text: OF THE EXECUTIVE DIRECTOR OF THE EUROPEAN AVIATION SAFETY AGENCY

text: OJ L 79, 19.03.2008, p. 1. OJ L 243, 27.9.2003, p. 6. Regulation as last amended by

text: Regulation (EC) No 1194/2009 of 30 November 2009

text: (OJ L 321, 8.12.2009, p. 5).

text: R.F012-02 © European Aviation Safety Agency, 2010. All rights reserved. Proprietary document. Page 1 of 20

text: Commission Regulation (EC) No 1194/2009 of 30 November 2009

text: amending

text: Regulation (EC) No 1702/2003

text: laying down implementing rules for the airworthiness and environmental certification of aircraft and related products, parts and appliances as well as for certification of design and production organisations (OJ L 321, 8.12.2009, p. 5). Management Board Decision concerning the procedure to be applied by the Agency for the issuing of opinions, certification specifications and guidance material (Rulemaking Procedure), EASA MB/08/07, 13.6.2007. See NPA 12/2004 & CRD 12/2004, NPA 2007-06 & CRD 2007-06 and NPA 2007-13 & CRD 2007-13 available at http://www.easa.europa.eu/ws_prod/r/r_archives.php.

identifier: AMC & GM to Part 21 — Issue 1, Amendment 6

beslut: ED Decision 2010/001/R

title: AMC & GM to Part 21 — Issue 1, Amendment 6

text: ED Decision 2010/001/R 23/03/2010

text: European Aviation Safety Agency

text: DECISION N 2010/001/R

text: OF 23 MARCH 2010

text: Amending the Annex to Decision No. 2003/01/RM of the Executive Director of the Agency of 17 October 2003 on acceptable means of compliance and guidance material for the airworthiness and environmental certification of aircraft and related products, parts and appliances, as well as for the certification of design and production organisations (‘AMC and GM to Part-21’)

text: ‘Miscellaneous Part-21’,

text: ‘Permit to Fly for Continuing Airworthiness Management Organisation and Approved Maintenance Organisations’

text: and

text: ‘Authorised Release Certificate EASA Form 1’

text: THE EXECUTIVE DIRECTOR OF THE EUROPEAN AVIATION SAFETY AGENCY, Having regard to the

text: Regulation (EC) No 216/2008

text: of the European Parliament and of the Council of 20 February 2008 on common rules in the field of civil aviation and establishing a European Aviation Safety Agency, and repealing

text: Council Directive 91/670/EEC

text: Regulation (EC) No 1592/2002

text: and Directive

text: (hereinafter ‘The Basic Regulation’), and in particular

text: Articles 18

text: ED Decision 2010/001/R 23/03/2010 (2) An amendment to the

text: is introduced by

text: . This amending regulation introduces new and amended rules related to the issuance of permits to fly, the definition of principal place of business and the authorised release certificate and it also contains miscellaneous improvements. (3) It is necessary to support the above amendment to

text: Commission Regulation (EC) 1702/2003

text: by amended and new AMCs and GM. The Decision No 2003/1/RM of 17 October 2003 on acceptable means of compliance and guidance material for the airworthiness and environmental certification of aircraft and related products, parts and appliances, as well as for the certification of design and production organisations (‘AMC and GM to Part-21’) shall therefore be amended. (4) The Agency, pursuant to

text: Article 52(1)

text: (c) of the Basic Regulation and articles 5(3) and 6 of the Rulemaking Procedure , has widely consulted interested parties on the matters that are subject of this Decision and has provided thereafter a written response to the comments received . (5) During the adoption process of the Agency Opinion 06-2008, the European Commission did not retain the examples of conditions that would necessitate statements in block 12 ‘Remarks’ of the ‘Authorised Release Certificate EASA Form 1’ in the completion instructions of that Form. These examples are therefore introduced in amended Acceptable Means of Compliance in the Annex to this decision.

text: HAS DECIDED:

text: Article 1

text: The Annex ‘Acceptable means of compliance and guidance material to be used in the airworthiness certification of products, parts and appliances and the approval of organisations involved in their design or manufacture’ to Decision ED/2003/01/RM of the Executive Director of the Agency of 17 October 2003 is hereby amended as provided in Annex 1 to this decision.

text: Article 2

text: This decision shall enter into force on 30 March. It shall be published in the Official Publication of the Agency.

text: Done in Cologne, on 23 March 2010.

text: P. GOUDOU

text: ED Decision 2010/001/R 23/03/2010 Annex 1 to ED Decision 2010/001/R

text: The Annex ‘Acceptable Means of Compliance and Guidance Material to be used in the airworthiness certification of products, parts and appliances and the approval of organisations involved in their design or manufacture’ to Decision ED/2003/01/RM of the Executive Director of the Agency of 17 October 2003 is hereby amended as follows: The text of amendments is arranged to show deleted text or new text as shown below:

text: 1. Text to be deleted is shown with a line through it.

text: 2. New text to be inserted is highlighted with grey shading.

text: 3. … Indicates that remaining text is unchanged in front of or following the reflected amendment.

text: The GM 21A.101 is amended as follows:

text: GM 21A.101 Establishment of the type-certification basis of Changed Aeronautical Products

text: 4. EXPLANATION OF TERMINOLOGY

text: The following is a summary of the terminology used throughout this advisory or guidance material. Further explanations of some of these terms can be found in paragraphs 5, 6, 7, and 8. a. Type-certification basis: the applicable airworthiness codes as established in 21A.17 and 21A.101, as appropriate, special conditions, equivalent level of safety findings; and exemptions deviations applicable to the product to be certificated. Note: This GM is not intended for determining the applicable aircraft noise, fuel venting and engine emissions environmental protection requirements for changed products.

text: The AMC 3 to 21A.129(c) is amended as follows:

text: AMC 3 to 21A.129(c)

text: AMC No 3 to 21A.129(c) Obligations of the manufacturer – Condition for safe operation

text: …. 3 Technical records which identify the location and serial numbers of significant components that have traceability requirements for continued airworthiness purposes including those identified in 21A.801 and 21A.805. …. 17 16 The installed compass and/or compass systems have been adjusted and compensated and a deviation card displayed in the aircraft. 18 17 Software criticality list. 19 18 A record of rigging and control surface movement measurements. 20 19 Details of installations which will be removed before starting commercial air transport operations (e.g., ferry kits for fuel, radio or navigation). 21 20 List of all applicable Service Bulletins and airworthiness directives that have been implemented.

text: ED Decision 2010/001/R 23/03/2010 The AMC No 2 to 21A.130(b) is replaced by the following.

text: AMC No 2 to 21A.130(b) Statement of Conformity for Products (other than complete aircraft), parts and/or appliances – The Authorised Release Certificate (EASA Form 1)

text: A. INTRODUCTION This AMC relates specifically to the use of the EASA Form 1 for manufacturing purposes under Part-21 Subpart F. It can be used as a supplement to the completion instructions in Part-21, Appendix I which covers the use of the EASA Form 1. 1. PURPOSE AND USE The EASA Form 1 is prepared and signed by the manufacturer. For production under Part-21 Subpart F it is presented for validation by the competent authority. Under Subpart F the Certificate may only be issued by the competent authority. A mixture of items released under Subpart G and under Subpart F of Part-21 is not permitted on the same certificate. 2. GENERAL FORMAT Refer to Part-21 Appendix I. 3. COPIES Refer to Part-21 Appendix I. The Part-21 Subpart F originator must retain a copy of the certificate in a form that allows verification of original data. 4. ERROR(S) ON THE CERTIFICATE If an end user finds an error(s) on a certificate, they must identify it/them in writing to the originator. The originator may prepare and sign a new certificate for validation by the competent authority if they can verify and correct the error(s). The new certificate must have a new tracking number, signature and date. The request for a new certificate may be honoured without reverification 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.

