Airworthiness Directives; Rolls-Royce plc Turbofan Engines, 56025-56026 [2014-22351]

Download as PDF Federal Register / Vol. 79, No. 181 / Thursday, September 18, 2014 / Proposed Rules specified in ALS document number 02334, issue 4, dated May 31, 2014, into your FAAaccepted maintenance program (maintenance manual). (4) Actions new to this AD for all airplanes: (i) For airplanes with Halon Fire Extinguishers that have not yet reached the 10 year life limit after the effective date of this AD, when the Halon Fire Extinguisher reaches its life limit of 10 years, before further flight, replace with an airworthy Halon Fire Extinguisher following Chapter 04–00–00 of the AMM, document number 01975, issue 19, dated May 31, 2014, of the Pilatus PC–6 Maintenance Manual; or ALS document number 02334, issue 4, dated May 31, 2014; as applicable. (ii) For airplanes with Halon Fire Extinguishers that have reached the 10 year life limit on or before the effective date of this AD, within the next 30 days after the effective date of this AD or within the next 10 hours TIS after the effective date of this AD, whichever occurs first, replace with an airworthy Halon Fire Extinguisher following Chapter 04–00–00 of the AMM, document number 01975, issue 19, dated May 31, 2014, of the Pilatus PC–6 Maintenance Manual; or ALS document number 02334, issue 4, dated May 31, 2014; as applicable. (iii) Repetitively, after replacing the airplanes Halon Fire Extinguisher as required in paragraphs (f)(4)(i) or (f)(4)(ii), within 10 years after each last replacement, replace with an airworthy Halon Fire Extinguisher. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS (g) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4059; fax: (816) 329– 4090; email: doug.rudolph@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (h) Related Information Refer to European Aviation Safety Agency (EASA) AD No.: 2014–0181, dated July 31, 2014, for related information. You may examine the MCAI on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2041–0717. For service information related to this AD, contact PILATUS AIRCRAFT LTD., Customer Liaison Manager, CH–6371 STANS, Switzerland; telephone: +41 (0) 41 619 65 80; fax: +41 (0) 41 619 65 76; Internet: http:// VerDate Sep<11>2014 17:14 Sep 17, 2014 Jkt 232001 www.pilatus-aircraft.com; email: fodermatt@ pilatus-aircraft.com. You may review 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. Issued in Kansas City, Missouri, on September 12, 2014. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–22273 Filed 9–17–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0561; Directorate Identifier 2014–NE–12–AD] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211 Trent 768– 60, 772–60, and 772B–60 turbofan engines. This proposed AD was prompted by fractures of the highpressure/intermediate-pressure (HP/IP) turbine support internal oil feed tube. This proposed AD would require inspection of the oil feed tube sealing sleeve and removal of those oil feed tube sealing sleeves that fail inspection. We are proposing this AD to prevent failure of the HP/IP turbine support internal oil feed tube, which could result in uncontained engine failure and damage to the airplane. DATES: We must receive comments on this proposed AD by November 17, 2014. SUMMARY: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: 202–493–2251. ADDRESSES: PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 56025 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–2014– 0561; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the mandatory continuing airworthiness information (MCAI), the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Wego Wang, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7134; fax: 781–238– 7199; email: wego.wang@faa.gov. 