This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

61717 

Vol. 80, No. 198 

Wednesday, October 14, 2015 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0486; Directorate 

Identifier 2015–NE–07–AD; Amendment 39– 

18282; AD 2015–20–04] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Canada Corp. Turboshaft 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Pratt & Whitney Canada Corp. (P&WC) 

PT6B–37A turboshaft engines. This AD 

requires initial and repetitive 

inspections until replacement of the No. 

10 bearing, and eventual replacement of 

the No. 9 bearing, both located in the 

engine reduction gearbox (RGB) 

assembly. This AD was prompted by 

reports of incorrect engine torque for 

PT6B–37A engines. We are issuing this 

AD to prevent axial migration of the No. 

10 bearing in the engine RGB assembly, 

which could result in engine 

overtorque, failure of the engine, inflight shutdown, and loss of the 

rotorcraft. 

DATES: This AD becomes effective 

November 18, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of November 18, 2015. 

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; Web site: http://

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. 

It is also available on the Internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2015– 

0486. 

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– 

0486; 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. 

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 by adding an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on June 19, 2015 (80 FR 35260). 

The NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Five incidences of incorrect engine torque 

indication have been reported for PT6B–37A 

engine installations on AW119MKII 

helicopters. A lower than actual engine 

torque indication due to a faulty indication 

system, particularly on a helicopter being 

operated at max allowable torque (90 to 

110%) range, may result in undetected overtorque condition. 

Repeated over-torque conditions that are 

undetected and consequently are not 

corrected in accordance with conditional 

inspection requirements of original 

equipment manufacturer (OEM) Instructions 

for Continued Airworthiness (ICAs), may 

have a negative impact on the operational 

safety of the aircraft. Investigation by P&WC 

has determined the root cause of the subject 

torque indication anomaly to be the axial 

migration of part number (P/N) 3310433–03 

bearings at the engine torque sensing gear 

location. 

The axial migration of the No. 10 

bearing is caused by non-optimal 

bearing internal clearance. This 

migration may cause an erroneous 

torque reading, possibly leading to 

engine overtorque and engine failure. 

We are also requiring replacement of the 

No. 9 bearing since it may also migrate, 

has the same part number as a No. 10 

bearing, and could be installed in the 

same location as a No. 10 bearing. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 35260, June 19, 2015). 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed. 

Related Service Information Under 1 

CFR Part 51 

P&WC has issued Service Bulletin 

(SB) No. PT6B–72–39095, Revision No. 

3, dated December 29, 2014. The service 

information describes procedures for 

inspecting affected bearings. 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 

this final rule. 

Other Related Service Information. 

P&WC has also issued SB No. PT6B– 

72–39092, Revision No. 4, dated 

December 29, 2014. The service 

information describes procedures for 

removing affected bearings. 

Costs of Compliance 

We estimate that this AD affects 83 

engines installed on rotocraft of U.S. 

registry. We estimate that it will take 

about 3 hours per engine to comply with 

this AD. We also estimate that it would 

take about 1 hour per engine to replace 

the affected bearings. The average labor 

rate is $85 per hour. Required parts cost 

about $49,800 per engine. Based on 


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61718 Federal Register / Vol. 80, No. 198 / Wednesday, October 14, 2015 / Rules and Regulations 

these figures, we estimate the cost of 

this AD on U.S. operators to be 

$4,161,620. 

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): 

2015–20–04 Pratt & Whitney Canada Corp.: 

Amendment 39–18282; Docket No. 

FAA–2015–0486; Directorate Identifier 

2015–NE–07–AD. 

(a) Effective Date 

This AD becomes effective November 18, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Pratt & Whitney Canada 

Corp. (P&WC) PT6B–37A turboshaft engines 

with engine serial numbers identified in 

Table 1 of paragraph 4, Appendix, in P&WC 

Service Bulletin (SB) No. PT6B–72–39095, 

Revision No. 3, dated December 29, 2014. 

(d) Reason 

This AD was prompted by reports of 

incorrect engine torque for PT6B–37A 

turboshaft engines. We are issuing this AD to 

prevent axial migration of the No. 10 bearing 

in the engine reduction gearbox (RGB) 

assembly, which could lead to engine 

overtorque, failure of the engine, in-flight 

shutdown, and loss of the rotorcraft. 

(e) Actions and Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) Initial Inspection 

(i) Within 50 flight hours (FHs) time in 

service after the effective date of this AD, 

inspect the No. 10 bearing, part number (P/ 

N) 3310433–03, in the RGB assembly for 

axial movement. Use paragraphs 3.A. to 3.C. 

in the Accomplishment Instructions in 

P&WC SB No. PT6B–72–39095, Revision No. 

3, dated December 29, 2014, to do the 

inspection. If the bearing fails the inspection, 

replace the No. 9 and No. 10 bearings before 

further flight. 

(2) Repetitive Inspection 

(i) For engines with 500 FHs or less total 

time since new (TSN), repeat the inspection 

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

100 FHs time since last inspection (TSLI) 

until 500 hours total TSN, and, thereafter, 

every 200 FHs TSLI until removal. 