text: 5. COMPLETION OF THE CERTIFICATE BY THE ORIGINATOR Refer to Part-21 Appendix I for completion of the certificate. Specific Part-21 Subpart F instructions that differ from the Part-21 Appendix I are provided below. Block 1 – Approving Competent Authority/Country State the name and country of the competent authority under whose jurisdiction this certificate is issued. When the competent authority is the Agency, ‘EASA’ must be stated. Block 12 – Remarks Examples of conditions which would necessitate statements in block 12 are:  When the certificate is used for prototype purposes, the following statement must be entered at the beginning of block 12:

text: ED Decision 2010/001/R 23/03/2010 ‘NOT ELIGIBLE FOR INSTALLATION ON IN-SERVICE TYPE-CERTIFICATED AIRCRAFT’.  Re-certification of items from ‘prototype’ (conformity only to non-approved data) to ‘new’ (conformity to approved data and in a condition for safe operation) once the applicable design data is approved. 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.  When a new certificate is issued to correct error(s), the following statement must be entered in block 12: ‘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’. Additionally, for production under Subpart F, this block must include the Statement of Conformity by the manufacturer under 21A.130. For this purpose, the appropriate Block 13a statement must be included in the block 12 and not referenced in a separate document. The statement may be pre-printed, computer generated or stamped, and must be followed by the signature of the manufacturer’s authorised person under 21A.130(a), the name and the position/identification of such person and the date of the signature. Block 13b – Authorised Signature This space shall be completed with the signature of the competent authority representative validating the block 12 manufacturer Statement of Conformity, under 21A.130(d). To aid recognition, a unique number identifying the representative may be added. Block 13c – Approval/Authorisation Number Enter the authorisation number reference. This number or reference is given by the competent authority to the manufacturer working under Part-21 Subpart F.

text: The AMC No 2 to 21A.133(b) and (c) is amended as follows:

text: AMC No 2 to 21A.133(b) and (c) Eligibility – Link between design and production organisations

text: … Arrangement Sample Form

text: ARRANGEMENT i.a.w. 21A.133(b) and (c)

text: The undersigned agree on the following commitments: relevant interface procedures

text: The design organisation [NAME] takes responsibility to: assure correct and timely transfer of up-to-date applicable design data (e.g. drawings, material specifications, dimensional data, processes, surface treatments, shipping conditions, quality requirements, etc.) to the production organisation approval holder [NAME],

text: ED Decision 2010/001/R 23/03/2010

text: provide visible statement(s) of approved design data.

text: The production organisation approval holder [NAME] takes responsibility to: assist the design organisation [Name] in dealing with continuing airworthiness matter and for required actions, assist the design organisation [Name] in case of products prior to type certification in showing compliance with airworthiness requirements, develop, where applicable, its own manufacturing data in compliance with the airworthiness data package.

text: The design organisation [Name] and the POA holder [Name] take joint responsibility to: deal adequately with production deviations and non conforming parts in accordance with the applicable procedures of the design organisation and the production organisation approval holder, achieve adequate configuration control of manufactured parts, to enable the POA holder to make the final determination and identification for conformity or airworthiness release and eligibility status.

text: The scope of production covered by this arrangement is detailed in ... [DOCUMENT REFERENCE/ ATTACHED LIST]

text: [When the design organisation is not the same legal entity as the production organisation approval holder]

text: Transfer of approved design data The TC/STC/ETSO holder [NAME] acknowledges that the approved design data provided, controlled and modified in accordance with the arrangement are recognised as approved by the primary certification Competent Aauthority and therefore the parts and appliances manufactured in accordance with these data and found in a condition for safe operation may be released certifying airworthiness that the item was manufactured in conformity to approved design data and is in a condition for safe operation.

text: Direct Delivery Authorisation This acknowledgment includes also [OR does not include] the general agreement for direct delivery to end users in order to guarantee continued airworthiness control of the released parts and appliances. for the [NAME of the design organisation/DOA for the [NAME of the POA holder] holder]

text: date signature date signature

text: xx.xx.xxxx xx.xx.xxxx ([NAME in block letters]) ([NAME in block letters])

text: ED Decision 2010/001/R 23/03/2010

text: The GM 21A.145(c)(2) is amended as follows:

text: GM 21A.145(c)(2) Approval Requirements – Responsible managers

text: … The competent authority requires the nominated managers to be identified and their credentials submitted on an EASA Form Four 4 (see format in EASA administrative procedures acceptable means of compliance and guidance material to Annex 1 to

text: Commission Regulation (EC) No 2042/2003

text: , Appendix X EASA Form 4) to the competent authority in order that they may be seen to be appropriate in terms of relevant knowledge and satisfactory experience related to the nature of the production activities as performed by the Part-21 Section A Subpart G organisation. …

text: The GM 21A.151 is amended as follows:

text: GM 21A.151 Terms of approval – Scope and categories

text: … B1 Turbine Engines B2 Piston Engies Engines B3 APU’s B4 Propellers …

text: The AMC 21A.163(c) is amended as follows:

text: AMC No 1 to 21A.163(c) Computer generated signature and electronic exchange of the EASA Form 1

text: 1. Submission to the competent authority

text: Any POA holder/applicant intending to implement an electronic computer generated signature procedure to issue EASA Form 1 and/or to exchange electronically such data contained on the EASA Form 1, must should document it and submit it to the competent authority as part of the documents attached with its exposition and dealing with the issue of airworthiness certifications.

text: 2. Characteristics of the computer generated signature system electronic system generating the EASA Form 1

text: The electronic system must should: — guarantee secure access for each certifying staff; — insure ensure integrity and accuracy of the data certified by the signature of the Form and be able to show evidence of the authenticity of the EASA Form 1 (recording and record keeping) with suitable security, safeguards and backups; — be active only at the location where the part is being released with an EASA Form 1; — not permit to sign a blank form; — not permit modification provide a high degree of assurance that the data has not been modified after signature (if modification is necessary after issuance, i.e. re-certification of a part), a new form with a new number and reference to the initial certification issuance should be made); - insure integrity of the data certified by the signature of the Form and be able to show evidence of the authenticity of the EASA Form 1(recording and record keeping) — provide for a ‘personal’ electronic signature, identifying the signatory. The signature should be generated only in the presence of the signatory.

text: ED Decision 2010/001/R 23/03/2010

text: An electronic signature means data in electronic form which are attached to or logically associated with other electronic data and which serve as a method of authentication and should meet the following criteria:  it is uniquely linked to the signatory;  it is capable of identifying the signatory;  it is created using means that the signatory can maintain under their sole control. The electronic signature is defined as an electronically generated value based on a cryptographic algorithm and appended to data in a way to enable the verification of the data’s source and integrity. POA holders/applicants are reminded that additional national and/or European requirements may need to be satisfied when operating computer generated signature electronic systems. ‘Directive

text: of the European Parliament and of the Council of 13 December 1999 on a Community framework for electronic signatures’, as last amended may constitute a reference. The electronic system should be based on a policy and management structure (confidentiality, integrity and availability), such as:  administrators, signatories;  scope of authorisation, rights;  password and secure access, authentication, protections, confidentiality;  track changes;  minimum blocks to be completed, completeness of information;  archives;  etc. The electronic system generating the EASA Form 1 may contain additional data such as:  manufacturer code;  customer identification code;  workshop report;  inspection results;  etc.

text: 3. Characteristics of the computer generated signature EASA Form 1 generated from the electronic system

text: The computer generated signature must to take the form of a representation of the hand-written signature of the person signing (i.e. scanned signature).In addition to facilitate understanding and acceptance of the EASA Form 1 released with a computer generated signature the following statement should be printed in Block 13 of the Form: ‘This document has been issued according to an approved computer generated signature procedure’. To facilitate understanding and acceptance of the EASA Form 1 released with an electronic signature, the following statement should be in Block 13b: ‘Electronic Signature on File’. In addition to this statement, it is accepted to print or display a signature in any form such as a representation of the hand-written signature of the person signing (i.e. scanned signature) or their name. When printing the electronic form, the EASA Form 1 should meet the general format as specified in Appendix I to Part-21. A watermark-type ‘PRINTED FROM ELECTRONIC FILE’ should be printed on the document. When the electronic file contains a hyperlink to data, required to determine the airworthiness of the item(s), the data associated to the hyperlink, when printed, should be in a legible format and be identified as a reference from the EASA Form 1.

text: Additional information not required by the EASA Form 1 completion instructions may be added to the printed copies of EASA Form 1 as long as the additional data do not prevent

text: ED Decision 2010/001/R 23/03/2010 a person from filling out, issuing, printing, or reading any portion of the EASA Form 1. This additional data should be provided only in block 12 unless it is necessary to include it in another block to clarify the content of that block.

