(a) the issue of type-certificates, restricted type-certificates, supplemental type-certificates and changes to those certificates;

(b) the issue of certificates of airworthiness, restricted certificates of airworthiness, permits to fly and authorised release certificates;

(c) the issue of repair design approvals;

(d) the showing of compliance with environmental protection requirements;

(e) the issue of noise certificates;

(f) the identification of products, parts and appliances;

(g) the certification of certain parts and appliances;

(h) the certification of design and production organisations;

(i) the issue of airworthiness directives.

(a) ‘JAA’ means the ‘Joint Aviation Authorities’;

(b) ‘JAR’ means ‘Joint Aviation Requirements’;

(c) ‘Part 21’ means the requirements and procedures for the certification of aircraft and related products, parts and appliances, and of design and production organisations laid down in Annex I to this Regulation;

(d) ‘Part M’ means the applicable continuing airworthiness requirements adopted in pursuance of Regulation (EC) No 216/2008;

(e) ‘principal place of business’ means the head office or registered office of the undertaking within which the principal financial functions and operational control of the activities referred to in this Regulation are exercised;

(f) ‘article’ means any part and appliance to be used on civil aircraft;

(g) ‘ETSO’ means European Technical Standard Order. The European Technical Standard Order is a detailed airworthiness specification issued by the European Aviation Safety Agency (the ‘Agency’) to ensure compliance with the requirements of this Regulation as a minimum performance standard for specified articles;

(h) ‘EPA’ means European Part Approval. European Part Approval of an article means the article has been produced in accordance with approved design data not belonging to the type-certificate holder of the related product, except for ETSO articles;

(i) ‘ELA1 aircraft’ means the following manned European Light Aircraft:

(j) ‘ELA2 aircraft’ means the following manned European Light Aircraft:

(a) the product shall be deemed to have a type-certificate issued in accordance with this Regulation when:

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(b) the design of an individual aircraft, which was on the register of a Member State before 28 September 2003, shall be deemed to have been approved in accordance with this Regulation when:

(a) if a product is under certification by several Member States, the most advanced project shall be used as the reference;

(b) points 21.A.15(a), (b) and (c) of Annex I (Part 21) shall not apply;

(c) by way of derogation from point 21.A.17A of Annex I (Part 21), the type-certification basis shall be that established by the JAA or, where applicable, the Member State at the date of application for the approval;

(d) compliance findings made under JAA or Member State procedures shall be deemed to have been made by the Agency for the purpose of complying with points 21.A.20(a) and (d) of Annex I (Part 21).

(a) if an approval process is being carried out by several Member States, the most advanced project shall be used as the reference;

(b) point 21.A.93 of Annex I (Part 21) shall not apply;

(c) the applicable type-certification basis shall be that established by the JAA or, where applicable, the Member State at the date of application for the approval of change;

(d) compliance findings made under JAA or Member State procedures shall be deemed to have been made by the Agency for the purpose of complying with points 21.A.103(a)(2) and (b) of Annex I (Part 21).

(a) if a certification process was being carried out by several Member States, the most advanced project shall be used as the reference;

(b) point 21.A.113 (a) and (b) of Annex I (Part 21) shall not apply;

(c) the applicable certification basis shall be that established by the JAA or, where applicable, the Member State at the date of application for the supplemental type-certificate or the major change approval;

(d) the compliance findings made under JAA or Member State procedures shall be deemed to have been made by the Agency for the purpose of complying with point 21.A.115(a) of Annex I (Part 21).

(a) if an authorisation process was being carried out by several Member States, the most advanced project shall be used as the reference;

(b) point 21.A.603 of Annex I (Part 21) shall not apply;

(c) the applicable data requirements laid down in point 21.A.605 of Annex I (Part 21) shall be those established by the relevant Member State, at the date of application for the approval or authorisation;

(d) compliance findings made by the relevant Member State shall be deemed to have been made by the Agency for the purpose of complying with point 21.A.606(b) of Annex I (Part 21).

(a) that State is the State of design; and

(b) the Agency has determined that the system of that State includes the same independent level of checking of compliance as provided by this Regulation, either through an equivalent system of approvals of organisations or through direct involvement of the competent authority of that State.

(a) that State is the State of manufacture; and

(b) the Agency has determined that the system of that State includes the same independent level of checking of compliance as provided by this Regulation, either through an equivalent system of approvals of organisations or through direct involvement of the competent authority of that State.

(a) for organisations having their principal place of business in a Member State, the authority designated by that Member State; or the Agency if so requested by that Member State; or

(b) for organisations having their principal place of business in a non-member State, the Agency.

(a) System for Collection, Investigation and Analysis of Data

The holder of a type-certificate, restricted type-certificate, supplemental type-certificate, European Technical Standard Order (ETSO) authorisation, major repair design approval or any other relevant approval deemed to have been issued under this Regulation shall have a system for collecting, investigating and analysing reports of and information related to failures, malfunctions, defects or other occurrences which cause or might cause adverse effects on the continuing airworthiness of the product, part or appliance covered by the type-certificate, restricted type-certificate, supplemental type-certificate, ETSO authorisation, major repair design approval or any other relevant approval deemed to have been issued under this Regulation. Information about this system shall be made available to all known operators of the product, part or appliance and, on request, to any person authorised under other associated implementing Regulations.

(b) Reporting to the Agency

(c) Investigation of Reported Occurrences

(a) An airworthiness directive means a document issued or adopted by the Agency which mandates actions to be performed on an aircraft to restore an acceptable level of safety, when evidence shows that the safety level of this aircraft may otherwise be compromised.

(b) The Agency shall issue an airworthiness directive when:

(c) When an airworthiness directive has to be issued by the agency to correct the unsafe condition referred to in point (b), or to require the performance of an inspection, the holder of the type-certificate, restricted type-certificate, supplemental type-certificate, major repair design approval, ETSO authorisation or any other relevant approval deemed to have been issued under this Regulation, shall:

(d) An airworthiness directive shall contain at least the following information:

(a) the satisfactory coordination of design and production required by 21A.122, 21A.130(b)(3) and (4), 21A.133 and 21A.165(c)(2) and (3) as appropriate, and

(b) the proper support of the continued airworthiness of the product, part or appliance.

(a) Any organisation applying for a type-certificate or restricted type-certificate shall demonstrate its capability by holding a design organisation approval, issued by the Agency in accordance with Subpart J.

(b) By way of derogation from point (a), as an alternative procedure to demonstrate its capability, an applicant may seek the agreement of the Agency for the use of procedures setting out the specific design practices, resources and sequence of activities necessary to comply with this Annex I (Part 21), when the product is one of the following:

(c) By way of derogation from point (a), an applicant may choose for demonstration of capability by providing the Agency with the certification programme required by point 21.A.20(b) when the product is one of the following:

(a) An application for a type-certificate or restricted type-certificate shall be made in a form and manner established by the Agency.

(b) An application for an aircraft type-certificate or restricted type-certificate shall be accompanied by a three-view drawing of that aircraft and preliminary basic data, including the proposed operating characteristics and limitations.

(c) An application for an engine or propeller type-certificate shall be accompanied by a general arrangement drawing, a description of the design features, the operating characteristics, and the proposed operating limitations, of the engine, or propeller.

(d) An application for a type-certificate or restricted type-certificate for an aircraft shall include, or be supplemented with, after the initial application, the application for approval of operational suitability data, consisting of, as applicable:

(a) The Agency shall prescribe special detailed technical specifications, named special conditions, for a product if the related certification specifications do not contain adequate or appropriate safety standards for the product, because:

(b) The special conditions shall contain such safety standards as the Agency finds necessary to establish a level of safety equivalent to that established in the applicable certification specifications.

(a) The type-certification basis to be notified for the issuance of a type-certificate or a restricted type-certificate shall consist of:

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(b) An application for type-certification of large aeroplanes and large rotorcraft shall be effective for five years and an application for any other type-certificate shall be effective for three years, unless an applicant shows at the time of application that its product requires a longer period of time for design, development, and testing, and the Agency approves a longer period.

(c) In the case where a type-certificate has not been issued, or it is clear that a type-certificate will not be issued, within the time limit established under point (b), the applicant may:

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(d) If an applicant chooses to comply with a certification specification of an amendment to the airworthiness codes that is effective after the filing of the application for a type-certificate, the applicant shall also comply with any other certification specification that the Agency finds is directly related.

(a) The Agency shall notify to the applicant the operational suitability data certification basis. It shall consist of:

(b) If an applicant chooses to comply with an amendment to the certification specifications that is effective after the filing of the application for a type-certificate, the applicant shall also comply with any other certification specification that the Agency finds is directly related.

(a) The applicable noise requirements for the issue of a type-certificate for an aircraft are prescribed according to the provisions of Chapter 1 of Annex 16, Volume I, Part II to the Chicago Convention and:

(b) The applicable emission requirements for the issue of a type-certificate for an aircraft and engine are prescribed in Annex 16 to the Chicago Convention:

(c) The Agency shall issue, in accordance with Article 19 of Regulation (EC) No 216/2008, certification specifications providing for acceptable means to demonstrate compliance with the noise and the emission requirements laid down in points (a) and (b) respectively.

