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landing gear
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Published: 01 December 2004
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Published: 01 December 2004
Fig. 3.15 One-piece alloy D357.0 main landing gear door uplock support for the 767 airplane. The casting replaced a sheet metal assembly; the conversion eliminated 27 separate parts and reduced assembly time by 65%. Source: Ref 5
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Published: 01 January 2015
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Published: 01 December 2000
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Published: 01 October 2011
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in Overview of the Mechanisms of Failure in Heat Treated Steel Components
> Failure Analysis of Heat Treated Steel Components
Published: 01 September 2008
Fig. 52 Schematic of the assembly of a Boeing 757 main landing gear showing the location of fracture
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in Overview of the Mechanisms of Failure in Heat Treated Steel Components
> Failure Analysis of Heat Treated Steel Components
Published: 01 September 2008
Fig. 53 Fracture surface of Boeing 757 main landing gear truck beam on Icelandic Air aircraft TF-FIJ
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in Case Studies of Steel Component Failures in Aerospace Applications
> Failure Analysis of Heat Treated Steel Components
Published: 01 September 2008
Fig. 9 Macrograph documenting the appearance of the as-received main landing gear lever attach pin
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in Case Studies of Steel Component Failures in Aerospace Applications
> Failure Analysis of Heat Treated Steel Components
Published: 01 September 2008
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in Case Studies of Steel Component Failures in Aerospace Applications
> Failure Analysis of Heat Treated Steel Components
Published: 01 September 2008
Fig. 17 Appearance of longitudinal crack in the main landing gear linear actuating piston rod cylinder
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in Case Studies of Steel Component Failures in Aerospace Applications
> Failure Analysis of Heat Treated Steel Components
Published: 01 September 2008
Fig. 24 Appearance of the main landing gear lever showing the location of the primary and secondary cracks. (a) Overall view (33 mm). (b) Location of primary and secondary cracks at site of ion vapor deposit (IVD) removal (10 mm)
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in Case Studies of Steel Component Failures in Aerospace Applications
> Failure Analysis of Heat Treated Steel Components
Published: 01 September 2008
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in Cold Spray Applications in the Defense Industry
> High Pressure Cold Spray: Principles and Applications
Published: 01 June 2016
Fig. 9.18 B-1 nose landing gear false axle showing the wear damage that occurs during operation. Courtesy of South Dakota School of Mines and Technology
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in Cold Spray Applications in the Defense Industry
> High Pressure Cold Spray: Principles and Applications
Published: 01 June 2016
Fig. 9.25 Example of hydraulic tube chafing from the landing gear line on the U.S. Air Force B-1B. Courtesy of South Dakota School of Mines and Technology
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Published: 01 November 2012
Fig. 45 17-4 PH stainless steel main landing gear deflection yoke that failed because of intergranular stress-corrosion cracking. (a) Macrograph of fracture surface. (b) Higher-magnification view of the boxed area in (a) showing area of intergranular attack. Courtesy of W.L. Jensen, Lockheed
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Series: ASM Technical Books
Publisher: ASM International
Published: 01 September 2008
DOI: 10.31399/asm.tb.fahtsc.t51130351
EISBN: 978-1-62708-284-6
... Abstract This chapter presents various case histories that illustrate a variety of failure mechanisms experienced by the high-strength steel components in aerospace applications. The components covered are catapult holdback bar, AISI 420 stainless steel roll pin, main landing gear (MLG) lever...
Abstract
This chapter presents various case histories that illustrate a variety of failure mechanisms experienced by the high-strength steel components in aerospace applications. The components covered are catapult holdback bar, AISI 420 stainless steel roll pin, main landing gear (MLG) lever, inboard flap hinge bolt, nose landing gear piston axle, multiple-leg aircraft-handling sling, aircraft hoist sling, internal spur gear, and MLG axle. In addition, the chapter provides information on full-scale fatigue testing, nondestructive testing, and failure analysis of fin attach bolts.
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270180
EISBN: 978-1-62708-301-0
... Abstract The nose landing gear on an aircraft malfunctioned during landing roll. After the incident, two fractured studs were found in the retraction jack support beam. Based on visual examination and the results of SEM fractography, investigators concluded that the studs failed by fatigue...
Abstract
The nose landing gear on an aircraft malfunctioned during landing roll. After the incident, two fractured studs were found in the retraction jack support beam. Based on visual examination and the results of SEM fractography, investigators concluded that the studs failed by fatigue, a vulnerability because of the way they were mounted. A sketch showing the correct mounting configuration is included in the report.
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in Case Studies of Steel Component Failures in Aerospace Applications
> Failure Analysis of Heat Treated Steel Components
Published: 01 September 2008
Fig. 10 Magnetic particle inspection indications on the flange of the main landing gear lever attach pin
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in Case Studies of Steel Component Failures in Aerospace Applications
> Failure Analysis of Heat Treated Steel Components
Published: 01 September 2008
Fig. 14 Metallographic examination of cracks evident in the flange of the main landing gear lever attach pin, showing loss of chromium at cracks (20 μm)
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Published: 01 May 2018
FIG. 9.10 The Boeing 777 is the first commercial plane to use a titanium alloy (Ti-10V-2Fe-3Al) for landing gear. Source: Wikimedia Commons/Altair78.
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