Federal Register / Vol. 79, No. 41 / Monday, March 3, 2014 / Rules and Regulations 11699 

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. 

(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. 

(f) 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, 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. 

(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 

http://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 

http://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: http://

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 

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 

http://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 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 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 

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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. 

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 

■ 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 

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Federal Register / Vol. 79, No. 41 / Monday, March 3, 2014 / Rules and Regulations 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 http://

www.agustawestland.com/technicalbulletins. 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 

http://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 

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) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

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. 

ADDRESSES: 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 http://

www.airbushelicopters.com/techpub. 

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, 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 

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