AD 98-04-48 ACTIVE

This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model AS 332L2 helicopters. This action requires modifying the main rotor blade vibration absorber (vibration absorber) by replacing the weight support assemblies with reinforced weight support assemblies. This amendment is prompted by a report of the failure of a weight support assembly in-flight. The actions specified in this AD are intended to prevent failure of a vibration absorber weight support assembly, which could lead to adverse vibrations, contact between the fuselage and a main rotor blade or loss of a main rotor blade; and subsequent loss of control of the helicopter.

Final rule; request for comments

98-04-48 EUROCOPTER FRANCE: Amendment 39-10359. Docket No. 97-SW-29-AD.
Applicability: Model AS 332L2 helicopters with main rotor blade vibration absorbers (vibration absorbers), part number (P/N) 332A11-0460-01, 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 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 (b) 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 within 25 hours time-in-service (TIS) after the effective date of this AD, unless accomplished previously.

To prevent failure of a vibration absorber weight support assembly, which could lead to adverse vibrations, contact between the fuselage and a main rotor blade or loss of a main rotor blade; and subsequent loss of control of the helicopter, accomplish the following:

(a) Convert the vibration absorbers, P/N 332A11-0460-01 into P/N 332A11-0460-02 by replacing the weight support assemblies, P/N 332A11-0470-00, with weight support assemblies, P/N 332A11-0474-00, in accordance with the Accomplishment Instructions of Eurocopter France Service Bulletin No. 62.00.43, dated February 13, 1997.

(b) 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.

(c) Special flight permits will not be issued.

(d) The modification shall be done in accordance with the Accomplishment Instructions of Eurocopter France Service Bulletin No. 62.00.43, dated February 13, 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 American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; 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 Direction De L'Aviation Civile (France) AD 97-026-005(B) R2, dated March 12, 1997.

(e) This amendment becomes effective on March 12, 1998.

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 Model AS 332L2 helicopters with vibration absorbers, part number (P/N) 332A11-0460-01, installed. The DGAC advises that failure of a vibration absorber can result in adverse vibrations, contact between the fuselage and a main rotor blade or loss of a main rotor blade; and subsequent loss of control of the helicopter.

Eurocopter France has issued Eurocopter Service Bulletin No. 62.00.43, dated February 13, 1997, which specifies converting the vibration absorbers, P/N 332A11-0460-01, to vibration absorbers, P/N 332A11-0460-02, by replacing the weight support assemblies, P/N 332A11-0470-00, with reinforced weight support assemblies, P/N 332A11-0474-00. The DGAC classified this service bulletin as mandatory and issued French AD 97-026-005(B) R2, dated March 12, 1997, applicable to Eurocopter France Model AS 332L2 helicopters with vibration absorbers, P/N 332A11-0460-01, 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 AS 332L2 helicopters of the same type design registered in the United States, this AD is being issued to prevent failure of a vibration absorber weight support assembly, which could lead to adverse vibrations, contact between the fuselage and a main rotor blade or loss of a main rotor blade; and subsequent loss of control of the helicopter. This AD requires modifying the main rotor blade vibration absorber by replacing the weight support assemblies with reinforced weight support assemblies. The actions are required to be accomplished in accordance with the service bulletin described previously.

None of the Eurocopter France Model AS 332L2 helicopters affected by this action are on the U.S. Register. All helicopters included in the applicability of this rule are currently operated by non-U.S. operators under foreign registry; therefore; they are not directly affected by this AD action. However, the FAA considers that this rule is necessary to ensure that the unsafe condition is addressed in the event that any of these subject helicopters are imported and placed on the U.S. Register in the future.

Should an affected helicopter be imported and placed on the U.S. Register in the future, it would require approximately 8 work hours to accomplish the required actions, at an average labor rate of $60 per work hour. Required parts would cost $11,300 per helicopter. Based on these figures, the cost impact of this AD would be $11,780 per helicopter.

Since this AD action does not affect any helicopter that is currently on the U.S. Register, it has no adverse economic impact and imposes no additional burden on any person. Therefore, notice and public procedures hereon are unnecessary and the amendment may be made effective in less than 30 days after publication in the Federal Register.

Comments Invited
Although this action is in the form of a final rule that involves requirements affecting flight safety and, thus, was not preceded by notice and an opportunity for public comment, comments are invited on this rule. Interested persons are invited to comment on this 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 under the caption "ADDRESSES." All communications received on or before the closing date for comments will be considered, and this rule may be amended in light of the comments received. Factual information that supports the commenter's ideas and suggestions is extremely helpful in evaluating the effectiveness of the AD action and determining whether additional rulemaking action would be needed.

Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify the 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 that summarizes each FAA-public contact concerned with the substance of this AD will be filed in the Rules Docket.

Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this rule must submit a self-addressed, stamped postcard on which the following statement is made: "Comments to Docket No. 97-SW-29-AD." The postcard will be date stamped and returned to the commenter.

The regulations adopted herein will 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 final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment.

The FAA has determined that notice and prior public comment are unnecessary in promulgating this regulation and therefore, it can be issuedimmediately to correct an unsafe condition in aircraft since none of these model helicopters are registered in the United States, and that it is not a "significant regulatory action" under Executive Order 12866. It has been determined further that this action involves an emergency regulation under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). If it is determined that this emergency regulation otherwise would be significant under DOT Regulatory Policies and Procedures, a final regulatory evaluation will be prepared and placed in the Rules Docket. A copy of it, if filed, may be obtained from the Rules Docket at the location provided under the caption " ;ADDRESSES."

List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends 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.

39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive to read as follows:

Submit comments in triplicate to the Federal Aviation Administration (FAA), Office of the Regional Counsel, Southwest Region, Attention: Rules Docket No. 97-SW-29-AD, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.
The service information referenced in this AD 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; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

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.