Subject matter and scope
Article 2
Regulation (EU) 2015/640 is amended as follows (1) Article 1 is replaced by the following: ‘Article 1 Subject matter and scope 1. This Regulation lays down common additional airworthiness specifications related to the continuing airworthiness and safety improvements of aircraft. 2. This Regulation applies to: (a) operators of: (i) aircraft registered in a Member State; (ii) aircraft registered in a third country and used by an operator for which a Member State ensures oversight; (b) holders of a type-certificate, restricted type-certificate, supplemental type-certificate or a change and repair design approval approved by the Agency in accordance with Commission Regulation (EU) No 748/2012 ( * ) or deemed to have been issued in accordance with Article 3 of that Regulation; (c) the applicants for a type-certificate or a restricted type-certificate for a turbine-powered large aeroplane, for which the application was submitted before 1 January 2019 and who are issued with the certificate after 26 August 2020 when specified in Annex I (Part-26). ( * ) Commission Regulation (EU) No 748/2012 of 3 August 2012 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 224, 21.8.2012, p. 1 ).’;" (2) In Article 2, the following points (e) to (o) are added: ‘(e) “limit of validity” (LOV) means, in the context of the engineering data that supports the structural maintenance programme, a period of time, stated as a number of total accumulated flight cycles or flight hours or both, during which it is demonstrated that widespread fatigue damage will not occur in the aeroplane; (f) “airworthiness limitation section” (ALS) means a section in the instructions for continued airworthiness, as required by points 21.A.61, 21.A.107 and 21.A.120A of Annex I (Part 21) to Regulation (EU) No 748/2012, that contains airworthiness limitations that set out each mandatory replacement time, inspection interval and related inspection procedure; (g) “corrosion prevention and control programme” (CPCP) means a document reflecting a systematic approach to prevent and to control corrosion in an aeroplane’s primary structure, consisting of basic corrosion tasks, including inspections, areas subject to those tasks, defined corrosion levels and compliance times (implementation thresholds and repeat intervals). A baseline CPCP is established by the type certificate holder, which can be adapted by operators to create a CPCP in their maintenance programme specific to their operations; (h) “widespread fatigue damage” (WFD) means a simultaneous presence of cracks at multiple locations in the structure of an aeroplane that are of such size and number that the structure will no longer meet the fail-safe strength or residual strength used for certification of that structure; (i) “baseline structure” refers to the structure that is designed under the type certificate for that aeroplane model (that is, the ‘as delivered aeroplane model configuration’); (j) “fatigue-critical baseline structure” (FCBS) means the baseline structure of an aeroplane that is classified by the type certificate holder as a fatigue-critical structure; (k) “fatigue-critical modified structure” (FCMS) means any fatigue critical structure of an aeroplane introduced or affected by a change to its type design and that is not already listed as part of the fatigue-critical baseline structure; (l) “damage tolerance evaluation” (DTE) is a process that leads to a determination of maintenance actions necessary to detect or preclude fatigue cracking that could contribute to a catastrophic failure. When applied to repairs and changes, a DTE includes the evaluation of the repair or change and the fatigue critical structure affected by the repair or change; (m) “damage tolerance inspection” (DTI) means a documented inspection requirement or other maintenance action developed by holders of a type-certificate or restricted type-certificate as a result of a damage tolerance evaluation. A DTI includes the areas to be inspected, the inspection method, the inspection procedures (including the sequential inspection steps and acceptance and rejection criteria), the inspection threshold and any repetitive intervals associated with those inspections. DTIs may also specify maintenance actions such as replacement, repair or modification; (n) “repair evaluation guideline” (REG) means a process established by the type certificate holder that guides operators to establish damage tolerance inspections for repairs that affect fatigue-critical structure to ensure the continued structural integrity of all relevant repairs; (o) “fatigue-critical structure” (FCS) means a structure of an aeroplane that is susceptible to fatigue cracking that could lead to a catastrophic failure of the aeroplane.’; (3) Annex I (Part-26) is amended in accordance with Annex II to this Regulation.