Airworthiness Directives; Pratt & Whitney Division Turbofan Engines, 74358-74360 [2016-25799]

Download as PDF Lhorne on DSK30JT082PROD with PROPOSALS 74358 Federal Register / Vol. 81, No. 207 / Wednesday, October 26, 2016 / Proposed Rules been embodied: Modify the outer wing, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–57–0203, Revision 04, dated February 18, 2015. (x) For airplanes on which Airbus Mandatory Service Bulletin A300–57–0258, dated September 30, 2014, has not been embodied: Modify the wing structure and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–57–0258, dated September 30, 2014. (xi) For airplanes on which Airbus Mandatory Service Bulletin A300–57–0259, dated September 30, 2014, has not been embodied: Modify the wing structure, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–57–0259, dated September 30, 2014. (2) If it is determined that Airbus Service Bulletin A300–53–0374, Revision 04, dated July 5, 2013 (mod 12794) has not been embodied: Within the compliance time specified in paragraphs (h)(2)(i), (h)(2)(ii), (h)(2)(iii), and (h)(2)(iv) of this AD, as applicable, modify the rear fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 53–0374, Revision 04, dated July 5, 2013, except as required by paragraph (i) of this AD. (i) For Model A300 B2 and A300 B4–100 airplanes, fuselage frame (FR) 55: Within 31,300 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later. (ii) For Model A300 B2 and A300 B4–100 airplanes, FR 58: Within 49,700 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later. (iii) For Model A300 B4–200 airplanes, FR 55: Within 33,600 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later. (iv) For Model A300 B4–200 airplanes, FR 58: Within 55,800 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later. (3) If it is determined that Airbus Service Bulletin A300–53–0373, Revision 03, dated September 1, 2010 (mod 12796) has not been embodied: Within the compliance time specified in paragraphs (h)(3)(i), (h)(3)(ii), and (h)(3)(iii) of this AD, as applicable, modify the rear fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–0373, Revision 03, dated September 1, 2010, except as required by paragraph (i) of this AD. (i) For Model A300 B2 airplanes: Within 42,700 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later. (ii) For Model A300 B4–100 airplanes: Within 41,700 flight cycles since first flight of the airplane, or within 4 months after the VerDate Sep<11>2014 15:05 Oct 25, 2016 Jkt 241001 effective date of this AD, whichever occurs later. (iii) For Model A300 B4–200 airplanes: Within 47,900 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later. (i) Service Information Exception Where any service information identified in table 1 to paragraphs (g), (h), and (i) of this AD specifies to contact the manufacturer for instructions or solutions, before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). (j) Terminating Action for Certain Requirements in AD 2004–23–20 Accomplishing the modification required by paragraph (h)(1)(iii) of this AD terminates the modification required by paragraph (i) of AD 2004–23–20 for that airplane only. (k) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–2125. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or PO 00000 Frm 00044 Fmt 4702 Sfmt 4702 changes to procedures or tests identified as RC require approval of an AMOC. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2015–0173, dated August 24, 2015, for related information. You may examine the MCAI on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016–9298. (2) For service information identified in this final rule, contact Airbus SAS, Airworthiness Office–EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: continued.airworthiness-wb.external@ airbus.com; Internet http://www.airbus.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on October 13, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–25662 Filed 10–25–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–8836; Directorate Identifier 2016–NE–17–AD] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney Division 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 Division (PW) PW4074, PW4074D, PW4077, PW4077D, PW4084, PW4084D, PW4090, and PW4090–3 turbofan engines. This proposed AD was prompted by an uncontained failure of a high-pressure turbine (HPT) hub during takeoff. This proposed AD would require an inspection to measure the surface condition of the aft side web/rim fillet of HPT 1st stage hubs and removal from service of hubs that fail inspection. We are proposing this AD to prevent failure of the HPT 1st stage hub, uncontained hub release, damage to the engine, and damage to the airplane. DATES: We must receive comments on this proposed AD by December 12, 2016. SUMMARY: E:\FR\FM\26OCP1.SGM 26OCP1 Federal Register / Vol. 81, No. 207 / Wednesday, October 26, 2016 / Proposed Rules 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 Division, 400 Main St., East Hartford, CT 06118; phone: 800–565–0140; fax: 860–565–5442. 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. ADDRESSES: 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–2016– 8836; 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: JoAnn Theriault, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7105; fax: 781–238–7199; email: jo-ann.theriault@faa.gov. SUPPLEMENTARY INFORMATION: Lhorne on DSK30JT082PROD with PROPOSALS 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– 2016–8836; Directorate Identifier 2016– NE–07–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 VerDate Sep<11>2014 15:05 Oct 25, 2016 Jkt 241001 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 uncontained failure of an HPT hub during takeoff. The root cause of the event is a machining anomaly (cutter mismatch) in the aft web/rim fillet area of the HPT 1st stage hub. The machining mismatch raises the stress and significantly reduces the life of the hub. The defect was introduced when the part was originally manufactured. This condition, if not corrected, could result in failure of the HPT 1st stage hub, uncontained hub release, damage to the engine, and damage to the airplane. Related Service Information Under 1 CFR Part 51 We reviewed PW Service Bulletin (SB) PW4G–112–72–342, dated September 23, 2016. This PW SB provides guidance on performing the HPT 1st stage hub web/rim fillet replication inspection and measurement for the affected HPT hubs. 