Search Results

Standard

Arresting Hook Installation, Land Based Aircraft, Emergency

2007-08-09

HISTORICAL

ARP1538A

This document covers the recommended criteria and performance requirements for the design and installation of an aircraft emergency arresting hook intended for use with emergency runway arresting systems. Design criteria for fully operational hooks and for carrier based aircraft hook installations are contained in specification MIL-A-18717.

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ARRESTING HOOK INSTALLATION, LAND BASED AIRCRAFT, EMERGENCY

1978-04-01

HISTORICAL

ARP1538

This document covers the recommended criteria and performance requirements for the design and installation of an aircraft emergency arresting hook intended for use with emergency runway arresting systems. Design criteria for fully operational hooks and for carrier based aircraft hook installations are contained in specification MIL-A-18717.

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Aircraft Nosewheel Steering Systems

2012-07-03

HISTORICAL

ARP1595A

This document provides recommended practices for the design, development, and verification testing of aircraft nosewheel steering (NWS) systems.

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AIRCRAFT NOSEWHEEL STEERING SYSTEMS

1982-03-31

HISTORICAL

ARP1595

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Design and Verification of Aircraft Nose Wheel Steering Systems

2023-11-16

CURRENT

ARP1595B

This document provides recommended practices for the design, development, and verification testing of NWS systems.

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Landing Gear Shock Strut Heat Damage

2016-11-11

HISTORICAL

AIR5913

Standard

Aircraft Nosewheel Steering/Centering Systems

2019-04-17

CURRENT

AIR1752A

The intent of this AIR is twofold: (1) to present descriptive summary of aircraft nosewheel steering and centering systems, and (2) to provide a discussion of problems encountered and “lessons learned” by various airplane manufacturers and users. This document covers both military aircraft (land-based and ship-based) and commercial aircraft. It is intended that the document be continually updated as new aircraft and/or new “lessons learned” become available.

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AIRCRAFT NOSE WHEEL STEERING/CENTERING SYSTEMS

2011-08-10

HISTORICAL

AIR1752

This document covers both military aircraft (land-based and ship-based) and commercial aircraft. It is intended that the document be continually updated as new aircraft and/or new "lessons learned" become available.

Standard

Landing Gear Structural Requirements as Listed in the MIL-886X Series of Specifications

2012-10-03

HISTORICAL

AS8860A

This specification contains landing gear strength and rigidity requirements, which, in combination with other applicable specifications, define the structural design, analysis, test, and data requirements for fixed wing piloted airplanes. These requirements include, but are not limited to the following: a General Specifications 1 The shock-absorption characteristics and strength of landing-gear units and the strength and rigidity of their control systems and of their carry-through structures.

Standard

Landing Gear Structural Requirements as Listed in the MIL-886X Series of Specifications

2012-05-03

HISTORICAL

AS8860

This specification contains landing gear strength and rigidity requirements, which, in combination with other applicable specifications, define the structural design, analysis, test, and data requirements for fixed wing piloted airplanes. These requirements include, but are not limited to the following: a General Specifications 1 The shock-absorption characteristics and strength of landing-gear units and the strength and rigidity of their control systems and of their carry-through structures.

Standard

DESIGN, DEVELOPMENT AND TEST CRITERIA - SOLID STATE PROXIMITY SWITCHES/SYSTEMS FOR LANDING GEAR APPLICATIONS

1983-09-01

HISTORICAL

AIR1810

This document will examine the more important considerations relative to the utilization of "one piece", or integral electronics proximity switches, and "two piece", or separate sensor and electronics proximity switches, for applications on aircraft landing gear.

Standard

Design, Development and Test Criteria - Solid State Proximity Switches/Systems for Landing Gear Applications

2001-10-01

HISTORICAL

AIR1810B

This document will examine the more important considerations relative to the utilization of "one piece", or integral electronics proximity switches, and "two piece", or separate sensor and electronics proximity switches, for applications on aircraft landing gear. In general, the recommendations included are applicable for other demanding aircraft sensor installations where the environment is equally severe.

Standard

DESIGN, DEVELOPMENT AND TEST CRITERIA - SOLID STATE PROXIMITY SWITCHES/SYSTEMS FOR LANDING GEAR APPLICATIONS

1991-06-01

HISTORICAL

AIR1810A

This document will examine the more important considerations relative to the utilization of "one piece", or integral electronics proximity switches, and "two piece", or separate sensor and electronics proximity switches, for applications on aircraft landing gear. In general, the recommendations included are applicable for other demanding aircraft sensor installations where the environment is equally severe.

Standard

Development and Qualification of Composite Landing Gears

2020-09-17

CURRENT

AIR5552

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).

Standard

Gland Design: Nominal 3/8 Inch Cross Section for Compression-Type Seals

2023-06-12

CURRENT

AS4832B

This SAE Aerospace Standard (AS) offers gland details for a 0.364 inch (9.246 mm) cross-section gland (nominal 3/8 inch) with proposed gland lengths for compression-type seals with two backup rings over a range of 7 to 21 inches (178 to 533 mm) in diameter. The dash number system used is similar to AS568A. A 600 series has been chosen as a logical extension of AS568A, and the 625 number has been selected for the initial number, since 300 and 400 series in MIL-G-5514 and AS4716 begin with 325 and 425 sizes. Seal configurations and design are not a part of this document. This gland is for use with compression-type seals including, but not limited to, O-rings, T-rings, D-rings, cap seals, etc.

Standard

Gland Design: Nominal 3/8 Inch Cross Section for Compression-Type Seals

2019-06-17

HISTORICAL

AS4832A

This SAE Aerospace Standard (AS) offers gland details for a 0.364 inch (9.246 mm) cross-section gland (nominal 3/8 inch) with proposed gland lengths for compression-type seals with two backup rings over a range of 7 to 21 inches (178 to 533 mm) in diameter. The dash number system used is similar to AS568A. A 600 series has been chosen as a logical extension of AS568A, and the 625 number has been selected for the initial number, since 300 and 400 series in MIL-G-5514 and AS4716 begin with 325 and 425 sizes. Seal configurations and design are not a part of this document. This gland is for use with compression-type seals including, but not limited to, O-rings, T-rings, D-rings, cap seals, etc.

Standard

AIRCRAFT LANDING GEAR

1995-01-01

HISTORICAL

ARP1311A

This SAE Aerospace Recommended Practice (ARP) applies to landing gear structures and mechanisms (excluding wheels, tires, and brakes) for all types and models of civil and military aircraft applications. All axles, wheel forks, axle beams, links, arms, mechanical and air-oil energy absorbers braces, lock assemblies, trunnion beams, etc., that sustain loads originating at the ground, and that are not integral parts of the airframe structure should be designed in accordance with this document. Hydraulic actuators (retraction, steering, positioning, and/or damping) should also be included in this coverage. It should be the responsibility of the airframe manufacturer to determine the compatibility of these needs with the aircraft and to specify requirements in excess of these minima where appropriate.

Standard

LANDING GEAR - AIRCRAFT

2011-08-10

HISTORICAL

ARP1311

This ARP applies to all types and models of civil aircraft for landing gear structure and mechanism excepting wheels, tires and brakes. All axles, wheel forks, axle beams, links, arms, mechanical and air-oil energy absorbers, braces, lock assemblies, trunnion beams, etc., that sustain loads originating at the ground and that are not integral parts of the airframe structure shall be in accordance with this practice.

Standard

Landing Gear Structures and Mechanisms

2015-04-27

HISTORICAL

ARP1311C

This SAE Aerospace Recommended Practice (ARP) applies to landing gear structures and mechanisms (excluding wheels, tires, and brakes and other landing gear systems) for all types and models of civil and military aircraft. All axles, wheel forks, links, arms, mechanical and gas/oil shock struts, downlock and uplock assemblies, braces, trunnion beams, and truck beams etc., that sustain loads originating at the ground, and that are not integral parts of the airframe structure, should be designed and validated in accordance with this document. Hydraulic actuators (retraction, main and nose gear steering, positioning, damping, etc.) should also be included in this coverage. System level, non-structural components such as retraction/extension valves, controllers, secondary structure and mechanisms in the airframe (e.g., manual release mechanisms, slaved doors) as well as equipment that is located in the cockpit are not addressed in this ARP.

Standard

Aircraft Landing Gear

2004-06-24

HISTORICAL

ARP1311B

This SAE Aerospace Recommended Practice (ARP) applies to landing gear structures and mechanisms (excluding wheels, tires, and brakes) for all types and models of civil and military aircraft including all aircraft with vertical landing and crash attenuation requirements. All axles, wheel forks, axle beams, links, arms, mechanical and nitrogen/oil energy absorbers, lock assemblies, braces, trunnion beams, and truck beams etc., that sustain loads originating at the ground, and that are not integral parts of the airframe structure, should be designed in accordance with this document. Hydraulic actuators (retraction, main and nose gear steering, positioning, and/or damping) should also be included in this coverage.