Parts Manufacturer Approval Procedures - with Changes 1 and 2

10/27/2023 Order 8110.42D CHG 2 Chapter 1. Administrative Information and Background 1-1. Purpose. We, the Federal Aviation Administration, or FAA, wrote this order to prescribe the responsibilities and procedures for approving replacement and modification articles for installation on type-certificated products. It implements an approval process required by Title 14, of the Code of Federal Regulations (14 CFR), part 21, subpart K for issuing a parts manufacturer approval (PMA). We also explain the role of a designated engineering representative (DER) and organization designation authorization (ODA) along with their organization management office (OMT) in the PMA process. FAA Order 8120.22, Production Approval Procedures , contains the procedures for evaluation, approval, and management of the production activities of manufacturers who produce articles under PMA.

1-2. Audience. All FAA AIR office personnel, ODAs, OMTs, and DERs who use the approval process for issuing a PMA.

1-3. Where Can I find This Order? You can find this order on the FAA website at https://www.faa.gov/regulations_policies/orders_notices/ and on the Dynamic Regulatory System website at https://drs.faa.gov .

1-4. Cancellation. FAA Order 8110.42C, Parts Manufacturer Approval Procedures , dated June 23, 2008, is canceled.

1-5. Acronyms. See appendix J, List of Acronyms.

1-6. Definitions. See appendix K, Definitions and Terms.

1-7. Deviations. Engineering and manufacturing personnel in the FAA must follow the procedures in this order and FAA Order 8120.22 to ensure a standard process for PMA. The Design and Maintenance Systems section (AIR-631) under the Policy and Standards Division (AIR-600) coordinates and dispositions any deviations from this order. If a deviation becomes necessary, the involved FAA employee substantiates and documents the need, gets concurrence from the appropriate supervisor, then sends a deviation request with concurrences for review to the Organization and Systems Policy Branch (AIR-630).

1-8. The Roles of the FAA and Applicant. Table 1, in this chapter, summarizes the respective roles of the FAA and an applicant. Applicants show and state that their articles’ designs comply with applicable regulations using the guidance in advisory circular (AC) 21.303-4. The certification branch approves these designs, and the certificate management (CM) section approves the associated production facility(s) and quality system(s). See appendix A, PMA Process Flowcharts. The certification branch adjusts its level of review and approval through the exercise of management options based on project risk. Coordination between the applicable certification branch and CM section/branch ensures that the applicant’s processes produce replacement and modification articles that conform to the approved design.

1-1 10/27/2023 Order 8110.42D CHG 2 Table 1. Summary of FAA and Applicant Roles in PMA Applicants: Certification Branches: CM Sections/Branches: • Show that the design meets the • Assess application for required • Process PMA applications based applicable airworthiness standards by items including geographical on license agreements and either of the following two ways: location. supplemental type certificates • Assess risk of the PMA project. (STCs).

(1) Show that the PMA article’s Determine Composite Risk Value • Make assessment for Undue design is identical to the design of an (CRV) and select corresponding Burden per FAA Order 8100.11, article that is covered under a type management options to set the level Developing Undue Burden and No certificate (TC), or of FAA involvement. Undue Burden Decision Papers (2) Use test and computation that • Find compliance with agency Under 14 CFR Part 21 .

shows the PMA article’s design meets regulations and standards through • Verify conformity to the the airworthiness requirements that programs and procedures to approve approved design.

apply to the affected products.

articles.

• Issue PMA supplements after • Identify installation eligibility.

• Review and complete PartSCP if approval of the article’s design and needed. establishment of the applicant’s • Ensure the article performs its production quality system.

• Review installation eligibility.

intended function(s) via a compliance • Approve the holder’s quality • Review and monitor service checklist.

difficulties. manual.

• Provide a plan for continued • Review and monitor service • Witness or delegate various operational safety (COS).

functions. difficulties.

• Perform a safety assessment by • Issue the FAA-PMA production • Review COS plan.

assessing the consequences of PMA approval letter.

• Coordinate with aircraft article failure on the next higher • Submit copies of supplement evaluation division for ICA review assembly and associated product(s).

information for publishing in DRS.

as needed.

• Provide statement that existing • Conduct surveillance at the PMA • Notify applicant of a design’s instructions for continued airworthiness holder’s and supplier’s facilities, compliance with airworthiness (ICA) are applicable to the PMA article both foreign and domestic.

requirements.

or provide draft supplemental ICAs for • Investigate and submit • Forward supplement package to the PMA article or product as necessary.

enforcement reports when PMA the CM section/branch after design • Set up and maintain a quality system holders and non-PMA holders do not approval.

that meets the requirements of comply with 14 CFR.

• Investigate and submit 14 CFR 21.307. Document this system See FAA Order 8120.22, enforcement reports when PMA in a quality manual.

Production Approval Procedures, holders and non-PMA holders do • Monitor, report, and investigate for more details.

not comply with 14 CFR.

service difficulties.

See chapter 2 for more details.

• Draft a part certificate certification plan (PartSCP) if applicable.

• Make a statement of compliance per § 21.303(a)(5).

See AC 21.303-4 for further details.

1-2

10/27/2023 Order 8110.42D CHG 2 Chapter 2. Certification Branch Responsibilities 2-1 General Responsibilities. The geographic certification branch, as specified in FAA Order 8100.5, Aircraft Certification Service Mission, Responsibilities, Relationships, and Programs , has several responsibilities for PMA applications. The project engineers at these offices make findings of compliance with applicable regulations. ODA units have nearly the same responsibilities and authorities for finding compliance of replacement articles via tests and computations as certification branch personnel. Both the certification branch and ODA unit use the same criteria to find prospective articles meet the airworthiness requirements of their respective products. However, ODA holders must develop their own procedures that follow our design approval process in PMA. The ODA responsibilities, authorities and limitations are in FAA Order 8100.15, Organization Designation Authorization Procedures . Additionally, when determined to be appropriate the use of FAA Order 8110.119, Streamline Process for Parts Manufacturer Approval (PMA) is encouraged . The certification branch has the following administrative and technical responsibilities: a. Accepts Application . The certification branch in the applicant’s geographical area accepts the application for a PMA based on identicality without a licensing agreement or test and computation. Acknowledgement of receipt of an application is optional but encouraged. Use any manner acceptable to the certification branch to include letters, email or phone calls. If the PMA basis is identicality with evidence of a licensing agreement or a STC, return the application and direct the applicant to the geographical CM section/branch per FAA Order 8120.22. If project delays are expected due to current FAA workload issues and/or project prioritization concerns, the certification branch must notify the applicant accordingly via an email or letter.

b. Confirms Location of Manufacturer . If the quality system is outside the United States, the FAA may issue or extend a PMA to foreign facilities if regulatory oversight places no undue burden on us as determined by the geographical CM section/branch. The certification branch, under the guidance of the CM section/branch, must work with the System Oversight Division (AIR-800), to determine if the oversight poses an undue burden. See FAA Order 8100.11, Requirements for Finding Undue Burden and No Undue Burden Under 14 CFR Part 21 , for more details.

c. Determines Need for a PartSCP . PartSCPs are appropriate for PMA projects that need extensive and time-consuming showings of compliance through analyses, testing or involve sophisticated manufacturing processes. These projects usually involve critical parts, life-limited parts, influencing parts (only applicable for engine life-limited parts) or articles with complex designs. The PartSCP is an agreement between the PMA applicant and the FAA on applicable documents, project schedule, certification basis, testing, conformity inspections, communication/coordination, and delegation involved in the project. See appendix B, Part Specific Certification Plan, for an example of a PartSCP. Use of the PartSCP is at the discretion of the reviewing certification branch.

