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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

Descriptions of Systems Integration Test Rigs (Iron Birds) For Aerospace Applications

2021-04-07
WIP
AIR5992A
This Aerospace Information Report (AIR) provides information on systems integration rigs, commonly referred to as “Iron Birds” for aerospace applications. a. It includes background historical information including descriptions of Iron Birds produced to date, important component elements and selection rationale, hydraulic system design and operational modes and illustrates the design approaches to be considered. b. It provides illustrations of the various systems that should be considered for Iron Bird testing in the development phase and utilization during the production program. c. It includes recommendations for simulation, component development tests, system integration and lessons learned.
Standard

Utility System Characterization, An Overview

2021-02-23
WIP
AIR5428A
Modern air vehicles consist of many subsystems, traditionally managed as a federation of independent subsystems. Advances in control technologies, digital electronics and electro-mechanical hardware, provide potential opportunities to integrate subsystems for future aircraft. This document does not define any particular integration strategy. Its purpose is to provide information about traditional federated subsystems from the functional, control, resource, and hardware perspective. To be able to integrate subsystems, one must have a basic understanding of the subsystems, and this document provides an introduction or starting point for initiating the integration process.
Standard

Aerospace - Passive Side Stick Unit General Requirements for Fly-by Wire Transport and Business

2020-04-23
CURRENT
ARP6001B
This SAE Aerospace Recommended Practice (ARP) provides recommendations for design and test requirements for a generic “passive” side stick that could be used for fly-by wire transport and business aircraft. It addresses the following: The functions to be implemented The geometric and mechanical characteristics The mechanical and electrical interfaces The safety and certification requirements
Standard

Aerospace - Vehicle Management Systems - Flight Control Design, Installation and Test of, Military Unmanned Aircraft, Specification Guide For

2019-10-24
WIP
ARP94910A
This document establishes recommended practices for the specification of general performance, design, test, development, and quality assurance requirements for the flight control related functions of the Vehicle Management Systems (VMS) of military Unmanned Aircraft (UA), the airborne element of Unmanned Aircraft Systems (UAS), as defined by ASTM F 2395-07. The document is written for military unmanned aircraft intended for use primarily in military operational areas. The document also provides a foundation for considerations applicable to safe flight in all classes of airspace.
Standard

Mechanical Control Design Guide

2019-04-17
WIP
ARP5770A
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

Integrated Rudder and Brake Pedal Unit, General Requirements for Fly-By Wire Transport and Business Aircraft

2018-10-15
CURRENT
ARP6252
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

Aerospace - Passive Side Stick Unit General Requirements for Fly by Wire Transport and Business

2018-10-04
HISTORICAL
ARP6001A
This SAE Aerospace Recommended Practice (ARP) provides general requirements for a generic “passive” side stick that could be used for fly by wire transport and business aircraft. It addresses the following: The functions to be implemented The geometric and mechanical characteristics The mechanical and electrical interfaces The safety and certification requirements
Standard

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

2018-08-13
CURRENT
AS94900A
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

Methodology for Investigation of Flight Control System Anomalies

2018-04-24
WIP
AIR5875A
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.
Standard

Aircraft Flight Control Systems Descriptions

2016-07-18
CURRENT
AIR4094A
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.
Standard

Primary Flight Control Hydraulic Actuation System Interface Definition

2015-10-19
CURRENT
AIR4922A
This SAE Aerospace Information Report (AIR) provides a description of the interfaces and their requirements for generic and specific hydraulic actuation systems used in the flight control systems of manned aircraft. Included are the basic control system characteristics and functional requirements, and the essential interfaces (structural, mechanical, hydraulic power, control input, status monitoring, and environment). Major design issues, requirements, and other considerations are presented and discussed.
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

Actuation System Failure Detection Methods

2013-05-05
WIP
AIR5273A
This 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

Aerospace Active Inceptor Systems for Aircraft Flight and Engine Controls

2013-02-10
CURRENT
ARP5764
The purpose of this document is to develop the general characteristics and requirements for feel-force control systems for active cockpit controllers, also known as Active Inceptors. The document presents technical material that describes the recommended key characteristics and design considerations for these types of systems. Where appropriate, the effects of platform specific requirements (e.g., single axis/dual axis, single seat/dual seat, civil/military, rotorcraft/fixed wing aircraft, etc.) are clearly identified. The material developed will serve as a reference guide for: a Aircraft prime contractors who want to understand active cockpit controller technology and develop their own set of requirements; b Suppliers that develop active cockpit controller equipment and; c Regulatory Authorities who will be involved in the certification of these types of systems.
Standard

Aerospace - Vehicle Management Systems - Flight Control Design, Installation and Test of, Military Unmanned Aircraft, Specification Guide For

2012-12-19
CURRENT
ARP94910
This document establishes recommended practices for the specification of general performance, design, test, development, and quality assurance requirements for the flight control related functions of the Vehicle Management Systems (VMS) of military Unmanned Aircraft (UA), the airborne element of Unmanned Aircraft Systems (UAS), as defined by ASTM F 2395-07. The document is written for military unmanned aircraft intended for use primarily in military operational areas. The document also provides a foundation for considerations applicable to safe flight in all classes of airspace.
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