text: 4. Electronic exchange of the electronic EASA Form 1 The electronic exchange of the electronic EASA Form 1 should be accomplished on a voluntary basis. Both parties (issuer and receiver) should agree on electronic transfer of the EASA Form 1. For that purpose, the exchange needs to include:  all data of the EASA Form 1, including data referenced from the EASA Form 1;  all data required for authentication of the EASA Form 1. In addition, the exchange may include:  data necessary for the electronic format;  additional data not required by the EASA Form 1 completion instructions, such as manufacturer code, customer identification code. The system used for the exchange of the electronic EASA Form 1 should provide:  a high level of digital security; the data should be protected, unaltered or uncorrupted;  traceability of data back to its source should be possible. Trading partners wishing to exchange EASA Form 1 electronically should do so in accordance with these means of compliance stated in this document. It is recommended that they use an established, common, industry method such as Air Transport Association (ATA) Spec 2000 Chapter 16. The applicant(s) is/are reminded that additional national and/or European requirements may need to be satisfied when operating the electronic exchange of the electronic EASA Form 1. The receiver should be capable of regenerating the EASA Form 1 from the received data without alteration; if not the system should revert back to the paper system. When the receiver needs to print the electronic form, refer to the subparagraph 3 above.

text: The following new AMC to 21A.163(c) is introduced:

text: AMC No 2 to 21A.163(c) – Completion of the EASA Form 1

text: EASA Form 1 Block 8 ‘Part Number’

text: The part number as it appears on the item, is usually defined in the design data; however in the case of a kit of parts, media containing software or any other specific condition of supply may be defined in production data developed from design data. Information about the contents of the kit or media may be given in block 12 or in a separate document cross-referenced from block 12.

text: EASA Form 1 Block 12 ‘Remarks’

text: Examples of conditions which would necessitate statements in block 12 are:  When the certificate is used for prototype purposes the following statement must be entered at the beginning of block 12: ‘NOT ELIGIBLE FOR INSTALLATION ON IN-SERVICE TYPE-CERTIFICATED AIRCRAFT’.  Re-certification of items from ‘prototype’ (conformity only to non-approved data) to ‘new’ (conformity to approved data and in a condition for safe operation) once the applicable design data is approved. The following statement must be entered in block 12: RE-CERTIFICATION OF ITEMS FROM ‘PROTOTYPE’ TO ‘NEW’:

text: ED Decision 2010/001/R 23/03/2010 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.  When a new certificate is issued to correct error(s) the following statement must be entered in block 12: ‘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’. Examples of data to be entered in this block as appropriate:  For complete engines, a statement of compliance with the applicable emissions requirements current at the date of manufacture of the engine.  For ETSO articles, state the applicable ETSO number.  Modification standard.  Compliance or non-compliance with airworthiness directives or Service Bulletins.  Details of repair work carried out, or reference to a document where this is stated.  Shelf life data, manufacture date, cure date, etc.  Information needed to support shipment with shortages or re-assembly after delivery.  References to aid traceability, such as batch numbers. The AMC 21A.163(e) is amended as follows: …

text: 2.4 Issue of the permit to fly under the POA privilege

text: The procedure must describe the process to prepare the EASA Form 20b and how compliance with 21A.711(c) and (de) is established before signature of the permit to fly. …

text: 2.6 Interface with the local authority for the flight

text: The procedure must include provisions describing the communication with the local authority for compliance with the local requirements which are outside the scope of the conditions of 21A.708(b) (see 21A.711(de)).

text: ED Decision 2010/001/R 23/03/2010 The GM No 3 to 21A.165(c) is amended as follows:

text: GM No 3 to 21A.165(c) Obligations of the manufacturer – Condition for safe operation

text: 3. Technical records which identify the location and serial numbers of significant components that have special traceability requirements for continued airworthiness purposes including those identified in 21A.801 and 21A.805. … 15 Where applicable there should be a certificate for noise and for the aircraft radio station. 17 16 The installed compass and/or compass systems have been adjusted and compensated and a deviation card displayed in the aircraft. 18 17 Software criticality list. 19 18 A record of rigging and control surface movement measurements. 20 19 Details of installations which will be removed before starting commercial air transport operations (e.g. ferry kits for fuel, radio or navigation). 21 20 Where maintenance work has been performed under the privilege of 21A.163(d) issue a release to service that includes a statement that the aircraft is in a condition for safe operation. 22 21 List of all applicable Service Bulletins and airworthiness directives that have been implemented. … The GM No 4 to 21A.165(c) is amended as follows:

text: GM No 4 to 21A.165(c) Airworthiness Release or Conformity Certificate

text: The EASA Form 1, when used as a release certificate as addressed in 21A.165(c)(2) and (3), may be issued in two ways:  As an airworthiness release, only when by virtue of the arrangement described in 21A.133(b) and (c), it can be determined that the part conforms to the approved design data and is in a condition for safe operation.  As a conformity certificate, only when by virtue of the arrangement described in 21A.133(b) and (c), it can be determined that the part conforms to applicable design data which is not (yet) approved, for a reason that is indicated in block 13 12. Parts released with an EASA Form 1 as a conformity certificate are not eligible for installation in a type-certificated aircraft. The EASA Form 1 should only be used for conformity release purposes when it is possible to indicate the reason that prevents its issue as for airworthiness release purposes.

text: ED Decision 2010/001/R 23/03/2010 The Form 18A in AMC 21A.263(c)(6) is amended as follows:

text: AMC 21A.263(c)(6) Procedure for the approval of the conditions for issue of a permit to fly

text: FLIGHT CONDITIONS FOR A PERMIT TO FLY – APPROVAL FORM

text: 1. Applicant 2. Approval form nr approval nr Issue:

text: [Name and organisation approval [number and issue, for traceability

text: number of organisation providing the purposes] flight conditions and associated

text: substantiations]

text: 3. Aircraft manufacturer/type 4. Serial number(s)

text: 5. Purpose

text: [Purpose in accordance with 21A.701(a)]

text: 5 6. Aircraft configuration

text: The above aircraft for which a permit to fly is requested is defined in [add reference to the document(s) identifying the detailed configuration of the aircraft]. [For change(s) affecting the initial approval form: description of change(s). This

text: form must be re-issued.]

text: 6 7. Substantiations

text: [References to the document(s) justifying that the aircraft (as described in 56.) can perform the intended flight(s) safely under the defined conditions or

text: restrictions.]

text: [For change(s) affecting the initial approval form: reference(s) to additional

text: substantiation(s). This form must be re-issued.]

text: 7 8. Conditions/Restrictions

text: The above aircraft must be used with the following conditions or restrictions: [Details of these conditions/restrictions, or reference to relevant document, including specific maintenance instructions and conditions to perform these

text: instructions.]

text: 8 9. Statement

text: The determination of the flight conditions has been made in accordance with the relevant DOA procedure agreed by the Agency. The aircraft as defined in block 6 above has no features and characteristics making it unsafe for the intended operation under the identified conditions and restrictions.

text: ED Decision 2010/001/R 23/03/2010

text: [strikethrough what is not applicable] 9a 10a. Approved under the authority of DOA EASA.21J.xyz [when privilege

text: of 21A.263(c)(6) applies]

text: 9b 10b. Submitted under the authority of DOA EASA.21J. xyz [when

text: privilege of 21A.263(c)(6) does not apply]

text: 10 11. Date of issue 11 12. Name and signature

text: [Authorised signatory]

text: 12 13. EASA approval and date

text: [when privilege of 21A.263(c)(6) does not apply]

text: EASA Form 18A Issue 2 … The AMC 21A.263(c)(7) is amended as follows:

text: AMC 21A.263(c)(7) Procedure for the issue of a permit to fly

text: 2.3 Issue of the permit to fly under the DOA privilege

text: The procedure must describe the process to prepare the EASA Form 20b and how compliance with 21A.711(b) and (de) is established before signature of the permit to fly. …

text: 2.5 Interface with the local authority for the flight

text: ED Decision 2010/001/R 23/03/2010

text: The GM 21A.307 is deleted.

text: The following references in the GM to Subpart P flow-charts are amended as follows:

text: GM to Subpart P

text: Flow-chart 2: approval of flight conditions

text: Application to Related to YES EASA, with data safety of the and approval design? form [21A.709(a)(1)] NO

text: NO Case covered by privilege?

text: YES Application to competent Request to authority [21A.709(a)(2), DOA with AMC 21A.709(b)] appropriate privilege

text: Approval Approval Approval Approval process process process process 21A.710(a)(2) 21A.710(a)(2) 21A.710(a)(1)(ii) 21A.710(a)(1)(i) 21A.710(b) 21A.710(b) 21A.710(a)(2) 21A.710(a)(1)

text: ED Decision 2010/001/R 23/03/2010

text: Flow-chart 4: Changes after first issue of permit to fly

text: NO Case covered by privilege?

text: Approval Approval Approval Approval Process Process Process Process 21A.710(a)(2) 21A.710(a)(2) 21A.710(a)(1)(ii) 21A.710(a)(1)(i) 21A.710(b) 21A.710(b) 21A.710(a)(2) 21A.710(a)(1)

text: Need to re-issue YES 3 the permit to fly itself? [21A.713]

text: NO

text: END

text: ED Decision 2010/001/R 23/03/2010

text: The GM 21A.701(a) is amended as follows:

text: GM 21A.701(a) Permit to fly when certificate of airworthiness or restricted certificate of airworthiness is not appropriate

text: … (11) Flying the aircraft to a location where maintenance or airworthiness review are to be performed, or to a place of storage: — Ferry flights in cases where maintenance is not performed in accordance with approved programmes, where an AD has not been complied with where certain equipment outside the Master Minimum Equipment List (MMEL) is unserviceable or when the aircraft has sustained damage beyond the applicable limits. …

text: The Form 18B in AMC 21A.709(b) is amended as follows: …

text: 1. Applicant 2. Approval form nr

text: [Name of organisation providing the Issue:

text: flight conditions and associated [number and issue, for traceability substantiations] purposes]

text: 5. Purpose

text: [Purpose in accordance with 21A.701(a)]

text: 5 6. Aircraft configuration

text: The above aircraft for which a permit to fly is requested is defined in [add reference to the document(s) identifying the configuration of the aircraft]. [For change(s) affecting the initial approval form: description of change(s). This

text: form must be re-issued.]

text: 6 7. Substantiations

text: restrictions.]

text: 7 8. Conditions/Restrictions

text: instructions.]

text: 8 9. Statement

text: The flight conditions have been established and justified in accordance with 21A.708. The aircraft as defined in block 6 above has no features and characteristics

text: ED Decision 2010/001/R 23/03/2010 making it unsafe for the intended operation under the identified conditions and restrictions.

text: [when approved under a privilege of an approved organisation] 9 10. Approved under [ORGANISATION APPROVAL NUMBER]

text: [authorised signatory]

text: [when not approved under a privilege of an approved organisation]

text: 12 13. Approval and date [the appropriate approval: EASA, competent authority]

text: EASA Form 18B Issue 2 … The numbering of GM 21A.711(d) is amended as follows:

text: GM 21A.711(de) Additional conditions and restrictions

text: … The following new GM 21A.804(a)(1) is introduced in Subpart Q – Identification of products, parts and appliances

text: GM 21A.804(a)(1) Identification of parts and appliances

text: It is not the intent of 21A.804(a)(1) to introduce an obligation for a production organisation (manufacturer) to mark new parts or appliances with information which is not identified by the design approval holder. Therefore, the physical marking of parts and appliances is only required when established by the design approval (TC, STC, ETSO, repair, minor change) holder. For designs (TC, STC, ETSO, repair, change) approved after the date of entry into force of

text: Commission Regulation (EC) No 1194/2009

text: amending Regulation 1702/2003, the design approval holder is required to identify to the manufacturer how the marking in accordance with 21A.804(a)(1) should be done. This can be limited to identifying a marking field, possible depth and/or means etc., without prescribing the actual text or symbols to be used. The GM No 1 to 21B.50 is deleted. The GM No 2 to 21B.50 is deleted. The EASA Form 56 to GM No 2 to 21B.220(c) is amended as follows:

text: PART TWO OF FIVE

text: (Page 2 of 6)

text: 21A.139 Quality System

text: … (b) The quality system shall contain: (1) As applicable within the scope of approval, control procedures for:

text: ED Decision 2010/001/R 23/03/2010 … (ix) +-------+ Airworthiness coordination with the applicant for, or holder of, a design approval. … (xvii) +-------+ +-------+ Issue of permit to fly and approval of associated flight conditions. …

text: (b) The quality system shall contain (cont’d) - (2) An independent quality assurance function to monitor compliance with, and adequacy of, the documented procedures of the quality system. This monitoring shall include a feedback system to the person or group of persons specified referred to in 21A.145(c)(2) and ultimately to the manager specified referred to in 21A.145 (c)(1) to ensure, as necessary, corrective action. (Page 3 of 6)

text: 21A.145 Approval requirements

text: … (c) with regard to management and staff: … (2) A person or a group of persons have been nominated by the production organisation to ensure that the organisation is in compliance with the requirements of this Part, and are identified, together with the extent of their authority. Such person(s) shall act under the direct authority of the senior accountable manager referred to in subparagraph (1). The knowledge, background and experience of the persons nominated shall be appropriate to discharge their responsibilities. (Page 4 of 6) …

text: 21A.147 Changes to the approved production organisation

text: … (b) The competent authority shall establish the conditions under which a Subpart G approved production organisation approved under this Subpart may operate during such changes unless the competent authority determines that the approval should be suspended. (Page 5 of 6) …

text: 21A.163 Privileges

text: Pursuant to the terms of approval issued under 21A.135, the holder of a production organisation approval may: … (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 21A.711(c) including approval of the flight conditions in accordance with 21A.710(b).

text: ED Decision 2010/001/R 23/03/2010 (Page 6 of 6) …

text: 21A.165 Obligations of the holder (cont’d)

text: … (c) (2) Determine that other products, parts or appliances are complete and conform to the approved design data and are in a condition for safe operation before issuing EASA Form 1 to certify airworthiness conformity to approved design data and in a condition for safe operation, and additionally in case of engines, determine according to data provided by the engine type-certificate holder that each completed engine is in compliance with the applicable emissions requirements as defined in 21A.18(b), current at the date of manufacture of the engine, to certify emissions compliance, or … (j) Where applicable, under the privilege of 21A.163(e), determine the conditions under which a permit to fly can be issued. +------------------------------------+ +------------------------------------+ (k) Where applicable, under the privilege of 21A.163(e), establish compliance with 21A.711(b) and (e) before issuing a permit to fly (EASA Form 20b, see Appendix) to an aircraft. +------------------------------------+ +------------------------------------+

text: PART THREE OF FIVE

text: (Page 1 of 2)

text: Production organisation exposition

text: … (2) The title(s) and names of the persons nominated managers accepted by the competent authority in accordance with 21A.145(c)(2). (3) The duties and responsibilities of the person manager(s) as required by 21A.145(c)(2) including matters on which they may deal directly with the competent authority on behalf of the organisation. (4) An organisational chart showing associated chains of responsibility of the managers/persons as required by 21A.145(c)(1) and (c)(2). (Page 2 of 2) … (9) The procedure for the notification of organisational changes to the competent authority. The AMC No 2 to 21B.230 is deleted.

text: ED Decision 2010/001/R 23/03/2010 The AMC 21B.235(c) is amended as follows:

text: AMC 21B.235(c) Continuation of POA

text: At the end of the 24 months continued surveillance cycle, the POATL responsible for the POA should complete an EASA Form 56 (see GM No 2 to 21B.220(c)) as a summary report for the continued surveillance including the recommendation for continuation of the POA as applicable. The EASA Form 56 should be countersigned by the person responsible within the competent authority for his acceptance. At this stage there is no limitation to the number of level two findings that may be open, provided they are within the time limits of the respective corrective action plans. The GM 21B.325(a) is amended as follows:

text: GM 21B.325(a) Airworthiness Certificates

text: 1 Completion of the certificate of airworthiness by a Member State

text: Block 5: Insert restrictions developed in accordance with Part-21, including any reference to limitations as indicated in GM 21B.320(b)(6).

