Airworthiness Directives; Agusta S.p.A. Helicopters (Type Certificate Currently Held by AgustaWestland S.p.A) (AgustaWestland), 11699-11701 [2014-04310]

Download as PDF Federal Register / Vol. 79, No. 41 / Monday, March 3, 2014 / Rules and Regulations (f) Alternative Methods of Compliance (AMOCs) 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): ■ 2014–03–01 Agusta S.p.A. Helicopters: Amendment 39–17738; Docket No. FAA–2012–0886; Directorate Identifier 2008–SW–067–AD. (a) Applicability This AD applies to Agusta Model AB139 and AW139 helicopters, with a wire strike protection system (WSPS) top cable cutter assembly, part number (P/N) 423–83001–1, installed, which is part of the WSPS, P/N 4G9540F00211 or P/N 4G9540F00311, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as inflight contact between the top cable cutter assembly and main rotor (M/R) blades. This condition could result in damage to the M/ R blades and subsequent loss of helicopter control. (c) Effective Date This AD becomes effective April 7, 2014. mstockstill on DSK4VPTVN1PROD with RULES (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions (1) Within 200 hours time-in-service, remove the WSPS upper installation, P/N 4G9540A00111, including top cable cutter assembly, P/N 423–83001–1. (2) Before installing a WSPS upper installation, P/N 4G9540A00111, either: (i) Rework the top cable cutter assembly, P/ N 423–83001–1, in accordance with the Compliance Instructions, paragraph 3.1 through 3.5, and Figure 1 of Agusta Bolletino Technico No. 139–126, dated June 20, 2008. Re-identify the top cable cutter assembly in a visible and permanent way by adding ‘‘BT 139–126 Rev./’’ or ‘‘FAA’’ at the end of the part number; or (ii) Replace the top cable cutter assembly, P/N 423–83001–1, with an airworthy top cable cutter assembly that has been reworked and re-identified in accordance with paragraph (e)(2)(i) of this AD. (3) Do not install a top cable cutter assembly, P/N 423–83001–1, on any helicopter unless it has been reworked and re-identified in accordance with paragraph (e)(2)(i) of this AD. VerDate Mar<15>2010 16:16 Feb 28, 2014 Jkt 232001 11699 DEPARTMENT OF TRANSPORTATION (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, TX 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. Federal Aviation Administration (g) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2008–0148, dated August 5, 2008. You may view the EASA AD on the Internet at https://www.regulations.gov in Docket No. FAA–2012–0886. (h) Subject Joint Aircraft Service Component (JASC) Code: 5320: Fuselage Miscellaneous Structure. (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) Agusta Bolletino Technico No. 139–126, dated June 20, 2008. (ii) Reserved. (3) For Agusta service information identified in this AD, contact Agusta, Via Giovanni Agusta, 520 21017 Cascina Costa di Samarate (VA), Italy, telephone 39 0331– 229111, fax 39 0331–229605/222595, or at https://customersupport.agusta.com/ technical_advice.php. (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/ibrlocations.html. Issued in Fort Worth, Texas, on January 24, 2014. Kim Smith, Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2014–02153 Filed 2–28–14; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 14 CFR Part 39 [Docket No. FAA–2013–0643; Directorate Identifier 2012–SW–096–AD; Amendment 39–17773; AD 2014–04–14] RIN 2120–AA64 Airworthiness Directives; Agusta S.p.A. Helicopters (Type Certificate Currently Held by AgustaWestland S.p.A) (AgustaWestland) Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for AgustaWestland Model A109S, AW109SP, A119, and AW119 MKII helicopters to require removing certain rod end assemblies from service. This AD was prompted by reports of fractures on the rod end assemblies that could damage the main rotor assembly and lead to loss of control of the helicopter. DATES: This AD is effective April 7, 2014. 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. ADDRESSES: 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 foreign authority’s AD, 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 E:\FR\FM\03MRR1.SGM 03MRR1 11700 Federal Register / Vol. 79, No. 41 / Monday, March 3, 2014 / Rules and Regulations 76137; telephone (817) 222–5110; email robert.grant@faa.gov. SUPPLEMENTARY INFORMATION: Discussion On July 23, 2013, at 78 FR 44042, 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 AgustaWestland Model A109S, AW109SP, A119, and AW119 MKII helicopters with a main rotor lag damper assembly, part number (P/N) 109–0112–39–103, 109–0112–39–105, 109–0112–05–105, or 109–0112–05– 107, installed with a rod end assembly, P/N M004–01H007–041 or M004– 01H007–045, with a serial number (S/N) 84 through 132, or 4964 through 5011. The NPRM proposed to require removing certain rod end assemblies from service. The proposed requirements were intended to prevent damage to the main rotor assembly and subsequent loss of control of the helicopter. The NPRM was prompted by AD No. 2012–0208, dated October 5, 2012, issued by the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union. AD No. 2012–0208 requires correcting an unsafe condition for AgustaWestland Model A109LUH, A109S, AW109SP, A119, and AW119 MKII helicopters. EASA advises that cases of in-flight fractures of rod end assembly, P/N M004–01H007–045, installed on main rotor lag dampers have been reported on Model A109LUH and AW109SP helicopters. An investigation revealed that two batches of rod end assemblies, P/N M004– 01H007–041 and M004–01H007–045, could have cracks, according to EASA. EASA states that this condition, if not corrected, could lead to main rotor damage, possibly resulting in loss of control of the helicopter. mstockstill on DSK4VPTVN1PROD with RULES Comments We gave the public the opportunity to participate in developing this AD, but we received no comments on the NPRM (78 FR 44042, July 23, 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 VerDate Mar<15>2010 16:16 Feb 28, 2014 Jkt 232001 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. Differences Between This AD and the EASA AD EASA requires compliance with the inspection and removal of any affected parts from service within 25 hours flight hours or three months. We require removing the affected parts from service within 25 hours time-in-service. The EASA AD applies to AgustaWestland Model A109LUH, and this AD does not because that model has no U.S. type certificate. Related Service Information AgustaWestland issued Bollettino Tecnico (BT) No. 109S–49 for Model A109S helicopters, BT No. 109SP–052 for Model AW109SP helicopters, and BT No. 119–50 for Model A119 and AW119 MKII helicopters. All of the BTs are dated October 3, 2012. The BTs specify a one-time inspection of each rod end assembly, P/Ns M004–01H007– 041 and M004–01H007–045, to determine its serial number. The BTs then require removal from service of certain serial-numbered rod end assemblies because fractures had been reported on rod ends in these batches. According to the BTs, no one was injured in the helicopters, and no helicopters were damaged because of these fractures. Costs of Compliance We estimate that this AD affects 91 helicopters of U.S. Registry and that labor costs average $85 a work-hour. Based on these estimates, we expect the following costs: • Replacing a rod end assembly requires 1.5 work-hours for a labor cost of $128. Parts cost $3,918 for a total cost of $4,046 per helicopter, $368,186 for the U.S. fleet. According to the manufacturer’s service information, costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage by manufacturers. Accordingly, 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. PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 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 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): ■ 2014–04–14 Agusta S.p.A. Helicopters (Type Certificate Currently Held by E:\FR\FM\03MRR1.SGM 03MRR1 Federal Register / Vol. 79, No. 41 / Monday, March 3, 2014 / Rules and Regulations AgustaWestland S.p.A) (AgustaWestland): Amendment 39– 17773; Docket No. FAA–2013–0643; Directorate Identifier 2012–SW–096–AD. (a) Applicability This AD applies to AgustaWestland Model A109S, AW109SP, A119, and AW119 MKII helicopters with a main rotor lag damper assembly (lag damper), part number (P/N) 109–0112–39–103, 109–0112–39–105, 109– 0112–05–105, or 109–0112–05–107, installed with a rod end assembly, P/N M004– 01H007–041 or M004–01H007–045, with a serial number (S/N) 84 through 132, or 4964 through 5011, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as a crack in a rod end assembly, which could result in fracture of the rod end assembly, damage to the main rotor, and subsequent loss of control of the helicopter. (c) Effective Date This AD becomes effective April 7, 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 (1) Within 25 hours time-in-service, remove the rod end assembly from service. (2) Do not install a rod end assembly, P/ N M004–01H007–041 or M004–01H007–045, with a S/N 84 through 132 or 4964 through 5011, on any helicopter. (f) Special Flight Permits Special flight permits are prohibited. mstockstill on DSK4VPTVN1PROD with RULES (g) Additional Information (1) AgustaWestland Bollettino Tecnico No. 109S–49, No. 109SP–052, and No. 119–50, all dated October 3, 2012, which are not incorporated by reference, contain additional information about the subject of this AD. 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/technicalbulletins. You may review the referenced 16:16 Feb 28, 2014 Jkt 232001 (h) Subject Joint Aircraft Service Component (JASC) Code: 6200, Main Rotor System. Issued in Fort Worth, Texas, on February 20, 2014. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2014–04310 Filed 2–28–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0770; Directorate Identifier 2011–SW–057–AD; Amendment 39–17771; AD 2014–04–12] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters (Type Certificate Previously Held by Eurocopter France) (Airbus Helicopters) Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: (g) 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. VerDate Mar<15>2010 service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. (2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2012–0208, dated October 5, 2012. You may view the EASA AD on the Internet at https://www.regulations.gov in Docket No. FAA–2013–0643. SUMMARY: We are adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model EC225LP helicopters. This AD adds a new operating limitation that requires increasing the minimum density altitude flight limitation for helicopters without certain Eurocopter modifications installed. This AD is prompted by a report that flights below a certain density altitude create oscillations in the main rotor which can transfer dynamic loads to the structure, the main gearbox (MGB), and the main servo-control inputs, which could result in subsequent loss of control of the helicopter. DATES: This AD is effective April 7, 2014. For service information identified in this AD, contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at https:// www.airbushelicopters.com/techpub. You may review the referenced service ADDRESSES: PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 11701 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, 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: Gary Roach, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email gary.b.roach@faa.gov. SUPPLEMENTARY INFORMATION: Discussion On September 6, 2013, at 78 FR 54792, 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 Eurocopter France (now Airbus Helicopters) Model EC225LP helicopters, except those with certain modifications (MODs) installed. The NPRM proposed to require, within 50 hours time-in-service (TIS), amending the Rotorcraft Flight Manual (RFM) to limit minimum flight altitude to ¥2,000 feet density altitude. The proposed requirements were intended to prevent oscillations in the main rotor that can transfer dynamic loads to the structure, the MGB, and the main servo-control inputs, which could result in subsequent loss of control of the helicopter. The NPRM was prompted by AD No. 2008–0007R3, dated May 12, 2010, issued by EASA, which is the Technical Agent for the Member States of the European Union. EASA issued AD No. 2008–0007R3 to correct an unsafe condition for Model EC 225 LP helicopters that are ‘‘not equipped of all three modifications MOD 0726582, MOD 0726477, and MOD 0726583, or, if not equipped of MOD 0726592, or, if equipped with all three modifications MOD 0726606, MOD 0726610, MOD 0726611 and missing accomplishment E:\FR\FM\03MRR1.SGM 03MRR1

