81_FR_12889 81 FR 12841 - Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Turbofan Engines

81 FR 12841 - Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Turbofan Engines

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 48 (March 11, 2016)

Page Range12841-12843
FR Document2016-05463

We propose to supersede airworthiness directive (AD) 2006-18- 14 that applies to all Rolls-Royce Deutschland Ltd & Co KG (RRD) Tay 650-15 and Tay 651-54 turbofan engines. AD 2006-18-14 requires 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. This proposed AD would require re-calculating the cyclic life, and would impose a reduced cyclic life, of stage 1 HPT disk, P/N JR32013. We are proposing 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.

Federal Register, Volume 81 Issue 48 (Friday, March 11, 2016) 
[Federal Register Volume 81, Number 48 (Friday, March 11, 2016)]
[Proposed Rules]
[Pages 12841-12843]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-05463]


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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]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede airworthiness directive (AD) 2006-18-
14 that applies to all Rolls-Royce Deutschland Ltd & Co KG (RRD) Tay 
650-15 and Tay 651-54 turbofan engines. AD 2006-18-14 requires 
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. 
This proposed AD would require re-calculating the cyclic life, and 
would impose a reduced cyclic life, of stage 1 HPT disk, P/N JR32013. 
We are proposing 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.

DATES: We must receive comments on this proposed AD by May 10, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed 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. You may view this service information at the FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA. For 
information on the availability of this material at the FAA, call 781-
238-7125.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-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 proposed 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 in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

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: [email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2006-
25513; Directorate Identifier 99-NE-61-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On August 30, 2006, we issued AD 2006-18-14, Amendment 39-14753 (71 
FR 52988, September 8, 2006), for all RRD Tay 650-15 and Tay 651-54 
turbofan engines. AD 2006-18-14 requires 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, that have been exposed to 
different engine flight plan profiles. AD 2006-18-14 also requires 
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. AD 2006-18-14 
resulted from RRD updating their low-cycle-fatigue analysis for stage 1 
HPT disks and stage 1 LPT disks and reducing their cyclic life limits. 
We issued AD 2006-18-14 to prevent cracks leading to turbine disk 
failure, which could result in an uncontained engine failure and damage 
to the airplane.

Actions Since AD 2006-18-14 Was Issued

    Since we issued AD 2006-18-14, RRD reviewed the cyclic life limit 
of parts affected by AD 2006-18-14; RRD concluded that the stage 1 HPT 
disk, P/N JR32013, requires further cyclic life limit reduction. RRD 
did not further reduce the cyclic life limit of stage 1 HPT disk, P/N 
JR33838, or stage 1 LPT disk, P/N JR32318A. Accordingly, the cyclic 
life limits of stage 1 HPT disk, P/N JR33838, and stage 1 LPT disk, P/N 
JR32318A, as imposed by AD 2006-18-14, remain unchanged in this 
proposed AD.
    Since AD 2006-18-14 was issued, the European Aviation Safety Agency 
(EASA) issued AD 2015-0056, dated March 31, 2015 to reduce the cyclic 
life limits of the stage 1 HPT disk, P/N JR32013.

[[Page 12842]]

Related Service Information Under 1 CFR Part 51

    RRD has issued Alert Non-Modification Service Bulletin (NMSB) No. 
TAY-72-A1821, Revision 1 dated March 26, 2015. The Alert NMSB describes 
procedures to re-calculate the consumed cyclic life of stage 1 HPT 
disk, P/N JR32013. 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 
of this NPRM.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require re-calculating and re-establishing 
the cyclic life of stage 1 HPT disk, P/N JR32013. This proposed AD 
would also require removing from service those stage 1 HPT disks, P/N 
JR32013, depending on engine flight plan profiles and engine models, at 
certain reduced cyclic life limits, using a drawdown schedule.

