(1)

have an MTOM of less than 250 g, including payload;

(2)

have a maximum speed in level flight of 19 m/s;

(3)

have a maximum attainable height above the take-off point limited to 120 m;

(4)

be safely controllable with regards to stability, manoeuvrability and the command and control link performance, by a remote pilot following the manufacturer’s instructions, as necessary under all anticipated operating conditions including following the failure of one or, if appropriate, more systems;

(5)

be designed and constructed in such a way as to minimise injury to people during operation, sharp edges shall be avoided, unless technically unavoidable under good design and manufacturing practice. If equipped with propellers, the UA shall be designed in such a way as to limit any injury that may be inflicted by the propeller blades;

(6)

be exclusively powered by electricity;

(7)

if equipped with a follow-me mode and when this function is on, be in a range not exceeding 50 m from the remote pilot, and make it possible for the remote pilot to regain control of the UA;

(8)

be placed on the market with manufacturer’s instructions providing:

(9)

include an information notice published by the European Union Aviation Safety Agency (EASA) providing the applicable limitations and obligations, in accordance with Implementing Regulation (EU) 2019/947;

(10)

Points (4), (5) and (6) do not apply to UAS that are toys in the meaning of Directive 2009/48/EC on the safety of toys.

(1)

be made of materials and have performance and physical characteristics such as to ensure that in the event of an impact at terminal velocity with a human head, the energy transmitted to the human head is less than 80 J, or, as an alternative, shall have an MTOM of less than 900 g, including payload;

(2)

have a maximum speed in level flight of 19 m/s;

(3)

have a maximum attainable height above the take-off point limited to 120 m or be equipped with a system that limits the height above the surface or above the take-off point to 120 m or to a value selectable by the remote pilot; if the value is selectable, clear information about the height of the UA above the surface or take-off point during flight shall be provided to the remote pilot;

(4)

be safely controllable with regards to stability, manoeuvrability and the command and control link performance, by a remote pilot with adequate competency as defined in Implementing Regulation (EU) 2019/947 and following the manufacturer’s instructions, as necessary under all anticipated operating conditions including following the failure of one or, if appropriate, more systems;

(5)

have the requisite mechanical strength for the UA, including any necessary safety factor, and, where appropriate, stability to withstand any stress to which it is subjected to during use without any breakage or deformation that might interfere with its safe flight;

(6)

be designed and constructed in such a way as to minimise injury to people during operation, sharp edges of the UA shall be avoided, unless technically unavoidable under good design and manufacturing practice; if equipped with propellers, the UA shall be designed in such a way as to limit any injury that may be inflicted by the propeller blades;

(7)

in case of a loss of the command and control link, have a reliable and predictable method for the UA to recover the command and control link or if this fails, terminate the flight in a way that reduces the effect on third parties in the air or on the ground;

(8)

unless it is a fixed-wing UA, have a guaranteed A-weighted sound power level LWA determined as per Part 13 not exceeding the levels established in Part 15;

(9)

unless it is a fixed-wing UA, have the indication of the guaranteed A-weighted sound power level affixed on the UA and/or its packaging as per Part 14;

(10)

be exclusively powered by electricity;

(11)

have a unique serial number compliant with standard ANSI/CTA-2063-A-2019, Small Unmanned Aerial Systems Serial Numbers, 2019;

(12)

have a direct remote identification that:

(13)

be equipped with a geo-awareness function that provides:

(14)

if the UA has a function that limits its access to certain airspace areas or volumes, this function shall operate in such a manner that it interacts smoothly with the flight control system of the UA without adversely affecting flight safety; in addition, clear information shall be provided to the remote pilot when this function prevents the UA from entering these airspace areas or volume;

(15)

provide the remote pilot with clear warning when the battery of the UA or its command unit reaches a low level such that the remote pilot has sufficient time to safely land the UA;

(16)

be equipped:

(17)

if equipped with a follow-me mode and when this function is on, be in a range not exceeding 50 m from the remote pilot, and make it possible for the remote pilot to regain control of the UA;

(18)

be placed on the market with manufacturer’s instructions providing:

(19)

include an information notice published by EASA providing the applicable limitations and obligations, in accordance with Implementing Regulation (EU) 2019/947;.

