Federal Register / Vol. 80, No. 84 / Friday, May 1, 2015 / Rules and Regulations 24791 

the airplane, in accordance with step 2) in 

‘‘DESIRED ACTION’’ of Boeing Multi 

Operator Message MOM–MOM–15–0248– 

01B, dated April 19, 2015; or Boeing Multi 

Operator Message MOM–MOM–15–0248– 

01B(R1), dated April 20, 2015. The main and 

auxiliary power unit (APU) batteries do not 

need to be disconnected when performing 

the electrical power deactivation. Repeat the 

electrical power deactivation thereafter at 

intervals not to exceed 120 days. 

(1) Within 120 days after the last electrical 

power deactivation in accordance with step 

2) in ‘‘DESIRED ACTION’’ of Boeing Multi 

Operator Message MOM–MOM–15–0248– 

01B, dated April 19, 2015; or Boeing Multi 

Operator Message MOM–MOM–15–0248– 

01B(R1), dated April 20, 2015. 

(2) Within 120 days after the date of 

issuance of the original certificate of 

airworthiness or the date of issuance of the 

original export certificate of airworthiness. 

(3) Within 7 days after the effective date of 

this AD. 

(h) Special Flight Permit 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed. 

(i) 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 

paragraph (j) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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. 

(j) Related Information 

For more information about this AD, 

contact Kelly McGuckin, Aerospace 

Engineer, Systems and Equipment Branch, 

ANM–130S, FAA, Seattle Aircraft 

Certification Office (ACO), 1601 Lind Avenue 

SW., Renton, WA 98057–3356; phone: 425– 

917–6490; fax: 425–917–6590; email: 

Kelly.McGuckin@faa.gov. 

(k) 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) Boeing Multi Operator Message MOM– 

MOM–15–0248–01B, dated April 19, 2015. 

The date appears only on the first page of this 

document. 

(ii) Boeing Multi Operator Message MOM– 

MOM–15–0248–01B(R1), dated April 20, 

2015. The date appears only on the first page 

of this document. 

(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 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. 

(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 April 23, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–10066 Filed 4–30–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0766; Directorate 

Identifier 2013–NE–26–AD; Amendment 39– 

18149; AD 2014–17–08R1] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Canada Corp. Turboprop 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are revising airworthiness 

directive (AD) 2014–17–08 for all Pratt 

& Whitney Canada Corp. (P&WC) PT6A– 

114 and PT6A–114A turboprop engines. 

AD 2014–17–08 required initial and 

repetitive borescope inspections (BSIs) 

of compressor turbine (CT) blades, and 

the removal from service of blades that 

fail inspection. This new AD adds an 

additional single crystal CT blade, 

reduces the affected population, and 

corrects the Credit for Previous Action 

paragraph. This AD was prompted by 

P&WC development of an additional 

single crystal CT blade that corrects the 

unsafe condition. We are issuing this 

AD to prevent failure of CT blades, 

which could result in damage to the 

engine and damage to the airplane. 

DATES: This AD is effective June 5, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publications listed in 

this AD as of October 8, 2014 (79 FR 

52172, September 3, 2014). 

ADDRESSES: For service information 

identified in this AD, contact Pratt & 

Whitney Canada Corp., 1000 MarieVictorin, Longueuil, Quebec, Canada, 

J4G 1A1; phone: 800–268–8000; fax: 

450–647–2888; Internet: www.pwc.ca. 

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. Certain 

service information is also available on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2013– 

0766. 

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–2013– 

0766; 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 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. 

FOR FURTHER INFORMATION CONTACT: 

Barbara Caufield, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7146; fax: 781–238– 

7199; email: barbara.caufield@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to revise AD 2014–17–08, 

Amendment 39–17961 (79 FR 52172, 

September 3, 2014), (‘‘AD 2014–17– 

08’’). AD 2014–17–08 applied to all 

P&WC PT6A–114 and PT6A–114A 

turboprop engines. The NPRM 

published in the Federal Register on 

December 1, 2014 (79 FR 71031). The 

NPRM was prompted by P&WC 

development of an additional single 

crystal CT blade that corrects the unsafe 

condition. The addition of this new part 

number (P/N) reduces the affected 

population. The NPRM proposed to 

retain all the requirements of AD 2014– 

17–08. The NPRM also proposed to add 

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24792 Federal Register / Vol. 80, No. 84 / Friday, May 1, 2015 / Rules and Regulations 

the additional single crystal CT blade 

that corrects the unsafe condition, 

reduce the affected population, and 

correct the Credit for Previous Action 

paragraph. We are issuing this AD to 

prevent failure of CT blades, which 

could result in damage to the engine 

and damage to the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 71031, 

December 1, 2014) and the FAA’s 

response to each comment. 

Request To Clarify Disposition of 

Removed CT Blades 

Hawkins Aero Engineering, Inc. and 

another commenter requested that we 

state more clearly whether pre-SB 

(service bulletin) PT6A–72–1669 CT 

blades removed as a result of this AD 

can be reinstalled in the same engine, 

the same model engine, or a different 

model engine. 

We disagree. Paragraph (e)(1)(iii)(B) of 

this AD clearly states that to re-install 

removed pre-SB PT6A–72–1669 CT 

blades, the blades must pass a two-blade 

metallurgical inspection to determine 

airworthiness in accordance with 

paragraph 3.B., Accomplishment 

Instructions, of P&WC Service Bulletin 

(SB) No. PT6A–72–1669, Revision 9, 

dated June 28, 2013. We did not change 

this AD. 

Request To Not Mandate Installation of 

Single Crystal CT Blades 

One commenter requested that we not 

mandate the installation of single crystal 

CT blades because two of the P/Ns cited 

as replacement blades have experienced 

low-time failures, indicating a design or 

manufacturing flaw. 

We disagree. While there have been 

some failures of single crystal CT blades 

on a different engine model, that failure 

mode is well understood and does not 

affect the engines that are the subject of 

this AD. For the engines that are subject 

to this AD, single crystal blades provide 

a significant improvement in durability 

and a significant reduction in CT blade 

failures overall. We did not change this 

AD. 

Request To Reference Two Additional 

SBs 

One commenter requested that we 

reference P&WC SBs No. PT6A–72–1727 

and No. PT6A–72–1749 in addition to 

P&WC SB No. PT6A–72–1669 because 

each one of these SBs references one of 

the three single crystal CT blades that 

can be installed as terminating action to 

this AD. P&WC SB No. PT6A–72–1669 

alone only references one of the three 

blades listed as terminating action in 

paragraph (e)(2) of this AD. 

We agree. We added references to the 

two additional SBs in paragraph (h)(2) 

of this AD. 

Request To Include Alternative Method 

of Compliance (AMOC) for Inspections 

Hawkins Aero Engineering, Inc. 

requested that we include in the AD an 

AMOC to allow a visual inspection, 

accomplished by splitting the engine at 

the C-flange, as an alternative method to 

the required periodic borescope 

inspection of pre-SB PT6A–72–1669 CT 

blades. The commenter states that this 

suggested visual method would provide 

easier detection of cracks. 

We disagree. This AD contains the 

required method for resolving the 

unsafe condition. If an operator can 

accomplish required actions in a better 

way, or a way that better suits the 

operator’s business processes, and the 

alternative method provides an 

acceptable level of safety, then the 

operator can apply for an AMOC to use 

that method to address the unsafe 

condition in accordance with paragraph 

(g)(2) of this AD. We did not change this 

AD. 

Request That We Address Failures in 

Additional Blades 

Hawkins Aero Engineering, Inc. 

requested that we address single crystal 

CT blade failures either in this or in 

another AD because there have been 

several low-time single crystal CT blade 

failures in several different PT6 engine 

models, some of which are single engine 

installations. 

We disagree. Low-time failures that 

occurred on engine models not affected 

by this AD are due to a failure mode that 

is well understood. That failure mode 

does not occur in the engine models that 

are the subject of this AD. We did not 

change this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously. 

We have determined that these minor 

changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

71031, December 1, 2014) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in NPRM (79 FR 71031, 

December 1, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 300 

engines installed on airplanes of U.S. 

registry. We also estimate that it would 

take about 4 hours per engine to perform 

the required inspection and 8 hours to 

replace the blades. The average labor 

rate is $85 per hour. Required parts cost 

about $59,334 per engine. Based on 

these figures, we estimate the cost of 

this AD on U.S. operators to be 

$18,106,200. 

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 have 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 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. 

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Federal Register / Vol. 80, No. 84 / Friday, May 1, 2015 / Rules and Regulations 24793 

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 

removing Airworthiness Directive (AD) 

2014–17–08, Amendment 39–17961 (79 

FR 52172, September 3, 2014), and 

adding the following new AD: 

2014–17–08R1 Pratt & Whitney Canada 

Corp.: Amendment 39–18149; Docket 

No. FAA–2013–0766; Directorate 

Identifier 2013–NE–26–AD. 

(a) Effective Date 

This AD is effective June 5, 2015. 

(b) Affected ADs 

This AD replaces AD 2014–17–08, 

Amendment 39–17961 (79 FR 52172, 

September 3, 2014). 

(c) Applicability 

This AD applies to all Pratt & Whitney 

Canada Corp. (P&WC) PT6A–114 and PT6A– 

114A turboprop engines. 