Costs of Compliance

    We estimate that this proposed 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 proposed 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 proposed 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

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska to the extent 
that it justifies making a regulatory distinction, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by 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:

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

(a) Comments Due Date

    We must receive comments by May 10, 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 reducing the cyclic life limit for 
certain stage 1 HPT disks, P/N JR32013. We are issuing this AD to 
prevent cracks leading to turbine disk failure, 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, and/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, 
using paragraphs 3.A.(1)(b)(1) through 3.A.(1)(b)(4) of the 
Accomplishment Instructions of RRD Alert Non-Modification Service 
Bulletin (NMSB) No. TAY-72-A1821, Revision 1, dated March 26, 2015.
    (B) Reserved.
    (ii) If you change your flight plan profile and/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 of the part(s) as described 
in paragraph (e)(1)(i)(A) of this AD within 30 days of making the 
change.
    (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

[[Page 12843]]

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, 
is 20,000 FCSN; and the cyclic life limit for 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 life limit for stage 1 HPT disk, P/N JR33838, 
is 14,700 FCSN; and the cyclic life limit for 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, 
is 11,000 FCSN; and the cyclic life limit for 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 12,600 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: [email protected].

(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: 
[email protected].
    (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 http://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 
can be obtained from Rolls-Royce Deutschland Ltd & Co KG, using the 
contact information in paragraph (h)(4) of this AD.
    (4) For 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.
    (5) You may view this service information at the FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA. For 
information on the availability of this material at the FAA, call 
781-238-7125.

    Issued in Burlington, Massachusetts, on February 26, 2016.
Colleen M. D'Alessandro,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-05463 Filed 3-10-16; 8:45 am]
BILLING CODE 4910-13-P

