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Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c0006402
EISBN: 978-1-62708-217-4
... Abstract New aircraft wing panels extruded from 7075-T6 aluminum exhibited an unusual pattern of circular black interrupted lines, which could not be removed by scouring or light sanding. The panels, subsequent to profiling and machining, were required to be penetrated inspected, shot peened...
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.process.c9001541
EISBN: 978-1-62708-235-8
... Abstract A forging of 7075-T6 aluminum alloy, which formed a support for the cylinder of a cargo door, cracked at an attachment hole. Fluorescent penetrant inspection showed the crack ran above and below the hole out onto the machined flat surface of the flange. A 6500x electron fractograph...
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Published: 01 June 2019
Fig. 1 Forged aluminum alloy 7075-T6 receiver from an M16 rifle that failed by exfoliation corrosion. (a) Rifle receiver. 0.7×. Similar receivers were forged from three different materials to investigate the effects of processing on exfoliation resistance ( Table 1 ). Section A-A: (b), (c More
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Published: 01 June 2019
Fig. 1 Opened crack (a) in aluminum alloy 7075-T651 ejection seat swivel fixture that failed by SCC. Note crack propagation markings that suggest the crack initiated on the inside wall of the fixture and woody appearance of the fracture. (b) Higher-magnification view of fracture surface from More
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Published: 01 June 2019
Fig. 1 Aluminum alloy 7075-T6 aircraft wing panel (a) showing unusual surface appearance. (b) SEM of the panel surface showing cracked anodized coating. 160x. (c) SEM showing the anodized coating flaking away and corrosion deposit under the coating. 85x. (d) Cross section of corrosion site More
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Published: 01 June 2019
Fig. 1 Cracked aluminum alloy 7075-T6 aircraft pylon strut (a) with arrows indicating cracks. (b) SEM of crack C from (a) showing the mud crack pattern indicative of a corrosion mechanism. 820x More
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Published: 01 June 2019
Fig. 1 Aluminum alloy 7075-T73 landing-gear torque-arm assembly that was redesigned to eliminate fatigue fracture at a lubrication hole. (a) Configuration and dimensions (given in inches). (b) Fracture surface showing fatigue beach marks. Approximately 2× More
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Published: 01 January 2002
Fig. 46 Crack propagation in shear bands in a 7075-T6 plate specimen. Shear banding has occurred on four planes of high shear stress (two containing the width direction and two containing the thickness direction). Crack initiation has occurred in multiple locations, including the edge More
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Published: 01 January 2002
Fig. 86 Fracture on essentially one plane of high shear stress in a 7075-T6 cylindrical tensile specimen. There is a small flat region in the center of the specimen (not visible in photograph) that does not extend to the surface of the specimen. No fracture surface markings exist to indicate More
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Published: 01 January 2002
Fig. 14 Beach marks on a fatigue fracture in aluminum alloy 7075-T73 forging. The light-colored reflective bands are zones of fatigue crack propagation. At high magnifications, thousands of fatigue striations can be resolved within each band. The dull, fibrous bands are zones of crack More
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Published: 01 January 2002
Fig. 20 Fatigue-fracture zones in aluminum alloy 7075-T6 plates. (a) Fatigue crack that grew as a flat-face fracture with a shallow convex crack front. (b) Change in orientation of fatigue fracture from plane strain (arrow A) to plane stress (arrow B). More
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Published: 01 January 2002
Fig. 7 Fractured lug of an alloy 7075-T6 forging. Arrows show sites at machined hole where stress-corrosion cracks originated because of stress acting across the short transverse grain direction. Keller's reagent. 2× More
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Published: 30 August 2021
Fig. 39 Fracture weld joint on alloy 7075 collar side of the swing arm structure More
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Published: 30 August 2021
Fig. 28 Effect of burning on ductility in a 7075 aluminum alloy. (a) Properly heated. (b) Embrittled due to liquid phases formed in grain boundary. Profile of fracture surface of tensile specimens pulled to failure More
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Published: 30 August 2021
Fig. 2 (a) Cracked HL 22-8 aluminum alloy 7075-T6 fasteners. (b) Typical cracked fastener head. (c) Typical head cracks produced by installing fasteners in misaligned holes during testing More
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.modes.c0047199
EISBN: 978-1-62708-234-1
... Abstract The lower receiver of the M16 rifle is an anodized forging of aluminum alloy 7075-T6. Degradation of the receivers was observed after three years of service in a hot, humid atmosphere. The affected areas were those in frequent contact with the user's hands. There was no question...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c0006387
EISBN: 978-1-62708-217-4
... Abstract A routine examination on a seat ejection system found that the catapult attachment swivel fabricated from 7075-T651 aluminum alloy plate contained cracks on opposite sides of the part. This swivel, or bath tub, does not experience extreme loads prior to activation of the catapult...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c0091674
EISBN: 978-1-62708-217-4
... hinge brackets in service for cracks and for proper maintenance of paint. Also suggested was replacing the aluminum alloy 2015-T6 with alloy 7075-T6, and surface treatment for the 7075-T6 brackets was recommended using sulfuric acid anodizing and dichromate sealing. Finally, it was also recommended...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c0091809
EISBN: 978-1-62708-217-4
... Abstract Aluminum 7075 aircraft wing tanks failed in the 1950s. Investigation (visual inspection, biological analysis, and chemical analysis) supported the conclusion that MIC was the cause of the failures. Water condensed into the fuel tanks during flight led to microbial growth on the jet...