Airworthiness Directives; GE Aviation Czech s.r.o. Turboprop Engines, 44355-44357 [2017-19969]

Download as PDF Federal Register / Vol. 82, No. 183 / Friday, September 22, 2017 / Proposed Rules 2017–07–02, Amendment 39–18840 (82 FR 15120, March 27, 2017), and adding the following new AD: Sikorsky Aircraft Corporation (Sikorsky): Docket No. FAA–2017–0896; Product Identifier 2017–SW–034–AD. (a) Applicability This AD applies to Sikorsky Model 269D and Model 269D Configuration A helicopters with a KAflex engine side drive shaft part number (P/N) SKCP2738–7 and KAflex pulley side drive shaft P/N SKCP2738–5 installed, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as failure of a drive shaft. This condition could result in loss of rotor drive and subsequent loss of control of the helicopter. (c) Affected ADs This AD supersedes AD 2017–07–02, Amendment 39–18840 (82 FR 15120, March 27, 2017). (d) Comments Due Date We must receive comments by November 21, 2017. (e) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (f) Required Actions (1) Before further flight: (i) For Model 269D helicopters, remove from service any KAflex engine side drive shaft P/N SKCP2738–7 and any KAflex pulley side drive shaft P/N SKCP2738–5 that has 6,000 or more hours time-in-service (TIS). Thereafter, remove from service any KAflex engine side drive shaft P/N SKCP2738–7 and any KAflex pulley side drive shaft P/N SKCP2738–5 before accumulating 6,000 hours TIS. (ii) For Model 269D Configuration A helicopters, remove from service any KAflex engine side drive shaft P/N SKCP2738–7 and any KAflex pulley side drive shaft P/N SKCP2738–5 that has 1,200 or more hours TIS. Thereafter, remove from service any KAflex engine side drive shaft P/N SKCP2738–7 and any KAflex pulley side drive shaft P/N SKCP2738–5 before accumulating 1,200 hours TIS. (iii) If interchanged between Model 269D and Model 269D Configuration A helicopters, remove from service any KAflex engine side drive shaft P/N SKCP2738–7 and any KAflex pulley side drive shaft P/N SKCP2738–5 that has 1,200 or more hours TIS. Thereafter, if interchanged between Model 269D and Model 269D Configuration A helicopters, remove from service any KAflex engine side drive shaft P/N SKCP2738–7 and any KAflex pulley side drive shaft P/N SKCP2738–5 before accumulating 1,200 hours TIS. (2) Within 25 hours TIS, and thereafter at intervals not to exceed 25 hours TIS, using a belt drive alignment tool 269T3303–003, inspect the lower pulley to engine alignment by engaging the tool on the drive shaft and inserting in the lower pulley bore. Rotate the VerDate Sep<11>2014 16:19 Sep 21, 2017 Jkt 241001 tool 360° around the drive shaft and inspect for interference. If there is any interference with the rotation of the tool, before further flight, adjust the engine elevation alignment to eliminate the interference. (3) Within 25 hours TIS, and thereafter at intervals not to exceed 100 hours TIS: (i) Remove the drive shaft to adapter bolt and inspect the drive shaft alignment. Engage and disengage the splines a minimum of 3 times by sliding the engine power output shaft in and out of the engine. Inspect the alignment at each 90° interval by rotating the lower pulley with the power shaft disengaged. Determine whether the adapter slides on and off the drive shaft splines without spline engagement interference or resistance along the entire length of movement. If there is any spline engagement interference or resistance, before further flight, replace both the engine side and pulley side drive shafts. (ii) Inspect each drive shaft for a crack, any corrosion or pitting, a nick, a dent, and a scratch. If there is a crack, any corrosion or pitting, a nick, a dent, or a scratch that exceeds allowable limits, before further flight, replace both the engine side and pulley side drive shafts. (4) Within 25 hours TIS, and thereafter at intervals not to exceed 400 hours TIS, remove the engine side drive shaft and pulley side drive shaft and perform the following: (i) Inspect each flex frame (frame) bolted joint (joint) for movement by hand. If there is any movement, before further flight, replace both the engine side and pulley side drive shafts. (ii) Visually inspect each joint for fretting corrosion (which might be indicated by metallic particles) and each frame and mount bolt torque stripe for movement. If there is any fretting corrosion or torque stripe movement, before further flight, replace both the engine side and pulley side drive shafts. (iii) Using a 10x or higher power magnifying glass, visually inspect each joint for fretting and for a crack around the bolt head and washer side, and around the nut and washer side. Also inspect both sides of each frame for a crack on the inside and outside corner radii and radii edge (four). If there is any fretting, a crack at any point over the full circumference (360°) of the bolt head and washer side or the nut and washer