2023-02-17: Fuselage Main, Structure

1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. 2. The FAA amends § 39.13 by adding the following new airworthiness directive: 2023-02-17 Textron Aviation Inc. (Type Certificate previously held by Cessna Aircraft Company): Amendment 39-22324; Docket No. FAA-2020-1078; Project Identifier AD-2020-00716-A. (a) Effective Date This airworthiness directive (AD) is effective March 20, 2023. (b) Affected ADs None. (c) Applicability This AD applies to Textron Aviation Inc. (Type Certificate previously held by Cessna Aircraft Company) Model 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 cracking, 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. (g) Visual Inspection Within 200 hours time-in-service (TIS) after the effective date of this AD or within 12 calendar 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, SEL-57-08, Revision 2, dated August 3, 2020 (Textron SEL-57-08R2); or Textron Aviation Mandatory Single Engine Service Letter, SEL-57-09, Revision 1, dated August 3, 2020 (Textron SEL-57-09R1), 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, cracking, 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 Textron SEL-57-08R2 or Textron SEL-57-09R1, as applicable to your airplane model, for the location of the specific spar features. (1) If there is any cracking, 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 carry-thru spar from service or repair the area using a method approved as specified in paragraph (n) 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 Textron SEL-57-08R2 or Textron SEL-57-09R1, 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 Textron SEL-57-08R2 or Textron SEL-57-09R1, 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 (n) 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 Textron SEL-57-08R2 or Textron SEL-57-09R1, 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, cracking, or damage and there is no evidence of previous removal of corrosion, comply with the requirements in paragraph (h) of this AD within 200 hours TIS after the effective date of the AD or within 12 calendar months after the effective date of the AD, whichever occurs first. (h) Eddy Current Inspection (1) At the applicable compliance time required by paragraph (g) of this AD, complete an eddy current inspection of the carry-thru spar lower cap for cracking, corrosion, and damage in the following areas in accordance with step 7 of the Accomplishment Instructions in Textron SEL-57-08R2 or Textron SEL-57-09R1, as applicable to your airplane model. (i) The kick area as depicted in the 'Spar Dimensions' figure on page 7 of Textron SEL-57-08R2 or Textron SEL-57-09R1, 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 any cracking, 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 (n) 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 (g)(3) 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 calendar 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 Textron SEL-57-08R2 or Textron SEL-57-09R1, 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 Textron SEL-57-08R2 or Textron SEL-57-09R1, as applicable to your airplane model. (l) Credit for Previous Actions (1) You may take credit for the visual inspection and corrosion removal required by paragraph (g) of this AD if you performed the visual inspection and corrosion removal before the effective date of this AD using Textron Aviation Mandatory Single Engine Service Letter SEL-57-08, dated November 1, 2019 (Textron SEL-57-08); Textron Aviation Mandatory Single Engine Service Letter SEL-57-08, Revision 1, dated November 19, 2019 (Textron SEL-57-08R1); Textron Aviation Mandatory Single Service Letter SEL-57-09, dated November 19, 2019 (Textron SEL-57-09); Textron Aviation Mandatory Single Engine Service Letter SEL-57-06, dated June 24, 2019 (Textron SEL-57-06); Textron Aviation Mandatory Single Engine Service Letter SEL-57-06, Revision 1, dated November 19, 2019 (Textron SEL-57-06R1); Textron Aviation Mandatory Single Engine Service Letter, SEL-57-07, dated June 24, 2019 (Textron SEL-57-07); or Textron Aviation Mandatory Single Engine Service Letter, SEL-57-07, Revision 1, dated November 19, 2019 (Textron SEL-57-07R1). (2) You may take credit for the eddy current inspection of the lower cap kick area and all locations where corrosion was removed on the carry-thru spar lower cap and the corrosion removal as specified in paragraph (h) of this AD if you performed the eddy current inspection and corrosion removal required before the effective date of this AD using Textron SEL-57-08, Textron SEL-57-08R1, Textron SEL-57-06, Textron SEL-57-06R1, Textron SEL-57-07, Textron SEL-57-07R1, or Textron SEL-57-09. (3) You may take credit for the corrosion protection required by paragraph (i) of this AD if you performed those actions before the effective date of this AD using Textron SEL-57-08, Textron SEL-57-08R1, or Textron SEL-57-09. (4) To take credit for any previous action, you must have provided a completed Carry-Thru Spar Inspection Report, an attachment to Textron SEL-57-06, Textron SEL-57-06 R1, Textron SEL-57-07, Textron SEL-57-07R1, Textron SEL-57-08, Textron SEL-57-08R1, or Textron SEL-57-09 to Textron Aviation Inc. before the effective date of this AD, or you must comply with paragraph (k) of this AD within 30 days after the effective date of this AD. (m) Special Flight Permit (1) This AD prohibits a special flight permit if the inspection identifies cracking in the carry-thru spar. (2) Special flight permits, as described in 14 CFR 21.197 and 21.199, may be issued for airplanes on which corrosion was identified to operate to a location where the requirements of this AD can be accomplished. (3) Special flight permits, as described in 14 CFR 21.197 and 21.199, may be issued for an airplane demonstrating evidence of previous blending for which credit for previous actions, as defined in paragraph (l), cannot be granted or for an airplane demonstrating any damage other than corrosion or cracking, but concurrence by the Manager, Wichita ACO Branch, FAA is required before issuance of the special flight permit. Send requests for a special flight permit to your local Flight Standards District Office. (n) Alternative Methods of Compliance (AMOCs) (1) The Manager, Wichita ACO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (o) of this AD. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by a Textron Aviation, Inc. Unit Member (UM) of the Textron Organization Designation Authorization (ODA), that has been authorized by the Manager, Wichita ACO Branch, to make those findings. To be approved, the repair, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (o) Related Information For more information about this AD, contact Bobbie Kroetch, Aviation Safety Engineer, Wichita ACO Branch, FAA, 1801 Airport Road, Wichita, KS 67209; phone: (316) 946-4155; email: bobbie.kroetch@faa.gov or Wichita-COS@faa.gov . (p) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Textron Aviation Mandatory Single Engine Service Letter, SEL-57-08, Revision 2, dated August 3, 2020. (ii) Textron Aviation Mandatory Single Engine Service Letter, SEL-57-09, Revision 1, dated August 3, 2020. (3) For service information identified in this AD, contact Textron Aviation Inc., One Cessna Boulevard, Wichita, KS 67215; phone: (316) 517-6061; email: structures@txtav.com; website: support.cessna.com. (4) You may view this service information at FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, MO 64106. For information on the availability of this material at the FAA, call (817) 222-5110. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email: fr.inspection@nara.gov, or go to: www.archives.gov/federal-register/cfr/ibr-locations.html. Issued on February 1, 2023. Christina Underwood, Acting Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2023-02986 Filed 2-10-23; 8:45 am]BILLING CODE 4910-13-P