(a) The applicant for a type-certificate or a restricted type-certificate shall demonstrate compliance with the applicable type-certification basis, the applicable operational suitability data certification basis and environmental protection requirements and shall provide the Agency with the means by which such compliance has been demonstrated.

(b) The applicant shall provide the Agency with a certification programme detailing the means for compliance demonstration. This document shall be updated as necessary during the certification process.

(c) The applicant shall record justification of compliance within compliance documents according to the certification programme established under point (b).

(d) The applicant shall declare that it has demonstrated compliance with the applicable type-certification basis and environmental protection requirements, according to the certification programme established under point (b).

(e) Where the applicant holds an appropriate design organisation approval, the declaration of point (d) shall be made according to the provisions of Subpart J.

(a) demonstrating its capability in accordance with point 21.A.14;

(b) submitting the declaration referred to in point 21.A.20(d); and

(c) it is shown that:

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(d) In the case of an aircraft type-certificate, the engine or propeller, or both, if installed in the aircraft, have a type-certificate issued or determined in accordance with this Regulation;

(e) In the case of an aircraft type-certificate, it is demonstrated that the operational suitability data meets the applicable operational suitability data certification basis designated in accordance with 21.A.17B;

(f) By derogation from point (e), and at the request of the applicant included in the declaration referred to in point 21.A.20(d), an aircraft type-certificate may be issued before compliance with the applicable operational suitability data certification basis has been demonstrated, subject to the applicant demonstrating compliance with the operational suitability data certification basis before the operational suitability data must actually be used.

(a) For an aircraft that does not meet the provisions of point 21.A.21(c), the applicant shall be entitled to have a restricted type-certificate issued by the Agency after:

(b) By derogation from point 3 of point (a), and at the request of the applicant included in the declaration referred to in point 21.A.20(d), a restricted type-certificate may be issued before compliance with the applicable operational suitability data certification basis has been demonstrated, subject to the applicant demonstrating compliance with the operational suitability data certification basis before the operational suitability data must actually be used.

(c) The engine or propeller installed in the aircraft, or both, shall:

(a) The type design shall consist of:

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(b) Each type design shall be adequately identified.

(a) The applicant shall perform all inspections and tests necessary to demonstrate compliance with the applicable type-certification basis and environmental protection requirements.

(b) Before each test required by point (a) is undertaken, the applicant shall have determined:

(c) The applicant shall allow the Agency to make any inspection necessary to check compliance with point (b).

(d) The applicant shall allow the Agency to review any report and make any inspection and to perform or witness any flight and ground test necessary to check the validity of the declaration of compliance submitted by the applicant under point 21.A.20(d) and to determine that no feature or characteristic makes the product unsafe for the uses for which certification is requested.

(e) For tests performed or witnessed by the Agency under point (d):

(a) Flight testing for the purpose of obtaining a type-certificate shall be conducted in accordance with conditions for such flight testing specified by the Agency.

(b) The applicant shall make all flight tests that the Agency finds necessary:

(c) (Reserved)

(d) (Reserved)

(e) (Reserved)

(f) The flight tests prescribed in point (b)(2) shall include:

(a) undertake the obligations laid down in points 21.A.3A, 21.A.3B, 21.A.4, 21.A.55, 21.A.57, 21.A.61 and 21.A.62; and, for this purpose, shall continue to meet the qualification requirements for eligibility under point 21.A.14; and

(b) specify the marking in accordance with Subpart Q.

(a) A type-certificate and restricted type-certificate shall be issued for an unlimited duration. They shall remain valid subject to:

(b) Upon surrender or revocation, the type-certificate and restricted type-certificate shall be returned to the Agency.

(a) The holder of the type-certificate or restricted type-certificate shall furnish at least one set of complete instructions for continued airworthiness, comprising descriptive data and accomplishment instructions prepared in accordance with the applicable type-certification basis, to each known owner of one or more aircraft, engine or propeller upon its delivery or upon issue of the first certificate of airworthiness for the affected aircraft, whichever occurs later and thereafter make those instructions available on request to any other person required to comply with any of the terms of those instructions. The availability of some manual or portion of the instructions for continued airworthiness, dealing with overhaul or other forms of heavy maintenance, may be delayed until after the product has entered into service, but shall be available before any of the products reaches the relevant age or flight-hours/cycles.

(b) In addition, changes to the instructions for continued airworthiness shall be made available to all known operators of the product and shall be made available on request to any person required to comply with any of those instructions. A programme showing how changes to the instructions for continued airworthiness are distributed shall be submitted to the Agency.

(a) at least one set of complete operational suitability data prepared in accordance with the applicable operational suitability certification basis, to all known EU operators of the aircraft, before the operational suitability data must be used by a training organisation or an EU operator; and

(b) any change to the operational suitability data to all known EU operators of the aircraft; and

(c) on request, the relevant data referred to in points (a) and (b) above, to:

(a) Standard changes are changes to a type-certificate:

(b) Points 21.A.91 to 21.A.109 are not applicable to standard changes.

(a) Only the type-certificate holder may apply for approval of a major change to a type-certificate under this Subpart; all other applicants for a major change to a type-certificate shall apply under Subpart E.

(b) Any natural or legal person may apply for approval of a minor change to a type-certificate under this Subpart.

(a) A description of the change identifying:

(b) Identification of any re-investigations necessary to show compliance of the changed product with the applicable certification specifications and environmental protection requirements.

(c) When the change affects the operational suitability data, the application shall include, or be supplemented after the initial application to include the necessary changes to the operational suitability data.

(a) by the Agency; or

(b) by an appropriately approved design organisation under a procedure agreed with the Agency.

(a) An applicant for approval of a major change shall:

(b) Approval of a major change in a type-certificate is limited to that or those specific configuration(s) in the type-certificate upon which the change is made.

(a) An applicant for a change to a type-certificate shall demonstrate that the changed product complies with the certification specifications that are applicable to the changed product and that are in effect at the date of the application for the change, unless compliance with certification specifications of later effective amendments is chosen by the applicant or required under points (e) and (f), and with the applicable environmental protection requirements laid down in point 21.A.18.

(b) By derogation from point (a), an applicant may show that the changed product complies with an earlier amendment of the certification specifications referred to in point (a), and of any other certification specification the Agency finds is directly related. However, the earlier amended certification specifications shall not precede the corresponding certification specifications incorporated by reference in the type-certificate. The applicant may show compliance with an earlier amendment of the certification specifications for any of the following:

(c) An applicant for a change to an aircraft (other than a rotorcraft) of 2 722 kg (6 000 lbs) or less maximum weight or to a non-turbine rotorcraft of 1 361 kg (3 000 lbs) or less maximum weight may show that the changed product complies with the type-certification basis incorporated by reference in the type-certificate. However, if the Agency finds that the change is significant in an area, the Agency may designate compliance with an amendment to the type-certification basis incorporated by reference in the type-certificate in effect at the date of the application and any certification specification that the Agency finds is directly related, unless the Agency also finds that compliance with that amendment or certification specification would not contribute materially to the level of safety of the changed product or would be impractical.

(d) If the Agency finds that the certification specifications in effect at the date of the application for the change do not provide adequate standards with respect to the proposed change, the applicant shall also comply with any special conditions, and amendments to those special conditions, prescribed under the provisions of point 21.A.16B, to provide a level of safety equivalent to that established in the certification specifications in effect at the date of the application for the change.

(e) An application for a change to a type-certificate for large aeroplanes and large rotorcraft is effective for five years, and an application for a change to any other type-certificate is effective for three years. In a case where the change has not been approved, or it is clear that it will not be approved under the time limit established under this point, the applicant may:

(f) If an applicant chooses to comply with a certification specification of an amendment to the certification specifications that is effective after the filing of the application for a change to a type, the applicant shall also comply with any other certification specification that the Agency finds is directly related.

(g) When the application for a change to a type-certificate for an aircraft includes, or is supplemented after the initial application to include changes to the operational suitability data, the operational suitability data certification basis shall be designated in accordance with points (a), (b), (c), (d) and (f) above.

(a) The applicant shall be entitled to have a major change to a type-certificate approved by the Agency after:

(b) A minor change to a type-certificate shall only be approved in accordance with point 21.A.95 if it is shown that the changed product meets the applicable certification specifications, as specified in point 21.A.101.

(a) The holder of a minor change approval to a type-certificate shall furnish at least one set of the associated variations, if any, to the instructions for continued airworthiness of the product on which the minor change is to be installed, prepared in accordance with the applicable type-certification basis, to each known owner of one or more aircraft, engine, or propeller incorporating the minor change, upon its delivery, or upon issuance of the first certificate of airworthiness for the affected aircraft, whichever occurs later, and thereafter make those variations in instructions available, on request, to any other person required to comply with any of the terms of those instructions.

(b) In addition, changes to those variations of the instructions for continued airworthiness shall be made available to all known operators of a product incorporating the minor change and shall be made available, on request, to any person required to comply with any of those instructions.

(a) at least one set of changes to the operational suitability data prepared in accordance with the applicable operational suitability certification basis, to all known EU operators of the changed aircraft, before the operational suitability data must be used by a training organisation or an EU operator; and

(b) any further change to the affected operational suitability data, to all known EU operators of the changed aircraft; and

(c) on request, the relevant parts of the changes in points (a) and (b) above, to:

(a) undertake the obligations laid down in points 21.A.4, 21.A.105, 21.A.107 and 21.A.108; and

(b) specify the marking, including EPA (European Part Approval) letters, in accordance with point 21.A.804(a).

