Ad-47-16-03

[baldeagle27]

Forrest, or anyone else- does anyone know the origin of AD 47-16-03, as below? Were there failures of the strut fittings on the fuselage? Has anybody found cracks or bad welds in recent years?

47-16-03 TAYLORCRAFT: (Was Mandatory Note 11 of AD-700-1: Mandatory Note 12 of AD-699-1; and Mandatory Note 13 of AD-696-3.) Applies to All Models BC, BF, and BL Series Aircraft.

Compliance required immediately.

Inspect wing strut attachment fittings on lower fuselage longerons for cracks or evidence of poor weld. If cracks or defects are found, the fitting should be replaced or reinforced.

[Big Daddy]

I would'nt think so. Never heard of any. If my math is right the AD is only 57 years old?

[Forrest Barber]

AD

It was explained me as I sat on my Daddy's knee that the effected airplanes were on floats and got tremendous pounding. Then he explained that they suspected that at the factory someone did not do a real good weld job & they got by inspection.... Soooo if you have not had a problem then you probably will not after these many years.....

[12victor]

Ad-47-16-03

Both fittings on my BL project, which has not flown for decades, have small cracks at the base of the forward finger. My options in order of preference are:

1. replace - does anyone know where I can find a pair of fittings? Some time back I recall Forrest saying something about plans for fabricating these fittings.

2. repair/reinforce: Does anyone have an example an acceptable repair?

Thanks,
-Al

[Robert Lees]

Al, could you take a digital photo for the archives?

A macro photo may be required to catch the small detail, this would be of use to the Foundation, and would be archived anonymously.

Best wishes,

Rob

[12victor]

Rob,

I am not able to get you a photo, but here is a simple sketch that shows the location.

These cracks were located on the top side of the fitting only. Not the bottom side

From what I could tell, it appears that forward stress on the finger from improper or inadvertant forward motion of the lift strut may have caused it.

-Al

[Lubeck]

I had a similar crack in one of my fittings. I had an aircraft welder repair it at my home. That was 15 years ago.

[Forrest Barber]

That type crack usually happens when somebody "wiggles" a strut back and forth trying to put them into place. Usually it happens on the rear when you allow a wing to swing back when removing and having the rear spar bolt in place and the front is removed and the wing swings bacl. OucHHH because that can take out the wing attach fitting too!!

[12victor]

I guess it is possible that this crack is unrealated to the AD. In its earlier life, this aircraft had flipped over onto its back. That would have put a lot of forward stress on the wings.

My current plan is to grid out the crack, reweld and then weld on a reinforcement strip.

-Al

[Forrest Barber]

In the early life that imposed a real negative load on the system. I hope the wing attach fittings and spar butts were really checked out good!!

[mhorowit]

Re: Ad-47-16-03

I guess it is possible that this crack is unrealated to the AD. In its earlier life, this aircraft had flipped over onto its back. That would have put a lot of forward stress on the wings.

My current plan is to grid out the crack, reweld and then weld on a reinforcement strip.

-Al

Al - so how did this go? How did you manage to weld inside the finger? "grind out the crack" means getting down to the last part of the fracture? How did you get into the fixture to grind? - Mike

[Guest]

Re: Ad-47-16-03

Both fittings on my BL project, which has not flown for decades, have small cracks at the base of the forward finger. My options in order of preference are:

1. replace - does anyone know where I can find a pair of fittings? Some time back I recall Forrest saying something about plans for fabricating these fittings.

2. repair/reinforce: Does anyone have an example an acceptable repair?

Thanks,
-Al

My BC12D was apart in '92 for repairs and I found cracks similar to yours on both fittings.

I made a sheet metal (4130) overlay that wrapped around the fitting. I made it by wrapping heavy brown paper round the fitting then cutting and trimming until I had a template that could be used to cut out sheet metal that would wrap around the entire fiitting as if I was laminating a second thickness of metal on it.

I cut out the metal and welded in place. Used mig and gas welding. Might use tig instead now.

I got a field approval at the time but not sure it was required. The fsdo sent it to Darrel Romick who was a der that worked for Taylorcraft for a sanity check. A feild approval was issued.

It is five pages long, I could scan it if there is interest.

Dave.

[mhorowit]

Re: Ad-47-16-03

It is five pages long, I could scan it if there is interest.
Dave.

If you don't mind, I'd like to see the description of the repair - Mike

[Guest]

Re: Ad-47-16-03

I guess it is possible that this crack is unrealated to the AD. In its earlier life, this aircraft had flipped over onto its back. That would have put a lot of forward stress on the wings.

My current plan is to grid out the crack, reweld and then weld on a reinforcement strip.

-Al

Three years too late I know!

I had similar cracks and I realized now that one thing in common is that both planes flipped. Mine flipped and that was why it was apart for repairs.

hmm