Airworthiness directives › 2012-10-04
AD 2012-10-04 Airworthiness Directives; Cessna Aircraft Company Airplanes
Makes named: cessna. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
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.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
(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.
Unsafe condition
This AD was prompted by reports of cracks found in the wing lower main spar caps on the affected airplanes with cantilever metal wings. We are issuing this AD to prevent structural failure of the wing with consequent loss of control.
Affected ADs
None.
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1