(a) Any organisation applying for a supplemental type-certificate shall demonstrate its capability by holding a design organisation approval, issued by the Agency in accordance with Subpart J.

(b) By way of derogation from point (a), as an alternative procedure to demonstrate its capability, an applicant may seek Agency agreement for the use of procedures setting out the specific design practices, resources and sequence of activities necessary to comply with this Subpart.

(c) By way of derogation from points (a) and (b), an applicant may choose for demonstration of capability through Agency approval of a certification programme detailing the means for compliance demonstration for an STC on an aircraft, engine and propeller defined in point 21.A.14(c).

(a) An application for a supplemental type-certificate shall be made in a form and manner established by the Agency.

(b) An application for a supplemental type-certificate shall include the descriptions, identification, and changes to the operational suitability data required by point 21.A.93. In addition, such an application shall include a justification that the information on which those elements are based is adequate either from the applicant’s own resources, or through an arrangement with the type-certificate holder.

(a) submitting the declaration referred to in point 21.A.20(d); and

(b) it is demonstrated that:

(c) demonstrating its capability in accordance with point 21.A.112B;

(d) where, under point 21.A.113(b), the applicant has entered into an arrangement with the type-certificate holder,

(a) Minor changes to that part of a product covered by a supplemental type-certificate shall be classified and approved in accordance with Subpart D.

(b) Each major change to that part of a product covered by a supplemental type-certificate shall be approved as a separate supplemental type-certificate in accordance with this Subpart.

(c) By way of derogation from point (b), a major change to that part of a product covered by a supplemental type-certificate submitted by the supplemental type-certificate holder itself may be approved as a change to the existing supplemental type-certificate.

(a) undertake the obligations:

and for this purpose continue to meet the criteria of point 21.A.112B;

(b) specify the marking, including EPA letters, in accordance with point 21.A.804(a).

(a) A supplemental type-certificate shall be issued for an unlimited duration. It shall remain valid subject to:

(b) Upon surrender or revocation, the supplemental type-certificate shall be returned to the Agency.

(a) The holder of the supplemental type-certificate for an aircraft, engine, or propeller, shall furnish at least one set of the associated variations to the instructions for continued airworthiness, prepared in accordance with the applicable type-certification basis, to each known owner of one or more aircraft, engine, or propeller incorporating the features of the supplemental type-certificate, upon its delivery, or upon issuance of the first certificate of airworthiness for the affected aircraft, whichever occurs later, and thereafter make those variations in instructions available, on request, to any other person required to comply with any of the terms of those instructions. Availability of some manual or portion of the variations to the instructions for continued airworthiness, dealing with overhaul or other forms of heavy maintenance, may be delayed until after the product has entered into service, but shall be available before any of the products reaches the relevant age or flight-hours/cycles.

(b) In addition, changes to those variations of the instructions for continued airworthiness shall be made available to all known operators of a product incorporating the supplemental type-certificate and shall be made available, on request, to any person required to comply with any of those instructions. A programme showing how changes to the variations to the instructions for continued airworthiness are distributed shall be submitted to the Agency.

(a) at least one set of changes to the operational suitability data prepared in accordance with the applicable operational suitability certification basis, to all known EU operators of the changed aircraft, before the operational suitability data must be used by a training organisation or an EU operator; and

(b) any further change to the affected operational suitability data, to all known EU operators of the changed aircraft; and

(c) on request, the relevant parts of the changes in points (a) and (b) above, to:

(a) This Subpart establishes the procedure for demonstrating the conformity with the applicable design data of a product, part and appliance that is intended to be manufactured without a production organisation approval under Subpart G.

(b) This Subpart establishes the rules governing the obligations of the manufacturer of a product, part, or appliance being manufactured under this Subpart.

(a) it holds or has applied for an approval covering the design of that product, part or appliance; or

(b) it has ensured satisfactory coordination between production and design, through an appropriate arrangement with the applicant for, or holder of, an approval of such a design.

(a) Each application for an agreement to the showing of conformity of individual products, parts and appliances under this Subpart shall be made in a form and manner established by the competent authority.

(b) Such application shall contain:

(a) having established a production inspection system that ensures that each product, part or appliance conforms to the applicable design data and is in condition for safe operation;

(b) having provided a manual that contains:

(c) demonstrating that it is able to provide assistance in accordance with points 21.A.3A and 21.A.129(d).

(a) When objective evidence is found showing non-compliance of the holder of a letter of agreement with the applicable requirements of this Annex I (Part 21), the finding shall be classified as follows:

(b) A level three finding is any item where it has been identified, by objective evidence, to contain potential problems that could lead to a non-compliance under point (a).

(c) After receipt of notification of findings according to point 21.B.125:

(d) In case of level one or level two findings, the letter of agreement may be subject to a partial or full limitation, suspension and revocation under point 21.B.145. The holder of the letter of agreement shall provide confirmation of receipt of the notice of limitation, suspension or revocation of the letter of agreement in a timely manner.

(a) The letter of agreement shall be issued for a limited duration not exceeding one year. It shall remain valid unless:

(b) Upon surrender, revocation or expiry, the letter of agreement shall be returned to the competent authority.

(a) The production inspection system required under point 21.A.125A(a) shall provide a means for determining that:

(b) The production inspection system required by point 21.A.125A(a), shall also be such as to ensure that:

(a) Each manufacturer of an aircraft manufactured under this Subpart shall establish an approved production ground and flight test procedure and check-off forms, and in accordance with those forms, test each aircraft produced, as a means of establishing relevant aspects of compliance with point 21.A.125A(a).

(b) Each production test procedure shall include at least the following:

(a) make each product, part or appliance available for inspection by the competent authority;

(b) maintain at the place of manufacture the technical data and drawings necessary to determine whether the product conforms to the applicable design data;

(c) maintain the production inspection system that ensures that each product conforms to the applicable design data and is in condition for safe operation;

(d) provide assistance to the holder of the type-certificate, restricted type-certificate or design approval in dealing with any continuing airworthiness actions that are related to the products, parts or appliances that have been produced;

(e) establish and maintain an internal occurrence reporting system in the interest of safety, to enable the collection and assessment of occurrence reports in order to identify adverse trends or to address deficiencies, and to extract reportable occurrences. This system shall include evaluation of relevant information relating to occurrences and the promulgation of related information;

(f)

(a) Each manufacturer of a product, part or appliance manufactured under this Subpart shall raise a statement of conformity, an EASA Form 52 (see Appendix VIII), for complete aircraft, or EASA Form 1 (see Appendix I), for other products, parts or appliances. This statement shall be signed by an authorised person who holds a responsible position in the manufacturing organisation.

(b) A statement of conformity shall include:

(c) Each manufacturer of such a product, part or appliance shall:

present a current statement of conformity, for validation by the competent authority.

(d) The competent authority shall validate by counter-signature the statement of conformity if it finds after inspection that the product, part or appliance conforms to the applicable design data and is in condition for safe operation.

(a) the procedure for the issuance of a production organisation approval for a production organisation showing conformity of products, parts and appliances with the applicable design data;

(b) the rules governing the rights and obligations of the applicant for, and holders of, such approvals.

(a) justify that, for a defined scope of work, an approval under this Subpart is appropriate for the purpose of showing conformity with a specific design; and

(b) hold or have applied for an approval of that specific design; or

(c) have ensured, through an appropriate arrangement with the applicant for, or holder of, an approval of that specific design, satisfactory coordination between production and design.

(a) The production organisation shall demonstrate that it has established and is able to maintain a quality system. The quality system shall be documented. This quality system shall be such as to enable the organisation to ensure that each product, part or appliance produced by the organisation or by its partners, or supplied from or subcontracted to outside parties, conforms to the applicable design data and is in condition for safe operation, and thus exercise the privileges set forth in point 21.A.163.

(b) The quality system shall contain:

(a) The organisation shall submit to the competent authority a production organisation exposition providing the following information:

(b) The production organisation exposition shall be amended as necessary to remain an up-to-date description of the organisation, and copies of any amendments shall be supplied to the competent authority.

(a) with regard to general approval requirements, facilities, working conditions, equipment and tools, processes and associated materials, number and competence of staff, and general organisation are adequate to discharge obligations under point 21.A.165;

(b) with regard to all necessary airworthiness, noise, fuel venting and exhaust emissions data:

(c) with regard to management and staff:

(d) with regard to certifying staff, authorised by the production organisation to sign the documents issued under point 21.A.163 under the scope or terms of approval:

(a) After the issue of a production organisation approval, each change to the approved production organisation that is significant to the showing of conformity or to the airworthiness and characteristics of noise, fuel venting and exhaust emissions of the product, part or appliance, particularly changes to the quality system, shall be approved by the competent authority. An application for approval shall be submitted in writing to the competent authority and the organisation shall demonstrate to the competent authority before implementation of the change, that it will continue to comply with this Subpart.

(b) The competent authority shall establish the conditions under which a production organisation approved under this Subpart may operate during such changes unless the competent authority determines that the approval should be suspended.

(a) When objective evidence is found showing non-compliance of the holder of a production organisation approval with the applicable requirements of this Annex I (Part 21), the finding shall be classified as follows:

(b) A level three finding is any item where it has been identified, by objective evidence, to contain potential problems that could lead to a non-compliance under point (a).

(c) After receipt of notification of findings according to point 21.B.225,

(d) In case of level one or level two findings, the production organisation approval may be subject to a partial or full limitation, suspension or revocation under point 21.B.245. The holder of the production organisation approval shall provide confirmation of receipt of the notice of limitation, suspension or revocation of the production organisation approval in a timely manner.

(a) A production organisation approval shall be issued for an unlimited duration. It shall remain valid unless:

(b) Upon surrender or revocation, the certificate shall be returned to the competent authority.

(a) perform production activities under this Annex I (Part 21);

(b) in the case of complete aircraft and upon presentation of a statement of conformity (EASA Form 52) under point 21.A.174, obtain an aircraft certificate of airworthiness and a noise certificate without further showing;

(c) in the case of other products, parts or appliances, issue authorised release certificates (EASA Form 1) without further showing;

(d) maintain a new aircraft that it has produced and issue a certificate of release to service (EASA Form 53) in respect of that maintenance;

(e) under procedures agreed with its competent authority for production, for an aircraft it has produced and when the production organisation itself is controlling under its POA the configuration of the aircraft and is attesting conformity with the design conditions approved for the flight, to issue a permit to fly in accordance with point 21.A.711(c) including approval of the flight conditions in accordance with point 21.A.710(b).

(a) ensure that the production organisation exposition furnished in accordance with point 21.A.143 and the documents to which it refers, are used as basic working documents within the organisation;

(b) maintain the production organisation in conformity with the data and procedures approved for the production organisation approval;

(c)

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(d) record all details of work carried out;

(e) establish and maintain an internal occurrence reporting system in the interest of safety, to enable the collection and assessment of occurrence reports in order to identify adverse trends or to address deficiencies, and to extract reportable occurrences. This system shall include evaluation of relevant information relating to occurrences and the promulgation of related information;

(f)

(g) provide assistance to the holder of the type-certificate or design approval in dealing with any continuing airworthiness actions that are related to the products parts or appliances that have been produced;

(h) establish an archiving system incorporating requirements imposed on its partners, suppliers and subcontractors, ensuring conservation of the data used to justify conformity of the products, parts or appliances. Such data shall be held at the disposal of the competent authority and be retained in order to provide the information necessary to ensure the continuing airworthiness of the products, parts or appliances;

(i) where, under its terms of approval, the holder issues a certificate of release to service, determine that each completed aircraft has been subjected to necessary maintenance and is in condition for safe operation, prior to issuing the certificate;

(j) where applicable, under the privilege of point 21.A.163(e), determine the conditions under which a permit to fly can be issued;

(k) where applicable, under the privilege of point 21.A.163(e), establish compliance with points 21.A.711(c) and (e) before issuing a permit to fly to an aircraft.

(a) certificates of airworthiness shall be issued to aircraft which conform to a type-certificate that has been issued in accordance with this Annex I (Part 21);

(b) restricted certificates of airworthiness shall be issued to aircraft:

(a) Pursuant to point 21.A.172, an application for an airworthiness certificate shall be made in a form and manner established by the competent authority of the Member State of registry.

(b) Each application for a certificate of airworthiness or restricted certificate of airworthiness shall include:

(c) Unless otherwise agreed, the statements referred to in points (b)(2)(i) and (b)(3)(ii) shall be issued no more than 60 days before presentation of the aircraft to the competent authority of the Member State of registry.

(a) Where ownership of an aircraft has changed:

(b) Where ownership of an aircraft has changed, and the aircraft has a restricted certificate of airworthiness not conforming to a restricted type-certificate, the airworthiness certificates shall be transferred together with the aircraft provided the aircraft remains on the same register, or issued only with the formal agreement of the competent authority of the Member State of registry to which it is transferred.

(a) An airworthiness certificate shall be issued for an unlimited duration. It shall remain valid subject to:

(b) Upon surrender or revocation, the certificate shall be returned to the competent authority of the Member State of registry.

(a) Pursuant to point 21.A.203, an application for a noise certificate shall be made in a form and manner established by the competent authority of the Member State of registry.

(b) Each application shall include:

(c) Unless otherwise agreed, the statements referred to in point (b)(1) shall be issued no more than 60 days before presentation of the aircraft to the competent authority of the Member State of registry.

(a) if the aircraft remains on the same register, the noise certificate shall be transferred together with the aircraft; or

(b) if the aircraft moves to the register of another Member State, the noise certificate shall be issued upon presentation of the former noise certificate.

(a) A noise certificate shall be issued for an unlimited duration. It shall remain valid subject to:

(b) Upon surrender or revocation, the certificate shall be returned to the competent authority of the Member State of registry.

(a) in accordance with points 21.A.14, 21.A.112B, 21.A.432B or 21.A.602B; or

(b) for approval of minor changes or minor repair design, when requested for the purpose of obtaining privileges under point 21.A.263.

(a) The design organisation shall demonstrate that it has established and is able to maintain a design assurance system for the control and supervision of the design, and of design changes, of products, parts and appliances covered by the application. This design assurance system shall be such as to enable the organisation:

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(b) The design assurance system shall include an independent checking function of the showings of compliance on the basis of which the organisation submits compliance statements and associated documentation to the Agency.

(c) The design organisation shall specify the manner in which the design assurance system accounts for the acceptability of the parts or appliances designed or the tasks performed by partners or subcontractors according to methods which are the subject of written procedures.

(a) The design organisation shall furnish a handbook to the Agency describing, directly or by cross-reference, the organisation, the relevant procedures and the products or changes to products to be designed.

(b) Where any parts or appliances or any changes to the products are designed by partner organisations or subcontractors, the handbook shall include a statement of how the design organisation is able to give, for all parts and appliances, the assurance of compliance required by point 21.A.239(b), and shall contain, directly or by cross-reference, descriptions and information on the design activities and organisation of those partners or subcontractors, as necessary to establish this statement.

(c) The handbook shall be amended as necessary to remain an up-to-date description of the organisation, and copies of amendments shall be supplied to the Agency.

(d) The design organisation shall furnish a statement of the qualifications and experience of the management staff and other persons responsible for making decisions affecting airworthiness and environmental protection in the organisation.

(a) the staff in all technical departments are of sufficient numbers and experience and have been given appropriate authority to be able to discharge their allocated responsibilities and these, together with the accommodation, facilities and equipment are adequate to enable the staff to achieve the airworthiness, operational suitability and environmental protection objectives for the product;

(b) there is full and efficient coordination between departments and within departments in respect of airworthiness, operational suitability and environmental protection matters.

(a) The design organisation shall make arrangements that allow the Agency to make any investigations, including investigations of partners and subcontractors, necessary to determine compliance and continued compliance with the applicable requirements of this Subpart.

(b) The design organisation shall allow the Agency to review any report and make any inspection and perform or witness any flight and ground test necessary to check the validity of the compliance statements submitted by the applicant under point 21.A.239(b).

(a) When objective evidence is found showing non-compliance of the holder of a design organisation approval with the applicable requirements of this Annex I (Part 21), the finding shall be classified as follows:

(b) A level three finding is any item where it has been identified, by objective evidence, to contain potential problems that could lead to a non-compliance under point (a).

(c) After receipt of notification of findings under the applicable administrative procedures established by the Agency,

(d) In case of level one or level two findings, the design organisation approval may be subject to a partial or full suspension or revocation under the applicable administrative procedures established by the Agency. The holder of the design organisation approval shall provide confirmation of receipt of the notice of suspension or revocation of the design organisation approval in a timely manner.

(a) A design organisation approval shall be issued for an unlimited duration. It shall remain valid unless:

(b) Upon surrender or revocation, the certificate shall be returned to the Agency.

(a) The holder of a design organisation approval shall be entitled to perform design activities under this Annex I (Part 21) and within its scope of approval.

(b) Subject to point 21.A.257(b), the Agency shall accept without further verification the following compliance documents submitted by the applicant for the purpose of obtaining:

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(c) The holder of a design organisation approval shall be entitled, within its terms of approval and under the relevant procedures of the design assurance system:

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(a) maintain the handbook in conformity with the design assurance system;

(b) ensure that this handbook is used as a basic working document within the organisation;

(c) determine that the design of products, or changes or repairs thereof, as applicable, comply with applicable requirements and have no unsafe feature;

(d) except for minor changes or repairs approved under the privilege of point 21.A.263, provide to the Agency statements and associated documentation confirming compliance with point (c);

(e) provide to the Agency information or instructions related to required actions under point 21.A.3B;

(f) where applicable, under the privilege of point 21.A.263(c)(6), determine the conditions under which a permit to fly can be issued;

(g) where applicable, under the privilege of point 21.A.263(c)(7), establish compliance with points 21.A.711(b) and (e) before issuing a permit to fly to an aircraft.

(a) in conjunction with the type-certification procedures of Subpart B, D or E for the product in which it is to be installed; or

(b) where applicable, under the ETSO authorisation procedures of Subpart O; or

(c) in the case of standard parts, in accordance with officially recognised Standards.

