Airworthiness Directives; Rolls-Royce plc (RR) RB211-524 Series Turbofan Engines, 40217-40219 [2011-16954]

Download as PDF 40217 Rules and Regulations Federal Register Vol. 76, No. 131 Friday, July 8, 2011 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0624; Directorate Identifier 2010–NE–11–AD; Amendment 39– 16724; AD 2011–13–01] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc (RR) RB211–524 Series Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: wreier-aviles on DSKGBLS3C1PROD with RULES SUMMARY: An investigation into the loss of a TRU during landing has revealed that this incident was preceded by the detachment of the TRUs fixed structure front ring rivet lines on the rear flange. It was concluded that the loss of rivet lines was directly associated with a previous translating cowl gearbox stubshaft fracture and the subsequent repair of the fixed structure to Engine Manual repair No. FRS5887. This repair instructs the replacement of the damaged section of the structure but does not require the rivets adjacent to the repair to be replaced although latest analysis has shown that the rivets may have weakened as a result of a translating cowl gearbox stubshaft failure. We are issuing this AD to prevent failure of the attachment rivets resulting in loss of engine structural integrity, which may result in release of the thrust reverser unit from the engine. DATES: This AD becomes effective August 12, 2011. VerDate Mar<15>2010 15:25 Jul 07, 2011 Jkt 223001 We must receive comments on this AD by August 8, 2011. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of August 12, 2011. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: 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 https:// www.regulations.gov; 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 AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Alan Strom, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: alan.strom@faa.gov; telephone (781) 238–7143; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2009–0253, dated November 30, 2009 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: An investigation into the loss of a TRU during landing has revealed that this incident was preceded by the detachment of the TRUs fixed structure front ring rivet lines on the rear flange. PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 It was concluded that the loss of rivet lines was directly associated with a previous translating cowl gearbox stubshaft fracture and the subsequent repair of the fixed structure to Engine Manual repair No. FRS5887. This repair instructs the replacement of the damaged section of the structure but does not require the rivets adjacent to the repair to be replaced although latest analysis has shown that the rivets may have weakened as a result of a translating cowl gearbox stubshaft failure. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Rolls-Royce has issued RR Alert Service Bulletin RB.211–78–AG084, Revision 5, dated February 4, 2011. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This 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 United Kingdom, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are issuing 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. Differences Between the AD and the MCAI or Service Information EASA AD 2009–0253, dated November 30, 2009, requires the following compliance times: For engines on which the thrust reverser unit (TRU) was previously repaired using either engine manual repair No. FRS4976 or engine manual repair No. FRS5887 and FRS6669 as a result of a translating cowl gearbox stubshaft failure, the MCAI requires compliance before March 31, 2010. This AD requires compliance within 215 cycles-in-service (CIS) after the effective date of this AD. For engines on which the TRU was previously repaired using engine manual repair No. FRS5887 only, the E:\FR\FM\08JYR1.SGM 08JYR1 40218 Federal Register / Vol. 76, No. 131 / Friday, July 8, 2011 / Rules and Regulations MCAI requires compliance before December 31, 2012. This AD requires compliance within 2,225 CIS after the effective date of this AD. FAA’s Determination of the Effective Date Since no domestic operators use this product, notice and opportunity for public comment before issuing this AD are unnecessary. Therefore, we are adopting this regulation immediately. wreier-aviles on DSKGBLS3C1PROD with RULES Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2011–0624; Directorate Identifier 2010–NE–11–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to https:// 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 AD. Using the search function of the Web site, anyone can find and read the comments in any of our dockets, including, if provided, the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78). 