AD 2005-25-06 Airworthiness Directives; Fokker Model F27 Mark 050 Airplanes

Models named: F27 Mark 050. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to all Fokker Model F27 Mark 050 airplanes, certificated in any category.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Restatement of the Requirements of AD 99-27-13 Repetitive Corrective Action (f) Within 30 days after January 21, 2000 (the effective date of AD 99-27-13), use a torque wrench to tighten the screws for the attachment of the leading edges of the elevators in accordance with Fokker Service Bulletin SBF50-55-007, dated June 5, 1998; or Revision 2, dated June 17, 2002. After the effective date of this AD, only Revision 2 may be used. Repeat the tightening thereafter at intervals not to exceed 12 months until the initial tightening required by paragraph (i) of this AD is accomplished. (g) Within 24 months after January 21, 2000, use a torque wrench to tighten the screws for the attachment of the leading edges of the rudder in accordance with Fokker Service Bulletin SBF50-55-009, Revision 1, dated July 23, 1999; or Revision 2, dated June 17, 2002. After the effective date of this AD, only Revision 2 may be used. Repeat the tightening thereafter at intervals not to exceed 4,000 flight hours, or 24 months, whichever occurs first, until the initial tightening required by paragraph (j) of this AD is accomplished. (h) Within 6 months after January 21, 2000, use a torque wrench to tighten the screws for the attachment of the leading edges of the ailerons in accordance with Fokker Service Bulletin SBF50-57-020, Revision 1, dated July 23, 1999; or Revision 2, dated June 17, 2002. After the effective date of this AD, only Revision 2 may be used. Repeat the tightening thereafter at intervals not to exceed 12 months until the initial tightening required by paragraph (k) of this AD is accomplished. New Requirements of This AD New Repetitive Intervals (i) Within 6 months after the effective date of this AD or 12 months after accomplishing the action in paragraph (f) of this AD, whichever occurs earlier: Use a torque wrench to tighten the screws for the attachment of the leading edges of the elevators in accordance with Fokker Service Bulletin SBF50-55-007, Revision 2, dated June 17, 2002. Repeat the tightening thereafter at intervals not to exceed 6 months until the modification required by paragraph (l) of this AD is accomplished. Doing the actions in this paragraph terminates the repetitive actions of paragraph (f) of this AD. (j) Within 12 months after the effective date of this AD or 24 months after accomplishing the action in paragraph (g) of this AD, whichever occurs earlier: Use a torque wrench to tighten the screws for the attachment of the leading edge of the rudder in accordance with Fokker Service Bulletin SBF50-55-009, Revision 2, dated June 17, 2002. Repeat the tightening thereafter at intervals not to exceed 12 months until the modification required by paragraph (l) of this AD is accomplished. Doing the actions in this paragraph terminates the repetitive actions of paragraph (g) of this AD. (k) Within 6 months after the effective date of this AD or 6 months after accomplishing the action in paragraph (h) of this AD, whichever occurs earlier: Use a torque wrench to tighten the screws for the attachment of the leading edges of the ailerons in accordance with Fokker Service Bulletin SBF50-57-020, Revision 2, dated June 17, 2002. Repeat the tightening thereafter at intervals not to exceed 6 months until the modification required by paragraph (l) of this AD is accomplished. Doing the actions in this paragraph terminates the repetitive actions of paragraph (h) of this AD. Terminating Modification (l) At the earlier of the times in paragraph (l)(1) and (l)(2) of this AD, modify the elevator, rudder, and aileron leading edge attachments by installing additional locking devices in accordance with the Accomplishment Instructions of the service bulletins in Table 1 of this AD. Doing the modifications terminates the applicable repetitive actions in paragraphs (f), (g), (h), (i), (j), and (k) of this AD, as specified in Table 1. (1) Within 24 months after the effective date of this AD. (2) Within 180 months since the date of issuance of the original Airworthiness Certificate or the date of issuance of the original Export Certificate of Airworthiness. Table 1.—Fokker Service Bulletins for Terminating Modification Fokker service bulletin Location Terminates the actions required in paragraph— SBF50-55-008, Revision 3, dated June 17, 2002 Elevator leading edge (f) and (i). SBF50-55-010, Revision 2, dated June 17, 2002 Rudder leading edge (g) and (j). SBF50-57-021, Revision 2, dated June 17, 2002 Aileron leading edge (h) and (k). Note 1: Fokker Service Bulletin SBF50-55-010, Revision 2, refers to Fokker Service Bulletin SBF50-55-011, dated October 29, 2001, as an additional source of service information for modifying the rudder attachments. Fokker Service Bulletin SBF50-57-021, Revision 2, refers to Fokker Service Bulletin SBF50-57-025, dated October 29, 2001, as an additional source of service information for modifying the aileron attachments. Alternative Methods of Compliance (AMOCs) (m)(1) The Manager, ANM-116, International Branch, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (n) Dutch airworthiness directive 2000-131/2, dated July 31, 2002, also addresses the subject of this AD. Material Incorporated by Reference (o) You must use the service information that is specified in Table 2 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. Table 2.—All Material Incorporated by Reference Fokker service bulletin Revision level Date SBF50-55-007 Original June 5, 1998. SBF50-55-007 2 June 17, 2002. SBF50-55-008 3 June 17, 2002. SBF50-55-009 1 July 23, 1999. SBF50-55-009 2 June 17, 2002. SBF50-55-010 2 June 17, 2002. SBF50-57-020 1 July 23, 1999. SBF50-57-020 2 June 17, 2002. SBF50-57-021 2 June 17, 2002. (1) The incorporation by reference of the service bulletins in Table 3 of this AD is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Table 3.—New Material Incorporated by Reference Fokker service bulletin Revision level Date SBF50-55-007 Revision 2 June 17, 2002. SBF50-55-008 Revision 3 June 17, 2002. SBF50-55-009 Revision 2 June 17, 2002. SBF50-55-010 Revision 2 June 17, 2002. SBF50-57-020 Revision 2 June 17, 2002. SBF50-57-021 Revision 2 June 17, 2002. (2) The incorporation by reference of the service bulletins in Table 4 of this AD was approved previously by the Director of the Federal Register as of January 21, 2000, (65 FR 695, January 6, 2000). Table 4.—Material Previously Incorporated by Reference Fokker service bulletin Revision level Date SBF50-55-007 Original June 5, 1998. SBF50-55-009 Revision 1 July 23, 1999. SBF50-57-020 Revision 1 July 23, 1999. (3) Contact Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands, for copies of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Issued in Renton, Washington, on November 30, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-23779 Filed 12-9-05; 8:45 am] BILLING CODE 4910-13-P

This AD results from a report of an in-flight vibration caused by a loose leading edge section of the elevator. We are issuing this AD to prevent binding of the flight controls caused by loose attachment screws, which could result in reduced controllability of the airplane.