(a) accompanied by an authorised release certificate (EASA Form 1), certifying that the item was manufactured in conformity to approved design data and is marked in accordance with Subpart Q; or

(b) a standard part; or

(c) in the case of ELA1 or ELA2 aircraft, a part or appliance that is:

(a) This Subpart establishes the procedure for the approval of repair design, and establishes the rights and obligations of the applicants for, and holders of, those approvals.

(b) This Subpart defines standard repairs that are not subject to an approval process under this Subpart.

(c) A ‘repair’ means elimination of damage and/or restoration to an airworthy condition following initial release into service by the manufacturer of any product, part or appliance.

(d) Elimination of damage by replacement of parts or appliances without the necessity for design activity shall be considered as a maintenance task and shall therefore require no approval under this Annex I (Part 21).

(e) A repair to an ETSO article other than an Auxiliary Power Unit (APU) shall be treated as a change to the ETSO design and shall be processed in accordance with point 21.A.611.

(a) Standard repairs are repairs:

(b) Points 21.A.432A to 21.A.451 are not applicable to standard repairs.

(a) Any natural or legal person that has demonstrated, or is in the process of demonstrating, its capability under point 21.A.432B shall be eligible as an applicant for a major repair design approval under the conditions laid down in this Subpart.

(b) Any natural or legal person shall be eligible to apply for approval of a minor repair design.

(a) An applicant for a major repair design approval shall demonstrate its capability by holding a design organisation approval, issued by the Agency in accordance with Subpart J.

(b) By way of derogation from point (a), as an alternative procedure to demonstrate its capability, an applicant may seek Agency agreement for the use of procedures setting out the specific design practices, resources and sequence of activities necessary to comply with this Subpart.

(c) By way of derogation from points (a) and (b), an applicant may seek the agreement of the Agency for the approval of a certification programme setting out the specific design practices, resources and sequence of activities necessary to comply with this Annex I (Part 21) for a repair on a product defined in point 21.A.14(c).

(a) The applicant for approval of a repair design shall:

(b) Where the applicant is not the type-certificate or supplemental type-certificate or APU ETSO authorisation holder, as applicable, the applicant may comply with the requirements of point (a) through the use of its own resources or through an arrangement with the type-certificate or supplemental type-certificate or APU ETSO authorisation holder as applicable.

(a) A repair may be ‘major’ or ‘minor’. The classification shall be made in accordance with the criteria of point 21.A.91 for a change in the type-certificate.

(b) A repair shall be classified ‘major’ or ‘minor’ under point (a) either:

(a) by the Agency; or

(b) by an appropriately approved organisation that is also the type-certificate, the supplemental type-certificate or APU ETSO authorisation holder, under a procedure agreed with the Agency; or

(c) for minor repairs only, by an appropriately approved design organisation under a procedure agreed with the Agency.

(a) under Subpart F; or

(b) by an organisation appropriately approved in accordance with Subpart G; or

(c) by an appropriately approved maintenance organisation.

(a) The embodiment of a repair shall be made in accordance with Part-M or Part-145 as appropriate, or by a production organisation appropriately approved in accordance with Subpart G, under the point 21.A.163(d) privilege.

(b) The design organisation shall transmit to the organisation performing the repair all the necessary installation instructions.

(a) When a damaged product, part or appliance, is left unrepaired, and is not covered by previously approved data, the evaluation of the damage for its airworthiness consequences may only be made:

Any necessary limitations shall be processed in accordance with the procedures of point 21.A.443.

(b) Where the organisation evaluating the damage under point (a) is neither the Agency nor the type-certificate, supplemental type-certificate or APU ETSO authorisation holder, this organisation shall justify that the information on which the evaluation is based is adequate either from its organisation’s own resources or through an arrangement with the type-certificate, supplemental type-certificate or APU ETSO authorisation holder, or manufacturer, as applicable.

(a) be held by the repair design approval holder at the disposal of the Agency; and

(b) be retained by the repair design approval holder in order to provide the information necessary to ensure the continued airworthiness of the repaired products, parts or appliances.

(a) The holder of the repair design approval shall furnish at least one complete set of those changes to the instructions for continued airworthiness which result from the design of the repair, comprising descriptive data and accomplishment instructions prepared in accordance with the applicable requirements, to each operator of aircraft incorporating the repair. The repaired product, part or appliance may be released into service before the changes to those instructions have been completed, but this shall be for a limited service period, and in agreement with the Agency. Those changes to the instructions shall be made available on request to any other person required to comply with any of the terms of those changes to the instructions. The availability of some manual or portion of the changes to the instructions for continued airworthiness, dealing with overhaul or other forms of heavy maintenance, may be delayed until after the product has entered into service, but shall be available before any of the products reaches the relevant age or flight-hours/cycles.

(b) If updates to those changes to the instructions for continued airworthiness are issued by the holder of the repair design approval after the repair has been first approved, these updates shall be furnished to each operator and shall be made available on request to any other person required to comply with any of the terms of those changes to the instructions. A programme showing how updates to the changes to the instructions for continued airworthiness are distributed shall be submitted to the Agency.

(a) Each holder of a major repair design approval shall:

(b) Except for type-certificate holders or APU authorisation holders for which point 21.A.44 applies, the holder of a minor repair design approval shall:

(a) for production, by holding a production organisation approval, issued in accordance with Subpart G, or through compliance with Subpart F procedures; and

(b) for design:

(a) An application for an ETSO authorisation shall be made in a form and manner established by the Agency and shall include an outline of the information required by point 21.A.605.

(b) When a series of minor changes in accordance with point 21.A.611 is anticipated, the applicant shall set forth in its application the basic model number of the article and the associated part numbers with open brackets after it to denote that suffix change letters or numbers (or combinations of them) will be added from time to time.

(a) points 21.A.15, 21.A.16B, 21.A.17A, 21.A.17B, 21.A.20, 21.A.21, 21.A.31, 21.A.33, 21.A.44 shall apply by way of derogation from points 21.A.603, 21.A.606(c), 21.A.610 and 21.A.615, except that an ETSO Authorisation shall be issued in accordance with 21.A.606 instead of the type-certificate.

(b) subpart D or Subpart E is applicable for the approval of design changes by way of derogation from point 21.A.611. When Subpart E is used, a separate ETSO authorisation shall be issued instead of a supplemental type-certificate.

(c) Subpart M is applicable to the approval of repair designs.

(a) a statement of compliance certifying that the applicant has met the requirements of this Subpart;

(b) a Declaration of Design and Performance (DDP);

(c) one copy of the technical data required in the applicable ETSO;

(d) the exposition (or a reference to the exposition) referred to in point 21.A.143 for the purpose of obtaining an appropriate production organisation approval under Subpart G or the manual (or a reference to the manual) referred to in point 21.A.125A(b) for the purpose of manufacturing under Subpart F without production organisation approval;

(e) for an APU, the handbook (or a reference to the handbook) referred to in point 21.A.243 for the purpose of obtaining an appropriate design organisation approval under Subpart J;

(f) for all other articles, the procedures referred to in point 21.A.602B(b)(2).

(a) demonstrating its capability in accordance with point 21.A.602B; and

(b) demonstrating that the article complies with the technical conditions of the applicable ETSO, and submitting the corresponding statement of compliance;

(c) expressly stating that it is prepared to comply with point 21.A.609.

(a) The DDP shall contain at least the following information:

(b) The DDP shall be endorsed with the date and signature of the holder of the ETSO authorisation, or its authorised representative.

(a) manufacture each article in accordance with Subpart G or Subpart F that ensures that each completed article conforms to its design data and is safe for installation;

(b) prepare and maintain, for each model of each article for which an ETSO authorisation has been issued, a current file of complete technical data and records in accordance with point 21.A.613;

(c) prepare, maintain and update master copies of all manuals required by the applicable airworthiness specifications for the article;

(d) make available to users of the article and to the Agency on request those maintenance, overhaul and repair manuals necessary for the usage and maintenance of the article, and changes to those manuals;

(e) mark each article in accordance with point 21.A.807;

(f) comply with points 21.A.3A, 21.A.3B and 21.A.4;

(g) continue to meet the qualification requirements of point 21.A.602B.

(a) Each manufacturer who requests approval to deviate from any performance standard of an ETSO shall demonstrate that the standards from which a deviation is requested are compensated for by factors or design features providing an equivalent level of safety.

(b) The request for approval to deviate, together with all pertinent data, shall be submitted to the Agency.

(a) The holder of the ETSO authorisation may make minor design changes (any change other than a major change) without further authorisation by the Agency. In this case, the changed article keeps the original model number (part number changes or amendments shall be used to identify minor changes) and the holder shall forward to the Agency any revised data that are necessary for compliance with point 21.A.603(b).

(b) Any design change by the holder of the ETSO authorisation that is extensive enough to require a substantially complete investigation to determine compliance with an ETSO is a major change. Before making such a change, the holder shall assign a new type or model designation to the article and apply for a new authorisation under point 21.A.603.

(c) No design change by any natural or legal person other than the holder of the ETSO authorisation who submitted the statement of compliance for the article is eligible for approval under this Subpart O unless the person seeking the approval applies under point 21.A.603 for a separate ETSO authorisation.

