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Series: ASM Failure Analysis Case Histories
Volume: 2
Publisher: ASM International
Published: 01 December 1993
DOI: 10.31399/asm.fach.v02.c9001292
EISBN: 978-1-62708-215-0
... inspection of the struts was recommended. Crack propagation Fractography Military planes Scanning electron microscopy 7049 UNS A97049 Fatigue fracture Background A crack was detected in one arm of the right-hand horizontal brace of the nose landing gear shock strut from a large military...
Series: ASM Failure Analysis Case Histories
Volume: 1
Publisher: ASM International
Published: 01 December 1992
DOI: 10.31399/asm.fach.v01.c9001027
EISBN: 978-1-62708-214-3
... holes was recommended, along with nondestructive inspection of the region at intervals determined by fractographic analysis of the fatigue crack growth. Bolted joints Drives Helicopters Military planes Shafts (power) 4340 UNS G43400 Corrosion fatigue Background The 4340 steel main...
Series: ASM Failure Analysis Case Histories
Volume: 1
Publisher: ASM International
Published: 01 December 1992
DOI: 10.31399/asm.fach.v01.c9001023
EISBN: 978-1-62708-214-3
.... The wear had been caused by incorrect machining of the shaft splines, which prevented the bevel gear nut from locating correctly against the gear. Aerospace engines Aircraft components Bevel gears Drives Engine components Jet planes Military planes Splines 16 NCD 13 Fretting wear...
Series: ASM Failure Analysis Case Histories
Volume: 1
Publisher: ASM International
Published: 01 December 1992
DOI: 10.31399/asm.fach.v01.c9001024
EISBN: 978-1-62708-214-3
... of an improperly designed heating element used to cure fiberglass repairs. Extrusions Fatigue failure Military planes 6061-T651 UNS A96061 Fatigue fracture Background About an hour after takeoff, a Marine Corps helicopter crashed, killing all on board. In the ensuing investigation, a large...
Series: ASM Failure Analysis Case Histories
Volume: 1
Publisher: ASM International
Published: 01 December 1992
DOI: 10.31399/asm.fach.v01.c9001030
EISBN: 978-1-62708-214-3
... MoS2). Control of machining parameters to prevent formation of brittle martensite, use of galvanically compatible fasteners, and use of an alternate lubricant were recommended. Airframes, corrosion Fasteners Jet planes Marine environments Military planes Solid lubricants Ti-6Al-4V UNS...
Series: ASM Failure Analysis Case Histories
Volume: 1
Publisher: ASM International
Published: 01 December 1992
DOI: 10.31399/asm.fach.v01.c9001021
EISBN: 978-1-62708-214-3
... growth rate data to be determined for the configuration of interest. Crack propagation Fatigue life Jet planes Military planes Wings (aircraft) AU4SG Fatigue fracture Background Following the crash of a Mirage III-0 aircraft, a small crack was detected in a bolt hole in the wing main...
Series: ASM Failure Analysis Case Histories
Volume: 2
Publisher: ASM International
Published: 01 December 1993
DOI: 10.31399/asm.fach.v02.c9001295
EISBN: 978-1-62708-215-0
... flight conditions was the major cause of failure. Recommendations emphasized the need for a suitable shock absorber to be fitted at the constant-tensioning device of the winch system. Military applications Military planes Shock loading Fe-0.8C (Other, general, or unspecified) fracture...
Series: ASM Failure Analysis Case Histories
Volume: 1
Publisher: ASM International
Published: 01 December 1992
DOI: 10.31399/asm.fach.v01.c9001025
EISBN: 978-1-62708-214-3
... that the inspection interval be reduced to one-third of its original duration for the current level of inspection reliability, or that inspection procedures be improved in order that cracks substantially smaller than 13 mm (0.5 in.) can be reliably detected. Forgings Military planes 2014-T61 UNS A92014...
Series: ASM Failure Analysis Case Histories
Volume: 2
Publisher: ASM International
Published: 01 December 1993
DOI: 10.31399/asm.fach.v02.c9001291
EISBN: 978-1-62708-215-0
... for fatigue crack growth during service. It was recommended that the damaged undercarriage struts be withdrawn from service pending further analysis and development of a repair technique. Crack propagation Military planes 35NCD16 Surface treatment related failures Intergranular fracture Fatigue...
