AD 98-22-01 Airworthiness Directives; Fokker Model F.28 Mark 0100 Series Airplanes

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

Model F.28 Mark 0100 series airplanes, equipped with Messier-Dowty Nose Landing Gear (NLG) having part number (P/N) 201071001 or P/N 201071002, on which the NLG main fitting has not been overhauled in accordance with Component Maintenance Manual 32- 20-51; certificated in any category. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Required as indicated, unless accomplished previously. To prevent cracking of the NLG main fitting, which could lead to collapse of the NLG during takeoff and landing and possible injury to the flightcrew and passengers, accomplish the following: (a) Perform a one-time visual inspection to detect cracking of the NLG main fitting, in accordance with Fokker Service Bulletin SBF100-32-112, dated November 14, 1997, at the applicable time specified in either paragraph (a)(1) or (a)(2) of this AD. If any cracking is found, prior to further flight, accomplish the requirements of paragraph (b) of this AD. (1) For airplanes that have accumulated fewer than 15,000 total flight cycles as of the effective date of this AD: Inspect prior to the accumulation of 8,000 total flight cycles, or within 90 days after the effective date of this AD, whichever occurs later. (2) For airplanes that have accumulated 15,000 or more total flight cycles as of the effective date of this AD: Inspect within 30 days after the effective date of this AD. [[Page 58627]] (b) Perform a one-time eddy current and/or dye penetrant inspection to detect cracking of the NLG main fitting, in accordance with Messier-Dowty Service Bulletin F100-32-92, dated November 14, 1997, at the applicable time specified in either paragraph (b)(1) or (b)(2) of this AD. Accomplishment of the inspection required by paragraph (b) of this AD, if accomplished prior to the inspection required by paragraph (a) of this AD, terminates the inspection requirement of paragraph (a) of this AD. (1) For airplanes that have accumulated fewer than 15,000 total flight cycles as of the effective date of this AD: Inspect prior to the accumulation of 8,000 total flight cycles, or within 180 days after the effective date of this AD, whichever occurs later. (2) For airplanes that have accumulated 15,000 or more total flight cycles as of the effective date of this AD: Inspect within 60 days after the effective date of this AD. (c) If any crack is detected during the inspection required by paragraph (b) of this AD, prior to further flight, rework the NLG main fitting in accordance with Messier-Dowty Service Bulletin F100- 32-92, dated November 14, 1997. (d) Within 7 days after accomplishing the inspection required by either paragraph (a) or (b) of this AD, or within 7 days after the effective date of this AD, whichever occurs later, submit a report of the inspection results (both positive and negative findings) to Fokker Services B.V., Technical Support Department, P.O. Box 75047, 1117 ZN Schiphol Airport, the Netherlands. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. (e) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. (f) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (g) Except as provided by paragraph (d) of this AD, the actions shall be done in accordance with Fokker Service Bulletin SBF100-32- 112, dated November 14, 1997, and Messier-Dowty Service Bulletin F100-32-92, dated November 14, 1997. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Fokker Services B.V., Technical Support Department, P.O. Box 75047, 1117 ZN Schiphol Airport, the Netherlands. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Note 3: The subject of this AD is addressed in Dutch airworthiness directive BLA 1997-116 (A), dated November 28, 1997. (h) This amendment becomes effective on December 7, 1998. Issued in Renton, Washington, on October 13, 1998. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-29002 Filed 10-30-98; 8:45 am] BILLING CODE 4910-13-P