(20)

if equipped with a network remote identification system it shall:

(1)

have an MTOM of less than 4 kg, including payload;

(2)

have a maximum attainable height above the take-off point limited to 120 m or be equipped with a system that limits the height above the surface or above the take-off point to 120 m or to a value selectable by the remote pilot. If the value is selectable, clear information about the height of the UA above the surface or take-off point during flight shall be provided to the remote pilot;

(3)

be safely controllable with regard to stability, manoeuvrability and the command and control link performance, by a remote pilot with adequate competency as defined in Implementing Regulation (EU) 2019/947 and following the manufacturer’s instructions, as necessary under all anticipated operating conditions including following the failure of one or, if appropriate, more systems;

(4)

have the requisite mechanical strength for the UA, including any necessary safety factor, and, where appropriate, stability to withstand any stress to which it is subjected to during use without any breakage or deformation that might interfere with its safe flight;

(5)

in the case of a tethered UA, have a tensile length of the tether that is less than 50 m and a mechanical strength that is no less than:

(6)

be designed and constructed in such a way as to minimise injury to people during operation, sharp edges of the UA shall be avoided, unless technically unavoidable under good design and manufacturing practice; if equipped with propellers, the UA shall be designed in such a way as to limit any injury that may be inflicted by the propeller blades;

(7)

unless tethered, in case of a loss of the command and control link, have a reliable and predictable method for the UA to recover the command and control link or, if it fails, terminate the flight in a way that reduces the effect on third parties in the air or on the ground;

(8)

unless tethered, be equipped with a command and control link protected against unauthorised access to the command and control functions;

(9)

unless it is a fixed-wing UA, be equipped with a low-speed mode selectable by the remote pilot and limiting the ground speed to no more than 3 m/s.

(10)

unless it is a fixed-wing UA, have a guaranteed A-weighted sound power level LWA determined as per Part 13 not exceeding the levels established in Part 15;

(11)

unless it is a fixed-wing UA, have the indication of the guaranteed A-weighted sound power level affixed on the UA and/or its packaging as per Part 14;

(12)

be exclusively powered by electricity;

(13)

have a unique serial number compliant with standard ANSI/CTA-2063-A-2019, Small Unmanned Aerial Systems Serial Numbers, 2019;

(14)

have a direct remote identification that:

(15)

be equipped with a geo-awareness function that provides:

(16)

if the UA has a function that limits its access to certain airspace areas or volumes, this function shall operate in such a manner that it interacts smoothly with the flight control system of the UA without adversely affecting flight safety; in addition, clear information shall be provided to the remote pilot when this function prevents the UA from entering these airspace areas or volumes;

(17)

provide the remote pilot with clear warning when the battery of the UA or its command unit reaches a low level such that the remote pilot has sufficient time to safely land the UA;

(18)

be equipped:

(19)

be placed on the market with manufacturer’s instructions providing:

(20)

include an information notice published by EASA providing the applicable limitations and obligations, in accordance with Implementing Regulation (EU) 2019/947;

(21)

if equipped with a network remote identification system it shall:

(1)

have an MTOM of less than 25 kg, including payload, and have a maximum characteristic dimension of less than 3 m;

(2)

have a maximum attainable height above the take-off point limited to 120 m or be equipped with a system that limits the height above the surface or above the take-off point to 120 m or to a value selectable by the remote pilot. If the value is selectable, clear information about the height of the UA above the surface or take-off point during flight shall be provided to the remote pilot;

(3)

be safely controllable with regard to stability, manoeuvrability and the command and control link performance, by a remote pilot with adequate competency as defined in Implementing Regulation (EU) 2019/947 and following the manufacturer’s instructions, as necessary under all anticipated operating conditions including following the failure of one or, if appropriate, more systems;

(4)

in the case of a tethered UA, have a tensile length of the tether that is less than 50 m and a mechanical strength of no less than:

(5)

unless tethered, in case of a loss of the command and control link, have a reliable and predictable method for the UA to recover the command and control link or, if it fails, terminate the flight in a way that reduces the effect on third parties in the air or on the ground;

(6)

unless it is a fixed-wing UA, have the indication of the guaranteed A-weighted sound power level LWA determined as per Part 13 affixed on the UA and/or its packaging as per Part 14;

(7)

be exclusively powered by electricity;

(8)

have a unique serial number compliant with standard ANSI/CTA-2063-A-2019, Small Unmanned Aerial Systems Serial Numbers, 2019;

(9)

unless tethered, have a direct remote identification that:

(10)

be equipped with a geo-awareness function that provides:

(11)

if the UA has a function that limits its access to certain airspace areas or volumes, this function shall operate in such a manner that it interacts smoothly with the flight control system of the UA without adversely affecting flight safety; in addition, clear information shall be provided to the remote pilot when this function prevents the UA from entering these airspace areas or volumes;

(12)

unless tethered, be equipped with a command and control link protected against unauthorised access to the command and control functions;

