Skip Nav Destination
Close Modal
By
Harry Czyzewski
Search Results for
Hinges
Update search
Filter
- Title
- Authors
- Author Affiliations
- Full Text
- Abstract
- Keywords
- DOI
- ISBN
- EISBN
- Issue
- ISSN
- EISSN
- Volume
- References
Filter
- Title
- Authors
- Author Affiliations
- Full Text
- Abstract
- Keywords
- DOI
- ISBN
- EISBN
- Issue
- ISSN
- EISSN
- Volume
- References
Filter
- Title
- Authors
- Author Affiliations
- Full Text
- Abstract
- Keywords
- DOI
- ISBN
- EISBN
- Issue
- ISSN
- EISSN
- Volume
- References
Filter
- Title
- Authors
- Author Affiliations
- Full Text
- Abstract
- Keywords
- DOI
- ISBN
- EISBN
- Issue
- ISSN
- EISSN
- Volume
- References
Filter
- Title
- Authors
- Author Affiliations
- Full Text
- Abstract
- Keywords
- DOI
- ISBN
- EISBN
- Issue
- ISSN
- EISSN
- Volume
- References
Filter
- Title
- Authors
- Author Affiliations
- Full Text
- Abstract
- Keywords
- DOI
- ISBN
- EISBN
- Issue
- ISSN
- EISSN
- Volume
- References
NARROW
Format
Topics
Book Series
Date
Availability
1-20 of 53
Search Results for Hinges
Follow your search
Access your saved searches in your account
Would you like to receive an alert when new items match your search?
1
Sort by
Book Chapter
Failure of Nylon Hinges
Available to PurchaseSeries: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.auto.c0090466
EISBN: 978-1-62708-218-1
... Abstract A production lot of mechanical hinges used in an automotive application had failed during incoming quality-control routine actuation testing. A change in part supplier had taken place between the approval of the prototype parts that performed acceptably and the receipt of the first lot...
Abstract
A production lot of mechanical hinges used in an automotive application had failed during incoming quality-control routine actuation testing. A change in part supplier had taken place between the approval of the prototype parts that performed acceptably and the receipt of the first lot of production parts. The mechanical hinges were specified to be injection molded from an impact-modified, 13% glass-fiber-reinforced nylon 6/6 resin. Investigation of samples representing the failed components and the original prototype parts included visual inspection, 118x SEM images, micro-FTIR, DSC analysis, and TGA. It supported the conclusion that the hinge assemblies failed through brittle fracture associated with stress overload during the actuation of the parts. The failed part material was found to be degraded, most likely occurring during the compounding of the resin or during the actual molding of the parts. While resins for both failed and non-failed parts produced results characteristic of a 13% glass-fiber-reinforced, impact-modified nylon 6/6, the failed part material, contained a significantly lower level of rubber, which rendered the parts less impact resistant and subsequently lowered the ductility of the molded hinge assemblies. No recommendations were made.
Book Chapter
Stress-Corrosion Cracking of Aircraft Hinge Brackets
Available to PurchaseSeries: 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
... Abstract Forged aluminum alloy 2014-T6 hinge brackets in naval aircraft rudder and aileron linkages were found cracked in service. The cracks were in the hinge lugs, adjacent to a bushing made of cadmium-plated 4130 steel. Investigation (visual inspection and 250X micrographs) supported...
Abstract
Forged aluminum alloy 2014-T6 hinge brackets in naval aircraft rudder and aileron linkages were found cracked in service. The cracks were in the hinge lugs, adjacent to a bushing made of cadmium-plated 4130 steel. Investigation (visual inspection and 250X micrographs) supported the conclusion that the failure of the hinge brackets occurred by SCC. The corrosion was caused by exposure to a marine environment in the absence of paint in stressed areas due to chipping. The stress resulted from the interference fit of the bushing in the lug hole. Recommendations included inspecting all 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 that the interference fit of the bushing in the lug hole be discontinued.
Book Chapter
Corrosion Failure of Wing Flap Hinge Bearings
Available to PurchaseSeries: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c0006448
EISBN: 978-1-62708-217-4
... Abstract Three wing flap hinge bearings were received by the laboratory for analysis. The bearings were fabricated from chromium-plated type 440C martensitic stainless steel. The intergranular fracture pattern seen in the electron fractographs, coupled with the corrosion pits observed...
Abstract
Three wing flap hinge bearings were received by the laboratory for analysis. The bearings were fabricated from chromium-plated type 440C martensitic stainless steel. The intergranular fracture pattern seen in the electron fractographs, coupled with the corrosion pits observed on the inner diam of the bearings, strongly suggested that failure initiated by pitting and progressed by SCC or hydrogen embrittlement from the plating operation. It was recommended that the extent of the flap hinge bearing cracking problem be determined by using nondestructive inspection because it is possible to crack hardened type 440C during the chromium plating process. An inspection for pitting on the bearing inner diam was also recommended. It was suggested that electroless nickel be used as a coating for the entire bearing. A review of the chromium plating and baking sequence was recommended also to ensure that a source of hydrogen is not introduced during the plating operation.
