Federal Register: July 8, 2010 (Volume 75, Number 130)
DOCID: fr08jy10-27 FR Doc 2010-16511
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
CFR Citation: 14 CFR Part 39
Docket ID: [Docket No. FAA-2010-0564; Directorate Identifier 2010-SW-13-AD]
RIN ID: RIN 2120-AA64
NOTICE: PROPOSED RULES
ACTION: Airworthiness Directives:
DOCUMENT ACTION: Notice of proposed rulemaking (NPRM).
Airworthiness Directives; Arrow Falcon Exporters, Inc. (Previously Utah State University), et al., Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P Helicopters; and Southwest Florida Aviation Model UH-1B (SW204 and SW204HP) and UH-1H (SW205) Helicopters
DATES: Comments must be received on or before September 7, 2010.
This document proposes adopting a new airworthiness directive (AD) for the specified typecertificated military surplus helicopters. The AD would require: Creating a component history card or equivalent record for each main rotor grip (grip); determining and recording the total hours timeinservice (TIS) for each grip; visually inspecting the upper and lower tangs of the grip for a crack; inspecting the grip buffer pads for delamination and if delamination is present, inspecting the grip surface for corrosion or other damage; inspecting the grip for a crack using ultrasonic (UT) and fluorescentpenetrant inspection methods; and establishing a retirement life for certain grips. This proposal is prompted by three inflight failures of grips installed on Bell Helicopter Textron, Inc. (BHTI) Model 212 helicopters, which resulted from cracks originating in the lower main rotor blade bolt lug. The actions specified by the proposed AD are intended to prevent failure of the grip, separation of a main rotor blade, and subsequent loss of control of the helicopter.
Arrow Falcon Exporters, Inc.; et al.,
We invite you to submit any written data, views, or arguments regarding this proposed AD. Send your comments to the address listed under the caption ADDRESSES. Include the docket number ``FAA20100564, Directorate Identifier 2010SW13AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed rulemaking. Using the search function of our docket Web site, you can find and read the comments to any of our dockets, including the name of the individual who sent or signed the comment. You may review the DOT's complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 1947778).
Examining the Docket
You may examine the docket that contains the proposed AD, any
comments, and other information in person at the Docket Operations
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Operations office (telephone
(800) 6475527) is located in Room W12140 on the ground floor of the West Building at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. Discussion
This document proposes adopting a new AD for Model HH1K, TH1F,
TH1L, UH1A, UH1B, UH1E, UH1F, UH1H, UH1L, and UH1P helicopters;
and Southwest Florida Aviation Model UH1B (SW204 and SW204HP) and UH
1H (SW205) helicopters. The AD would require creating a component
history card or equivalent record for each grip; determining and
recording the total hours TIS for each grip; visually inspecting the
upper and lower tangs of the grip for a crack; inspecting the grip
buffer pads for delamination, and if delamination is present,
inspecting the grip surface for corrosion or other damage; inspecting
the grip for a crack using UT and fluorescentpenetrant inspection
methods; and establishing a retirement life for grips, part number (P/ N) 204011121009, ASI40111219, and P/N 204011121121. This
proposal is prompted by three inflight failures of grips, P/N 204011 121009 and 121, installed on BHTI Model 212 helicopters, which resulted from cracks originating in the lower main rotor blade bolt lug. Grips with these same P/Ns, and those produced under an FAA Parts Manufacturing Approval (PMA) that have a design approval based on their being identical to the original BHTImanufactured grips, are eligible for installation on certain modified Model HH1K, TH1F, TH1L, and UH 1 helicopters. These helicopters have an FAAapproved modification which increases their power rating to the equivalent of the twinengine Model 212 helicopter power rating. Grips, P/N 204011121005, and 113, are also affected by the proposed AD if they were ever installed on a Model 205B or Model UH1N helicopter; and grip, P/N 204011121 117, is also affected if it was ever installed on a Model 205B helicopter. Additionally, BHTI has developed a new, improved replacement grip that will not require the repetitive UT inspections and will have a 25,000 hour TIS and 500,000 Retirement Index Number (RIN) retirement life for the BHTI Model 212 helicopters. The RIN count accumulated for the new replacement grips will be increased by one for each takeoff or each external lift event. The actions specified by the proposed AD are intended to prevent failure of the grip, separation of a main rotor blade, and subsequent loss of control of the helicopter.
We have reviewed the following service information:
Both ASBs contain BHTI Nondestructive Inspection Procedure, Log. No. 00340, Revision E, dated April 9, 2002, which describes procedures for an UT inspection of the grip. We have also reviewed BHTI Operations Safety Notice (OSN) 204856, OSN 205859, and OSN 2128513, all dated November 14, 1985, which describe a cracked Model 212 helicopter grip that was returned to BHTI.
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,
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
[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.