Final rule; request for comments.
We are publishing a new airworthiness directive (AD) for Bell Helicopter Textron Canada Limited (Bell) Model 206L, 206L-1, 206L-3, and 206L-4 helicopters with certain main rotor blades installed to reduce the life limit of those blades. This AD is prompted by two accidents and the subsequent investigations that revealed that, in each accident, a main rotor blade failed because of fatigue cracking. These actions are intended to prevent failure of the main rotor blade and subsequent loss of control of the helicopter.
This AD becomes effective May 4, 2012 to all persons except those persons to whom it was made immediately effective by Emergency AD No. 2012-02-51, issued on February 1, 2012, which contained the requirements of this AD.
We must receive comments on this AD by June 18, 2012.
You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically.
Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
Hand Delivery: Deliver to the “Mail” address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Examining the AD Docket: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the economic evaluation, and other information. The street address for the Docket Operations Office (telephone 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt.
For service information identified in this AD, contact Bell Helicopter Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437-2862 or (800) 363-8023, fax (450) 433-0272, or at http://www.bellcustomer.com/files/. You may review a copy of the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.
FOR FURTHER INFORMATION CONTACT:
Sharon Miles, Aerospace Engineer, FAA, Rotorcraft Directorate, Regulations and Policy Group, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5110, email firstname.lastname@example.org.
This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments prior to it becoming effective. However, we invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that resulted from adopting this AD. The most helpful comments reference a specific portion of the AD, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit them only one time.
We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this rulemaking during the comment period. We will consider all the comments we receive and may conduct additional rulemaking based on those comments.
Transport Canada Civil Aviation (TCCA) issued TCCA AD No. CF-2011-44R1, on February 1, 2012, to correct this same unsafe condition on the Bell Model 206 L, L-1, L-3, and L-4 helicopters. TCCA advises that there is no reliable inspection method to detect the cracks on these blades before blade failure and has reduced the life limit on all affected blades from 3,600 hours time-in-service (TIS) to 1,400 hours TIS and mandated removal from service of those blades that exceed the new life limit. Bell has determined that the fatigue cracks occurred as a result of the use by a Bell supplier of unapproved manufacturing processes, which have since been corrected, and are limited to a specific range of part numbers and serial numbers.
We issued EAD 2012-02-51 also on February 1, 2012, for Bell Model 206L, 206L-1, 206L-3, and 206L-4 helicopters with certain main rotor blades installed and reduced the life limit on these blades to correct the unsafe condition caused by this fatigue cracking.
These helicopters have been approved by the aviation authority of Canada and are approved for operation in the United States. Pursuant to our bilateral agreement with Canada, TCCA, its technical representative, has notified us of the unsafe condition described in the TCCA AD. We are issuing this AD because we evaluated all information provided by the TCCA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs.
Related Service Information
Bell Helicopter Alert Service Bulletin No. 206L-09-159 Revision A, dated November 13, 2009, describes procedures to identify and mark the affected main rotor blades, requires a “recurring wipe check,” and requires performing a one-time radiographic inspection with the results to be determined by Bell.
This AD requires reducing the life limit from 3,600 hours time-in-service (TIS) to 1,400 hours TIS for certain part-numbered and serial-numbered main rotor blades, revising the life limit in the Airworthiness Limitations section of the Instructions for Continued Airworthiness or maintenance manual, and recording the revised life limit on the component history card or equivalent record.
Costs of Compliance
We estimate that this AD will affect 697 helicopters of U.S. Registry. At an average labor rate of $85 per work-hour, we estimate the following costs:
- Determining the main rotor blades' part and serial numbers will require about 1 work-hour for a cost per helicopter of $85, or $59,245 for the U.S. fleet.
- Replacing an affected main rotor blade will require about 8 work-hours for labor cost of $680 per helicopter and parts costs of about $44,958 per helicopter, for a total cost per helicopter of $45,638.
FAA's Justification and Determination of the Effective Date
Providing an opportunity for public comments prior to adopting these AD requirements would delay implementing the safety actions needed to correct this known unsafe condition. Therefore, we find that the risk to the flying public justifies waiving notice and comment prior to the adoption of this rule because the required corrective actions must be accomplished before further flight, a very short period of time.
