Airworthiness Directives; AgustaWestland S.p.A. (Type Certificate Previously Held by Agusta S.p.A.) (Agusta) Helicopters, 24551-24553 [2014-09414]

Download as PDF Federal Register / Vol. 79, No. 84 / Thursday, May 1, 2014 / Rules and Regulations (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes ODA that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (1) For more information about this AD, contact Susan L. Monroe, Aerospace Engineer, Cabin Safety and Environmental Systems Branch, ANM–150S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6457; fax: 425–917–6590; email: susan.l.monroe@faa.gov. (2) Service information identified in this AD that is not incorporated by reference may be obtained at the addresses specified in paragraphs (l)(3) and (l)(4) of this AD. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Boeing Alert Service Bulletin 777– 35A0029, Revision 1, dated April 29, 2013. (ii) Reserved. (3) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766– 5680; Internet https:// www.myboeingfleet.com. (4) You may view this service information at 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. tkelley on DSK3SPTVN1PROD with RULES Issued in Renton, Washington, on April 17, 2014. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–09413 Filed 4–30–14; 8:45 am] BILLING CODE 4910–13–P 16:24 Apr 30, 2014 Jkt 232001 [Docket No. FAA–2013–0943; Directorate Identifier 2013–SW–001–AD; Amendment 39–17836; AD 2014–09–01] any comments received, and other information. The street address for the Docket Operations Office (phone: 800– 647–5527) is U.S. Department of Transportation, Docket Operations Office, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. RIN 2120–AA64 (k) Related Information VerDate Mar<15>2010 24551 FOR FURTHER INFORMATION CONTACT: Airworthiness Directives; AgustaWestland S.p.A. (Type Certificate Previously Held by Agusta S.p.A.) (Agusta) Helicopters Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email robert.grant@faa.gov. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUPPLEMENTARY INFORMATION: Discussion We are adopting a new airworthiness directive (AD) for Agusta Model A109C, A109E, A109K2, and A119 helicopters. This AD requires a recurring visual inspection of the tail rotor (T/R) blade retaining bolts (bolts) for a crack, corrosion, damage, or missing cadmium plating in the central part of the bolt and, depending on findings, a liquid penetrant inspection. This AD also requires replacing a cracked or damaged bolt. This AD was prompted by two reported incidents of cracked bolts. The actions of this AD are intended to detect an unairworthy bolt and prevent failure of a bolt, release of a T/R blade, and subsequent loss of control of the helicopter. DATES: This AD is effective June 5, 2014. The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of June 5, 2014. ADDRESSES: For service information identified in this AD, contact AgustaWestland, Product Support Engineering, Via del Gregge, 100, 21015 Lonate Pozzolo (VA) Italy, ATTN: Maurizio D’Angelo; telephone 39–0331– 664757; fax 39–0331–664680; or at https://www.agustawestland.com/ technical-bulletins. 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. SUMMARY: 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 AD, the European Aviation Safety Agency (EASA) AD, any incorporated-by-reference service information, the economic evaluation, PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 On November 20, 2013, at 78 FR 69595, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 by adding an AD that would apply to certain Agusta Model A109C, A109E, A109K2, and A119 helicopters. The NPRM proposed to require a recurring visual inspection of each bolt, part number (P/N) 109–8131– 09–1, for a crack, corrosion, a nick, other damage, or missing cadmium plating in the central part of the bolt. If a crack is not detected by the visual inspection, the NPRM proposed to require a liquid penetrant inspection. If there is a crack, corrosion, damage, or missing cadmium plating in the central part of the bolt, the NPRM proposed to require replacing the bolt before further flight. The NPRM also proposed to prohibit installing certain bolts on any helicopter unless it has passed the proposed inspections. The proposed requirements were intended to detect an unairworthy bolt and prevent failure of a bolt, release of a T/R blade, and subsequent loss of control of the helicopter. The NPRM was prompted by AD No. 2013–0009, dated January 11, 2013, issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition for Agusta Model A109C, A109K2, A109E, and A119 helicopters, all serial numbers. EASA advises that cracks were reported in bolts, P/N 109– 8131–09–1, installed on a Model A109K2 and a Model A109E helicopter. EASA further states that investigations conducted by Agusta revealed the cracks were in the same area of the bolts and corresponded with corrosion pits. EASA specified that this condition, if not detected and corrected, could cause damage to, or loss of, a T/R blade, possibly resulting in loss of control of the helicopter. E:\FR\FM\01MYR1.SGM 01MYR1 24552 Federal Register / Vol. 79, No. 84 / Thursday, May 1, 2014 / Rules and Regulations Comments We gave the public the opportunity to participate in developing this AD, but we did not receive any comments on the NPRM (78 FR 69595, November 20, 2013). FAA’s Determination These helicopters have been approved by the aviation authority of Italy and are approved for operation in the United States. Pursuant to our bilateral agreement with Italy, EASA, its technical representative, has notified us of the unsafe condition described in the EASA AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs and that air safety and the public interest require adopting the AD requirements as proposed. Interim Action We consider this AD to be an interim action. If final action is later identified, we might consider additional rulemaking. tkelley on DSK3SPTVN1PROD with RULES Related Service Information AgustaWestland issued Bollettino Tecnico (BT) No. 109–135 for Model A109C helicopters, BT No. 109EP–125 for Model A109E helicopters, BT No. 109K–55 for Model A109K2 helicopters, and BT No. 119–052 for Model A119 helicopters. All of the BTs are dated December 19, 2012. The BTs specify to perform a visual inspection of bolt, P/ N 109–8131–09–1, in accordance with the maintenance manual applicable to the model helicopter for condition, corrosion, and nicks. The BTs specify replacement of the bolt if there is any damage, even if minor, or if there is missing cadmium plating in the central part of the bolt. The BTs state that if a crack is not revealed from the visual inspection, then to perform a liquid penetrant inspection. The BTs further specify repeating the visual inspection of the bolts at intervals specific to the model helicopter. The BTs state the results of the inspections must be communicated to AgustaWestland. Costs of Compliance We estimate this AD affects 132 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. We estimate it will take 2 work-hours to perform the initial visual and liquid penetrant inspections and 1 work-hour to perform each recurring visual inspection at an average labor cost of $85 per work-hour. Based on these VerDate Mar<15>2010 16:24 Apr 30, 2014 Jkt 232001 figures, it will cost about $170 to perform the initial inspections and about $85 to perform each recurring visual inspection. A replacement bolt will cost approximately $1,067; no additional labor cost is expected for replacement. 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 helicopters identified in this rulemaking action. Regulatory Findings 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 above, 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, PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 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): ■ 2014–09–01 AgustWestland S.p.A. (Type Certificate Previously Held by Agusta S.p.A) (Agusta) Helicopters: Amendment 39–17836; Docket No. FAA–2013–0943; Directorate Identifier 2013–SW–001–AD. (a) Applicability This AD applies to Agusta Model A109C, A109E, A109K2, and A119 helicopters with a tail rotor blade retaining bolt (bolt), part number 109–8131–09–1, installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a crack in a bolt. This condition could result in failure of a bolt, release of a tail rotor blade, and subsequent loss of control of the helicopter. (c) Effective Date This AD becomes effective June 5, 2014. (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions For each bolt with less than 400 hours time-in-service (TIS), before exceeding 500 hours TIS on the bolt, and for each bolt with 400 or more hours TIS, before accumulating an additional 100 hours TIS or 2 months on the bolt, whichever occurs first: (1) Visually inspect each bolt for a crack, damage, corrosion, a nick, or missing cadmium plating in the central part of the bolt. (i) If there is a crack, corrosion, a nick, any other damage, or missing cadmium plating in the central part of the bolt, before further flight, replace the bolt with an airworthy bolt. (ii) If there is not a crack as a result of the initial visual inspection as required by paragraph (e)(1) of this AD, liquid-penetrant inspect the bolt in accordance with Annex A of AgustaWestland Bollettino Tecnico (BT) No. 109–135, BT No. 109EP–125, BT No. 109K–55, or BT No. 119–052, all dated December 19, 2012, as applicable to your model helicopter. If there is a crack, before further flight, replace the bolt with an airworthy bolt. (2) Thereafter, for Agusta Model A109C helicopters, repeat the required actions of paragraph (e)(1) of this AD at intervals not to exceed 300 additional hours TIS or 6 months, whichever occurs first. For Agusta Model A109E, A109K2, and A119 helicopters, E:\FR\FM\01MYR1.SGM 01MYR1 Federal Register / Vol. 79, No. 84 / Thursday, May 1, 2014 / Rules and Regulations repeat the required actions of paragraph (e)(1) of this AD at intervals not to exceed 200 additional hours TIS or 6 months, whichever occurs first. (3) Do not install a bolt that has accumulated more than 400 hours TIS on any helicopter unless it has passed the required actions of paragraph (e)(1) of this AD. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Robert Grant, Aviation Safety Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222– 5110; email robert.grant@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. (g) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2013–0009, dated January 11, 2013. You may view the EASA AD on the Internet at https://www.regulations.gov in Docket No. FAA–2013–0943. tkelley on DSK3SPTVN1PROD with RULES (h) Subject Joint Aircraft Service Component (JASC) Code: 6400, Tail Rotor. (i) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) AgustaWestland Bollettino Tecnico No. 109–135, December 19, 2012. (ii) AgustaWestland Bollettino Tecnico No. 109EP–125, December 19, 2012. (iii) AgustaWestland Bollettino Tecnico No. 109K–55, December 19, 2012. (iv) AgustaWestland Bollettino Tecnico No. 119–052, December 19, 2012. (3) For AgustaWestland service information identified in this AD, contact AgustaWestland, Product Support Engineering, Via del Gregge, 100, 21015 Lonate Pozzolo (VA) Italy, ATTN: Maurizio D’Angelo; telephone 39–0331–664757; fax 39–0331–664680; or at https:// www.agustawestland.com/technicalbulletins. (4) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. For information on the availability of this material at the FAA, call (817) 222–5110. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call VerDate Mar<15>2010 16:24 Apr 30, 2014 Jkt 232001 (202) 741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Fort Worth, Texas, on April 18, 2014. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2014–09414 Filed 4–30–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0023; Directorate Identifier 2013–CE–048–AD; Amendment 39–17837; AD 2014–09–02] RIN 2120–AA64 Airworthiness Directives; M7 Aerospace LLC Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain M7 Aerospace LLC Models SA26–T, SA26–AT, SA226–AT, SA226–T, SA226–T(B), SA226–TC, SA227–AC (C– 26A), SA227–AT, SA227–TT, SA227– BC (C–26A), SA227–CC, and SA227–DC (C–26B) airplanes. This AD was prompted by reports of jamming of the aileron control cable chain in the pilot and copilot control columns due to inadequate lubrication and maintenance of the chain. This AD requires repetitively replacing and lubricating the aileron chain, sprocket, and bearings in the control columns. We are issuing this AD to correct the unsafe condition on these products. DATES: This AD is effective June 5, 2014. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of June 5, 2014. ADDRESSES: For service information identified in this AD, contact M7 Aerospace LP, 10823 NE Entrance Road, San Antonio, Texas 78216; phone: (210) 824–9421; fax: (210) 804–7766; Internet: https://www.elbitsystems-us.com; email: none. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call 816–329– 4148. Examining the AD Docket You may examine the AD docket on the Internet at https:// Frm 00027 Fmt 4700 Sfmt 4700 www.regulations.gov by searching for and locating it in Docket No. FAA– 2014–0023; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Andrew McAnaul, Aerospace Engineer, FAA, ASW–150 (c/o San Antonio MIDO), 10100 Reunion Place, Suite 650, San Antonio, Texas 78216; phone: (210) 308–3365; fax: (210) 308–3370; email: andrew.mcanaul@faa.gov. SUPPLEMENTARY INFORMATION: Discussion SUMMARY: PO 00000 24553 We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain M7 Aerospace LLC Models SA26–T, SA26–AT, SA226–AT, SA226–T, SA226–T(B), SA226–TC, SA227–AC (C–26A), SA227–AT, SA227–TT, SA227–BC (C–26A), SA227– CC, and SA227–DC (C–26B) airplanes. The NPRM published in the Federal Register on January 21, 2014 (79 FR 3336). The NPRM proposed to require repetitively replacing and lubricating the aileron chain, sprocket, and bearings in the control columns. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the proposal and the FAA’s response to the comments. Request To Withdraw the Proposed AD Pat Kremer of Ameriflight, LLC stated that the proposed AD is too broad of a stroke across the industry because of a limited number of operators that have not performed maintenance to the level in the proposed AD. Pat Kremer also stated they replace the aileron chains every 10,000 hours time-in-service (TIS) (the compliance time in the proposed AD), along with the respective cables, on their fleet of 45 Model SA227 airplanes, and they have only occasionally found bearings that are worn. He also stated that they have never found a faulty sprocket. From these statements, we infer that Pat Kremer wants the proposed AD withdrawn because it is unnecessary E:\FR\FM\01MYR1.SGM 01MYR1

