Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Turbofan Engines, 57447-57449 [2016-20081]
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Federal Register / Vol. 81, No. 163 / Tuesday, August 23, 2016 / Rules and Regulations
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
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 reestablishing 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
https://www.regulations.gov by searching
for and locating Docket No. FAA–2006–
25513.
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SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
VerDate Sep<11>2014
14:39 Aug 22, 2016
Jkt 238001
www.regulations.gov 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: philip.haberlen@faa.gov.
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.
PO 00000
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Fmt 4700
Sfmt 4700
57447
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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57448
Federal Register / Vol. 81, No. 163 / Tuesday, August 23, 2016 / Rules and Regulations
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.
(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.
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.
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:
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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),
VerDate Sep<11>2014
14:39 Aug 22, 2016
Jkt 238001
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
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
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.
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Frm 00010
Fmt 4700
Sfmt 4700
(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
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Federal Register / Vol. 81, No. 163 / Tuesday, August 23, 2016 / Rules and Regulations
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:
ANE-AD-AMOC@faa.gov.
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(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:
philip.haberlen@faa.gov.
(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 https://www.regulations.gov 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.
VerDate Sep<11>2014
14:39 Aug 22, 2016
Jkt 238001
(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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–8989; Directorate
Identifier 2016–CE–025–AD; Amendment
39–18617; AD 2016–17–04]
RIN 2120–AA64
Airworthiness Directives; All Hot Air
Balloons
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all hot
´
air balloons to determine if BALONY
´ˇ
´ˇ
KUBICEK spol. s r.o. Model Kubıcek
burners equipped with fuel hoses made
of ‘‘EGEFLEX’’ material are installed.
This AD results from mandatory
continuing airworthiness information
(MCAI) issued by the aviation authority
of another country to identify and
correct an unsafe condition on an
aviation product. The MCAI describes
the unsafe condition as propane leaks
found on burners equipped with fuel
hoses made of EGEFLEX material. We
are issuing this AD to require actions to
address the unsafe condition on these
products.
SUMMARY:
This AD is effective August 29,
2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of August 29, 2016.
DATES:
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
57449
We must receive comments on this
AD by October 7, 2016.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
´
´ˇ
this AD, contact BALONY KUBICEK
´
spol. s r.o., Jarnı 2a, 614 00 Brno, Czech
Republic, telephone: +420 545 422 620;
fax: +420 545 422 621; email: info@
kubicekballons.cz; Internet: https://
www.kubicekballoons.eu. You may view
this referenced service information at
the FAA, Small Airplane Directorate,
901 Locust, Kansas City, Missouri
64106. For information on the
availability of this material at the FAA,
call (816) 329–4148. It is also available
on the Internet at https://
www.regulations.gov by searching for
locating Docket No. FAA–2016–8989.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
8989; 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 regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (telephone (800) 647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Karl
Schletzbaum, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4123; fax: (816)
329–4090; email: karl.schletzbaum@
faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued AD No. 2016–
0151, dated July 26, 2016 (referred to
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]]>Agencies
[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 [www.gpo.gov]
[FR Doc No: 2016-20081]
[[Page 57447]]
=======================================================================
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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 https://www.regulations.gov by searching for and locating Docket No. FAA-2006-
25513.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov 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: philip.haberlen@faa.gov.
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.
[[Page 57448]]
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: ANE-AD-AMOC@faa.gov.
(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:
philip.haberlen@faa.gov.
(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 https://www.regulations.gov 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:
https://www.archives.gov/federal-register/cfr/ibr-locations.html.
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