2-1 10/27/2023 Order 8110.42D CHG 2 d. Assess PMA Risk . Perform a risk assessment of the prospective PMA project.

Utilize relevant guidance to obtain a level of project involvement determination. This assessment weighs organizational and technical indicators to gauge the probability of non - compliance.

(1) Consider organizational indicators like the applicant’s relationship with the FAA, safety culture, organizational stability, quality system, and use of suppliers and outside service providers. Also, consider technical indicators like the significance of the article and its design, use of new or sophisticated technologies for its manufacture and the service history of the article. Assess the applicant’s experience and capabilities to design articles that meet applicable airworthiness requirements.

(2) The article’s impact on the safety of its product indicates the severity of non - compliance with applicable airworthiness requirements. Use the applicant’s safety assessment of the article as the initial basis for this indicator. Adjust the indicator based on FAA experience and knowledge of the corresponding article from the eligible product’s type certificate (TC).

e. Engineering and Test Data . As established at the beginning of the process, the certification branch may review/verify or accept the following applicant submittals through the exercise of the above management options. The project certification branch may seek FAA expertise from other certification branches, technical policy sections, and senior technical experts as needed. Depending on the safety significance of the article, the project risk, and management options, they may: (1) Verify if the safety assessment properly characterizes the significance of the proposed article to the safety of its product.

(2) Verify if the applicant reported an acceptable service history for the original article.

(3) Verify if the applicant identified the eligibility for installation on type- certificated products.

(4) Verify the PMA application identifies airworthiness requirements applicable to the type-certificated product on which the PMA article is installed. Verify the design data is adequate to produce and conform the article.

(5) Review the differences between the proposed and original articles.

Assess the applicant’s technical justification for these differences and associated impacts on the next higher assembly and product. For example, weight and other mass properties can influence vibratory response and performance of rotating components. Also, assess the applicant’s analysis of these differences on an assembly and associated product(s). Coordinate with the accountable technical policy sections for product specific related guidance.

2-2 10/27/2023 Order 8110.42D CHG 2 (6) Assess requests by applicants for conformity inspections and engage the CM section/branch when these inspections are necessary.

(7) Review reports and approve test plans.

(8) Verify if the applicant’s substantiating data show compliance with applicable airworthiness standards.

(9) Assess the suitability of the applicant’s COS plan.

2-2 Applicant Approaches. Applicants rely on three strategies to show compliance with airworthiness standards through test reports and computations. The most common strategy combines elements of comparative analysis and direct showings of compliance to specific airworthiness requirements. See paragraph 2-8. Evaluate whether the applicant’s approach is viable and provides the needed showings of compliance for associated replacement article.

2-3 Coordination with Certificate Management Certification Branch. Coordinate with the CM certification branch and the accountable section on all critical parts, life-limited parts and influencing parts (in the case of engine life-limited parts). Coordination on other articles is at the discretion of each certification branch. When coordination is needed, send the CM certification branch a copy of the certification project notification (CPN) after notifying the accountable section. See FAA Order 8110.115 Certification Project Initiation and Certification Project Notification for the CPN form or utilize the CPN database. The CM certification branch sets the level of its involvement depending on the article’s attributes, safety significance, service history and other indicators. If the article basis is identicality, confirm with the CM certification branch (and CM section/branch when appropriate) that the applicant’s submitted manufacturing processes are identical to those for the critical, life-limited or influencing part (in the case of engine life- limited parts) produced under the TC or STC. Consult with AIR-620, Technical Policy Branch, for specific guidance on the coordination method and scope.

2-4 Verification of Installation Eligibility. Review the applicant’s evidence of eligibility.

Verify assertions and consult other information at your discretion. Illustrated parts catalogs (IPC) from TC holders provide credible information about installation eligibility for the original article, but the IPCs are not FAA-approved. Accept the use of the IPC as the sole means for showing installation eligibility only on non-critical articles (see appendix K for the definition of “critical part”). In this case, confirm the authenticity and currency of that IPC and its applicability to the PMA article. Otherwise, consider a combination of IPC and other evidence that supports eligibility.

NOTE: The records of PMA database in DRS have some inaccurate eligibility listings.

If suspect, confirm these eligibility listings with the issuing CM sections/branches or holders of the respective PMAs.

2-5 Service History Considerations. Review the applicant’s report or evidence on the service history of the original article. Identify that the article is not subject to an airworthiness directive (AD) and free of systemic continued airworthiness problems. If the original article from a type 2-3 10/27/2023 Order 8110.42D CHG 2 certificate has a potential unsafe condition and the replacement article has a similar design, perform the following: a. Reject the PMA application if an existing AD removes the associated DAH’s article from service immediately or in the future, unless the applicant shows that installing the article does not produce the same unsafe condition. Consult the CM certification branch for this determination. Inform the applicant that installation of the PMA replacement article on eligible products will require an alternative means of compliance (AMOC). Record this AMOC requirement in the notification letter of design approval and the approval basis column on the relevant supplement.

b. Consider delaying the processing or rejecting the PMA application if we are discussing or developing an AD to remove the DAH’s article from service, unless the applicant shows that the article does not have the same unsafe condition.

c. Terminating corrective action by redesign and replacement is preferable, but not always feasible. Some ADs mandate repetitive inspections of an article to prevent a condition from compromising safety. The certification branch has the discretion to consider replacement articles that retain the need for these repetitive inspections to attain an equivalent level of safety. Coordinate with the responsible CM certification branch for concurrence. Inform the applicant that installation of the PMA replacement article on eligible products will require an AMOC. Record this AMOC requirement in the Letter of Design and the approval basis column on the relevant supplement.

d. If an article is not identical or substantially identical to the TC holder’s article, confirm the applicant shows that installing their article does not create an unsafe condition.

Review relevant test reports or witness product-level and assembly-level tests. Do not encourage flight testing outside the FAA approved process.

e. If the original article has a service bulletin to remove it from service, PMA for a replacement article is still feasible. A service bulletin alone is not enough to reject a PMA application unless that service bulletin resolves functional or installation disparities that the PMA does not.

f. If the article is having service difficulties and the FAA is ACTIVELY pursuing corrective action (that is, a design change per § 21.99) with the TC holder, reject the application for PMA, unless the applicant shows that installing the article does not produce the same unsafe condition.

NOTE: Coordinate with the CM certification branch in all cases where in-service issues exist to resolve their specific concerns prior to PMA issuance. Also, consult the FAA Service Difficulty Reporting (SDR) system, Manage Safety Analyze Data (MSAD) system and the TC product support database for service difficulties.

2-6 Life-Limited Parts. Review the applicant’s substantiation of any life-limited parts.

Confirm these data include analyses and tests that establish a part’s life limit using a life system accepted by the FAA. Fatigue tests of these parts by applicants are typically essential to setting life limits. Prior to PMA issuance and/or ICA acceptance, ensure applicants have noted material, 2-4 10/27/2023 Order 8110.42D CHG 2 manufacturing, testing and process controls that preserve the life limits inherent in their designs.

Confirm the applicant publishes these life limits in their ICA. For engine articles, review the applicant’s substantiation of any influencing parts. 14 CFR 33.70 introduces the concept of influencing parts (ref. AC 33.70-1) which are engine parts that affect the environment and operating conditions of a life-limited part in that engine. If the influencing part is determined to fit the definition of a critical part, then it must be processed according to the instructions found in this order for critical parts.

2-7 Special Considerations—Identicality without a License Agreement. Make a finding of identicality if an applicant shows a PMA article’s design is the same in every respect to an article’s design from a TC, STC or TSO. Applicants must sufficiently define their designs to allow comparison of dimensions, tolerances, materials, processes, and specifications. This is typically only possible when the applicant possesses and submits, as part of their application, the original design drawing and related production specifications referenced within that drawing. After PMA approval, any major changes to the processes and/or specifications controlling the manufacture of the article (or the use of industry standards over OEM processes/specifications) should be assessed by the applicant and reviewed by the certification branch and CM certification branch as needed.

