Airworthiness Directive · Amendment 39-17053 · Wings
Cessna Aircraft Company Airplanes
This AD applies to the following Cessna model airplanes listed in paragraphs (c)(1) through (c)(13) of this AD, certificated in any category:
(1) 210G: Serial numbers (S/Ns) 21058819 through 21058936,
(2) T210G: S/Ns T210-0198 through T210-0307,
(3) 210H: S/Ns 21058937 through 21059061,
(4) T210H: S/Ns T210-0308 through T210-0392,
(5) 210J: S/Ns 21059062 through 21059199,
(6) T210J: S/Ns 21058140, and T210-0393 through T210-0454,
(7) 210K and T210K: S/Ns 21059200 through 21059502,
(8) 210L and T210L: S/Ns 21059503 through 21061041, and 21061043 through 21061573,
(9) 210M and T210M: S/Ns 21061042, 21061574 through 21062954,
(10) 210N and T210N: S/Ns 21062955 through 21064897,
(11) P210N: S/Ns P21000001 through P21000834,
(12) 210R and T210R: S/Ns 21064898 through 21065009, and
(13) P210R: S/Ns P21000835 through P21000874.
We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company Models 210G, T210G, 210H, T210H, 210J, T210J, 210K, T210K, 210L, T210L, 210M, T210M, 210N, T210N, P210N, 210R, T210R, and P210R airplanes. This AD requires an inspection(s) of the left and right wing lower main spar caps for cracks and either replacing cracked wing lower main spar caps, wing spars, or wings (as applicable) with serviceable spar caps, spars, or wings that are found free of cracks or incorporating an FAA-approved modification. This AD also requires reporting the results of the inspections to the FAA. This AD was prompted by reports of cracks found in the wing lower main spar caps on the above-referenced airplanes with cantilever metal wings. We are issuing this AD to correct the unsafe condition on these products.
(1) For airplanes with 10,000 hours time-in-service (TIS) or more as of June 5, 2012, (the effective date of this AD), do the following in accordance with Cessna Single Engine Service Letter SEL-57-01, Revision 1, dated May 9, 2012:
(i) Before further flight after June 5, 2012 (the effective date of this AD), do an external visual inspection of the outer skin underneath the main spar cap fitting between wing station (WS) 25.25 and WS 45.00 for cracks.
(ii) If no cracks are found during the inspection required in paragraph (g)(1)(i) of this AD, within the next 5 hours TIS after June 5, 2012 (the effective date of this AD), do an internal visual inspection of the wing lower main spar caps between WS 25.25 and WS 45.00 for cracks.
(2) For airplanes with 5,000 hours TIS or more, but less than 10,000 hours TIS as of June 5, 2012 (the effective date of this AD), within the next 25 hours TIS after June 5, 2012 (the effective date of this AD), do an internal visual inspection of the wing lower main spar caps between WS 25.25 and WS 45.00 for cracks in accordance with Cessna Single Engine Service Letter SEL-57-01, Revision 1, dated May 9, 2012.
(3) For airplanes with less than 5,000 TIS as of June 5, 2012 (the effective date of this AD), when the airplane reaches 5,000 hours TIS or within the next 25 hours TIS after June 5, 2012 (the effective date of this AD), whichever occurs later, do an internal visual inspection of the wing lower main spar caps between WS 25.25 and WS 45.00 for cracks in accordance with Cessna Single Engine Service Letter SEL-57-01, Revision 1, dated May 9, 2012.
If cracks are found during the inspections required in paragraphs (g)(1)(i), (g)(1)(ii), (g)(2), or (g)(3) of this AD, before further flight after the inspection in which cracks are found, either replace the cracked part (spar cap, wing spar, or wing, as applicable) with a serviceable part that is found free of cracks or modify the spar cap, wing spar, or wing (as applicable) following a procedure approved for this AD by the FAA, Wichita Aircraft Certification Office (ACO).
Within 10 days after each inspection or 10 days after June 5, 2012 (the effective date of this AD), whichever occurs later, report the results of the inspections to the FAA, Wichita ACO, Attn: Gary D. Park, Aerospace Engineer, 1801 Airport Road, Room 100; fax: (316) 946-4107; email: WICHITA-COS@FAA.GOV. Include the following information in addition to the undated Attachment (titled Wing Lower Main Spar Cap Inspection Report) to Cessna Single Engine Service Letter SEL-57-01, Revision 1, dated May 9, 2012. Please identify AD 2012-10-04 in the subject line if submitted through email.
(1) Hours TIS at time of inspection.
(2) Installed wing modifications.
(3) Approved gross weight increases.
(4) Extended low altitude operations (i.e., pipe line survey, surface spotting, sight-seeing, etc.)
(5) A description of any cracks detected.
This paragraph provides credit for the actions required in paragraphs (g) and (h) of this AD if already done before June 5, 2012 (the effective date of this AD) following Cessna Single Engine Service Letter SEL-57-01, dated April 27, 2012.
A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