(13)

provide the remote pilot with clear warning when the battery of the UA or its command unit reaches a low level such that the remote pilot has sufficient time to safely land the UA;

(14)

be equipped:

(15)

be placed on the market with manufacturer’s instructions providing:

(16)

include an information notice published by EASA providing the applicable limitations and obligations, in accordance with Implementing Regulation (EU) 2019/947;

(17)

if equipped with a network remote identification system it shall:

(1)

have an MTOM of less than 25 kg, including payload;

(2)

be safely controllable and manoeuvrable by a remote pilot following the manufacturer’s instructions, as necessary under all anticipated operating conditions including following the failure of one or, if appropriate, more systems;

(3)

not be capable of automatic control modes except for flight stabilisation assistance with no direct effect on the trajectory and lost link assistance provided that a pre-determined fixed position of the flight controls in case of lost link is available;

(4)

be placed on the market with manufacturer’s instructions providing:

(5)

include an information notice published by EASA providing the applicable limitations and obligations, in accordance with Implementing Regulation (EU) 2019/947.

(1)

allow the upload of the UAS operator registration number required in accordance with Article 14 of Implementing Regulation (EU) 2019/947 and any additional number provided by the registration system; the system shall perform a consistency check verifying the integrity of the full string provided to the UAS operator at the time of registration; in case of inconsistency, the system shall emit an error message to the UAS operator;

(2)

have a unique serial number compliant with standard ANSI/CTA-2063-A-2019, Small Unmanned Aerial Systems Serial Numbers, 2019, affixed to the add-on and its packaging or its manufacturer’s instructions in a legible manner;

(3)

ensure, in real time during the whole duration of the flight, the direct periodic broadcast from the UA using an open and documented transmission protocol, in a way that it can be received directly by existing mobile devices within the broadcasting range, of at least the following data:

(4)

reduce the ability of tampering the functionality of the direct remote identification system; and

(5)

be placed on the market with manufacturer’s instructions providing the reference of the transmission protocol used for the direct remote identification emission and the instruction to:

1.

2.

The manufacturer shall develop the technical documentation in accordance with Article 17 of this Regulation.

3.

The manufacturer shall take all measures necessary so that the manufacturing process and its monitoring ensure compliance of the manufactured product with the technical documentation referred to in point 2 of this Part and with the requirements set out in Parts 1, 5, 6, 16 or 17 which apply to them.

4.

5.

The manufacturers’ obligations set out in point 4 may be fulfilled by an authorised representative, on their behalf and under their responsibility, provided that they are specified in the mandate.

1.

2.

3.

The application shall include:

4.

For the product:

For the specimen(s):

5.

6.

The EU certificate and its annexes shall contain all relevant information to allow the conformity of manufactured products with the examined type to be evaluated and to allow for in service control.

Where the type does not satisfy the applicable requirements of this Regulation, the notified body shall refuse to issue an EU-type examination certificate and shall inform the applicant accordingly, giving detailed reasons for its refusal.

7.

The manufacturer shall inform the notified body that holds the technical documentation relating to the EU-type examination certificate of all modifications to the approved type that may affect the product’s conformity with the essential requirements of this Regulation or the conditions for the certificate’s validity. Such modifications shall require additional approval and attached to the original EU-type examination certificate.

8.

Each notified body shall inform the other notified bodies concerning the EU-type examination certificates and/or any additions thereto which it has refused, withdrawn, suspended or otherwise restricted, and, upon request, concerning the certificates and/or additions thereto which it has issued.

The Commission, the Member States and the other notified bodies may, on request, obtain a copy of the EU-type examination certificates and/or additions thereto. On a reasoned request, the Commission and the Member States may obtain a copy of the technical documentation and the results of the examinations carried out by the notified body.

The notified body shall keep a copy of the EU-type examination certificate, its annexes and additions, as well as the technical file including the documentation submitted by the manufacturer for 10 years after the product has been assessed or until the validity of the certificate expires.

9.

10.

1.

2.

The manufacturer shall take all measures necessary so that the manufacturing process and its monitoring ensure conformity of the manufactured product with the approved type described in the EU-type examination certificate and with the applicable requirements set out in Parts 1 to 6, 16 and 17.

3.

4.

The manufacturer’s obligations set out in point 3 may be fulfilled by their authorised representative, on their behalf and under their responsibility, provided that this is specified in the mandate.

1.

2.

The manufacturer shall operate an approved quality system for design, manufacture, final inspection and testing of the product concerned as specified in point 3 and shall be subject to surveillance as specified in point 4.

3.

4.

5.

A copy of the EU declaration of conformity shall be made available to the relevant authorities upon request.

