AD 2016-17-01

[Federal Register Volume 81, Number 163 (Tuesday, August 23, 2016)]
[Rules and Regulations]
[Pages 57447-57449]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2016-20081]



[[Page 57447]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25513; Directorate Identifier 99-NE-61-AD; 
Amendment 39-18614; AD 2016-17-01]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding airworthiness directive (AD) 2006-18-14 for 
all Rolls-Royce Deutschland Ltd & Co KG (RRD) Tay 650-15 and Tay 651-54 
turbofan engines. AD 2006-18-14 required calculating and re-
establishing the cyclic life of stage 1 high-pressure turbine (HPT) 
disks, part number (P/N) JR32013 and P/N JR33838, and stage 1 low-
pressure turbine (LPT) disk, P/N JR32318A. In addition, this AD 
requires re-calculating the cyclic life, and would impose a reduced 
cyclic life of stage 1 HPT disk, P/N JR32013. This AD was prompted by 
RRD review of the cyclic life limit of parts affected by AD 2006-18-14 
and the RRD conclusion that the stage 1 HPT disk, P/N JR32013, requires 
further cyclic life limit reduction. We are issuing this AD to prevent 
failure of stage 1 HPT disks, P/N JR32013 and P/N JR33838, and stage 1 
LPT disk, P/N JR32318A, uncontained disk release and damage to the 
airplane.

DATES: This AD is effective September 27, 2016. The Director of the 
Federal Register approved the incorporation by reference a certain 
publication listed in this AD as of September 27, 2016.

ADDRESSES: For service information identified in this final rule, 
contact Rolls-Royce Deutschland Ltd & Co KG; Eschenweg 11, Dahlewitz, 
15827 Blankenfelde-Mahlow, Germany; phone: 49-0-33-7086-1064; fax: 49-
0-33-7086-3276. 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. It is also available on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2006-
25513.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2006-
25513; 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, 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: Philip Haberlen, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 
District Avenue, Burlington, MA 01803; phone: 781-238-7770; fax: 781-
238-7199; email: <a href="/cdn-cgi/l/email-protection#f5859d9c999c85db9d9497908799909bb5939494db929a83"><span class="__cf_email__" data-cfemail="6b1b030207021b45030a090e19070e052b0d0a0a450c041d">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2006-18-14, Amendment 39-14753 (71 FR 52988, 
September 8, 2006), (``AD 2006-18-14''). AD 2006-18-14 applied to the 
specified products. The NPRM published in the Federal Register on March 
11, 2016 (81 FR 12841). The NPRM proposed to require calculating and 
re-establishing the cyclic life of stage 1 HPT disks, P/N JR32013 and 
P/N JR33838, and stage 1 LPT disk, P/N JR32318A. The NPRM also proposed 
to require removing from service, using a drawdown schedule, those 
stage 1 HPT disks and stage 1 LPT disks operated under Tay 650-15 
engine flight plan profiles A, B, C, or D; or operated under the Tay 
651-54 engine datum flight profile, at reduced cyclic life limits found 
in the RRD Time Limits Manual (TLM) T-TAY-3RR, Chapter 05, Time Limits, 
Subject 05-10-01, dated September 15, 2014 and T-TAY-5RR, Chapter 05-
10-01, dated September 15, 2014.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received.

Changes to Related Service Information Under 1 CFR Part 51

    We removed Alert Non-Modification Service Bulletin (NMSB) No. TAY-
72-A1821, Revision 1, dated March 26, 2015 from Related Service 
Information under 1 CFR part 51, which is not incorporated by reference 
in this AD.
    We added the RRD TLM T-TAY-3RR, Chapter 05, Time Limits, Subject 
05-10-01, dated September 15, 2014.

Request To Change Compliance

    RRD requests that the cyclic life limits for the HPT stage 1 disk, 
P/N JR33838, installed in RRD Tay 650-15 and Tay 651-54 engines to be 
changed in this AD to match the life limits found in the RRD TLM T-TAY-
3RR, Chapter 05, Time Limits, Subject 05-10-01, dated September 15, 
2014 and the RRD TLM T-TAY-5RR, Chapter 05-10-01, dated September 15, 
2014. RRD updated their lifing analysis for the HPT stage 1 disk, P/N 
JR33838 and their new analysis justified an increased cyclic life limit 
for the HPT stage 1 disk, P/N JR33838 installed in the RRD Tay 650-15 
and Tay 651-54 engines for certain flight profiles. These life 
increases were reflected in the applicable service bulletin and the TLM 
and the FAA did not have an opportunity to mandate the increase in the 
cyclic life limits via AD until now. The FAA previously addressed the 
increase in the life limits via a global AMOC.
    We agree. The FAA accepts RRD's new lifing analysis. We changed the 
cyclic life limits in paragraphs (e)(3)(i)(B), (C), and (D) of this AD 
for the HPT stage 1 disk, P/N JR33838, installed in RRD Tay 650-15 
engines to 21,000 flight cycles since new (FCSN), 18,000 FCSN, and 
14,250 FCSN for flight profiles B, C, and D, respectively. We also 
changed the cyclic life limit in paragraph (e)(3)(i)(E) of this AD for 
the HPT stage 1 disk, P/N JR33838, installed in RRD Tay 651-54 engines 
to 14,250 FCSN for any flight profile.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously. We determined that these 
changes will not increase the economic burden on any operator or 
increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    RRD TLM T-TAY-3RR, Chapter 05, Time Limits, Subject 05-10-01, dated 
September 15, 2014, contains information on re-calculating the cyclic 
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.

