[Federal Register Volume 75, Number 114 (Tuesday, June 15, 2010)]
[Proposed Rules]
[Pages 33738-33740]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-14318]
[[Page 33738]]
=======================================================================
-----------------------------------------------------------------------
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) RB211-524 Series
and RB211 Trent 500, 700, and 800 Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) issued by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:
During manufacture of a number of HP Compressor Stage 1 and 2
discs with axial dovetail slots, anomalies at the disc post corners
have been found. Fatigue crack initiation and subsequent crack
propagation at the disc post may result in release of two blades and
the disc post. This may potentially be beyond the containment
capabilities of the engine casings. Thus, these anomalies present at
the disc posts constitute a potentially unsafe condition.
We are proposing this AD to detect cracks in the high-pressure
compressor (HPC) Stage 1 and 2 disc posts, which could result in
failure of the disc post and HPC blades, release of uncontained engine
debris, and damage to the airplane.
DATES: We must receive comments on this proposed AD by July 30, 2010.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for sending your
comments electronically.
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.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Fax: (202) 493-2251.
Contact Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, United
Kingdom; phone: 011 44 1332 242424, fax: 011 44 1332 249936; e-mail:
royce.com">tech.help@rolls-royce.com, for the service information identified in
this proposed AD.
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 proposed 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.
FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; e-mail:
[email protected]; telephone (781) 238-7176; fax (781) 238-7199.
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 based on 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
with FAA personnel concerning this proposed 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).
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2009-0073R1, dated April 8, 2009, (referred to
after this as ``the MCAI'') to correct an unsafe condition for the
specified products. The MCAI states:
During manufacture of a number of HP Compressor Stage 1 and 2
discs with axial dovetail slots, anomalies at the disc post corners
have been found. Fatigue crack initiation and subsequent crack
propagation at the disc post may result in release of two blades and
the disc post. This may potentially be beyond the containment
capabilities of the engine casings. Thus, these anomalies present at
the disc posts constitute a potentially unsafe condition.
For the reasons described above, this AD requires repetitive
inspections of the axial dovetail slots and follow-on corrective
action, depending on findings.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Rolls-Royce plc has issued Alert Service Bulletin RB.211-72-AF964,
Revision 1, dated June 6, 2008. The actions described in this service
information are intended to correct the unsafe condition identified in
the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of the
United Kingdom, and is approved for operation in the United States.
Pursuant to our bilateral agreement with the United Kingdom, they have
notified us of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all information provided by EASA, and determined the unsafe
condition exists and is likely to exist or develop on other products of
the same type design.
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
proposed 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 proposed 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
[[Page 33739]]
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 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 this 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); 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 regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
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 adding the following new AD:
Rolls-Royce plc (RR): Docket No. FAA-2010-0562; Directorate
Identifier 2009-NE-29-AD.
Comments Due Date
(a) We must receive comments by July 30, 2010.
Affected Airworthiness Directives (ADs)
(b) None.
Applicability
(c) This AD applies to 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. These engines are installed on,
but not limited to, Boeing 747, 767, and 777 series airplanes and
Airbus A330 and A340 series airplanes.
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, FK20195, FK25502, or FW23711.
[dash]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[dash]17, 892B-17, and 895- FW11590, or FW61622.
17.
------------------------------------------------------------------------
Reason
(d) This AD results from reports that:
``During manufacture of a number of HP Compressor Stage 1 and 2
discs with axial dovetail slots, anomalies at the disc post corners
have been found. Fatigue crack initiation and subsequent crack
propagation at the disc post may result in release of two blades and
the disc post. This may potentially be beyond the containment
capabilities of the engine casings. Thus, these anomalies present at
the disc posts constitute a potentially unsafe condition.''
We are issuing this AD to detect cracks in the high-pressure
compressor (HPC) Stage 1 and 2 disc posts, which could result in
failure of the disc post and HPC blades, release of uncontained
engine debris, and damage to the airplane.
Actions and Compliance
(e) Unless already done, do the following actions.
(1) Perform a fluorescent penetrant inspection of the HP
compressor stage 1 to 4 rotor discs at the first shop visit after
accumulating 1000 cycles since new on the stage 1 to 4 rotor disks
or at the next shop visit after the effective date of this AD which
ever occurs later. Use paragraph 3.E.(1) through 3.E.(10)(i) of the
Accomplishment Instructions of Rolls-Royce Alert Service Bulletin
(ASB) RB.211-72-AF964, Revision 1, dated June 6, 2008 to do the
inspections.
(2) Thereafter at every engine shop visit, perform the
inspection specified by paragraph (e)(1) of this AD.
Definitions
(f) For the purpose of this AD, an ``engine shop visit'' is the
induction of an engine into the shop for maintenance involving the
separation of pairs of major mating engine flanges, except that the
separation of engine flanges solely for the purposes of
transportation without subsequent engine maintenance does not
constitute an engine shop visit.
Other FAA AD Provisions
(g) Alternative Methods of Compliance (AMOCs): The Manager,
Engine Certification Office, FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures found in 14 CFR
39.19.
Related Information
(h) Refer to MCAI EASA Airworthiness Directive 2009-0073R1,
dated April 8, 2009, and RR ASB RB.211-72-AF964, Revision 1, dated
June 6, 2008, for related information. Contact Rolls-Royce plc, P.O.
Box 31, Derby, DE24 8BJ, United Kingdom; phone: 011 44 1332 242424,
fax: 011 44 1332 249936; e-mail: royce.com">tech.help@rolls-royce.com, for a
copy of this service information.
(i) Contact James Lawrence, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
[email protected]; telephone (781) 238-7176; fax (781) 238-
7199, for more information about this AD.
[[Page 33740]]
Issued in Burlington, Massachusetts, on June 7, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2010-14318 Filed 6-14-10; 8:45 am]
BILLING CODE 4910-13-P