For the purposes of establishing identicality, the FAA may exclude cosmetic attributes like color.

Additionally, a finding of identicality typically infers that the existing product ICA(s) remain valid with respect to the PMA unless otherwise noted. In the event this is not the case, the certification branch must be wary of making a finding of identicality without sound engineering review and compliance determinations. It is the applicant’s responsibility to provide all necessary information and explanation regarding this issue.

NOTE: The applicant’s design need not conform to the latest revision level of the TC, STC, or technical standard order (TSO) authorization drawing when the applicant shows that the previously approved articles are still eligible for installation on the listed product models.

a. Limitations of Reverse Engineering. Take special care in evaluating identicality based on reverse engineering. Reverse engineering is one way to develop the article’s design. However, reverse engineering will not normally produce an identical design. The applicant is unlikely to show that tolerances, processes, and manufacturing specifications are identical. Reject and return applications for identicality that rely solely on reverse engineering or use analyses in their comparisons. Redirect the applicant to the test and computation method.

b. Identicality Not Found. If the design data (including the manufacturing processes) do not show that the article is identical to an article covered under a TC, reject, and return the application to the applicant. Notify the applicant that the design was not identical to that of an article covered under a TC. See appendix E, Sample Design Rejection Letter. The applicant may submit a new application package under the test and computation method.

c. Design Changes. Limit design changes on PMA articles based on identicality without a license agreement. Limit these changes to article marking, updated 2-5 10/27/2023 Order 8110.42D CHG 2 specifications, and so on. Changes to nominal dimensions, tolerances, or manufacturing process alter the basis of the PMA and require prior approval via test reports and computations method.

2-8 Special Considerations—Test Reports and Computations . The applicant shows that the proposed design complies with the applicable regulations. Many applicants will use the comparative analysis approach to compare a PMA article to a TC holder’s or licensee’s article to identify design differences and their effects on associated compliance with regulations. The comparative analysis approach must still tie back to the product’s certification basis per § 21.303 (a) and (b). This can often be accomplished by basic engineering analysis for most PMA articles; however, some designs have a greater level of complexity which requires the development of certification level testing to perform side-by-side comparisons with the original article in the actual (or adequately replicated) operating environment(s). Certification branch engineers must always involve the appropriate technical policy branch experts or senior technical experts whenever necessary to ensure compliance is found. Another approach is general analysis which simply shows direct compliance with applicable regulations. Most applicants use a combination of comparative and general analyses. Review the applicant’s design and associated showings of compliance with the applicable airworthiness requirements. Also, consult with other FAA organizations such as the technical policy branch, senior technical experts, and designees as needed to aid the design and compliance reviews.

a. Statement of Compliance. Verify the applicant’s compliance checklist for completeness. Confirm if the applicant listed the appropriate airworthiness standards, their associated means of compliance and documentation. Verify the applicant made a statement of compliance per § 21.303(a)(5).

b. Safety Assessment. Review the applicant’s assessment of the article’s safety significance and its determination as critical, non-critical, life-limited, not life-limited, influencing (for engine parts per § 33.70) or non-influencing. The basis for this determination lies in an associated failure modes effects analysis. This analysis is at least qualitative and considers the effect of article failure on the next higher assembly and its performance. Additionally, the analysis describes failure effects of the next higher assembly on the product and its performance given the failure of the embedded article.

Remember that if design changes are introduced with the PMA article, the safety assessment of the PMA part must consider all known service problems in assessing the adequacy of the design change. Review relevant criteria in 14 CFR 27.602, 14 CFR 29.602, and §§ 33.70 and 33.75. Confirm these critical/non-critical and/or life- limited or influencing determinations as necessary with the CM certification branch. Use available FAA expertise to aid in evaluating these assessments. See the criteria for critical part determinations in appendix K, Definition and Terms.

c. Reverse Engineering. Applicants typically use this process to duplicate attributes of articles without original design data. The process entails disassembly, measurement of features, and material and functional analyses of an original article. The process may need subsequent testing to confirm the article’s intended function with the PMA article installed. Review the applicant’s data to confirm it adequately defines the original’s design using appropriate sample sizes. This data defines dimensions, material 2-6 10/27/2023 Order 8110.42D CHG 2 properties (e.g., microstructure and chemical composition), special processes (e.g., welds, heat treat, coatings), and continued airworthiness requirements of both the original and duplicate article. Confirm use of qualified or accredited laboratories for analyses of materials and processes. Assess the applicant’s rationale for use of any other laboratories (such as in-house labs) in establishing the design of the article. Also, confirm that the applicant has adequately captured potential sources of variability in both the original design and the duplicate article. Potential sources of variability include processing characteristics (lots, billets, etc.), material supply vendor, and other such considerations.

NOTE: The FAA does not qualify or accredit any laboratory. However, the certification branch must have confidence that the data from all laboratories are adequate to show design compliance to the regulations. To establish the required confidence, the certification branch may need to review a laboratory’s accreditation certificate(s) and/or employee qualifications along with input from the applicable FAA senior technical expert.

d. Test Plans and Reports. Review any test plans and test results that show the article is equivalent to the original or complies with applicable airworthiness standards.

Also, verify that the results confirm the functionality of the articles in their assemblies/products. Request additional testing as needed to confirm equivalency to the original article.

e. ICA or Maintenance Instructions. Review the applicant’s proposed ICA or maintenance instructions. In both instances, coordinate the certification branch’s assessment and position with the appropriate aircraft evaluation division (AED) of the Flight Standards Service (FS) on the project CPN per FAA Order 8110.54, Instructions for Continued Airworthiness Responsibilities, Requirements, and Contents . If the applicant proposes that no new ICA or maintenance instructions are necessary, assess the applicant’s rationale for such and denote this on the CPN. Communicate acceptance of this approach in an email or a letter of notification back to the applicant upon project completion.

f. Article Design Changes – Pre PMA-Approval.

(1) Review the applicant’s assessment of an article’s effect on its product. Confirm any changes to a product’s type design from installation of the PMA article are minor.

Otherwise, direct the applicant to the STC process. Type design changes are classified by § 21.93(a) as either major or minor. Minor changes have no appreciable effect on the weight, balance, structural strength, reliability, operational characteristics, or other characteristics affecting the airworthiness of the product. All other changes are "major changes”. Also, if installation of the PMA article affects the acoustical and emissions attributes of a product then the change (article) requires special consideration and attention per § 21.93(b).

(2) Scrutinize any change to the design of a critical part. Even minor changes in this part’s design may have appreciable effects on its product. Direct the applicant to an STC for such.

2-7 10/27/2023 Order 8110.42D CHG 2 2-9 Evaluating the Drawing Package. Confirm the application includes adequate detailed design data to define the characteristics of an article sufficient to conform it. These data include drawings, technical data that confirms structural strength, article marking information, manufacturing and process specifications that define the configuration, and other pertinent data.

Confirm the drawing control procedures (e.g., revision history, or cognizant engineering offices) are commensurate with the safety significance of the article. Consider the following areas when evaluating any data package: a. Manufacturing and Process Specifications. Manufacturing procedures and process specifications may affect the article’s airworthiness. If the applicant’s detail drawings refer to a TC holder’s process specifications, then the applicant must submit these specifications in a manner determined by the certification branch. Consult with the CM certification branch as necessary to determine if these specifications affect the design’s airworthiness.

b. Source Control Drawings. Review source control drawings to determine if the applicant has proper control over the article’s configuration and manufacture. Verify the applicant submitted all applicable detail drawings and specifications. These drawings and specifications are needed to evaluate the sources listed on source control drawings. See AC 21-43, Production Under 14 CFR Part 21, Subparts F, G, K, and O , for information on supplier control guidance for PAHs. Coordinate with the responsible CM section/branch, when necessary, using a request for conformity.

c. Drawing Notes.

