1-20 of 88 Search Results for

aircraft corrosion damage

Follow your search
Access your saved searches in your account

Would you like to receive an alert when new items match your search?
Close Modal
Sort by
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c0091678
EISBN: 978-1-62708-217-4
... reagent) supported the conclusion that the cause of failure was SCC resulting from exposure to a marine environment. The fracture occurred in normal operation at a point where damage from pitting and intergranular corrosion acted as a stress raiser, not because of overload. The pitting and intergranular...
Series: ASM Failure Analysis Case Histories
Volume: 1
Publisher: ASM International
Published: 01 December 1992
DOI: 10.31399/asm.fach.v01.c9001022
EISBN: 978-1-62708-214-3
...Abstract Abstract Two complete aircraft undercarriage-leg 2014 aluminum alloy forgings and a number of sectional ends that exhibited cracks during nondestructive testing were examined to determine the extent of damage and the type of cracking. Cracks were primarily confined to the diaphragm...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001746
EISBN: 978-1-62708-217-4
...Abstract Abstract Brittle intergranular fracture, typical of a hydrogen-induced delayed failure, caused the failure of an AISI 4340 Cr-Mo-Ni landing gear beam. Corrosion resulting from protective coating damage released nascent hydrogen, which diffused into the steel under the influence...
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
... cut from the yoke in the region of the cracking indicated that the failure was caused by fatigue-crack initiation and growth from severe corrosion damage to a pillow-block bolt hole. Corrosion occurred because of failure of the protection scheme. An upgraded corrosion protection scheme for the bolt...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001731
EISBN: 978-1-62708-217-4
... 4340 UNS G43400 Hydrogen damage and embrittlement Stress-corrosion cracking Mixed-mode fracture Quenched and tempered steels heat treated to ultimate tensile strengths above 260,000 psi have been used in a number of applications in the aircraft and missile field. The success of these ultrahigh...
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
..., including coating degradation, is excessive. Grain-boundary attack and/or pitting by oxidation/hot corrosion, is excessive. Foreign object damage is severe. Destructive sampling and testing indicate life exhaustion. Excessive deformation has occurred due to creep, causing distortion...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001504
EISBN: 978-1-62708-217-4
... in the next case in more detail. Axle, Crank Lever of Fighter Aircraft Main Landing Gear A main landing gear axle of a fighter aircraft failed catastrophically upon landing when the hub locating the axle in the hydraulic tube fractured circumferentially ( Figs 3 ). This failure damaged the aircraft...
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
... R56406 Stress-corrosion cracking Background Visual Examination of General Physical Features Testing Procedure and Results Discussion Conclusion and Recommendations References References 1. Structures Manual , Grumman Aircraft Corp., 1968 . 2. Rich D.L...
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
... singularly complicated items is significant. Additionally, the knowledge that is required spans many different disciplines. These disciplines, in the case of aircraft, can include aerodynamics, fluid flow, mechanics, mechanisms, structures, metallurgy, materials science, corrosion, inspection methods...
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
... the point of fatigue initiation. Etched in Tucker's reagent. 7.70× Abstract Abstract A crack was detected in one arm of the right-hand horizontal brace of the nose landing gear shock strut from a large military aircraft. The shock strut was manufactured from a 7049 aluminum alloy forging...
Series: ASM Handbook Archive
Volume: 11
Publisher: ASM International
Published: 01 January 2002
DOI: 10.31399/asm.hb.v11.a0003515
EISBN: 978-1-62708-180-1
.... and Wolff T.A. , Life Extension and Damage Tolerance of Aircraft , Fatigue and Fracture , Vol 19 , ASM Handbook , ASM International , 1996 , p 557 – 565 14. Swift T. , Damage Tolerance Certification of Commercial Aircraft , Fatigue and Fracture , Vol 19 , ASM Handbook , ASM...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c0091809
EISBN: 978-1-62708-217-4
... a widespread potential for MIC wherever conditions permit microbial growth on aluminum or its alloys. Reference Reference 1. Hagenauer A. , Hilpert R. , and Hack T. , Microbiological Investigations of Corrosion Damage in Aircraft , Werkst. Korros. , Vol 45 , 1994 , p 355 – 360...
Series: ASM Failure Analysis Case Histories
Volume: 1
Publisher: ASM International
Published: 01 December 1992
DOI: 10.31399/asm.fach.v01.c9001020
EISBN: 978-1-62708-214-3
... A twin-turboprop transport aircraft sustained considerable damage when one of its main landing gear assemblies collapsed during landing. Applications Circumstances Leading to Failure Pertinent Specifications Specimen Selection One other location on the main strut assembly...
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
... intergranular cracking and fatigue. Fig. 6 Closer view of the intergranular and fatigue cracking, showing the marked corrosion damage (pitting) on the surface. O, overload region. Fig. 7 Closer view of the surface of one of the cracks through the chromium plating. This crack was associated...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c0046870
EISBN: 978-1-62708-217-4
...) was recommended as a standard maintenance procedure for shafts with long service lives. Aircraft components Shafts (power) Torsional fatigue AMS 6415 UNS G43400 Pitting corrosion Corrosion fatigue The hollow, splined alloy steel aircraft shaft shown in Fig. 1 cracked in service after more than...
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
...Abstract 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...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001145
EISBN: 978-1-62708-217-4
... configuration of the chamber and the stress distribution also have a bearing upon the failure modes. Several failures are reviewed to illustrate the problems. Aircraft components Breech chambers Electroless nickel plating Overheating 4340 UNS G43400 High-temperature corrosion and oxidation Stress...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001745
EISBN: 978-1-62708-217-4
... service operation may have loosened the fitting. Aircraft components Fittings Fluid penetrant testing 2XXX-T6 Fretting wear Intergranular corrosion Stress-corrosion cracking The part illustrated by Fig. 1 failed in a coastal environment, probably because corrosive chlorides got between...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001707
EISBN: 978-1-62708-217-4
..., Corrosion Resistant, Bars, Forgings, and Extrusions, 13Cr -8.0Ni - 2.2Mo - 1.1Al , SAE , Warrendale ( 1991 ) 4. Fracture Mechanics and Damage Tolerance Analysis Software, 2 nd Ed., FractuREsearch , Galena ( 1989 ) 5. Metals Handbook , Vol. 10 , 9th Ed. , Materials Characterization , p...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c0006436
EISBN: 978-1-62708-217-4
... cracking Pitting corrosion The failed pylon attachment stud illustrated in Fig. 1(a) was reportedly found during a routine walk-around inspection. Half of the stud was found lying on the apron under the aircraft. Fig. 1 H-11 tool steel pylon attachment stud (a) that failed by corrosion. (b...