side, or a crack in any of the corner radii edges, before further flight, replace both the engine side and pulley side drive shafts. (5) As an optional terminating action to the repetitive inspections in this AD, you may install KAflex engine side drive shaft P/N SKCP2738–9 and KAflex pulley side drive shaft P/N SKCP2738–101. (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Boston ACO Branch, FAA, may approve AMOCs for this AD. Send your proposal to: Michael Schwetz, Aviation Safety Engineer, Boston ACO Branch, Compliance and Airworthiness Division, FAA, 1200 District Avenue, Burlington, Massachusetts 01803; telephone (781) 238– 7761; email michael.schwetz@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 44355 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. (h) Additional Information Appendix B of Sikorsky S–330 Model 269D Helicopter Basic Handbook of Maintenance Instructions, No. CSP–D–2, dated February 1, 1993, and revised October 15, 2014; Appendix B of Sikorsky S–330 Model 269D Config. ‘‘A’’ Helicopter Basic Handbook of Maintenance Instructions, No. CSP–D–9, dated July 20, 2001, and revised October 15, 2014; and Sikorsky 269D Helicopter Alert Service Bulletin DB–052, Basic Issue, dated January 16, 2014, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact Sikorsky Aircraft Corporation, Customer Service Engineering, 124 Quarry Road, Trumbull, CT 06611; telephone 1–800– Winged–S or 203–416–4299; email wcs_cust_ service_eng.gr-sik@lmco.com. You may review the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N– 321, Fort Worth, TX 76177. (i) Subject Joint Aircraft Service Component (JASC) Code: 6310, Engine/Transmission Coupling. Issued in Fort Worth, Texas, on September 11, 2017. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2017–19945 Filed 9–21–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0658; Product Identifier 2017–NE–20–AD] RIN 2120–AA64 Airworthiness Directives; GE Aviation Czech s.r.o. Turboprop Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain GE Aviation Czech s.r.o. M601D–11, M601E–11, M601E–11A, M601E–11AS, M601E–11S, and M601F turboprop engines. This proposed AD was prompted by a review that determined that certain power turbine (PT) rotors have less overspeed margin than originally declared during product SUMMARY: E:\FR\FM\22SEP1.SGM 22SEP1 44356 Federal Register / Vol. 82, No. 183 / Friday, September 22, 2017 / Proposed Rules certification. This proposed AD would require removal of the affected PT disks. We are proposing this AD to correct the unsafe condition on these products. DATES: We must receive comments on this NPRM by November 6, 2017. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: 202–493–2251. For service information identified in this proposed AD, contact GE Aviation ´ Czech s.r.o., Beranovych 65, 199 02 ˇ Praha 9—Letnany, Czech Republic; phone: +420 222 538 111; fax: +420 222 538 222. You may view this service information at the FAA, Engine and Propeller Standards Branch, 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–2017– 0658; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the mandatory continuing airworthiness information (MCAI), the regulatory evaluation, any comments received, and other information. The 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 Green, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781– 238–7754; fax: 781–238–7199; email: robert.green@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this NPRM. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2017–0658; Directorate Identifier 2017– NE–20–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM 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 with FAA personnel concerning this NPRM. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD 2017– 0100, dated June 8, 2017 (referred to hereinafter as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: It was identified during a recent design review that power turbine (PT) rotors with certain disks, part number (P/N) M601– 3220.6 and P/N M601–3220.7, have a reduction in the declared theoretical PT rotor overspeed limit. This condition, if not corrected, may lead to high energy debris release in case of PT rotor overspeed occurrence, possibly resulting in damage to, and/or reduced control of, the aeroplane. You may obtain further information by examining the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0658. Related Service Information GE Aviation Czech s.r.o. has issued Alert Service Bulletin (ASB) No. ASB– M601E–72–50–00–0069, ASB–M601D– 72–50–00–0052, ASB–M601F–72–50– 00–0035, ASB–M601T–72–50–00–0028, and ASB–M601Z–72–50–00–0038, (single document), dated February 21, 2017. The ASB describe procedures for replacing the PT disk. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of Czech Republic, and is approved for operation in the United States. Pursuant to our bilateral agreement with the European Community, EASA has notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. This proposed AD would require removal of the affected PT disks. Costs of Compliance We estimate that this proposed AD affects 50 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Disk removal and replacement ....................... 56 work-hours × $85 per hour = $4,760 ........ 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, VerDate Sep<11>2014 16:19 Sep 21, 2017 Jkt 241001 Parts cost 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 PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 $6,989 Cost per product $14,749 Cost on U.S. operators $587,450 products identified in this rulemaking action. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has E:\FR\FM\22SEP1.SGM 22SEP1 Federal Register / Vol. 82, No. 183 / Friday, September 22, 2017 / Proposed Rules delegated the authority to issue ADs applicable to engines, propellers, and appliances to the Manager, Engine and Propeller Standards Branch, Policy and Innovation Division. 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 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): ■ GE Aviation Czech s.r.o. (Type Certificate previously held by WALTER Engines a.s., Walter a.s., and MOTORLET a.s.): Docket No. FAA–2017–0658; Product Identifier 2017–NE–20–AD. (a) Comments Due Date We must receive comments by November 6, 2017. (b) Affected ADs None. VerDate Sep<11>2014 16:19 Sep 21, 2017 Jkt 241001 (c) Applicability This AD applies to certain GE Aviation Czech s.r.o. M601D–11, M601E–11, M601E– 11A, M601E–11AS, M601E–11S, and M601F turboprop engines, with power turbine (PT) rotor disks, part number (P/N) M601–3220.6 or P/N M601–3220.7, installed. (d) Subject Joint Aircraft System Component (JASC) Code 7250, Turbine Section. (e) Reason This AD was prompted by a review that determined that PT rotors with certain disks, P/N M601–3220.6 or P/N M601–3220.7, have less overspeed margin than originally declared during product certification. We are issuing this AD to prevent failure of the PT rotor, uncontained release of the PT rotor disk, damage to the engine, and damage to the airplane. (f) Compliance (1) Comply with this AD within the compliance times specified, unless already done. (2) After the effective date of this AD, remove the affected PT disk from service during the next engine shop visit, or within 5 years, whichever occurs first. (g) Installation Prohibition After the effective date of this AD, do not install an affected PT disk on any engine. (h) Definition For the purpose of this AD, an engine shop visit is when an engine is overhauled or rebuilt. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, ECO Branch, 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 manager of the certification office, send it to the attention of the person identified in paragraph (j)(1) of this AD. You may email your request to: ANE-AD-AMOC@ faa.gov. (2) 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. (j) Related Information (1) For more information about this AD, contact Robert Green, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238– 7754; fax: 781–238–7199; email: robert.green@faa.gov. (2) Refer to MCAI European Aviation Safety Agency AD 2017–0100, dated June 8, 2017, for more information. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA–2017–0658. (3) GE Aviation Czech s.r.o. Alert Service Bulletin No. ASB–M601E–72–50–00–0069, PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 44357 ASB–M601D–72–50–00–0052, ASB–M601F– 72–50–00–0035, ASB–M601T–72–50–00– 0028, and ASB–M601Z–72–50–00–0038, (single document), dated February 21, 2017, can be obtained from GE Aviation Czech s.r.o, using the contact information in paragraph (j)(4) of this proposed AD. (4) For service information identified in this proposed AD, contact GE Aviation Czech ´ s.r.o., Beranovych 65, 199 02 Praha 9— ˇ Letnany, Czech Republic; phone: +420–222– 538–111; fax: +420–222–538–222. (5) You may view this service information at the FAA, Engine and Propeller Standards Branch, 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 September 13, 2017. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2017–19969 Filed 9–21–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0750; Product Identifier 2017–NE–24–AD] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Corporation Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Rolls-Royce Corporation (RRC) AE 3007A and AE 3007C model turbofan engines. This proposed AD was prompted by an updated analysis that lowered the life limit of fan wheels installed on the affected engines. This proposed AD would require removal of the affected fan wheel at new, lower life limits. We are proposing this AD to address the unsafe condition on these products. SUMMARY: We must receive comments on this proposed AD by November 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 DATES: E:\FR\FM\22SEP1.SGM 22SEP1

