48028 Federal Register / Vol. 79, No. 158 / Friday, August 15, 2014 / Rules and Regulations 

0064, Revision 2, dated June 14, 2012: At the 

applicable times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Special Attention 

Service Bulletin 777–78–0064, Revision 2, 

dated June 14, 2012, except as provided by 

paragraph (k) of this AD, do a detailed 

inspection for cracking of the outer V-blade 

fittings at the latch beam end and hinge beam 

end of each thrust reverser half, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 777–78–0064, Revision 2, 

dated June 14, 2012. 

(1) If no cracking is found, repeat the 

inspections thereafter at the times specified 

in paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Special Attention Service Bulletin 777–78– 

0064, Revision 2, dated June 14, 2012. 

(2) If any cracking is found, before further 

flight, replace the affected thrust reverser half 

with a serviceable thrust reverser half, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 777–78–0064, Revision 2, 

dated June 14, 2012. Repeat the inspections 

thereafter at the times specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Special 

Attention Service Bulletin 777–78–0064, 

Revision 2, dated June 14, 2012. 

(k) Service Information Exception 

Where Boeing Special Attention Service 

Bulletin 777–78–0064, Revision 2, dated June 

14, 2012, specifies an initial compliance time 

‘‘after the date on Revision 2 of this service 

bulletin,’’ this AD requires compliance 

within the specified time after the effective 

date of this AD. 

(l) Reporting Not Required 

Although Boeing Special Attention Service 

Bulletin 777–78–0064, Revision 2, dated June 

14, 2012, specifies to submit certain 

information to the manufacturer, this AD 

does not include that requirement. 

(m) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane and the 

approval must specifically refer to this AD. 

(4) AMOCs approved previously in 

accordance with AD 2006–26–06, 

Amendment 39–14864 (71 FR 77586, 

December 27, 2006), are not approved as 

AMOCs for this AD. 

(n) Related Information 

(1) For more information about this AD, 

contact Narinder Luthra, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6513; fax: 425–917–6590; 

email: narinder.luthra@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be obtained at the addresses specified in 

paragraphs (o)(5) and (o)(6) of this AD. 

(o) 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. 

(3) The following service information was 

approved for IBR on September 19, 2014. 

(i) Boeing Special Attention Service 

Bulletin 777–78–0061, Revision 1, dated 

August 28, 2007. 

(ii) Boeing Special Attention Service 

Bulletin 777–78–0064, Revision 2, dated June 

14, 2012. 

(4) The following service information was 

approved for IBR on January 11, 2007 (71 FR 

77586, December 27, 2006). 

(i) Boeing Special Attention Service 

Bulletin 777–78–0061, dated July 6, 2006. 

(ii) Reserved. 

(5) 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. 

(6) You may view this 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. 

(7) 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 July 23, 

2014. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–18313 Filed 8–14–14; 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; Amendment 39– 

17939; AD 2014–16–15] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Turbomeca S.A. Makila 2A and Makila 

2A1 turboshaft engines. This AD 

requires initial and repetitive visual 

inspections, and replacement of the 

splines of the high-pressure (HP) fuel 

pump/metering valve and the module 

M01 drive gear, if necessary. This AD 

was prompted by the failure of two HP 

fuel pumps that resulted in engine inflight shutdowns. We are issuing 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: This AD becomes effective 

September 19, 2014. 

ADDRESSES: 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. 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 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this 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 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 


emcdonald on DSK67QTVN1PROD with RULES
Federal Register / Vol. 79, No. 158 / Friday, August 15, 2014 / Rules and Regulations 48029 

FOR FURTHER INFORMATION CONTACT: 

Katheryn Malatek, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7747; fax: 781–238– 

7199; email: Katheryn.malatek@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on May 12, 2014 (79 FR 26905). 

The NPRM proposed 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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 26905, May 12, 2014). 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 8 

engines installed on helicopters of U.S. 

registry. We also estimate that it will 

take about 2 hours per engine to comply 

with this 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 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 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 this AD: 

(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. 

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): 

2014–16–15 Turbomeca S.A.: Amendment 

39–17939; Docket No. FAA–2014–0219; 

Directorate Identifier 2014–NE–04–AD. 

(a) Effective Date 

This AD becomes effective September 19, 

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 the failure of 

two HP fuel pumps that resulted in engine 

in-flight shutdowns. We are issuing 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 (FHs) 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 FHs 

since-last-inspection. 

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

the module M01 drive gear fails 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 M01 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 Katheryn Malatek, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7747; fax: 781–238– 

7199; email: Katheryn.malatek@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency (EASA) AD 2014–0059, dated 

March 10, 2014, and EASA AD 2014–0059R1, 

dated April 15, 2014, for more information. 

You may examine the MCAIs in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0219-0003. 

