80_FR_23819 80 FR 23737 - Airworthiness Directives; Rolls-Royce plc Turbofan Engines

80 FR 23737 - Airworthiness Directives; Rolls-Royce plc Turbofan Engines

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 82 (April 29, 2015)

Page Range23737-23739
FR Document2015-09816

We propose to adopt a new airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4- C-37 turbofan engines. This proposed AD was prompted by RR updating the life limits for certain high-pressure turbine (HPT) disks. This proposed AD would require reducing the cyclic life limits for certain HPT disks, removing those disks that have exceeded the new life limit, and replacing them with serviceable parts. We are proposing this AD to prevent failure of the HPT disk, which could result in uncontained disk release, damage to the engine, and damage to the airplane.

Federal Register, Volume 80 Issue 82 (Wednesday, April 29, 2015) 
[Federal Register Volume 80, Number 82 (Wednesday, April 29, 2015)]
[Proposed Rules]
[Pages 23737-23739]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-09816]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 80, No. 82 / Wednesday, April 29, 2015 / 
Proposed Rules

[[Page 23737]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0593; Directorate Identifier 2015-NE-08-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 all 
Rolls-Royce plc (RR) RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-
C-37 turbofan engines. This proposed AD was prompted by RR updating the 
life limits for certain high-pressure turbine (HPT) disks. This 
proposed AD would require reducing the cyclic life limits for certain 
HPT disks, removing those disks that have exceeded the new life limit, 
and replacing them with serviceable parts. We are proposing this AD to 
prevent failure of the HPT disk, which could result in uncontained disk 
release, damage to the engine, and damage to the airplane.

DATES: We must receive comments on this proposed AD by June 29, 2015.

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.
    For service information identified in this proposed AD, Rolls-Royce 
plc, Corporate Communications, P.O. Box 31, Derby, England, DE24 8BJ; 
phone: 011-44-1332-242424; fax: 011-44-1332-249936; email: http://www.rolls-royce.com/contact/civil_team.jsp; Internet: https://www.aeromanager.com. You may view this service information at the FAA, 
Engine & Propeller Directorate, 12 New England Executive Park, 
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-2015-
0593; 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: [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-2015-0593; 
Directorate Identifier 2015-NE-08-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 2014-0249R1, dated February 18, 2015 (referred to hereinafter as 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    An engineering analysis, carried out by RR, of the lives of 
critical parts of the RB211-535E4-37 engine, has resulted in reduced 
cyclic life limits for certain high pressure (HP) turbine discs. The 
reduced limits are published in the RR RB211-535E4-37 Time Limits 
Manual (TLM): 05-10-01-800-000, current Revision dated July 2014.
    Operation of critical parts beyond these reduced cyclic life 
limits may result in part failure, possibly resulting in the release 
of high-energy debris, which may cause damage to the aeroplane and/
or injury to the occupants.

    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-2015-0593.

Related Service Information Under 1 CFR Part 51

    We reviewed RR Non-Modification Service Bulletin (NMSB) No. RB.211-
72-G188, Revision No. 1, dated October 30, 2013, and RR RB211-535E4-37, 
Time Limits Manual (TLM): 05-10-01-800-000, Revision dated July 1, 
2014; and RR RB211-535E4-37, TLM: 05-00-01-800-000, Revision dated July 
1, 2014. The NMSB describes the updated lifing analysis of the affected 
HP turbine disks. The TLMs provide revised life limits for the affected 
HP turbine disks. This service information is reasonably available 
because the interested parties have access to it through their normal 
course of business or see ADDRESSES for other ways to access this 
service information.

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 and 
service information referenced above. We are proposing this AD because 
we evaluated all

[[Page 23738]]

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 reducing the cyclic life limits 
for certain HPT disks, removing those disks that have exceeded the new 
life limit, and replacing them with serviceable parts.

Costs of Compliance

    We estimate that this proposed AD affects 650 engines installed on 
airplanes of U.S. registry. We also estimate that it would take about 0 
hours per engine to comply with this proposed AD. The average labor 
rate is $85 per hour. Pro-rated cost of required parts cost would be 
about $12,213 per engine. Based on these figures, we estimate the cost 
of this proposed AD on U.S. operators to be $7,938,450.

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. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

    Rolls-Royce plc: Docket No. FAA-2015-0593; Directorate 
Identifier 2015-NE-08-AD.

