Cessna 210 Wing Spar AD info

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1 month 2 weeks ago #1981 by Brian Garrett
That's interesting about the optional corrosion proof coating. I would think that information would be part of the sale notes - so in theory, we should be able to see if we already have the corrosion proofing on our spar? We're an M model.

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1 month 2 weeks ago #1980 by STEVE ELLS
Paolo; After talking to the FAA and very experienced 210 maintenance experts, I learned that removal of the corrosion inhibiting coating (CIC)--typically zinc chromate primer--is not required prior to the visual inspection.

This means that the FAA has decided that a previously applied CIC is not a sufficient reason to not comply with the AD.

You can comment to the AD; the address and reference number is included in my original post in this thread.

Best,
Steve

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1 month 2 weeks ago #1978 by PAOLO MONTANARI
being aware of the AD I note that the reason to exclude the model from N on is because they are corrosion proof coated by factory.
Many Aircraft before the N model exited the factory with optional corrosion proof coating (mine included T210M dtd 1977). I wander if anybody evidenced that to the FAA or will do it.
Being the reason of corrosion proof to exclude the aicraft from the AD accomplishement, I think interesting to note it to FAA.
For me it would be extremely difficult to speak with FAA as I am from Italy .I think that some association or expert who knows FAA can have better chances of success and avoid FAA to be submerged by single case letters.

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1 month 2 weeks ago - 1 month 2 weeks ago #1977 by Kent Dellenbusch
Steve Ells is sharing this information about the new Cessna 210 wing spar AD

FAA releases Airworthiness Directive on Cessna 210 Wing Spar Carry through Structure.
By Steve Ells
The FAA issued an Airworthiness Directive (AD) mandating a visual inspection and an eddy current inspection on the lower surface of the wing spar carry-through structure casting The AD number is AD 2020-03-16.
Cessna Flyer readers can view the entire content of the AD by going to www.regulations.gov and entering “FAA-2020-0156” in the search window.
The following is from the AD:
“SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all Textron Aviation Inc. (Textron) (type certificate previously held by Cessna Aircraft Company) Models 210G, T210G, 210H, T210H, 210J, T210J, 210K, T210K, 210L, T210L, 210M, and T210M airplanes. This AD requires visual and eddy current inspections of the carry-thru spar lower cap, corrective action if necessary, application of a protective coating and corrosion inhibiting compound (CIC), and reporting the inspection results to the FAA.”
As many owners of cantilever wing structure (ones without wing struts) Cessna 210s know, a fatal Australian Cessna 210 crash on May 26, 2019 occurred after the right wing separated from the airplane.
The initial investigation showed that the wing spar carry through casting structure of the Australian 210 failed due to fatigue cracking that was initiated from a corrosion pit measuring 0.011 inches deep.
On Nov. 1, 2019 Cessna issued Service Letter SEL-57-08, that directed owners to open the headliner for access, then to visually inspect the entire surface of the carry-through structure. Owners were requested (manufacturer’s service letters are not mandatory) to send Textron Aviation (the present owner of the Cessna 210 Type Certificate Data Sheet and support) information describing the results of the inspections. The Service Letter was revised and updated the service letter; it’s now SEL-57-08 R1.
The reports received by Textron Aviation from inspections of the affect 210 series airplanes have revealed significant and widespread corrosion of the spar carry-through structure.
The following paragraph describes the findings:
“As of January 29, 2020, Textron has received 194 inspection reports on Models 210G, T210G, 210H, T210H, 210J, T210J, 210K, T210K, 210L, T210L, 210M, and T210M airplanes. Of these 194 reports, 96 airplanes have reported corrosion (49 percent) with 18 of those reports (9 percent) resulting in removing the carry-thru spar from service. The corrosion observed included several instances of exfoliation corrosion and stress corrosion cracking. The FAA has determined that the large number of corrosion reports and the severity of the corrosion identified on a critical single load path part necessitate issuance of an immediately adopted rule.
Based on the data in the inspection reports, the FAA issued the AD without a Notice of Proposed Rule Making (NPRM). This process is used when data supports an immediate response; it’s called a Direct to Final Rule issuance.
The AD mandates that visual and eddy current inspections be completed by April 21, 2020
The compliance window for the AD is much shorter than the window for complying with the Cessna Service Letters. The Service Letter specified a 12-month window from the date of issuance to complete the inspection; the AD mandates a 60-day window.
The AD not only shortens that inspection window to 60 days from the issuance of the AD, it also mandates that both a visual inspection and an eddy current inspection be completed within the 60-day window of all sections where corrosion has been found.
The AD also requires owners to submit a report of the findings of the visual inspection and the eddy current inspection. The FAA will use the information from the reports. Here’s what the AD says, “The FAA will use the results of the one-time eddy current inspection of the lower cap kick area, in part, to determine the necessity of future rulemaking action.”
Interim Action
“The FAA considers this AD interim action. This AD requires a one-time visual inspection of specified areas on the carry-thru spar lower cap and an eddy current inspection of the lower cap kick area and any locations where corrosion was removed. This AD also requires reporting the inspection results to the FAA. The FAA will analyze the inspection results received to determine further rulemaking action. “

Owners that have completed the visual and eddy current inspection and have found no defects, or been advised by Cessna that the material removed to clean up existing corrosion does not render the part unairworthy, have 12 months from the completion of the inspection to apply a corrosion inhibiting coating (CIC).
Even though the AD was issued, the FAA is requesting that interested individuals and companies submit comments after reviewing the AD Go to www.regulations.gov . Follow the instructions for submitting comments. Search for Docket No. FAA-2020-0156.
The 60-day window for completion of the inspections closes on April 21, 2020. Textron issued Service Letter SEL-20-01 on October 7, 2014. This 17-page bulletin lists certified eddy current inspection facilities recognized by Cessna.

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Last edit: 1 month 2 weeks ago by Kent Dellenbusch.

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