82 FR 44355 - Airworthiness Directives; GE Aviation Czech s.r.o. Turboprop Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 183 (September 22, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 183 (September 22, 2017)
| Page Range | 44355-44357 | |
| FR Document | 2017-19969 |
[Federal Register Volume 82, Number 183 (Friday, September 22, 2017)] [Proposed Rules] [Pages 44355-44357] From the Federal Register Online [www.thefederalregister.org] [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: [email protected]. 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: [email protected]. (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: [email protected]. (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
![Federal Register / Vol. 82, No. 183 / Friday, September 22, 2017 / Proposed Rules 44355
2017–07–02, Amendment 39–18840 (82 tool 360° around the drive shaft and inspect 14 CFR part 91, subpart K, we suggest that
FR 15120, March 27, 2017), and adding for interference. If there is any interference you notify your principal inspector, or
the following new AD: with the rotation of the tool, before further lacking a principal inspector, the manager of
flight, adjust the engine elevation alignment the local flight standards district office or
Sikorsky Aircraft Corporation (Sikorsky): to eliminate the interference. certificate holding district office before
Docket No. FAA–2017–0896; Product (3) Within 25 hours TIS, and thereafter at operating any aircraft complying with this
Identifier 2017–SW–034–AD. intervals not to exceed 100 hours TIS: AD through an AMOC.
(a) Applicability (i) Remove the drive shaft to adapter bolt
and inspect the drive shaft alignment. Engage (h) Additional Information
This AD applies to Sikorsky Model 269D and disengage the splines a minimum of 3 Appendix B of Sikorsky S–330 Model 269D
and Model 269D Configuration A helicopters times by sliding the engine power output Helicopter Basic Handbook of Maintenance
with a KAflex engine side drive shaft part shaft in and out of the engine. Inspect the Instructions, No. CSP–D–2, dated February 1,
number (P/N) SKCP2738–7 and KAflex alignment at each 90° interval by rotating the 1993, and revised October 15, 2014;
pulley side drive shaft P/N SKCP2738–5 lower pulley with the power shaft Appendix B of Sikorsky S–330 Model 269D
installed, certificated in any category. disengaged. Determine whether the adapter Config. ‘‘A’’ Helicopter Basic Handbook of
(b) Unsafe Condition slides on and off the drive shaft splines Maintenance Instructions, No. CSP–D–9,
without spline engagement interference or dated July 20, 2001, and revised October 15,
This AD defines the unsafe condition as
resistance along the entire length of 2014; and Sikorsky 269D Helicopter Alert
failure of a drive shaft. This condition could
movement. If there is any spline engagement Service Bulletin DB–052, Basic Issue, dated
result in loss of rotor drive and subsequent
interference or resistance, before further January 16, 2014, which are not incorporated
loss of control of the helicopter.
flight, replace both the engine side and by reference, contain additional information
(c) Affected ADs pulley side drive shafts. about the subject of this AD. For service
This AD supersedes AD 2017–07–02, (ii) Inspect each drive shaft for a crack, any information identified in this AD, contact
Amendment 39–18840 (82 FR 15120, March corrosion or pitting, a nick, a dent, and a Sikorsky Aircraft Corporation, Customer
27, 2017). scratch. If there is a crack, any corrosion or Service Engineering, 124 Quarry Road,
pitting, a nick, a dent, or a scratch that Trumbull, CT 06611; telephone 1–800–
(d) Comments Due Date exceeds allowable limits, before further Winged–S or 203–416–4299; email wcs_cust_
We must receive comments by November flight, replace both the engine side and service_eng.gr-sik@lmco.com. You may
21, 2017. pulley side drive shafts. review the service information at the FAA,
(4) Within 25 hours TIS, and thereafter at Office of the Regional Counsel, Southwest
(e) Compliance intervals not to exceed 400 hours TIS, Region, 10101 Hillwood Pkwy., Room 6N–
You are responsible for performing each remove the engine side drive shaft and pulley 321, Fort Worth, TX 76177.
action required by this AD within the side drive shaft and perform the following:
(i) Inspect each flex frame (frame) bolted (i) Subject
specified compliance time unless it has
already been accomplished prior to that time. joint (joint) for movement by hand. If there Joint Aircraft Service Component (JASC)
is any movement, before further flight, Code: 6310, Engine/Transmission Coupling.