(a) Comments Due Date

    We must receive comments by June 29, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Rolls-Royce plc (RR), RB211-535E4-37, 
RB211-535E4-B-37, and RB211-535E4-C-37 turbofan engines.

(d) Reason

    This AD was prompted by RR updating the life limits for certain 
high-pressure turbine (HPT) disks. We are issuing this AD to prevent 
failure of the HPT disk, which could result in uncontained disk 
release, damage to the engine, and damage to the airplane.

(e) Actions and Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) After the effective date of this AD, use RR RB211-535E4-37 
Time Limits Manual (TLM): 05-10-01-800-000, Revision dated July 1, 
2014 (referred to hereafter as `the TLM'), to determine the new life 
limits for the affected engine models and configurations, with the 
exception of those engine models mentioned in paragraph (e)(2) of 
this AD.
    (2) For RR RB211-535E4-B-37 or RB211-535E4-C-37 engines with an 
affected HPT disk that was previously installed on an RB211-535E4-37 
engine operated under Flight Plan A, use task 05-00-01-800-000 in 
the TLM to re-calculate equivalent cycles since new to obtain the 
new life limit.
    (3) If an affected engine model has an HPT disk installed with 
P/N UL27681 or UL39767, remove the affected HPT disk before the 
accumulated cyclic life exceeds either 19,500 flight cycles (FCs) 
under Flight Plan A, or 14,700 FCs under Flight Plan B, or within 25 
FCs after the effective date of this AD, whichever occurs later.
    (4) For all affected engines, other than those specified in 
paragraph (e)(3) in this AD, remove each HPT disk before exceeding 
its applicable life limit as specified in the TLM.
    (5) Install an HPT disk eligible for installation.

(f) Definition

    For the purpose of this AD, a part eligible for installation is 
one with a part number listed in the TLM with a total accumulated 
cyclic life that is less than the applicable life limit specified in 
the TLM.

(g) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, 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 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: 
[email protected].
    (2) Refer to MCAI European Aviation Safety Agency AD 2014-
0249R1, dated February 18, 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-2015-0593.
    (3) RR Non-Modification Service Bulletin No. RB.211-72-G188, 
Revision No. 1, dated October 30, 2013, and RR RB211-535E4-37, TLM: 
05-10-01-800-000, Revision dated July 1, 2014; and RR RB211-535E4-
37, TLM: 05-00-01-800-000, Revision dated July 1, 2014, which are 
not incorporated by reference in this AD, can be obtained from 
Rolls-Royce plc, using the contact information in paragraph (h)(4) 
of this proposed AD.
    (4) For service information identified in this proposed AD, 
contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, 
Derby, England, DE24 8BJ; phone: 011-44-1332-242424; fax: 011-44-
1332-249936; email: http://www.rolls-royce.com/contact/civil_team.jsp; Internet: https://www.aeromanager.com.
    (5) You may view this service information at the FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, 
MA. For information on the availability of this material at the FAA, 
call 781-238-7125.


[[Page 23739]]


    Issued in Burlington, Massachusetts, on April 22, 2015.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-09816 Filed 4-28-15; 8:45 am]
 BILLING CODE 4910-13-P

23737 Proposed Rules Federal Register Vol. 80, No. 82 Wednesday, April 29, 2015 This section of the FEDERAL REGISTER Corporate Communications, P.O. Box Discussion contains notices to the public of the proposed 31, Derby, England, DE24 8BJ; phone: The European Aviation Safety Agency issuance of rules and regulations. The 011–44–1332–242424; fax: 011–44– purpose of these notices is to give interested (EASA), which is the Technical Agent 1332–249936; email: http://www.rolls- for the Member States of the European persons an opportunity to participate in the royce.com/contact/civil_team.jsp; Community, has issued EASA AD 2014– rule making prior to the adoption of the final rules. Internet: https://www.aeromanager.com. 0249R1, dated February 18, 2015 You may view this service information (referred to hereinafter as ‘‘the MCAI’’), at the FAA, Engine & Propeller to correct an unsafe condition for the DEPARTMENT OF TRANSPORTATION Directorate, 12 New England Executive specified products. The MCAI states: Park, Burlington, MA. For information on the availability of this material at the An engineering analysis, carried out by RR, Federal Aviation Administration of the lives of critical parts of the RB211– FAA, call 781–238–7125. 535E4–37 engine, has resulted in reduced 14 CFR Part 39 cyclic life limits for certain high pressure Examining the AD Docket [Docket No. FAA–2015–0593; Directorate (HP) turbine discs. The reduced limits are You may examine the AD docket on published in the RR RB211–535E4–37 Time Identifier 2015–NE–08–AD] the Internet at http:// Limits Manual (TLM): 05–10–01–800–000, RIN 2120–AA64 www.regulations.gov by searching for current Revision dated July 2014. and locating Docket No. FAA–2015– Operation of critical parts beyond these Airworthiness Directives; Rolls-Royce 0593; or in person at the Docket reduced cyclic life limits may result in part plc Turbofan Engines failure, possibly resulting in the release of Operations office between 9 a.m. and 5 high-energy debris, which may cause damage AGENCY: Federal Aviation p.m., Monday through Friday, except to the aeroplane and/or injury to the Administration (FAA), DOT. Federal holidays. The AD docket occupants. ACTION: Notice of proposed rulemaking contains this proposed AD, the You may obtain further information (NPRM). mandatory continuing airworthiness by examining the MCAI in the AD information (MCAI), the regulatory docket on the Internet at http:// SUMMARY: We propose to adopt a new evaluation, any comments received, and www.regulations.gov by searching for airworthiness directive (AD) for all other information. The address for the and locating Docket No. FAA–2015– Rolls-Royce plc (RR) RB211–535E4–37, Docket Office (phone: 800–647–5527) is 0593. RB211–535E4–B–37, and RB211– in the ADDRESSES section. Comments 535E4–C–37 turbofan engines. This will be available in the AD docket Related Service Information Under 1 proposed AD was prompted by RR shortly after receipt. CFR Part 51 updating the life limits for certain high- FOR FURTHER INFORMATION CONTACT: We reviewed RR Non-Modification pressure turbine (HPT) disks. This Wego Wang, Aerospace Engineer, Service Bulletin (NMSB) No. RB.211– proposed AD would require reducing Engine Certification Office, FAA, Engine 72–G188, Revision No. 1, dated October the cyclic life limits for certain HPT & Propeller Directorate, 12 New England 30, 2013, and RR RB211–535E4–37, disks, removing those disks that have Executive Park, Burlington, MA 01803; Time Limits Manual (TLM): 05–10–01– exceeded the new life limit, and phone: 781–238–7134; fax: 781–238– 800–000, Revision dated July 1, 2014; replacing them with serviceable parts. 7199; email: wego.wang@faa.gov. and RR RB211–535E4–37, TLM: 05–00– We are proposing this AD to prevent SUPPLEMENTARY INFORMATION: 01–800–000, Revision dated July 1, failure of the HPT disk, which could 2014. The NMSB describes the updated result in uncontained disk release, Comments Invited lifing analysis of the affected HP turbine damage to the engine, and damage to the We invite you to send any written disks. The TLMs provide revised life airplane. relevant data, views, or arguments about limits for the affected HP turbine disks. DATES: We must receive comments on this proposed AD. Send your comments This service information is reasonably this proposed AD by June 29, 2015. to an address listed under the available because the interested parties ADDRESSES: You may send comments by ADDRESSES section. Include ‘‘Docket No. have access to it through their normal any of the following methods: FAA–2015–0593; Directorate Identifier course of business or see ADDRESSES for • Federal eRulemaking Portal: Go to 2015–NE–08–AD’’ at the beginning of other ways to access this service http://www.regulations.gov. Follow the your comments. We specifically invite information. instructions for submitting comments. comments on the overall regulatory, FAA’s Determination and Requirements • Mail: Docket Management Facility, economic, environmental, and energy aspects of this proposed AD. We will of This Proposed AD U.S. Department of Transportation, 1200 New Jersey Avenue SE., West Building consider all comments received by the This product has been approved by closing date and may amend this the aviation authority of the United mstockstill on DSK4VPTVN1PROD with PROPOSALS Ground Floor, Room W12–140, Washington, DC 20590–0001. proposed AD based on those comments. Kingdom, and is approved for operation • Hand Delivery: Deliver to Mail We will post all comments we in the United States. Pursuant to our address above between 9 a.m. and 5 receive, without change, to http:// bilateral agreement with the European p.m., Monday through Friday, except www.regulations.gov, including any Community, EASA has notified us of Federal holidays. personal information you provide. We the unsafe condition described in the • Fax: 202–493–2251. will also post a report summarizing each MCAI and service information For service information identified in substantive verbal contact with FAA referenced above. We are proposing this this proposed AD, Rolls-Royce plc, personnel concerning this proposed AD. AD because we evaluated all VerDate Sep<11>2014 16:59 Apr 28, 2015 Jkt 235001 PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 E:\FR\FM\29APP1.SGM 29APP1

