Federal Register / Vol. 79, No. 106 / Tuesday, June 3, 2014 / Rules and Regulations 31855 

(iv) Boeing Service Bulletin 777–24–0075, 

Revision 4, dated January 8, 2014. 

(v) Boeing Service Bulletin 777–24–0087, 

Revision 2, dated August 16, 2007. 

(vi) Boeing Service Bulletin 777–28A0039, 

Revision 2, dated September 20, 2010. 

(3) For 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 referenced 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: http://

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

Issued in Renton, Washington, on May 15, 

2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–12650 Filed 6–2–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0984; Directorate 

Identifier 2013–SW–022–AD; Amendment 

39–17859; AD 2014–11–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Previously Eurocopter 

France) (Airbus Helicopters) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters Model EC225LP helicopters 

to require measuring the operating load 

of the cockpit fuel shut-off controls and 

replacing the tangential gearbox if the 

operating load threshold is exceeded. 

This AD was prompted by the jamming 

of the left-hand (LH) side of the fuel 

shut-off and general cut-off controls 

(controls). The actions of this AD are 

intended to prevent the jamming of the 

controls so that a pilot can shut down 

an engine during an engine fire or 

during an emergency landing. 

DATES: This AD is effective July 8, 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: 

James Blyn, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

james.blyn@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On November 25, 2013, at 78 FR 

70242, 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 with a tangential gearbox, 

part number 200181 or 704A34112012. 

The NPRM proposed to require 

measuring the operating load of the 

cockpit fuel shut-off controls and 

replacing the tangential gearbox if the 

operating load threshold is exceeded. 

The proposed requirements were 

intended to prevent the jamming of the 

controls so that a pilot can shut down 

an engine during an engine fire or 

during an emergency landing. 

The NPRM was prompted by AD No. 

2013–0098–E, dated April 24, 2013, 

issued by EASA, which is the Technical 

Agent for the Member States of the 

European Union, to correct an unsafe 

condition for Eurocopter France (now 

Airbus Helicopters) Model EC 225 LP 

helicopters. EASA advises that during 

maintenance on a helicopter, the LH 

side of the cockpit’s emergency 

shutdown controls were reported 

jammed, making it impossible to operate 

the LH fuel shut-off and the general cutout handles. EASA states that this 

condition could lead to failure to 

manually operate the emergency 

shutdown controls during an emergency 

landing or fire. To address this unsafe 

condition, EASA AD No. 2013–0098–E 

requires an operating load check of the 

two cockpit fuel shut-off handles and, 

depending on findings, lubrication and/ 

or replacement of the two tangential 

gearboxes. 

Since we issued the NPRM, 

Eurocopter France changed its name to 

Airbus Helicopters, Inc. This AD reflects 

that change and updates the contact 

information to obtain service 

documentation. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we received no comments on the NPRM 

(78 FR 70242, November 25, 2013). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of France and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, 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 the minor changes 

previously described. These changes are 

consistent with the intent of the 

proposals in the NPRM (78 FR 70242, 

November 25, 2013) and will not 

increase the economic burden on any 

operator nor increase the scope of this 

AD. 

Differences Between This AD and the 

EASA AD 

The EASA AD requires differing 

compliance times based on when the 

helicopter’s original Certificate of 

Airworthiness or Export Certificate of 

Airworthiness was issued. This AD 

makes no distinction regarding 

compliance times because there are only 

4 affected aircraft on the U.S. registry. 

Related Service Information 

Eurocopter issued Emergency Alert 

Service Bulletin No. 76A001, Revision 

0, dated April 22, 2013, for the Model 


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31856 Federal Register / Vol. 79, No. 106 / Tuesday, June 3, 2014 / Rules and Regulations 

EC225LP civil helicopter and the Model 

EC725AP military helicopter to notify 

its operators that during a scheduled 

inspection of the fuel shut-off controls, 

a mechanic noticed that one of the shutoff controls jammed. This jamming 

made maneuvering the fuel shut-off and 

the general cut-out controls impossible. 

After an investigation, Eurocopter 

determined that the jamming originated 

in the tangential gearbox installed on 

this control. Traces of corrosion were 

observed on the internal bearings of the 

LH tangential gearbox, Eurocopter 

reported. The jamming of the fuel cutoff control prevents the engine input 

fuel valve and the engine compartment 

ventilation flap from closing and 

prevents the activation of the general 

cut-out control. 

Eurocopter consequently called for a 

mandatory ‘‘check’’ of the fuel shut-off 

valve maneuvering loads, lubricating 

the tangential gearbox bearings, and 

depending on the load measurement, 

replacing the tangential gearbox. 

Costs of Compliance 

We estimate that this AD affects 4 

helicopters of U.S. Registry and that 

labor costs average $85 a work-hour. 

Based on these estimates, we expect the 

following costs: 

• Measuring the operating load of the 

two cockpit fuel shut-off controls 

require .25 work-hours for a labor cost 

of about $21, or $84 for the U.S. fleet. 

No parts are needed. 

• Lubricating the tangential gearbox 

requires 4 work-hours. The cost of 

consumable materials is minimal for a 

total cost of $340 per helicopter. 

