2005-17-01: Stabilizer-trim attachment and structural components

2005-17-01 Pilatus Aircraft Ltd.: Amendment 39-14221; Docket No. FAA-2005-20515; Directorate Identifier 2005-CE-09-AD. When Does This AD Become Effective? (a) This AD becomes effective on September 29, 2005. What Other ADs Are Affected By This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects the following airplanes, all manufacturer serial numbers (MSN), that are certificated in any category. Note 1: These airplanes are also identified as Fairchild Republic Company PC-6 series airplanes and Fairchild Heli Porter PC- 6 series airplanes. Models (1) PC 6 (2) PC 6 H1 (3) PC 6 H2 (4) PC 6/350 (5) PC 6/350 H1 (6) PC 6/350 H2 (7) PC 6/A (8) PC 6/A H1 (9) PC 6/A H2 (10) PC 6/B H2 (11) PC 6/B1 H2 (12) PC 6/B2 H2 (13) PC 6/B2 H4 (14) PC 6/C H2 (15) PC 6/C1 H2 What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of mandatory continuing airworthiness information (MCAI)issued by the airworthiness authority for Switzerland. We are issuing this AD to detect and correct cracks in the stabilizer-trim attachment and surrounding structural components, which could result in failure of the stabilizer-trim attachment. This failure could lead to loss of control of the airplane. What Must I Do To Address This Problem? (e) To address this problem, you must do the following: Actions Compliance Procedures (1) Inspect the following: (i) the stabilizer-trim attachment and structural components (fitting, connecting piece, bearing fork, bearing support assembly, and auxiliary frame, as applicable) for cracks and corrosion; and. (ii) the diameters of the actuator attachment bolt holes on the fittings, auxiliary frame, and connecting piece (as applicable) for discrepancies. Within the next 100 hours time-in-service (TIS) after September 29, 2005 (the effective date of this AD). Repetitively inspect thereafter at intervals not-to-exceed 3,500 hours TIS or 7 years, whichever occurs first. Follow Pilatus PC 6 Service Bulletin No. 53 001, Rev. No. 1, dated June 1, 2005. (2) If cracks are found during any inspection required in paragraph (e)(1)(i) of this AD, replace the defective part with a new part. Replace the defective part before further flight after the inspection in which cracks are found. After each replacement, continue with the repetitive inspection requirement in paragraph (e)(1) of this AD. Follow Pilatus PC 6 Service Bulletin No. 53 001, Rev. No. 1, dated June 1, 2005. (3) If corrosion or discrepancies are found during any inspection required in paragraphs (e)(1)(i) and (e)(1)(ii) of this AD, do the following: (i) replace the defective part with a new part if the corrosion or discrepancy is beyond the repairable limits stated in the service information; or. (ii) repair the defective part if the corrosion or discrepancy is within the repairable limits stated in the service information. Replace or repairthe defective part before further flight after the inspection in which corrosion or discrepancies are found. After each replacement or repair, continue with the repetitive inspection requirement in paragraph (e)(1) of this AD. Follow Pilatus PC 6 Service Bulletin No. 53 001, Rev. No. 1, dated June 1, 2005. (4) Replace the following: (i) all Fairchild connecting pieces, part number (P/N) 6232.0026.XX, with a Pilatus connecting piece, P/N 6232.0026.XX. The Fairchild part has a rivet in the middle that is not on the Pilatus part; and. (ii) all fittings, P/N 116.40.06.033 without an index after the P/N, with an improved part, P/N 116.40.06.033 with an index of "A"or "B" after the P/N or with P/N 116.40.06.112. Within the next 100 hours TIS after September 29, 2005 (the effective date of this AD). After replacement, repetitively inspect thereafter at intervals not-to-exceed 3,500 hours TIS or 7 years, whichever occurs first. If after the inspection required in paragraph (e)(1) ofthis AD, you determine that you already have a P/N 116.40.06.033 with an index of "A"or "B"or a P/N 116.40.06.112 installed, repetitively inspect thereafter at intervals not-to-exceed 3,500 hours TIS or 7 years, whichever occurs first after the part was installed. Follow Pilatus PC 6 Service Bulletin No. 53 001, Rev. No. 1, dated June 1, 2005. (5) Do not install any of the following: (i) Fairchild connecting piece, P/N 6232.0026.XX (it has a rivet in the middle that is not on the Pilatus part); and. (ii) fitting, P/N 116.40.06.033, without an index after the part number. As of September 29, 2005 (the effective date of this AD). Follow Pilatus PC 6 Service Bulletin No. 53 001, Rev. No. 1, dated June 1, 2005. Note 2: Even though not required in this AD, the FAA recommends that you send all defective parts to Pilatus at the address specified in paragraph (h) of this AD. With the part, include the aircraft serial number, flying hours, and cycles. May I Request an Alternative Method of Compliance? (f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Standards Office, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4059; facsimile: (816) 329-4090. Is There Other Information That Relates to This Subject? (g) Swiss AD HB-2005-263, effective date June 16, 2005, also addresses the subject of this AD. Does This AD Incorporate Any Material by Reference? (h) You must do the actions required by this AD following the instructions in Pilatus PC-6 Service Bulletin No. 53-001, Rev. No. 1, dated June 1, 2005. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, Switzerland; telephone: +41 41 619 6580; facsimile: +41 41 619 6576. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2005-20515; Directorate Identifier 2005-CE-09-AD.