著者

藤原 源吉

出版者

公益社団法人 日本材料学会

雑誌

材料 (ISSN:05145163)

巻号頁・発行日

vol.45, no.1, pp.2-8, 1996-01-15 (Released:2009-06-03)

参考文献数

10

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This article describes the findings of research for some recent transport airplane's accidents related to fatigue cracks. One is a B747SR's accident due to crack initiating at the fastener holes (to say Multiple-Site Damage). The other describes the crash of UAL's DC10-10 (N1819U), in Sioux City, Iowa, U. S. A., on July 19, 1989, which experienced a catastrophic failure of the No. 2 tail-mounted engine during cruise flight. The third explains the in flight separation of the No. 2 engine and engine pylon from B747-100F, shortly after departure from Anchorage International Airport, Anchorage, Alaska, on March 31, 1993. As a result of investigation for B747-100F's accident, National Transportation Safety Board made some important recommendations (One is to amend the design load requirements of Title 14 Code of Federal Regulations Part 25 to consider multiple axis loads encountered during severe turbulence) to the Federal Aviation Administration. Also, current aging airplane service data have identified that there are more cracked airplanes with increasing fleet edge, and possibly several fatigue cracks in some of the cracked airplanes. Especialy, MSD helped focus the attention of the aeronautical field on the problems of operating an aging transport airplanes. Therefore, FAA proposed to rivise the Advisory Circular No. 25·571-1A (Damage tolerance and fatigue evaluation of structure) on 3/5/1986. This article describes one operator's viewpoint on the means to maintain the safety of aircraft structures in consideration of the revised structural fatigue evaluation standards.

著者

藤原 源吉

出版者

日本信頼性学会

雑誌

日本信頼性学会誌 : 信頼性 (ISSN:09192697)

巻号頁・発行日

vol.26, no.2, pp.130-139, 2004-04-01

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我が国の民間航空機の整備に信頼性管理方式を導入して以来,筆者は幾多の航空機事故に直面し,さまざまな信頼性管理の問題点を経験した.当解説は,これらの問題点はどこにあったのかを示し,反省すべき点の幾つかを指摘した.

著者

藤原 源吉

出版者

社団法人日本材料学会

雑誌

材料 (ISSN:05145163)

巻号頁・発行日

vol.45, no.1, pp.2-8, 1996-01-15

被引用文献数

13

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This article describes the findings of research for some recent transport airplane's accidents related to fatigue cracks. One is a B747SR's accident due to crack initiating at the fastener holes (to say Multiple-Site Damage). The other describes the crash of UAL's DC10-10 (N1819U), in Sioux City, Iowa, U.S.A., on July 19, 1989, which experienced a catastrophic failure of the No.2 tail-mounted engine during cruise flight. The third explains the in flight separation of the No.2 engine and engine pylon from B747-100F, shortly after departure from Anchorage International Airport, Anchorage, Alaska, on March 31, 1993. As a result of investigation for B747-100F's accident, National Transportation Safety Board made some important recommendations (One is to amend the design load requirements of Title 14 Code of Federal Regulations Part 25 to consider multiple axis loads encountered during severe turbulence) to the Federal Aviation Administration. Also, current aging airplane service data have identified that there are more cracked airplanes with increasing fleet edge, and possibly several fatigue cracks in some of the cracked airplanes. Especialy, MSD helped focus the attention of the aeronautical field on the problems of operating an aging transport airplanes. Therefore, FAA proposed to rivise the Advisory Circular No.25·571-1A (Damage tolerance and fatigue evaluation of structure) on 3/5/1986. This article describes one operator's viewpoint on the means to maintain the safety of aircraft structures in consideration of the revised structural fatigue evaluation standards.

著者

藤原 源吉

出版者

社団法人日本材料学会

雑誌

材料 (ISSN:05145163)

巻号頁・発行日

vol.43, no.493, pp.1188-1194, 1994-10-15

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Well Over 32 percent of the commercial air carrier fleet, worldwide, are beyond their original 20-year design life goal. In the past, 20-year old aircraft were most often replaced by newer aircraft for airline service. However, this is no longer true, and by the turn of the century, 64 percent of the current fleet will be at least 20 years old. This is because economic and market conditions have resulted in the use of commercial jet airplanes beyond their original economic design life objectives. As aircraft exceed their economic design life objectives, the incidence of fatigue increases and corrosion may become more widespread. The purpose of this paper is to discuss our experience with aging aircraft, the basic considerations of fracture mechanics treatment of cracks initiating at rivet holes(to say Multiple-Site Damage) and some problems due to fatigue cracks in aircraft components from the operators viewpoint.