39254 Federal Register / Vol. 76, No. 129 / Wednesday, July 6, 2011 / Rules and Regulations

Unsafe Condition Airframe Branch, ANM–120L, FAA, Los previously sent to all known U.S. (e) This AD was prompted by a report of Angeles Aircraft Certification Office (ACO), owners and operators. That EAD a crack found in the upper center skin panel 3960 Paramount Blvd., Lakewood, California currently requires removing each at the aft inboard corner of a right horizontal 90712–4137; phone: 562–627–5233; fax: 562– locknut and verifying sufficient drag 627–5210; e-mail: [email protected]. stabilizer. We are issuing this AD to detect torque and retorquing, or if the locknut and correct cracks in the horizontal stabilizer Material Incorporated by Reference does not have sufficient drag torque, upper center skin panel. Uncorrected cracks might ultimately lead to the loss of overall (j) You must use Boeing Alert Service replacing the locknut with an airworthy structural integrity of the horizontal Bulletin MD80–55A068, dated July 16, 2010, locknut. This AD retains the existing stabilizer. to do the actions required by this AD, unless EAD requirements but also requires the AD specifies otherwise. within a specified time, modifying the Compliance (1) The Director of the Federal Register expandable bolts and installing a cotter (f) Comply with this AD within the approved the incorporation by reference of pin. This AD is prompted by a locknut this service information under 5 U.S.C. compliance times specified, unless already working loose from a bolt attaching the done. 552(a) and 1 CFR part 51. (2) For service information identified in tailboom support strut at the aft cluster Inspections this AD, contact Boeing Commercial fitting because the locknut installed on (g) Before the accumulation of 20,000 total Airplanes, Attention: Data & Services the expandable bolt did not have the flight cycles, or within 4,379 flight cycles Management, 3855 Lakewood Boulevard, MC proper threads. We are issuing this AD after the effective date of this AD, whichever D800–0019, Long Beach, California 90846– to modify each expandable bolt to allow occurs later, do eddy current inspections to 0001; phone: 206–544–5000, extension 2; fax: adding a cotter pin to prevent the strut detect cracking of the left and right upper 206–766–5683; e-mail: center skin panels of the horizontal stabilizer, and driveshaft separating from the [email protected]; Internet: https:// and subsequent loss of in accordance with the Accomplishment www.myboeingfleet.com. Instructions of Boeing Alert Service Bulletin (3) You may review copies of the service control of the helicopter. MD80–55A068, dated July 16, 2010. information at the FAA, Transport Airplane DATES: This AD is effective July 21, (1) If no crack is found during any Directorate, 1601 Lind Avenue, SW., Renton, 2011. inspection required by paragraph (g) of this Washington. For information on the The Director of the Federal Register AD, repeat the applicable inspections availability of this material at the FAA, call approved the incorporation by reference thereafter at the applicable times specified in 425–227–1221. paragraph 1.E., ‘‘Compliance,’’ of Boeing of certain publications listed in the AD (4) You may also review copies of the as of July 21, 2011. Alert Service Bulletin MD80–55A068, dated service information that is incorporated by July 16, 2010. reference at the National Archives and We must receive any comments on (2) If any crack is found during any Records Administration (NARA). For this AD by September 6, 2011. inspection required by paragraph (g) of this information on the availability of this ADDRESSES: You may send comments by AD, before further flight, replace the skin material at an NARA facility, call 202–741– panel with a new skin panel, in accordance any of the following methods: 6030, or go to http://www.archives.gov/ • with the Accomplishment Instructions of Federal eRulemaking Portal: Go to federal_register/code_of_federal_regulations/ Boeing Alert Service Bulletin MD80–55A068, http://www.regulations.gov. Follow the ibr_locations.html. dated July 16, 2010. Within 20,000 flight instructions for submitting comments. cycles after the replacement, do eddy current Issued in Renton, Washington, on June 16, • Fax: 202–493–2251. inspections as required by paragraph (g) of 2011. • Mail: U.S. Department of this AD. Ali Bahrami, Transportation, Docket Operations, Alternative Methods of Compliance Manager, Transport Airplane Directorate, M–30, West Building Ground Floor, (AMOCs) Aircraft Certification Service. Room W12–140, 1200 New Jersey (h)(1) The Manager, Los Angeles Aircraft [FR Doc. 2011–15990 Filed 7–5–11; 8:45 am] Avenue, SE., Washington, DC 20590. • Certification Office (ACO), FAA, has the BILLING CODE 4910–13–P Hand Delivery: U.S. Department of authority to approve AMOCs for this AD, if Transportation, Docket Operations, requested using the procedures found in 14 M–30, West Building Ground Floor, CFR 39.19. In accordance with 14 CFR 39.19, DEPARTMENT OF TRANSPORTATION Room W12–140, 1200 New Jersey send your request to your principal inspector Avenue, SE., Washington, DC 20590, or local Flight Standards District Office, as Federal Aviation Administration between 9 a.m. and 5 p.m., Monday appropriate. If sending information directly through Friday, except Federal holidays. to the manager of the ACO, send it to the 14 CFR Part 39 attention of the person identified in the For service information identified in Related Information section of this AD. [Docket No. FAA–2011–0593; Directorate this AD, contact Schweizer Aircraft (2) Before using any approved AMOC, Identifier 2011–SW–002–AD; Amendment Corporation, Elmira/Corning Regional notify your appropriate principal inspector, 39–16723; AD 2011–12–16] Airport, 1250 Schweizer Road, or lacking a principal inspector, the manager Horseheads, NY 14845, telephone (607) of the local flight standards district office/ RIN 2120–AA64 739–3821, fax: (607) 796–2488, e-mail certificate holding district office. address [email protected], or at (3) An AMOC that provides an acceptable Airworthiness Directives; Schweizer level of safety may be used for any repair Aircraft Corporation (Schweizer) Model http://www.sacusa.com/support. required by this AD if it is approved by the 269A, A–1, B, C, C–1, and TH–55 Series Examining the AD Docket Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has You may examine the AD docket on been authorized by the Manager, Los Angeles AGENCY: Federal Aviation the Internet at http:// ACO, to make those findings. For a repair Administration (FAA), DOT. www.regulations.gov; or in person at the method to be approved, the repair must meet ACTION: Final rule; request for Docket Management Facility between the certification basis of the airplane and 14 comments. 9 a.m. and 5 p.m., Monday through CFR 25.571, Amendment 45, and the Friday, except Federal holidays. The AD approval must specifically refer to this AD. SUMMARY: We are superseding an docket contains this AD, the regulatory Related Information existing emergency airworthiness evaluation, any comments received, and (i) For more information about this AD, directive (EAD) for the specified other information. The street address for contact Roger Durbin, Engineer, Schweizer model helicopters that was the Docket Office (telephone: 800–647–

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5527) is in the ADDRESSES section. 1, B, and C helicopters, and No. C1B– corrected, could result in the strut and Comments will be available in the AD 032 for Model 269C–1 helicopters, both driveshaft separating from the docket shortly after receipt. dated December 21, 2010. The service helicopter and subsequent loss of FOR FURTHER INFORMATION CONTACT: information specifies verifying control of the helicopter. Therefore, we Stephen Kowalski, Aviation Safety sufficient drag torque on each locknut find that notice and opportunity for Engineer, FAA, Airframe and and applying the proper torque to each prior public comment are impracticable Propulsion Branch, ANE–171, 1600 locknut. The service information also because of the short compliance time Stewart Ave., Suite 410, Westbury, New specifies modifying both expandable and that good cause exists for making York 11590, telephone (516) 228–7327, bolts to allow the addition of a cotter this amendment effective in less than 30 fax (516) 794–5531. pin. days. SUPPLEMENTARY INFORMATION: FAA’s Determination Comments Invited Discussion We are issuing this AD because we This AD is a final rule that involves On December 20, 2010, we issued evaluated all the relevant information requirements affecting flight safety, and EAD 2011–01–52, Directorate Identifier and determined the unsafe condition we did not provide notice and an 2010–SW–111–AD, for the specified described previously is likely to exist or opportunity to comment before it Schweizer model helicopters. That EAD develop on other helicopters of these becomes effective. However, we invite requires, before further flight, removing same type designs. you to send any written data, views, or the locknut and reinstalling the locknut AD Requirements while determining the locknut drag arguments about this AD. Send your torque. If the drag torque is a minimum This AD retains the requirements in comments to an address listed under the of 2 in-lbs, retorquing the locknut to 23 the existing EAD. This AD also requires, ADDRESSES section. Include the Docket in-lbs is required. If the drag torque is within 10 hours time-in-service (TIS), Number FAA–2011–0593 and not at least 2 in-lbs, replacing the modifying both expandable bolts by Directorate Identifier 2011–SW–002–AD locknut with an airworthy locknut is drilling a hole through each bolt to at the beginning of your comments. We required. That AD resulted from a allow the addition of a cotter pin. specifically invite comments on the locknut working loose from a bolt Thereafter, you may not install an overall regulatory, economic, attaching the tailboom support strut at expandable bolt unless that bolt has environmental, and energy aspects of the aft cluster fitting. Further been modified in accordance with this this AD. We will consider all comments investigation revealed that the locknut AD. Modifying both expandable bolts in received by the closing date and may installed on the expandable bolt did not accordance with this AD is terminating amend this AD because of those have the proper threads. We issued that action for the requirements of comments. EAD to prevent the strut and driveshaft paragraphs (e)(1) and (e)(2) of this AD. We will post all comments we separating from the helicopter and Differences Between the AD and the receive, without change, to http:// subsequent loss of control of the Service Information www.regulations.gov, including any helicopter. personal information you provide. We We refer to flight hours as hours TIS. Actions Since AD Was Issued will also post a report summarizing each FAA’s Justification and Determination substantive verbal contact we receive Since we issued AD 2011–01–52, the of the Effective Date about this AD. manufacturer has introduced a modification of the expandable bolts to An unsafe condition exists that Costs of Compliance allow the addition of a cotter pin. requires the immediate adoption of this AD. The FAA has found that the risk to We estimate that this AD affects 585 Relevant Service Information the flying public justifies waiving notice helicopters of U.S. registry. We estimate We reviewed Schweizer Service and comment prior to adoption of this the following costs to comply with this Bulletins No. B–295 for Model 269A, A– rule because this condition, if not AD:

ESTIMATED COSTS

Cost per Cost on U.S. Action Labor cost Parts cost helicopter operators

Inspection ...... 5 work-hour × $85 per hour = $43 ...... negligible ...... $43 $25,155 Modification ...... 1.5 work-hours × $85 per hour = $128 ...... negligible ...... 128 74,880

We estimate the total cost impact of We are issuing this rulemaking under products identified in this rulemaking this AD to be $100,035. the authority described in Subtitle VII, action. Part A, Subpart III, Section 44701, Authority for This Rulemaking Regulatory Findings ‘‘General requirements.’’ Under that Title 49 of the United States Code section, Congress charges the FAA with This AD will not have federalism specifies the FAA’s authority to issue promoting safe flight of civil aircraft in implications under Executive Order rules on aviation safety. Subtitle I, air commerce by prescribing regulations 13132. This AD will not have a Section 106, describes the authority of for practices, methods, and procedures substantial direct effect on the States, on the FAA Administrator. Subtitle VII, the Administrator finds necessary for the relationship between the national Aviation Programs, describes in more safety in air commerce. This regulation government and the States, or on the detail the scope of the Agency’s is within the scope of that authority distribution of power and authority. because it addresses an unsafe condition responsibilities among the various that is likely to exist or develop on levels of government.

