On February 24, 2010, the FAA issued EAD 2010-05-51 for the ECF Model EC120B helicopters. This AD requires, within specified intervals, inspecting the rotor hub for a crack and removing the identification plate and cleaning the area. If you find scoring, paint flaking or left-over identification plate adhesive, the AD requires sanding the area until the primer coat becomes visible and inspecting the rotor hub for a crack. If you find a crack, the AD requires, before further flight, replacing the rotor hub with an airworthy rotor hub. This amendment is prompted by an emergency landing due to excessive vibrations originating from the main rotor. After an investigation, it was determined the rotor hub had failed in the attachment area of one of the three drag damper fittings. This condition, if not corrected, could result in failure of a hub, excessive vibrations, loss of a main rotor blade, and subsequent loss of control of the helicopter.
EASA, the airworthiness authority for France, notified the FAA that an unsafe condition may exist on these helicopter models. EASA advises of an emergency landing due to a set of amplitude vibrations originating from the main rotor.
ECF has issued Emergency Alert Service Bulletin No. 05A012, Revision 1, dated February 19, 2010 (EASB), which specifies inspecting the rotor hub for a crack. Also, if you find local deterioration (scoring or paint spalling), the EASB specifies sanding the area, removing the finish paint until the primer coat becomes visible, and inspecting the area for a crack. If you find a crack, the EASB specifies replacing the affected rotor hub with a new rotor hub.
EASA classified this service bulletin as mandatory and issued AD No. 2010-0026-E, dated February 19, 2010, to ensure the continued airworthiness of these helicopters in France.
This AD differs from the MCAI AD in that we refer to flight hours as time-in-service (TIS). Also, we do not require you to contact the manufacturer.
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 with France, EASA, their technical agent, has kept the FAA informed of the situation described above. The FAA has examined the findings of 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.
Since the unsafe condition described is likely to exist or develop on other ECF Model EC120B helicopters of the same type design, the FAA issued EAD 2010-05-51. The AD requires, at specified intervals, inspecting the rotor hub for a crack. If you find scoring, paint flaking or left-over identification plate adhesive, the AD requires sanding the area and inspecting the specified areas of the rotor hub for a crack. If you find a crack, the AD requires, before further flight, replacing the rotor hub with an airworthy rotor hub. The actions must be done by following specified portions of the EASB. The short compliance time involved is required because the previously described critical unsafe condition can adversely affect the controllability and structural integrity of the helicopter. Therefore, inspecting the rotor hub for a crack is required within 15 hours TIS, and if you find a crack, replacing the rotor hub with an airworthy rotor hub is required before further flight, and this AD must be issued immediately.
Since it was found that immediate corrective action was required, notice and opportunity for prior public comment thereon were impracticable and contrary to the public interest, and good cause existed to make the AD effective immediately by individual letters issued on February 24, 2010, to all known U.S. owners and operators of ECF Model EC120B helicopters. These conditions still exist, and the AD is hereby published in the Federal Register as an amendment to 14 CFR 39.13 to make it effective to all persons. However, we made a minor editorial change in paragraph (a) of this AD. We added the word, "Eurocopter'' in front of the words, "Emergency Alert Service Bulletin,'' which we inadvertently omitted in the EAD. We have determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD.
The FAA estimates that this AD will affect 114 helicopters of U.S. registry, and inspecting the rotor hub for a crack will take a minimal amount of time. It will take about 1 hour to do the sanding, assuming 37 rotor hubs require sanding. It will take about 6 hours to replace a rotor hub, assuming 2 helicopters will require replacement of a rotor hub. The average labor rate is $85 per hour. Required parts will cost about $61,685 per helicopter. Based on these figures, we estimate the total cost impact of the AD on U.S. operators to be $127,535.
Comments Invited
This AD is a final rule that involves requirements that affect flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any written data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include "Docket No. FAA-2010-0410; Directorate Identifier 2010-SW-024-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD. We will consider all comments received by the closing date and may amend the 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 AD. 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 the comment. You may review the DOT's complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477-78).
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: