Browse Topic: Landing gear

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Computational Investigation of a Flexible Airframe Taxiing Over an Uneven Runway for Aircraft Vibration Testing01-17-02-001112/15/2023
Ground vibration testing (GVT) is an important phase of the development, or the structural modification of an aircraft program. The modes of vibration and their associated parameters extracted from the GVT are used to modify the structural model of the aircraft to make more reliable dynamics predictions to satisfy certification authorities. Due to the high cost and the extensive preparations for such tests, a new method of vibration testing called taxi vibration testing (TVT) rooted in operational modal analysis (OMA) was recently proposed and investigated by the German Institute for Aerospace Research (DLR) as alternative to conventional GVT. In this investigation, a computational framework based on fully coupled flexible multibody dynamics for TVT is presented to further investigate the applicability of the TVT to flexible airframes. The time domain decomposition (TDD) method for OMA was used to postprocess the response of the airframe during a TVT. The framework was then used to
Al-bess, Lohay, Khouli, Fidel
Journal Article
Gland Design, O-Ring and Other SealsAS4716D (Current)11/09/2021
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.
A-6C2 Seals Committee
Technical Standard
Gland Design, O-Ring and Other SealsAS4716D-TEST-REC (Historical)11/09/2021
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.
A-6C2 Seals Committee
Technical Standard
Crashworthy Landing Gear DesignAIR4566A (Current)08/09/2021
The intent of this SAE Aerospace Information Report (AIR) is to document the design requirements and approaches for the crashworthy design of aircraft landing gear. This document covers the field of commercial and military airplanes and helicopters. This summary of crashworthy landing gear design requirements and approaches may be used as a reference for future aircraft.
A-5B Gears, Struts and Couplings Committee
Information Report
Aircraft Tail BumpersAIR1800B (Current)06/22/2021
This SAE Aerospace Information Report (AIR) covers the field of civilian, commercial and military airplanes and helicopters. This summary of tail bumper design approaches may be used by design personnel as a reference and guide for future airplanes and helicopters that require tail bumpers. Those described herein will consist of simple rub strips, structural loops with a wear surface for runway contact, retractable installations with replaceable shock absorbers and wear surfaces and complicated retractable tail landing gears with shock strut, wheels and tires. The information will be presented as a general description of the installation, its components and their functions.
A-5B Gears, Struts and Couplings Committee
Information Report
Overview of Aircraft Landing Gear Shimmy Analysis MethodsAIR6280 (Current)06/10/2021
This SAE Aerospace Information Report (AIR) provides an overview of the tire properties, strut properties, damper properties, and other landing gear mechanical properties that contribute to shimmy stability and are required for shimmy analysis. A variety of analysis techniques and assumptions are presented.
A-5 Aerospace Landing Gear Systems Committee
Information Report
Overview of Aircraft Landing Gear Shimmy Analysis MethodsAIR6280-TEST-REC (Historical)06/10/2021
This SAE Aerospace Information Report (AIR) provides an overview of the tire properties, strut properties, damper properties, and other landing gear mechanical properties that contribute to shimmy stability and are required for shimmy analysis. A variety of analysis techniques and assumptions are presented.
A-5 Aerospace Landing Gear Systems Committee
Information Report
Landing Gear AlignmentAIR5556 (Current)04/23/2021
The purpose of this Aerospace Information Report is to provide the industry with methodologies for measuring tire/wheel gear alignment and the range of acceptable alignment settings for various types of non-military landing gear. This AIR will focus on the general aviation, corporate, and regional aircraft landing gear but could have applicability to commercial aircraft.
A-5 Aerospace Landing Gear Systems Committee
Information Report
Landing Gear StorageARP5936 (Current)04/23/2021
This document categorizes the different types of storage requirements, either on the aircraft or new unused or overhauled on the shelf, for aircraft landing gears/components. Recommendations and examples of proper landing gear storage are outlined. Reclamation recommendations are provided for aircraft landing gear returning from long-term storage.
A-5 Aerospace Landing Gear Systems Committee
Recommended Practice
Wheel ChocksAIR4905A (Current)04/08/2021
The purpose of this document is to present general considerations for the design and use of aircraft wheel chocks. The design and use of aircraft wheel chocks is a good deal more complicated than it may appear at first glance.
