Federal Register / Vol. 79, No. 224 / Thursday, November 20, 2014 / Rules and Regulations 69039 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification 

Within 6,600 flight hours after the effective 

date of this AD, but no later than 36 months 

after the effective date of this AD: Modify the 

MLG by installing a new bracket on the left 

and right lower aft-wing planks, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

601R–32–110, dated December 19, 2013. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the New York ACO, send it to 

ATTN: Program Manager, Continuing 

Operational Safety, FAA, New York ACO, 

1600 Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516 228–7300; fax 516– 

794–5531. Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, New York ACO, ANE–170, 

Engine and Propeller Directorate, FAA; or 

Transport Canada Civil Aviation (TCCA); or 

Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(i) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–10, dated 

February 12, 2014, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0489-0002. 

(j) 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 this AD specifies otherwise. 

(i) Bombardier Service Bulletin 601R–32– 

110, dated December 19, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. 

(4) You may view this 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. 

(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: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

November 5, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–26985 Filed 11–19–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0472; Directorate 

Identifier 2013–SW–040–AD; Amendment 

39–18018; AD 2014–23–02] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. Helicopters (Type Certificate 

Currently Held by AgustaWestland 

S.p.A.) (Agusta) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Agusta Model A109E, A109K2, A119, 

and AW119 MKII helicopters. This AD 

requires repetitively performing a 

magnetic particle inspection of the 

Gleason crown for a crack. This AD was 

prompted by a report of a crack that was 

found on a Gleason crown, which if not 

detected, could cause damage to or loss 

of the main rotor drive and subsequent 

loss of control of the helicopter. 

DATES: This AD is effective December 

26, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of December 26, 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 

http://www.agustawestland.com/

technical-bullettins. 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 http://

www.regulations.gov or in person at the 

Docket Operations Office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the 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: Rao 

Edupuganti, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

rao.edupuganti@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On July 16, 2014, at 79 FR 41462, 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 

Agusta Model A109E, A109K2, A119, 

and AW119 MKII helicopters with a 

main transmission, part number (P/N) 

109–0400–03–103, 109–0400–05–103, 

and 109–0400–03–109, with a Gleason 

crown, P/N 109–0403–07–103, installed. 

The NPRM proposed to require, for 

main transmissions with 2,400 or more 

hours time-in-service (TIS), performing 

repetitive magnetic particle inspections 

of the Gleason crown for a crack. If there 

is a crack, the NPRM proposed replacing 

the Gleason crown assembly before 

further flight. The NPRM also proposed 

to prohibit installing a Gleason crown, 

P/N 109–0403–07–103, or a Gleason 

crown assembly, P/N 109–0401–27–101 

or P/N 109–0401–27–109, on any 

helicopter. The proposed requirements 

were intended to detect a crack, which 

could cause damage to or loss of the 

main rotor drive and subsequent loss of 

control of the helicopter. 

The NPRM was prompted by AD No. 

2013–0118, dated June 3, 2013, issued 

by EASA, which is the Technical Agent 


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69040 Federal Register / Vol. 79, No. 224 / Thursday, November 20, 2014 / Rules and Regulations 

for the Member States of the European 

Union, to correct an unsafe condition 

for Agusta Model A109K2, A109E, 

A119, and AW119MKII helicopters. 

EASA advises that during an overhaul 

of an A119 main transmission, P/N 109– 

0400–05–103, a crack on the Gleason 

crown, P/N 109–0403–07–103, was 

found. EASA further states that the 

crack originated from the bottom of one 

of the 40 threaded holes in the Gleason 

crown, and that this part-numbered 

Gleason crown is also installed on 

Model A109 helicopters. EASA states 

that this condition, if not corrected, 

could cause damage to or loss of the 

main rotor drive and loss of control of 

the helicopter. To correct this unsafe 

condition, EASA AD No. 2013–0118 

requires repetitive magnetic particle 

inspections of the Gleason crown and, if 

there is a crack, replacing the Gleason 

crown with a different part-numbered 

Gleason crown. EASA AD No. 2013– 

0118 also prohibits installing a Gleason 

crown, P/N 109–0403–07–103, or a 

Gleason crown assembly, P/N 109– 

0401–27–101 or P/N 109–0401–27–109, 

on any helicopter, as Gleason crown, P/ 

N 109–0403–07–103, is a component of 

these assemblies. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (79 FR 41462, July 16, 2014). 