Agencies

[Federal Register Volume 79, Number 41 (Monday, March 3, 2014)]
[Rules and Regulations]
[Pages 11699-11701]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-04310]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0643; Directorate Identifier 2012-SW-096-AD; 
Amendment 39-17773; AD 2014-04-14]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for 
AgustaWestland Model A109S, AW109SP, A119, and AW119 MKII helicopters 
to require removing certain rod end assemblies from service. This AD 
was prompted by reports of fractures on the rod end assemblies that 
could damage the main rotor assembly and lead to loss of control of the 
helicopter.

DATES: This AD is effective April 7, 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 foreign authority's AD, 
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

[[Page 11700]]

76137; telephone (817) 222-5110; email robert.grant@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    On July 23, 2013, at 78 FR 44042, 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 AgustaWestland Model 
A109S, AW109SP, A119, and AW119 MKII helicopters with a main rotor lag 
damper assembly, part number (P/N) 109-0112-39-103, 109-0112-39-105, 
109-0112-05-105, or 109-0112-05-107, installed with a rod end assembly, 
P/N M004-01H007-041 or M004-01H007-045, with a serial number (S/N) 84 
through 132, or 4964 through 5011. The NPRM proposed to require 
removing certain rod end assemblies from service. The proposed 
requirements were intended to prevent damage to the main rotor assembly 
and subsequent loss of control of the helicopter.
    The NPRM was prompted by AD No. 2012-0208, dated October 5, 2012, 
issued by the European Aviation Safety Agency (EASA), which is the 
Technical Agent for the Member States of the European Union. AD No. 
2012-0208 requires correcting an unsafe condition for AgustaWestland 
Model A109LUH, A109S, AW109SP, A119, and AW119 MKII helicopters. EASA 
advises that cases of in-flight fractures of rod end assembly, P/N 
M004-01H007-045, installed on main rotor lag dampers have been reported 
on Model A109LUH and AW109SP helicopters. An investigation revealed 
that two batches of rod end assemblies, P/N M004-01H007-041 and M004-
01H007-045, could have cracks, according to EASA. EASA states that this 
condition, if not corrected, could lead to main rotor damage, possibly 
resulting in loss of control of the helicopter.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we received no comments on the NPRM (78 FR 44042, July 23, 
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.

