Certification Directorate. Continuing Airworthiness of Type Design Procedure (CAP) C.P006-01

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1 1. COVER SHEET Certification Directorate Continuing Airworthiness of Type Design (CAP) Name Signature Date Caroline RUGA Original signed Paul VAN EENIGE Original signed Prepared by: Marco CAPACCIO Original signed Markus GÖRNEMANN Original signed Rachel DAESCHLER Original signed Verified by: Alain LEROY Original signed Reviewed by: Régine HAMELIJNCK Original signed Authorised by: Dr. rbert LOHL Original signed Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 1 of 42

2 2. DOCUMENT CONTROL SHEET Process concerned: Process owner: Head of Products Department - C Purpose This procedure describes how the Agency ensures the Continuing Airworthiness of Type Design. It has been defined to implement Article 15 of Decision 12/2007 of 01 October 2007 of the Management Board concerning the general principles related to the certification procedures to be applied by the Agency for the issuing of certificates for products, parts and appliances ( PCP Decision ), mandating the Executive Director to establish the necessary associated detailed procedures for the implementation of this Decision [ ]. 2.2 Scope This procedure describes how EASA shall internally handle the continuing airworthiness functions related to the type design of aeronautical products under its scope of competences. 2.3 Reference Documents 1 a) Internal 1. Decision. 2003/1/RM of 17 October 2003 of the Executive Director 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 ). 2. Decision 2003/12/RM of 5 vember 2003 of the Executive Director on general acceptable means of compliance for airworthiness of products, parts and appliances («AMC-20»). 3. Decision 12/2007 of 01 October 2007 of the Management Board concerning the general principles related to the certification procedures to be applied by the Agency for the issuing of certificates for products, parts and appliances (hereinafter referred to as PCP Decision). 4. Decision 2/2003 of 14 October 2003 of the Executive Director on the implementation of airworthiness directives for products, parts and appliances designed in third countries and repealing Decision 1/2003 of the Executive Director of the Agency of 26 September 2003 on the implementation of airworthiness directives for aircraft designed in third countries. 1 References to any statute, statutory instrument, Agency rule, procedure and policy shall include any amendments or consolidations thereof in as much as the referenced document remains relevant for this procedure. Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 2 of 42

3 5. Decision 10/2007 of 28 March 2007 of the Management Board on guidelines for the allocation of certification tasks to national aviation authorities or qualified entities. 6. Decision 2004/02/CF of the Executive Director of the Agency of 10 December 2004 on the acceptance of certification findings made by Transport Canada, Civil Aviation Department (TCCA) for products designed in Canada. 7. Decision 2004/03/CF of the Executive Director of the Agency of 10 December 2004 on the acceptance of certification findings made by Departamento de Aviação Civil, Centro Técnico Aeroespacial (DAC/CTA) for products designed in Brazil. 8. Decision 2004/04/CF of the Executive Director of the Agency of 10 December 2004 on the acceptance of certification findings made by the Federal Aviation Administration (FAA) for products designed in the United States of America and repealing Decision 2004/01/RM. 9. Decision 2007/03/E of the Executive Director of the Agency of 29 March 2007 on the delegation of powers from the Executive Director to certain staff members of the Certification Directorate. All the above references can be also found on the EASA website at: and b) External 1. Regulation (EC) 1592/2002 of the European Parliament and of the Council of 15 July 2002 on common rules in the field of civil aviation and establishing a European Aviation Safety Agency (hereinafter referred to as Basic Regulation), and amendments thereto. 2. Commission Regulation (EC) 1702/2003 of 24 September 2003 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 amendments thereto. 3. Commission Regulation (EC) 2042/2003 of 20 vember 2003 laying down implementing rules for the continuing airworthiness of aircraft and aeronautical products, parts and appliances, and on the approval of organisations and personnel involved in these tasks, and amendments thereto. 4. Commission Regulation (EC) 593/2007 of 31 May 2007 on the fees and charges levied by the European Aviation Safety Agency, and amendments thereto. All the above references can be also found on the EASA website at: and ICAO Annex 8 Part II Chapter 4. Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 3 of 42

4 2.4 Functions Concerned (Users) - Airworthiness Directives, Safety Management and Research Section (hereafter called AD Section) - Head of Products Department - Certification Managers - Project Certification Managers - Responsible Parties 2.5 Table of Contents 1. COVER SHEET DOCUMENT CONTROL SHEET Purpose Scope Reference Documents Functions Concerned (Users) Table of Contents Related Work Instructions / s Related Forms Other Related QMS Documents Definitions and Abbreviations Log of Issues LEGAL FRAMEWORK BASIC PRINCIPLES FOR CONTINUING AIRWORTHINESS ACTIVITIES General Occurrence Reporting: Maintenance Organisation Responsibilities Owner/Operator Responsibilities Certificate Holder Responsibilities NAA Responsibilities EASA Responsibilities Recommendations from Accident Investigation Authorities Other Continuing Airworthiness Activities Corrective Actions AIRWORTHINESS DIRECTIVE PROCESSES Standard Process for Issuing ADs Process Chart Process Steps Description for Standard Process for Issuing ADs Process for Final AD with Request for Comments (Consultation) Process Chart Process Steps Description for Final AD with Request for Comments (Consultation) Process for Emergency ADs Process Chart Process Steps Description for Emergency ADs Process for Changes to Previously Issued ADs Process Chart Process Steps Description for Changes to Previously Issued ADs Process for Adoption of Foreign ADs Process Chart Process Steps Description for Adoption of Foreign ADs EASA APPROVAL OF ALTERNATIVE METHODS OF COMPLIANCE (AMOC) Definition Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 4 of 42

5 6.2 Application Applicable Charges AMOC Approval Process Process Chart Process Steps Description for AMOC Approval AMOC to Foreign AD Approval Process Process Chart Process Steps Description for AMOC to Foreign AD SAFETY INFORMATION BULLETIN (SIB) General SIB Process Process Chart Process Steps Description for SIB LIST OF RECORDS Related Work Instructions / s Reference C.I001 C.I003 C.I007 C.I009 C.P Related Forms Reference EASA Form 42 EASA Form 43 EASA Form 44 EASA Form 110 EASA Form 111 EASA Form 112 EASA Form 113 EASA Form 114 EASA Form 115 EASA Form 116 EASA Form 117 Title Decisions and Signatures Disseminating Safety Related Information EASA AD Writing Manual (draft) Record Keeping & Archiving (draft) Application and Task Allocation for Product Certificates and Approvals Title Application for Approval of Alternative Methods of Compliance (AMOC) with Airworthiness Directives (AD) AMOC Internal Technical Visa template Technical Occurrence Report AD template Emergency AD template PAD template AD Technical Visa template AD CM Approval template PAD CRD template AD Cancellation tice template SIB template 2.8 Other Related QMS Documents Reference Title --- EASA Approval Letter AMOC S.L001 Accreditation Status of National Aviation Authorities for Allocation of Certification Tasks Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 5 of 42

6 2.9 Definitions and Abbreviations a) Abbreviations a/c Aircraft AD AFM AMC AMOC CAA CAP CM CM P&A CRD DAH EAD EASA EC ETSOA ETSOAH EU GM ICAO ICAO SARP JAR MCAI MS NAA PAD PCA PCM P&A PCM RTA SIB SoD SoR STC TC b) Definitions Certificate Holder EU Applicant Airworthiness Directive Aircraft Flight Manual Acceptable Means of Compliance Alternative Method of Compliance Civil Airworthiness Authority (non-eu) Continuing Airworthiness of Type Design EASA Certification Manager for the relevant product EASA Certification Manager Parts and Appliances Comment Response Document Design Approval Holder Emergency AD European Aviation Safety Agency European Community European Technical Standard Order Authorisation European Technical Standard Order Authorisation Holder European Union Guidance Material International Civil Aviation Organisation ICAO Standard and Recommended Practice Joint Aviation Requirements Mandatory Continuing Airworthiness Information Member State National Aviation Authority of EU Member State Proposed AD Primary Certificating Authority (State of Design; EASA for EU products) Project Certification Manager Parts and Appliances Project Certification Manager (EASA staff or staff from NAA under contractual arrangements) Request for Technical Advice Safety Information Bulletin State of Design State of Registry Supplemental Type Certificate Type Certificate In accordance with Part 21A.3 (a) and (b), the Certificate Holder is the holder of a TC, restricted TC, STC, ETSO authorisation, major repair design approval or any other relevant approval deemed to have been issued under Part 21 Applicant from EU Member State, rway, Iceland, Switzerland or Liechtenstein Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 6 of 42

7 PCM Substantive change to an AD n-substantive change to an AD Wherever the term PCM is used in this procedure, the term PCM means the PCM in coordination with his/her team, as appropriate Substantive changes may affect part numbers, service bulletin and manual references, compliance time, applicability, methods of compliance, corrective action, inspection requirements, and effective dates. Any change that is not considered to be a substantive change to an AD Log of Issues Issue # Issue date Change description CAP, Issue 1 CAP Issue 2 C.P First Issue General revision of CAP Issue 1 dated General revision of CAP Issue 2 dated , reformatted i.a.w. EASA QMS documentation rules Related documents affected by new issue CAP Issue 2 partially amends CAP Issue 1 dated repeals and replaces Internal Working CAP Issue 2 dated Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 7 of 42

8 3. LEGAL FRAMEWORK In accordance with article 15 (1) of the Basic Regulation, the Agency shall, where applicable and as specified in the Chicago Convention or its Annexes, carry out on behalf of EU Member States the functions and tasks of the State of Design (SoD), manufacture or registry when related to design approval. The issuance of Type Certificates (TC) and changes thereto, and European Technical Standard Order Authorisations (ETSOA) is a fundamental part of the materialisation of this principle. According to subparagraph (j) of article 15 (1) of the Basic Regulation, the Agency shall also ensure the continuing airworthiness functions associated with the products, parts and appliances it has certified, including reacting without undue delay to a safety problem and issuing the applicable mandatory information, i.e. Airworthiness Directives (ADs). The continuing airworthiness functions shall be performed in accordance with the provisions of Annex I of the Basic Regulation and Annex Part 21, paragraphs 21A.3 and 21A.3B of Commission Regulation (EC) 1702/2003 of 24 September 2003 laying down implementing rules for the airworthiness and environmental certification of aircraft and related products, parts and appliances and the related Acceptable Means of Compliance ( AMC ) and Guidance Material ( GM ). According to Articles 44 (1) and 13 (c) of the Basic Regulation, the EASA Management Board shall establish transparent procedures for taking individual decisions for airworthiness and environmental certification. Under these provisions, the Management Board has adopted Decision 12/2007 of 01 October 2007 concerning the general principles related to the certification procedures to be applied by the Agency for the issuance of certificates for products, parts and appliances (hereinafter referred to as PCP Decision ). The objective of the PCP Decision is to establish the general principles to be followed by the Agency to perform environmental and airworthiness certification of aeronautical products, parts and appliances, including post certification activities, in accordance with the applicable implementing rules of the Basic Regulation, according to Article 1(1). Article 15 of the PCP Decision mandates the Executive Director to establish the necessary associated detailed procedures for the implementation of this Decision [ ]. Decision 2005/04/ADM of the Executive Director of the Agency of 3 March 2005 on the delegation of powers of the Executive Director to certain staff members of the Certification Directorate to take decisions for the application of Articles 15 of the Basic Regulation as specified in Article 13(c) of the Basic Regulation [ ]. This procedure has been adopted by the Certification Director under this mandate. Rights and obligations derived from applicable bilateral agreements as specified in Article 9 of the Basic Regulation shall not be affected. This procedure shall be followed in order to achieve standardised processes within the Agency. Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 8 of 42

9 4. BASIC PRINCIPLES FOR CONTINUING AIRWORTHINESS ACTIVITIES 4.1 General It is the obligation of the Certificate Holder to collect and review all available information related to the safety of the type design in order to take appropriate and on time action to correct any potential unsafe condition. Data relevant for assessing the continuing airworthiness of an approved type design may derive from regular type design reviews, mandatory occurrence and event reporting, accident or incident investigations, information collected by aviation authorities or any other sources. 4.2 Occurrence Reporting: In accordance with AMC 20-8 (Reference Decision 12/2003 of 5 vember 2003 of the Executive Director on general acceptable means of compliance for airworthiness of products, parts and appliances AMC-20 ), in general terms, an occurrence needs to be reported if the event has resulted, or may result in an unsafe condition. EASA Form 44 may be used for this purpose. t all reportable events generated by AMC 20-8 need to be investigated by EASA. This procedure is applicable only to reportable events linked to design, having an implication upon the certification or maintenance aspects of aircraft, products, parts and appliances Maintenance Organisation Responsibilities In accordance with Part 145.A.60, the approved maintenance organisation is responsible for reporting occurrences discovered during performance of maintenance tasks to its competent authority (authority which has the oversight responsibility for the approved maintenance organisation), the State of Registry (SoR), the TC holder and the operator Owner/Operator Responsibilities In accordance with JAR-OPS 1 and (b) & (c), the operator is responsible for reporting to the State of Operator, events occurring during operations, and when the defect may have an impact on the continuing airworthiness of the aircraft type, to the organisation responsible for the design, or if applicable, the organisation responsible for continued airworthiness. In accordance with Part M.A.202, faults discovered during maintenance shall be reported to the TC/STC holder, SoR and/or State of Operator Certificate Holder Responsibilities The Certificate Holder shall have a system to collect and analyse the data related to reportable occurrences. This system shall be made available to all operators of the product. The Certificate Holder shall carry out an analysis of the data received, and if a potentially hazardous or possible unsafe condition is identified, report all such occurrences to the EASA PCM. If applicable the Certificate Holder shall carry out an investigation, according to the criteria of Part 21A.3 (c). Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 9 of 42

10 tes: 1. AMC 20-8 and Part 21A.3 (b) identify that such reports should be made within 72 hours of the identification of a potentially hazardous or possible unsafe condition. EASA Form 44 may be used for this purpose. 2. For products where EASA is not the Primary Certificating Authority (PCA), reporting shall be in accordance with the appropriate Working Arrangement/Bilateral agreement NAA Responsibilities In accordance with Part 21B.45, each National Aviation Authority (NAA) shall ensure transmission of information related to occurrences which have been shown to result or could potentially result in an unsafe condition to EASA, to ensure appropriate exchange of information relevant for safety. Part 21A.3 and AMC 20-8 provide criteria for the assessment of occurrences and the need for reporting to EASA. When urgent action is considered necessary due to the potential safety impact of an occurrence the NAA of the SoR shall urgently contact EASA. Furthermore, following part 21B.60 the NAA shall transfer any received foreign AD to EASA EASA Responsibilities Where EASA is the PCA and consequently carries out on behalf of EU Member States the functions and tasks of the State of Design (SoD), when related to design approval, the EASA PCM shall, based on analysis and investigations by the Certificate Holder or based on any other information, define appropriate actions. The subsequent action may range from recommendation for improvements by the Certificate Holder to corrective action (inspection, maintenance action or design change) that needs to be made mandatory by the issue of an Airworthiness Directive (AD). The criteria for issuance of an AD are defined in 21A.3B and associated AMC material. Where EASA is not the PCA and consequently carries out on behalf of EU Member States the functions and tasks of the State of Registry (SoR) the EASA PCM shall, in accordance with the procedures contained in the appropriate Working Arrangement/Bilateral Agreement, review occurrences as reported. Where a safety concern exists, the EASA PCM shall contact the PCA to ensure their awareness of the potential for an unsafe condition and to establish their expected action. Based on the PCA response, the EASA PCM shall decide whether further EASA action is necessary. The EASA PCM, if necessary in consultation with his/her team, should decide upon the acceptability of any proposed solution, and monitor that corrective action shall be developed and published by the Certificate Holder and approved by the PCA in a time frame acceptable to EASA. When EASA, after consultation with the PCA, is not satisfied with the actions taken by the PCA or deems necessary to deviate from the airworthiness directive issued by the PCA, an EASA AD may be issued. This AD may either (1) replace or modify an existing PCA AD or (2) be issued in the absence of a PCA AD, as necessary, to ensure that corrective actions are taken which address the issue in a manner consistent with EASA regulations. The normal process as Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 10 of 42

11 described in Chapter 5.1 below should be followed, unless an urgent action is needed (see Article 12 of MB Decision 12/2007 of 01 October 2007). Irrespective of the above and in accordance with Article 11 of the Basic Regulation, EASA and NAA shall exchange any safety related information available to them, including maintenance and operations related issues, with all Member States and other affected parties as appropriate in order to put them into a position to take adequate measures. Chapter 7 concerning the issuance of Safety Information Bulletins (SIB) also pertains to this subject. te: Given the fact that an airworthiness directive is defined in Commission Regulation (EC) 1702/2003 Part 21A.3B2, only the Agency can issue ADs proper in the European Union. As a result, for non-design related issues, NAAs should preferably issue their mandatory measure, if the recommendation is adopted, under another publication name than AD. 4.3 Recommendations from Accident Investigation Authorities EASA maintains a tracking system to record status of safety recommendations addressed to the Agency and their closing actions in a database. te: The database should be the means by which feedback is provided to the Accident Investigation Organisations regarding the EASA status and closure of Safety Recommendations arising from reported Accidents and Serious Incidents. Reference is made to E.P001 for the coordination of responses to recommendations resulting from accidents and serious incidents. 4.4 Other Continuing Airworthiness Activities The analysis of available occurrence reporting databases (e.g. those based on Directive 2003/42/EC of the European Parliament and of the Council of 13 June 2003), safety related recommendations by NAAs, actions by EU Member States under Art 10.1 of the Basic Regulation and any other information coming from any person or organisation may be considered to ensure the continuing airworthiness of products, parts and appliances. In addition, the PCM shall organise regular airworthiness review meetings in order to permanently monitor the continuing airworthiness of products, parts and appliances under his/her (team) responsibility. 4.5 Corrective Actions Continuing airworthiness activities as described above may result in the need for corrective actions for certified products, parts and appliances. It is recommended that every effort should be made to define actions that terminate repetitive inspections or tests. When EASA is the PCA for the product, part or appliance, and therefore assumes the EU Member States obligations as SoD, it shall issue an AD whenever it is necessary to correct an unsafe situation related to an aircraft design. EASA will notify by , followed by regular mail the AD to its addressee, the Certificate Holder, in the English language or, when requested, in the language of the EU Member State which has jurisdiction over it. 2 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. Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 11 of 42

12 Moreover EASA shall, to fulfil obligations deriving from ICAO SARPs, transmit the information to all the Contracting States that have informed EASA that an aircraft subject to that AD has been entered on their registry (including EU Member States), to allow those States to fulfil their obligations as SoR. The information will be transmitted by in the English language. When EASA is not the PCA for the product, part or appliance, and, therefore only assumes the EU Member States obligations as SoR when related to design approval. It shall upon receipt of information that an AD has been issued by the SoD of an aircraft that has entered the registry of one of the EU Member States, either adopt the AD without any changes or issue its own AD based on the SoD AD (Reference ED Decision 02/2003). In the case of adoption of a foreign AD without any changes a simplified process shall apply as described in Chapter 5.5 Process for Adoption of Foreign AD. When EASA issues its own AD, it will notify the AD by , followed by regular mail to its addressee, the foreign TC/STC holder, in the English language. Moreover, EASA shall, to fulfil obligations deriving from ICAO SARPs inform the SoD and the EU Member States on the content of the issued AD to allow them to fulfil their obligations as SoR, enforcing the AD. The information will be transmitted by in the English language. As soon as EASA has issued and distributed an AD, EU Member States shall inform their operators and owners of the affected aircraft that they have to comply with the AD as it derives from their obligations under Part M (Commission Regulation (EC). 2042/2003 Annex 1). Community operators will then have to contact, if needed, the type approval holder to obtain all the necessary information to comply with the AD concerned. All these EASA notification and information obligations shall be carried out according to the procedures described in MB Decision 12/2007 of 01 October Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 12 of 42

13 5. AIRWORTHINESS DIRECTIVE PROCESSES This Chapter contains 5 flowcharts: 5.1 Standard process for Issuing Airworthiness Directives (AD) 5.2 Process for Final AD with Request for Comments (Consultation) 5.3 Process for Emergency ADs 5.4 Process for Changes to Previously Issued ADs 5.5 Process for Adoption of Foreign ADs Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 13 of 42

14 5.1 Standard Process for Issuing ADs Process Chart Start (010) Determination of existence of an unsafe condition [EASA/C] (020) Request Certificate Holder to propose corrective action [PCM] (030) Step te Link AD Airworthiness Directive 010 CM Certification Manager CRD Comment Response Document MS Member State (EU) 020 PAD Proposed Airworthiness Directive PCA Primary Certification Authority PCM Project Certification Manager SoR State of Registry 030 SoD State of Design Rev Receipt of proposal from Certificate Holder and relevant supporting documents and request for review [PCM] (040) 040 From Chapter 5.2 step 070 proposal + supporting documents Review proposal and draft PAD in consultation with his team member(s), agree on draft PAD with Certificate Holder [PCM] (050) PAD draft Agreement on draft PAD? [PCM-certificate holder] (060) 060 Raise the issue to EASA CM for final decision [PCM] (070) 070 Involve Panel of Experts if necessary, take decision and communicate decision to Certificate Holder [CM/PCM] (080) 080 Amend draft PAD as required by CM, forward PAD + supporting documents to AD Section [PCM] (090) PAD draft 2 & supporting documents 090 C.I007 Review PAD for language, standardisation and consistency, make changes as appropriate and submit to PCM for acceptance [AD Section] (100) PAD draft C.I007 Final draft PAD accepted [PCM] (110)? 110 Provide instructions on PAD review to AD Section [PCM] (120) 120 Publish PAD for consultation on EASA official website [AD Section] (130) PAD version Submit comments [Interested parties] (140) comments on PAD 140 Collect comments and format in draft CRD, submit to PCM [AD Section] (150) 150 draft CRD on PAD (EASA Form 115) Review comments and provide responses, consult with Certificate Holder, amend PAD as appropriate, submit PAD to AD Section [PCM] (160) draft CRD on PAD with responses / PAD version A Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 14 of 42

15 5.1.1 Process Chart, continued A Step te Link Rev Format PAD into AD, allocate number, and send to PCM for final review and approval [AD Section] (170) draft AD 170 Final draft AD approved [PCM] (180)? 180 Sign Technical Visa and collect additional info from Certificate Holder and send draft AD to CM for final review and approval [PCM](200) Technical Visa (EASA Form 113) Provide instructions on changes to draft AD to AD Section [PCM] (190) AD approved [CM] (210)? 210 Provide instructions on changes to draft AD to AD Section [CM] (220) 220 Sign AD [CM] (230) 230 EASA AD From Chapter 5.2 step 180 From Chapter 5.3 step 150 Prepare AD distribution [AD Section] (250) tify AD to Certificate Holder by , followed by regular mail [AD Section] (240) 240 AD notification , followed by regular mail 250 Is EASA the PCA? [AD Section ] (260)? 260 Distribute AD to SoR / Contracting State/EU MS [AD Section] (270) AD distribution Distribute AD to SoD / EU MS [AD Section] (280) AD distribution Manage publication of AD on official EASA website \\ [AD Section] (290) 290 Archive all relevant documents related to the AD published [AD Section] (300) AD archives file 300 C.I009 End (310) 310 Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 15 of 42

16 5.1.2 Process Steps Description for Standard Process for Issuing ADs 010 Start of the Standard AD process 020 Definition and determination of an unsafe condition : Ref. AMC 21A.3B(b) and GM 21A.3B(b) 030 When EASA has determined that an unsafe condition exists in an approved aircraft type design, as a result of a deficiency in the aircraft, or an engine, propeller, part or appliance installed on this aircraft, and that condition is likely to exist or develop in other aircraft, the EASA PCM of the affected product (aircraft, engine or propeller) shall request the Certificate Holder to propose appropriate corrective actions for EASA approval. 040 Details of these proposals shall be submitted by the Certificate Holder to the EASA PCM, including all the relevant technical publications, e.g. Service Bulletins, All Operator Telex, etc. If the unsafe condition is related to an ETSO article installed (or eligible to be installed) on an aircraft, coordination between the aircraft PCM and the Certification Manager Parts and Appliances (CM P&A) should take place for possible equipment AD issuance. In such case the AD shall affect the aircraft where the part or appliance is installed. 050 The EASA PCM, in consultation with his/her team shall review the proposed corrective action submitted by the Certificate Holder and shall then draft a PAD using standard EASA Form 112. Early involvement of the EASA AD Section in the drafting process is desirable for standardisation purposes. If deemed necessary by the EASA PCM, further co-ordination with the Certificate Holder and, in case of non EU products, the PCA may take place In case of disagreement between the EASA PCM and the Certificate Holder on the draft PAD, the EASA PCM shall raise the issue to the CM for final decision. 080 The CM may decide to consult the Panel of Experts and seek its advice. Based on the opinion of the Panel of Experts, final decision will be taken by the CM. The PCM will inform the Certificate Holder in writing ( or regular mail) on the decision taken 090 Following the decision of the CM, the PCM may amend the draft PAD, if deemed necessary. In the absence of any proposal from the Certificate Holder or if the Certificate Holder is not willing to sufficiently co-operate, the PCM shall draft an own PAD. The final version of the PAD, together with the referenced [approved and published] technical publication(s) as supplied by the Certificate Holder, shall be sent to the EASA Airworthiness Directive Section (AD Section) for further processing. 100 Once the AD Section receives a PAD, the format will be reviewed for use of language, standardisation and consistency of wording The AD Section shall then publish the PAD for consultation on the EASA official publication (EASA website). The comment period shall be in principle one month, but shall never be less than 2 weeks. If deemed necessary, the EASA PCM may decide to modify this period in accordance with the importance of the PAD. 140 Comments shall be sent to the AD Section. Address and contact information shall be published on the EASA official publication (EASA website). 150 The AD Section shall collect all comments received. After collecting and formatting in a draft Comment Response Document (CRD, EASA Form 115), those comments shall be sent to the EASA PCM. 160 The EASA PCM shall review the comments received and shall produce appropriate responses in the CRD. The Panel of Experts may be consulted where appropriate. The EASA PCM shall inform the CM and the AD Section when consultation with the Panel of Experts has been sought. The EASA PCM shall amend the PAD as required, in co-ordination with the Certificate Holder. Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 16 of 42