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Other Related Service Information

    RRD TLM T-TAY-5RR, Chapter 05-10-01, dated September 15, 2014 
provides the new, reduced cyclic life limits for RRD Tay 651-54 engines 
operated under any engine flight plan profile.
    RRD Alert Non-Modification Service Bulletin TAY-72-A1821, Revision 
1, dated March 26, 2015, provides reduced cyclic life limits for RRD 
Tay 650-15 and RRD Tay 651-54 engines operated under various affected 
flight plan profiles.

Costs of Compliance

    We estimate that this AD affects 25 engines installed on airplanes 
of U.S. registry. We also estimate that it would take about 0.5 hours 
per engine to comply with this AD. The average labor rate is $85 per 
hour. The pro-rated life limit reduction cost is about $23,053 per 
engine. Based on these figures, we estimate the cost of this AD on U.S. 
operators to be $577,388.

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

    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 that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under 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 part 39 of the Federal Aviation 
Regulations (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 removing airworthiness directive (AD) 
2006-18-14, Amendment 39-14753 (71 FR 52988, September 8, 2006), (``AD 
2006-18-14''), and adding the following new AD:

2016-17-01 Rolls-Royce Deutschland Ltd & Co KG (formerly Rolls-Royce 
plc): Amendment 39-18614; Docket No. FAA-2006-25513; Directorate 
Identifier 99-NE-61-AD.

(a) Effective Date

    This AD is effective September 27, 2016.

(b) Affected ADs

    This AD supersedes AD 2006-18-14.

(c) Applicability

    This AD applies to Rolls-Royce Deutschland Ltd & Co (RRD) KG Tay 
650-15 and Tay 651-54 turbofan engines with stage 1 high-pressure 
turbine (HPT) disks, part number (P/N) JR32013 or P/N JR33838, or 
stage 1 low-pressure turbine (LPT) disks, P/N JR32318A, installed.

(d) Unsafe Condition

    This AD was prompted by RRD review of the cyclic life limit of 
parts affected by AD 2006-18-14 and the RRD conclusion that the 
stage 1 HPT disk, P/N JR32013, requires further cyclic life limit 
reduction. We are issuing this AD to prevent failure of stage 1 HPT 
disks, P/N JR32013 and P/N JR33838, and stage 1 LPT disk, P/N 
JR32318A, which could result in an uncontained engine failure and 
damage to the airplane.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Re-calculate the cyclic life of stage 1 HPT disks, P/N 
JR32013, as follows:
    (i) If a stage 1 HPT disk, P/N JR32013, was ever operated under 
a different engine flight plan profile than the engine flight plan 
profile operated on the last flight, or was ever installed and 
operated in a different engine model, do the following:
    (A) Within 30 days after the effective date of this AD, re-
calculate the cyclic life for each stage 1 HPT disk, P/N JR32013. 
Use the RRD Time Limits Manual (TLM) T-TAY-3RR, Chapter 05, Time 
Limits, Subject 05-10-01, Task 05-10-01-800-000, Subtask 05-10-01-
860-036, paragraph 1(E) or (1)(F), dated September 15, 2014 to re-
calculate the cyclic life.
    (B) Reserved.
    (ii) If you change your flight plan profile or install a stage 1 
HPT disk, P/N JR32013 or P/N JR33838, or stage 1 LPT disk, P/N 
JR32318A, into a different engine model after the effective date of 
this AD, re-calculate the cyclic life within 30 days of making the 
change. Use the RRD TLM T-TAY-3RR, Chapter 05, Time Limits, Subject 
05-10-01, Task 05-10-01-800-000, Subtask 05-10-01-860-036, paragraph 
1(E) or (1)(F), dated September 15, 2014 to re-calculate the cyclic 
life.
    (2) For engines with a stage 1 HPT disk, P/N JR32013, installed, 
do the following:
    (i) Remove from service any stage 1 HPT disk, P/N JR32013, 
within 100 flight cycles after the effective date of this AD or 
before exceeding the new, reduced cyclic life limits specified in 
paragraphs (e)(2)(i)(A) through (e)(2)(i)(E) of this AD, whichever 
occurs later, as follows:
    (A) For RRD Tay 650-15 engines operated under engine flight plan 
profile A, the new, reduced cyclic life limit is 18,900 flight 
cycles-since-new (FCSN).
    (B) For RRD Tay 650-15 engines operated under engine flight plan 
profile B, the new, reduced cyclic life limit is 15,500 FCSN.
    (C) For RRD Tay 650-15 engines operated under engine flight plan 
profile C, the new, reduced cyclic life limit is 11,500 FCSN.
    (D) For RRD Tay 650-15 engines operated under engine flight plan 
profile D, the new, reduced cyclic life limit is 9,300 FCSN.
    (E) For RRD Tay 651-54 engines operated under any engine flight 
plan profile, the new, reduced cyclic life limit is 10,873 FCSN.
    (ii) Reserved.
    (3) For engines with a stage 1 HPT disk, P/N JR33838, or stage 1 
LPT disk, P/N JR32318A, installed, do the following:
    (i) Remove from service any stage 1 HPT disk, P/N JR33838, or 
stage 1 LPT disk, P/N JR32318A, before exceeding the cyclic life 
limits specified in paragraphs (e)(3)(i)(A) through (e)(3)(i)(E) of 
this AD, as follows:
    (A) For RRD Tay 650-15 engines operated under engine flight plan 
profile A, the cyclic life limit for stage 1 HPT disk, P/N JR33838, 
and stage 1 LPT disk, P/N JR32318A, is 23,000 FCSN.
    (B) For RRD Tay 650-15 engines operated under engine flight plan 
profile B, the cyclic life limit for stage 1 HPT disk, P/N JR33838, 
and stage 1 LPT disk, P/N JR32318A, is 21,000 FCSN.
    (C) For RRD Tay 650-15 engines operated under engine flight plan 
profile C, the cyclic

