Advisory Circular (AC) No. 521-011

Foreign Aeronautical Products

Issuing Office: Civil Aviation, Standards Document No.: AC 521-011
File Classification No.: Z 5000-34 Issue No. 01
RDIMS No.: 5612166-V24 Effective Date: 2025-08-22

Table of contents

1.0 Introduction

  1. (1) This Advisory Circular (AC) is provided for information and guidance purposes. It describes an example of an acceptable means, but not the only means, of demonstrating compliance with regulations and standards. This AC on its own does not change, create, amend, or permit deviations from regulatory requirements, nor does it establish minimum standards.

1.1 Purpose

  1. (1) The purpose of this document is to provide information and guidance on acceptable means of compliance to Subpart 521 Division XI of the Canadian Aviation Regulations (CARs) for the validation and acceptance of foreign design approvals issued in respect of foreign aeronautical products registered in Canada.

1.2 Applicability

  1. (1) This document applies to Transport Canada Civil Aviation (TCCA) personnel, delegates, and the aviation industry including foreign applicants and foreign Design Approval Document Holders (DADH).

1.3 Description of changes

  1. (1) Not applicable.

2.0 References and requirements

2.1 Reference documents

  1. (1) It is intended that the following reference materials be used in conjunction with this document:
    1. (a) Aeronautics Act (R.S.C., 1985, c. A-2)
    2. (b) Part I, Subpart 1 of the Canadian Aviation Regulations (CARs) — Interpretation;
    3. (c) Part I, Subpart 4 of the CARs — Charges;
    4. (d) Part V, Subpart 7 of the CARs — Flight Authority and Certificate of Noise Compliance;
    5. (e) Part V, Subpart 21 of the CARs — Approval of the Type Design or a Change to the Type Design of an Aeronautical Product;
    6. (f) AC 521-002 — Type Certification Requirements of Aircraft, Engines and Propellers;
    7. (g) AC 521-004 — Changes to the Type Design of an Aeronautical Product;
    8. (h) Transport Canada form number 26-0756 — Type Certificate Application;
    9. (i) Transport Canada form number 26-0764 — Canadian Technical Standard Order (CAN-TSO) Design Approval Application;
    10. (j) Transport Canada form number 26-0469 — Design Change Approval Application;
    11. (k) Airworthiness agreement or similar arrangement — Consult agreements and arrangements that Canada holds with other countries, regions or governing bodies: https://tc.canada.ca/en/aviation/aircraft-airworthiness/international-agreements-arrangements;
    12. (l) United States (US) Eligible Aircraft List — List of US designed and manufactured aircraft models that are eligible for the issue of a Canadian "standard" Certificate of Airworthiness (C of A) on the basis of their FAA Type Certificate (TC): https://tc.canada.ca/en/aviation/aircraft-airworthiness/aircraft-certification/us-eligible-aircraft-list;
    13. (m) Civil aviation contacts and offices — Regional service centres: https://tc.canada.ca/en/aviation/civil-aviation-contacts-offices#headquarters_and_regional;
    14. (n) Aviation service standards — Service standards which publicly state the level of performance that stakeholders can reasonably expect to encounter under normal circumstances which Transport Canada has developed as part of its ongoing commitment to quality client service: https://tc.canada.ca/en/corporate-services/transparency/aviation-service-standards; and
    15. (o) Annex 8 to the Convention on International Civil Aviation (International Civil Aviation Organization (ICAO) Annex 8) — Airworthiness of Aircraft.

2.2 Cancelled documents

  1. (1) As of the effective date of this document, the following documents are cancelled:
    1. (a) Staff Instruction (SI) 511-001, Issue 02, 2007-06-15 — Type Certification of Foreign Aeronautical Products – Determining the Level of Airworthiness Review;
    2. (b) SI 511-004, Issue 02, 2008-03-14 — Type Certification of Foreign Aeronautical Products;
    3. (c) SI 513-002, Issue 03, 2008-12-01 — Reciprocal Acceptance of Repair Design Approvals Between the FAA and TCCA;
    4. (d) SI 513-003, Issue 01, 2008-09-15 — Acceptance and Approval of Foreign Design Changes; and
    5. (e) Airworthiness Notice (AN) B004 Edition 4, 2000-09-12 — Acceptance of Foreign Designed Modifications and Repairs.
  2. (2) By default, it is understood that the publication of a new issue of a document automatically renders any earlier issues of the same document null and void.

