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[Federal Register: May 19, 2010 (Volume 75, Number 96)]
[Proposed Rules]               
[Page 27964-27966]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr19my10-15]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-1157; Directorate Identifier 2009-NE-26-AD]
RIN 2120-AA64

 
Airworthiness Directives; Rolls-Royce plc (RR) RB211-22B and 
RB211-524 Series Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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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: Several low pressure turbine (LPT) shafts have been found

[[Page 27965]]

with cracks originating from the rear cooling air holes. The cracks 
were found at normal component overhaul, by the standard Magnetic 
Particle Inspection (MPI) technique defined in the associated engine 
manual. The cracks have been found to initiate from corrosion pits. 
Propagation of a crack from the rear cooling air holes may result in 
shaft failure and subsequently in an uncontained Low Pressure Turbine 
failure. For the reasons stated above, this AD requires the inspection 
of the affected engines' LPT shafts and replacement of the shaft, as 
necessary. We are proposing this AD to detect cracks, initiated by 
corrosion pits, originating from the rear cooling air holes, which 
could result in shaft failure and subsequently in an uncontained 
failure of the LPT and damage to the airplane.

DATES: We must receive comments on this proposed AD by July 6, 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: Telephone 011 44 1332 242424; fax 011 44 1332 249936, 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: Tara Chaidez, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
tara.chaidez@faa.gov; telephone (781) 238-7773; 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-2009-1157; 
Directorate Identifier 2009-NE-26-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 2007-0310 R1, dated January 8, 2008 (referred 
to after this as ``the MCAI''), to correct an unsafe condition for the 
specified products.] The MCAI states:

    Several low pressure turbine (LPT) shafts have been found with 
cracks originating from the rear cooling air holes. The cracks were 
found at normal component overhaul, by the standard Magnetic 
Particle Inspection (MPI) technique defined in the associated engine 
manual. The cracks have been found to initiate from corrosion pits. 
Propagation of a crack from the rear cooling air holes may result in 
shaft failure and subsequently in an uncontained Low Pressure 
Turbine failure. For the reasons stated above, this AD requires the 
inspection of the affected engines' LPT shafts and replacement of 
the shaft, as necessary.

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-AF336, 
dated October 24, 2007. 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 10 products of U.S. registry. We also estimate that 
it would take about 7 work-hours per product to comply with this 
proposed AD. The average labor rate is $85 per work-hour. Required 
parts would cost about $15,000 per product. Based on these figures, we 
estimate the cost of the proposed AD on U.S. operators to be $155,950.

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 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

[[Page 27966]]

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: Docket No. FAA-2009-1157; Directorate Identifier 
2009-NE-26-AD.

Comments Due Date

    (a) We must receive comments by July 6, 2010.

Affected Airworthiness Directives (ADs)

    (b) None.

Applicability

    (c) This AD applies to Rolls-Royce plc RB211-22B series and 
RB211-524B4-D-02, RB211-524D4-19, RB211-524D4-39, RB211-524D4-B-19, 
RB211-524D4-B-39, RB211-524D4X-19, and RB211-524D4X-B-19 model 
turbofan engines. These engines are installed on, but not limited 
to, Boeing 747 series and Lockheed L-1011 series airplanes.

Reason

    (d) This AD results from:

    Several low pressure turbine (LPT) shafts have been found with 
cracks originating from the rear cooling air holes. The cracks were 
found at normal component overhaul, by the standard Magnetic 
Particle Inspection (MPI) technique defined in the associated engine 
manual. The cracks have been found to initiate from corrosion pits. 
Propagation of a crack from the rear cooling air holes may result in 
shaft failure and subsequently in an uncontained Low Pressure 
Turbine failure. For the reasons stated above, this AD requires the 
inspection of the affected engines' LPT shafts and replacement of 
the shaft, as necessary.

    We are issuing this AD to detect cracks, initiated by corrosion 
pits, originating from the rear cooling air holes, which could 
result in shaft failure and subsequently in an uncontained failure 
of the LPT and damage to the airplane.

Actions and Compliance

    (e) Unless already done, do the following actions.

Initial Inspection Requirements

    (1) At the next engine shop visit after the effective date of 
this AD when the LPT shaft is completely disassembled to piece-part 
level, inspect the LPT shaft using paragraphs 3.A.(1)(a) through 
3.A.(4)(l) of the accomplishment instructions of Rolls-Royce Service 
Bulletin RB.211-72-AF336, dated October 24, 2007.

Repetitive Inspection Requirements

    (2) Thereafter, reinspect the LPT shaft using paragraphs 
3.A.(1)(a) through 3.A.(4)(l) of the accomplishment instructions of 
Rolls-Royce Service Bulletin RB.211-72-AF336, dated October 24, 2007 
and the following schedule in Table 1 of this AD:

         Table 1--Repetitive Inspection Interval by Engine Model
------------------------------------------------------------------------
                                               Maximum time between
              Engine model                 inspections (engine cycles)
------------------------------------------------------------------------
(i) RB211-22B Series, all models.......  3,500.
(ii) RB211-524B4-D-02..................  4,000.
(iii) RB211-524D4-19, RB211-524D4-39,    At the next engine shop visit
 RB211-524D4-B-19, RB211-524D4-B-39,      after the last inspection.
 RB211-524D4X-19 and RB211-524D4X-B-19.
------------------------------------------------------------------------

Remove Parts With Cracks

    (3) Remove cracked LPT shafts, found using paragraphs (e)(1) or 
(e)(2) of this AD, from service before further flight.

Definitions

    (4) 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. 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

    (f) 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

    (g) Refer to MCAI EASA Airworthiness Directive 2007-0310 R1, 
dated January 8, 2008, and Rolls-Royce plc Alert Service Bulletin 
RB.211-72-AF336, dated October 24, 2007, for related information. 
Contact Rolls-Royce plc P.O. Box 31, Derby, DE24 8BJ, United 
Kingdom; telephone 044 1332 242424; fax 044 1332 249936, for a copy 
of this service information.
    (h) Contact Tara Chaidez, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
tara.chaidez@faa.gov; telephone (781) 238-7773; fax (781) 238-7199, 
for more information about this AD.

    Issued in Burlington, Massachusetts, on May 12, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2010-11998 Filed 5-18-10; 8:45 am]
BILLING CODE 4910-13-P
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