(1) Pay particular attention to the viability of identicality applications that use TC or technical standard orders authorization (TSOA) holder drawings or specifications with notes stating: (a) Articles supplied to this drawing shall be in strict accordance with samples (first articles) approved by ( name of applicant) engineering department unless prior written approval is given to subsequent change.

(b) Source approval is required for raw stock through total fabrication.

(c) This drawing represents a critical item and must successfully complete substantiation tests and be approved by engineering.

(d) Other similar statements implying special source selection criteria.

(2) If the applicant cannot provide the above information to support identicality, refer the applicant to the test and computation method.

d. Dimensional Tolerance.

2-8 10/27/2023 Order 8110.42D CHG 2 (1) Variations in the sample measurements and accepted engineering practices determine the tolerances in article dimensions. The resulting tolerances for the PMA article cannot exceed the minimum and maximum dimensions measured on the sampled approved parts.

Exceeding these limits requires further substantiation and acceptance by the certification branch.

(2) Reserved.

e. Material Analysis .

(1) Semi-quantitative methods of determining material properties are not supported by the FAA as acceptable for standalone processes. For such methods, additional supporting data such as maintenance manuals, service bulletins or secondary analysis methods are needed to establish a basis for comparison to the OEM material. Consulting the FAA senior technical expert is recommended to ensure the most up to date methods and practices are being used.

(2) Reserved.

2-10 Article Marking Requirements. Check the article’s marking scheme specified in its design data. The applicant must specify a permanent and legible method of marking.

14 CFR 45.15(a) sets the marking requirements for PMA articles. These markings must identify the article as “FAA-PMA”, the article’s part number and the name, trademark, or symbol of the manufacturer. The detailed marking scheme and methodology can be identified in their quality control document, a controlled process specification, an engineering order, or other acceptable means if it has traceability and is referenced in their PMA application package.

a. Marking Critical Parts. Critical parts also follow the marking requirements in § 45.14. This requirement adds a serial number or equivalent to the part markings. The method for marking a critical part is essential design data that the FAA reviews. The applicant ensures and the certification branch confirms the marking location and that the process does not degrade airworthiness. To do this, we require applicants to define the marking location and method on their drawings.

b. Marking an Assembly. Applicants apply PMA part markings required by § 45.15 to the top-level assembly of the approved replacement or modification part. We do not require applicants to mark subassemblies or individual detail parts. For example, if the top-level assembly is a hydraulic pump, mark this assembly accordingly. Marking the detail parts of the pump is optional unless production of these parts occurs under separate PMAs. When PMA holders separately sell detail parts for installation in their approved assembly, they note the information required by § 45.15 on the accompanying shipping documentation. The shipping documentation for individual detail parts of a PMA assembly must contain the information required by § 45.15(a)(1) through (3) and must identify the detail parts as subcomponents of the PMA assembly. The PMA holder’s design data may contain the marking information for detail parts of the assembly. This provides a means of tracing the individual detail parts to their related PMA assemblies.

c. Part Numbering. If the PMA part replaces an original part, the applicant assigns a part number that distinguishes the PMA part number from the corresponding TC holder part number.

Adding a prefix or suffix to the TC holder’s part number is enough as long as the prefix or suffix does not compromise the TC holder’s part marking practices. The applicant may also use a prefix or suffix to satisfy § 45.15(a)(2) requirements for marking the part with a name, trademark, or symbol.

This only applies if the prefix or suffix is consistent across the applicant’s product line. Also, each part bears “FAA-PMA” to meet another § 45.15 requirement.

2-9 10/27/2023 Order 8110.42D CHG 2 (1) Supplier Numbers. Some applicants are suppliers to PAHs. Often these PAHs use the supplier part numbers in their approved designs. When these suppliers later apply for a PMA, they may continue to use their original part numbers with the added marking requirements of 14 CFR 45.15(a)(1) and (2). These added requirements entail permanently marking the part with “FAA-PMA,” and the name, trademark, or PMA holder’s symbol.

(2) Parts Manufactured Under License . When the PMA basis is identicality by showing evidence of a licensing agreement, the PMA part may have the same number as the type-certificated part. However, we require the applicant to meet the requirements of § 45.15(a)(1) and (2) by permanently marking the part with “FAA-PMA” and the PMA holder’s name, trademark, or symbol.

d. Parts Impractical to Mark. If we find the part too small or impractical to mark all the information on it, then an attaching tag or container label must have the missing information. Often the number of eligible type-certificated products is too long to include with the part. Since the list is likely to change, a tag or label on a container may refer to the applicant’s publicly available part eligibility information. Section 45.15(b) requires making the installation-eligibility information contained in a manual or catalog readily available. Providing a manual or catalog via the Internet meets the intent of “readily available.” However, access to the Internet is not universal. The PMA holder must have an alternative means of providing the manual or catalog.

e. Marking a PMA Part on a TSO Article. Markings for a PMA part that goes on a TSO article follows the same protocols previously stated. Section 45.15 requires the holder to mark parts as prescribed per the approved design. The installation eligibility in these markings notes the name and model of each applicable type-certificated product. To meet the requirements of § 45.15, record the PMA installation-eligibility information (that is, A310-200 series, B737-300 series, and so on) on the part. Do not list the TSO identification information (that is, TSO-C149, TSO-C63C, TSO-C85A, and so on). However, if an applicant holds a TSOA on the same part, then mark the part with both PMA and TSO markings.

2-11 Conformity Inspections. Coordinate conformity inspections with the responsible CM section/branch when the article’s attributes, significance to safety, history of the applicant or other indicators warrant. These inspections are at the discretion of the certification branch with coordination from the CM section/branch. Conformity inspections confirm that a modification or replacement article complies with an approved design and that the associated manufacturing facilities have the capabilities to produce this design. FAA certification tests may require these inspections. The certification branch may accept inspection reports on non-critical articles from applicants with existing approved quality systems in place of performing conformity inspections.

The use of the National Automated Conformity Inspection Process (NACIP) is preferred; however, a hardcopy of FAA Form 8120-10, Request for Conformity, is still applicable to request an in inspection. For projects that require flight testing, use FAA Form 8110-1, Type Inspection Authorization.

2-12 Design Compliance. Perform the following steps after finding that the applicant showed compliance with the applicable airworthiness requirements: a. Keep the submitted data package for certification branch project files or obtain a written agreement with the applicant for on-demand access. Use the guidance in AC 20 - 179, Data Retention Agreements and Government Records. Return previously FAA- approved design data that the applicant voluntarily submitted to show identicality. In the 2-10 10/27/2023 Order 8110.42D CHG 2 official certification branch files, list, or catalog this previously approved data to facilitate future project review and QMS audits.

b. Notify the applicant of the article’s compliance with applicable airworthiness requirements in writing (typically found in the notification letter of design approval).

Inform the applicant that the CM section/branch in the manufacturing facility will assess the associated quality system. Use email or traditional mail to communicate with the applicant. See appendix F for a sample of the notification letter of design approval referred to above. Adjust this sample to comply with office guidelines on format as needed.

c. Coordinate with the CM section/branch to generate the numbered PMA supplement. Send the certification branch signed PMA supplement and a copy of the applicant’s notification letter of design approval to the responsible CM section/branch. At the discretion of the CM section/branch, send advance electronic copies of these documents to expedite processing of the PMA.

NOTE: In regard to the eligibility information listed on the supplement, all details and description for make/model/series must match the applicable and current TCDS information.

