ISO/TC 20 - Aircraft and space vehicles

This document addresses the design process of a collocation and the basic contents of collocation design process which include considerations, initial collocation strategy design, simulation evaluation of collocation strategy, optimal collocation strategy selection and collocation agreement. This document gives guidelines for multi-geo spacecraft collocation, and it applies in particular to multi-geo constellation.

This document provides the baseline standard on the subject of testing at the system, subsystem and unit levels for applicable unmanned spacecraft programmes. It also provides the requirements for documentation associated with testing activities. This document contains provisions for qualification and acceptance testing, or proto-flight testing (PFT). It assumes that hardware development is complete.

This document defines the Application Program Interface in terms of: the components that provide the services of the API; the functionality provided by each of the components; the interfaces provided by each of the components; and the externally visible behavior associated with the interfaces exported by the components. It does not specify: individual implementations or products; the internal design of the components; and the technology used for communications. This document defines those aspects of the Application Program Interface, which are common for all SLE service types or for a subset of the SLE service types, e.g., all return link services or all forward link services. It also defines a framework for specification of service type-specific elements of the API. Service-specific aspects of the API are defined by supplemental Recommended Practice documents for SLE return link services (references [10], [11], and [12]) and SLE forward link services (references [13] and [14]). This document for the Application Program Interface responds to the requirements imposed on such an API by the CCSDS SLE transfer service Recommended Standards that were available when this document was released.

This document specifies two standard message formats for use in transferring spacecraft attitude information between space agencies: the Attitude Parameter Message (APM) and the Attitude Ephemeris Message (AEM). Such exchanges are used for: - preflight planning for tracking or attitude estimation support; - scheduling attitude and data processing support; - carrying out attitude operations; - performing attitude comparisons; - carrying out attitude propagations and/or sensor predictions; - testing to initialize sub-system simulators (communications, power, etc.). This document includes sets of requirements and criteria that the message formats have been designed to meet. For exchanges where these requirements do not capture the needs of the participating agencies, another mechanism may be selected.

The purpose of this document is to define the Space Link Extension (SLE) Return Operational Control Fields (ROCF) service in conformance with the SLE Reference Model (reference [1]). The ROCF service is an SLE transfer service that delivers to a mission user all operational control fields from one master channel or one virtual channel. This document defines, in an abstract manner, the ROCF service in terms of: the operations necessary to provide the service; the parameter data associated with each operation; the behaviors that result from the invocation of each operation; and the relationship between, and the valid sequence of, the operations and resulting behaviors. It does not specify: individual implementations or products; the implementation of entities or interfaces within real systems; the methods or technologies required to acquire telemetry frames from signals received from a spacecraft; the methods or technologies required to provide a suitable environment for communications; or the management activities required to schedule, configure, and control the ROCF service. NOTE  –   Reference [1] defines the Return Master Channel Operational Control Field (Rtn MC-OCF) service and the Return Virtual Channel Operational Control Field (Rtn VC-OCF) service as two distinct services. Subsequent study has indicated that it is preferable to define one service that provides the functionality of both. The ROCF service defined here does just that. It is anticipated that a future issue of reference [1] will take the same approach, deleting the Rtn MC-OCF and Rtn VC-OCF services and replacing them with the Rtn OCF service.

The purpose of this document is to provide a common reference and framework of standards for digital motion video and imagery, and to provide recommendations for utilization of international standards for sharing or distributing motion video and imagery between spacecraft elements and ground systems. The scope of this document includes traditional real-time streaming video and television, including human and robotic spacecraft-to-spacecraft and spacecraft-to-ground systems, as well as video recorded and distributed later, either as a real-time stream or as a file transfer. In this context, real-time streaming includes all modes where video is sent from a spacecraft in a continuous stream and is intended for immediate use when received, regardless of the latency of the transmission path. Other specialized motion imagery applications, such as high-speed scientific motion imagery and multi-spectral motion imagery, are not addressed in this document. However, if a specialized imagery camera system has a requirement to interface to spacecraft systems in a video mode, it would be required to match these interfaces. Ground-systems-to-ground-systems video distribution is obviously a key component of the entire video system. However, this is not the primary focus of this document. Currently, there are significant differences in the ways mission video products are exchanged between the various space agencies on the ground. This is the result of differences in network topologies between space agencies, and agreements for video sharing. Those differences preclude there being a standard methodology for delivering video imagery between agencies. Prior to the commencement of video transmission between space agencies, system design reviews and performance testing should be done between the ground systems in use to assure operability when video imagery comes from spacecraft.

This document defines, in an abstract manner, the RAF service in terms of: the operations necessary to provide the service; the parameter data associated with each operation; the behaviors that result from the invocation of each operation; and the relationship between, and the valid sequence of, the operations and resulting behaviors. It does not specify: individual implementations or products; the implementation of entities or interfaces within real systems; the methods or technologies required to acquire telemetry frames from signals received from a spacecraft; the methods or technologies required to provide a suitable environment for communications; or the management activities required to schedule, configure, and control the RAF service.

The purpose of this document is to define the Space Link Extension (SLE) Return Channel Frames (RCF) service in conformance with the SLE Reference Model (reference [1]). The RCF service is an SLE transfer service that delivers to a mission user all telemetry frames from one master channel or one virtual channel. This document defines, in an abstract manner, the RCF service in terms of: the operations necessary to provide the service; the parameter data associated with each operation; the behaviors that result from the invocation of each operation; and the relationship between, and the valid sequence of, the operations and resulting behaviors. It does not specify: individual implementations or products; the implementation of entities or interfaces within real systems; the methods or technologies required to acquire telemetry frames from signals received from a spacecraft; the methods or technologies required to provide a suitable environment for communications; or the management activities required to schedule, configure, and control the RCF service. NOTE  –   Reference [1] defines the Return Master Channel Frames (Rtn MC Frames) service and the Return Virtual Channel Frames (Rtn VC Frames) service as two distinct services. Subsequent study has indicated that it is preferable to define one service that provides the functionality of both. The RCF service defined here does just that. It is anticipated that a future issue of reference [1] will take the same approach, deleting the Rtn MC Frames and Rtn VC Frames services and replacing them with the RCF service. Â

This document defines the Forward Space Packet (FSP) service in conformance with the transfer services specified in reference [1], Cross Support Reference Model―Part 1: SLE Services. The FSP service is a Space Link Extension (SLE) transfer service that enables a mission to send Space Packets to a spacecraft in sequence-controlled or expedited mode. This document defines, in an abstract manner, the FSP service in terms of: the operations necessary to provide the transfer service; the parameter data associated with each operation; the behaviors that result from the invocation of each operation; and the relationship between, and the valid sequence of, the operations and resulting behaviors. It does not specify: individual implementations or products; the implementation of entities or interfaces within real systems; the methods or technologies required to radiate Space Packets to a spacecraft and to acquire telemetry frames from the signals received from that spacecraft for extraction of the Operational Control Field; the methods or technologies required for communications; or the management activities necessary to schedule, configure, and control the FSP service. NOTE  –   While the FSP service as described in reference [1] is conceived to handle a variety of packet data structures, this version of the FSP Recommended Standard is restricted to the handling of Space Packets as defined in reference [6]. This version of the FSP Recommended Standard is specific to the transfer of Space Packets to be transmitted via the Telecommand protocol stack as defined in references [3], [4], and [5]. The Cross Support Reference Model (reference [1]) specifies that the FSP service may also be used in conjunction with the Advanced Orbiting System protocol stack, but that mode of operation is outside the scope of this version of the Recommended Standard. The FSP service is provided in the online delivery mode, as defined in reference [1]. The offline delivery mode is the subject of further study.

