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[Federal Register: August 23, 2010 (Volume 75, Number 162)]
[Rules and Regulations]               
[Page 51654-51656]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr23au10-4]                         

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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; 
Amendment 39-16402; AD 2010-17-10]
RIN 2120-AA64

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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This 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 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.

DATES: This AD becomes effective September 27, 2010. The Director of 
the Federal Register approved the incorporation by reference of certain 
publications listed in this AD as of September 27, 2010.

ADDRESSES: The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

FOR FURTHER INFORMATION CONTACT: Alan Strom, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
alan.strom@faa.gov; telephone (781) 238-7143; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on May 19, 2010 (75 FR 
27964). That NPRM proposed 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. The commenter supports the 
NPRM.

Conclusion

    We reviewed the available data, including the comment received, and 
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 10 products of U.S. registry. We also estimate that it 
will take about 7 work-hours per product to comply with this AD. The 
average labor rate is $85 per work-hour. Required parts will cost about 
$15,000 per product. Based on these figures, we estimate the cost of 
the 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

[[Page 51655]]

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 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 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 regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

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 (phone (800) 647-5527) is provided in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
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 adding the following new AD:

2010-17-10 Rolls-Royce plc: Amendment 39-16402. Docket No. FAA-2009-
1157; Directorate Identifier 2009-NE-26-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective 
September 27, 2010.

Affected 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
----------------------------------------------------------------------------------------------------------------
                 Engine model                           Maximum time between 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, RB211-    At the next engine shop visit after the last inspection.
 524D4-B-19, RB211-524D4-B-39, RB211-524D4X-19
 and RB211-524D4X-B-19.
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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.

Alternative Methods of Compliance (AMOCs)

    (f) 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, for related information.
    (h) Contact Alan Strom, Aerospace Engineer, Engine Certification 
Office, FAA, Engine and Propeller Directorate, 12 New England 
Executive Park, Burlington, MA 01803; e-mail: alan.strom@faa.gov; 
telephone (781) 238-7143; fax (781) 238-7199, for more information 
about this AD.

Material Incorporated by Reference

    (i) You must use Rolls-Royce Service Bulletin RB.211-72-AF336, 
dated October 24, 2007, to do the actions required by this AD, 
unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.

[[Page 51656]]

    (2) For service information identified in this AD, contact 
Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, United Kingdom; 
telephone 044 1332 242424; fax 044 1332 249936.
    (3) 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.

    Issued in Burlington, Massachusetts, on August 5, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2010-20705 Filed 8-20-10; 8:45 am]
BILLING CODE 4910-13-P
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