2.3 Definitions and abbreviations

  1. (1) The following definitions are used in this document:
    1. (a) Additional Technical Condition (ATC): Any TCCA requirement that is in addition to, or any variation of, the airworthiness and environmental standards defined in the foreign civil aviation authority’s Design Approval Document (DAD) to ensure that the airworthiness standards provide a level of safety equivalent to that provided by the applicable TCCA airworthiness requirements and that the environmental standards provide noise, fuel venting, and exhaust emission levels that are no higher than those provided by TCCA’s applicable environmental requirements. Similar to “additional airworthiness requirements” or “Canadian variations” as defined in the Airworthiness Manual (AWM) and Title 14 of the US Code of Federal Regulations (14 CFR);
    2. (b) Aeronautical product: Any aircraft, aircraft engine, aircraft propeller, aircraft appliance or part, or a component part of any of those things, including any computer system and software. (Ref: section 3(1) of the Aeronautics Act);
    3. (c) Airworthiness agreement or similar arrangement: A formal agreement, either between Canada and another State at the treaty level, or between TCCA and a Foreign Civil Aviation Authority (FCAA) at the Departmental level. These agreements define the working relationship between Canada and the FCAA. In this document, the term “Bilateral Agreement” or “Bilateral Aviation Safety Agreement” is used to describe a high-level agreement either between TCCA and an FCAA under the authority of the Aeronautics Act or a legally binding agreement between the Canadian government and a foreign government. A “Technical Arrangement” and “Memorandum of Understanding” are terms commonly used to describe lower-level agreements at the Departmental level;
    4. (d) Applicant: An individual or organization responsible for the design of an aeronautical product, or a representative of such an individual or organization that makes an application for the issuance of or a change to a DAD in respect of an aeronautical product. (Ref: section 521.01 of the CARs);
    5. (e) Design Approval Document (DAD): A Type Certificate, a Supplemental Type Certificate, a Repair Design Approval, a Part Design Approval, or a Canadian Technical Standard Order (CAN-TSO) design approval. (Ref: section 521.01 of the CARs);
    6. (f) Federal Aviation Regulations: Title 14 of the Code of Federal Regulations (14 CFR), Chapter 1 (Federal Aviation Administration, Department of Transportation) published by the Government of the United States, as amended from time to time;
    7. (g) Foreign Civil Aviation Authority (FCAA): In this AC, refers to the Civil Aviation Authority (CAA) of the exporting State of Design (SoD);
    8. (h) Level of review: Level of technical and administrative involvement in a validation program and type design examination based on risk factors including knowledge of the exporting authority’s civil airworthiness system, presence of an airworthiness agreement or similar arrangement, and the technical complexity of, and familiarity with, the aeronautical product, design change, or repair;
    9. (i) State of Design (SoD): As defined by ICAO Annex 8, means the State (country) having jurisdiction over the organization responsible for the type design or approved design of an aeronautical product. In the case of a change or repair, the State of Design is the country or state overseeing the organization responsible for the design and certification of the change/repair to the aeronautical product involved. It should be noted that although the European Union is not a “State”, the European Union Aviation Safety Agency (EASA) does perform the function of CAA for the State of Design of some of its member states; and
    10. (j) Type design examination: A process used by TCCA to facilitate the review of foreign design approvals for the purpose of accepting the design approval or issuing a Canadian equivalent for foreign aeronautical products being imported. The process consists of a series of activities undertaken to review the certification basis and/or applicable standards along with the associated technical data to ensure that the design of the foreign aeronautical product provides an airworthiness level of safety and levels of noise, fuel venting and exhaust emissions consistent with those intended by the applicable Parts and Subparts of the CARs.
  2. (2) The following abbreviations are used in this document:
    1. (a) 14 CFR: Federal Aviation Regulation (in reference to parts of Title 14 of the US Federal Code of Regulations;
    2. (b) AC: Advisory Circular;
    3. (c) AML: Approved Model List;
    4. (d) ATC: Additional Technical Condition;
    5. (e) AWM: Airworthiness Manual;
    6. (f) CAA: Civil Aviation Authority;
    7. (g) CAA-UK: Civil Aviation Authority (of the United Kingdom of Great Britain and Northern Ireland);
    8. (h) CAR: Canadian Aviation Regulations;
    9. (i) CAN-TSO: Canadian Technical Standard Order;
    10. (j) CASI: Civil Aviation Safety Inspector;
    11. (k) DAD: Design Approval Document;
    12. (l) DADH: Design Approval Document Holder;
    13. (m) EASA: European Union Aviation Safety Agency;
    14. (n) FAA: Federal Aviation Administration;
    15. (o) FCAA: Foreign Civil Aviation Authority;
    16. (p) ICA: Instructions for Continued Airworthiness;
    17. (q) ICAO: International Civil Aviation Organization;
    18. (r) IPA: Implementation Procedures for Airworthiness;
    19. (s) MD-M: Minister’s Delegate – Maintenance;
    20. (t) NAPA: National Aeronautical Product Approval;
    21. (u) PCM: Project Certification Manager;
    22. (v) PDA: Part Design Approval;
    23. (w) PMA: Parts Manufacturer Approval;
    24. (x) RDA: Repair Design Approval;
    25. (y) RMAC: Regional Manager, Aircraft Certification;
    26. (z) SCA: Special Conditions – Airworthiness;
    27. (aa) SDR: Service Difficulty Report;
    28. (bb) SoD: State of Design;
    29. (cc) SoR: State of Registry;
    30. (dd) STC: Supplemental Type Certificate;
    31. (ee) TC: Type Certificate;
    32. (ff) TCCA: Transport Canada Civil Aviation;
    33. (gg) TCDS: Type Certificate Data Sheet;
    34. (hh) TIP: Technical Implementation Procedures;
    35. (ii) TSO: Technical Standard Order;
    36. (jj) TTL:Technical Team Lead (former title, see RMAC)
    37. (kk) UK: United Kingdom; and
    38. (ll) US: United States.

3.0 Background

  1. (1) This AC is organized to mirror the sections and subsections of Subpart 521 Division XI of the CARs so that the associated guidance can be read in conjunction with Subpart 521 of the CARs. Please note all sections and subsections of Subpart 521 of the CARs may not be represented in this document. Only the sections that have recommended acceptable means of compliance are included.

3.1 Validation and acceptance of foreign design approvals of aeronautical products

  1. (1) Conducting a Canadian validation of a foreign design approval allows for issuance of a Canadian approval or the acceptance of the foreign design approval. Specifically for an aircraft, validation of the foreign Type Certificate (TC) is needed so that the requisite flight authority can be issued under Subpart 507 of the CARs for its intended type of operation. The purpose of validation is:
    1. (a) To ensure the design of the product provides a level of safety equivalent to that specified in Subpart 521 of the CARs;
    2. (b) To ensure that the Foreign Civil Aviation Authority’s (FCAA) environmental standards provide noise, fuel venting, and exhaust emission levels that are commensurate with or better than the levels intended by the applicable parts and subparts of the CARs; and
    3. (c) To enable TCCA to gain the knowledge required to ensure the continued airworthiness of the product when registered in Canada.
    4. Note: Further guidance will be developed and published to define and explain these continuing airworthiness requirements and objectives in greater detail.
  2. (2) Validation is not a recertification of the FCAA’s original approval. Validation is a set of activities completed by TCCA for products that are already or will be certified or approved by the FCAA. This distinction between validation and recertification reflects the different responsibilities each authority has within their unique roles.
  3. (3) Validating foreign design approvals is not only a service provided to the civil aviation industry for products entering Canada, but also a part of the oversight responsibility of TCCA. The review of foreign design approvals aids TCCA in the familiarization of new and novel technologies incorporated on foreign aeronautical products, design changes, and repairs when they first enter Canada. An additional aspect of the review is to ensure there is no known unsafe condition at time of validation. The continued absence of unsafe conditions with the product being validated is overseen by the Continuing Airworthiness Division of the National Aircraft Certification Branch.
  4. (4) Consistent with these objectives and to facilitate the validation activity, a type design examination is carried out. As outlined in sections 521.455 and 521.456 of the CARs, the purpose of a type design examination is to ensure that the levels of airworthiness safety and environmental protection of the foreign design are equivalent to those of a design that would have been approved under the Canadian system.
  5. (5) The type design examination determines if the foreign aeronautical product, designed to comply with the FCAA’s requirements and standards, provides an airworthiness level of safety and levels of noise, fuel venting, and exhaust emissions that would be equivalent if the aeronautical product had been designed to comply with the applicable Canadian airworthiness standards and regulations. Once the validation of the foreign design approval is successful and equivalency is determined, the foreign Design Approval Document (DAD) may be accepted, or a Canadian DAD may be issued. The applicable Canadian requirements and airworthiness manual (AWM) standards will be listed on the Canadian DAD.
  6. (6) Canada and TCCA have entered into airworthiness agreements or similar arrangements with other countries and FCAA (e.g. United States (US), European Union, United Kingdom (UK), Brazil, China, etc.). These agreements and arrangements were developed to recognize the comparable regulatory oversight systems and comparable levels of aviation safety required, achieved, and maintained by TCCA and a FCAA. These agreements and arrangements facilitate and ease the burden of the civil aviation activities, including aircraft certification and continuing airworthiness activities, by reducing work and duplication of effort and recognizing the other authority’s expertise and rigour. Refer to section 2.1(1)(k) of this AC for a link to the list of TCCA’s international airworthiness agreements and similar arrangements.
  7. (7) Using implementation procedures which support these agreements and arrangements, TCCA can rely on the system and capabilities of the FCAA in finding compliance with AWM standards and facilitate the review and acceptance of mandatory continuing airworthiness information. These implementation procedures contain acceptance, review, and validation procedures applicable to each country and authority. Where differences arise between this AC and the implementation procedures of an agreement or arrangement, the implementation procedure prevails and is the primary reference.
  8. (8) Due to the agreements or arrangements that are in place with certain countries and their associated FCAA, TCCA can apply differing levels of review for the validation activities. These differing levels of review permit TCCA to use risk-based procedures and give maximum credit possible to the FCAA and its airworthiness certification system. The extent of TCCA’s evaluation of the product and its interaction with the FCAA varies with the level of review corresponding to a validation program.
  9. (9) Some airworthiness agreements and arrangements allow for the automatic acceptance of some design approvals which do not require further validation procedures. For example, based on TCCA’s bilateral agreements with other FCAA, certain Supplemental Type Certificates (STCs) for design changes, Repair Design Approvals (RDAs) for repairs, Part Design Approvals (PDAs) for replacement parts, and design approvals for Technical Standard Orders (TSOs), are accepted without review, including any of the equivalent design approvals as defined by the bilateral agreements. This is discussed in greater detail in section 4.3.
  10. Note: A foreign design approval cannot be automatically accepted by TCCA through an intermediary or third-party country. For airworthiness agreement or arrangement benefits to be realized between the participating States, the agreement or arrangement needs to be between the originating Civil Aviation Authority (CAA) of the State of Design (SoD) and the importing authority or State. This applies both when Canada is importing and exporting aeronautical products.
  11. (10) Subpart 521 of the CARs allows for the validation of design approvals from countries with which Canada does not have an airworthiness agreement or similar arrangement. However, this requires a review of, and familiarization with, the foreign regulatory system and a more thorough validation procedures using a more detailed level of review of the design approval being validated. The completion of these reviews can provide the basis for the SoD to enter into an airworthiness agreement with Canada or a similar arrangement between TCCA and the FCAA to facilitate the validation of future design approvals.