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 VerDate Mar<15>2010 15:25 Jul 07, 2011 Jkt 223001 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 AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this AD: 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); and 3. 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. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2011–13–01 Rolls-Royce plc (RR): Amendment 39–16724; Docket No. FAA–2011–0624; Directorate Identifier 2010–NE–11–AD. Effective Date (a) This airworthiness directive (AD) becomes effective August 12, 2011. Affected ADs (b) None. Applicability (c) This AD applies to RB211–524D4–19, –524D4–B–19, –524D4–39, –524D4–B–39, –524D4X–19, –524D4X–B–19, –524H–36, –524H2–19, –524H–T–36, –524H2–T–19, –524G2–19, –524G3–19, –524G2–T–19, and PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 –524G3–T–19 engines with thrust reverser units (TRUs) that have a part number (P/N) specified in paragraph 1.A. of RR Alert Service Bulletin (ASB) RB.211–78–AG084, Revision 5, dated February 4, 2011, installed. These engines are installed on, but not limited to, Boeing 747 series and 767 series airplanes. Reason (d) The EASA AD 2009–0253, dated November 30, 2009, states the following: An investigation into the loss of a TRU during landing has revealed that this incident was preceded by the detachment of the TRUs fixed structure front ring rivet lines on the rear flange. It was concluded that the loss of rivet lines was directly associated with a previous translating cowl gearbox stubshaft fracture and the subsequent repair of the fixed structure to Engine Manual repair No. FRS5887. This repair instructs the replacement of the damaged section of the structure but does not require the rivets adjacent to the repair to be replaced although latest analysis has shown that the rivets may have weakened as a result of a translating cowl gearbox stubshaft failure. We are issuing this AD to prevent failure of the attachment rivets resulting in loss of engine structural integrity, which may result in release of the thrust reverser unit from the engine. (e) If no repairs were performed as a result of a stubshaft failure, no further action is necessary. Actions and Compliance (f) Unless already done, do the following actions: (1) If the TRU has previously had engine manual repair No. FRS5887 and either engine manual repair No. FRS4976 or engine manual repair No. FRS6669 as a result of a translating cowl gearbox stubshaft failure, then perform the actions specified in Section 3. Accomplishment Instructions of RR ASB RB.211–78–AG084, Revision 5, dated February 4, 2011, within 215 cycles-inservice (CIS) after the effective date of this AD. (2) If the TRU has previously only had engine manual repair No. FRS5887 as a result of a translating cowl gearbox stubshaft failure, then perform the actions specified in Section 3. Accomplishment Instructions of RR ASB RB.211–78–AG084, Revision 5, dated February 4, 2011, within 2,225 CIS after the effective date of this AD. Previous Credit (g) Actions specified in paragraph (f)(1) and (f)(2) of this AD that are performed using RR ASB RB.211–78–AG084, Revision 4, dated December 22, 2009, RR ASB RB.211– 78–AG084, Revision 3, dated November 6, 2009, comply with paragraph (f)(1) and (f)(2) of this AD. FAA AD Differences (h) This AD differs from the Mandatory Continuing Airworthiness Information (MCAI) and/or service information as follows: (1) For engines on which the TRU was previously repaired using either engine manual repair No. FRS4976 or engine manual E:\FR\FM\08JYR1.SGM 08JYR1 Federal Register / Vol. 76, No. 131 / Friday, July 8, 2011 / Rules and Regulations repair No. FRS6669 and engine manual repair FRS5887 as a result of a