(f) Required Actions replace both the engine side and pulley side Issued in Fort Worth, Texas, on September
(1) Before further flight: drive shafts. 11, 2017.
(i) For Model 269D helicopters, remove (ii) Visually inspect each joint for fretting
from service any KAflex engine side drive corrosion (which might be indicated by Lance T. Gant,
shaft P/N SKCP2738–7 and any KAflex metallic particles) and each frame and mount Director, Compliance & Airworthiness
pulley side drive shaft P/N SKCP2738–5 that bolt torque stripe for movement. If there is Division, Aircraft Certification Service.
has 6,000 or more hours time-in-service any fretting corrosion or torque stripe [FR Doc. 2017–19945 Filed 9–21–17; 8:45 am]
(TIS). Thereafter, remove from service any movement, before further flight, replace both BILLING CODE 4910–13–P
KAflex engine side drive shaft P/N the engine side and pulley side drive shafts.
SKCP2738–7 and any KAflex pulley side (iii) Using a 10x or higher power
drive shaft P/N SKCP2738–5 before magnifying glass, visually inspect each joint DEPARTMENT OF TRANSPORTATION
accumulating 6,000 hours TIS. for fretting and for a crack around the bolt
(ii) For Model 269D Configuration A head and washer side, and around the nut Federal Aviation Administration
helicopters, remove from service any KAflex and washer side. Also inspect both sides of
engine side drive shaft P/N SKCP2738–7 and each frame for a crack on the inside and
any KAflex pulley side drive shaft P/N outside corner radii and radii edge (four). If 14 CFR Part 39
SKCP2738–5 that has 1,200 or more hours there is any fretting, a crack at any point over [Docket No. FAA–2017–0658; Product
TIS. Thereafter, remove from service any the full circumference (360°) of the bolt head Identifier 2017–NE–20–AD]
KAflex engine side drive shaft P/N and washer side or the nut and washer side,
SKCP2738–7 and any KAflex pulley side or a crack in any of the corner radii edges, RIN 2120–AA64
drive shaft P/N SKCP2738–5 before before further flight, replace both the engine
accumulating 1,200 hours TIS. side and pulley side drive shafts. Airworthiness Directives; GE Aviation
(iii) If interchanged between Model 269D (5) As an optional terminating action to the Czech s.r.o. Turboprop Engines
and Model 269D Configuration A helicopters, repetitive inspections in this AD, you may
remove from service any KAflex engine side install KAflex engine side drive shaft P/N AGENCY: Federal Aviation
drive shaft P/N SKCP2738–7 and any KAflex SKCP2738–9 and KAflex pulley side drive Administration (FAA), DOT.
pulley side drive shaft P/N SKCP2738–5 that shaft P/N SKCP2738–101. ACTION: Notice of proposed rulemaking
has 1,200 or more hours TIS. Thereafter, if (NPRM).