3.2 Foreign changes to validated design approvals

  1. (1) Consistent with the provisions set forth in sections 521.455 and 521.456 of the CARs, if a design change (including the design of a repair or replacement part) is made by a foreign Design Approval Document Holder (DADH) to an approved design which was accepted or for which a Canadian design approval was issued, the change will need to be approved by the FCAA and require validation by TCCA including a type design examination of the change to the approved design depending on airworthiness agreements or similar arrangements in place.
  2. (2) As in section 3.1, TCCA’s objective is to leverage the FCAA’s work as much as possible for the validation of a foreign change to an approved design. As with initial design approval validation, the level of review is established on a case-by-case basis based on the risk level of the design approval and the familiarity with the FCAA.
  3. (3) In the case of a validated foreign design change, either a corresponding Canadian design approval will be issued or the foreign design change will be accepted depending on the level of review required and implementation procedures of airworthiness agreements or similar arrangements. See section 4.6.2 for more detail.

4.0 Division XI – Foreign aeronautical products

4.1 Application – section 521.451 of the CARs

  1. (1) This section applies to foreign applicants for, and foreign holders of, a Canadian DAD in respect of a foreign design approval for a foreign aeronautical product (including design change or repair design) to be imported into Canada or installed on a Canadian-registered aircraft.

4.2 Eligibility requirements – section 521.452 of the CARs

  1. (1) For a foreign design approval to be eligible for a corresponding Canadian design approval, it is necessary for the FCAA responsible for the foreign design approval in respect of the aeronautical product, the design change, or repair design to have issued or have plans to issue their own design approval. This means that while the design approval validation activity can begin prior to the FCAA issuing their own design approval, acceptance of the design approval or issuance of a Canadian design approval after a successful validation will not occur until the FCAA has issued their own design approval.
  2. (2) A foreign applicant cannot apply directly to TCCA. Where an application is required, the application is submitted through the prospective applicant’s and holder’s CAA. If an application is submitted directly to TCCA, the applicant will be notified that their application will not be processed and that they should resubmit it through their CAA.
  3. (3) Although not specifically stated in section 521.452 of the CARs, section 521.455 states that an applicant must meet the applicable requirements of Subpart 521 of the CAR for a subject design approval. The implementation procedures for certain agreements and arrangements also state that foreign DADH are required to hold or have access to relevant type design information and make it available upon request. Accordingly, the applicant is required to have the technical capability, or access to the technical capability, to develop the data required to maintain the product in an airworthy condition.
  4. (4) A person or enterprise other than the DADH may also apply for TCCA approval or acceptance of a foreign design approval provided that applicant has, or has access to, the technical capability outlined in paragraph (3) above. More broadly, that applicant has access to the technical capability to carry out the responsibilities of a DADH under Subpart 521 Division VIII of the CARs. This situation will likely occur when an aircraft importer intends to pursue the issue of the required Canadian design approval in person. In this situation, a design approval may be issued in the name of the importer or operator. Refer to Section 5.0 for further guidance.

