Based on these figures, we estimate the total cost impact of the AD on U.S. operators to be $365,218, assuming the bearing is replaced on the entire fleet after 1 oil level check, 1 magnetic plug inspection, and 1 end play inspection.

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 removing Amendment 3914581 (71 FR 25930, May 3, 2006), and by adding a new airworthiness directive (AD), Amendment 3915290, to read as follows:
20072508 Eurocopter France: Amendment 3915290. Docket No. FAA 200728448; Directorate Identifier 2006SW24AD. Supersedes AD 20060910, Amendment 3914581, Docket No. FAA200624588,
Directorate Identifier 2006SW07AD.

Applicability

Model SA365N1, AS365N2, AS 365 N3, SA366G1, EC 155B, and EC155B1 helicopters, with a tail rotor (T/R) pitch control rod assembly double bearing (bearing) installed, certificated in any category.
Compliance

Required as indicated.

To detect metal chips on the magnetic plug to prevent damage to the bearing resulting in end play, loss of T/R pitch control, and subsequent loss of control of the helicopter, do the following: (a) Before the first flight of each day for Model SA365N1, AS 365N2, AS 365 N3, and SA366G1 helicopters, check the T/R gearbox (TGB) oil level. An owner/operator (pilot) holding at least a private pilot certificate may perform the visual check of the oil level but must enter compliance into the aircraft maintenance records in accordance with 14 CFR 43.11 and 91.417(a)(2)(v). (b) If the oil level is not at maximum during the check in paragraph (a) of this AD, before further flight, a qualified mechanic must fill it to the maximum level.
(c) During each required inspection not to exceed 15 hours time inservice (TIS) or 7 days, whichever occurs first, if the oil level is not at the maximum level, fill it to the maximum level for Model EC 155B and EC155B1 helicopters.
(d) Inspect the magnetic plug of the TGB for any chips as follows:
(1) At intervals not to exceed 25 hours TIS for helicopters with a magnetic plug without a chip electrical indication in the cockpit, or
(2) At intervals not to exceed 100 hours TIS and after any illumination of the TGB ``CHIP'' warning light for helicopters with a chip electrical indication in the cockpit.
(e) If you find any chips during the inspection in paragraph (d) of this AD, before further flight, follow the Accomplishment Instructions, paragraph 2.B.2.b), of Eurocopter Alert Service Bulletin No. 05.00.54 for Model SA365N1, AS365N2, AS 365 N3; No. 05A015 for Model EC 155B and EC155B1; or No. 05.37 for Model SA 366G1, all dated August 25, 2006 (ASBs), as appropriate for your model helicopter.
(1) If the quantity of chips on the magnetic plug, as referenced in the Operational Procedures, paragraph 2.B.2.b)1) of the ASBs is at or above the removal criteria, before further flight, replace the TGB with an airworthy TGB.
(2) If the quantity of chips on the magnetic plug is below the removal criteria, as referenced in the Operational Procedure, paragraph 2.B.2.b)2) of the ASBs.
(i) Inspect for axial play in the T/R hub pitch control change spider (spider) by following the additional steps in the Operational Procedure, paragraph 2.B.2.b)2) of the ASBs.
(ii) If there is axial play in the spider, before further flight, replace the bearing with an airworthy bearing.
(f) 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: Uday Garadi, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort Worth, Texas 761930110, telephone (817) 2225123, fax (817) 2225961.
(g) Special flight permits will not be issued.
(h) Do the inspections by following the specified portions of Eurocopter Alert Service Bulletin No. 05.00.54 for Model SA365N1, AS365N2, AS 365 N3; No. 05A015 for Model EC 155B and EC155B1; or No. 05.37 for Model SA366G1 helicopters, all dated August 25, 2006, as applicable. 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
[[Page 69606]]
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 202 7416030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html .
(i) This amendment becomes effective on January 14, 2008.

Note: The subject of this AD is addressed in European Aviation Safety Agency Revised Emergency AD No. 20060258 R1E on August 29, 2006, which replaced AD No. 20060051E, dated February 20, 2006.

Issued in Fort Worth, Texas, on November 27, 2007. Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E723605 Filed 12707; 8:45 am]
BILLING CODE 491013P

FOR FURTHER INFORMATION CONTACT Uday Garadi, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort Worth, Texas 761930110, telephone (817) 2225123, fax (817) 2225961.