AD 2004-24-08 SUPERSEDED

This amendment adopts a new airworthiness directive (AD) for the specified Bell Helicopter Textron Canada (BHTC) model helicopters. This action requires an initial inspection and, at specified intervals, certain repetitive checks and inspections of the tail rotor blade (blade) for a deformation, a crack, and a bent or deformed tail rotor weight (weight). Also, this action requires, before further flight, replacing each blade with an airworthy blade if a deformation, a crack, or a bent or deformed weight is found. This amendment is prompted by three reports of skin cracks originating near the blade trailing edge balance weight. This condition, if not detected, could result in blade failure and subsequent loss of control of the helicopter.

Final rule; request for comments.

2004-24-08 Bell Helicopter Textron Canada: Amendment 39-13884. Docket No. 2004-SW-12-AD. \n\n\tApplicability: Model 206A, B, L, L-1, L-3, and L-4 helicopters, with a tail rotor blade (blade) with the following part number (P/N) and serial number (S/N) installed, certificated in any category. \n\n\n\n\n\nModel 206A & B; Blade, P/N 206-016-201- \n133, S/N with prefix ??CS''and no ??V''suffix \n\nModel 206A, B, L, L-1, L-3, & L-4, Blade, P/N 206-016-201-131, S/N with prefix ??CS''and \nno ??V''suffix \n1381 through 1442 \n7000 through 7018 \n10174 through 10218. \n1492 through 1517 \n7020 through 7043 \n10220. \n1520 through 1542 \n7045 through 7050 \n10232. \n1550 \n7052 through 7132 \n10235. \n1556 \n7134 through 7246 \n10237 through 10241. \n1560 \n7248 through 7270 \n10244. \n1562 \n7272 through 7277 \n10245. \n1564 through 1567 \n7279 through 7339 \n10248. \n1569 through 1606 \n7342 through 7368 \n10250 through 10264. \n1609 \n7784 \n10266 through 10268. \n1611 \n7786 \n10270 through 10274. \n1612 \n7788 \n10276 through 10278. \n1614 through 1631 \n7790 through 7796 \n10280 through 10282. \n1633 through 1675 \n7798 through 7819 \n10284 through 10292. \n1677 \n7821 through 7833 \n10296. \n1678 \n7835 through 7839 \n10300 through 10330. \n1680 through 1682 \n7841 through 8001 \n10332. \n1684 through 1787 \n8003 through 8026 \n10333. \n1789 through 1803 \n8029 through 8061 \n10335 through 10347. \n1810 through 1812 \n8064 through 8117 \n10349. \n1814 \n8119 \n10351 through 10359. \n1816 \n\n\n1820 \n8142 through 8176 \n10367. \n1823 through 1831 \n8178 through 8262 \n10373. \n1834 through 1836 \n8264 through 8294 \n10374. \n1838 \n8298 through 8368 \n10377 through 10385. \n1840 through 1844 \n8370 through 8375 \n10387 through 10408. \n1846 \n8378 through 8416 \n10410. \n1848 through 1882 \n8419 \n10414 through 10417. \n1884 through 1887 \n8421 \n10419 through 10427. \n1889 through 1893 \n8425 through 8428 \n10430. \n1896 through 1898 \n8430 through 8438 \n10432. \n1900 \n8440 \n10437. \n1904 \n8441 \n10438. \n1909 through 1912 \n8443 \n10442 through 10445. \n1915 \n8445 through 8447 \n10458 through 10466. \n1916 \n8449 through 8606 \n10469. \n1919 through 1921 \n8608 through 8622 \n10470. \n1924 \n8624 through 8626 \n10474. \n1928 through 1931 \n8628 through 8632 \n10476 through 10478. \n1933 \n8635 through 8653 \n10480 through 10487. \n1934 through 1939 \n8655 through 8686 \n10489 through 10491. \n1943 \n8690 \n10493 through 10495. \n1945 \n8692 through 8700 \n10497 through 10503. \n1947 \n8703 through 8715 \n10505 through 10588. \n1948 \n8717 through 8722 \n10591 through 10606. \n1952 through 1957 \n8724 through 8742 \n10608 through 10610. \n1960 \n8745 through 8828 \n10612 through 10620. \n1962 through 1965 \n8830 through 8835 \n10623. \n\n8838 through 8840 \n10624. \n\n8842 through 8881 \n10631 through 10655. \n\n8883 through 9032 \n10657 through 10669. \n\n9034 through 9139 \n10672. \n\n9141 through 9198 \n10673. \n\n9200 \n10676 through 10678. \n\n9202 through 9302 \n10680 through 