81 FR 48724 - Airworthiness Directives; Rolls-Royce plc Turbofan Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 143 (July 26, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 143 (July 26, 2016)
| Page Range | 48724-48725 | |
| FR Document | 2016-17160 |
[Federal Register Volume 81, Number 143 (Tuesday, July 26, 2016)] [Proposed Rules] [Pages 48724-48725] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-17160] ======================================================================== Proposed Rules Federal Register ________________________________________________________________________ This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. ======================================================================== Federal Register / Vol. 81, No. 143 / Tuesday, July 26, 2016 / Proposed Rules [[Page 48724]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-6744; Directorate Identifier 2016-NE-12-AD] RIN 2120-AA64 Airworthiness Directives; Rolls-Royce plc 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 certain Rolls-Royce plc (RR) RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent 884B-17, RB211-Trent 892-17, RB211- Trent 892B-17, and RB211-Trent 895-17 turbofan engines that have not incorporated RR modification 72-J195 in production or RR Service Bulletin (SB) RB.211-72-J195. This proposed AD was prompted by inspection of RR Trent 800 engines returned from service that revealed flame erosion and axial cracking on the aft face of the stage 3 disk rim of the high-pressure compressor (HPC) stage 1-4 rotor disks shaft. This proposed AD would require machining the HPC stage 3 inner shroud, inspecting the HPC stage 1-4 rotor disks shaft, and replacing the HPC stage 1-4 rotor disks shaft if found defective. We are proposing this AD to prevent uncontained failure of the HPC stage 1-4 rotor disks shaft, damage to the engine, and damage to the airplane. DATES: We must receive comments on this NPRM by September 26, 2016. 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 NPRM, contact Rolls- Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE24 8BJ; phone: 011-44-1332-242424; fax: 011-44-1332-249936; email: http://www.rolls-royce.com/contact/civil_team.jsp; Internet: https://customers.rolls-royce.com/public/rollsroycecare. 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- 6744; 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, Engine Certification Office, FAA, Engine & Propeller Directorate, 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 proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2016-6744; Directorate Identifier 2016-NE-12-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 based on 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 2016-0078, dated April 20, 2016 (corrected April 27, 2016) (referred to hereinafter as ``the MCAI''), to correct an unsafe condition for the specified products. The MCAI states: Inspection of Trent 800 engines returned from service revealed flame eroded areas and axial cracking on the rear Stage 3 disc of the High Pressure Compressor (HPC) Stage 1-4 drum. This is considered to be the result of a localised fire originating from an excessive rub at the stage 3-4 forward seal fin. This condition, if not detected and corrected, could lead to an uncontained engine failure and release of high energy debris, possibly resulting in damage to the aeroplane and injury to occupants. 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-2016-6744. Related Service Information Under 1 CFR Part 51 RR has issued SB RB.211-72-J195, dated February 26, 2016. The SB describes procedures to machine the HPC stage 3 inner shroud and to inspect the HPC stage 1-4 rotor disks shaft. 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 and Requirements of This Proposed AD This product has been approved by the aviation authority of the United Kingdom, 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. We are proposing this AD [[Page 48725]] 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 machining the HPC stage 3 inner shroud, inspecting the HPC stage 1-4 rotor disks shaft, and replacing the HPC stage 1-4 rotor disks shaft if found defective. Costs of Compliance We estimate that this proposed AD affects 125 engines installed on airplanes of U.S. registry. We estimate it would take 8 hours to comply with the inspection required by this proposed AD. Machining the HPC stage 3 inner shroud is required during routine overhaul; therefore, no additional time is needed for this action. 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 $85,000. 