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, except for minor editorial 

changes. These changes are consistent 

with the intent of the proposals in the 

NPRM (79 FR 41462, July 16, 2014) and 

will not increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Differences Between This AD and the 

EASA AD 

This AD requires compliance within 

200 hours TIS for main transmissions 

with 2,400 or more hours. The EASA 

AD requires different compliance times, 

depending on the number of flight hours 

the transmission has accumulated. 

Related Service Information 

We reviewed Agusta Bollettino 

Tecnico (BT) No. 109EP–128 for Model 

A109E helicopters, Agusta BT No. 

109K–57 for Model A109K2 helicopters, 

and Agusta BT No. 119–058 for Model 

A119 and AW119MKII helicopters, each 

Revision A and dated May 28, 2013. 

Each BT describes procedures for 

performing a magnetic particle 

inspection on the Gleason crown, P/N 

109–0403–07–103, for a crack. If there is 

a crack, each BT specifies replacing the 

Gleason crown assembly with a Gleason 

crown assembly, P/N 109–0401–27–107. 

We also reviewed Agusta BT No. 

109EP–126 for Model A109E 

helicopters, Agusta BT No. 109K–56 for 

Model A109K2 helicopters, and Agusta 

BT No. 119–053 for Model A119 and 

AW119MKII helicopters, each dated 

December 20, 2012. These BTs contain 

procedures for upgrading the 

transmission system by replacing the 

Gleason crown assembly with a Gleason 

crown assembly, P/N 109–0401–27–107. 

Costs of Compliance 

We estimate that this AD affects 218 

helicopters of U.S. registry. We estimate 

the following costs to comply with this 

AD. At an average labor rate of $85 per 

hour, magnetic particle inspecting the 

Gleason crown requires about 24 workhours, for an estimated cost per 

helicopter of $2,040, and a total cost of 

$444,720 for the U.S. fleet, per 

inspection cycle. 

If required, replacing the Gleason 

crown assembly requires about 24 workhours, and required parts will cost 

$29,000, for a cost per helicopter of 

$31,040. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, 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 

■ 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): 

2014–23–02 Agusta S.p.A. Helicopters 

(Type Certificate Currently Held By 

AgustaWestland S.p.A.) (Agusta): 

Amendment 39–18018; Docket No. 

FAA–2014–0472; Directorate Identifier 

2013–SW–040–AD. 


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Federal Register / Vol. 79, No. 224 / Thursday, November 20, 2014 / Rules and Regulations 69041 

(a) Applicability 

This AD applies to Agusta Model A109E, 

A109K2, A119, and AW119 MKII helicopters 

with a main transmission, part number (P/N) 

109–0400–03–103, 109–0400–05–103, or 

109–0400–03–109, with a Gleason crown, P/ 

N 109–0403–07–103, installed, certificated in 

any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in a Gleason crown. This condition 

could cause damage to or loss of the main 

rotor drive and subsequent loss of control of 

the helicopter. 

(c) Effective Date 

This AD becomes effective December 26, 

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) For main transmissions with 2,400 or 

more hours time-in-service (TIS), within 200 

hours TIS and thereafter at intervals not 

exceeding 1,600 hours TIS, magnetic particle 

inspect the Gleason crown, P/N 109–0403– 

07–103, for a crack by following the 

procedures in: 

(i) Annex 1 of Agusta Bollettino Tecnico 

(BT) No. 109EP–128, Revision A, dated May 

28, 2013, for Model A109E helicopters; 

(ii) Annex 1 of Agusta BT No. 109K–57, 

Revision A, dated May 28, 2013, for Model 

A109K2 helicopters; or 

(iii) Annex 1 of Agusta BT No. 119–058, 

Revision A, dated May 28, 2013, for Model 

A119 and AW119MKII helicopters. 