translating cowl gearbox stubshaft failure, the MCAI requires compliance before March 31, 2010. This AD requires compliance within 215 cycles-in-service (CIS) after the effective date of this AD. (2) For engines on which the TRU was previously repaired using engine manual repair No. FRS5887 only, the MCAI requires compliance before December 31, 2012. This AD requires compliance within 2,225 CIS after the effective date of this AD. Other FAA AD Provisions (i) The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (j) Refer to MCAI EASA Airworthiness Directive 2009–0253, dated November 30, 2009, for related information. (k) Contact Alan Strom, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: alan.strom@faa.gov; telephone (781) 238–7143; fax (781) 238–7199, for more information about this AD. Material Incorporated by Reference wreier-aviles on DSKGBLS3C1PROD with RULES (l) You must use Rolls-Royce (RR) Alert Service Bulletin (ASB) RB.211–78–AG084, Revision 5, dated February 4, 2011, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, United Kingdom; telephone 011 44 1332 242424; fax 011 44 1332 249936. (3) You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. [FR Doc. 2011–16954 Filed 7–7–11; 8:45 am] BILLING CODE 4910–13–P VerDate Mar<15>2010 15:25 Jul 07, 2011 Jkt 223001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0714; Directorate Identifier 2011–CE–024–AD; Amendment 39–16744; AD 2011–14–09] RIN 2120–AA64 Airworthiness Directives; Various Aircraft Equipped With Rotax Aircraft Engines 912 A Series Engine Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: Alternative Methods of Compliance (AMOCs) Issued in Burlington, Massachusetts, on June 8, 2011. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. DEPARTMENT OF TRANSPORTATION We are adopting a new airworthiness directive (AD) for the products listed above that will supersede an existing AD. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: SUMMARY: During a production process review, a deviation in hardening of certain Part Number (P/N) 944072 washers has been detected, which exceeds the hardness of the design specification. The affected washers are part of the magneto ring flywheel hub installation and have been installed on a limited number of engines. No defective washers have been shipped as spare parts. This condition, if not corrected, could lead to cracks in the washer, loosening of the magneto flywheel hub and consequent ignition failure, possibly resulting in damage to the engine, in-flight engine shutdown and forced landing, damage to the aeroplane and injury to occupants. This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective July 25, 2011. As of June 16, 2011 (76 FR 31465, June 1, 2011), the Director of the Federal Register approved the incorporation by reference of Rotax Aircraft Engines Mandatory Service Bulletin SB–912–058 SB–914–041, dated April 15, 2011, listed in this AD. We must receive comments on this AD by August 22, 2011. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 40219 M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact BRP–Rotax GmbH & Co. KG, Welser Strasse 32, A–4623 Gunskirchen, Austria; phone: +43 7246 601 0; fax: +43 7246 601 9130; Internet: https://www.rotax-aircraft-engines.com. You may review copies of the 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. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone (800) 647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Sarjapur Nagarajan, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4145; fax: (816) 329–4090; e-mail: sarjapur.nagarajan@faa.gov. SUPPLEMENTARY INFORMATION: Discussion On May 10, 2011, we issued AD 2011–11–03, Amendment 39–16702 (76 FR 31465, June 1, 2011). That AD required actions intended to address an unsafe condition on the products listed above. Since we issued AD 2011–11–03, we determined that we inadvertently omitted certain airplanes equipped with Rotax 912 A series engines from the Applicability section. We have also determined that we included certain airplanes in the Applicability section that are not equipped with Rotax 912 A series engines. Relevant Service Information Rotax Aircraft Engines has issued Mandatory Service Bulletin SB–912–058 and SB–914–041 (same document), E:\FR\FM\08JYR1.SGM 08JYR1

Agencies

[Federal Register Volume 76, Number 131 (Friday, July 8, 2011)]
[Rules and Regulations]
[Pages 40217-40219]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-16954]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 
Prices of new books are listed in the first FEDERAL REGISTER issue of each 
week.

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


Federal Register / Vol. 76, No. 131 / Friday, July 8, 2011 / Rules 
and Regulations

[[Page 40217]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0624; Directorate Identifier 2010-NE-11-AD; 
Amendment 39-16724; AD 2011-13-01]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc (RR) RB211-524 Series 
Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD results from mandatory continuing 
airworthiness information (MCAI) issued by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    An investigation into the loss of a TRU during landing has 
revealed that this incident was preceded by the detachment of the 
TRUs fixed structure front ring rivet lines on the rear flange. It 
was concluded that the loss of rivet lines was directly associated 
with a previous translating cowl gearbox stubshaft fracture and the 
subsequent repair of the fixed structure to Engine Manual repair No. 
FRS5887. This repair instructs the replacement of the damaged 
section of the structure but does not require the rivets adjacent to 
the repair to be replaced although latest analysis has shown that 
the rivets may have weakened as a result of a translating cowl 
gearbox stubshaft failure.

We are issuing this AD to prevent failure of the attachment rivets 
resulting in loss of engine structural integrity, which may result in 
release of the thrust reverser unit from the engine.

DATES: This AD becomes effective August 12, 2011.
    We must receive comments on this AD by August 8, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of August 12, 
2011.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: 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 https://www.regulations.gov; 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 AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is the same as 
the Mail address provided in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Alan Strom, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
alan.strom@faa.gov; telephone (781) 238-7143; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2009-0253, dated November 30, 2009 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:
    An investigation into the loss of a TRU during landing has revealed 
that this incident was preceded by the detachment of the TRUs fixed 
structure front ring rivet lines on the rear flange. It was concluded 
that the loss of rivet lines was directly associated with a previous 
translating cowl gearbox stubshaft fracture and the subsequent repair 
of the fixed structure to Engine Manual repair No. FRS5887. This repair 
instructs the replacement of the damaged section of the structure but 
does not require the rivets adjacent to the repair to be replaced 
although latest analysis has shown that the rivets may have weakened as 
a result of a translating cowl gearbox stubshaft failure.
    You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Rolls-Royce has issued RR Alert Service Bulletin RB.211-78-AG084, 
Revision 5, dated February 4, 2011. The actions described in this 
service information are intended to correct the unsafe condition 
identified in the MCAI.

FAA's Determination and Requirements of This 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 United Kingdom, they have 
notified us of the unsafe condition described in the MCAI and service 
information referenced above. We are issuing 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.

Differences Between the AD and the MCAI or Service Information

    EASA AD 2009-0253, dated November 30, 2009, requires the following 
compliance times:
    For engines on which the thrust reverser unit (TRU) was previously 
repaired using either engine manual repair No. FRS4976 or engine manual 
repair No. FRS5887 and FRS6669 as a result of a translating cowl 
gearbox stubshaft failure, the MCAI requires compliance before March 
31, 2010. This AD requires compliance within 215 cycles-in-service 
(CIS) after the effective date of this AD.
    For engines on which the TRU was previously repaired using engine 
manual repair No. FRS5887 only, the

[[Page 40218]]

MCAI requires compliance before December 31, 2012. This AD requires 
compliance within 2,225 CIS after the effective date of this AD.

FAA's Determination of the Effective Date

    Since no domestic operators use this product, notice and 
opportunity for public comment before issuing this AD are unnecessary. 
Therefore, we are adopting this regulation immediately.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2011-0624; Directorate 
Identifier 2010-NE-11-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
those comments.
    We will post all comments we receive, without change, to https://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 AD. Using the search function of the 
Web site, anyone can find and read the comments in any of our dockets, 
including, if provided, the name of the individual who sent the comment 
(or signed the comment on behalf of an association, business, labor 
union, etc.). You may review the DOT's complete Privacy Act Statement 
in the Federal Register published on April 11, 2000 (65 FR 19477-78).

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 AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify this AD:
    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); and
    3. 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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 AD:

2011-13-01 Rolls-Royce plc (RR): Amendment 39-16724; Docket No. FAA-
2011-0624; Directorate Identifier 2010-NE-11-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective August 
12, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to RB211-524D4-19, -524D4-B-19, -524D4-39, -
524D4-B-39, -524D4X-19, -524D4X-B-19, -524H-36, -524H2-19, -524H-T-
36, -524H2-T-19, -524G2-19, -524G3-19, -524G2-T-19, and -524G3-T-19 
engines with thrust reverser units (TRUs) that have a part number 
(P/N) specified in paragraph 1.A. of RR Alert Service Bulletin (ASB) 
RB.211-78-AG084, Revision 5, dated February 4, 2011, installed. 
These engines are installed on, but not limited to, Boeing 747 
series and 767 series airplanes.