10683. \n\n9304 through 9339 \n10685. \n\n9341 through 9371 \n10687. \n\n9373 through 9411 \n10689 through 10702. \n\n9413 \n10707. \n\n9415 through 9417 \n10712. \n\n9419 through 9496 \n10715. \n\n9498 through 9585 \n10730. \n\n9587 through 9594 \n10732 through 10734. \n\n9596 through 9618 \n10736. \n\n9621 through 9629 \n10738. \n\n9632 through 9642 \n10739. \n\n9645 through 9651 \n10746. \n\n9653 through 9673 \n10750. \n\n9675 through 9707 \n10756. \n\n9709 through 9724 \n10760. \n\n9727 through 9731 \n10761. \n\n9733 through 9735 \n10765. \n\n9737 through 9739 \n10770. \n\n9741 through 9748 \n10774 through 10776. \n\n9751 through 9785 \n10778. \n\n9787 \n10781. \n\n9788 \n10783 through 10785. \n\n9790 through 9792 \n10792. \n\n9795 through 9847 \n10794. \n\n9849 through 9928 \n10798. \n\n9930 through 9937 \n10799. \n\n9940 through 9942 \n10806 through 10808. \n\n9944 through 9952 \n10811. \n\n9955 through 9972 \n10814 through 10822. \n\n9974 through 9989 \n10824. \n\n9991 through 9995 \n10825. \n\n9997 through 10004 \n10829. \n\n10006 through 10009 \n10831. \n\n10011 \n10917.\n\n10013 through 10018 \n 10923. \n\n10021 through 10030 \n10931. \n\n10034 \n10936. \n\n10036 through 10057 \n10937. \n\n10061 through 10082 \n10940. \n\n10090 through 10092 \n10943. \n\n10094 through 10100 \n10945. \n\n10116 \n10947. \n\n10119 \n10948. \n\n10121 \n10964. \n\n10123 through 10134 \n10965. \n\n10136 through 10140 \n10973. \n\n10142 through 10144 \n10982. \n\n10146 through 10172 \n10985.\n\n\n 10986. \n\n\n\n\n\n\n\n\tCompliance: Required as indicated. \n\n\tTo prevent blade failure and subsequent loss of control of the helicopter, do the following: \n\t(a) Before further flight, unless accomplished previously, and before installing any blade with a P/N and S/N listed in the applicability section of this AD, clean the blade. Using a 10X or higher magnifying glass, inspect both sides of each blade for a deformation, a crack, and a bent ordeformed weight in the area shown in Figure 1 of this AD. \n\n\tNote 1: Paint irregularities on the blade may indicate a crack. \n\n\n\n\n\t(b) After doing paragraph (a) of this AD, at the following intervals, clean both sides of each blade and do either paragraph (1) or (2) as follows: \n\n\t(1) At intervals not to exceed 12 hours time-in-service (TIS), using a 10X or higher magnifying glass, inspect both sides of each blade for a deformation, a crack, and a bent or deformed weight in the area shown in Figure 1 of this AD, or \n\n\t(2) Inspect and check both sides of each blade for a deformation, a crack, and a bent or deformed weight in the area shown in Figure 1 of this AD as follows: \n\n\t(i) Using a 10X or higher magnifying glass, inspect at intervals not to exceed 24 hours TIS, and\n\n\t(ii) Check at intervals not to exceed 3 hours TIS between the inspections required by paragraph (b)(2)(i) of this AD. An owner/ operator (pilot), holding at least a private pilot certificate, may perform this visual check and must enter compliance with this paragraph into the helicopter maintenance records by following 14 CFR sections 43.11 and 91.417(a)(2)(v). \n\n\t(c) Before further flight, replace any blade that has a deformation, a crack, or a bent or deformed weight with an airworthy blade. \n\n\tNote 2: Bell Helicopter Textron Alert Service Bulletin No. 206- 04-100 for Model 206A and B and No. 206L-04-127 for Model 206L series, both Revision B, both dated May 28, 2004, pertain to the subject of this AD. \n\n\t(d) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Safety Management Group, Rotorcraft Directorate, FAA, for information about previously approved alternative methods of compliance. \n\n\t(e) This amendment becomes effective on December 16, 2004. \n\n\tNote 3: The subject of this AD is addressed in Transport Canada (Canada) AD No. CF-2004-05R1, dated June 28, 2004.

