MODUK DEF STAN 00-970: PART 9 PDF

APPLICABILITY AND SCOPE

General

This Part of the Defence Standard has been written specifically to cover the design and airworthiness requirements for UAV Systems as defined in clause 1.3.

This Part of the Defence Standard does not differentiate between target drones, surveillance, stealth or combat UAV Systems that are, or have been, designed from the outset for operation without an on-board pilot. Neither does it give mandatory requirements for the method of control or launch to be used. These aspects shall be identified and covered in the appropriate UAV System Requirements Specification.

The operational role of the UAV System will determine its complexity and the safe guards needed to ensure that it is capable of performing its defined tasks safely.

Scope

The mandatory requirements set out in this standard are those basic requirements needed for the design and development of airworthy UAV Systems for all three UK Armed Services.

In addition to the mandatory requirements set out in this document, the airworthiness standards set out in NATO STANAG 4671 Unmanned Aerial Vehicles System Airworthiness Requirements (USAR) Edition 2 are also mandated, supplemented by the following UK national reservations.

UK national reservations:

 Amend USAR paragraph U50. Insert new paragraph U50(c) Demonstrate that there is adequate margin (e.g. 15%, to be agreed with the Certifying Authority) between V_s and V_{min FCS} (i.e. to take account of gust) and that V_{min FCS is} robust.

 Insert after USAR paragraph 201(ii).iii) V_minDEMO to be equivalent to V_minFCS

 Amend USAR paragraph AMC.1309(b). Insert the additional sentence at (5)(c)(i). more severe criteria may be needed for large aircraft; Insert the additional sub-paragraphs after (5)(c)(1).

 For large aircraft from 5,700kg up to 20,000kg MTOW (with the exception of propeller-driven twin-engine UAS, refer paragraph B). At UAV system level, the combination of all Catastrophic failure conditions is characterised by an occurrence of 10-6 per flying hour or less (with the calculation method subject to Certifying Authority agreement).

 For propeller-driven twin-engine UAS from 8,618kg up to 20,000kg MTOW, at UAV system level, the combination of all Catastrophic failure conditions is characterised by an occurrence of 10-6 per flying hour or less (with the calculation method subject to Certifying Authority agreement).