Inspections and microstructural analysis revealed intergranular corrosion of 6061-T6 aluminum alloy aircraft fuel line beneath ferrules. The cause of the corrosion was traced to the fuel line marking process, which involved electrolytic labeling. Although subsequent rinsing of the fuel lines washed off most of the electrolyte, some was trapped between the 6061-T6 tubing and the ferrule. This condition made intergranular corrosion of the fuel lines inevitable. The attack caused grains to become dislodged, giving the appearance of pitting. Corrosion penetrated approximately 0.13 mm (0.005 in.) into the tubing. Experiments indicated that the corrosion products were inactive. It was recommended that another marking process be used that does not involve corrosive materials. The prevention of electrolyte from being trapped between the tubing and ferrules by using a MIL-S-8802 sealant was recommended.

An articulated rod (made from 4337 steel (AMS 6412) forging, quenched and tempered to 36 to 40 HRC) used in an overhauled aircraft engine was fractured after being in operation for 138 h. Visual examination revealed that the rod was broken into two pieces 6.4 cm from the center of the piston-pin-bushing bore. The fracture was nucleated at an electroetched numeral 5 on one of the flange surfaces. A notch, caused by arc erosion during electroetching, was revealed by metallographic examination of a polished-and-etched section through the fracture origin. A remelted zone and a layer of untempered martensite constituted the microstructure of the metal at the origin. Small cracks, caused by the high temperatures developed during electro-etching, were observed in the remelted area. It was concluded that fatigue fracture of the rod was caused by the notch resulting from electroetching and thus electroetched marking of the articulated rods was discontinued as a corrective measure.

The accident at Three Mile Island Unit No. 2 on 28 March 1979 was the worst nuclear accident in US history. By Jan 1990, it was possible to electrochemically machine coupons from the lower head using a specially designed tool. The specimens contained the ER308L stainless steel cladding and the A533 Grade B plate material to a depth of about mid-wall. The microstructures of these specimens were compared to that of specimens cut from the Midland, Michigan reactor vessel, made from the same grade and thickness but never placed in service. These specimens were subjected to known thermal treatments between 800 and 1100 deg C for periods of 1 to 100 min. Microstructural parameters in the control specimens and in those from TMI-2 were quantified. Selective etchants were used to better discriminate desired microstructural features, particularly in the cladding. This report is a progress report on the quantification of changes in both the degree of carbide precipitation and delta ferrite content and shape in the cladding as a function of temperature and time to refine the estimates of the maximum temperatures experienced.

An open electrical circuit was found between plated through-holes in a six-layer printed circuit board after thermal cycling. The copper plating was very thin in the failure area but did make an electrical contact during initial testing. During thermal cycling, differential z-expansion between the epoxy board and copper caused the thin plating to crack. During electrical testing of a four-layer circuit board, an open electrical circuit was found between the plated through-holes. Plating discontinuity was caused by poor drilling using a dull drill with improper speed (rpm) and/or feed rate as was observed by nonuniform plating and nodule formation in the plated layer. In a third example, an open electrical circuit was found in a six-layer board between two adjacent plated through-holes. A plating void was on one side of the conductor joining the two holes. Continuity was found when tested from one side of the board but lost when tested from the other. In a fourth case, an open circuit found between a plated through-hole and contact pad on a six-layer printed circuit board was caused by an etching defect.

Rough operation of the roller bearing mounted in an electric motor/gearbox assembly was observed. The bearing components made of low-alloy steel (4620 or 8620) and the cup, cone and rollers were carburized, hardened and tempered. The contact surfaces of these components (cup, cone and roller) were revealed to be uniformly electrolytically etched by visual examination. The action similar to anodic etching was believed to have occurred as a result of stray currents in the electric motor (not properly grounded) and the presence of an electrolyte (moisture) between the cup and roller surfaces of the bearing. As a remedial action, the bearing was insulated for protection from stray currents by grounding of the motor and the moisture was kept out by sealing both bearings in the assembly.

A helicopter tail rotor blade spar failed in fatigue, allowing the outer section of the blade to separate in flight. The 7075-T7351 aluminum alloy blade had fiberglass pockets. The blade spar was a hollow “D” shape, and corrosion pits were present on the inner surface of the hollow spar A single corrosion pit, 0.38 mm (0.015 in.) deep, led to a fatigue failure of the spar The failure initiated on the pylon side of the blade. Dimensional analysis of the spar near the failure revealed measurements within engineering drawing tolerances. Though corrosion pitting was present, there was an absence of significant amounts of corrosion product and all of the pits were filled with corrosion-preventative primer. This indicated that the pitting occurred during spar manufacture, prior to the application of the primer The pitting resulted from multiple nickel plating and defective plating removal by acid etching. Post-plating baking operations subsequently reduced the fatigue strength of the spar.