This amendment adopts a new AD for the specified BHTC model helicopters. This action requires an initial inspection and certain repetitive checks and inspections of the blade, at specified intervals, for a deformation, a crack, and a bent or deformed weight. Also, this action requires, before further flight, replacing each blade with an airworthy blade if a deformation, a crack, or a bent or deformed weight is found. This amendment is prompted by three reports of skin cracks originating near the blade trailing edge balance weight. In two reports, a loss of the weight and a strip of material along the trailing edge led to an imbalance and fracture of three of the four tail rotor gearbox attachment bolts. In one of these incidents the gearbox shifted resulting in failure of the drive shaft and loss of yaw control. This condition, if not detected, could result in blade failure and subsequent loss of control of the helicopter. \n\n\tBHTC has issued Alert Service Bulletin No. 206-04-100 for Model 206A and B and No. 206L-04-127 for Model 206L series helicopters, both Revision B, both dated May 28, 2004. These service bulletins specify checking and inspecting the blades for a deformation, a crack, and a bent or deformed weight and a one-time inspection by Rotor Blades Inc. in Louisiana, USA, and if the blades pass the one-time inspection, adding a "V" at the end of the serial number. The service bulletins also specify replacing any blade with a deformation, a crack, or bent or deformed weight. \n\n\tTransport Canada, the airworthiness authority for Canada, notified the FAA that an unsafe condition may exist on these helicopter models. Transport Canada advises of three reports of skin cracks originating near the blade trailing edge balance weight. Two of the occurrences caused a loss of the weight and a strip of material along the trailing edge leading to an imbalance, which caused the fracture of three of the four tail rotor gearbox attachments. One of these occurrences resulted in the gearbox shifting that caused failure of the drive shaft and resulting loss of yaw control. Transport Canada classified the alert service bulletins as mandatory and issued AD No. CF-2004-05R1, dated June 28, 2004, to ensure the continued airworthiness of these helicopters in Canada. \n\n\tThese helicopter models are manufactured in Canada 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, Transport Canada has kept the FAA informed of the situation described above. The FAA has examined the findings of Transport Canada, 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 helicopters of the same type designs registered in the United States. Therefore, the FAA is issuing this AD to detect a blade with a deformation, a crack, or a bent or deformed weight and to prevent blade failure and subsequent loss of control of the helicopter. This AD requires the following for the specified BHTC helicopters with certain blade part numbers and serial numbers: \n\n\tBefore further flight, unless accomplished previously, and before installing any blade with an affected part number and serial number, cleaning the blade. Then, using a 10X or higher magnifying glass, inspecting both sides of each blade for a deformation, a crack, and a bent or deformed weight. \n\n\tThereafter, cleaning both sides of each blade and using a 10X or higher magnifying glass, inspecting for a deformation, a crack, and a bent or deformed weight as follows: \n\n\tAt intervals not to exceed 12 hours time-in-service (TIS), or \n\n\tAt intervals not to exceed 24 hours TIS and checking both sides of each blade for a deformation, a crack, and a bent or deformed weightat intervals not to exceed 3 hours TIS between inspections. An owner/operator (pilot) may perform the 3-hour TIS check for deformed or cracked blades and for bent or deformed weights. Pilots may perform these checks because they require no tools, can be done by observation, and can be done equally well by a pilot or a mechanic. However, the pilot must enter compliance with these requirements into the helicopter maintenance records by following 14 CFR 43.11 and 91.417(a)(2)(v). \n\n\tBefore further flight, replacing each blade with an airworthy blade if you find a deformation, a crack, or a bent or deformed weight. \n\n\tThe 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 blade, for a deformation, a crack, and a bent or deformed weight is required before further flight and at short specified time intervals, and this AD must beissued immediately. \n\n\tSince a situation exists that requires the immediate adoption of this regulation, it is found that notice and opportunity for prior public comment hereon are impracticable, and that good cause exists for making this amendment effective in less than 30 days.\n\n\tThe FAA estimates that this AD will: \n\n\tAffect 2194 helicopters. \n\n\tTake about 1/4 work hour for a blade check or inspection and 3 work hours to replace one blade at an average labor rate of $65 per work hour. \n\n\tRequired parts will cost about $5,848 per helicopter. (The service bulletin states that warranty credit will be given based on hour usage on the blade with remaining life hours and other restrictions.) Based on these figures, the total estimated cost impact of the AD on U.S. operators is $21,315,807, assuming 226 checks or inspections and replacing one blade on each helicopter in the fleet. \n\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 RulesDocket 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 to this rule must submit a self- addressed, stamped postcard on which the following statement is made: "Comments to Docket No. 2004-SW-12-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 economic 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\n1. 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\n2. Section 39.13 is amended by adding a new airworthiness directive to read as follows:

Submit comments in triplicate to the Federal Aviation Administration (FAA), Office of the Regional Counsel, Southwest Region, Attention: Rules Docket No. 2004-SW-12-AD, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. You may also send comments electronically to the Rules Docket at the following address: 9-asw-adcomments@faa.gov.

Sharon Miles, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort Worth, Texas 76193-0111, telephone (817) 222-5122, fax (817) 222- 5961.