17 160 (Ctd.) Process Steps Description for Standard Process for Issuing ADs, continued In normal circumstances, the time between the start of the consultation process and issuance of the AD should not last more than two months. 170 The AD Section shall format the PAD into the AD Format, allocate the AD number (see EASA Form 110) and send it to the CM for final review and approval The PCM is finally responsible to agree with any change suggested/proposed by the AD Section, to sign a Technical Visa (see EASA Form 113) and to collect from the Certificate Holder any information which could be eventually requested by other CAAs, e.g. the number of a/c worldwide needing corrective action; a statement on the availability of parts; an estimate of the number of labour hours; and the cost of parts required for the corrective action. 210 The CM shall review and approve the final AD in coordination with the EASA PCM With signature by the CM, the PAD turns into an EASA AD. The effective date of a standard AD shall be no less than 14 days after the issue date, which is also the date it is published on the EASA official publication (EASA website), see step 290. However, if it is deemed necessary, the PCM may request a different effective date. 240 The AD Section will notify the AD by , followed by regular mail to the Certificate Holder. A reference to the possibility for appeal as specified in Articles 35 to 41 of the Basic Regulation shall be included. 250 In addition to the above notification to the Certificate Holder, the AD Section shall send the information on published EASA ADs (aircraft, engines, propellers, parts and appliances installed on aircraft) by , depending on whether EASA is the PCA Where EASA is PCA, information on the AD, in accordance with 4.3.2, Chapter 4 of Part II of Annex 8 to the Chicago Convention, shall be sent to: (a) Any SoR who, in accordance with Chapter of Part II of ICAO Annex 8, has advised the SoD that it has entered the aircraft on its register (if this notification has been made to the EU SoD, the latter has to inform the Agency); and (b) Any other ICAO Contracting State on request (if this notification has been made to the EU SoD, the latter has to inform the Agency); and (c) The EU Member States to allow them to fulfil their obligations as SoR, enforcing the AD. te: In the case that there is any other suitable mean of notifying, found to be more convenient and effective than the system, EASA may decide to use it. The system will be used as the normal system. 280 Where EASA is not PCA, information on ADs shall be sent to: (a) The SoD in accordance with Chapter of Part II of Annex 8 to the Chicago Convention; and (b) The EU Member States to allow them to fulfil their obligations as SoR, enforcing the AD. An electronic receipt should be requested by the AD Section, from the recipient States. te: In the case that there is any other suitable mean of notifying, found to be more convenient and effective than the system, EASA may decide to use it. The system will be used as the normal system. Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 17 of 42

18 5.1.2 Process Steps Description for Standard Process for Issuing ADs, continued 290 The AD Section shall manage the publication of the approved AD in the EASA Official Publication (EASA website for AD: For adoption of Foreign ADs refer to Chapter 5.5 of this procedure. Additional automatic notification: When available, auto notification to any registered users shall be generated with the uploading of the AD on the EASA Official Publication (EASA website), drawing the attention of the recipients to the new uploaded AD. 300 Record keeping and archiving is ensured as defined in work instruction C.I End of Standard Process for Issuing an ADs. Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 18 of 42

19 5.2 Process for Final AD with Request for Comments (Consultation) Process Chart Start (010) Determination of situation requiring immediate action [EASA] (020) Request Certificate Holder to propose corrective action [PCM] (030) Step te Link AD Airworthiness Directive 010 CM Certification Manager CRD Comment Response Document MS Member State (EU) 020 PAD Proposed Airworthiness Directive PCA Primary Certification Authority PCM Project Certification Manager SoD State of Design 030 SoR State of Registry Rev Receipt of proposal from Certificate Holder and relevant supporting documents and request for review [PCM] (040) 040 Assess compliance time and need for immediate action [PCM] (050) Proposal + supporting documents 050 Need for "Emergency AD" confirmed? [PCM] (060) 060 From Chapter 5.3 step 060 Go to Chapter 5.3 step 070 Need for "Final AD with Request for Comments (Consultation)"? [PCM] (070) 070 Go to Chapter 5.1 step 050 Prepare justification and reasons for issuing "Final AD with Request for Comments (Consultation)" [PCM] (080) Justification for "Final AD with Request for Comments (Consultation)" Review proposal and draft a PAD, agree on draft PAD with Certificate Holder, forward to AD Section, together with justification for "Final AD with Request for Comments (Consultation)" [PCM] (090) PAD draft 1 + justification for "Final AD with Request for Comments (Consultation)" C.I007 Review PAD for language, standardisation and consistency, make changes as appropriate [AD Section] (100) 100 C.I007 PAD draft 2 Format PAD into "Final AD with Request for Comments (Consultation)", allocate number, and send to PCM for review and approval [AD Section] (110) draft AD (EASA Form 110) 110 Sign Technical Visa and collect additional info from Certificate Holder and send draft "Final AD with Request for Comments (Consultation)" to CM for final review and approval [PCM](140) Technical Visa (EASA Form 113) Final draft of "Final AD with Request for Comments (Consultation)" approved? [PCM] (120) Provide instructions on changes to draft AD to AD Section [CM] (130) AD approved? [CM] (150) 150 Provide instructions on changes to draft AD to AD Section [CM] (160) 160 Sign "Final AD with Request for Comments (Consultation)" [CM] (170) EASA "Final AD with Request for Comments (Consultation)" (EASA Form 110) 170 Launch immediate notification, distribution and publication of "Final AD with Request for Comments (Consultation)" [AD Section] (180) 180 Go to Chapter 5.1 step 240 and 250 Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 19 of 42

20 5.2.2 Process Steps Description for Final AD with Request for Comments (Consultation) 010 Start of the Final AD with Request for Comments (Consultation) process. 020 According to Article 12.5 of the PCP Decision such a case exists where a prior publication for comments would make timely compliance with the corrective actions impossible, or where the substance of an Airworthiness Directive has been previously subject to a national Airworthiness Directive. 030 The EASA PCM of the affected product shall request the Certificate Holder to propose appropriate corrective actions for EASA approval In case of situations which require immediate action by EASA, the EASA PCM shall review the proposed corrective action submitted by the Certificate Holder. Depending on the agreed compliance time, the EASA PCM shall assess if a Proposed AD (publication delayed by consultation period), a Final AD with Request for Comments (Consultation) (consultation period after the AD issuance) or Process for Emergency ADs (short compliance time, e.g. before next flight or within 30 calendar days after the [planned] effective date) is appropriate If the proposed compliance time frame is too short to allow an adequate public consultation period (e.g. within 60 days) but not urgent enough to qualify for an Emergency AD, a Final AD with Request for Comments (Consultation) may be issued. In these cases, the EASA PCM will decide not to implement a consultation process prior to AD issuance. A justification explaining why the consultation process shall not be followed and the reasons for issuing a Final AD with Request for Comments (Consultation) shall be provided in the text of the AD, under the item (17) Remarks (see EASA Form 110). 090 The EASA PCM shall then draft the AD in co-ordination with the Certificate Holder. Early involvement of the EASA AD Section in the drafting process is desirable for standardisation purposes. As the AD requires immediate notification and publication, the EASA PCM shall send the draft AD to the AD Section as soon as possible, in conjunction with the referred assessment, for immediate processing, approval and publication on the EASA Official Publication (EASA website). 100 Once the AD Section receives a draft AD, the format will be reviewed for use of language, standardisation and consistency of wording. 110 The AD Section shall format the final draft into the AD Format, allocate the AD number (see EASA Form 110) and send it to the CM for final review and approval The PCM is finally responsible to agree with any change suggested/proposed by the AD Section, to sign a Technical Visa (see EASA Form 113) and to collect from the Certificate Holder any information which could be eventually requested by other CAAs, e.g. the number of a/c worldwide needing corrective action; a statement on the availability of parts; an estimate of the number of labour hours; and the cost of parts required for the corrective action Approval of the Final AD with Request for Comments (Consultation) by the CM follows the same rules as defined in Chapter 5.1 Standard Process for Issuing ADs steps 180 to 230. Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 20 of 42

21 5.2.2 Process Steps Description for Final AD with Request for Comments (Consultation), continued 180 After approval by the CM, the AD Section shall launch the immediate notification, distribution and publication of Final AD with Request for Comments (Consultation), following the same provisions as defined under Chapter 5.1 Standard Process for Issuing ADs steps 240 to 290. Record keeping and archiving is ensured as defined in work instruction C.I009. Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 21 of 42

22 5.3 Process for Emergency ADs Process Chart Start (010) Determination of situation requiring emergency action [EASA] (020) Request Certificate Holder to propose corrective action [PCM] (030) Step te Link AD Airworthiness Directive 010 CM Certification Manager CRD Comment Response Document EAD Emergency AD 020 MS Member State (EU) PAD Proposed Airworthiness Directive PCA Primary Certification Authority PCM Project Certification Manager 030 SoD State of Design SoR State of Registry Rev Receipt of proposal from Certificate Holder and relevant supporting documents and request for review [PCM] (040) Assess compliance time and need for emergency action [PCM] (050) proposal + supporting documents EAD Need for EAD confirmed? [PCM] (060) AD or "Final AD with Request for Comments (Consultation)" 060 From Chapter 5.2 step 060 Go to Chapter 5.2 step 070 Prepare justification and reasons for issuing EAD, draft EAD in consultation with Certificate Holder, forward to AD Section [PCM] (070) 070 C.I007 EAD draft 1 (EASA Form 113) Review EAD for language, standardisation and consistency, make changes as appropriate, allocate number, and send to PCM for review and approval [AD Section] (080) Emergency AD draft C.I007 Sign Technical Visa, collect additional info from Certificate Holder and send EAD to CM for review and approval [PCM] (110) Technical Visa (EASA Form 113) Draft EAD approved? [PCM] (090) Provide instructions on changes to draft EAD to AD Section [PCM] (100) EAD approved? [CM] (120) 120 Provide instructions on changes to draft EAD to AD Section [CM] (130) 130 Sign EAD [CM] (140) EAD, final 140 Launch immediate notification, distribution and publication of EAD [AD Section] (150) 150 Go to Chapter 5.1 step 240 and 250 Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 22 of 42

