Commission Implementing Regulation (EU) 2024/2954 of 29 November 2024 amending Regulation (EU) 2015/640 as regards the introduction of new additional airworthiness requirements
Date: 2024-11-29
Institutions: Directorate-General for Mobility and Transport, European Commission
Subjects: European Aviation Safety Agency, air safety, aircraft, civil aviation, helicopter, technical specification, transport authorisation




L_202402954EN.000101.fmx.xml












Official Journal of the European Union


EN
L series













2024/2954


2.12.2024







            COMMISSION IMPLEMENTING REGULATION (EU) 2024/2954
of 29 November 2024
         
amending Regulation (EU) 2015/640 as regards the introduction of new additional airworthiness requirements


THE EUROPEAN COMMISSION,

Having regard to the Treaty on the Functioning of the European Union,


Having regard to Regulation (EU) 2018/1139 of the European Parliament and of the Council of 4 July 2018 on common rules in the field of civil aviation and establishing a European Union Aviation Safety Agency, and amending Regulations (EC) No 2111/2005, (EC) No 1008/2008, (EU) No 996/2010, (EU) No 376/2014 and Directives 2014/30/EU and 2014/53/EU of the European Parliament and of the Council, and repealing Regulations (EC) No 552/2004 and (EC) No 216/2008 of the European Parliament and of the Council and Council Regulation (EEC) No 3922/91 (1), and in particular Article 17(1), point (h) thereof,

Whereas:







(1)


Pursuant to Article 76(3) of Regulation (EU) 2018/1139, the European Union Aviation Safety Agency (the ‘Agency’) issues certification specifications and regularly updates them in order to ensure that they remain fit for purpose. However, an aircraft the design of which has already been certified is not required to comply with the updated version of the applicable certification specifications when it is produced or while in service. Therefore, in order to support continuing airworthiness and safety improvements, compliance of such aircraft with additional airworthiness requirements that were not included in the initial certification specifications at the time of certification of the designs should be introduced. Commission Regulation (EU) 2015/640 (2) sets out such additional airworthiness requirements.












(2)


The scope of Regulation (EU) 2015/640 should be amended to make it consistent with Article 2 of Regulation (EU) 2018/1139 as regards aircraft operators.












(3)


Article 3 of Regulation (EU) 2015/640 specifies the scope for operators for which a Member State ensures oversight when operating the aircraft referred to in Article 1 of that Regulation. Article 1 was subsequently amended by Implementing Regulation (EU) 2020/1159 (3) to include that scope, so that Article 3 became redundant with the introduction of Article 1(2), point (a). Hence, Article 3 of Regulation (EU) 2015/640 should be deleted.












(4)


The certification specifications for Small Rotorcraft (CS-27) and Large Rotorcraft (CS-29) contain specifications related to crash-resistant fuel systems (‘CRFS’) for helicopters. However, a significant part of the in-service helicopters is not equipped with a CRFS, while several fatal accidents could have been survivable had the helicopters been equipped with such a system. This fact has also been highlighted in safety recommendations issued by various accident investigation bodies. In view of the risk of fatal accidents and of the need to maintain a high uniform level of civil aviation safety in the Union, it is proportionate and cost-efficient to render some of those specifications applicable to some in-service helicopters operated in the Union and to those that will be produced after the entry into force of this Regulation.












(5)


The Council of the International Civil Aviation Organization adopted new Standards and Recommended Practices (‘SARPs’) with Amendment 109 to Annex 8 to the Convention on International Civil Aviation, signed on 7 December 1944 in Chicago (the ‘Chicago Convention’) to ensure that the design approval holder makes available information on design characteristics associated with the cargo compartment fire protection capabilities of aeroplanes and helicopters to all known operators of such aircraft. These SARPs should be incorporated to maintain the safety of operations for aircraft that transport dangerous goods in the cargo compartment. Such information should assist operators in determining the limitations of specific cargo compartment fire protection capabilities established during certification when conducting the risk assessment for the transport of dangerous goods as required by Commission Regulation (EU) No 965/2012 (4).












(6)


The SARPs should be incorporated into Union legislation for small and large aeroplanes and for small and large helicopters and should be applicable to those aircraft for which the individual certificate of airworthiness is first issued on or after 1 January 2025. The new requirements for small aeroplanes and small helicopters should be proportionate to the safety risk and should apply only in the cases of cargo compartments separated from the flight deck. Due to the extension of the scope of Subpart B of Annex I to include small aeroplanes, some existing requirements of that Subpart should be amended to specify that they apply to large aeroplanes.












(7)


With effect from 26 February 2021, Implementing Regulation (EU) 2020/1159 inserted in Annex I (Part-26) to Regulation (EU) 2015/640 a new point 26.205 requiring operators of large aeroplanes used in commercial air transport to ensure that every aeroplane for which the first individual certificate of airworthiness is issued on or after 1 January 2025 is equipped with a runway overrun awareness and alerting system (‘ROAAS’). Several large aeroplane type-certificate holders are facing industrial issues resulting in significant delays preventing them from being able to deliver newly produced aeroplanes equipped with a certified ROAAS before 1 January 2025. Operators taking delivery of such aeroplanes will not be able to comply with point 26.205. Hence, the date of application of point 26.205 should be postponed to reflect the current industrial capabilities and to permit business continuity for large aeroplane operators. This date postponement should not have a significant impact on safety.












(8)


With effect from 26 August 2023, Implementing Regulation (EU) 2020/1159 inserted in Annex I (Part-26) to Regulation (EU) 2015/640 a new point 26.157. In accordance with that provision, all in-service large aeroplanes certified by the Agency and used in commercial air transport on or after 26 August 2023 are to comply with additional airworthiness requirements for the conversion of Class D cargo or baggage compartments. However, since for certain types of operations, certain large, low-occupancy aeroplanes present a lower risk of an in-flight fire starting in their Class D cargo or baggage compartment and developing into an uncontrollable fire, the operators of those aeroplanes need to be exempted from the obligation to comply with point 26.157 in order to avoid imposing non-proportionate and non-cost-efficient burdens on them. For this reason, Commission Implementing Regulation (EU) 2022/1254 (5) replaced Appendix 1 ‘List of aeroplane models not subject to certain provisions of Annex I (Part-26)’, with a new list, including aeroplane types and models for which point 26.157 is not to apply. Further investigations concluded that other low-occupancy large aeroplane types not included in that list, could also be involved in operations (primarily business operations), presenting a lower risk of an in-flight fire starting in their Class D cargo or baggage compartment and developing into an uncontrollable fire. In order to avoid imposing non-proportionate and non-cost-efficient burdens on their operators, those aeroplane models therefore need to be equally exempted from the obligation to comply with point 26.157.












