[Federal Register Volume 63, Number 63 (Thursday, April 2, 1998)] [Proposed Rules] [Pages 16165-16167] From the Federal Register Online via the Government Publishing Office [www.gpo.gov] [FR Doc No: 98-8578] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 97-NM-329-AD] RIN 2120-AA64 Airworthiness Directives; Fokker Model F28 Mark 0100 Series Airplanes AGENCY: Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: This document proposes the adoption of a new airworthiness directive (AD) that is applicable to certain Fokker Model F28 Mark 0100 series airplanes. This proposal would require interim inspections to detect discrepancies of the main fitting subassembly of the main landing gear, and follow-on corrective actions, if necessary. This proposal would also require inspection to detect discrepancies of the fitting, repair of the fitting, if necessary, and application of new surface protection on the fitting. Accomplishment of these actions would terminate the interim inspections. This proposal is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by the proposed AD are intended to prevent cracking of the main fitting subassembly of the main landing gear, which could result in collapse of the main landing gear. DATES: Comments must be received by May 4, 1998. ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 97-NM-329-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056. Comments may be inspected at this location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except Federal holidays. The service information referenced in the proposed rule may be obtained from Fokker Services B.V., Technical Support Department, P.O. Box 75047, 1117 ZN Schiphol Airport, the Netherlands. This information may be examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. FOR FURTHER INFORMATION CONTACT: Norman B. Martenson, Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2110; fax (425) 227-1149. SUPPLEMENTARY INFORMATION: Comments Invited Interested persons are invited to participate in the making of the proposed rule by submitting such written data, views, or arguments as they may desire. Communications shall identify the Rules Docket number and be submitted in triplicate to the address specified above. All communications received on or before the closing date for comments, specified above, will be considered before taking action on the proposed rule. The proposals contained in this notice may be changed in light of the comments received. Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the proposed rule. All comments submitted will be available, both before and after the closing date for comments, in the Rules Docket for examination by interested persons. A report summarizing each FAA-public contact concerned with the substance of this proposal will be filed in the Rules Docket. Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this notice must submit a self-addressed, stamped postcard on which the following statement is made: ``Comments to Docket Number 97-NM-329-AD.'' The postcard will be date stamped and returned to the commenter. Availability of NPRMs Any person may obtain a copy of this NPRM by submitting a request to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 97-NM-329-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056. Discussion The Rijksluchtvaartdienst (RLD), which is the airworthiness authority for the Netherlands, notified the FAA that an unsafe condition may exist on certain Fokker Model F28 Mark 0100 series airplanes. The RLD advises that an operator has reported in-service cracking in the main fitting subassembly of the main landing gear. This cracking resulted from corrosion at the side stay attachment fitting. Investigation revealed that the corrosion initiated after the surface protection was damaged during honing of the bushes. Such cracking, if not corrected, could result in collapse of the main landing gear. [[Page 16166]] Explanation of Relevant Service Information Messier-Dowty, the landing gear manufacturer, has issued Service Bulletin F100-32-86, Revision 2, dated July 3, 1997, which describes procedures for interim repetitive visual and eddy current inspections to detect paint damage, corrosion, or cracking of the main fitting subassembly of the main landing gear. The service bulletin also describes procedures for a one-time detailed visual and a one-time eddy current inspection to detect discrepancies (paint damage, corrosion, or cracking) of the fitting; repair of the fitting, if necessary; and application of new surface protection on the fitting. Accomplishment of these actions would eliminate the need for the interim repetitive inspections. Accomplishment of the actions specified in the service bulletin is intended to adequately address the identified unsafe condition. The RLD classified this service bulletin as mandatory and issued Dutch airworthiness directive 1996-133/2(A), dated January 31, 1997, in order to assure the continued airworthiness of these airplanes in the Netherlands. FAA's Conclusions This airplane model is manufactured in the Netherlands and is type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the RLD has kept the FAA informed of the situation described above. The FAA has examined the findings of the RLD, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States. Explanation of Requirements of Proposed Rule Since an unsafe condition has been identified that is likely to exist or develop on other airplanes of the same type design registered in the United States, the proposed AD would require accomplishment of the actions specified in the service bulletin described previously, except as discussed below. Difference Between Proposed Rule and Service Bulletin Operators should note