AD 2013-24-16 Airworthiness Directives; Schempp-Hirth Flugzeugbau GmbH Gliders

This AD applies to Schempp-Hirth Flugzeugbau GmbH Model Duo Discus T gliders, serial numbers (S/N) 1 through 240, certificated in any category.

Unless already done, do the following actions as specified in paragraphs (f)(1) through (f)(6) of this AD, including all subparagraphs: (1) Within 30 days after January 28, 2014 (the effective date of this AD), incorporate amended pages into the applicable FAA-approved sailplane flight manual (SFM), following Action 1 of Schempp-Hirth Flugzeugbau GmbH Technical Note No. 890-13, 2nd issue, dated March 5, 2013. (2) Within 60 days after January 28, 2014 (the effective date of this AD), do the actions specified in paragraphs (f)(2)(i) through (f)(2)(iii) of this AD: (i) Incorporate amended pages into the FAA-approved SFM and sailplane maintenance manual (SMM), as applicable, following Action 2 and Action 3 of Schempp-Hirth Flugzeugbau GmbH Technical Note No. 890-13, 2nd issue, dated March 5, 2013. (ii) Install the amended cockpit placards following Action 4 of Schempp-Hirth Flugzeugbau GmbH Technical Note No. 890-13, 2nd issue, dated March 5, 2013. Replace previous placard as necessary. (iii) Transfer weight and balance data from weight and balance report into the weight and balance log sheet following Action 5 of Schempp-Hirth Flugzeugbau GmbH Technical Note No. 890-13, 2nd issue, dated March 5, 2013. (3) The actions required by paragraph (f)(1) and (f)(2)(i) of this AD may be performed by the owner/operator (pilot) holding at least a private pilot certificate and must be entered into the aircraft records showing compliance with this AD following 14 CFR § 43.9 (a)(1) through (4) 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. (4) Initially within 30 days after January 28, 2014 (the effective date of this AD) and repetitively thereafter at intervals not to exceed 12 calendar months, visually inspect (pre-flight) the power plant (propeller hub and propeller blades) for cracks or other damage using the following service information in paragraphs (f)(4)(i) and (f)(4)(ii) of this AD: (i) For S/N 1 through 174: Use step (4)(c) of the Visual inspection of the power plant section on page 4.3.3 of Schempp-Hirth Flugzeugbau GmbH Duo Discus T Flight Manual issue May 2000, Revision No. 12, Date of issue November 2011; as specified in Schempp-Hirth Flugzeugbau GmbH Technical Note No. 890-13, 2nd issue, dated March 5, 2013. (ii) For S/N 175 through 240: Use step (4)(c) of the Visual inspection of the power plant section on page 4.3.3, of Schempp-Hirth Flugzeugbau GmbH Duo Discus T Flight Manual issue October 2007, Revision No. 2, Date of issue November 2011; as specified in Schempp-Hirth Flugzeugbau GmbH Technical Note No. 890-13, 2nd issue, dated March 5, 2013. Note 1 to paragraph (f)(4)(ii) of this AD: The flight manual references TN 890-13 and MB 890-8; however, neither are part of the flight manual. Also, MB 890-8 does not apply to the airplanes included in the Applicability of this AD. (5) If any cracks or other damage is found during any inspection required by paragraph (f)(4) of this AD, before further flight, replace any parts found with cracks and repair any damage. (6) The revised SFM pages require pre-flight checks that may be done by the pilot. However, the inspection actions required in paragraph (f)(4) of this AD, to include all subparagraphs, are separate from the pilot pre-flight checks and must be done by a properly certificated aircraft mechanic.

The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Jim Rutherford, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4165; fax: (816) 329-4090; email: jim.rutherford@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.

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 describes the unsafe condition as the instructions provided to inspect the propeller hub and blades are insufficient for detecting cracks and/or other damage, and other operating instructions provided by the flight and maintenance manual are incorrect and insufficient. We are issuing this AD to ensure that the instructions for inspecting the propeller hub and blades are sufficient to detect cracks and/or other damage and instructions of the flight and maintenance manual are correct and sufficient.

None.