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Items (212,829)

CIRCUIT BREAKER - AIRCRAFT, TRIP FREE, PUSH PULL, 25 THRU 35 AMPS, TYPE I -55 TO +121 °C

03/27/2023

AE-7P Protective and Control Devices

Vehicle Management Systems - Flight Control Function, Design, Installation and Test of Piloted Military Aircraft, General Specification

AS94900A (Current)

08/13/2018

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

PACKING, PREFORMED, HYDROCARBON FUEL RESISTANT, "O" RING

AS29513C (Current)

11/09/2021

A-6C2 Seals Committee

HOSE ASSEMBLY, LINED SILICONE, 125 PSI, FLARELESS, POTABLE WATER, STRAIGHT TO 90

AS4471C (Current)

08/14/2018

G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies

HOSE ASSEMBLY, LINED SILICONE, 125 PSI, FLARELESS, POTABLE WATER, STRAIGHT MALE TO 90° FEMALE

AS4477C (Current)

08/14/2018

G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies

HOSE ASSEMBLY, LINED SILICONE, 125 PSI, FLARELESS, POTABLE WATER, STRAIGHT MALE TO 45° FEMALE

AS4476C (Current)

08/14/2018

G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies

FITTING, PLUG, PIPE, EXTERNAL THREAD, COUNTERSUNK HEX HEAD

AS4864A (Current)

01/07/2013

G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies

National Aerospace and Defense Contractors Accreditation Program (Nadcap) Audit and Inspection Procedures and Checklists for the Sealant Manufacturers Accreditation Program

AS7200/1B (Current)06/19/2017

This document has been declared "CANCELLED" as of June 2017 and has been superseded by PRI AC7200/1. By this action, this document will remain listed in the Numerical Section of the Aerospace Standards Index noting that it is superseded by PRI AC7200/1. Cancelled specifications are available from SAE

Nadcap Management Council

HOSE ASSEMBLY, POLYTETRAFLUOROETHYLENE, METAL BRAID, MEDIUM PRESSURE, FLARELESS, 45° TO 90

AS651C (Current)

06/20/2011

G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies

HOSE ASSEMBLY, POLYTETRAFLUOROETHYLENE, METAL BRAID, MEDIUM PRESSURE, FLARELESS, 45° TO 45

AS650C (Current)

06/20/2011

G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies

Regional Aircraft Towbar Attach Fitting Interface

AS5488A (Current)

06/20/2011

This SAE Aerospace Standard (AS) specifies the interface requirements for towbar attachment fittings on the nose gear (when towing operations are performed from the nose gear) of conventional tricycle type landing gears of commercial civil transport aircraft with a maximum ramp weight between 8600 kg (19 000 lb) and 50 000 kg (110 000 lb), commonly designated as "regional aircraft". Its purpose is to achieve towbar attachment fittings interface standardization by aircraft weight category (which determines towbar forces) in order to ensure that one single type of towbar with a standard connection can be used for all aircraft types within or near that weight category, so as to assist operators and airport handling companies in reducing the number of different towbar types used

AGE-3 Aircraft Ground Support Equipment Committee

RIVET - TUBULAR, COUNTERSUNK, AS7228

AS3228B (Current)

11/05/2019

E-25 General Standards for Aerospace and Propulsion Systems

BEARING, PLAIN, ROD END, SELF-ALIGNING, SELF-LUBRICATING, WIDE, INTERNALLY THREADED, STEEL, CORROSION RESISTANT (CRES) −65 TO +325 °F

AS81935/7A (Current)06/20/2011

ACBG Plain Bearing Committee

HOSE ASSEMBLY, POLYTETRAFLUOROETHYLENE, METAL BRAID, MEDIUM PRESSURE, FLARELESS, STRAIGHT TO 90

AS649C (Current)

06/20/2011

G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies

Statistical Process Control Systems

EIA557B (Current)

07/01/2015

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

HOSE ASSEMBLY, POLYTETRAFLUOROETHYLENE, METAL BRAID, MEDIUM PRESSURE, FLARED, STRAIGHT TO STRAIGHT

AS640A (Current)

06/20/2011

G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies

Minimum Performance Standards for Static Electric Power Inverters

AS8023B (Current)08/03/2011

This SAE Aerospace Standard (AS) establishes the minimum performance standards for equipment used as secondary alternating current (AC) electrical power sources in aerospace electric power systems

AE-7B Power Management, Distribution and Storage

Thermophysical Properties of the Natural Environment, Gases, Liquids, and Solids

AIR1168/9A (Current)07/25/2011

This AIR is arranged in the following four sections: 2A - Properties of the Natural Environment 2B - Properties of Gases 2C - Properties of Liquids 2D - Properties of Solids A summary of each section is given below

