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This specification covers the general requirements for the design, installation, and performance of thermal anti-icing equipment for the wings and empennage surfaces in aircraft.

A review of droplet sizing instruments used for icing research is presented. These instruments include the Forward Scattering Spectrometer Probe, the Optical Array Probe, the Phase Doppler Particle Analyzer, the Malvern Particle Size Analyzer, the oil slide technique, and the rotating multicylinder. The report focuses on the theory of operation of these instruments and practical considerations when using them in icing facilities.

This Icing Technology Bibliography is a compendium of references from the open literature, including both national and foreign sources. Due to the generality of the subject, and the difficulty of fully investigating every available source, the present Bibliography is not intended to be complete. However, it will be updated every 18 months by the SAE AC-9C Aircraft Icing Technology Subcommittee. Any suggestions in terms of additional references, sources, and corrections should be referred to the Icing Technology Bibliography Panel of the SAE AC-9C Aircraft Icing Technology Subcommittee.

This Icing Technology Bibliography is a compendium of references from the open literature that were published prior to the original 1987 issuance of the AIR, including both national and foreign sources. Due to the generality of the subject, and the difficulty of fully investigating every available source, the Bibliography in this document is not intended to be complete.

This SAE Aerospace Recommended Practice (ARP) document establishes criteria and recommended practices for the use of airborne icing tankers to aid in design and certification of aircraft ice protection systems and components. Several icing tankers are described, along with their capabilities and suggested use. Sample data for these tanker spray systems are included, shown with 14 CFR Parts 25 and 29, Appendix C icing envelopes for continuous maximum and intermittent maximum icing conditions. (Note: In the remainder of this document, the phrase “Appendix C icing envelopes” will be used for brevity.) This ARP is intended as a guide toward standard practice and is subject to change to keep pace with experience and technical advances.

This specification covers the general requirements for pneumatic deicing systems for wings, empennages, radomes, radio masts, air induction system entrance cones, and ducts of aircraft. Deicing boots shall be of one type, operating at 15 to 22 psig pressure.

This information report provides a review of liquid drop and ice crystal particle sizing instruments used for facility based icing research and in-flight testing commonly used for aircraft certification icing envelopes. This report will provide an overview of the theory of operation of these instruments and practical considerations when using them for cloud characterization. Methods in use for data reduction (including combining output from multiple probes) as well as potential error sources are provided for information. Measurement methods from prior revisions of this AIR that are no longer commonly used (e.g. oil slides and rotating cylinders) will be retained for reference. This document does not include other icing cloud measurements such as liquid or total water contents, or measurement of other types of phenomena such as snow, sleet or hail.

This SAE Aerospace Information Report (AIR) contains information on most of the major icing simulation ground facilities. An effort was made to obtain data from as many facilities as possible over a two year time period. The data in this document represents the state of the facilities in calendar year 1996. Facilities are constantly changing and upgrading and, therefore, some facility specifications may change during the life of this report. Of the 27 facilities described in this report, the primary use is split with approximately half for engine testing and half for wind tunnel testing. The facilities are limited to ground facilities and, therefore, icing tankers have not been included.

This SAE Aerospace Information Report (AIR) contains information on most of the major icing simulation ground facilities. An effort was made to obtain data from as many facilities as possible over a two year time period. The data in this document represents the state of the facilities in calendar year 1996. Facilities are constantly changing and upgrading and, therefore, some facility specifications may change during the life of this report. Of the 27 facilities described in this report, the primary use is split with approximately half for engine testing and half for wind tunnel testing. The facilities are limited to ground facilities and, therefore, icing tankers have not been included.

This document provides information regarding ice detector technology and design. The SAE document AS5498 provides detailed information regarding the requirements, specifications, qualification, and certification of icing detection systems. This document is not meant to replace AS5498, but to enhance it by considering unique aspects of sensing technology and, in particular, those that may not be certificated at the time of this revision. To that end, an effort has been made not to duplicate information contained in AS5498. Icing rate information is included where applicable. The primary application is associated with ice forming on the leading edges of airfoils and inlets while the aircraft is in flight. Information related to detection of ice over cold fuel tanks and icing at low-velocity operation is included. The material is primarily applicable to fixed-wing aircraft. Unique requirements for engine inlets and rotorcraft are also provided.

This Aerospace Information Report (AIR) identifies and summarizes the various factors that should be considered during design, development, certification, or testing of helicopter rotor blade ice protection. Although various concepts of ice protection are mentioned in this report, the text is limited generally to those factors associated with design and substantiation of cyclic electrothermal ice protection systems as applicable to the protection of helicopter rotor blades. Other systems are described briefly in Appendix A. Applications consider main rotor blades, conventional tail rotor blades, and other types of antitorque devices. The information contained in this report is also limited to the identification of factors that should be considered and why the factor is important. Specific design, analysis and test methodologies are not included. For additional information refer to the references in Section 7.

This SAE Aerospace Information Report (AIR) identifies and summarizes the various factors that should be considered during design, development, certification, or testing of helicopter rotor blade ice protection systems. Although various concepts of ice protection are mentioned in this report, the text is limited generally to those factors associated with design and substantiation of cyclic electrothermal ice protection systems as applicable to the protection of helicopter rotor blades. Other systems are described briefly in Appendix A. Applications consider main rotor blades, conventional tail rotor blades, and other types of antitorque devices. The information contained in this report is also limited to the identification of factors that should be considered and why the factor is important. Specific design, analysis and test methodologies are not included. For additional information refer to the references listed in 2.1.

This SAE Aerospace Information Report (AIR) identifies and summarizes the various factors that should be considered during design, development, certification, or testing of helicopter rotor blade ice protection systems. Although various concepts of ice protection are mentioned in this report, the text is limited generally to those factors associated with design and substantiation of cyclic electrothermal ice protection systems as applicable to the protection of helicopter rotor blades. Other systems are described briefly in Appendix A. Applications consider main rotor blades, conventional tail rotor blades, and other types of antitorque devices. The information contained in this report is also limited to the identification of factors that should be considered and why the factor is important. Specific design, analysis and test methodologies are not included. For additional information refer to the references listed in 2.1.

This SAE Aerospace Standard (AS) establishes minimum ice and rain performance criteria for electrically-heated pitot and pitot-static probes intended for use on the following classes of fixed-wing aircraft and rotorcraft. The classes of fixed-wing aircraft are defined by aircraft flight envelopes and are shown in Figure 1. The flight envelopes generally fall into the classes as shown below: The user of this standard must evaluate the aircraft level installation requirements for the probe against the class definition criteria to ensure adequate coverage for the application. It may be necessary to step up in class or modify the test conditions in order to meet the applicable installation requirements. NOTE: Class 2 is divided into two subgroups identified as either Class 2a or Class 2b. Class 2a probe applications typically include aircraft that operate within the mid to lower end of the Class 2 altitude range and that only use probe output to display basic airspeed and/or altitude.

This SAE Aerospace Information Report (AIR) provides a comprehensive overview of primary water content measurement instrumentation, for both facility-based icing research and in-flight icing research, over the range of commonly used aircraft certification icing envelopes. It includes information on the theory of operation of the instruments, system errors and limitations, and practical considerations when using them for cloud characterization. This document does not address other icing cloud measurements of interest, such as particle sizing, or measurement of phenomena such as snow, sleet, or hail.