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–2014–0561; Directorate Identifier 2014–NE–12–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 based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD 2014– 0168, dated July 16, 2014 (referred to hereinafter as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: There have been nine occurrences of high oil consumption, caused by fracture of the High/ Intermediate Pressure (HP/IP) turbine support internal oil feed tube Part Number (P/N) FW45909. The oil feed tube threaded end adaptor and sealing sleeve P/N FW15003 are designed to form a sliding joint which, if restrained, can compress the oil feed tube during thermal contraction of the turbine casing at the end E:\FR\FM\18SEP1.SGM 18SEP1 56026 Federal Register / Vol. 79, No. 181 / Thursday, September 18, 2014 / Proposed Rules of the flight cycle. On each subsequent flight, the thermal growth and contraction of the turbine casing relative to the oil tube, during the heating and cooling phases of the flight cycle, apply a load cycle to the tube, which may lead to low cycle fatigue fracture. This AD requires removal of certain HP/IP turbine support internal oil feed tube sealing sleeves to prevent oil exhaustion that could result in uncontained engine failure and damage to the airplane. You may obtain further information by examining the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0561. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of the United Kingdom, and is approved for operation in the United States. Pursuant to our bilateral agreement with the European Community, EASA has notified us of the unsafe condition described in the MCAI. We are proposing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. This proposed AD would require a one-time on-wing or inshop inspection of the affected engines and removal from service of all affected P/N FW15003 oil feed tube sealing sleeves. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS Costs of Compliance We estimate that this proposed AD affects 69 engines installed on airplanes of U.S. registry. We also estimate that it would take about 8.5 hours per engine to comply with this proposed AD. The average labor rate is $85 per hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $49,853. 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 VerDate Sep<11>2014 17:14 Sep 17, 2014 Jkt 232001 safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. Amend § 39.13 by adding the following new airworthiness directive (AD): ■ Rolls-Royce plc: Docket No. FAA–2014– 0561; Directorate Identifier 2014–NE– 12–AD. (a) Comments Due Date We must receive comments by November 17, 2014. (b) Affected ADs None. (c) Applicability This AD applies to Rolls-Royce plc (RR) RB211 Trent 768–60, 772–60, and 772B–60 PO 00000 Frm 00007 Fmt 4702 Sfmt 9990 (d) Reason This AD was prompted by fractures of the HP/IP turbine support internal oil feed tube. We are issuing this AD to prevent failure of the HP/IP turbine support internal oil feed tube, which could result in uncontained engine failure and damage to the airplane. (e) Actions and Compliance Comply with this AD within the compliance times specified, unless already done. (1) Within 6 months after the effective date of this AD, perform on-wing or in-shop inspection for, and remove from service, any affected HP/IP turbine support internal oil feed tube sealing sleeve. (2) Remove from service any HP/IP turbine support internal oil feed tube sealing sleeve on which markings cannot be sufficiently identified to determine whether said sealing sleeve is part of the affected population. (3) From the effective date of this AD, you may install on engines HP/IP turbine support internal oil feed tube sealing sleeves, P/N FW15003, that are marked with the prefix ‘‘B/N’’ followed by a six digit batch number, provided that the part is marked with 102013, 112013 or 102013L. (f) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs to this AD. Use the procedures found in 14 CFR 39.19 to make your request. (g) Related Information PART 39—AIRWORTHINESS DIRECTIVES § 39.13 turbofan engines serial numbers 41693– 42309 inclusive, 42313, 42318, 42319, 42320, 42328, and 42330 with high-pressure/ intermediate-pressure (HP/IP) turbine support internal oil feed tube sealing sleeve part number (P/N) FW15003 installed that is marked with the prefix ‘‘B/N’’ followed by a six digit batch number, and does not contain the marking 102013, 112013 or 102013L. (1) For more information about this AD, contact Wego Wang, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7134; fax: 781–238–7199; email: wego.wang@faa.gov. (2) Refer to MCAI European Aviation Safety Agency AD 2014–0168, dated July 16, 2014, 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–2014–0561. Issued in Burlington, Massachusetts, on September 9, 2014. Richard P. Warren, Acting Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2014–22351 Filed 9–17–14; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\18SEP1.SGM 18SEP1

Agencies

[Federal Register Volume 79, Number 181 (Thursday, September 18, 2014)]
[Proposed Rules]
[Pages 56025-56026]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-22351]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0561; Directorate Identifier 2014-NE-12-AD]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Rolls-Royce plc (RR) RB211 Trent 768-60, 772-60, and 772B-60 
turbofan engines. This proposed AD was prompted by fractures of the 
high-pressure/intermediate-pressure (HP/IP) turbine support internal 
oil feed tube. This proposed AD would require inspection of the oil 
feed tube sealing sleeve and removal of those oil feed tube sealing 
sleeves that fail inspection. We are proposing this AD to prevent 
failure of the HP/IP turbine support internal oil feed tube, which 
could result in uncontained engine failure and damage to the airplane.

DATES: We must receive comments on this proposed AD by November 17, 
2014.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor, 
Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: 202-493-2251.

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-2014-
0561; or in person at the Docket Operations office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the mandatory continuing airworthiness 
information (MCAI), the regulatory evaluation, any comments received, 
and other information. The address for the Docket Office (phone: 800-
647-5527) is in the ADDRESSES section. Comments will be available in 
the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Wego Wang, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; phone: 781-238-7134; fax: 
781-238-7199; email: wego.wang@faa.gov.

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-2014-0561; 
Directorate Identifier 2014-NE-12-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 based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact 
with FAA personnel concerning this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD 2014-0168, dated July 16, 2014 (referred to hereinafter as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

There have been nine occurrences of high oil consumption, caused by 
fracture of the High/Intermediate Pressure (HP/IP) turbine support 
internal oil feed tube Part Number (P/N) FW45909.
The oil feed tube threaded end adaptor and sealing sleeve P/N 
FW15003 are designed to form a sliding joint which, if restrained, 
can compress the oil feed tube during thermal contraction of the 
turbine casing at the end

[[Page 56026]]

of the flight cycle. On each subsequent flight, the thermal growth 
and contraction of the turbine casing relative to the oil tube, 
during the heating and cooling phases of the flight cycle, apply a 
load cycle to the tube, which may lead to low cycle fatigue 
fracture.

    This AD requires removal of certain HP/IP turbine support internal 
oil feed tube sealing sleeves to prevent oil exhaustion that could 
result in uncontained engine failure and damage to the airplane.
    You may obtain further information by examining the MCAI in the AD 
docket on the Internet at http://www.regulations.gov by searching for 
and locating Docket No. FAA-2014-0561.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of the 
United Kingdom, and is approved for operation in the United States. 
Pursuant to our bilateral agreement with the European Community, EASA 
has notified us of the unsafe condition described in the MCAI. We are 
proposing this AD because we evaluated all information provided by EASA 
and determined the unsafe condition exists and is likely to exist or 
develop on other products of the same type design. This proposed AD 
would require a one-time on-wing or in-shop inspection of the affected 
engines and removal from service of all affected P/N FW15003 oil feed 
tube sealing sleeves.

Costs of Compliance

    We estimate that this proposed AD affects 69 engines installed on 
airplanes of U.S. registry. We also estimate that it would take about 
8.5 hours per engine to comply with this proposed AD. The average labor 
rate is $85 per hour. Based on these figures, we estimate the cost of 
this proposed AD on U.S. operators to be $49,853.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. Amend Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Rolls-Royce plc: Docket No. FAA-2014-0561; Directorate Identifier 
2014-NE-12-AD.

(a) Comments Due Date

    We must receive comments by November 17, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Rolls-Royce plc (RR) RB211 Trent 768-60, 772-
60, and 772B-60 turbofan engines serial numbers 41693-42309 
inclusive, 42313, 42318, 42319, 42320, 42328, and 42330 with high-
pressure/intermediate-pressure (HP/IP) turbine support internal oil 
feed tube sealing sleeve part number (P/N) FW15003 installed that is 
marked with the prefix ``B/N'' followed by a six digit batch number, 
and does not contain the marking 102013, 112013 or 102013L.

(d) Reason

    This AD was prompted by fractures of the HP/IP turbine support 
internal oil feed tube. We are issuing this AD to prevent failure of 
the HP/IP turbine support internal oil feed tube, which could result 
in uncontained engine failure and damage to the airplane.

(e) Actions and Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Within 6 months after the effective date of this AD, perform 
on-wing or in-shop inspection for, and remove from service, any 
affected HP/IP turbine support internal oil feed tube sealing 
sleeve.
    (2) Remove from service any HP/IP turbine support internal oil 
feed tube sealing sleeve on which markings cannot be sufficiently 
identified to determine whether said sealing sleeve is part of the 
affected population.
    (3) From the effective date of this AD, you may install on 
engines HP/IP turbine support internal oil feed tube sealing 
sleeves, P/N FW15003, that are marked with the prefix ``B/N'' 
followed by a six digit batch number, provided that the part is 
marked with 102013, 112013 or 102013L.

(f) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, may approve AMOCs 
to this AD. Use the procedures found in 14 CFR 39.19 to make your 
request.

(g) Related Information

    (1) For more information about this AD, contact Wego Wang, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7134; fax: 781-238-7199; email: 
wego.wang@faa.gov.
    (2) Refer to MCAI European Aviation Safety Agency AD 2014-0168, 
dated July 16, 2014, 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-2014-0561.

    Issued in Burlington, Massachusetts, on September 9, 2014.
Richard P. Warren,
Acting Assistant Directorate Manager, Engine & Propeller Directorate, 
Aircraft Certification Service.
[FR Doc. 2014-22351 Filed 9-17-14; 8:45 am]
BILLING CODE 4910-13-P