AC-9 Aircraft Environmental Systems Committee

Accelerometer Group, Counting (MS25447 and MS25448

AS22145A (Current)

08/22/2012

This specification covers the design and performance requirements for a single axis, four load-factor level counting accelerometer group referred to hereafter as “equipment

A-4 Aircraft Instruments Committee

Flange Accessory 4.125 Pilot Diameter - QAD

AS523A (Current)

10/01/2001

AE-1 Engine Accessory Installations Committee

Reducers, Pneumatic Pressure, Missile

AS1297B (Current)

10/06/2014

The complete specification for a pneumatic pressure reducer for high pressure pneumatic systems used in missiles comprises: (1) this standard, which includes many of the general performance requirements, (2) a detailed procurement specification describing envelope and operating conditions, and (3) the "Pneumatic Components, Aeronautical - General Specification For - MIL-P-8564" which covers general requirements common to all components for use in high pressure pneumatic systems

A-6C5 Components Committee

FUSE HOLDER, BLOCK-TYPE, 1-, 2-, 3-POLE, 35- TO 60-AMPERE, AIRCRAFT

AS24001A (Current)

10/06/2014

AE-7P Protective and Control Devices

Adapter - 8.000 Bolt Circle to 4.125 Pilot Diameter - QAD

AS530A (Current)

10/01/2001

AE-1 Engine Accessory Installations Committee

HOSE ASSEMBLY, LINED SILICONE, 125 PSI, FLARELESS, POTABLE WATER, STRAIGHT MALE TO STRAIGHT FEMALE

AS4475C (Current)

08/14/2018

G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies

HOSE ASSEMBLY, LINED SILICONE, 125 PSI, FIXED CAVITY COUPLING, POTABLE WATER, STRAIGHT MALE TO 45° MALE

AS4705D (Current)

08/14/2018

G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies

HOSE ASSEMBLY, LINED SILICONE, 125 PSI, FIXED CAVITY COUPLING, POTABLE WATER, STRAIGHT MALE TO STRAIGHT MALE

AS4704D (Current)

08/14/2018

G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies

HOSE ASSEMBLY, LINED SILICONE, 125 PSI, FLARELESS, POTABLE WATER, STRAIGHT MALE TO STRAIGHT MALE

AS4478C (Current)

08/14/2018

G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies

CRIMPING TOOL, TYPE 2, TERMINAL, HAND, WIRE TERMINATION FOR SIZE 16 SHIELDED CONTACTS (SHIELD CRIMP SLEEVE

AS22520/20A (Current)12/05/2019

AE-8C2 Terminating Devices and Tooling Committee

BOLT, MACHINE - DOUBLE HEXAGON EXTENDED WASHER HEAD, CLOSE TOLERANCE SHANK, AMS4967 (UNS R56400), 160 KSI, .5625-18, UNJF-3A

AS3153B (Current)

12/05/2019

E-25 General Standards for Aerospace and Propulsion Systems

Airborne Icing Tankers

ARP5904 (Current)

06/17/2019

This SAE Aerospace Recommended Practice (ARP) document establishes criteria and recommended practices for the use of airborne icing tankers to aid in design and certification of aircraft ice protection systems and components. Several icing tankers are described, along with their capabilities and suggested use. Sample data for these tanker spray systems are included, shown with 14 CFR Parts 25 and 29, Appendix C icing envelopes for continuous maximum and intermittent maximum icing conditions. (Note: In the remainder of this document, the phrase “Appendix C icing envelopes” will be used for brevity.) This ARP is intended as a guide toward standard practice and is subject to change to keep pace with experience and technical advances

AC-9C Aircraft Icing Technology Committee

PIN, COTTER - CRES, UNS S32100, AS7211

AS9245B (Current)

04/10/2019

E-25 General Standards for Aerospace and Propulsion Systems

BOLT, MACHINE - DOUBLE HEXAGON EXTENDED WASHER HEAD, CORROSION AND HEAT RESISTANT STEEL, UNS S66286, UTS 130 KSI MIN, .3750-24 UNJF-3A

AS9559E (Current)

04/04/2024

E-25 General Standards for Aerospace and Propulsion Systems

HOSE ASSEMBLY, POLYTETRAFLUOROETHYLENE, METAL BRAID, MEDIUM PRESSURE, FLARED, STRAIGHT TO 90

AS642A (Current)

06/20/2011

G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies

Zero Acceptance Number Sampling Procedures and Tables for Inspection by Attributes of Isolated Lots

EIA585 (Current)

07/01/2015

(From Standards Proposal No. 2358, formulated under the cognizance of the EIA Quality and Reliability Engineering (QRE) Committee

Systems Management Council

Assessment of Quality Levels in PPM Using Variables Test Data

EIA591 (Current)