• Replacing the tangential gearbox 

requires 4 work-hours for a labor cost of 

$340. Parts cost $4,943 for a total cost 

of $5,283 per helicopter. 

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): 

2014–11–08 Airbus Helicopters 

(Previously Eurocopter France): 

Amendment 39–17859; Docket No. 

FAA–2013–0984; Directorate Identifier 

2013–SW–012–AD. 

(a) Applicability 

This AD applies to Model EC225LP 

helicopters with a tangential gearbox, part 

number (P/N) 200181 or 704A34112012, 

installed, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

the jamming of the fuel shut-off and the 

general cut-off controls. This condition could 

prevent a pilot from shutting down an engine 

during an engine fire or emergency landing. 

(c) Effective Date 

This AD becomes effective July 8, 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 15 hours time-in-service or 7 

days, whichever occurs first, measure the 

operating load of each cockpit fuel shut-off 

control. 

(i) If the operating load is more than 3 daN 

(6.74 ft-lb), before further flight, lubricate 

each tangential gearbox and measure the 

operating load of each cockpit fuel shut-off 

control. 

(ii) If the operating load is less than or 

equal to 3 daN (6.74 ft-lb), within 6 months, 

lubricate each tangential gearbox and 

measure the operating load of each cockpit 

fuel shut-off control. 

(iii) If the operating load is more than 3 

daN (6.74 ft-lb) after lubricating the 

tangential gearbox, replace the affected 

tangential gearbox before the next flight. 

(2) Before installing a tangential gearbox, 

P/N 200181 or 704A34112012, lubricate the 

upper and lower bearings. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: James Blyn, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

james.blyn@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) Eurocopter Emergency Alert Service 

Bulletin No. 76A001, Revision 0, dated April 

22, 2013, which is not incorporated by 

reference, contains additional information 

about the subject of this AD. For service 

information, 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. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2013–0098–E, dated April 24, 2013. You 

may view the EASA AD on the Internet at 

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

FAA–2013–0984. 


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Federal Register / Vol. 79, No. 106 / Tuesday, June 3, 2014 / Rules and Regulations 31857 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: Engine Controls, 7600. 

Issued in Fort Worth, Texas, on May 21, 

2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–12717 Filed 6–2–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0336; Directorate 

Identifier 2013–SW–063–AD; Amendment 

39–17857; AD 2014–11–07] 

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), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Agusta 

Model A109A, A109A II, A109C, 

A109E, A109K2, A109S, AW109SP, 

A119, and AW119 MKII helicopters. 

This AD requires inspecting and 

replacing certain part-numbered main 

rotor swashplate support nuts. This AD 

is prompted by a report of two cracked 

nuts found on an A109S helicopter. 

These actions are intended to detect a 

cracked nut and prevent failure of the 

main rotor system, and subsequent loss 

of control of the helicopter. 

DATES: This AD becomes effective June 

18, 2014. 

We must receive comments on this 

AD by August 4, 2014. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at 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 (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

For service information identified in 

this 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. 

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: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 

However, we invite you to participate in 

this rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit them only one time. We will file 

in the docket all comments that we 

receive, as well as a report summarizing 

each substantive public contact with 

FAA personnel concerning this 

rulemaking during the comment period. 

We will consider all the comments we 

receive and may conduct additional 

rulemaking based on those comments. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Emergency AD 

No. 2013–0265–E, dated October 30, 

2013, to correct an unsafe condition for 

Agusta Model A109A, A109A II, A109C, 

A109E, A109K2, A109LUH, A109S, 

AW109SP, A119, and AW119 MKII 

helicopters. EASA advises that during a 

scheduled inspection of the rotating 

control installation, two nuts, part 

number (P/N) MS21042–4, which 

connect the swashplate support to the 

upper case of the main transmission 

were found cracked. EASA states a 

subsequent investigation determined 

that the cracks in the nuts resulted from 

a production deficiency, which caused 

hydrogen embrittlement, at the nut 

manufacturer. EASA also states that this 

condition, if not detected and corrected, 

could lead to failure of the main rotor 

function and subsequent loss of control 

of the helicopter. The EASA Emergency 

AD requires repetitive inspections of 

each nut, P/N MS21042–4, for a crack, 

replacing any nut that has a crack with 

a different part-numbered nut, and, 

within 3 months, replacing each nut 

that does not have a crack with a 

different part-numbered nut. EASA 

Emergency AD 2013–0265–E also 

prohibits installing a nut, P/N 

MS21042–4, to connect the swashplate 

support to the upper case on any 

helicopter. 

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. 

Related Service Information 

Agusta has issued Bollettino Tecnico 

(BT) No. 109–137 for Model A109A, 

A109A II and A109C helicopters; BT 

No. 109EP–131 for Model A109E 

helicopters; BT No. 109K–59 for Model 

A109K2 helicopters; BT No. 109S–056 

for Model A109S helicopters; BT No. 

109SP–070 for Model AW109SP 

helicopters; and BT No. 119–062 for 

Model A119 and AW119 MKII 

helicopters. All of the BTs are Revision 

0 and are dated October 29, 2013. Each 

BT describes procedures for inspecting 


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