Airworthiness Directives; The Enstrom Helicopter Corporation, 28172-28175 [2015-11732]

Download as PDF 28172 Federal Register / Vol. 80, No. 95 / Monday, May 18, 2015 / Rules and Regulations preempted; (2) no retroactive effect will be given to this rule; and (3) no administrative proceedings will be required before parties may file suit in court challenging this rule. E-Government Act FSIS and USDA are committed to achieving the purposes of the EGovernment Act (44 U.S.C. 3601, et seq.) by, among other things, promoting the use of the Internet and other information technologies and providing increased opportunities for citizen access to Government information and services, and for other purposes. asabaliauskas on DSK5VPTVN1PROD with RULES USDA Nondiscrimination Statement No agency, officer, or employee of the USDA shall, on the grounds of race, color, national origin, religion, sex, gender identity, sexual orientation, disability, age, marital status, family/ parental status, income derived from a public assistance program, or political beliefs, exclude from participation in, deny the benefits of, or subject to discrimination any person in the United States under any program or activity conducted by the USDA. To file a complaint of discrimination, complete the USDA Program Discrimination Complaint Form, which may be accessed online at http:// www.ocio.usda.gov/sites/default/files/ docs/2012/Complain_combined_6_8_ 12.pdf, or write a letter signed by you or your authorized representative. Send your completed complaint form or letter to USDA by mail, fax, or email: Mail: U.S. Department of Agriculture, Director, Office of Adjudication, 1400 Independence Avenue SW., Washington, DC 20250–9410. Fax: (202)690–7442/ Email: program.intake@usda.gov Persons with disabilities who require alternative means for communication (Braille, large print, audiotape, etc.) should contact USDA’s TARGET Center at (202) 720–2600 (voice and TDD). Additional Public Notification Public awareness of all segments of rulemaking and policy development is important. Consequently, FSIS will announce it on-line through the FSIS Web page located at: http:// www.fsis.usda.gov/federal-register. FSIS also will make copies of this Federal Register publication available through the FSIS Constituent Update, which is used to provide information regarding FSIS policies, procedures, regulations, Federal Register notices, FSIS public meetings, and other types of information that could affect or would be of interest to our constituents and stakeholders. The Update is available on VerDate Sep<11>2014 17:45 May 15, 2015 Jkt 235001 the FSIS Web page. Through the Web page, FSIS is able to provide information to a much broader, more diverse audience. In addition, FSIS offers an email subscription service which provides automatic and customized access to selected food safety news and information. This service is available at: http:// www.fsis.usda.gov/subscribe. Options range from recalls to export information, regulations, directives, and notices. Customers can add or delete subscriptions themselves, and have the option to password-protect their accounts. List of Subjects in 9 CFR Part 317 Food labeling, Food packaging, Meat inspection, Nutrition, Reporting and recordkeeping requirements. For the reasons discussed in the preamble, FSIS amends 9 CFR Chapter III as follows: PART 317—LABELING, MARKING DEVICES, AND CONTAINERS 1. The authority citation for part 317 continues to read as follows: ■ Authority: 21 U.S.C. 601–695; 7 CFR 2.18, 2.53. 2. Amend § 317.2 by adding a new paragraph (e)(3) to read as follows: ■ § 317.2 Labels: definition; required features. * * * * * (e) * * * (3) Product name and required validated cooking instructions for needle- or blade-tenderized beef products. (i) Unless the product is destined to be fully cooked or to receive another full lethality treatment at an official establishment, the product name for a raw or partially cooked beef product that has been mechanically tenderized, whether by needle or by blade, must contain the term ‘‘mechanically tenderized,’’ ‘‘needle tenderized,’’ or ‘‘blade tenderized,’’ as a descriptive designation and an accurate description of the beef component. (ii) The product name must appear in a single easy-to-read type style and color and on a single-color contrasting background. The print may appear in upper and lower case letters, with the lower case letters not smaller than 1⁄3 the size of the largest letter. (iii) The labels on raw or partially cooked needle- or blade-tenderized beef products destined for household consumers, hotels, restaurants, or similar institutions must contain validated cooking instructions, including the cooking method, that PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 inform consumers that these products need to be cooked to a specified minimum internal temperature, whether the product needs to be held for a specified time at that temperature or higher before consumption to ensure that potential pathogens are destroyed throughout the product, and a statement that the internal temperature should be measured by a thermometer. These validated cooking instructions may appear anywhere on the label. * * * * * Done, at Washington, DC, on May 13, 2015. Alfred V. Almanza, Acting Administrator. [FR Doc. 2015–11916 Filed 5–15–15; 8:45 am] BILLING CODE 3410–DM–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–1537; Directorate Identifier 2015–SW–014–AD; Amendment 39–18160; AD 2015–08–51] RIN 2120–AA64 Airworthiness Directives; The Enstrom Helicopter Corporation Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are publishing a new airworthiness directive (AD) for Enstrom Helicopter Corporation (Enstrom) Model F–28A, 280, F–28C, F– 28C–2, F–28C–2R, 280C, F–28F, F–28F– R, 280F, 280FX, and 480 helicopters. This AD was sent previously to all known U.S. owners and operators of these helicopters and supersedes Emergency AD (EAD) 2015–04–51, dated February 12, 2015. This AD requires inspecting certain main rotor spindles (spindles) for cracks and reporting the inspection results to the FAA. This AD is prompted by a fatal accident and reports of spindles with cracks. The actions specified in this AD are intended to detect a crack in a spindle and prevent loss of a main rotor blade and subsequent loss of control of the helicopter. DATES: This AD becomes effective June 2, 2015 to all persons except those persons to whom it was made immediately effective by EAD 2015–08– 51, issued on April 10, 2015, which contains the requirements of this AD. We must receive comments on this AD by July 17, 2015. SUMMARY: E:\FR\FM\18MYR1.SGM 18MYR1 Federal Register / Vol. 80, No. 95 / Monday, May 18, 2015 / Rules and Regulations 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. ADDRESSES: 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, any comments received, 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 Enstrom Helicopter Corporation, 2209 22nd Street, Menominee, MI; telephone (906) 863– 1200; fax (906) 863–6821; or at www.enstromhelicopter.com. You may review 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: Gregory J. Michalik, Senior Aerospace Engineer, Chicago Aircraft Certification Office, Small Airplane Directorate, FAA, 2300 East Devon Ave., Des Plaines, IL 60018; (847) 294–7135; email gregory.michalik@faa.gov. SUPPLEMENTARY INFORMATION: asabaliauskas on DSK5VPTVN1PROD with RULES 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 VerDate Sep<11>2014 17:45 May 15, 2015 Jkt 235001 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 On February 12, 2015, we issued EAD 2015–04–51, which was prompted by a fatal accident. Preliminary results of the investigation indicated that the accident was caused by a crack in the spindle, which resulted in the main rotor blade separating from the helicopter. The crack was discovered at the last thread of the spindle retention nut threads. While the investigation could not determine when the crack initiated, it was able to determine that the crack existed, undetected, for a significant amount of time before the separation. EAD 2015–04–51 required, before further flight, conducting a magnetic particle inspection (MPI) in any spindle that had 5,000 or more hours time-inservice (TIS) or where the hours TIS of the spindle is not known. If there was a crack in the spindle, EAD 2015–04–51 required replacing it before further flight. EAD 2015–04–51 also required reporting the inspection results to the FAA within 72 hours. Since we issued EAD 2015–04–51, inspection reports received by the FAA indicate approximately 20% of the spindles reported with TIS data had evidence of cracks. The FAA also received inspection reports of spindles without TIS data which did not have evidence of cracks. The inspection reports include spindles with cracks at less than 5,000 hours TIS. With analysis of available data, we determined the need to expand the applicability to include spindles with 1,500 or more hours TIS. On April 10, 2015, we issued EAD 2015–08–51, which supersedes EAD 2015–04–51. EAD 2015–08–51 retains all of the requirements of EAD 2014–04– 51 except it reduces the TIS of the spindles to be inspected from 5,000 hours to 1,500 hours. EAD 2015–08–51 was sent previously to all known U.S. owners and operators of these helicopters. FAA’s Determination We are issuing this AD because we evaluated all the relevant information PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 28173 and determined the unsafe condition described previously is likely to exist or develop in other products of these same type designs. Related Service Information Enstrom has issued Service Directive Bulletin No. 0119, Revision 1, dated April 1, 2015, for all serial numbered Model F–28A, F–28C, F–28F, 280, 280C, 280F, and 280FX helicopters with a main rotor spindle, part number (P/N) 28–14282–11 and 28–14282–13. Enstrom has also issued Service Directive Bulletin No. T–050, Revision 1, dated April 1, 2015, for Model 480 helicopters, serial numbers 5001 through 5004 and 5006, and with a main rotor spindle, P/N 28–14282–13, except those aircraft modified with tensiontorsion straps. Both service directives specify, for any spindle that has been in service more than 3,500 hours, within 5 hours TIS, sending the spindle to Enstrom for an MPI. For any spindle with less than 3,500 hours TIS, the service directives specify sending the spindle to Enstrom for an MPI at or before it reaches 3,500 hours TIS. The service directives also specify repeating the MPI every 300 hours for spindles with over 3,500 hours TIS. AD Requirements This AD requires conducting an MPI before further flight to determine if a crack exists in any spindle that has 1,500 or more hours TIS or where the hours TIS of the spindle is not known. If there is a crack in the spindle, this AD requires replacing it before further flight. The MPI of the spindle must be conducted by a Level II or Level III inspector qualified in the MPI method in the Aeronautics Sector according to the EN4179 or NAS410 standard or equivalent. This AD also requires reporting certain information to the FAA within 72 hours. Differences Between This AD and the Service Information This AD requires that the MPI be conducted by a Level II or Level III inspector or equivalent and that the results of the MPI be reported to the FAA, whereas the service information specifies that the MPI be accomplished by or reported to Enstrom. This AD requires an MPI on spindles with 1,500 or more hours TIS, whereas the service information specifies performing an initial MPI on spindles with 3,500 or more hours TIS. This AD does not require a recurring inspection, whereas the service information specifies to repeat the MPI every 300 hours TIS for spindles with over 3,500 hours TIS. This AD requires the MPI before further E:\FR\FM\18MYR1.SGM 18MYR1 28174 Federal Register / Vol. 80, No. 95 / Monday, May 18, 2015 / Rules and Regulations flight, whereas the service information specifies that it be accomplished within 5 hours TIS. Interim Action We consider this AD to be an interim action. The inspection reports that are required by this AD will enable us to obtain better insight into the root cause and extent of the cracking, and eventually to develop final action to address the unsafe condition. Once final action has been identified, we might consider further rulemaking. Costs of Compliance We estimate that this AD affects 323 helicopters of U.S. Registry and that operators may incur the following costs to comply with this AD. Inspecting the spindles will take about 15 work-hours per helicopter and reporting the required inspection information will take about 0.5 work-hour. We estimate an average labor rate of $85 per workhour, for a total cost of $1,318 per helicopter and $425,714 for the U.S. fleet. Replacing a spindle will cost $8,164 for parts and no additional workhours. asabaliauskas on DSK5VPTVN1PROD with RULES Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120–0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting required by this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591. ATTN: Information Collection Clearance Officer, AES–200. 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 found and continue to find that the risk to the flying public justifies waiving notice and comment prior to the adoption of this rule VerDate Sep<11>2014 17:45 May 15, 2015 Jkt 235001 because the previously described unsafe condition can adversely affect the controllability of the helicopter and the initial required action must be accomplished before further flight. Since it was found that immediate corrective action was required, notice and opportunity for prior public comment before issuing this AD were impracticable and contrary to the public interest and good cause existed to make the AD effective immediately by EAD 2015–08–51, issued on April 10, 2015, to all known U.S. owners and operators of these helicopters. These conditions still exist and the AD is hereby published in the Federal Register as an amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 39.13) to make it effective to all persons. 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. 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 PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 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 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2015–08–51 The Enstrom Helicopter Corporation (Enstrom): Amendment 39– 18160; Docket No. FAA–2015–1537; Directorate Identifier 2015–SW–014–AD. (a) Applicability This AD applies to Enstrom Model F–28A, 280, F–28C, F–28C–2, F–28C–2R, 280C, F– 28F, F–28F–R, 280F, and 280FX helicopters, all serial numbers; and Enstrom Model 480 helicopters, serial numbers 5001 through 5006; with a main rotor spindle (spindle), part number (P/N) 28–14282–11 or 28– 14282–13, installed, certificated in any category. This AD applies to any helicopter that has a spindle with 1,500 or more hours time-in-service (TIS) or where the hours TIS of the spindle is not known. (b) Unsafe Condition This AD defines the unsafe condition as a crack in the spindle, which, if not detected, could result in loss of a main rotor blade and subsequent loss of control of the helicopter. (c) Affected ADs This AD supersedes Emergency AD 2015– 04–51, Directorate Identifier 2015–SW–002– AD, dated February 12, 2015. (d) Effective Date This AD becomes effective June 2, 2015 to all persons except those persons to whom it was made immediately effective by Emergency AD 2015–08–51, issued on April 10, 2015, which contains the requirements of this AD. (e) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has been accomplished on or after February 11, 2015. E:\FR\FM\18MYR1.SGM 18MYR1 Federal Register / Vol. 80, No. 95 / Monday, May 18, 2015 / Rules and Regulations (f) Required Actions (1) Before further flight, conduct a magnetic particle inspection (MPI) of the spindle to determine if a crack exists, paying particular attention to the threaded portion of the spindle. The MPI of the spindle must be conducted by a Level II or Level III inspector qualified in the MPI in the Aeronautics Sector according to the EN4179 or NAS410 standard or equivalent. If there is a crack in the spindle, replace it with an airworthy spindle before further flight. (2) Within 72 hours after accomplishing the MPI, report the information requested in Appendix 1 to this AD by mail to the Manager, Chicago Aircraft Certification Office, Federal Aviation Administration, ATTN: Gregory J. Michalik, 2300 East Devon Ave., Des Plaines, IL, 60018; by fax to (847) 294–7834; or email to gregory.michalik@ faa.gov. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Chicago Aircraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Gregory J. Michalik, Senior Aerospace Engineer, Chicago Aircraft Certification Office, Small Airplane Directorate, FAA, 2300 East Devon Ave., Des Plaines, IL, 60018; (847) 294–7135; email gregory.michalik@ faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR 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. (3) Any AMOC approved previously in accordance with EAD 2015–04–51, dated February 12, 2015, is approved as an AMOC for the corresponding requirements in paragraph (f)(1) of this AD. asabaliauskas on DSK5VPTVN1PROD with RULES (h) Additional Information Enstrom Helicopter Corporation Service Directive Bulletin No. 0119, Revision 1, dated April 1, 2015, and Enstrom Helicopter Corporation Service Directive Bulletin No. T– 050, Revision 1, dated April 1, 2015, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact Enstrom Helicopter Corporation, 2209 22nd Street, Menominee, MI; telephone (906) 863–1200; fax (906) 863– 6821; or at www.enstromhelicopter.com. You may review this service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. (i) Subject Joint Aircraft Service Component (JASC) Code: 6220, Main Rotor Head. Appendix 1 to AD 2015–08–51 Spindle Inspection (Sample Format) Provide the following information by mail to the Manager, Chicago Aircraft Certification Office, Federal Aviation Administration, ATTN: Gregory J. Michalik, 2300 East Devon VerDate Sep<11>2014 17:45 May 15, 2015 Jkt 235001 Ave., Des Plaines, IL, 60018; by fax to (847) 294–7834; or email to gregory.michalik@ faa.gov. Aircraft Registration No.: Helicopter Model: Helicopter Serial Number: Helicopter Owner or Operator: Contact Phone No.: Spindle Part Number and Serial Number: Total Hours Time-in-Service (TIS) on Spindle: Total Hours TIS on Helicopter (if hours TIS on spindle were not available): Who Performed the Inspection: Date and Location Inspection was Accomplished: Crack Found? If yes, describe the crack size, location, orientation (provide a sketch or picture): Provide Any Other Comments: Issued in Fort Worth, Texas, on May 8, 2015. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2015–11732 Filed 5–15–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HOMELAND SECURITY Coast Guard 33 CFR Part 100 [Docket No. USCG–2015–0282] Eighth Coast Guard District Annual Marine Event; Mayor’s Hike, Bike and Paddle; Ohio River 602.0–603.5; Louisville, KY Coast Guard, DHS. Notice of enforcement of regulation. AGENCY: ACTION: The Coast Guard will enforce the Mayor’s Hike, Bike and Paddle marine event for all waters of the Ohio River, beginning at mile marker 602.0 and ending at 603.5, Louisville, KY. This rule will be enforced from 9:00 a.m. to 12:30 p.m. on May 25, 2015. This action is necessary to protect persons, property, and infrastructure from potential damage and safety hazards associated with the Mayor’s Hike, Bike and Paddle. During the enforcement period, deviation from the regulations is prohibited unless specifically authorized by the Captain of the Port (COTP) Ohio Valley or a designated representative. DATES: The regulations in 33 CFR 100.801, Table 1, Line 35 will be enforced from 9:00 a.m. to 12:30 p.m. on May 25, 2015. FOR FURTHER INFORMATION CONTACT: If you have questions on this document, call or email Petty Officer James C. SUMMARY: PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 28175 Robinson, U.S. Coast Guard; telephone 502–779–5347, email James.c.robinson@ uscg.mil or Petty Officer Stephen F. McConnell, U.S. Coast Guard; telephone 502–779–5334, email Stephen.F.McConnell@uscg.mil. SUPPLEMENTARY INFORMATION: The Coast Guard will enforce the ‘‘Mayor’s Hike, Bike and Paddle’’ marine event in 33 CFR 100.801, Table 1, Line 35 from 9:00 a.m. to 12:30 p.m. on May 25, 2015. These regulations can be found in the Code of Federal Regulations, at 33 CFR 100.801. Under the provisions of 33 CFR 100.801, a vessel may not enter the regulated area, unless it receives permission from the COTP Ohio Valley or a designated representative. Spectator vessels may safely transit outside the regulated area but may not anchor, block, loiter in, or impede the transit of official patrol vessels. The Coast Guard may be assisted by other Federal, State, or local law enforcement agencies in enforcing this regulation. This document is issued under authority of 5 U.S.C. 552(a), and 33 U.S.C. 1233. In addition to this document in the Federal Register, the Coast Guard will provide the maritime community with extensive advance notification of this enforcement period via the Local Notice to Mariners (LNM) and Broadcast Notice to Mariners (BNM). If the COTP Ohio Valley determines that the regulated area need not be enforced for the full duration stated in the notice, he or she may use a BNM to grant general permission to enter the regulated area. Dated: April 22, 2015. R.V. Timme, Captain, U.S. Coast Guard, Captain of the Port Ohio Valley. [FR Doc. 2015–11941 Filed 5–15–15; 8:45 am] BILLING CODE 9110–04–P DEPARTMENT OF HOMELAND SECURITY Coast Guard 33 CFR Part 100 [Docket No. USCG–2015–0240] RIN 1625–AA08 Eighth Coast Guard District Annual Special Local Regulation; REV3 Triathlon; Tennessee River 646.0– 649.0; Knoxville, TN Coast Guard, DHS. Notice of enforcement of regulation. AGENCY: ACTION: E:\FR\FM\18MYR1.SGM 18MYR1

Agencies

[Federal Register Volume 80, Number 95 (Monday, May 18, 2015)]
[Rules and Regulations]
[Pages 28172-28175]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-11732]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-1537; Directorate Identifier 2015-SW-014-AD; 
Amendment 39-18160; AD 2015-08-51]
RIN 2120-AA64


Airworthiness Directives; The Enstrom Helicopter Corporation

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: We are publishing a new airworthiness directive (AD) for 
Enstrom Helicopter Corporation (Enstrom) Model F-28A, 280, F-28C, F-
28C-2, F-28C-2R, 280C, F-28F, F-28F-R, 280F, 280FX, and 480 
helicopters. This AD was sent previously to all known U.S. owners and 
operators of these helicopters and supersedes Emergency AD (EAD) 2015-
04-51, dated February 12, 2015. This AD requires inspecting certain 
main rotor spindles (spindles) for cracks and reporting the inspection 
results to the FAA. This AD is prompted by a fatal accident and reports 
of spindles with cracks. The actions specified in this AD are intended 
to detect a crack in a spindle and prevent loss of a main rotor blade 
and subsequent loss of control of the helicopter.

DATES: This AD becomes effective June 2, 2015 to all persons except 
those persons to whom it was made immediately effective by EAD 2015-08-
51, issued on April 10, 2015, which contains the requirements of this 
AD.
    We must receive comments on this AD by July 17, 2015.

[[Page 28173]]


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, any 
comments received, 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 Enstrom 
Helicopter Corporation, 2209 22nd Street, Menominee, MI; telephone 
(906) 863-1200; fax (906) 863-6821; or at www.enstromhelicopter.com. 
You may review 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: Gregory J. Michalik, Senior Aerospace 
Engineer, Chicago Aircraft Certification Office, Small Airplane 
Directorate, FAA, 2300 East Devon Ave., Des Plaines, IL 60018; (847) 
294-7135; email gregory.michalik@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

    On February 12, 2015, we issued EAD 2015-04-51, which was prompted 
by a fatal accident. Preliminary results of the investigation indicated 
that the accident was caused by a crack in the spindle, which resulted 
in the main rotor blade separating from the helicopter. The crack was 
discovered at the last thread of the spindle retention nut threads. 
While the investigation could not determine when the crack initiated, 
it was able to determine that the crack existed, undetected, for a 
significant amount of time before the separation. EAD 2015-04-51 
required, before further flight, conducting a magnetic particle 
inspection (MPI) in any spindle that had 5,000 or more hours time-in-
service (TIS) or where the hours TIS of the spindle is not known. If 
there was a crack in the spindle, EAD 2015-04-51 required replacing it 
before further flight. EAD 2015-04-51 also required reporting the 
inspection results to the FAA within 72 hours.
    Since we issued EAD 2015-04-51, inspection reports received by the 
FAA indicate approximately 20% of the spindles reported with TIS data 
had evidence of cracks. The FAA also received inspection reports of 
spindles without TIS data which did not have evidence of cracks. The 
inspection reports include spindles with cracks at less than 5,000 
hours TIS. With analysis of available data, we determined the need to 
expand the applicability to include spindles with 1,500 or more hours 
TIS.
    On April 10, 2015, we issued EAD 2015-08-51, which supersedes EAD 
2015-04-51. EAD 2015-08-51 retains all of the requirements of EAD 2014-
04-51 except it reduces the TIS of the spindles to be inspected from 
5,000 hours to 1,500 hours. EAD 2015-08-51 was sent previously to all 
known U.S. owners and operators of these helicopters.

FAA's Determination

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of these same type 
designs.

Related Service Information

    Enstrom has issued Service Directive Bulletin No. 0119, Revision 1, 
dated April 1, 2015, for all serial numbered Model F-28A, F-28C, F-28F, 
280, 280C, 280F, and 280FX helicopters with a main rotor spindle, part 
number (P/N) 28-14282-11 and 28-14282-13. Enstrom has also issued 
Service Directive Bulletin No. T-050, Revision 1, dated April 1, 2015, 
for Model 480 helicopters, serial numbers 5001 through 5004 and 5006, 
and with a main rotor spindle, P/N 28-14282-13, except those aircraft 
modified with tension-torsion straps. Both service directives specify, 
for any spindle that has been in service more than 3,500 hours, within 
5 hours TIS, sending the spindle to Enstrom for an MPI. For any spindle 
with less than 3,500 hours TIS, the service directives specify sending 
the spindle to Enstrom for an MPI at or before it reaches 3,500 hours 
TIS. The service directives also specify repeating the MPI every 300 
hours for spindles with over 3,500 hours TIS.

AD Requirements

    This AD requires conducting an MPI before further flight to 
determine if a crack exists in any spindle that has 1,500 or more hours 
TIS or where the hours TIS of the spindle is not known. If there is a 
crack in the spindle, this AD requires replacing it before further 
flight. The MPI of the spindle must be conducted by a Level II or Level 
III inspector qualified in the MPI method in the Aeronautics Sector 
according to the EN4179 or NAS410 standard or equivalent. This AD also 
requires reporting certain information to the FAA within 72 hours.

Differences Between This AD and the Service Information

    This AD requires that the MPI be conducted by a Level II or Level 
III inspector or equivalent and that the results of the MPI be reported 
to the FAA, whereas the service information specifies that the MPI be 
accomplished by or reported to Enstrom. This AD requires an MPI on 
spindles with 1,500 or more hours TIS, whereas the service information 
specifies performing an initial MPI on spindles with 3,500 or more 
hours TIS. This AD does not require a recurring inspection, whereas the 
service information specifies to repeat the MPI every 300 hours TIS for 
spindles with over 3,500 hours TIS. This AD requires the MPI before 
further

[[Page 28174]]

flight, whereas the service information specifies that it be 
accomplished within 5 hours TIS.

Interim Action

    We consider this AD to be an interim action. The inspection reports 
that are required by this AD will enable us to obtain better insight 
into the root cause and extent of the cracking, and eventually to 
develop final action to address the unsafe condition. Once final action 
has been identified, we might consider further rulemaking.

Costs of Compliance

    We estimate that this AD affects 323 helicopters of U.S. Registry 
and that operators may incur the following costs to comply with this 
AD. Inspecting the spindles will take about 15 work-hours per 
helicopter and reporting the required inspection information will take 
about 0.5 work-hour. We estimate an average labor rate of $85 per work-
hour, for a total cost of $1,318 per helicopter and $425,714 for the 
U.S. fleet. Replacing a spindle will cost $8,164 for parts and no 
additional work-hours.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting required by this AD 
is mandatory. Comments concerning the accuracy of this burden and 
suggestions for reducing the burden should be directed to the FAA at 
800 Independence Ave. SW., Washington, DC 20591. ATTN: Information 
Collection Clearance Officer, AES-200.

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 found and 
continue to find that the risk to the flying public justifies waiving 
notice and comment prior to the adoption of this rule because the 
previously described unsafe condition can adversely affect the 
controllability of the helicopter and the initial required action must 
be accomplished before further flight.
    Since it was found that immediate corrective action was required, 
notice and opportunity for prior public comment before issuing this AD 
were impracticable and contrary to the public interest and good cause 
existed to make the AD effective immediately by EAD 2015-08-51, issued 
on April 10, 2015, to all known U.S. owners and operators of these 
helicopters. These conditions still exist and the AD is hereby 
published in the Federal Register as an amendment to section 39.13 of 
the Federal Aviation Regulations (14 CFR 39.13) to make it effective to 
all persons.

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

0
1. The authority citation for part 39 continues to read as follows:

     Authority:  49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2015-08-51 The Enstrom Helicopter Corporation (Enstrom): Amendment 
39-18160; Docket No. FAA-2015-1537; Directorate Identifier 2015-SW-
014-AD.

(a) Applicability

    This AD applies to Enstrom Model F-28A, 280, F-28C, F-28C-2, F-
28C-2R, 280C, F-28F, F-28F-R, 280F, and 280FX helicopters, all 
serial numbers; and Enstrom Model 480 helicopters, serial numbers 
5001 through 5006; with a main rotor spindle (spindle), part number 
(P/N) 28-14282-11 or 28-14282-13, installed, certificated in any 
category. This AD applies to any helicopter that has a spindle with 
1,500 or more hours time-in-service (TIS) or where the hours TIS of 
the spindle is not known.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in the spindle, 
which, if not detected, could result in loss of a main rotor blade 
and subsequent loss of control of the helicopter.

(c) Affected ADs

    This AD supersedes Emergency AD 2015-04-51, Directorate 
Identifier 2015-SW-002-AD, dated February 12, 2015.

(d) Effective Date

    This AD becomes effective June 2, 2015 to all persons except 
those persons to whom it was made immediately effective by Emergency 
AD 2015-08-51, issued on April 10, 2015, which contains the 
requirements of this AD.

 (e) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless it has been 
accomplished on or after February 11, 2015.

[[Page 28175]]

(f) Required Actions

    (1) Before further flight, conduct a magnetic particle 
inspection (MPI) of the spindle to determine if a crack exists, 
paying particular attention to the threaded portion of the spindle. 
The MPI of the spindle must be conducted by a Level II or Level III 
inspector qualified in the MPI in the Aeronautics Sector according 
to the EN4179 or NAS410 standard or equivalent. If there is a crack 
in the spindle, replace it with an airworthy spindle before further 
flight.
    (2) Within 72 hours after accomplishing the MPI, report the 
information requested in Appendix 1 to this AD by mail to the 
Manager, Chicago Aircraft Certification Office, Federal Aviation 
Administration, ATTN: Gregory J. Michalik, 2300 East Devon Ave., Des 
Plaines, IL, 60018; by fax to (847) 294-7834; or email to 
gregory.michalik@faa.gov.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Chicago Aircraft Certification Office, FAA, may 
approve AMOCs for this AD. Send your proposal to: Gregory J. 
Michalik, Senior Aerospace Engineer, Chicago Aircraft Certification 
Office, Small Airplane Directorate, FAA, 2300 East Devon Ave., Des 
Plaines, IL, 60018; (847) 294-7135; email gregory.michalik@faa.gov.
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR 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.
    (3) Any AMOC approved previously in accordance with EAD 2015-04-
51, dated February 12, 2015, is approved as an AMOC for the 
corresponding requirements in paragraph (f)(1) of this AD.

(h) Additional Information

    Enstrom Helicopter Corporation Service Directive Bulletin No. 
0119, Revision 1, dated April 1, 2015, and Enstrom Helicopter 
Corporation Service Directive Bulletin No. T-050, Revision 1, dated 
April 1, 2015, which are not incorporated by reference, contain 
additional information about the subject of this AD. For service 
information identified in this AD, contact Enstrom Helicopter 
Corporation, 2209 22nd Street, Menominee, MI; telephone (906) 863-
1200; fax (906) 863-6821; or at www.enstromhelicopter.com. You may 
review this service information at the FAA, Office of the Regional 
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas 76137.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 6220, Main Rotor 
Head.

Appendix 1 to AD 2015-08-51

Spindle Inspection (Sample Format)

    Provide the following information by mail to the Manager, 
Chicago Aircraft Certification Office, Federal Aviation 
Administration, ATTN: Gregory J. Michalik, 2300 East Devon Ave., Des 
Plaines, IL, 60018; by fax to (847) 294-7834; or email to 
gregory.michalik@faa.gov.

Aircraft Registration No.:
Helicopter Model:
Helicopter Serial Number:
Helicopter Owner or Operator:
Contact Phone No.:
Spindle Part Number and Serial Number:
Total Hours Time-in-Service (TIS) on Spindle:
Total Hours TIS on Helicopter (if hours TIS on spindle were not 
available):
Who Performed the Inspection:
Date and Location Inspection was Accomplished:
Crack Found? If yes, describe the crack size, location, orientation 
(provide a sketch or picture):
    Provide Any Other Comments:

    Issued in Fort Worth, Texas, on May 8, 2015.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-11732 Filed 5-15-15; 8:45 am]
BILLING CODE 4910-13-P