(ii) For engines with more than 500 FHs 

total TSN perform the inspection required by 

paragraph (e)(1) to this AD within 200 FHs 

TSLI, and, thereafter, every 200 FHs TSLI 

until removal. 

(3) Removal and Replacement of Affected 

Bearings 

(i) For engine serial numbers (S/Ns) PCE– 

PU0192, PU0193, PU0201, PU0208, PU0209, 

PU0212, PU0213, PU0214, PU0216, PU0219, 

and PU0220, remove the No. 9 and No. 10 

bearings, P/N 3310433–03, within 450 FHs or 

42 months after the effective date of this AD, 

whichever occurs first, and replace with 

parts eligible for installation. 

(ii) For all engine S/Ns identified in 

Applicability paragraph (c) of this AD, other 

than those listed in paragraph (e)(3)(i) of this 

AD, remove the No. 9 and No. 10 bearings, 

P/N 3310433–03, and replace with parts 

eligible for installation within 42 months 

after the effective date of this AD. 

(iii) Replacement of the No. 9 and No. 10 

bearing, P/N 3310433–03, with the No. 9 and 

No. 10 bearing, P/N 3310233–03 or P/N 

3310533–03, is terminating action for this 

AD. 

(f) Reporting Requirements 

You do not have to contact your Local 

Field Service Representative as discussed in 

paragraph 3.C.(3) of P&WC SB No. PT6B–72– 

39095, Revision No. 3, dated December 29, 

2014. 

(g) Credit for Previous Action 

If you previously replaced the No. 9 and 

No. 10 bearings in accordance with the 

instructions contained in P&WC SB No. 

PT6B–72–39092, Revision No. 2, dated 

August 8, 2014, or earlier revisions, then you 

have complied with this AD. 

(h) Alternative Methods of Compliance 

(AMOCs) 

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. 

(i) 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) Refer to MCAI Transport Canada AD 

CF–2015–01, dated January 20, 2015, 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. http://

www.regulations.gov/#!docketDetail;D=FAA2015-0486. 

(j) 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) Pratt & Whitney Canada Corp. Service 

Bulletin (SB) No. PT6B–72–39095, Revision 

No. 3, dated December 29, 2014. 

(ii) Reserved. 

(3) For Pratt & Whitney Canada Corp. 

service information identified in this AD, 

contact Pratt & Whitney Canada Corp., 1000 

Marie-Victorin, Longueuil, Quebec, Canada, 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 198 / Wednesday, October 14, 2015 / Rules and Regulations 61719 

J4G 1A1; phone: 800–268–8000; fax: 450– 

647–2888; Web site: www.pwc.ca. 

(4) 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. 

(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 22, 2015. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2015–25711 Filed 10–13–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–1059; Directorate 

Identifier 2013–NE–36–AD; Amendment 39– 

18281; AD 2015–20–03] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Canada Corp. Turboprop 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2014–14– 

02 for certain Pratt & Whitney Canada 

Corp. (P&WC) PW120, PW121, PW121A, 

PW124B, PW127, PW127E, PW127F, 

PW127G, and PW127M turboprop 

engines. AD 2014–14–02 required 

removal of the O-ring seal from the fuel 

manifold fitting. This new AD requires 

replacement of the fuel nozzle and the 

fuel manifold flow adapter. This AD 

was prompted by reports of fuel leaks at 

the interface between the fuel manifold 

and the fuel nozzle that resulted in 

engine fire. We are issuing this AD to 

correct the unsafe condition on these 

products. 

DATES: This AD is effective November 

18, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 18, 2015. 

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; Web site: 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. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2013– 

1059. 

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– 

1059; 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, 

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 supersede AD 2014–14–02, 

Amendment 39–17896 (79 FR 39958, 

July 11, 2014), (‘‘AD 2014–14–02’’). AD 

2014–14–02 applied to certain P&WC 

PW120, PW121, PW121A, PW124B, 

PW127, PW127E, PW127F, PW127G, 

and PW127M turboprop engines. The 

NPRM published in the Federal 

Register on June 2, 2015 (80 FR 31325). 

The NPRM proposed to require 

replacement of the fuel nozzle and the 

fuel manifold flow adapter. 

Related Service Information Under 1 

CFR Part 51 

We reviewed P&WC SB No. PW100– 

72–21861, dated November 21, 2014, 

which identifies the final fuel nozzle 

configuration. 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 this AD. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 31325, June 2, 2015) or on the 

determination of the cost to the public. 

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 150 

engines installed on airplanes of U.S. 

registry. We also estimate that it will 

take about 2.5 hours per engine to 

comply with this AD. The average labor 

rate is $85 per hour. Required parts cost 

about $146,594 per engine. Based on 

these figures, we estimate the cost of 

this AD on U.S. operators to be 

$22,020,975. 

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 

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), 


tkelley on DSK3SPTVN1PROD with RULES