(9)


With effect from 26 February 2021, Implementing Regulation (EU) 2020/1159 inserted in Annex I (Part-26) to Regulation (EU) 2015/640 a new point 26.370, addressing the continuing airworthiness of ageing large aeroplane structures that requires the operators or owners to prepare the aircraft maintenance programme provided for in Annex I (Part-M) to Commission Regulation (EU) No 1321/2014 (6) so as to include the elements listed in that point. However, aircraft owners do not fall within the scope of Regulation (EU) 2015/640, and the operators should not be directly required to prepare the maintenance programme of the aeroplanes, since that programme is developed by the organisation responsible for the management of continuing airworthiness. Point 26.370 should therefore be made applicable only to operators to ensure that the maintenance programme includes the required elements without requiring the operators to prepare that programme themselves .












(10)


In addition, point 26.370 should not specifically refer to Annex I (Part-M) to Regulation (EU) No 1321/2014, since the scope of Part-M does not cover all large aeroplanes operated by the operators that fall within the scope of Regulation (EU) 2015/640 and to whom point 26.370 applies.












(11)


Other requirements in Regulation (EU) 2015/640 that are related to point 26.370 should be amended to ensure that the instructions for continued airworthiness are made available by the design approval holder to all known operators of the affected aeroplanes and, upon request, to any other person required to comply with such instructions, including the organisations responsible for the management of continuing airworthiness.












(12)


The second sentence of the definition of corrosion prevention and control programme in Article 2, point (g) should be deleted because it is not part of the definition, and the substance of that sentence is already contained in point 26.304 of Annex I (Part-26) to Regulation (EU) 2015/640 and in point (k) of CS 26.370 of certifications specifications for additional airworthiness specifications for operations (CS-26).












(13)


Other requirements, such as those related to ageing aeroplane structures, should be clarified. Additionally, references to major changes and turbine-powered aircraft should be deleted due to their redundancy with the scope of the supplemental type certificate and the definition of large aeroplanes, respectively.












(14)


The measures provided for in this Regulation are based on Opinion No 05/2024 (7) issued by the Agency in accordance with Article 75(2), point (b), and Article 76(1) of Regulation (EU) 2018/1139.












(15)


The measures provided for in this Regulation are in accordance with the opinion of the Committee established by Article 127 of Regulation (EU) 2018/1139,





HAS ADOPTED THIS REGULATION:



Article 1
Regulation (EU) 2015/640 is amended as follows:






(1)


in Article 1, paragraph 2 is replaced by the following:

‘2.   This Regulation applies to:






(a)


operators of:






(i)


aircraft registered in a Member State, unless and to the extent that the Member State has transferred its responsibilities pursuant to the Chicago Convention to a third country and the aircraft is operated by a third-country aircraft operator;










(ii)


aircraft registered in a third country and operated by an aircraft operator established, residing or with a principal place of business in the territory to which the Treaties apply;














(b)


holders of a type certificate, restricted type certificate, supplemental type certificate, design change approval, or repair design approval issued by the Agency in accordance with Commission Regulation (EU) No 748/2012 (*1) or deemed to have been issued in accordance with Article 3 of that Regulation;










(c)


the applicants for a type certificate or a restricted type certificate for a large aeroplane, for which the application was submitted before 1 January 2019 and who are issued with the certificate after 26 August 2020 when specified in Annex I (Part-26).






(*1)  Commission Regulation (EU) No 748/2012 of 3 August 2012 laying down implementing rules for the airworthiness and environmental certification of aircraft and related products, parts and appliances, as well as for the certification of design and production organisations (OJ L 224, 21.8.2012, p. 1, ELI: http://data.europa.eu/eli/reg/2012/748/oj).’;"
                        










(2)


Article 2 is amended as follows:






(a)


points (b) to (ca) are replaced by the following:






‘(b)


“large aeroplane” means an aeroplane that has the Certification Specifications for Large Aeroplanes “CS-25” or equivalent in its certification basis;










(ba)


“small aeroplane” means an aeroplane that has the Certification Specifications for Normal-Category Aeroplanes “CS-23” or equivalent in its certification basis;










(c)


“large helicopter” means a helicopter that has the Certification Specifications for Large Rotorcraft “CS-29” or equivalent in its certification basis;










(ca)


“small helicopter” means a helicopter that has the Certification Specifications for Small Rotorcraft “CS-27” or equivalent in its certification basis;’;














(b)


point (g) is replaced by the following:






‘(g)


“corrosion prevention and control programme” (“CPCP”) means a document reflecting a systematic approach to prevent and to control corrosion in an aeroplane’s primary structure, consisting of basic corrosion tasks, including inspections, areas subject to those tasks, defined corrosion levels and compliance times (implementation thresholds and repeat intervals);’;














(c)


points (i) and (j) are replaced by the following:






‘(i)


“baseline structure” means the structure that is designed under the type certificate or restricted type certificate for that aeroplane model (that is, the “as delivered aeroplane model configuration”);










(j)


“fatigue-critical baseline structure” (“FCBS”) means the baseline structure of an aeroplane that is classified by the type-certificate or restricted type-certificate holder as a fatigue-critical structure;’;














(d)


points (m) and (n) are replaced by the following:






‘(m)


“damage tolerance inspection” (DTI) means a documented inspection requirement or any other maintenance action developed by holders of a type certificate, restricted type certificate, supplemental type certificate or existing major change approval as specified in Annex I (Part-26) as a result of a damage tolerance evaluation, including the areas to be inspected, the inspection method, the inspection procedures (including the sequential inspection steps and acceptance and rejection criteria), the inspection threshold and any repetitive intervals associated with those inspections and also, where appropriate, specification of maintenance actions such as replacement, repair or change;










(n)


“repair evaluation guideline” (“REG”) means a process and implementation schedule for conducting surveys established by the type-certificate or restricted type-certificate holder for repairs that affect fatigue-critical structures to ensure the continued structural integrity of all relevant repairs, as specified in point 26.309 of Annex I (Part-26);’;


















(3)


Article 3 is deleted;










(4)


Annex I (Part-26) is amended in accordance with the Annex to this Regulation.