2-13 Revising the PMA Supplement. Often an existing supplement needs correcting for typographical errors or updating contacts. While each certification branch or CM section/branch sets an appropriate method to correct or update the supplement, they must maintain original signatures from each office (certification branch and CM section/branch) on all altered supplements even in the event of a revision. Some offices issue a revised supplement with corrections. Then, they send the revised supplement to the PMA holder and request return of the original incorrect supplement. An applicant may send the certification branch an amended supplement request and supporting data to expand installation eligibility, however, while this is acceptable, the preferred method for expanding eligibility is generating a new supplement. The applicant will submit to the certification branch updated supplements in Microsoft Word table format with a note stating the specific certification branch and/or CM section/branch action (for example, correction, revision, amendment, superseding, cancellation, or change of address).

2-14 Non-Compliance. If you cannot find compliance, send the applicant a rejection letter and return the applicant’s data package in its entirety. Do not divulge any information from other parties used in the course of the design evaluation. See appendix E for a sample of an FAA design rejection letter. Adjust the format of the letter as needed but keep the basic information from the sample.

2-15 Article Design Changes – Post PMA Approval.

a. PMA holders control their designs and assess the magnitude and impact of later changes. Review later design changes as necessary. Section 21.319 classifies changes in the designs of PMA articles as either major or minor. Minor changes have no appreciable effect on the approval basis of the PMA. Also, any design change that has an 2-11 10/27/2023 Order 8110.42D CHG 2 appreciable effect on the product on which the article is installed is a major design change.

b. The responsible certification branch sets the manner for approving and the interval for the applicant submitting minor changes to the design of a PMA article. One method of compliance to § 21.319 is through a written agreement with the PMA holder to periodically provide a list of applicants approved minor changes to the certification branch. The holder provides sufficient information to affirm the change is minor. This information lists the articles by name and number, their latest FAA-approved drawing revision with date of approval, and a brief description of each change. The certification branch keeps a record of these approvals and provides documentation of such to the PMA holder. Additionally, the certification branch must notify the applicable CM section/branch of the submission time interval so that they can ensure it is accurately captured in the applicant’s quality system.

c. A change in the approval basis from identicality to tests and computations has an appreciable effect on an article’s approval basis and is thus considered a major change requiring a new PMA application and approval.

d. Scrutinize the supporting data for any change to the design of a critical part. Even minor changes in this part’s design may have appreciable effects on its product. Direct the applicant to an STC for such.

2-16 Change of Licensing Agreement Status. Order 8120.22 redirects approval of minor design changes by holders of PMA via license agreement to the responsible certification branch after termination (or otherwise non-supported) of the agreement. Approval of these minor changes entails revising the approval basis of the associated PMA as follows: a. PMA via Identicality w/o Licensing Agreement. The transition to identicality without a license agreement requires a new application and associated supplement. The respective article’s P/N needs a suffix or prefix to distinguish it from that from the license agreement or type certificate. Since the descriptive data shows the change is minor, the article’s design remains compliant to applicable airworthiness requirements and associated eligibilities remain unchanged from the original approval. This minor change review by the certification branch is the same as that done for a PMA via tests and computations.

b. PMA via Test and Computation. The transition from a PMA via identicality w/ a licensing agreement to one via tests and computations will require a full evaluation of the new PMA data the same as any new PMA. The shift in PMA basis negates the finding of identicality and requires new design data, test reports and computations to show compliance with airworthiness requirements. Treat this change of PMA basis as a major design per § 21.319.

2-12

10/27/2023 Order 8110.42D CHG 2 Chapter 3. CM Section/Branch Responsibilities 3-1. PMA Activities. Refer to FAA Order 8120.22, Chapter 4, Parts Manufacturer Approval (Part 21, Subpart K) , Section 2, for CM section/branch responsibilities in PMA.

3-2. Reserved.

3-1

03/21/2014 Order 8110.42D Chapter 4. Designated Engineering Representatives and Organization Designation Authorization 4-1. ODA Roles in the PMA Process. ODAs operate under the procedures of their FAA approved manuals per FAA Order 8100.15. With respect to PMA guidance, we intend this Order to at least be referenced if not specifically followed by the ODA within their approved manual. It is the purview of the OMT to ensure national policy is followed in all instances.

4-2. DER Roles in the PMA Process . Only the FAA or an ODA can issue PMA. DERs do not issue PMAs but support the FAA approval process with findings within their limitations. DERs make findings of compliance based on the applicant’s showing at the discretion of the FAA and not the applicant. We list DER limitations in FAA Order 8110.37E, Designated Engineering Representative (DER) Handbook , paragraph 2-7.

NOTE: A DER may only recommend approval within the scope of their authority for critical parts.

4-3. Test and Computation . Findings under test and computation are within the normal scope of DER delegation. DERs find compliance with the appropriate airworthiness regulations and record these findings and their approval on FAA Form 8110-3, Statement of Compliance with Federal Aviation Standards . See the following appendices in this order for examples of DER findings: a. Appendix G, Form 8110-3, Test Reports and Computation (General Analysis) . Appendix G shows DER findings of compliance from tests and computations using a general analysis approach.

b. Appendix H, Form 8110-3, Test Reports and Computation (Comparative Analysis) . Appendix H shows DER findings of compliance from tests and computations using a comparative analysis approach.

4-4. Identicality Provisions . Identicality is unique to PMA. A DER requires a special FAA authorization to make this finding. The DER adheres to the provisions in FAA Order 8110.37 when conducting PMA activities for findings of identicality. See appendix I for an example of a completed FAA Form 8110-3 for identicality.

4-5. Findings of Identicality . Designees verify the following for findings of identicality: a. The TC, STC or TSO authorization data listed on Form 8110-3 is approved type design data for the indicated product models.

b. The stated eligibility of the PMA is appropriate.

c. No mandatory corrective actions are necessary in the article.

d. No unresolved service difficulties will make the article ineligible for installation.

4-1 10/27/2023 Order 8110.42D, CHG 2 Appendix A Appendix A. PMA Process Flowcharts Figure A-1. PMA Process Applicant PMA Letter & Data No No Identicality with License Agreement Identicality without Licensing Agreement OR OR STC Test and Computation Approval CM section/branch Certification branch Method Evaluate Quality Evaluate Design Yes System and Data Conformity Design Production Yes Approved? Approved?

Issue PMA A-1 10/27/2023 Order 8110.42D, CHG 2 Appendix A Figure A-2. PMA Process for Tests & Computations Review eligibility, service experience & ADs.

Delegate Start Review safety assessment & compliance list Application, data & quality Delegate manual Review COS Plan Delegate Set risk high High Initiate CPN and CM certification Review data, Critical or LLP? Yes branch drawings & coordination showings of Establish PartSCP compliance Delegate Confirm No Yes Review & approve sufficiency of test plan drawing package Assess risk Delegate Tests Issue conformity needed? request Level of No Involvement Delegate Confirm Complete conformity & evaluation of data witness tests Medium Delegate Compliant marking scheme Delegate Conform article & installation Delegate Send PMA application & supplement to CM Low section/branch. Notify applicant A-2 10/27/2023 Order 8110.42D, CHG 2 Appendix A Figure A-3. PMA Process for Identicality without License Agreement Start Application, Design & originally approved Data, Quality Manual Critical part or Assess risk No LLP?

Yes Yes Level of Involvement Set Risk High Initiate CPN and CM certification Medium – High Low branch Delegate coordination Compare design data, Spot check manufacturing Check processes, eligibility & Data supplement Reject and return Identical? No data Yes Conformity/ First Article Inspection Send application to CM section/branch A-3 10/27/2023 Order 8110.42D CHG 2 Appendix B Appendix B. Part Specific Certification Plan Note: This document is a template and an aid to help define content and format when drafting a PartSCP. All text in italics is instructional for editing or deletion as necessary. Retain all text not in italics in the PartSCP but edit as necessary for each project.