Since an unsafe condition exists that requires the immediate adoption of this AD, we determined that notice and opportunity for public comment before issuing this AD are impracticable and contrary to the public interest and that good cause exists for making this amendment effective in less than 30 days.
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.
We 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, I certify that this AD:
1. Is not a “significant regulatory action” under Executive Order 12866;
2. Is not a “significant rule” under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; and
4. 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 and placed it in the AD docket.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39—AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD):
2012-02-51 Bell Helicopter Textron Canada Limited: Amendment 39-17016; Docket No. FAA-2012-0395; Directorate Identifier 2012-SW-007-AD.
This AD applies to Bell Helicopter Textron Canada Limited (Bell) Model 206L, 206L-1, 206L-3, and 206L-4 helicopters, certificated in any category, with a main rotor blade part number (P/N) 206-015-001-107, 206-015-001-109, 206-015-001-111, 206-015-001-115, 206-015-001-117, 206-015-001-119, or 206-015-001-121, and a main rotor blade serial number listed in Table 1 of this AD.
| || || || || |
|Affected Main Rotor Blade Serial Numbers|
|(All blade serial numbers listed in Table 1 of this AD have the prefix “A-.”)|
|901 through 928||2285, 2286||2787, 2788||4293 through 4298||4684.|
|930 through 935||2290||2808 through 2817||4301||4686 through 4708.|
|937, 938||2292 through 2294||2819 through 2822||4305||4710.|
|941||2297||2824||4308||4713 through 4716.|
|943 through 994||2301, 2302||2826 through 2828||4314, 4315||4719 through 4722.|
|996 through 1000||2304, 2305||2832||4318||4725.|
|1002 through 1020||2308||2835||4330||4728, 4729.|
|1022 through 1032||2311||2840 through 2842||4334 through 4336||4731.|
|1034 through 1047||2313, 2314||2844||4381, 4382||4734 through 4737.|
|1049 through 1134||2316||2848 through 2850||4392||4739 through 4742.|
|1136 through 1140||2318, 2319||2852, 2853||4394, 4395||4744 through 4751.|
|1142 through 1157||2322 through 2324||2855||4405 through 4409||4753 through 4757.|
|1159 through 1166||2328 through 2331||2858||4416||4759.|
|1168 through 1182||2357||2862 through 2864||4418||4762.|
|1184 through 1351||2374||2900||4423 through 4426||4764.|
|1353 through 1363||2379||2996||4433||4774.|
|1365 through 1382||2515||3212||4445||4778 through 4780.|
|1384 through 1401||2553, 2554||3219||4448||4784.|
|1403 through 1519||2561, 2562||3339||4462, 4463||4786 through 4825.|
|1521 through 1590||2564 through 2570||3369||4484||4827 through 4840.|
|1593 through 1646||2573||3381||4500||4842 through 4863.|
|1648 through 1718||2576||3447||4508||4865 through 4905.|
|1720 through 1798||2580||3571, 3572||4512||4907 through 4948.|
|1800 through 1821||2583||3622||4517||4950 through 4957.|
|1824 through 1829||2585, 2586||3705||4522||4959 through 4963.|
|1832 through 2060||2588, 2589||3831||4528, 4529||4965.|
|2062 through 2072||2593, 2594||3971, 3972||4532||4969 through 4973.|
|2074||2596, 2597||4025 through 4030||4534||4975.|
|2077 through 2081||2599||4117||4547||4979, 4980.|
|2092 through 2095||2602||4143||4550||4983, 4984.|
|2098, 2099||2604, 2605||4201 through 4205||4567||4987.|
|2101 through 2104||2607 through 2610||4209||4573||4989.|
|2107, 2108||2621||4214 through 4217||4590||4992.|
|2110 through 2124||2623, 2624||4248||4604, 4605||4994 through 5006.|
|2126 through 2145||2638||4250, 4251||4608, 4609||5010.|
|2147 through 2158||2640 through 2672||4253, 4254||4612 through 4621||5015.|
|2161 through 2163||2674 through 2701||4256 through 4260||4624 through 4629||5018.|
|2165, 2166||2706 through 2708||4262 through 4267||4631, 4632||5023.|
|2169 through 2175||2727, 2728||4269||4638, 4639||5036.|
|2177 through 2183||2730 through 2742||4271, 4272||4652||5047.|
|2185 through 2192||2744 through 2764||4274 through 4276||4654||5054.|
|2220, 2221||2766, 2767||4278||4657||5066, 5067.|
