Airworthiness directives › 2013-09-09
AD 2013-09-09 Airworthiness Directives; Slingsby Sailplanes Ltd. Sailplanes
Applicability*9
This AD applies to Slingsby Sailplanes Ltd. Models Dart T.51, Dart T.51/17, and Dart T.51/17R sailplanes, all serial numbers, that are: (1) Equipped with aluminum alloy spar booms; and (2) certificated in any category.
Compliance
Unless already done, do the following actions specified in paragraphs (f)(1) and (f)(2) of this AD: (1) Within the next 6 calendar months after December 14, 1998 (the effective date retained from AD 98-22-15, Amendment 39-10863 (63 FR 58624, November 2, 1998)), inspect the aluminum alloy spar booms and the wing attach fittings for delamination or corrosion damage following the ACTION section of Slingsby Aviation Ltd. Technical Instruction T.I. No. 109/T51, Issue No. 2, dated October 7, 1997, or the ACTION section of Slingsby Aviation Ltd. Technical Instruction T.I. No. 109/T51, Issue 3, dated August 21, 2000. Note 1 to paragraph (f)(1) of this AD: Slingsby Aviation Ltd. Technical Instruction T.I. No. 109/T51, Issue No. 2, dated October 7, 1997, and T.I. No. 109/T51, Issue 3, dated August 21, 2000, include guidance to determine whether an affected sailplane is equipped with aluminum alloy spar booms. (2) If any corrosion or delamination damage is found during the inspection required by paragraph (f)(1) of this AD, before further flight, contact the manufacturer at the address specified in paragraph (j)(5) of this AD to obtain an FAA-approved repair scheme and incorporate the repair.
Required actions
Unless already done, do the following actions specified in paragraphs (g)(1) and (g)(2) of this AD: (1) Within 5 years after the last inspection required by AD 98-22-15, Amendment 39-10863 (63 FR 58624, November 2, 1998) and repetitively thereafter at intervals not to exceed 12 months, using an endoscope, inspect the aluminum alloy spar booms and the wing attach fittings for delamination or corrosion damage following paragraph 11 of the ACTION section of Slingsby Aviation Ltd. Technical Instruction T.I. No. 109/T51, Issue 3, dated August 21, 2000. (2) If any corrosion or delamination damage is found during any inspection required by paragraph (g)(1) of this AD, before further flight, contact the manufacturer at the address specified in paragraph (j)(5) of this AD to obtain an FAA-approved repair scheme and incorporate the repair.
Unsafe condition
This AD was prompted by an incident of glue joint failure on a starboard wing caused by water entering the area of the airbrake box that resulted in delamination and corrosion in the area of the aluminum alloy spar booms and the wing attach fittings. The manufacturer has also issued revised service information that changes the repetitive inspection interval and method. We are issuing this AD to prevent failure of the spar assembly and adjoining structure, which could result in reduced controllability or complete loss of control.
Affected ADs
This AD supersedes AD 98-22-15, Amendment 39-10863 (63 FR 58624, November 2, 1998).
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