4.3 Application for a design approval – section 521.453 of the CARs

  1. (1) Prior to submitting an application, the applicant should ensure that the requirements outlined in section 4.2 have been met so that the application can be processed with minimal delay.
  2. (2) In the case of an application from a jurisdiction with which TCCA has an airworthiness agreement or similar arrangement, validation will be performed in accordance with the procedures defined in the agreement or arrangement’s supporting documents (Ref. section 2.1(1)(k)).
  3. (3) Some airworthiness agreements include allowances for specific products or design approvals which are automatically accepted without the need for application or review such as:
    1. (a) Articles or appliances on the common TSO list between TCCA and the European Union Aviation Safety Agency (EASA) and all United States (US) TSO and United Kingdom (UK) TSO design approvals;
    2. (b) Federal Aviation Administration (FAA) issued Parts Manufacturer Approvals (PMA) and EASA/Civil Aviation Agency – United Kingdom (CAA-UK) issued STCs for replacement parts;
    3. (c) Repairs approved by the FAA, EASA, or CAA-UK in accordance with their respective implementation procedures;
    4. (d) Some design changes (including those classified as “minor” or “Basic” per the FAA/TCCA Implementation Procedures for Airworthiness (IPA)) made by a US DADH on previously validated or accepted aeronautical products that do not require TCCA to issue an amended Type Certificate (TC), Type Certificate Data Sheet (TCDS), STC, or amended STC;
    5. (e) Some design changes (classified as “Minor” or “Level 2 Major” per the EASA/TCCA and CAA-UK/TCCA Technical Implementation Procedures (TIP)) made by an EASA or UK DADH on previously validated or accepted aeronautical products and approved by the FCAA in accordance with its procedures, against the certification basis of both the FCAA and TCCA; and
    6. (f) FAA STCs intended for installation on eligible products (as defined in the FAA/TCCA IPA), limited to Normal, Utility, and Aerobatic category aircraft and their engines, including VLA designs, with a maximum take-off weight of 12,500 lb. or less, and Normal category rotorcraft and their engines.
    7. Note: Prior to Revision 3 of the FAA/TCCA IPA coming into force on July 25, 2021, FAA STCs that were installed on a broader set of aircraft were also eligible for automatic acceptance without application for validation. These included US SoD aircraft in the Normal, Utility, and Aerobatic categories, including VLA designs, type certified on the basis of Federal Aviation Regulation (14 CFR) Part 23 or equivalent standards and US SoD rotorcraft in the Normal category type certified on the basis of 14 CFR Part 27 or equivalent standards. This eligibility was irrespective of the aircraft’s inclusion on the eligible aircraft list. Some of these STCs were issued a corresponding TCCA STC while others were issued a letter of acceptance or were automatically accepted based solely on the FAA’s findings of compliance and subsequent approval. These FAA STCs constituted approved data for the purposes of installation on a Canadian-registered aircraft. As a result, the updated limitation to automatic acceptance of FAA STCs as outlined in subparagraph 4.3(3)(f) does not invalidate or nullify the compliance of any aircraft on which an eligible product was installed and whose maintenance release was signed prior to July 25, 2021. As of July 25, 2021, a FAA STC no longer solely constitutes approved data for the purposes of ensuing installations on Canadian-registered non-eligible aircraft (i.e. any aircraft not listed in section 2.1(1)(l)), since those STCs are subject to an application for validation in accordance with subparagraph 4.3(2) of this document and the FAA/TCCA IPA. This also means that applicable changes effective after July 25, 2021 to existing FAA STCs previously accepted and installed on non-eligible aircraft prior to July 25, 2021 are subject to an application for validation. The validation program and associated review will depend on the aircraft type and the complexity of the change per the FAA/TCCA IPA.
  4. (4) The above list is not meant to be exhaustive as the relevant implementation procedures or similar arrangements provided in section 2.1(1)(k) are amended from time to time and are consulted to ensure existing provisions or limitations have not been changed and to establish whether new products and/or design approvals have been added to the list of automatic acceptance.
  5. (5) Per the provisions set out in the relevant implementation procedures of airworthiness agreements or similar arrangements, TCCA may suspend the privilege of automatically accepting the products and design approvals in cases where an airworthiness concern or risk is identified by TCCA, and where, following consultation with the FCAA, there is no mutually acceptable solution for addressing that concern or risk.
  6. (6) More information on procedures and limitations for these cases is included in the relevant implementation procedures of the agreements which can be found at the link provided in section 2.1(1)(k).
  7. (7) In order to validate a foreign design approval in respect of an aeronautical product, including a design change or repair design, the applicant will, under subsection 521.543(1) of the CARs, submit an application to the Minister through its CAA. The design approval will undergo a type design examination as well as other validation activities based on the level of review corresponding to the complexity and risk associated with the aeronautical product. Refer to Subpart 104 of the CARs (Ref. section 2.1(1)(c)) and TCCA’s Aviation Service Standards ((Ref. section 2.1(1)(n)) for applicable fees, charges, published timeliness service standards, and performance information associated with specific design approvals and levels of review.
  8. (8) The following application forms are either available for download online or may be ordered:
    1. (a) 26-0756 – Type Certificate Application (Ref. section 2.1(1)(f));
    2. (b) 26-0764 – Canadian Technical Standard Order (CAN-TSO) Design Approval Application (Ref. section 2.1(1)(i)); and
    3. (c) 26-0469 – Design Change Approval Application (Includes STCs, RDAs, PDAs, and TC revisions, Ref. section 2.1(1)(j)).
    4. Note: While the use of specific forms is not mandated, an application that contains the information identified on these forms will be required.
  9. (9) The following data and supporting documents should be provided to facilitate assessment of the application and review by TCCA. The relevant implementation procedures of airworthiness agreements or similar arrangements should also be followed to ensure any specific application requirements are met. It should be noted that some of the data below may be a duplication of the information specified in the implementation procedures or on the application forms noted in paragraph (8) above. The actual data and documents required will depend on the type of design approval being validated:
    1. (a) A detailed description of the project/product;
    2. (b) The reason for application including a reference to the criteria that resulted in the submission (i.e. classification per the applicable bilateral agreement);
    3. (c) A copy of the DAD and TCDS, if available, that identifies the certification basis upon which the FCAA’s design approval was based. If a TCDS is not available, or has not yet been completed, the FCAA should submit the document that defines the certification basis or approval basis;
    4. (d) The date of application to the FCAA to determine the applicable amendment level of associated Canadian design or environmental standards, and the applicant’s requested date for TCCA approval;
    5. (e) If available at the time of application, technical data to enable the TCCA to complete the type design examination including but not limited to the following:
      1. (i) Compliance Checklist;
      2. (ii) Approved Manuals or changes to Approved Manuals as applicable including the Aircraft Flight Manual and Airworthiness Limitations section of the ICAs;
      3. (iii) Master Documentation List/Master Drawing List;
      4. (iv) Weight and Balance data; and
      5. (v) Instructions for Continued Airworthiness (ICA) which may include the following documents:
        1. (A) An installation manual;
        2. (B) A maintenance manual;
        3. (C) An overhaul manual;
        4. (D) Servicing instructions;
        5. (E) An illustrated parts manual;
        6. (F) A structural repair manual;
        7. (G) Supplemental integrity instructions; and
        8. (H) An MRB Report. and
    6. (f) If known at the time of application, include the following:
      1. (i) A description of all novel or unusual design features known to the applicant or the FCAA;
      2. (ii) All known or expected special conditions – airworthiness (SCAs), exemptions, deviations, equivalent level of safety findings, and any elect-to-comply to later amendment levels of the certification basis;
      3. (iii) Any Issue Papers or notification of findings raised during the FCAA’s certification activities;
      4. (iv) Information on any market interest and associated product delivery schedules; and
      5. (v) Any additional data/information for known in-service issues to understand continuing airworthiness implications and how they have been addressed.
  10. (10) In the case of the validation of the TC of a new aircraft type or derivative, or subsequent design changes by the TC holder, the CAA of the applicant will forward the application to the Chief of Project Management Division of the National Aircraft Certification Branch. For all other design approval validations, the application should be forwarded by the FCAA to the responsible TCCA Regional Manager, Aircraft Certification (RMAC) – formerly known asTechnical Team Lead (TTL) in the geographical region where the aircraft is located or intended to be imported (Ref. section 2.1(1)(m)).
  11. (11) For applications involving an STC, RDA, PDA, or CAN-TSO DAD without an established Canadian customer or timeframe to begin operations, the FCAA will forward the application to the Chief, Regional Engineering using the following central e-mail address: tc.civav.stc.cts.avciv.tc@tc.gc.ca.