text: 2 Completion of the restricted certificate of airworthiness by a Member State

text: 3 Completion of the permit to fly by a Member State

text: Block 4: Insert purpose of flight in accordance with

text: Article 5(4)

text: (e)(ii) first indent of the Basic Regulation. Block 5: Insert restrictions in accordance with

text: Article 5(4)

text: (e)(ii) second and third indent of the Basic Regulation.


text: OF THE EXECUTIVE DIRECTOR OF THE EUROPEAN AVIATION SAFETY AGENCY

text: OF 16 DECEMBER 2010

text: TE.RPRO.00035-001 © European Aviation Safety Agency. All rights reserved. Page 1 of 11 Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

text: Management Board Decision concerning the procedure to be applied by the Agency for the issuing of opinions, certification specifications and guidance material (Rulemaking Procedure), EASA MB/08/07, 13.6.2007. See NPA 2008-01 & CRD 2008-01, NPA 2009-11 & CRD 2009-11 and NPA 2010-01 & CRD 2010-01 available at http://www.easa.europa.eu/ws_prod/r/r_archives.php.

text: TE.RPRO.00035-001 © European Aviation Safety Agency. All rights reserved. Page 2 of 11 Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

text: TE.RPRO.00035-001 © European Aviation Safety Agency. All rights reserved. Page 3 of 11 Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

text: TE.RPRO.00035-001 © European Aviation Safety Agency. All rights reserved. Page 4 of 11 Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

text: TE.RPRO.00035-001 © European Aviation Safety Agency. All rights reserved. Page 5 of 11 Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

text: TE.RPRO.00035-001 © European Aviation Safety Agency. All rights reserved. Page 6 of 11 Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

text: TE.RPRO.00035-001 © European Aviation Safety Agency. All rights reserved. Page 7 of 11 Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

text: TE.RPRO.00035-001 © European Aviation Safety Agency. All rights reserved. Page 8 of 11 Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

text: TE.RPRO.00035-001 © European Aviation Safety Agency. All rights reserved. Page 9 of 11 Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

text: TE.RPRO.00035-001 © European Aviation Safety Agency. All rights reserved. Page 10 of 11 Proprietary document. Copies are not controlled. Confirm revision status through the EASA-Internet/Intranet.

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identifier: AMC & GM to Part 21 — Issue 1, Amendment 7

amnesord: Part 21 - Airworthiness and Environmental Certification

beslut: ED Decision 2010/016/R

publisher: Europeiska unionens byrå för luftfartssäkerhet

sprak: en

title: AMC & GM to Part 21 — Issue 1, Amendment 7

serie: amc-gm

text: ED Decision 2010/016/R 16/12/2010

type: stycke

text: European Aviation Safety Agency

type: rubrik

text: DECISION N 2010/016/R

text: amending the Annex to Decision No. 2003/01/RM of the Executive Director of the Agency of 17 October 2003

text: on

text: Acceptable Means of Compliance and Guidance Material for the airworthiness and environmental certification of aircraft and related products, parts and appliances, as well as for the certification of design and production organisations

text: («AMC and GM to Part-21»)

text: ‘Extended Range Operations with Two-Engined Aeroplanes ETOPS Certification and Operation’,

text: ‘Systematic review and transposition of existing FAA TSO standards for parts and appliances into EASA ETSO’

text: And

text: ‘Other party supplier control’

text: THE EXECUTIVE DIRECTOR OF THE EUROPEAN AVIATION SAFETY AGENCY, Having regard to the

text: Regulation (EC) No 216/2008

text: of the European Parliament and of the Council of 20 February 2008 on common rules in the field of civil aviation and establishing a European Aviation Safety Agency, and repealing

text: Council Directive 91/670/EEC

text: Regulation (EC) No 1592/2002

text: and Directive

text: (hereinafter ‘The Basic Regulation’), and in particular

text: Articles 18

text: (c), 38(3)(a) and (e) thereof, Having regard to the

text: Commission Regulation (EC) No 1702/2003 of 24 September 2003

text: laying down implementing rules for the airworthiness and environmental certification of aircraft and related products, parts and appliances, as well as for the certification of design and production organisations , OJ L 79, 19.03.2008, p. 1. OJ L 243, 27.9.2003, p. 6. Regulation as last amended by

text: Regulation (EC) No 1194/2009 of 30 November 2009

text: (OJ L 321, 8.12.2009, p. 5).

text: ED Decision 2010/016/R 16/12/2010

text: Whereas: (1) The Agency shall, pursuant to Article 18 of the Basic Regulation, issue Certification Specifications, including Airworthiness Codes and Acceptable Means of Compliance, as well as guidance material for the application of the Basic Regulation and its Implementing Rules. (2) The Agency is obliged, pursuant to Article 19 of the Basic Regulation, to reflect the state of the art and the best practices in the fields concerned and to update the Certification Specifications taking into account the worldwide aircraft experience in service, and scientific and technical progress. (3) The Agency, pursuant to

text: Article 52(1)

text: (c) of the Basic Regulation and articles 5(3) and 6 of the Rulemaking Procedure , has widely consulted interested parties on the matters that are subject of this Decision and has provided thereafter a written response to the comments received . (4) Rulemaking task MDM.001 aimed at providing an improved set of requirements containing guidance for both holders of type-certificate and operators to support ETOPS.

text: (5) Chapter 21A.3(a) of Part-21 already requires certificate and approval holders to have a ‘System for Collection, Investigation and Analysis of Data’. However, there are no associated existing Acceptable Means of Compliance (AMC) detailing how this process is expected to be put in place. For this reason, the Agency has decided to create a new AMC explaining what is expected in the case of ETOPS significance occurrences. (6) Rulemaking task ETSO.007 proposes introduction of new ETSO specifications that are, where possible, technically similar to the existing Federal Aviation Administration (FAA) TSO.

text: (7) These new ETSO standards require statements regarding environmental categories and design assurance levels for complex hardware. The standard form for the Declaration of Design and Performance does not show these new requirements. For this reason, the Agency has decided to amend the current standard form provided in the AMC&GM to Part-21 and include the new requirements. (8) Rulemaking task 21.042 aimed at providing criteria for holders of a Production Organisation Approval (POA) for supplier surveillance and assessment by a party other than the POA holder.

text: (9) The Agency therefore decided to create new AMC’s that the POA holder can use for supplier surveillance and assessment by a party other than the POA holder. These AMC provide criteria for the POA holder to show that, while the POA holder retains full responsibility, a party other than the POA holder performs supplier surveillance and assessment activities.

text: HAS DECIDED:

text: Article 1

text: ED Decision 2010/016/R 16/12/2010 organisations involved in their design or manufacture’ to Decision ED/2003/01/RM of the Executive Director of the Agency of 17 October 2003 is hereby amended as provided in Annex 1 to this decision.

text: Article 2

text: This decision shall enter into force on 23 December 2010. It shall be published in the Official Publication of the Agency.

text: Done in Cologne, on 16 December 2010.

text: P. GOUDOU

text: ED Decision 2010/016/R 16/12/2010

text: Annex 1 to ED Decision 2010/016/R

text: The Annex ‘Acceptable Means of Compliance and Guidance Material to be used in the airworthiness certification of products, parts and appliances and the approval of organisations involved in their design or manufacture’ to Decision ED/2003/01/RM of the Executive Director of the Agency of 17 October 2003 is hereby amended as follows:

text: The text of amendments is arranged to show deleted text or new text as shown below:

text: 1. Text to be deleted is shown with a strikethrough.

text: 2. New text to be inserted is highlighted with grey shading.

text: 3. … Indicates that remaining text is unchanged in front of or following the reflected amendment.

text: The title of AMC to 21A.3(a) is amended as follows:

text: AMC No 1 to 21A.3(a)

text: A new AMC No 2 to 21A.3(a) is added as follows:

text: AMC No 2 to 21A.3(a) Collection, investigation and analysis of data related to ETOPS significant occurrences

text: (1) Holders of a type-certificate, restricted type-certificate, supplemental typecertificate or any other relevant approval deemed to have been issued under Part- 21 and which includes extended range operation with two-engined aeroplane (ETOPS) capability should implement a specific tracking, reporting and resolution system for ETOPS significant occurrences, suitable to ensure the initial and continued fleet compliance with the applicable ETOPS reliability objectives. This system should be part of the system for collection, investigation and analysis of data required by 21.A.3(a). Appropriate coordination should exist between Engine TC holder, propeller TC holder and APU ETSO approval holder with the aircraft TC holder to ensure compliance with the ETOPS reliability objectives. (2) For tracking, reporting and resolution of ETOPS significant occurrences refer to EASA AMC 20-6.