Reason

    (d) The EASA AD 2009-0253, dated November 30, 2009, states the 
following:
    An investigation into the loss of a TRU during landing has 
revealed that this incident was preceded by the detachment of the 
TRUs fixed structure front ring rivet lines on the rear flange. It 
was concluded that the loss of rivet lines was directly associated 
with a previous translating cowl gearbox stubshaft fracture and the 
subsequent repair of the fixed structure to Engine Manual repair No. 
FRS5887. This repair instructs the replacement of the damaged 
section of the structure but does not require the rivets adjacent to 
the repair to be replaced although latest analysis has shown that 
the rivets may have weakened as a result of a translating cowl 
gearbox stubshaft failure.
    We are issuing this AD to prevent failure of the attachment 
rivets resulting in loss of engine structural integrity, which may 
result in release of the thrust reverser unit from the engine.
    (e) If no repairs were performed as a result of a stubshaft 
failure, no further action is necessary.

Actions and Compliance

    (f) Unless already done, do the following actions:
    (1) If the TRU has previously had engine manual repair No. 
FRS5887 and either engine manual repair No. FRS4976 or engine manual 
repair No. FRS6669 as a result of a translating cowl gearbox 
stubshaft failure, then perform the actions specified in Section 3. 
Accomplishment Instructions of RR ASB RB.211-78-AG084, Revision 5, 
dated February 4, 2011, within 215 cycles-in-service (CIS) after the 
effective date of this AD.
    (2) If the TRU has previously only had engine manual repair No. 
FRS5887 as a result of a translating cowl gearbox stubshaft failure, 
then perform the actions specified in Section 3. Accomplishment 
Instructions of RR ASB RB.211-78-AG084, Revision 5, dated February 
4, 2011, within 2,225 CIS after the effective date of this AD.

Previous Credit

    (g) Actions specified in paragraph (f)(1) and (f)(2) of this AD 
that are performed using RR ASB RB.211-78-AG084, Revision 4, dated 
December 22, 2009, RR ASB RB.211-78-AG084, Revision 3, dated 
November 6, 2009, comply with paragraph (f)(1) and (f)(2) of this 
AD.

FAA AD Differences

    (h) This AD differs from the Mandatory Continuing Airworthiness 
Information (MCAI) and/or service information as follows:
    (1) For engines on which the TRU was previously repaired using 
either engine manual repair No. FRS4976 or engine manual

[[Page 40219]]

repair No. FRS6669 and engine manual repair FRS5887 as a result of a 
translating cowl gearbox stubshaft failure, the MCAI requires 
compliance before March 31, 2010. This AD requires compliance within 
215 cycles-in-service (CIS) after the effective date of this AD.
    (2) For engines on which the TRU was previously repaired using 
engine manual repair No. FRS5887 only, the MCAI requires compliance 
before December 31, 2012. This AD requires compliance within 2,225 
CIS after the effective date of this AD.

Other FAA AD Provisions

Alternative Methods of Compliance (AMOCs)

    (i) The Manager, Engine Certification Office, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19.

Related Information

    (j) Refer to MCAI EASA Airworthiness Directive 2009-0253, dated 
November 30, 2009, for related information.
    (k) Contact Alan Strom, Aerospace Engineer, Engine Certification 
Office, FAA, Engine and Propeller Directorate, 12 New England 
Executive Park, Burlington, MA 01803; e-mail: alan.strom@faa.gov; 
telephone (781) 238-7143; fax (781) 238-7199, for more information 
about this AD.

Material Incorporated by Reference

    (l) You must use Rolls-Royce (RR) Alert Service Bulletin (ASB) 
RB.211-78-AG084, Revision 5, dated February 4, 2011, to do the 
actions required by this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, United Kingdom; 
telephone 011 44 1332 242424; fax 011 44 1332 249936.
    (3) You may review copies at the FAA, New England Region, 12 New 
England Executive Park, Burlington, MA; or at the National Archives 
and Records Administration (NARA). For information on the 
availability of this material at NARA, call (202) 741-6030, or go 
to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on June 8, 2011.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2011-16954 Filed 7-7-11; 8:45 am]
BILLING CODE 4910-13-P