Airworthiness directives › 2005-08-07
AD 2005-08-07 Airworthiness Directives; Pilatus Aircraft Limited Models B4-PC11, B4-PC11A, and B4-PC11AF Sailplanes
Makes named: pilatus. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
(c) This AD affects Models B4-PC11, B4-PC11A, and B4-PC11AF sailplanes, all serial numbers, that are certificated in any category.
Required actions
(e) To address this problem, you must do the following: Actions Compliance Procedures (1) Inspect the control-column support (part number (P/N) 112.35.11.072) for cracks Initially inspect within 12 calendar months after the last inspection under Pilatus Aircraft Ltd. Service Bulletin No. 1005, Revision No. 1, dated April 9, 2003, or Pilatus Aircraft Ltd. Service Bulletin No. 1005, Revision No. 2, dated April 22, 2004, where no cracks were found or within the next 30 days after June 2, 2005 (the effective date of this AD), whichever occurs later, unless already done. Repetitively inspect 2004. thereafter at intervals not to exceed every 12 calendar months regardless of whether the control-column support was replaced Follow Pilatus B4-PC 11 Aircraft Ltd. Service Bulletin No. 1005, Revision No. 2, dated April 22, 2004. (2) If any cracks are found after the inspection required by paragraph (e)(1) of this AD, replace the control-column support (P/N 112.35.11.072) with a new control-column support (P/N 112.35.11.072) Before further flight after the inspection required by paragraph (e)(1) of this AD where you found the crack. Continue the repetitive inspections required by paragraph (e)(1) of this AD Follow Pilatus B4-PC 11 Aircraft Ltd. Service Bulletin No. 1005, Revision No. 2, dated April 22, 2004.
Unsafe condition
(d) This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified in this AD are intended to detect and correct cracks in the control-column support, which could result in failure of the support. This failure could lead to loss of the primary flight control system.
Affected ADs
(b) None.
Read the original on the Federal Register →
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1