[4910 - 13 - P ] 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 20 1 5 - 20 - 04 ] RIN 2120 - AA64 Airworthiness Directives; Pratt & Whitney Canada Corp . Turbo shaft Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule
. SUMMARY: We are adopting a new airworthiness directive (AD) for certain Pratt & Whitn ey Canada Corp. (P&WC) PT6B

- 37A turbo shaft engines
. This AD requires initial
an d repetitive inspection s 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
. W e 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, in

flight shutdown, and loss of the rotorcraft
. DATES: This AD becomes effective [ INSERT DATE 35 DAYS AFTER DATE OF PUBLICATION IN THE FEDERAL REGISTER ]. The Director of the Federal Register approved the incorporation by reference of certain publication s listed in this AD as of [INSERT DATE 35 DAYS AFTER DATE OF PUBLICATION IN THE FEDERAL REGISTER ].ADDRESSES: 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; Web site: http:// www.pwc.ca . You may view this service info rmation 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
sea rching for and locating Docket No. FAA

- 201 5

- 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

- 201 5

- 0486 ; or in person at the Docket Management Facility bet ween 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: Ba rbara Caufield , Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803 ; p hone : 781

- 238

- 7146 ; fax : 781

- 238

- 7199 ; e mail: barbara.caufield@faa.gov
.

2SUPPLEMENTARY INFORMATION: D iscussion 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. Th e NPRM was published in the Federal Register on June 1 9 , 2015 ( 80 FR 35260 ). Th e NPRM proposed to correct an
un safe 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 in dication system, particularly on a helicopter being operated at max allowable torque (90 to 110%) range, may result in undetected over

- torque condition. Repeated over

- torque conditions that are undetected and consequently are not corrected in accordance wi th 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 th e 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 develop ing this AD. We received no comments on the NPRM ( 80 FR 35260 , June 1 9 , 2015 )
. 3Conclusion We reviewed the available data and determined that air safety and the public interest require adopting th is 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. Co s ts of Compliance We estimate that this AD affects 83 engines installed on rotocraft o f 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 par ts cost about $ 49,800 per engine. Based on these figures, we estimate the cost of this AD on U.S. operators to be $ 4,161,620
. Authority for T his Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, s ection 106, describes the authority of the FAA Administrator.

“ Subtitle VII : Aviation Programs ,” describes in more detail the scope of the Agency’s authority. 4We are issuing this rulemaking under the author ity described in “Subtitle VII, P art A, S ubpart III, S ection 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
neces sary 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 w ill not have federalism implications under Executive Order 13132. This AD w ill not have a substantial direct effect on the States, on the relationship between the national g overnment and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify th is 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 1 1034, 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 entitie s 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.

5Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amend s 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) : 201 5

- 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 [ INSERT DATE 35 DAYS AFTER DATE OF PU BLICATION IN THE FEDERAL REGISTER ]. (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 Bulle tin (SB) No. PT6B

- 72

- 39095, Revision No. 3, dated December 29, 2014.

6(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 engin e 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 In structions 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 FH s 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 tha n 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
.

7(3) Removal and Replacement of Affected Bearings (i) For engine serial numbers (S/Ns) PCE

- PU0192, PU0 193, 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 installati on 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 Y ou 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 bearin gs 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.

8( 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 , Aerospa ce 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 , d ated January 20, 2015 , for more information. You may examine th e 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=FAA

- 2015

- 0486
. ( j ) Material Inco rporated 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 applicabl e 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
.

9(3) For Pratt & Whitney Canada Corp. service infor mation 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; 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 inform ation on the availability of this material at NARA, call 202

- 741

- 6030, or go to: http://www.archives.gov/federal

- register/cfr/ibr

locations.html. Issued in Burlington, Massachusetts, on September 22, 2015
.

Colleen M. D’Alessandro , Directorate Manager , Engine & Propeller Directorate, Aircraft Certification Service
.

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