Document ID: FAA-2010-0562-0026
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Rolls-Royce plc Turbofan Engines
Posted Date: 2013-10-02T04:00Z

[Federal Register Volume 78, Number 191 (Wednesday, October 2, 2013)]
[Rules and Regulations]
[Pages 60658-60660]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-23432]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0562; Directorate Identifier 2009-NE-29-AD; 
Amendment 39-17603; AD 2013-19-21]
RIN 2120-AA64

Airworthiness Directives; Rolls-Royce plc Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding airworthiness directive (AD) AD 2012-04-13, 
for all Rolls-Royce plc (RR) model RB211 Trent 553-61, 553A2-61, 556-
61, 556A2-61, 556B-61, 556B2-61, 560-61, and 560A2-61; and RB211 Trent 
768-60, 772-60, and 772B-60; and RB211-Trent 875-17, 877-17, 884-17, 
884B-17, 892-17, 892B-17, and 895-17; and RB211-524G2-T-19, -524G3-T-
19, -524H-T-36, and -524H2-T-19 turbofan engines that have a high-
pressure (HP) compressor stage 1 to 4 rotor disc installed, with a 
certain part number (P/N) installed. AD 2012-04-13 required repetitive 
inspections of the axial dovetail slots and follow-on corrective action 
depending on findings. This new AD expands the population of affected 
parts. This AD also changes, for the purposes of this AD, the 
definition of ``engine shop visit.'' This AD was prompted by reports of 
additional affected HP compressor rotor discs that require the same 
action. We are issuing this AD to detect cracks in the HP compressor 
stage 1 and 2 disc posts, which could result in failure of the disc 
post and HP compressor blades, damage to the engine, and damage to the 
airplane.

DATES: This AD is effective November 6, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of November 6, 
2013.

ADDRESSES: The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.
    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: 011-44-1332-245418; 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. 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 mandatory continuing 
airworthiness information (MCAI), the regulatory evaluation, any 
comments received, and other information. The street address for the 
Docket Office (phone: 800-647-5527) is provided in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: Frederick Zink, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: 781-238-7779; 
fax: 781-238-7199; email: frederick.zink@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2012-04-13, Amendment 39-16969 (77 FR 13483, 
March 7, 2012), (``AD 2012-04-13''). AD 2012-04-13 applied to the 
specified products. The NPRM published in the Federal Register on May 
14, 2013 (78 FR 28161). The NPRM proposed to continue to require 
repetitive inspections of the axial dovetail slots and follow-on 
corrective action depending on findings. The NPRM also proposed to 
expand the population of affected parts, and to change, for the 
purposes of this AD, the definition of ``engine shop visit.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
and the FAA's response to each comment.

Support for the Proposed AD

    The Boeing Company supports the NPRM (78 FR 28161, May 14, 2013) as 
written.
    We made no change to this AD.

Request To Revise Definition of Engine Shop Visit

    American Airlines (AAL) and RR requested that we change the 
definition of engine shop visit. The commenters noted that the 
definition of engine shop visit in the NPRM (78 FR 28161, May 14, 2013) 
differs from that in RR Alert Non-Modification Service Bulletin No. 
RB.211-72-AF964, Revision 3, dated January 11, 2013. AAL also indicated 
that the definition of engine shop visit in the NPRM, if adopted, would 
dramatically increase turn time and costs and affect availability of 
spare engines.
    We agree. We revised this AD by changing the definition of engine 
shop visit to read: ``For the purpose of this AD, an ``engine shop 
visit'' is whenever the HP compressor rotor is accessible and the 
compressor blades have been removed.''

[[Page 60659]]

Request To Correct Paragraph Designations in Compliance Section

    AAL requested that we correct references in the compliance section 
of the NPRM (78 FR 28161, May 14, 2013) that did not refer to the 
correct paragraph designation.
    We agree. The references should be to ``paragraph (f)'' or 
``paragraph (f)(2),'' as applicable, rather than to ``paragraph (e).'' 
We changed this AD by revising several references in the compliance 
section and the Credit for Previous Action paragraph from ``paragraph 
(e)'' to ``paragraph (f)'' or to ``paragraph (f)(2),'' as applicable.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described. We determined that these changes 
will not increase the economic burden on any operator or increase the 
scope of this AD.

Costs of Compliance

    We estimate that this AD affects about 432 engines installed on 
airplanes of U.S. registry. We also estimate that it will take about 20 
hours per product to comply with this AD. The average labor rate is $85 
per hour. No parts are required. Based on these figures, we estimate 
the cost of the AD on U.S. operators to be $734,400.

Authority for This Rulemaking

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

Regulatory Findings

    We have determined that this 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 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) 
2012-04-13, Amendment 39-16969 (77 FR 13483, March 7, 2012) and adding 
the following new AD:

2013-19-21 Rolls Royce plc: Amendment 39-17603; Docket No. FAA-2010-
0562; Directorate Identifier 2009-NE-29-AD.

(a) Effective Date

    This AD is effective November 6, 2013.

