Airworthiness directives › 2016-11-12
AD 2016-11-12 Airworthiness Directives; EVEKTOR, spol. s.r.o. Gliders
Applicability*9
This AD applies to EVEKTOR, spol. s.r.o. Models L 13 SEH VIVAT and L 13 SDM VIVAT gliders (type certificate previously held by AEROTECHNIK s.r.o.), all serial numbers, certificated in any category.
Compliance
Unless already done, do the following actions in paragraphs (f)(1) and (f)(2) of this AD, including all subparagraphs: (1) Model L 13 SEH VIVAT gliders: (i) Within the next 60 days after November 27, 2000 (the effective date retained from AD 2000-20-12), inspect the tail-fuselage attachment fitting, part number (P/N) A 102 021N, for damage and material hardness following the procedures in AEROTECHNIK CZ s.r.o. Mandatory Service Bulletin SEH 13-005a, dated November 18, 1999. (ii) If you find the tail-fuselage attachment fitting is damaged or the material does not meet the hardness requirements specified in the service bulletin during the inspection required in paragraph (f)(1)(i) of this AD, before further flight, you must contact the manufacturer to obtain an FAA-approved replacement part for P/N A 102 021N and FAA-approved installation instructions and install the replacement part. Use the contact information found in paragraph (i)(4) to contact the manufacturer. (iii) As of November 27, 2000 (the effective date retained from AD 2000-20-12), do not install, on any glider, a P/N A 102 021N attachment fitting that has not passed the inspection required in paragraph (f)(1)(i) of this AD. (2) Model L 13 SDM VIVAT gliders: (i) Within the next 60 days after July 14, 2016 (the effective date of this AD), inspect the tail-fuselage attachment fitting, P/N A 102 021N, for damage and material hardness following the procedures in AEROTECHNIK CZ s.r.o. Mandatory Service Bulletin SEH 13-005a, dated November 18, 1999. (ii) If you find the tail-fuselage attachment fitting is damaged or the material does not meet the hardness requirements specified in the service bulletin during the inspection required in paragraph (f)(2)(i) of this AD, before further flight, you must contact the manufacturer to obtain an FAA-approved replacement part for P/N A 102 021N and FAA-approved installation instructions and install the replacement part. Use the contact information found in paragraph (i)(4) to contact the manufacturer. (iii) As of July 14, 2016 (the effective date of this AD), do not install, on any glider, a P/N A 102 021N attachment fitting that has not passed the inspection required in paragraph (f)(2)(i) of this AD.
Required actions
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.
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 describes the unsafe condition as insufficient material strength of the tail-fuselage attachment fitting. We are issuing this proposed AD to detect and correct tail-fuselage fittings with insufficient material strength, which if left uncorrected could result in detachment of the tail from the fuselage with consequent loss of control.
Affected ADs
This AD supersedes AD 2000-20-12, Amendment 39-11923 (65 FR 61262; October 17, 2000) (“AD 2000-20-12”).
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