Airworthiness directives: Eurocopter France,

[Federal Register: March 9, 2000 (Volume 65, Number 47)]

[Proposed Rules]

[Page 12489-12490]

From the Federal Register Online via GPO Access [wais.access.gpo.gov]

[DOCID:fr09mr00-20]

[[Page 12489]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-SW-45-AD]

Airworthiness Directives; Eurocopter France Model SA-365N1, AS- 365N2, and SA-366G1 Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

SUMMARY: This document proposes the supersedure of an existing airworthiness directive (AD), applicable to Eurocopter France Model SA- 365N1, AS-365N2, and SA-366G1 helicopters, that currently requires initial and repetitive inspections of the tail rotor blade Kevlar tie- bar (Kevlar tie-bar) for cracks or delaminations. This action would require the same actions required by the existing AD, and would correct an incorrectly stated part number (P/N) in the existing AD. This proposal is prompted by a report of delamination of a Kevlar tie-bar. The actions specified by the proposed AD are intended to detect cracks that could lead to delamination of the Kevlar tie-bar, loss of tail rotor control, and subsequent loss of control of the helicopter.

DATES: Comments must be received on or before May 8, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), Office of the Regional Counsel, Southwest Region, Attention: Rules Docket No. 99-SW-45-AD, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. Comments may be inspected at this location between 9:00a.m. and 3:00p.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, telephone (972) 641-3460, fax (972) 641- 3527. 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: Jim Grigg, Aerospace Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, Texas 76193-0111, telephone (817) 222-5490, 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 filedin 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 No. 99-SW-45-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. 99-SW-45-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, notified the FAA that an unsafe condition may exist on Model SA-365N1, AS-365N2, and SA-366G1 helicopters. The DGAC advises that delamination outside certain tolerance limits may occur on Kevlar tie-bars.

On April 30, 1998, the FAA issued AD 98-10-04, Amendment 39-10515 (63 FR 25158, May 7, 1998), to require, within 10 hours time-in-service (TIS), and thereafter at intervals not to exceed 250 hours TIS, inspecting the Kevlar tie-bar for a crack or delamination and replacing any blade in which a crack or delamination is found with an airworthy blade. That action was prompted by a report of delamination of a Kevlar tie-bar. That condition, if not corrected, could result in loss of tail rotor control and subsequent loss of control of the helicopter.

Since the issuance of that AD, the FAA has discovered that a blade P/N was incorrectly stated in the existing AD. That P/N was incorrectly stated as 365A12-0020-20. The correct P/N is 365A12-0020-02.

These helicopter models are manufactured in France and are 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 these type designs 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 Model SA-365N1, AS-365N2, and SA-366G1 helicopters of the same type design, the proposed AD would supersede AD 98-10-04 to require, within 10 hours TIS, and thereafter at intervals not to exceed 250 hours TIS, inspecting the Kevlar tie-bar for a crack or delamination and replacing any blade in which a crack or delamination is found.

The FAA estimates that 47 helicopters of U.S. registry would be affected by this proposed AD, that it would take approximately 4 work hours per helicopter to accomplish the proposed actions, and that the average labor rate is $60 per work hour. Required parts would cost approximately $3,000 per blade. Based on these figures, the total cost impact of the proposed AD on U.S. operators is estimated to be $152,280 to replace one blade and perform one inspection on each helicopter.

The regulations adopted herein will not have a substantial direct effect 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, it is determined that this final rule does not have federalism implications under Executive Order 13132.

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

[[Page 12490]]

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 removing Amendment 39-10515 (63 FR 25158, May 7, 1998), and by adding a new airworthiness directive (AD), to read as follows:

   Eurocopter France: Docket No. 99-SW-45-AD. Supersedes AD 98-10-04, Amendment 39-10515, Docket No. 97-SW-49-AD.

   Applicability: Model SA-365N1, AS-365N2, and SA-366G1 helicopters, with tail rotor blade (blade), Part Number 365A12-010- all dash numbers, 365A12-0020-00, 365A33-2131-all dash numbers, or 365A12-0020-02, installed, certificated in any category.

   Note 1: This AD applies to each helicopter 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 helicopters 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.

   To detect cracks that could lead to delamination of the tail rotor blade Kevlar tie-bar (Kevlar tie-bar), loss of tail rotor control, and subsequent loss of control of the helicopter, accomplish the following:

   (a) Within 10 hours time-in-service (TIS), and thereafter at intervals not to exceed 250 hours TIS, inspect each Kevlar tie-bar for a crack or delamination in accordance with paragraph B, Operational Procedure, of Eurocopter France Service Bulletin 05.00.34, Revision 3, dated November 14, 1996.

   (b) If any delamination or cracking is found during any of the inspections required by paragraph (a) of this AD, remove the blade and replace it with an airworthy blade before further flight.

   (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, Regulations Group, 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, Regulations Group.

   Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Regulations Group.

   (d) Special flight permits may be issued in accordance with Secs. 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 92-185-33(B)R4, dated December 4, 1996.

   Issued in Fort Worth, Texas, on March 1, 2000. Eric Bries, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.

   [FR Doc. 00-5734Filed3-8-00; 8:45 am]

   BILLING CODE 4910-13-P