23738 Federal Register / Vol. 80, No. 82 / Wednesday, April 29, 2015 / Proposed Rules information provided by EASA and (3) Will not affect intrastate aviation (3) If an affected engine model has an HPT determined the unsafe condition exists in Alaska to the extent that it justifies disk installed with P/N UL27681 or and is likely to exist or develop on other making a regulatory distinction, and UL39767, remove the affected HPT disk products of the same type design. This (4) Will not have a significant before the accumulated cyclic life exceeds proposed AD would require reducing economic impact, positive or negative, either 19,500 flight cycles (FCs) under Flight the cyclic life limits for certain HPT on a substantial number of small entities Plan A, or 14,700 FCs under Flight Plan B, disks, removing those disks that have under the criteria of the Regulatory or within 25 FCs after the effective date of exceeded the new life limit, and Flexibility Act. this AD, whichever occurs later. replacing them with serviceable parts. (4) For all affected engines, other than List of Subjects in 14 CFR Part 39 those specified in paragraph (e)(3) in this AD, Costs of Compliance Air transportation, Aircraft, Aviation remove each HPT disk before exceeding its We estimate that this proposed AD safety, Incorporation by reference, applicable life limit as specified in the TLM. affects 650 engines installed on Safety. (5) Install an HPT disk eligible for installation. airplanes of U.S. registry. We also The Proposed Amendment estimate that it would take about 0 Accordingly, under the authority (f) Definition hours per engine to comply with this delegated to me by the Administrator, For the purpose of this AD, a part eligible proposed AD. The average labor rate is the FAA proposes to amend 14 CFR part for installation is one with a part number $85 per hour. Pro-rated cost of required 39 as follows: listed in the TLM with a total accumulated parts cost would be about $12,213 per cyclic life that is less than the applicable life engine. Based on these figures, we PART 39—AIRWORTHINESS limit specified in the TLM. estimate the cost of this proposed AD on DIRECTIVES U.S. operators to be $7,938,450. (g) Alternative Methods of Compliance ■ 1. The authority citation for part 39 (AMOCs) Authority for This Rulemaking continues to read as follows: The Manager, Engine Certification Office, Title 49 of the United States Code Authority: 49 U.S.C. 106(g), 40113, 44701. FAA, may approve AMOCs for this AD. Use specifies the FAA’s authority to issue the procedures found in 14 CFR 39.19 to rules on aviation safety. Subtitle I, § 39.13 [Amended] make your request. You may email your section 106, describes the authority of ■ 2. The FAA amends § 39.13 by adding request to: ANE–AD–AMOC@faa.gov. the FAA Administrator. ‘‘Subtitle VII: the following new airworthiness (h) Related Information Aviation Programs,’’ describes in more directive (AD): (1) For more information about this AD, detail the scope of the Agency’s Rolls-Royce plc: Docket No. FAA–2015– contact Wego Wang, Aerospace Engineer, authority. 0593; Directorate Identifier 2015–NE–08–AD. Engine Certification Office, FAA, Engine & We are issuing this rulemaking under (a) Comments Due Date Propeller Directorate, 12 New England the authority described in ‘‘Subtitle VII, We must receive comments by June 29, Executive Park, Burlington, MA 01803; Part A, Subpart III, Section 44701: 2015. phone: 781–238–7134; fax: 781–238–7199; General requirements.’’ Under that email: wego.wang@faa.gov. (b) Affected ADs section, Congress charges the FAA with (2) Refer to MCAI European Aviation promoting safe flight of civil aircraft in None. Safety Agency AD 2014–0249R1, dated air commerce by prescribing regulations (c) Applicability February 18, 2015, for more information. You for practices, methods, and procedures This AD applies to all Rolls-Royce plc may examine the MCAI in the AD docket on the Administrator finds necessary for (RR), RB211–535E4–37, RB211–535E4–B–37, the Internet at http://www.regulations.gov by safety in air commerce. This regulation and RB211–535E4–C–37 turbofan engines. searching for and locating it in Docket No. is within the scope of that authority FAA–2015–0593. (d) Reason because it addresses an unsafe condition (3) RR Non-Modification Service Bulletin that is likely to exist or develop on This AD was prompted by RR updating the No. RB.211–72–G188, Revision No. 1, dated life limits for certain high-pressure turbine October 30, 2013, and RR RB211–535E4–37, products identified in this rulemaking (HPT) disks. We are issuing this AD to action. TLM: 05–10–01–800–000, Revision dated prevent failure of the HPT disk, which could result in uncontained disk release, damage to July 1, 2014; and RR RB211–535E4–37, TLM: Regulatory Findings 05–00–01–800–000, Revision dated July 1, the engine, and damage to the airplane. We determined that this proposed AD 2014, which are not incorporated by (e) Actions and Compliance reference in this AD, can be obtained from would not have federalism implications under Executive Order 13132. This Comply with this AD within the Rolls-Royce plc, using the contact compliance times specified, unless already information in paragraph (h)(4) of this proposed AD would not have a done. substantial direct effect on the States, on proposed AD. (1) After the effective date of this AD, use (4) For service information identified in the relationship between the national RR RB211–535E4–37 Time Limits Manual this proposed AD, contact Rolls-Royce plc, Government and the States, or on the (TLM): 05–10–01–800–000, Revision dated Corporate Communications, P.O. Box 31, distribution of power and July 1, 2014 (referred to hereafter as ‘the TLM’), to determine the new life limits for Derby, England, DE24 8BJ; phone: 011–44– responsibilities among the various the affected engine models and 1332–242424; fax: 011–44–1332–249936; levels of government. configurations, with the exception of those email: http://www.rolls-royce.com/contact/ mstockstill on DSK4VPTVN1PROD with PROPOSALS For the reasons discussed above, I engine models mentioned in paragraph (e)(2) civil_team.jsp; Internet: https:// certify this proposed regulation: of this AD. www.aeromanager.com. (1) Is not a ‘‘significant regulatory (2) For RR RB211–535E4–B–37 or RB211– (5) You may view this service information action’’ under Executive Order 12866, 535E4–C–37 engines with an affected HPT at the FAA, Engine & Propeller Directorate, disk that was previously installed on an 12 New England Executive Park, Burlington, (2) Is not a ‘‘significant rule’’ under RB211–535E4–37 engine operated under the DOT Regulatory Policies and MA. For information on the availability of Flight Plan A, use task 05–00–01–800–000 in Procedures (44 FR 11034, February 26, the TLM to re-calculate equivalent cycles this material at the FAA, call 781–238–7125. 1979), since new to obtain the new life limit. VerDate Sep<11>2014 16:59 Apr 28, 2015 Jkt 235001 PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 E:\FR\FM\29APP1.SGM 29APP1

