Sofema Aviation Services (SAS) www.sassofia.com considers the elements related to the needed to demonstrate to EASA a compliance plan meeting the intent of Part 26/ CS 26 applicable to Restricted Type Certificate Holders as well as Type Certificate Holders & Applicants.
Compliance with point 26.301 of Part-26 is demonstrated when a compliance plan exists that includes the following:
- A project schedule identifying all the major milestones for meeting the compliance dates as specified in points 26.302 to 26.309 of Part-26, as applicable;
- A proposed means of compliance with the applicable requirements as specified in points 26.302 to 26.309 of Part-26, including as appropriate, methods and procedures for:
o Performing the damage tolerance evaluation (DTE) of baseline structure, modified structure and published repairs;
o Identifying the aeroplane structural configuration to be evaluated;
o Identifying widespread fatigue damage (WFD)-susceptible structure;
o Identifying the source of engineering data that will be used to perform the required evaluations;
o Performing the WFD evaluation of structure;
o Establishing a limit of validity (LOV) and plans for distribution upon approval (including the incorporation of the LOV into the (airworthiness limitation section) ALS);
o Identifying and developing the maintenance actions required to support the LOV;
o Developing a baseline corrosion prevention and control programme (CPCP);
o Establishing a process to ensure the continuing structural integrity programme remains valid;
o Establishing the list of fatigue-critical baseline structures (FCBSs);
o Developing the repair evaluation guidelines (REGs);
A plan for submitting a draft of all the required compliance items for review by EASA not less than 60 days before the applicable compliance date.
- For aeroplane structures certified on the basis of JAR 25.571 Change 6 or 14 CFR §25.571 Amendment 44 or equivalent, or earlier amendments, a fatigue and damage tolerance evaluation according to JAR 25.571 Change 7 or 14 CFR §25.571 Amendment 45 or equivalent, or later amendment, exists.
Note: Residual strength loads may be based upon the fail-safe load cases of the original certification basis.
- In addition, the inspection and other procedures resulting from this evaluation:
o Are contained in an existing ALS; or
o Are contained in a supplemental structural inspection document (SSID) mandated by an airworthiness directive (AD).
Next Steps
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Sofema Aviation Services www.sassofia.com & Sofema Online www.sofemaonline.com provides EASA regulatory compliant and vocational training including related to CAMO, AMC20-20 and Part 26 / CS 26. If you want to know more about our services, please see the websites or email us at team@sassofia.com
Tags:
(R)TC, Aircraft Airworthiness, Aircraft Maintenance, Airworthiness Directive (AD), Compliance, Compliance plan, Corrosion Prevention and Control Programme (CPCP), CS 26, CS 26.301, Damage Tolerance Evaluation (DTE), EASA, EASA Part 26, Fatigue-critical Baseline Structures (FCBSs), Limit of Validity (LOV), Repair Evaluation Guidelines (REGs), Restricted type-certificate, SAS blogs, Supplemental Structural Inspection Document (SSID), WFD, Widespread Fatigue Damage (WFD)
