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Federal Register / Vol. 86, No. 89 / Tuesday, May 11, 2021 / Proposed Rules
3 Would not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:

Authority: 49 U.S.C. 106g, 40113, 44701.
39.13

Amended
2. The FAA amends 39.13 by adding the following new airworthiness directive:

Textron Aviation Inc. Type Certificate previously held by Cessna Aircraft Company: Docket No. FAA20201078;
Project Identifier AD202000716A.
a Comments Due Date The FAA must receive comments on this airworthiness directive AD by June 25, 2021.
b Affected ADs None.
c Applicability This AD applies to Textron Aviation Inc.
Type Certificate previously held by Cessna Aircraft Company Models 210N, 210R, P210N, P210R, T210N, T210R, 177, 177A, 177B, 177RG, and F177RG airplanes, all serial numbers, certificated in any category.
d Subject Joint Aircraft System Component JASC
Code 5310, Fuselage Main, Structure.
e Unsafe Condition This AD was prompted by the in-flight break-up of a Model T210M airplane, due to fatigue cracking of the carry-thru spar that initiated at a corrosion pit and subsequent corrosion reports on other Model 210-series and Model 177-series airplanes. The FAA is issuing this AD to detect and correct cracks, corrosion, and other damage of the carry-thru spar lower cap, which, if not corrected, could lead to the carry-thru spar being unable to support the required structural loads and could result in separation of the wing and loss of airplane control.
f Compliance Comply with this AD within the compliance times specified, unless already done.

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g Visual Inspection Within 200 hours time-in-service TIS
after the effective date of this AD or within 12 months after the effective date of this AD, whichever occurs first, prepare the carry-thru spar lower cap for inspection by following steps 4 and 5 of the Accomplishment Instructions in Textron Aviation Mandatory Single Engine Service Letter, SEL5708, Revision 2, dated August, 3, 2020 SEL57
08R2 or Textron Aviation Mandatory Single Engine Service Letter, SEL5709, Revision 1, dated August, 3, 2020 SEL5709R1, as applicable to your airplane model. Visually inspect the carry-thru spar lower cap including the lower surface, upper surface, and edge with a 10X magnification lens looking for corrosion, cracks, and damage.
You are not required to inspect the lower cap to web radius, spar web, upper cap, or lugs.
Refer to the Spar Dimensions and the Spar Detail figures on page 7 of SEL5708R2 or SEL5709R1, as applicable to your airplane model, for the location of the specific spar features.
1 If there is a crack, before further flight, remove the carry-thru spar from service.
2 If there is damage or evidence of previous removal of corrosion blending, before further flight, either remove the carrythru spar from service or repair the area using a method approved as specified in paragraph o of this AD. Comply with the requirements in paragraph h of this AD before further flight.
3 If there is any corrosion, before further flight, remove the corrosion in the affected area by following steps 6.B.1 through 7 of the Accomplishment Instructions in SEL57
08R2 or SEL5709R1, as applicable to your airplane model, and then mechanically measure the depth of the blended area using a straight edge and feeler gauge or a depth gauge micrometer.
i If the material removed in the blended area exceeds the allowable blend limits specified in table 1 including the notes of SEL5708R2 or SEL5709R1, as applicable to your airplane model, before further flight, either remove the carry-thru spar from service or repair the area using a method approved as specified in paragraph o of this AD. Comply with the requirements in paragraph h of this AD before further flight.
ii If the material removed in the blended area does not exceed the allowable blend limits specified in table 1 including the notes of SEL5708R2 or SEL5709R1, as applicable to your airplane model, comply with the requirements in paragraph h of this AD before further flight.
4 If the visual inspection did not detect corrosion, cracks, or damage and there is no evidence of previous removal of corrosion, comply with the requirements in paragraph h of this AD before further flight.
h Eddy Current Inspection 1 Complete an eddy current inspection of the carry-thru spar lower cap for cracks, corrosion, and damage in the following areas in accordance with step 7 of the Accomplishment Instructions in SEL57
08R2 or SEL5709R1, as applicable to your airplane model.
i The kick area as depicted in the Spar Dimensions figure on page 7 of SEL57

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08R2 or SEL5709R1, as applicable to your airplane. You must complete an eddy current inspection of the lower cap kick area of your airplane regardless of whether corrosion was found and removed as a result of the visual inspection in paragraph g of this AD.
ii All areas where corrosion was found and removed as a result of the inspection in paragraph g of this AD.
2 If there is a crack, before further flight, remove the carry-thru spar from service.
3 If there is any damage, before further flight, either remove the carry-thru spar from service or repair the area using a method approved as specified in paragraph o of this AD. After completing the repair, repeat the eddy current inspection of the repaired area before further flight.
4 If there is any corrosion, before further flight, remove the corrosion by following the requirements in paragraph g3 of this AD.
You must repeat the eddy current inspection and comply with paragraph h of this AD for the area where the additional material was removed, but you do not have to repeat the eddy current inspection of the kick area.
i Corrosion Protection Within 12 months after the effective date of this AD, apply protective coating and corrosion inhibiting compound CIC by following steps 9 and 10 of the Accomplishment Instructions in SEL57
08R2 or SEL5709R1, as applicable to your airplane model.
j Installation Prohibition As of the effective date of this AD, do not install on any airplane a carry-thru spar unless it has been inspected as required by paragraphs g and h of this AD and corrosion protection applied as required by paragraph i of this AD.
k Reporting Requirement Within 30 days after completing the inspections required by this AD or within 30
days after the effective date of this AD, whichever occurs later, report to the FAA by email Wichita-COS@faa.gov all information requested in the Carry-Thru Spar Inspection Report Attachment to SEL5708R2 or SEL
5709R1, as applicable to your airplane model.
l Credit for Previous Actions 1 You may take credit for the visual inspection required by paragraph g of this AD if you performed the visual inspection before the effective date of this AD using Textron Aviation Mandatory Single Engine Service Letter SEL5708, dated November 1, 2019 SEL5708; Textron Aviation Mandatory Single Engine Service Letter SEL
5708, Revision 1, dated November 19, 2019
SEL5708R1; Textron Aviation Mandatory Single Service Letter SEL5709, dated November 19, 2019 SEL5709; Textron Aviation Mandatory Single Engine Service Letter SEL5706, dated June 24, 2019 SEL
5706; Textron Aviation Mandatory Single Engine Service Letter SEL5706, Revision 1, dated November 19, 2019 SEL5706R1;
Textron Aviation Mandatory Single Engine Service Letter, SEL5707, dated June 24, 2019 SEL5707; or Textron Aviation Mandatory Single Engine Service Letter,
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