23 5.3.2 Process Steps Description for Emergency ADs 010 Start of the Emergency AD process. 020 According to Article 12.7 of the PCP Decision such a case exists where the Agency has determined that urgent action is necessary to correct an unsafe condition. 030 The EASA PCM of the affected product shall request the Certificate Holder to propose appropriate corrective actions for EASA approval In case of situations which require emergency action by EASA the EASA PCM shall review the proposed corrective action submitted by the Certificate Holder. Based on the agreed compliance time (e.g. before next flight or within 30 calendar days after the [planned] effective date), the EASA PCM shall assess if an Emergency AD is appropriate, using EASA Form The EASA PCM shall then draft the Emergency AD in co-ordination with the Certificate Holder, if available. In these cases, the EASA PCM will decide not to implement any consultation process. A justification explaining why the consultation process shall not be followed and the reasons for issuing an Emergency AD shall be provided in the text of the draft Emergency AD, under the item (14) Reason. Early involvement of the EASA AD Section in the drafting process is desirable for standardisation purposes. As an Emergency AD requires immediate notification and publication, the EASA PCM shall send the final draft of the Emergency AD to the AD Section as soon as possible, in conjunction with the referred assessment, for immediate processing, approval and publication on the EASA Official Publication (EASA website). 080 Once the AD Section receives a draft Emergency AD, the format will be reviewed for use of language, standardisation and consistency of wording. The AD Section shall allocate the Emergency AD number (EASA Form 111) and send it to the CM for final review and approval The PCM is finally responsible to agree with any change suggested/proposed by the AD Section, to sign a Technical Visa (see EASA Form 113) and to collect from the Certificate Holder any information which could be eventually requested by other CAAs, e.g. the number of a/c worldwide needing corrective action; a statement on the availability of parts; an estimate of the number of labour hours; and the cost of parts required for the corrective action Approval of the Emergency AD by the CM follows the same rules as defined in Chapter 5.1 Standard Process for Issuing ADs steps 180 to After approval of the Emergency AD by the CM, the AD Section shall ensure notification, distribution and publication of the Emergency AD, following the same provisions as defined under Chapter 5.1 Standard Process for Issuing ADs steps 240 to 290, but with urgent application. The AD Section shall notify the Certificate Holder immediately by followed by regular mail of the issuance of Emergency ADs. The effective date of the Emergency AD shall be not less than two working days after the issue date of the Emergency AD, which is also the date it is published on the EASA official publication (EASA website) unless otherwise specified in the AD itself. This is to allow sufficient time for the receiving NAAs (States of Registry) to distribute the Emergency AD to the owners and operators of the affected aircraft. Record keeping and archiving is ensured as defined in work instruction C.I009. Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 23 of 42

24 5.4 Process for Changes to Previously Issued ADs Process Chart Start (010) Assess type of action on AD to be implemented [PCM] (020) Step te Link AD Airworthiness Directive 010 CM Certification Manager PCM Project Certification Manager 020 Rev CHANGE Assess type of change on AD to be implemented [PCM] (040) Need for AD cancellation? [PCM] (030) CANCELLATION Carry out AD cancellation process [PCM/AD Section] (050) SUBSTANTIVE CHANGE Is it a substantive NON -SUBSTANTIVE CHANGE 060 change? [PCM] (060) Assess whether change affects substance of AD [PCM] (070) 070 Classify as correction and perform correction process [PCM/AD Section] (080) 080 SUPERSEDURE Need for superseding AD? [PCM] (090) REVISION Classify as supersedure and perform supersedure process [PCM] (100) Classify as revision and perform revision process [PCM/AD Section] (110) Archive all relevant documents related to the change to the AD [AD Section] (120) 120 C.I009 End (130) 130 Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 24 of 42

25 5.4.2 Process Steps Description for Changes to Previously Issued ADs 010 Start of the Changes to Previously Issued AD process. 020 Already issued and valid ADs may be subject to 4 different types of measures affecting their content or validity: Cancellation Correction Revision Supersedure. The cancellation is the withdrawal, i.e. complete revocation of an AD without replacement. In case of correction, supersedure or revision, the previously published AD will be either amended (correction & revision) or cancelled and replaced by a new AD (supersedure). The simplest form of an AD non-substantive change is a corrected AD, i.e. the change has no effect on compliance with the AD. An AD may require correction of a typographical error. Any change that shall be tracked (i.e. affects compliance with the AD) shall be issued as a revision or superseding AD. The most common reasons for changing a previously issued Airworthiness Directive and the type of Airworthiness Directive action that should be considered are listed in the table below: Type of Change Revision Supersedure Correction n-substantive correction X Additional Requirement* X Expanded applicability* X Reduced compliance time* X Additional inspection(s)* X Mandatory terminating action* X Reduced applicability**+ X Extended compliance time**+ X Optional inspection method**+ X Optional terminating action**+ X Substantive correction - impossible+ X Substantive correction - possible+ X * Any Airworthiness Directive that imposes a new requirement is issued as a superseding AD, even if other portions of the Airworthiness Directive are considered relieving. ** A relieving Airworthiness Directive should be issued as a revision. + If it is impossible to comply with an original Airworthiness Directive as in the case of a non-existent part number, the new Airworthiness Directive may be issued as a revision. If it is possible to comply with an original Airworthiness Directive, as in the case of an existing but incorrect part number, the Airworthiness Directive is issued as a superseding AD. 030 In some cases, information becomes available to the Certificate Holder (and subsequently to the EASA PCM) that the requirement contained in an AD is no longer appropriate. Either the problem identified and addressed by the AD does not, in fact, constitute an unsafe condition, or the required actions do not address the problem adequately (enough), could actually exacerbate the problem and/or more investigation is needed. Any of these situations could lead the PCM to decide to withdraw the requirement, without having available sufficient information to supersede this with a new requirement (i.e. a superseding AD). 040 If changes to previously issued ADs are deemed necessary by the Agency, if necessary after consultation with the relevant Certificate Holder, these changes shall be issued as corrections or revisions to the original AD depending on the nature of the material being changed. In addition, ADs may be superseded by new ADs depending on the nature of the material being changed. Although this information is presented in terms of final ADs, it may be used for public consultation. Table of step 020 must be used to determine what type of change is being carried out, thus determining the type of document to be issued. When using the table or the information contained in this section, there are three considerations to bear in mind: Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 25 of 42

26 5.4.2 Process Steps Description for Changes to Previously Issued ADs, continued 040 Ctd.) (a) The first is whether the AD is to be changed because of an editorial or typographical error; e.g., the published document was wrong and the change is classified as a correction. If the AD was correct as published but then has to be changed, this is classified as a revision or supersedure. (b) The second consideration is whether the information is substantive or nonsubstantive; that is, whether it affects the substance of the AD. (c) The final consideration is the effect the change will have on the AD system and on the owners/operators affected by the AD. Issuance of corrected, revised or superseding ADs for aircraft, engines, propellers or parts and appliances installed on aircraft shall be processed by the AD Section, following the provisions of Chapter Standard Process for Issuing ADs steps 240 to Cancellation of an AD : The EASA PCM shall asses in coordination with the Certificate Holder, if the AD should be withdrawn and shall draft the proposed AD Cancellation tice [EASA Form 116] to the AD Section. Keep the following in mind for withdrawal of an AD: - check whether the AD being withdrawn mentions or affects another AD in the system - be sure that withdrawal of the AD will not leave an unsafe conditions unresolved.. The standard procedure is to issue the proposed cancellation as a PAD, soliciting public comment to ensure that the removal will not cause unanticipated problems by reinstating a former rule on an operator. The PCM may also propose to the CM (through the AD Section) an AD cancellation to be immediately effective, if deemed appropriate. ADs issued by EU Member States, in accordance with their respective national numbering systems before 28 September 2003 in their role of State of Design Authority or issued after 28 September 2003 and approved by EASA, that need withdrawal/cancellation, shall be cancelled by an EASA AD Cancellation tice (EASA Form 116). An AD Cancellation tice retains the original AD number with the addition of -CN, e.g.: CN. 070 Does the change affect the substance of the AD (e.g. new requirement, change in applicability, change in compliance time)? 080 Correction of an AD: If a non-substantive error is discovered in an AD before it is placed on the EASA web, it may be recalled for correction. Anyone who thinks that there is a non-substantive error in a published AD should contact the AD Section in order to advise. The AD Section shall review the supposed error in the AD in coordination with the EASA PCM, if necessary. In cases where (e.g.) a typographical error must be corrected, the PCM need not be involved. After agreement of the PCM, the AD Section shall publish the corrected AD, following the provisions of Chapter Standard Process for Issuing ADs steps 240 to 290. As the change to the AD is non-substantive, no CM approval is required. If a non-substantive error in a PAD is discovered after the document is on the EASA web for public consultation, but before it has been finally adopted and published as AD, the AD Section should be alerted to either: (a) Cancel the publication. The document can only be removed from public display when a statement from the PCM indicating the reasons for withdrawing the document is received by the AD Section. (b) Keep the consultation process, but putting on display a correction document, explaining the corrections made in the PAD. The AD Section shall decide, in coordination with the PCM, on one of the two above options. Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 26 of 42

