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in Common Causes of Failures
> Failure Analysis of Engineering Structures: Methodology and Case Histories
Published: 01 October 2005
Fig. 2.13 (a) Spiral cracks on the shank surface of a quill shaft and (b) SEM photograph of the cracks
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in Common Causes of Failures
> Failure Analysis of Engineering Structures: Methodology and Case Histories
Published: 01 October 2005
Fig. 2.26 (a) Porcelain insulator showing the step in its shank and (b) magnified view of the shank
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in Common Causes of Failures
> Failure Analysis of Engineering Structures: Methodology and Case Histories
Published: 01 October 2005
Fig. 2.27 (a) Fracture at the step in the shank and (b) magnified view of the 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. 65 Schematic of the failed arresting hook shank showing location of loads
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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. 68 Metallography of the arresting hook shank. (a) Typical quenched and tempered martensite found. This is typical for the hardness of the arresting hook shank. (b) Pulled material at 4.3 mm (0.17 in.) intervals along the inner bore of the arresting hook shank. Origin is to the left. (c
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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. 73 Fracture surface of the exposed crack in the shank of bolt I
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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. 77 Machining marks and polishing evident on the shank of the failed bolt
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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. 80 SEM micrograph showing initiation of cracking on the shank of bolt I at localized surface wear (400 μm)
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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. 82 SEM micrograph of machining marks at the head-to-shank fillet radius of bolt I (1 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
Fig. 85 Micrograph of the crack found in the head-to-shank fillet radius of the failed bolt. Etched with 2% nital (25 μm)
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Published: 01 September 2008
Fig. 32 Close-up view of the bolt-shank fracture surface. Note the heavy scale on the zone 1 surface. Source: Ref 19
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Published: 01 May 2018
FIG. 10.23 Maurice “Bud” Shank recruited a team of scientists and engineers to improve jet engine performance.
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Published: 01 June 1985
Fig. 3-18. Spindle shank, 1×. 5% nital etching reveals a welded structure.
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Published: 01 June 1985
Fig. 3-19. Carbon gradient traverse taken from a shank section of a hypoid pinion. Note that the 0.40% carbon level at 0.059 in. is very close to the effective case depth.
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Published: 01 June 1985
Fig. 4-29. Splined section of a pinion shank. Torsional tensile fatigue in one direction showing the 45° tensile failure lines and evidence of longitudinal shear cracking.
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Published: 01 December 2004
Fig. 8 Tensile-test specimen with turned-down shank. Source: Ref 3
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in Failure of Dowel Bolts in an Aircraft Engine
> Failure Analysis of Engineering Structures: Methodology and Case Histories
Published: 01 October 2005
Fig. CH17.6 Circumferential grooves on the shanks of the bolts
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Book Chapter
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270102
EISBN: 978-1-62708-301-0
... at the shank was increased. Still, there were a series of accidents caused by the failure of dowel bolts. Detailed investigations revealed that the bolts failed due to fatigue. Fatigue was initiated by fretting in some bolts. Background The spur and bevel gears of an aircraft engine were fastened...
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in Avoidance, Control, and Repair of Fatigue Damage[1]
> Fatigue and Durability of Structural Materials
Published: 01 March 2006
Fig. 11.65 Geometry of taper pin fastening. Installation sequence: 1. Following hole preparation with tapered drill, tapered shank bolt is inserted in hole and firmly seated by hand pressure. 2. Full contact along entire shank of bolt and hole prevents rotation of bolt while tightening washer
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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
... treated to the 1240 to 1380 MPa (180 to 200 ksi tensile strength range. Figure 28 shows the inboard flap hinge bolt and nut as received for examination. The bolt was approximately 102 mm (4 in.) long. The bolt consisted essentially of the shank, which was approximately 23 mm (0.9 in.) in diameter...
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