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Standard

Gland Design: Nominal 3/8 in Cross Section for Custom Compression Type Seals

1994-06-01
CURRENT
AS4832
This SAE Aerospace Standard (AS) offers gland details for a 0.364 cross section gland (nominal 3/8 in) with proposed gland lengths for compression type seals with two backup rings over a range of 8 to 20 in in diameter. A dash number system is proposed similar to AS568A. A 600 series has been chosen as a logical extension of AS568A and the 625 number has been arbitrarily chosen for the initial number. (Both 300 and 400 series begin with 325 and 425 sizes.) Seal configurations and design are not a part of this document. This gland is for use with custom compression type seals including, but not limited to, O-rings, T-rings, D-rings, etc.
Standard

Gland Design: Nominal 3/8 in Cross Section for Custom Compression Type Seals

2018-06-13
WIP
AS4832A
This SAE Aerospace Standard (AS) offers gland details for a 0.364 cross section gland (nominal 3/8 in) with proposed gland lengths for compression type seals with two backup rings over a range of 8 to 20 in diameter. A dash number system is proposed similar to AS568A. A 600 series has been chosen as a logical extension of AS568A and the 625 number has been arbitrarily chosen for the initial number. (Both 300 and 400 series begin with 325 and 425 sizes.) Seal configurations and design are not a part of this document. This gland is for use with custom compression type seals including, but not limited to, O-rings, T-rings, D-rings, etc.
Standard

Gland Design: Scraper, Landing Gear, Installation

2008-11-24
CURRENT
AS4052B
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.
Standard

Gland Design: Scraper, Landing Gear, Installation

2001-04-01
HISTORICAL
AS4052A
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 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. AS4088 is similar to this document, but was developed by SAE A-6 for flight control and general-purpose cylinders. It differs from this document primarily by the clearance between the rod (piston) and outer gland wall. Since landing gears are more susceptible to dirt contamination, the additional clearance provides a larger path to allow excessive dirt accumulation to exit the gland.
Standard

External Hydraulic Fluid Leakage Definition for Landing Gear Shock Absorbers

2018-07-25
CURRENT
ARP6408
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.
Standard

Landing Gear Servicing

2018-07-03
CURRENT
ARP5908A
The present document addresses gas and hydraulic fluid servicing required on commercial and military aircraft landing gears, for both single and dual chamber (also known as dual stage and two stage) shock struts. This document should be considered as landing gear industry recommended practice but in no way is meant to supersede the shock strut OEM’s published procedures.
Standard

Landing Gear Servicing

2008-03-25
HISTORICAL
ARP5908
The present document addresses gas and hydraulic fluid servicing required on commercial and military aircraft landing gears, for both single and dual chamber shock struts.
Standard

Landing Gear Component Heat Damage

2018-07-02
CURRENT
AIR5913A
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.
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