Federal Register / Vol. 81, No. 48 / Friday, March 11, 2016 / Proposed Rules 12841 telephone (817) 222–5110; email 9-ASW- DATES: We must receive comments on comments on the overall regulatory, FTW-AMOC-Requests@faa.gov. this proposed AD by May 10, 2016. economic, environmental, and energy (2) For operations conducted under a 14 aspects of this proposed AD. We will CFR part 119 operating certificate or under ADDRESSES: You may send comments, 14 CFR part 91, subpart K, we suggest that using the procedures found in 14 CFR consider all comments received by the you notify your principal inspector, or 11.43 and 11.45, by any of the following closing date and may amend this lacking a principal inspector, the manager of methods: proposed AD because of those the local flight standards district office or • Federal eRulemaking Portal: Go to comments. certificate holding district office before http://www.regulations.gov. Follow the operating any aircraft complying with this We will post all comments we instructions for submitting comments. receive, without change, to http:// AD through an AMOC. • Fax: 202–493–2251. www.regulations.gov, including any (g) Additional Information • Mail: U.S. Department of personal information you provide. We The subject of this AD is addressed in Transportation, Docket Operations, M– will also post a report summarizing each European Aviation Safety Agency (EASA) AD 30, West Building Ground Floor, Room substantive verbal contact we receive No. 2011–0207, dated October 20, 2011. You W12–140, 1200 New Jersey Avenue SE., may view the EASA AD on the Internet at about this proposed AD. Washington, DC 20590. http://www.regulations.gov in Docket No. • Hand Delivery: Deliver to Mail Discussion FAA-2016–4278. address above between 9 a.m. and 5 (h) Subject p.m., Monday through Friday, except On August 30, 2006, we issued AD Joint Aircraft Service Component (JASC) Federal holidays. 2006–18–14, Amendment 39–14753 (71 Code: 2900: Hydraulic Power. For service information identified in FR 52988, September 8, 2006), for all this proposed AD, contact Rolls-Royce RRD Tay 650–15 and Tay 651–54 Issued in Fort Worth, Texas, on March 3, turbofan engines. AD 2006–18–14 2016. Deutschland Ltd & Co KG, Eschenweg 11, Dahlewitz, 15827 Blankenfelde- requires calculating and re-establishing Scott A. Horn, Mahlow, Germany; phone: 49–0–33– the cyclic life of stage 1 HPT disks, P/ Acting Manager, Rotorcraft Directorate, N JR32013 and P/N JR33838, and stage Aircraft Certification Service. 7086–1064; fax: 49–0–33–7086–3276. You may view this service information 1 LPT disk, P/N JR32318A, that have [FR Doc. 2016–05368 Filed 3–10–16; 8:45 am] at the FAA, Engine & Propeller been exposed to different engine flight BILLING CODE 4910–13–P Directorate, 1200 District Avenue, plan profiles. AD 2006–18–14 also Burlington, MA. For information on the requires removing from service, using a availability of this material at the FAA, drawdown schedule, those stage 1 HPT DEPARTMENT OF TRANSPORTATION call 781–238–7125. disks and stage 1 LPT disks operated Federal Aviation Administration Examining the AD Docket under Tay 650–15 engine flight plan profiles A, B, C, or D; or operated under You may examine the AD docket on the Tay 651–54 engine datum flight 14 CFR Part 39 the Internet at http:// profile, at reduced cyclic life limits. AD [Docket No. FAA–2006–25513; Directorate www.regulations.gov by searching for 2006–18–14 resulted from RRD Identifier 99–NE–61–AD] and locating Docket No. FAA–2006– updating their low-cycle-fatigue RIN 2120–AA64 25513; or in person at the Docket analysis for stage 1 HPT disks and stage Management Facility between 9 a.m. 1 LPT disks and reducing their cyclic Airworthiness Directives; Rolls-Royce and 5 p.m., Monday through Friday, life limits. We issued AD 2006–18–14 to Deutschland Ltd & Co KG Turbofan except Federal holidays. The AD docket prevent cracks leading to turbine disk Engines contains this proposed AD, the failure, which could result in an mandatory continuing airworthiness uncontained engine failure and damage AGENCY: Federal Aviation information, regulatory evaluation, any to the airplane. Administration (FAA), DOT. comments received, and other ACTION: Notice of proposed rulemaking information. The address for the Docket Actions Since AD 2006–18–14 Was (NPRM). Office (phone: 800–647–5527) is in the Issued SUMMARY: We propose to supersede ADDRESSES section. Comments will be available in the AD docket shortly after Since we issued AD 2006–18–14, RRD airworthiness directive (AD) 2006–18– receipt. reviewed the cyclic life limit of parts 14 that applies to all Rolls-Royce FOR FURTHER INFORMATION CONTACT: affected by AD 2006–18–14; RRD Deutschland Ltd & Co KG (RRD) Tay Philip Haberlen, Aerospace Engineer, concluded that the stage 1 HPT disk, P/ 650–15 and Tay 651–54 turbofan Engine Certification Office, FAA, Engine N JR32013, requires further cyclic life engines. AD 2006–18–14 requires & Propeller Directorate, 1200 District limit reduction. RRD did not further calculating and re-establishing the Avenue, Burlington, MA 01803; phone: reduce the cyclic life limit of stage 1 cyclic life of stage 1 high-pressure turbine (HPT) disks, part number (P/N) 781–238–7770; fax: 781–238–7199; HPT disk, P/N JR33838, or stage 1 LPT JR32013 and P/N JR33838, and stage 1 email: philip.haberlen@faa.gov. disk, P/N JR32318A. Accordingly, the low-pressure turbine (LPT) disk, P/N cyclic life limits of stage 1 HPT disk, P/ SUPPLEMENTARY INFORMATION: JR32318A. This proposed AD would N JR33838, and stage 1 LPT disk, P/N asabaliauskas on DSK3SPTVN1PROD with PROPOSALS require re-calculating the cyclic life, and Comments Invited JR32318A, as imposed by AD 2006–18– would impose a reduced cyclic life, of We invite you to send any written 14, remain unchanged in this proposed stage 1 HPT disk, P/N JR32013. We are relevant data, views, or arguments about AD. proposing this AD to prevent failure of this proposed AD. Send your comments Since AD 2006–18–14 was issued, the stage 1 HPT disks, P/N JR32013 and P/ to an address listed under the European Aviation Safety Agency N JR33838, and stage 1 LPT disk, P/N ADDRESSES section. Include ‘‘Docket No. (EASA) issued AD 2015–0056, dated JR32318A, which could result in an FAA–2006–25513; Directorate Identifier March 31, 2015 to reduce the cyclic life uncontained engine failure and damage 99–NE–61–AD’’ at the beginning of your limits of the stage 1 HPT disk, P/N to the airplane. comments. We specifically invite JR32013. VerDate Sep<11>2014 16:25 Mar 10, 2016 Jkt 238001 PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 E:\FR\FM\11MRP1.SGM 11MRP1