(d) Unsafe Condition 

This AD was prompted by several 

incidents of compressor turbine (CT) blade 

failure, causing power loss, and engine 

failure. We are issuing this AD to prevent 

failure of CT blades, which could lead to 

damage to the engine and damage to the 

airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) For engines installed with CT blades 

other than P&WC single crystal CT blades, 

part numbers (P/Ns) 3072791–01, 3072791– 

02, or 3079351–01, do the following: 

(i) Until removed, per the requirements of 

this AD, borescope inspect the CT blade 

leading and trailing edges, within the 

following intervals, whichever occurs later: 

(A) 150 operating hours after October 8, 

2014; or 

(B) 500 operating hours since new; or 

(C) 500 operating hours since last 

borescope inspection (BSI) of the CT blades; 

or 

(D) Before next flight after the effective 

date of this AD. 

(ii) Thereafter, repeat the inspection 

required by paragraph (e)(1)(i) of this AD 

every 500 flight hours time since last 

inspection. 

(iii) At the next hot section inspection 

(HSI) after the effective date of this AD, and 

each HSI thereafter, replace the complete set 

of CT blades with any of the following: 

(A) New CT blades; 

(B) CT blades that have passed a two-blade 

metallurgical inspection. Use paragraph 3.B., 

Accomplishment Instructions, of P&WC 

Service Bulletin (SB) No. PT6A–72–1669, 

Revision 9, dated June 28, 2013, to do the 

inspection; or 

(C) P&WC single crystal CT blades, P/N 

3072791–01, 3072791–02, or 3079351–01. 

(2) Replacement of the complete set of CT 

blades with single crystal CT blades, P/N 

3072791–01, 3072791–02, or 3079351–01 is 

terminating action for the requirements of 

paragraph (e)(1) of this AD. 

(3) By October 8, 2017, replace the 

complete set of CT blades with P&WC single 

crystal CT blades, P/N 3072791–01, 

3072791–02, or 3079351–01. 

(f) Credit for Previous Action 

Performance of the metallurgical 

examination specified in paragraph 

(e)(1)(iii)(B) of this AD on CT blades other 

than P&WC single crystal CT blades, P/N 

3072791–01, 3072791–02, or 3079351–01, 

before the effective date of this AD fulfills the 

initial inspection requirements of paragraph 

(e)(1)(i) of this AD. However, you must still 

comply with the repetitive BSI requirement 

of paragraph (e)(1)(ii) of this AD until you 

complete the mandatory terminating action 

of paragraph (e)(3) of this AD. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) AMOCs previously approved for AD 

2014–17–08, Amendment 39–17961 (79 FR 

52172, September 3, 2014) are approved for 

this AD. 

(2) The Manager, Engine Certification 

Office, FAA, may approve AMOCs for this 

AD. Use the procedures found in 14 CFR 

39.19 to make your request. You may email 

your request to: ANE-AD-AMOC@faa.gov. 

(h) Related Information 

(1) For more information about this AD, 

contact Barbara Caufield, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7146; fax: 781–238– 

7199; email: barbara.caufield@faa.gov. 

(2) P&WC SB No. PT6A–72–1727, dated 

August 23, 2013, and SB No. PT6A–72–1749, 

dated September 23, 2014, which are not 

incorporated by reference in this AD, can be 

obtained from P&WC using the contact 

information in paragraph (i)(4) of this AD. 

(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. 

(3) The following service information was 

approved for IBR on October 8, 2014 (79 FR 

52172, September 3, 2014). 

(i) Pratt & Whitney Canada Service Bulletin 

No. PT6A–72–1669, Revision 9, dated June 

28, 2013. 

(ii) Reserved. 

(4) For P&WC 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. 

(5) You may view this service information 

at 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. 

(6) 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 

April 17, 2015. 

Thomas A. Boudreau, 

Acting Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2015–10075 Filed 4–30–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2015–0794; Airspace 

Docket No. 15–ASO–5] 

Proposed Amendment of Class E 

Airspace; Jupiter, FL 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; technical 

amendment. 

SUMMARY: This action amends Class D 

Airspace at Jupiter, FL, by removing 

reference to Restricted Area R–2936 in 

the regulatory text of the Class D 

airspace area as the restricted area is no 

longer needed. This action also updates 

the geographic coordinates of the 

airport. 

DATES: Effective 0901 UTC, June 25, 

2015. The Director of the Federal 

Register approves this incorporation by 

reference action under title 1, Code of 

Federal Regulations, part 51, subject to 

the annual revision of FAA Order 

7400.9 and publication of conforming 

amendments. 

ADDRESSES: FAA Order 7400.9Y, 

Airspace Designations and Reporting 

Points, and subsequent amendments can 

be viewed online at http://www.faa.gov/ 

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