Document ID: FAA-2010-0562-0021
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Rolls-Royce plc Turbofan Engines
Posted Date: 2013-05-14T04:00Z

[Federal Register Volume 78, Number 93 (Tuesday, May 14, 2013)]
[Proposed Rules]
[Pages 28161-28163]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-11337]

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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]
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) 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. The existing AD requires 
repetitive inspections of the axial dovetail slots, and follow-on 
corrective action depending on findings. This proposed AD expands the 
population of affected parts. This proposed AD also changes, for the 
purposes of this AD, the definition of ``engine shop visit.'' We are 
proposing 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: We must receive comments on this proposed AD by July 15, 2013.

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; 
phone: 011-44-1332-242424; fax: 011-44-1332-249936; or email: http://www.rolls-royce.com/contact/civil_team.jsp; or download the 
publication from https://www.aeromanager.com. 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

[[Page 28162]]

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: 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:

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-2010-0562; 
Directorate Identifier 2009-NE-29-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 February 23, 2012, we issued AD 2012-04-13, Amendment 39-16969 
(77 FR 13483, March 7, 2012), for all 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 HP compressor stage 1 to 4 rotor disc installed, with a P/N 
listed in Table 1 of that AD. That AD requires repetitive inspections 
of the axial dovetail slots, and follow-on corrective action depending 
on findings. That AD changed the definition of a shop visit to be less 
restrictive. We issued that 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.

Actions Since Existing AD Was Issued

    Since we issued AD 2012-04-13, Amendment 39-16969 (77 FR 13483, 
March 7, 2012), RR engineering identified additional affected HP 
compressor rotor discs that require the same action. As a result of the 
additional population of discs, this proposed rule would increase the 
total cost to the U.S. fleet.
    Also, since we issued AD 2012-04-13, Amendment 39-16969 (77 FR 
13483, March 7, 2012), we changed the definition of ``engine shop 
visit'' to be less restrictive. In the existing AD, we define ``engine 
shop visit'' to be whenever all compressor blades are removed from the 
HP compressor drum. In this proposed AD, we define ``engine shop 
visit'' to be whenever the HP compressor rotor is accessible for 
removal of the compressor blades. Under the revised definition in this 
proposed AD, engine shop visit will occur more frequently, likely 
resulting in earlier inspection of the Stage 1 to 4 rotor disc than 
would occur under the original definition. This is more in line with 
the instructions in revised RR Alert Non-Modification Service Bulletin 
(NMSB) RB.211-72-AF964, Revision 3, dated January 11, 2013.

Relevant Service Information

    We reviewed RR Alert NMSB RB.211-72-AF964, Revision 3, dated 
January 11, 2013. The Alert NMSB describes procedures for cleaning and 
inspecting the axial dovetail slots. We also reviewed European Aviation 
Safety Agency AD No. 2013-0042, dated February 26, 2013, which requires 
inspection of the new rotor discs.

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 these same type 
designs.

Proposed AD Requirements

    This proposed AD would retain all of the requirements of AD 2012-
04-13, Amendment 39-16969 (77 FR 13483, March 7, 2012). This proposed 
AD would expand the population of parts to be inspected.

Costs of Compliance

    We estimate that this proposed AD would affect about 432 engines 
installed on airplanes of U.S. registry. We also estimate that it would 
take about 20 hours per product to comply with this AD. The average 
labor rate is $85 per hour. No parts would be required per product. 
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 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 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

[[Page 28163]]

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:

Rolls-Royce plc: Docket No. FAA-2010-0562; Directorate Identifier 
2009-NE-29-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by July 15, 
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 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 560A2-61.
(2) RB211 Trent 768-60, 772-60, and      FK22745, FK24031, FK23313,
 772B-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, -     FK25502, FW20195, FW23711,
 524H-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.

(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 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, perform the cleaning 
and inspection required by paragraph (e) 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, perform the 
cleaning and inspection required by paragraph (e) of this AD before 
return to service.
    (5) If cracks or anomalies are found during the inspection 
required by paragraph (e) of this AD, accomplish the applicable 
corrective actions before return to service.

(g) Definition

    For the purpose of this AD, an ``engine shop visit'' is whenever 
the HP compressor rotor is accessible for removal of the compressor 
blades.

(h) Credit for Previous Actions

    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 (e)(1) 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 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 RR Alert NMSB No. RB.211-72-AF964, Revision 3, 
dated January 11, 2013, and European Aviation Safety Agency AD No. 
2013-0042, dated February 26, 2013, for related information.
    (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; or email: http://www.rolls-royce.com/contact/civil_team.jsp; or download the publication from https://www.aeromanager.com. 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.

    Issued in Burlington, Massachusetts, on May 1, 2013.
Colleen M. D'Alessandro,
Assistant Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2013-11337 Filed 5-13-13; 8:45 am]
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