12842 Federal Register / Vol. 81, No. 48 / Friday, March 11, 2016 / Proposed Rules Related Service Information Under 1 that is likely to exist or develop on (c) Applicability CFR Part 51 products identified in this rulemaking This AD applies to Rolls-Royce RRD has issued Alert Non- action. Deutschland Ltd & Co (RRD) KG Tay 650–15 and Tay 651–54 turbofan engines with stage Modification Service Bulletin (NMSB) Regulatory Findings 1 high-pressure turbine (HPT) disks, part No. TAY–72–A1821, Revision 1 dated number (P/N) JR32013 or P/N JR33838, or March 26, 2015. The Alert NMSB We have determined that this stage 1 low-pressure turbine (LPT) disks, describes procedures to re-calculate the proposed AD would not have federalism P/N JR32318A, installed. consumed cyclic life of stage 1 HPT implications under Executive Order 13132. This proposed AD would not (d) Unsafe Condition disk, P/N JR32013. This service information is reasonably available have a substantial direct effect on the This AD was prompted by RRD reducing States, on the relationship between the the cyclic life limit for certain stage 1 HPT because the interested parties have disks, P/N JR32013. We are issuing this AD access to it through their normal course national Government and the States, or to prevent cracks leading to turbine disk of business or by the means identified on the distribution of power and failure, which could result in an uncontained in the ADDRESSES section of this NPRM. responsibilities among the various engine failure and damage to the airplane. levels of government. FAA’s Determination (e) Compliance For the reasons discussed above, I We are proposing this AD because we certify that the proposed regulation: Comply with this AD within the evaluated all the relevant information compliance times specified, unless already (1) Is not a ‘‘significant regulatory done. and determined the unsafe condition action’’ under Executive Order 12866, (1) Re-calculate the cyclic life of stage 1 described previously is likely to exist or HPT disks, P/N JR32013, as follows: develop in other products of the same (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and (i) If a stage 1 HPT disk, P/N JR32013, was type design. ever operated under a different engine flight Procedures (44 FR 11034, February 26, Proposed AD Requirements plan profile than the engine flight plan 1979), profile operated on the last flight, and/or was This proposed AD would require re- (3) Will not affect intrastate aviation ever installed and operated in a different calculating and re-establishing the in Alaska to the extent that it justifies engine model, do the following: cyclic life of stage 1 HPT disk, P/N making a regulatory distinction, and (A) Within 30 days after the effective date JR32013. This proposed AD would also of this AD, re-calculate the cyclic life for each (4) Will not have a significant stage 1 HPT disk, P/N JR32013, using require removing from service those economic impact, positive or negative, paragraphs 3.A.(1)(b)(1) through 3.A.(1)(b)(4) stage 1 HPT disks, P/N JR32013, on a substantial number of small entities of the Accomplishment Instructions of RRD depending on engine flight plan profiles under the criteria of the Regulatory Alert Non-Modification Service Bulletin and engine models, at certain reduced Flexibility Act. (NMSB) No. TAY–72–A1821, Revision 1, cyclic life limits, using a drawdown dated March 26, 2015. schedule. List of Subjects in 14 CFR Part 39 (B) Reserved. (ii) If you change your flight plan profile Costs of Compliance Air transportation, Aircraft, Aviation and/or install a stage 1 HPT disk, P/N