Airworthiness Directives; Pratt & Whitney Turbofan Engines, 93855-93857 [2016-30114]

Download as PDF Federal Register / Vol. 81, No. 246 / Thursday, December 22, 2016 / Proposed Rules based on mortality rates for annuitants paid from the Civil Service Retirement and Disability Fund; and increases each year at an assumed rate of cost-of-living adjustment. Assumed rates of interest, mortality, and cost-of-living adjustments used in computing the present value are those used by the Board of Actuaries of the Civil Service Retirement System for valuation of the Federal Employees’ Retirement System based on dynamic assumptions. The present value factors are unisex factors obtained as a composite of sex-distinct present value factors. Separate present value factors apply for FERS annuities that receive cost-of-living adjustments before the retiree attains age 62, versus FERS annuities that do not receive cost-ofliving adjustments before the retiree attains age 62. * * * * * ■ 21. Add § 842.616 to subpart F to read as follows: § 842.616 factors. Publication of present value When OPM publishes in the Federal Register notice of normal cost percentages under § 841.407 of this chapter, it will also publish updated present value factors. ■ 22. Amend § 842.702 by revising the definition of ‘‘present value factor’’ to read as follows: § 842.702 Definitions. * * * * * Present value factor has the same meaning in this subpart as defined in § 842.602. * * * * * PART 847—ELECTIONS OF RETIREMENT COVERAGE BY CURRENT AND FORMER EMPLOYEES OF NONAPPROPRIATED FUND INSTRUMENTALITIES 23. The authority citation for part 847 continues to read as follows: ■ Authority: 5 U.S.C. 8332(b)(17) and 8411(b)(6) and sections 1131 and 1132 of Pub. L. 107–107, December 28, 2001, 115 Stat 1242; 5 U.S.C. 8347(a) and 8461(g) and section 1043(b) of Pub. L. 104–106, Div. A, Title X, Feb. 10, 1996, 110 Stat. 434. Subpart B also issued under 5 U.S.C. 8347(q) and 8461(n). Subpart A—General Provisions 24. Amend § 847.103(b) by revising the definition of ‘‘actuarial present value’’ and adding the definition of ‘‘present value factor’’ in alphabetical order as follows: Lhorne on DSK30JT082PROD with PROPOSALS ■ § 847.103 * Definitions. * * (b) * * * VerDate Sep<11>2014 * * 15:19 Dec 21, 2016 Jkt 241001 Actuarial present value means the amount of monthly annuity at time of retirement multiplied by the applicable present value factor. * * * Present value factor has the same meaning in this part as defined in § 842.602. * * * * * § 847.602 [Removed and Reserved] ■ 25. Remove and reserve § 847.602. [FR Doc. 2016–30487 Filed 12–21–16; 8:45 am] BILLING CODE 6325–38–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0740; Directorate Identifier 2013–NE–24–AD] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2014–05– 32, which applies to all Pratt & Whitney (PW) PW2037, PW2037D, PW2037M, PW2040, PW2040D, PW2043, PW2143, PW2643, and F117–PW–100 turbofan engines. AD 2014–05–32 currently requires one-time eddy current inspection (ECI) of affected engines with certain diffuser and HPT cases installed. AD 2014–05–32 also requires a fluorescent-penetrant inspection (FPI) of the diffuser case rear flange and the HPT case front flange. Since we issued AD 2014–05–32, the manufacturer determined through analysis that the inspections required by AD 2014–05–32 are not adequate to maintain safety. This proposed AD would add additional repetitive, on-wing ECI inspections. We are proposing this AD to correct the unsafe condition on these products. DATES: We must receive comments on this proposed AD by February 6, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room SUMMARY: PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 93855 W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108; phone: 860–565–8770; fax: 860–565– 4503. You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. 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– 0740; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Brian Kierstead, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7772; fax: 781–238–7199; email: brian.kierstead@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2013–0740; Directorate Identifier 2013–NE–24–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. E:\FR\FM\22DEP1.SGM 22DEP1 93856 Federal Register / Vol. 81, No. 246 / Thursday, December 22, 2016 / Proposed Rules Discussion On March 6, 2014, we issued AD 2014–05–32, Amendment 39–17804 (79 FR 17856, March 31, 2014), (‘‘AD 2014– 05–32’’), for all PW PW2037, PW2037D, PW2037M, PW2040, PW2040D, PW2043, PW2143, PW2643, and F117– PW–100 turbofan engines. AD 2014–05– 32 requires a one-time ECI of affected engines with certain diffuser and HPT cases installed. AD 2014–05–32 also requires an FPI of the diffuser case rear flange and HPT case front flange. AD 2014–05–32 resulted from a rupture of the diffuser-to-HPT case flange. We issued AD 2014–05–32 to prevent failure of the diffuser-to-HPT case flange, which could lead to uncontained engine failure and damage to the airplane. Actions Since AD 2014–05–32 Was Issued Since we issued AD 2014–05–32, the manufacturer identified a subpopulation of diffuser cases installed on the affected engines with a repaired flange that has a lower fatigue capability. The repaired flange cannot be distinguished from non-repaired flanges on diffuser cases installed on the affected engines. We determined, therefore, that the inspections required by AD 2014–05–32 are not adequate to maintain safety. To correct this unsafe condition, we are now proposing additional, repetitive ECI inspections. Related Service Information Under 1 CFR Part 51 We reviewed PW Service Bulletin No. PW2000 72–763, Revision No. 1, dated August 30, 2013; and PW Alert Service Bulletin No. PW2000 A72–765, Revision No. 1, dated July 13, 2016. This service information describes procedures for a one-time ECI inspection of the engine diffuser case and the HPT case, and repetitive on-wing ECIs of the engine diffuser case assembly, respectively. 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. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would retain the requirements of AD 2014–05–32 except it would eliminate the Prohibition Statement. We determined that this statement is unnecessary for compliance with the AD. In addition, this proposed AD would require repetitive, on-wing ECI inspections. This proposed AD would also remove the PW2240 and PW2337 engines from the applicability section since these engines were removed from PW Type Certificate Number E17NE. Costs of Compliance We estimate that this proposed AD will affect 910 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action On-wing/module ECI Inspection. FPI Inspection ........................ Labor cost 8 work-hours × $85 per hour = $680. 3 work-hours × $85 per hour = $255. Lhorne on DSK30JT082PROD with PROPOSALS 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 proposed AD would not have federalism VerDate Sep<11>2014 15:19 Dec 21, 2016 Parts cost Jkt 241001 Cost per product $0 $680 ....................................... 20 $275 per inspection cycle ...... implications under Executive Order 13132. This proposed AD would 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 the proposed regulation: (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. PO 00000 Frm 00006 Cost on U.S. operators Fmt 4702 Sfmt 4702 $230,520 per inspection cycle. $250,250 per inspection cycle. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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) 2014–05–32, Amendment 39–17804 (79 FR 17856, March 31, 2014), and adding the following new AD: ■ Pratt & Whitney: Docket No. FAA–2013– 0740; Directorate Identifier 2013–NE– 24–AD. (a) Comments Due Date The FAA must receive comments on this AD action by February 6, 2017. E:\FR\FM\22DEP1.SGM 22DEP1 Federal Register / Vol. 81, No. 246 / Thursday, December 22, 2016 / Proposed Rules This AD replaces AD 2014–05–32, Amendment 39–17804 (79 FR 17856, March 31, 2014). (c) Applicability This AD applies to all Pratt & Whitney (PW) PW2037, PW2037D, PW2037M, PW2040, PW2040D, PW2043, PW2143, PW2643, and F117–PW–100 turbofan engines. (d) Subject Joint Aircraft System Component (JASC) Code 72, Turbine/Turboprop Engine. (e) Unsafe Condition This AD was prompted by a rupture of the diffuser-to-high-pressure turbine (HPT) case flange. We are issuing this AD to prevent failure of the diffuser-to-HPT case flange, which could lead to uncontained engine failure and damage to the airplane. Lhorne on DSK30JT082PROD with PROPOSALS (f) Compliance Unless already done, comply with this AD within the compliance times specified. (1) For diffuser case, part number (P/N) 1B7461, serial numbers (S/Ns) DGGUAK1306 and DGGUAK1308, and HPT case, P/N 1B2440, S/N DKLBCS1032: (i) Within 100 flight cycles or 30 days after May 5, 2014, whichever is later, eddy current inspect the diffuser case and the HPT case Mflange. Use PW Service Bulletin (SB) No. PW2000 72–763, Revision No. 1, dated August 30, 2013, to do the inspection. (ii) Reserved. (2) For all diffuser and HPT cases, at the next piece-part opportunity and every piecepart opportunity thereafter, perform a high sensitivity fluorescent-penetrant inspection (FPI) of the entire diffuser case rear flange (M-flange) and bolt holes, and the entire HPT case forward flange (M-flange) and bolt holes. (3) For diffuser cases that have not incorporated PW SB PW2000–72–364 or have incorporated either PW SB PW2000–72–700 or PW2000 Series Engine Manual, Repair-28, Task 72–41–01–300–028 (M-flange replacement), perform initial and repetitive eddy current inspections (ECIs) of the Mflange of the diffuser case in accordance with paragraph (f)(4) of this AD. (4) Use, as applicable, either the Accomplishment Instructions, ‘‘For Engines Installed on the Aircraft,’’ paragraphs 3.(I) through 3.(J), or the Accomplishment Instructions, ‘‘For Engines Removed from the Aircraft,’’ paragraphs 3.(D) through 3.(E), of PW Alert Service Bulletin (ASB) No. PW2000 A72–765, Revision No. 1, dated July 13, 2016, to do the ECI as follows: (i) Perform an initial inspection within the following period, whichever occurs later: (A) Within 5,500 cycles since new or since M-flange replacement, or (B) Within 2,500 cycles since last piecepart FPI inspection, or (C) Within 500 cycles from the effective date of this AD. (ii) If no crack indications are found, reinspect within 2,500 cycles since last ECI or last piece-part FPI inspection, whichever occurs first. 15:19 Dec 21, 2016 Jkt 241001 (iii) If crack indications are found, measure the crack length and determine the re-inspect interval in accordance with: (A) Paragraphs 5.(C) through 5.(D) of PW ASB No. PW2000 A72–765, Revision No. 1, dated July 13, 2016, ‘‘For Engines Installed on the Aircraft’’; or (B) Paragraphs 4.(C) through 4.(D) of PW ASB No. PW2000 A72–765, Revision No. 1, dated July 13, 2016, ‘‘For Engines Removed from the Aircraft.’’ (iv) Remove from service diffuser cases with cracks exceeding 0.170 inches. OFFICE OF THE UNITED STATES TRADE REPRESENTATIVE (g) Definition (b) Affected ADs VerDate Sep<11>2014 93857 SUMMARY: For the purpose of this AD, piece-part opportunity is defined as when the part is completely disassembled. (h) Credit for Previous Actions If you performed an ECI of the diffuser case and HPT case M-flange using the Accomplishment Instructions of PW SB No. PW2000 72–763, Revision No. 1, dated August 13, 2013, or an earlier version, or you performed a high sensitivity FPI of the diffuser case and HPT case at the piece-part opportunity after January 1, 2010, you met the requirements of paragraph (f)(1) of this AD. (i) 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. (j) Related Information (1) For more information about this proposed AD, contact Brian Kierstead, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7772; fax: 781–238–7199; email: brian.kierstead@faa.gov. (2) PW SB No. PW2000 72–763, Revision No. 1, dated August 30, 2013; and PW ASB No. PW2000 A72–765, Revision No. 1, dated July 13, 2016, can be obtained from PW using the contact information in paragraph (j)(3) of this AD. (3) For service information identified in this proposed AD, contact Pratt & Whitney, United Technologies Corporation, 400 Main St., East Hartford, CT 06108; phone: 860– 565–8770; fax: 860–565–4503. (4) You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. Issued in Burlington, Massachusetts, on December 1, 2016. Colleen M. D’Alessandro, Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2016–30114 Filed 12–21–16; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 15 CFR Parts 2004 and 2005 [Docket Number USTR–2016–0027] RIN 0350–AA09 Privacy Act Policies and Procedures Office of the United States Trade Representative. ACTION: Proposed rule. AGENCY: As part of a comprehensive review of agency practices related to the disclosure of records and information, the Office of the United States Trade Representative (USTR) is updating both its systems of records and implementing rule under the Privacy Act of 1974 (Privacy Act). This proposed rule describes how individuals can find out if a USTR system of records contains information about them and, if so, how to access or amend a record. The proposed rule would move the Privacy Act regulation from part 2005 into a new subpart C to part 2004. USTR previously renamed and reorganized part 2004 to include all of the rules governing disclosure of USTR records and information. Elsewhere in this issue of the Federal Register, USTR is publishing a notice concerning updates to its Privacy Act systems of records. DATES: We must receive your written comments on or before January 23, 2017. ADDRESSES: You should submit written comments through the Federal eRulemaking Portal: http:// www.regulations.gov. The docket number for this rulemaking is USTR– 2016–0027. USTR invites comments on all aspects of the proposed rule, and will revise the language as appropriate after taking all timely comments into consideration. Copies of all comments will be available for public viewing at www.regulations.gov upon completion of processing. You can view a submission by entering the docket number USTR–2016–0027 in the search field at http://www.regulations.gov. We will post comments without change and will include any personal information you provide, such as your name, mailing address, email address, and telephone number. FOR FURTHER INFORMATION CONTACT: Janice Kaye, Monique Ricker or Melissa Keppel, Office of General Counsel, Office of the US Trade Representative, Anacostia Naval Annex, Building 410/ Door 123, 250 Murray Lane SW., Washington DC 20509, jkaye@ustr.eop. gov; mricker@ustr.eop.gov; mkeppel@ ustr.eop.gov; 202–395–3150. E:\FR\FM\22DEP1.SGM 22DEP1

Agencies

[Federal Register Volume 81, Number 246 (Thursday, December 22, 2016)]
[Proposed Rules]
[Pages 93855-93857]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-30114]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0740; Directorate Identifier 2013-NE-24-AD]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2014-05-
32, which applies to all Pratt & Whitney (PW) PW2037, PW2037D, PW2037M, 
PW2040, PW2040D, PW2043, PW2143, PW2643, and F117-PW-100 turbofan 
engines. AD 2014-05-32 currently requires one-time eddy current 
inspection (ECI) of affected engines with certain diffuser and HPT 
cases installed. AD 2014-05-32 also requires a fluorescent-penetrant 
inspection (FPI) of the diffuser case rear flange and the HPT case 
front flange. Since we issued AD 2014-05-32, the manufacturer 
determined through analysis that the inspections required by AD 2014-
05-32 are not adequate to maintain safety. This proposed AD would add 
additional repetitive, on-wing ECI inspections. We are proposing this 
AD to correct the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by February 6, 
2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Pratt & 
Whitney, 400 Main St., East Hartford, CT 06108; phone: 860-565-8770; 
fax: 860-565-4503. You may view this service information at the FAA, 
Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. 
For information on the availability of this material at the FAA, call 
781-238-7125.

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-
0740; 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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Brian Kierstead, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 
District Avenue, Burlington, MA 01803; phone: 781-238-7772; fax: 781-
238-7199; email: brian.kierstead@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0740; 
Directorate Identifier 2013-NE-24-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

[[Page 93856]]

Discussion

    On March 6, 2014, we issued AD 2014-05-32, Amendment 39-17804 (79 
FR 17856, March 31, 2014), (``AD 2014-05-32''), for all PW PW2037, 
PW2037D, PW2037M, PW2040, PW2040D, PW2043, PW2143, PW2643, and F117-PW-
100 turbofan engines. AD 2014-05-32 requires a one-time ECI of affected 
engines with certain diffuser and HPT cases installed. AD 2014-05-32 
also requires an FPI of the diffuser case rear flange and HPT case 
front flange. AD 2014-05-32 resulted from a rupture of the diffuser-to-
HPT case flange. We issued AD 2014-05-32 to prevent failure of the 
diffuser-to-HPT case flange, which could lead to uncontained engine 
failure and damage to the airplane.

Actions Since AD 2014-05-32 Was Issued

    Since we issued AD 2014-05-32, the manufacturer identified a 
subpopulation of diffuser cases installed on the affected engines with 
a repaired flange that has a lower fatigue capability. The repaired 
flange cannot be distinguished from non-repaired flanges on diffuser 
cases installed on the affected engines. We determined, therefore, that 
the inspections required by AD 2014-05-32 are not adequate to maintain 
safety. To correct this unsafe condition, we are now proposing 
additional, repetitive ECI inspections.

Related Service Information Under 1 CFR Part 51

    We reviewed PW Service Bulletin No. PW2000 72-763, Revision No. 1, 
dated August 30, 2013; and PW Alert Service Bulletin No. PW2000 A72-
765, Revision No. 1, dated July 13, 2016. This service information 
describes procedures for a one-time ECI inspection of the engine 
diffuser case and the HPT case, and repetitive on-wing ECIs of the 
engine diffuser case assembly, respectively. 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.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would retain the requirements of AD 2014-05-32 
except it would eliminate the Prohibition Statement. We determined that 
this statement is unnecessary for compliance with the AD. In addition, 
this proposed AD would require repetitive, on-wing ECI inspections. 
This proposed AD would also remove the PW2240 and PW2337 engines from 
the applicability section since these engines were removed from PW Type 
Certificate Number E17NE.

Costs of Compliance

    We estimate that this proposed AD will affect 910 engines installed 
on airplanes of U.S. registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
On-wing/module ECI Inspection....  8 work-hours x $85               $0  $680...............  $230,520 per
                                    per hour = $680.                                          inspection cycle.
FPI Inspection...................  3 work-hours x $85               20  $275 per inspection  $250,250 per
                                    per hour = $255.                     cycle.               inspection cycle.
----------------------------------------------------------------------------------------------------------------

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    (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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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 removing Airworthiness Directive (AD) 
2014-05-32, Amendment 39-17804 (79 FR 17856, March 31, 2014), and 
adding the following new AD:

Pratt & Whitney: Docket No. FAA-2013-0740; Directorate Identifier 
2013-NE-24-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by February 6, 
2017.

[[Page 93857]]

(b) Affected ADs

    This AD replaces AD 2014-05-32, Amendment 39-17804 (79 FR 17856, 
March 31, 2014).

(c) Applicability

    This AD applies to all Pratt & Whitney (PW) PW2037, PW2037D, 
PW2037M, PW2040, PW2040D, PW2043, PW2143, PW2643, and F117-PW-100 
turbofan engines.

(d) Subject

    Joint Aircraft System Component (JASC) Code 72, Turbine/
Turboprop Engine.

(e) Unsafe Condition

    This AD was prompted by a rupture of the diffuser-to-high-
pressure turbine (HPT) case flange. We are issuing this AD to 
prevent failure of the diffuser-to-HPT case flange, which could lead 
to uncontained engine failure and damage to the airplane.

(f) Compliance

    Unless already done, comply with this AD within the compliance 
times specified.
    (1) For diffuser case, part number (P/N) 1B7461, serial numbers 
(S/Ns) DGGUAK1306 and DGGUAK1308, and HPT case, P/N 1B2440, S/N 
DKLBCS1032:
    (i) Within 100 flight cycles or 30 days after May 5, 2014, 
whichever is later, eddy current inspect the diffuser case and the 
HPT case M-flange. Use PW Service Bulletin (SB) No. PW2000 72-763, 
Revision No. 1, dated August 30, 2013, to do the inspection.
    (ii) Reserved.
    (2) For all diffuser and HPT cases, at the next piece-part 
opportunity and every piece-part opportunity thereafter, perform a 
high sensitivity fluorescent-penetrant inspection (FPI) of the 
entire diffuser case rear flange (M-flange) and bolt holes, and the 
entire HPT case forward flange (M-flange) and bolt holes.
    (3) For diffuser cases that have not incorporated PW SB PW2000-
72-364 or have incorporated either PW SB PW2000-72-700 or PW2000 
Series Engine Manual, Repair-28, Task 72-41-01-300-028 (M-flange 
replacement), perform initial and repetitive eddy current 
inspections (ECIs) of the M-flange of the diffuser case in 
accordance with paragraph (f)(4) of this AD.
    (4) Use, as applicable, either the Accomplishment Instructions, 
``For Engines Installed on the Aircraft,'' paragraphs 3.(I) through 
3.(J), or the Accomplishment Instructions, ``For Engines Removed 
from the Aircraft,'' paragraphs 3.(D) through 3.(E), of PW Alert 
Service Bulletin (ASB) No. PW2000 A72-765, Revision No. 1, dated 
July 13, 2016, to do the ECI as follows:
    (i) Perform an initial inspection within the following period, 
whichever occurs later:
    (A) Within 5,500 cycles since new or since M-flange replacement, 
or
    (B) Within 2,500 cycles since last piece-part FPI inspection, or
    (C) Within 500 cycles from the effective date of this AD.
    (ii) If no crack indications are found, re-inspect within 2,500 
cycles since last ECI or last piece-part FPI inspection, whichever 
occurs first.
    (iii) If crack indications are found, measure the crack length 
and determine the re-inspect interval in accordance with:
    (A) Paragraphs 5.(C) through 5.(D) of PW ASB No. PW2000 A72-765, 
Revision No. 1, dated July 13, 2016, ``For Engines Installed on the 
Aircraft''; or
    (B) Paragraphs 4.(C) through 4.(D) of PW ASB No. PW2000 A72-765, 
Revision No. 1, dated July 13, 2016, ``For Engines Removed from the 
Aircraft.''
    (iv) Remove from service diffuser cases with cracks exceeding 
0.170 inches.

(g) Definition

    For the purpose of this AD, piece-part opportunity is defined as 
when the part is completely disassembled.

(h) Credit for Previous Actions

    If you performed an ECI of the diffuser case and HPT case M-
flange using the Accomplishment Instructions of PW SB No. PW2000 72-
763, Revision No. 1, dated August 13, 2013, or an earlier version, 
or you performed a high sensitivity FPI of the diffuser case and HPT 
case at the piece-part opportunity after January 1, 2010, you met 
the requirements of paragraph (f)(1) of this AD.

(i) 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.

(j) Related Information

    (1) For more information about this proposed AD, contact Brian 
Kierstead, Aerospace Engineer, Engine Certification Office, FAA, 
Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 
01803; phone: 781-238-7772; fax: 781-238-7199; email: 
brian.kierstead@faa.gov.
    (2) PW SB No. PW2000 72-763, Revision No. 1, dated August 30, 
2013; and PW ASB No. PW2000 A72-765, Revision No. 1, dated July 13, 
2016, can be obtained from PW using the contact information in 
paragraph (j)(3) of this AD.
    (3) For service information identified in this proposed AD, 
contact Pratt & Whitney, United Technologies Corporation, 400 Main 
St., East Hartford, CT 06108; phone: 860-565-8770; fax: 860-565-
4503.
    (4) You may view this service information at the FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA. For 
information on the availability of this material at the FAA, call 
781-238-7125.

    Issued in Burlington, Massachusetts, on December 1, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-30114 Filed 12-21-16; 8:45 am]
 BILLING CODE 4910-13-P