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fractographic evaluation

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Published: 01 January 2002
Fig. 6 Fractographic evaluation for life assessment purposes. (a) Wing spar that had mechanically induced damage at a fastener hole (indicted by an arrow). (b) Plot showing how fracture information is used to establish initial and recurring inspection requirements More
Image
Published: 01 January 2002
Fig. 9 Fractographic evaluation of multiple-site fatigue damage in a lower wing skin. The evaluation determined that the damage was caused by abusive machining marks that accelerated the fatigue crack growth rate. (a) Location of cracks in the a lower wing skin pocket. (b) Machine marks More
Image
Published: 30 August 2021
Fig. 6 Fractographic evaluation for life assessment purposes. (a) Wing spar that had mechanically induced damage at a fastener hole (indicted by an arrow). (b) Plot showing how fracture information is used to establish initial and recurring inspection requirements More
Image
Published: 30 August 2021
Fig. 9 Fractographic evaluation of multiple-site fatigue damage in a lower wing skin. The evaluation determined that the damage was caused by abusive machining marks that had accelerated the fatigue crack growth rate. (a) Location of cracks in the lower wing skin pocket. (b) Machine marks More
Series: ASM Handbook
Volume: 11B
Publisher: ASM International
Published: 15 May 2022
DOI: 10.31399/asm.hb.v11B.a0006917
EISBN: 978-1-62708-395-9
... the circumstances surrounding the failure, a fractographic evaluation to assess the cracking, and analytical testing to evaluate the material, design, manufacturing, and environmental factors. environmental stress cracking fractographic evaluation plastics MANY FRACTURE MECHANISMS exist that can lead...
Image
Published: 01 January 2002
Fig. 11 The measured crack growth rate (crack length versus time) determined by optical measurements or fractographic evaluation used to validate life prediction estimates. In this example, for an aircraft wing, the predicted crack growth and the actual crack growth based on measured crack More
Image
Published: 30 August 2021
Fig. 11 The measured crack growth rate (crack length versus time) is determined by optical measurements or fractographic evaluation in order to validate life-prediction estimates. In this example for an aircraft wing, the predicted crack growth and the actual crack growth (which is based More
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.power.c9001594
EISBN: 978-1-62708-229-7
... Utilities Electric Company (TU Electric) has implemented in response to these failures. High-cycle fatigue is invisible to proven commercial nondestructive evaluation (NDE) methods during crack initiation and the initial phases of crack growth. Under a constant applied stress, cracks grow at accelerating...
Series: ASM Handbook Archive
Volume: 11
Publisher: ASM International
Published: 01 January 2002
DOI: 10.31399/asm.hb.v11.a0003512
EISBN: 978-1-62708-180-1
... spar mechanically induced during the drilling of the hole. The failure analyst was able to identify the location of the damage and extent of fatigue crack growth, which was used to establish inspection intervals ( Ref 23 ) Fig. 6 Fractographic evaluation for life assessment purposes. (a) Wing...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001144
EISBN: 978-1-62708-217-4
... the aircraft was landed. The helicopter main rotor blade spar fracture was analyzed by conventional and advanced computerized fractographic techniques. Digital fractographic Imaging Analysis of theoretical and actual fracture surfaces was applied for automatic detection of fatigue striation spacing...
Image
Published: 15 January 2021
Fig. 28 (a) Light micrograph of a cross section of a partially broken specimen of solution-annealed AISI 304 stainless steel after stress-corrosion crack testing in boiling (151 °C, or 304 °F) magnesium chloride. Scanning electron fractographs of the completely broken specimen: (b More
Image
Published: 01 January 2002
Fig. 8 Failure evaluation of a cracked gate valve stem determined that no subcritical crack growth had occurred from the forging defect. Therefore, similar gate valve stems could remain in service with a periodic inspection. (a) Cracked gate valve stem. 1×. (b) Forging defect in the radius. 50 More
Image
Published: 30 August 2021
Fig. 8 Failure evaluation of a cracked gate valve stem determined that no subcritical crack growth had occurred due to a forging defect. Therefore, similar gate valve stems could remain in service with a periodic inspection. (a) Cracked gate valve stem. Original magnification: 1×. (b) Forging More
Series: ASM Handbook
Volume: 11A
Publisher: ASM International
Published: 30 August 2021
DOI: 10.31399/asm.hb.v11A.a0006802
EISBN: 978-1-62708-329-4
... in a wing skin spar mechanically induced during the drilling of the hole. The failure analyst was able to identify the location of the damage and the extent of fatigue crack growth, which was used to establish inspection intervals ( Ref 28 ). Fig. 6 Fractographic evaluation for life assessment...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.chem.c9001718
EISBN: 978-1-62708-220-4
... the Widmanstätten structure. 1 Fig. 8 Both impellers display a Widmanstätten structure. (100×) Fractography One of the linear defects observed on the impeller blades was sectioned and parted to permit fractographic evaluation. The fracture surface ( Figure 9 ) consists of three distinct regions...
Series: ASM Failure Analysis Case Histories
Volume: 2
Publisher: ASM International
Published: 01 December 1993
DOI: 10.31399/asm.fach.v02.c9001361
EISBN: 978-1-62708-215-0
...° relative to (a). 9400×. (c) SEM fractograph of a typical field on the fracture surface. The fractograph was overexposed to highlight the secondary cracks/inclusions network. 1128× Metallography The body was evaluated for material cleanliness. The size and frequency of microinclusions in the body...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001708
EISBN: 978-1-62708-217-4
... vessels. Usually the investigation commences with a site visit by a failure analysis specialist and a naval architect, to gather the background information leading to an initial evaluation of the damage. Blade fractures are usually of the brittle type as the thick blade material has a coarse ascast...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.modes.c9001537
EISBN: 978-1-62708-234-1
... fractographic analysis was performed to determine the exact cause of failure. Fig. 1 In a forging of 7079-T6, failure started at Region 1. Numbered regions refer to failure modes shown in Fig. 2 . Top photo, 3 4 ×; Bottom, 2 1 2 × Fig. 2 Fractography revealed...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.design.c0089730
EISBN: 978-1-62708-233-4
... with the expansion and contraction of the bellows. Investigation (visual inspection, hardness testing, and 30x fractographs) supported the conclusion that the liners failed in fatigue initiated at the intersection of the longitudinal weld forming the liner and the circumferential weld by which it attached...
Series: ASM Failure Analysis Case Histories
Volume: 3
Publisher: ASM International
Published: 01 December 2019
DOI: 10.31399/asm.fach.v03.c9001753
EISBN: 978-1-62708-241-9
... Abstract A failure analysis investigation was conducted on a fractured aluminum tailwheel fork which failed moments after the landing of a privately owned, 1955 twin-engine airplane. Nondestructive evaluation via dye-penetrant inspection revealed no discernible surface cracks. The chemical...