Series: ASM Failure Analysis Case Histories
Volume: 1
Publisher: ASM International
Published: 01 December 1992
DOI: 10.31399/asm.fach.v01.c9001081
EISBN: 978-1-62708-214-3
... Military planes Turbine disks AM355 UNS S35500 Fatigue fracture Background Several compressor disks in military fighter and trainer aircraft gas turbine engines cracked prematurely in the bolt hole regions. The disks were made from precipitation-hardened AM355 martensitic stainless steel...
Series: ASM Failure Analysis Case Histories
Volume: 1
Publisher: ASM International
Published: 01 December 1992
DOI: 10.31399/asm.fach.v01.c9001026
EISBN: 978-1-62708-214-3
... for defects before further processing and that foundry practices be reviewed to correct deficiencies leading to excessive hydrogen absorption during melting and casting. Castings Cleavage Martensitic stainless steels Military planes Supports Transgranular fracture Wings (aircraft) 17-4 PH UNS...
Series: ASM Handbook Archive
Volume: 11
Publisher: ASM International
Published: 01 January 2002
DOI: 10.31399/asm.hb.v11.a0003504
EISBN: 978-1-62708-180-1
... published Nowlan and Heap's report, the U.S. military embarked on developing RCM processes for its own use, one for the U.S. Army, one for the U.S. Air Force, and two for the U.S. Navy, because the shipboard and aviation communities of the Navy insisted that a RCM process that worked for one would not work...
Series: ASM Handbook Archive
Volume: 11
Publisher: ASM International
Published: 01 January 2002
DOI: 10.31399/asm.hb.v11.a0001812
EISBN: 978-1-62708-180-1
... stress raisers and unfavorable shear planes. Source: Ref 4 The shape and size of the head-to-shank fillet also have an important influence on fatigue performance. In general, the radius of this fillet should be as large as possible while at the same time permitting adequate head-bearing area...
Series: ASM Handbook Archive
Volume: 11
Publisher: ASM International
Published: 01 January 2002
DOI: 10.31399/asm.hb.v11.a0003573
EISBN: 978-1-62708-180-1
... at bottom was slack quenched because of faulty loading practice (stacking), and it failed by distortion (flattening) because of the resultant mixed microstructure. Fig. 10 4140 steel slat track from a military aircraft wing. The track bent because one end did not become fully austenitic during...
Series: ASM Handbook
Volume: 11
Publisher: ASM International
Published: 15 January 2021
DOI: 10.31399/asm.hb.v11.a0006797
EISBN: 978-1-62708-295-2
...) is satisfactory Fig. 10 4140 steel slat track from a military aircraft wing. The track bent because one end did not become fully austenitic during heat treatment, producing a low-strength structure of ferrite and tempered martensite. Fig. 13 Gas-nitrided 4140 steel (27–31 HRC) drive-gear...
Series: ASM Handbook Archive
Volume: 11
Publisher: ASM International
Published: 01 January 2002
DOI: 10.31399/asm.hb.v11.a0003516
EISBN: 978-1-62708-180-1
... 275.6 40 Four attached Intact 3 103.4 15 Four attached Intact 4 275.6 40 Four attached Not intact 5 103.4 15 Four attached Not intact Plane stress and transitional fracture toughness data for 0.050 in. thick 2024-T3 aluminum alloy sheet Table 1 Plane stress...
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
... in the absence of the crack. The basic relation in fracture mechanics is one that equates K to a critical value. This critical value is often taken as a property of the material called the plane-strain fracture toughness, conventionally denoted as K Ic . When equality is achieved between K and K Ic...
Series: ASM Handbook
Volume: 11
Publisher: ASM International
Published: 15 January 2021
DOI: 10.31399/asm.hb.v11.a0006753
EISBN: 978-1-62708-295-2
... determined to be extending from shallow (0.013 mm, or 0.0005 in.) zones exhibiting ductile shear (see area between arrows in Fig. 16 ). Viewing the OD surface of the sleeve adjacent to the fracture plane revealed an extensive network of microcracks on the OD in the radius between the bulb and cylindrical...
Series: ASM Handbook Archive
Volume: 11
Publisher: ASM International
Published: 01 January 2002
DOI: 10.31399/asm.hb.v11.a0003500
EISBN: 978-1-62708-180-1
Series: ASM Handbook Archive
Volume: 11
Publisher: ASM International
Published: 01 January 2002
DOI: 10.31399/asm.hb.v11.a0003524
EISBN: 978-1-62708-180-1
... are moved in opposite directions, normal to the fracture plane. Generally, a saw cut can be made from the back of the fractured part to a point near the tip of the crack, using extreme care to avoid actually reaching the tip of the crack. This saw cut will reduce the amount of solid metal that must...