Federal Register / Vol. 79, No. 91 / Monday, May 12, 2014 / Proposed Rules 26905 

www.regulations.gov/

#!documentDetail;D=FAA-2013-0766-0002. 

(3) For service information identified in 

this AD, contact Pratt & Whitney Canada 

Corp., 1000 Marie-Victorin, Longueuil, 

Quebec, Canada, J4G 1A1; phone: 800–268– 

8000; fax: 450–647–2888; Internet: 

www.pwc.ca. 

(4) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

Issued in Burlington, Massachusetts, on 

April 18, 2014. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–09929 Filed 5–9–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0219; Directorate 

Identifier 2014–NE–04–AD] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Turbomeca S.A. Makila 2A and Makila 

2A1 turboshaft engines. This proposed 

AD was prompted by failure of two 

high-pressure (HP) fuel pumps that 

resulted in engine in-flight shutdowns. 

This proposed AD would require initial 

and repetitive visual inspections, and 

replacement of the splines of the HP 

fuel pump/metering valve and the 

module M01 drive gear, if necessary. We 

are proposing this AD to prevent failure 

of the HP fuel pump, which could lead 

to an in-flight shutdown, damage to the 

engine, and forced landing or accident. 

DATES: We must receive comments on 

this proposed AD by July 11, 2014. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: 202–493–2251. 

For service information identified in 

this proposed AD, contact Turbomeca, 

S.A., 40220 Tarnos, France; phone: 33 

(0)5 59 74 40 00; telex: 570 042; fax: 33 

(0)5 59 74 45 15. You may view this 

service information at the FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0219; 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 proposed AD, the 

mandatory continuing airworthiness 

information (MCAI), the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

in the ADDRESSES section. Comments 

will be available in the AD docket 

shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

James E. Gray, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: (781) 238–7742; fax: (781) 238– 

7199; email: James.E.Gray@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2014–0219; Directorate Identifier 

2014–NE–04–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2014– 

0059, dated March 10, 2014 (referred to 

hereinafter as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Two uncommanded in-flight shutdowns on 

Makila 2A/2A1 engines have been reported. 

The results of the technical investigations 

concluded that these events were caused by 

deterioration of the splines on the highpressure (HP) fuel pump drive link, which 

eventually interrupted the fuel supply to the 

engine. 

This condition, if not detected and 

corrected, could lead to further cases of 

uncommanded engine in-flight shutdown, 

and may ultimately lead to an emergency 

landing. 

We are proposing this AD to prevent 

failure of the HP fuel pump, which 

could lead to an in-flight shutdown, 

damage to the engine, and forced 

landing or accident. 

You may obtain further information 

by examining the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0219. 

Relevant Service Information 

Turbomeca S.A. has issued 

Mandatory Service Bulletin (MSB) No. 

298 73 2818, Version F, dated March 5, 

2014. The MSB describes procedures for 

cleaning and visually inspecting the 

splines of the HP fuel pump/metering 

valve and the module M01 drive gear for 

wear, corrosion, scaling, pitting, and 

chafing. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of France, and is 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with the European 

Community, EASA has notified us of 

the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing 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 

products of the same type design. This 

proposed AD would require initial and 

repetitive visual inspections, and 

replacement of the splines of the HP 

fuel pump/metering valve and the 

module M01 drive gear, if necessary. 

Costs of Compliance 

We estimate that this proposed AD 

affects 8 engines installed on helicopters 

of U.S. registry. We also estimate that it 

would take about 2 hours per engine to 


tkelley on DSK3SPTVN1PROD with PROPOSALS
26906 Federal Register / Vol. 79, No. 91 / Monday, May 12, 2014 / Proposed Rules 

comply with this proposed AD. The 

average labor rate is $85 per hour. 

Required parts cost about $750 per 

engine. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $1,360. 

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 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

Turbomeca S.A.: Docket No. FAA–2014– 

0219; Directorate Identifier 2014–NE– 

04–AD. 

(a) Comments Due Date 

We must receive comments by July 11, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Turbomeca S.A. Makila 

2A and Makila 2A1 turboshaft engines with 

a high-pressure (HP) fuel pump, part number 

(P/N) 0 298 91 806 0 or P/N 0 298 91 805 

0, installed, that have not incorporated 

Turbomeca modification TU 59. 

(d) Reason 

This AD was prompted by failure of two 

HP fuel pumps that resulted in engine inflight shutdowns. We are proposing this AD 

to prevent failure of the HP fuel pump, which 

could lead to an in-flight shutdown, damage 

to the engine, and forced landing or accident. 

(e) Actions and Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Within 25 flight hours (FH) or 6 months 

after the effective date of this AD, whichever 

occurs earlier, clean and visually inspect the 

splines of the HP fuel pump/metering valve 

and the module M01 drive gear for wear, 

corrosion, scaling, pitting, and chafing. 

(2) Thereafter, reinspect every 100 FH 

since-last-inspection. 

(3) If the HP fuel pump/metering valve or 

the module M01 drive gear fail the inspection 

required by this AD, replace it with a part 

eligible for installation before further flight. 

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

not install any HP fuel pump, HP fuel pump 

drive shaft, module 01 drive gear, or module 

M01 77-tooth gear onto any engine, or install 

any engine onto any helicopter, unless the 

HP fuel pump/metering valve and the 

module M01 drive gear passed the inspection 

required by paragraph (e) of this AD. 

(f) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs to this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. 

(g) Related Information 

(1) For more information about this AD, 

contact James E. Gray, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: (781) 238–7742; fax: (781) 238–7199; 

email: James.E.Gray@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2014–0059, dated March 

10, 2014, for more information. You may 

examine the MCAI in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating it in Docket No. 

FAA–2014–0219. 

(3) Turbomeca S.A. Mandatory Service 

Bulletin No. 298 73 2818, Version F, dated 

March 5, 2014, pertains to the subject of this 

AD and can be obtained from Turbomeca 

S.A., using the contact information in 

paragraph (g)(4) of this AD. 

(4) For service information identified in 

this AD, contact Turbomeca, S.A., 40220 

Tarnos, France; phone: 33 (0)5 59 74 40 00; 

telex: 570 042; fax: 33 (0)5 59 74 45 15. 

(5) You may view this service information 

at the FAA, Engine & Propeller Directorate, 

12 New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

Issued in Burlington, Massachusetts, on 

May 6, 2014. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–10782 Filed 5–9–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0913; Directorate 

Identifier 2012–NE–23–AD] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International Inc. Turboprop Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Honeywell International Inc. TPE331–5, 

–5A, –5AB, –5B, –10, –10R, –10U, 

–10UF, –10UG, –10UGR, and –10UR 

model turboprop engines. This 

proposed AD was prompted by engine 

propeller shaft coupling failures, 

leading to unexpected propeller pitch 

changes resulting in high aerodynamic 

and asymmetric drag on the airplanes 

using these engines. This proposed AD 

would require removing certain part 

number (P/N) propeller shaft couplings 

from service. This proposed AD would 

also require inserting a copy of 

Honeywell International Inc. Operating 


tkelley on DSK3SPTVN1PROD with PROPOSALS