|2248||2769||4280 through 4284||4659||5071, 5072.|
|2257 through 2267||2771, 2772||4286, 4287||4662||5075, 5076.|
|2272 through 2283||2775 through 2777||4290, 4291||4666 through 4682||5081.|
|5087||5397||5535 through 5537||5679 through 5686||5851.|
|5094||5399 through 5400||5539, 5540||5688||5856.|
|5152||5402 through 5411||5542||5690 through 5705||5861 through 5865.|
|5155||5413, 5414||5546 through 5549||5707 through 5709||5870.|
|5158, 5159||5416 through 5439||5552, 5553||5711, 5712||5882.|
|5163, 5164||5441||5556 through 5561||5716 through 5721||5884 through 5886.|
|5166 through 5171||5443 through 5445||5566 through 5568||5723 through 5726||5889 through 5891.|
|5176 through 5178||5447||5570 through 5574||5729 through 5734||5899 through 5901.|
|5180 through 5182||5450||5576 through 5583||5736 through 5745||5903 through 5905.|
|5186 through 5191||5459||5588 through 5591||5747 through 5752||5912.|
|5193 through 5199||5465 through 5468||5594||5757||5915.|
|5201 through 5205||5472||5598 through 5600||5762||5921.|
|5207||5475||5602 through 5605||5766 through 5769||5925, 5926.|
|5209 through 5212||5481||5608, 5609||5771||5929 through 5951.|
|5218 through 5253||5483||5612||5781, 5782||5992.|
|5255 through 5273||5488||5616 through 5623||5791||6216.|
|5275 through 5288||5491, 5492||5625, 5626||5793 through 5800||6247.|
|5297, 5298||5497 through 5507||5637 through 5641||5815 through 5817||6597.|
|5301 through 5321||5509 through 5512||5643||5822 through 5826||6611, 6612.|
|5323 through 5331||5516||5645 through 5653||5828, 5829||6661.|
|5333 through 5340||5518 through 5521||5655 through 5666||5833||6714.|
|5343||5526 through 5530||5668, 5669||5837.|
|5345 through 5395||5533||5671 through 5677||5844, 5845.|
(b) Unsafe Condition
This AD defines the unsafe condition as fatigue cracking of a main rotor blade. This condition could result in failure of the main rotor blade and subsequent loss of control of the helicopter.
(c) Effective Date
This AD becomes effective May 4, 2012 to all persons except those persons to whom it was made immediately effective by Emergency AD No. 2012-02-51, issued on February 1, 2012.
You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.
(e) Required Actions
(1) Before further flight, reduce the life limit of the main rotor blades with a serial number listed in Table 1 of this AD from 3,600 hours time-in-service (TIS) to 1,400 hours TIS; revise the life limit in the Airworthiness Limitations section of the Instruction for Continued Airworthiness or maintenance manual; and record the revised life limit on the component history card or equivalent record.
(2) Before further flight, remove from service any main rotor blade which has accumulated 1,400 or more hours TIS.
(f) Special Flight Permits
Special flight permits are prohibited.
(g) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Sharon Miles, Aerospace Engineer, FAA, Rotorcraft Directorate, Regulations and Policy Group, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222 5110, email email@example.com.
(2) For operations conducted under a Part 119 operating certificate or under Part 91, Subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC.
(h) Additional Information
(1) Bell Helicopter Alert Service Bulletin (ASB) No. 206L-09-159 Revision A, dated November 13, 2009, which is not incorporated by reference, contains additional information about the subject of this AD. For this service information, contact Bell Helicopter Textron Canada Limited, 12,800 Rue de l'Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437-2862 or (800) 363-8023, fax (450) 433-0272, or at http://www.bellcustomer.com/files/. You may review a copy of this service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.
(2) The subject of this AD is addressed in Transport Canada Civil Aviation AD No. CF-2011-44R1, dated February 1, 2012.
Joint Aircraft Service Component (JASC) Code: 6210, Main rotor blades.
Issued in Fort Worth, Texas, on April 3, 2012.
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012-9314 Filed 4-18-12; 8:45 am]
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