27 5.4.2 Process Steps Description for Changes to Previously Issued ADs, continued 080 (Ctd) If a non-substantive error is discovered in the published version of the AD, the AD Section shall determine, in coordination with the EASA PCM if necessary, whether it was an error submitted by the PCM in the original document or an editorial or typographical error that occurred at the AD Section. If the error was in the original document submitted by the PCM, then the PCM shall review, propose and send the corrected AD to the AD Section. The AD Section shall publish the corrected AD, following the provisions of Chapter 5.1 Standard Process for Issuing ADs steps 240 to 290. If the error was an editorial or typographical error that occurred at the AD Section, then the AD Section shall review, correct and submit to the PCM for endorsement. Then the AD Section shall publish the corrected AD, following the provisions of Chapter 5.1 Standard Process for Issuing ADs steps 240 to 290. As in both cases the change to the AD is non-substantive, no CM approval is required. te 1: An explanation for the corrected AD shall be provided in the AD itself under item (14) Reason. The correction content shall also be provided where appropriate. te 2: A corrected AD does not get a new AD number. This is the reason why corrections are limited to non-substantive errors. Any change that shall be tracked (i.e., affects compliance with the AD) shall be issued as a revision or superseding AD. Correction of a substantive error shall be issued as either a superseding AD or a revision. 090 In most instances, supersedure requires additional operator record keeping may not be warranted by the nature of the change to an AD. The table defined in step 020 shows the type of changes where an AD revision may be appropriate. However, if the new AD imposes new requirements (ref. table of step 020), it shall be issued as a superseding AD even if it otherwise meets the criteria described step 110. ADs issued by EU Member States, in accordance with their respective national numbering systems before 28 September 2003 in their role of State of Design Authority or issued after 28 September 2003 and approved by EASA, that need correction or revision, shall be superseded by a new EASA AD with the following statement to be added Aircraft already compliant with EU Member State AD, no further action is required by this EASA AD. 100 Supersedure : With a few notable exceptions, a substantive change to an AD should be issued as a superseding AD. Substantive changes, including corrections, are those made to any instruction or reference that affects the substance of the AD. Substantive changes may affect part numbers, service bulletin and manual references, compliance time, applicability, methods of compliance, corrective action, inspection requirements, and effective dates. In general, whenever there is an additional (or different) requirement imposed or an expanded scope of required inspection, the change must be issued as a superseding AD. Substantive changes to an AD should be assessed by the EASA PCM in coordination with the Certificate Holder, and properly reported to the CM through the AD Section. The following steps have to be followed: If an error occurs in an AD, then: (a) The EASA PCM shall assess in coordination with the Certificate Holder if it is possible to comply with the AD as published. If so, he shall inform the CM through the AD Section and a superseding AD should be submitted by the EASA PCM to the AD Section. Additionally, the EASA PCM shall asses if the superseding AD should be a PAD, a Final AD with request for comments (consultation) or Emergency AD and shall send the relevant EASA Form 113 to the AD Section. The EASA PCM shall send the draft AD immediately to the AD Section for approval and publication. Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 27 of 42

28 5.4.2 Process Steps Description for Changes to Previously Issued ADs, continued 100 (Ctd.) The following steps have to be followed: If an error occurs in an AD, then: The reason paragraph should include a discussion of each change, how each change affects compliance, and the fact that all other parts of the AD remain as originally published. (b) If the EASA PCM assesses (in coordination with the Certificate Holder) that it is IMPOSSIBLE to comply with the AD as published (such as the publication of a nonexistent part number), he shall inform the CM through the AD Section, and a revised AD should be issued if it meets the proper criteria. A superseding AD shall comply with all of the requirements of a new AD as per standard AD process (Chapter 5.1), Final AD with request for comments (consultation) process (Chapter 5.2) or Emergency AD process (Chapter 5.3), including notice, opportunity for comment (if it is issued as Proposed AD), incorporation by reference, and any other regulatory requirements, including any new requirements effective since the publication of the AD. The following shall be taken into account when an AD is being superseded: (a) The revised/superseded information section shall indicate that a previous AD is being superseded (b) Where appropriate, credit should be given for corrective actions already accomplished in compliance with the superseded AD. When restating old compliance dates, i.e. compliance dates already included in the superseded AD, they have to be limited to those requirements already included in the superseded AD only. When applicability is expanded, old compliance dates should not be used. On the other hand, it is also important to make sure that provisions of the previous AD that are intended to remain in effect are not omitted inadvertently. A careful "side-by-side" comparison of the previous AD and the new AD draft is essential and strongly recommended. (c) A superseding AD shall get a new AD number; the website record for the superseded AD is amended to reflect the new SUPERSEDED status. The AD Section shall archive the superseded AD [ref. Record keeping and Archiving work instruction C.I009]. The public shall continue to have access to superseded ADs. 110 Revision of an AD : The EASA PCM shall asses in coordination with the Certificate Holder, if a revised AD should be issued and shall forward the proposed revised AD to the CM through the AD Section. The approval of the revised AD is preceded by a technical visa, signed by the PCM Cases when a revised AD is appropriate: (a) To issue necessary changes that are non-substantive. Examples include a change in the address where a service bulletin is available or a change in the name of the contact person, or something equally non-substantive. (b) If the change is relieving in nature, such as the addition of an optional terminating action. While this would normally be viewed as a substantive change requiring a superseding AD, the reasons for requiring a superseding AD do not apply. In the case of an optional terminating action added to an AD that continues to require a repetitive inspection, failure to record the correct revision number is not critical to compliance. The same required inspection shall be performed under all revisions; compliance with an earlier version would have no effect on safety. (c) (d) For reduced applicability. Because this is a type of relieving AD, it is not critical to record a new AD number. To correct substantive errors that cause compliance to be impossible. For example, an AD that requires the installation of a nonexistent part (no such part number) is impossible to comply with, and the issue of whether the proper revision number is recorded is not critical to compliance. Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 28 of 42

29 5.4.2 Process Steps Description for Changes to Previously Issued ADs, continued 110 Revised ADs shall retain their original paragraph designations because maintenance record entries that refer to specific paragraphs will be incorrect if the information is moved or replaced. A change in the designation of a paragraph that contains a requirement results in the issuance of a superseding AD. The EASA PCM shall submit the proposed revised AD to the CM through the AD Section for endorsement and publication. The reason paragraph should include a discussion of each change, how each change affects compliance, and the fact that all other parts of the AD remain as originally published. The following shall be taken into account when an AD is being revised: (a) The revised/superseded information section shall indicate that a previous AD is being revised or superseded. (b) A revised AD retains its AD number with the addition of the revision number, e.g., R1. When ADs revisions are for changes that are non-substantive, public consultation will not be used. If the CM agrees with the proposed revised AD, he shall approve it and forward to the AD Section for publication on the EASA web. The full text of a revised AD shall be published on the EASA official publication (EASA AD website) and redistributed. 120 Record keeping and archiving of documents related to the AD change process is defined in work instruction C.I End of the Changes to Previously Issued AD process. Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 29 of 42

30 5.5 Process for Adoption of Foreign ADs Start (010) Monitor foreign (E)AD [AD Section] (020) Receive and review foreign (E)AD [PCM] (030) Process Chart Foreign AD Step te Link AD Airworthiness Directive 010 CM Certification Manager CRD Comment Response Document EAD Emergency Airworthiness Directive 020 MS Member State (EU) PAD Proposed Airworthiness Directive PCA Primary Certification Authority PCM Project Certification Manager SoR State of Registry SoD State of Design 030 Rev Foreign (E)AD accepted without change? [PCM] (040) 040 Inform and coordinate with PCA and certificate holder [PCM] (050) 050 Draft deviating PAD or EAD and raise the issue to the CM [PCM] (060) Inform AD Section that foreign (E)AD is accepted without change [PCM] (080) Inform the PCA before publication of PAD or EAD [CM] (070) Manage publication of Foreign (E)AD on official EASA website \\ [AD Section] (090) Go to Chapter 5.1 step 100 Archive all relevant documents related to the foreign (E)AD published [AD Section] (100) 100 C.I009 End (110) Foreign (E)AD archives file 110 Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 30 of 42