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For the reasons discussed above, I Compliance (2) For service information identified in certify that this AD: (e) Required as indicated, unless already this AD, contact Schweizer Aircraft (1) Is not a ‘‘significant regulatory done. Corporation, Elmira/Corning Regional Airport, 1250 Schweizer Road, Horseheads, action’’ under Executive Order 12866, (1) Before further flight, remove both the left-hand and right-hand locknuts, P/N NY 14845, telephone (607) 739–3821, fax: (2) Is not a ‘‘significant rule’’ under MS21043–3. Reinstall the locknuts while (607) 796–2488, e-mail address DOT Regulatory Policies and Procedures determining the locknut drag torque. If the [email protected], or at http:// (44 FR 11034, February 26, 1979), drag torque is a minimum of 2 in-lbs., www.sacusa.com/support. (3) Will not affect intrastate aviation retorque the locknut to 23 in-lbs. If the drag (3) You may also review copies of the in Alaska to the extent that it justifies torque is not at least 2 in-lbs, replace the service information that is incorporated by making any regulatory distinctions, and locknut with an airworthy locknut. reference at the FAA, Office of the Regional (2) Within 10 hours time-in-service, modify Counsel, 2601 Meacham Blvd., Room 663, (4) Will not have a significant each expandable bolt, P/N ADB221–1A, Fort Worth, , or at the National economic impact, positive or negative, torque locknut, P/N MS21043–3, and install Archives and Records Administration on a substantial number of small entities cotter pin, P/N MS24665–132 or MS24665– (NARA). For information on the availability under the criteria of the Regulatory 151, in accordance with the Procedure of this material at an NARA facility, call 202– Flexibility Act. Section, Part II, of Schweizer Service Bulletin 741–6030, or go to http://www.archives.gov/ (SB) No. B–295, dated December 21, 2010, for federal_register/code_of_federal_regulations/ List of Subjects in 14 CFR Part 39 Model 269A, A–1, B, C, and TH–55 series ibr_locations.html. helicopters or SB No. C1B–032, dated Issued in Fort Worth, Texas, on June 3, Air transportation, Aircraft, Aviation December 21, 2010, for Model 269C–1 safety, Incorporation by reference, helicopters. 2011. Safety. (3) Before installing an expandable bolt, Kim Smith, Adoption of the Amendment P/N ADB221–1A, to secure the tailboom Manager, Rotorcraft Directorate, Aircraft support strut to the tailboom aft cluster Certification Service. Accordingly, under the authority fitting, modify the expandable bolt in [FR Doc. 2011–16571 Filed 7–5–11; 8:45 am] accordance with paragraph (e)(2) of this AD. delegated to me by the Administrator, BILLING CODE 4910–13–P the FAA amends Part 39 of the Federal (f) Modifying both expandable bolts by torquing the locknuts and installing the Aviation Regulations (14 CFR Part 39) as cotter pins as required by this AD is follows: terminating action for the requirements of DEPARTMENT OF TRANSPORTATION paragraph (e)(1) and (e)(2) of this AD. PART 39—AIRWORTHINESS Federal Aviation Administration DIRECTIVES Special Flight Permit (g) Special flight permits will not be 14 CFR Part 39 ■ 1. The authority citation for Part 39 issued. continues to read as follows: Alternative Methods of Compliance [Docket No. FAA–2011–0152; Directorate Authority: 49 U.S.C. 106(g), 40113, 44701. (AMOCs) Identifier 2010–NM–079–AD; Amendment (h) The Manager, New York Aircraft 39–16739; AD 2011–14–04] § 39.13 [Amended] Certification Office (NYACO), FAA, has the ■ 2. The FAA amends § 39.13 by adding authority to approve AMOCs for this AD if RIN 2120–AA64 requested using the procedures found in 14 the following new AD: CFR 39.19. In accordance with 14 CFR 39.19, Airworthiness Directives; Dassault 2011–12–16 Schweizer Aircraft send your request to your principal inspector Aviation Model FALCON 7X Airplanes Corporation (Schweizer): Amendment or local Flight Standards District Office, as 39–16723; Docket No. FAA–2011–0593; appropriate. If sending information directly AGENCY: Federal Aviation Directorate Identifier 2011–SW–002–AD. to the manager of the NYACO, send it to the Administration (FAA), Department of attention of the Program Manager, Effective Date Continuing Operational Safety. Transportation (DOT). (a) This AD is effective July 21, 2011. Note: Before using any approved AMOC, ACTION: Final rule. Affected ADs we request that you notify your appropriate principal inspector, or lacking a principal SUMMARY: We are adopting a new (b) This AD supersedes Emergency AD inspector, the manager of the local flight airworthiness directive (AD) for the 2011–01–52, issued December 20, 2010; standards district office or certificate holding products listed above. This AD results Directorate Identifier 2010–SW–111–AD. district office. from mandatory continuing airworthiness information (MCAI) Applicability Related Information (c) Schweizer Model 269A, A–1, B, C originated by an aviation authority of (i) For more information about this AD, another country to identify and correct helicopters (serial number (S/N) 1846 and contact Stephen Kowalski, Aviation Safety larger); C–1 helicopters (S/N 0156 and Engineer, FAA, Airframe and Propulsion an unsafe condition on an aviation larger); and TH–55 series helicopters with an Branch, ANE–171, 1600 Stewart Ave., Suite product. The MCAI describes the unsafe Aft Cluster Fitting Modification Kit, part 410, Westbury, New York 11590, telephone condition as: number (P/N) SA–269K–106, installed; (516) 228–7327, fax (516) 794–5531. certificated in any category. On some Falcon 7X aeroplanes, it has been Subject determined potential low clearance between Unsafe Condition electrical wiring or hydraulic pipe and (j) Joint Aircraft System Component nearby structure. (d) This AD was prompted by a locknut (JASC)/Air Transport Association (ATA) of Although no in service incident has been working loose on the tailboom aft cluster America Code 5302: Rotorcraft Tailboom. fitting strut because the locknut installed on reported, there is no certainty that the one expandable bolt did not have the proper Material Incorporated by Reference minimum clearances would be maintained threads. This AD contains terminating action (k) You must use the specified portions of over time. In the worst case, interference or to require modifying each expandable bolt to the service information contained in contact with structure might occur and lead allow installing a cotter pin to prevent the Schweizer Service Bulletins B–295 or C1B– to electrical short circuits or fluid leakage, strut and driveshaft separating from the 032, both dated December 21, 2010, for your potentially resulting in loss of several helicopter and subsequent loss of control of model helicopter to do the actions required functions essential for safe flight. the helicopter. by this AD. * * * * *

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