Article 2
This Regulation shall enter into force on the twentieth day following that of its publication in the Official Journal of the European Union.




This Regulation shall be binding in its entirety and directly applicable in all Member States.
Done at Brussels, 29 November 2024.


For the Commission


The President

Ursula VON DER LEYEN
            





(1)  
            OJ L 212, 22.8.2018, p. 1, ELI: http://data.europa.eu/eli/reg/2018/1139/oj.

(2)  Commission Regulation (EU) 2015/640 of 23 April 2015 on additional airworthiness specifications for a given type of operations and amending Regulation (EU) No 965/2012 (OJ L 106, 24.4.2015, p. 18, ELI: http://data.europa.eu/eli/reg/2015/640/oj).

(3)  Commission Implementing Regulation (EU) 2020/1159 of 5 August 2020 amending Regulations (EU) No 1321/2014 and (EU) No 2015/640 as regards the introduction of new additional airworthiness requirements (OJ L 257, 6.8.2020, p. 14, ELI: http://data.europa.eu/eli/reg_impl/2020/1159/oj).

(4)  Commission 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, ELI: http://data.europa.eu/eli/reg/2012/965/oj).

(5)  Commission Implementing Regulation (EU) 2022/1254 of 19 July 2022 amending Regulation (EU) 2015/640 as regards the introduction of new additional airworthiness requirements (OJ L 191, 20.7.2022,p. 47, ELI: http://data.europa.eu/eli/reg_impl/2022/1254/oj).

(6)  Commission Regulation (EU) No 1321/2014 of 26 November 2014 on the continuing airworthiness of aircraft and aeronautical products, parts and appliances, and on the approval of organisations and personnel involved in these tasks (OJ L 362, 17.12.2014, p. 1, ELI: http://data.europa.eu/eli/reg/2014/1321/oj).

(7)  Opinion No 05/2024 of 21 June 2024 of the European Union Aviation Safety Agency, Part-26 – Helicopter crash-resistant fuel systems, Information on cargo compartment fire protection capabilities, Runway overrun awareness and alerting systems, Conversion of Class D compartments.




ANNEX
Annex I to Regulation (EU) 2015/640 is amended as follows:






(1)


the table of contents is replaced by the following:

                                 ‘CONTENTS







SUBPART A –

GENERAL PROVISIONS











26.10

Competent authority











26.20

Temporary inoperative equipment











26.30

Demonstration of compliance











SUBPART B –

AEROPLANES











26.50

Seats, berths, safety belts, and harnesses











26.60

Emergency landing – dynamic conditions











26.100

Location of emergency exits











26.105

Emergency exit access











26.110

Emergency exit markings











26.120

Interior emergency lighting and emergency light operation











26.150

Compartment interiors











26.155

Flammability of cargo compartment liners











26.156

Thermal or acoustic insulation materials











26.157

Conversion of Class D compartments











26.160

Lavatory fire protection











26.170

Fire extinguishers











26.175

Cargo compartment fire protection











26.200

Landing gear aural warning











26.201

Tyre inflation pressure











26.205

Runway overrun awareness and alerting systems











26.250

Flight crew compartment door operating systems – single incapacitation











26.300

Continuing structural integrity programme for ageing aeroplanes structures – general requirements











26.301

Compliance Plan for (R)TC holders











26.302

Fatigue and damage tolerance evaluation











26.303

Limit of validity











26.304

Corrosion prevention and control programme











26.305

Validity of the continuing structural integrity programme











26.306

Fatigue-critical baseline structures











26.307

Damage tolerance data for existing changes to fatigue-critical structures











26.308

Damage tolerance data for existing repairs to fatigue-critical structures











26.309

Repair evaluation guidelines











26.330

Damage tolerance data for existing supplemental type certificates (STCs), other existing major changes and existing repairs affecting those STCs or changes











26.331

Compliance plan for STC holders











26.332

Identification of changes affecting fatigue-critical structures











26.333

Damage tolerance data for STCs and repairs to those STCs approved on or after 1 September 2003











26.334

Damage tolerance data for STCs and other existing major changes and repairs affecting those STCs or changes approved before 1 September 2003











26.370

Maintenance programme











SUBPART C –

HELICOPTERS











26.400

Fire extinguishers











26.405

Cargo compartment fire protection











26.410

Emergency controls operated underwater











26.415

Underwater emergency exits











26.420

Emergency equipment for flight over water











26.425

Provision of substantiated sea conditions











26.430

Resistance of an emergency flotation system to damage











26.431

Determination of the robustness of emergency flotation system designs











26.435

Automatic deployment of an emergency flotation system











26.440

Fuel system crash resistance











Appendix 1 –

List of aeroplane models not subject to certain provisions of Annex I (Part-26)’;














(2)


point 26.10 is replaced by the following:
‘26.10   Competent authority







(a)


For the purposes of this Annex, the competent authority to which an aircraft operator needs to demonstrate compliance of its aircraft, the design of which has already been certified, with the requirements of this Annex shall be the competent authority responsible for the oversight of that operator or the Agency if the responsibility for the oversight of the operator has been allocated to the Agency in accordance with Article 64 or 65 of Regulation (EU) 2018/1139.










(b)


For the purposes of this Annex, the competent authority to which a holder of a type certificate (TC), restricted TC, supplemental type certificate (STC), design change approval or repair design approval needs to demonstrate compliance with the requirements of this Annex shall be the Agency.’;














(3)


point 26.30 is replaced by the following:
‘26.30   Demonstration of compliance







(a)


The Agency shall issue, in accordance with Article 76(3) of Regulation (EU) 2018/1139, certification specifications as standard means to demonstrate compliance with this Annex. The certification specifications shall be sufficiently detailed and specific to indicate the conditions under which compliance with the requirements of this Annex may be demonstrated.










(b)


Aircraft operators and holders of a TC, restricted TC, STC, design change approval, or repair design approval may demonstrate compliance with the requirements of this Annex by complying with either of the following:






(i)


the specifications issued by the Agency under point (a) or the equivalent certification specifications issued by the Agency under point 21.B.70 of Annex I (Part 21) to Regulation (EU) No 748/2012;










(ii)


technical standards offering an equivalent level of safety to that of the standards included in those certification specifications.














(c)


Holders of a TC, restricted TC, STC, design change approval, or repair design approval shall make available any change to the instructions for continued airworthiness (“ICA”) developed for the purpose of ensuring compliance with this Annex to all known operators of the affected aircraft and, on request, to any other person required to comply with such instructions, including continuing airworthiness management organisations. For the purposes of this Regulation, the ICA also include damage tolerance inspections (“DTIs”), repair evaluation guidelines (“REGs”), a baseline corrosion prevention and control programme (“CPCP”) and a list of fatigue-critical structures (“FCSs”) and airworthiness limitation sections (“ALSs”).’;














(4)


the title of Subpart B is replaced by the following:
‘SUBPART B –   AEROPLANES’;










(5)


point 26.100 is replaced by the following:
‘26.100   Location of emergency exits

Operators of large aeroplanes that are used in commercial air transport and that have a maximum operational passenger seating configuration of more than 19 with one or more emergency exits deactivated shall ensure that the distance(s) between the remaining exits remains (remain) compatible with effective evacuation, except for large aeroplanes that have an emergency exit configuration installed and approved before 1 April 1999.’;










(6)


point 26.156 is replaced by the following:
‘26.156   Thermal or acoustic insulation materials

Operators of large aeroplanes that are used in commercial air transport, and that were type certified on or after 1 January 1958, shall ensure that:






(a)


for large aeroplanes for which the first individual certificate of airworthiness was issued before 18 February 2021, when new thermal or acoustic insulation materials are installed as replacements on or after 18 February 2021, those new materials have flame propagation resistance characteristics which prevent or reduce the risk of flame propagation in the aeroplane;










(b)


for large aeroplanes for which the first individual certificate of airworthiness was issued on or after 18 February 2021, thermal and acoustic insulation materials have flame propagation resistance characteristics which prevent or reduce the risk of flame propagation in the aeroplane;










(c)


for large aeroplanes for which the first individual certificate of airworthiness was issued on or after 18 February 2021 and with a passenger capacity of 20 or more, thermal and acoustic insulation materials (including the means of fastening the materials to the fuselage) installed in the lower half of the aeroplane have flame penetration resistance characteristics which prevent or reduce the risk of flame penetration into the aeroplane after an accident and which ensure survivable conditions in the cabin for the time needed to evacuate the aeroplane.’;














(7)


point 26.157 is replaced by the following:
‘26.157   Conversion of Class D compartments

Operators of large aeroplanes that are used in commercial air transport, and that were type certified on or after 1 January 1958,shall ensure that:






(a)


for large aeroplanes, the operation of which involves the transport of passengers, each Class D cargo or baggage compartment, regardless of its volume, complies with the certification specifications applicable to a Class C compartment;










(b)


for large aeroplanes, the operation of which involves the transport of cargo only, each Class D cargo compartment, regardless of its volume, complies with the certification specifications applicable to either a Class C or a Class E compartment;




This point shall not apply to operators of an aeroplane model listed in Table A.1 of Appendix 1 to this Annex.’;










(8)


the following point 26.175 is inserted:
‘26.175   Cargo compartment fire protection







(a)


For large aeroplanes, as well as for small aeroplanes with a maximum take-off weight (MTOW) greater than 5 700 kg (12 500 lb), for which the individual certificate of airworthiness is first issued on or after 1 January 2025, the holders of:






—


TC or restricted TC, or










—


STC or design change approvals, if the change relates to the aeroplane cargo compartment fire protection capabilities,




shall make available information on the aeroplane design characteristics associated with the cargo compartment fire protection capabilities to all known operators of such aeroplanes.










(b)


For small aeroplanes with a MTOW of 5 700 kg (12 500 lb) or less and equipped with at least one cargo compartment separated from the flight deck, and for which the individual certificate of airworthiness is first issued on or after 1 January 2025, the holders of:






—


TC or restricted TC, or










—


STC or design change approvals, if the change relates to the aeroplane cargo compartment fire protection capabilities,




shall make available information on the aeroplane design characteristics associated with the cargo compartment fire protection capabilities for all cargo compartments that are separated from the flight deck to all known operators of such aeroplanes.










(c)


The information made available in accordance with points (a) and (b) shall be sufficiently detailed to support operators when conducting a risk assessment for the transportation of goods in the cargo compartment.
The information shall be contained in appropriate aeroplane documentation made available to operators and easily identifiable by the operators’ personnel responsible for conducting the risk assessment.










(d)


The design approval holder, who is required to make available the information in accordance with point (a) or (b), shall also make available changes to this information to all known operators of the aeroplanes affected by the change.’;














(9)


in point 26.205, point (a) is replaced by the following:






‘(a)


Operators of large aeroplanes used in commercial air transport shall ensure that every large aeroplane for which the first individual certificate of airworthiness is issued on or after 1 July 2026, is equipped with a runway overrun awareness and alerting system.’;














(10)


point 26.300 is replaced by the following:
‘26.300   Continuing structural integrity programme for ageing aeroplanes structures – general requirements







(a)


A holder of a TC or a restricted TC for a large aeroplane certified on or after 1 January 1958, for which the application for a TC was submitted before 1 January 2019, shall establish a continuing structural integrity programme for ageing aeroplane structures, which shall comply with the requirements set out in points 26.301 to 26.309.










(b)


Point (a) shall not apply to a large aeroplane model which was issued with a TC before 26 February 2021 and which meets any of the following conditions:






(i)


it is listed in Table A.1 of Appendix 1 to this Annex;










(ii)


it is not operated anymore after 26 February 2021;










(iii)


it has not been certified to conduct civil operation with a payload or passengers;










(iv)


it has a restricted TC issued before 26 February 2021 in accordance with damage tolerance requirements, provided that it is not operated beyond 75 % of its design service goal and is primarily operated in support of the approval holder’s manufacturing operation;










(v)


it is certified with a restricted TC and is designed primarily for firefighting.




The exceptions provided for in points (b)(ii) to (v) shall apply only after the holder of a TC or a restricted TC submitted to the Agency before 27 May 2021 for approval a list identifying the aeroplane type and models, variations or serial numbers together with information supporting the reasons why the aeroplane has been included in the list.