31 5.5.2 Process Steps Description for Adoption of Foreign ADs 010 Start of the process for Adoption of Foreign ADs. According to Article 1 of ED Decision 2/2003 any AD issued by the SoD for an aircraft imported from a third country, or for an engine, propeller, part or appliance imported from a third country and installed on an aircraft registered in a EU Member State, shall apply unless EASA has issued a different decision before the date of entry into force of that AD. Following Article 12 (8) of MB Decision 12/2007, EASA may adopt an AD from a foreign SoD without prior consultation if there is no request for it within 30 days of the issue of the foreign AD or of the initiation of the foreign authority consultation on the AD (whatever is the earliest). In case there is a written request for consultation on a Foreign AD or Proposed Foreign AD, an EASA Proposed AD may be drafted and the provisions contained in Chapter 5.1 Standard Process for Issuing ADs steps shall be followed. According to Article 12 (9) of MB Decision 12/2007, if the EASA PCM (or team) decides to deviate from a foreign AD, an EASA Proposed AD has to be issued following the procedure described under Chapter 5.1 Standard Process for Issuing ADs, identifying, inter alia, in this new AD the foreign AD upon which it is based and the differences between the two documents. 020 The AD Section shall ensure the monitoring of Foreign ADs, as issued by the State of Design for the affected product(s). 030 The AD Section shall ensure that each EASA PCM receives all Foreign ADs, as issued by the State of Design for the affected product(s). The AD Section will prepare publication of the Foreign AD on the EASA official publication (EASA website) before the effective date of that directive. 040 The PCM shall check if he concurs with the foreign decision or if a deviating corrective action is needed If the PCM does not concur with the Foreign AD or Emergency AD, he shall draft a deviating PAD in accordance with the instructions contained in Chapter 5.1 Standard Process for Issuing ADs steps 050 to 160 or Emergency AD in accordance with the instructions contained in Chapter 5.3 Emergency AD process steps 070 to 110. In this case the PCM shall raise the issue to the responsible CM who will ensure further co-ordination with higher management levels if deemed necessary. 070 In any case the CM shall inform the PCA before the PAD or EAD is published for public consultation. 080 If the PCM concurs with the Foreign AD or Emergency AD, then the principle of "simplified adoption" shall be assumed and, before the Foreign (E)AD s effective date, the PCM will inform the AD Section that the Foreign (E)AD is considered accepted. 090 Subsequently, the AD Section will arrange for publication of the Foreign (E)AD on the EASA official publication (EASA website). 100 Record keeping and archiving is ensured as defined in work instruction C.I End of the process for Adoption of Foreign ADs. Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 31 of 42

32 6. EASA APPROVAL OF ALTERNATIVE METHODS OF COMPLIANCE (AMOC) 6.1 Definition An AD is issued by the Agency and becomes a mandatory part of the relevant design approval. NAAs may however under their own responsibility and by strictly following the required procedure and observing the relevant preconditions use the relevant part of Article 10 of the Basic Regulation in individual cases to allow (temporary) deviation from an AD, by derogating from the requirement in Part M.A.303 to comply with ADs. An Alternative Method of Compliance (AMOC) is an EASA approved deviation to an AD. It is a different way, other than the one specified in an AD, to address an unsafe condition on products, parts and appliances. An AMOC must provide an acceptable level of safety, equivalent to the level of safety intended for compliance with the original AD. Only if a deviation to the AD is proposed by the relevant Certificate Holder it can lead to an update of the AD to include other means to comply with the AD or a new compliance time. Where an application for an AMOC is being processed concurrently with an application for minor/major change or STC, the responsible PCM(s) need to coordinate his/their activities in order that the minor/major change or STC approval is granted prior to or at the same time as the AMOC approval. If the AD subject of an approved AMOC is revised, such AMOC will continue to be valid and no further AMOC request is necessary. If the AD subject of an approved AMOC is superseded, then such AD is considered as cancelled; therefore an AMOC to the new AD (if the same conditions apply) has to be requested. Reference to the previous AMOC approval and the reasons why the same conditions are still applicable to the new AD should be made in the AMOC application form. 6.2 Application The Certificate Holder (against which the AD is written) or any operator / owner of EU registered aircraft may apply for approval of an Alternative Method of Compliance to the AD. Applications for approval of an Alternative Method of Compliance shall be sent to the EASA Airworthiness Directives Section, using EASA Form 42 which can be found on the EASA website. The request for the AMOC is subject to verification and approval by EASA. 6.3 Applicable Charges This activity is regarded as a service. Applicants for approval of Alternative Methods of Compliance will be charged in accordance with the Commission Regulation (EC). 593/2007 of 31 May 2007 on the fees and charges levied by the European Aviation Safety Agency (OJ L 140, 1 June 2007, p. 3). Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 32 of 42

33 According to Articles 10 and 11 of the afore-mentioned Regulation, the services provided by EASA give rise to charges which shall be equal to the real cost of the service provided, including administrative costs. The real costs associated with the service are determined as follows: 1. Hours performed by EASA technical experts and/or the EASA s contractors (NAAs) 2. Travel costs which are payable by EASA to its contractors or staff including: a) Transport costs (airplane ticket, visa costs, train, car, bus, taxi) b) Travel time costs (travel time x hourly rate) c) All other costs (accommodation and meals, incidental expenses and travel allowances paid to staff in the context of those activities). The applicable hourly rate is defined in Part II of the Annex of the Regulation. In the event of cancellation of the application, refusal of a quote (provided on request by an applicant) or refusal to issue the approval, the working hours already spent will be fully recovered. EASA will also recover, if applicable, any travel costs. This Chapter contains 2 flowcharts: 6.4 AMOC Approval Process 6.5 AMOC to Foreign AD Approval Process Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 33 of 42

34 6.4 AMOC Approval Process Process Chart From Chapter 6.5 step 030 Start (010) Review application for approval of AMOC with AD [AD Section] (020) Step te Link AMOC Alternative Methods of Compliance NAA National Aviation Authority 010 RP Responsible Party P&P EASA Plans & Programmes Department 020 PCM Project Certification Manager SoR State of Registry Rev Review application for eligibility, completeness and correctness [AD Section ] (030) 030 Application correct & complete? [AD Section] (040) Application accepted? [AD Section] (060) tify errors and/or omissions to applicant and request correction [AD Section ] (050) tification on errors & omissions Acknowledge receipt of application for AMOC approval, indicating Project no.; inform P&P to allocate task [AD Section] (080) Acknowledgement of receipt tify decision in writing together with reasons thereto [AD Section] (070) tification on refusal of application Enter all information in AMOC database, allocate P-, enter PCM information [AD Section] (090) 090 Allocate task to EASA PCM or RP i.a.w. C.P101 [P&P] (100) Allocation letter & precompleted TV Perform technical investigation [PCM/RP] (110) C.P Issue Technical Visa on AMOC application [PCM/RP] (140) Technical Visa (EASA Form 43) Enter all information in AMOC database, allocate AMOC approval no., issue EASA Approval Letter and submit letter to EASA CM [AD Section] (150) Does AMOC provide equivalent level of safety? [PCM/RP] (120) tify decision not to approve AMOC in writing together with reasons thereto [AD Section] (130) tification on refusal of AMOC approval Sign Approval Letter and return to AD Section [CM] (160) AMOC approval letter (EASA Form 43) Need to change existing AD? [AD Section&PCM] (170) tify NAA of SoR & applicant by (copy to PCM/RP) and send Approval Letter to applicant [AD Section] (190) tification to SoR NAA AMOC Approval letter Initiate AD Change process i.a.w. Chapter 5.4 [AD Section] (180) 180 C.P006 Chapter Provide original approval letter and invoicing letter to P&P [AD Section] (200) 200 Initiate RO process [P&P] (210) 210 Archive relevant documents and inform P&P that application is closed [AD Section] (220) End (230) AMOC Archives file 220 C.I Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 34 of 42

35 6.4.2 Process Steps Description for AMOC Approval 010 Start of the AMOC Approval process Definition An AD is issued by the Agency and becomes a mandatory part of the relevant design approval (TC, STC, ETSOA, minor change approval, repair approval). NAAs may under their own responsibility and by strictly following the required procedure and observing the relevant preconditions use Article 10.3 of the Basic Regulation in individual cases to allow (temporary) deviation from an AD, by derogating from the requirement in Part M.A.303 to comply with ADs. An Alternative Method of Compliance (AMOC) is an EASA approved deviation to an AD. It is a different way, other than the one specified in an AD, to address an unsafe condition on products, parts and appliances. An AMOC must provide an acceptable level of safety, equivalent to the level of safety intended for compliance with the original AD. 020 Applications for approval of an Alternative Method of Compliance shall be sent to the EASA AD Focal Point, using EASA Form 42 which can be found on the EASA website. Only if a deviation to the AD is proposed by the relevant Certificate Holder it can lead to an update of the AD to include other means to comply with the AD or a new compliance time Where incorrect or incomplete information is supplied, the AD Section shall notify the applicant as soon as possible by a letter detailing the omissions and errors. For any technical issue, the AD Section will consult the responsible EASA CM In case of refusal of an application, the AD Section will notify this decision in writing to the applicant together with the reasons thereto, including a reference to the possibility for appeal as specified in Articles 35 to 41 of the Basic Regulation. (*)The request for the AMOC is subject to verification by EASA and may qualify as a separate application for a respective certificate subject to the payment of fees according to Commission Regulation (EC). 593/2007 of 31 May 2007 on the fees and charges levied by the European Aviation Safety Agency (OJ L 140, 1 June 2007, p. 3). 080 The allocation of the task will be performed in accordance with C.P101. Once principle acceptance is given, the AD Section will check with the responsible EASA CM, if the application shall be further processed internally or if the technical investigation should be allocated to an external party. In cases where the technical investigation shall be performed internally, the CM will nominate an appropriate EASA staff member. In cases where the technical investigation shall be allocated to an external party which will handle the technical investigation on behalf of EASA, the selected external party may only be, by the time being, a Member State NAA which is appropriately accredited and has appropriate contractual arrangements with EASA, according to the current applicable legal framework (see MB Decision 10/2007 of 28 March 2007). The list of NAA accredited for allocation of certification tasks with their relevant scope of accreditation is defined in the document no. S.L001 (not published). The CM will finally select one NAA according to the necessary competence, previous accumulated experience, the available capacity requested thereof and, in case of equal suitability, the total estimated costs (hourly rate and estimated time to perform the task). The selected NAA will be informed in writing of its selection together with the reasons thereto. The selected NAA will be provided with any information needed for the effective performance of the technical investigation tasks. 090 Following receipt of the application, the AD Section shall enter all information into the AMOC database, allocate the AMOC P- (e.g. P-EASA.A.AMOC.XXXXX) and enter the PCM information into the database. Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 35 of 42

