On December 27, 2001, the FAA issued Emergency AD 2001-26-55 for ECF Model AS350B, AS350B1, AS350B2, AS350BA, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, and AS355N helicopters which requires, before further flight and thereafter at specified intervals, visually checking each blade skin for a crack and replacing any cracked blade before further flight. That action was prompted by the discovery of cracks in the skin of a blade. This condition, if not detected, could result in failure of a blade, severe vibration, loss of the TGB, and subsequent loss of control of the helicopter. \n\n\tThe FAA has reviewed Eurocopter Alert Telex No. 05.00.40 and 05.00.38, dated December 17, 2001, which describes procedures for visually checking the blade for cracks on the blade pressure face and blade suction face and requires replacing the blade before further flight if a crack is discovered. \n\n\tThe Direction Generale de L'Aviation Civile (DGAC), whichis the airworthiness authority for France, notified the FAA that an unsafe condition may exist on these helicopter models. The DGAC advises of a report where separation of a blade trailing edge section occurred due to crack growth in the blade skin. The unbalance caused by the loss of the blade section can cause the TGB to be torn off the tailboom. The DGAC classified the service telex as mandatory and issued AD No. T2001-640-089(A) and T2001-641-067(A), dated December 20, 2001, to ensure the continued airworthiness of these helicopters. \n\n\tThese helicopter models are manufactured in France and are 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, the DGAC has kept the FAA informed of the situation described above. The FAA has examined the findings of the DGAC, reviewed all available information, and determined that AD action is necessary for products of these type designs that are certificated for operation in the United States. \n\n\tThis unsafe condition is likely to exist or develop on other ECF Model AS350B, AS350B1, AS350B2, AS350BA, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, and AS355N helicopters of the same type designs. Therefore, the FAA issued Emergency AD 2001-26-55 to prevent failure of the blade, severe vibration, loss of the TGB, and subsequent loss of control of the helicopter. The AD requires, before further flight and thereafter before the first flight of each day or at intervals not to exceed 10 hours TIS, whichever occurs first, visually checking both sides (front and back) of each blade skin in the area of the trailing edge tab for a crack (see Area A of Figure 1 of this AD). Replacing any cracked blade is also required before further flight. \n\n\tThe visual check required by this AD may be performed by an owner/operator (pilot) holding at least a private pilot certificate and must be enteredinto the aircraft records showing compliance with the visual check requirements of paragraph (a) of this AD. However, if the owner/operator (pilot) is in doubt about the existence of a crack, an inspection with a magnifying glass must be accomplished by a mechanic. The short compliance time involved is required because the previously described critical unsafe condition can adversely affect the structural integrity and controllability of the helicopter. Therefore, the actions described previously are required before further flight and at the specified time intervals, and this AD must be issued immediately. \n\n\tSince 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 December 27, 2001, to all known U.S. owners and operators of ECF Model AS350B, AS350B1, AS350B2, AS350BA, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, and AS355N 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. \n\n\tThe FAA estimates that 653 helicopters of U.S. registry will be affected by this AD, that it will take approximately \1/4\ work hour per helicopter for each visual check, and that the average labor rate is $60 per work hour. Based on these figures, the total cost impact of the AD on U.S. operators is estimated to be $9795 to inspect the helicopter blade on each helicopter once. \n\nComments Invited \n\n\tAlthough this action is in the form of a final rule that involves requirements affecting flight safety and, thus, was not preceded by notice and an opportunity for public comment, comments are invited on this rule. Interested persons are invited to comment on this rule by submitting such written data, views, or arguments as they may desire. Communications should identify the Rules Docket number and be submitted in triplicate to the address specified under the caption ADDRESSES. All communications received on or before the closing date for comments will be considered, and this rule may be amended in light of the comments received. Factual information that supports the commenter's ideas and suggestions is extremely helpful in evaluating the effectiveness of the AD action and determining whether additional rulemaking action would be needed. \n\n\tComments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify the rule. All comments submitted will be available in the Rules Docket for examination by interested persons. A report that summarizes each FAA-public contact concerned with the substance of this AD will be filed in the Rules Docket. \n\n\tCommenters wishing the FAA to acknowledge receipt of their mailed comments submitted in response tothis rule must submit a self-addressed, stamped postcard on which the following statement is made: "Comments to Docket No. 2001-SW-74-AD." The postcard will be date stamped and returned to the commenter. \n\n\tThe regulations adopted herein 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. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132. \n\n\tThe FAA has determined that this regulation is an emergency regulation that must be issued immediately to correct an unsafe condition in aircraft, and that it is not a "significant regulatory action" under Executive Order 12866. It has been determined further that this action involves an emergency regulation under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). If it is determined that this emergency regulation otherwise would be significant under DOT Regulatory Policies and Procedures, a final regulatory evaluation will be prepared and placed in the Rules Docket. A copy of it, if filed, may be obtained from the Rules Docket at the location provided under the caption ADDRESSES. \n\nList of Subjects in 14 CFR Part 39 \n\n\tAir transportation, Aircraft, Aviation safety, Safety. \n\nAdoption of the Amendment \n\n\tAccordingly, 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: \n\nPART 39--AIRWORTHINESS DIRECTIVES \n\n\t1. The authority citation for part 39 continues to read as follows: \n\n\tAuthority: 49 U.S.C. 106(g), 40113, 44701. \n\nSec. 39.13 (Amended) \n\n\t2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: