This SAE Aerospace Information Report (AIR) supplies information on the flight control systems incorporated on various current and historic fixed wing, rotary wing, and tilt rotor aircraft. A brief description of the aircraft is followed by a description of the flight control system, some specific components, drawings of the internal arrangement, block diagrams, and schematics. System operation redundancy management is also presented.
Fluid, Aircraft Deicing/Anti-Icing, Non-Newtonian (Pseudoplastic), SAE Types II, III, and IV, NON-GLYCOL
The foundation specification (AMS1428) and the category specifications (AMS1428/1 and AMS1428/2) cover deicing/anti- icing materials in the form of a fluid. 1.1.1 Foundation and Category Specifications The foundation specification establishes the requirements for all Type I deicing/anti-icing fluids and defines the terms Glycol (Conventional and Non-Conventional) and Non-Glycol and contains technical and other requirements that apply to both Glycol (Conventional and Non-Conventional) and Non-Glycol based fluids. The category specification AMS1428/1 covers Glycol (Conventional and Non-Conventional) based fluids whereas the category specification AMS1428/2 covers Non-Glycol based fluids. 1.2 Other Scope Requirements Other Scope requirements are set in AMS1428.
Fluid, Aircraft Deicing/Anti-Icing, Non-Newtonian (Pseudoplastic), SAE Types II, III, and IV, glycol
1.1 Form The foundation specification (AMS1424M) and the category specifications (AMS1424/1 and AMS1424/2) cover deicing/anti-icing materials in the form of a fluid. 1.1.1 Foundation and Category Specifications The foundation specification establishes the requirements for all Type I deicing/anti-icing fluids and defines the terms Glycol (Conventional and Non-Conventional) and Non-Glycol and contains technical and other requirements that apply to both Glycol (Conventional and Non-Conventional) and Non-Glycol based fluids. The category specification AMS1424/1 covers Glycol (Conventional and Non-Conventional) based fluids whereas the category specification AMS1424/2 covers Non-Glycol based fluids. 1.2 Other Scope Requirements Other Scope requirements are set in AMS1424M.
The scope of this document is to provide review of recent history of loss-of-control accidents during airline revenue operations.
LED Replacement for Incandescent/Halogen Bulbs or Fluorescent Lamps Transport Category Aircraft and Rotorcraft
This SAE Aerospace Recommended Practice (ARP) establishes design and qualification guidance for interior aircraft lighting replacement of incandescent, halogen, or fluorescent light with LED lights.
The purpose of this SAE Aerospace Standard (AS) is to standardize the basic design, performance and testing requirements for “Cargo Stoppers” cargo tie-down accessories to be used in conjunction with approved tie-down straps meeting AS5385C (TSO C-172) requirements.
This report presents, paraphrased in tabular format, an overview of the Federal Aviation Regulations (FAR) for aircraft oxygen systems. It is intended as a ready reference for those considering the use of oxygen in aircraft and those wishing to familiarize themselves with the systems requirements for existing aircraft. This document is not intended to replace the oxygen related FAR but rather to index them in some order. For detailed information, the user is referred to the current issue of the relevant FAR paragraph referenced in this report.
This SAE Aerospace Standard (AS) establishes the general requirements for the design, construction, acceptance, and qualification testing of flat cut-off pressure compensated, variable delivery hydraulic pumps used in military aircraft hydraulic systems. It also provides parameters for a Procurement Specification to be used in conjunction with this AS. The hydraulic pumps defined by this AS are generally for use in aircraft hydraulic systems conforming to and as defined in AS5440 and MIL-H-8891, as applicable. NOTES: 1. Hydraulic pumps may incorporate features such as a clutch in the input drive, which will not be covered by this standard. 2. AS595 should be used for commercial aircraft hydraulic pumps. 3. This document should not be used for hydraulic pumps in Electro-Hydrostatic Actuator applications (EHAs).
A guide for the use by companies contracting for design of electronic products with the Department of Defense (DOD) and other government agencies. This Bulletin present concepts and techniques for quantifying electronic equipment reliability. The techniques are responsive to the requirements of various branches of the Department of Defense and are also useful with regard to other Government agencies (e.g., NASA).
Diminishing Manufacturing Sources and Material Shortages (DMSMS) is the loss or impending loss of manufacturers or suppliers of critical items and raw materials due to production discontinuance. DMSMS is an increasingly difficult problem for DoD weapon systems because the manufacturing lives of many critical items get shorter while the life cycles of military weapon systems keep increasing. Traditionally, efforts to mitigate the effects of DMSMS have been reactive; that is, the effects are addressed only when they are seen. This reactive approach to DMSMS solutions leads to decisions that put a premium on faster solution paths with attractive short-term gains in order to avoid system inoperability, while ignoring the long-term solution paths that would lead to generic families of solutions or larger-scale solutions with the capability of avoiding future DMSMS issues. In order to solve DMSMS issues with lower overall cost, DMSMS solutions must change from reactive to proactive.
This EIA Bulletin No. EMCB1-1, "Historical Rationale for Military EM1 Limits", is presented by the Electronic Industries Association G46 Electromagnetic Compatibility Committee. It has been prepared to provide a reference source for electromagnetic compatibility practitioners to enable more knowledgeable application of EMI requirements in equipment and system specifications and designs.
Accelerometers are transducers, or sensors, that convert acceleration into an electrical signal that can be used for airframe, drive, and propulsion system vibration monitoring and analysis within vehicle health and usage monitoring systems. This document defines interface requirements for accelerometers and associated interfacing electronics for use in a helicopter Health and Usage Monitoring System (HUMS). The purpose is to standardize the accelerometer-to-electronics interface with the intent of increasing interchangeability among HUMS sensors/systems and reducing the cost of HUMS accelerometers. Although this interface was specified with an internally amplified piezoelectric accelerometer in mind for Airframe and Drive Train accelerometers, this does not preclude the use of piezoelectric accelerometer with remote charge amplifier or any other sensor technology that meets the requirements given in this specification.
This SAE Aerospace Standard (AS) covers the requirements and technical guidance for evaluation of life-cycle cost, productivity, and safety/health factors related to power hand tool selection. It applies approaches to selection of quieter and lower vibration hand-held powered tools, with optimal ergonomic features, for the prevention of Hand-Arm Vibration Syndrome (HAVS), hearing loss and repetitive motion injuries. It suggests use of noise and vibration data provided by vendors to be verified and supplemented by information available through the National Institute for Occupational Safety and Health (NIOSH) and European Union databases. Inclusion/exclusion of data in this document is not intended to imply that all of the products described herein are the only production models that meet this standard. Consumers are requested to consult with manufacturers concerning lists of stock production models that meet this standard.
This SAE Aerospace Standard (AS) defines the minimum performance requirements and test parameters for air cargo unit load devices requiring approval of airworthiness for installation in an approved aircraft cargo compartment and restraint system that complies with the cargo restraint requirements of Title 14 CFR Part 25, except for the 9.0g forward ultimate inertia force of § 25.561 (b)(3)(ii).
This detail specification AMS1424/3 covers the use of In-Truck Manufacturing of a deicing SAE Type I deicing/anti-icing fluid. This detailed specification contains technical and other requirements that apply for the In-Truck Manufacturing of Type I deicing/anti-icing fluid.
Scope is unavailable.
This document provides information and guidance material to assist in assessing the need for and feasibility of developing deicing facilities, the planning (size and location) and design of deicing facilities, and assessing environmental considerations and operational considerations associated with de-icing facilities. The document presents relevant information necessary to define the need for a deicing facility and factors influencing its size, location and operation. The determination of the need for deicing facilities rests with Airports. Although this document intends to provide information to airport operator and deicing facility planner/designer, all stakeholders, including deicing service providers, should be involved in the development process.
This SAE Aerospace Recommended Practice (ARP) specifies dimensional and physical requirements of tow bar connections to tractor and aircraft (see Figure 1). It is applicable to all types of commercial transport category aircraft tow bar. The purpose of this SAE Aerospace Recommended Practice (ARP) is to standardize tow bar attachments to airplane and tractor according to the mass category of the towed aircraft, so that one tow bar head with different shear levels can be used for all aircraft that are within the same mass category and are manufactured in compliance with AS1614 or ISO 8267.
This SAE Aerospace Recommended Practice (ARP) contains the general requirements and test procedures for Dual Mode (NVIS Friendly visible and Covert) exterior lighting for most rotorcraft and fixed wing aircraft and could be applicable to ground vehicles that desire a Dual Mode lighting system.
This standard defines implementation requirements for the electrical interface between: a. aircraft carried miniature store carriage systems and miniature stores b. aircraft parent carriage and miniature stores c. surface based launch systems and miniature stores The interface provides a common interfacing capability for the initialization and employment of smart miniature munitions and other miniature stores from the host systems. Physical, electrical, and logical (functional) aspects of the interface are addressed.
This data dictionary provides a mathematically coherent set of definitions for quantity types used in data models for unmanned systems. In this data dictionary, a quantity is defined as a property of a phenomenon, substance, or body whose value has magnitude.
This document, the JAUS Automated Behaviors and Diagnostics Service Set, defines a message-passing interface for services commonly found in mobile unmanned systems. These services represent the platform-independent capabilities common across all domains. Additional capabilities are specified in the JAUS Core Service Set (AS5710) and are frequently referenced herein.
Methods and Processes for Evaluation of Aerodynamic Effects of SAE-Qualified Aircraft Ground Deicing/Anti-icing Fluids
This document describes methods that are known to have been used by aircraft manufacturers to evaluate aircraft aerodynamic performance and handling effects following application of aircraft ground deicing/anti-icing fluids (“fluids”), as well as methods under development. Guidance and insight based upon those experiences are provided, including: - Similarity Analyses - Icing Wind Tunnel Tests - Flight Tests - Computational Fluid Dynamics and other Numerical Analyses This document also describes: - The history of evaluation of the aerodynamic effects of fluids - The effects of fluids on aircraft aerodynamics - The testing for aerodynamic acceptability of fluids for SAE and regulatory qualification performed in accordance with AS5900 - Additionally, Appendices A to E present individual aircraft manufacturers’ histories and methodologies which substantially contributed to the improvement of knowledge and processes for the evaluation of fluid aerodynamic effects.
This SAE Aerospace Standard (AS), identical to ISO 14186, specifies the minimum design and performance criteria and testing methods of fire containment covers (FCCs) used either:
- a. in those cargo compartments of civil transport aircraft where they constitute one means of complying with applicable airworthiness regulations, or
b. on a voluntary basis, when deemed appropriate by operators to improve fire protection in aircraft cargo compartments where airworthiness regulations do not mandate their use.
IEEE-1394b, Interface Requirements for Military and Aerospace Vehicle Applications, establishes the requirements for the use of IEEE Std 1394™-2008 as a data bus network in military and aerospace vehicles. The portion of IEEE Std 1394™-2008 standard used by AS5643 is referred to as IEEE-1394 Beta (formerly referred to as IEEE-1394b.) It defines the concept of operations and information flow on the network. As discussed in 1.4, this specification contains extensions/restrictions to “off-the-shelf” IEEE-1394 standards and assumes the reader already has a working knowledge of IEEE-1394. This document is referred to as the “base” specification, containing the generic requirements that specify data bus characteristics, data formats, and node operation.
This specification covers the engineering requirements for producing a continuous thin epsilon iron carbonitride compound layer on parts by means of a gaseous, low-temperature process, and properties of the case.
This ARP addresses the issue of passengers smoking in aircraft lavatories and the need to improve warnings about the danger of fire caused by smoking.
This ARP document defines a comprehensive and widely-accepted set of guidelines for use or design of fiber optic sensors on aerospace applications.
This SAE Aerospace Recommended Practice (ARP) provides guidance to achieve the optimum integration of new aircraft systems which have an impact on the cockpit layout or crew operating procedures. This process may also be used for modification of existing cockpits.