### [4910-13-P] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2012-1005; Directorate Identifier 2012-NE-27-AD; Amendment 39-17349; AD 2013-03-14] 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) PT6C-67C turboshaft engines. This AD requires initial and repetitive borescope inspections to verify the presence ofa retaining ring securing the power turbine (PT) baffle located near the second stage PT disk. If the engine fails the inspection, this AD also requires removing the engine from service before further flight. This AD was prompted by five reported incidents of second stage PT disk damage. We
are issuing this AD to prevent damage to the PT disk which, if undetected, could cause uncontained PT disk failure and loss ofcontrol of the helicopter. DATES: This AD becomes effective [Insert date 35 days after date ofpublication in the FEDERAL REGISTER]. ADDRESSES: The Docket Operations office is located at Docket Management Facility, U
.S
. Department ofTransportation, 1200 New Jersey Avenue SE. , West Building Ground Floor, Room W12-140, Washington, DC 20590-0001.

### FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine & 

### Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: james.lawrence@ faa
.gov; phone: 781-238-7176 ; fax: 781-238-7199. SUPPLEMENTARY INFORMATION: Discussion We issued a notice ofproposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Fed eral Register 

### on October 25 , 2012 (77 FR 65142). That NPRM proposed to correct an unsafe condition for the specified products. The Mandatory Continuing Airworthiness Information states:

Comments There have been 5 reported incidents of second stage Power Turbine (PT) disk damage caused by the PT baffle moving and contacting the downstream side ofthe second stage PT disk
. In two ofthese incidents , the PT section ofthe engine failed to rotate (on ground) as a result ofbaffle interference. An investigation has determined that the root cause for the PT baffle displacement and the resultant PT disk damage was due to the failure ofthe retaining ring that holds the PT baffle in its intended position.

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (77 FR 65142 , October 25 , 2012). Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed (77 FR 65142 , October 25 , 2012).
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### Costs of Compliance Based on the service information, we estimate that this AD will affect about 220 engines ofU.S. registry. We also estimate that it will take about six hours per engine to comply with this AD. The average labor rate is $85 per work-hour. We anticipate that two engines will fail the initial inspection. Required parts will cost about $224,636 per engine
. Based on these figures , we estimate the cost ofthe AD on U
.S. operators to be $561 ,472. Our cost estimate is exclusive ofpossible warranty coverage. 

### Authority for This Rulemaking Title 49 ofthe United States Code specifies the FAA's authority to issue rules on aviation safety
. Subtitle I, section 106, describes the authority ofthe FAA Administrator.

" Subtitle VII: Aviation Programs ," describes in more detail the scope ofthe 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 ofthat 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

3the 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); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria ofthe Regulatory Flexibility Act. We prepared a regulatory evaluation ofthe estimated costs to comply with this AD and placed it in the AD docket. 

### Examining the AD Docket You may examine the AD docket on the Internet at http: //www.regulations.gov;
or in person at the Docket Operations office 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 street address for the Docket Operations office (phone: (800) 647-5527) is provided 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:

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### 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: 2013-03-14 Pratt & 

### Whitney Canada Corp: Amendment 39-17349; Docket No. FAA2012-1005; Directorate Identifier 2012-NE-27-AD. (a) Effective Date This airworthiness directive (AD) becomes effective [Insert date 35 days after date ofpublication in the FEDERAL REGISTER]. (b) Affected ADs None. (c) 

### Applicability This AD applies to Pratt & Whitney Canada Corp. (P&WC) PT6C-67C turboshaft engines that have not had P&WC Service Bulletin (SB) No. PT6C-72-41056 incorporated. (d) Reason This AD was prompted by five reported incidents of second stage power turbine (PT) disk damage. We are issuing this AD to prevent damage to the PT disk which, if undetected, could cause uncontained PT disk failure and loss ofcontrol ofthe helicopter. (e) 