36 6.4.2 Process Steps Description for AMOC Approval, continued 100 Having received a correct and complete application and determined the Project number and the Certification Team (EASA or NAA), the AD Section shall notify the applicant as soon as possible, but no later than 10 working days following the date of receipt by EASA, acknowledge receipt of the application. The AD Section will inform the applicant and the selected EASA team or NAA of the following: (a) Project number (e.g.: P-EASA.A.AMOC.XXXXX) (b) Which EASA certification team or NAA will perform the technical investigation. 110 If requested and appropriately substantiated the responsible CM may accept Alternative Methods of Compliance (AMOCs) for an AD; The PCM/responsible party shall check if the proposed solution can be accepted as an AMOC. If the proposed AMOC comprises changes to the approved type design, those changes must be approved separately following the applicable certification procedures. Temporary derogations / changes of inspection intervals or time limitations due to urgent operational needs may fall under the competence of the State of Registry using flexibility provisions of the basic regulation If the proposal does not provide an acceptable [equivalent] level of safety, the AMOC request is refused and the applicant shall be informed accordingly. 140 Upon completion of the technical investigation, the PCM/ Responsible Party shall produce and sign a Technical Visa using EASA Form 43. This technical visa constitutes the formal closure of the technical investigation and contains all information necessary to issue the AMOC approval. The PCM/ Responsible Party shall send the signed technical visa to the AD Section. 150 Following receipt of the Technical Visa from the PCM/Responsible Party the AD Section shall enter the information into the AMOC database and format the AMOC into the EASA Approval Letter Format (EASA Approval Letter AMOC), allocate the AMOC number (e.g. AD-Number. AMOC.XXXX) and send it to the CM for final review and approval. 160 The CM may accept the proposed AMOC by his signature on the corresponding EASA Approval Letter. 170 Depending on the nature of the AMOC, the AD concerned may need to be changed to include the alternative method of compliance. 180 The steps to be followed for changing an existing AD are described in PC04 Change to previously issued AD process. 190 The AD Section will notify the AMOC by to the applicant, copy to the external party/internal PCM, as well as to the NAA of the State of Registry of the affected aircraft and, at the same time, send the Original Approval Letter by regular mail. 200 The AD Section will provide the Original Approval Letter and invoicing letter to P&P for initiation of the recovery order in SI Upon generation of the invoice, the Original Approval Letter together with the invoicing letter and invoice will be sent by regular mail to the applicant. 220 All documents exchanged between the applicant, the AD Section, the PCM/Responsible Party and the CM are archived by the AD Section, as defined in C.I End of the AMOC Approval process. Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 36 of 42

37 6.5 AMOC to Foreign AD Approval Process Process Chart Start (010) 010 Review application for approval of AMOC with Foreign AD [AD Section] (020) 020 Criteria for direct adoption fulfilled? [AD Section] (030) 030 Inform applicant that no further action is required [AD Section] (040) Go to Chapter 6,4 step Archive correspondence & supporting documents [AD Section] (050) AMOC to Foreign AD archives file End (060) 050 C.I Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 37 of 42

38 6.5.2 Process Steps Description for AMOC to Foreign AD 010 Start of AMOC to Foreign AD Approval process When an AD of an imported product, part or appliance from a third country and installed on an aircraft registered in an EU Member State has been issued by the SoD and adopted by EASA, it may happen that an application for an Alternative Method of Compliance (AMOC) is received Criteria are defined in ED Decisions 2004/02/CF, 2004/03/CF or 2004/04/CF, as applicable 040 If the AMOC fulfils the requirements established in EASA ED Decision 2004/02/CF, 2004/03/CF or 2004/04/CF, as applicable. The applicant will be informed that no further action is required. In all other cases, the general procedure for AMOC approval defined under Chapter 6.4 AMOC Approval Process applies. 050 Record keeping and archiving is ensured as defined in work instruction C.I End of AMOC to Foreign AD Approval process. Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 38 of 42

39 7. SAFETY INFORMATION BULLETIN (SIB) 7.1 General SIBs are for information only; they do not contain mandatory instructions. Only when design related issues which may lead to unsafe condition are considered likely to exist or develop, issuance of an airworthiness directive is warranted. The following cases are possible: Information may be available to EASA concerning a (potential) unsafe condition on aircraft under national registers, but the causes of which are not type design related. In such a case, given the legal (regulatory) constraints, EASA cannot address an AD to the Certificate Holder to correct that unsafe condition. In such a case, the PCM may (also) elect the publication of an SIB. SIBs are therefore transmitted to EU NAAs and posted on the EASA website. Information may be available to EASA related to airworthiness concerns on aircraft under national registers, but for which insufficient evidence exists to qualify this as an unsafe condition. In such a case, the PCM may elect the publication of an SIB, containing information for the safe operation of the affected aircraft. Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 39 of 42

40 7.2 SIB Process Process Chart Start (010) Determination of existence of a non design related unsafe condition or existence of airworthiness concern for which unsufficient evidence exists to qualify this as unsafe condition [EASA/C] (020) Step te Link AD Airworthiness Directive CM Certification Manager 010 PCM Project Certification Manager SIB Safety Information Bulletin 020 Rev Review information, consult with AD Section and evaluate the need to issue SIB [PCM] (030) Need for SIB confirmed? [PCM & AD Section ] (040) 050 Justify decision not to issue an SIB and initiate alternative action, if required [PCM] (050) Draft the SIB, taking into account C.I003 and submit to AD Section, together with supporting documents [PCM] (070) SIB draft C.I003 End (060) Review draft SIB, make editorial changes as appropriate and submit to CM for validation [AD Section] (080) 080 SIB draft 2 SIB ready to be published? [CM] (090) 090 Request corrections/modifications [CM] (100) 100 Prepare for circulation and publication of SIB and supporting documents as appropriate [AD Section] (110) EASA SIB 110 Distribute SIB to EU Member States' NAAs and to known ICAO Contracting States' Authorities [AD Section] (120) SIB distribution Manage publication of SIB on official EASA website \\ [AD Section] (130) SIB notification Archive all relevant documents related to the SIB published [AD Section] (140) SIB archives file 140 C.I009 End (150) 150 Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 40 of 42

41 7.2.2 Process Steps Description for SIB 010 Start of SIB process SIBs are for information only; they do not contain mandatory instructions. Only when design related issues which may lead to unsafe condition are considered likely to exist or develop, an airworthiness directive, is warranted. 020 The following cases are possible: Information may be available to EASA concerning a (potential) unsafe condition on aircraft under national registers, but the causes of which are not type design related. In such a case, given the legal (regulation) constraints, EASA cannot address an AD to the Certificate Holder to correct that unsafe condition. In such a case, the PCM may (also) elect the publication of an SIB. SIBs are therefore transmitted to EU NAAs and posted on the EASA website. Information may be available to EASA related to airworthiness concerns on aircraft under national registers, but for which insufficient evidence exists to qualify this as an unsafe condition. In such a case, the PCM may elect the publication of an SIB, containing information for the safe operation of the affected aircraft. 030 The PCM shall prepare the SIB in close consultation with the AD Section If the need for an SIB is not confirmed, a note to the file shall be kept to justify the decision. In certain cases, it may however be necessary to disseminate the relevant information through other means. 060 End of the process in case the need to issue an SIB has not been confirmed by the PCM. 070 The AD Section shall perform all verifications as defined in C.I003 and if necessary, contact the affected parties and authorities involved with the SIB subject matter, in order to check the integrity and accuracy of the information to be published The CM shall verify the SIB to be published and in particular ensure that it complies with the rules set forth in C.I003 Disseminating Safety Related Information Once finalised and agreed the final text with the CM concurrence, the AD Section shall send the Safety Information Bulletin in the English language as attachment to an appropriate to: (a) the EU Member States NAAs; and (b) any other known ICAO Contracting State Authority that has requested to Agency to be so informed, in order to put them into a position to take appropriate action, if so desired. 130 In addition the AD Section shall manage the publication of the Safety Information Bulletins in the EASA Official Publication (EASA website). 140 All documents relevant to the SIB being published shall be archived in accordance with the work instruction C.I End of SIB process. Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 41 of 42

42 8. LIST OF RECORDS All records related to this procedure are defined in C.I009. Printed copies are not controlled. Confirm revision status through the EASA-Internet/Intranet. Page 42 of 42