AD 2012-04-13

[Federal Register Volume 77, Number 45 (Wednesday, March 7, 2012)]
[Rules and Regulations]
[Pages 13483-13485]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2012-5370]



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Federal Register / Vol. 77, No. 45 / Wednesday, March 7, 2012 / Rules 
and Regulations

[[Page 13483]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0562; Directorate Identifier 2009-NE-29-AD; 
Amendment 39-16969; AD 2012-04-13]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc (RR) Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding an existing airworthiness directive (AD) 
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 have a high-pressure (HP) compressor stage 1 
to 4 rotor disc with a part number (P/N) listed in Table 1 of the AD. 
That 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 continues to require those 
repetitive inspections and follow-on corrective actions. This new AD 
changes the definition of a shop visit to be less restrictive. 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.

DATES: This AD is effective April 11, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of April 11, 
2012.

ADDRESSES: 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 email 
from <a href="http://www.rolls-royce.com/contact/civil_team.jsp">http://www.rolls-royce.com/contact/civil_team.jsp</a>, or download 
the publication from <a href="https://www.aeromanager.com">https://www.aeromanager.com</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 address for the 
Docket Office (phone: 800-647-5527) is Document Management Facility, 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC 20590.

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#aacbc6cbc484d9ded8c5c7eacccbcb84cdc5dc"><span class="__cf_email__" data-cfemail="92f3fef3fcbce1e6e0fdffd2f4f3f3bcf5fde4">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2011-09-07, Amendment 39-16669 (76 FR 24793, 
May 3, 2011). That AD applies to the specified products. The NPRM 
published in the Federal Register on October 20, 2011 (76 FR 65136). 
That NPRM proposed to continue to require 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 NPRM 
also proposed to continue to require repetitive inspections at every 
shop visit. That NPRM also proposed to change the definition of a shop 
visit to be less restrictive.

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 NPRM

    Two commenters, the Boeing Company and American Airlines, support 
the intent of the NPRM (76 FR 65136, October 20, 2011).

Request To Change From a Supersedure to a Revision

    One commenter, American Airlines, requested that we change the 
proposed AD (76 FR 65136, October 20, 2011) from being an AD 
supersedure to being an AD revision of the existing AD 2011-09-07 (76 
FR 24793, May 3, 2011), or, have Rolls-Royce plc revise Alert Service 
Bulletin (ASB) No. RB.211-72-AF964 to remove the reference to AD 2011-
09-07, so that we can reference that latest ASB revision in the AD. The 
commenter stated that the ASB revision should be issued before the AD 
is issued, and referenced in the AD, to avoid the burden of needing 
global Alternative Methods of Compliances written.
    We do not agree. The reference to the previous AD (76 FR 24793, May 
3, 2011) in ASB No. RB.211-72-AF964 is not the section of the ASB 
incorporated by reference by this AD. We can not delay publishing an AD 
to wait for an administrative change to a service bulletin. 
Administrative updates to service bulletins are made for a variety of 
reasons. These revisions are easily handled by the alternative method 
of compliance process described in paragraph (i) of this AD. We did not 
change the AD.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and

[[Page 13484]]

determined that air safety and the public interest require adopting the 
AD as proposed.

Costs of Compliance

    Based on the service information, we estimate that this AD will 
affect about 371 products of U.S. registry. We also estimate that it 
will take about 20 work-hours per product to comply with this AD. The 
average labor rate is $85 per work-hour. No parts will 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 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 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) 
2011-09-07, Amendment 39-16669 (76 FR 24793, May 3, 2011), and adding 
the following new AD:

2012-04-13 Rolls-Royce plc: Amendment 39-16969; Docket No. FAA-2010-
0562; Directorate Identifier 2009-NE-29-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective April 11, 2012.

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

(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.

(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 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) Credit for Previous Action

    A cleaning and inspection performed before the effective date of 
this AD using Rolls-Royce ASB No. RB.211-72-AF964, Revision 1, dated 
June 6, 2008, or Revision 2, dated June 8, 2011, satisfies a 
cleaning and inspection cycle required by this AD.

(i) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA may approve AMOCs 
for this AD. Use

[[Page 13485]]

the procedures found in 14 CFR 39.19 to make your request.

(j) 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#1e7f727f70306d6a6c71735e787f7f30797168"><span class="__cf_email__" data-cfemail="1c7d707d72326f686e73715c7a7d7d327b736a">[email&#160;protected]</span></a>.
    (2) See European Aviation Safety Agency Airworthiness Directive 
2009-0073R1, dated April 8, 2009, for related information.

(k) Material Incorporated by Reference

    (1) You must use the following service information to do the 
actions required by this AD, unless the AD specifies otherwise. The 
Director of the Federal Register approved the incorporation by 
reference (IBR) under 5 U.S.C. 552(a) and 1 CFR part 51 of the 
following service information on the date specified:
    (i) Rolls-Royce Alert Service Bulletin No. RB.211-72-AF964, 
Revision 2, dated June 8, 2011 approved for IBR April 11, 2012.
    (ii) Rolls-Royce ASB No. RB.211-72-AF964, Revision 1, dated June 
6, 2008 approved for IBR June 7, 2011 (76 FR 24793, May 3, 2011).
    (2) 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 email from <a href="http://www.rolls-royce.com/contact/civil_team.jsp">http://www.rolls-royce.com/contact/civil_team.jsp</a>, or 
download the publication from <a href="https://www.aeromanager.com">https://www.aeromanager.com</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 February 23, 2012.
Peter A. White,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-5370 Filed 3-6-12; 8:45 am]
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