(2) If there is a crack, before further flight, 

replace the Gleason crown assembly with a 

Gleason Crown assembly, P/N 109–0401–27– 

107. Replacing the Gleason crown assembly 

with P/N 109–0401–27–107 is terminating 

action for the inspection requirements of this 

AD. 

(3) After the effective date of this AD, do 

not install a Gleason crown, P/N 109–0403– 

07–103, or a Gleason crown assembly, P/N 

109–0401–27–101 or P/N 109–0401–27–109, 

on any helicopter. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Rao Edupuganti, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

rao.edupuganti@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. 2013–0118, dated June 3, 2013. You may 

view the EASA AD on the Internet at 

http://www.regulations.gov in Docket No. 

FAA–2014–0472. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6320: Main Rotor Gearbox. 

(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. 

109EP–128, Revision A, dated May 28, 2013. 

(ii) AgustaWestland Bollettino Tecnico No. 

109K–57, Revision A, dated May 28, 2013. 

(iii) AgustaWestland Bollettino Tecnico 

No. 119–058, Revision A, dated May 28, 

2013. 

(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 http://

www.agustawestland.com/technicalbullettins. 

(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: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Fort Worth, Texas, on October 30, 

2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–26825 Filed 11–19–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

Bureau of Economic Analysis 

15 CFR Part 801 

[Docket No. 1206013202–4700–01] 

RIN 0691–AA83 

Direct Investment Surveys: BE–10, 

Benchmark Survey of U.S. Direct 

Investment Abroad 

AGENCY: Bureau of Economic Analysis, 

Commerce. 

ACTION: Final rule. 

SUMMARY: This final rule amends 

regulations of the Department of 

Commerce’s Bureau of Economic 

Analysis (BEA) to reinstate reporting 

requirements for the 2014 BE–10, 

Benchmark Survey of U.S. Direct 

Investment Abroad. Benchmark surveys 

are conducted every five years; the prior 

survey covered 2009. The benchmark 

survey covers the universe of U.S. direct 

investment abroad, and is BEA’s most 

comprehensive survey of such 

investment in terms of subject matter. 

For the 2014 benchmark survey, BEA 

will make changes in the data items 

collected. No changes will be made to 

the reporting requirements for the 

survey. This mandatory survey will be 

conducted under the authority of the 

International Investment and Trade in 

Services Survey Act (the Act). Unlike 

many other BEA surveys conducted 

pursuant to the Act, a response will be 

required from persons subject to the 

reporting requirements of the BE–10, 

Benchmark Survey of U.S. Direct 

Investment Abroad, whether or not they 

are contacted by BEA, in order to ensure 

that respondents subject to the 

requirements for U.S. direct investment 

abroad are identified. 

DATES: This final rule is effective 

December 22, 2014. 

FOR FURTHER INFORMATION CONTACT: 

Patricia Abaroa, Chief, Direct 

Investment Division (BE–50), Bureau of 

Economic Analysis, U.S. Department of 

Commerce, Washington, DC 20230; 

phone (202) 606–9591. 

SUPPLEMENTARY INFORMATION: On August 

14, 2014, BEA published a notice of 

proposed rulemaking that set forth 

revised reporting criteria for the BE–10, 

Benchmark Survey of U.S. Direct 

Investment Abroad (79 FR 47599– 

47603). On September 9, 2014, BEA 

published a correction to the notice of 

proposed rulemaking to correct the 

Regulation Identifier Number (RIN) that 

was listed in the first notice (79 FR 

53355). BEA received two comments on 

the proposed rule. 


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