Regulation (EU) 2022/1358
This Subpart establishes how the compliance of parts with the airworthiness requirements shall be shown.
21L.A.192 Showing of compliance
Regulation (EU) 2022/1358
(a) The showing of compliance with the airworthiness requirements of parts to be installed in a type‑certified product or an aircraft for which design compliance has been declared shall be made:
1. in conjunction with the type-certification procedures of Subpart B, D or E of this Annex for the product in which it is to be installed; or
2. in conjunction with the declaration of design compliance procedures of Subpart C or F of this Annex for the product in which it is to be installed; or
3. under the ETSO authorisation procedure of Subpart O of Section A of Annex I (Part 21) ; or
4. in the case of standard parts, in accordance with officially recognised standards.
(b) In all cases where the approval of a part is explicitly required by Union law or Agency measures, the part shall comply with the applicable ETSO or with the specifications recognised as equivalent by the Agency in the particular case.
AMC1 21L.A.192(a)(4) Showing of compliance
ED Decision 2023/013/R
STANDARD PARTS
(b) For sailplanes and powered sailplanes, where it is a non-required instrument and/or equipment certified under CS 22.1301(b), if that instrument or equipment, when installed, functioning, functioning improperly or not functioning at all, does not in itself, or by its effect upon the sailplane and its operation, constitute a safety hazard.
‘Required’ in the term ‘non-required’ as used in point (b) means required by the applicable certification specifications (CS 22.1303, CS 22.1305 and CS 22.1307) or required by the relevant operating regulations and the applicable rules of the air, or as required by air traffic management (e.g. a transponder in certain controlled airspace).
Examples of equipment which can be considered ‘standard parts’ are electrical variometers, bank/slip indicators ball type, total energy probes, capacity bottles (for variometers), final glide calculators, navigation computers, data logger / barograph / turnpoint camera, bug wipers and anti-collision systems.
Equipment which must be approved in accordance with the applicable certification specifications shall comply with the applicable ETSO or equivalent, and is not considered a ‘standard part’ (e.g. oxygen equipment).
GM1 21L.A.192(a)(4) Showing of compliance
ED Decision 2023/013/R
OFFICIALLY RECOGNISED STANDARDS
In this context, ‘officially recognised standards’ means:
(a) those standards established or published by an official body whether having legal personality or not, which are widely recognised by the air transport sector as constituting good practice;
(b) the standards used by the manufacturer of the equipment as mentioned in point (b) of AMC1 21L.A.192(a)(4).
21L.A.193 Release of parts for installation
Regulation (EU) 2022/1358
(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 965/201290Commission Regulation (EU) No 965/2012 of 5 October 2012 laying down technical requirements and administrative procedures related to air operations pursuant to Regulation (EC) No 216/2008 of the European Parliament and of the Council (OJ L 296, 25.10.2012, p. 1).; 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.
AMC1 21L.A.193(b)(3);(b)(4) Verification activities to be conducted on the part or appliance or release documentation prior to installation
ED Decision 2023/013/R
To prevent a non-negligible safety effect on the product due to the installation of a part referred to in point 21L.A.193(b)(3) and (b)(4) that could potentially not conform to its design, the design approval holder (DAH), declarant or EASA may identify in the ICAs (in the case of point 21L.A.193(b)(3)) or in CS‑STAN (in the case of point 21L.A.193(b)(4)) any specific verification activities to be conducted by the installer on the part or appliance before installing it on the product in accordance with Regulation (EU) No 1321/2014.
When assessing the safety effect of a part identified in point 21L.A.193(b)(3) or (b)(4), the DAH, declarant or EASA should assume that the installer has conducted, in accordance with Regulation (EU) No 1321/2014, any specific verification activities on the part or release documentation, as identified in the ICAs or in CS-STAN.
Example:
Information from the DAH contained in the ICAs: ‘Part XXX-YY must comply with flammability requirement JJJ-KKK’.
GM1 21L.A.193(b)(3);(b)(4) Meaning of ‘negligible safety effect’
ED Decision 2023/013/R
For the purposes of point 21L.A.193(b)(3) and (b)(4), when ‘a part or appliance for which the consequences of non-conformity to its design has a negligible safety effect when installed on the product’ is mentioned, it means that any non-conformity of the part not identified by the installer that conducted the specific verification activities referred to in point 21L.A.193(c) at worst:
(a) slightly reduces the operational or functional capabilities of the aircraft or its safety margins;
(b) causes some physical discomfort to its occupants; and
(c) slightly increases the workload of the flight crew.
GM1 21L.A.193(b)(4) Certification specifications referred to in point 21L.A.193(b)(4)
ED Decision 2023/013/R
The corresponding certification specifications issued by EASA and mentioned in point 21L.A.193(b)(4) are the Certification Specifications for Standard Changes and Standard Repairs (CS-STAN)91https://www.easa.europa.eu/en/certification-specifications/cs-stan-stan….
GM1 21L.A.193(b)(5) Equipment exempted from an airworthiness approval in accordance with Commission Regulation (EU) No 965/2012
ED Decision 2023/013/R
The equipment exempted from an airworthiness approval in accordance with Commission Regulation (EU) No 965/201292 that can be installed during maintenance as new equipment on an aircraft under point 21L.A.193(b)(5) is the equipment identified in the following points:
— CAT.IDE.A.100(a),
— CAT.IDE.H.100(a),
— NCC.IDE.A.100(b) and (c),
— NCC.IDE.H.100(b) and (c),
— NCO.IDE.A.100(b) and (c),
— NCO.IDE.H.100(b) and (c),
— NCO.IDE.S.100(b) and (c),
— NCO.IDE.B.100(b) and (c),
— SPO.IDE.A.100(b) and (c),
— SPO.IDE.H.100(b) and (c),
— SPO.IDE.S.100(b) and (c), and
— SPO.IDE.B.100(b) and (c)
of Commission Regulation (EU) No 965/2012.
GM1 21L.A.193(b)(6) Part that is part of a higher-level assembly
ED Decision 2023/013/R
An EASA Form 1 is not required for a part when that part is an element of a higher-level assembly for which an EASA Form 1 is not required.