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[Federal Register Volume 78, Number 35 (Thursday, February 21, 2013)]
[Rules and Regulations]
[Pages 11976-11978]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-03708]

[[Page 11976]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0624; Directorate Identifier 2010-NE-11-AD; 
Amendment 39-17358; AD 2013-04-01]
RIN 2120-AA64

Airworthiness Directives; Rolls-Royce plc Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are superseding an existing airworthiness directive (AD) 
for all Rolls-Royce plc (RR) RB211-524 series turbofan engines. That AD 
currently requires removal and repair of certain thrust reverser units 
(TRUs) prior to reinstallation. This AD requires the same actions for 
an expanded population of TRUs and extends the compliance time for 
repairing certain TRUs. This AD was prompted by additional engineering 
evaluation of TRUs, as a result of a translating cowl gearbox stubshaft 
failure and subsequent repair. We are issuing this AD to prevent 
failure of the attachment rivets, which may result in release of the 
TRU from the engine.

DATES: This AD is effective March 8, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of March 8, 
2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication as of August 12, 2011, (76 FR 
40217, July 8, 2011).
    We must receive any comments on this AD by April 8, 2013.

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.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Rolls-Royce 
plc, Corporate Communications, P.O. Box 31, Derby, England, DE248BJ; 
phone: 011-44-1332-242424; fax: 011-44-1332-249936, or email: http://www.rolls-royce.com/contact/civil_team.jsp. You may view this service 
information at the FAA, Engine & Propeller Directorate, 12 New England 
Executive Park, Burlington, MA 01803. 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; 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 (phone: 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: 781-238-7754; 
fax: 781-238-7199; email: Robert.Green@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    On June 8, 2011, we issued AD 2011-13-01, Amendment 39-16724 (76 FR 
40217, July 8, 2011), for all RR plc RB211-524 series turbofan engines. 
That AD required removal and repair of certain TRUs prior to 
reinstallation. That AD resulted from an investigation into the loss of 
a TRU during landing. The investigation revealed that the incident was 
preceded by the detachment of the TRU's fixed structure front ring 
rivet lines on the rear flange. It was determined that the loss of 
rivet lines was directly associated with a previous translating cowl 
gearbox stubshaft fracture and the repair of the fixed structure to 
Engine Manual repair No. FRS5887. At the time, the repair instructed 
the replacement of the damaged section of the structure but did not 
require the rivets adjacent to the repair to be replaced. Subsequent 
analysis has shown that the rivets may have weakened as a result of the 
translating cowl gearbox stubshaft failure.

Actions Since AD Was Issued

    Since we issued AD 2011-13-01, (76 FR 40217, July 8, 2011), 
engineering evaluation by RR has concluded that the compliance time for 
repairing TRUs that had only Engine Manual repair No. FRS5887 
incorporated as a result of a translating cowl gearbox stubshaft 
failure, can be extended. RR also concluded that TRUs previously 
repaired at the front ring with additional rivets using Engine Manual 
repair No. FRS5887 Part 2, and that have not had Engine Manual repair 
Nos. FRS4976 and FRS6669 applied to the rear ring at the No. 2 or No. 3 
gearbox position, constitute a new population that must be removed and 
repaired during the next scheduled engine removal. The European 
Aviation Safety Agency (EASA) has notified us of this same unsafe 
condition, and corrective actions described in EASA AD 2012-0255, dated 
November 30, 2012.

Relevant Service Information

    We reviewed RR Alert Non-Modification Service Bulletin (NMSB) No. 
RB.211-78-AG084, Revision 7, dated November 23, 2012. The NMSB 
describes procedures for removal, repair, and reinstallation of 
affected TRUs.

FAA's Determination

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

AD Requirements

    This AD requires removal and repair of TRUs that experienced a cowl 
gearbox stubshaft failure with subsequent repair of the fixed structure 
to Engine Manual repair No. FRS5887. This AD also requires removal and 
repair of TRUs previously repaired at the front ring with additional 
rivets using Engine Manual repair No. FRS5887 Part 2, and that have not 
had Engine Manual repair Nos. FRS4976 and FRS6669 applied to the rear 
ring at the No. 2 or No. 3 gearbox position.

FAA's Justification and Determination of the Effective Date

    The FAA has found that notice and comment prior to adoption of this 
rule is unnecessary because no engines are used on U.S. registered 
airplanes. Therefore, we find that good cause exists for making this 
amendment effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments before it becomes effective. However, we invite 
you to send any

[[Page 11977]]

written data, views, or arguments about this AD. Send your comments to 
an address listed under the ADDRESSES section. Include the Docket No. 
FAA-2011-0624 and 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 http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    We estimate that this AD will not affect any engines installed on 
airplanes of U.S. registry. Therefore, we estimate the cost of this AD 
to U.S. operators to be $0.

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends part 39 of the Federal Aviation 
Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
2011-13-01, Amendment 39-16724 (76 FR 40217, July 8, 2011) and adding 
the following new AD:

2013-04-01 Rolls-Royce plc: Amendment 39-17358; Docket No. FAA-2011-
0624; Directorate Identifier 2010-NE-11-AD.

(a) Effective Date

    This AD is effective March 8, 2013.