AGE-3 Aircraft Ground Support Equipment Committee
Information Report
Aircraft Tow BarARP1915E (Current)04/08/2021
This SAE Aerospace Recommended Practice (ARP) specifies dimensional and physical requirements of tow bar connections to tractor and aircraft (see Figure 1). It is applicable to all types of commercial transport category aircraft tow bar. The purpose of this SAE Aerospace Recommended Practice (ARP) is to standardize tow bar attachments to airplane and tractor according to the mass category of the towed aircraft, so that one tow bar head with different shear levels can be used for all aircraft that are within the same mass category and are manufactured in compliance with AS1614 or ISO 8267.
AGE-3 Aircraft Ground Support Equipment Committee
Recommended Practice
Gland Design: Scraper, Landing Gear, InstallationAS4052B-TEST-REC (Historical)02/03/2021
This SAE Aerospace Standard (AS) covers an alternate gland design for the installation of scraper/wiper rings in the lower end of landing gear shock struts for the purpose of contaminant exclusion. The defined scraper gland covered by this document, as shown in Table 1, is a variant of AS4716, the accepted gland standard for MS28775, O-ring packing seals. Piston rod diameters, gland internal diameters, groove sidewall angles and the surface finish are all defined by AS4716, but the gland outer retaining wall diameter is changed. The traditional scraper design installed into the glands detailed in Table 1 typically utilize components made from urethane or nitrile materials. These scraper designs, while still acceptable, must be reviewed in consideration to deicing, cleaners and disinfectant fluids applied to or in contact with the landing gear, as the materials of construction for the installed scrapers may not be compatible to these fluids. Exposure of the scraper to incompatible
A-5B Gears, Struts and Couplings Committee
Technical Standard
Aircraft Tail BumpersAIR1800A (Historical)02/03/2021
This SAE Aerospace Information Report (AIR) covers the field of civilian, commercial and military airplanes and helicopters. This summary of tail bumper design approaches may be used by design personnel as a reference and guide for future airplanes and helicopters that require tail bumpers. Those described herein will consist of simple rub strips, structural loops with a wear surface for runway contact, retractable installations with replaceable shock absorbers and wear surfaces and complicated retractable tail landing gears with shock strut, wheels and tires. The information will be presented as a general description of the installation, its components and their functions.
A-5B Gears, Struts and Couplings Committee
Information Report
Gland Design: Scraper, Landing Gear, InstallationAS4052B (Historical)02/03/2021
This SAE Aerospace Standard (AS) covers an alternate gland design for the installation of scraper/wiper rings in the lower end of landing gear shock struts for the purpose of contaminant exclusion. The defined scraper gland covered by this document, as shown in Table 1, is a variant of AS4716, the accepted gland standard for MS28775, O-ring packing seals. Piston rod diameters, gland internal diameters, groove sidewall angles and the surface finish are all defined by AS4716, but the gland outer retaining wall diameter is changed. The traditional scraper design installed into the glands detailed in Table 1 typically utilize components made from urethane or nitrile materials. These scraper designs, while still acceptable, must be reviewed in consideration to deicing, cleaners and disinfectant fluids applied to or in contact with the landing gear, as the materials of construction for the installed scrapers may not be compatible to these fluids. Exposure of the scraper to incompatible
A-5B Gears, Struts and Couplings Committee
Technical Standard
Description of High Lift Control SystemsAIR6016 (Current)12/10/2020
This SAE Information Report (AIR) provides descriptions of High Lift Systems of commercial and military aircraft. The main focus is on mechanical systems which may be actuated hydraulically or electrically.
A-6B3 Electro-Mechanical Actuation Committee
Information Report
Description of High Lift Control SystemsAIR6016-TEST-REC (Historical)12/10/2020
This SAE Information Report (AIR) provides descriptions of High Lift Systems of commercial and military aircraft. The main focus is on mechanical systems which may be actuated hydraulically or electrically.