text: The GM No. 2 to 21A.139(a) is amended as follows:

text: GM No. 2 to 21A.139(a)

text: Quality System – Conformity of supplied parts or appliances

text: The POA holder is responsible for determining and applying acceptance standards for physical condition, configuration status and conformity of supplied products, parts or appliances, whether to be used in production or delivered to customers as spare parts. This responsibility also includes BFE (Buyer Furnished Equipment) items. To discharge this responsibility the quality system needs an organisational structure and procedures to adequately control external suppliers. Elements of the quality system for the control of suppliers may be performed by other parties provided that the conditions of AMC No. 1 or No. 2 to 21A.139(b)(1)(ii) are met. Control can be based upon use of the following techniques (as appropriate to the system or product orientation necessary to ensure conformity).

text: ED Decision 2010/016/R 16/12/2010  qualification and auditing of supplier’s quality system,  ….

text: The following new AMC No. 1 to 21A.139(b)(1)(ii) is introduced:

text: AMC No. 1 to 21A.139(b)(1)(ii)

text: Vendor and sub-contractor assessment, audit and control – Production Organisation Approval (POA) holder using documented arrangements with other parties for assessment and surveillance of a supplier.

text: 1 General

text: Note

text: For the purpose of this AMC, vendors and sub-contractors are hereafter referred to as "suppliers", regardless of whether or not they hold a POA and audit and control is hereafter referred to as "surveillance". The production organisation is required by Part-21 to demonstrate that it has established and maintains a quality system that enables the organisation to ensure that each item produced conforms to the applicable design data and is in a condition for safe operation. To discharge this responsibility, the quality system should have, among other requirements, procedures to adequately carry out the assessment and surveillance of suppliers. The use of Other Parties (OP), such as a consulting firm or quality assurance company, for supplier assessment and surveillance does not exempt the POA holder from its obligations under 21A.165. The supplier assessment and surveillance, corrective action and follow-up activity conducted at any of its supplier’s facilities may be performed by OP. The purpose of using an OP cannot be to replace the assessment, audit and control of the POA Holder. It is to allow an element (i.e. the assessment of the quality system) to be delegated to another organisation under controlled conditions. The use of OP to perform supplier assessments and surveillance should be part of the production organisation quality system and fulfil the conditions of this AMC.

text: This AMC is applicable to a method whereby a POA holder has a documented arrangement with OP for the purpose of assessing and/or surveying a POA's supplier.

text: 2 Approval by the Competent Authority.

text: Implementing or changing procedures for using OP for supplier assessment and surveillance is a significant change to the quality system and requires approval in accordance with 21A.147.

text: 3 Conditions and criteria for the use of OP to perform supplier assessment and surveillance.

text: (a) The POA holder should include the use of OP for supplier assessment and surveillance in the POA holders’ quality system to demonstrate compliance with the applicable requirements of Part-21. (b) Procedures required for using OP for supplier assessment and surveillance should be consistent with other procedures of the POA holders’ quality system. (c) Procedures of the POA holder that uses OP to perform supplier assessment and surveillance should include the following: (1) Identification of the OP that will conduct supplier assessment and surveillance.

text: ED Decision 2010/016/R 16/12/2010 (2) A listing of suppliers under surveillance by the OP. This listing should be maintained by the POA holder and made available to the Competent Authority upon request. (3) The method used by the POA holder to evaluate and monitor the OP. The method should include the following as a minimum: (i) Verification that standards and checklists used by the OP are acceptable for the applicable scope. (ii) Verification that the OP is appropriately qualified and have sufficient knowledge, experience and training to perform their allocated tasks. (iii) Verification that the OP surveillance frequency of the suppliers is commensurate with the complexity of the product and with the surveillance frequency established by the POA holder’s suppliers control programme. (iv) Verification that the suppliers’ assessment and surveillance is conducted on-site by the OP. (v) Verification that the OP has access to applicable proprietary data to the level of detail necessary to survey suppliers functions. Where the POA holder uses an OP accredited by a signatory to the European cooperation for Accreditation (EA) Multilateral Agreement and working in accordance with an aviation standard (e.g. EN 9104 series of requirements) that describes requirements for the other party assessment and surveillance, the items (ii) and (iv) shall be deemed to be complied with. (4) A definition to what scope the OP will conduct suppliers surveillance on behalf of the POA holder. If the OP replaces surveillance in part, the POA holder should identify the functions that will continue to be surveyed by the POA holder. (5) The procedures used by the OP to notify the POA holder of nonconformities discovered at the suppliers facility, corrective action and follow-up.

text: (d) The POA should make arrangements that allow the Competent Authority to make investigation in accordance with 21A.157 to include OP activities.

text: ED Decision 2010/016/R 16/12/2010

text: The following new AMC No. 2 to 21A.139(b)(1)(ii) is introduced:

text: AMC No. 2 to 21A.139(b)(1)(ii) Vendor and sub-contractor assessment, audit and control - Production Organisation Approval (POA) holder using other party supplier certification

text: 1 General

text: Note

text: For the purpose of this AMC, vendors and sub-contractors are hereafter referred to as "suppliers", regardless of whether or not they hold a POA and audit and control is hereafter referred to as "surveillance". Other party supplier certification is a method whereby a supplier contracts with an appropriately recognised or accredited Other Party (OP) for the purpose of obtaining a certification from that OP. Certification indicates that the supplier has satisfactorily demonstrated to meet the applicable standard on a continuing basis. OP certification results in placing the supplier on the OP list of certified organisations, or in the supplier receiving a certificate identifying the requirements that have been met. Periodic follow-up evaluations are conducted by the OP to verify continued compliance with the requirements of the applicable standard. The production organisation is required by Part-21 to demonstrate that it has established and maintains a quality system that enables the organisation to ensure that each item produced conforms to the applicable design data and is in a condition for safe operation. To discharge this responsibility, the quality system should have, among other requirements, procedures to adequately carry out the assessment and surveillance of suppliers. The assessment and surveillance of suppliers by an OP should be deemed to satisfy the requirements of 21A.139(b)(1)(ii) when the conditions of this AMC are satisfied. The assessment and surveillance of suppliers by OP as part of supplier certification does not exempt the POA holder from its obligations under 21A.165. The supplier assessment and surveillance, corrective action and follow-up activity conducted at any of its supplier’s facilities may be performed by OP. The purpose of using an OP cannot be to replace the assessment, audit and control of the POA Holder. It is to allow an element (i.e. the assessment of the quality system) to be delegated to another organisation under controlled conditions. The use of suppliers that are certified by OP in accordance with this AMC should be part of a production organisation quality system.

text: 2 Approval by the Competent Authority.

text: Implementing or changing procedures for using suppliers that are certified by an OP is a significant change to the quality system and requires approval in accordance with 21A.147.

text: 3 Conditions and criteria for using supplier certification for the supplier assessment and surveillance.

text: (a) The POA holder should include the use of supplier certification for the supplier assessment and surveillance in the POA holder’s quality system to demonstrate compliance with the applicable requirements of Part-21. (b) Procedures required for use of supplier certification for the supplier assessment and surveillance should be consistent with other procedures of the POA holders’ quality system.

text: ED Decision 2010/016/R 16/12/2010

text: (c) Procedures of the POA holder that uses supplier certification for the supplier assessment and surveillance should include the following: (1) Listing of the OP that has certified or will certify suppliers and will conduct supplier assessment and surveillance or the scheme under which the accreditation of the OP is controlled. This listing should be maintained by the POA holder and made available to the Competent Authority upon request. (2) A listing of the certified suppliers under surveillance by the OP and used by the POA holder. This listing should be maintained by the POA holder and made available to the Competent Authority upon request. (3) The method used by the POA holder to evaluate and monitor the certification process of any OP certification body or OP certification scheme used. This applies not only to new suppliers, but also to any decision by the POA holder to rely on OP certification of current suppliers. The method should include the following as a minimum: (i) Verification that certification standards and checklists are acceptable and applied to the applicable scope. (ii) Verification that the OP is appropriately qualified and has sufficient knowledge, experience and training to perform its allocated tasks. (iii) Verification that the OP surveillance frequency of the suppliers is commensurate with the complexity of the product and with the surveillance frequency established by the POA holder’s suppliers control programme. (iv) Verification that the suppliers’ surveillance is conducted on-site by the OP. (v) Verification that the surveillance report will be made available to the Competent Authority upon request. (vi) Verification that the OP continues to be recognised or accredited. (vii) Verification that the OP has access to applicable proprietary data to the level of detail necessary to survey suppliers functions.

