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Standard

Gland Design, O-ring and Other Seals

2017-12-12
CURRENT
AS4716C
This SAE Aerospace Standard (AS) provides standardized gland (groove) design criteria and dimensions for O-ring seal glands for static and dynamic applications, and other seals.
Standard

Requirements for Aerospace Quality Management System Certification/Registrations Programs

2017-12-10
CURRENT
AS9104B
These requirements are applicable to IAQG sector schemes when making use of ABs, CRBs and their auditors, for the assessment and certification/registration of supplier quality systems in accordance with the requirements of this document. The quality management system standard used by the CRB shall be 9100/9110/9120, as appropriate to the supplier's activities. It shall be applied to the supplier's complete Quality System that covers aerospace products. Sectors may use these requirements for other standards. IAQG members have committed to recognize the equivalence of certification/registration of a suppliers quality management system to either of the AS, EN or JISQ/SJAC standards.
Standard

Handles and Attachments for Hand Socket Wrenches

2017-12-07
CURRENT
AS4283C
This SAE International Standard covers handles and attachments for use with sockets and crowfoot wrenches in aerospace applications involving high torque, limited clearances, and generally clean conditions. This document provides additional requirements beyond ASME B107.110, Category 10 appropriate for aerospace use. Inclusion of dimensional data in this document is not intended to imply all of the products described therein are stock production sizes. Consumers are requested to consult with manufacturers concerning lists of stock production sizes.
Standard

Qualifications Required for SAE Type II/III/IV Aircraft Deicing/Anti-Icing Fluid

2017-12-07
CURRENT
ARP5718B
This document describes: the preparatory steps to test experimental Type II, III, and IV fluids according to AMS1428; the recommendations for the preparation of samples for endurance time testing according to ARP5485; a short description of wind tunnel testing; a short description of the recommended field spray test; the protocol to generate draft holdover time guidelines from endurance time data obtained from ARP5485; the protocol for inclusion of Type II, III, and IV fluids on the FAA and Transport Canada lists of fluids and the protocol for updating the lists of fluids; the role of the SAE G-12 Aircraft Deicing Fluids Committee; the role of the SAE G-12 Holdover Time Committee; and the process for the publication of Type II, III, and IV holdover time guidelines. This document does not describe laboratory testing procedures. This document does not include the qualification requirements for AMS1424 Type I fluids (these are provided in ARP6207).
Standard

Coupling Assembly, Threadless, Flexible, Fixed Cavity, Self-Bonding, Procurement Specification

2017-12-07
CURRENT
AS1650E
This SAE Aerospace Standard (AS) defines the requirements for a threadless, flexible, self-bonding coupling assembly which, when installed on machined fixed cavity ferrules, provides a flexible connection for joining tubing and components in aircraft fuel, vent or other systems. This assembled coupling, hereafter referred to as the assembly, and is designed for use from −65 to +400 °F and at 125 psig nominal operating pressure. AS1650 was not designed for the new certification requirements for flammable leakage zones and fuel tanks for lightning protection and assembly redundancy. As such their use and installation may require additional efforts and equipment to support new FAA CFR compliance. The AS7510 flexible coupling should be the preferred coupling for use in flammable leakage zones and fuel tanks that require service life and functionality for lightning protection and part redundancy.
Standard

Electrical Computing Resolvers

2017-11-30
CURRENT
ARP826A
This document covers resolvers which are used to perform coordinate transformations as well as sine and cosine computations, It includes both the categories of compensated and uncompensated resolvers which perform these functions. Linear resolvers are also included because of their similarity to resolvers.
Standard

Electric Devices, Simple, General Specification For

2017-11-30
CURRENT
AS81099A
This specification gives general requirements for electric devices for which the detail requirements are given by standards only, as the detail requirements for the devices are not complex enough to warrant issuance of detail specifications for them.
Standard

Precision Control Motors – 400 Cycles

2017-11-30
CURRENT
ARP497B
This recommendation establishes objectives for high performance control motors to be used with aeronautical and associated equipment in protective enclosures or completely within the shell of the aircraft so that they are subjected only to the internal climatic conditions of heat, cold, shock, vibration, altitude, and humidity. Control motors larger than size #23 are not covered in this document.
Standard

Document for 270 Voltage Direct Current (270 V DC) System

2017-11-30
CURRENT
ARP4729A
This SAE Aerospace Recommended Practice (ARP) provides technical design and application information related to the generation, distribution, control, and utilization of aircraft 270 V DC electrical power systems and support equipment. This document also provides references and definitions to permit comparisons of various electrical systems and components.
Standard

Penalties IN Performance of Three-Phase, Four-Wire, 400-Cycle Motors Caused by the Opening of One Phase

2017-11-30
CURRENT
AIR34B
The scope of this SAE Aerospace Information Report (AIR) is to present a guide for the determination of probable power output and the effect on the aircraft system that will be experienced when operating three-phase motors with one phase open. Unfortunately, the above subject cannot be resolved by specific rules. Modern aircraft or missile electrical systems are composed of a wide variety of electrical and electronic components. These components react differently under identical impetus due to the latitude of their design. This latitude of design must be allowed wherever possible to the accessory designer due to the various specification requirements. Therefore, it cannot be over-emphasized that the effect on the airplane or missile system, as well as motor operation, of three-phase motors on two-phase power must be thoroughly investigated.
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