Division 21.A.433 Requirements for approval of a repair designF1

A repair design shall only be approved:

1. 1..

   when it has been demonstrated, following the certification programme referred to in point 21.A.432C(b), that the repair design complies with the type-certification basis incorporated by reference in, as applicable, either the type-certificate, the supplemental type-certificate or the APU F2UKTSO authorisation, as well as with any amendments established and notified by the F3CAA in accordance with point 21.B.450;

2. 2..

   when compliance with the type-certification basis that applies in accordance with point (a)(1) has been declared and the justifications of compliance have been recorded in the compliance documents;

3. 3..

   when no feature or characteristic has been identified that may make the product unsafe for the uses for which certification is requested; F4...

4. 4..

   where the applicant has specified that it provided certification data on the basis of an arrangement with the owner of the type-certification data in accordance with point 21.A.432C(b)(7):

   1. (i)

      when the holder has indicated that it has no technical objection to the information submitted under point (a)(2); and

   2. (ii)

      when the holder has agreed to collaborate with the repair design approval holder to ensure discharge of all obligations for continued airworthiness of the changed product through compliance with point 21.A.451 F5; and

5. 5.

   when, for a repair to an aeroplane subject to point 26.302 of Annex I to Regulation (EU) 2015/640, it has been demonstrated that the structural integrity of the repair and affected structure is at least equivalent to the level of structural integrity established for the baseline structure by point 26.302 of Annex I to that Regulation.

The applicant shall submit to the F6CAA the declaration referred to in point (a)(2) and, on request by the CAA, all necessary substantiation data.