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Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001553
EISBN: 978-1-62708-217-4
... deficiency. The usual way to eliminate decarburization is to machine off the soft skin or employ better quality control when making them. Many aircraft manufacturers employ forged parts with machined surfaces or with shot-peened as-forged surfaces without excessive decarburization. Connecting rods...
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
... 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 the...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001744
EISBN: 978-1-62708-217-4
.... Aircraft components Airplane engines Axles Fittings Repair welding Welding defects Chromium-nickel steel Brittle fracture Joining-related failures Two examples of brittle fracture promoted by small fatigue cracks due to welding deficiencies illustrate weld failures. Other parts involving...
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
... tensile stresses. A second factor was a cluster of non-metallic inclusions which had ‘tributary’ cracks starting from them. Also, eyebolts broke when used to lift a light aircraft (about 7000 lb.). The bolt failure was a brittle intergranular fracture, very likely due to a hydrogen-induced delayed failure...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001903
EISBN: 978-1-62708-217-4
... features typical of low stress intensity fatigue of aluminum alloys. The fatigue resulted from abnormal fretting owing to inadequate torquing of the main retention bolts. Aircraft maintenance engineers and owners were advised to adhere to specifications when torquing this joint. Aircraft components...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001904
EISBN: 978-1-62708-217-4
.... Aircraft components Alignment Bolts Fatigue life Helicopters Magnetic particle testing Shafts (power) 18Ni Steel eyebolt Corrosion fatigue Pitting corrosion The first of two examples demonstrating failures caused by corrosion concerns a steel eyebolt which failed by fatigue ( Figs. 1 , 2...
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
... Abstract The failures of two aircraft components, one from a landing gear and the other from an ejector rack mechanism, were investigated. Both were made from PH 13-8 Mo (UNS S13800) precipitation-hardening stainless steel which had been heat treated to the H1000 and H950 tempers respectively...
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
... Abstract Despite extensive aircraft landing gear design analyses and tests performed by designers and manufacturers, and the large number of trouble-free landings, aircraft users have experienced problems with and failures of landing gear components. Different data banks and over 200 failure...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001517
EISBN: 978-1-62708-217-4
... Abstract The purpose of this investigation was to determine the cause of the ultrasonic signal attenuation noted during an inspection of a composite aircraft component. Although ultrasonics was able to identify the location of the defective areas, destructive analysis had to be utilized to...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.mech.c0047975
EISBN: 978-1-62708-225-9
... Abstract An aircraft was grounded when illumination of the transmission oil-pressure light and an accompanying drop in pressure on the oil-pressure gage was reported by the pilot. No discrepancy in the bearing assemblies and related components was revealed by teardown analysis of the...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001706
EISBN: 978-1-62708-217-4
... Abstract The truck beam of the left main landing gear (MGL) of a Boeing 707 airplane collapsed on the ground just after the aircraft was unloaded and refueled. The investigation revealed that failure was caused by the propagation of an intergranular crack originating from the bottom of the pit...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001019
EISBN: 978-1-62708-217-4
... Abstract A broken aircraft crankshaft and a severely damaged main brass bearing were examined to determine whether engine failure was initiated in the bearing or in the crankshaft. The steel crankshaft failure was a classical fatigue fracture. The bearing had been subjected to extremely high...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c0047677
EISBN: 978-1-62708-217-4
... nuggets that were the result of shunting caused by poor fit-up. The forming procedures were revised to achieve a precise fit between the stiffener and the tank wall. Also, an increase in welding current was suggested. Aircraft components Fitting Fuel tanks 2024-T8511 UNS A92024 Joining-related...
Series: 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
... the interference fit of the bushing in the lug hole be discontinued. Aircraft components Hinge brackets Marine environments 2014-T6 UNS A92014 Stress-corrosion cracking Surface treatment related failures Forged aluminum alloy 2014-T6 hinge brackets in naval aircraft rudder and aileron...
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
.... Aircraft components Forgings Lugs Marine environments 2014-T6 UNS A92014 Intergranular corrosion Pitting corrosion Stress-corrosion cracking During a routine shear-pin check, the end lug on the barrel of the forward canopy actuator on a naval aircraft was found to have fractured. The lug was...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c0047673
EISBN: 978-1-62708-217-4
... positioning. The problem could be solved by better forming procedures to provide an accurate fit-up that would not interfere with electrode alignment. Aircraft components Fuel tanks Welding parameters 2024-T62 UNS A92024 Joining-related failures A series of resistance spot welds joining Z-shape...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c0047076
EISBN: 978-1-62708-217-4
... components Deck plates Surface defects 7178-T6 UNS A97178 Pitting corrosion Fatigue fracture Two cracks were discovered in a deck plate of an aircraft during overhaul and repair after 659 h of service. As shown in Fig. 1 , the cracks were on opposite sides of the deck plate in the flange joggles...
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
... tolerances) 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...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c9001529
EISBN: 978-1-62708-217-4
... a 0.25-in. (6.4-mm) radii around the affected rivets. The repair process involved removal of the locally-affected material and addition of a skin doubler to restore the aircraft structure to the originally designed condition. Damage features are described briefly. Aircraft components...
Series: ASM Failure Analysis Case Histories
Publisher: ASM International
Published: 01 June 2019
DOI: 10.31399/asm.fach.aero.c0047125
EISBN: 978-1-62708-217-4
... crack originated at a material imperfection and progressed in more than one plane because changes in the direction of wheel rotation altered the direction of the applied stresses. Recommendations included rewriting the inspection specifications to require sound forgings. Aircraft components...