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Video

Visionary's Take: An Engineering Journey into the Marketplace (Part 3 of 3)

2017-10-12
Can you become a visionary or are you born one? How does a visionary capture an opportunity and makes it a successful business? Are engineers more qualified to solve technical problems or run companies? SAE's "The Visionary's Take" addresses these and many other questions, by talking directly with those who have dared to tackle difficult engineering problems, and create real-life products out of their experience. In these short episodes, Sanjiv Singh and Lyle Chamberlain, respectively CEO and Chief Engineer from Near Earth Autonomy, talk about their experience in creating a brand-new company in the UAV world. Founded in 2011, Near Earth Autonomy brought together a group of engineers and roboticists, looking for unconventional solutions to very hard logistics problems, presenting danger to human life. The answers were developed by pushing technology to a higher level, testing quickly and often, and keeping an open mind to alternative ways of framing engineering challenges.
Video

Visionary's Take: An Engineering Journey into the Marketplace (Part 1 of 3)

2017-10-12
Can you become a visionary or are you born one? How does a visionary capture an opportunity and makes it a successful business? Are engineers more qualified to solve technical problems or run companies? SAE's "The Visionary's Take" addresses these and many other questions, by talking directly with those who have dared to tackle difficult engineering problems, and create real-life products out of their experience. In these short episodes, Sanjiv Singh and Lyle Chamberlain, respectively CEO and Chief Engineer from Near Earth Autonomy, talk about their experience in creating a brand-new company in the UAV world. Founded in 2011, Near Earth Autonomy brought together a group of engineers and roboticists, looking for unconventional solutions to very hard logistics problems, presenting danger to human life. The answers were developed by pushing technology to a higher level, testing quickly and often, and keeping an open mind to alternative ways of framing engineering challenges.
Standard

SAFE-LIFE LIMITS FOR LANDING GEAR STRUCTURES

2018-04-26
WIP
AIR6949
This document describes the approaches taken to define safe-life limits for the management of fatigue in landing gear structures, and the substantiation of those limits through full-scale fatigue testing. The safe-life scatter factors considered in a range of military and civil regulatory standards are also reviewed.
Standard

Fuel System Design Considerations for Composite Based Fuel Components

2018-11-19
WIP
AIR7493
This SAE Aerospace Information Report (AIR) is a compilation of engineering design guidelines and reference data useful to ensure composite materials used in fuel system components are compatible with an aircraft fuel system. This AIR is not a complete design manual, but offers insight into key aspects of composition design that must be adequately researched and verified before being used in a fuel system.
Standard

Fuel System Definitions and Glossary of Terms

2015-05-20
WIP
AIR6510
This SAE Aerospace Information Report (AIR) comprises the technical terms and nomenclature, together with their definitions and abbreviations that are used in Aircraft Fuel Systems.
Standard

Information Guide for Electric Motors which Drive Hydraulic Pumps

2016-04-25
WIP
AIR6855
This document provides an application guide for electric motors that drive aerospace hydraulic pumps. It provides details of the characteristics of electric motors powered by DC, Fixed Frequency AC, and Variable Frequency AC electrical systems. The applications include both military and commercial aircraft.
Standard

Landing Gear Safety Criticap Processes

2018-02-28
WIP
AIR6813
There are a number of safety critical processes that are common to landing gear systems. A safety critical process (CSP) is a landing gearmaintenance manufacturing, repair or overhaul process which if ommitted or preformed incorrectly will cause failure of a safety citical item (CSI) in operation. A CSI is a landing gear item whose failure or omission will cause more than $1M in damage, serious injury or death. This AIR will define methods and modes of failure for CSPs based on experience.
Standard

Considerations for Ground Fault Interrupter (GFI) / Arc Fault Circuit Breaker (AFCB) for fuel pumps power circuit protection installation, specification and testing

2016-02-08
WIP
AIR6384
This SAE Aerospace Information Report (AIR) is intended to provide guidance for installing GFI/AFCB in the fuel pumps power circuits for protection of fuel vapors ignition inside the tank in case of a failure that causing arcing inside the pump. Besides, this AIR is also intended to provide minimum specification and testing for ground fault interrupter (GFI) and arc fault circuit breaker (AFCB), addressing the issues associated with the verification requirements based on current regulatory guidance per AC25.981-1C.
Standard

Effects of Extremely Cold Temperature on Landing Gear Operation

2016-03-15
WIP
AIR6411
Provide information and guidance for landing gear operation in cold temperature environment. Covers all operational aspects on ground and in flight. Includes effects on: tires, wheels, brakes, shock strut, seals, and actuation.
Standard

Polymeric Bearings for Linear Actuators

2017-11-09
WIP
ARP7204
This SAE Aerospace Recommended Practice (ARP) provides guidelines for the application of polymeric bearings/wear rings for linear actuation systems. Design considerations are included for recommended fit and function in conjunction with material selection and load bearing capability.
Standard

Lubrication System Oil Tank Sizing

2018-02-26
WIP
ARP7976
This Aerospace Recommended Practice provides the considerations appropriate for Engine Lubrication System Oil Tank sizing, and provides means to confirm the oil volume held within the Oil Tank is adequate for satisfactory Lubrication System performance. Two scenarios should be considered when demonstrating that the Oil Tank capacity and oil volume held within the Oil Tank are adequate, sea level engine testing and in-flight operation, when demonstrating the capability of Lubrication System to operate in support of FAA Part 23 and Part 25, CFR Part 33, and corresponding EASA CS-E regulations, and equivalent Military application requirements.
Standard

Optical equipment safety in fuel tanks

2018-11-15
WIP
ARP7977
This project aims to develop a framework of requirements which support safe installation and operation of optical devices within an aircraft fuel tank, specifically: 1: To determine optical power and energy limits which ensure safe operation of optical installations within an aircraft fuel tank over aircraft life and under all phases of flight, taking the limits provided in IEC 60079-28:20015 as a starting point. 2: To demonstrate optical and electrical power and energy equivalences, where possible. 3: To determine requirements for optical installations, including bonding and electrostatic discharge for non-conductive components such as optical fibres. 4: To provide guidelines for analysis of the hazards presented by the typical internal components of optical devices, such as failure modes of photo diodes and cells.
Standard

Sizing of Emergency Braking Systems

2018-04-18
WIP
ARP6952
The pupose of this SAE AIR is to provide guidelines for sizing stored energy systems in use in emergency braking systems, in light of their intended purpose and applicable certification regulations.
Standard

Landing Gear Integrity Program

2016-03-17
WIP
ARP6412
The scope of the Landing Gear Integrity Programs (LGIP) Aerospace Recommended Practice (ARP) is intended to assist in the safe-life structural integrity management of the landing gear system and subsystems components. In addition, component reliability, availability, and maintainability is included in a holistic LGIP.
Standard

Engine Fuel System and Component Icing Test

2015-06-25
WIP
ARP6340
This ARP provides recommended practice on the considerations and methodology to demonstrate acceptable performance of the Engine components / fuel system, and APU, whilst operating throughout the flight cycle / engine duty for continuous operation with iced fuel and short duration operation with a snowshower resulting from release of accreted ice from fuel washed surfaces, where no anti-icing additives are present (e.g. Fuel System Icing Inhibitor FSII or alternative). Two scenarios must be considered when demonstrating the capability of Engine components / fuel system, and APU to operate with fuel borne ice to satisfy certification regulations applications in support of FAA Part 23 and Part 25, CFR Part 33, and corresponding EASA CS-E regulations, and equivalent Military application requirements.
Standard

Aircraft Brake Temperature Measurement

2017-10-26
WIP
ARP6812
This SAE Aerospace Recommended Practice (ARP) covers the functional, design, construction, and test requirements for Brake Temperature Monitoring Systems (BTMS), and sometimes referred to as Brake Temperature Indication Systems (BTIS). The BTMS is limited to aircraft where a dispatch indication and brake temperature indication is required. The scope of this BTMS equipment shall be limited to the 1) brake temperature sensor or indicator, 2) temperature reference measurement, if required, and 3) processing and communication of brake temperature. This recommended practice will not address cockpit ergonomics and aircraft operating procedures.
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