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Landing gear

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Series: ASM Failure Analysis Case Histories
Volume: 1
Publisher: ASM International
Published: 01 December 1992
DOI: 10.31399/asm.fach.v01.c9001020
EISBN: 978-1-62708-214-3
... upper attachment lug. Unetched. 17.2×. Fig. 9 Cracking associated with fracture of left upper attachment lug. Etched in 5% Keller's reagent. 237×. Fig. 1 General configuration of main landing gear undercarriage. Fig. 2 Main landing gear components. Fig. 3 Strut...
Series: ASM Failure Analysis Case Histories
Volume: 1
Publisher: ASM International
Published: 01 December 1992
DOI: 10.31399/asm.fach.v01.c9001025
EISBN: 978-1-62708-214-3
... Fig. 1 Schematic of the C130 aircraft main landing gear wheel, showing the bolted assembly the brake housing, and the flange in which fracture occurred. Fig. 2 Schematic of the redesigned C130 aircraft main landing gear wheel, showing the double flange used to strengthen the wheel...
Series: ASM Failure Analysis Case Histories
Volume: 2
Publisher: ASM International
Published: 01 December 1993
DOI: 10.31399/asm.fach.v02.c9001291
EISBN: 978-1-62708-215-0
... Fig. 1 Main landing gear sliding strut provided for destructive examination. Arrow indicates region that was hard chromium plated. Wheel axle is at lower end. Fig. 2 Indications of cracking in the hard chromium plating (arrow) at the axle (lower) end. Note the banded appearance...
Series: ASM Failure Analysis Case Histories
Volume: 2
Publisher: ASM International
Published: 01 December 1993
DOI: 10.31399/asm.fach.v02.c9001292
EISBN: 978-1-62708-215-0
... Fig. 1 As-received nose landing gear shock strut. Arrow indicates the crack in one of the support arms ∼125× Fig. 2 Fracture surface of the failed support arm. Cracking initiated in the highly textured area (T). Flat area (F) is fatigue cracking with bands of tearing probably caused...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001706
EISBN: 978-1-62708-217-4
... Abstract The truck beam of the left main landing gear (MGL) of a Boeing 707 airplane collapsed on the ground just after the aircraft was unloaded and refueled. The investigation revealed that failure was caused by the propagation of an intergranular crack originating from the bottom of the pit...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c0048164
EISBN: 978-1-62708-217-4
... Abstract A flat spring for the main landing gear of a light aircraft failed after safe execution of a hard landing. The spring material was identified by chemical analysis to be 6150 steel. The fracture was found to have occurred near the end of the spring that was inserted through a support...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001538
EISBN: 978-1-62708-217-4
... Abstract Examination of a cracked nose landing gear cylinder made of AISI 4340 Cr-Mo-Ni alloy steel proved that the part started to fail on the inside diam. When the nucleus of the stress-corrosion crack was studied in detail, iron oxide was found on the fracture surface. A 6500x micrograph...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001540
EISBN: 978-1-62708-217-4
... Abstract Ground maintenance personnel discovered hydraulic fluid leaking from two small cracks in a main landing gear cylinder made from AISI 4340 Cr-Mo-Ni alloy steel. Failure of the part had initiated on the ID of the cylinder. Numerous cracks were found under the chromium plate. A 6500x...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001542
EISBN: 978-1-62708-217-4
... Abstract A nose landing gear cylinder made from AISI 4340 Ni-Cr-Mo alloy steel was found cracked and leaking, causing partial depressurization. Investigation revealed the crack to be a stress-corrosion type, judging by the 6500x electron fractograph. It had started in a region of concentrated...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c0046146
EISBN: 978-1-62708-217-4
... Abstract The torque-arm assembly (aluminum alloy 7075-T73) for an aircraft nose landing gear failed after 22,779 simulated flights. The part, made from an aluminum alloy 7075-T73 forging, had an expected life of 100,000 simulated flights. Initial study of the fracture surfaces indicated...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001018
EISBN: 978-1-62708-217-4
... Abstract Initial investigation showed that a landing gear failure was the result of a hard landing with no evidence of contributory factors. The objective of reexamination was to determine whether there was any evidence of metallurgical failure. The landing gear was primarily an AISI type 6150...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001555
EISBN: 978-1-62708-217-4
... breakage of the axle had occurred intergranularly in a brittle manner, possibly, initiated by a shallow zone of fatigue along the sharp radius acting as stress riser. Aircraft components Axles Landing gear Radii Fe-0.33C-1.50Ni-1.15Cr Fatigue fracture Brittle fracture Intergranular fracture...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001504
EISBN: 978-1-62708-217-4
... Abstract Despite extensive aircraft landing gear design analyses and tests performed by designers and manufacturers, and the large number of trouble-free landings, aircraft users have experienced problems with and failures of landing gear components. Different data banks and over 200 failure...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001902
EISBN: 978-1-62708-217-4
... Abstract In a spring leg of a main landing gear, large brittle fracture zones indicated a predominately cleavage pattern with some ductile dimples, and a tiny fatigue segment disclosed fine striations. Factors influencing failure were surface decarburization, notch sensitivity of the modified...
Image
Published: 01 June 2019
Fig. 1 Landing-gear spring, 6150 steel, that broke during a hard landing. (a) Configuration and dimensions (given in inches) of the spring. (b) Fractograph showing fatigue crack that initiated the brittle fracture. 7× More
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Published: 01 December 1992
Fig. 1 General configuration of main landing gear undercarriage. More
Image
Published: 01 December 1992
Fig. 2 Main landing gear components. More
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Published: 01 December 1992
Fig. 1 Schematic of the C130 aircraft main landing gear wheel, showing the bolted assembly the brake housing, and the flange in which fracture occurred. More
Image
Published: 01 December 1992
Fig. 2 Schematic of the redesigned C130 aircraft main landing gear wheel, showing the double flange used to strengthen the wheel. More
Image
Published: 01 December 1993
Fig. 1 Main landing gear sliding strut provided for destructive examination. Arrow indicates region that was hard chromium plated. Wheel axle is at lower end. More