Airworthiness Directives; Bell Helicopter Textron Canada (Bell) Helicopters, 41877-41882 [2013-16727]

Download as PDF Federal Register / Vol. 78, No. 134 / Friday, July 12, 2013 / Proposed Rules wreier-aviles on DSK5TPTVN1PROD with PROPOSALS the date provided at the beginning of this notice. After the close of the comment period, DOE will review the comments received and determine whether computers are a covered product under EPCA. Comments, data, and information submitted to DOE’s email address for this proposed determination should be provided in WordPerfect, Microsoft Word, PDF, or text (ASCII) file format. Submissions should avoid the use of special characters or any form of encryption, and wherever possible comments should include the electronic signature of the author. No telefacsimiles (faxes) will be accepted. According to 10 CFR 1004.11, any person submitting information that he or she believes to be confidential and exempt by law from public disclosure should submit two copies: one copy of the document should have all the information believed to be confidential deleted. DOE will make its own determination as to the confidential status of the information and treat it according to its determination. Factors of interest to DOE when evaluating requests to treat submitted information as confidential include (1) A description of the items; (2) whether and why such items are customarily treated as confidential within the industry; (3) whether the information is generally known or available from public sources; (4) whether the information has previously been made available to others without obligations concerning its confidentiality; (5) an explanation of the competitive injury to the submitting persons which would result from public disclosure; (6) a date after which such information might no longer be considered confidential; and (7) why disclosure of the information would be contrary to the public interest. B. Issues on Which DOE Seeks Comments DOE welcomes comments on all aspects of this proposed determination. DOE is particularly interested in receiving comments from interested parties on the following issues related to the proposed determination for computers: • Definition(s) of computers; • Whether classifying computers as a covered product is necessary or appropriate to carry out the purposes of EPCA; • Calculations and values for average household energy consumption; and • Availability or lack of availability of technologies for improving energy efficiency of computers. The Department is interested in receiving views concerning other VerDate Mar<15>2010 14:58 Jul 11, 2013 Jkt 229001 relevant issues that participants believe would affect DOE’s ability to establish test procedures and energy conservation standards for computers. The Department invites all interested parties to submit in writing by August 12, 2013, comments and information on matters addressed in this notice and on other matters relevant to consideration of a determination for computers. After the expiration of the period for submitting written statements, the Department will consider all comments and additional information that is obtained from interested parties or through further analyses, and it will prepare a final determination. If DOE determines that computers qualify as a covered product, DOE will consider a test procedure and energy conservation standards for computers. Members of the public will be given an opportunity to submit written and oral comments on any proposed test procedure and standards. List of Subjects in 10 CFR part 430 Administrative practice and procedure, Confidential business information, Energy conservation, Reporting and recordkeeping requirements. Issued in Washington, DC, on July 5, 2013. Kathleen B. Hogan, Deputy Assistant Secretary for Energy Efficiency, Energy Efficiency and Renewable Energy. [FR Doc. 2013–16728 Filed 7–11–13; 8:45 am] BILLING CODE 6450–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0574; Directorate Identifier 2008–SW–22–AD] RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Canada (Bell) Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede an existing airworthiness directive (AD) for the Bell Model 407 helicopters. The existing AD currently requires preflight checking and repetitively inspecting for a crack in certain tailbooms that have been redesigned, replacing the tailboom if there is a crack, modifying and reidentifying certain tailbooms, installing SUMMARY: PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 41877 an improved horizontal stabilizer assembly, and assigning a 5,000 hour time-in-service (TIS) limit. Since we issued that AD, we have received several additional reports of cracked tailboom skins. This proposed AD would retain the existing requirements and apply additional inspection requirements. The proposed actions are intended to prevent separation of the tailboom and subsequent loss of control of the helicopter. DATES: We must receive comments on this proposed AD by September 10, 2013. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to https://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 https:// 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 proposed 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 proposed AD, contact Bell Helicopter Textron Canada, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437–2862 or (800) 363– 8023, fax (450) 433–0272 or at https:// www.bellcustomer.com/files/. You may review 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, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222–5110, fax (817) 222–5961, email sharon.y.miles@faa.gov. E:\FR\FM\12JYP1.SGM 12JYP1 41878 Federal Register / Vol. 78, No. 134 / Friday, July 12, 2013 / Proposed Rules SUPPLEMENTARY INFORMATION: Comments Invited 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 might result from adopting the proposals in this document. The most helpful comments reference a specific portion of the proposal, 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 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 proposed rulemaking. Before acting on this proposal, we will consider all comments we receive on or before the closing date for comments. We will consider comments filed after the comment period has closed if it is possible to do so without incurring expense or delay. We may change this proposal in light of the comments we receive. wreier-aviles on DSK5TPTVN1PROD with PROPOSALS Discussion On March 21, 2000, we issued AD 2000–06–10, Amendment 39–11651 (65 FR 16804, March 30, 2000), to require preflight checking and repetitively inspecting the tailboom for a crack and replacing the tailboom if a crack was found. On March 3, 2003, we issued AD 2003–05–03, Amendment 39–13079 (68 FR 11967, March 13, 2003), which superseded AD 2000–06–10. AD 2003– 05–03 requires prelight checks and repetitive inspections, modifying and reidentifying certain tailbooms, installing an improved horizontal stabilizer assembly, and assigning a 5,000-hour TIS life limit to certain tailbooms. AD 2003–05–03 was intended to prevent separation of the tailboom and subsequent loss of control of the helicopter. Actions Since Existing AD Was Issued Since we issued AD 2003–05–03, Transport Canada, which is the aviation authority for Canada, has issued Canadian AD No. CF–2008–04, dated January 11, 2008 (AD CF–2008–04), based on several reports of cracks to the tailboom skin on the left side in the area of horizontal stabilizer found by visual inspection. AD CF–2008–04 mandates new inspection requirements based on the manufacturer’s service information VerDate Mar<15>2010 14:58 Jul 11, 2013 Jkt 229001 discussed in the ‘‘Related Service Information’’ section of this NPRM. FAA’s Determination This helicopter model has been approved by the aviation authority of Canada and is approved for operation in the United States. Pursuant to our bilateral agreement, Transport Canada has kept the FAA informed of the situation described above. We are proposing this AD because we evaluated all known relevant information and determined that an unsafe condition is likely to exist or develop on other helicopters of these same type designs. Related Service Information We reviewed Bell Alert Service Bulletin (ASB) No. 407–07–80 and ASB No. 407–01–48, Revision C, both dated August 27, 2007. In ASB No. 407–07– 80, Bell states they have received additional reports of cracked tailboom skins, part number (P/N) 407–030–801– 157, affecting tailboom assemblies, P/N 407–530–014–101 and –103 (modified per AD 2003–05–03, reference ASB 407–01–48, Revision B, dated April 25, 2002), and original production tailboom assembly, P/N 407–030–801–107. Each report indicated a crack above the left side upper stabilizer attachment support at Station 98.89. Further investigation conducted by Bell revealed other areas of the tailbooms require additional attention. Thus, ASB 407–07–080 contains procedures for preparing the tailboom for repetitive inspection, preflight checking the tailboom, and repetitively inspecting the tailboom. Bell specifies that replacing the affected tailboom assembly, P/N 407–530–014– 101, –103 or 407–030–801–107, with tailboom assembly, P/N 407–030–801– 201, –203, –205, or later dash numbers is terminating action for Bell ASB No. 407–07–80. In ASB 407–01–48, Bell states that since issuing ASB 407–99–26, Revision C, dated February 28, 2002, they have received additional reports of cracks in the upper skins, which originated from holes where the fasteners are installed at the forward and aft section of the left upper stabilizer support, P/N 407–023– 800–117. ASB 407–01–48 contains procedures for inspecting the tailboom on the left side where the fasteners are installed, installing an improved horizontal stabilizer assembly and reidentifying the tailboom, and assigning a 5,000-hour TIS life limit to the tailboom. Proposed AD Requirements This proposed AD addresses certain part-numbered tailbooms that were modified and reidentified as one new P/ PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 N. These same P/Ns are addressed by new inspection requirements. This proposed AD retains the requirements of the superseded AD for certain partnumbered tailbooms and establishes new requirements for certain other P/ Ns, by requiring compliance with portions of the Bell ASBs as follows: • For tailboom, P/Ns 407–030–801– 101 and –105, which have not been modified, conduct daily preflight checks of the tailboom for a crack and repetitively inspect the tailboom for a crack. Within 600 hours TIS or 30 days, modify and re-identify these partnumbered tailbooms as P/N 407–530– 014–101 or 407–530–014–103, and install an improved horizontal stabilizer assembly. • For P/Ns 407–530–014–101 and –103 and P/N 407–030–801–107, revise the Airworthiness Limitations section of the maintenance manual by establishing a retirement life of 5,000 hours TIS, prepare the tailboom for daily visual checks and inspections, and inspect the tailboom for a crack. Thereafter, visually check the tailboom for a crack before the first flight of each day and repetitively inspect the tailboom for a crack every 100 hours TIS. • For all P/Ns, if there is a crack, before further flight, replace the tailboom. If there is no crack, ensure both surfaces are dry and protect each reworked area with a thin coat of clear coating. • An owner/operator (pilot) may perform the daily visual checks required by this proposed AD because these checks require no special tools and can be performed equally well by a pilot or a mechanic. This authorization is an exception to our standard maintenance regulations. Differences Between This Proposed AD and the Transport Canada AD This AD would not require you to contact the manufacturer. This AD does not state that replacing the affected tailboom with tailboom, P/N 407–030– 801–201, –203, –205, or later numbers constitutes terminating action because installing other part-numbered tailbooms than those listed in the applicability of this AD may also result in terminating action for the requirements of this AD. Costs of Compliance We estimate that this proposed AD would affect about 464 helicopters of U.S. registry. We estimate that operators would incur the following costs in order to comply with this AD. We estimate the time for conducting pilot checks is minimal and thus we are assuming there is no cost. It would take about .5 work- E:\FR\FM\12JYP1.SGM 12JYP1 Federal Register / Vol. 78, No. 134 / Friday, July 12, 2013 / Proposed Rules hour to perform the annotations in the helicopter records, 1.5 work hours to prepare the inspection area and do the magnification inspection, and 2.5 work hours to do the repetitive 100-hour TIS inspections at an average labor rate of $85 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators would be $1,445 per helicopter and $670,480 for the U.S. operator fleet to do the checks and inspections, based on 6 repetitive inspections the first year. The previous AD affected 284 helicopters, and we estimated 3.5 work hours to do the initial inspection, 1.5 work hours to do the recurring inspections, and 18 work hours to do the modification at an average labor rate of $60 per work hour. Required parts were estimated at $1,244 per helicopter. Based on these figures, the total cost of the AD on U.S. operators was estimated to be $3,254 per helicopter or $924,136, based on 8 repetitive inspections per year. According to Bell, the cost of a new tailboom is $82,850. Per Bell ASB 407– 07–80, the costs to replace the tailboom may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage by Bell. We have included all costs in our cost estimate. Authority for This Rulemaking wreier-aviles on DSK5TPTVN1PROD with PROPOSALS 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 VerDate Mar<15>2010 14:58 Jul 11, 2013 Jkt 229001 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the 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 proposed AD and placed it in the AD docket. 41879 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2003–05–03 (68 FR 11967, March 13, 2003) and by adding the following new AD: ■ Bell Helicopter Textron Canada: Docket No. FAA–2013–0574; Directorate Identifier 2008–SW–22–AD. (a) Applicability This AD applies to Model 407 helicopters, serial numbers 53000 through 53475, with tailboom, part number (P/N) 407–030–801– 101, –105, or –107, or 407–530–014–101 or –103, installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as cracks in the tailboom skin on the left side in the area of horizontal stabilizer, which could result in separation of the tailboom and subsequent loss of control of the helicopter. (c) Affected ADs This AD supersedes AD 2003–05–03, Amendment 39–13079 (68 FR 11967, March 13, 2003), which superseded AD 2000–06– 10, Amendment 39–11651 (65 FR 16804, March 30, 2000). (d) Comments Due Date We must receive comments by September 10, 2013. (e) Compliance List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: (f) Required Actions PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ PO 00000 Frm 00023 Fmt 4702 Sfmt 4702 (1) For tailboom, P/Ns 407–030–801–101 and –105: (i) Unmodified per Bell Alert Service Bulletin (ASB) 407–01–48, Revision C, dated August 27, 2007 (ASB 407–01–48): (A) Before the first flight of each day, visually check the tailboom for a crack, as depicted in Figure 1 to paragraph (f)(1)(i)(A) of this AD. BILLING CODE 4910–13–P E:\FR\FM\12JYP1.SGM 12JYP1 41880 wreier-aviles on DSK5TPTVN1PROD with PROPOSALS BILLING CODE 4910–13–C (B) For a tailboom with 600 or more hours time-in-service (TIS), within 25 hours TIS and thereafter at intervals not to exceed 50 hours TIS, visually inspect the tailboom for a crack using a 10X or higher magnifying glass by following the Accomplishment Instructions, Part II, of Bell ASB 407–99–26, Revision C, dated February 28, 2002, except this AD does not require you to contact Bell. VerDate Mar<15>2010 14:58 Jul 11, 2013 Jkt 229001 (ii) Within 600 hours TIS, but not later than 30 days: (A) Modify and re-identify each tailboom, P/N 407–030–801–101 as 407–530–014–101, and P/N 407–030–801–105 as 407–530–014– 103, by following the Accomplishment Instructions, Parts I and III, of ASB 407–01– 48. (B) Install improved horizontal stabilizer assembly, P/N 407–023–800–ALL, by following Bell Technical Bulletin No. 407– PO 00000 Frm 00024 Fmt 4702 Sfmt 4702 01–33, dated August 29, 2001, except this AD does not require you to contact Bell. (2) For tailboom, P/Ns 407–530–014–101 and –103, and P/N 407–030–801–107: (i) Before further flight after the tailboom is modified and re-identified, revise the Airworthiness Limitations section of the maintenance manual by establishing a retirement life of 5,000 hours TIS. Create a component history card or equivalent record and assign a life limit of 5,000 hours TIS by E:\FR\FM\12JYP1.SGM 12JYP1 EP12JY13.000</GPH> Federal Register / Vol. 78, No. 134 / Friday, July 12, 2013 / Proposed Rules Federal Register / Vol. 78, No. 134 / Friday, July 12, 2013 / Proposed Rules 41881 crack by following the Accomplishment Instructions, Part II, Steps 1.a) through 1.f), of Bell ASB 407–07–80, dated August 27, 2007 (ASB 407–07–80). (iii) Thereafter, before the first flight of each day, clean the area on the tailboom where paint has been removed and visually check the tailboom for a crack as depicted in Figure 2 to Paragraph (f)(2)(iii) of this AD. BILLING CODE 4910–13–C Instructions, Part IV, Steps 1 through 6, of ASB 407–07–80, except this AD does not require you to contact Bell. If there is corrosion within an allowable tolerance, repair each area of corrosion. (3) If there is a crack, before further flight, replace the tailboom. (4) If there is no crack, make sure both of the inspection area surfaces are dry and protect each reworked area with a thin coat of clear coating. (iv) Within 100 hours TIS and thereafter at intervals not to exceed 100 hours TIS, using a 10× or higher power magnifying glass, inspect each tailboom for a loose rivet, a crack, skin corrosion, or any other damage, by following the Accomplishment VerDate Mar<15>2010 14:58 Jul 11, 2013 Jkt 229001 PO 00000 Frm 00025 Fmt 4702 Sfmt 4702 BILLING CODE 4910–13–P E:\FR\FM\12JYP1.SGM 12JYP1 EP12JY13.001</GPH> wreier-aviles on DSK5TPTVN1PROD with PROPOSALS following the Accomplishment Instructions, Part IV, of ASB 407–01–48. (ii) Within 25 hours TIS or 30 days, whichever occurs first, prepare the tailboom for daily visual checks and recurring inspections and inspect the tailboom for a 41882 Federal Register / Vol. 78, No. 134 / Friday, July 12, 2013 / Proposed Rules (5) The actions required by paragraphs (f)(1)(i)(A) and (f)(2)(iii) of this AD may be performed by the owner/operator (pilot) holding at least a private pilot certificate and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR 43.9 (a)(1)–(4) and 91.417(a)(2)(v). This record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439. (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, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email sharon.y.miles@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. (h) Additional Information The subject of this AD is addressed in Transport Canada Civil Aviation (TCCA) AD No. CF–2008–04, dated January 11, 2008. You may view the TCCA AD on the Internet at https://www.regulations.gov in Docket No. FAA–2013–0574. (i) Subject Joint Aircraft Service Component (JASC) Code is 5300: Rotorcraft Tail Boom, and 5302: Middle Section. Issued in Fort Worth, Texas, on June 12, 2013. Kim Smith, Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2013–16727 Filed 7–11–13; 8:45 am] BILLING CODE 4910–13–P airplanes. That AD currently requires repetitive operational tests, repetitive measurements, and repetitive replacement of certain jackscrews. Since we issued that AD, the manufacturer revised the airplane maintenance manual (AMM) maintenance requirements and airworthiness limitations. This proposed AD would require revising the maintenance program to incorporate new or revised maintenance requirements and airworthiness limitations. We are proposing this AD to prevent reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by August 26, 2013. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Dassault Falcon Jet, P.O. Box 2000, South Hackensack, NJ 07606; telephone 201– 440–6700; Internet https:// www.dassaultfalcon.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. DEPARTMENT OF TRANSPORTATION Examining the AD Docket Federal Aviation Administration You may examine the AD docket on the Internet at https:// 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 proposed AD, the regulatory 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 FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 14 CFR Part 39 [Docket No. FAA–2013–0466; Directorate Identifier 2012–NM–156–AD] RIN 2120–AA64 wreier-aviles on DSK5TPTVN1PROD with PROPOSALS Airworthiness Directives; Dassault Aviation Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede airworthiness directive (AD) 2002–23– 19, which applies to all Dassault Aviation Model Falcon 2000 series SUMMARY: VerDate Mar<15>2010 14:58 Jul 11, 2013 Jkt 229001 PO 00000 Frm 00026 Fmt 4702 Sfmt 4702 Washington 98057–3356; phone: 425– 227–1137; fax: 425–227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2013–0466; Directorate Identifier 2012–NM–156–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On November 19, 2002, we issued AD 2002–23–19, Amendment 39–12963 (67 FR 71452, December 2, 2002), for all Dassault Aviation Model Falcon 2000 airplanes. (That AD superseded AD 99– 14–07, Amendment 39–11218 (64 FR 36561, July 7, 1999)). AD 2002–23–19 requires repetitive operational tests of the flap asymmetry detection system, repetitive replacement of the inboard flap jackscrews, and repetitive measurement of the screw/nut play of the jackscrews on the inboard and outboard flaps. Since we issued AD 2002–23–19, we have determined that existing maintenance requirements and airworthiness limitations are inadequate and additional inspections are necessary to address the identified unsafe condition. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2012– 0156, dated August 23, 2012 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: The airworthiness limitations and maintenance requirements for the Falcon 2000 type design are included in Dassault Aviation Falcon 2000 (F2000) Aircraft Maintenance Manual (AMM) chapter 5–40 and are approved by the European Aviation Safety Agency (EASA). EASA issued AD 2008–0221 to require accomplishment of the maintenance tasks, and implementation of the airworthiness limitations, as specified in E:\FR\FM\12JYP1.SGM 12JYP1

Agencies

[Federal Register Volume 78, Number 134 (Friday, July 12, 2013)]
[Proposed Rules]
[Pages 41877-41882]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-16727]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0574; Directorate Identifier 2008-SW-22-AD]
RIN 2120-AA64


Airworthiness Directives; Bell Helicopter Textron Canada (Bell) 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) for the Bell Model 407 helicopters. The existing AD currently 
requires preflight checking and repetitively inspecting for a crack in 
certain tailbooms that have been redesigned, replacing the tailboom if 
there is a crack, modifying and re-identifying certain tailbooms, 
installing an improved horizontal stabilizer assembly, and assigning a 
5,000 hour time-in-service (TIS) limit. Since we issued that AD, we 
have received several additional reports of cracked tailboom skins. 
This proposed AD would retain the existing requirements and apply 
additional inspection requirements. The proposed actions are intended 
to prevent separation of the tailboom and subsequent loss of control of 
the helicopter.

DATES: We must receive comments on this proposed AD by September 10, 
2013.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to https://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 https://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 proposed 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 proposed AD, contact 
Bell Helicopter Textron Canada, 12,800 Rue de l'Avenir, Mirabel, Quebec 
J7J1R4, telephone (450) 437-2862 or (800) 363-8023, fax (450) 433-0272 
or at https://www.bellcustomer.com/files/. You may review 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, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5110, 
fax (817) 222-5961, email sharon.y.miles@faa.gov.

[[Page 41878]]


SUPPLEMENTARY INFORMATION: 

Comments Invited

    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 might 
result from adopting the proposals in this document. The most helpful 
comments reference a specific portion of the proposal, 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 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 proposed rulemaking. Before acting on this proposal, we 
will consider all comments we receive on or before the closing date for 
comments. We will consider comments filed after the comment period has 
closed if it is possible to do so without incurring expense or delay. 
We may change this proposal in light of the comments we receive.

Discussion

    On March 21, 2000, we issued AD 2000-06-10, Amendment 39-11651 (65 
FR 16804, March 30, 2000), to require preflight checking and 
repetitively inspecting the tailboom for a crack and replacing the 
tailboom if a crack was found. On March 3, 2003, we issued AD 2003-05-
03, Amendment 39-13079 (68 FR 11967, March 13, 2003), which superseded 
AD 2000-06-10. AD 2003-05-03 requires prelight checks and repetitive 
inspections, modifying and reidentifying certain tailbooms, installing 
an improved horizontal stabilizer assembly, and assigning a 5,000-hour 
TIS life limit to certain tailbooms. AD 2003-05-03 was intended to 
prevent separation of the tailboom and subsequent loss of control of 
the helicopter.

Actions Since Existing AD Was Issued

    Since we issued AD 2003-05-03, Transport Canada, which is the 
aviation authority for Canada, has issued Canadian AD No. CF-2008-04, 
dated January 11, 2008 (AD CF-2008-04), based on several reports of 
cracks to the tailboom skin on the left side in the area of horizontal 
stabilizer found by visual inspection. AD CF-2008-04 mandates new 
inspection requirements based on the manufacturer's service information 
discussed in the ``Related Service Information'' section of this NPRM.

FAA's Determination

    This helicopter model has been approved by the aviation authority 
of Canada and is approved for operation in the United States. Pursuant 
to our bilateral agreement, Transport Canada has kept the FAA informed 
of the situation described above. We are proposing this AD because we 
evaluated all known relevant information and determined that an unsafe 
condition is likely to exist or develop on other helicopters of these 
same type designs.

Related Service Information

    We reviewed Bell Alert Service Bulletin (ASB) No. 407-07-80 and ASB 
No. 407-01-48, Revision C, both dated August 27, 2007. In ASB No. 407-
07-80, Bell states they have received additional reports of cracked 
tailboom skins, part number (P/N) 407-030-801-157, affecting tailboom 
assemblies, P/N 407-530-014-101 and -103 (modified per AD 2003-05-03, 
reference ASB 407-01-48, Revision B, dated April 25, 2002), and 
original production tailboom assembly, P/N 407-030-801-107. Each report 
indicated a crack above the left side upper stabilizer attachment 
support at Station 98.89. Further investigation conducted by Bell 
revealed other areas of the tailbooms require additional attention. 
Thus, ASB 407-07-080 contains procedures for preparing the tailboom for 
repetitive inspection, preflight checking the tailboom, and 
repetitively inspecting the tailboom. Bell specifies that replacing the 
affected tailboom assembly, P/N 407-530-014-101, -103 or 407-030-801-
107, with tailboom assembly, P/N 407-030-801-201, -203, -205, or later 
dash numbers is terminating action for Bell ASB No. 407-07-80.
    In ASB 407-01-48, Bell states that since issuing ASB 407-99-26, 
Revision C, dated February 28, 2002, they have received additional 
reports of cracks in the upper skins, which originated from holes where 
the fasteners are installed at the forward and aft section of the left 
upper stabilizer support, P/N 407-023-800-117. ASB 407-01-48 contains 
procedures for inspecting the tailboom on the left side where the 
fasteners are installed, installing an improved horizontal stabilizer 
assembly and re-identifying the tailboom, and assigning a 5,000-hour 
TIS life limit to the tailboom.

Proposed AD Requirements

    This proposed AD addresses certain part-numbered tailbooms that 
were modified and reidentified as one new P/N. These same P/Ns are 
addressed by new inspection requirements. This proposed AD retains the 
requirements of the superseded AD for certain part-numbered tailbooms 
and establishes new requirements for certain other P/Ns, by requiring 
compliance with portions of the Bell ASBs as follows:
     For tailboom, P/Ns 407-030-801-101 and -105, which have 
not been modified, conduct daily preflight checks of the tailboom for a 
crack and repetitively inspect the tailboom for a crack. Within 600 
hours TIS or 30 days, modify and re-identify these part-numbered 
tailbooms as P/N 407-530-014-101 or 407-530-014-103, and install an 
improved horizontal stabilizer assembly.
     For P/Ns 407-530-014-101 and -103 and P/N 407-030-801-107, 
revise the Airworthiness Limitations section of the maintenance manual 
by establishing a retirement life of 5,000 hours TIS, prepare the 
tailboom for daily visual checks and inspections, and inspect the 
tailboom for a crack. Thereafter, visually check the tailboom for a 
crack before the first flight of each day and repetitively inspect the 
tailboom for a crack every 100 hours TIS.
     For all P/Ns, if there is a crack, before further flight, 
replace the tailboom. If there is no crack, ensure both surfaces are 
dry and protect each reworked area with a thin coat of clear coating.
     An owner/operator (pilot) may perform the daily visual 
checks required by this proposed AD because these checks require no 
special tools and can be performed equally well by a pilot or a 
mechanic. This authorization is an exception to our standard 
maintenance regulations.

Differences Between This Proposed AD and the Transport Canada AD

    This AD would not require you to contact the manufacturer. This AD 
does not state that replacing the affected tailboom with tailboom, P/N 
407-030-801-201, -203, -205, or later numbers constitutes terminating 
action because installing other part-numbered tailbooms than those 
listed in the applicability of this AD may also result in terminating 
action for the requirements of this AD.

Costs of Compliance

    We estimate that this proposed AD would affect about 464 
helicopters of U.S. registry. We estimate that operators would incur 
the following costs in order to comply with this AD. We estimate the 
time for conducting pilot checks is minimal and thus we are assuming 
there is no cost. It would take about .5 work-

[[Page 41879]]

hour to perform the annotations in the helicopter records, 1.5 work 
hours to prepare the inspection area and do the magnification 
inspection, and 2.5 work hours to do the repetitive 100-hour TIS 
inspections at an average labor rate of $85 per work-hour. Based on 
these figures, we estimate the cost of the proposed AD on U.S. 
operators would be $1,445 per helicopter and $670,480 for the U.S. 
operator fleet to do the checks and inspections, based on 6 repetitive 
inspections the first year. The previous AD affected 284 helicopters, 
and we estimated 3.5 work hours to do the initial inspection, 1.5 work 
hours to do the recurring inspections, and 18 work hours to do the 
modification at an average labor rate of $60 per work hour. Required 
parts were estimated at $1,244 per helicopter. Based on these figures, 
the total cost of the AD on U.S. operators was estimated to be $3,254 
per helicopter or $924,136, based on 8 repetitive inspections per year.
    According to Bell, the cost of a new tailboom is $82,850. Per Bell 
ASB 407-07-80, the costs to replace the tailboom may be covered under 
warranty, thereby reducing the cost impact on affected individuals. We 
do not control warranty coverage by Bell. We have included all costs in 
our cost estimate.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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 proposed 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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 removing Airworthiness Directive (AD) 
2003-05-03 (68 FR 11967, March 13, 2003) and by adding the following 
new AD:

Bell Helicopter Textron Canada: Docket No. FAA-2013-0574; 
Directorate Identifier 2008-SW-22-AD.

(a) Applicability

    This AD applies to Model 407 helicopters, serial numbers 53000 
through 53475, with tailboom, part number (P/N) 407-030-801-101, -
105, or -107, or 407-530-014-101 or -103, installed, certificated in 
any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as cracks in the tailboom 
skin on the left side in the area of horizontal stabilizer, which 
could result in separation of the tailboom and subsequent loss of 
control of the helicopter.

(c) Affected ADs

    This AD supersedes AD 2003-05-03, Amendment 39-13079 (68 FR 
11967, March 13, 2003), which superseded AD 2000-06-10, Amendment 
39-11651 (65 FR 16804, March 30, 2000).

(d) Comments Due Date

    We must receive comments by September 10, 2013.

(e) 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.

(f) Required Actions

    (1) For tailboom, P/Ns 407-030-801-101 and -105:
    (i) Unmodified per Bell Alert Service Bulletin (ASB) 407-01-48, 
Revision C, dated August 27, 2007 (ASB 407-01-48):
    (A) Before the first flight of each day, visually check the 
tailboom for a crack, as depicted in Figure 1 to paragraph 
(f)(1)(i)(A) of this AD.
BILLING CODE 4910-13-P

[[Page 41880]]

[GRAPHIC] [TIFF OMITTED] TP12JY13.000

BILLING CODE 4910-13-C
    (B) For a tailboom with 600 or more hours time-in-service (TIS), 
within 25 hours TIS and thereafter at intervals not to exceed 50 
hours TIS, visually inspect the tailboom for a crack using a 10X or 
higher magnifying glass by following the Accomplishment 
Instructions, Part II, of Bell ASB 407-99-26, Revision C, dated 
February 28, 2002, except this AD does not require you to contact 
Bell.
    (ii) Within 600 hours TIS, but not later than 30 days:
    (A) Modify and re-identify each tailboom, P/N 407-030-801-101 as 
407-530-014-101, and P/N 407-030-801-105 as 407-530-014-103, by 
following the Accomplishment Instructions, Parts I and III, of ASB 
407-01-48.
    (B) Install improved horizontal stabilizer assembly, P/N 407-
023-800-ALL, by following Bell Technical Bulletin No. 407-01-33, 
dated August 29, 2001, except this AD does not require you to 
contact Bell.
    (2) For tailboom, P/Ns 407-530-014-101 and -103, and P/N 407-
030-801-107:
    (i) Before further flight after the tailboom is modified and re-
identified, revise the Airworthiness Limitations section of the 
maintenance manual by establishing a retirement life of 5,000 hours 
TIS. Create a component history card or equivalent record and assign 
a life limit of 5,000 hours TIS by

[[Page 41881]]

following the Accomplishment Instructions, Part IV, of ASB 407-01-
48.
    (ii) Within 25 hours TIS or 30 days, whichever occurs first, 
prepare the tailboom for daily visual checks and recurring 
inspections and inspect the tailboom for a crack by following the 
Accomplishment Instructions, Part II, Steps 1.a) through 1.f), of 
Bell ASB 407-07-80, dated August 27, 2007 (ASB 407-07-80).
    (iii) Thereafter, before the first flight of each day, clean the 
area on the tailboom where paint has been removed and visually check 
the tailboom for a crack as depicted in Figure 2 to Paragraph 
(f)(2)(iii) of this AD.
BILLING CODE 4910-13-P
[GRAPHIC] [TIFF OMITTED] TP12JY13.001

BILLING CODE 4910-13-C
    (iv) Within 100 hours TIS and thereafter at intervals not to 
exceed 100 hours TIS, using a 10x or higher power magnifying glass, 
inspect each tailboom for a loose rivet, a crack, skin corrosion, or 
any other damage, by following the Accomplishment Instructions, Part 
IV, Steps 1 through 6, of ASB 407-07-80, except this AD does not 
require you to contact Bell. If there is corrosion within an 
allowable tolerance, repair each area of corrosion.
    (3) If there is a crack, before further flight, replace the 
tailboom.
    (4) If there is no crack, make sure both of the inspection area 
surfaces are dry and protect each reworked area with a thin coat of 
clear coating.

[[Page 41882]]

    (5) The actions required by paragraphs (f)(1)(i)(A) and 
(f)(2)(iii) of this AD may be performed by the owner/operator 
(pilot) holding at least a private pilot certificate and must be 
entered into the aircraft records showing compliance with this AD in 
accordance with 14 CFR 43.9 (a)(1)-(4) and 91.417(a)(2)(v). This 
record must be maintained as required by 14 CFR 91.417, 121.380, or 
135.439.

(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, Aviation Safety 
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-
5110; email sharon.y.miles@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.

(h) Additional Information

    The subject of this AD is addressed in Transport Canada Civil 
Aviation (TCCA) AD No. CF-2008-04, dated January 11, 2008. You may 
view the TCCA AD on the Internet at https://www.regulations.gov in 
Docket No. FAA-2013-0574.

(i) Subject

    Joint Aircraft Service Component (JASC) Code is 5300: Rotorcraft 
Tail Boom, and 5302: Middle Section.

    Issued in Fort Worth, Texas, on June 12, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-16727 Filed 7-11-13; 8:45 am]
BILLING CODE 4910-13-P