This unsafe condition is likely to exist or develop on other helicopters of the same type designs. Therefore, the proposed AD would require:

We estimate that this proposed AD would affect 20 helicopters of U.S. registry, and the proposed actions would take the following approximate number of work hours per helicopter to accomplish at an average labor rate of $85 per work hour:

We have determined that this proposed AD would not have federalism implications under Executive Order 13132. Additionally, this proposed AD would 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 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. 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 a draft economic evaluation of the estimated costs to comply with this proposed AD. See the AD docket to examine the draft 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,
[[Page 39194]]
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.

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 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:
Arrow Falcon Exporters, Inc. (Previously Utah State University); Firefly Aviation Helicopter Services (Previously Erickson AirCrane Co.); California Department of Forestry; Garlick Helicopters, Inc.; Global Helicopter Technology, Inc.; Hagglund Helicopters, LLC (Previously Western International Aviation, Inc.); International Helicopters, Inc.; Precision Helicopters, LLC; Robinson Air Crane, Inc.; San Joaquin Helicopters (Previously Hawkins and Powers Aviation, Inc.); S.M.&T. Aircraft (Previously US Helicopters, Inc., UNC Helicopter, Inc., Southern Aero Corporation, and Wilco Aviation); Smith Helicopters; Southern Helicopter, Inc.; Southwest Florida Aviation International, Inc. (Previously Jamie R. Hill and Southwest Florida Aviation); Tamarack Helicopters, Inc. (Previously Ranger Helicopter Services, Inc.); US Helicopter, Inc. (Previously UNC Helicopter, Inc.); West Coast Fabrication; and Williams Helicopter Corporation (Previously Scott Paper Co.). Docket No. FAA 20100564; Directorate Identifier 2010SW13AD.

Applicability: Model HH1K, TH1F, TH1L, UH1A, UH1B, UH1E, UH1F, UH1H, UH1L, and UH1P helicopters, and Southwest Florida Aviation Model UH1B (SW204 and SW204HP) and UH1H (SW205)
helicopters, with main rotor grip (grip), part number (P/N) 204011 121009, 121, or ASI40111219, installed; or with grip, P/N 204 011121005 or 113, if the grip was ever installed on a Model 205B or a Model UH1N helicopter, or P/N 204011121117, installed, if the grip was ever installed on a Model 205B helicopter, certificated in any category.

Compliance: Required as indicated.

To prevent failure of a grip, separation of a main rotor blade, and subsequent loss of control of the helicopter, accomplish the following:
(a) Within 10 hours timeinservice (TIS), unless accomplished previously, create a component history card or equivalent record and determine and record the total hours TIS for each grip. If the total hours TIS cannot be determined from the helicopter records, assume and record 50 hours TIS for each month for which the hours cannot be determined with the grip installed on any helicopter. Continue to count and record the hours TIS and begin to count and record the number of times the helicopter engine(s) are started (engine start/ stop cycles).
(b) Within 10 hours TIS, unless accomplished previously, and then at intervals not to exceed 25 hours TIS, without removing the main rotor blades:
(1) Clean the exposed surfaces of the upper and lower tangs of each grip with denatured alcohol and wipe dry.
(2) Using a 10power or higher magnifying glass, visually inspect the exposed surfaces of the upper and lower tangs of each grip for a crack. Pay particular attention to the lower surface of each lower grip tang from the main rotor blade boltbushing flange to the leading and trailing edge of each grip tang. See Figure 1 of this AD.
BILLING CODE 491013P
[[Page 39195]]
[GRAPHIC] [TIFF OMITTED] TP08JY10.000
BILLING CODE 491013C
(c) At the intervals shown in Table 1 of this AD, ultrasonic (UT) inspect each grip for a crack in accordance with the Bell Helicopter Textron, Inc. (BHTI) Nondestructive Inspection Procedure, Log No. 00340, Revision E, dated April 9, 2002.
Table 1 Thereafter, at intervals not Within 30 to exceed the following number days, for a of hours TIS or the engine grip with the start/stop cycles, whichever UT inspect grip, P/N following or occurs first: more hours

FOR FURTHER INFORMATION CONTACT

DOT/FAA Southwest Region, Michael Kohner, ASW170, Aviation Safety Engineer, Rotorcraft Directorate, Rotorcraft Certification Office, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 2225170, fax (817) 2225783.