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: 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): Rolls-Royce plc: Docket No. FAA-2016-6744; Directorate Identifier 2016-NE-12-AD. (a) Comments Due Date We must receive comments by September 26, 2016. (b) Affected ADs None. (c) Applicability This AD applies to Rolls-Royce plc (RR) RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent 884B-17, RB211- Trent 892-17, RB211-Trent 892B-17, and RB211-Trent 895-17 turbofan engines that have not incorporated RR modification 72-J195, in production; or RR Service Bulletin RB.211-72-J195, dated February 26, 2016, in service. (d) Reason This AD was prompted by inspection of RR Trent 800 series engines returned from service that revealed flame erosion and axial cracking on the aft face of the stage 3 disk rim of the high- pressure compressor (HPC) stage 1-4 rotor disks shaft. We are issuing this AD to prevent uncontained failure of the HPC stage 1-4 rotor disks shaft, damage to the engine, and damage to the airplane. (e) Actions and Compliance Comply with this AD within the compliance times specified, unless already done. (1) Before exceeding 5,000 duty cycles, since new or since last HPC stage 1-4 rotor disks shaft piece-part inspection, whichever occurs later, do the following: (i) Perform dimensional, fluorescent penetrant, and visual inspections of the HPC stage 1-4 rotor disks shaft forward stage 3-4 seal fin and aft face of the stage 3 disk rim for wear, cracks, and flame erosion. Any findings of wear, cracks, or flame erosion constitute a failure of the HPC stage 1-4 rotor disks shaft. (ii) Machine the HPC stage 3 inner shroud to the dimensions shown in Figure 1 of RR Service Bulletin (SB) RB.211-72-J195, dated February 26, 2016. (2) If the HPC stage 1-4 rotor disks shaft fails the inspections required by paragraph (e)(1)(i) of this AD, remove and replace with a part eligible for installation before further flight. (f) 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: [email protected]. (g) Related Information (1) For more information about this AD, contact Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 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 2016-0078, dated April 20, 2016 (corrected April 27, 2016), 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-2016-6744. (3) RR SB RB.211-72-J195, dated February 26, 2016, can be obtained from RR, using the contact information in paragraph (g)(4) of this proposed AD. (4) For service information identified in this proposed AD, contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, England, DE24 8BJ; phone: 011-44-1332-242424; fax: 011-44- 1332-249936; email: http://www.rolls-royce.com/contact/civil_team.jsp; Internet: https://customers.rolls-royce.com/public/rollsroycecare. (5) 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 July 13, 2016. Colleen M. D'Alessandro, Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2016-17160 Filed 7-25-16; 8:45 am] BILLING CODE 4910-13-P
![48724
Proposed Rules Federal Register
Vol. 81, No. 143
Tuesday, July 26, 2016
This section of the FEDERAL REGISTER Ground Floor, Room W12–140, all comments received by the closing
contains notices to the public of the proposed Washington, DC 20590–0001. date and may amend this NPRM based
issuance of rules and regulations. The • Hand Delivery: Deliver to Mail on those comments.
purpose of these notices is to give interested address above between 9 a.m. and 5 We will post all comments we
persons an opportunity to participate in the p.m., Monday through Friday, except receive, without change, to http://
rule making prior to the adoption of the final
Federal holidays. www.regulations.gov, including any
rules.
• Fax: 202–493–2251. personal information you provide. We
For service information identified in will also post a report summarizing each
DEPARTMENT OF TRANSPORTATION this NPRM, contact Rolls-Royce plc, substantive verbal contact with FAA
Corporate Communications, P.O. Box personnel concerning this NPRM.
Federal Aviation Administration 31, Derby, England, DE24 8BJ; phone:
Discussion
011–44–1332–242424; fax: 011–44–
14 CFR Part 39 1332–249936; email: http://www.rolls- The European Aviation Safety Agency
royce.com/contact/civil_team.jsp; (EASA), which is the Technical Agent
[Docket No. FAA–2016–6744; Directorate Internet: https://customers.rolls- for the Member States of the European
Identifier 2016–NE–12–AD] royce.com/public/rollsroycecare. You Community, has issued EASA AD 2016–
may view this service information at the 0078, dated April 20, 2016 (corrected
RIN 2120–AA64
FAA, Engine & Propeller Directorate, April 27, 2016) (referred to hereinafter
Airworthiness Directives; Rolls-Royce 1200 District Avenue, Burlington, MA. as ‘‘the MCAI’’), to correct an unsafe
plc Turbofan Engines For information on the availability of condition for the specified products.
this material at the FAA, call 781–238– The MCAI states:
AGENCY: Federal Aviation 7125. Inspection of Trent 800 engines returned
Administration (FAA), DOT. from service revealed flame eroded areas and
Examining the AD Docket
ACTION: Notice of proposed rulemaking axial cracking on the rear Stage 3 disc of the
(NPRM). You may examine the AD docket on High Pressure Compressor (HPC) Stage 1–4
the Internet at http:// drum. This is considered to be the result of
SUMMARY: We propose to adopt a new www.regulations.gov by searching for a localised fire originating from an excessive
airworthiness directive (AD) for certain and locating Docket No. FAA–2016– rub at the stage 3–4 forward seal fin.
Rolls-Royce plc (RR) RB211–Trent 875– 6744; or in person at the Docket This condition, if not detected and
17, RB211–Trent 877–17, RB211–Trent corrected, could lead to an uncontained
Operations office between 9 a.m. and 5 engine failure and release of high energy
884–17, RB211–Trent 884B–17, RB211– p.m., Monday through Friday, except debris, possibly resulting in damage to the
Trent 892–17, RB211–Trent 892B–17, Federal holidays. The AD docket aeroplane and injury to occupants.
and RB211–Trent 895–17 turbofan contains this proposed AD, the
engines that have not incorporated RR mandatory continuing airworthiness You may obtain further information
modification 72–J195 in production or information (MCAI), the regulatory by examining the MCAI in the AD
RR Service Bulletin (SB) RB.211–72– evaluation, any comments received, and docket on the Internet at http://
J195. This proposed AD was prompted other information. The address for the www.regulations.gov by searching for
by inspection of RR Trent 800 engines Docket Office (phone: 800–647–5527) is and locating Docket No. FAA–2016–
returned from service that revealed in the ADDRESSES section. Comments 6744.
flame erosion and axial cracking on the will be available in the AD docket Related Service Information Under 1
aft face of the stage 3 disk rim of the shortly after receipt. CFR Part 51
high-pressure compressor (HPC) stage FOR FURTHER INFORMATION CONTACT:
1–4 rotor disks shaft. This proposed AD RR has issued SB RB.211–72–J195,
Robert Green, Aerospace Engineer, dated February 26, 2016. The SB
would require machining the HPC stage Engine Certification Office, FAA, Engine
3 inner shroud, inspecting the HPC describes procedures to machine the
& Propeller Directorate, 1200 District HPC stage 3 inner shroud and to inspect
stage 1–4 rotor disks shaft, and Avenue, Burlington, MA 01803; phone:
replacing the HPC stage 1–4 rotor disks the HPC stage 1–4 rotor disks shaft.
781–238–7754; fax: 781–238–7199; This service information is reasonably
shaft if found defective. We are email: robert.green@faa.gov.
proposing this AD to prevent available because the interested parties
SUPPLEMENTARY INFORMATION: have access to it through their normal
uncontained failure of the HPC stage 1–
4 rotor disks shaft, damage to the course of business or by the means
Comments Invited
engine, and damage to the airplane. identified in the ADDRESSES section.