4.4 Exceptions – section 521.454 of the CARs

  1. (1) Section 521.454 of the CARs identifies certain paragraphs that do not apply in respect of a foreign aeronautical product since the requirements have been satisfied by the applicant and their compliance is deemed to have been demonstrated to the FCAA as part of their own activities. For instance, findings of compliance to paragraph 521.44(a) of the CARs – conformity checks, paragraph 521.44(b) of the CARs – test flight equipment and procedures, section 521.47 of the CARs – function and reliability test flights, and paragraph 521.108(a) of the CARs – calibration of test equipment would have been already accomplished by the FCAA or, in the case of section 521.47 of the CARs, may be an ongoing post-certification activity.
  2. (2) Furthermore, and for the same reasons noted in paragraph (1) above, while inspection and test requirements defined in section 521.45 of the CARs as well as flight test operation manuals in section 521.46 do apply to foreign aeronautical products, the FCAA’s findings may be accepted by TCCA as meeting the intent of the requirements.
  3. (3) In addition, it may be determined that some responsibilities for DADH under Subpart 521 Division VIII of the CARs such as section 521.353 of the CARs – requirements for Service Difficulty Reports (SDRs) to the Minister are already being met as ICAO requires DADH to report SDRs to the State of Registry (SoR) and the manufacturer (Ref. section 2.1(1)(o)). Likewise, a foreign DADH may be found to already comply with section 521.354 of the CARs for an SDR system and section 521.355 of the CARs for investigation of SDRs where the FCAA would undertake these activities in compliance with ICAO Annex 8, as a minimum. This might also be outlined in applicable airworthiness agreements or similar arrangements.

4.5 Issuance – Design Approval Document – section 521.455 of the CARs

  1. (1) The purpose of carrying out the validation program is so that TCCA can determine whether the design of the foreign aeronautical product provides an equivalent level of safety as it would have had it been certificated in Canada. The type design examination is the procedural instrument used by TCCA to make this determination with regards to the certification or approval basis of the design in question.
  2. (2) Although the Canadian standards are not quoted on the foreign DAD, the goal of the type design examination is to establish the equivalence to Canadian standards of the findings of compliance made to the foreign standards.
  3. (3) FCAA and applicant involvement is expected with respect to some or all of the following validation activities which are to be coordinated by TCCA and the assigned Project Certification Manager (PCM) or Regional Engineer:
    1. (a) The initial briefing (virtual or onsite at TCCA);
    2. (b) Any follow-on technical briefings that may be necessary;
    3. (c) Developing a work plan (also known as validation plan);
    4. (d) Establishing the Canadian type design configuration and Canadian certification basis;
    5. (e) Review of approved manuals;
    6. (f) Review of the ICAs;
    7. (g) Processing of Issue Papers;
    8. (h) Review of design change procedures;
    9. (i) Inspection of the product for the purpose of gaining technical familiarity with the product including but not limited to any new or novel technologies and conducting flight tests;
    10. (j) Approval of design changes resulting from the TCCA review; and
    11. (k) Making statements of compliance with the Canadian certification basis including Canadian Additional Technical Conditions (ATC) with the guidance of applicable Canadian advisory material.

4.5.1 Type design examination – no airworthiness agreement or similar arrangement – subsection 521.455(1) of the CARs

  1. (1) Although it is not strictly required, it is highly beneficial for all parties involved to develop alternate arrangements between TCCA and the exporting authority to facilitate the acceptance by TCCA of any findings of compliance by the FCAA. Typically, these arrangements would be considered lower-level administrative or technical arrangements at the departmental level. Gaining knowledge of and experience with the exporting country’s regulatory system is the foundation of the validation principles which facilitates the acceptance of findings for the purpose of demonstrating the design’s equivalent level of safety when compared against Canadian requirements and standards. In the absence of agreements or arrangements, the administrative and procedural burden on all parties will be greatly increased.
  2. (2) A type design examination is performed using an appropriate level of review defined in the appendices of this AC. A two-fold approach may be required to gain knowledge and confidence in the national regulatory system of the exporting country, followed by a more detailed examination of the product’s design to determine whether compliance has been equivalently demonstrated with the relevant Canadian standards and requirements set out in Subpart 521 of the CARs for the design approval being applied for.
  3. (3) All efforts should be made to ensure that the outcome of the regulatory review culminates in the establishment of an airworthiness agreement between the SoD of the product and Canada or similar administrative arrangements including product specific arrangements. Such agreements and arrangements will help shape and define the roles and responsibilities of all parties involved during subsequent validation efforts or changes to validated design approvals, eliminate duplication or reiteration of efforts, and facilitate future collaborations between TCCA, the FCAA and applicants.

4.5.2 Type design examination with airworthiness agreement or similar arrangement – subsection 521.455(2) of the CARs

  1. (1) In the case of an application from a jurisdiction with which Canada has an airworthiness agreement or similar administrative arrangement between TCCA and the FCAA, the FCAA and the applicant should follow the procedures outlined in these agreements or arrangements and their supporting documents (Ref. section 2.1(1)(k)).
  2. (2) Per the procedures outlined in the agreements and arrangements mentioned above, some design approvals will be required to undergo a type design examination and other validation activities using an appropriate level of review defined in the appendices of this AC.

