Airworthiness Directives; Rolls-Royce Corporation (RRC) AE 3007A Series Turbofan Engines

[Federal Register Volume 74, Number 90 (Tuesday, May 12, 2009)]
[Rules and Regulations]
[Pages 22091-22093]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-11126]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0975; Directorate Identifier 2008-NE-29-AD; 
Amendment 39-15905; AD 2009-08-51]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Corporation (RRC) AE 3007A 
Series Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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SUMMARY: This document publishes in the Federal Register an amendment 
adopting emergency airworthiness directive (AD) 2009-08-51 that was 
sent previously to all known U.S. owners and operators of RRC AE 3007A 
series turbofan engines. This AD requires performing an eddy current 
inspection (ECI) or surface wave ultrasonic test (SWUT) inspection on 
each affected high-pressure turbine wheel. This AD results from 
additional reports of cracks in the high-pressure turbine (HPT) stage 2 
wheels identified from the required inspections in AD 2008-26-06. A 
revised risk assessment that includes these additional reports 
indicates we need to require a higher inspection rate. We are issuing 
this AD to prevent an uncontained failure of the HPT stage 2 wheel and 
damage to the airplane.

DATES: This AD becomes effective May 27, 2009 to all persons except 
those persons to whom it was made immediately effective by emergency AD 
2009-08-51, issued on April 10, 2009, which contained the requirements 
of this amendment. The Director of the Federal Register approved the 
incorporation by reference of certain publications listed in the 
regulations as of May 27, 2009.
    We must receive any comments on this AD by July 13, 2009.

ADDRESSES: Use one of the following addresses to comment on this AD.
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
    <bullet> Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor, 
Room W12-140, Washington, DC 20590-0001.
    <bullet> Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    <bullet> Fax: (202) 493-2251.

FOR FURTHER INFORMATION CONTACT: Kyri Zaroyiannis, Aerospace Engineer, 
Chicago Aircraft Certification Office, Small Airplane Directorate, FAA, 
2300 E. Devon Ave., Des Plaines, IL 60018; e-mail: 
[email protected]; telephone (847) 294-7836; fax (847) 294-7834.
    Contact Rolls-Royce Corporation, P.O. Box 420, Indianapolis, IN 
46206; telephone (317) 230-3774; fax (317) 230-8084; e-mail: 
royce.com">indy.pubs.services@rolls-royce.com, for the service information 
identified in this AD.

SUPPLEMENTARY INFORMATION: On April 10, 2009, the FAA issued emergency 
AD 2009-08-51, that applies to RRC AE 3007A series turbofan engines. 
That AD supersedes AD 2008-26-06, and requires performing an ECI or 
SWUT inspection on HPT stage 2 wheels for cracks. That AD resulted from 
additional reports of cracks in the HPT stage 2 wheels identified from 
the required inspections. A revised risk assessment that includes these 
additional reports indicates we needed to require a higher inspection 
rate. That emergency AD also addresses a group of low utilization 
engines above 16,350 cycles-since-new (CSN) that might not yet have 
been inspected. This condition, if not corrected, could result in a 
possible uncontained failure of the HPT stage 2 wheel and damage to the 
airplane.

Relevant Service Information

    We have reviewed RRC Alert Service Bulletin (ASB) AE 3007A-A-72-
367, Revision 1, dated April 7, 2009, that describes procedures for ECI 
of the HPT stage 2 wheel on AE 3007A series turbofan engines and RRC SB 
AE 3007A-72-368, Revision 1, dated April 6, 2009, that describes the 
procedures for SWUT inspection of the HPT stage 2 wheel on AE 3007A 
series turbofan engines.

FAA's Determination and Requirements of This AD

    Since the unsafe condition described is likely to exist or develop 
on other engines of the same type design, we

[[Page 22092]]

issued emergency AD 2009-08-51 to prevent an uncontained failure of the 
HPT stage 2 wheel, and damage to the airplane. This AD requires 
performing an ECI or SWUT inspection on each affected wheel. You must 
use the service information described previously to perform the actions 
required by this AD.

FAA's Determination of the Effective Date

    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we have found that notice and opportunity for 
public comment before issuing this AD are impracticable, and that good 
cause existed to make the AD effective immediately on April 10, 2009, 
to all known U.S. owners and operators of RRC AE 3007A series turbofan 
engines. These conditions still exist, and we are publishing the AD in 
the Federal Register as an amendment to Section 39.13 of part 39 of the 
Code of Federal Regulations (14 CFR part 39) to make it effective to 
all persons.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, we invite you to send us any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. FAA-2008-0975; 
Directorate Identifier 2008-NE-29-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify it.
    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 
with FAA personnel concerning this AD. Using the search function of the 
Web site, anyone can find and read the comments in any of our dockets, 
including, if provided, the name of the individual who sent the comment 
(or signed the comment on behalf of an association, business, labor 
union, etc.). You may review the DOT's complete Privacy Act Statement 
in the Federal Register published on April 11, 2000 (65 FR 19477-78).

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
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 Operations office (telephone (800) 647-5527) is the same as 
the Mail address provided in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

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 the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. 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.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary at the 
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Under the authority delegated to me by the Administrator, the Federal 
Aviation Administration 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 Amendment 39-15772 (73 FR 
78927, December 24, 2008), and by adding the following new 
airworthiness directive:

2009-08-51 Rolls-Royce Corporation (RRC) (Formerly Allison Engine 
Company): Amendment 39-15905. Docket No. FAA-2008-0975; Directorate 
Identifier 2008-NE-29-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective May 27, 
2009, to all persons except those persons to whom it was made 
immediately effective by emergency AD 2008-08-51, issued April 10, 
2009, which contained the requirements of this amendment.

Affected ADs

    (b) This AD supersedes AD 2008-26-06.

Applicability

    (c) This AD applies to RRC AE 3007A series turbofan engines with 
high-pressure turbine (HPT) stage 2 wheels, part number (P/N) 
23065892, 23069116, 23069438, 23069592, 23074462, 23074644, 
23075345, 23084520, or 23084781, installed. These engines are 
installed on, but not limited to, Empresa Brasileira de Aeronautica 
S. A. (EMBRAER) EMB-135 and EMB-145 airplanes.

Unsafe Condition

    (d) This AD results from additional reports of cracks in the HPT 
stage 2 wheels identified from the required inspections in AD 2008-
26-06. A revised risk assessment that includes these additional 
reports indicates we need to require a higher inspection rate. We 
are issuing this AD to prevent uncontained failure of the HPT stage 
2 wheel and damage to the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.

Eddy Current Inspection or Surface Wave Ultrasonic Test Inspection

    (f) Perform an eddy current inspection (ECI) or surface wave 
ultrasonic test (SWUT) inspection on each affected wheel by the 
cycle limit specified in Table 1 of this AD. Use paragraphs 2.A. 
through 2.C.(4) of RRC

[[Page 22093]]

Alert Service Bulletin (ASB) AE 3007A-A-72-367, Revision 1, dated 
April 7, 2009, or use paragraphs 2.A through 2.M.(8) of RRC Service 
Bulletin (SB) AE 3007A-72-368, Revision 1, dated April 6, 2009, to 
perform the inspections.

 Table 1--Compliance Times for ECI or SWUT Inspection of the HPT Stage 2
                    Wheels by Cycles-Since-New (CSN)
------------------------------------------------------------------------
  For HPT stage 2 wheels with CSN on
    the effective date of this AD:             Remove or inspect:
------------------------------------------------------------------------
17,500 or more.......................  Before the next flight.
15,560 to 17,499.....................  Within 75 cycles-in-service
                                        (CIS).
15,000 to 15,559.....................  Within 150 CIS.
14,700 to 14,999.....................  Within 200 CIS.
14,000 to 14,699.....................  Within 250 CIS.
13,580 to 13,999.....................  Within 450 CIS.
12,460 to 13,579.....................  Within 600 CIS.
------------------------------------------------------------------------

Installation Prohibition

    (g) After the effective date of this AD, don't return to 
service, any HPT stage 2 wheel that was installed in any RRC AE 
3007A series turbofan engine removed from service as a result of 
paragraph (f) of this AD unless the HPT stage 2 wheel has passed an 
inspection specified in RRC ASB AE 3007A-A-72-367, Revision 1, dated 
April 7, 2009 or RRC SB AE 3007A-72-368, Revision 1, dated April 6, 
2009.

Removal From Service

    (h) After the effective date of this AD, remove from service any 
HPT stage 2 wheel covered by this AD that has accumulated 22,500 
CSN.
    (i) After the effective date of this AD, don't install any HPT 
stage 2 wheel that has 22,500 or more CSN.

Credit for Previous Inspections

    (j) HPT stage 2 wheels already inspected and passed using RRC 
ASB AE 3007A-A-72-367, Revision 1, dated April 7, 2009, or earlier 
issue; or RRC SB AE 3007A-72-368, Revision 1, dated April 6, 2009, 
or earlier issue, meet the requirements for the initial inspections 
specified in paragraph (f) of this AD.

Alternative Methods of Compliance

    (k) The Manager, Chicago Aircraft Certification Office, has the 
authority to approve alternative methods of compliance for this AD 
if requested using the procedures found in 14 CFR 39.19.

Special Flight Permits

    (l) Under 14 CFR part 39.23, we are limiting the special flight 
permits for this AD by restricting the flight to essential flight 
crew only.

Related Information

    (m) Contact Kyri Zaroyiannis, Aerospace Engineer, Chicago 
Aircraft Certification Office, Small Airplane Directorate, FAA, 2300 
E. Devon Ave., Des Plaines, IL 60018; e-mail: 
[email protected]; telephone (847) 294-7836; fax (847) 294-
7834, for more information about this AD.

Material Incorporated by Reference

    (n) You must use the service information specified in Table 2 of 
this AD to perform the inspections required by this AD. The Director 
of the Federal Register approved the incorporation by reference of 
the documents listed in Table 2 of this AD in accordance with 5 
U.S.C. 552(a) and 1 CFR part 51. You can get a copy from Rolls-Royce 
Corporation, P.O. Box 420, Indianapolis, IN 46206; telephone (317) 
230-3774; fax (317) 230-8084; e-mail: royce.com">indy.pubs.services@rolls-royce.com. You may review copies at the FAA, New England Region, 12 
New England Executive Park, Burlington, MA; or 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: 
http://www.archives.gov/federal-register/cfr/ibr-locations.html.

                                       Table 2--Incorporation by Reference
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Rolls-Royce Corporation service information
                    No.                                  Page              Revision              Date
----------------------------------------------------------------------------------------------------------------
Alert Service Bulletin AE 3007A-A-72-367...  ALL........................          1  April 7, 2009.
    Total pages: 6
Service Bulletin AE 3007A-72-368...........  ALL........................          1  April 6, 2009.
    Total pages: 22
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    Issued in Burlington, Massachusetts, on May 4, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-11126 Filed 5-11-09; 8:45 am]
BILLING CODE 4910-13-P

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