2020-18-01: Fuselage

Adoption of the Amendment \n\n\n\tAccordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: \n\nPART 39--AIRWORTHINESS DIRECTIVES \n\n0 1. The authority citation for part 39 continues to read as follows: \n\n\n\tAuthority: 49 U.S.C. 106(g), 40113, 44701. \n\n\n\nSec. 39.13 (Amended) \n\n0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): \n\n2020-18-01 Textron Aviation Inc.: Amendment 39-21222; Docket No. FAA 2018-0049; Product Identifier 2017-CE-031-AD. \n\n(a) Effective Date \n\n\n\tThis AD is effective November 12, 2020. \n\n(b) Affected ADs \n\n\n\tNone. \n\n(c) Applicability \n\n\n\tThis AD applies to the following Textron Aviation Inc. (type certificate previously held by Cessna Aircraft Company) model airplanes, certificated in any category: BILLING CODE 4910-13-P \n\n((Page 63198)) \n\n(GRAPHIC) (TIFF OMITTED) TR07OC20.000 \n\n\n\n((Page 63199)) \n\n\n\n(GRAPHIC) (TIFF OMITTED) TR07OC20.001 \n\nBILLING CODE 4910-13-C \n\n(d) Subject \n\n\n\tJoint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 53, Fuselage. \n\n(e) Unsafe Condition \n\n\n\tThis AD was prompted by a report of cracks found in the lower area of the forward cabin doorpost bulkhead. The FAA is issuing this AD to detect and address cracking of the wing strut attach point. The unsafe condition, if not addressed, could result in failure of the wing in operation, which could result in loss of control of the airplane. \n\n(f) Compliance \n\n\n\tComply with this AD within the compliance times specified, unless already done. \n\n(g) Initial Inspections \n\n\n\t(1) For airplanes without a lower forward doorpost bulkhead and wing strut fitting reinforcement service kit (service kit) installed in accordance with Cessna Single Engine Service Bulletin SEB95-19, dated December 29, 1995 (SEB95-19), or Cessna Single Engine Service Bulletin SEB93-5, Revision 2, dated May 29, 2019 (SEB93-5R2): At the applicable compliance time specified in paragraph (g)(1)(i) or (ii) of this AD, do a visual inspection of the lower forward doorpost at the strut attach fitting for cracks in accordance with steps 1.A., 1.B., 1.C., and 1.B. (the step following step 1.C.) of the Accomplishment Instructions in SEB95-19; or steps 1.A. and 1.B. of the Accomplishment Instructions in SEB93-5R2; as applicable to your model airplane. \n\t(i) For airplanes that have accumulated less than 4,000 hours time-in-service (TIS) as of the effective date of this AD: Initially inspect prior to the accumulation of 4,000 hours TIS or within the next 200 hours TIS after the effective date of this AD, whichever occurs later. \n\t(ii) For airplanes that have accumulated 4,000 or more hours TIS as of the effective date of this AD: Initially inspect within 200 hours TIS after the effective date of this AD or within 12 calendar months after the effective date of this AD, whichever occurs first. \n\t(2) For airplanes with a service kit installed in accordance with SEB95-19 or SEB93-5R2: At the later of the times specified in paragraphs (g)(2)(i) and (ii) of this AD, do a visual inspection of the lower forward doorpost at the strut attach fitting for cracks in accordance with steps 1.A., 1.B., 1.C., and 1.B. (the step following step 1.C.) of the Accomplishment Instructions in SEB95-19; or steps 1.A. and 1.B. of the Accomplishment Instructions in SEB93-5R2; as applicable to your model airplane. Do not remove the installed service kit; instead, inspect for cracking that extends beyond the modified parts. \n\t(i) At the applicable time specified in paragraph (g)(1)(i) or (ii) of this AD. \n\t(ii) Within 1,000 hours TIS or 36 calendar months, whichever occurs first, since installing the service kit. \n\n(h) Repetitive Inspections \n\n\n\t(1) If no cracks are found during the initial inspection required by paragraph (g)(1) or (2) of this AD, thereafter repeat the inspection at intervals not to exceed 36 calendar months or 1,000 hours TIS, whichever occurs first from the last inspection, as long as no cracks are found. \n\t(2) If cracks are found during any inspection required by paragraph (g)(1) or (h)(1) of this AD, do the inspection specified in paragraph (g)(2) of this AD within 36 calendar months or 1,000 hours TIS, whichever occurs first after installing the service kit required by paragraph (i)(1) of this AD. Thereafter, repeat the inspection at intervals not to exceed 36 calendar months or 1,000 hours TIS, whichever occurs first from the last inspection, as long as no additional cracks are found. \n\n(i) Corrective Actions \n\n\n\t(1) If cracks are found during any inspection required by paragraph (g)(1) or paragraph (h)(1) of this AD, before further flight, install a service kit in accordance with step 1.D. of the Accomplishment Instructions in SEB95-19; or step 1.C. of the Accomplishment Instructions in SEB93-5R2; as applicable to your model airplane. \n\t(2) If cracks are found during anyinspection required by paragraph (g)(2) or (h)(2) of this AD, before further flight, repair the area using a method approved by the Manager, Wichita ACO Branch, FAA. For a repair method to be approved by the Manager, Wichita ACO Branch as required by this paragraph, the Manager's approval letter must specifically refer to this AD. You may use the contact information in paragraph (n)(1) of this AD to obtain FAA approval of your repair method. \n\n(j) Reporting Requirement \n\n\n\tWithin 30 days after the effective date of this AD, or within 30 days after completing the initial inspection required by paragraph (g) of this AD, whichever occurs later, report the findings of the initial inspection (regardless if cracks were found or not) to the FAA at Wichita-COS@faa.gov. Thereafter, within 30 days after completing each repetitive inspection required by paragraph (h) of this AD, if any crack was found, report the crack findings to the FAA at Wichita-COS@faa.gov. Include in your reports the following information: \n\n((Page 63200)) \n\n\n\t(1) Name and address of the owner; \n\t(2) Date of the inspection; \n\t(3) Name, address, telephone number, and email address of the person submitting the report; \n\t(4) Airplane serial number and total hours TIS on the airplane at the time of the inspection; and \n\t(5) If any crack was found during the inspection, provide detailed crack information as specified below: \n\t(i) A sketch or picture detailing the crack location; \n\t(ii) Measured length of the crack(s) found; \n\t(iii) Installation of a Cessna service kit or any other kit or repair before the inspection; and \n\t(iv) Installation of any supplemental type certificates (STCs), alterations, repairs, or field approvals affecting the area of concern or affecting gross weight. \n\n(k) Credit for Previous Actions \n\n\n\t(1) You may take credit for the initial inspection required by paragraph (g) of this AD if you performed the inspection before the effective date of this AD using CessnaSingle Engine Service Bulletin SEB93-5, dated March 26, 1993; or Cessna Single Engine Service Bulletin SEB93-5, Revision 1, dated September 8, 1995. \n\t(2) You may take credit for the installation required by paragraph (i)(1) of this AD as follows. \n\t(i) For Model 207, T207, 207A, and T207A airplanes with a service kit installed using SK206-42, SK206-42A, SK206-42B, or SK206-42C: You may take credit for the installation if done before the effective date of this AD using Cessna Single Engine Service Bulletin SEB93-5, dated March 26, 1993, or Cessna Single Engine Service Bulletin SEB93-5, Revision 1, dated September 8, 1995; if the reinforcement of the lower forward doorpost bulkhead and wing strut fitting specified in Cessna Single Engine Service Kit SK207- 19A, dated May 29, 2019, is also accomplished within 200 hours TIS after the effective date of this AD. \n\t(ii) For all other models: You may take credit for the installation if done before the effective date of this AD using CessnaSingle Engine Service Bulletin SEB93-5, dated March 26, 1993; or Cessna Single Engine Service Bulletin SEB93-5, Revision 1, dated September 8, 1995. \n\n(l) Paperwork Reduction Act Burden Statement \n\n\n\tA 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 1 hour 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. \n\n(m) Alternative Methods of Compliance (AMOCs) \n\n\n\t(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 (n)(1) of this AD. \n\t(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. \n\n(n) Related Information \n\n\n\t(1) For more information about this AD, contact Bobbie Kroetch, Aerospace Engineer, Wichita ACO Branch, 1801 Airport Road, Room 100, Wichita, Kansas67209; telephone: (316) 946-4155; fax: (316) 946- 4107; email: bobbie.kroetch@faa.gov or Wichita-COS@faa.gov. \n\t(2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(3) and (4) of this AD. \n\n(o) Material Incorporated by Reference \n\n\n\t(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. \n\t(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. \n\t(i) Cessna Single Engine Service Bulletin SEB93-5, Revision 2, dated May 29, 2019. \n\t(ii) Cessna Single Engine Service Bulletin SEB95-19, dated December 29, 1995. \n\t(3) For service information identified in this AD, contact Textron Aviation Inc., Textron Aviation Customer Service, One Cessna Blvd., Wichita, Kansas 67215; telephone: (316) 517-5800; email: customercare@txtav.com; internet: https://support.cessna.com. \n\t(4) You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329-4148. \n\t(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 fedreg.legal@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html. \n\n\n\tIssued on August 24, 2020. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. (FR Doc. 2020-22039 Filed 10-6-20; 8:45 am) BILLING CODE 4910-13-P