We invite you to send any written
DATES: We must receive comments on relevant data, views, or arguments about FAA’s Determination and Requirements
this NPRM by September 26, 2016. this proposed AD. Send your comments of This Proposed AD
rmajette on DSK2TPTVN1PROD with PROPOSALS
ADDRESSES: You may send comments by to an address listed under the This product has been approved by
any of the following methods: ADDRESSES section. Include ‘‘Docket No. the aviation authority of the United
• Federal eRulemaking Portal: Go to FAA–2016–6744; Directorate Identifier Kingdom, and is approved for operation
http://www.regulations.gov. Follow the 2016–NE–12–AD’’ at the beginning of in the United States. Pursuant to our
instructions for submitting comments. your comments. We specifically invite bilateral agreement with the European
• Mail: Docket Management Facility, comments on the overall regulatory, Community, EASA has notified us of
U.S. Department of Transportation, 1200 economic, environmental, and energy the unsafe condition described in the
New Jersey Avenue SE., West Building aspects of this NPRM. We will consider MCAI. We are proposing this AD
VerDate Sep<11>2014 13:47 Jul 25, 2016 Jkt 238001 PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 E:\FR\FM\26JYP1.SGM 26JYP1](https://thefederalregister.org/doc/81_FR_48867/page/1.svg)
![Federal Register / Vol. 81, No. 143 / Tuesday, July 26, 2016 / Proposed Rules 48725
because we evaluated all information Procedures (44 FR 11034, February 26, (i) Perform dimensional, fluorescent
provided by EASA and determined the 1979), penetrant, and visual inspections of the HPC
unsafe condition exists and is likely to (3) Will not affect intrastate aviation stage 1–4 rotor disks shaft forward stage 3–
exist or develop on other products of the in Alaska to the extent that it justifies 4 seal fin and aft face of the stage 3 disk rim
same type design. This proposed AD making a regulatory distinction, and for wear, cracks, and flame erosion. Any
would require machining the HPC stage (4) Will not have a significant findings of wear, cracks, or flame erosion
3 inner shroud, inspecting the HPC economic impact, positive or negative, constitute a failure of the HPC stage 1–4 rotor
stage 1–4 rotor disks shaft, and on a substantial number of small entities disks shaft.
replacing the HPC stage 1–4 rotor disks under the criteria of the Regulatory (ii) Machine the HPC stage 3 inner shroud
shaft if found defective. Flexibility Act. to the dimensions shown in Figure 1 of RR
Service Bulletin (SB) RB.211–72–J195, dated
Costs of Compliance List of Subjects in 14 CFR Part 39 February 26, 2016.
We estimate that this proposed AD Air transportation, Aircraft, Aviation (2) If the HPC stage 1–4 rotor disks shaft
affects 125 engines installed on safety, Incorporation by reference, fails the inspections required by paragraph
airplanes of U.S. registry. We estimate it Safety. (e)(1)(i) of this AD, remove and replace with
would take 8 hours to comply with the a part eligible for installation before further
The Proposed Amendment
flight.
inspection required by this proposed
Accordingly, under the authority
AD. Machining the HPC stage 3 inner (f) Alternative Methods of Compliance
delegated to me by the Administrator,
shroud is required during routine (AMOCs)
the FAA proposes to amend 14 CFR part
overhaul; therefore, no additional time The Manager, Engine Certification Office,
39 as follows:
is needed for this action. The average FAA, may approve AMOCs for this AD. Use
labor rate is $85 per hour. Based on PART 39—AIRWORTHINESS the procedures found in 14 CFR 39.19 to
these figures, we estimate the cost of DIRECTIVES make your request. You may email your
this proposed AD on U.S. operators to request to: ANE-AD-AMOC@faa.gov.
be $85,000. ■ 1. The authority citation for part 39
continues to read as follows: (g) Related Information
Authority for This Rulemaking
Authority: 49 U.S.C. 106(g), 40113, 44701. (1) For more information about this AD,
Title 49 of the United States Code contact Robert Green, Aerospace Engineer,
specifies the FAA’s authority to issue § 39.13 [Amended] Engine Certification Office, FAA, Engine &
rules on aviation safety. Subtitle I, ■ 2. The FAA amends § 39.13 by adding Propeller Directorate, 1200 District Avenue,
section 106, describes the authority of the following new airworthiness Burlington, MA 01803; phone: 781–238–
the FAA Administrator. ‘‘Subtitle VII: directive (AD): 7754; fax: 781–238–7199; email:
Aviation Programs,’’ describes in more Rolls-Royce plc: Docket No. FAA–2016– robert.green@faa.gov.