Part Specific Certification Plan Between [Insert the name of the applicant/company] and the [Insert the FAA certification branch] Project Number (leave blank until number assigned) List of Revisions Revision Revision Description Approved Release Date Number by: B-1 03/21/2014 Order 8110.42D Appendix B Table of Contents Section Title/Subject Page 1.0 Introduction 1.1 Scope 1.2 Project Description 1.3 Background 1.4 Component Description 2.0 Applicable Documents 3.0 Project Schedule 4.0 Certification Basis 5.0 Tests 6.0 Conformity Inspections 7.0 Communiation and Coordination 8.0 Delegations 9.0 Signatures B-2 10/27/2023 Order 8110.42D, CHG 2 Appendix B 1.0 Introduction 1.1 Scope The purpose of this PartSCP is to define and document the requirements and tasks required for FAA evaluation and PMA approval of replacement articles. The [ insert the applicable FAA certification branch ] of the FAA and the applicant will jointly manage and maintain this PartSCP.

1.2 Project Description This section must contain a brief description of the aircraft, engine, propeller, or TSO article requested for PMA approval including the article name, part number, and make/model eligibility.

1.3 Background (include service history) 1.4 Component Description 1.5 ICA Plan 2.0 Applicable Documents The following documents are required as article of this PartSCP to substantiate the manufacture of the articles and to show compliance to the regulations: Item Document/Drawing Revision Description 1 12121212 A ABC Aircraft Top Drawing 2 IPC IR Illustrated Parts Catalog or other proof on installation eligibility 3.0 Project Schedule Milestones as Applicable Proposed Completion Date Submittal of PartSCP First article conformity Test plan submittal to FAA Test plan approval Testing completed Test report submittal to FAA DER approved 8110-3 reports/drawings Final data submittal for PMA completion Issuance of engineering design approval Additional milestones as appropriate B-3 10/27/2023 Order 8110.42D, CHG 2 Appendix B 4.0 Certification Basis The certification basis and compliance with the applicable regulations is required if the substantiation is accomplished by test and computation.

5.0 Tests The applicant will propose any tests necessary to show compliance with the applicable regulations.

These tests support the associated general or comparative analysis.

6.0 Conformity Inspections Please list any expected conformity inspections necessary for this project.

7.0 Communication and Coordination The focal points for official communication between the FAA and the applicant are as follows: FAA certification branch project manager [Insert name and phone number] [Insert company name] project manager [Insert name and phone number] This does not prevent team members from engaging or communicating with any other team member, however team members must inform the project focal point. Both the FAA and the applicant will provide to each other a listing of their project team members.

The project focal points will manage the project by conducting regularly scheduled status briefings.

8.0 Delegation Both the FAA and the applicant agree to foster an environment where the designees, the FAA, and the applicant maintain open communications. The FAA supports using designees to the extent possible to help complete the project in the identified timeframe.

The applicant will propose the use of any suitable designee in specific test plans for FAA concurrence, and the designees will complete the task. It is important the applicant keep the designees and the FAA focal point informed of any potential shift in the project schedule.

9.0 Signatures The FAA and the applicant agree to the provisions of this PartSCP as indicated by the signature of their authorized representatives.

FAA Concurrence: Date: Project Manager Date: CM Section /Branch [If applicable] Applicant Concurrence: Date: Project Manager B-4 10/27/2023 Order 8110.42D CHG 2 Appendix C Appendix C. List of FAA CM Sections/Branches Go to https://www.faa.gov/about/office_org/field_offices/certificate_management_sections to locate the appropriate Certificate Management branch or section.

C-1 10/27/2023 Order 8110.42D CHG 2 Appendix D Appendix D. Sample FAA-PMA Supplement for Identicality (Non-Licensing Agreement) or Test and Computation Use this MS Word table format where each article name and number occupy a separate row. Do not delete or add extra fields, rows, or columns to separate data. Each page of the supplement must contain the PMA header and page number footer to ensure correctness in the event supplement pages are separated. While minor formatting may vary between offices, all information shown below must be present for the supplement to be valid.

FEDERAL AVIATION ADMINISTRATION - PARTS MANUFACTURER APPROVAL Smith Engineering Corporation PMA NO._________________ (Applicant address) SUPPLEMENT NO._________ DATE____________________ Article Name Article Approved Approval Basis and Make/TCH Model /Series Number Replacement Approved Design Data Eligibility Eligibility for Article Number Spring SE24689 24689 Identicality per 14 CFR Pratt & PT6T-3, 3A, -3B, 21.303 DWG No: Whitney 3BE, -3D, -3DE, SE 25206, Rev: None Canada Corp 3DF, -6 Date: 3/31/13 or later FAA-approved revisions Pin SE24695 24695 Test and Computations Boeing 737-700 Series, per 14 CFR 21.303, 767-400ER Series DWG No: SE 25207, Rev: None Date: 3/31/13 or later FAA-approved revisions DC-10-10, Boeing DC-10-30, (McDonnell DC-10-40, Douglas) MD-11, MD-11F -------------------------------------------END OF DATA------------------------------------------ - GENERAL NOTES: Provide minor design changes in a manner as determined by the certification branch. Process major design changes to drawings and specifications in the same manner as that for an original FAA-PMA.

The FAA accepted the ICA approach for the above articles with their designs. These ICA may refer to those of the respective articles from the holders of type certificates. Otherwise, provide supplemental ICA for differences in the replacement articles. Make referral statements or supplemental ICA readily available per § 21.50.

__________________________ _____________________________ Manager, Manager, ( certification branch name) (CM section/branch name) Pg. 1 of X D-1 10/27/2023 Order 8110.42D CHG 2 Appendix E Appendix E. Sample Design Rejection Letter ( certification branch name ) U.S. Department of Transportation ( certification branch address ) Federal Aviation Administration [Date] ( Applicant Name ) (Applicant address ) (Applicant contact) : This is in response to your request for design approval based on identicality. We reviewed your data and did not find it identical to the corresponding approved data. Enclosed is the data you sent to us.

Sincerely, ________________________________________ Manager, (certification branch name) Enclosure(s) E-1 10/27/2023 Order 8110.42D CHG 2 Appendix F Appendix F. Sample Notification Letter of Design Approval ( C M branch name ) U.S. Department of Transportation ( CM branch address ) Federal Aviation Administration [Date] ( Applicant name ) ( Applicant address ) ( Applicant contact ): This is in response to your letter, dated ( application date ), requesting parts manufacturer approval on ( applicant name ), ( article name ), ( article number ) that is eligible on the ( approved eligibility list ).

We have reviewed the data submitted and find they meet the requirements of 14 CFR 21.311. We noted design approval on the PMA supplement. Note that this is a notification letter only and does not constitute design or production approval. We sent the PMA supplement with your application to (CM section / branch name, address, contact numbers) The ( CM section / branch name ) will grant production approval after validating your quality system.

The FAA-PMA letter and PMA supplement from the ( CM section / branch name ) documents that approval.

Minor design changes must be submitted to the ( certification branch name ) at regular intervals not to exceed ( agreed to time frame ).

------------------------------------------ Choose the best scenario ----------------------------------------- - We concur with your determination that installation of your PMA'd articles do not require supplemental instructions for continued airworthiness (ICA).

-or- We concur with your instructions for continued airworthiness (ICA) as required by 14 CFR 21.50(b) for this PMA. The ICAs have been coordinated with the ( specific Aircraft Evaluation Division (AED)) as required by PMA Order 8110.42. The AED acceptance for this project is recorded via FAA memorandum dated: ( memo date ) from the ( specific AED ) to ( certification branch project engineer ).

