Search Results

This document presents Flight Test Techniques, Data Analysis Methods, and Reporting examples related to installed turbine Power Available and Power Assurance demonstrations as required by CFR Title 14 Part 29.45(c) and (f).

Over the past several years the FZG A/8.3/90 test method has been used to evaluate current qualified aviation lubricants. The results of the effort have been summarized in this document as a historical reference to document the findings made from the committee.

To inform users on proper use, procedures and common errors when using electronic compensation for tooling on horizontal and vertical balancing machines

This Aerospace Informational Report (AIR) provides guidance on using environmental, electrochemical, and electrical resistance measurements to monitor environment spectra and corrosivity of service environments, focusing on parameters of interest, existing measurement platforms, deployment requirements, and data processing techniques. The sensors and monitoring systems provide discrete time-based records of 1) environmental parameters such as temperature, humidity, and contaminants; 2) measures of alloy corrosion in the sensor; and 3) protective coating performance in the sensor. These systems provide measurements of environmental parameters, sensor material corrosion rate, and sensor coating condition for use in assessing the risk of atmospheric corrosion of the structure.

Provide guidance on how balance machine vector data is captured and reported. Provide an understanding of how to transform balance machine vector data to alternate locations. Provide guidance on how vector imbalances may be used to evaluate and diagnose balance process performance.

This SAE Aerospace Information Report (AIR) provides technical information regarding Engine Control Systems Interdependencies strategies and/or functions. This concerns aircraft with multiple power sources: at least two engines, whatever the nature of the power source is (electrical motor or gas turbine engine). Within this document the aircraft stands for fixed-wing aircraft as well as rotorcraft. The term EECS or FADEC is used for the engine electronic control system, whereas the term EEC is used for the electronic unit itself. The scope includes civilian aircraft powered by turbofan, turboprop, turboshaft and electrical engines equipped with electronic engine controls. Military aircraft is taken into consideration, however restricted topics that change the operational behaviors are not discussed.

This Aerospace Information Report (AIR) identifies considerations on power available and inlet distortion for rotorcraft with Inlet Barrier Filter (IBF) installations. This document provides a more in-depth understanding of the physics behind power available and inlet distortion characterization for rotorcraft with Inlet Barrier Filter (IBF) installations, including case studies and calculation examples. It is intended to support the methods of compliance to power available and inlet distortion requirements for rotorcraft with Inlet Barrier Filter (IBF) installations recommended in ARP6912.

This is an initial release of an Aerospace Information Report to provide methods for Engine Suppliers to follow to execute their in house performance models to generate datasets that are provided to airframe customers early in the conceptual design phase of an aircraft program. This AIR provides some general guidance for execution order and input settings to be used to execute the model.

This document will address techniques or methods that have been used within the industry to address the problem of engine stability margin accounting when combinations of distortion types exist in an aircraft installation. Its focus is combining temperature, planar wave, and swirl distortion with time-variant spatial total pressure distortion. Example methodologies will be presented along with example cases where co-existing distortions have been evaluated. It will also address the areas where the industries' knowledge base is lacking (experimental data or computational methods) and the future work that is needed for methodology development in these areas. This document is viewed to be updated every five years as more information (data either experimentally or analytically) becomes available.

Set forth dimensions and specifications for Nickel Alloy N07718 100 deg csk 0.114” to 0.3750” diameter screws with AS6305 recess.

This document defines the technical guidelines for the safe integration, operation and maintenance, and for certification of Liquid Hydrogen Storage Systems (LHSS) in aircraft. This document also defines guidelines for safe refuelling operation of hydrogen for aircraft. This document does not address airport infrastructure, nor how the refuelling means is specified, except the provisions required for the safety of the aircraft refuelling operation.

This document establishes process parameters for gas turbine rotor balancing. Adherence to the recommendations made herein will facilitate attainment of the usually high degree of accuracy and precision required for jet engine rotor balance.

This document describes a method for measuring deformations, and fragment distribution patterns during an impact between a soft or frangible projectile and a regular helispherical leading edge. The document describes the hardware, setup, and instrumentation required. In this test method a soft body projectile impacts a helispherical leading edge symmetric to the curvature and centric in the transversal direction. The ductile target is backup by a rigid adapter structure behind. The target must be sufficiently large so that the projectile flows around its curvature and induces an indentation. This test is intended for measuring the remaining plastic deformation of the target after the impact. The projectile breakup pattern data may also be captured during this test. The values stated in either SI units or inch-pound units are considered separate standards. The values stated in each system may not be exactly equivalent; therefore, each system must be considered as independent.

This document defines the technical guidelines for the safe integration, operation and maintenance, and for certification of Gaseous Hydrogen Storage Systems (GHSS) in general aviation. This document also defines guidelines for safe refuelling operation of gaseous hydrogen for aircraft. This document does not address airport infrastructure, nor how the refuelling means is specified, except the provisions required for the safety of the aircraft refuelling operation.

This document describes a method for measuring deformations from a normal impact between a soft or frangible projectile and clamped plate. The document describes the hardware, setup, and instrumentation required. In this test method a soft body projectile impacts a square ductile plate clamped on all four sides. This test is intended for measuring the remaining plastic deformation of the target after the impact.The values stated in either SI units or inch-pound units are considered separate standards. The values stated in each system may not be exactly equivalent; therefore, each system must be considered as independent. This standard does not address all of the safety concerns associated with its use. It is the responsibility of each user of this standard to ensure that any safety issues are properly addressed.

The E-36 committee is requested to develop a standard or recommended practice for Control System Fault Accommodation to provide guidance on the fault detection and accommodation strategies and robust validation toward certification to FAA Control System regulation 33.28. FAA has written an issue paper on this outlining the risks and vulnerabilities in fault detection/ accommodation based on industry/agency experience over many years; and suggested means of compliance in terms of tests, analyses, simulations. The E-36 is requested to factor in the issue paper and build on the guidance content into an SAE document for reference by the industry. In this endeavor, it is recommended that the SAE standard/ARP consider conventional gas turbine controls as well as emerging architectures such Hybrid and Electric Propulsion Systems.

The scope of these standards will relate to single-axis moment scales only. Topics covered include dimensional characteristics of single-axis moment scale interfaces, general tooling requirements, scale and tooling accuracy, and display instrument accuracy requirements. Additionally, general guidelines for qualification of equipment and tooling are included, as are general requirements for single-axis blade distribution software.

This document defines the Level 1 tests required for qualifying an artificial bird for certification testing of aircraft and aircraft engines. Level 1 refers to the lowest level of the test pyramid associated with the building block approach defined in the CMH-17 Composite Materials Handbook. The test pyramid consists of a sequence of 5 levels of testing, ranging from the most basic at the lowest level of the pyramid to the most complex at the apex. Typically the number of tests performed has an inverse relationship to the complexity of the tests. The building block approach is used for defining the tests required to qualify an artificial bird that would be accepted by regulatory agencies for certification testing of aircraft, including rotorcraft, fixed wing fuselages and engines, where bird strike testing is currently required. This document only describes the tests required for Level 1 of the test pyramid. Separate documents define the tests required at higher levels.

The SAE E-32 Committee is requested to develop standards for Commercial Aircraft Engine Monitoring to support the Continued Airworthiness of aircraft in general, with particular emphasis on the ETOPS (Extended Operations) to support the regulations. 14CFR A33.3 (c) ETOPS Requirements. For an applicant seeking eligibility for an engine to be installed on an airplane approved for ETOPS, the Instructions for Continued Airworthiness must include procedures for engine condition monitoring. The engine condition monitoring procedures must be able to determine prior to flight, whether an engine is capable of providing, within approved engine operating limits, maximum continuous power or thrust, bleed air, and power extraction required for a relevant engine inoperative diversion. For an engine to be installed on a two-engine airplane approved for ETOPS, the engine condition monitoring procedures must be validated before ETOPS eligibility is granted.

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.