58342 Federal Register / Vol. 80, No. 188 / Tuesday, September 29, 2015 / Rules and Regulations 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, New York Aircraft 

Certification Office, FAA, may approve 

AMOCs to this AD. Use the procedures found 

in 14 CFR 39.19 to make your request. 

AMOCs previously approved for AD 2008– 

14–07, Amendment 39–15602 (73 FR 39574, 

July 10, 2008) (‘‘AD 2008–14–07’’) and AD 

2011–26–04, Amendment 39–16894 (76 FR 

79051, December 21, 2011) (‘‘AD 2011–26– 

04’’) are approved as AMOCs to the 

corresponding requirements in paragraph (e) 

of this AD. 

(h) Related Information 

(1) For more information about this AD, 

contact Norm Perenson, Aerospace Engineer, 

New York Aircraft Certification Office, FAA, 

Engine & Propeller Directorate, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

phone: 516–228–7337; fax: 516–794–5531; 

email: norman.perenson@faa.gov. 

(2) FAA Special Airworthiness Information 

Bulletin NE–07–49R1 contains additional 

information on this subject. 

(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) Lycoming Engines Mandatory Service 

Bulletin (MSB) No. 342G, dated July 16, 

2013. 

(ii) Lycoming Engines MSB No. 342G, 

Supplement No. 1, dated August 29, 2013. 

(iii) Lycoming Engines MSB No. 342G, 

Supplement No. 2, dated January 23, 2014. 

(3) For Lycoming Engines service 

information identified in this AD, contact 

Lycoming Engines, 652 Oliver Street, 

Williamsport, PA 17701; phone: 800–258– 

3279; fax: 570–327–7101; Internet: http://

www.lycoming.com/Lycoming/SUPPORT/

TechnicalPublications/ServiceBulletins.aspx. 

(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. 

(5) You may view this service information 

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 Burlington, Massachusetts, on 

September 11, 2015. 

Thomas A. Boudreau, 

Acting Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2015–23617 Filed 9–28–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2775; Directorate 

Identifier 2015–CE–021–AD; Amendment 

39–18277; AD 2015–19–15] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft Ltd. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

PILATUS AIRCRAFT LTD. Models PC– 

12, PC–12/45, and PC–12/47E airplanes. 

This AD results from mandatory 

continuing airworthiness information 

(MCAI) issued by an aviation authority 

of another country to identify and 

correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as a malfunction of 

the universal joint. We are issuing this 

AD to require actions to address the 

unsafe condition on these products. 

DATES: This AD is effective November 3, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 3, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

2775; or in person at 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. 

For service information identified in 

this AD, contact PILATUS AIRCRAFT 

LTD, Customer Support Manager, CH– 

6371 STANS, Switzerland; phone: +41 

(0)41 619 33 33; fax: +41 (0)41 619 73 

11; email: SupportPC12@pilatusaircraft.com; Internet: http:// 

www.pilatus-aircraft.com. You may 

view this referenced service information 

at the FAA, Small Airplane Directorate, 

901 Locust, Kansas City, Missouri 

64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. It is also available 

on the Internet at http:// 

www.regulations.gov by searching for 

Docket No. FAA–2015–2775. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4059; fax: (816) 329–4090; email: 

doug.rudolph@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to adding an AD that would 

apply to PILATUS AIRCRAFT LTD. 

Model PC–12, PC–12/45, and PC–12/ 

47E airplanes. The NPRM was 

published in the Federal Register on 

July 14, 2015 (80 FR 40949). The NPRM 

proposed to correct an unsafe condition 

for the specified products and was 

based on mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country. The MCAI states: 

A case of malfunctioning was reported of 

a universal joint installed between the 

control tube assembly and the control 

column on a PC–12/47E aeroplane. 

Investigation determined that the 

malfunction was caused by an incorrectly 

manufactured universal joint. Universal 

joints from the same manufacturing batch 

were provided to operators between 01 

March 2014 and 28 February 2015, and are 

thus potentially affected. 

This condition, if not corrected, could lead 

to other cases of malfunctioning of a 

universal joint, possibly resulting in reduced 

control of the aeroplane. 

To address this potential unsafe condition, 

Pilatus Aircraft Ltd. issued Service Bulletin 

(SB) No. 27–022 to provide instructions for 

replacement of the universal joints in the 

flight controls. 

For the reason described above, this 

AD requires removal from service of the 

potentially incorrectly manufactured 

universal joints. The MCAI can be found 

in the AD docket on the Internet at: 

http://www.regulations.gov/ 

#!documentDetail;D=FAA-2015-2775- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 40949, July 14, 2015) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (80 FR 

40949, July 14, 2015) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 


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Federal Register / Vol. 80, No. 188 / Tuesday, September 29, 2015 / Rules and Regulations 58343 

proposed in the NPRM (80 FR 40949, 

July 14, 2015). 

Related Service Information Under 1 

CFR Part 51 

We reviewed PILATUS AIRCRAFT 

LTD. PILATUS PC–12 Service Bulletin 

No: 27–022, dated March 17, 2015. The 

service information describes 

procedures for replacement of the 

universal joint on the aileron control 

system. This service information is 

reasonably available because the 

interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section of the AD. 

Costs of Compliance 

We estimate that this AD will affect 

55 products of U.S. registry. We also 

estimate that it would take about 3 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts would cost about $1,000 

per product. 

Based on these figures, we estimate 

the cost of the AD on U.S. operators to 

be $69,025 or $1,255 per product. 

According to the manufacturer, all 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 

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, 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. 

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–2015– 

2775; 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 the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (telephone (800) 647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

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 AD: 

2015–19–15 Pilatus Aircraft Ltd.: 

Amendment 39–18277; Docket No. 