safety, Incorporation by reference, JR32013 or P/N JR33838, or stage 1 LPT disk, We estimate that this proposed AD Safety. P/N JR32318A, into a different engine model affects 25 engines installed on airplanes after the effective date of this AD, re-calculate of U.S. registry. We also estimate that it The Proposed Amendment the cyclic life of the part(s) as described in would take about 0.5 hours per engine paragraph (e)(1)(i)(A) of this AD within 30 to comply with this proposed AD. The Accordingly, under the authority days of making the change. average labor rate is $85 per hour. The delegated to me by the Administrator, (2) For engines with a stage 1 HPT disk, pro-rated life limit reduction cost is the FAA proposes to amend 14 CFR part P/N JR32013, installed, do the following: about $23,053 per engine. Based on 39 as follows: (i) Remove from service any stage 1 HPT these figures, we estimate the cost of disk, P/N JR32013, within 100 flight cycles PART 39—AIRWORTHINESS after the effective date of this AD or before this proposed AD on U.S. operators to DIRECTIVES exceeding the new, reduced cyclic life limits be $577,388. specified in paragraphs (e)(2)(i)(A) through Authority for This Rulemaking ■ 1. The authority citation for part 39 (e)(2)(i)(E) of this AD, whichever occurs later, continues to read as follows: as follows: Title 49 of the United States Code (A) For RRD Tay 650–15 engines operated specifies the FAA’s authority to issue Authority: 49 U.S.C. 106(g), 40113, 44701. under engine flight plan profile A, the new, rules on aviation safety. Subtitle I, reduced cyclic life limit is 18,900 flight § 39.13 [Amended] Section 106, describes the authority of cycles-since-new (FCSN). the FAA Administrator. Subtitle VII, ■ 2. The FAA amends § 39.13 by (B) For RRD Tay 650–15 engines operated Aviation Programs, describes in more removing airworthiness directive (AD) under engine flight plan profile B, the new, 2006–18–14, Amendment 39–14753 (71 reduced cyclic life limit is 15,500 FCSN. detail the scope of the Agency’s FR 52988, September 8, 2006) (‘‘AD (C) For RRD Tay 650–15 engines operated authority. under engine flight plan profile C, the new, We are issuing this rulemaking under 2006–18–14’’), and adding the following reduced cyclic life limit is 11,500 FCSN. the authority described in Subtitle VII, new AD: (D) For RRD Tay 650–15 engines operated Part A, Subpart III, Section 44701, under engine flight plan profile D, the new, asabaliauskas on DSK3SPTVN1PROD with PROPOSALS Rolls-Royce Deutschland Ltd & Co KG ‘‘General requirements.’’ Under that (formerly Rolls-Royce plc): Docket No. reduced cyclic life limit is 9,300 FCSN. section, Congress charges the FAA with FAA–2006–25513; Directorate Identifier (E) For RRD Tay 651–54 engines operated promoting safe flight of civil aircraft in 99–NE–61–AD. under any engine flight plan profile, the new, air commerce by prescribing regulations reduced cyclic life limit is 10,873 FCSN. (a) Comments Due Date (ii) Reserved. for practices, methods, and procedures (3) For engines with a stage 1 HPT disk, P/ We must receive comments by May 10, the Administrator finds necessary for 2016. N JR33838, or stage 1 LPT disk, safety in air commerce. This regulation P/N JR32318A, installed, do the following: is within the scope of that authority (b) Affected ADs (i) Remove from service any stage 1 HPT because it addresses an unsafe condition This AD supersedes AD 2006–18–14. disk, P/N JR33838, or stage 1 LPT disk, P/N VerDate Sep<11>2014 16:25 Mar 10, 2016 Jkt 238001 PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 E:\FR\FM\11MRP1.SGM 11MRP1