(a) witness any tests;

(b) inspect the technical data files on that article.

(a) An ETSO authorisation shall be issued for an unlimited duration. It shall remain valid unless:

(b) Upon surrender or revocation, the certificate shall be returned to the Agency.

(a) Permits to fly shall be issued in accordance with this Subpart to aircraft that do not meet, or have not been shown to meet, applicable airworthiness requirements but are capable of safe flight under defined conditions and for the following purposes:

(b) This Subpart establishes the procedure for issuing permits to fly and approving associated flight conditions, and establishes the rights and obligations of the applicants for, and holders of, those permits and approvals of flight conditions.

(a) Any natural or legal person shall be eligible as an applicant for a permit to fly except for a permit to fly requested for the purpose of point 21.A.701(a)(15) where the applicant shall be the owner.

(b) Any natural or legal person shall be eligible for application for the approval of the flight conditions.

(a) the authority designated by the Member State of registry; or

(b) for unregistered aircraft, the authority designated by the Member State which prescribed the identification marks.

(a) Pursuant to point 21.A.703 and when the applicant has not been granted the privilege to issue a permit to fly, an application for a permit to fly shall be made to the competent authority in a form and manner established by that authority.

(b) Each application for a permit to fly shall include:

(c) Where the flight conditions are not approved at the time of application for a permit to fly, an application for approval of the flight conditions shall be made in accordance with point 21.A.709.

(a) the configuration(s) for which the permit to fly is requested;

(b) any condition or restriction necessary for safe operation of the aircraft, including:

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(c) the substantiation that the aircraft is capable of safe flight under the conditions or restrictions of point (b);

(d) the method used for the control of the aircraft configuration, in order to remain within the established conditions.

(a) Pursuant to point 21.A.707(c) and when the applicant has not been granted the privilege to approve the flight conditions, an application for approval of the flight conditions shall be made:

(b) Each application for approval of the flight conditions shall include:

(a) When approval of the flight conditions is related to the safety of the design, the flight conditions shall be approved by:

(b) When approval of the flight conditions is not related to the safety of the design, the flight conditions shall be approved by the competent authority, or the appropriately approved organisation that will also issue the permit to fly.

(c) Before approving the flight conditions, the Agency, the competent authority or the approved organisation must be satisfied that the aircraft is capable of safe flight under the specified conditions and restrictions. The Agency or the competent authority may make or require the applicant to make any necessary inspections or tests for that purpose.

(a) A permit to fly (EASA Form 20a, see Appendix III) may be issued by the competent authority under the conditions specified in point 21.B.525.

(b) An appropriately approved design organisation may issue a permit to fly (EASA Form 20b, see Appendix IV) under the privilege granted under point 21.A.263(c)(7), when the flight conditions referred to in point 21.A.708 have been approved in accordance with point 21.A.710.

(c) An appropriately approved production organisation may issue a permit to fly (EASA Form 20b, see Appendix IV) under the privilege granted under point 21.A.163(e), when the flight conditions referred to in point 21.A.708 have been approved in accordance with point 21.A.710.

(d) An appropriately approved continuing airworthiness management organisation may issue a permit to fly (EASA Form 20b, see Appendix IV) under the privilege granted under point M.A.711 of Annex I (Part M) to Commission Regulation (EC) No 2042/2003 ( 4 ), when the flight conditions referred to in point 21.A.708 have been approved in accordance with point 21.A.710.

(e) The permit to fly shall specify the purpose(s) and any conditions and restrictions which have been approved in accordance with point 21.A.710.

(f) For permits issued under points (b), (c) or (d), a copy of the permit to fly and associated flight conditions shall be submitted to the competent authority at the earliest opportunity but not later than 3 days.

(g) Upon evidence that any of the conditions specified in point 21.A.723(a) are not met for a permit to fly that an organisation has issued pursuant to points (b), (c) or (d), that organisation shall immediately revoke that permit to fly and inform without delay the competent authority.

(a) Any change that invalidates the flight conditions or associated substantiation established for the permit to fly shall be approved in accordance with point 21.A.710. When relevant an application shall be made in accordance with point 21.A.709.

(b) A change affecting the content of the permit to fly requires the issuance of a new permit to fly in accordance with point 21.A.711.

(a) A permit to fly is not transferable.

(b) Notwithstanding point (a) for a permit to fly issued for the purpose of point 21.A.701(a)(15), where ownership of an aircraft has changed, the permit to fly shall be transferred together with the aircraft provided the aircraft remains on the same register, or issued only with the agreement of the competent authority of the Member State of registry to which it is transferred.

(a) A permit to fly shall be issued for a maximum of 12 months and shall remain valid subject to:

(b) Notwithstanding point (a), a permit to fly issued for the purpose of point 21.A.701(a)(15) may be issued for unlimited duration.

(c) Upon surrender or revocation, the permit to fly shall be returned to the competent authority.

(a) All documents produced to establish and justify the flight conditions shall be held by the holder of the approval of the flight conditions at the disposal of the Agency and competent authority and shall be retained in order to provide the information necessary to ensure the continued airworthiness of the aircraft.

(b) All documents associated with the issue of permits to fly under the privilege of approved organisations, including inspection records, documents supporting the approval of flight conditions and the permit to fly itself, shall be held by the related approved organisation at the disposal of the Agency or the competent authority and shall be retained in order to provide the information necessary to ensure the continued airworthiness of the aircraft.

(a) The identification of products shall include the following information:

(b) Any natural or legal person that manufactures an aircraft or engine under Subpart G or Subpart F shall identify that aircraft or engine by means of a fireproof plate that has the information specified in point (a) marked on it by etching, stamping, engraving, or other approved method of fireproof marking. The identification plate shall be secured in such a manner that it is accessible and legible, and will not likely be defaced or removed during normal service, or lost or destroyed in an accident.

(c) Any natural or legal person that manufactures a propeller, propeller blade, or propeller hub under Subpart G or Subpart F shall identify it by means of a plate, stamping, engraving, etching or other approved method of fireproof identification that is placed on it on a non-critical surface, contains the information specified in point (a), and will not likely be defaced or removed during normal service or lost or destroyed in an accident.

(d) For manned balloons, the identification plate prescribed in point (b) shall be secured to the balloon envelope and shall be located, if practicable, where it is legible to the operator when the balloon is inflated. In addition, the basket, load frame assembly and any heater assembly shall be permanently and legibly marked with the manufacturer’s name, part number, or equivalent, and serial number, or equivalent.

(a) No person shall remove, change, or place identification information referred to in point 21.A.801(a) on any aircraft, engine, propeller, propeller blade, or propeller hub, or in point 21.A.807(a) on an APU, without the approval of the Agency.

(b) No person shall remove or install any identification plate referred to in point 21.A.801, or in point 21.A.807 for an APU, without the approval of the Agency.

(c) By way of derogation from points (a) and (b), any natural or legal person performing maintenance work under the applicable associated implementing rules may, in accordance with methods, techniques and practices established by the Agency:

(d) No person shall install an identification plate removed in accordance with point (c)(2) on any aircraft, engine, propeller, propeller blade, or propeller hub other than the one from which it was removed.

(a) Each part or appliance shall be marked permanently and legibly with:

(b) By way of derogation from point (a), if the Agency agrees that a part or appliance is too small or that it is otherwise impractical to mark a part or appliance with any of the information required by point (a), the authorised release document accompanying the part or appliance or its container shall include the information that could not be marked on the part.

(a) Each holder of an ETSO authorisation under Subpart O shall permanently and legibly mark each article with the following information:

(b) By way of derogation from point (a), if the Agency agrees that a part is too small or that it is otherwise impractical to mark a part with any of the information required by point (a), the authorised release document accompanying the part or its container shall include the information that could not be marked on the part.

(c) Each person who manufactures an APU under Subpart G or Subpart F shall identify that APU by means of a fireproof plate that has the information specified in point (a) marked on it by etching, stamping, engraving, or other approved method of fireproof marking. The identification plate shall be secured in such a manner that it is accessible and legible, and will not likely be defaced or removed during normal service, or lost or destroyed in an accident.

(a) This Section establishes the procedure for the competent authority of the Member State when exercising its tasks and responsibilities concerned with the issuance, maintenance, amendment, suspension and revocation of certificates, approvals and authorisations referred to in this Annex I (Part 21).

(b) The Agency shall develop in accordance with Article 19 of Regulation (EC) No 216/2008 certification specifications and guidance material to assist Member States in the implementation of this Section.

(a) General:

The Member State shall designate a competent authority with allocated responsibilities for the implementation of Section A, Subparts F, G, H, I and P with documented procedures, organisation structure and staff.

(b) Resources:

(c) Qualification and training:

All staff shall be appropriately qualified and have sufficient knowledge, experience and training to perform their allocated task.

(a) The competent authority of the Member State shall establish documented procedures to describe its organisation, means and methods to fulfil the requirements of this Annex I (Part 21). The procedures shall be kept up to date and serve as the basic working documents within that authority for all related activities.

(b) A copy of the procedures and their amendments shall be available to the Agency.

(a) The competent authority of the Member State shall notify any significant change in its organisation and documented procedures to the Agency.

