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Eight B787 pulled from service over structural issues

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Eight B787 pulled from service over structural issues

Old 27th Dec 2020, 16:20
  #101 (permalink)  
 
Join Date: Feb 2004
Location: kent, england
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Haven't read this entire thread, so forgive my possibly naive comment.

Airbus are built in a part of the world which is very regulated, and many of it's governments are centre left... So if a person on the production line, or in the engineering dept etc. sees a possible fault, or a short cut too far to increase profits over safety, they would have no problem with raising this issue up the chain of command.

If a similarly minded person raised a concern elsewhere around the globe, they may not dare raise a reasonable concern for fear or being demoted, sacked etc.

The company I work for has a totally open culture to reporting absolutely anything that might compromise safety.
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Old 1st Jan 2021, 09:30
  #102 (permalink)  
 
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Originally Posted by Dave Therhino View Post
According to the article, it's not a fatigue issue - it's an inability to withstand limit loads issue (so yes, at least a theoretical back end falling off issue). Due to improper shim thicknesses installed during joining of the sections, installation of the fasteners for the joint causes localized pull-up loads and stress to be introduced in the composite material at the highly stressed areas of the joint. The surface discontinuities then apparently add stress concentrations. The joint strength with these conditions is apparently insufficient to withstand one or more of the applicable design limit loads. I don't know what flight conditions set the most critical limit loads for the section 47/48 joint, but gust loads, engine failure on takeoff, and hard landing touchdown are likely candidates.
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Dave, why is EFATO included in the limit loads of that section. Just can't seem to get my mind around it...thanks in advance?
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Old 1st Jan 2021, 11:36
  #103 (permalink)  
 
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I had presumed it was because of the large compensatory rudder use creating unusually high lateral fuselage bending load between wing and tail.
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Old 1st Jan 2021, 15:21
  #104 (permalink)  
 
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Measure twice, cut once!
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Old 1st Jan 2021, 19:03
  #105 (permalink)  
 
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Pugilistic Animus

Again, I don't know exactly which load case is most critical for the joint in question, but lateral loads caused by the quick initial large movement of the rudder to compensate for assymetric thrust are one of the significant loads. I do know that in the past there was a fitting cracking issue on the 747 at the joint of the aft fuselage to the center wing section where the engine out case was the critical load case.
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Old 1st Jan 2021, 22:31
  #106 (permalink)  
 
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Ah yes, I now see how it may be possible during EFATO as a potential limiting case. Thank You Dave!
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Old 5th Jan 2021, 02:35
  #107 (permalink)  
 
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https://seekingalpha.com/article/439...ems-loom-large
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