[[Page 57449]]

life limit for stage 1 HPT disk, P/N JR33838, and stage 1 LPT disk, 
P/N JR32318A, is 18,000 FCSN.
    (D) For RRD Tay 650-15 engines operated under engine flight plan 
profile D, the cyclic life limit for stage 1 HPT disk, P/N JR33838, 
and stage 1 LPT disk, P/N JR32318A, is 14,250 FCSN.
    (E) For RRD Tay 651-54 engines operated under any engine flight 
plan profile, the cyclic life limit for stage 1 HPT disk, P/N 
JR33838, is 14,250 FCSN and the cyclic life limit for stage 1 LPT 
disk, P/N JR32318A, is 20,000 FCSN.
    (ii) Reserved.

(f) Installation Prohibition

    After the effective date of this AD, do not install any part 
identified in paragraph (e) of this AD into any engine, or return 
any engine to service with any part identified in paragraph (e) of 
this AD, installed, if the part exceeds the cyclic life limit 
specified in paragraphs (e)(2) and (e)(3) of this AD.

(g) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, 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: <a href="/cdn-cgi/l/email-protection#5a1b141f771b1e771b1715191a3c3b3b743d352c"><span class="__cf_email__" data-cfemail="377679721a76731a767a78747751565619505841">[email&#160;protected]</span></a>.

(h) Related Information

    (1) For more information about this AD, contact Philip Haberlen, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; 
phone: 781-238-7770; fax: 781-238-7199; email: 
<a href="/cdn-cgi/l/email-protection#7c0c141510150c52141d1e190e1019123c1a1d1d521b130a"><span class="__cf_email__" data-cfemail="d2a2babbbebba2fcbab3b0b7a0beb7bc92b4b3b3fcb5bda4">[email&#160;protected]</span></a>.
    (2) Refer to MCAI European Aviation Safety Agency, AD 2015-0056, 
dated March 31, 2015, for more information. You may examine the MCAI 
in the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by 
searching for and locating it in Docket No. FAA-2006-25513.
    (3) Rolls-Royce Deutschland Ltd & Co KG Alert Non-Modification 
Service Bulletin No. TAY-72-A1821, Revision 1, dated March 26, 2015, 
which is not incorporated by reference in this AD, can be obtained 
from Rolls-Royce Deutschland Ltd & Co KG, using the contact 
information in paragraph (i)(3) of this AD.
    (4) RRD TLM T-TAY-5RR, Chapter 05-10-01, dated September 15, 
2014.
    (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.

(i) 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) Rolls-Royce Deutschland Ltd & Co KG, Time Limits Manual T-
TAY-3RR, Chapter 05, Time Limits, Subject 05-10-01, dated September 
15, 2014.
    (ii) Reserved.
    (3) For Rolls-Royce Deutschland Ltd & Co KG service information 
identified in this AD, contact Rolls-Royce Deutschland Ltd & Co KG, 
Eschenweg 11, Dahlewitz, 15827 Blankenfelde-Mahlow, Germany; phone: 
49-0-33-7086-1064; fax: 49-0-33-7086-3276.
    (4) You may view this service information at FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA. For 
information on the availability of this material at the FAA, call 
781-238-7125.
    (5) You may view this service information at the National 
Archives and Records Administration (NARA). For information on the 
availability of this material at NARA, call 202-741-6030, or go to: 
<a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Burlington, Massachusetts, on August 16, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-20081 Filed 8-22-16; 8:45 am]
 BILLING CODE 4910-13-P