Agencies

[Federal Register Volume 82, Number 183 (Friday, September 22, 2017)]
[Proposed Rules]
[Pages 44355-44357]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-19969]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0658; Product Identifier 2017-NE-20-AD]
RIN 2120-AA64


Airworthiness Directives; GE Aviation Czech s.r.o. Turboprop 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain GE Aviation Czech s.r.o. M601D-11, M601E-11, M601E-11A, M601E-
11AS, M601E-11S, and M601F turboprop engines. This proposed AD was 
prompted by a review that determined that certain power turbine (PT) 
rotors have less overspeed margin than originally declared during 
product

[[Page 44356]]

certification. This proposed AD would require removal of the affected 
PT disks. We are proposing this AD to correct the unsafe condition on 
these products.

DATES: We must receive comments on this NPRM by November 6, 2017.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor, 
Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: 202-493-2251.
    For service information identified in this proposed AD, contact GE 
Aviation Czech s.r.o., Beranov[yacute]ch 65, 199 02 Praha 9--
Let[ncaron]any, Czech Republic; phone: +420 222 538 111; fax: +420 222 
538 222. You may view this service information at the FAA, Engine and 
Propeller Standards Branch, 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-2017-
0658; or in person at the Docket Operations office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the mandatory continuing airworthiness 
information (MCAI), the regulatory evaluation, any comments received, 
and other information. The 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 Green, Aerospace Engineer, ECO 
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7754; fax: 781-238-7199; email: robert.green@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this NPRM. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2017-0658; 
Directorate Identifier 2017-NE-20-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this NPRM. We will 
consider all comments received by the closing date and may amend this 
NPRM 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 
with FAA personnel concerning this NPRM.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD 2017-0100, dated June 8, 2017 (referred to hereinafter as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    It was identified during a recent design review that power 
turbine (PT) rotors with certain disks, part number (P/N) M601-
3220.6 and P/N M601-3220.7, have a reduction in the declared 
theoretical PT rotor overspeed limit.
    This condition, if not corrected, may lead to high energy debris 
release in case of PT rotor overspeed occurrence, possibly resulting 
in damage to, and/or reduced control of, the aeroplane.

    You may obtain further information by examining the MCAI in the AD 
docket on the Internet at http://www.regulations.gov by searching for 
and locating Docket No. FAA-2017-0658.

