A proposal to amend 14 CFR part 39 to include an AD for the specified model helicopters was published in the Federal Register on May 21, 2007 (72 FR 28456). That action proposed to require, within 110 hours time-in-service (TIS) or 4 months, whichever occurs first, or before installing a collective lever with an affected grip assembly on a helicopter, inspecting the bonding between the twist grip drive tube and the control pinion on both the pilot and co-pilot collective lever. If debonding is present, replacing the collective lever before further flight was proposed.
The European Aviation Safety Agency (EASA) notified us that an unsafe condition may exist on Eurocopter Model EC 130 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. EASA advises that analysis of an incident that occurred during autorotation training revealed a failure of the twist grip drive tube and control pinion bonded attachment. The engine remained at idle speed although the twist grip had been turned back to the flight position. The autorotation procedure continued to the ground without damage to the helicopter. The failure has been attributed to non- compliant surface preparation during manufacture.
Eurocopter, an EADS Company, has issued Alert Service Bulletin EC130 No. 76A001, dated February 10, 2006, which specifies a check by use of a twist grip adjusting gauge of the bonding between the twist grip drive tube and the control pinion on both the pilot and co-pilot collective lever. EASA classified this service bulletin as mandatory and issued AD No. 2006-0079, dated April 3, 2006, to ensure the continued airworthiness of these helicopters in France.
This helicopter model is manufactured in France and is type certificated for operation in the United States under the provisions of 14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the applicable bilateral agreement, France, through the EASA, has kept the FAA informed of the situation described above. The FAA has examined the findings of the EASA, 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.
Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were received on the proposal or the FAA's determination of the cost to the public. The FAA has determined that air safety and the public interest require the adoption of the rule as proposed.
The FAA estimates that this AD will affect 73 helicopters of U.S. registry. The debonding inspection will take approximately 0.25 work hours per helicopter and replacing a collective lever will take approximately 2 workhours at an average labor rate of $80 per work hour. If replacement is necessary, required parts will cost approximately:
$8,651 for a co-pilot twist grip assembly, part number (P/ N) 350A27521201;
$12,542 for a pilot twist grip assembly, P/N 350A27520903;
$5 for a clamp, P/N ASNA0021;
$2 for a bolt, P/N 22125BC050014L; and
$1 for a nut, P/N 22431BC050L.
Based on these figures, we estimate the total cost impact of this AD on U.S. operators to be $10,271, assuming one co-pilot twist grip assembly is replaced in one helicopter, that the twist grip adjusting gage (tool) and spring scale needed are on-site and available, and that the co-pilot 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 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: