The test procedure included in this document are used to determine a benchmark SgRP for Class A vehicles where design intent information is unknown.
Presents the seating accommodation model used to determine seat track length for accommodation in design.
This SAE Aerospace Information Report (AIR) is applicable to rotorcraft structural health monitoring (SHM) applications, both commercial and military, where end users are seeking guidance on the definition, development, integration, qualification, and certification of SHM technologies to achieve enhanced safety and reduced maintenance burden based on the lessons learned from existing Health and Usage Monitoring Systems (HUMS). While guidance on SHM business case analysis would be useful to the community, such guidance is beyond the scope of this AIR. For the purpose of this document, SHM is defined as “the process of acquiring and analyzing data from on-board sensors to evaluate the health of a structure.” The suite of on-board sensors could include any presently installed aircraft sensors as well as new sensors to be defined in the future. Interrogation of the sensors could be done onboard during flight or using ground support equipment.
This document describes requirements for standardized processes (and associated technologies) that ensure type design data are retrievable and usable for the life of a type certificate (50+ years). These processes are primarily concerned with, but not limited to, digital type design data retained in threedimensional representations and associated data that is required for complete product definition, such as tolerances, specification call-outs, product structure and configuration control data, etc. This process standard includes process requirements for managing the evolution of technologies required to ensure the availability of the data for the life of the product. This data must be available to meet regulatory, legal, contractual and business requirements. This process standard is not intended to incorporate every company specific requirement and does not dictate specific organizational structures within a company.
This SAE Aerospace Recommended Practice (ARP) provides guidance for the presentation of gas turbine engine transient performance models with the capacity to be implemented as computer programs operating in real time and is intended to complement AS681. Such models will be used in those applications where a transient program must interface with physical systems. These applications are characterized by the requirement for real time transient response. These models require attention to unique characteristics that are beyond the scope of AS681. This document is intended to facilitate the development of mathematical models and the coordination of their requirements with the user. It will not unduly restrict the modeling methodology used by the supplier. The objective of this document is to define a recommended practice for the delivery of mathematical models intended for real time use. Models used in this application may also be contained in deliverable computer programs covered by AS681.
The purpose of this document is to specify the functional requirements for a miniature connector to be used for health monitoring purposes on aircrafts (including harsh environment such as the powerplant). It is actually a family of miniature connectors that is specified in this document for various uses (e.g. pin counts) and environments. This specification will be used by the SAE connector committee to work on a dedicated connector standard.
This standard defines the minimum requirements for conducting Measurement Systems Analysis (MSA) for variable and attribute assessment on characteristics as defined on the drawing or specification. It does not define the detailed analytical methods for each type of study as these can be found in existing published texts (see Section 2 for guidance).
This SAE Aerospace Standard (AS) covers combustion heaters used in the following applications: a. Cabin heating (all occupied regions and windshield heating) b. Wing and empennage anti-icing c. Engine and accessory heating (when heater is installed as part of the aircraft) d. Aircraft de-icing
This ARP is intended to promote better understanding of gas system characteristics and operation in order to aid in system selection and design. Various gas systems are classified in a broad sense, component operation is described in moderate detail, pertinent design parameters are discussed, and possible modes for system operation are listed.
The ARP shall cover the objectives and activities of Verification & Vallidation Processes required to assure high quality and/or criticality level of an IVHM Systems and Software.
This SAE Aerospace Recommended Practice (ARP) documents a common understanding of terms, compliance issues and occupant injury criteria to facilitate certification of oblique facing seat installations specific to Part 25 aircraft.
This specification covers the general requirements for aircraft tank mounted, centrifugal type, fuel booster pumps, used for engine fuel feed and/or fuel transfer.
This document discusses, in broad general terms, typical present instrumentation practice for post-overhaul gas turbine engine testing. Production engine testing and engine development work are outside the scope of this document as they will typically use many more channels of instrumentation, and in most cases will have requirements for measurements that are never made in post-overhaul testing, such as fan airflow measurements, or strain measurements on compressor blades. The specifications for each parameter to be measured, in terms of measurement range and measurement accuracy, are established by the engine manufacturers. Each test cell instrument system should meet or exceed those requirements. Furthermore, each instrument system should be recalibrated regularly, to ensure that it is still performing correctly.
This document describes the CAD model data of legs and back hardware available from SAE for the HPM-1 three-dimensional H-point machine. The elements of the CAD model include the feet, lower and thighs as well as headroom probe and t-bar. Also included are datum points and lines, and calibration references. The intended purpose for this information is to provide a CAD reference for design and benchmarking as well as a calibration reference for the physical HPM-1 audits. The content and format of the data files that are available are also described. The actual CAD model files are included with this product and are provided in the following formats: CATIA v4 (without parametrics), CATIA v5 (without parametrics), IGES, and STEP.
This document describes guidelines, methods and tools used to perform the ongoing safety assessment process for transport airplanes in commercial service (hereafter, airplane). The process described herein is intended to support an overall safety management program. It is associated with showing compliance with the regulations, and also with assuring a company that it meets its own internal standards. The methods outlined herein identify a systematic means, but not the only means, to assess ongoing safety. This document does not address the economic decision-making associated with the safety management process. While this decision-making is an integral part of the safety management process, this document addresses only the ongoing safety assessment process. To put it succinctly, this document addresses the "Is it safe?" part of safety management. It does not address the "How much does it cost?" part of the safety management.
This Bulletin provides a brief description of tin whisker formation and describes various methods recommended by government and industry to reduce the risk of tin whisker-induced failures in electronic hardware. It is not a mandate nor does it contain any requirements.
This SAE Aerospace Information Report (AIR) examines the need for and the application of a power train usage metric that can be used to more accurately determine the TBO for helicopter transmissions. It provides a formula for the translation of the recorded torque history into mechanical usage. It provides examples of this process and recommends a way forward. This document of the SAE HM-1 IVHM Committee is not intended as a legal document and does not provide detailed implementation steps, but does address general implementation concerns and potential benefits.
This SAE Aerospace Information Report (AIR) provides information on aircraft cabin air quality, including: - Airborne contaminant gases, vapors, and aerosols. - Identified potential sources. - Comfort, health and safety issues. - Airborne chemical measurement. - Regulations and standards. - Operating conditions and equipment that may cause aircraft cabin contamination by airborne chemicals (including Failure Conditions and normal Commercial Practices). - Airborne chemical control systems. It does not deal with airflow requirements.
This document describes the CAD model data available from SAE for the two-dimensional H-point template (HPM-1).
This ARP provides insights on how to perform a cost benefit analysis (CBA) to determine the return on investment that would result from implementing an integrated Health Management (HM) system on an air vehicle. The word “integrated” refers to the combination or “roll up” of sub-systems health management tools to create a platform centric system. The document describes the complexity of features that can be considered in the analysis, the different tools and approaches for conducting a CBA and differentiates between military and commercial applications. This document is intended to help those who might not necessarily have a deep technical understanding or familiarity with HM systems but want to either quantify or understand the economic benefits (i.e., the value proposition) that a HM system could provide.
This SAE Aerospace Information Report (AIR) provides Nuclear, Biological and Chemical (NBC) protection considerations for environmental control system (ECS) design. It is intended to familiarize the ECS designer with the subject in order to know what information will be required to do an ECS design where NBC protection is a requirement. This is not intended to be a thorough discussion of NBC protection. Such a document would be large and would be classified. Topics of NBC protection that are more pertinent to the ECS designer are discussed in more detail. Those of peripheral interest, but of which the ECS designer should be aware are briefly discussed. Only radiological aspects of nuclear blast are discussed. The term CBR (Chemical, Biological, and Radiological) has been used to contrast with NBC to indicate that only the radiological aspects of a nuclear blast are being discussed.
This document provides informational background, rationale and a technical case to allow consideration of the removal of the magnesium alloy restriction in aircraft seat construction as contained in AS8049B. The foundation of this argument is flammability characterization work performed by the FAA at the William J. Hughes Technical Center (FAATC), Fire Safety Branch in Atlantic City, New Jersey, USA. The rationale and detailed testing results are presented along with flammability reports that have concluded that the use of specific types of magnesium alloys in aircraft seat construction does not increase the hazard level potential in the passenger cabin in a post-crash fire scenario. Further, the FAA has developed a lab scale test method, reference DOT/FAA/TC-13/52, to be used as a certification test, or method of compliance (MOC) to allow acceptability of the use of magnesium in the governing TSO-C127 and TSO-C39C.
The objective of this Minimum Operational Performance Specification is to specify the minimum performance of onboard inflight icing detection systems. Throughout the document, these devices are referred to as Flight Icing Detection Systems (FIDS). These systems are intended to either provide information which indicates the presence of ice accreted in flight on monitored surfaces or indicate the presence of icing conditions in the atmosphere. They may operate the airplane anti-ice/deice systems. Detection of ice accreted on the ground is not considered in this document but can be found in ED-104. This MOPS was written for the use of FIDS on airplanes only, as defined in paragraph 1.5. Use on other aircraft may require additional considerations. Chapter 1 of this document provides information required to understand the need for the equipment characteristics and tests defined in the remaining chapters.
This standard establishes general requirements and descriptions of specific activities for performance of LORA during the life cycle of products or equipment. When these requirements and activities are performed in a logical and iterative nature, they comprise the LORA process.
The purpose of this SAE Aerospace Information Report (AIR) is to provide management, designers, and operators with information to assist them to decide what type of power train monitoring they desire. This document is to provide assistance in optimizing system complexity, performance and cost effectiveness. This document covers all power train elements from the point at which the gas generator energy is transferred to mechanical energy for propulsion purposes. The document covers engine power train components, their interfaces, transmissions, gearboxes, hanger bearings, shafting and associated rotating accessories, propellers and rotor systems as shown in Figure 1. This document addresses application for rotorcraft, turboprop, and propfan drive trains for both commercial and military aircraft. Information is provided to assist in; a. Defining technology maturity and application risk b. Cost benefit analysis (Value analysis) c. Selection of system components d.
This SAE Aerospace Standard (AS) provides a method for gas turbine engine performance computer programs to be written using FORTRAN COMMON blocks. If a "function-call application program interface" (API) is to be used, then ARP4868 and ARP5571 are recommended as alternatives to that described in this document. When it is agreed between the program user and supplier that a particular program shall be supplied in FORTRAN, this document shall be used in conjunction with AS681 for steady-state and transient programs. This document also describes how to take advantage of the FORTRAN CHARACTER storage to extend the information interface between the calling program and the engine subroutine.
To provide a method that accounts for the attenuation due to line-of-sight blockage of aircraft noise by terrain features.
To provide a method for modeling the noise directivity behind start-of-takeoff roll based on empirical data from modern jet aircraft. This method would replace the method described in Section 3.3.1 of SAE-AIR-1845A "Procedure for the Calculation of Airplane Noise in the Vicinity of Airports."
Definition of Commonly Used Day Types (Atmospheric Ambient Temperature Characteristics Versus Pressure Altitude)
“Hot Day”, “Tropical Day”, “Standard Day”, “Polar Day”, and “Cold Day” are part of the lexicon of the aircraft industry. These terms are generally understood to refer to specific, generally accepted characteristics of atmospheric temperature versus pressure altitude. There are also other, less well-known days, defined by their frequency of occurrence, such as “1% Hot Day”, “10% Cold Day”, or “Highest Recorded Day”. These temperature characteristics have their origins in multiple sources, including U.S. military specifications which are no longer in force.
SAE ARP 5120 provides recommended best practices, procedures, and technology to guide the physical and functional development, integration, verification, and validation of highly reliable Engine Health Management System (EHMS) for gas turbine engines, including aircraft engines and Auxiliary Power Units (APUs). This ARP also serves as a concise reference of considerations, approaches, activities, and requirements for producing the end-to-end engine health monitoring system comprised of both on and off-board subsystems for the sensing, acquisition, analysis, detection, and data handling functions of an EHMS. These functions and related maintenance activities promote engine safety. These functions may also be used to effect continued operation or return to service decisions when demonstrated as compliant with the applicable airworthiness requirements defined by the responsible Aviation Authority. Where practical, this document delineates between military and commercial practices.