(c)


For a large aeroplane model which was issued with a first type certificate before 26 February 2021 and for which an existing change or repair is not and will not be incorporated in any aeroplane in operation on or after 26 February 2022, points (a)(ii) and (iii) of point 26.307 and point 26.308(a)(ii) shall not apply if before 26 February 2022 the holder of a TC or a restricted TC submitted to the Agency for approval the list of all changes and repairs.’;














(11)


in point 26.301, the introductory phrase of point (a) is replaced by the following:

                        ‘A holder of a TC or a restricted TC for a large aeroplane certified on or after 1 January 1958, for which the application for a TC was submitted before 1 January 2019, shall:’;










(12)


in point 26.302, point (a) is replaced by the following:






‘(a)


A holder of a TC or a restricted TC, for a large aeroplane certified to carry 30 passengers or more, or with a payload capacity of 3 402 kg (7 500 lb) or more, certified on or after 1 January 1958, for which the application for a TC was submitted before 1 January 2019, shall carry out a fatigue and damage tolerance evaluation of the aeroplane structure and develop the DTI that will prevent catastrophic failures due to fatigue throughout the operational life of the aeroplane.’;














(13)


points 26.303 to 26.309 are replaced by the following:
‘26.303   Limit of validity







(a)


A holder of a TC or a restricted TC, for a large aeroplane certified on or after 1 January 1958, for which the application for a TC was submitted before 1 January 2019, and certified with a MTOW greater than 34 019 kg (75 000 lb), shall:






(i)


establish a limit of validity (LOV) and include that LOV in an amended ALS;










(ii)


identify existing and new maintenance actions upon which the LOV depends, and develop service information necessary to implement those maintenance actions and submit the service information for the maintenance actions to the Agency in accordance with a binding schedule agreed with the Agency.




The aeroplane structural configurations to be evaluated for the purpose of establishing the LOV shall include all model variations and derivatives approved under the TC before 26 February 2021 and all structural changes and replacements to the structural configurations of those aeroplanes that are required by an airworthiness directive issued before 26 February 2021.
By way of derogation from point (ii), a holder of a TC or a restricted TC for a large aeroplane shall not be required to develop and submit to the Agency the service information for a maintenance action applicable to a large aeroplane model that will not be operated anymore after the scheduled point of submission for the service information of that maintenance action. For this exception to take effect, the holder of a TC or a restricted TC shall inform the Agency not later than the date on which the aeroplane model ceases operation.










(b)


The holder of the TC or the restricted TC shall submit the LOV established in accordance with point (a) and the amendment to the ALS referred to in that point together with the binding schedule to the Agency, before the deadlines established in the following points (i), (ii) and (iii), for approval:






(i)


26 August 2022 for a fatigue-critical structure with a certification basis that does not include a damage tolerance evaluation;










(ii)


26 February 2026 for an aeroplane structure subject to ongoing full-scale fatigue testing on the date of the applicability of this amending Regulation;










(iii)


26 February 2025 for all other aeroplane structures.














(c)


An applicant for a TC or a restricted TC, as referred to in Article 1(2)(c), for a large aeroplane with a MTOW greater than 34 019 kg (75 000 lb), shall:






(i)


establish a LOV and include that LOV in the ALS;










(ii)


identify existing and new maintenance actions upon which the LOV depends, and develop service information necessary to implement those maintenance actions and submit the service information for the maintenance actions to the Agency in accordance with a binding schedule agreed with the Agency.














(d)


The applicant for a TC or a restricted TC, as referred to in Article 1(2), point (c), shall submit the LOV established in accordance with point (c) of this point and the ALS referred to in that point together with the binding schedule to the Agency, for approval:






(i)


before the date approved by the Agency in the plan of the applicant for completing tests and analyses of any aeroplane structure requiring new full-scale fatigue testing to support the establishment of the LOV;










(ii)


before 26 February 2025 for all other aeroplane structures.









26.304   Corrosion prevention and control programme







(a)


A holder of a TC or a restricted TC for a large aeroplane certified on or after 1 January 1958, for which the application for a TC was submitted before 1 January 2019, shall establish a baseline corrosion prevention and control programme (CPCP).










(b)


Unless the baseline CPCP referred to in point (a) has already been approved by the Agency in accordance with point 21.A.3B(c)(1) of Annex I (Part 21) to Regulation (EU) No 748/2012 or in a maintenance review board report (MRBR) approved by the Agency, the holder of a TC or a restricted TC shall submit the CPCP to the Agency before 26 February 2023, for approval.










(c)


An applicant for a TC or a restricted TC, as referred to in Article 1(2), point (c), for a large aeroplane shall establish a baseline CPCP prior to the TC being issued.





26.305   Validity of the continuing structural integrity programme







(a)


A holder of a TC or a restricted TC for a large aeroplane certified on or after 1 January 1958, for which the application for a TC was submitted before 1 January 2019, shall establish and implement a process that ensures that the continuing structural integrity programme remains valid throughout the operational life of the aeroplane, taking into account service experience and current operations.










(b)


The holder of a TC or a restricted TC shall submit a description of the process referred to in point (a) to the Agency before 26 February 2023 for approval. The holder of a TC or a restricted TC shall implement the process within 6 months after its approval by the Agency.










(c)


An applicant for a TC or a restricted TC, as referred to in Article 1(2), point (c), for a large aeroplane, shall establish and implement a process that ensures that the continuing structural integrity programme remains valid throughout the operational life of the aeroplane, taking into account service experience and current operations. It shall submit a description of the process to the Agency before 26 February 2023, or before the issuance of the certificate, whichever occurs later, for approval and shall implement the process within 6 months after its approval by the Agency.





26.306   Fatigue-critical baseline structures







(a)


A holder of a TC or a restricted TC for a large aeroplane certified on or after 1 January 1958, for which the application for a TC was submitted before 1 January 2019, and certified to carry 30 passengers or more, or with a payload capacity of 3 402 kg (7 500 lb) or more, shall identify and list the fatigue-critical baseline structures (FCBS) for all aeroplane model variations and derivatives included in the TC or restricted TC.










(b)


The holder of a TC or a restricted TC shall submit the list of the structures referred to in point (a) to the Agency before 26 August 2021, for approval.










(c)


Upon approval of the list referred to in point (a) by the Agency, the holder of a TC or a restricted TC shall make it available to the holders of a STC or a major change approval that are required to comply with point 26.330, and to all known operators of such aeroplanes and, on request, to organisations responsible for the management of continuing airworthiness to support the operators that are required to comply with point 26.370.










(d)


An applicant for a TC or a restricted TC, as referred to in Article 1(2), point (c), for a large aeroplane to be certified to carry 30 passengers or more, or with a payload capacity of 3 402 kg (7 500 lb) or more, shall identify and list the FCBS for all aeroplane model variations and derivatives included in the TC or restricted TC. It shall submit the list of these structures to the Agency before 26 August 2021, or before the issuance of the certificate, whichever occurs later, for approval.










