21L.A.193 Release of parts for installation

(a)A part or product shall only be installed in a product when it is identified by the holder of a type certificate, supplemental type certificate, design change, repair design approval or with a declaration of design compliance as being suitable for installation, and when it is:

1.in a condition for safe operation;

2.marked in accordance with Subpart Q of this Annex; and

3.accompanied by an authorised release certificate (EASA Form 1) certifying that the item was manufactured in conformity with the applicable design data.

(b)By way of derogation from point (a)(3) and provided that the conditions in point (c) are met, the following parts do not require an authorised release certificate (EASA Form 1) in order to be installed in a type-certified product or in an aircraft for which design compliance has been declared:

1.a standard part;

2.a part that is:

(i)not life limited, nor part of the primary structure, nor part of the flight controls;

(ii)identified for installation in the specific aircraft by the holder of a type certificate, supplemental type certificate, design change, repair design approval or a declaration of design compliance;

(iii)to be installed in an aircraft whose owner has verified compliance with the applicable conditions in (i) and (ii), and has accepted responsibility for this compliance;

3.a part for which the consequences of a non-conformity with its approved design data or declared design data has a negligible safety effect on the product and which is identified as such by the holder of the design approval or the declarant of design compliance in the instructions for continued airworthiness. In order to determine the safety effects of a non-conforming part, the design approval holder or declarant of a declaration of design compliance may establish in the instructions for continued airworthiness specific verification activities to be conducted by the installer of the part on the product;

4.in the case of the embodiment of a standard change as per point 21L.A.102 or a standard repair as per point 21L.A.202, a part for which the consequences of a non-conformity with its design data have a negligible safety effect on the product, and the part is identified as such in the certification specifications for standard changes and standard repairs issued in accordance with point 21.B.70 of Annex I (Part 21) . In order to determine the safety effects of a non-conforming part, specific verification activities to be conducted by the person that installs the part in the product may be established in these certification specifications;

5.a part that is exempted from an airworthiness approval in accordance with Commission Regulation (EU) No 965/2012; and

6.a part that is an item of a higher assembly identified in points (b)(1) to (b)(5).

(c)Parts listed in point (b) are eligible for installation in a type-certified product or in an aircraft for which design compliance has been declared without being accompanied by an EASA Form 1, provided that the installer holds a document issued by the person or organisation that manufactured the part, which declares the name of the part, the part number, and the conformity of the part with its design data, and which contains the date of issuance.