Document ID: FAA-2010-0562-0014
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Rolls-Royce plc Turbofan Engines
Posted Date: 2011-10-20T04:00Z

[Federal Register Volume 76, Number 203 (Thursday, October 20, 2011)]
[Proposed Rules]
[Pages 65136-65138]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-27069]

 ========================================================================
 Proposed Rules
                                                 Federal Register
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
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 

  Federal Register / Vol. 76, No. 203 / Thursday, October 20, 2011 / 
Proposed Rules  

[[Page 65136]]

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 (RR) Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) that applies to all RR model RB211-524G2-T-19, -524G3-T-19, -524H-
T-36, and -524H2-T-19; and RB211-Trent 553-61, 553A2-61, 556-61, 556A2-
61, 556B-61, 556B2-61, 560-61, 560A2-61; RB211-Trent 768-60, 772-60, 
772B-60; and RB211-Trent 875-17, 877-17, 884-17, 884B-17, 892-17, 892B-
17, and 895-17 turbofan engines that have a high-pressure (HP) 
compressor stage 1 to 4 rotor disc with a part number (P/N) listed in 
Table 1 of this proposed AD. The existing AD currently requires 
repetitive inspections of the axial dovetail slots, and follow-on 
corrective action depending on findings. Since we issued that AD, we 
determined that the definition of shop visit is too restrictive in the 
existing AD. This proposed AD would continue to require those 
repetitive inspections and follow-on corrective actions, and it would 
change the definition of a shop visit to be less restrictive. 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, release of uncontained engine debris, and damage to 
the airplane.

DATES: We must receive comments on this proposed AD by December 19, 
2011.

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: 011-44-1332-245418 or e-mail from 
http://www.rolls-royce.com/contact/civil_team.jsp, or download the 
publication from https://www.aeromanager.com. 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 and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; phone: 781-238-7143; fax: 
781-238-7199; e-mail: 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-2010-0562; 
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 April 12, 2011, we issued AD 2011-09-07, Amendment 39-16669 (76 
FR 24793, May 3, 2011), for all RR model RB211-524G2-T-19, -524G3-T-19, 
-524H-T-36, and -524H2-T-19; and RB211 Trent 553-61, 553A2-61, 556-61, 
556A2-61, 556B-61, 556B2-61, 560-61, 560A2-61; RB211 Trent 768-60, 772-
60, 772B-60; and RB211 Trent 875-17, 877-17, 884-17, 884B-17, 892-17, 
892B-17, and 895-17 turbofan engines. That AD requires initial and 
repetitive fluorescent penetrant inspections of the HP compressor stage 
1 to 4 rotor discs at the first shop visit after accumulating 1,000 
cycles-since-new on the stage 1 to 4 rotor discs or at the next shop 
visit after the effective date of that AD, which ever occurs later. 
That AD also requires repetitive inspections at every shop visit. That 
AD resulted from findings of anomalies at the corners of the disc posts 
during manufacture of stage 1 and stage 2 discs with axial dovetails 
slots. We issued that AD to detect cracks in the HP compressor stage 1 
and stage 2 disc posts, which could result in failure of the disc post 
and release of HP compressor blades, release of uncontained engine 
debris, and damage to the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2011-09-07, Amendment 39-16669 (76 FR 24793, May 
3, 2011), we found that the definition of ``shop visit'' in the AD is 
too restrictive, in that it would require operators to inspect more 
often than required to ensure safety. We also found that Alert Service 
Bulletin (ASB) No. RB.211-72-AF964, Revision 2, dated June 8, 2011, 
also may be appropriate to

[[Page 65137]]

the corrective action in that AD, as is ASB No. RB.211-72-AF964, 
Revision 1, dated June 6, 2008 which is referenced in AD 2011-09-07.

Relevant Service Information

    We reviewed RR ASB No. RB.211-72-AF964, Revision 1, dated June 6, 
2008, and Revision 2, dated June 8, 2011. The ASB describes procedures 
for cleaning and inspecting the axial dovetail slots.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the definition of shop visit was too 
restrictive, and that 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 change the definition of a shop visit in AD 
2011-09-07 to ``whenever all compressor blades are removed from the HP 
compressor drum.'' This proposed AD would also allow using ASB No. 
RB.211-72-AF964, Revision 1, dated June 6, 2008, or ASB No. RB.211-72-
AF964, Revision 2, dated June 8, 2011, to perform the inspection.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 371 products of U.S. registry. We also estimate that 
it would take about 20 work-hours per product to comply with this AD. 
The average labor rate is $85 per work-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 $630,700.

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) 2011-09-07, Amendment 39-166679 (76 FR 24793, May 3, 2011), 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 December 19, 
2011.

(b) Affected ADs

    This AD supersedes AD 2011-09-07, Amendment 39-16669 (76 FR 
24793, May 3, 2011).

(c) Applicability

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

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

(d) Unsafe Condition

    This AD was prompted by our determination that the definition of 
``shop visit'' in the existing AD is too restrictive, in that it 
would require operators to inspect more often than required to 
ensure safety. 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, release of uncontained 
engine debris, and damage to the airplane.

(e) Compliance

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

[[Page 65138]]

(f) Cleaning and Inspection

    (1) Clean and perform a fluorescent penetrant inspection of the 
HP compressor stage 1 to 4 rotor discs at the first shop visit after 
accumulating 1,000 cycles since new on the stage 1 to 4 rotor discs 
or at the next shop visit after the effective date of this AD, which 
ever occurs later.
    (2) Use paragraph 3.A through 3.E.(11) of the Accomplishment 
Instructions of Rolls-Royce Alert Service Bulletin (ASB) No. RB.211-
72-AF964, Revision 1, dated June 6, 2008, or ASB No. RB.211-72-
AF964, Revision 2, dated June 8, 2011, to do the inspections.
    (3) Thereafter at every engine shop visit, perform the 
inspection specified by paragraph (f) of this AD.

(g) Definition

    For the purpose of this AD, an ``engine shop visit'' is whenever 
all compressor blades are removed from the HP compressor drum.

(h) 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.

(i) Related Information

    (1) For more information about this AD, contact Alan Strom, 
Aerospace Engineer, Engine Certification Office, FAA, Engine and 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7143; fax: 781-238-7199; e-mail: 
alan.strom@faa.gov.
    (2) See European Aviation Safety Agency Airworthiness Directive 
2011-0073R1, dated April 8, 2009, 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: 011-44-1332-245418 
or e-mail from http://www.rolls-royce.com/contact/civil_team.jsp, 
or download the publication from https://www.aeromanager.com. You 
may review copies 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 October 14, 2011.
Peter A. White,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-27069 Filed 10-19-11; 8:45 am]
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