(b) Affected ADs

    This AD supersedes AD 2011-13-01, Amendment 39-16724 (76 FR 
40217, July 8, 2011).

(c) Applicability

    This AD applies to Rolls-Royce plc (RR) 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 turbofan engines with thrust reverser units 
(TRUs) that have a part number (P/N) specified in paragraph 1.A. of 
RR Alert Non-Modification Service Bulletin (NMSB) No. RB.211-78-
AG084, Revision 7, dated November 23, 2012, installed.

(d) Unsafe Condition

    This AD was prompted by additional engineering evaluation of 
TRUs, as a result of a translating cowl gearbox stubshaft failure 
and subsequent repair. We are issuing this AD to prevent failure of 
the attachment rivets, which may result in release of the TRU from 
the engine.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) If no repairs were performed as a result of a stubshaft 
failure, no further action is necessary.
    (2) If before December 14, 2009, the TRU has incorporated Engine 
Manual repair No. FRS5887 and incorporated either Engine Manual 
repair No. FRS4976 or No. FRS6669 as a result of a translating cowl 
gearbox stubshaft failure, then repair the TRU before further 
flight. Use the procedures in Section 3., Accomplishment 
Instructions, of RR Alert NMSB No. RB.211-78-AG084, Revision 5, 
dated February 4, 2011, to do the repair.
    (3) If before December 14, 2009, the TRU has incorporated Engine 
Manual repair No. FRS4976, or No. FRS6669 as a result of a 
translating cowl gearbox stubshaft failure, and it is not known 
whether Engine Manual repair No. FRS5887 was incorporated 
concurrently, then repair the TRU within 200 engine flight cycles 
after the effective date of this AD. Use the procedures in Section 
3., Accomplishment Instructions, of RR Alert NMSB No. RB.211-78-
AG084, Revision 5, dated February 4, 2011, to do the repair.
    (4) If before December 14, 2009, the TRU has incorporated only 
Engine Manual repair No. FRS5887 as a result of a translating cowl 
gearbox stubshaft failure, then repair the TRU within 1,150 engine 
flight cycles after the effective date of this AD. Use the 
procedures in Section 3., Accomplishment Instructions, of RR Alert 
NMSB No. RB.211-78-AG084, Revision 7, dated November 23, 2012, to do 
the repair.
    (5) If the TRU has previously been repaired at the front ring 
with additional rivets using Engine Manual repair No. FRS5887 Part 
2, and has not had Engine Manual repair Nos. FRS4976 and FRS6669 
applied to the rear ring at the No. 2 or No. 3 gearbox position:
    (i) Remove the TRU from the engine during the next scheduled 
engine removal after the effective date of this AD; and
    (ii) Before returning the TRU to service, repair the TRU using 
the procedure in Section 3.A.(4), Accomplishment Instructions, of RR 
Alert NMSB No. RB.211-78-AG084, Revision 7, dated November 23, 2012.

(f) Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (1) Actions performed before the effective date of this AD using 
RR Alert NMSB No. RB.211-78-AG084, Revision 4, dated December 22, 
2009, or RR Alert NMSB No. RB.211-78-AG084, Revision 3, dated 
November 24, 2009, satisfy the requirements of paragraphs (e)(2) and 
(e)(3) of this AD.
    (2) Actions performed before the effective date of this AD using 
RR Alert NMSB No. RB.211-78-AG084, Revision 6, dated November 16, 
2012, or Revision 5, dated February 4, 2011, or Revision 4, dated 
December 22, 2009, or Revision 3, dated November 24, 2009, satisfy 
the requirements of paragraph (e)(4) of this AD.
    (3) Actions performed before the effective date of this AD using 
RR Alert NMSB No. RB.211-78-AG084, Revision 6, dated

[[Page 11978]]

November 16, 2012, satisfy the requirements of paragraph (e)(5)(ii) 
of this AD.

(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.

(h) Related Information

    (1) Refer to EASA Airworthiness Directive 2012-0255, dated 
November 30, 2012, for related information.
    (2) Contact Robert Green, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; phone: 781-238-7754; 
fax: 781-238-7199; email: Robert.Green@faa.gov, for more information 
about this AD.

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Rolls-Royce plc Alert Non-Modification Service Bulletin No. 
RB.211-78-AG084, Revision 7, dated November 23, 2012.
    (ii) Reserved.
    (3) The following service information was approved for IBR on 
August 12, 2011, (76 FR 40217, July 8, 2011).
    (i) Rolls-Royce plc Alert Non-Modification Service Bulletin No. 
RB.211-78-AG084, Revision 5, dated February 4, 2011.
    (ii) Reserved.
    (4) For Rolls-Royce plc service information identified in this 
AD, contact Rolls-Royce plc, Corporate Communications, P.O. Box 31, 
Derby, England, DE248BJ; phone: 011-44-1332-242424; fax: 011-44-
1332-249936, or email: http://www.rolls-royce.com/contact/civil_team.jsp.
    (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.
    (6) You may view this service information at the National 
Archives and Records Administration (NARA). For information on the 
availability of this material at NARA, call 202 741 6030, or go to: 
http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on February 7, 2013.
Robert J. Ganley,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-03708 Filed 2-20-13; 8:45 am]
BILLING CODE 4910-13-P
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