A-6B3 Electro-Mechanical Actuation Committee
Information Report
Aerospace Rod Scraper Gland Design StandardAS4088F-TEST-REC (Historical)11/03/2020
This SAE Aerospace Standard (AS) defines gland details for scrapers for rod diameters from 1/4 to 15-1/2 inch (6.35 to 393.70 mm) inclusive, corresponding to AS568 O-ring Dash No. sizes -108/-111, -206/-222, -325/-349, and -425/-460. The gland details herein allow the use of more stable, efficient, and reliable scraper devices than MS33675 glands.
A-6C2 Seals Committee
Technical Standard
Aerospace Rod Scraper Gland Design StandardAS4088F (Current)11/03/2020
This SAE Aerospace Standard (AS) defines gland details for scrapers for rod diameters from 1/4 to 15-1/2 inch (6.35 to 393.70 mm) inclusive, corresponding to AS568 O-ring Dash No. sizes -108/-111, -206/-222, -325/-349, and -425/-460. The gland details herein allow the use of more stable, efficient, and reliable scraper devices than MS33675 glands.
A-6C2 Seals Committee
Technical Standard
Tire Overspeed Landing TestARP5257B (Current)09/18/2020
This document covers the basis of, and test procedure for, an overspeed landing test on aircraft tires with rated speeds of 190 mph (306 km/h) and above. The conditions requiring an overspeed test, alternatives, test requirements and pass/fail criteria are addressed.
A-5C Aircraft Tires Committee
Recommended Practice
Tire Pressure Monitoring Systems (TPMS) for AircraftARP6137 (Current)09/18/2020
A tire pressure monitoring system (TPMS) is a means to electronically measure and report the current tire pressure. Some systems are capable of transmitting the information to the flight deck while other systems are for use on the ground by maintenance personnel (only). This SAE Aerospace Recommended Practice (ARP) document is intended to establish overall component and system function guidelines and minimum performance levels for a TPMS. The system should visually indicate the tire inflation pressure status. These guidelines include, but are not limited to: a) Design recommendations for system components, which: 1 monitor tire inflation, and, 2 are located in/on the tire/wheel assembly, landing gear axle, and/or aircraft avionics compartment. b) Recommended performance and safety guidelines for a TPMS.
A-5C Aircraft Tires Committee
Recommended Practice
Recommended Wheel Tie Bolt Preload ProcedureARP5481A (Current)09/17/2020
This SAE Aerospace Recommended Practice (ARP) provides the recommended procedure for obtaining desired preloads in aircraft wheel tie bolts when mounting tires and assembling the wheel. It is generally referred to as the snug-angle bolted joint assembly procedure. It is also known as the “torque-turn” procedure in the heavy equipment ground vehicle industry.
A-5A Wheels, Brakes and Skid Controls Committee
Recommended Practice
Development and Qualification of Composite Landing GearsAIR5552 (Current)09/17/2020
This information report provides general guidance for the design considerations, qualification in endurance, strength and fatigue of landing gear using composite components as principle structural elements. The information discussed herein includes the development and evaluation of design data considering: the potential for imbedded manufacturing defects, manufacturing process variations, the component operating environment, potential damage threats in service, rework and overhaul, and inspection processes. This AIR mainly discusses the use of thick composites for landing gear structural components. Considerations and recommendations provided in this AIR may therefore differ greatly from considerations and recommendations found in widely accepted composite design references such as CMH-17 and Advisory Circulars such as AC 20-107(B).
A-5B Gears, Struts and Couplings Committee
Information Report
Rear Fuselage PackerTBMG-3759909/01/2020
Kaman UK Darwen, UK +44 1254 706000
Magazine Article
Landing Gear Shock Absorption Testing of Civil AircraftARP5644A (Current)07/14/2020
The intent of this document is to provide recommended practices for conducting shock absorption testing of civil aircraft landing gear equipped with oleo-pneumatic shock absorbers. The primary focus is for Part 25 aircraft, but differences for Part 23, 27, and 29 aircraft are provided where appropriate.
A-5B Gears, Struts and Couplings Committee
Recommended Practice
Advanced Assembly Solutions for the Airbus RACER Joined-Wing Configuration20AERP06_0306/01/2020
Compound helicopters, featuring lateral rotors as well as a primary rotor, are increasingly seen as the future of rotorcraft design. Capable of supporting a range of service applications, compound rotorcraft have the potential to deliver increased efficiencies and higher speeds relative to traditional rotorcraft. The Rapid And Cost Effective Rotorcraft (RACER) demonstrator is being developed by Airbus Helicopters (AH) to further validate the compound rotorcraft configuration. AH have chosen to employ a joined-wing design, which increases the stiffness relative to a traditional wing design. The RACER de sign also includes two lateral rotors, mounted aft of the Nacelles at the outboard extent of the wings, as depicted in Figure 1. Two assembly methodologies were considered for the RACER wing structures - determinate assembly or traditional assembly set by jigs. Determinate assembly, also known as ‘part-to-part’ or ‘jig-less’ assembly relies on the precision manufacturing of a few
Magazine Article
Advanced Assembly Solutions for the Airbus RACER Joined-Wing ConfigurationTBMG-3710506/01/2020
Compound helicopters, featuring lateral rotors as well as a primary rotor, are increasingly seen as the future of rotorcraft design. Capable of supporting a range of service applications, compound rotorcraft have the potential to deliver increased efficiencies and higher speeds relative to traditional rotorcraft. The Rapid And Cost Effective Rotorcraft (RACER) demonstrator is being developed by Airbus Helicopters (AH) to further validate the compound rotorcraft configuration. AH have chosen to employ a joined-wing design, which increases the stiffness relative to a traditional wing design. The RACER design also includes two lateral rotors, mounted aft of the Nacelles at the outboard extent of the wings, as depicted in Figure 1.
Magazine Article
Landing Gear Fatigue Spectrum Development For Part 25 AircraftAIR5914 (Current)02/28/2020
This SAE Aerospace Information Report (AIR) provides guidelines for the development of landing gear fatigue spectra for the purpose of designing and certification testing of Part 25 landing gear. Many of the recommendations herein are generalizations based on data obtained from a wide range of landing gears. The aircraft manufacturer or the landing gear supplier is encouraged to use data more specific to their particular undercarriage whenever possible.
A-5B Gears, Struts and Couplings Committee
Information Report
Conceptual Design, Material, and Structural Optimization of a Naval Fighter Nose Landing Gear for the Estimated Static Loads01-12-02-000912/13/2019
The Naval Nose Landing Gear (NLG) structural assembly consists of components with complex structural geometry and critical functionalities. The landing gear components are subjected to high static and dynamic loads, so they must be appropriately designed, dimensioned, and made by materials with mechanical characteristics that meet high strength, stiffness, and less weight requirements. This article contributes to the shape, size, and material optimization for the NLG of a supersonic naval aircraft for the estimated static loads. The estimated modal frequency values of the NLG assembly using Finite Element Analysis (FEA) software were compared with available Ground Vibration Test data of an aircraft to literally prove the accuracy and suitability of finite element (FE) model that can be used for any further analysis. Static structural analysis was performed for the critical landing load cases, and the Reserve Factor (RF) values of the landing gear components were calculated to determine
Journal Article
Changing How the Aerospace Industry Makes PartsTBMG-3568412/01/2019
Technology that increases production rates and part quality, while reducing setup times and costs, is seeing a surge in demand within the aerospace sector as the commercial aircraft backlog continues to grow.
Magazine Article
Valve, Inflation, Aircraft WheelAS6817 (Current)11/14/2019
This SAE Aerospace Standard (AS) defines the configuration of aircraft wheel inflation valve assemblies, including required tolerances, materials, and appropriate finishes.
A-5A Wheels, Brakes and Skid Controls Committee
Technical Standard
The Challenge of Replacing Hard ChromeTBMG-3535910/01/2019
The search for a suitable replacement for hard chrome on aerospace components has been a key supply chain priority for aircraft manufacturers. This is because of the documented health risks to workers and the impact on the environment from exposure to hexavalent chromium, a carcinogen that occurs during the chrome plating process and is the most toxic form of chromium.