interchanged between Model 269D and (g) Alternative Methods of Compliance
Model 269D Configuration A helicopters, (AMOCs) SUMMARY: We propose to adopt a new
remove from service any KAflex engine side (1) The Manager, Boston ACO Branch, airworthiness directive (AD) for certain
drive shaft P/N SKCP2738–7 and any KAflex FAA, may approve AMOCs for this AD. Send GE Aviation Czech s.r.o. M601D–11,
pulley side drive shaft P/N SKCP2738–5 your proposal to: Michael Schwetz, Aviation M601E–11, M601E–11A, M601E–11AS,
before accumulating 1,200 hours TIS. Safety Engineer, Boston ACO Branch,
M601E–11S, and M601F turboprop
(2) Within 25 hours TIS, and thereafter at Compliance and Airworthiness Division,
intervals not to exceed 25 hours TIS, using FAA, 1200 District Avenue, Burlington, engines. This proposed AD was
a belt drive alignment tool 269T3303–003, Massachusetts 01803; telephone (781) 238– prompted by a review that determined
inspect the lower pulley to engine alignment 7761; email michael.schwetz@faa.gov. that certain power turbine (PT) rotors
by engaging the tool on the drive shaft and (2) For operations conducted under a 14 have less overspeed margin than
inserting in the lower pulley bore. Rotate the CFR part 119 operating certificate or under originally declared during product
VerDate Sep<11>2014 16:19 Sep 21, 2017 Jkt 241001 PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 E:\FR\FM\22SEP1.SGM 22SEP1](https://thefederalregister.org/doc/82_FR_44538/page/1.svg)
![Federal Register / Vol. 82, No. 183 / Friday, September 22, 2017 / Proposed Rules 44357
delegated the authority to issue ADs (c) Applicability ASB–M601D–72–50–00–0052, ASB–M601F–
applicable to engines, propellers, and This AD applies to certain GE Aviation 72–50–00–0035, ASB–M601T–72–50–00–
appliances to the Manager, Engine and Czech s.r.o. M601D–11, M601E–11, M601E– 0028, and ASB–M601Z–72–50–00–0038,
11A, M601E–11AS, M601E–11S, and M601F (single document), dated February 21, 2017,
Propeller Standards Branch, Policy and
turboprop engines, with power turbine (PT) can be obtained from GE Aviation Czech
Innovation Division. s.r.o, using the contact information in
rotor disks, part number (P/N) M601–3220.6
Regulatory Findings or P/N M601–3220.7, installed. paragraph (j)(4) of this proposed AD.
(4) For service information identified in
We determined that this proposed AD (d) Subject this proposed AD, contact GE Aviation Czech
would not have federalism implications Joint Aircraft System Component (JASC) s.r.o., Beranových 65, 199 02 Praha 9—
under Executive Order 13132. This Code 7250, Turbine Section. Letňany, Czech Republic; phone: +420–222–
proposed AD would not have a 538–111; fax: +420–222–538–222.
(e) Reason (5) You may view this service information
substantial direct effect on the States, on
This AD was prompted by a review that at the FAA, Engine and Propeller Standards
the relationship between the national
determined that PT rotors with certain disks, Branch, 1200 District Avenue, Burlington,
Government and the States, or on the P/N M601–3220.6 or P/N M601–3220.7, have MA. For information on the availability of
distribution of power and less overspeed margin than originally this material at the FAA, call 781–238–7125.
responsibilities among the various declared during product certification. We are
Issued in Burlington, Massachusetts, on
levels of government. issuing this AD to prevent failure of the PT
September 13, 2017.
For the reasons discussed above, I rotor, uncontained release of the PT rotor
disk, damage to the engine, and damage to Robert J. Ganley,
certify this proposed regulation:
the airplane. Manager, Engine and Propeller Standards
(1) Is not a ‘‘significant regulatory Branch, Aircraft Certification Service.
action’’ under Executive Order 12866, (f) Compliance
[FR Doc. 2017–19969 Filed 9–21–17; 8:45 am]
(2) Is not a ‘‘significant rule’’ under (1) Comply with this AD within the
BILLING CODE 4910–13–P
the DOT Regulatory Policies and compliance times specified, unless already
Procedures (44 FR 11034, February 26, done.