(b) The competent authority of the Member State shall update its documented procedures relating to any change to regulations in a timely manner to ensure effective implementation.

(a) The competent authority of the Member State shall establish a process for the resolution of disputes within its organisation documented procedures.

(b) Where a dispute, which cannot be resolved, exists between the competent authorities of the Member States it is the responsibility of the managers as defined in point 21.B.25(b)(2) to raise the issue with the Agency for mediation.

(a) The competent authority of the Member State shall ensure coordination as applicable with other related certification, investigation, approval or authorisation teams of that authority, other Member States and the Agency to ensure efficient exchange of information relevant for safety of the products, parts and appliances.

(b) The competent authority of the Member State shall notify any difficulty in the implementation of this Annex I (Part 21) to the Agency.

(a) The competent authority shall appoint an investigation team for each applicant for, or holder of, a letter of agreement to conduct all relevant tasks related to this letter of agreement, consisting of a team-leader to manage and lead the investigation team and, if required, one or more team members. The team-leader shall report to the manager responsible for the activity, as defined in point 21.B.25 (b)(2).

(b) The competent authority shall perform sufficient investigation activities for an applicant for, or holder of, a letter of agreement to justify recommendations for the issuance, maintenance, amendment, suspension or revocation of the letter of agreement.

(c) The competent authority shall prepare procedures for the investigation of applicants for, or holders of, a letter of agreement as part of the documented procedures covering at least the following elements:

(a) When during audits or by other means objective evidence is found by the competent authority, showing non-compliance of the holder of a letter of agreement with the applicable requirements of Section A of this Annex, this finding shall be classified in accordance with point 21.A.125B(a).

(b) The competent authority shall take the following actions:

(c) Action shall be taken by the competent authority to suspend the letter of agreement in whole or in part in case of failure to comply within the timescale granted by the competent authority.

(a) When satisfied that the manufacturer is in compliance with the applicable requirements of Section A, Subpart F, the competent authority shall issue a letter of agreement to the showing of conformity of individual products, parts or appliances (EASA Form 65, see Appendix XI) without undue delay.

(b) The letter of agreement shall contain the scope of the agreement, a termination date and, where applicable, the appropriate limitations relating to the authorisation.

(c) The duration of the letter of agreement shall not exceed one year.

(a) the manufacturer is properly using the EASA Form 52 (see Appendix VIII) as a statement of conformity for complete aircraft, and the EASA Form 1 (see Appendix I) for products other than complete aircraft, parts and appliances; and

(b) inspections performed by the competent authority of the Member State before validation of the EASA Form 52 (see Appendix VIII) or the EASA Form 1 (see Appendix I), as per point 21.A.130(c) did not reveal any findings of non-compliance with the requirements or the procedures as contained in the manual provided by the manufacturer, or any non-conformity of the respective products, parts or appliances. These inspections shall check at least that:

(c) any termination date for the letter of agreement has not been reached.

(a) The competent authority shall investigate, as appropriate, in accordance with point 21.B.120 any amendment of the letter of agreement.

(b) When the competent authority is satisfied that the requirements of Section A, Subpart F continue to be complied with, it shall amend the letter of agreement accordingly.

(a) The limitation, suspension or revocation of the letter of agreement shall be communicated in writing to the holder of the letter of agreement. The competent authority shall state the reasons for the limitation, suspension or revocation and inform the holder of the letter of agreement on its right to appeal.

(b) When a letter of agreement has been suspended it shall only be reinstated after compliance with Section A Subpart F has been re-established.

(a) The competent authority shall establish a system of record-keeping that allows adequate traceability of the process to issue, maintain, amend, suspend or revoke each individual letter of agreement.

(b) The records shall at least contain:

(c) The records shall be archived for a minimum retention period of six years after termination of the letter of agreement.

(d) The competent authority shall also maintain records of all Statements of Conformity (EASA Form 52, see Appendix VIII) and Authorised Release Certificates (EASA Form 1, see Appendix I) that it has validated.

(a) The competent authority shall appoint a production organisation approval team for each applicant, or holder of, a production organisation approval to conduct all relevant tasks related to this production organisation approval, consisting of a team leader to manage and lead the approval team and, if required, one or more team members. The team leader shall report to the manager responsible for the activity as defined in point 21.B.25(b)(2).

(b) The competent authority shall perform sufficient investigation activities for an applicant for, or holder of, a production organisation approval to justify recommendations for the issuance, maintenance, amendment, suspension or revocation of the approval.

(c) The competent authority shall prepare procedures for the investigation of a production organisation approval as part of the documented procedures covering at least the following elements:

(a) When during audits or by other means objective evidence is found by the competent authority, showing non-compliance of the holder of a production organisation approval with the applicable requirements of Section A, this finding shall be classified in accordance with point 21.A.158(a).

(b) The competent authority shall take the following actions:

(c) Action shall be taken by the competent authority to suspend the approval in whole or in part in case of failure to comply within the timescale granted by the competent authority.

(a) When satisfied that the production organisation is in compliance with the applicable requirements of Section A, Subpart G, the competent authority shall issue a Production Organisation Approval (EASA Form 55, see Appendix X) without undue delay.

(b) The reference number shall be included on the EASA Form 55 in a manner specified by the Agency.

(a) In order to justify the maintenance of the production organisation approval the competent authority shall perform continued surveillance:

(b) Continued surveillance shall be performed in accordance with point 21.B.220.

(c) The competent authority shall provide through planned continued surveillance that a production organisation approval is completely reviewed for compliance with this Annex I (Part 21) during a period of 24 months. The continued surveillance may be made up of several investigation activities during this period. The number of audits may vary depending upon the complexity of the organisation, the number of sites and the criticality of the production. As a minimum the holder of a production organisation approval shall be subject to continued surveillance activity by the competent authority at least once every year.

(a) The competent authority shall monitor any minor change through the continued surveillance activities.

(b) The competent authority shall investigate as appropriate in accordance with point 21.B.220 any significant change of a production organisation approval or application by the holder of a production organisation approval for an amendment of the scope and terms of approval.

(c) When the competent authority is satisfied that the requirements of Section A, Subpart G continue to be complied with it shall amend the production organisation approval accordingly.

(a) In case of a level one or level two finding, the competent authority shall partly or fully limit, suspend or revoke a production organisation approval as follows:

(b) The limitation, suspension or revocation of the production organisation approval shall be communicated in writing to the holder of the production organisation approval. The competent authority shall state the reasons for the suspension or revocation and inform the holder of the production organisation approval of its right to appeal.

(c) When a production organisation approval has been suspended it shall only be reinstated after compliance with Section A, Subpart G has been re-established.

(a) The competent authority shall establish a system of record-keeping that allows adequate traceability of the process to issue, maintain, amend, suspend or revoke each individual production organisation approval.

(b) The records shall at least contain:

(c) The records shall be archived for a minimum retention period of six years.

(a) The competent authority of the Member State of registry shall perform sufficient investigation activities for an applicant for, or holder of, an airworthiness certificate to justify the issuance, maintenance, amendment, suspension or revocation of the certificate or permit.

(b) The competent authority of the Member State of registry shall prepare evaluation procedures covering at least the following elements:

(a) The competent authority of the Member State of registry shall issue or change a certificate of airworthiness (EASA Form 25, see Appendix VI) without undue delay when it is satisfied that the requirements of point 21.B.326 and the applicable requirements of Section A of Subpart H of this Annex I (Part 21) are met.

(b) The competent authority of the Member State of registry shall issue or change a Restricted certificate of airworthiness (EASA Form 24, see Appendix V) without undue delay when it is satisfied that requirements of point 21.B.327 and the applicable requirements of Section A of Subpart H of this Annex I (Part 21) are met.

(c) For a new aircraft or used aircraft originating from a non-member State, in addition to the appropriate airworthiness certificate referred to in point (a) or (b), the competent authority of the Member State of registry shall issue an initial airworthiness review certificate (EASA Form 15a, see Appendix II).

(a) new aircraft:

(b) used aircraft:

(a) The competent authority of the Member State of registry shall issue a restricted certificate of airworthiness for:

(b) For an aircraft that cannot comply with the essential requirements referred to in Regulation (EC) No 216/2008 and which is not eligible for a restricted type-certificate, the Agency shall, as necessary to take account of deviations from these essential requirements:

(c) Limitations for use will be associated with restricted certificates of airworthiness, including airspace restrictions, as necessary to take account of deviations from essential requirements for airworthiness laid down in Regulation (EC) No 216/2008.

(a) Upon evidence that any of the conditions specified in point 21.A.181(a) is not met, the competent authority of the Member State of registry shall suspend or revoke an airworthiness certificate.

(b) Upon issuance of the notice of suspension and revocation of a certificate of airworthiness or restricted certificate of airworthiness the competent authority of the Member State of registry shall state the reasons for the suspension or revocation and inform the holder of the certificate of its right to appeal.

(a) The competent authority of the Member State of registry shall establish a system of record-keeping that allows adequate traceability of the process to issue, maintain, amend, suspend or revoke each individual airworthiness certificate.

(b) The records shall at least contain:

(c) The records shall be archived for a minimum retention period of six years after leaving that national register.

