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 Department of Transportation Federal Aviation Administration 14 CFR Part 39
[Docket No. FAA-2012-0395; Directorate Identifier 2012-SW-007-AD; Amendment 39-17016; AD 2012-02-51]
RIN 2120-AA64
 AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT).
 ACTION: Final rule; request for comments.
 SUMMARY: 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.
 DATES: 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.
 ADDRESSES: 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.
                    *Fax:*
                         202-493-2251.
                    *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 
                        *sharon.y.miles@faa.gov.*


SUPPLEMENTARY INFORMATION: Comments Invited 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. Discussion 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. FAA's Determination 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 
                    ( print page 23389)
                    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. AD Requirements 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. Regulatory Findings 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. List of Subjects in 14 CFR Part 39 Air transportation
Aircraft
Aviation safety
Incorporation by reference
Safety
 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: Authority:
                        49 U.S.C. 106(g), 40113, 44701. § 39.13
 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. (a) Applicability 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. Table 1
**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.( print page 23390)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
6247.5291, 5292
5495
5628
5808
6270.5297, 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. (d) Compliance 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 
                            ( print page 23391)
                            Directorate, Regulations and Policy Group, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222 5110, email 
                            *sharon.y.miles@faa.gov.* (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. (i) Subject Joint Aircraft Service Component (JASC) Code: 6210, Main rotor blades. Issued in Fort Worth, Texas, on April 3, 2012. Kim Smith, Manager, Rotorcraft Directorate, Aircraft Certification Service.


[FR Doc. 2012-9314 Filed 4-18-12; 8:45 am] BILLING CODE 4910-13-P