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A-6A3 Flight Control and Vehicle Management Systems Cmt Fluid power systems Pressure

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Standard

Vehicle Management Systems - Flight Control Function, Design, Installation and Test of Piloted Military Aircraft, General Specification For
2024-04-16
WIP
AS94900B
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.
Standard

Integrated Rudder and Brake Pedal Unit, General Requirements for Fly-By Wire Transport and Business Aircraft
2023-10-23
WIP
ARP6252A
This Aerospace Recommended Practice (ARP) provides general requirements for a generic, integrated rudder and brake pedal unit, incorporating a passive force-feel system that could be used for fixed-wing fly-by wire transport and business aircraft.This ARP addresses the following:- The functions to be implemented- The mechanical interconnection between captain and F/O station- The geometric and mechanical characteristics- The mechanical, electrical, and electronic interfaces- The safety and certification requirements
Standard

Aircraft Flight Control Actuation System Failure-Detection Methods
2022-12-16
CURRENT
AIR5273A
This SAE Aerospace Information Report (AIR) provides descriptions of aircraft flight control actuation system failure-detection methods. The fault-detection methods are those used for ground and in-flight detection of failures in electrohydraulic actuation systems for primary flight controls.
Standard

Skew and Disconnect Detection in High Lift Systems
2021-09-09
WIP
ARP5775
The document provides a definition of skew and disconnect occuring in high lift systems in flight controls including their hazard assessment, describes generic solutions and provides a for specifying requirements.
Standard

Design and Test Recommendations for Dielectric Strength and Insulation Resistance for Line Replaceable Units
2021-04-26
WIP
ARP5769
Scope: This Aerospace Recommended Practice (ARP) provides guidelines for specifying dielectric withstanding strength and insulation resistance design and test requirements for aircraft line replaceable units (LRU's) used within a flight control and/or a utility system. 1.1 Purpose The testing is intended to verify that an LRU can operate safely at its rated voltage and withstand momentary over potentials due to switching, troubleshooting testing, surges, etc.. The testing is also intended to verify adequate design margin of the insulation system and detect workmanship problems.
Standard

Description of Actuation Systems for Aircraft With Fly-By-Wire Flight Control Systems
2018-07-24
CURRENT
AIR4253B
This SAE Aerospace Information Report (AIR) provides design information of various contemporary aircraft fly-by-wire (FBW) flight control actuation systems that may be useful in the design of future systems for similar applications. It is primarily applicable to manned aircraft. It presents the basic characteristics, hardware descriptions, redundancy concepts, functional schematics, and discussions of the servo controls, failure monitoring, and fault tolerance. All existing FBW actuation systems are not described herein; however, those most representing the latest designs are included. While this AIR is intended as a reference source of information for aircraft actuation system designs, the exclusion or omission of any other appropriate actuation system or subsystem should not limit consideration of their use on future aircraft.
Standard

Aerospace Fly-by-Light Actuation Systems
2014-12-18
CURRENT
AIR4982A
This SAE Aerospace Information Report (AIR) has been prepared to provide information regarding options for optical control of fluid power actuation devices. It is not intended to establish standards for optical fluid power control, but rather is intended to provide a baseline or foundation from which standards can be developed. It presents and discusses approaches for command and communication with the actuation device via electro-optic means. The development of standards will require industry wide participation and cooperation to ensure interface commonality, reliability, and early reduction to practice. To facilitate such participation, this document provides potential users of the technology a balanced consensus on its present state of development, the prospects for demonstration of production readiness, and a discussion of problem areas within this technology.
Standard

Mechanical Control Design Guide
2012-11-01
HISTORICAL
ARP5770
This SAE Aerospace Recommended Practice (ARP) provides guidelines for the configuration and design of mechanical control signal transmission systems and subsystems. It is focused on the recommended practices for designing cable and pulley, pushrod and bellcrank and push-pull flexible cable control systems. These systems are typically used in some combination to transmit pilot commands into primary, secondary and utility control system commands (mechanical or electrical) or aircraft surface commands. On mechanically controlled aircraft, most pilot control commands are initiated through cockpit mounted wheels, sticks, levers, pedals or cranks that are coupled by pushrods or links to cable systems. The cable systems are routed throughout the aircraft and terminated in close proximity to the commanded surface or function where cranks and pushrods are again used to control the commanded function.
Standard

Fluidic Technology
2012-05-31
CURRENT
ARP993D
The scope of this document is limited to encompass terminology, symbols, performance criteria and methods reflecting the current status of the technology.
Standard

