2023-03-22: Engine (Turbine/Turboprop)

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 2015-09-04 R1, Amendment 39-18492 (81 FR 26124, May 2, 2016); and b. Adding the following new airworthiness directive: 2023-03-22 DG Flugzeugbau GmbH and Schempp-Hirth Flugzeugbau GmbH: Amendment 39-22347; Docket No. FAA-2022-1406; Project Identifier MCAI-2022-00590-G. (a) Effective Date This airworthiness directive (AD) is effective April 5, 2023. (b) Affected ADs This AD replaces AD 2015-09-04 R1, Amendment 39-18492 (81 FR 26124, May 2, 2016). (c) Applicability This AD applies to DG Flugzeugbau GmbH Model DG-1000T gliders and Schempp-Hirth Flugzeugbau GmbH (Schempp-Hirth) Model Duo Discus T gliders, all serial numbers, certificated in any category, with a Solo Vertriebs-und Entwicklungs-GmbH (previously Solo Kleinmotoren GmbH) (Solo) Model 2350 C or Model 2350 D engine installed. (d) Subject Joint Aircraft System Component (JASC) Code 7200, Engine (Turbine/Turboprop). (e) Unsafe Condition This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as occurrences of rupture of the eccentric axle on Solo Model 2350 C engines (installed on DG Flugzeugbau GmbH Model DG-1000T gliders in the United States) and an occurrence on a Solo Model 2350 D engine (installed on Schempp-Hirth Model Duo Discus T gliders in the United States). The FAA is issuing this AD to prevent failure of the engine shaft with consequent propeller detachment. The unsafe condition, if not addressed, could result in damage to the glider or injury of persons on the ground. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) For DG Flugzeugbau GmbH Model DG-1000T gliders equipped with a Solo Model 2350 C engine, before further flight after the effective date of this AD, replace each eccentric axle that is not part number (P/N) 2031211V2 with an eccentric axle that is P/N 2031211V2 that has zero hours time-in-service (TIS). Note 1 to paragraph (g)(1): DG Flugzeugbau Technical Note 1000/26, dated September 23, 2015, contains information related to replacing the eccentric axle specific for the DG Flugzeugbau GmbH Model DG-1000T gliders. Solo Kleinmotoren GmbH Technische Mitteilung (English translation: Service Bulletin), Nr. 4603-17, datum (English translation: dated) July 15, 2015, contains information related to replacing the eccentric axle for the Solo Model 2350 C engine, but is not specific to the DG Flugzeugbau GmbH Model DG-1000T gliders. (2) For Schempp-Hirth Model Duo Discus T gliders equipped with a Solo Model 2350 D engine, within 30 hours TIS of engine operation after the effective date of this AD, replace each eccentric axle that is not P/N 2031211V2 with an eccentric axle that is P/N 2031211V2 that has zero hours TIS in accordance with Action 1, Note 2, and Pictures 1 through 6 of Solo Kleinmotoren GmbH Technische Mitteilung (English translation: Service Bulletin), Nr. 4603-19, dautm (English translation: dated) January 31, 2022. Note 2 to paragraph (g)(2): This service information contains German to English translation. The European Union Aviation Safety Agency (EASA) used the English translation in referencing the document. For enforceability purposes, the FAA will refer to the Solo Kleinmotoren service information in English as it appears on the document. (3) For all gliders, after the initial replacement required by paragraph (g)(1) or (2) of this AD, as applicable, or if an eccentric axle P/N 2031211V2 was installed as of the effective date of this AD, within intervals not to exceed 50 hours TIS of engine operation, replace each eccentric axle P/N 2031211V2 with an eccentric axle P/N 2031211V2 that has zero hours TIS as specified in paragraph (g)(1) or (2) of this AD, as applicable. (4) It is allowed to operate a glider having a Solo Model 2350 C or Model 2350 D engine installed with the engine inoperative instead of replacing the eccentric axle. To operate with the engine inoperative, place a copy of this AD into the Limitations section of the existing aircraft flight manual for your glider and do not operate the engine. (i) Remove this operating limitation after replacing the eccentric axle as required by paragraphs (g)(1) or (2) and (3) of this AD. (ii) The owner/operator (pilot) holding at least a private pilot certificate may perform both the incorporation and removal of the operating limitation and the actions must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR 43.9(a) and 14 CFR 91.417(a)(2)(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439. (h) Alternative Methods of Compliance (AMOCs) The Manager, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in § 39.19. In accordance with § 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 International Validation Branch, mail it to the address identified in paragraph (i)(2) of this AD or email to: 9-AVS-AIR-730-AMOC@faa.gov . If mailing information, also submit information by email. 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. (i) Additional Information (1) Refer to EASA AD 2022-0044R1, dated April 29, 2022, for related information. This EASA AD may be found in the AD docket at regulations.gov under Docket No. FAA-2022-1406. (2) For more information about this AD, contact Jim Rutherford, Aviation Safety Engineer, General Aviation & Rotorcraft Section, International Validation Branch, FAA, 901 Locust, Room 301, Kansas City, MO 64106; phone: (816) 329-4165; email: jim.rutherford@faa.gov . (3) Solo service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (j)(3) and (4) of this AD. (j) Material Incorporated by Reference (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. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Solo Kleinmotoren GmbH Technische Mitteilung (English translation: Service Bulletin), Nr. 4603-19, datum (English translation: dated) January 31, 2022. Note 3 to paragraph (j)(2)(i): This service information contains German to English translation. The EASA used the English translation in referencing the document. For enforceability purposes, the FAA will refer to the Solo Kleinmotoren service information in English as it appears on the document. (ii) [Reserved] (3) For Solo service information identified in this AD, contact Solo Kleinmotoren GmbH, Postfach 600152, D71050 Sindelfingen, Germany; phone: +49 703 1301-0; fax: +49 703 1301-136; email: aircraft@solo-germany.com ; website: aircraft.solo.global/gb/ . (4) You may view this service information at the 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 10, 2023. Christina Underwood, Acting Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2023-03997 Filed 2-28-23; 8:45 am]BILLING CODE 4910-13-P