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 require an inspection to measure the surface condition of the aft side web/rim fillet of HPT 1st stage hubs and removal from service of hubs that fail inspection. We estimate that this proposed AD affects 119 engines installed on airplanes of U.S. registry. We also estimate that it would take about 1 hour per engine to do the inspection. The average labor rate is $85 per hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $10,115. Frm 00045 Fmt 4702 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 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 Costs of Compliance PO 00000 74359 Sfmt 4702 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: ■ E:\FR\FM\26OCP1.SGM 26OCP1 74360 Federal Register / Vol. 81, No. 207 / Wednesday, October 26, 2016 / Proposed Rules 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 Division: Docket No. FAA– 2016–8836; Directorate Identifier 2016– NE–17–AD. (a) Comments Due Date We must receive comments by December 12, 2016. (b) Affected ADs None. (c) Applicability This AD applies to all Pratt & Whitney Division (PW) PW4074, PW4074D, PW4077, PW4077D, PW4084, PW4084D, PW4090, and PW4090–3 turbofan engines. (d) Unsafe Condition This AD was prompted by an uncontained failure of a high-pressure turbine (HPT) hub during takeoff. We are issuing this AD to prevent failure of the HPT 1st stage hub, uncontained hub release, damage to the engine, and damage to the airplane. (e) Compliance Comply with this AD within the compliance times specified, unless already done. (1) At the next engine shop visit after the effective date of this AD, perform the HPT 1st stage hub web/rim fillet replication inspection and measurement using the Accomplishment Instructions, Part A, paragraphs 2.A. and 2.B.(1) to 2.B.(4) or Part B, paragraphs 1.A. and 1.B.(1) to 1.B.(4), of PW Service Bulletin (SB) PW4G–112–72– 342, dated September 23, 2016. (2) If the hub fails inspection, remove the hub from service before further flight and replace with a part eligible for installation. (f) Definition For the purpose of this AD, an ‘‘engine shop visit’’ is the induction of an engine into the shop for maintenance involving the separation of any major mating flange, except that the separation of engine flanges solely for the purposes of transportation without subsequent maintenance does not constitute an engine shop visit. Lhorne on DSK30JT082PROD with PROPOSALS (g) Installation Prohibition After the effective date of this AD, do not install or re-install into any engine any HPT 1st stage hub that has not been inspected and passed the inspection required by paragraph (e) 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. You may email your request to: ANE-AD-AMOC@faa.gov. (i) Related Information (1) For more information about this AD, contact Jo-Ann Theriault, Aerospace VerDate Sep<11>2014 15:05 Oct 25, 2016 Jkt 241001 Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781– 238–7105; fax: 781–238–7199; email: joann.theriault@faa.gov. (2) PW SB PW4G–112–72–342, dated September 23, 2016, can be obtained from PW using the contact information in paragraph (i)(3) of this AD. (3) For service information identified in this AD, contact Pratt & Whitney Division, 400 Main St., East Hartford, CT 06118; phone: 800–565–0140; fax: 860–565–5442. (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. Federal Aviation Administration 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 Bombardier, Inc., QSeries Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375–4000; fax 416–375–4539; email thd.qseries@ aero.bombardier.com; Internet http:// www.bombardier.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. 14 CFR Part 39 Examining the AD Docket Issued in Burlington, Massachusetts, on October 19, 2016. Colleen M. D’Alessandro, Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2016–25799 Filed 10–25–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION [Docket No. FAA–2016–9299; Directorate Identifier 2016–NM–119–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Bombardier Inc. Model DHC–8–102, –103, and –106 airplanes; DHC–8–200 series airplanes; and Model DHC–8–300 series airplanes. This proposed AD was prompted by reports of incorrect installation of the auto-ignition system due to crossed wires at one of the splices in the auto-relight system. This proposed AD would require inspecting the auto-ignition system for correct wiring, and doing corrective actions if necessary. We are proposing this AD to detect and correct incorrect wiring of the auto-ignition system, which could result in inability to restart the engine in flight and consequent reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by December 12, 2016. SUMMARY: You may send comments, using the procedures found in 14 CFR ADDRESSES: PO 00000 Frm 00046 Fmt 4702 Sfmt 4702 You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9299; 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 Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Morton Lee, Aerospace Engineer, Propulsion and Services Branch, ANE– 173, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7355; fax 516–794–5531. 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–2016–9299; Directorate Identifier 2016–NM–119–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy E:\FR\FM\26OCP1.SGM 26OCP1

Agencies

[Federal Register Volume 81, Number 207 (Wednesday, October 26, 2016)]
[Proposed Rules]
[Pages 74358-74360]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-25799]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-8836; Directorate Identifier 2016-NE-17-AD]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney Division 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 Division (PW) PW4074, PW4074D, PW4077, PW4077D, PW4084, 
PW4084D, PW4090, and PW4090-3 turbofan engines. This proposed AD was 
prompted by an uncontained failure of a high-pressure turbine (HPT) hub 
during takeoff. This proposed AD would require an inspection to measure 
the surface condition of the aft side web/rim fillet of HPT 1st stage 
hubs and removal from service of hubs that fail inspection. We are 
proposing this AD to prevent failure of the HPT 1st stage hub, 
uncontained hub release, damage to the engine, and damage to the 
airplane.

DATES: We must receive comments on this proposed AD by December 12, 
2016.

[[Page 74359]]


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 Division, 400 Main St., East Hartford, CT 06118; phone: 800-
565-0140; fax: 860-565-5442. 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-2016-
8836; 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: Jo-Ann Theriault, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 
District Avenue, Burlington, MA 01803; phone: 781-238-7105; fax: 781-
238-7199; email: jo-ann.theriault@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-2016-8836; 
Directorate Identifier 2016-NE-07-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 uncontained failure of an HPT hub during 
takeoff. The root cause of the event is a machining anomaly (cutter 
mismatch) in the aft web/rim fillet area of the HPT 1st stage hub. The 
machining mismatch raises the stress and significantly reduces the life 
of the hub. The defect was introduced when the part was originally 
manufactured. This condition, if not corrected, could result in failure 
of the HPT 1st stage hub, uncontained hub release, damage to the 
engine, and damage to the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed PW Service Bulletin (SB) PW4G-112-72-342, dated 
September 23, 2016. This PW SB provides guidance on performing the HPT 
1st stage hub web/rim fillet replication inspection and measurement for 
the affected HPT hubs. 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 require an inspection to measure the surface 
condition of the aft side web/rim fillet of HPT 1st stage hubs and 
removal from service of hubs that fail inspection.

Costs of Compliance

    We estimate that this proposed AD affects 119 engines installed on 
airplanes of U.S. registry. We also estimate that it would take about 1 
hour per engine to do the inspection. The average labor rate is $85 per 
hour. Based on these figures, we estimate the cost of this proposed AD 
on U.S. operators to be $10,115.

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 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:


[[Page 74360]]


    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 Division: Docket No. FAA-2016-8836; Directorate 
Identifier 2016-NE-17-AD.

(a) Comments Due Date

    We must receive comments by December 12, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Pratt & Whitney Division (PW) PW4074, 
PW4074D, PW4077, PW4077D, PW4084, PW4084D, PW4090, and PW4090-3 
turbofan engines.

(d) Unsafe Condition

    This AD was prompted by an uncontained failure of a high-
pressure turbine (HPT) hub during takeoff. We are issuing this AD to 
prevent failure of the HPT 1st stage hub, uncontained hub release, 
damage to the engine, and damage to the airplane.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) At the next engine shop visit after the effective date of 
this AD, perform the HPT 1st stage hub web/rim fillet replication 
inspection and measurement using the Accomplishment Instructions, 
Part A, paragraphs 2.A. and 2.B.(1) to 2.B.(4) or Part B, paragraphs 
1.A. and 1.B.(1) to 1.B.(4), of PW Service Bulletin (SB) PW4G-112-
72-342, dated September 23, 2016.
    (2) If the hub fails inspection, remove the hub from service 
before further flight and replace with a part eligible for 
installation.

(f) Definition

    For the purpose of this AD, an ``engine shop visit'' is the 
induction of an engine into the shop for maintenance involving the 
separation of any major mating flange, except that the separation of 
engine flanges solely for the purposes of transportation without 
subsequent maintenance does not constitute an engine shop visit.

(g) Installation Prohibition

    After the effective date of this AD, do not install or re-
install into any engine any HPT 1st stage hub that has not been 
inspected and passed the inspection required by paragraph (e) 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. You may email your request to: ANE-AD-AMOC@faa.gov.

(i) Related Information

    (1) For more information about this AD, contact Jo-Ann 
Theriault, Aerospace Engineer, Engine Certification Office, FAA, 
Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 
01803; phone: 781-238-7105; fax: 781-238-7199; email: jo-ann.theriault@faa.gov.
    (2) PW SB PW4G-112-72-342, dated September 23, 2016, can be 
obtained from PW using the contact information in paragraph (i)(3) 
of this AD.
    (3) For service information identified in this AD, contact Pratt 
& Whitney Division, 400 Main St., East Hartford, CT 06118; phone: 
800-565-0140; fax: 860-565-5442.
    (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 October 19, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-25799 Filed 10-25-16; 8:45 am]
 BILLING CODE 4910-13-P