4.5.3 Issuance and acceptance of Design Approval Documents – subsection 521.455(3)

  1. (1) An equivalent DAD can be issued when TCCA has completed the validation program and determined that the design of the foreign aeronautical product provides an equivalent level of safety to that specified in the appropriate division of Subpart 521 of the CARs.
  2. (2) It is important to note that once the validation program is completed and it is determined that an equivalent Canadian design approval will be issued, it is the Canadian certification basis stated in terms of the AWM if possible, that will be specified on the DAD.
  3. (3) Where a design change approval or repair approval document issued by an FCAA is applicable to a limited serial number range of an aeronautical product, TCCA will issue an STC or RDA, respectively, limited by that same serial number range as appropriate.
  4. (4) Alternatively, TCCA may accept the DAD issued by the FCAA in accordance with the provisions of the airworthiness agreement or similar arrangement in place. This privilege is limited to STCs subject to a Level 1 review (see Appendix A1). The foreign design approval will instead be accepted in which case TCCA will communicate the acceptance via a letter.
  5. Note: This acceptance of DAD should not be confused with the privilege of automatic acceptance previously described in paragraph 4.3(3). Contrary to automatic acceptance, an application for validation is to be submitted.
  6. (5) These accepted design approvals constitute approved data for the purposes of installation on a Canadian-registered aircraft.
  7. (6) The above acceptance reflects the configuration and models applicable at the time of application. Any major change to the type design or an addition of non-eligible models to a STC – or an associated Approved Model List (AML) – requires an application in accordance with the implementation procedures of the airworthiness agreement or similar arrangement and section 4.6 below to update the associated records.
  8. (7) As with domestic design approval, the validated design approval will not also constitute an approval to manufacture the aeronautical product.
  9. (8) The applicant is required to submit a signed declaration to TCCA attesting that the product has been demonstrated to comply with the certification basis (see AC 521-002 or AC 521-004 as appropriate). The declaration is required before the DAD is issued.
    1. (a) The declaration is not required by TCCA if the FCAA is making the finding of compliance with the Canadian certification basis, however the FCAA may require such a declaration to support their finding.
  10. (9) Except as outlined in section 4.4, a foreign holder of a Canadian DAD or of an accepted design approval originally approved by a FCAA is required to fulfill their responsibilities as a DADH under Subpart 521 Division VIII of the CARs and the provisions specified in the airworthiness agreement or similar arrangement. To this end, a signed undertaking to carry out those responsibilities will need to be provided to TCCA prior to issuance of the approval (see AC 521-002 or AC 521-004 as appropriate).
    1. (a) A signed undertaking is only required on first issuance of a Canadian DAD or letter of acceptance of a foreign approval.
    2. (b) Even if the FCAA is overseeing some of the Division VIII commitments in accordance with the airworthiness agreement or similar arrangement (ref. section 4.4), the signed undertaking is still required by TCCA.

4.6 Changes to a type design – section 521.456 of the CARs

  1. (1) This section applies to a foreign holder of a Canadian DAD previously issued or of a foreign design approval accepted by TCCA under section 521.455 of the CARs who makes a change to the approved design of the aeronautical product for which the design approval was issued or accepted.

4.6.1 Type design examination of a design change – subsection 521.456(1) of the CARs

  1. (1) If a FCAA has issued an approval for a change to the design already validated or accepted in Canada and requests validation of this change on behalf of the DADH, TCCA will validate or accept the change and perform a type design examination as required using an appropriate level of review per the appendices of this AC.
  2. (2) Since efforts should have been made per section 4.5.1 to establish an airworthiness agreement between the SoD of the product and Canada or similar administrative arrangements including product specific arrangements, such agreements and arrangements would help to guide validation efforts of changes to validated design approvals. In such a case where agreements or arrangements are in place, the FCAA and the applicant should follow the procedures outlined in these agreements or arrangements and their supporting documents (Ref. section 2.1(1)(k)).
  3. (3) Per the procedures outlined in the airworthiness agreements and arrangements mentioned above, some design change approvals will require validation including a type design examination using an appropriate level of review defined in the appendices of this AC. The DADH is required to re-apply for validation of such changes through their FCAA and per the procedures of section 4.3.
  4. (4) If no such airworthiness agreements or arrangements are in place, the DADH will be required to apply for validation of all changes to the approved design through their FCAA and per the procedures of section 4.3.
  5. (5) It is not uncommon for an application for a design change to an aeronautical product to have a certification basis or approval basis that includes standards other than those of the AWM. This may be the case for products where TCCA accepted a foreign approval, no Canadian approval or acceptance exists, or the certification basis consists of standards no longer accepted in Canada for new type designs. In such cases, and subject to TCCA approval, an applicant may elect to use standards of airworthiness that will provide an equivalent level of safety to the standards shown on the relevant DAD’s TCDS or other applicable documentation.

4.6.2 Approval of a change to the design of a foreign aeronautical product – subsection 521.456(2) of the CARs

  1. (1) Similar to section 4.5.3, the change to the design of the foreign aeronautical product can be approved by either amending the Canadian DAD or accepting the foreign design approval in accordance with any airworthiness agreement or similar arrangement in place.
  2. (2) As mentioned in section 4.5.3, a foreign holder of a Canadian DAD or of an accepted design approval originally approved by a FCAA in respect of a design change is required to fulfill their responsibilities as a DADH in accordance with Subpart 521 Division VIII of the CARs and the provisions specified in the airworthiness agreement or similar arrangement.
  1. (1) Prior to making firm commitments regarding the importation of an aircraft or other aeronautical products into Canada, the owners and the operators or their representatives should produce a list of all foreign design changes installed thereon and provide this information to the regional aircraft certification office in the location where the aircraft will be operated (Ref. section 2.1(1)(m)). The required information should be conveyed directly to the Regional Engineer, or to the Regional Engineer through either a Civil Aviation Safety Inspector (CASI) – Airworthiness or a Minister’s Delegate – Maintenance (MD-M) involved with the importation activity. In accordance with the review criteria in this AC, the Regional Engineer will then determine the appropriate level of review and inform the interested party accordingly. Failure to involve TCCA as early as possible may incur delays in obtaining the required corresponding approvals and possibly jeopardize the issue of the required flight authority in time to meet the operator’s planned schedule of operations.
  2. (2) TCCA validation of a foreign design approval is not sufficient for the operation of a Canadian-registered aircraft. Each aircraft is required to have a flight authority and, for commercial operations, must be added to an Air Operator’s Certificate. The granting of these authorities requires further regulatory activities.
  3. (3) To conduct these activities in an efficient manner, it is appropriate to undertake them as part of the validation program:
    1. (a) Flight Authority – The issuance of a certificate of airworthiness requires approval of any deviations from the certified type design. Deviations from the certified type design are achieved by the incorporation of approved STCs or similarly approved design changes. When the type design holder is also the holder of an STC, such as a completion centre STC, it may be appropriate for the deviations to be reviewed at the same time as the basic type design to facilitate issuance of the necessary STCs or design change approvals. It will otherwise be necessary for any deviations to be reviewed at the time of aircraft importation in accordance with normal procedures. Details may be found in Subpart 507 of the CARs.
    2. (b) Operational Authority – Operators of aircraft registered in Canada are required to comply with all relevant CARs, the extent and effect of which depends on the category of aircraft and its intended type of operation. The requirements applied in this area are referred to as operating and flight rules and aircraft equipment requirements (e.g. an operational evaluation may be required). Details may be found in Part VI and VII of the CARs.
  4. (4) Once advised by TCCA of the applicable review requirements, the aircraft owner or operator is responsible for negotiating arrangements with the respective design data holders for the submission of applications to TCCA on its behalf, including copies of the pertinent technical data as specified in section 4.3 of this AC.
  5. (5) It may not be possible to issue a design approval in the name of the foreign DADH when:
    1. (a) The foreign DADH is no longer in business, or cannot be located by the interested Canadian aircraft owner or operator;
    2. (b) The foreign DADH has made their proprietary data available to the Canadian owner or operator, and does not wish to pursue the issue of a corresponding design approval on behalf of the Canadian owner or operator;
    3. (c) The Canadian owner or operator is required to produce additional technical data to show compliance with additional airworthiness and operational requirements; or
    4. (d) The foreign DADH refuses to have a Canadian design approval issued in their name.
  6. (6) When any of the above scenarios occur, and in accordance with prior arrangements made with a foreign DADH, a Canadian operator may seek validation of a foreign design approval, including the issue of a DAD limited by serial number in the name of the Canadian aircraft owner or operator, subject to the following conditions:
    1. (a) The Canadian owner or operator applies to TCCA for a design approval in accordance with the requirements of the applicable division of Subpart 521 of the CARs;
    2. (b) The DAD will not reference the foreign design approval;
    3. (c) The issue of the design approval limited by serial number is to be treated as a Canadian approval after it has been shown that the product and the Canadian holder meet the requirements of Subpart 521 of the CARs;
    4. (d) The foreign design approval will not be considered as having been subject to a validation program nor will it be indexed as such within the National Aeronautical Product Approval database (NAPA); and
    5. (e) The design approval of the same aeronautical product installed on subsequent aircraft may be recorded by revising the original DAD limited by serial number issued in satisfaction of any of the conditions specified in paragraph (4) above or in accordance with an airworthiness agreement or similar arrangement, provided that the aircraft is to be operated by the same operator. A separate design approval would need to be issued for a different operator.