(e)


Upon approval of the list referred to in point (d) by the Agency, the applicant for a TC or a restricted TC, as referred to in Article 1(2), point (c), shall make it available to all known operators of such aeroplanes and, on request, to organisations responsible for the management of continuing airworthiness to support the operators that are required to comply with point 26.370.





26.307   Damage tolerance data for existing changes to fatigue-critical structures







(a)


A holder of a TC or a restricted TC for a large aeroplane certified on or after 1 January 1958 and certified to carry 30 passengers or more, or with a payload capacity of 3 402 kg (7 500 lb) or more, for changes and fatigue-critical modified structures (FCMS) existing on 26 February 2021 shall:






(i)


review existing design changes and identify all changes that affect FCBS identified in accordance with point 26.306;










(ii)


for each change identified in accordance with point (i), identify any associated FCMS;










(iii)


for each change identified in accordance with point (i), perform a damage tolerance evaluation and establish and document the associated DTIs.














(b)


The holder of a TC or a restricted TC shall submit the list of all FCMS identified in accordance with point (a)(ii) to the Agency before 26 February 2022, for approval.










(c)


The holder of a TC or a restricted TC shall submit the damage tolerance data, including DTI, resulting from the evaluation performed in accordance with point (a)(iii) to the Agency before 26 August 2022, for approval.










(d)


Upon approval by the Agency of the FCMS list submitted in accordance with point (b), the holder of a TC or a restricted TC shall make that list available to the holders of a STC or a major change approval that are required to comply with point 26.330 and to all known operators of such aeroplanes and, on request, to organisations responsible for the management of continuing airworthiness to support the operators that are required to comply with point 26.370.





26.308   Damage tolerance data for existing repairs to fatigue-critical structures







(a)


A holder of a TC or a restricted TC for a large aeroplane certified on or after 1 January 1958 and certified to carry 30 passengers or more, or with a payload capacity of 3 402 kg (7 500 lb) or more, for published repairs existing on 26 February 2021 shall:






(i)


review the repair data and identify each repair specified in the data that affects the FCBS and the FCMS identified in accordance with point 26.306(a) and point 26.307(a)(ii);










(ii)


perform a damage tolerance evaluation for each repair identified in accordance with point (i), unless previously performed.














(b)


The holder of a TC or a restricted TC shall submit the damage tolerance data, including the damage tolerance inspections (DTI), resulting from the evaluation performed in accordance with point (a)(ii) to the Agency before 26 May 2022, for approval, unless it is already approved in accordance with point 21.A.435(b)(2) of Annex I (Part 21) to Regulation (EU) No 748/2012 before 26 August 2022.





26.309   Repair evaluation guidelines







(a)


A holder of a TC or a restricted TC for a large aeroplane certified on or after 1 January 1958 and certified to carry 30 passengers or more, or with a payload capacity of 3 402 kg (7 500 lb) or more, and for which the TC or restricted TC was issued before 11 January 2008, shall develop repair evaluation guidelines (REGs) to establish:






(i)


a process for conducting surveys of affected aeroplanes that enables the identification and documentation of all existing repairs affecting the fatigue-critical structures identified in accordance with point 26.306(a) and point 26.307(a)(ii);










(ii)


a process that enables operators and organisations responsible for the management of continuing airworthiness to obtain a DTI for repairs identified in accordance with point (i);










(iii)


an implementation schedule that provides time frames for conducting aeroplane surveys, obtaining DTIs and incorporating DTIs into the maintenance programme of the aeroplane.














(b)


The holder of a TC or a restricted TC shall submit the REGs developed in accordance with point (a) to the Agency before 26 February 2023, for approval.’;














(14)


points 26.330 to 26.334 are replaced by the following:
‘26.330   Damage tolerance data for existing supplemental type certificates (STCs), other existing major changes and existing repairs affecting those STCs or changes







(a)


A holder of a STC issued before 26 February 2021, or a holder of a major change approval that has been deemed approved in accordance with Article 4 of Regulation (EU) No 748/2012, for large aeroplanes certified on or after 1 January 1958 to carry 30 or more passengers, or with a payload capacity of 3 402 kg (7 500 lb) or more, shall address the adverse effects of those changes and repairs to those changes on the aeroplane structure to support the compliance with point 26.370(a)(ii) and shall comply with the requirements set out in points 26.331 to 26.334.










(b)


Point (a) shall not apply to major changes and repairs to a large aeroplane model first certified before 26 February 2021 when that aeroplane model meets any of the following conditions:






(i)


it is listed in Table A.1 of Appendix 1 to this Annex;










(ii)


it is not operated anymore after 26 February 2021;










(iii)


it has not been certified to conduct civil operation with a payload or passengers;










(iv)


it has a restricted TC and has been certified in accordance with damage tolerance requirements, provided that it is not operated beyond 75 % of its design service goal and is primarily operated in support of the restricted TC holder’s manufacturing operation;










(v)


it is issued with a restricted TC and is designed primarily for firefighting.














(c)


Point (a) shall not apply to major changes and repairs to a large aeroplane first certified before 26 February 2021 when the changes or repairs are not, and will not be, incorporated in any large aeroplane in operation on or after 26 August 2022.










(d)


The exceptions provided for in points (b)(ii) to (v) and (c) shall apply only after the change approval holder submits a list of changes that affect the FCBS, together with information supporting the reasons why each change has been included in the list, to the Agency before 26 February 2022 for approval.





26.331   Compliance plan for STC holders

The approval holder referred to in point 26.330(a) shall:






(a)


establish a compliance plan that addresses the requirements of points 26.332 to 26.334;










(b)


submit the compliance plan referred to in point (a) of this point to the Agency before 25 August 2021, for approval.





26.332   Identification of changes affecting fatigue-critical structures







(a)


The approval holder referred to in point 26.330(a) shall:






(i)


review the changes and identify those changes that affect FCBS;










(ii)


for each change identified in accordance with point (i), identify any associated FCMS;










(iii)


identify the published repairs affecting each change identified in accordance with point (i).














(b)


For a change approval that was issued on or after 1 September 2003, the approval holder referred to in point (a) shall develop and submit a list of the changes and FCMS identified in accordance with points (a)(i) and (ii) to the Agency before 26 February 2022 for approval, and, upon approval by the Agency, make the list available to all known operators of such aeroplanes and, on request, to organisations responsible for the management of continuing airworthiness to support the operators that are required to comply with point 26.370(a)(ii).