This document defines the Communications Link Transmission Unit (CLTU) service in conformance with the transfer services specified in reference [1], Cross Support Reference Model—Part 1: SLE Services. The Forward CLTU service is a Space Link Extension (SLE) transfer service that enables a mission to send Communications Link Transmission Units (CLTUs) to a spacecraft. This document defines, in an abstract manner, the Forward CLTU service in terms of: the operations necessary to provide the transfer service; the parameter data associated with each operation; the behaviors that result from the invocation of each operation; and the relationship between, and the valid sequence of, the operations and resulting behaviors. It does not specify: individual implementations or products; the implementation of entities or interfaces within real systems; the methods or technologies required to radiate data to a spacecraft and to acquire telemetry frames from the signals received from that spacecraft for extraction of the Operational Control Field; the methods or technologies required for communications; or the management activities necessary to schedule, configure, and control the Forward CLTU service.

1.1 This document provides general utilization requirements and recommendations and calculation methods adequate to guarantee the effectiveness and ultimate strength of tie-down/lashing arrangements performed to restrain cargo on board civil transport aircraft during flight, including the following: a) cargo loaded and tied down onto airworthiness approved air cargo pallets, themselves restrained into aircraft lower deck or main deck or upper deck cargo systems meeting the restraint requirements of air cargo pallets approved in accordance with ISO8097 (NAS 3610) or ISO 21100, or b) additional tie-down on aircraft structure when necessitated by pallet maximum gross mass or centre of gravity limits, or c) non-unitized individual pieces of cargo, or pieces of cargo placed onto an unrestrained pallet (floating pallet) into either lower deck, main deck or upper deck containerized cargo compartments of an aircraft, when using for this purpose restraint slings (wire rope cables) specified in ISO 20291-1. 1.2 Restraint slings as specified in this document can also be used for permanent or semi-permanent attachment of a special purpose device, such as aircraft engine transport stand (see ISO 11241), horse stall (see ISO 9469), automobile transport device (see ISO 8268) or other, whether or not airworthiness approved, onto an aircraft pallet. 1.3 This document applies to cargo tie-down/lashing arrangements using exclusively air cargo restraint slings conforming to ISO 20291-1. NOTE      Where tie-down is performed onto aircraft structure as per 1.1 b) or c), additional restrictions can be stated in the aircraft's authority approved Weight and Balance Manual. 1.4 This document specifies industry recognized means of complying with airworthiness authorities general regulations applicable to load securing on board civil transport aircraft (see 14 CFR Part 25 and EASA CS-25, CCAR-25 or Japanese Airworthiness Standard Part 3), and aircraft manufacturers authority approved Weight and Balance Manuals for each aircraft type as specified therein. 1.5 The wire rope slings in this document are intended exclusively for restraint purposes on board aircraft and are not intended to be used as lifting slings for handling or any other purpose.

This document specifies the design criteria and testing methods adequate to guarantee the ultimate strength and operational dependability of cargo restraint sling assemblies made of steel wire rope, with a 22,25 kN (5 000 lbf) rated ultimate load capability, as can be used by the airline industry in order to restrain on board civil transport aircraft during flight, including the following: —   cargo loaded and tied down onto airworthiness approved air cargo pallets, themselves restrained into aircraft lower deck, main deck or upper deck cargo systems and meeting the requirements of ISO 8097 (NAS 3610) or ISO 21100, or —   non-unitized individual pieces of cargo, or pieces of cargo placed onto an unrestrained ("floating") pallet into either lower deck, main deck or upper deck containerized cargo compartments of an aircraft, to be restrained onto aircraft structure attachment (tie-down) points. Two types of wire rope restraint slings are defined: a) type A: adjustable length restraint sling assemblies, including a tension retaining device and termination fittings attached to the wire rope end eyes; b) type B: fixed length restraint sling extensions, to be used in conjunction with a type A cable; extensions are usually terminated at both ends by eyes, without additional fittings, and can be attached through hooks or shackles. The cables specified in this document are intended exclusively for restraint purposes on board aircraft, and not for use as lifting slings.

This document defines the geometry of the interface of removable 24° cone couplings for fluid systems in aircraft. The connection with the pipe of each one of the connecting elements can be of different design. This document specifies the dimensions which allow the interchangeability of the male and female elements and of the nut used for the connection. The dimensions define the maximum volume of the male fitting.

This document establishes a system for sealing the port connection of couplings used in the aerospace industry. It specifies dimensions to achieve interchangeability of the port connection, the fitting end and a seal. The seal can be a standard O‑ring or a special ring.

This document specifies a common process for selecting and implementing meteoroid and space debris environment models used in the impact flux assessment for design and operation of spacecraft and other purposes. This document provides guidelines and requirements for the process.

The document considers peculiarities of the space environment impact on a special kind of materials: nanostructured materials (i.e. materials with structured objects which size in at least one dimension lies within 1Â nm to 100Â nm) and specifies the methods of mathematical simulation of such processes. It emphasizes the necessity of applying multiscale simulation approach and does not include any special details concerning concrete materials, elements of spacecraft construction and equipment, etc. This document provides the general description of the methodology of applying computer simulation methods which relate to different space and time scales to modelling processes occurring in nanostructured materials under the space environment impact. The document can be applied as a reference document in spacecraft designing, forecasting the spacecraft lifetime, conducting ground-based tests, and analysing changes of material properties during operation.

This document specifies the requirements for producing and testing an unsealed anodic coating on titanium and titanium alloys. The anodic coating is produced by the sulfuric acid process. The coating is used with solid film lubricants for protection of titanium fasteners against galling, for limited protection of less noble metals against galvanic corrosion when in contact with titanium or for other approved uses.

This document specifies the requirements for producing and testing a general purpose chemical conversion coating on aluminium alloys. The chemical conversion coating is used in the manufacture of aerospace products in order to improve paint adhesion and resistance to corrosion. This process can also be used for touch-up of anodic coatings.

This document establishes the baseline requirements for the design, fabrication and testing of space flight pressure components. It also establishes the requirements for the assembly, installation, test, inspection, operation and maintenance of the pressure systems in spacecraft and launch vehicles. These requirements, when implemented on a particular space system, ensure a high level of confidence in achieving safe and reliable operation. This document applies to all pressure components other than pressure vessels and pressurized structures in a pressure system. It covers lines, fittings, valves, bellows, hoses and other appropriate components that are integrated to form a pressure system. The requirements for pressure vessels and pressurized structures are set forth in ISOÂ 14623. This document does not apply to engine components.

This document contains information on the design and operational practices for launch vehicle orbital stages for mitigating space debris. This document provides information to engineers on the requirements and recommendations in the space debris mitigation standards to reduce the growth of space debris by ensuring that launch vehicle orbital stages are designed, operated, and disposed of in a manner that prevents them from generating debris throughout their orbital lifetime.

This document specifies the dimensions of normal bihexagonal head bolts, with close or large tolerance normal shank and short or medium length MJ threads, in metallic material, coated or uncoated, with strength classes less than or equal to 1 100 MPa. This document is applicable to the compilation of aerospace product standards.

This document establishes the requirements for simulation of the space control system, including the objective, architecture and procedure, etc. This document is applicable to four phases of control system development, including conceptual design, detailed design, prototype and integrated system. The control system referred to in this document is the flight control system for guidance, navigation and control (GNC) of space systems which include launch vehicle, satellite and spaceship, etc. This document establishes a minimum set of requirements for simulation of the flight control system, and provides guidance to engineers on what to simulate in each phase of control system development. The requirements are generic in nature because of their broad applicability to all types of simulations. Implementation details of the requirements are addressed in project-specific standards, requirements, and handbooks, etc.

This document defines detailed space debris mitigation requirements and recommendations for the design and operation of launch vehicle orbital stages in Earth orbit. The requirements defined in this document are applicable for: — avoiding the release of space debris; — disposing of a launch vehicle orbital stage after the end of its mission so as to avoid a break-up in orbit; — disposing of a launch vehicle orbital stage after the end of its mission so as to minimize interference with the protected regions; — safely re-entering a launch vehicle orbital stage.

This document establishes the general requirements for variable displacement uni-directional and bi-directional hydraulic motors, suitable for use in aircraft hydraulic systems at pressures up to 35 000 kPa (5 000 psi). These requirements include: — design requirements; — test requirements. Primary and secondary function motors (see Clause 4) are covered in this document; however, actuators with internal rotation angle limits and low-speed motors are not covered. This document is intended to be used in conjunction with the detail specification that is particular to each application.

This document describes the procedures for training personnel who will be involved in the operation of unmanned aircraft systems (UAS). This document defines: a) knowledge, skill, attitude and qualification criteria that are needed for UAS pilots and training organizations that provides training to trainees of UAS remote pilots and other personnel involved in UAS operations; b) training curriculum and contents for specific learning courses; c) qualification and confirmation criteria for the training organizations; d) general procedures for providing training of UAS personnel. The requirements for a specific course as described in the annexes can be more restrictive in some cases.

The following documents are referred to in the text in such a way that some or all of their content constitutes requirements of this document. For dated references, only the edition cited applies. For undated references, the latest edition of the referenced document (including any amendments) applies. ISO 7500‑1, Metallic materials — Calibration and verification of static uniaxial testing machines — Part 1: Tension/compression testing machines — Calibration and verification of the force-measuring system

This document specifies the lead and runout requirements for rolled external threads for aerospace construction, and the inspection method to be used in case of dispute. It is applicable whenever it is referenced in a definition document.

This document specifies the lead and runout thread and undercut requirements for internal threads (blind tapped holes) for aerospace construction. It is applicable whenever it is referenced in a definition document.

This document contains information on the design and operational practices for launch vehicle orbital stages for mitigating space debris. This document provides information to engineers on what are required or recommended in the family of space debris mitigation standards to reduce the growth of space debris by ensuring that spacecraft is designed, operated, and disposed of in a manner that prevents them from generating debris throughout their orbital lifetime.

This document provides detailed information on the various methods of assessing the health status of lithium-ion space batteries in flight and makes recommendations to battery suppliers, spacecraft manufacturers and operators to ease this assessment.

This document specifies criteria and requirements for the use of explosive systems and explosive devices commonly used on spacecraft and other space products, including launch vehicles and space vehicle systems. It addresses the aspects of design, analysis, verification, manufacturing, operations and safety. To the greatest extent possible, requirements from past and existing standards have been analyzed, selected and tailored to be incorporated herein. In addition, the requirements herein include those generated as a result of lessons learned from launch and space vehicle programs. NOTE Specific requirements for man-rating are not addressed.

This document establishes general test requirements for launch vehicles equipped with liquid-propellant engines, launched from stationary ground-, sea- and air-based launchers, in all phases of their development.

This document provides requirements for launch system designers or interface designers regarding interfaces between LV and EGSE, which is used to support on-line processing. It defines electrical interface types, design requirements, environment requirements, verification methods (analyses and tests), and interface check operation requirements. This document is intended to minimize design costs and reduce risks from errors resulting from miscommunication. It does not limit LV or EGSE organizational requirements to specify a unique interface.

This document specifies the minimum requirements for airworthiness approval of air cargo pallets, nets and containers, generally designated as air cargo unit load devices (ULD). This document is intended to provide a uniform technical reference for air cargo unit load devices approval. As a prerequisite, it is presupposed that the applicable general civil aviation requirements and the aircraft manufacturer's approved Weight and Balance Manual are followed. This document defines the minimum performance requirements and test parameters for air cargo unit load devices requiring approval of airworthiness for installation in an approved aircraft cargo compartment and restraint system that complies with the cargo restraint and occupant protection requirements of EASA CS-25 or 14 CFR Part 25, except for the 9,0 g forward ultimate inertia force of § 25.561(b) (3) (ii). This document applies to airworthiness approved air cargo unit load devices intended for carriage on board civil transport category airplanes type certificated under EASA CS-25 or 14 CFR Part 25, or equivalent. This document exclusively applies to unit load devices airworthiness approval and testing parameters. It does not apply to aircraft design or aircraft operating requirements, which are provided by the approved Weight and Balance Manual for each aircraft type. Other aspects that do not directly pertain to air cargo unit load devices airworthiness approval and testing are not covered by this document and are defined in other International Standards (see Bibliography), e.g.: — ULD design specifications, — ULD in service damage limits, — ULD restraint malfunction limitations, — ULD test methods, — ULD load distribution models, — ULD maximum allowable contours, — ULD CG (centre for gravity) location control means, — ULD pressure equalization methods, — ULD utilization guidelines. Air cargo unit load devices qualified prior to publication of this document were approved in accordance with the requirements of ISO 8097:2001. This document is intended as a TSO approval reference for all new models of unit load devices in the sizes and types it covers, in replacement of ISO 8097. For air cargo unit load devices the size or type of which is not covered in this document, see the requirements of ISO 8097:2001, if their size or type is contained therein, or other equivalent criteria, if not. NOTE 1 ISO 8097 is based on USA National Aerospace Standard NAS 3610 revision 10:1990, Specification for Cargo Unit Load Devices. NOTE 2 The requirements for cargo covers are not defined in this document, except insofar as net restraint is incorporated therein.

This document specifies the dimensions of connections for starting aircraft engines by air, which are necessary to ensure international interchangeability of connectors with adaptors. lt also gives the minimum clearances required on the aircraft to provide adequate access for the ground adaptor.

This document defines terms and definitions relating to unmanned aircraft systems that are widely used in science and technology.

This document defines the tolerances of form and position of metric nuts meant for aerospace construction. These tolerances comply with ISO 1101, ISO 2692 and ISO 5459.

This document presents the requirements for requirements management (RM) for space projects. This document addresses the space programme/project management requirements, applicable through a top-down approach in a contractual relationship between customers and suppliers. The objective of this document is to state and establish a common reference framework for all the customers and suppliers in the space sector to deploy requirements management for all space products and projects. This document on requirements management includes — a definition of the requirements management scope for the space sector, — the standard processes for requirements management within the product lifecycle management, and — a set of rules for requirements management activities to be implemented by the actors (customers and suppliers), including rules derived from best practices. The primary target audience for this document includes — the requirements management/systems engineering process owners of the customers and suppliers, — the programme/project managers managing the space programmes, and — the chief engineers and the quality managers. The term "programme" is understood as a group of several projects. Both "programme" and "project" can be used in the same context throughout this document. In addition, this document allows customer/supplier flexibility in its implementation and tailoring.

This document provides results of a survey on UTM which indicates aggregated data from survey respondents. It does not cover detailed analysis of regions and organizations. UTM is expected to reveal hundreds of commercial applications already in place, as well as social systems as their background conditions. The results can be used to analyze benefits and gaps for possible future standardization topics in consultation with authorities such as ICAO.

This document specifies characteristics of hose assemblies with corrosion‑resistant metallic braid and convoluted polytetrafluoroethylene (PTFE) inner tube for use in aircraft fluid systems at temperatures between ‑55 °C and +200 °C and at nominal pressures, depending on bore size, up to 6,8 MPa. Special approval from the proper national authority can be required if these hoses are to be part of a pressurized gas storage system. Two types of hose assembly are covered in this document: — Type 1: Non‑conductive inner tube; and — Type 2: Conductive inner tube.

This document defines the industry agreed model for load distribution on air cargo unit load devices (ULD) bases to apply the maximum allowable centre of gravity (C.G.) eccentricity. Its purpose is to establish a common reference load distribution algorithm for: a) comparable and repeatable ULD testing methods, or equivalent numeric simulations; b) aircraft structure and cargo systems design assumptions, consistent with existing airframers practices; and c) definition of operators unit load devices utilization rules and cargo build-up training programs. It applies to all types of unit load devices intended for use on board civil transport aircraft and airworthiness approved in accordance with the performance requirements and testing parameters of either ISO 21100 or, as applicable, ISO 8097. It also applies to non-airworthiness approved (non-certified) containers as defined in ISO 4118, the utilisation of which is controlled by the provisions of the aircraft type's Weight and Balance Manual and other airframe manufacturer's documents.

This document specifies the design, performance and testing requirements for "Cargo Stopper" air cargo restraint accessories with a 22 250 N (5 000 lbf) rated load capacity, to be used in conjunction with air cargo restraint straps meeting ISO 16049-1 (TSO/ETSO ̶ C172), or air cargo restraint slings meeting ISO 20291-1, with the same rated load. Cargo stopper devices designed to this document are intended to be used in either of the following typical instances: a) to ensure restraint/tie-down of a piece of cargo that does not lend itself to either direct hooking of tie-down straps or passing a strap around without risk of slippage; a common example is long shaped cargo items with a narrow cross-section, whether or not overhanging from the pallet, individual or in bundles, e.g. pipes or beams; see ISO 16049-2:2020, 7.4; b) to restrain cargo smaller than the pallet net's mesh, or identified as "piercing" cargo, presenting a hazard to the aircraft in the event of it being released during flight; c) when a crate containing cargo, even though its cross-section is large enough to be directly tied-down with the pallet net or restraint straps, contains or can contain a heavy item, e.g. a piece of machinery, shaft, or similar, with a cross-section lower than the pallet net's mesh size; NOTE Such "hidden" items have been known to break free from insufficiently strong crates when subjected to in-flight accelerations, then pass due to their small size through the net mesh restraining the crate and be released into the cargo compartment. d) to assist in tying-down odd-shaped cargo pieces where it is difficult or not allowed to directly attach tie-down straps or pass them around the load in an effective manner.

This document defines procedures, contents and requirements for test reviews which are composed of the Test Readiness Review (TRR), Post Test Review (PTR) and Test Review Board (TRB). This document is applicable to tests of space systems and space products, including environment tests and functional and performance tests, especially for system level tests and complicated tests.

This document specifies requirements for the classification and grading of civil unmanned aircraft system (UAS). This document applies to heavier than air aircraft as well as lighter than air aircraft of any possible architecture. This document applies to the industrial conception, development, design, production and delivery of civil UAS. It also applies to modification, repair and maintenance of civil UAS. The characteristics in this document can be used individually or in combination, to meet specific needs of the classification and grading of civil UAS. Risk-based categorization of UAS operations is prerogative of the aviation authorities and it is hence out of scope of this document.

This Recommended Standard defines the Monitored Data service in terms of: a) the CSTS procedures that constitute the service; b) the extensions and refinements of the behavior of those CSTS procedures necessary to provide the transfer service; c) the extensions and refinements of standard CSTS operations associated with each of the procedures; d) the relationships among the procedures that constitute the service. It does not specify: a) individual implementations or products; b) the implementation of entities or interfaces within real systems; c) the methods or technologies required to measure the values of monitored parameters and to detect the occurrence of events of interest; d) the methods or technologies required for communication; e) the management activities necessary to schedule, configure, and control the MD-CSTS; f) the specific parameters that are to be reported and events that are to be notified by the MD-CSTS.

This document establishes the minimum requirements for deicing/anti-icing methods on the ground of main line and regional airplanes, in accordance with ICAO, Document 9640-AN/9401) and the relevant civil aviation requirements, to facilitate the safe operation of main line and regional civil transport airplanes during icing conditions. This document does not specify requirements for specific aircraft model types. Airlines' published manuals, procedures or methods supplement the information contained in this document. Frost, ice or snow deposits, which can seriously affect the aerodynamic performance and/or controllability of an aircraft, are effectively removed by the application of the procedures specified in this document. It is the airplane operator's responsibility to consult airplane manufacturer's aircraft operations manual, aircraft maintenance manual and service letters to determine any limitations/restrictions relating to the use of deicing/anti-icing methods meeting this document for the type and model of airplane to be treated.

1.1.1 This Recommended Standard defines, in an abstract manner, a CSTS in terms of: a) the procedures necessary to provide the service; b) the states of the service; c) the behavior of each procedure; d) the states of the procedures; e) the operations necessary to constitute the procedures; and f) the parameters associated with each operation. 1.1.2 It does not specify: a) individual application services, implementations, or products; b) the implementation of entities or interfaces within real systems; c) the methods or technologies required to acquire data; d) the methods or technologies required to provide a suitable environment for communications; or e) the management activities required to schedule and configure services.