text: Where the POA holder uses an OP accredited by a signatory to the European cooperation for Accreditation (EA) Multilateral Agreement and working in accordance with an aviation standard (e.g. EN 9104 series of requirements) that describes requirements for the OP certification, the items (ii), (iv) and (v) shall be deemed to be complied with.

text: (5) Procedures that ensure that the POA is aware of the loss of an existing certification. (6) Procedures that ensure that the POA holder is aware of nonconformities and has access to detailed information of these nonconformities.

text: (7) Procedures to evaluate the consequences of nonconformities and take appropriate actions. (d) The POA should make arrangements that allow the Competent Authority to make investigation in accordance with 21A.157 to include OP activities

text: ED Decision 2010/016/R 16/12/2010

text: The AMC 21A.608 is amended as follows:

text: Declaration of Design and Performance

text: STANDARD FORM

text: 1 Name and address of manufacturer. 2 Description and identification of article including:

text: Modification Standard Master drawing record Weight and overall dimensions 3 Specification reference, i.e., ETSO No. and Manufacturer’s design specification. 4 The rated performance of the article directly or by reference to other documents. 5 Particulars of approvals held for the equipment. 6 Reference to qualification test report. 7 Service and Instruction Manual reference number. 8 Statement of compliance with the appropriate ETSO and any deviations therefrom. 9 A statement of the level of compliance with the ETSO in respect of the ability of the article to withstand various ambient conditions or to exhibit various properties.

text: The following are examples of information to be given under this heading depending on the nature of the article and the requirements of the ETSO.

text: a. Working and ultimate pressure or loads. b. Limitations of voltage and frequency. c. Time rating (e.g., continuous, intermittent) or duty cycle. d. Limits of accuracy of measuring instruments. e. Whether the equipment is “flameproof” (explosion-proof). f. Whether the equipment is “fire-resistant”. g. The compass safe distance. h. Level of radio interference. j. Radio and audio frequency susceptibility.

text: ED Decision 2010/016/R 16/12/2010 k. Degree of vibration which the equipment will withstand. l. Degree of acceleration and shock which the equipment will withstand. m. Degree of waterproofness or sealing of equipment. n. Ability to withstand sand and dust. o. Ability to resist salt spray and aircraft fluids. p. Fungus resistance. q. Temperature and altitude category. r. Humidity category. s. Any other known limitations which may limit the application in the aircraft e.g., restrictions in mounting attitude. a. Environmental Qualification i. Temperature and Altitude ii. Temperature Variation iii. Humidity iv. Operational Shocks and Crash Safety v. Vibration vi. Explosion Proofness vii. Waterproofness viii. Fluids Susceptibility ix. Sand and Dust x. Fungus Resistance xi. Salt Spray xii. Magnetic Effect xiii. Power Input xiv. Voltage Spike xv. Audio Frequency Conducted Susceptibility - Power Inputs xvi. Induced Signal Susceptibility xvii. Radio Frequency Susceptibility (Radiated and Conducted) xviii. Emission of Radio Frequency Energy xix. Lightning Induced Transient Susceptibility xx. Lightning Direct Effects xxi. Icing xxii. Electrostatic Discharge xxiii. Fire, Flammability

text: (NOTE: The manufacturer should list environmental categories for each of the sections of the issue of EUROCAE ED-14/RTCA DO-160 that was used to qualify the article.)

text: b. For radio transmitters the transmitting frequency band, maximum transmitting power, and emission designator. c. Working and ultimate pressure or loads.

text: ED Decision 2010/016/R 16/12/2010 d. Time rating (e.g., continuous, intermittent) or duty cycle. e. Limits of accuracy of measuring instruments. f. Any other known limitations which may limit the application in the aircraft e.g., restrictions in mounting attitude.

text: 10 A statement of the software level(s) used or “None” if not applicable. (NOTE: Software levels are those defined in the applicable issue of EUROCAE ED–12/RTCA document DO–178.)

text: 11 A statement of design assurance level for complex hardware or a statement indicating whether complex hardware is embedded or not in the product.

text: (NOTE: Complex hardware design assurance levels are those defined in the applicable issue of EUROCAE ED–80/RTCA DO-254.)

text: 1112 The declaration in this document is made under the authority of

text: ……………………………………………………………………………(name of manufacturer) (Manufacturer’s name) cannot accept responsibility for equipment used outside the limiting conditions stated above without their agreement.

text: Date: ………….Signed…………………………..(Manufacturer’s authorised representative)

type: vagledning

utgivare: easa


text: OF THE EXECUTIVE DIRECTOR OF THE EUROPEAN AVIATION SAFETY AGENCY

text: OF 19 AUGUST 2011

text: OJ L 79, 19.3.2008, p. 1. Regulation as last amended by

text: Regulation (EC) No 1108/2009

text: of the European Parliament and of the Council of 21 October 2009 (OJ L 309, 24.11.2009, p. 51). OJ L 243, 27.9.2003, p. 6. Regulation as last amended by

text: Regulation (EC) No 1194/2009 of 30 November 2009

text: (OJ L 321, 8.12.2009, p. 5). OJ L 199, 31.7.2009, p. 6.

text: R.F012-02 © European Aviation Safety Agency, 2010. All rights reserved. Proprietary document. Page 1 of 6

text: Management Board Decision concerning the procedure to be applied by the Agency for the issuing of Opinions, Certification Specifications and Guidance Material (‘Rulemaking Procedure’), EASA MB 08-2007, 13.6.2007. See the Notice of Proposed Amendment (NPA) No 2010-13 and the Comment Response Document (CRD) to NPA 2010-13 both documents are available under http://www.easa.europa.eu/ws_prod/r/r_archives.php.

identifier: AMC & GM to Part 21 — Issue 1, Amendment 8

beslut: ED Decision 2011/006/R

text: ED Decision 2011/006/R 19/08/2011

text: European Aviation Safety Agency

text: DECISION N 2011/006/R

text: Amending Decision No. 2003/1/RM of the Executive Director of the Agency of

text: ‘Environmental protection – classification of changes to a type design’

text: THE EXECUTIVE DIRECTOR OF THE EUROPEAN AVIATION SAFETY AGENCY, Having regard to the

text: Regulation (EC) No 216/2008

text: of the European Parliament and of the Council of 20 February 2008 on common rules in the field of civil aviation and establishing a European Aviation Safety Agency, and repealing

text: Council Directive 91/670/EEC

text: Regulation (EC) No 1592/2002

text: and Directive

text: (hereinafter the ‘Basic Regulation’), and in particular

text: Articles 18

text: (c), 19(b) and 38(3)(a) thereof, Having regard to the

text: Commission Regulation (EC) No 1702/2003 of 24 September 2003

text: laying down implementing rules for the airworthiness and environmental certification of aircraft and related products, parts and appliances, as well as for the certification of design and production organisations , and in particular 21A.18 of the Annex (Part-21) thereof,

text: Whereas: (1) The Commission has amended the Basic Regulation with

text: Commission Regulation (EC) No 690/2009 of 30 July 2009

text: to include references to the latest amendments of Volumes I and II of Annex 16 to the Chicago Convention.

text: ED Decision 2011/006/R 19/08/2011 (2) The Agency shall, pursuant to Article 18 of the Basic Regulation, issue certification specifications codes and acceptable means of compliance, as well as guidance material for the application of the Basic Regulation and its implementing rules. (3) Pursuant to Article 19 of the Basic Regulation, certification specifications, acceptable means of compliance and guidance material adopted by the Agency shall reflect the state of the art and the best practices in the fields concerned and be updated taking into account worldwide experience from in-service aircraft, as well as scientific and technical progress. (4) The Agency, pursuant to

text: Article 52(1)

text: (c) of the Basic Regulation and Articles 5 and 6 of the Rulemaking Procedure , has widely consulted interested parties on the matters that are subject of this Decision and has provided thereafter a written response to the comments received .