(b) Affected ADs

    This AD supersedes AD 2012-04-13, Amendment 39-16969 (77 FR 
13483, March 7, 2012).

(c) Applicability

    This AD applies to the following Rolls-Royce plc (RR) model 
turbofan engines that have a high-pressure (HP) compressor stage 1 
to 4 rotor disc installed, with a part number (P/N) listed in Table 
1 to paragraph (c) of this AD:
    (1) RB211 Trent 553-61, 553A2-61, 556-61, 556A2-61, 556B-61, 
556B2-61, 560-61, and 560A2-61; and
    (2) RB211 Trent 768-60, 772-60, and 772B-60; and
    (3) RB211-Trent 875-17, 877-17, 884-17, 884B-17, 892-17, 892B-
17, and 895-17; and
    (4) RB211-524G2-T-19, -524G3-T-19, -524H-T-36, and -524H2-T-19.

Table 1 to Paragraph (c)--Affected HP Compressor Stage 1 to 4 Rotor Disc
                          P/Ns by Engine Model
------------------------------------------------------------------------
                                            HP Compressor stage 1 to 4
              Engine model                        rotor disc P/N
------------------------------------------------------------------------
1. RB211 Trent 553-61, 553A2-61, 556-    FK30524 or FW88340.
 61, 556A2-61, 556B-61, 556B2-61, 560-
 61, and 560A2[dash]61.
2. RB211 Trent 768-60, 772-60, and 772B- FK22745, FK24031, FK23313,
 60.                                      FK25502, FK26185, FK32129,
                                          FW20195, FW20196, FW20197,
                                          FW20638, FW23711, FW88695,
                                          FW88696, FW88697, FW88698,
                                          FW88699, FW88700, FW88701,
                                          FW88702, or FW88703.
3. RB211 Trent 875-17, 877-17, 884-17,   FK24009, FK26167, FK32580,
 884B-17, 892-17, 892B-17, and 895-17.    FW11590, FW61622, FW88723,
                                          FW88724, or FW88725.
4. RB211-524G2-T-19, -524G3-T-19, -524H- FK25502, FW20195, FW23711,
 T-36, and -524H2-T-19.                   FW88695, FW88696, or FW88697.
------------------------------------------------------------------------

(d) Unsafe Condition

    We are issuing this AD to detect cracks in the HP compressor 
stage 1 and 2 disc posts, which could result in failure of the disc 
post and HP compressor blades, damage to the engine, and damage to 
the airplane.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

[[Page 60660]]

(f) Cleaning and Inspection

    (1) Clean and perform a fluorescent-penetrant inspection of the 
HP compressor stage 1 to 4 rotor disc at the first shop visit after 
accumulating 1,000 cycles since new (CSN) on the stage 1 to 4 rotor 
disc or at the next shop visit after the effective date of this AD, 
whichever occurs later.
    (2) Use paragraphs 3.A. through 3.E.(11) of the Accomplishment 
Instructions of RR Alert Non-Modification Service Bulletin (NMSB) 
No. RB.211-72-AF964, Revision 3, dated January 11, 2013, to do the 
cleaning and inspection.
    (3) Thereafter, at every engine shop visit, clean and inspect as 
required by paragraph (f)(2) of this AD.
    (4) If on the effective date of this AD, an engine with an 
affected part has 1,000 CSN or more, and is in the shop, clean and 
inspect as required by paragraph (f)(2) of this AD before returning 
the engine to service.
    (5) If cracks or anomalies are found during the inspection 
required by paragraph (f)(2) of this AD, accomplish the applicable 
corrective actions before returning the engine to service.

(g) Definition

    For the purpose of this AD, an ``engine shop visit'' is whenever 
the HP compressor rotor is accessible and the compressor blades have 
been removed.

(h) Credit for Previous Action

    If you performed cleanings and inspections before the effective 
date of this AD using RR NMSB No. RB.211-72-AF964, Revision 1, dated 
June 6, 2008, or Revision 2, dated June 8, 2011, then you met the 
requirements of paragraph (f) of this AD.

(i) 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.

(j) Related Information

    (1) For more information about this AD, contact, contact 
Frederick Zink, Aerospace Engineer, Engine Certification Office, 
FAA, Engine & Propeller Directorate, 12 New England Executive Park, 
Burlington, MA 01803; phone: 781-238-7779; fax: 781-238-7199; email: 
frederick.zink@faa.gov.
    (2) Refer to European Aviation Safety Agency AD No. 2013-0042, 
dated February 26, 2013, for related information. You may examine 
this AD on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2010-0562-0023.

(k) 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 Alert Non-Modification Service Bulletin No. 
RB.211-72-AF964. Revision 3, dated January 11, 2013.
    (ii) None.
    (3) 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; email: http://www.rolls-royce.com/contact/civil_team.jsp; 
or download from https://www.aeromanager.com.
    (4) 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.
    (5) 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 September 18, 2013.
Carlos A. Pestana,
Acting Directorate Assistant Manager, Engine & Propeller Directorate, 
Aircraft Certification Service.
[FR Doc. 2013-23432 Filed 10-1-13; 8:45 am]
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