Airworthiness Directives; Pratt & Whitney Turbofan Engines, 64419-64421 [2013-25459]

Download as PDF Federal Register / Vol. 78, No. 209 / Tuesday, October 29, 2013 / Proposed Rules legitimate domestic objective, such as the protection of safety, and does not operate in a manner that excludes imports that meet this objective. The statute also requires consideration of international standards and, where appropriate, that they be the basis for U.S. standards. The FAA assessed the potential effect of the AD and determined that because it addresses an immediate safety issue the AD is not considered an unnecessary obstacle to the foreign commerce of the United States. Unfunded Mandates Assessment Title II of the Unfunded Mandates Reform Act of 1995 (Pub. L. 104–4) requires each Federal agency to prepare a written statement assessing the effects of any Federal mandate in a proposed or final agency rule that may result in an expenditure of $100 million or more (in 1995 dollars) in any one year by State, local, and tribal governments, in the aggregate, or by the private sector; such a mandate is deemed to be a ‘‘significant regulatory action.’’ The FAA currently uses an inflation-adjusted value of $143.1 million in lieu of $100 million. The AD does not contain such a mandate; therefore, the requirements of Title II of the Act do not apply. mstockstill on DSK4VPTVN1PROD with PROPOSALS Comments Invited We invite you to send any written relevant data, views, or arguments about this IRFA. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2013–0393; Directorate Identifier 2012– CE–025–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the IRFA as related to the AD action. The most helpful comments will reference a specific portion of the IRFA or related rulemaking document, explain the reason for any recommended change, and include supporting data. 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 the AD. Issued in Kansas City, Missouri, on October 22, 2013. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–25526 Filed 10–28–13; 8:45 am] BILLING CODE 4910–13–P VerDate Mar<15>2010 16:26 Oct 28, 2013 Jkt 232001 64419 DEPARTMENT OF TRANSPORTATION Examining the AD Docket Federal Aviation Administration You may examine the AD docket on the Internet at http:// www.regulations.gov; 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: Robert Morlath, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7154; fax: 781–238– 7199; email: robert.c.morlath@faa.gov. SUPPLEMENTARY INFORMATION: 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 adopt a new airworthiness directive (AD) for all Pratt & Whitney (PW) PW2037, PW2037D, PW2037M, PW2040, PW2040D, PW2043, PW2146, PW2240, PW2337, PW2643, and F117–PW–100 turbofan engines. This proposed AD was prompted by a rupture of the diffuserto-high-pressure turbine (HPT) case flange. This proposed AD would require a one-time eddy current inspection (ECI) of affected engines with certain diffuser and HPT cases installed. This AD also proposes to require a fluorescentpenetrant inspection (FPI) of the diffuser case rear flange and HPT case front flange. We are proposing this AD to prevent failure of the diffuser-to-HPT case flange, which could lead to uncontained engine failure and damage to the airplane. DATES: We must receive comments on this proposed AD by December 30, 2013. SUMMARY: 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 proposed AD, 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, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. ADDRESSES: PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. 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. Discussion We received a report of an engine event in October 2011 that resulted in a rupture of the engine diffuser-to-HPT case flange. The rupture caused the engine cowl doors to break open, which resulted in damage to the underside of the airplane’s wing. Subsequent investigation revealed that the root cause of this rupture was a crack that originated in HPT case M-flange boltholes (the forward flange of the HPT case that mates with the rear outer flange of the diffuser case). This condition, if not corrected, could result in failure of the diffuser-to-HPT case flange, which may cause an uncontained engine failure and damage to the airplane. E:\FR\FM\29OCP1.SGM 29OCP1 64420 Federal Register / Vol. 78, No. 209 / Tuesday, October 29, 2013 / Proposed Rules Relevant Service Information We reviewed PW Service Bulletin (SB) No. PW2000 72–763, Revision 1, dated August 30, 2013, and PW PW2000 Series Engine Manual part number 1A6231. The SB describes procedures for inspecting the flanges of the HPT case and the diffuser case. 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 require an on-wing ECI of the diffuser case and HPT case flanges. This proposed AD would also require an FPI of all engine diffuser cases and all HPT cases. Regulatory Findings Differences Between the Proposed AD and the Service Information PW SB No. PW2000 72–763, Revision 1, dated August 30, 2013, requires that operators complete an on-wing ECI by August 31, 2013. We are proposing that the ECI be performed within 100 flight cycles or 30 days after the effective date of this AD, whichever is earlier. Costs of Compliance We estimate that this proposed AD will affect 638 engines installed on airplanes of U.S. registry. Of the 638 engines, we estimate that about 58 engines will be subject to ECI and all engines will be subject to the FPI. We also estimate that it would take about 5 hours to perform the ECI and 3 hours to perform the FPI required by this proposed AD. Materials cost for the FPI will be about $20 per engine. The average labor rate is $85 per hour. Based on these figures, we estimate the total cost of this proposed AD to U.S. operators to be $200,100. 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 proposed 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. 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): ■ Pratt & Whitney: Docket No. FAA–2013– 0740; Directorate Identifier 2013–NE– 24–AD. (a) Comments Due Date We must receive comments by December 30, 2013. (b) Affected ADs We 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 this 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: None. (c) Applicability This AD applies to all Pratt & Whitney (PW) PW2037, PW2037D, PW2037M, PW2040, PW2040D, PW2043, PW2146, PW2240, PW2337, PW2643, and F117–PW– 100 turbofan engines. (d) 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. (e) Compliance Unless already done, comply with this AD within the compliance times specified. (1) For diffuser and HPT cases identified by serial number (S/N) in Table 1 to paragraph (e) of this AD: (i) Within 100 flight cycles or 30 days after the effective date of this AD, whichever is earlier, eddy current inspect the diffuser case and the HPT case M-flange. (ii) For engines installed on the aircraft, use paragraphs 3.G. through 3.L. in the ‘‘For Engines Installed on the Aircraft’’ section of the Accomplishment Instructions of PW Service Bulletin (SB) No. PW2000 72–763, Revision 1, dated August 30, 2013, to perform the inspection. (iii) For engines removed from the aircraft, use paragraphs 3.B. through 3.G. in the ‘‘For Engines Removed From the Aircraft’’ section of the Accomplishment Instructions of PW Service Bulletin (SB) No. PW2000 72–763, Revision 1, dated August 30, 2013, to perform the inspection. mstockstill on DSK4VPTVN1PROD with PROPOSALS TABLE 1 TO PARAGRAPH (e)—DIFFUSER AND HPT CASE P/NS AND SERIAL NUMBERS Diffuser case part No. (P/N) Diffuser case S/N 1B7407–001 ................................... 1B7407 ........................................... 1B7407 ........................................... 1B7407 ........................................... 1B7407–001 ................................... 1B3055–001 ................................... 1B7461 ........................................... DGUSAA0114 ............................... WE2452 ........................................ DGUSAA0097 ............................... DGUSAA0670 ............................... DGUSAA0622 ............................... DGUSAA0247 ............................... DGGUAK1308 .............................. VerDate Mar<15>2010 16:26 Oct 28, 2013 Jkt 232001 PO 00000 Frm 00013 HPT case P/N Fmt 4702 1A9030 1B2440 1B2440 1B2440 1B2440 1B2440 1B2440 Sfmt 4702 HPT case S/N ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... E:\FR\FM\29OCP1.SGM RM6300 DKLBB40125 DKLBCH3429 DKLBCS1032 DKLBC00030 DKLBC07691 DKLBDB5108 29OCP1 Federal Register / Vol. 78, No. 209 / Tuesday, October 29, 2013 / Proposed Rules 64421 TABLE 1 TO PARAGRAPH (e)—DIFFUSER AND HPT CASE P/NS AND SERIAL NUMBERS—Continued Diffuser case part No. (P/N) Diffuser case S/N 1B7461 ........................................... 1B7461 ........................................... 1B7477 ........................................... 1B7477 ........................................... 1B7477 ........................................... 1B7477 ........................................... 1B4091–001 ................................... 1B4091–002 ................................... 1B4091–005 ................................... 1B7461 ........................................... 1B7477 ........................................... 1B7407 ........................................... 1B7407 ........................................... 1B7477 ........................................... 1B7477 ........................................... 1B7407–001 ................................... 1B7407 ........................................... DGGUAK1306 .............................. DGGUAK1356 .............................. DGGUAL1445 ............................... DGGUAL1492 ............................... DGGUAL1501 ............................... DGGUAL1597 ............................... RT6356 ......................................... ST2044 ......................................... PF3203 ......................................... DGGUAK1377 .............................. DGGUAL1548 ............................... DGGUAK0189 .............................. DGUSAA0443 ............................... DGGUAL1441 ............................... DGGUAL1560 ............................... DGUSAA0329 ............................... DGUSAA0334 ............................... (2) For all diffuser and HPT cases: (i) At the next piece part exposure and every piece part exposure thereafter, perform a high sensitivity fluorescent-penetrant inspection (FPI) of the entire diffuser case rear flange (M-flange) and bolt holes. (ii) At the next piece part exposure and every piece part exposure thereafter, perform a high sensitivity FPI of the entire HPT case forward flange (M-flange) and bolt holes. (f) Prohibition Statement After the effective date of this AD, do not install any engine with a diffuser or HPT case with serial number listed in Table 1 to paragraph (e) of this AD, onto any aircraft, that was not inspected per paragraph (e) of this AD. mstockstill on DSK4VPTVN1PROD with PROPOSALS (g) Credit for Previous Actions If you performed an eddy current inspection of the diffuser case and HPT case M-flange using paragraphs 3.G. through 3.L. in the ‘‘For Engines Installed on the Aircraft’’ section or paragraphs 3.B. through 3.G. in the ‘‘For Engines Removed from the Aircraft’’ section of the Accomplishment Instructions of PW SB PW2000 72–763, dated March 22, 2013, you met the requirements of paragraph (e)(1) of this AD. (h) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. HPT case P/N 1B2440 1B2440 1A9030 1A9030 1A9030 1A9030 1B2440 1A9030 1A9030 1B2440 1B2440 1B2440 1B2440 1B2440 1A9030 1B2440 1B2440 1B2440 1B2440 1B2440 1B2440 1B2440 1B2440 1B2440 1B2440 1B2440 1B2440 Issued in Burlington, Massachusetts, on October 7, 2013. Colleen M. D’Alessandro, Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2013–25459 Filed 10–28–13; 8:45 am] (i) Related Information (1) For more information about this AD, contact Robert Morlath, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England VerDate Mar<15>2010 16:26 Oct 28, 2013 Jkt 232001 ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... Executive Park, Burlington, MA 01803; phone: 781–238–7154; fax: 781–238–7199; email: robert.c.morlath@faa.gov. (2) Pratt & Whitney Engine Manual, part number 1A6231, Chapter 72–41–00, Inspection/Check-02, (Task 72–41–00–230– 002) and Chapter 72–52–00, Inspection/ Check-02 (Task 72–52–00–230–000), which are not incorporated by reference in this AD, can be obtained from Pratt & Whitney, using the contact information in paragraph (i)(3) of this AD. (3) For service information identified in this 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, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. BILLING CODE 4910–13–P PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 HPT case S/N DKLBDB5153 DKLBDU3358 RM6353 PD3348 PD3280 ND5644 DKLBBP0225 DKLBBR3621 PD3290 WG6904 WV1807 WX2639 WZ4057 WX2664 RM6359 DKLBCM8956 DKLBCM0214 DKLBDB5069 DKLBB02548 DKLBDC7336 DKLBDU3372 WM6913 DKLBBF6606 DKLBBB2861 DKLBCT1660 DKLBB94641 DKLBBX8092 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0766; Directorate Identifier 2013–NE–26–AD] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney Canada Corp. Turboprop Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Pratt & Whitney Canada Corp. (P&WC) PT6A– 114 and PT6A–114A turboprop engines. This proposed AD was prompted by several incidents of compressor turbine (CT) blade failure, including two fatalities, resulting in power loss and inflight shutdown (IFSD) of the engine. This proposed AD would require initial and repetitive borescope inspections (BSIs) of CT blades, and the removal from service of blades that fail inspection. We are proposing this AD to prevent failure of CT blades, which could lead to damage to the engine or to the airplane. DATES: We must receive comments on this proposed AD by December 30, 2013. SUMMARY: E:\FR\FM\29OCP1.SGM 29OCP1

Agencies

[Federal Register Volume 78, Number 209 (Tuesday, October 29, 2013)]
[Proposed Rules]
[Pages 64419-64421]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-25459]


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

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 adopt a new airworthiness directive (AD) for all 
Pratt & Whitney (PW) PW2037, PW2037D, PW2037M, PW2040, PW2040D, PW2043, 
PW2146, PW2240, PW2337, PW2643, and F117-PW-100 turbofan engines. This 
proposed AD was prompted by a rupture of the diffuser-to-high-pressure 
turbine (HPT) case flange. This proposed AD would require a one-time 
eddy current inspection (ECI) of affected engines with certain diffuser 
and HPT cases installed. This AD also proposes to require a 
fluorescent-penetrant inspection (FPI) of the diffuser case rear flange 
and HPT case front flange. We are proposing this AD to prevent failure 
of the diffuser-to-HPT case flange, which could lead to uncontained 
engine failure and damage to the airplane.

DATES: We must receive comments on this proposed AD by December 30, 
2013.

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 proposed AD, 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, 12 New England Executive Park, 
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; 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: Robert Morlath, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: 781-238-7154; 
fax: 781-238-7199; email: robert.c.morlath@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. 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.

Discussion

    We received a report of an engine event in October 2011 that 
resulted in a rupture of the engine diffuser-to-HPT case flange. The 
rupture caused the engine cowl doors to break open, which resulted in 
damage to the underside of the airplane's wing. Subsequent 
investigation revealed that the root cause of this rupture was a crack 
that originated in HPT case M-flange boltholes (the forward flange of 
the HPT case that mates with the rear outer flange of the diffuser 
case). This condition, if not corrected, could result in failure of the 
diffuser-to-HPT case flange, which may cause an uncontained engine 
failure and damage to the airplane.

[[Page 64420]]

Relevant Service Information

    We reviewed PW Service Bulletin (SB) No. PW2000 72-763, Revision 1, 
dated August 30, 2013, and PW PW2000 Series Engine Manual part number 
1A6231. The SB describes procedures for inspecting the flanges of the 
HPT case and the diffuser case.

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 require an on-wing ECI of the diffuser case 
and HPT case flanges. This proposed AD would also require an FPI of all 
engine diffuser cases and all HPT cases.

Differences Between the Proposed AD and the Service Information

    PW SB No. PW2000 72-763, Revision 1, dated August 30, 2013, 
requires that operators complete an on-wing ECI by August 31, 2013. We 
are proposing that the ECI be performed within 100 flight cycles or 30 
days after the effective date of this AD, whichever is earlier.

Costs of Compliance

    We estimate that this proposed AD will affect 638 engines installed 
on airplanes of U.S. registry. Of the 638 engines, we estimate that 
about 58 engines will be subject to ECI and all engines will be subject 
to the FPI. We also estimate that it would take about 5 hours to 
perform the ECI and 3 hours to perform the FPI required by this 
proposed AD. Materials cost for the FPI will be about $20 per engine. 
The average labor rate is $85 per hour. Based on these figures, we 
estimate the total cost of this proposed AD to U.S. operators to be 
$200,100.

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 proposed 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 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 this 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 adding the following new airworthiness 
directive (AD):

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

(a) Comments Due Date

    We must receive comments by December 30, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Pratt & Whitney (PW) PW2037, PW2037D, 
PW2037M, PW2040, PW2040D, PW2043, PW2146, PW2240, PW2337, PW2643, 
and F117-PW-100 turbofan engines.

(d) 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.

(e) Compliance

    Unless already done, comply with this AD within the compliance 
times specified.
    (1) For diffuser and HPT cases identified by serial number (S/N) 
in Table 1 to paragraph (e) of this AD:
    (i) Within 100 flight cycles or 30 days after the effective date 
of this AD, whichever is earlier, eddy current inspect the diffuser 
case and the HPT case M-flange.
    (ii) For engines installed on the aircraft, use paragraphs 3.G. 
through 3.L. in the ``For Engines Installed on the Aircraft'' 
section of the Accomplishment Instructions of PW Service Bulletin 
(SB) No. PW2000 72-763, Revision 1, dated August 30, 2013, to 
perform the inspection.
    (iii) For engines removed from the aircraft, use paragraphs 3.B. 
through 3.G. in the ``For Engines Removed From the Aircraft'' 
section of the Accomplishment Instructions of PW Service Bulletin 
(SB) No. PW2000 72-763, Revision 1, dated August 30, 2013, to 
perform the inspection.

                     Table 1 to Paragraph (e)--Diffuser and HPT Case P/Ns and Serial Numbers
----------------------------------------------------------------------------------------------------------------
     Diffuser case part No. (P/N)         Diffuser case S/N           HPT case P/N             HPT case S/N
----------------------------------------------------------------------------------------------------------------
1B7407-001...........................  DGUSAA0114.............  1A9030.................  RM6300
1B7407...............................  WE2452.................  1B2440.................  DKLBB40125
1B7407...............................  DGUSAA0097.............  1B2440.................  DKLBCH3429
1B7407...............................  DGUSAA0670.............  1B2440.................  DKLBCS1032
1B7407-001...........................  DGUSAA0622.............  1B2440.................  DKLBC00030
1B3055-001...........................  DGUSAA0247.............  1B2440.................  DKLBC07691
1B7461...............................  DGGUAK1308.............  1B2440.................  DKLBDB5108

[[Page 64421]]

 
1B7461...............................  DGGUAK1306.............  1B2440.................  DKLBDB5153
1B7461...............................  DGGUAK1356.............  1B2440.................  DKLBDU3358
1B7477...............................  DGGUAL1445.............  1A9030.................  RM6353
1B7477...............................  DGGUAL1492.............  1A9030.................  PD3348
1B7477...............................  DGGUAL1501.............  1A9030.................  PD3280
1B7477...............................  DGGUAL1597.............  1A9030.................  ND5644
1B4091-001...........................  RT6356.................  1B2440.................  DKLBBP0225
1B4091-002...........................  ST2044.................  1A9030.................  DKLBBR3621
1B4091-005...........................  PF3203.................  1A9030.................  PD3290
1B7461...............................  DGGUAK1377.............  1B2440.................  WG6904
1B7477...............................  DGGUAL1548.............  1B2440.................  WV1807
1B7407...............................  DGGUAK0189.............  1B2440.................  WX2639
1B7407...............................  DGUSAA0443.............  1B2440.................  WZ4057
1B7477...............................  DGGUAL1441.............  1B2440.................  WX2664
1B7477...............................  DGGUAL1560.............  1A9030.................  RM6359
1B7407-001...........................  DGUSAA0329.............  1B2440.................  DKLBCM8956
1B7407...............................  DGUSAA0334.............  1B2440.................  DKLBCM0214
                                                                1B2440.................  DKLBDB5069
                                                                1B2440.................  DKLBB02548
                                                                1B2440.................  DKLBDC7336
                                                                1B2440.................  DKLBDU3372
                                                                1B2440.................  WM6913
                                                                1B2440.................  DKLBBF6606
                                                                1B2440.................  DKLBBB2861
                                                                1B2440.................  DKLBCT1660
                                                                1B2440.................  DKLBB94641
                                                                1B2440.................  DKLBBX8092
----------------------------------------------------------------------------------------------------------------

    (2) For all diffuser and HPT cases:
    (i) At the next piece part exposure and every piece part 
exposure thereafter, perform a high sensitivity fluorescent-
penetrant inspection (FPI) of the entire diffuser case rear flange 
(M-flange) and bolt holes.
    (ii) At the next piece part exposure and every piece part 
exposure thereafter, perform a high sensitivity FPI of the entire 
HPT case forward flange (M-flange) and bolt holes.

(f) Prohibition Statement

    After the effective date of this AD, do not install any engine 
with a diffuser or HPT case with serial number listed in Table 1 to 
paragraph (e) of this AD, onto any aircraft, that was not inspected 
per paragraph (e) of this AD.

(g) Credit for Previous Actions

    If you performed an eddy current inspection of the diffuser case 
and HPT case M-flange using paragraphs 3.G. through 3.L. in the 
``For Engines Installed on the Aircraft'' section or paragraphs 3.B. 
through 3.G. in the ``For Engines Removed from the Aircraft'' 
section of the Accomplishment Instructions of PW SB PW2000 72-763, 
dated March 22, 2013, you met the requirements of paragraph (e)(1) 
of this AD.

(h) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, may approve AMOCs 
for this AD. Use the procedures found in 14 CFR 39.19 to make your 
request.

(i) Related Information

    (1) For more information about this AD, contact Robert Morlath, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7154; fax: 781-238-7199; email: 
robert.c.morlath@faa.gov.
    (2) Pratt & Whitney Engine Manual, part number 1A6231, Chapter 
72-41-00, Inspection/Check-02, (Task 72-41-00-230-002) and Chapter 
72-52-00, Inspection/Check-02 (Task 72-52-00-230-000), which are not 
incorporated by reference in this AD, can be obtained from Pratt & 
Whitney, using the contact information in paragraph (i)(3) of this 
AD.
    (3) For service information identified in this 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, 12 New England Executive Park, Burlington, 
MA. For information on the availability of this material at the FAA, 
call 781-238-7125.

    Issued in Burlington, Massachusetts, on October 7, 2013.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2013-25459 Filed 10-28-13; 8:45 am]
BILLING CODE 4910-13-P