text: HAS DECIDED:

text: Article 1

text: Paragraph 8 ‘Environment’ of Appendix A to GM 21A.91 ‘Examples of Major Changes per discipline’ to Decision ED/2003/01/RM of the Executive Director of the Agency of 17 October 2003 is hereby amended as provided in the Annex to this Decision.

text: Article 2

text: This Decision shall enter into force on 26 August 2011. It shall be published in the Official Publication of the Agency.

text: Done in Cologne, on 19 August 2011.

text: P. GOUDOU

text: ED Decision 2011/006/R 19/08/2011 Annex to ED Decision 2011/xxx/R

text: Paragraph 8 ‘Environment’ of Appendix A to GM 21A.91 ‘Examples of Major Changes per discipline’ to Decision ED/2003/01/RM of the Executive Director of the Agency of 17 October 2003 on acceptable means of compliance and guidance material for the airworthiness and environmental certification of aircraft and related products, parts and appliances, as well as for the certification of design and production organisations (‘AMC and GM to Part-21’) is hereby amended as shown below.

text: The text of amendments is arranged to show deleted text or new text as follows:

text: 1. Text to be deleted is shown with a line through it.

text: 2. New text to be inserted is highlighted with grey shading.

text: 3. ‘…’ indicates that remaining text is unchanged in front of or following the reflected amendment.

text: RESULTING TEXT:

text: AMC and GM to Part-21

text: Appendix A to GM 21A.91: Examples of Major Changes per discipline

text: 8 Environment

text: A change that introduces an increase in noise or emissions. The introductory text to Appendix A to GM 21A.91 describes how in Part-21 a negative definition is given of minor changes only. This philosophy is similar to the manner in which the ICAO Standards and Recommended Practices for environmental protection (ICAO Annex 16) and the associated Guidance Material (ICAO Environmental Technical Manual) define changes affecting a product’s environmental characteristics in terms of “no-acoustical changes” and “noemissions changes” (i.e. changes which do not appreciably affect the product’s environmental characteristics).

text: Following the general philosophy of this Appendix, however, it is preferred to give examples of changes which might have an appreciable effect on a product’s environmental characteristics (i.e. the effect might be greater than the noacoustic change and no-emissions change criteria) and might therefore lead to a major change classification.

text: Where a change is made to an aircraft or aircraft engine, the effect of the change on the product’s environmental characteristics should be taken into account. Examples of changes that might have an appreciable effect on the product’s environmental characteristics, and might therefore be classified as a major change, are listed below. The examples are not exhaustive and will not, in every case, result in an appreciable change to the product’s environmental characteristics, and therefore, will not per-se and in every case result in a major change classification.

text: ED Decision 2011/006/R 19/08/2011

text: An appreciable effect is considered to be one which exceeds the ICAO criteria for a no-acoustical change or a no-emissions change. For the definition of a noacoustical change refer to the section of the ICAO Environmental Technical Manual, Volume I (ICAO Doc 9501, Volume I – Procedures for the Noise Certification of Aircraft) concerning changes to aircraft type designs involving noacoustical changes (see also the definitions of a ‘derived version’ in ICAO Annex 16, Volume I). For the definition of a no-emissions change refer to the section of the ICAO Environmental Technical Manual, Volume II (ICAO Doc 9501, Volume II – Procedures for the Emissions Certification of Aircraft Engines) concerning no-emissions changes.

text: (i) Noise: A change that introduces either: - an increase in the noise certification level(s); or - a reduction in the noise certification level(s) for which the applicant wishes to take credit.

text: Examples of noise-related changes that might lead to a major change classification are:

text: (1) For jet and heavy (maximum take-off mass greater than 8618 kg) propeller-driven aeroplanes: - A change that might affect the aircraft’s take-off performance including:  a change to the maximum take-off mass;  a change to V2 (“take-off safety speed”); or  a change to the lift augmentation devices, including their configuration under normal take-off operating conditions. - A change that might affect the aircraft’s landing performance including:  a change to the maximum landing mass;  a change to VREF (reference landing speed); or  a change to the lift augmentation devices, including their deployment under normal landing operating conditions. - A change to the Centre of Gravity (CG) limits; - A change that increases the aircraft’s drag; - A change that alters the external profile of the aircraft, including the installation or change of shape or size of any item on the external surface of the aircraft that might protrude into the airflow such as winglets and vortex generators; generally the installation of small antennas does not represent an acoustical change; - A change that introduces an open-ended hollow cavity at more or less right angles to the airflow (e.g. hollow pins in undercarriage assemblies); - A change of engine or, if fitted, propeller type; - A change in engine thrust rating; - A change to the engine rotating parts or stators, such as geometry, blade profile or blade number; - A change to the aerodynamic flow lines through the engine; - A change that affects the engine thermodynamic cycle, including a change to the engine’s bypass ratio; - A change to the engine nacelle, including a change to the acoustic liners; - A change to the engine exhaust; - A change to the engine bleed valves, including bleed valve scheduling;

text: ED Decision 2011/006/R 19/08/2011

text: - A change in the operation of engine power off-takes (e.g. the operation of the Environmental Control System (ECS) during a normal take-off or approach); - A change to the Auxiliary Power Unit (APU), including associated operating limitations (e.g. a change that allows the APU to be operated during a normal approach when previously it was not allowed); - A change to the propeller pitch and/or propeller speed during a normal take-off or approach; - A change that causes a change to the angle at which air flows into the propeller.

text: (2) For light (maximum take-off mass 8618 kg or less) propeller-driven aeroplanes: - A change that might affect the aircraft’s take-off performance including:  a change to the maximum take-off mass;  a change to the take-off distance;  a change to the rate of climb; or  a change to Vy (best rate of climb speed). - A change that increases the aircraft’s drag (e.g. the installation of external cargo pods, external fuel tanks, larger tyres to a fixed undercarriage, floats etc.); - A change of engine or propeller type; - A change in take-off power including a change in engine speed (tachometer “red line”) or, for piston engines, a change to the manifold pressure limitations; - A change to the highest power in the normal operating range (“top of green arc”); - In the case of an aircraft where take-off power/engine speed is time limited, a change in the period over which take-off power/engine speed may be applied; - A change to the engine inlet or exhaust including, if fitted, the inlet or exhaust muffler; - A change in propeller diameter, tip shape, blade thickness or the number of blades; - The installation of a variable or adjustable pitch propeller in place of a fixed pitch propeller and vice versa; - A change that causes a change to the angle at which air flows into the propeller.

text: (3) For helicopters: - A change that might affect the take-off and/or landing performance, including a change in take-off mass and VY (best rate of climb speed); - A change to VNE (never-exceed airspeed) or to VH (airspeed in level flight obtained using the torque corresponding to minimum engine installed, maximum continuous power available for sea level pressure, 25°C ambient conditions at the relevant maximum certificated mass); - A change to the maximum take-off engine power or maximum continuous power; - A change to the gearbox torque limits; - A change of engine type; - A change to the engine intake or exhaust; - A change to the maximum normal operating rpm of the main or tail rotors;

text: ED Decision 2011/006/R 19/08/2011

text: - A change to the main or tail rotors, including a change in diameter, blade thickness or blade tip profile.

text: Note: The effect on the helicopter’s noise characteristics of either carrying external loads or the installation of external equipment need not be considered.

text: (ii) Emissions: A change that introduces an increase or decrease in the emissions certification levels. Examples of smoke and gaseous engine emission-related changes that might lead to a major change classification are:

text: - A change in engine thrust rating; - A change to the aerodynamic flow lines through the engine; - A change that affects the engine thermodynamic cycle, specifically relevant engine cycle parameters (e.g. combustor pressure P3, combustor entry temperature T3, Air Fuel Ratio (AFR)); - A change to the compressor that might influence the combustor inlet conditions and engine overall pressure ratio; - A change to the combustor design (geometry); - A change to the cooling of the combustor; - A change to the air mass flow through the combustor; - A change that affects the fuel spray characteristics.