Airworthiness Directives; Pratt & Whitney Canada Corp Turboshaft Engines, 11563-11565 [2013-03266]

Download as PDF Federal Register / Vol. 78, No. 33 / Tuesday, February 19, 2013 / Rules and Regulations additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards. DATES: Effective date: March 21, 2013. FOR FURTHER INFORMATION CONTACT: Joe Jacobsen, FAA, Airplane and Flight Crew Interface Branch, ANM–111, Transport Airplane Directorate, Aircraft Certification Service, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone 425–227–2011; facsimile 425–227–1149. SUPPLEMENTARY INFORMATION: Background On May 14, 2009, Embraer S.A. applied for a type certificate for their new Model EMB–550 airplane. The Model EMB–550 airplane is the first of a new family of jet airplanes designed for corporate flight, fractional, charter, and private owner operations. The aircraft has a conventional configuration with a low wing and T-tail empennage. The primary structure is metal with composite empennage and control surfaces. The Model EMB–550 airplane is designed for 8 passengers, with a maximum of 12 passengers. It is equipped with two Honeywell HTF7500–E medium bypass ratio turbofan engines mounted on aft fuselage pylons. Each engine produces approximately 6,540 pounds of thrust for normal takeoff. The primary flight controls consist of hydraulically powered fly-by-wire elevators, aileron and rudder, controlled by the pilot or copilot sidestick. The longitudinal control law design of the Embraer S.A. Model EMB–550 airplane incorporates an overspeed protection system in the normal mode. This mode prevents the pilot from inadvertently or intentionally exceeding a speed approximately equivalent to VFC or attaining VDF. Current Title 14, Code of Federal Regulations (14 CFR) part 25 did not envision a high speed limiter that might preclude or modify flying qualities assessments in the overspeed region. sroberts on DSK5SPTVN1PROD with RULES Type Certification Basis Under the provisions of 14 CFR 21.17, Embraer S.A. must show that the Model EMB–550 airplane meets the applicable provisions of part 25, as amended by Amendments 25–1 through 25–127 thereto. If the Administrator finds that the applicable airworthiness regulations (i.e., 14 CFR part 25) do not contain adequate or appropriate safety standards for the Model EMB–550 airplane because of a novel or unusual design VerDate Mar<15>2010 15:41 Feb 15, 2013 Jkt 229001 feature, special conditions are prescribed under the provisions of § 21.16. Special conditions are initially applicable to the model for which they are issued. Should the type certificate for that model be amended later to include any other model that incorporates the same or similar novel or unusual design feature, the special conditions would also apply to the other model under § 21.101. In addition to the applicable airworthiness regulations and special conditions, the Model EMB–550 airplane must comply with the fuel vent and exhaust emission requirements of 14 CFR part 34 and the noise certification requirements of 14 CFR part 36 and the FAA must issue a finding of regulatory adequacy under section 611 of Public Law 92–574, the ‘‘Noise Control Act of 1972.’’ The FAA issues special conditions, as defined in 14 CFR 11.19, in accordance with § 11.38, and they become part of the type-certification basis under § 21.17(a)(2). Novel or Unusual Design Features The Model EMB–550 airplane will incorporate the following novel or unusual design feature: an electronic flight control system which contains flyby-wire control laws, including envelope protections, for the overspeed protection and roll limiting function. Current part 25 requirements do not contain appropriate standards for high speed protection systems. Discussion As further discussed previously, a special condition is necessary in addition to the requirements of § 25.143 for the operation of the high speed protection. The general intent is that the overspeed protection does not impede normal maneuvering and speed control and that the overspeed protection does not restrict or prevent emergency maneuvering. Therefore, these special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards. Discussion of Comments Notice of proposed special conditions No. 25–12–12–SC for the Embraer S.A. Model EMB–550 airplanes was published in the Federal Register on November 20, 2012 (77 FR 69572). No comments were received, and the special conditions are adopted as proposed. PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 11563 Applicability As discussed above, these special conditions are applicable to the Model EMB–550 airplane. Should Embraer S.A. apply at a later date for a change to the type certificate to include another model incorporating the same novel or unusual design feature, the special conditions would apply to that model as well. Conclusion This action affects only certain novel or unusual design features on one model of airplanes. It is not a rule of general applicability. List of Subjects in 14 CFR Part 25 Aircraft, Aviation safety, Reporting and recordkeeping requirements. ■ The authority citation for these special conditions is as follows: Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. The Special Conditions Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for Embraer S.A. Model EMB–550 airplanes. 1. In addition to § 25.143, the following requirement applies: Operation of the high speed limiter during all routine and descent procedure flight must not impede normal attainment of speeds up to overspeed warning. Issued in Renton, Washington, on February 12, 2013. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–03676 Filed 2–15–13; 8:45 am] BILLING CODE 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 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain SUMMARY: E:\FR\FM\19FER1.SGM 19FER1 11564 Federal Register / Vol. 78, No. 33 / Tuesday, February 19, 2013 / Rules and Regulations Pratt & Whitney Canada Corp. (P&WC) PT6C–67C turboshaft engines. This AD requires initial and repetitive borescope inspections to verify the presence of a 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 of control of the helicopter. This AD becomes effective March 26, 2013. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of March 26, 2013. DATES: The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. ADDRESSES: FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; email: james.lawrence@faa.gov; phone: 781–238–7176; fax: 781–238–7199. SUPPLEMENTARY INFORMATION: Discussion sroberts on DSK5SPTVN1PROD with RULES We issued a notice of proposed 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 Federal 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: 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 of the second stage PT disk. In two of these incidents, the PT section of the engine failed to rotate (on ground) as a result of baffle 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 of the retaining ring that holds the PT baffle in its intended position. Comments 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). VerDate Mar<15>2010 15:41 Feb 15, 2013 Jkt 229001 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). Costs of Compliance Based on the service information, we estimate that this AD will affect about 220 engines of U.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 of the AD on U.S. operators to be $561,472. Our cost estimate is exclusive of possible warranty coverage. We prepared a regulatory evaluation of the 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 https:// 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 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. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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); and 3. 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. (a) Effective Date This airworthiness directive (AD) becomes effective March 26, 2013. PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 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: ■ 2013–03–14 Pratt & Whitney Canada Corp: Amendment 39–17349; Docket No. FAA–2012–1005; Directorate Identifier 2012–NE–27–AD. (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 of control of the helicopter. (e) Actions and Compliance Unless already done, do the following actions. E:\FR\FM\19FER1.SGM 19FER1 Federal Register / Vol. 78, No. 33 / Tuesday, February 19, 2013 / Rules and Regulations (f) 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 of this 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 of this 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 of this AD, inspect within 500 operating hours, 750 PT cycles, or before exceeding 1,750 PT cycles, whichever occurs first. (2) Thereafter, repetitively borescopeinspect to verify the presence of the 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.(1) through 3.A.(6) to do the borescope inspections required by this AD. (4) If the retaining ring is missing or the PT baffle is out of position, 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.(1) through 3.E.(15), is an optional terminating action to the repetitive inspections required by this AD. sroberts on DSK5SPTVN1PROD with RULES (h) Credit for Previous Actions (1) If you 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 of paragraph (f)(1) of this AD. (2) If you performed the engine modification before the effective date of this AD using P&WC SB No. PT6C–72–41056, dated April 1, 2011, or Revision 1, 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 of this 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 39.19 to make your request. (j) Related Information (1) 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; VerDate Mar<15>2010 15:41 Feb 15, 2013 Jkt 229001 email: 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. (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) 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 1A1; phone: 800–268– 8000; fax: 450–647–2888; Web site: https:// www.pwc.ca. (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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Burlington, Massachusetts, on February 1, 2013. Colleen M. D’Alessandro, Assistant Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2013–03266 Filed 2–15–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0942; Directorate Identifier 2012–NE–24–AD; Amendment 39– 17355; AD 2013–03–21] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney Canada Corp. Turboshaft Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain serial number Pratt & Whitney Canada Corp. PW206B, PW206B2, PW206C, PW207C, PW207D, PW207D1, PW207D2, and PW207E turboshaft engines. This AD was prompted by the SUMMARY: PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 11565 discovery that certain power turbine (PT) disks were made to specific heat codes that may not achieve the maximum in-service life. This AD requires re-identification of the PT disk to a part number (P/N) with a lower life limit. We are issuing this AD to prevent possible uncontained PT disk failure and loss of helicopter control. DATES: This AD becomes effective March 26, 2013. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 26, 2013. ADDRESSES: The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 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; phone: 781–238–7176; fax: 781–238– 7199; email: james.lawrence@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed 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 Federal Register on November 7, 2012 (77 FR 66767). That NPRM proposed to correct an unsafe condition for the specified products. The Mandatory Continuing Airworthiness Information states: Certain power turbine (PT) disks, part number (P/N) 3044188–01, made to specific heat codes may not achieve the established maximum in-service life when installed in Turbomachinery Assembly P/N 3058588. The PT disk in-service life for engines using this specific PT disk and compressor turbine (CT) vane combination is reduced when operated in a particular temperature and speed environment. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (77 FR 66767, November 7, 2012). Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed (77 FR 66767, November 7, 2012). Costs of Compliance We estimate that this AD will affect about 83 engines installed on E:\FR\FM\19FER1.SGM 19FER1

Agencies

[Federal Register Volume 78, Number 33 (Tuesday, February 19, 2013)]
[Rules and Regulations]
[Pages 11563-11565]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-03266]


-----------------------------------------------------------------------

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

[[Page 11564]]

Pratt & Whitney Canada Corp. (P&WC) PT6C-67C turboshaft engines. This 
AD requires initial and repetitive borescope inspections to verify the 
presence of a 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 of control of the helicopter.

DATES: This AD becomes effective March 26, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of March 26, 
2013.

ADDRESSES: The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 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; email: 
james.lawrence@faa.gov; phone: 781-238-7176; fax: 781-238-7199.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed 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 Federal 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:

    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 of the second stage PT disk. In two 
of these incidents, the PT section of the engine failed to rotate 
(on ground) as a result of baffle 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 of the retaining ring that holds the PT baffle in its 
intended position.

Comments

    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).

Costs of Compliance

    Based on the service information, we estimate that this AD will 
affect about 220 engines of U.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 of 
the AD on U.S. operators to be $561,472. Our cost estimate is exclusive 
of possible warranty coverage.

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); and
    3. 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.
    We prepared a regulatory evaluation of the 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 https://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:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2013-03-14 Pratt & Whitney Canada Corp: Amendment 39-17349; Docket 
No. FAA-2012-1005; Directorate Identifier 2012-NE-27-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective March 26, 
2013.

(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 of control of the helicopter.

(e) Actions and Compliance

    Unless already done, do the following actions.

[[Page 11565]]

(f) 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 of this 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 of this 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 of this 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 of the 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.(1) through 3.A.(6) to do the 
borescope inspections required by this AD.
    (4) If the retaining ring is missing or the PT baffle is out of 
position, 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.(1) through 3.E.(15), is an optional 
terminating action to the repetitive inspections required by this 
AD.

(h) Credit for Previous Actions

    (1) If you 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 of 
paragraph (f)(1) of this AD.
    (2) If you performed the engine modification before the 
effective date of this AD using P&WC SB No. PT6C-72-41056, dated 
April 1, 2011, or Revision 1, 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 of 
this 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 39.19 to make your 
request.

(j) Related Information

    (1) 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; email: 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.

(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) 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 1A1; phone: 800-268-8000; fax: 450-647-2888; Web site: 
https://www.pwc.ca.
    (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: 
https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on February 1, 2013.
Colleen M. D'Alessandro,
Assistant Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2013-03266 Filed 2-15-13; 8:45 am]
BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.