(c)


For a change approval that was issued before 1 September 2003, the approval holder referred to in point (a) shall:






(i)


develop and submit a list of the changes identified in accordance with point (a)(i) to the Agency before 26 February 2022, for approval;










(ii)


upon request of operators and organisations responsible for the management of continuing airworthiness to support the operators that are required to comply with point 26.370(a)(ii), identify and list any FCMS associated with the change and submit this data to the Agency within 12 months from the request, for approval;










(iii)


upon approval of any data submitted according to points (c)(i) and (ii), make that data available to all known operators of such aeroplanes and, on request, to organisations responsible for the management of continuing airworthiness to support the operators that are required to comply with point 26.370(a)(ii).









26.333   Damage tolerance data for STCs and repairs affecting those STCs approved on or after 1 September 2003
                                    







(a)


For a change approval that was issued on or after 1 September 2003, the approval holder referred to in point 26.330(a) shall:






(i)


for changes and published repairs identified in accordance with points (a)(i) and (a)(iii) of point 26.332, respectively, perform a damage tolerance evaluation;










(ii)


establish and document the associated DTI, unless this has already been done.














(b)


The approval holder referred to in point (a) shall submit the damage tolerance data resulting from the damage tolerance evaluation performed in accordance with point (a)(i) to the Agency before 26 February 2023, for approval, unless it is already approved in accordance with point 21.B.111 of Annex I (Part 21) to Regulation (EU) No 748/2012.










(c)


By way of derogation from point (b), for changes that did not have a damage tolerance evaluation requirement in the certification basis, the approval holder referred to in point (a) shall submit the damage tolerance data resulting from the damage tolerance evaluation performed in accordance with point (a) to the Agency, within the following deadlines, whichever occurs later, for approval:






(i)


prior to an aeroplane with that change incorporated being operated in accordance with Annex IV (Part-CAT) to Regulation (EU) No 965/2012; or










(ii)


before 26 February 2023.









26.334   Damage tolerance data for STCs and other existing major changes and repairs affecting those STCs or changes approved before 1 September 2003
                                    







(a)


Upon request of operators and organisations responsible for the management of continuing airworthiness, to support the compliance with point 26.370(a)(ii), for a change approval that was issued before 1 September 2003, the approval holder referred to in point 26.330(a) shall:






(i)


for changes and published repairs identified in accordance with points (a)(i) and (a)(iii) of point 26.332, respectively, perform a damage tolerance evaluation;










(ii)


establish and document the associated DTI, unless this has already been done.














(b)


The approval holder referred to in point (a) shall submit the damage tolerance data resulting from the evaluation performed in accordance with point (a)(i) to the Agency:






(i)


within 24 months from receipt of a request, for requests received before 26 February 2023, for approval; or










(ii)


before 26 February 2025 or within 12 months from receipt of a request, whichever occurs later, for requests received on or after 26 February 2023, for approval.’;


















(15)


point 26.370 is replaced by the following:
‘26.370   Maintenance programme







(a)


Operators of large aeroplanes certified on or after 1 January 1958 shall ensure that the maintenance programmes of those aeroplanes include:






(i)


for large aeroplanes certified to carry 30 passengers or more, or with a payload capacity greater than 3 402 kg (7 500 lb), approved DTIs;










(ii)


for large aeroplanes operated in accordance with Annex IV (Part-CAT) to Regulation (EU) No 965/2012 and certified to carry 30 passengers or more, or with a payload capacity greater than 3 402 kg (7 500 lb), a means for addressing the adverse effects that repairs and changes may have on fatigue-critical structures and on inspections provided for in point (a)(i);










(iii)


for large aeroplanes certified with a MTOW greater than 34 019 kg (75 000 lb), an approved LOV;










(iv)


a CPCP.














(b)


The following deadlines shall apply to the obligation referred to in point (a):






(i)


the maintenance programme of the aeroplanes shall be revised to address the requirements of points (a)(i), (ii) and (iv) before 26 February 2024 or before operating the aeroplane, whichever occurs later;










(ii)


the maintenance programme of the aeroplanes shall be revised to address the requirements of point (a)(iii) before 26 August 2021, or 6 months after the publication of the LOV, or before operating the aeroplane, whichever occurs later.














(c)


For a large aeroplane model first certified before 26 February 2021 and:






(i)


that is not operated anymore after 26 February 2024, points (a)(i), (a)(ii) and (a)(iv) shall not apply;










(ii)


that is not operated anymore after 26 August 2021, point (a)(iii) shall not apply;










(iii)


with a restricted TC issued before 26 February 2021 in accordance with damage tolerance requirements, provided that it is not operated beyond 75 % of its design service goal and is primarily operated in support of the approval holder’s manufacturing operation, points (a)(i), (a)(ii) and (a)(iv) shall not apply.














(d)


For a large aeroplane model with a restricted TC issued before 26 February 2021 and the primary purpose of which is firefighting, points (a)(i) and (a)(ii) shall not apply.’;














(16)


the following point 26.405 is inserted:
‘26.405   Cargo compartment fire protection







(a)


For both small and large helicopters equipped with at least one cargo compartment separated from the flight deck, and for which the individual certificate of airworthiness is first issued on or after 1 January 2025, the holders of:






—


TC or restricted TC, or










—


STC or design change approvals, if the change relates to the helicopter cargo compartment fire protection capabilities,




shall make available information on the helicopter design characteristics associated with the cargo compartment fire protection capabilities for all cargo compartments that are separated from the flight deck to all known operators of such helicopters.










(b)


The information made available in accordance with point (a) shall be sufficiently detailed to support operators when conducting a risk assessment for the transportation of goods in the cargo compartment.
The information shall be contained in appropriate helicopter documentation made available to operators and be easily identifiable by the operators’ personnel responsible for conducting the risk assessment.










(c)


The design approval holder, who is required to make available information in accordance with point (a), shall also make available changes to this information to all known operators of the helicopters affected by the change.’;














(17)


the following point 26.440 is added:
‘26.440   Fuel system crash resistance

Operators of small helicopters and large helicopters shall ensure that the likelihood of a post-crash fire is minimised as far as practicable in the design of the fuel system when:






(a)


the helicopter type certificate was issued on or after 2 October 1994, and:






(1)


the helicopter first individual certificate of airworthiness is issued on or after 22 December 2026, or










(2)


the helicopter first individual certificate of airworthiness is issued before 22 December 2026, and:






(i)


if any individual certificate of airworthiness is issued by a Member State on or after 22 December 2024 after an import of the helicopter from a non-Member State, or










(ii)


if:






(A)


the helicopter has been designed for six or more occupants, and is operated on or after 22 December 2031; or










(B)


the helicopter has been designed for five or less occupants, and is operated on or after 22 December 2039.






















(b)


the helicopter type certificate was issued before 2 October 1994, and:






(1)


the helicopter first individual certificate of airworthiness is issued on or after 22 December 2026 or,










(2)


the helicopter first individual certificate of airworthiness is issued before 22 December 2026 and if any individual certificate of airworthiness is issued by a Member State on or after 22 December 2024 after an import of the helicopter from a non-Member State.’;


















(18)


Appendix 1 is replaced by the following:


‘Appendix 1
List of aeroplane models not subject to certain provisions of Annex I (Part-26)

Table A.1










TC holder


Type


Models


Manufacturer serial number


Provisions of Annex I (Part-26) that do NOT apply




The Boeing Company


707


All


 


26.301 to 26.334




The Boeing Company


720


All


 


26.301 to 26.334




The Boeing Company


DC-10


DC-10-10
DC-10-30
DC-10-30F


All


26.301 to 26.334




The Boeing Company


DC-8


All


 


26.301 to 26.334




The Boeing Company


DC-9


DC-9-11,
DC-9-12,
DC-9-13,
DC-9-14,
DC-9-15,
DC-9-15F,
DC-9-21,
DC-9-31,
DC-9-32,
DC-9-32 (VC-9C),
DC-9-32F,
DC-9-32F (C-9A, C-9B),
DC-9-33F,
DC-9-34,
DC-9-34F,
DC-9-41,
DC-9-51


All


26.301 to 26.334




The Boeing Company


MD-90


MD-90-30


All


26.301 to 26.334




FOKKER SERVICES B.V.


F27


Mark 100, 200, 300, 400, 500, 600, 700


All


26.301 to 26.334




FOKKER SERVICES B.V.


F28


Mark 1000, 1000C, 2000, 3000, 3000C, 3000R, 3000RC, 4000


All


26.301 to 26.334




GULFSTREAM AEROSPACE CORP.


G-159


G-159 (Gulfstream I)


All


26.301 to 26.334




GULFSTREAM AEROSPACE CORP.


G-II_III_IV_V


G-1159A (GIII)
G-1159B (GIIB)
G-1159 (GII)


All


26.301 to 26.334




KELOWNA FLIGHTCRAFT LTD.


CONVAIR 340/440


440


All


26.301 to 26.334




LEARJET INC.


Learjet 24/25/31/36/35/55/60


24, 24A, 24B, 24B-A, 24D,24D-A, 24F, 24F-A, 25, 25B, 25C, 25D, 25F


All


26.301 to 26.334




LOCKHEED MARTIN CORPORATION


1329


All


 


26.301 to 26.334




LOCKHEED MARTIN CORPORATION


188


All


 


26.301 to 26.334




LOCKHEED MARTIN CORPORATION


382


382, 382B, 382E, 382F, 382G


All


26.301 to 26.334




LOCKHEED MARTIN CORPORATION


L-1011


All


 


26.301 to 26.334




PT. DIRGANTARA INDONESIA


CN-235


All


 


26.301 to 26.334




SABRELINER CORPORATION


NA-265


NA-265-65


All


26.301 to 26.334




VIKING AIR LIMITED


SD3


SD3-30
Sherpa
SD3 Sherpa


All


26.301 to 26.334




VIKING AIR LIMITED


DHC-7


All


 


26.301 to 26.334




VIKING AIR LIMITED


CL-215


CL-215-6B11


All


26.301 to 26.334




TUPOLEV PUBLIC STOCK COMPANY


TU-204


204-120CE


All


26.301 to 26.334




AIRBUS


A320 series


A320-251N, A320-271N


10033, 10242, 10281 and 10360


26.60




AIRBUS


A321 series


A321-271NX


10257, 10371 and 10391


26.60.




AIRBUS


A330 series


A330-243, A330-941


1844, 1861, 1956, 1978, 1982, 1984, 1987, 1989, 1998, 2007, 2008 and 2011


26.60




ATR-GIE Avions de Transport Régional


ATR 72 series


ATR72-212A


1565, 1598, 1620, 1629, 1632, 1637, 1640, 1642, 1649, 1657, 1660, 1661


26.60




The Boeing Company


737 series


737-8 and 737-9


43299, 43304, 43305, 43310, 43321, 43322, 43332, 43334, 43344, 43348, 43391, 43579, 43797, 43798, 43799, 43917, 43918, 43919, 43921, 43925, 43927, 43928, 43957, 43973, 43974, 43975, 43976, 44867, 44868, 44873, 60009, 60010, 60040, 60042, 60056, 60057, 60058, 60059, 60060, 60061, 60063, 60064, 60065, 60066, 60068, 60194, 60195, 60389, 60434, 60444, 60455, 61857, 61859, 61862, 61864, 62451, 62452, 62453, 62454, 62533, 63358, 63359, 63360, 64610, 64611, 64612, 62613, 64614, 65899, 66147, 66148, 66150


26.60




GULFSTREAM AEROSPACE LP.


Gulfstream G100 series


1125 Astra
1125 Astra SP
G100/Astra SPX


All


26.157




GULFSTREAM AEROSPACE LP


Gulfstream G100 series


Gulfstream G150


All


26.157




GULFSTREAM AEROSPACE LP.


GALAXY G200 series


Gulfstream 200/Galaxy


All


26.157




LEARJET INC.


Learjet Model 45


All


All


26.157




LEARJET INC.


Learjet 24/25/31/36/35/55/60


55, 55B, 55C


All


26.157




LEARJET INC.


Learjet Model 60


All


All


26.157




TEXTRON AVIATION INC.


650 series


650


All


26.157




TEXTRON AVIATION INC.


Cessna 500/550/S550/560/560XL series


500
550
560
560XL
S550


All


26.157




TEXTRON AVIATION INC.


Hawker Series


BAe.125 Series
Hawker 750
Hawker 800XP


All


26.157




TEXTRON AVIATION INC.


CESSNA 750 (Citation X) series


750


All


26.157






                        ’
                     






ELI: http://data.europa.eu/eli/reg_impl/2024/2954/oj
ISSN 1977-0677 (electronic edition)