Federal Register / Vol. 81, No. 48 / Friday, March 11, 2016 / Proposed Rules 12843 JR32318A, before exceeding the cyclic life (5) You may view this service information S.A., 40220 Tarnos, France; phone: (33) limits specified in paragraphs (e)(3)(i)(A) at the FAA, Engine & Propeller Directorate, 05 59 74 40 00; fax: (33) 05 59 74 45 15. through (e)(3)(i)(E) of this AD, as follows: 1200 District Avenue, Burlington, MA. For You may view this service information (A) For RRD Tay 650–15 engines operated information on the availability of this under engine flight plan profile A, the cyclic material at the FAA, call 781–238–7125. at the FAA, Engine & Propeller life limit for stage 1 HPT disk, P/N JR33838, Directorate, 1200 District Avenue, Issued in Burlington, Massachusetts, on Burlington, MA. For information on the and stage 1 LPT disk, P/N JR32318A, is February 26, 2016. availability of this material at the FAA, 23,000 FCSN. (B) For RRD Tay 650–15 engines operated Colleen M. D’Alessandro, call 781–238–7125. under engine flight plan profile B, the cyclic Manager, Engine & Propeller Directorate, life limit for stage 1 HPT disk, P/N JR33838, Aircraft Certification Service. Examining the AD Docket is 20,000 FCSN; and the cyclic life limit for [FR Doc. 2016–05463 Filed 3–10–16; 8:45 am] You may examine the AD docket on stage 1 LPT disk, P/N JR32318A, is 21,000 the Internet at http:// BILLING CODE 4910–13–P FCSN. (C) For RRD Tay 650–15 engines operated www.regulations.gov by searching for under engine flight plan profile C, the cyclic and locating Docket No. FAA–2010– life limit for stage 1 HPT disk, P/N JR33838, DEPARTMENT OF TRANSPORTATION 0219; or in person at the Docket is 14,700 FCSN; and the cyclic life limit for Management Facility between 9 a.m. stage 1 LPT disk, P/N JR32318A, is 18,000 Federal Aviation Administration and 5 p.m., Monday through Friday, FCSN. except Federal holidays. The AD docket (D) For RRD Tay 650–15 engines operated 14 CFR Part 39 contains this proposed AD, the under engine flight plan profile D, the cyclic mandatory continuing airworthiness [Docket No. FAA–2010–0219; Directorate life limit for stage 1 HPT disk, P/N JR33838, is 11,000 FCSN; and the cyclic life limit for Identifier 2010–NE–14–AD] information, regulatory evaluation, any stage 1 LPT disk, P/N JR32318A, is 14,250 RIN 2120–AA64 comments received, and other FCSN. information. The address for the Docket (E) For RRD Tay 651–54 engines operated Airworthiness Directives; Turbomeca Office (phone: 800–647–5527) is in the under any engine flight plan profile, the S.A. Turboshaft Engines ADDRESSES section. Comments will be cyclic life limit for stage 1 HPT disk, P/N available in the AD docket shortly after JR33838, is 12,600 FCSN and the cyclic life AGENCY: Federal Aviation receipt. limit for stage 1 LPT disk, P/N JR32318A, is Administration (FAA), DOT. 20,000 FCSN. FOR FURTHER INFORMATION CONTACT: ACTION: Notice of proposed rulemaking Contact Brian Kierstead, Aerospace (ii) Reserved. (NPRM). Engineer, Engine Certification Office, (f) Installation Prohibition FAA, Engine & Propeller Directorate, SUMMARY: We propose to supersede After the effective date of this AD, do not 1200 District Avenue, Burlington, MA install any part identified in paragraph (e) of airworthiness directive (AD) 2010–11– 10 that applies to all Turbomeca S.A., 01803; phone: 781–238–7772, fax: 781– this AD into any engine, or return any engine Astazou XIV B and XIV H turboshaft 238–7199; email: brian.kierstead@ to service with any part identified in paragraph (e) of this AD, installed, if the part engines. AD 2010–11–10 requires faa.gov. exceeds the cyclic life limit specified in inspection of certain third stage turbine SUPPLEMENTARY INFORMATION: paragraphs (e)(2) and (e)(3) of this AD. wheels and removal of any damaged wheel. This AD was prompted by a Comments Invited (g) Alternative Methods of Compliance (AMOCs) report of a third stage turbine wheel We invite you to send any written The Manager, Engine Certification Office, crack detected during engine overhaul. relevant data, views, or arguments about may approve AMOCs for this AD. Use the This proposed AD would expand the this proposed AD. Send your comments procedures found in 14 CFR 39.19 to make population and frequency of repetitive to an address listed under the your request. You may email your request to: inspections. We are proposing this AD ADDRESSES section. Include ‘‘Docket No. ANE-AD-AMOC@faa.gov. to prevent uncontained failure of the FAA–2010–0219; Directorate Identifier (h) Related Information third stage turbine wheel, which could 2010–NE–14–AD’’ at the beginning of result in damage to the engine and your comments. We specifically invite (1) For more information about this AD, contact Philip Haberlen, Aerospace Engineer, damage to the helicopter. comments on the overall regulatory, Engine Certification Office, FAA, Engine & DATES: We must receive comments on economic, environmental, and energy Propeller Directorate, 1200 District Avenue, this proposed AD by May 10, 2016. aspects of this proposed AD. We will Burlington, MA 01803; phone: 781–238– ADDRESSES: You may send comments, consider all comments received by the 7770; fax: 781–238–7199; email: using the procedures found in 14 CFR closing date and may amend this philip.haberlen@faa.gov. proposed AD because of those 11.43 and 11.45, by any of the following (2) Refer to MCAI European Aviation comments. Safety Agency, AD 2015–0056, dated March methods: 31, 2015, for more information. You may • Federal eRulemaking Portal: Go to We will post all comments we examine the MCAI in the AD docket on the http://www.regulations.gov. Follow the receive, without change, to http:// Internet at http://www.regulations.gov by instructions for submitting comments. www.regulations.gov, including any searching for and locating it in Docket No. • Fax: 202–493–2251. personal information you provide. We FAA–2006–25513. • Mail: U.S. Department of will also post a report summarizing each (3) Rolls-Royce Deutschland Ltd & Co KG Transportation, Docket Operations, M– substantive verbal contact we receive asabaliauskas on DSK3SPTVN1PROD with PROPOSALS Alert Non-Modification Service Bulletin No. 30, West Building Ground Floor, Room about this proposed AD. TAY–72–A1821, Revision 1, dated March 26, W12–140, 1200 New Jersey Avenue SE., 2015 can be obtained from Rolls-Royce Discussion Washington, DC 20590. Deutschland Ltd & Co KG, using the contact information in paragraph (h)(4) of this AD. • Hand Delivery: Deliver to Mail On May 19, 2010, we issued AD (4) For service information identified in address above between 9 a.m. and 5 2010–11–10, Amendment 39–16315 (75 this AD, contact Rolls-Royce Deutschland Ltd p.m., Monday through Friday, except FR 30270, June 1, 2010), (‘‘AD 2010–11– & Co KG, Eschenweg 11, Dahlewitz, 15827 Federal holidays. 10’’), for all Turbomeca S.A., Astazou Blankenfelde-Mahlow, Germany; phone: 49– For service information identified in XIV B and XIV H turboshaft engines. AD 0–33–7086–1064; fax: 49–0–33–7086–3276. this proposed AD, contact Turbomeca 2010–11–10 requires inspection of VerDate Sep<11>2014 16:25 Mar 10, 2016 Jkt 238001 PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 E:\FR\FM\11MRP1.SGM 11MRP1


Document Created: 2016-03-11 01:51:52
Document Modified: 2016-03-11 01:51:52
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionProposed Rules
ActionNotice of proposed rulemaking (NPRM).
DatesWe must receive comments on this proposed AD by May 10, 2016.
ContactPhilip 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: [email protected]
FR Citation81 FR 12841 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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