(a) The competent authority of the Member State of registry shall perform sufficient investigation activities for an applicant for, or holder of, a noise certificate to justify the issuance, maintenance, amendment, suspension or revocation of the certificate.

(b) The competent authority of the Member State of registry shall prepare evaluation procedures as part of the documented procedures covering at least the following elements:

(a) Upon evidence that some of the conditions specified in point 21.A.211(a) are not met, the competent authority of the Member State of registry shall suspend or revoke a noise certificate.

(b) Upon issuance of the notice of suspension and revocation of a noise certificate the competent authority of the Member State of registry shall state the reasons for the suspension and revocation and shall inform the holder of the certificate on its right to appeal.

(a) The competent authority of the Member State of registry shall establish a system of record-keeping with minimum retention criteria that allows adequate traceability of the process to issue, maintain, amend, suspend or revoke each individual noise certificate.

(b) The records shall at least contain:

(c) The records shall be archived for a minimum retention period of six years after leaving that national register.

(a) The competent authority shall perform sufficient investigation activities to justify the issuance, or revocation of the permit to fly.

(b) The competent authority shall prepare evaluation procedures covering at least the following elements:

(a) upon presentation of the data required by point 21.A.707; and

(b) when the flight conditions referred to in point 21.A.708 have been approved in accordance with point 21.A.710; and

(c) when the competent authority, through its own investigations, which may include inspections, or through procedures agreed with the applicant, is satisfied that the aircraft conforms to the design defined under point 21.A.708 before flight.

(a) Upon evidence that any of the conditions specified in point 21.A.723(a) are not met for a permit to fly it has issued, the competent authority shall revoke that permit to fly.

(b) Upon issuance of the notice of revocation of a permit to fly the competent authority shall state the reasons for the revocation and inform the holder of the permit to fly on the right to appeal.

(a) The competent authority shall operate a system of record-keeping that provides adequate traceability of the process for the issue and revocation of each individual permit to fly.

(b) The records shall at least contain:

(c) The records shall be kept for a minimum of six years after the permit ceases to be valid.

1.1. A primary purpose of the certificate is to declare the airworthiness of new aviation products, parts and appliances (‘the item(s)’).

1.2. Correlation must be established between the certificate and the item(s). The originator must retain a certificate in a form that allows verification of the original data.

1.3. The certificate is acceptable to many airworthiness authorities, but may be dependent on bilateral agreements and/or the policy of the airworthiness authority.

1.4. The certificate is not a delivery or shipping note.

1.5. Aircraft are not to be released using the certificate.

1.6. The certificate does not constitute approval to install the item on a particular aircraft, engine, or propeller but helps the end user determine its airworthiness approval status.

1.7. A mixture of production released and maintenance released items is not permitted on the same certificate.

1.8. A mixture of items certified in conformity with ‘approved data’ and to ‘non-approved data’ is not permitted on the same certificate.

2.1. The certificate must comply with the format attached including block numbers and the location of each block. The size of each block may however be varied to suit the individual application, but not to the extent that would make the certificate unrecognisable.

2.2. The certificate must be in ‘landscape’ format but the overall size may be significantly increased or decreased so long as the certificate remains recognisable and legible. If in doubt consult the competent authority.

2.3. The User/Installer responsibility statement can be placed on either side of the form.

2.4. All printing must be clear and legible to permit easy reading.

2.5. The certificate may either be pre-printed or computer generated but in either case the printing of lines and characters must be clear and legible and in accordance with the defined format.

2.6. The certificate should be in English, and if appropriate, in one or more other languages.

2.7. The details to be entered on the certificate may be either machine/computer printed or hand-written using block letters and must permit easy reading.

2.8. Limit the use of abbreviations to a minimum, to aid clarity.

2.9. The space remaining on the reverse side of the certificate may be used by the originator for any additional information but must not include any certification statement. Any use of the reverse side of the certificate must be referenced in the appropriate block on the front side of the certificate.

3.1. There is no restriction in the number of copies of the certificate sent to the customer or retained by the originator.

4.1. If an end-user finds an error(s) on a certificate, he must identify it/them in writing to the originator. The originator may issue a new certificate if they can verify and correct the error(s).

4.2. The new certificate must have a new tracking number, signature and date.

4.3. The request for a new certificate may be honoured without re-verification of the item(s) condition. The new certificate is not a statement of current condition and should refer to the previous certificate in block 12 by the following statement: ‘This certificate corrects the error(s) in block(s) [enter block(s) corrected] of the certificate [enter original tracking number] dated [enter original issuance date] and does not cover conformity/condition/release to service’. Both certificates should be retained according to the retention period associated with the first.

(i) the production of a new item in conformity with non-approved design data;

(ii) re-certification by the organisation identified in block 4 of the previous certificate after alteration or rectification work on an item, prior to entry into service, (e.g. after incorporation of a design change, correction of a defect, inspection or test, or renewal of shelf-life.) Details of the original release and the alteration or rectification work are to be entered in block 12.

(i) the production of a new item in conformity with the approved design data;

(ii) re-certification by the organisation identified in block 4 of the previous certificate after alteration or rectification work on an item, prior to entry into service, (e.g. after incorporation of a design change, correction of a defect, inspection or test, or renewal of shelf-life.) Details of the original release and the alteration or rectification work are to be entered in block 12;

(iii) re-certification by the product manufacturer or the organisation identified in block 4 of the previous certificate of items from ‘prototype’ (conformity only to non-approved data) to ‘new’ (conformity to approved data and in a condition for safe operation), subsequent to approval of the applicable design data, provided that the design data has not changed. The following statement must be entered in block 12:

‘RE-CERTIFICATION OF ITEMS FROM ‘PROTOTYPE’ TO ‘NEW’: THIS DOCUMENT CERTIFIES THE APPROVAL OF THE DESIGN DATA [INSERT TC/STC NUMBER, REVISION LEVEL], DATED [INSERT DATE IF NECESSARY FOR IDENTIFICATION OF REVISION STATUS], TO WHICH THIS ITEM (THESE ITEMS) WAS (WERE) MANUFACTURED.’

The box ‘approved design data and are in a condition for safe operation’ should be marked in block 13a;

(iv) the examination of a previously released new item prior to entry into service in accordance with a customer-specified standard or specification (details of which and of the original release are to be entered in block 12) or to establish airworthiness (an explanation of the basis of release and details of the original release are to be entered in block 12).

1. Mark the ‘approved design data and are in a condition for safe operation’ box if the item(s) was/were manufactured using approved design data and found to be in a condition for safe operation.

2. Mark the ‘non-approved design data specified in block 12’ box if the item(s) was/were manufactured using applicable non-approved design data. Identify the data in block 12 (e.g. pending type-certificate, for test only, pending approved data).

Mixtures of items released against approved and non-approved design data are not permitted on the same certificate.

1.1. Use of the aircraft Statement of Conformity issued by a manufacturer producing under Part 21 Section A Subpart F is described under point 21.A.130 and the corresponding acceptable means of compliance.

1.2. The purpose of the aircraft Statement of Conformity (EASA Form 52) issued under Part 21 Section A Subpart G is to enable the holder of an appropriate production organisation approval to exercise the privilege to obtain an individual aircraft certificate of airworthiness from the competent authority of the Member State of registry.

2.1. The Statement of Conformity must comply with the format attached including block numbers and the location of each block. The size of each block may however be varied to suit the individual application, but not to the extent that would make the Statement of Conformity unrecognisable. If in doubt consult the competent authority.

2.2. The Statement of Conformity must either be pre-printed or computer generated but in either case the printing of lines and characters must be clear and legible. Pre-printed wording is permitted in accordance with the attached model but no other certification statements are permitted.

2.3. Completion may be either machine/computer printed or hand-written using block letters to permit easy reading. English, and where relevant, one or more of the official language(s) of the issuing Member State are acceptable.

2.4. A copy of the Statement and all referenced attachments are to be retained by the approved production organisation.

3.1. There should be an entry in all blocks to make the document a valid statement.

3.2. A Statement of Conformity may not be issued to the competent authority of the Member State of registry unless the design of the aircraft and its installed products are approved.

3.3. The information required in blocks 9, 10, 11, 12, 13 and 14 may be by reference to separate identified documents held on file by the production organisation, unless the competent authority agrees otherwise.

3.4. This Statement of Conformity is not intended to include those items of equipment that may be required to be fitted in order to satisfy applicable operational rules. However, some of these individual items may be included in block 10 or in the approved type design. Operators are therefore reminded of their responsibility to ensure compliance with the applicable operational rules for their own particular operation.

1. ‘Flight test engineer’ means any engineer involved in flight test operations either on the ground or in flight.

2. ‘Lead flight test engineer’ means a flight test engineer assigned for duties in an aircraft for the purpose of conducting flight tests or assisting the pilot in the operation of the aircraft and its systems during flight test activities.

3. ‘Flight tests’ mean:

3.1. Category One (1)

3.2. Category Two (2)

3.3. Category Three (3)

Flights performed for the issuance of statement of conformity for a new-built aircraft which do not require flying outside of the limitations of the type certificate or the aircraft flight manual.

3.4. Category Four (4)

Flights not classified as Category 1 or 2 on an aircraft of an already certified type, in case of an embodiment of a not yet approved design change.