### Actions and Compliance Unless already done, do the following actions.

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### (t) Borescope Inspections (1) Borescope-inspect to verify the presence of a retaining ring securing the PT baffle located near the second stage PT disk, as follows: (i) For engines with 2,200 PT cycles or more on the effective date ofthis AD , inspect within 100 operating hours or 150 PT cycles , whichever occurs first. (ii) For engines with more than 1,400 PT cycles but fewer than 2,200 PT cycles
on the effective date ofthis AD , inspect within 250 operating hours, 350 PT cycles , or before exceeding 2,350 PT cycles , whichever occurs first. (iii) For engines with 1,400 PT cycles or fewer on the effective date ofthis AD, inspect within 500 operating hours , 750 PT cycles, or before exceeding 1,750 PT cycles , whichever occurs first. (2) Thereafter, repetitively borescope-inspect to verify the presence ofthe retaining ring securing the PT baffle located near the second stage PT disk, on or before
an additional 600 flight hours or 900 PT cycles, whichever occurs first. (3) Use P&WC Alert SB No
. PT6C-72-A41060, Revision 3, dated October 11, 2012 , paragraphs 3.A.(l) through 3.A.(6) to do the borescope inspections required by this AD. (4) Ifthe retaining ring is missing or the PT baffle is out ofposition, then remove the engine from service before further flight. (g) 

### Optional Terminating Action Performing the engine improvement modifications in P&WC SB No
. PT6C-72- 41056 , Revision 5, dated January 17, 2013 , paragraphs 3
.A. through 3.C.(12) and 3.E
.(l)



### 6through 3
.E
.( 15) , is an optional terminating action to the repetitive inspections required by this AD. (h) Credit for Previous Actions (1) Ifyou performed the initial borescope inspection before the effective date of this AD using P&WC Special Instruction No. 45-2011R2 , dated July 27 , 2011 , or P&WC Alert SB No. PT6C-72-A41060, dated August 12, 2011 , or Revision 1, dated September 29 , 2011 , or Revision 2 , dated February 10, 2012 , you met the requirements ofparagraph (f)(1) ofthis AD
. (2) If you performed the engine modification before the effective date ofthis AD using P&WC SB No. PT6C-72-41056, dated April! , 2011 , or Revision I , dated June 17 , 2011 , or Revision 2, dated October 6, 2011 , or Revision 3 , dated February 3 , 2012 , or Revision 4 , dated February 13 , 2012 , you met the requirements ofthis AD and no further action is required. (i) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, may approve AMOCs for this AD
. Use the procedures found in 14 CFR 3 9
. 19 to make your request. (j) Related Information (I) For more information about this AD , contact James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: james.lawrence @ faa.gov ; phone: 781-238-7176 ; fax: 781-238-7199. (2) Refer to Transport Canada AD CF-2012-24, dated August 2, 2012, for related information. 7(k) Material Incorporated 

### by Reference ( 1) The Director ofthe Federal Register approved the incorporation by reference (IBR) ofthe 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 (P&WC) Alert Service Bulletin (SB) No. PT6C-72-A41060, Revision 3 , dated October 11 , 2012. (ii) P&WC SB No
. PT6C-72-41056 , Revision 5, dated January 17 , 2013. (3) For service information identified in this AD , contact Pratt & Whitney Canada Corp. , 1000 Marie

-Victorin, Longueuil , Quebec, Canada, J4G 1Al ; phone : 800-268- 8000 ; fax: 450-647-2888; Web site: http ://www .pwc.c a. (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 ofthis material at the FAA, call 781-238-7125
. (5) You may view this service infom1ation at the National Archives and Records Administration (NARA). For information on the availability ofthis material at NARA, ca11202-741-6030 , or go to: http ://www. archi ves.gov/f ederal-regi ster /cfr/ibrlocati ons.html.

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### Issued in Burlington, Massachusetts , on February 1, 2013
.

Colleen M
. D 'Alessandro, Assistant Manager, Engine & 

### Propeller Directorate, Aircraft Certification Service
.

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