detail the scope of the Agency’s 6744; Directorate Identifier 2016–NE– (2) Refer to MCAI European Aviation
authority. 12–AD. Safety Agency AD 2016–0078, dated April
We are issuing this rulemaking under 20, 2016 (corrected April 27, 2016), for more
(a) Comments Due Date
the authority described in ‘‘Subtitle VII, information. You may examine the MCAI in
We must receive comments by September the AD docket on the Internet at http://
Part A, Subpart III, Section 44701: 26, 2016.
General requirements.’’ Under that www.regulations.gov by searching for and
section, Congress charges the FAA with (b) Affected ADs locating it in Docket No. FAA–2016–6744.
promoting safe flight of civil aircraft in None. (3) RR SB RB.211–72–J195, dated February
air commerce by prescribing regulations 26, 2016, can be obtained from RR, using the
(c) Applicability contact information in paragraph (g)(4) of this
for practices, methods, and procedures
This AD applies to Rolls-Royce plc (RR) proposed AD.
the Administrator finds necessary for RB211–Trent 875–17, RB211–Trent 877–17, (4) For service information identified in
safety in air commerce. This regulation RB211–Trent 884–17, RB211–Trent 884B–17, this proposed AD, contact Rolls-Royce plc,
is within the scope of that authority RB211–Trent 892–17, RB211–Trent 892B–17, Corporate Communications, P.O. Box 31,
because it addresses an unsafe condition and RB211–Trent 895–17 turbofan engines
that have not incorporated RR modification Derby, England, DE24 8BJ; phone: 011–44–
that is likely to exist or develop on
72–J195, in production; or RR Service 1332–242424; fax: 011–44–1332–249936;
products identified in this rulemaking
Bulletin RB.211–72–J195, dated February 26, email: http://www.rolls-royce.com/contact/
action.
2016, in service. civil_team.jsp; Internet: https://
Regulatory Findings customers.rolls-royce.com/public/
(d) Reason
rollsroycecare.
We determined that this proposed AD This AD was prompted by inspection of RR (5) You may view this service information
would not have federalism implications Trent 800 series engines returned from at the FAA, Engine & Propeller Directorate,
under Executive Order 13132. This service that revealed flame erosion and axial
1200 District Avenue, Burlington, MA. For
proposed AD would not have a cracking on the aft face of the stage 3 disk
rim of the high-pressure compressor (HPC) information on the availability of this
substantial direct effect on the States, on material at the FAA, call 781–238–7125.
the relationship between the national stage 1–4 rotor disks shaft. We are issuing
this AD to prevent uncontained failure of the Issued in Burlington, Massachusetts, on
Government and the States, or on the HPC stage 1–4 rotor disks shaft, damage to
distribution of power and July 13, 2016.
the engine, and damage to the airplane.
rmajette on DSK2TPTVN1PROD with PROPOSALS
responsibilities among the various Colleen M. D’Alessandro,
levels of government. (e) Actions and Compliance Manager, Engine & Propeller Directorate,
For the reasons discussed above, I Comply with this AD within the Aircraft Certification Service.
certify this proposed regulation: compliance times specified, unless already [FR Doc. 2016–17160 Filed 7–25–16; 8:45 am]
done.
(1) Is not a ‘‘significant regulatory (1) Before exceeding 5,000 duty cycles, BILLING CODE 4910–13–P
action’’ under Executive Order 12866, since new or since last HPC stage 1–4 rotor
(2) Is not a ‘‘significant rule’’ under disks shaft piece-part inspection, whichever
the DOT Regulatory Policies and occurs later, do the following:
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Document Created: 2018-02-08 08:00:32
Document Modified: 2018-02-08 08:00:32
| 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 September 26, 2016. | |
| Contact | Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7754; fax: 781- 238-7199; email: [email protected] | |
| FR Citation | 81 FR 48724 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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