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The purpose of this SAE Aerospace Information Report (AIR) is to provide information that would be useful to potential users/operators and decision makers for evaluating and quantifying the benefits of an Engine Monitoring Systems (EMS) versus its cost of implementation. This document presents excerpts from reports developed to analyze “actual aircraft cost/benefits results”. These are presented as follows: a First, to outline the benefits and cost elements pertaining to EMS that may be used in performing a cost versus benefits analysis. b Second, to present considerations for use in conducting the analysis. c Third, to provide examples of analyses and results as they relate to the user/operator and decision-maker community. The document encompasses helicopters and fixed wing aircraft and distinguishes between civilian and military considerations.

This document is intended to explain, in detail, the rationale behind the features and functions of the AS4074, Linear, Token-passing, Bus (LTPB). The discussions also address the considerations which a system designer should take into account when designing a system using this bus. Other information can be found in these related documents: AIR4271 - Handbook of System Data Communication AS4290 - Validation Test Plan for AS4074

This document is intended to explain, in detail, the rationale behind the features and functions of the AS4074, Linear, Token-passing, Bus (LTPB). The discussions also address the considerations which a system designer should take into account when designing a system using this bus. Other information can be found in these related documents:

Shortly after World War II, as aircraft became more sophisticated and power-assist, flight-control functions became a requirement, hydraulic system operating pressures rose from the 1000 psi level to the 3000 psi level found on most aircraft today. Since then, 4000 psi systems have been developed for the U.S. Air Force XB-70 and B-1 bombers and a number of European aircraft including the tornado multirole combat aircraft and the Concorde supersonic transport. The V-22 Osprey incorporates a 5000 psi hydraulic system. The power levels of military aircraft hydraulic systems have continued to rise. This is primarily due to higher aerodynamic loading, combined with the increased hydraulic functions and operations of each new aircraft. At the same time, aircraft structures and wings have been getting smaller and thinner as mission requirements expand. Thus, internal physical space available for plumbing and components continues to decrease.

Shortly after World War II, as aircraft became more sophisticated and power-assist, flight-control functions became a requirement, hydraulic system operating pressures rose from the 1000 psi level to the 3000 psi level found on most aircraft today. Since then, 4000 psi systems have been developed for the U.S. Air Force XB-70 and B-1 bombers and a number of European aircraft including the tornado multirole combat aircraft and the Concorde supersonic transport. The V-22 Osprey incorporates a 5000 psi hydraulic system. The power levels of military aircraft hydraulic systems have continued to rise. This is primarily due to higher aerodynamic loading, combined with the increased hydraulic functions and operations of each new aircraft. At the same time, aircraft structures and wings have been getting smaller and thinner as mission requirements expand. Thus, internal physical space available for plumbing and components continues to decrease.

The emphasis in this standard is the development of data word and message formats for AS15531 or MIL-STD-1553 data bus applications. This standard is intended as a guide for the designer to identify standard data words and messages for use in avionics systems and subsystems. These standard words and messages, as well as the documentation format for interface control document (ICD) sheets, provide the basis for defining 15531/1553 systems. Also provided in this standard is the method for developing additional data word formats and messages that may be required by a particular system but are not covered by the formats provided herein. It is essential that any new word formats or message formats that are developed for a 15531/1553 application follow the fundamental guidelines established in this standard in order to ease future standardization of these words and messages. The standard word formats presented represent a composite result of studies conducted by the U.S.

The emphasis in this standard is the development of data word and message formats for AS15531 or MIL-STD-1553 data bus applications. This standard is intended as a guide for the designer to identify standard data words and messages for use in avionics systems and subsystems. These standard words and messages, as well as the documentation format for interface control document (ICD) sheets, provide the basis for defining 15531/1553 systems. Also provided in this standard is the method for developing additional data word formats and messages that may be required by a particular system but are not covered by the formats provided herein. It is essential that any new word formats or message formats that are developed for a 15531/1553 application follow the fundamental guidelines established in this standard in order to ease future standardization of these words and messages. The standard word formats presented represent a composite result of studies conducted by the U.S.

This document covers recommendations for the application of existing qualified and approved in-service fixed wing aircraft tires, wheels and brakes to military and commercial rotorcraft. NOTE: This document does not address the use of radial tires due to insufficient data to support their approved use on rotorcraft, see paragraph 4.3.14 for specific impact on ground resonance.

This specification covers the general requirements for the design and installation of fluid anti-icing, de-greasing, and washing systems installed in military aircraft.

This study addresses the adequacy of sockets, wrenches, and torque adapters conforming to AS954 to wrench 12 point fasteners with wrenching configurations conforming to AS870C. Reported wrenching problems with smaller sizes are investigated through examining the combined tolerances on the fasteners and wrenches, conducting torque testing on typical high strength lock nuts. Possible solutions to correct these wrenching problems are presented.

The effectiveness of Engine Life Usage Monitoring and Parts Management systems is largely determined by the aircraft-specific requirements. This AIR addresses the following areas: a Safety. b Life-limiting criteria. c Life usage algorithm development. d Data acquisition and management. e Parts life tracking. f Design feedback. g Cost effectiveness. This AIR primarily examines the requirements and techniques currently in use, including: a Parts classification and control requirements. b Failure causes of life-limited parts. c Engine life prediction and usage measurement techniques. d Method validation. e Parts life usage data management. f Lessons learned. g Life usage tracking benefits.

The effectiveness of Engine Life Usage Monitoring and Parts Management systems is largely determined by the aircraft-specific requirements. This document addresses the following areas: a Safety b Life-limiting criteria c Life usage algorithm development d Data acquisition and management e Parts life tracking f Design feedback g Cost effectiveness It primarily examines the requirements and techniques currently in use, and considers the potential impact of new technology to the following areas: a Parts classification and control requirements b Failure causes of life-limited parts c Engine life prediction and usage measurement techniques d Method validation e Parts life usage data management f Lessons learned g Life usage tracking benefits

The original purpose of this document was to establish interface requirements for modular avionics backplanes to be prototyped up to 1995. The document was issued as ARD50011 in September 1992. It is being reissued as an SAE Aerospace Information Report (AIR) in order to: a Preserve the requirements for more than 2 years b Support design of retrofits and avionics systems to be fielded in the years 1995 to 2000 c Provide a baseline for updating the requirements of future integrated systems These requirements were and are intended to promote standardization of modular avionic backplane interfaces. These requirements have been driven predominantly, but not exclusively, by aerospace type military platforms.

The original purpose of this document was to establish interface requirements for modular avionics backplanes to be prototyped up to 1995. The document was issued as ARD50011 in September 1992. It is being reissued as an SAE Aerospace Information Report (AIR) in order to: a Preserve the requirements for more than 2 years b Support design of retrofits and avionics systems to be fielded in the years 1995 to 2000 c Provide a baseline for updating the requirements of future integrated systems These requirements were and are intended to promote standardization of modular avionic backplane interfaces. These requirements have been driven predominantly, but not exclusively, by aerospace type military platforms.

This Aerospace Information Report (AIR) has been prepared by the Systems Applications and Requirements Subcommittee of SAE Committee AS-2. It is intended to provide guidance primarily, but not exclusively, for specifiers and designers of data communication systems for real time military avionics applications within a platform. The subject of high speed data transmission is addressed from two standpoints: (1) the influence of developments in technology on avionics architectures as a whole and (2) the way in which specific problems, such as video, voice, closed loop control, and security may be handled. While the material has been prepared against a background of experience within SAE AS-2 relating to the development of a family of high speed interconnect standards, reference to specific standards and interconnect systems is minimized.

This Aerospace Information Report (AIR) has been prepared by the Systems Applications and Requirements Subcommittee of SAE Committee AS-2. It is intended to provide guidance primarily, but not exclusively, for specifiers and designers of data communication systems for real time military avionics applications within a platform. The subject of high speed data transmission is addressed from two standpoints: (1) the influence of developments in technology on avionics architectures as a whole and (2) the way in which specific problems, such as video, voice, closed loop control, and security may be handled. While the material has been prepared against a background of experience within SAE AS-2 relating to the development of a family of high speed interconnect standards, reference to specific standards and interconnect systems is minimized.

The Aerospace Recommended Practices of this document are intended for nitrogen-based Flammability Reduction Means (FRM) implemented on transport category, turbine powered airplanes. The recommended practices herein, therefore, relate only to the transport category aircraft, and focus specifically on contemporary inerting systems equipment. Such systems are referred to a Fuel Tank Inerting Systems (FTIS) in this document. This document does not cover the following: Military aircraft applications Air separation technologies other than hollow fiber membrane (HFM) and pressure swing adsorption (PSA) Inerting of conventional unheated wing tanks or aircraft dry bays Expected future technology solutions for the generation of inert gas. The advice contained in this document is aimed towards providing aircraft manufacturers with guidance on the key issues associated with contemporary aircraft fuel tank inerting systems to supplement the guidance in FAA Advisory Circular AC 25.981-2.

This SAE Aerospace Recommended Practice (ARP) is intended as a guide to aid in the specification and testing of Direct Drive Servovalves, but does not include the associated electronic controller. The recommendations contained in this ARP are primarily confined to the input and output characteristics of Direct Drive Servovalves (DDV). The only exception to this approach involves the definition and specification of chip shear force, which is not typically measurable by nondestructive external testing. The information presented should be useful in standardizing the terminology, the specification of physical and performance parameters, and the test procedures used in conjunction with these components. Direct drive servovalves are of two basic types: open loop and closed loop. In the case of open loop direct drive servovalves, the significant input is the motor current as is the case with electrohydraulic servovalves covered in ARP490.

The report presents air conditioning data for aircraft cargo which is affected by temperature, humidity, ventilation rate and atmospheric pressure. The major emphasis is on conditioning of perishable products and warm-blooded animals. The report also covers topics peculiar to cargo aircraft or which are related to the handling of cargo.

The report presents air conditioning data for aircraft cargo which is affected by temperature, humidity, ventilation rate and atmospheric pressure. The major emphasis is on conditioning of perishable products and warm-blooded animals. The report also covers topics peculiar to cargo aircraft or which are related to the handling of cargo.