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Cadmium plating
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in Failure in Aircraft Parts Made of Ultra-High-Strength Steel
> ASM Failure Analysis Case Histories: Air and Spacecraft
Published: 01 June 2019
Fig. 9 Small nicks or dents found under the cadmium plating (Cd) and paint (P) in the outside surface of the cylinder near the fracture origin. 1% Nital etch, ×500.
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in Hydrogen Embrittlement Cracking in a Batch of Steel Forgings
> Handbook of Case Histories in Failure Analysis
Published: 01 December 1993
Fig. 1 Heat-treated end frame component after cadmium plating. Several tiny cracklike indications, primarily in the base fillet radial zones, were detected by magnetic-particle testing.
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Book Chapter
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c0048630
EISBN: 978-1-62708-217-4
... to finger-tightness, and the consequent wrench torquing caused the actual fractures. The very small radius of the fillet between the bolt head and the shank undoubtedly accentuated the embrittling effect of the hydrogen. To prevent reoccurrence, the cleaning and cadmium-plating procedures were stipulated...
Abstract
Two clevis-head self-retaining bolts used in the throttle-control linkage of a naval aircraft failed on the aircraft assembly line. Specifications required the bolts to be heat treated to a hardness of 39 to 45 HRC, followed by cleaning, cadmium electroplating, and baking to minimize hydrogen embrittlement. The bolts broke at the junction of the head and shank. The nuts were, theoretically, installed fingertight. The failure was attributed to hydrogen embrittlement that had not been satisfactorily alleviated by subsequent baking. The presence of burrs on the threads prevented assembly to finger-tightness, and the consequent wrench torquing caused the actual fractures. The very small radius of the fillet between the bolt head and the shank undoubtedly accentuated the embrittling effect of the hydrogen. To prevent reoccurrence, the cleaning and cadmium-plating procedures were stipulated to be low-hydrogen in nature, and an adequate post plating baking treatment at 205 deg C (400 deg F), in conformity with ASTM B 242, was specified. A minimum radius for the head-to-shank fillet was specified at 0.25 mm (0.010 in.). All threads were required to be free of burrs. A 10-day sustained-load test was specified for a sample quantity of bolts from each lot.
Book Chapter
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.mech.c0046057
EISBN: 978-1-62708-225-9
... Abstract After less than 30 days in service, several cadmium-plated retaining rings, made of 4140 steel tubing and heat treated to 36 to 40 HRC, broke during operation that included holding components of a segmented fitting in place under a constant load. Photographic and 100x nital-etched...
Abstract
After less than 30 days in service, several cadmium-plated retaining rings, made of 4140 steel tubing and heat treated to 36 to 40 HRC, broke during operation that included holding components of a segmented fitting in place under a constant load. Photographic and 100x nital-etched micrographic examination showed a microstructure of tempered martensite with low inclusion content as well as a pit or burned spot on the outer area of the ring. The defect was approximately 0.18 mm (0.007 in.) deep and 0.5 mm (0.020 in.) in diam and had a hardness of 58 to 60 HRC. The base metal adjacent to the defect had a hardness of 36 to 40 HRC. Small cracks or fissures were also evident within the defect. Thus, the rings failed in brittle fracture as the result of an arc strike (or burn) on the surface of the ring. At the site of the arc strike, a small region of hard, brittle untempered martensite was formed as the result of an arc strike during the cadmium-plating operation. Fracture occurred readily when the ring was stressed. No recommendations were made.
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Published: 01 January 2002
Fig. 12 Cadmium-plated 8740 steel aircraft-wing assembly nut that failed by hydrogen embrittlement. The nut was not baked after electroplating to release hydrogen. (a) Overall view. 5×. (b) Fracture surface. 9×. (c) Scanning electron micrograph of typical intergranular fracture shown in box
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Published: 01 January 2002
Fig. 13 Cadmium-plated alloy steel self-retaining bolts that fractured because of hydrogen damage. (a) Fractured and unused intact bolt. (b) Fractured bolt; brittle fracture surface is indicated by A and B. (c) and (d) Electron fractographs of surfaces A and B, respectively, showing brittle
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Published: 01 January 2002
Fig. 14 Cadmium-plated AISI 8740 alloy steel fasteners that failed by hydrogen embrittlement. See also Fig. 15 .
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Published: 01 January 2002
Fig. 16 Cadmium-plated 4140 steel nuts from a military jet engine that failed by LME. (a) Fragmented and cracked nuts. (b) Typical fracture surface. (c) Electron fractograph showing brittle intergranular fracture
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Published: 01 January 2002
Fig. 1 Cadmium-plated AISI 8740 steel nut that failed by hydrogen embrittlement. Failure occurred seven days after installation on an aircraft wing structure. See also Fig. 2. 5×. Courtesy of Lockheed-Georgia Company
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Published: 01 January 2002
Fig. 2 Fracture surface of failed cadmium-plated nut in Fig. 1 . (a) Macrograph of fracture surface; 15×. (b) Scanning electron micrograph of the area in the box in (a) showing typical intergranular fracture; 3950×. Courtesy of Lockheed-Georgia Company
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Published: 01 January 2002
Fig. 3 Service failure of a low-alloy steel nut by LMIE. Cadmium-plated, 4140 low-alloy steel (44 HRC) nuts were inadvertently used on bolts for clamps used to join ducts that carried hot (500 °C, or 930 °F) air from the compressor of a military jet engine. (a) The nuts were fragmented
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Published: 01 January 2002
Fig. 6 Failed Ti-6AI-4V shear fastener. The fasteners were cadmium plated for galvanic compatibility with the aluminum structure. (a) Photograph showing failure at the head-to-shank fillet. (b) Intergranular fracture morphology. Failure was attributed to LMIE caused by excessive temperature
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Image
Published: 15 January 2021
Fig. 1 Cadmium-plated AISI 8740 steel nut that failed by hydrogen embrittlement. Failure occurred seven days after installation on an aircraft wing structure. See also Fig. 2 . Original magnification: 5×. Courtesy of Lockheed-Georgia Company
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Image
Published: 15 January 2021
Fig. 2 Fracture surface of failed cadmium-plated nut in Fig. 1 . (a) Macrograph of fracture surface. Original magnification: 15×. (b) Scanning electron micrograph of the area in the box in (a) showing typical intergranular fracture. Original magnification: 3950×. Courtesy of Lockheed-Georgia
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Published: 15 January 2021
Fig. 7 Failed Ti-6Al-4V shear fasteners. The fasteners were cadmium plated for galvanic compatibility with the aluminum structure. (a) Photograph showing failure at the head-to-shank fillet. (b) Intergranular fracture morphology. Failure was attributed to liquid-metal-induced embrittlement
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in Corrosion of a Ballast Gas Elbow Assembly
> ASM Failure Analysis Case Histories: Failure Modes and Mechanisms
Published: 01 June 2019
Fig. 1 Cadmium-plated 4340 steel ballast gas elbow assembly (a) with arrow showing hole where corrosion was found. (b) SEM of corrosion products on inside hole surface. 430x
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in Brittle Fracture of a Cadmium-Plated 4140 Steel Retaining Ring at a Hard Spot Caused by an Arc Strike
> ASM Failure Analysis Case Histories: Mechanical and Machine Components
Published: 01 June 2019
Fig. 1 Retaining ring of cadmium-plated 4140 steel that failed by brittle fracture at a hard spot caused by an arc strike during plating. (a) View of retaining ring, and section showing location of arc strike. Dimensions given in inches. (b) Photograph of the retaining ring showing pit
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in Hydrogen Embrittlement of Alloy Steel Fasteners
> ASM Failure Analysis Case Histories: Mechanical and Machine Components
Published: 01 June 2019
Fig. 1 Cadmium-plated AISI 8740 alloy steel fasteners that failed by hydrogen embrittlement. See also Fig. 2 .
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in Fracture of an Accumulator Ring Due to Hydrogen Embrittlement
> ASM Failure Analysis Case Histories: Processing Errors and Defects
Published: 01 June 2019
Fig. 1 Hydrogen-embrittlement fracture in a cadmium-plated 4140 steel forged accumulator ring. (a) Ring segment showing a fine crack (arrow). (b) Electron fractograph showing the predominantly intergranular fracture. 7800×
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in Brittle Fracture of a Clamp Because of Burning During Forging
> ASM Failure Analysis Case Histories: Processing Errors and Defects
Published: 01 June 2019
Fig. 1 Cadmium-plated 8740 steel aircraft wing clamp that failed because of burning during forging. (a) View of assembled clamp and detail showing locations of fractures. Dimensions given in inches. (b) Fracture surfaces showing brittle, intergranular nature of fracture. Approximately 2×. (c
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