Magazine Article
The Challenge of Replacing Hard Chrome19AERP10_0310/01/2019
The search for a suitable replacement for hard chrome on aerospace components has been a key supply chain priority for aircraft manufacturers. This is because of the documented health risks to workers and the impact on the environment from exposure to hexavalent chromium, a carcinogen that occurs during the chrome plating process and is the most toxic form of chromium. As a result, chromium is a highly regulated chemical in major markets worldwide. In the European Union, hexavalent chromium falls under the domain of the EU regulation, REACH (Registration, Evaluation, Authorization and Restriction of Chemicals), which establishes guidelines for the safe use of chemicals throughout the supply chain. Chromium is also closely regulated in the United States by OSHA.
Magazine Article
Advanced Assembly Solutions for the Airbus RACER Joined-Wing Configuration2019-01-188409/16/2019
The Rapid And Cost Effective Rotorcraft (RACER) is being developed by Airbus Helicopters (AH) to demonstrate a new Vertical Take-Off and Landing configuration to fill the mobility gap between conventional helicopters and aeroplanes. RACER is a compound rotorcraft featuring wings and multiple rotors. The wing arrangement suggested by AH is defined as a staggered bi-plane joined configuration with an upper and a lower straight wing, either side of the fuselage, connected at their outboard extent to form a triangular structure. The ASTRAL consortium, consisting of the University of Nottingham and GE Aviation Systems, are responsible for the design, manufacture, assembly and testing of the wings. Producing an optimised strategy to assemble a joined-wing configuration for a passenger carrying rotorcraft is challenging and novel. The objective of this work concerns all aspects of assembling the joined-wing structure. The joined-wing and fuselage structures will be produced independently and
Bainbridge, David, Bacharoudis, Konstantinos, Cini, Andrea, Turner, Alison, Popov, Atanas, Ratchev, Svetan
Technical Paper
Landing Gear Integration into Aircraft Structure in Early Design Stage2019-01-189009/16/2019
The demanded development towards various emission reduction goals set up by several institutions forces the aerospace industry to think about new technologies and alternative aircraft configurations. With these alternative aircraft concepts, the landing gear layout is also affected. Turbofan engines with very high bypass ratios could increase the diameter of the nacelles extensively. In this case, mounting the engines above the wing could be a possible arrangement to avoid an exceedingly long landing gear. Thus, the landing gear could be shortened and eventually mounted at the fuselage instead of the wings. Other technologies such as high aspect ratio wings have an influence on the landing gear integration as well. To assess the difference, especially in weight, between the conventional landing gear configuration and alternative layouts a method is developed based on preliminary structural designs of the different aircraft components, namely landing gear, wing and fuselage. Simplified
Kling, Ulrich, Hornung, Mirko
Technical Paper
Origami-Inspired Material Softens Impact ForcesTBMG-3512709/01/2019
Landing is stressful on a rocket’s legs because they must handle the force from the impact with the landing pad. One way to combat this is to build legs out of materials that absorb some of the force and soften the blow. Inspired by the paper-folding art of origami, researchers created a paper model of a metamaterial that uses “folding creases” to soften impact forces and instead promote forces that relax stresses in the chain.
Magazine Article
429P2-17 Digital Information Transfer System (DITS), Part 2, Discrete Word Data StandardsARINC429P2-17 (Current)08/01/2019
This standard defines the air transport industry's standards for the transfer of digital data between avionics system elements. Part 2 provides the formats of data words with discrete bit encoding.
Airlines Electronic Engineering Committee
Specification
New and Newly Retreaded Tire AppearanceARP6307A (Current)07/02/2019
This document is for establishing and addressing anomalies on appearance of new and newly retreaded tires prior to installation on aircraft. It is intended to use cosmetics as well as functionality to make a determination of acceptability. However, if cosmetic appearance is not a requirement, use the inspection criteria from ARP6225. This ARP does not supersede (E)TSO-C62 minimum requirements, including marking requirements.
A-5C Aircraft Tires Committee
Recommended Practice
Advanced Over-the-Wing Nacelle Transport ConfigurationTBMG-3476007/01/2019
NASA’s Langley Research Center has developed a new aircraft design with the engine nacelle over the wing, improving engine ground clearance and freeing landing gear design. While previous over-the-wing designs have produced unacceptably high drag conditions, the new NASA design reduces drag on the wing. By optimizing the nacelle design and the wing leading edge location, NASA’s design confines the shock to the leading edge of the wing. Also, placing the exhaust nozzle over the wing reduces noise to the communities below.