------------------------------------------------------------------------------------------------------------------ If you have any further questions, please contact ( certification branch project engineer and phone number ) Sincerely, ________________________________________ Manager, ( certification branch name ) cc: Manager, ( CM section / branch name ) F-1 03/21/2014 Order 8110.42D CHG 1 Appendix G Appendix G. Example of FAA Form 8110-3, Test and Computation (General Analysis) ..S . DE P'ARTl l:NT Of TRANSPORT A TION 1. DATE FED El'W. A VIA 110N AD MINIST RA TI ON Octo ber !0 20 01 STATEMENT O F CO M PLI ANC E WITH THE FE DERA L AVIATION REGUL ATIONS AI RC RAF T OR AIR C RAF T CO MP O NEN T IDE NT IF I CA T IO N 2. MAK E 3. MO DEL NO . 4. TYPE (Aircraft, Engine, 5. NAME OF AP P LI CANT Propel.let , efc .)

Gen era] El ectric S am :s I ngiu e Par ts CT 6-50, CF6-S0, CF6- Eug ine soc: LI ST OF DATA 6. I DE NTIFICATION 7. TITL E A l234 5X Oil Pump S haf t D r.m ing R e, ·. D 04 /01/2001 RPT- 2468 C er tification and Compliance Repo rt Re,·. B 04 /1 2/ 20 01 - - -E l'< 'D- - - 8. PURPOSE OF DATA lu S up po rt of PM :\ De si gn :\ p p ro,·aJ for t he listed article; Test & Co mp u t ati on by Ge ne ral :\ ua l ysi!i; f A.-\ Proj e.ct # X...'X.\: 9. AP P LI CABLE REQUIREMENTS (List speci.ic secfion.s ) 14 C FR 33. x:x , amdt ( n: •xx) 10. CE RT IFIC AT I ON - U nd er al.ll -i.h o ri ty vest ed h) • dir ecti on of the Administ ra t or an cl in aoco r elanc e wi th co ndi ti ons an el limitations of a pp o intme nt w,_ele r P an 183 of th e Federal Aviation Reg ula tions, ela ta listed a bov e an cl on an a ch e el she ets nu.mh er e el NIA ha ve h een exam.in.e el in acoorelance wi th estahlish e cl proced ur es anel fo unel ,o co mp ly wi th a pp licable req:W .rements of the Fe el a-a l A\"'l.a ti on Reg ula tions.

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J oe Smith FA A Fo rm 811 0- 3 ( 03 /I 0) SIJPE RCED ESP REV!O USEDmON(REPRES ENTA TION) G-1 03/21/2014 Order 8110.42D CHG 2 Appendix H Appendix H. Example of FAA Form 8110-3, Test and Computation S. DEP ARTM ENT Of TR ~ SPQUATIOff 1 .0ATE t' eDe.'Vol A'll~ TIO Jri' At,,IIN IS TI\ ATICN OctoD e-r 20 , 2002 ST AT E MENT O F CO M PL IA N CE WI TH T HE FEDE RAL AVIAT ION RE GULAT IONS AI RC RAFT OR AJ RCRAFT COMPONENT IDENTIFICATION J . MO DEL NO. 5. IIAW: E O F APP LICAN T 2.MAK E 4. TYPE {AJIClafr , E ng~ , PropeJ.te r, e !C .J MC DO NN E LL DOUGLAS SAM' S AIRP LU- 'E PAR TS OC-S- 83 , - 87 and M O..S8 AI RP LANE LIST Of DATA 6. I DE NTI FI CATION 7. TIT L ,E A ll 346X T ray T :tb le-Dr ani ng Re~. A 04/011: 00l Certi fi c at ion a nd Comp li an ce Re p ort RPT-l469 Re~. A 04/ ll /1002 · ·- END -·· S. PURPOSE OF D ATA In Support of Pl · lA Design A ppro, •al for the list e-d part ; T ut & Co mpu ta tion by Com pa n lin An al ys t$ ; FAA Proj ee- 1 # .\."'\X 9. A?Pl.l CAS LE REOUIREM ENTS (Ust S peGfl'IC ~ J 14 C FR 25. u. , a md t ( ll ·U ) 10. CERTIFICATION - U nd er autho ri ty .e -s ted by direction of t he Adminis tr ator an d iD accor dance wi t h eo oditioos and timi[ at io os of ap pointment un j e.r P art 183 of the Fed era l Ari at ioo Regulatio ns . da ta lin edabo, e an d oo attaclled ha , e been e-s amioed iD ac eo r da nee ;ri th es ta b l!s hed procedures and fo un d shee ts numbered co co mply wi t h applicable reqtiremezus of t he Federal A\ 'lation Re ,gulations.

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Findings J oe Smith FAA Fo nn 811 Q.• 3 (03 11 D } SU PERSEOES, P REV IOUS E DI TI ON (REP RES E NT A TIO N} I-1 10/27/2023 Order 8110.42D CHG 2 Appendix J Appendix J. List of Acronyms Acronym Definition 14 CFR Title 14 of the Code of Federal Regulations AC Advisory circular AD Airworthiness directive AED Aircraft E valuation D ivision AIR - 500 Integrated Certificate Management Division AIR - 600 Policy and Standards Division AIR - 800 System Oversight Division AMOC Alternative means of compliance CM Certificate Management COS Continued operational safety CPN Certification project notification DAH Design approval holder DER Designated engineering representative FAA Federal Aviation Administration ICA Instructions for continued airworthiness IPC Illustrated parts catalog ODA Organiz ation designation authorization J-1 10/27/2023 Order 8110.42D CHG 2 Appendix K Appendix K. Definitions and Terms When following procedures in this order, the following definitions and terms apply: 1. Accredited laboratory is a laboratory which prescribes to a set of national standards and follows at least one of the available industry defined accreditation processes and maintains current certificated documentation as proof. These laboratories also employ qualified individuals with technical degrees in the fields of chemistry, engineering, or metallurgy.

2. Article means a material, part, component, process, or appliance. Articles may include sealants, modified standard parts, brake assemblies, etc.

3. Certificate management (CM) certification branch is the CM certification branch that issues and has oversight over the original design approval for the product/appliance for which the PMA applicant’s article is eligible for installation.

4. Certificate management (CM) branch are the branches responsible for production approval and certificate management activities. The certificating CM branch is the office that issued the initial production approval or has certificate management responsibility for producing the product/appliance on which the PMA applicant’s article is eligible for installation.

5. Certificate management (CM) section are the sections of the CM branch responsible for production approval and certificate management activities. The certificating CM section is the office that issued the initial production approval or has certificate management responsibility for producing the product/appliance on which the PMA applicant’s article is eligible for installation.

6. Certification branch is the field branch of AIR. The project certification branch has geographic responsibility for finding the design complies with applicable airworthiness standards. It administers and secures compliance with agency regulations, programs, standards, and procedures governing the design approval of replacement and modification articles.

7. Continued operational safety (COS) assures the integrity of a product throughout its service life. This involves problem prevention, service monitoring and corrective actions that feedback into a product’s design and production .

8. Critical part is an article identified as critical by the design approval holder during the product type validation process, or otherwise by the exporting authority. Typically, such components include articles for which a replacement time, inspection interval, or related procedure is specified in the airworthiness limitations section or certification maintenance requirements of the manufacturer’s maintenance manual or ICA.

9. Design is all drawings, data and specifications that show the article’s configuration and all information on dimensions, tolerances, materials, processes, and procedures necessary to define all article characteristics. A master drawing list is the summary of these drawing and specifications. The design can also include the airworthiness limitations section of the ICA.

10. Distributor is any person engaged in the sale or transfer of products and articles for installation in type certificated aircraft, aircraft engines or propellers, and that conducts no manufacturing activities.

K-1 10/27/2023 Order 8110.42D CHG 2 Appendix K 11. Eligibility relates to the type-certificated products that the PMA articles are approved for installation.

12. FAA - PMA letter is the initial production approval document issued to the PMA applicant by the appropriate CM section. This letter accompanies a PMA supplement.

K-2 10/27/2023 Order 8110.42D CHG 2 Appendix K The supplement is the CM section’s record of design approval and the articles that the manufacturer may produce. Later CM section transmittal letters that reference the initial PMA letters may revise eligibilities or add a new article to PMA supplements.

13. Instructions for continued airworthiness (ICA) documents directions and requirements to maintain the continued airworthiness of an aircraft, engine, or propeller.

14. Life-limited part is an article with an established replacement time, inspection interval, or related procedure in the airworthiness limitations section as required by §§ 21.50, 23.1529, 25.1529, 27.1529, 29.1529, 31.82, 33.4, and 35.4. Early type certificate data sheet (TCDS) has mandatory replacements or inspections for some products. These products were certified before 14 CFR had the above airworthiness requirements. Also, a technical standard order (TSO) authorization may note or reference mandatory replacement or inspection for an affected article.

15. Make is the common name associated with the original design of the product.

16. Manufacturer is a person (14 CFR Part 1) who causes production of a product or article.

PAHs or their suppliers are likely manufacturers.

17. Manufacturing facility is the location of the approved quality system that produces the article.

18. Model is the TCDS designation to classify a product of a particular style of design.

19. Modification article is new to the product and approved under a major or minor change to the type design. An STC is the most common source of modification articles.

20. Owner/operator produced article requires participation in controlling an article’s design, manufacture, or quality. Significant participation in one or more of the following actions establishes an owner/operator as the manufacturer of an article: a. Fabricating or finishing the article or performing a value-added article inspection.

b. Developing the design or performance data to manufacture the article.

c. Selecting materials to manufacture the article.

d. Developing fabrication processes or assembly methods to manufacture the article.

e. Developing quality control procedures to manufacture the article.

f. Controlling or supervising the manufacture of the article.

21. Product is an aircraft, aircraft engine, or propeller. See § 21.1(b).

22. Production approval holder (PAH) is the holder of a production certificate, PMA, or TSO authorization. This person controls the design and quality of a product or article.

23. Qualified laboratory is a laboratory which is not accredited; nonetheless, does follow defined processes along with employing qualified individuals with technical degrees in the fields of chemistry, engineering, or metallurgy.

24. Quality system is an organizational structure with responsibilities, procedures, processes, and resources that implements a management function to determine and enforce quality principles. The quality system encompasses quality assurance and quality control for replacement and modification articles that conform to the approved design.

K-3 10/27/2023 Order 8110.42D CHG 2 Appendix K 25. Replacement article is a direct substitute for an article approved under a type certificate. It is a fit, form and functional replacement for an original article in a product’s type design.

26. Revision is a correction of typographical errors or an update of administrative data on existing PMA supplements.

27. Series is a grouping of similar product models identified on the applicable TCDS.

28. Source control drawing is a drawing in which specific production and/or process details, typically found in the “Notes”, are directly controlled by the PMA DAH and flow down to their suppliers. This control is typically accomplished via additional agreements outside the direct purview of the drawing.

29. Standard parts conform to established industry-wide or government specifications. These specifications stipulate the design, manufacturing, and uniform identification requirements. The specifications are readily available to any persons or organizations who want to produce these articles. Also, standard parts may include those that solely meet uniform performance criteria if the Administrator finds complete compliance with industry-wide and government performance specifications. These specifications must include performance, test and acceptance criteria, and uniform identification requirements. The Administrator deemed discrete electrical and electronic components that conform to their applicable performance criteria as standard parts. See Volume 62 Federal Register 9923, March 5, 1997.

30. Supplier is any person as defined by 14 CFR Part 1, Definitions and Abbreviations, that furnishes products, articles, or services (at any tier in the supply chain) that are used or consumed in the manufacture of or installed on aviation products of articles.

31. Technical standard order authorization (TSOA) is an FAA design and production authorization issued to a specific manufacturer of an article that we found to meet or exceed a specific TSO’s minimum performance standard. The Technical Policy branch (AIR-620) is responsible for TSOs. The geographic CM branch is responsible for issuing the TSO authorization to the applicant. The TSO authorization is not an installation approval. We approve the installation of the article as part of the type design of a type-certificated product or subsequently by STC.

32. Type certificate holder is an individual or company who has been issued a design approval by the FAA and meets the requirements of § 21.21.

K-4 10/27/2023 Order 8110.42D CHG 2 Appendix L Appendix L. Related Publications and How to Get Them 1. Title 14, Code of Federal Regulations (CFR). If needed, you can get copies of 14 CFR on- line at https://www.ecfr.gov/current/title-14 .

2. FAA Orders.

The following orders are available on the Dynamic Regulatory System (DRS) at https://drs.faa.gov/browse .

Order 8100.5, Aircraft Certification Service Mission, Responsibilities, Relationships, and Programs Order 8100.11, Developing Undue Burden and No Undue Burden Decision Papers Under 14 CFR Part 21 Order 8100.15, Organization Designation Authorization Procedures Order 8110.4, Type Certification Order 8110.37, Designated Engineering Representative (DER) Guidance Handbook • Order 8110.54, Instructions for Continued Airworthiness Responsibilities, Requirements, and Contents • Order 8110.115, Certification Project Initiation and Certification Project Notification • Order 8110.119, Streamlined Process for Parts Manufacturer Approval (PMA) Order 8120.22, Production Approval Procedures Order 8150.1, Technical Standard Order Program L-1 10/27/2023 8110.42D, CHG 2 Appendix M Appendix M. Administrative Information 1. Distribution. This order is distributed to all Aircraft Certification Service (AIR) and Flight Standards Service (FS) offices, other interested offices, delegated organizations, and designees.

2. Authority to Change This Order. The issuance, revision, or cancellation of the material in this order is the responsibility of AIR-630.

3. Suggestions for Improvement. Please forward all comments on deficiencies, clarifications, or improvements to this order to the AIR Directives Management Officer at (DMO) via email at 9-AWA-AVS-AIR-DMO@faa.gov or the FAA DRS at https://drs.faa.gov . You will find FAA Form 1320-19, Directive Feedback Information , in Appendix N for your convenience.

4. Records Management. Refer to FAA Orders 0000.1, FAA Standard Subject Classification System and 1350.14, Records Management , or see your office Records Management Officer (RMO)/Directives Management Officer (DMO) for guidance regarding retention or disposition of records.

M-1 10/27/2023 8110.42D, CHG 2 Appendix N Appendix N. Directives Feedback Information Please submit any written comments or recommendations for improving this directive or suggest new items or subjects that should be added to it. If you find an error, please tell us about it.

Subject: Order 8110.42D Chg 2, Part Manufacturer Approval Procedures To: Directive Management Officer at 9-AVS-AIR-Directives Management Officer (FAA), (Please mark all appropriate line items) ☐ An error (procedural or typographical) has been noted in paragraph _______ on page ______.

☐ Recommend paragraph _______ on page _______ be changed as follows: (attach separate sheet if necessary) ☐ In a future change to this order, please include coverage on the following subject: (briefly describe what you want added.)

☐ Other comments: ☐ I would like to discuss the above. Please contact me.

Submitted by: __________________________________Date: __________________ Telephone Number: __________________Routing Symbol: _________________ FAA Form 1320-19 (08/21) Supersedes Previous Edition N-1