Federal Register / Vol. 80, No. 82 / Wednesday, April 29, 2015 / Proposed Rules 23739 Issued in Burlington, Massachusetts, on p.m., Monday through Friday, except personal information you provide. We April 22, 2015. Federal holidays. will also post a report summarizing each Colleen M. D’Alessandro, For service information identified in substantive verbal contact we receive Assistant Directorate Manager, Engine & this proposed AD, contact Boeing about this proposed AD. Propeller Directorate, Aircraft Certification Commercial Airplanes, Attention: Data Service. Discussion & Services Management, P.O. Box 3707, [FR Doc. 2015–09816 Filed 4–28–15; 8:45 am] MC 2H–65, Seattle, WA 98124–2207; We have received a report of BILLING CODE 4910–13–P telephone 206–544–5000, extension 1; improperly installed outboard stowage fax 206–766–5680; Internet https:// bin modules in the passenger www.myboeingfleet.com. You may view compartment found during DEPARTMENT OF TRANSPORTATION this referenced service information at maintenance. Further investigation the FAA, Transport Airplane revealed that certain attachment bracket Federal Aviation Administration Directorate, 1601 Lind Avenue SW., bushings of the outboard stowage bin Renton, WA. For information on the module were missing or had moved out 14 CFR Part 39 availability of this material at the FAA, of the holes, and pins were installed [Docket No. FAA–2015–0932; Directorate call 425–227–1221. It is also available incorrectly. These bushings were Identifier 2014–NM–205–AD] on the Internet at http:// designed to prevent disengagement of www.regulations.gov by searching for the quick release pins; however, RIN 2120–AA64 and locating Docket No. FAA–2015– migration of the bushings deters this. It Airworthiness Directives; The Boeing 0932. was determined that the interference fit Company Airplanes of the bushings in the attachment Examining the AD Docket brackets was incorrect. Subsequently, AGENCY: Federal Aviation You may examine the AD docket on installation of the quick release pins Administration (FAA), DOT. the Internet at http:// during production has caused bushings ACTION: Notice of proposed rulemaking www.regulations.gov by searching for to migrate or detach. This condition, if (NPRM). and locating Docket No. FAA–2015– not corrected, could result in separation 0932; or in person at the Docket of the lateral support tie rod, SUMMARY: We propose to adopt a new Management Facility between 9 a.m. detachment of the outboard stowage bin airworthiness directive (AD) for certain and 5 p.m., Monday through Friday, module, and consequent injuries to The Boeing Company Model 747–8 except Federal holidays. The AD docket passengers or flightcrew. series airplanes. This proposed AD was contains this proposed AD, the prompted by a report of improperly Related Service Information Under 1 regulatory evaluation, any comments installed outboard stowage bin modules CFR Part 51 received, and other information. The in the passenger compartment found street address for the Docket Office We reviewed Boeing Special during maintenance. Further (phone: 800–647–5527) is in the Attention Service Bulletin 747–25– investigation revealed that certain ADDRESSES section. Comments will be 3649, dated July 24, 2014. The service attachment bracket bushings were available in the AD docket shortly after information describes procedures for missing or had moved out of the holes. receipt. installing a spacer on the end of each This proposed AD would require FOR FURTHER INFORMATION CONTACT: quick-release pin that attaches the installing a spacer on the end of each Stanley Chen, Aerospace Engineer, outboard stowage bin module to the quick-release pin that attaches the Cabin Safety and Environmental lateral support tie rods of the main deck outboard stowage bin module to the Systems Branch, ANM–150S, FAA, passenger compartment. Refer to this lateral support tie rods of the main deck Seattle Aircraft Certification Office, service information for information on passenger compartment. We are 1601 Lind Avenue SW., Renton, WA the procedures and compliance times. proposing this AD to prevent 98057–3356; phone: 425–917–6585; fax: This service information is reasonably detachment of the quick-release pin, 425–917–6590; email: stanley.chen@ available; see ADDRESSES for ways to which could result in separation of the faa.gov. access this service information. lateral support tie rod and subsequent SUPPLEMENTARY INFORMATION: FAA’s Determination detachment of the module and consequent injuries to passengers or Comments Invited We are proposing this AD because we flightcrew. evaluated all the relevant information We invite you to send any written and determined the unsafe condition DATES: We must receive comments on relevant data, views, or arguments about described previously is likely to exist or this proposed AD by June 15, 2015. this proposal. Send your comments to develop in other products of the same ADDRESSES: You may send comments, an address listed under the ADDRESSES type design. using the procedures found in 14 CFR section. Include ‘‘Docket No. FAA– 11.43 and 11.45, by any of the following 2015–0932; Directorate Identifier 2014– Proposed AD Requirements methods: NM–205–AD’’ at the beginning of your This proposed AD would require • Federal eRulemaking Portal: Go to comments. We specifically invite accomplishing the actions specified in http://www.regulations.gov. Follow the comments on the overall regulatory, the service information identified instructions for submitting comments. economic, environmental, and energy mstockstill on DSK4VPTVN1PROD with PROPOSALS previously. • Fax: 202–493–2251. aspects of this proposed AD. We will • Mail: U.S. Department of consider all comments received by the Explanation of ‘‘RC’’ Steps in Service Transportation, Docket Operations, M– closing date and may amend this Information 30, West Building Ground Floor, Room proposed AD because of those The FAA worked in conjunction with W12–140, 1200 New Jersey Avenue SE., comments. industry, under the Airworthiness Washington, DC 20590. We will post all comments we Directives Implementation Aviation • Hand Delivery: Deliver to Mail receive, without change, to http:// Rulemaking Committee, to enhance the address above between 9 a.m. and 5 www.regulations.gov, including any AD system. One enhancement was a VerDate Sep<11>2014 16:59 Apr 28, 2015 Jkt 235001 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 E:\FR\FM\29APP1.SGM 29APP1


Document Created: 2015-12-16 08:26:04
Document Modified: 2015-12-16 08:26:04
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 June 29, 2015.
ContactWego 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: [email protected]
FR Citation80 FR 23737 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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