Related Service Information

    GE Aviation Czech s.r.o. has issued Alert Service Bulletin (ASB) 
No. ASB-M601E-72-50-00-0069, ASB-M601D-72-50-00-0052, ASB-M601F-72-50-
00-0035, ASB-M601T-72-50-00-0028, and ASB-M601Z-72-50-00-0038, (single 
document), dated February 21, 2017. The ASB describe procedures for 
replacing the PT disk.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of Czech 
Republic, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the European Community, EASA has 
notified us of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all information provided by EASA and determined the unsafe 
condition exists and is likely to exist or develop on other products of 
the same type design. This proposed AD would require removal of the 
affected PT disks.

Costs of Compliance

    We estimate that this proposed AD affects 50 engines installed on 
airplanes of U.S. registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Disk removal and replacement..........  56 work-hours x $85 per           $6,989         $14,749        $587,450
                                         hour = $4,760.
----------------------------------------------------------------------------------------------------------------

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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has

[[Page 44357]]

delegated the authority to issue ADs applicable to engines, propellers, 
and appliances to the Manager, Engine and Propeller Standards Branch, 
Policy and Innovation Division.

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):

GE Aviation Czech s.r.o. (Type Certificate previously held by WALTER 
Engines a.s., Walter a.s., and MOTORLET a.s.): Docket No. FAA-2017-
0658; Product Identifier 2017-NE-20-AD.

(a) Comments Due Date

    We must receive comments by November 6, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to certain GE Aviation Czech s.r.o. M601D-11, 
M601E-11, M601E-11A, M601E-11AS, M601E-11S, and M601F turboprop 
engines, with power turbine (PT) rotor disks, part number (P/N) 
M601-3220.6 or P/N M601-3220.7, installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7250, Turbine 
Section.

(e) Reason

    This AD was prompted by a review that determined that PT rotors 
with certain disks, P/N M601-3220.6 or P/N M601-3220.7, have less 
overspeed margin than originally declared during product 
certification. We are issuing this AD to prevent failure of the PT 
rotor, uncontained release of the PT rotor disk, damage to the 
engine, and damage to the airplane.

(f) Compliance

    (1) Comply with this AD within the compliance times specified, 
unless already done.
    (2) After the effective date of this AD, remove the affected PT 
disk from service during the next engine shop visit, or within 5 
years, whichever occurs first.

(g) Installation Prohibition

    After the effective date of this AD, do not install an affected 
PT disk on any engine.

(h) Definition

    For the purpose of this AD, an engine shop visit is when an 
engine is overhauled or rebuilt.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, ECO Branch, 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 manager of the 
certification office, send it to the attention of the person 
identified in paragraph (j)(1) of this AD. You may email your 
request to: ANE-AD-AMOC@faa.gov.
    (2) 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.

(j) Related Information

    (1) For more information about this AD, contact Robert Green, 
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7754; fax: 781-238-7199; email: 
robert.green@faa.gov.
    (2) Refer to MCAI European Aviation Safety Agency AD 2017-0100, 
dated June 8, 2017, for more information. You may examine the MCAI 
in the AD docket on the Internet at http://www.regulations.gov by 
searching for and locating it in Docket No. FAA-2017-0658.
    (3) GE Aviation Czech s.r.o. Alert Service Bulletin No. ASB-
M601E-72-50-00-0069, ASB-M601D-72-50-00-0052, ASB-M601F-72-50-00-
0035, ASB-M601T-72-50-00-0028, and ASB-M601Z-72-50-00-0038, (single 
document), dated February 21, 2017, can be obtained from GE Aviation 
Czech s.r.o, using the contact information in paragraph (j)(4) of 
this proposed AD.
    (4) For service information identified in this proposed AD, 
contact GE Aviation Czech s.r.o., Beranov[yacute]ch 65, 199 02 Praha 
9--Let[ncaron]any, Czech Republic; phone: +420-222-538-111; fax: 
+420-222-538-222.
    (5) You may view this service information at the FAA, Engine and 
Propeller Standards Branch, 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 September 13, 2017.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2017-19969 Filed 9-21-17; 8:45 am]
 BILLING CODE 4910-13-P