Power Sources for Fluidic Controls
2012-05-31
CURRENT
AIR1245B
This SAE Aerospace Information Report (AIR) presents a review of the types and general characteristics of power sources that may be used to provide the power for gaseous or liquid fluidic control systems. Fluidic definitions, terminology, units and symbols are defined in Reference 2.1.1.
Standard

FLUIDIC TECHNOLOGY
2011-08-10
HISTORICAL
ARP993A
The scope of this document is limited to encompass terminology, symbols, performance criteria and certain elementary test methods reflecting the current status of the technology.
Standard

Fluidic Technology
2007-01-11
HISTORICAL
ARP993C
The scope of this document is limited to encompass terminology, symbols, performance criteria and methods reflecting the current status of the technology.
Standard

Aerospace Fly-by-Light Actuation Systems
2007-01-11
HISTORICAL
AIR4982
This SAE Aerospace Information Report (AIR) has been prepared to provide information regarding options for optical control of fluid power actuation devices. It is not intended to establish standards for optical fluid power control, but rather is intended to provide a baseline or foundation from which standards can be developed. It presents and discusses approaches for command and communication with the actuation device via electro-optic means. The development of standards will require industry wide participation and cooperation to ensure interface commonality, reliability, and early reduction to practice. To facilitate such participation, this document provides potential users of the technology a balanced consensus on its present state of development, the prospects for demonstration of production readiness, and a discussion of problem areas within this technology.
Standard

Power Sources for Fluidic Controls
2007-01-11
HISTORICAL
AIR1245A
This SAE Aerospace Information Report (AIR) presents a review of the types and general characteristics of power sources that may be used to provide the power for gaseous or liquid fluidic control systems. Fluidic definitions, terminology, units and symbols are defined in Reference 2.1.1.
Standard

Description of Actuation Systems for Aircraft With Fly-By-Wire Flight Control Systems
2001-04-01
HISTORICAL
AIR4253A
This information report (AIR) provides design information of various contemporary aircraft fly-by-wire (FBW) flight control actuation systems that may be useful in the design of future systems for similar applications. It is primarily applicable to manned aircraft. It presents the basic characteristics, hardware descriptions, redundancy concepts, functional schematics, and discussions of the servo controls, failure monitoring, and fault tolerance. All existing FBW actuation systems are not described herein; however, those most representing the latest designs are included. While this AIR is intended as a reference source of information for aircraft actuation system designs, the exclusion or omission of any other appropriate actuation system or subsystem should not limit consideration of their use on future aircraft.
Standard

DESCRIPTION OF ACTUATION SYSTEMS FOR AIRCRAFT WITH FLY-BY-WIRE FLIGHT CONTROL SYSTEMS
1999-05-01
HISTORICAL
AIR4253
This AIR provides a description of representative state-of-the-art, fly-by-wire (FBW) actuation systems used in flight control systems of manned aircraft. It presents the basic characteristics, hardware descriptions, redundancy concepts, functional schematics, and discussions of the servo controls, failure monitoring, and fault tolerance. All existing FBW actuation systems are not described herein; however, those most representing the latest designs are included. While this AIR is intended as a reference source of information for future aircraft actuation system designs, the exclusion or omission of any other appropriate actuation system or subsystem should not limit consideration of their use on future aircraft.
Standard

FLUIDIC TECHNOLOGY
1995-06-01
HISTORICAL
ARP993
The scope of this document is limited to encompass terminology, symbols, performance criteria and certain elementary test methods reflecting the current status of the technology.
Standard

FLUIDIC TECHNOLOGY
1995-06-01
HISTORICAL
ARP993B
The scope of this document is limited to encompass terminology, symbols, performance criteria and methods reflecting the current status of the technology.
Standard

POWER SOURCES FOR FLUIDIC CONTROLS
1991-11-01
HISTORICAL
AIR1245
This AIR concerns itself with the end use of Fluidic (or Flueric) control hardware on aerospace vehicle applications. The fluidic control hardware application is viewed as a system comprised of the following subsystems: Power Source Power Conditioner Fluidic/Flueric Control(s) This AIR identifies potential power sources and relates the design of the fluidic/flueric controls to the nature of both the power source and, as required, the power conditioner. In the unlikely event that the power source yields a fluid which is always at the desired pressure level, temperature range and flow rate capacity and, further, is free of particulate or liquid contaminate, pressure pulsation, etc., no power conditioner is required. Experience has shown that the power conditioner is usually necessary to assure operability and reliability of the total control system.
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