Book Chapter
Failure of a Helicopter Rotor
Available to PurchaseSeries: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c0006444
EISBN: 978-1-62708-217-4
... Abstract Helicopter rotor blade components that included the horizontal hinge pin, the associated nut, and the locking washer were examined. Visual examination of the submitted parts revealed that the hinge pin, fabricated from 4340 steel, was broken and that the fracture face showed a flat...
Abstract
Helicopter rotor blade components that included the horizontal hinge pin, the associated nut, and the locking washer were examined. Visual examination of the submitted parts revealed that the hinge pin, fabricated from 4340 steel, was broken and that the fracture face showed a flat beach mark pattern indicative of a preexisting crack. The threaded area of the pin had an embedded thread that did not appear to come from the pin. A chemical analysis was conducted on the embedded thread and on an associated attachment to determine the origin of the thread. Analysis showed that the thread and nut were 4140 steel. Scanning electron fractographic examination of the fracture initiation site strongly suggested that the fracture progressed by fatigue. It was concluded that the failure of the horizontal hinge pin initiated at areas of localized corrosion pits. The pits in turn initiated fatigue cracks, resulting in a failure mode of corrosion fatigue. It was recommended that all of the horizontal hinge pins be inspected. Those pins determined to be satisfactory for further use should be stripped of cadmium, shot peened, and coated with cadmium to a minimum thickness of 0.0127 mm (0.0005 in.).
Book Chapter
Brittle Fracture of a Clamp Because of Burning During Forging
Available to PurchaseSeries: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.process.c0047176
EISBN: 978-1-62708-235-8
... Abstract A ring clamp (8740 (AMS 6322), steel forged and cadmium plated) used for attaching ducts to an aircraft engine became loose after three hours of service. When the clamp was removed from the engine, the hinge tabs on one clamp half were found to be broken. Analysis (visual inspection...
Abstract
A ring clamp (8740 (AMS 6322), steel forged and cadmium plated) used for attaching ducts to an aircraft engine became loose after three hours of service. When the clamp was removed from the engine, the hinge tabs on one clamp half were found to be broken. Analysis (visual inspection and microscopic and metallographic examination) supported the conclusion that both hinge tabs on the clamp half fractured in a brittle manner as the result of gross overheating, or burning, during forging. The mechanical properties of the metal, especially toughness and ductility, were greatly reduced by burning. Evidence that burning was confined to the hinge end of the clamp indicated that the metal was overheated before or during the upset forging operation. Recommendations included notifying the supplier of the burned condition on the end of the clamp. The clamps should be macroetched before cadmium plating to detect overheating. The clamps in stock should be inspected to ensure that the metal had not been weakened by overheating during the upset forging operation.
Book Chapter
Brittle Fracture Leading to Failure of a Bridge Section
Available to PurchaseSeries: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.bldgs.c9001544
EISBN: 978-1-62708-219-8
... Abstract A large crack developed at a girder-truss joint area of the Fremont bridge in Portland, OR, on 28 Oct 1971. It occurred during a positioning procedure involving a junction piece welded to a girder, starting as a brittle fracture and terminating in plastic hinges in the girder web welds...
Abstract
A large crack developed at a girder-truss joint area of the Fremont bridge in Portland, OR, on 28 Oct 1971. It occurred during a positioning procedure involving a junction piece welded to a girder, starting as a brittle fracture and terminating in plastic hinges in the girder web welds. The arch rib top plate, as it met the main girder, formed a composite beam of A588/A36 composition. Investigation showed the original design of the failed component called for an angle of high geometric stress concentration (90 deg with no radius) in a region of substantial transverse weld joints. While the material met chemical and mechanical property requirements, tests showed it had low fracture toughness and critical-sized flaws oriented normal to the principal stress in the failed junction piece. Fabrication procedures resulted in high residual stresses and a metallurgical notch at the radius in the junction piece. Stresses induced during jacking (the procedure used to raise bridge components into position) applied the stresses in the critical radius that triggered the cracking.
Book Chapter
Compression Fracture of a Graphite-Epoxy Test Structure Due to a Buckling Instability
Available to PurchaseSeries: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.modes.c0048498
EISBN: 978-1-62708-234-1
... Abstract A graphite-epoxy tapered-box structure, which consisted of two honeycomb skin panels fastened to a spanwise spar with intermediate chordwise ribs, fractured during testing. Hinge-line deflection of the front spar was revealed. Through-thickness cracks in the forward and trailing edges...
Abstract
A graphite-epoxy tapered-box structure, which consisted of two honeycomb skin panels fastened to a spanwise spar with intermediate chordwise ribs, fractured during testing. Hinge-line deflection of the front spar was revealed. Through-thickness cracks in the forward and trailing edges of the compression-loading skin panel were revealed by nondestructive visual examination. A band of de-lamination between the areas of through-thickness skin fracture at the front and rear spar was revealed. A map of the local directions of crack propagation over the fracture surface was generated by the orientation of river patterns and resin microflow during microscopic examination of sectioned samples of the panel. It was discovered that crack initiation occurred at the periphery of a fastener hole located at the front spar. Propagation occurred chordwise across the compression-loaded skin panel. As a corrective measure, the fastener spacing was reduced to prevent the buckling mode that precipitated fracture.
Image
Aluminum alloy 2014-T6 hinge bracket that failed by SCC in service. (a) Hin...
Available to PurchasePublished: 01 January 2002
Fig. 37 Aluminum alloy 2014-T6 hinge bracket that failed by SCC in service. (a) Hinge bracket. Actual size. Arrow indicates crack. (b) Micrograph showing secondary cracking adjacent and parallel to the fracture surface. Etched with Keller's reagent. 250×
More
Image
Optical microscopy image of fracture surfaces of a knee implant hinge post,...
Available to Purchase
in Failure Analysis of Medical Devices
> Analysis and Prevention of Component and Equipment Failures
Published: 30 August 2021
Fig. 20 Optical microscopy image of fracture surfaces of a knee implant hinge post, which fractured in vivo
More
Image
Optical microscopy images of the subject hinge post fragment fracture surfa...
Available to Purchase
in Failure Analysis of Medical Devices
> Analysis and Prevention of Component and Equipment Failures
Published: 30 August 2021
Fig. 21 Optical microscopy images of the subject hinge post fragment fracture surfaces, with beach marks clearly evident
More
Image
Scanning electron microscopy image of the subject hinge post posterior inte...
Available to Purchase
in Failure Analysis of Medical Devices
> Analysis and Prevention of Component and Equipment Failures
Published: 30 August 2021
Fig. 23 Scanning electron microscopy image of the subject hinge post posterior internal threads indicating significant wear caused by component looseness
More
Image
in An Overview of Aircraft Accident Investigation and Component Failures
> Analysis and Prevention of Component and Equipment Failures
Published: 30 August 2021
Fig. 6 Diagram of the elevator hinge pin assembly
More
Image
Cracked type 440C stainless steel (a) aircraft wing flap hinge bearings. (b...
Available to Purchase
in Corrosion Failure of Wing Flap Hinge Bearings
> ASM Failure Analysis Case Histories: Air and Spacecraft
Published: 01 June 2019
Fig. 1 Cracked type 440C stainless steel (a) aircraft wing flap hinge bearings. (b) Crack configuration of bearing 1 from (a). (c) Crack configuration of bearing 2 from (a). (d) Fracture surface of second crack in bearing 1. Arrow shows the probable fracture origin. 2.5x. (e) Fracture surface
More
Image
Aluminum alloy 2014-T6 hinge bracket that failed by SCC in service. (a) Hin...
Available to Purchase
in Stress-Corrosion Cracking of Aircraft Hinge Brackets
> ASM Failure Analysis Case Histories: Air and Spacecraft
Published: 01 June 2019
Fig. 1 Aluminum alloy 2014-T6 hinge bracket that failed by SCC in service. (a) Hinge bracket. Actual size. Arrow indicates crack. (b) Micrograph showing secondary cracking adjacent and parallel to the fracture surface. Etched with Keller's reagent. 250×
More
Image
in Failure of a Fairground Ride
> ASM Failure Analysis Case Histories: Improper Maintenance, Repair, and Operating Conditions
Published: 01 June 2019
Fig. 4 Fractured retaining bolt. The hinge pin is shown in the top of the figure.
More
Image
(a) Photograph of an aluminum alloy 2014-T6 hinge bracket. Arrow indicates ...
Available to PurchasePublished: 15 January 2021
Fig. 48 (a) Photograph of an aluminum alloy 2014-T6 hinge bracket. Arrow indicates crack location. (b) Micrograph of a cross section prepared through the fracture surface. Arrows indicate stress-corrosion cracking. Original magnification: 250×
More
Image
The crack in each web terminated in a plastic hinge. Note paint flaking in ...
Available to Purchase
in Brittle Fracture Leading to Failure of a Bridge Section
> ASM Failure Analysis Case Histories: Buildings, Bridges, and Infrastructure
Published: 01 June 2019
Fig. 2 The crack in each web terminated in a plastic hinge. Note paint flaking in area at tip of crack.
More
Image
Corrosion fatigue of a 4340 steel helicopter rotor assembly. (a) Horizontal...
Available to PurchasePublished: 01 June 2019
Fig. 1 Corrosion fatigue of a 4340 steel helicopter rotor assembly. (a) Horizontal hinge pin. (b) Nut. (c) Locking washers. (d) and (e) Views of the hinge pin fracture surface. A beach mark is visible in (e). (f) Dent on one of the threaded surfaces of the horizontal hinge pin. (g) Corrosion
More
Image
Scanning electron images showing (a) brittle fracture features on the faile...
Available to PurchasePublished: 01 January 2002
Fig. 41 Scanning electron images showing (a) brittle fracture features on the failed hinge and (b) ductile fracture features on the laboratory fracture. 118×
More
Image
Scanning electron images showing (a) brittle fracture features on the faile...
Available to PurchasePublished: 01 June 2019
Fig. 1 Scanning electron images showing (a) brittle fracture features on the failed hinge and (b) ductile fracture features on the laboratory fracture. 118×
More
1