that, although the service bulletin specifies that the manufacturer may be contacted for disposition of certain discrepancies where the repair cannot be accomplished within the limits specified in the service bulletin, this proposal would require such repairs to be accomplished in accordance with a method approved by the FAA. Differences Between Proposed Rule and Foreign AD Operators should note that this AD proposes to mandate the repetitive inspections described in Appendix B of Messier-Dowty Service Bulletin F100-32-86 as interim action, prior to the accomplishment of the terminating actions (detailed inspections, repair, and application of surface protection) described in the Accomplishment Instructions of the service bulletin. [Accomplishment of the interim inspections specified in this service bulletin is optional in Dutch airworthiness directive 1996-133/2(A).] The FAA has determined that mandating the interim inspections will maintain continued operational safety while allowing U.S. operators an opportunity to schedule the terminating action. Cost Impact The FAA estimates that 127 airplanes of U.S. registry would be affected by this proposed AD. It would take approximately 2 work hours per airplane to accomplish the proposed interim inspections. Based on an average labor rate of $60 per work hour, the cost impact of the proposed interim inspections on U.S. operators is estimated to be $15,240, or $120 per airplane, per inspection cycle. It would take approximately 14 work hours per airplane to accomplish the proposed terminating actions. Based on an average labor rate of $60 per work hour, the cost impact of the proposed terminating actions on U.S. operators is estimated to be $106,680, or $840 per airplane. The cost impact figures discussed above are based on assumptions that no operator has yet accomplished any of the proposed requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. Regulatory Impact The regulations proposed herein would not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this proposal would not have sufficient federalism implications to warrant the preparation of a Federalism Assessment. For the reasons discussed above, I certify that this proposed regulation (1) is not a ``significant regulatory action'' under Executive Order 12866; (2) is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) if promulgated, will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A copy of the draft regulatory evaluation prepared for this action is contained in the Rules Docket. A copy of it may be obtained by contacting the Rules Docket at the location provided under the caption ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: PART 39--AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 2. Section 39.13 is amended by adding the following new airworthiness directive: Fokker: Docket 97-NM-329-AD. Applicability: Model F28 Mark 0100 series airplanes, equipped with Messier-Dowty main landing gear units having the part numbers and serial numbers specified in Messier-Dowty Service Bulletin F100- 32-86, Revision 2, dated July 3, 1997; 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 (c) 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. Compliance: Required as indicated, unless accomplished previously. [[Page 16167]] To prevent cracking of the main fitting subassembly of the main landing gear, which could result in collapse of the main landing gear, accomplish the following: (a) Within 60 days after the effective date of this AD, perform a visual and an eddy current inspection to detect discrepancies (paint damage, corrosion or cracking) of the main fitting subassembly of the main landing gear, in accordance with Appendix B of Messier-Dowty Service Bulletin F100-32-86, Revision 2, dated July 3, 1997. (1) If no discrepancy is detected, or if any discrepancy is detected that is within the limits specified in Appendix B of the service bulletin: Repeat the inspections required by paragraph (a) of this AD thereafter at intervals not to exceed 60 days. (2) If any discrepancy is detected that is outside the limits specified in Appendix B of the service bulletin: Prior to further flight, accomplish the requirements of paragraph (b) of this AD. (b) Within 6 months after the effective date of this AD, perform a one-time eddy current inspection and a one-time visual inspection to detect discrepancies (paint damage, corrosion, or cracking) of the main fitting subassembly of the main landing gear, in accordance with the Accomplishment Instructions of Messier-Dowty Service Bulletin F100-32-86, Revision 2, dated July 3, 1997. Accomplishment of the actions required by this paragraph constitute terminating action for the requirements of this AD. (1) If no discrepancy is detected, prior to further flight, apply a protective treatment to the main fittings in accordance with the service bulletin. (2) If any discrepancy is detected that can be repaired within the limits specified in the service bulletin, prior to further flight, repair the discrepancy, and apply a protective treatment to the main fittings, in accordance with the service bulletin. (3) If any discrepancy is detected that cannot be repaired within the limits specified in the service bulletin, prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. (c) 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. 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. (d) 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. Note 3: The subject of this AD is addressed in Dutch airworthiness directive 1996-133/2(A), dated January 31, 1997. Issued in Renton, Washington, on March 25, 1998. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 98-8578 Filed 4-1-98; 8:45 am] BILLING CODE 4910-13-U