Canadian Aviation Regulations — 521.369
521.369 (1) This section applies in respect of an aeroplane for which a type certificate has been issued and that is (a) a commuter category aeroplane operated under Subpart 4 of Part VII; or (b) a transport category aeroplane operated under Subpart 4 or 5 of Part VII. (2) Before an aeroplane referred to in subsection (1) meets the applicable in-service criterion specified in subsection (3), the holder of the type certificate in respect of the aeroplane shall (a) develop supplemental integrity instructions in accordance with subsection (4) and submit them to the Minister for approval in accordance with subsection (5); and (b) on their approval, make the supplemental integrity instructions available to each owner and each operator of an aeroplane of that type. (3) The in-service criterion that determines whether supplemental integrity instructions are required in respect of the aeroplane is that (a) the aeroplane reaches the design life goal — which is the expected period of operational service of the aeroplane — as established by the type certificate holder, and a corrosion protection and control program is in place; or (b) the aeroplane completes 20 years of service and (i) no corrosion protection and control program is in place, or (ii) no design life goal has been established. (4) The supplemental integrity instructions required under subsection (2) shall (a) specify a method for maintaining the conformity of the aeroplane with its certification basis; (b) incorporate any recommendation resulting from a detailed engineering assessment of the primary airframe structure of the aeroplane and from the service history of that aeroplane; (c) identify, for periodic review, all principal structural elements whose failure could result in the loss of the aeroplane or significantly reduce the overall structural strength of its airframe; (d) contain a supplemental structural integrity document that consists of (i) a description of each principal structural element that has been selected for supplementary inspection, modification or replacement, and its structural location, component or damage site, (ii) a description of the type of damage expected — such as fatigue, corrosion, delamination, disbondment, accidental damage or multiple-site damage — for each structural location identified, and (iii) a reference to any existing maintenance manual or service bulletin intended for the aeroplane; (e) recommend, for each principal structural element that has been selected for supplementary inspection under paragraph (d), (i) an initial or threshold inspection and the intervals for repeat inspections, and (ii) inspection methods and inspection procedures appropriate for the type of damage referred to in subparagraph (d)(ii), including any alternatives to the intervals for inspections and to the methods and procedures used; (f) specify any modifications, replacements or corrosion control measures, optional or mandatory, that could change or terminate the inspection requirements set out in paragraph (e); and (g) provide guidance for reporting to the Minister the findings from any inspection conducted using the supplemental structural integrity document. (5) The Minister shall approve the supplemental integrity instructions submitted in respect of an aeroplane if the Minister determines that the instructions provide a level of safety equivalent to that provided by the standards of airworthiness in force at the time the type certificate was issued in respect of the aeroplane. (6) The holder of a type certificate in respect of an aeroplane who proposes to make a change to the supplemental integrity instructions for the aeroplane shall (a) submit the change to the Minister for approval; and (b) on approval of the change, make the changed instructions available to each owner and each operator of an aeroplane of that type. SOR/2009-280, s. 26