AD 97-26-18

This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model SA-360C helicopters. This action requires replacement of the main gear box (MGB) input bevel pinion (bevel pinion). This amendment is prompted by service reports of bevel pinion fatigue cracking. This condition, if not corrected, could result in failure of the MGB and a subsequent forced landing.

Final rule; request for comments

97-26-18 EUROCOPTER FRANCE: Amendment 39-10261. Docket No. 97-SW-50-AD.
Applicability: Model SA-360C helicopters with main gearbox (MGB), part number (P/N) 360A32-2000-all dash numbers, 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 (c) 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 fatigue cracking of the MGB bevel pinion, failure of the MGB, and a subsequent forced landing, accomplish the following:

(a) Before further flight, and thereafter at intervals not to exceed 1,000 hours time-in-service (TIS), replace the MGB bevel pinion, P/N 360A32-1021-20, on MGBs that have accumulated 900 or more hours TIS since first installed on any helicopter or since the last MGB overhaul.

(b) On or before the accumulation of 1,000 hours TIS, and thereafter at intervals not to exceed 1,000 hours TIS, replace the bevel pinion, P/N 360A32-1021-20, on MGBs that have accumulated less than 900 hours TIS since first installed on any helicopter or since the last MGB overhaul. This AD revises the Airworthiness Limitations section of the maintenance manual by establishing a new retirement life for the bevel pinion, P/N 360A32-1021-20, of 1,000 hours TIS.

NOTE 2: Eurocopter France Mandatory Service Bulletin No. 01.35, dated January 14, 1997, contains additional information concerning the subject of this AD.

(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, Rotorcraft Standards Staff, FAA, Rotorcraft Directorate. 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 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Standards Staff.

(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 helicopter to a location where the requirements of this AD can be accomplished.

NOTE 4: The subject of this AD is addressed in Direction Generale de L Aviation Civile (France) AD 97-027-041(B), dated February 12, 1997.

(e) This amendment becomes effective on January 5, 1998.

The Direction Generale De L Aviation (DGAC), which is the airworthiness authority for France, recently notified the FAA that an unsafe condition may exist on Eurocopter France Model SA-360C helicopters with MGB, part number (P/N) 360A32-2000-all dash numbers, installed. The DGAC advises that replacement of the MGB bevel pinion, P/N 360A32-1021-20, is necessary at 1,000 hours time-in-service (TIS) intervals to prevent fatigue cracking of the bevel pinion, failure of the MGB, and a subsequent forced landing.

Eurocopter France has issued Service Bulletin No. 01.35, dated January 14, 1997, which specifies replacement of the MGB bevel pinion at 1,000 hour TIS intervals. The DGAC classified this service bulletin as mandatory and issued DGAC AD 97-027-041(B), dated February 12, 1997, 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-360C helicopters of the same type design registered in the United States, this AD is being issued to prevent bevel pinion fatigue cracking, failure of the MGB, and a subsequent forced landing. This AD requires replacement of the bevel pinion at specified TIS intervals.

None of the Eurocopter France Model SA-360C helicopters affected by this AD 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, it will require approximately 8.5 work hours to accomplish the required actions, at an average labor rate of $60 per work hour. Required parts will cost $17,000 per helicopter for each replacement. Based on these figures, the cost impact of this AD will be $17,510 per helicopter for each MGB bevel pinion replacement.

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-50-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 issued immediately 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 placedin 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, 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 USC 106(g), 40113, 44701.

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