6.0 Information management

  1. Not applicable.

7.0 Document history

  1. Not applicable.

8.0 Contact us

  1. For more information, please contact:
    Aircraft Certification Standards Division (AARTC)
    E-mail: TC.AARTQuestions.TC@tc.gc.ca
  2. We invite suggestions for amendment to this document. Submit your comments to:
    AART Documentation Services / Services de documentation AART
    E-mail: AARTDocServices-ServicesdocAART@tc.gc.ca

Original signed by

Linda Kovacic
Director, Standards Branch
Civil Aviation

Appendix A — Levels of review

  1. (1) Three different levels of review have been established to facilitate the validation of foreign design approvals intended for import into Canada. The levels utilize elements of risk management and have been developed to enable TCCA to take advantage of, and give maximum credit to, the FCAA responsible for the design approval of the imported products. In each case, however, compliance with Canadian standards of airworthiness will be assured.

  2. (2) The level of review to be undertaken will be determined in part by the extent to which the standards applied by the FCAA have been recognized by and found acceptable to TCCA, and by the type of product and design approval involved.

    Note: Some airworthiness agreements include allowances for specific products or design approvals which are automatically accepted without the need for application or review. See paragraph 4.3(3) for further details.

A1. Level 1 criteria and requirements

  1. (1) This level of review is appropriate for a foreign design approval that was issued by an FCAA whose regulatory system, design approval, and certification process as well as airworthiness and environmental standards are well known to TCCA, thus permitting a high degree of confidence that the foreign design approval process was comparable and equivalent to that which would have been undertaken by TCCA.
  2. (2) A level 1 review is applicable where TCCA has entered into airworthiness agreements or similar arrangements with other countries and FCAAs that may allow for directly accepting or giving full credit to the compliance determinations made by the FCAA and that enable maximum acceptance of findings for a given design approval based on the implementation procedures of the airworthiness agreement or similar arrangement.
  3. (3) Level 1 is essentially an administrative process with minimal review of technical data and would usually apply to less complex products and changes to design approvals.
  4. (4) The applicant is to provide, through their FCAA, technical documentation listed in section 4.3 of this AC or as specified by the designated PCM or Regional Engineer.
  5. (5) The FCAA will make a statement of compliance with TCCA-established airworthiness requirements and design-related operating requirements.
  6. (6) The criteria and requirements of this level of review correspond to the “Streamlined Validation” process referred to in some airworthiness agreements and similar arrangements (Ref. section 2.1(1)(k)).
  7. (7) In accordance with the airworthiness agreement or similar arrangement, once TCCA has completed the validation program, a Canadian DAD can be issued. For STCs, where supported by the airworthiness agreement or similar arrangement, TCCA will issue a letter of acceptance in lieu of a Canadian STC. See section 4.5.3 for more details.

A2. Level 2 criteria and requirements

  1. (1) While still giving maximum credit to the findings of compliance already made by the responsible FCAA, level 2 review is applicable to progressively more complex products used in transporting passengers or providing services including their engines and propellers that are to be incorporated in Canadian-designed aircraft.
  2. (2) This level of review is appropriate when TCCA determines that acquisition of pertinent technical data or knowledge of the design approval and product is necessary. This involves a documentation review and a potential for in-person review, either on-site or at TCCA, consistent with any airworthiness agreement or similar arrangement in place between TCCA and the FCAA to achieve the following objectives, as applicable:
    1. (a) Determine whether compliance has been equivalently demonstrated with the TCCA-established type certification basis or basis of approval;
    2. (b) Determine compliance with TCCA-established design-related operational requirements;
    3. (c) Determine compliance with TCCA-established ATCs;
    4. Note: For some design changes affecting compliance with existing ATCs on TCCA’s certification basis, this may be satisfied by requesting the FCAA to make a statement that the subject design approval complies with applicable Canadian ATCs.
    5. (d) Review exemptions or deviations granted and Findings of Equivalent Safety made by the FCAA to establish whether they meet Canadian compliance expectations;
    6. (e) Review of any novel or unusual design features to establish whether the SCAs issued by the FCAA meet the Canadian compliance expectations or whether additional SCAs need to be raised;
    7. (f) Gain knowledge necessary to support in service design change activity and to discharge continuing airworthiness responsibilities; and
    8. (g) Gain sufficient knowledge of the aeronautical product as to enable the managing of technical assistance between authorities and the delegation of certain compliance verification or testing activities to the FCAA, where required.
  3. (3) Typically, this level of review will be applied to design approvals originating from a country whose regulatory system, standards and design approval processes are sufficiently known to TCCA and with which TCCA has entered into airworthiness agreements or similar arrangements.
  4. (4) In certain cases, a FCAA’s design approval and supporting data provided at the time of application may already be sufficient for TCCA to establish compliance with its certification basis. Where such compliance can be established during TCCA’s initial review of the application package, and TCCA deems minimal or no further action is required (and where supported by the airworthiness agreement or other arrangement), TCCA may at this point conclude the technical validation process with a minimal work plan or no work plan. In such cases, TCCA may proceed directly to the issuance of its validation design approval.
  5. (5) The applicant is to provide, through their FCAA, technical documentation listed in section 4.3 of this AC or as specified by the designated PCM or Regional Engineer.
  6. (6) The FCAA will make a statement of compliance with TCCA-established airworthiness requirements and design-related operating requirements.
  7. (7) In accordance with the implementation procedures of the airworthiness agreement or similar arrangement, once TCCA has completed the validation program, an equivalent Canadian DAD can be issued.

