Airworthiness directives: Eurocopter France,

[Federal Register: November 3, 1998 (Volume 63, Number 212)]

[Proposed Rules]

[Page 59252-59255]

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

[DOCID:fr03no98-23]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-SW-14-AD]

Airworthiness Directives; Eurocopter France Model SA. 315B, SA. 316B, SA. 316C, SA. 319B, and SE. 3160 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. 315B, SA. 316B, SA. 316C, SA. 319B, and SE. 3160 helicopters. This proposal would require inspecting the main rotor blade cuff attachment fitting in the area of the main rotor blade (blade) attachment bolts for cracks, and removing and replacing the blade if a crack is found. This proposal is prompted by a report of a crack in a main rotor blade cuff attachment fitting/spar assembly that was discovered during fatigue testing by the manufacturer. The actions specified by the proposed AD are intended to prevent failure of a main rotor blade cuff attachment fitting at a bolt hole location, loss of a main rotor blade, and subsequent loss of control of the helicopter.

DATES: Comments must be received on or before January 4, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), Office of the Regional Counsel, Southwest Region, Attention: Rules Docket No. 97-SW-14-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.

FOR FURTHER INFORMATION CONTACT: Mr. Richard Monschke, Aerospace Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5116, 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. 97-SW-14-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-14-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 Model SA. 315B, SA. 316B, SA. 316C, SA. 319B, and SE. 3160 helicopters. The DGAC advises that, within 400 operating hours, and thereafter at every 400 operating hours, a crack detection inspection of the main rotor blade cuff attachment fitting in the area of the main rotor blade attachment bolt holes must be performed. The DGAC issued AD 96-081-036(B)R1, applicable to Eurocopter France Model SA. 315B helicopters, and AD 96-082-54(B)R1 applicable to Eurocopter France Model SA. 316B, SA. 316C, SA. 319B, and SE. 3160 helicopters, both dated April 24, 1996, in order to assure the continued airworthiness of these helicopters in France.

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 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. 315B, SA. 316B, SA. 316C, SA. 319B, and SE. 3160 helicopters of the same type design registered in the United States, the proposed AD would require inspecting the attachment fitting in the area of the blade attachment bolt holes for cracks, and removing and replacing any blade in which a crack is found.

The FAA estimates that 83 helicopters of U.S. registry would be affected by this proposed AD, that it would take approximately 2 work hours per helicopter to accomplish the proposed initial inspection and 2 work hours per helicopter for each repetitive inspection, and that the average labor rate is $60 per work hour. Required parts would cost $40,000 per blade, if needed. Based on these figures, the total cost impact of the proposed AD on U.S. operators is

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estimated to be $49,960 for one inspection and one blade replacement for each helicopter per year.

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-14-AD.

   Applicability: Model SA. 315B, SA. 316B, SA. 316C, SA. 319B, and SE. 3160 helicopters, with a main rotor blade, part number (P/N) 316OS.11.10.000, 316OS.11.30.000, 316OS.11.35.000, 316OS.11.40.000, 316OS.11.45.000, 316OS.11.50.000, or 316OS.11.55.000, 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: (1) For blades with less than 400 hours time-in- service (TIS), required prior to the accumulation of 400 hours TIS, unless accomplished previously, and thereafter at intervals not to exceed 400 hours TIS; or (2) for blades with 400 hours or more TIS, required within 50 hours TIS or 30 calendar days, whichever occurs first, unless accomplished previously, and thereafter at intervals not to exceed 400 hours TIS:

   To prevent failure of a main rotor blade (blade) cuff attachment fitting at a bolt hole location, loss of a blade, and subsequent loss of control of the helicopter, accomplish the following:

   (a) Inspect both upper and lower blade surfaces of each blade cuff for cracks (see Figure 1) as follows:

   (1) Use a mild liquid detergent or equivalent to remove all dirt from the blade cuff.

   (2) Inspect the blade cuff for cracks, paying particular attention to the area around the attaching bolts, using a 10-power or higher magnifying glass.

   (3) If a crack is suspected, remove any paint and clean the area under inspection using a Naptha-type solvent or equivalent, and conduct a dye penetrant inspection. Completely isolate the area under inspection with self-adhesive aluminum tape to prevent solvent or penetrating dye seepage into the other areas of the blade.

   (b) If a crack is detected, remove the blade and replace it with an airworthy blade.

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   (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, 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.

   (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 3: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD 96-081-036(B)R1 and AD 96- 082-054(B)R1, both dated April 24, 1996.

   Issued in Fort Worth, Texas, on October 27, 1998. Eric Bries, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.

   [FR Doc. 98-29378Filed11-2-98; 8:45 am]

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