2024-16-01: Fuselage 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: a. Removing Airworthiness Directive 2000-18-09, Amendment 39-11894 (65 FR 55175, September 13, 2000); and b. Adding the following new airworthiness directive: 2024-16-01 Bell Textron Inc. (Type Certificate previously held by Bell Helicopter Textron, Inc.): Amendment 39-22807; Docket No. FAA-2024-2010; Project Identifier AD-2024-00366-R. (a) Effective Date This airworthiness directive (AD) is effective September 4, 2024. (b) Affected ADs This AD replaces AD 2000-18-09, Amendment 39-11894 (65 FR 55175, September 13, 2000). (c) Applicability This AD applies to Bell Textron Inc. (type certificate previously held by Bell Helicopter Textron, Inc.), Model 205A, 205A-1, 205B, 212, 412, 412CF, and 412EP helicopters, certificated in any category, identified in paragraphs (c)(1) and (2) of this AD. (1) Model 205A, 205A-1, and 205B helicopters, with an upper left-hand cap angle (cap angle) part number (P/N) 205-030-207-005 installed. (2) Model 212, 412, 412CF, and 412EP helicopters, with a cap angle P/N 212-030-191-001 installed. (d) Subject Joint Aircraft System Component (JASC) Code: 5300, Fuselage structure. (e) Unsafe Condition This AD was prompted by reports of a fatigue crack in a tail boom attachment cap angle. The FAA is issuing this AD to prevent failure of a cap angle. The unsafe condition, if not addressed, could result in failure of the fuselage and bulkhead, and subsequent separation of the tail boom and loss control of the helicopter. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) For Model 205A, 205A-1, 205B, 212, 412CF, and 412 helicopters identified in paragraph (c) of this AD; and for Model 412EP helicopters identified in paragraph (c)(2) of this AD with serial numbers 36087 through 36693 inclusive, within 25 hours time-in-service (TIS) after the effective date of this AD, and thereafter at intervals not to exceed 25 hours TIS; and for Model 412EP helicopters identified in paragraph (c)(2) of this AD with serial numbers 36694 through 36999 inclusive and 37002 through 37999 inclusive, within 50 hour TIS after the effective date of this AD, and thereafter at intervals not to exceed 50 hours TIS, accomplish the actions required by paragraphs (g)(1)(i) and (ii) of this AD. (i) Visually inspect for the presence of sealant around the forward edge of the left-hand tail boom cap angle fitting in the "Inspection Area" depicted in Figure 1., of Bell Alert Service Bulletin (ASB) 205-24-122, Bell ASB 205B-24-77, Bell ASB 212-24-169, Bell ASB 412-24-197, or Bell ASB 412CF-24-77, all dated April 22, 2024, as applicable to your model helicopter. If there is any sealant, before further flight, remove any sealant by following the Accomplishment Instructions, paragraph 2., of Bell ASB 205-24-122, Bell ASB 205B-24-77, Bell ASB 212-24-169, Bell ASB 412-24-197, or Bell ASB 412CF-24-77, all dated April 22, 2024, as applicable to your model helicopter. (ii) Using a 10X or higher power magnifying glass and flashlight, visually inspect the cap angle and adjacent structure for a crack in the "Inspection Area" depicted in Figure 1., of Bell ASB 205-24-122, Bell ASB 205B-24-77, Bell ASB 212-24-169, Bell ASB 412-24-197, or Bell ASB 412CF-24-77, all dated April 22, 2024, as applicable to your model helicopter. (A) If there is any crack in the cap angle, before further flight, remove the cap angle from service and install an airworthy cap angle. (B) If there is any crack in the adjacent structure, before further flight, repair the structure in accordance with a method approved by the Manager, Central Certification Branch, FAA. For a repair method to be approved by the Manager, Central Certification Branch, FAA; as required by this paragraph, the Manager's approval letter must specifically refer to this AD. (2) If there is a crack as a result of any instance of an inspection required by paragraph (g)(1)(ii) of this AD, within 10 days after completing the inspection, report the information in Appendix 1 to this AD by email to OperationalSafety@faa.gov. (h) Special Flight Permit Special flight permits may be issued in accordance with 14 CFR 21.197 and 21.199 to operate the helicopter to a location where the actions required by this AD can be performed, provided after takeoff, the flight is straight and level until landing, and avoids areas of known turbulence and provided no passengers are onboard. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Central Certification 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 (j) of this AD. Information may be emailed to: AMOC@faa.gov . (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. (j) Related Information For more information about this AD, contact Hung Nguyen, Aviation Safety Engineer, FAA, 1801 S Airport Road, Wichita, KS 67209; phone: (562) 627-5362; email: hung.v.nguyen@faa.gov . (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the material listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this material as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Bell Alert Service Bulletin (ASB) 205-24-122, dated April 22, 2024. (ii) Bell ASB 205B-24-77, dated April 22, 2024. (iii) Bell ASB 212-24-169, dated April 22, 2024. (iv) Bell ASB 412-24-197, dated April 22, 2024. (v) Bell ASB 412CF-24-77, dated April 22, 2024. (3) For Bell material identified in this AD, contact Bell Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; phone: (450) 437-2862 or (800) 363-8023; fax: (450) 433-0272; email: productsupport@bellflight.com; website: bellflight.com/support/contact-support. (4) You may view this material at the FAA, Office of Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Fort Worth, TX 76177. For information on the availability of this material at the FAA, call (817) 222-5110. (5) You may view this material at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email fr.inspection@nara.gov . Appendix 1 to AD 2024-16-01 Report the following information for each crack by email to: OperationalSafety@faa.gov. In the subject line of the email, include the text "AD 2024-16-01". (1) Date of inspection that revealed a crack in the cap angle or in the adjacent structure. (2) Helicopter Model: (3) Date of previous inspection of the cap angle and adjacent structure: (4) Helicopter serial number: (5) Total hours time-in-service accumulated since new on the airframe: (6) Helicopter N-number: (7) Cap angle(s) part number: (8) Describe in detail any information and findings, including any previous maintenance or modification of the cracked area, any cracks in the surrounding areas such as the fitting or web, and, if possible, provide photos. Issued on August 1, 2024. Victor Wicklund, Deputy Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2024-18580 Filed 8-15-24; 11:15 am]BILLING CODE 4910-13-P