Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Turbofan Engines, 44713-44715 [2017-20531]

Download as PDF Federal Register / Vol. 82, No. 185 / Tuesday, September 26, 2017 / Rules and Regulations (g) Installation Prohibition After the effective date of this AD: (1) Do not install an engine that is equipped with a clutch and has an affected gearbox listed in Figure 1 to paragraph (c) of this AD; (2) Do not install an affected gearbox on an engine unless it has passed the inspection required by paragraph (f)(2)(iii) of this AD; and (3) Do not install a clutch on an engine previously modified in accordance with the requirements of paragraph (f)(2) of this AD or already incorporating a dual mass flywheel. the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. (h) 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 ECO Branch, send it to the attention of the person identified in paragraph (i)(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. DEPARTMENT OF TRANSPORTATION Pmangrum on DSK3GDR082PROD with RULES (i) 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 2017–0034, dated February 20, 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–2017–0241. (j) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Technify Motors GmbH Service Bulletin No. SB TMG 125–1020 P1, Initial Issue, dated January 27, 2016. (ii) Reserved. (3) For Technify Motors GmbH service information identified in this AD, contact Technify Motors GmbH, Platanenstrasse 14, D–09356 Sankt Egidien, Germany; phone: +49 37204 696 0; fax: +49 37204 696 29125; email: info@centurion-engines.com. You may view this referenced service information at 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. (4) You may view this service information at the National Archives and Records Administration (NARA). For information on VerDate Sep<11>2014 15:04 Sep 25, 2017 Jkt 241001 Issued in Burlington, Massachusetts, on September 13, 2017. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2017–20419 Filed 9–25–17; 8:45 am] BILLING CODE 4910–13–P Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0140; Product Identifier 2017–NE–05–AD; Amendment 39– 19048; AD 2017–19–18] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) model Tay 620–15 turbofan engines. This AD requires reducing the maximum approved life limit. This AD was prompted by RRD recalculating the life limit for certain high-pressure compressor (HPC) stage 12 rotor disks. We are issuing this AD to correct the unsafe condition on these products. DATES: This AD becomes effective October 31, 2017. ADDRESSES: For service information identified in this final rule, contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11–15827 Dahlewitz, Blankenfelde-Mahlow, Germany; phone: +49 0 33–7086–1944; fax: +49 0 33– 7086–3276. You may view this service information at the FAA, Engine and Propeller Standards Branch, Policy and Innovation Division, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238–7125. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2017– 0140. SUMMARY: 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– 0140; or in person at the Docket PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 44713 Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this 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 Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer, FAA, ECO Branch, Compliance and Airworthiness Division, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7754; fax: 781–238–7199; email: robert.green@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to the specified products. The NPRM was published in the Federal Register on May 26, 2017 (82 FR 24257). The NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: Based on revised stress analysis and life calculation, Rolls-Royce Deutschland (RRD) determined new provisional life limits for HPC stage 12 rotor disc Part Number (P/N) JR18449, reducing the maximum approved life limit defined in the Tay 620–15 and Tay 620–15/20 engine Time Limits Manual (TLM), Chapter 05–10–01, Task 05–10–01– 800–000, currently at revision dated 15 September 2014. Failure to replace a HPC stage 12 rotor disc P/N JR18449, before exceeding the thresholds defined by this AD, could lead to an uncontained HPC stage 12 rotor disc failure, 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– 0140. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (82 FR 24257, May 26, 2017) or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting this AD as proposed. E:\FR\FM\26SER1.SGM 26SER1 44714 Federal Register / Vol. 82, No. 185 / Tuesday, September 26, 2017 / Rules and Regulations Related Service Information RRD has issued Alert NonModification Service Bulletin (NMSB) TAY–72–A1813, Revision 1, dated January 27, 2017. The Alert NMSB provides instructions to determine or re- calculate the consumed and remaining service life. 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. Costs of Compliance We estimate that this AD affects 25 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Pro-rated life ................................................... 1 work-hour × $85 per hour = $85 ................. 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 delegated the authority to issue ADs applicable to engines, propellers, and associated appliances to the Manager, Engine and Propeller Standards Branch, Policy and Innovation Division. Pmangrum on DSK3GDR082PROD with RULES Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will 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. VerDate Sep<11>2014 15:04 Sep 25, 2017 Jkt 241001 Parts cost For the reasons discussed above, I certify this AD: (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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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): ■ 2017–19–18 Rolls-Royce Deutschland Ltd & Co KG: Amendment 39–19048; Docket No. FAA–2017–0140; Product Identifier 2017–NE–05–AD. (a) Effective Date This AD becomes effective October 31, 2017. (b) Affected ADs None. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 $3,858 Cost per product $3,943 Cost on U.S. operators $98,575 (c) Applicability This AD applies to Rolls-Royce Deutschland Ltd & Co KG (RRD) model Tay 620–15 turbofan engines with high-pressure compressor (HPC) modules M03100AA, or M03100AB, or M03100AC and HPC stage 12 rotor disk, part number (P/N) JR18449, installed. (d) Subject Joint Aircraft System Component (JASC) 7230, Turbine Engine Compressor Section. (e) Reason This AD was prompted by RRD recalculating the life limit for HPC stage 12 rotor disk, P/N JR18449. We are issuing this AD to prevent failure of the HPC stage 12 rotor disk, uncontained HPC stage 12 rotor disk release, damage to the engine, and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) Within 30 days after the effective date of this AD, determine whether the HPC stage 12 rotor disk has operated in both flight profiles A and B. If the rotor disk was operated, or is operating, in both flight profiles A and B, re-calculate the consumed cyclic life using 16,700 flight cycles (FC) as the maximum approved life limit for flight profile B. (2) After the effective date of this AD, the maximum approved life limit for affected rotor disks operating in flight profile B is 16,700 FC. Calculate the consumed cyclic life accumulated since new using 16,700 FC as the maximum approved life limit for flight profile B. (3) For those engines operating in flight profile B with an HPC stage 12 rotor disk, P/ N JR18449, installed, that do not have an engine shop visit after the effective date of this AD before the re-calculated consumed cyclic life of the HPC stage 12 disk exceeds 16,700 FC, remove the affected rotor disk from service before the re-calculated consumed cyclic life exceeds the threshold(s) defined in Figure 1 to paragraph (g) of this AD. E:\FR\FM\26SER1.SGM 26SER1 Federal Register / Vol. 82, No. 185 / Tuesday, September 26, 2017 / Rules and Regulations 44715 FIGURE 1 TO PARAGRAPH (g)—REMOVE AFFECTED ROTOR DISKS FROM SERVICE Recalculated consumed cyclic life on the effective date of this AD (i) less than 15,700 FC ........ (ii) 15,700 FC or more, but less than 16,700 FC. (iii) 16,700 FC or more ......... Remove affected rotor disks from service Before exceeding 16,700 FC since new Either: (A) Within 1,000 FC or 19 months after the effective date of this AD, whichever occurs first; or (B) Before exceeding 16,700 FC since new, whichever occurs later. Either: (A) Within 1,000 FC after the effective date of this AD, or (B) Before exceeding 20,000 FC since new, or (C) Within 19 months after the effective date of this AD, whichever occurs first. (h) Installation Prohibition After the effective date of this AD, installation of a serviceable spare engine or release to service of an engine after any shop visit, is allowed, provided the installed HPC stage 12 rotor disk, P/N JR18449, is a serviceable part. (i) Definition For the purpose of this AD, a serviceable part is an HPC stage 12 rotor disk, P/N JR18449, that has not exceeded 20,500 FC for flight profile A or 16,700 FC for flight profile B, as applicable to engine operation. Pmangrum on DSK3GDR082PROD with RULES (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, FAA, ECO Branch, Compliance and Airworthiness Division, 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. (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. (k) Related Information (1) For more information about this AD, contact Robert Green, Aerospace Engineer, FAA, ECO Branch, Compliance and Airworthiness Division, 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 2017–0010, dated January 16, 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–2017–0140. (3) RRD Alert Non-Modification Service Bulletin TAY–72–A1813, Revision 1, dated January 27, 2017, which is not incorporated by reference in this AD, can be obtained from RRD, using the contact information in paragraph (k)(4) of this AD. (4) For service information identified in this AD, contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11–15827 Dahlewitz, Blankenfelde-Mahlow, Germany; phone: +49 0 33–7086–1944; fax: +49 0 33–7086–3276. (5) You may view this service information at the FAA, Engine and Propeller Standards Branch, Policy and Innovation Division, 1200 VerDate Sep<11>2014 15:04 Sep 25, 2017 Jkt 241001 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. (l) Material Incorporated by Reference None. Issued in Burlington, Massachusetts, on September 13, 2017. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2017–20531 Filed 9–25–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0767; Product Identifier 2017–NE–26–AD; Amendment 39– 19049; AD 2017–19–19] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) Trent XWB–75, Trent XWB–79, Trent XWB–79B, and Trent XWB–84, turbofan engines. This AD requires replacement of the lowpressure compressor (LPC) case support inboard pins. This AD was prompted by LPC case support inboard pins that may have reduced integrity due to incorrect heat treatment. We are issuing this AD to correct the unsafe condition on these products. DATES: This AD becomes effective October 11, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publications listed in this AD as of October 11, 2017. SUMMARY: PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 We must receive comments on this AD by November 13, 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: 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 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.rollsroyce.com/contact/civil_team.jsp; Internet: https://customers.rollsroyce.com/public/rollsroycecare. You may view this service information at the FAA, Engine and Propeller Standards Branch, Policy and Innovation Division, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238–7125. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0767. 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– 0767; 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 AD, the mandatory continuing airworthiness information (MCAI), regulatory evaluation, any comments received, and other information. The address for the Docket E:\FR\FM\26SER1.SGM 26SER1

Agencies

[Federal Register Volume 82, Number 185 (Tuesday, September 26, 2017)]
[Rules and Regulations]
[Pages 44713-44715]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-20531]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0140; Product Identifier 2017-NE-05-AD; Amendment 
39-19048; AD 2017-19-18]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG 
Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Rolls-Royce Deutschland Ltd & Co KG (RRD) model Tay 620-15 turbofan 
engines. This AD requires reducing the maximum approved life limit. 
This AD was prompted by RRD recalculating the life limit for certain 
high-pressure compressor (HPC) stage 12 rotor disks. We are issuing 
this AD to correct the unsafe condition on these products.

DATES: This AD becomes effective October 31, 2017.

ADDRESSES: For service information identified in this final rule, 
contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11-15827 
Dahlewitz, Blankenfelde-Mahlow, Germany; phone: +49 0 33-7086-1944; 
fax: +49 0 33-7086-3276. You may view this service information at the 
FAA, Engine and Propeller Standards Branch, Policy and Innovation 
Division, 1200 District Avenue, Burlington, MA 01803. For information 
on the availability of this material at the FAA, call 781-238-7125. It 
is also available on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2017-0140.

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-
0140; 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 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 
Document Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer, FAA, 
ECO Branch, Compliance and Airworthiness Division, 1200 District 
Avenue, Burlington, MA 01803; phone: 781-238-7754; fax: 781-238-7199; 
email: robert.green@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to the specified products. The 
NPRM was published in the Federal Register on May 26, 2017 (82 FR 
24257). The NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    Based on revised stress analysis and life calculation, Rolls-
Royce Deutschland (RRD) determined new provisional life limits for 
HPC stage 12 rotor disc Part Number (P/N) JR18449, reducing the 
maximum approved life limit defined in the Tay 620-15 and Tay 620-
15/20 engine Time Limits Manual (TLM), Chapter 05-10-01, Task 05-10-
01-800-000, currently at revision dated 15 September 2014. Failure 
to replace a HPC stage 12 rotor disc P/N JR18449, before exceeding 
the thresholds defined by this AD, could lead to an uncontained HPC 
stage 12 rotor disc failure, 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-2017-0140.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (82 FR 24257, May 26, 
2017) or on the determination of the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD as proposed.

[[Page 44714]]

Related Service Information

    RRD has issued Alert Non-Modification Service Bulletin (NMSB) TAY-
72-A1813, Revision 1, dated January 27, 2017. The Alert NMSB provides 
instructions to determine or re-calculate the consumed and remaining 
service life. 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.

Costs of Compliance

    We estimate that this AD affects 25 engines installed on airplanes 
of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Pro-rated life........................  1 work-hour x $85 per             $3,858          $3,943         $98,575
                                         hour = $85.
----------------------------------------------------------------------------------------------------------------

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

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will 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 AD:
    (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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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):

2017-19-18 Rolls-Royce Deutschland Ltd & Co KG: Amendment 39-19048; 
Docket No. FAA-2017-0140; Product Identifier 2017-NE-05-AD.

(a) Effective Date

    This AD becomes effective October 31, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Rolls-Royce Deutschland Ltd & Co KG (RRD) 
model Tay 620-15 turbofan engines with high-pressure compressor 
(HPC) modules M03100AA, or M03100AB, or M03100AC and HPC stage 12 
rotor disk, part number (P/N) JR18449, installed.

(d) Subject

    Joint Aircraft System Component (JASC) 7230, Turbine Engine 
Compressor Section.

(e) Reason

    This AD was prompted by RRD recalculating the life limit for HPC 
stage 12 rotor disk, P/N JR18449. We are issuing this AD to prevent 
failure of the HPC stage 12 rotor disk, uncontained HPC stage 12 
rotor disk release, damage to the engine, and damage to the 
airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    (1) Within 30 days after the effective date of this AD, 
determine whether the HPC stage 12 rotor disk has operated in both 
flight profiles A and B. If the rotor disk was operated, or is 
operating, in both flight profiles A and B, re-calculate the 
consumed cyclic life using 16,700 flight cycles (FC) as the maximum 
approved life limit for flight profile B.
    (2) After the effective date of this AD, the maximum approved 
life limit for affected rotor disks operating in flight profile B is 
16,700 FC. Calculate the consumed cyclic life accumulated since new 
using 16,700 FC as the maximum approved life limit for flight 
profile B.
    (3) For those engines operating in flight profile B with an HPC 
stage 12 rotor disk, P/N JR18449, installed, that do not have an 
engine shop visit after the effective date of this AD before the re-
calculated consumed cyclic life of the HPC stage 12 disk exceeds 
16,700 FC, remove the affected rotor disk from service before the 
re-calculated consumed cyclic life exceeds the threshold(s) defined 
in Figure 1 to paragraph (g) of this AD.

[[Page 44715]]



   Figure 1 to Paragraph (g)--Remove Affected Rotor Disks From Service
------------------------------------------------------------------------
 Recalculated consumed cyclic
life on the effective date of   Remove affected rotor disks from service
           this AD
------------------------------------------------------------------------
(i) less than 15,700 FC......  Before exceeding 16,700 FC since new
(ii) 15,700 FC or more, but    Either:
 less than 16,700 FC.          (A) Within 1,000 FC or 19 months after
                                the effective date of this AD, whichever
                                occurs first; or
                               (B) Before exceeding 16,700 FC since new,
                               whichever occurs later.
(iii) 16,700 FC or more......  Either:
                               (A) Within 1,000 FC after the effective
                                date of this AD, or
                               (B) Before exceeding 20,000 FC since new,
                                or
                               (C) Within 19 months after the effective
                                date of this AD,
                               whichever occurs first.
------------------------------------------------------------------------

(h) Installation Prohibition

    After the effective date of this AD, installation of a 
serviceable spare engine or release to service of an engine after 
any shop visit, is allowed, provided the installed HPC stage 12 
rotor disk, P/N JR18449, is a serviceable part.

(i) Definition

    For the purpose of this AD, a serviceable part is an HPC stage 
12 rotor disk, P/N JR18449, that has not exceeded 20,500 FC for 
flight profile A or 16,700 FC for flight profile B, as applicable to 
engine operation.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, FAA, ECO Branch, Compliance and Airworthiness 
Division, 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.
    (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.

(k) Related Information

    (1) For more information about this AD, contact Robert Green, 
Aerospace Engineer, FAA, ECO Branch, Compliance and Airworthiness 
Division, 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 2017-0010, 
dated January 16, 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-2017-0140.
    (3) RRD Alert Non-Modification Service Bulletin TAY-72-A1813, 
Revision 1, dated January 27, 2017, which is not incorporated by 
reference in this AD, can be obtained from RRD, using the contact 
information in paragraph (k)(4) of this AD.
    (4) For service information identified in this AD, contact 
Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11-15827 Dahlewitz, 
Blankenfelde-Mahlow, Germany; phone: +49 0 33-7086-1944; fax: +49 0 
33-7086-3276.
    (5) You may view this service information at the FAA, Engine and 
Propeller Standards Branch, Policy and Innovation Division, 1200 
District Avenue, Burlington, MA. For information on the availability 
of this material at the FAA, call 781-238-7125.

(l) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on September 13, 2017.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2017-20531 Filed 9-25-17; 8:45 am]
 BILLING CODE 4910-13-P