[Federal Register Volume 63, Number 14 (Thursday, January 22, 1998)] [Proposed Rules] [Pages 3273-3275] From the Federal Register Online via the Government Publishing Office [www.gpo.gov] [FR Doc No: 98-1428] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 97-SW-07-AD] Airworthiness Directives; Eurocopter France Model SA 330F, G, and J Helicopters 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 Eurocopter France Model SA 330F, G, and J helicopters. This proposal would require visually inspecting the intermediate gearbox (IGB) fairing safety stop (safety stop) for cracks, crazing, or edge wear, and if cracks, crazing, or edge wear exceeds the established limits, replacing the safety stop; and, inspecting to ensure that the inclined drive shaft fairing hinge pin is properly locked. A terminating action is provided in the AD by installing an additional safety stop on the IGB fairing. This proposal is prompted by one report of an accident involving the loss of the inclined drive shaft fairing. The actions specified by the proposed AD are intended to prevent loss of the inclined drive shaft fairing and impact with the tail rotor, and subsequent loss of control of the helicopter. DATES: Comments must be received by March 23, 1998. ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), Office of the Regional Counsel, Southwest Region, Attention: Rules Docket No. 97-SW-07-AD, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. 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 American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005. This information may be examined at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas. FOR FURTHER INFORMATION CONTACT: Mr. Mike Mathias, Aerospace Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5123, fax (817) 222-5961. 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 should 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 [[Page 3274]] must submit a self-addressed, stamped postcard on which the following statement is made: ``Comments to Docket No. 97-SW-07-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, Office of the Regional Counsel, Southwest Region, Attention: Rules Docket No. 97-SW-07-AD, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. Discussion The Direction Generale De L'Aviation Civile (DGAC) which is the airworthiness authority for France, recently notified the FAA that an unsafe condition may exist on Eurocopter France SA 330F, G, and J helicopters. The DGAC advises that there was one reported accident that was caused by the loss of the inclined drive shaft fairing. Eurocopter France has issued Eurocopter France SA 330 Service Bulletin No. 54.20, Revision 1, dated February 27, 1996, which specifies visually inspecting the safety stop for wear, cracks or crazing, and determining if the edge has ruptured locally, and replacing the safety stop. The DGAC classified this service bulletin as mandatory and issued DGAC AD 96-095-076(B), dated April 24, 1996, in order to assure the continued airworthiness of these helicopters in France. This helicopter model is manufactured in France 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 DGAC has kept the FAA informed of the situation described above. The FAA has examined the findings of the DGAC, 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. Since an unsafe condition has been identified that is likely to exist or develop on other Eurocopter France Model SA 330F, G, and J helicopters of the same type design registered in the United States, the proposed AD would require visually inspecting the safety stop for cracks, crazing, or edge wear that exceeds the limits stated in Note II of the Accomplishment Instructions of Eurocopter France SA 330 Service Bulletin No. 54.20, Revision 1, dated February 27, 1996, and if cracks, crazing, or edge wear exceeds the established limits, replacing the safety stop; and, inspecting to ensure that the inclined drive shaft fairing hinge pin is properly locked. Both inspections are required within 7 calendar days after the effective date of the AD, and upon completion of the last flight of each day. Installing an additional safety stop (right-angle clip) on the IGB fairing within 60 calendar days after the effective date of the AD is terminating action for the requirements of this AD. The actions would be required to be accomplished in accordance with the service bulletin described previously. The FAA estimates that 1 helicopter of U.S. registry would be affected by this proposed AD, that it would take approximately 1 work hour to perform the inspection, and two work hours to install the safety stop, and that the average labor rate is $60 per work hour. Required parts would cost approximately $50 per helicopter. Based on these figures, the total cost impact of the proposed AD on U.S. operators is estimated to be $230. 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 a new airworthiness directive to read as follows: Eurocopter France: Docket No. 97-SW-07-AD. Applicability: Model SA 330 F, G, and J helicopters, certificated in any category. Note 1: This AD applies to each helicopter 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 helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (d) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any helicopter from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent loss of the inclined drive shaft fairing hinge pin (hinge pin), that could result in loss of the inclined drive shaft fairing, impact with the tail rotor, and subsequent loss of control of the helicopter, accomplish the following: (a) Within 7 calendar days after the effective date of this AD, and thereafter, upon the completion of the last flight of each day, visually inspect the intermediate gearbox (IGB) fairing safety stop (safety stop) and the hinge pin in accordance with the Accomplishment Instructions of Eurocopter France SA 330 Service Bulletin No. 54.20, Revision 1, dated February 27, 1996. (1) Inspect the IGB fairing safety stop, part number (P/N) 330A24-2086-20, for cracks or crazing, and edge wear that exceeds the limits stated in Note II of the Accomplishment Instructions of Eurocopter France SA 330 Service Bulletin No. 54.20, Revision 1, dated February 27, 1996, and if cracks, crazing, or edge wear that exceeds the established limits is detected, remove the safety stop and replace it with an airworthy safety stop; and, (2) Inspect the hinge pin to ensure it is properly locked. (b) Within 60 calendar days after the effective date of this AD, install an additional safety stop, P/N 330A24-2119-21, to prevent the hinge pin from backing out of its hole in [[Page 3275]] case of a locking arm failure, in accordance with Accomplishment Instructions of Eurocopter France SA 330 Service Bulletin No. 54.20, Revision 1, dated February 27, 1996. (c) Installation of an airworthy additional safety stop, P/N 330A24-2119-21, constitutes terminating action for the requirements of this AD. (d) 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, Rotorcraft Standards Staff, Rotorcraft Directorate, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Standards Staff. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Standards Staff. (e) 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 helicopter to a location where the requirements of this AD can be accomplished. Note 3: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD 96-095-076(B), dated April 24, 1996. Issued in Fort Worth, Texas, on January 14, 1998. Eric Bries, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 98-1428 Filed 1-21-98; 8:45 am] BILLING CODE 4910-13-U