Differences Between This AD and the EASA AD

    EASA requires compliance with the inspection and removal of any 
affected parts from service within 25 hours flight hours or three 
months. We require removing the affected parts from service within 25 
hours time-in-service. The EASA AD applies to AgustaWestland Model 
A109LUH, and this AD does not because that model has no U.S. type 
certificate.

Related Service Information

    AgustaWestland issued Bollettino Tecnico (BT) No. 109S-49 for Model 
A109S helicopters, BT No. 109SP-052 for Model AW109SP helicopters, and 
BT No. 119-50 for Model A119 and AW119 MKII helicopters. All of the BTs 
are dated October 3, 2012. The BTs specify a one-time inspection of 
each rod end assembly, P/Ns M004-01H007-041 and M004-01H007-045, to 
determine its serial number. The BTs then require removal from service 
of certain serial-numbered rod end assemblies because fractures had 
been reported on rod ends in these batches. According to the BTs, no 
one was injured in the helicopters, and no helicopters were damaged 
because of these fractures.

Costs of Compliance

    We estimate that this AD affects 91 helicopters of U.S. Registry 
and that labor costs average $85 a work-hour. Based on these estimates, 
we expect the following costs:
     Replacing a rod end assembly requires 1.5 work-hours for a 
labor cost of $128. Parts cost $3,918 for a total cost of $4,046 per 
helicopter, $368,186 for the U.S. fleet.
    According to the manufacturer's service information, costs of this 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage by 
manufacturers. Accordingly, 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 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):

2014-04-14 Agusta S.p.A. Helicopters (Type Certificate Currently 
Held by

[[Page 11701]]

AgustaWestland S.p.A) (AgustaWestland): Amendment 39-17773; Docket 
No. FAA-2013-0643; Directorate Identifier 2012-SW-096-AD.

(a) Applicability

    This AD applies to AgustaWestland Model A109S, AW109SP, A119, 
and AW119 MKII helicopters with a main rotor lag damper assembly 
(lag damper), part number (P/N) 109-0112-39-103, 109-0112-39-105, 
109-0112-05-105, or 109-0112-05-107, installed with a rod end 
assembly, P/N M004-01H007-041 or M004-01H007-045, with a serial 
number (S/N) 84 through 132, or 4964 through 5011, certificated in 
any category.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in a rod end 
assembly, which could result in fracture of the rod end assembly, 
damage to the main rotor, and subsequent loss of control of the 
helicopter.

(c) Effective Date

    This AD becomes effective April 7, 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

    (1) Within 25 hours time-in-service, remove the rod end assembly 
from service.
    (2) Do not install a rod end assembly, P/N M004-01H007-041 or 
M004-01H007-045, with a S/N 84 through 132 or 4964 through 5011, on 
any helicopter.

(f) Special Flight Permits

    Special flight permits are prohibited.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: 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

    (1) AgustaWestland Bollettino Tecnico No. 109S-49, No. 109SP-
052, and No. 119-50, all dated October 3, 2012, which are not 
incorporated by reference, contain additional information about the 
subject of this AD. 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.
    (2) The subject of this AD is addressed in European Aviation 
Safety Agency (EASA) AD No. 2012-0208, dated October 5, 2012. You 
may view the EASA AD on the Internet at https://www.regulations.gov 
in Docket No. FAA-2013-0643.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6200, Main Rotor 
System.

    Issued in Fort Worth, Texas, on February 20, 2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-04310 Filed 2-28-14; 8:45 am]
BILLING CODE 4910-13-P
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