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 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 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 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 document also does not address any specific organizational structures for accomplishing the safety assessment process.
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.
The purpose of this SAE Information Report is to list and explain major equipment, instrumentation, and procedure variables which can affect inter-laboratory differences and repeatability of photometric measurements of various lighting devices listed in SAE Technical Reports. The accuracy guidelines listed in the report are for the purpose of controlling variables that are not a direct function of the lighting device being measured. The control of these individual variables is necessary to control the overall accuracy of photometric measurements. These accuracy guidelines apply to the measurement of the luminous intensities and reflected intensities of devices at the specified geometrically distributed test points and areas. These guidelines do not apply to photometric equipment used to measure license plate lamps.
This document describes the CAD model data available from SAE for the two-dimensional H-point template (HPM-1).
This SAE Recommended Practice identifies graphic symbols used in electrical circuit diagrams. The symbols aid troubleshooting electrical systems.
Potential Failure Mode and Effects Analysis in Design (Design FMEA), Potential Failure Mode and Effects Analysis in Manufacturing and Assembly Processes (Process FMEA)
This FMEA Standard describes Potential Failure Mode and Effects Analysis in Design (DFMEA) and Potential Failure Mode and Effects Analysis in Manufacturing and Assembly Processes (PFMEA). It assists users in the identification and mitigation of risk by providing appropriate terms, requirements, ranking charts, and worksheets. As a Standard, this document contains requirements "must" and recommendations "should" to guide the user through the FMEA process. The FMEA process and documentation must comply with this Standard as well as any corporate policy concerning this Standard. Documented rationale and agreement with the customer is necessary for deviations in order to justify new work or changed methods during customer or third-party audit reviews.
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. Prognostics is a capability within some HM systems that provides an estimation of remaining useful life (RUL) or time to failure and so Prognostic Health Management (PHM) is used where this predictive element exists.
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 is actually a more accurate term to describe the subject of this paper, but NBC has become more widely used in the aircraft industry.
This SAE Recommended Practice describes how to position and posture the H-point design tool (HPD) described in Appendix B, and how to establish the seating reference point (SgRP), design H-point travel path, and other key reference points that are used in the design and specification of both driver and passenger seat positions. This practice also provides a method for determining the length of the seat track for a driver seat that adjusts fore/aft. The seat track length is based on a desired level of driver accommodation, assuming a U.S. population containing an equal number of male and female drivers. The procedure can be used to establish driver seat track accommodation for new vehicle designs or to evaluate accommodation in existing vehicles. A general method for determining driver seat track length for any driver population (male and female stature distribution) at any selected accommodation percentile and gender mix is given in Appendix A. Application of this document is limited to Class A Vehicles (Passenger Cars, Multipurpose Passenger Vehicles, and Light Trucks) as defined in SAE J1100.
This document provides dimension definitions that facilitate geometric quantification and evaluation of seats. This document has been designed for use in CAD, however, many dimensions require establishing HPM position and attitude. Refer to the appropriate document for these procedures. These dimensions are package independent in that they do not require use of the HPM-ll supplemental thigh/leg/shoe. Three types of seat geometry reference points and measurements have been developed. 1. Simple reference points and measurements not related to H-point 2. H-point dependent reference points and measurement that utilize the seat characterization capabilities of the HPM to quantify seat measurements 3. Cross sectional seat trim outlines For convenience and simplicity, many terms associated with H-point devices use human body parts in their name. However, they should not be construed as measures that indicate interaction with any or all occupants concerning accommodation, human capabilities, or comfort.
This recommended practice is a source of information for body and trim engineers and represents existing technology in the field of on-highway vehicle seating systems. It provides a more uniform system of nomenclature, definitions of functional requirements, and testing methods of various material components of motor vehicle seating systems.
Methods will be developed to characterize In Flight Entertainment (IFE) component impact performance separate from seat design. These methods will address both initial seat head impact criterion (HIC) testing and subsequent IFE component changes. Methods will evaluate head blunt trauma, post-impact sharp edges, and egress impediment. Criteria development will involve defining test methods, test parameters, measurements, and acceptance criteria. Particular emphasis on evaluating IFE changes that require coordination and evaluation per SAE ARP 6448, Appendix B.
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. Other flammability studies are also cited in the AIR document to substantiate the FAA findings.
This SAE Recommended Practice establishes a uniform procedure for a flat-road simulation of a mountain-fade test of the brake systems of light-duty trucks and multipurpose passenger vehicles up to and including 4500 kg (10 000 lb) GVW and all classes of passenger cars. The purpose of this test code is to establish brake system characteristics while simulating a mountain descent. This procedure is intended to be used to evaluate the following characteristics of a brake system: a. Brake temperature relative to fluid boil b. Fade resistance and reserve pedal travel c. Overall structural durability d. Subjective stability
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. It describes typical equipment applications and operational objectives and is the basis for the performance criteria stated in Chapter 2 to Chapter 4.
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. Selection of technology e.
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.
1.1 This SAE Aerospace Standard (AS) provides performance station designation and nomenclature systems for aircraft propulsion systems and their derivatives. 1.2 The parameter naming conventions presented herein are for use in all communications concerning propulsion system performance such as computer programs, data reduction, design activities, and published documents. They are intended to facilitate calculations by the program user without unduly restricting the method of calculation used by the program supplier. 1.3 The list of symbols presented herein will be used for identification of input and output parameters. These symbols are not required to be used as internal parameter names within the engine subprogram
This SAE Aerospace Standard (AS) provides performance station designation and nomenclature systems for aircraft propulsion systems and their derivatives. The systems presented herein are for use in all communications concerning propulsion system performance such as computer programs, data reduction, design activities, and published documents. They are intended to facilitate calculations by the program user without unduly restricting the method of calculation used by the program supplier. The list of symbols presented herein will be used for identification of input and output parameters. These symbols are not required to be used as internal parameter names within the engine subprogram.
To provide a method that accounts for the attenuation due to line-of-sight blockage of aircraft noise by terrain features.
Aircraft Ground Operations Modeling – Part 1: behind start-of-takeoff roll noise directivity modeling
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.
This document is intended for use by manufacturers of aircraft, engines and Electronic Engine Controls [EECs] as a component change process and evaluation guideline. Its purpose is to provide an effective means of managing the modification of electronic hardware.