AD 2004-20-10 Airworthiness Directives; Valentin GmbH & Co. Taifun 17E Sailplanes

(c) This AD affects the following sailplane models and serial numbers that are certificated in any category: Valentin GmbH & Co. Taifun 17E, all serial numbers are affected except those where Service Bulletin 23-818 has been complied with.

(e) To address this problem, you must do the following:   Actions Compliance Procedures (1) Perform the following actions with the motor glider rigged. (i) An operational check of the front wing locking mechanism left and right for damage, deformation, and smooth operation over full travel range. (ii) A visual inspection through the operation hole on the bottom side of the wings, ensure the bolt (item 3 of drawing F1-1340) is in the fully locked front position. Confirm a fully locked position by withdrawal of the signal pin (Item 15 and Item 11 of drawing F1-1340) into the wing's upper surface and ensure the pin is level with that surface. While in this full front stop position, measure the potential movement of the bolt. If residual movement of 2mm or greater exists, replace the stop key (Item 25 of drawing F1-1340). Inspect within 25 hours time-in-service (TIS) after November 24, 2004 (the effective date of this AD). Repetitively inspect every 25 hours TIS thereafter Inspect following the Korff + CO.KG Service Bulletin SB-KOCO 03/818, dated December 12, 2002 (German LBA approved December 20, 2002) (2) Perform the following actions with the motor glider derigged (i) An operational check of the front wing locking mechanism left and right for damage, deformation, and smooth operation over full travel range. (ii) A visual inspection of the motor glider for stop key movement. You should not be able to move the stop key by hand more than 2mm backwards in the full locked front position. Inspect within 25 hours TIS after November 24, 2004 (the effective date of this AD). Repetitively inspect every 25 hours TIS thereafter Inspect following the Korff + CO.KG Service Bulletin SB-KOCO 03/818, dated December 12, 2002 (German LBA approved December 20, 2002) (3) If deficiencies are found during the inspections required in paragraphs (e)(1) and (e)(2), correct, repair, or replace the defective parts Do corrective actions prior to further flight Correct, repair, or replace defective parts following the Korff + CO.KG Service Bulletin SB-KOCO 03/818, dated December 12, 2002 (German LBA approved December 20, 2002) (4) Perform the following inspections, and if any of the following conditions are found, contact the manufacturer at the address specified in paragraph (g) of this AD for FAA-approved corrective action and perform the corrective action. You must send a copy of correspondence you send to the manufacturer to the FAA at the address in paragraph (f) (i) Inspect the wing side shear force fittings for abrasion, deformation, and correct screwing to the root rib. (ii) Inspect the wing and fuselage side root ribs for damage (delamination) and around all fittings (shear force fittings, wing connection studs, wing connection bushings, connection to the telescopic rods, rear center studs and bushings). Inspect for defective bonding to the shells as well as defective connections to the spar or the wing spar box. Inspect within 25 hours TIS after November 24, 2004 (the effective date of this AD). Repetitively inspect every 25 hours TIS thereafter. Perform corrective action prior to further flight Inspect following the Korff + CO.KG Service Bulletin SB-KOCO 03/818, dated December 12, 2002 (German LBA approved December 20, 2002) (5) When corrective action or maintenance is done, do an operational check of the motor glider in the rigged and derigged configuration After corrective action or maintenance is done, you must do the operational check prior to further flight Do the operational check following the Korff + CO.KG Service Bulletin SB-KOCO 03/818, dated December 12, 2002 (German LBA approved December 20, 2002) Note: We recommend that you make the “Flight Manual” and “Instructions for Continued Airworthiness” changes that are listed under Actions: 5. of Korff + CO.KG Service Bulletin SB-KOCO 03/818, dated December 12, 2002 (German LBA approved December 20, 2002).

(d) This AD is the result of an incorrectly locked shear force fitting, which may have caused wing-locking mechanism disengagement. The actions specified in this AD are intended to detect and correct malfunction of the wing-locking mechanism, which could result in failure of the wing attachment assembly. This failure could lead to unlocking of wing in flight and subsequent loss of control of the sailplane.

(b) None.