Piper Spar NDI - Performing AD 2020-26-16
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- Опубліковано 18 бер 2021
- Bill show what it takes to perform AD AD 2020-26-16 and SB 1345
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Will be nice to see the reinstalling of the bolts.... good info..
bolts ccome out easier then I expected ,good to know
Not too bad. The last one was a bit stubborn. Thanks for watching!
Hey really interesting!
Does exists another way to inspect the area? In El Salvador we don't have Eddy current tester in the whole country!
These folks are the Olympus eddy current equipment representatives for El Salvador. Hopefully they can help you out.
METAL-MET USA, CORP
8285 NW, 64th St., Unit 8.
Miami, Florida 33166
USA
Tel: +1 7863505404
Fax: +1 3057162882
info@metalmetusa/com
Go to: www.olympus-ims.com/en/ec-flaw/
and send them a message also. Hope this helps! Thanks for watching!
What a great video…this is it??? I thought you had to take the wing completely off that’s primarily why we didn’t do that for our 75 arrow 2. This is good news, even though we aren’t even close to factored hours on our arrow it’s be nice just for peace of mind.
Thanks for watching! Appreciate the comments!
What’s Apex charge for their NDI? Thanks for posting!
$450. Thanks for watching!
how did you re-install the bolts after you knocked them out..did you cut an access panel ???
No additional access panel required. Just reach through the spar in the cabin and install bolts as the factory did when the wing was installed originally.
@@HangaRatz Did they go in easy? Did you have to lube them before installing?
Does Piper pay for the AD to be complied with since it’s technically a manufacturer defect? Just cautious as I’m looking to purchasing a Piper Archer.
Short answer is no. Corrosion is not a design or manufacturer's defect. And the aircraft have a stated warranty when new anyway. Have a thorough pre-buy accomplished prior to any purchase. Thanks for watching!
What do you mean when you say "Factored" hours?
There is a formula to derive factored hours in the AD and Piper service bulletin. We have another video that explains it all! Thanks for watching!
Watch out for the washer SNAFU?
Which one is that?
@@HangaRatz Apparently Piper had a washer problem and some were sent out that weren’t beveled on one side. The beveled side has to be to the spar under the bolt head to prevent damaging the spar. If all is true it possibly might create a new AD for those that have had the inspection or wing bolts removed.
Hammering out the bolts is a big no-no!
What is your method?
And just how would you remove them? You could do a jack from underneath, although that would probably add more stress. The vibration from the tapping will remove the micro corrosion from around the bolts. I guess to do it absolutely perfect, replace the bolts after removing. But I'm sure they are much stronger than they need to be.
@@HangaRatz The AD says do not drive bolts out.
I wouldn't accept that inspection. Fastener hole inspections should be calibrated with a proper hole calibration block, not a flat notch block. I have never seen an aircraft EC procedure that allows a fastener hole inspection done with a flat block.
You are correct. That was cut in after we inspected the spar. The standard that we used for this demonstration was just a generic block to illustrate the test set indication versus a piece of aluminum that appeared to be "flawless"... ...at least in 1080dpi.... The magic of post production. Thanks for watching!