AD 2012-06-23

[Federal Register Volume 77, Number 66 (Thursday, April 5, 2012)]
[Rules and Regulations]
[Pages 20508-20511]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2012-8163]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0821; Directorate Identifier 2010-NE-30-AD; 
Amendment 39-17004; AD 2012-06-23]
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-Trent 875-17, RB211-Trent 877-17, 
RB211-Trent 884-17, RB211-Trent 884B-17, RB211-Trent 892-17, RB211-
Trent 892B-17, and RB211-Trent 895-17 turbofan engines. That AD 
currently requires initial and repetitive ultrasonic inspections (UIs) 
of certain low-pressure (LP) compressor blades identified by serial 
number (S/N). This AD requires the same actions but expands the 
population of blades. This AD was prompted by RR concluding that 
additional blades affected must be inspected. We are issuing this AD to 
prevent LP compressor blades from failing due to blade root cracks, 
which could lead to uncontained engine failure and damage to the 
airplane.

DATES: This AD is effective April 20, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of April 20, 
2012.
    We must receive any comments on this AD by May 21, 2012.

ADDRESSES: You may send comments by any of the following methods:

[[Page 20509]]

    <bullet> Federal eRulemaking Portal: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a>. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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, 
telephone: 011-44-1332-242424; fax: 011-44-1332-245418, or email:<a href="http://www.rolls-royce.com/contact/civil_team.jsp">http://www.rolls-royce.com/contact/civil_team.jsp</a>. You may review copies of 
the referenced 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a>; 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: Alan Strom, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; phone: 781-238-7143; fax: 
781-238-7199; email: <a href="/cdn-cgi/l/email-protection#6e0f020f00401d1a1c01032e080f0f40090118"><span class="__cf_email__" data-cfemail="62030e030c4c1116100d0f220403034c050d14">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Discussion

    On April 1, 2011, we issued AD 2011-08-07, Amendment 39-16657 (76 
FR 24798, May 3, 2011), for all RR RB211-Trent 875-17, RB211-Trent 877-
17, RB211-Trent 884-17, RB211-Trent 884B-17, RB211-Trent 892-17, RB211-
Trent 892B-17, and RB211-Trent 895-17 turbofan engines. On September 9, 
2011, we also issued a correction (76 FR 59013, September 23, 2011) to 
that AD. That AD requires initial and repetitive UIs of certain LP 
compressor blades identified by S/N. That AD resulted 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. We issued that AD to prevent LP 
compressor blades from failing due to blade root cracks, which could 
lead to uncontained engine failure and damage to the airplane.

Actions Since AD Was Issued

    Since we issued AD 2011-08-07 (76 FR 24798, May 3, 2011), RR 
determined that additional S/Ns of LP compressor blades are affected 
and require inspection. EASA has also issued AD 2012-0025, dated 
February 8, 2012, to expand the population of affected LP compressor 
blades operating in Europe. About 2,300 of the added blades require 
inspection within 70 cycles of the effective date of the AD since those 
blades have more fatigue damage from prior use.
    This superseding AD differs from EASA AD 2012-0025. This AD only 
requires inspection of LP compressor blades that are listed in 
Appendices 3A through 3G of RR Alert Service Bulletin (ASB) No. RB.211-
72-AG244, Revision 4, dated December 22, 2011. We are developing 
another AD to require inspection of LP compressor blades listed in 
Appendices 3H through 3L of RR ASB No. RB.211-72-AG244, Revision 4, 
dated December 22, 2011.

Relevant Service Information

    We reviewed Rolls-Royce plc ASB No. RB.211-72-AG244, Revision 4, 
dated December 22, 2011. The service information describes procedures 
for performing UIs of the LP compressor blades.

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 accomplishing the actions specified in the service 
information described previously except that this AD only requires 
inspection of LP compressor blades that are listed in Appendices 3A 
through 3G of RR ASB No. RB.211-72-AG244, Revision 4, dated December 
22, 2011.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because about 
2,300 LP compressor blades require inspection within 70 cycles after 
the effective date of the AD. This equates to about one month's time 
for Trent 800 engines flying two flights per day. Therefore, we find 
that notice and opportunity for prior public comment are impracticable 
and 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 written data, views, or arguments about this AD. Send 
your comments to an address listed under the ADDRESSES section. Include 
the docket number FAA-2010-0821 and directorate identifier 2010-NE-30-
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 <a href="http://www.regulations.gov">http://www.regulations.gov</a>, 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

    Based on the service information, we estimate that this AD will 
affect about 158 engines installed on airplanes of U.S. registry. We 
also estimate that it will take about 3 hours per engine inspection, 
and six inspections per year. The average labor rate is $85 per work-
hour. We estimate that one LP compressor blade per year will need 
replacement, at a cost of about $82,000. Based on these figures, we 
estimate the annual cost of the AD on U.S. operators to be $323,740. 
Our cost estimate is exclusive of possible warranty coverage.

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,

[[Page 20510]]

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, 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) 
2011-08-07, Amendment 39-16657 (76 FR 24798, May 3, 2011) and adding 
the following new AD:

2012-06-23 Rolls-Royce plc: Amendment 39-17004; Docket No. FAA-2010-
0821; Directorate Identifier 2010-NE-30-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective April 20, 
2012.

(b) Affected ADs

    This AD supersedes AD 2011-08-07, Amendment 39-16657 (76 FR 
24798, May 3, 2011).

(c) Applicability

    This AD applies to Rolls-Royce plc (RR) RB211-Trent 875-17, 
RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent 884B-17, RB211-
Trent 892-17, RB211-Trent 892B-17, and RB211-Trent 895-17 turbofan 
engines.

(d) Unsafe Condition

    This AD was prompted by the determination by RR that additional 
serial numbers (S/Ns) of low-pressure (LP) compressor blades are 
affected and need to be inspected. We are issuing this AD to prevent 
LP compressor blades from failing due to blade root cracks, which 
could lead to uncontained engine failure and damage to the airplane.

(e) Actions and Compliance

    Unless already done, do the following actions.
    (1) Perform an initial ultrasonic inspection (UI) of the 
affected LP compressor blades identified by S/N in Appendices 3A 
through 3G of RR Alert Service Bulletin (ASB) No. RB.211-72-AG244, 
Revision 4, dated December 22, 2011. Use Table 1 of this AD to 
determine your initial inspection threshold.

                 Table 1--Initial Inspection Thresholds
------------------------------------------------------------------------
Appendix number of RR ASB No. RB.211-72-
   AG244, revision 4, that identifies
  affected LP compressor blades by S/N     Initial inspection threshold
 
------------------------------------------------------------------------
3A and 3B..............................  Within 70 flight cycles after
                                          the effective date of this AD.
3C.....................................  Within 10 months after the
                                          effective date of this AD.
3D.....................................  Within 22 months after the
                                          effective date of this AD.
3E.....................................  Within 34 months after the
                                          effective date of this AD.
3F.....................................  Within 46 months after the
                                          effective date of this AD.
3G.....................................  Within 58 months after the
                                          effective date of this AD.
------------------------------------------------------------------------

     (2) Thereafter, perform repetitive UIs of the affected LP 
compressor blades within every 100 flight cycles.
    (3) Use paragraphs 3.A.(1) through 3.A.(2) of Accomplishment 
Instructions of RR ASB No. RB.211-72-AG244, Revision 4, dated 
December 22, 2011, and paragraphs 1 through 3.B. of Appendix 1 of 
that ASB, or paragraphs 3.B.(1) through 3.B.(3) of Accomplishment 
Instructions of RR ASB No. RB.211-72-AG244, Revision 4, dated 
December 22, 2011, and paragraphs 1 through 3.C. of Appendix 2 of 
that ASB, to perform the UIs.
    (4) Do not return to service any engine with blades that failed 
the inspection required by this AD.
    (5) For blades that are removed from the engine and pass 
inspection, re-apply dry film lubricant, and install all blades in 
their original position.
    (6) After the effective date of this AD, do not install any 
affected LP compressor blade unless it has passed the initial and 
repetitive UIs required by this AD.

(f) Credit for Previous Actions

    You may take credit for the initial inspection that is required 
by paragraph (e)(1) of this AD if you performed the initial 
inspection before the effective date of this AD using RR ASB No. 
RB.211-72-AG244, dated August 7, 2009; ASB No. RB.211-72-AG244, 
Revision 1, dated January 26, 2010; ASB No. RB.211-72-AG244, 
Revision 2, dated August 18, 2011; or ASB No. RB.211-72-AG244, 
Revision 3, dated December 13, 2011.

(g) FAA AD Differences

    This AD differs from EASA AD 2012-0025, dated February 8, 2012. 
That AD requires inspecting LP compressor blades that are listed in 
Appendices 3A through 3L of RR ASB No. RB.211-72-AG244, Revision 4, 
dated December 22, 2011, whereas this AD only requires inspection of 
LP compressor blades that are listed in Appendices 3A through 3G of 
the ASB.

(h) Alternative Methods of Compliance

    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.

(i) Related Information

    (1) For more information about this AD, contact Alan Strom, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7143; fax: 781-238-7199; email: 
<a href="/cdn-cgi/l/email-protection#f998959897d78a8d8b9694b99f9898d79e968f"><span class="__cf_email__" data-cfemail="f6979a9798d8858284999bb6909797d8919980">[email&#160;protected]</span></a>.
    (2) Refer to EASA AD 2012-0025, dated February 8, 2012, for 
related information.

(j) Material Incorporated by Reference

    (1) You must use Rolls-Royce plc Alert Service Bulletin No. 
RB.211-72-AG244, Revision 4, dated December 22, 2011,

[[Page 20511]]

Appendix 1, Appendix 2, and Appendices 3A through 3G of that ASB, to 
do the actions required by this AD, unless the AD specifies 
otherwise. The Director of the Federal Register approved the 
incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Rolls-Royce plc, Corporate Communications, P.O. Box 31, Derby, 
England, DE248BJ, telephone: 011-44-1332-242424; fax: 011-44-1332-
245418, or email: <a href="http://www.rolls-royce.com/contact/civil_team.jsp">http://www.rolls-royce.com/contact/civil_team.jsp</a>.
    (3) You may review copies of the 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.
    (4) You may also review copies of the service information that 
is incorporated by reference 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: <a href="http://www.archives.gov/federal-register/cfr/ibr_locations.html">http://www.archives.gov/federal-register/cfr/ibr_locations.html</a>.

    Issued in Burlington, Massachusetts, on March 20, 2012.
Peter A. White,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-8163 Filed 4-4-12; 8:45 am]
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