Agencies

[Federal Register Volume 79, Number 84 (Thursday, May 1, 2014)]
[Rules and Regulations]
[Pages 24551-24553]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-09414]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0943; Directorate Identifier 2013-SW-001-AD; 
Amendment 39-17836; AD 2014-09-01]
RIN 2120-AA64


Airworthiness Directives; AgustaWestland S.p.A. (Type Certificate 
Previously Held by Agusta S.p.A.) (Agusta) Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for Agusta 
Model A109C, A109E, A109K2, and A119 helicopters. This AD requires a 
recurring visual inspection of the tail rotor (T/R) blade retaining 
bolts (bolts) for a crack, corrosion, damage, or missing cadmium 
plating in the central part of the bolt and, depending on findings, a 
liquid penetrant inspection. This AD also requires replacing a cracked 
or damaged bolt. This AD was prompted by two reported incidents of 
cracked bolts. The actions of this AD are intended to detect an 
unairworthy bolt and prevent failure of a bolt, release of a T/R blade, 
and subsequent loss of control of the helicopter.

DATES: This AD is effective June 5, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of June 5, 2014.

ADDRESSES: For service information identified in this AD, contact 
AgustaWestland, Product Support Engineering, Via del Gregge, 100, 21015 
Lonate Pozzolo (VA) Italy, ATTN: Maurizio D'Angelo; telephone 39-0331-
664757; fax 39-0331-664680; or at https://www.agustawestland.com/technical-bulletins. 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.

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 AD, the European Aviation Safety 
Agency (EASA) AD, any incorporated-by-reference service information, 
the economic evaluation, any comments received, and other information. 
The street address for the Docket Operations Office (phone: 800-647-
5527) is U.S. Department of Transportation, Docket Operations Office, 
M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue 
SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort Worth, 
Texas 76137; telephone (817) 222-5110; email robert.grant@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    On November 20, 2013, at 78 FR 69595, the Federal Register 
published our notice of proposed rulemaking (NPRM), which proposed to 
amend 14 CFR part 39 by adding an AD that would apply to certain Agusta 
Model A109C, A109E, A109K2, and A119 helicopters. The NPRM proposed to 
require a recurring visual inspection of each bolt, part number (P/N) 
109-8131-09-1, for a crack, corrosion, a nick, other damage, or missing 
cadmium plating in the central part of the bolt. If a crack is not 
detected by the visual inspection, the NPRM proposed to require a 
liquid penetrant inspection. If there is a crack, corrosion, damage, or 
missing cadmium plating in the central part of the bolt, the NPRM 
proposed to require replacing the bolt before further flight. The NPRM 
also proposed to prohibit installing certain bolts on any helicopter 
unless it has passed the proposed inspections. The proposed 
requirements were intended to detect an unairworthy bolt and prevent 
failure of a bolt, release of a T/R blade, and subsequent loss of 
control of the helicopter.
    The NPRM was prompted by AD No. 2013-0009, dated January 11, 2013, 
issued by EASA, which is the Technical Agent for the Member States of 
the European Union, to correct an unsafe condition for Agusta Model 
A109C, A109K2, A109E, and A119 helicopters, all serial numbers. EASA 
advises that cracks were reported in bolts, P/N 109-8131-09-1, 
installed on a Model A109K2 and a Model A109E helicopter. EASA further 
states that investigations conducted by Agusta revealed the cracks were 
in the same area of the bolts and corresponded with corrosion pits. 
EASA specified that this condition, if not detected and corrected, 
could cause damage to, or loss of, a T/R blade, possibly resulting in 
loss of control of the helicopter.

[[Page 24552]]

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we did not receive any comments on the NPRM (78 FR 69595, 
November 20, 2013).

FAA's Determination

    These helicopters have been approved by the aviation authority of 
Italy and are approved for operation in the United States. Pursuant to 
our bilateral agreement with Italy, EASA, its technical representative, 
has notified us of the unsafe condition described in the EASA AD. We 
are issuing this AD because we evaluated all information provided by 
EASA and determined the unsafe condition exists and is likely to exist 
or develop on other helicopters of these same type designs and that air 
safety and the public interest require adopting the AD requirements as 
proposed.

Interim Action

    We consider this AD to be an interim action. If final action is 
later identified, we might consider additional rulemaking.

Related Service Information

    AgustaWestland issued Bollettino Tecnico (BT) No. 109-135 for Model 
A109C helicopters, BT No. 109EP-125 for Model A109E helicopters, BT No. 
109K-55 for Model A109K2 helicopters, and BT No. 119-052 for Model A119 
helicopters. All of the BTs are dated December 19, 2012. The BTs 
specify to perform a visual inspection of bolt, P/N 109-8131-09-1, in 
accordance with the maintenance manual applicable to the model 
helicopter for condition, corrosion, and nicks. The BTs specify 
replacement of the bolt if there is any damage, even if minor, or if 
there is missing cadmium plating in the central part of the bolt. The 
BTs state that if a crack is not revealed from the visual inspection, 
then to perform a liquid penetrant inspection. The BTs further specify 
repeating the visual inspection of the bolts at intervals specific to 
the model helicopter. The BTs state the results of the inspections must 
be communicated to AgustaWestland.

Costs of Compliance

    We estimate this AD affects 132 helicopters of U.S. Registry. We 
estimate that operators may incur the following costs in order to 
comply with this AD. We estimate it will take 2 work-hours to perform 
the initial visual and liquid penetrant inspections and 1 work-hour to 
perform each recurring visual inspection at an average labor cost of 
$85 per work-hour. Based on these figures, it will cost about $170 to 
perform the initial inspections and about $85 to perform each recurring 
visual inspection. A replacement bolt will cost approximately $1,067; 
no additional labor cost is expected for replacement.

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 helicopters identified in this 
rulemaking action.

Regulatory Findings

    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 above, 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):

2014-09-01 AgustWestland S.p.A. (Type Certificate Previously Held by 
Agusta S.p.A) (Agusta) Helicopters: Amendment 39-17836; Docket No. 
FAA-2013-0943; Directorate Identifier 2013-SW-001-AD.

(a) Applicability

    This AD applies to Agusta Model A109C, A109E, A109K2, and A119 
helicopters with a tail rotor blade retaining bolt (bolt), part 
number 109-8131-09-1, installed, certificated in any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in a bolt. This 
condition could result in failure of a bolt, release of a tail rotor 
blade, and subsequent loss of control of the helicopter.

(c) Effective Date

    This AD becomes effective June 5, 2014.

(d) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless it has already been 
accomplished prior to that time.

(e) Required Actions

    For each bolt with less than 400 hours time-in-service (TIS), 
before exceeding 500 hours TIS on the bolt, and for each bolt with 
400 or more hours TIS, before accumulating an additional 100 hours 
TIS or 2 months on the bolt, whichever occurs first:
    (1) Visually inspect each bolt for a crack, damage, corrosion, a 
nick, or missing cadmium plating in the central part of the bolt.
    (i) If there is a crack, corrosion, a nick, any other damage, or 
missing cadmium plating in the central part of the bolt, before 
further flight, replace the bolt with an airworthy bolt.
    (ii) If there is not a crack as a result of the initial visual 
inspection as required by paragraph (e)(1) of this AD, liquid-
penetrant inspect the bolt in accordance with Annex A of 
AgustaWestland Bollettino Tecnico (BT) No. 109-135, BT No. 109EP-
125, BT No. 109K-55, or BT No. 119-052, all dated December 19, 2012, 
as applicable to your model helicopter. If there is a crack, before 
further flight, replace the bolt with an airworthy bolt.
    (2) Thereafter, for Agusta Model A109C helicopters, repeat the 
required actions of paragraph (e)(1) of this AD at intervals not to 
exceed 300 additional hours TIS or 6 months, whichever occurs first. 
For Agusta Model A109E, A109K2, and A119 helicopters,

[[Page 24553]]

repeat the required actions of paragraph (e)(1) of this AD at 
intervals not to exceed 200 additional hours TIS or 6 months, 
whichever occurs first.
    (3) Do not install a bolt that has accumulated more than 400 
hours TIS on any helicopter unless it has passed the required 
actions of paragraph (e)(1) of this AD.

(f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, FAA, 2601 Meacham Blvd., Fort 
Worth, Texas 76137; telephone (817) 222-5110; email 
robert.grant@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.

(g) Additional Information

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) AD No. 2013-0009, dated January 11, 2013. You may view 
the EASA AD on the Internet at https://www.regulations.gov in Docket 
No. FAA-2013-0943.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6400, Tail Rotor.

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) AgustaWestland Bollettino Tecnico No. 109-135, December 19, 
2012.
    (ii) AgustaWestland Bollettino Tecnico No. 109EP-125, December 
19, 2012.
    (iii) AgustaWestland Bollettino Tecnico No. 109K-55, December 
19, 2012.
    (iv) AgustaWestland Bollettino Tecnico No. 119-052, December 19, 
2012.
    (3) For AgustaWestland service information identified in this 
AD, contact AgustaWestland, Product Support Engineering, Via del 
Gregge, 100, 21015 Lonate Pozzolo (VA) Italy, ATTN: Maurizio 
D'Angelo; telephone 39-0331-664757; fax 39-0331-664680; or at https://www.agustawestland.com/technical-bulletins.
    (4) You may view this service information at FAA, Office of the 
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, 
Fort Worth, Texas 76137. For information on the availability of this 
material at the FAA, call (817) 222-5110.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call (202) 741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on April 18, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-09414 Filed 4-30-14; 8:45 am]
BILLING CODE 4910-13-P
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