6.

7.

Each notified body shall inform the other notified bodies of the quality system approvals which it has refused, suspended or withdrawn, and, upon request, of quality system approvals which it has issued.

8.

The manufacturer’s obligations set out in points 3(1), 3(5), 5 and 6 may be fulfilled by their authorised representative, on their behalf and under their responsibility, provided that this is specified in the mandate.

1.

a complete description of the product including:

2.

conceptual design and manufacturing drawings and schemes of components, sub-assemblies, circuits and other relevant similar elements;

3.

descriptions and explanations necessary for the understanding of those drawings and schemes and the operation of the product;

4.

a list of the harmonised standards applied in full or in part, the references of which have been published in the Official Journal of the European Union, and, where those harmonised standards have not been applied, descriptions of the solutions adopted to meet the essential requirements set out in Article 4, including a list of other relevant technical specifications applied. In the event of partly applied harmonised standards, the technical documentation shall specify the parts which have been applied;

5.

copy of the EU declaration of conformity;

6.

where the conformity assessment module in Part 8 has been applied, copy of the EU type examination certificate and its annexes as delivered by the notified body involved;

7.

results of design calculations made, examinations carried out, and other relevant similar elements;

8.

test reports;

9.

copies of the documents that the manufacturer has submitted to the notified body if any involved;

10.

the supporting evidence for the adequacy of the technical design solution. This supporting evidence shall mention any documents that have been used, in particular where the relevant harmonised standards and/or technical specifications have not been applied in full. The supporting evidence shall include, where necessary, the results of tests carried out by the appropriate laboratory of the manufacturer, or by another testing laboratory on his behalf and under his responsibility;

11.

addresses of places of manufacture and storage.

1.

2.

3.

4.

5.

6.

7.

8.

9.

10.

11.

Signed for and on behalf of: …

[place and date of issue]:

[name, function] [signature]:

—

[Name of manufacturer] hereby declares that the UAS [identification of the UAS: type or serial number] is of class … … [for UAS include the class number of the product as defined in Parts 1 to 5, 16 or 17 of this Annex; for a kit of accessories, indicate the class into which the UAS is converted] and has a guaranteed sound power level of …. dB(A) [for non fixed-wing UAS classes 1, 2, 3, 5 and 6 only]

—

and in compliance with Regulations … [list all the Regulations that the product complies with].

—

The full EU declaration of conformity is accessible at the following website: [website address]

(1)

be an aircraft other than a fixed-wing aircraft unless tethered;

(2)

if it is equipped with a geo-awareness function, comply with paragraph (10) of Part 4;

(3)

during flight, provide the remote pilot with clear and concise information on the height of the UA above the surface or take-off point;

(4)

unless tethered, be equipped with a low-speed mode selectable by the remote pilot and limiting the ground speed to not more than 5 m/s;

(5)

unless tethered, provide means for the remote pilot to terminate the flight of the UA, which shall:

(6)

unless tethered, provide the remote pilot with means to continuously monitor the quality of the command and control link and receive an alert when it is likely that the link is going to be lost or degraded to the extent of compromising the safe conduct of the operation, and another alert when the link is lost; and

(7)

in addition to the information indicated in point (15)(a) of Part 4, include in the manufacturer’s instructions a description of the means to terminate the flight required in point (5).

(8)

A class C5 UAS may consist in a class C3 UAS fitted with an accessories kit that ensures the conversion of the UAS C3 into a class C5 UAS. In this case, the class C5 label shall be affixed on all the accessories.

(1)

not alter the compliance of the class C3 UAS with the requirements of Part 4;

(2)

ensure compliance of the UAS fitted with the accessories kit with all additional requirements defined in this Part with the exception of point (3) above; and

(3)

be accompanied by manufacturer’s instructions providing:

(1)

have a maximum ground speed in level flight of not more than 50 m/s;

(2)

if it is equipped with a geo-awareness function, comply with paragraph (10) of Part 4;

(3)

during flight, provide the remote pilot with clear and concise information on the geographical position of the UA, its speed and its height above the surface or take-off point;

(4)

provide means to prevent the UA from breaching the horizontal and vertical limits of a programmable operational volume;

(5)

provide means for the remote pilot to terminate the flight of the UA, which shall:

(6)

provide means to programme the UA trajectory;

(7)

provide the remote pilot with means to continuously monitor the quality of the command and control link and receive an alert when it is likely that the link is going to be lost or degraded to the extent of compromising the safe conduct of the operation, and another alert when the link is lost; and

(8)

in addition to the information indicated in point (15)(a) of Part 4, include in the manufacturer’s instructions: