Document ID: FAA-2010-0821-0015
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Rolls-Royce plc Turbofan Engines
Posted Date: 2012-05-03T04:00Z

[Federal Register Volume 77, Number 86 (Thursday, May 3, 2012)]
[Proposed Rules]
[Pages 26216-26218]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-10693]

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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]
RIN 2120-AA64

Airworthiness Directives; Rolls-Royce plc Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) that applies to 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. The existing AD currently requires initial and repetitive 
ultrasonic inspections (UIs) of certain low-pressure (LP) compressor 
blades identified by serial number (S/N). This proposed AD would 
require the same actions but expands the population of blades. We are 
proposing 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: We must receive comments on this proposed AD by July 2, 2012.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, 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: Deliver to Mail address above 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: 
http://www.rolls-royce.com/contact/civil_team.jsp. 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 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 proposed 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: alan.strom@faa.gov.

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-2010-0821; 
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 proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed 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 proposed AD.

Discussion

    On March 20, 2012, we issued AD 2012-06-23, Amendment 39-17004 (77 
FR 20508, April 5, 2012), 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. That AD 
requires initial and repetitive UIs of certain LP compressor blades 
identified by S/N. That AD superseded AD 2011-08-07, Amendment 39-16657 
(76 FR 24798, May 3, 2011) and resulted from RR concluding that 
additional blades affected must be inspected. We issued that AD to 
prevent LP compressor blades from failing due to blade root cracks, 
which could lead to uncontained

[[Page 26217]]

engine failure and damage to the airplane.

Actions Since Existing AD Was Issued

    We issued AD 2012-06-23, Amendment 39-17004 (77 FR 20508, April 5, 
2012), to ensure timely inspection of the listed blades in Appendices 
3A through 3G of Rolls-Royce plc Alert Service Bulletin (ASB) No. 
RB.211-72-AG244, Revision 4, dated December 22, 2011. We now need AD 
action to add the inspection of the blades listed in Appendices 3H 
through 3L of that ASB.

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 listed in Appendices 3A 
through 3L of that ASB.

FAA's Determination

    We are proposing 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.

Proposed AD Requirements

    This proposed AD would retain all of the requirements of AD 2012-
06-23 (77 FR 20508, April 5, 2012). This proposed AD would require 
adding inspections of the blades listed in Appendices 3H through 3L of 
ASB No. RB.211-72-AG244, Revision 4, dated December 22, 2011. This 
proposed AD would also require accomplishing the actions specified in 
the service information described previously.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 158 engines installed on airplanes of U.S. registry. 
We also estimate that it would 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 would 
need replacement, at a cost of about $82,000. Based on these figures, 
we estimate the annual cost of the proposed 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, 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 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 that the 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, 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

    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]

    2. The FAA amends Sec.  39.13 by removing airworthiness directive 
(AD) 2012-06-23, Amendment 39-17004 (77 FR 20508, April 5, 2012), and 
adding the following new AD:

Rolls-Royce plc: Docket No. FAA-2010-0821; Directorate Identifier 
2010-NE-30-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by July 2, 2012.

(b) Affected ADs

    This AD supersedes AD 2012-06-23, Amendment 39-17004 (77 FR 
20508, April 5, 2012).

(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 need to add the inspections of the 
low-pressure (LP) compressor blades listed by serial number (S/N) in 
Appendices 3H through 3L of Rolls-Royce plc Alert Service Bulletin 
(ASB) No. RB.211-72-AG244, Revision 4, dated December 22, 2011. 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) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Perform an initial ultrasonic inspection (UI) of the 
affected LP compressor blades identified by S/N in Appendices 3A 
through 3L of RR 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
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Appendix number of RR ASB No.
 RB.211-72-AG244, revision 4,
 that identifies affected LP                              Initial inspection threshold
   compressor blades by S/N
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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.

[[Page 26218]]

 
3F...........................  Within 46 months after the effective date of this AD.
3G...........................  Within 58 months after the effective date of this AD.
3H...........................  Within 70 months after the effective date of this AD.
3I...........................  Within 82 months after the effective date of this AD.
3J...........................  Within 94 months after the effective date of this AD.
3K...........................  Within 106 months after the effective date of this AD.
3L...........................  Within 118 months after the effective date of this AD.
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    (2) Thereafter, perform repetitive UIs of the affected LP 
compressor blades within every 100 flight cycles.
    (3) Use paragraph 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 before re-installing the 
blades.
    (6) After the effective date of this AD, do not install any 
affected LP compressor blade that has reached the initial inspection 
threshold in Table 1, unless it has passed the initial and 
repetitive UIs required by this AD.

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

    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) 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.

(h) 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: 
alan.strom@faa.gov.
    (2) Refer to European Aviation Safety Agency AD 2012-0025, dated 
February 8, 2012, for related information.
    (3) 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: http://www.rolls-royce.com/contact/civil_team.jsp. 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.

    Issued in Burlington, Massachusetts, on April 27, 2012.
Colleen M. D'Alessandro,
Assistant Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2012-10693 Filed 5-2-12; 8:45 am]
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