A3. Level 3 criteria and requirements

  1. (1) Level 3 would usually be applied where products to be imported into Canada have been approved by an FCAA of which TCCA may have little knowledge or insufficient experience and knowledge of the organization and standards policies and procedures pertinent to a specific category of product. Level 3 combines a two-fold approach of gaining knowledge and confidence in the regulatory system of the exporting country, followed by a more detailed evaluation of the specific product and its design approval against Canadian standards.
    1. (a) In cases where the FCAA is well known to TCCA but there is no airworthiness agreement or similar arrangement, the credit given to the FCAA will be at the discretion of TCCA and a review of the FCAA may not be required.
  2. (2) For a level 3 review, credit given for any findings of compliance made by the FCAA will be at the discretion of TCCA. In specific cases, a flight evaluation may also be required.
  3. (3) A level 3 review will typically require an on-site visit to the applicant’s facilities.
  4. (4) The expected objectives for this level of review are shown below, as applicable:
    1. (a) Gain knowledge of the foreign regulatory airworthiness system including organization, pertinent policies, standards, and procedures specific to the product type and design approval being validated;
    2. (b) Determine whether compliance has been equivalently demonstrated with the TCCA-established type certification basis or basis of approval;
    3. (c) Determine compliance with TCCA-established ATCs;
    4. (d) Review exemptions or deviations granted and "Findings of Equivalent Safety" made by the FCAA to establish whether they meet Canadian compliance expectations;
    5. (e) Review of any novel or unusual design features to establish whether the SCAs issued by the FCAA meet the Canadian compliance expectations or whether additional SCAs need to be raised;
    6. (f) Gain necessary knowledge to support in-service design change activity and to discharge continuing airworthiness responsibilities;
    7. (g) Gain sufficient knowledge of the aeronautical product as to enable the the managing of technical assistance between authorities and the delegation of certain compliance verification or testing activities to the FCAA, where required; and
    8. (h) Advise on, and subsequently implement, required Canadian import procedures.
  5. (5) The applicant is to provide, through their FCAA, technical documentation listed in section 4.3 of this AC or as specified by the designated PCM or Regional Engineer.
  6. (6) The FCAA will make a statement of compliance with TCCA-established airworthiness requirements and design-related operating requirements.
  7. (7) Under section 521.455 and 521.456 of the CARs, once TCCA has completed the validation program, an equivalent Canadian DAD can be issued.
  8. (8) Following successful completion of the validation program, all efforts should be made by TCCA and the FCAA to engage in discussions to develop formal airworthiness agreements between Canada and the exporting SoD or similar administrative arrangements between TCCA and the FCAA, the scope of which will depend on the size, complexity and nature of the completed validation program as well as considerations for the potential of future validation activities between Canada and the exporting authority. Such agreements and arrangements will help shape and define roles and responsibilities and help to eliminate duplication or reiteration of efforts during subsequent validation efforts or changes to validated design approvals.

Appendix B — Expected Levels of Review

  1. (1) This appendix provides the expected levels of review based on the existence and details of airworthiness agreements or similar arrangements. Where an existing agreement lacks specificity, TCCA’s knowledge of countries' regulatory system, confidence in their FCAA with respect to the design approval process, and their experience in the exportation of their aeronautical products to Canada will inform the level of review.
  2. (2) Appendix A provides criteria for an established level of review, in the absence of an airworthiness agreement or similar arrangement, or when such an arrangement leaves room for judgement. Table B1 identifies the expected level of review for a given design approval, as indicated in such agreements.
  3. (3) There are two groups of countries/authorities:
    1. (a) Those with which with which Canada/TCCA has an airworthiness agreement or similar arrangement in place which is bound by treaty ratification principles and permits a suitable degree of confidence that their design approval process is equivalent to that of TCCA. To see an up-to-date list of countries with such agreements, refer to section 2.1(1)(k).
    2. (b) All other countries with which Canada has no agreement or arrangement or with which TCCA has little knowledge or experience with their respective airworthiness authorities. Applicants for validation of design approvals of all aeronautical products from these countries can expect a level 3 review (See appendix A) for all approvals.
  4. (4) As mentioned in section 3.1 of this AC, where differences arise between the guidelines presented in these appendices and an agreement’s implementation procedure or similar arrangement, the implementation procedure or arrangement prevails and is the primary reference.
  5. (5) The overall objective is to reduce TCCA involvement based on risk management, combined with satisfactory knowledge of, and experience with, an FCAA and their aeronautical product manufacturers.
  6. (6) It follows, however, that loss of confidence in an FCAA, or perhaps the credibility given to a specific applicant, could increase TCCA involvement in the review process. Efforts need to be made to resolve such issues through the maintenance of confidence procedures established by airworthiness agreements or similar arrangements.

Table B1 – Level of review for design approvals from Countries with Airworthiness Agreements or Similar Arrangements (Ref. section 2.1(1)(k))

Category

Review Type
AWM 522 – Gliders and Powered Gliders

Level 2A
AWM 523-VLA – Very Light Airplanes and
AWM 523 – Normal Category, Certification Level 1, 2, 3

Level 2A,D
AWM 523 – Normal Category, Certification Level 4

Level 2
AWM 525 – Transport Category Airplanes

Level 2
AWM 527 – Normal Category Rotorcraft

Level 2
AWM 529 – Transport Category Rotorcraft

Level 2
AWM 531 – Manned Free Balloons

Level 2A
AWM 541 – Airships (non-rigid)

Level 2A
AWM 541 – Airships (rigid)

Level 2
Advanced Air Mobility

Level 2
Agricultural or Special Purpose Category Aircraft

Level 2A
Restricted Category Aircraft

Level 2
AWM 533 – Engines (Turbofan, Turboprop, Turboshaft)

Level 2
AWM 533 – Engines (Piston)

Level 1
AWM 533 – Electric or Hybrid Engines

Level 2
AWM 533 – Airship (non-rigid) Engines

Level 2A
AWM 533 – Airship (Rigid) Engines

Level 2
AWM 535 – Propellers

Level 1
STCs

Level 2A,B
Major Modifications / Changes to the Type Design

Level 2A,B
Minor Modifications

Level 1C
TSOs, Parts (PMAs, PDAs), Repairs (RDAs, field repairs, etc.)

Level 1C
  1. Notes:
    1. A – simplified level 2 review (see section A2(4)) may be applicable, depending on the provisions of the airworthiness agreement or similar arrangement.
    2. B – some STCs and Major modifications may be eligible for level 1 review or automatic acceptance, as specified in the relevant airworthiness agreements or similar arrangements
    3. C – under most airworthiness agreements or similar arrangements, these are automatically accepted by TCCA
    4. D – With unusual feature(s) or service history problem(s), full level 2 review will be applied
 
Date modified: