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This procurement specification covers bolts, screws, and studs made from a work-strengthened corrosion and heat resistant, age hardenable nickel base alloy of the type identified under the Unified Numbering System as UNS N07718. The following properties are covered: 220 ksi minimum ultimate tensile strength at room temperature 180 ksi minimum ultimate tensile strength at 900 °F 114 ksi tension to 11.4 ksi tension fatigue at room temperature
E-25 General Standards for Aerospace and Propulsion Systems
This document applies to the development of Plans for integrating and managing COTS assemblies in electronic equipment and Systems for the commercial, military, and space markets; as well as other ADHP markets that wish to use this document. For purposes of this document, COTS assemblies are viewed as electronic assemblies such as printed wiring assemblies, relays, disk drives, LCD matrices, VME circuit cards, servers, printers, laptop computers, etc. There are many ways to categorize COTS assemblies1, including the following spectrum: At one end of the spectrum are COTS assemblies whose design, internal parts2, materials, configuration control, traceability, reliability, and qualification methods are at least partially controlled, or influenced, by ADHP customers (either individually or collectively). An example at this end of the spectrum is a VME circuit card assembly. At the other end of the spectrum are COTS assemblies whose design, internal parts, materials, configuration control
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G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
The AS81824 specification covers environment resistant, permanent crimp type, splices having heat shrinkable insulating sleeve and meltable environmental seals or heatless sealing sleeves. The splices may be used with tin, nickel, and silver-plated conductors in applications where the total temperature of the splice application does not exceed 200 °C or as specified in the detail specification.
AE-8C2 Terminating Devices and Tooling Committee
This document is intended to be used for laser systems mounted on aircraft and intended for use in the navigable airspace. This does not include lasers onboard aircraft where the beam is contained within an enclosure so that the beam cannot enter into airspace, nor does it include lasers from satellites and spacecraft in outer space. It may be used in conjunction with: AS4970, ARP5535, ARP5572, ARP5293, and the ANSI Z136 laser safety standards.
G-10T Laser Safety Hazards Committee
Aircraft surface precipitation static (p-static) charge can be generated when aircraft fly through ice particles, rain, snow and dust. However, in the context of p-static protection, this document is used for providing guidance for any thing that charges the outer surface of the aircraft (e.g. engine exhaust). P-static discharges from the aircraft can disrupt aircraft communication, navigation, and surveillance radios, and can damage aircraft radomes and windshields. This SAE Aerospace Recommended Practice (ARP) defines design considerations for aircraft p-static control and related methods to verify acceptable aircraft p-static performance. This ARP addresses p-static charging due to the aircraft flying through ice particles, rain, snow and dust. It does not address other triboelectric charging that may be present in an aircraft, such as triboelectric fuel charging or environmental control system or air conditioning static charging. It does not address electrostatic charging created
AE-2 Lightning Committee
This SAE Aerospace Information Report (AIR) outlines comprehensive aircraft flight control system fault isolation methodology that has proven to be effective. The methodology presented in this Information Report has been used in several successful fault isolation efforts on military aircraft.
A-6A3 Flight Control and Vehicle Management Systems Cmt
This SAE Aerospace Information Report (AIR) includes a discussion of liquid and particulate contaminants which enter the aircraft through the environmental control system (ECS). Gaseous contaminants such as ozone, fuel vapors, sulphates, etc. are also covered in this AIR. This publication is concerned with contamination sources which interface with ECS and fuel tank inerting systems, and the effects of this contamination on equipment. Methods of control will be limited to the equipment and interfacing ducting which normally falls within the responsibility of the ECS designer.
AC-9 Aircraft Environmental Systems Committee
This document categorizes the different types of storage requirements, either on the aircraft or new unused or overhauled on the shelf, for aircraft landing gears/components. Recommendations and examples of proper landing gear storage are outlined. Reclamation recommendations are provided for aircraft landing gear returning from long-term storage.
A-5 Aerospace Landing Gear Systems Committee
This standard applies to pressure reducers for gaseous breathing oxygen systems and for all performance profiles without regard to particular inlet or outlet pressures. Attention is given, however, to construction requirements for reducers with maximum supply pressures to 2250 psig (155 bar) and reduced pressures of 50 to 150 psig (3.4 to 10.5 bar).
A-10 Aircraft Oxygen Equipment Committee
The present document addresses gas and hydraulic fluid servicing required on commercial and military aircraft landing gears, for both single and dual chamber (also known as dual stage and two stage) shock struts. This document should be considered as landing gear industry recommended practice but in no way is meant to supersede the shock strut OEM’s published procedures.
A-5B Gears, Struts and Couplings Committee
This standard establishes the dimensional and visual quality requirements, lot requirements and packaging and labeling requirements for O-rings molded from AMS7601 butyl rubber. It shall be used for procurement purposes.
A-6C2 Seals Committee
This SAE Aerospace Standard (AS) provides the general performance, design, installation, test, development, and quality assurance requirements for the flight control related functions of the Vehicle Management Systems (VMS) of military piloted aircraft. It also provides specification guidance for the flight control interfaces with other systems and subsystems of the aircraft.
A-6A3 Flight Control and Vehicle Management Systems Cmt
This SAE Aerospace Standard (AS) covers the requirements for thermocouple extension cable. Manufacturers of primary thermocouple wire in accordance with this specification must be qualified to the similar wire type specified in Table 1.
AE-8D Wire and Cable Committee
This glossary of tire military/industry represents the latest state-of-the-art terms and definitions for military use. This SAE Recommended Practice shall remain open for comments from the reader and shall also be reviewed and updated periodically. Many similar terms and definitions were reviewed from which the ones best applied to military use were selected. It is the purpose of this task force to provide technical definitions in present day use.
Truck and Bus Tire Committee
This SAE Aerospace Standard (AS) applies to a personal, portable oxygen concentrator (POC) to be supplied and used by a passenger requiring supplemental oxygen therapy while traveling on board civil, commercial, or personal aircraft. It covers a POC during both self-powered battery operation and while powered from an aircraft seat’s electrical power through the use of an accessory adapter. The POC is not intended to be connected to the aircraft’s oxygen systems or to be used by any aircraft personnel in any method of treatment or first aid of the general flying public.
A-10 Aircraft Oxygen Equipment Committee
This Aerospace Information Report (AIR) is the primary vehicle for providing the survey results to industry and government. The Institute of Defense Analysis (IDA), has performed a study which concludes that computerized techniques must be developed to integrate RM&S into product design in order to permit design influence from inception throughout the product life cycle. This AIR addresses the DoD initiative for developing Computer Aided Acquisition and Logistic Support (CALS) and industry's role in its evolution. AIR 4276 provides the detailed results of an industry/government survey inquiring into the extent of computerization of RM&S into the design process. Background information describes the evolution of the survey and why it was developed. The results provide demographic information about the respondents, the existence and extent of their CALS policy and plans, the priority placed on each RM&S task, and the extent to which these tasks have been computerized into the design
G-11M, Maintainability, Supportability and Logistics
The general requirements of an SPC system shall encompass, but are not limited to, the following elements: a Overall quality system b Management commitment c SPC system documentation d Critical process nodes e Gage characterization and capability f Process characterization and capability g Control system documentation h On-line/off-line control i Training j Supplier SPC systems k Calibration l Preventive maintenance m Self audit
Systems Management Council
This document provides definitions pertaining to dual and coaxial counter-rotating propellers.
E-25 General Standards for Aerospace and Propulsion Systems
This specification establishes the performance requirements for the identification of wire and cable by indirect markings that have been applied to electrical insulating materials including heat shrink sleeving, wrap around labels and “tie-on” tags as well as any other types of materials used for indirect marking. This specification covers the processes used to mark these materials, including impact ink marking, thermal transfer, hot stamp, and lasers, etc. This specification does not cover the direct marking on insulated electrical wires and cables.
AE-8A Elec Wiring and Fiber Optic Interconnect Sys Install
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