2006-23-01: Main landing gear bay

2006-23-01 Pilatus Aircraft Ltd.: Amendment 39-14813; Docket No. FAA-2006-25582; Directorate Identifier 2006-CE-42-AD. Effective Date (a) This AD becomes effective on December 13, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Model PC-7 airplanes, manufacturer serial numbers 101 through 618 inclusive, that are certificated in any category. 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 nose skin and adjacent structure above the left and right main landing gear bay and in the forward support structure of the floor panel. Crack propagation in certain areas could lead to failure of the main wing torsion box. This failure could result in loss of control. Compliance (e) To address this problem, you must do the following: Actions Compliance Procedures (1) Inspect: (i) The forward area of the floor panel and the related structure for cracks using magnified, visual methods. (ii) The nose skin and adjacent structure above the left and right main landing gear bay for cracks using eddy-current, non-destructive methods. Initially inspect within the next 150 hours time-in-service or 6 calendar months, whichever occurs first, after December 13, 2006 (the effective date of this AD), unless already done. Repetitively inspect thereafter at intervals specified in paragraph 2. B. of Pilatus PC-7 Aircraft Maintenance Manual (AMM) 05-10-00, dated March 4, 2005. Do the initial inspection following Pilatus PC-7 Service Bulletin No. 57-009, dated January 29, 2004. Do the repetitive inspections following the procedures in AMM 57-10-03, dated March 4, 2005, and AMM 05-30-05, dated February 28, 2006. (2) If crack damage is found during any inspection required by paragraph (e)(1) of this AD, obtain an FAA-approved repair solution from the manufacturer through the FAA at the address specified in paragraph (f) of this AD and incorporate the repair. Before further flight after any inspection in which crack damage is found. Further flight with crack damage is not permitted. After incorporating the repair, repetitively inspect as specified in paragraph (e)(1) of this AD. Obtain an FAA-approved repair solution from the manufacturer through the FAA at the address specified in paragraph (f) of this AD and incorporate the repair. Alternative Methods of Compliance (AMOCs) (f) The Manager, Standards Staff, FAA, Small Airplane Directorate, Attn: Doug Rudolph, Aerospace Engineer, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4059; fax: (816) 329-4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (g) The Federal Office for Civil Aviation Swiss AD HB-2006-374, effective date August 2, 2006, also addresses the subject of this AD. Material Incorporated by Reference (h) You must use Pilatus PC-7 Service Bulletin No. 57-009, dated January 29, 2004, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, Switzerland; telephone: +41 41 619 63 19; fax: +41 41 619 6224. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202- 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html .