FAA–2015–2775; Directorate Identifier 

2015–CE–021–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective November 3, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to PILATUS AIRCRAFT 

LTD. Models PC–12, PC–12/45, and PC–12/ 

47E airplanes, manufacturer serial numbers 

244, 307, 409, 646, 1447 through 1450, 1461, 

1462, 1466 through 1514, 1516 through 1520, 

and 1523, certificated in any category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 27: Flight Controls. 

(e) Reason 

This AD results from mandatory 

continuing airworthiness information (MCAI) 

originated by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as a 

malfunction of the universal joint. We are 

issuing this AD to replace defective aileron 

control system universal joints. 

(f) Actions and Compliance 

Unless already done, do the following 

actions in paragraphs (f)(1) and (f)(2) of this 

AD, to include all subparagraphs. 

(1) For airplanes equipped with aileron 

control system universal joints part number 

(P/N) 944.61.73.012 or P/N 527.10.12.195, 

purchased between March 1, 2014, and 

February 28, 2015; or universal joints 

installed in service through an aileron 

control system inspection kit P/N 

500.50.12.314, purchased between March 1, 

2014, and February 28, 2015, do one of the 

following actions as applicable: 

(i) For airplanes with less than 200 flight 

cycles since first flight of the airplane or less 

than 200 flight cycles since installation of an 

affected universal joint or inspection kit, 

whichever applies: Within 10 flight cycles 

after November 3, 2015 (the effective date of 

this AD) or 3 months after November 3, 2015 

(the effective date of this AD), whichever 

occurs first, replace with a new universal 

joint P/N 527.10.12.195 purchased after 

March 1, 2015, and marked with a placard 

‘‘RT iO’’ following the Accomplishment 

Instructions in PILATUS PC–12 Service 

Bulletin No: 27–022, dated March 17, 2015. 

(ii) For airplanes with 200 flight cycles or 

more since first flight of the airplane or 200 

flight cycles or more since installation of an 

affected universal joint or inspection kit, 

whichever applies: Within 12 months after 

November 3, 2015 (the effective date of this 

AD), replace with a new universal joint P/N 

527.10.12.195 purchased after March 1, 2015, 

and marked with a placard ‘‘RT iO’’ 

following the Accomplishment Instructions 

in PILATUS PC–12 Service Bulletin No: 27– 

022, dated March 17, 2015. 

(iii) For all airplanes where total flight 

cycles are not tracked: The conversion 

formula is one flight cycle equals one flight 

hour. 

(2) For all airplanes: After November 3, 

2015 (the effective date of this AD), do not 

install the following parts on any airplane 

after the modification of the airplane as 

required in paragraphs (f)(1)(i) and (f)(1)(ii) of 

this AD or any airplane that does not have 

an affected part installed: 

(i) A universal joint P/N 944.61.73.012 or 

P/N 527.10.12.195 (except for a P/N 


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58344 Federal Register / Vol. 80, No. 188 / Tuesday, September 29, 2015 / Rules and Regulations 

527.10.12.195 marked with a placard ‘‘RT 

iO’’). 

(ii) Inspection kit P/N 500.50.12.314 

purchased between March 1, 2014, and 

February 28, 2015. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4059; fax: (816) 329– 

4090; email: doug.rudolph@faa.gov. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, a federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(h) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) AD No.: 2015–0111, dated 

June 16, 2015, for related information. The 

MCAI can be found in the AD docket on the 

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

#!documentDetail;D=FAA-2015-2775-0002. 

(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) PILATUS PC–12 Service Bulletin No: 

27–022, dated March 17, 2015. 

(ii) Reserved. 

(3) For PILATUS AIRCRAFT LTD. service 

information identified in this AD, contact: 

PILATUS AIRCRAFT LTD, Customer 

Support Manager, CH–6371 STANS, 

Switzerland; phone: +41 (0)41 619 33 33; fax: 

+41 (0)41 619 73 11; email: 

SupportPC12@pilatus-aircraft.com; Internet: 

http://www.pilatus-aircraft. 

(4) You may view this service information 

at the FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. In 

addition, you can access this service 

information on the Internet at http:// 

www.regulations.gov by searching for and 

locating Docket No. FAA–2015–2775. 

(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 Kansas City, Missouri, on 

September 18, 2015. 

Melvin Johnson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–24464 Filed 9–28–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0494; Directorate 

Identifier 2014–NM–160–AD; Amendment 

39–18275; AD 2015–19–13] 

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 inadvertent deployment of 

a single outboard spoiler during flight. 

This AD requires replacement of the 

power control units (PCUs) for the 

outboard spoilers with upgraded PCUs. 

We are issuing this AD to prevent 

leakage of the piston head seal and 

piston rod seals of the outboard spoiler 

PCUs, which could result in inadvertent 

spoiler deployment and reduced 

controllability of the airplane. 

DATES: This AD becomes effective 

November 3, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 3, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-0494; 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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0494. 

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 

March 24, 2015 (80 FR 15521). 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2014–22, 

dated July 16, 2014 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Bombardier, Inc. Model 

DHC–8–400 series airplanes. The MCAI 

states: 

Although [Canadian] AD CF–2009–26 

[dated May 21, 2009 (http://

wwwapps3.tc.gc.ca/Saf-Sec-Sur/2/CAWISSWIMN/attachment.asp?aiid=CF-2009- 

26&revid=0&cntr=CF&file=CFCF-2009- 

26.pdf&type=PDE), which corresponds to 

FAA AD 2009–25–05, Amendment 39–16124 


asabaliauskas on DSK5VPTVN1PROD with RULES