AD 2006-17-16 Airworthiness Directives; Fokker Model F.28 Mark 0070 and 0100 Airplanes

Models named: F.28 Mark 0070, 0100. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to all Fokker Model F.28 Mark 0070 and 0100 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. Wing Rear Spar Lower Girder Inspection/Related Investigative/Corrective Actions (f) Within 4,000 flight hours or 21 months after the effective date of this AD, whichever occurs first: Do a detailed inspection to detect corrosion on the wing rear spar lower girder between wing STA 8700 and wing STA 9200, and do all related investigative and applicable corrective actions, by accomplishing all the actions specified in the Accomplishment Instructions of Fokker Service Bulletin SBF100-57-038, dated April 15, 2005, except as provided by paragraphs (g) and (h) of this AD. Do all related investigative and corrective actions before further flight. If any damage is found that measures more than or equal to 1.3 millimeters (mm) deep, or if the thickness of the remaining material of the rear spar lower girder is less than or equal to 2.1 mm thick, repair in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). Note 1: For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.” (g) If, during the accomplishment of the corrective actions required by paragraph (f) of this AD, the service bulletin specifies contacting the manufacturer for certain repair instructions: Before further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116; or the EASA (or its delegated agent). Reporting Inspection and Damage Results (h) Submit a report of the findings (both positive and negative) of the inspection required by paragraph (f) of this AD to Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands; fax +31 252 627211; e-mail Technicalservices.FokkerServices@stork.com; at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD. Use the reporting forms in Figures 3 and 4 of Fokker Service Bulletin SBF100-57-038, dated April 15, 2005. Under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq. ), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120-0056. (1) If the inspection was done after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, International Branch, ANM-116, 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 (j) Dutch airworthiness directive NL-2005-006, dated April 29, 2005, also addresses the subject of this AD. Material Incorporated by Reference (k) You must use Fokker Service Bulletin SBF100-57-038, dated April 15, 2005, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands, for a copy 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 August 16, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-13969 Filed 8-24-06; 8:45 am] BILLING CODE 4910-13-P

This AD results from reports of corrosion of the wing rear spar lower girder between wing station (STA) 8700 and wing STA 9200. We are issuing this AD to detect and correct corrosion of the wing rear spar lower girder, which could result in reduced structural integrity of the wing rear spar.