07/01/2015

Systems Management Council

General Procedure for Capability Approval of Electronic Components

EIA601A (Current)

07/01/2015

This standard specifies requirements for the approval and maintenance of a manufacturer's capability and the procedures for the test and release of passive electronic components manufactured under capability approval. It also includes requirements for generic specifications that invoke this standard. It applies to all passive electronic components to be released under the capability requirements of an EIA generic and/or sectional and/or detail specification

Systems Management Council

Spacecraft Thermal Balance

AIR1168/12A (Current)07/25/2011

In the design of spacecraft, heat transfer becomes a criterion of operation to maintain structural and equipment integrity over long periods of time. The spacecraft thermal balance between cold space and solar, planetary, and equipment heat sources is the means by which the desired range of equipment and structural temperatures are obtained. With the total spacecraft balance set, subsystem and component temperatures can be analyzed for their corresponding thermal requirements. This section provides the means by which first-cut approximations of spacecraft surface, structure, and equipment temperatures may be made, using the curves of planetary and solar heat flux in conjunction with the desired coating radiative properties. Once the coating properties have been determined, the material to provide these requirements may be selected from the extensive thermal radiative properties tables and curves. These can then be cross checked to determine the degradation effects of space that may

AC-9 Aircraft Environmental Systems Committee

Spacecraft Boost and Entry Heat Transfer

AIR1168/11A (Current)07/25/2011

The prediction of vehicle temperatures during ascent through the earth’s atmosphere requires an accurate knowledge of the aerodynamic heating rates occurring at the vehicle surface. Flight parameters required in heating calculations include the local airstream velocity, pressure, and temperature at the boundary layer edge for the vehicle location in question. In addition, thermodynamic and transport air properties are required at these conditions. Both laminar and turbulent boundary layers occur during the boost trajectory. Experience has shown that laminar and turbulent heating are of equivalent importance. Laminar heating predominates in importance in the stagnation areas, but the large afterbody surfaces are most strongly affected by turbulent heating. Once the local flow conditions and corresponding air properties have been obtained, the convective heating rate may be calculated for a particular wall temperature. This assumes that the boundary layer flow regime (that is, turbulent

AC-9 Aircraft Environmental Systems Committee

Aerospace Pressurization System Design

AIR1168/7A (Current)07/25/2011

The pressurization system design considerations presented in this AIR deal with human physiological requirements, characteristics of pressurization air sources, methods of controlling cabin pressure, cabin leakage control, leakage calculation methods, and methods of emergency cabin pressure release

AC-9 Aircraft Environmental Systems Committee

Insert - Screw Thread, Thin Wall, Self-Locking, UNS N07718, Silver Plated, Class: 185 ksi/1025 °F, Procurement Specification

AS3506B (Current)

04/09/2019

This SAE Aerospace Standard (AS) establishes the requirements for AS3504 and AS3505 thin wall self-locking inserts made from a corrosion and heat resistant, age hardenable nickel base alloy of the type identified under the Unified Numbering System as UNS N07718

E-25 General Standards for Aerospace and Propulsion Systems

DRYING OF THERMOSETTING COMPOSITE MATERIALS

ARP4977 (Current)

05/14/2021

This SAE Aerospace Recommended Practice (ARP) describes standard methods for drying commercial aircraft composite structures prior to repair and gives general guidelines on use and applicability. It addresses the removal of liquids that have collected inside the structures through open damage, microcracks, or porosity and the removal of absorbed moisture from the composite material. The methods described in this document shall only be used when specified in an approved repair document or with the agreement of the original equipment manufacturer (OEM) or regulatory authority. If this document is used for the drying of materials other than thermosetting composite materials, the fitness for this purpose must be determined by the user

AMS CACRC Commercial Aircraft Composite Repair Committee

Guide for Preparing An ECS Computer Program User's Manual

ARP1623A (Current)10/01/1997

The purpose of this recommended practice is to provide aircraft industry with guidelines as to the pertinent information which should be contained in a user's manual for an environmental control system (ECS) computer program. This recommended practice is intended to facilitate the preparation of a user's manual without unduly restricting its format or content

AC-9 Aircraft Environmental Systems Committee

Design Specification for Regional Aircraft Towbarless Tow Vehicle for Pushback and/or Maintenance Towing Operations

ARP5916A (Current)

03/28/2022

The tow vehicle should be designed for towbarless push-back and/or maintenance towing of regional type aircraft as specified in 1.3. The design will ensure that the unit will safely secure the aircraft nose landing gear within the coupling system for any operational mode. The purpose of this towing procedure is to achieve a safer and faster operation than is possible with conventional towing equipment

AGE-3 Aircraft Ground Support Equipment Committee