1979), (2) After the effective date of this AD,
remove the affected PT disk from service DEPARTMENT OF TRANSPORTATION
(3) Will not affect intrastate aviation during the next engine shop visit, or within
in Alaska to the extent that it justifies 5 years, whichever occurs first. Federal Aviation Administration
making a regulatory distinction, and
(4) Will not have a significant (g) Installation Prohibition
14 CFR Part 39
economic impact, positive or negative, After the effective date of this AD, do not
install an affected PT disk on any engine. [Docket No. FAA–2017–0750; Product
on a substantial number of small entities
Identifier 2017–NE–24–AD]
under the criteria of the Regulatory (h) Definition
Flexibility Act. For the purpose of this AD, an engine shop RIN 2120–AA64
List of Subjects in 14 CFR Part 39 visit is when an engine is overhauled or
rebuilt. Airworthiness Directives; Rolls-Royce
Air transportation, Aircraft, Aviation Corporation Turbofan Engines
(i) Alternative Methods of Compliance
safety, Incorporation by reference, (AMOCs) AGENCY: Federal Aviation
Safety. Administration (FAA), DOT.
(1) The Manager, ECO Branch, FAA, has
The Proposed Amendment the authority to approve AMOCs for this AD ACTION: Notice of proposed rulemaking
if requested using the procedures found in 14 (NPRM).
Accordingly, under the authority CFR 39.19. In accordance with 14 CFR 39.19,
delegated to me by the Administrator, send your request to your principal inspector SUMMARY: We propose to adopt a new
the FAA proposes to amend 14 CFR part or local Flight Standards District Office, as airworthiness directive (AD) for certain
39 as follows: appropriate. If sending information directly Rolls-Royce Corporation (RRC) AE
to the manager of the certification office,
send it to the attention of the person
3007A and AE 3007C model turbofan
PART 39—AIRWORTHINESS
identified in paragraph (j)(1) of this AD. You engines. This proposed AD was
DIRECTIVES
may email your request to: ANE-AD-AMOC@ prompted by an updated analysis that
■ 1. The authority citation for part 39 faa.gov. lowered the life limit of fan wheels
continues to read as follows: (2) Before using any approved AMOC, installed on the affected engines. This
notify your appropriate principal inspector, proposed AD would require removal of
Authority: 49 U.S.C. 106(g), 40113, 44701. or lacking a principal inspector, the manager the affected fan wheel at new, lower life
of the local flight standards district office/ limits. We are proposing this AD to
§ 39.13 [Amended] certificate holding district office.
address the unsafe condition on these
(j) Related Information products.
■ 2. The FAA amends § 39.13 by adding
(1) For more information about this AD, DATES: We must receive comments on
the following new airworthiness contact Robert Green, Aerospace Engineer,
directive (AD): this proposed AD by November 6, 2017.
ECO Branch, FAA, 1200 District Avenue,
GE Aviation Czech s.r.o. (Type Certificate Burlington, MA 01803; phone: 781–238– ADDRESSES: You may send comments,
previously held by WALTER Engines 7754; fax: 781–238–7199; email: using the procedures found in 14 CFR
a.s., Walter a.s., and MOTORLET a.s.): robert.green@faa.gov. 11.43 and 11.45, by any of the following
Docket No. FAA–2017–0658; Product (2) Refer to MCAI European Aviation methods:
Identifier 2017–NE–20–AD. Safety Agency AD 2017–0100, dated June 8, • Federal eRulemaking Portal: Go to
2017, for more information. You may http://www.regulations.gov. Follow the
(a) Comments Due Date examine the MCAI in the AD docket on the
Internet at http://www.regulations.gov by
instructions for submitting comments.
We must receive comments by November
6, 2017. searching for and locating it in Docket No. • Fax: 202–493–2251.
FAA–2017–0658. • Mail: U.S. Department of
(b) Affected ADs (3) GE Aviation Czech s.r.o. Alert Service Transportation, Docket Operations, M–
None. Bulletin No. ASB–M601E–72–50–00–0069, 30, West Building Ground Floor, Room
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Document Created: 2017-09-22 01:52:44
Document Modified: 2017-09-22 01:52:44
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this NPRM by November 6, 2017. | |
| Contact | Robert Green, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781- 238-7754; fax: 781-238-7199; email: [email protected] | |
| FR Citation | 82 FR 44355 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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