Magazine Article
Landing Gear Shock Absorption Testing of Civil AircraftARP5644 (Historical)04/17/2019
The intent of this document is to provide recommended practices for conducting shock absorption testing of civil aircraft landing gear equipped with oleo-pneumatic shock absorbers. The primary focus is for Part 25 aircraft, but differences for Part 23, 27, and 29 aircraft are provided where appropriate.
A-5B Gears, Struts and Couplings Committee
Recommended Practice
Landing Response Analysis on High-Performance Aircraft * Using Estimated Touchdown States01-12-01-000104/08/2019
A novel use of state estimation methods as initial input for a landing response analysis is proposed in this work. Six degrees of freedom (DOF) non-linear landing response model is conceived by considering longitudinal dynamics of aircraft as a rigid body with heave-and-pitch motions coupled onto a bicycle landing gear† arrangement. The DOF for each landing gear consist of vertical and longitudinal motions of un-sprung mass, considering strut bending flexibility. The measurement data for state estimation is obtained for three landing cases using non-linear flight mechanics model interfaced with pilot-in-loop simulation. State estimation methods such as Upper Diagonal Adaptive Extended Kalman Filter (UD-AEKF) with fuzzy-based adaptive tuning and Un-scented Kalman Filter (UKF) were adapted for landing maneuver problem. On the basis of estimation error metrics, aircraft state from UKF is considered during onset of touchdown. These estimated states are used as an initial condition for the
Suresh, P.S., Sura, Niranjan Kumar, Shankar, K.
Journal Article
The Application of Additive Manufacturing to the 2018 SAE Aero Design Challenge2019-01-132803/19/2019
This project focuses on the application of polymer additive manufacturing to the 2018 SAE Aero Design Regular Class competition for North Carolina A&T State’s 2017/2018 senior project team. The Regular Class SAE Aero Design challenge requires participating teams to create a high lift, high efficiency remote controlled aircraft that is designed to carry as many passengers and additional cargo mass as possible while still being able to meet land and air performance requirements defined by the competition rules. Constraints set by the competition rules include material constraints, a max gross weight of 55 lb, a limited power supply of 1000 W, a 12-ft wingspan limitation, enclosed cargo and passenger bays, the ability to unload and load all cargo and return the plane to a flight ready configuration within 1 minute, and a takeoff distance of 200 ft. The wide use of additive manufacturing and hot wire foam cutting for this aircraft design has allowed for accurate and efficient component
Blake, Nathan David, Waters, Cynthia, Esau, Simon, Kizito, John
Technical Paper
Design of a Wing for Formula One Category Airplanes2019-01-133703/19/2019
This paper describes the design of an International Formula One (IF1) racing airplane wing. The first step consists in the simulation of the airplane flying on the race track to obtain details about the condition in which the wing needs to be designed and optimized. The paper describes the details and formulation used to perform this simulation using parametric flight paths and a point model dynamic model. A scheme analytically obtains the control laws for the simulation with Frenet-Serret frames over the parametric flight path. Two different airplanes, with different power levels, are simulated on a typical IF1 race track to determine the range of lift coefficient in which the wing must be designed. Based on this lift coefficient range, a set of four new airfoils are designed based on the NLF0414-F airfoil. Their usage over the wing span is determined, using nonlinear lifting line method to assure that during races the wing operates inside the laminar drag bucket. Finally, this paper
Andrade de Oliveira, Paulo Henriques Iscold
Technical Paper
Aircraft Tire Inspection - In-Service Removal CriteriaARP6225A (Historical)02/13/2019
This document is for establishing tire removal criteria of on-wing civil aircraft tires only. This document is primarily intended for use with commercial aircraft, but may be used on other categories of civil aircraft, as applicable. The criteria are harmonized with the Care and Service Manuals of the tire manufacturers for both radial and bias tires.
A-5C Aircraft Tires Committee
Recommended Practice
Multirole Utility HelicoptersTBMG-3377502/01/2019
Airbus Helicopters Marignane Cedex, France +33 (0)4 42 85 60 51
Magazine Article
Grease: Wide Temperature Range Lithium or Lithium Complex Thickened for Aircraft Wheel BearingsAMS3058A (Current)08/09/2018
This specification covers grease for use on aircraft wheel bearings. It also defines the quality control requirements to assure batch conformance and materials traceability, and the procedures to manage and communicate changes in the grease formulation and brand. This specification invokes the Performance Review Institute (PRI) product qualification process. Requests for submittal information may be made to the PRI at the address in 2.2, referencing this specification. Products qualified to this specification are listed on a Qualified Products List (QPL) managed by the PRI. Additional tests and evaluations may be required by individual equipment builders before a grease is approved for use in their equipment. Approval and/or certification for use of a specific grease in aero and aero-derived marine and industrial applications is the responsibility of the individual equipment builder and/or governmental authorities and is not implied by compliance with or qualification to this
AMS M Aerospace Greases Committee
Material Specification
External Hydraulic Fluid Leakage Definition for Landing Gear Shock AbsorbersARP6408 (Current)07/25/2018
The purpose of this SAE Aerospace Recommended Practice (ARP) is to provide a practical definition of external hydraulic fluid leakage exhibited by landing gear shock absorbers/struts. The definition will outline normal (acceptable weepage) and excessive leakage (unacceptable leakage) of shock absorbers/struts that is measurable. The definition of leakage is applicable to new gear assemblies, refurbished/remanufactured (overhauled) shock absorbers/struts, leakage of shock absorbers/struts encountered during acceptance flights, newly delivered and in-service aircraft. This ARP is intended to provide guidelines for acceptable leakage of landing gear shock absorbers/struts between the ambient temperatures of -65 °F (-54 °C) and 130 °F (54 °C) and to outline the procedure for measuring such leakage. The specific limits that are applied to any particular aircraft shall be adjusted by the aircraft manufacturer before inclusion in the applicable maintenance manual.
A-5B Gears, Struts and Couplings Committee
Recommended Practice
Landing Gear Component Heat DamageAIR5913A (Current)07/02/2018
The purpose of this report is to outline types of in-service heat damage that have been observed in high strength steel landing gear components, with an emphasis on a particular type that is referred to as “Ladder Cracking” which can develop in landing gear shock struts. The report discusses how ladder cracking can be detected visually and evaluated by non-destructive inspection methods, and how it can be repaired at overhaul with the prior approval of the Original Equipment Manufacturer. This report also describes the use of a bearing material that has resolved this problem without introducing other problems. Examples of other types of service induced heat damage are also discussed.
A-5B Gears, Struts and Couplings Committee
Information Report
Exits and Their Operation - Air Transport Cabin EmergencyARP488F (Current)03/14/2018
This SAE Aerospace Recommended Practice (ARP) provides design and performance recommendations for emergency exits in the passenger cabin.
S-9B Cabin Interiors and Furnishings Committee
Recommended Practice
Stretchable Mesh for Cavity Noise ReductionTBMG-2856503/01/2018
NASA’s Langley Research Center has developed a landing gear cavity modification that reduces noise produced during aircraft approach and landing. The modification is an innovative stretchable mesh assembly that deploys and retracts with the landing gear to reduce high-intensity low- to mid-frequency airframe noise. The envisioned low-profile mesh concept enables mitigation of cavity noise without sealing of the cavity or incurring appreciable penalties of increased weight, and conforms easily and smoothly to the interior edges of an aircraft wheel well. The concept is potentially suitable for retrofit of current aircraft and for inclusion into future civil transport fleets, and causes no adverse effects to the aerodynamic characteristics of the aircraft. The technology has been validated in wind tunnel testing. NASA is seeking partners who are interested in co-development or licensure of the technology for a variety of applications.
Magazine Article
Aerospace Rod Scraper Gland Design StandardAS4088E (Historical)02/06/2018
This SAE Aerospace Standard (AS) defines gland details for scrapers for rod diameters from 1/4 to 15-1/2 inch (6.35 to 393.70 mm) inclusive, corresponding to AS568 O-ring Dash No. sizes -108/-111, -206/-222, -325/-349, and -425/-460. The gland details herein allow the use of more stable, efficient and reliable scraper devices than MS33675 glands. NOTE: Scraper configurations are not specified in this document.
A-6C2 Seals Committee
Technical Standard
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