing — Department of Mechanical Engineering and Aeronautics, University of Patras, 2022
- Algorithm for Compression Design Allowable Determination of Composite Laminates with Initial Delaminations — School of Chemistry, Beihang University, 2021
- Airworthiness Verification Method for Changes in Composite Structural Component Suppliers — Shanghai Aircraft Manufacturing Co., Ltd., CN pending, 2025
- Composite Material Equivalency Evaluation Method for Aviation Applications — AVIC Xi'an Aircraft Design Research Institute, CN pending, 2023
- Reliability-Based Bottom-Up Manufacturing Cost Optimisation for Composite Aircraft Structures — Department of Architecture, University of Ferrara, 2022
- Aircraft Cost Modelling, Integrated in a Multidisciplinary Design Context — Centre for Aeronautics, Cranfield University, 2019
- Design for Manufacturing of Composite Structures for Commercial Aircraft – The Development of a DFM Strategy at SAAB Aerostructures — Linköping University / SAAB Aerostructures, 2014
- Repair of Composites: Design Choices Leading to Lower Life-Cycle Cost — Dronamics Ltd., 2016
- Measurement of Interlaminar Tensile Strength and Elastic Properties of Composites Using Open-Hole Compression Testing and Digital Image Correlation — Boeing Research & Technology, The Boeing Company, 2019
- Non-Destructive Inspection of Composite Aileron during Fatigue Test — VZLU Czech Aerospace Research Centre, 2021
- Non-Linear Analysis in Post-Buckling Regime of a Tilt Rotor Composite Wing Structure Using Detailed Model and Robust Loading Approach — Magnaghi Aeronautica (MA Group Company), 2023
- Numerical Evaluation of Structural Safety of Linear Actuator for Flap Control of Aircraft Based on Airworthiness Standard — School of ICT, Robotics & Mechanical Engineering, Hankyong National University, 2021
- The Design of Static Test Scheme for Composite Aileron Structure of Large Aircraft — Composite Center, COMAC, 2021
- Aviation Certified Composite Material Bolted Joint, Bonded Joint, and Buckling Stability Evaluation System — ANH Structures, KR active, 2023
- Apparatus for Evaluating Strength Analysis of Aviation Certified Composite Material — ANH Structures, KR active, 2025
- Proof of a Composite Repair Concept for Aeronautical Structures: A Simplified Method — Université de Toulouse / ICA, 2019
- Federal Aviation Administration (FAA) — Regulatory authority for FAA AC 20-107B composite structure airworthiness guidance
- European Union Aviation Safety Agency (EASA) — European counterpart regulatory framework for composite aircraft structure certification
All data, patent citations, and institutional attributions on this page are sourced from the references above and from PatSnap's proprietary innovation intelligence platform. Patent status information is current as of the publication date of this page.
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