(3) Turbomeca S.A. Mandatory Service 

Bulletin No. 298 73 2818, Version F, dated 

March 5, 2014, which is not incorporated by 

reference in this AD, 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. 


emcdonald on DSK67QTVN1PROD with RULES
48030 Federal Register / Vol. 79, No. 158 / Friday, August 15, 2014 / Rules and Regulations 

(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. 

(h) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

August 6, 2014. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–19228 Filed 8–14–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1068; Directorate 

Identifier 2013–NM–196–AD; Amendment 

39–17923; AD 2014–15–20] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model DHC–8–400 

series airplanes. This AD was prompted 

by reports of failure of the high pressure 

shutoff valves (HPSOVs) causing the 

timer and monitor unit (TMU) to 

become inoperative since the HPSOV 

and the TMU are on the same circuit 

breaker. This AD requires a wiring 

modification to segregate the HPSOV 

power supply from the TMU. We are 

issuing this AD to prevent an 

inoperative TMU, which could result in 

the loss of the automatic de-icing mode, 

and lead to an increased workload for 

the flight crew and loss of control of the 

airplane. 

DATES: This AD becomes effective 

September 19, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 19, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-1068; or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For service information identified in 

this AD, contact Bombardier, Inc., QSeries Technical Help Desk, 123 Garratt 

Boulevard, Toronto, Ontario M3K 1Y5, 

Canada; telephone 416–375–4000; fax 

416–375–4539; email thd.qseries@

aero.bombardier.com; Internet http://

www.bombardier.com. You may view 

this referenced 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. 

FOR FURTHER INFORMATION CONTACT: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7318; fax 

516–794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Bombardier, Inc. Model 

DHC–8–400 series airplanes. The NPRM 

published in the Federal Register on 

January 2, 2014 (79 FR 76). Transport 

Canada Civil Aviation (TCCA), which is 

the aviation authority for Canada, has 

issued Canadian Airworthiness 

Directive CF–2013–27, dated September 

25, 2013 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for the specified 

products. The MCAI states: 

There have been several in-service reports 

of the failure of high pressure shutoff valves 

(HPSOV) causing the Timer and Monitor 

Unit (TMU) to become inoperative since the 

HPSOV and TMU are on the same circuit 

breaker. 

An inoperative TMU would result in the 

loss of the automatic de-icing mode and 

would lead to an increased workload for the 

flightcrew. In the case where additional 

failures occur during a critical flight phase, 

the significantly increased workload could 

lead to loss of control of the aeroplane. 

This [Canadian] AD mandates a wiring 

modification to segregate the HPSOV power 

supply from the TMU. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-1068- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM (79 FR 76, 

January 2, 2014) and the FAA’s response 

to the comment. 

Request To Use the Latest Service 

Information 

Horizon Air requested that we revise 

the proposed AD (79 FR 76, January 2, 

2014) to allow compliance for 

Bombardier Service Bulletin 84–36–04, 

Revision B, dated January 2, 2014, or 

Bombardier Service Bulletin 84–36–04, 

Revision A, dated April 17, 2013. 

We agree with the commenter’s 

request to reference the latest service 

information. We have revised this AD 

by referencing Bombardier Service 

Bulletin 84–36–04, Revision B, dated 

January 2, 2014, throughout this AD. We 

have also revised paragraph (h) of this 

AD to give credit for actions done before 

the effective date of this AD in 

accordance with Bombardier Service 

Bulletin 84–36–04, Revision A, dated 

April 17, 2013, as well as Bombardier 

Service Bulletin 84–36–04, dated March 

13, 2013. 

‘‘Contacting the Manufacturer’’ 

Paragraph in This AD 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all MCAI ADs in which the 

FAA develops an AD based on a foreign 

authority’s AD. 

The MCAI or referenced service 

information in an FAA AD often directs 

the owner/operator to contact the 

manufacturer for corrective actions, 

such as a repair. Briefly, the Airworthy 

Product paragraph allowed owners/ 

operators to use corrective actions 

provided by the manufacturer if those 

actions were FAA-approved. In 

addition, the paragraph stated that any 

actions approved by the State of Design 

Authority (or its delegated agent) are 

considered to be FAA-approved. 

In the NPRM (79 FR 76, January 2, 

2014), we proposed to prevent the use 

of repairs that were not specifically 

developed to correct the unsafe 

condition, by requiring that the repair 

approval provided by the State of 

Design Authority or its delegated agent 

specifically refer to this FAA AD. This 

change was intended to clarify the 

method of compliance and to provide 

operators with better visibility of repairs 

that are specifically developed and 

approved to correct the unsafe 

condition. In addition, we proposed to 

change the phrase ‘‘its delegated agent’’ 

to include a design approval holder 

(DAH) with State of Design Authority 

design organization approval (DOA), as 

applicable, to refer to a DAH authorized 

to approve required repairs for the 

proposed AD. 


emcdonald on DSK67QTVN1PROD with RULES