AD 98-06-26 Airworthiness Directives; Fokker Model F28 Mark 0100 Series Airplanes

Makes named: dowty. Models named: F28 Mark 0100 series. Read the applicability below — it usually turns on serial or part numbers too.

Model F28 Mark 0100 series airplanes equipped with Dowty Aerospace main landing gear (MLG) part number 201072011, 201072012, 201072013, 201072014, 201072015, or 201072016; certificated in any category. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been 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 (g) 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 failure of the MLG wheel axle due to problems associated with corrosion and cracking, accomplish the following: (a) Within 30 days after the effective date of this AD, remove the MLG wheels and brakes and perform a visual inspection to detect corrosion and cracking in the wheel axles of the MLG sliding members in accordance with Fokker Service Bulletin F100-32-079, Revision 1, dated October 4, 1993, and paragraph 2.A. of the Accomplishment Instructions of Dowty Aerospace Service Bulletin F100-32-63, Revision 2, dated September 23, 1993. (b) Following accomplishment of the inspection required by paragraph (a) of this AD, accomplish either paragraph (b)(1) or (b)(2) of this AD. (1) Repeat the inspection required by paragraph (a) of this AD thereafter at intervals not to exceed 3 months in accordance with Fokker Service Bulletin SBF100-32-080, dated October 4, 1993, and Dowty Aerospace Service Bulletin F100-32-64, Revision 1, dated February 18, 1994, until the actions required by paragraph (e) of this AD are accomplished. Or (2) Accomplish paragraphs (b)(2)(i), (b)(2)(ii), and (b)(2)(iii) of this AD at the times specified in those paragraphs in accordance with Fokker Service Bulletin SBF100-32-083, dated March 23, 1994. (i) Within 3 months after the accomplishment of an inspection required by paragraph (a) or (b)(1) of this AD: Rework the axles in accordance with Part 2 of the Accomplishment Instructions of the service bulletin. Repeat this rework thereafter at intervals not to exceed 12 months or 2,200 landings, whichever occurs first. And (ii) Prior to or concurrent with accomplishing the initial rework specified in paragraph (b)(2)(i) of this AD: Replace the main wheel brake units in accordance with Part 1 of the Accomplishment Instructions of the service bulletin. And (iii) Within 3 months after the first accomplishment of the rework required by paragraph (b)(2)(i) of this AD: Begin performing interim inspections (``sampling program'') to detect corrosion and cracking in the wheel axles of the MLG sliding members, in accordance with Part 3 of the Accomplishment Instructions of the service bulletin. Perform these inspections at the intervals specified in the service bulletin until the actions required by paragraph (e) of this AD are accomplished. (c) If any corrosion is found during any inspection required by this AD, prior to further flight, rework the affected area and [[Page 13505]] perform a non-destructive testing (NDT) inspection to detect cracks in the MLG wheel axles, in accordance with Appendix A of Dowty Aerospace Service Bulletin F100-32-63, Revision 2, dated September 23, 1993 (if corrosion is found during the initial inspection required by this AD); or Dowty Aerospace Service Bulletin F100-32- 64, Revision 1, dated February 18, 1994 (if corrosion is found during a repetitive inspection required by this AD); as applicable. After rework, perform repetitive inspections of the affected area in accordance with paragraph (b)(1) of this AD until the actions required by paragraph (e) of this AD are accomplished. (d) If any crack is found during any inspection required by this AD, prior to further flight, replace the affected sliding member with a serviceable sliding member in accordance with Dowty Aerospace Service Bulletin F100-32-63, Revision 2, dated September 23, 1993 (if any crack is found during the initial inspection required by this AD); or Dowty Aerospace Service Bulletin F100-32-64, Revision 1, dated February 18, 1994 (if any crack is found during a repetitive inspection required by this AD); as applicable. After replacement of the affected sliding member, perform the repetitive inspections in accordance with paragraph (b)(1) of this AD until the actions required by paragraph (e) of this AD are accomplished. (e) At the next major gear overhaul, or within 5 years after the effective date of this AD, whichever occurs first: Rework the sliding member, and replace the main wheel brake units in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-32-081, dated March 23, 1994. Accomplishment of these actions constitutes terminating action for the repetitive inspections and the interim actions specified in paragraph (b) of this AD. Note 2: Fokker Service Bulletin SBF100-32-081 refers to Dowty Aerospace Service Bulletin F100-32-64, Revision 1, dated February 18, 1994, as an additional source of service information for accomplishment of the rework and replacement. (f) As of the effective date of this AD, no person shall install a Dowty Aerospace MLG, part number 201072011, 201072012, 201072013, 201072014, 201072015, or 201072016, on any airplane unless the requirements of this AD have been accomplished on that MLG. Following its installation, the repetitive inspections required by paragraph (b) of this AD shall be accomplished on that MLG. (g) 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 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. (h) 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. (i) The actions shall be done in accordance with the following Fokker service bulletins or Dowty Aerospace service bulletins, as applicable, which contain the specified effective pages: ---------------------------------------------------------------------------------------------------------------- Revision level shown on Service bulletin referenced and date Page No. page Date shown on page ---------------------------------------------------------------------------------------------------------------- Fokker SBF100-32-079, Revision 1, 1-3 1..................... October 4, 1993. October 4, 1993. 4 Original............... August 2, 1993. Fokker SBF100-32-080, October 4, 1993 1-4 Original............... October 4, 1993. Fokker SBF100-32-081, March 23, 1994. 1-6 Original............... March 23, 1994. Fokker SBF100-32-083, March 23, 1994. 1-6 Original............... March 23, 1994. Dowty Aerospace F100-32-63, Revision 1-3 2...................... September 23, 1993. 2, September 23, 1993. 4 Original............... July 29, 1993. Appendix A........................... 1-2 Original............... July 29, 1993 Appendix B........................... 1 2...................... September 23, 1993. Dowty Aerospace F100-32-64, Revision 1-6 1...................... February 18, 1994. 1, February 18, 1994. Appendix A........................... 1-2 Original............... September 23, 1993. Appendix B........................... 1 Original............... September 23, 1993. Appendix C........................... 1 1...................... February 18, 1994. ---------------------------------------------------------------------------------------------------------------- The incorporation by reference of these documents 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 4: The subject of this AD is addressed in Dutch airworthiness directive BLA No. 93-108/2 (A), dated November 1, 1993. (j) This amendment becomes effective on April 24, 1998. Issued in Renton, Washington, on March 11, 1998. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-6948 Filed 3-19-98; 8:45 am] BILLING CODE 4910-13-U