Based on these figures, we estimate the total cost impact of this AD on U.S. operators to be $10,271, assuming one copilot twist grip assembly is replaced in one helicopter, that the twist grip adjusting gage (tool) and spring scale needed are onsite and available, and that the copilot twist grip assembly is not covered by warranty, and no pilot twist grip assembly will need to be replaced. The manufacturer has indicated that parts are covered by warranty up to 1,000 hours or 2 years after the purchase of a new helicopter, however, it indicated that labor is not covered by a warranty.

Regulatory Findings

We have determined that this AD will not have federalism implications under Executive Order 13132. This AD 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.

For the reasons discussed above, I certify that the 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. 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.

We prepared an economic evaluation of the estimated costs to comply with this AD. See the AD docket to examine the economic evaluation. Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority.

We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.

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 39AIRWORTHINESS 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:

20080622 Eurocopter France: Amendment 3915434. Docket No. FAA200728229; Directorate Identifier 2006SW23AD.

Applicability: Model EC130 B4 helicopters, with a twist grip assembly, part number (P/N) 350A27520900, 350A27520901,
350A27520902, or 350A27520903, with a serial number below 64, installed on the pilot's side, and a twist grip assembly, P/N 350A27521201, with a serial number below 67, installed on the co pilot's side, certificated in any category.

Compliance: Required within 110 hours timeinservice (TIS) or 4 months, whichever occurs first, and before installing a replacement collective lever with an affected twist grip assembly on a helicopter, unless accomplished previously.

To detect a reduced bonding strength of the control pinion on the pilot and copilot collective lever drive tubes, which could lead to failure of a twist grip drive tube and control pinion bonded attachment, resulting in loss of engine throttle control and subsequent loss of control of the helicopter, accomplish the following:
(a) Inspect the pilot and copilot collective levers for proper bonding between the twist grip drive tubes and the control pinions in accordance with paragraphs 2.B.1. and 2.B.2. of the
Accomplishment Instructions, in Eurocopter, an EADS Company, Alert Service Bulletin EC130 No. 76A001, dated February 10, 2006, except you are neither required to contact the manufacturer nor return a noncompliant collective lever.
(b) If a twist grip turns when applying the 35N load to the twist grip, before further flight, replace the collective lever with an airworthy collective lever that has been inspected in accordance with paragraph (a) of this AD, or a collective lever with a twist grip assembly that is not listed in the Applicability of this AD. (c) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Safety Management Group, ATTN: Ed Cuevas, Aviation Safety Engineer, Rotorcraft Directorate, FAA, Fort Worth, Texas 761930111, telephone (817) 2225355, fax (817) 2225961, for information about previously approved alternative methods of compliance.
(d) The inspection and replacement, if necessary, shall be done in accordance with the specified portions of Eurocopter, an EADS Company, Alert Service Bulletin EC130 No. 76A001, dated February 10, 2006. The Director of the Federal Register approved this
incorporation by reference 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 750534005, telephone (972) 6413460, fax (972) 6413527. 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 National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 2027416030, or go to: http://www.archives.gov/federal_register/code_of_federal_ regulations/ibr_locations.html.
[[Page 15397]]
(e) This amendment becomes effective on April 28, 2008.

Note: The subject of this AD is addressed in EASA (France) AD 20060079, dated April 3, 2006.

Issued in Fort Worth, Texas, on March 10, 2008.
Mark R. Schilling,
Acting Manager, Rotocraft Directorate, Aircraft Certification Service. [FR Doc. E85494 Filed 32108; 8:45 am]
BILLING CODE 491013P

FOR FURTHER INFORMATION CONTACT Ed Cuevas, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Safety Management Group, Fort Worth, Texas 761930111, telephone (817) 2225355, fax (817) 2225961.