Airworthiness Directives; Rolls-Royce plc (RR) RB211-22B and RB211-524 Series Turbofan Engines, 27964-27966 [2010-11998]

Download as PDF 27964 Federal Register / Vol. 75, No. 96 / Wednesday, May 19, 2010 / Proposed Rules The unsafe condition is loss of braking capability and possible brake fires, which could reduce the ability of the flightcrew to safely land the airplane. the compliance times specified, unless the actions have already been done. Compliance (f) You are responsible for having the actions required by this AD performed within Actions (g) Do the following actions. (1) Within 6 months after the effective date of this AD, do a detailed inspection for wear of the brake QD couplings by measuring dimension ‘‘A,’’ in accordance with Part 1 of the Accomplishment Instructions of Fokker Service Bulletin SBF100–32–156, Revision 1, dated June 29, 2009. Repeat the inspection thereafter at the applicable intervals specified in Table 1 of this AD, except as required by paragraph (g)(2) of this AD. TABLE 1—REPETITIVE INSPECTION INTERVALS If dimension ‘‘A’’ is— Repeat the inspection at intervals not to exceed— Greater than or equal to 0.76 mm ......................................................................................................................................... Less than 0.76 mm but greater than or equal to 0.72 mm ................................................................................................... Less than 0.72 mm but greater than or equal to 0.68 mm ................................................................................................... Less than 0.68 mm but greater than or equal to 0.61 mm ................................................................................................... Less than 0.61 mm but greater than 0.53 mm ...................................................................................................................... 6 months. 3 months. 30 days. 7 days. 24 hours. (2) If, during any inspection required by paragraph (g)(1) of this AD, dimension ‘‘A’’ on any brake QD coupling is less than or equal to 0.53 mm, before further flight, replace the affected brake QD coupling with an improved unit having P/N AE73059E or P/N AE73091E, as applicable, in accordance with Part 2 of the Accomplishment Instructions of Fokker Service Bulletin SBF100–32–156, Revision 1, dated June 29, 2009. (3) Within 24 months after the effective date of this AD, replace all remaining brake QD couplings having P/N AE70690E, P/N AE70691E, P/N AE99111E, and P/N AE99119E with improved units, in accordance with Part 2 of the Accomplishment Instructions of Fokker Service Bulletin SBF100–32–156, Revision 1, dated June 29, 2009. (4) Installation of brake QD couplings with an improved unit having P/N AE73059E or P/N AE73091E at all locations terminates the repetitive inspections required by paragraph (g)(1) of this AD. (5) Replacing the brake QD couplings is also acceptable for compliance with the corresponding requirements of paragraphs (g)(1), (g)(2), and (g)(3) of this AD if done before the effective date of this AD, in accordance with any of the service bulletins specified in Table 2 of this AD: TABLE 2—FOKKER CREDIT SERVICE BULLETINS Fokker Service Bulletins Revision Fokker Service Bulletin SBF100–32–127 ............................................................... Fokker Service Bulletin SBF100–32–127 ............................................................... Fokker Service Bulletin SBF100–32–156 ............................................................... Original ................................................... 1 ............................................................. Original ................................................... FAA AD Differences erowe on DSK5CLS3C1PROD with PROPOSALS-1 Note 1: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (h) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1137; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective VerDate Mar<15>2010 13:46 May 18, 2010 Jkt 220001 Date July 20, 2001. March 6, 2009. March 6, 2009. actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. DEPARTMENT OF TRANSPORTATION Related Information AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). (i) Refer to MCAI EASA Airworthiness Directive 2009–0176, dated August 6, 2009; and Fokker Service Bulletin SBF100–32–156, Revision 1, dated June 29, 2009; for related information. Issued in Renton, Washington, on May 4, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–11904 Filed 5–18–10; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 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 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 E:\FR\FM\19MYP1.SGM 19MYP1 Federal Register / Vol. 75, No. 96 / Wednesday, May 19, 2010 / Proposed Rules erowe on DSK5CLS3C1PROD with PROPOSALS-1 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 https://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 https:// 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; VerDate Mar<15>2010 13:46 May 18, 2010 Jkt 220001 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 https:// 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, PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 27965 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 E:\FR\FM\19MYP1.SGM 19MYP1 27966 Federal Register / Vol. 75, No. 96 / Wednesday, May 19, 2010 / Proposed Rules 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. § 39.13 [Amended] 2. The FAA amends § 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 RollsRoyce 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 ............................................................ (ii) RB211–524B4–D–02 ........................................................................... (iii) RB211–524D4–19, RB211–524D4–39, RB211–524D4–B–19, RB211–524D4–B–39, 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 erowe on DSK5CLS3C1PROD with PROPOSALS-1 (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, VerDate Mar<15>2010 13:46 May 18, 2010 Jkt 220001 3,500. 4,000. At the next engine shop visit after the last inspection. 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 PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0480; Directorate Identifier 2010–NM–035–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Model 747–400 and 747– 400D Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain Model 747–400 and 747–400D series airplanes. This proposed AD would E:\FR\FM\19MYP1.SGM 19MYP1

Agencies

[Federal Register Volume 75, Number 96 (Wednesday, May 19, 2010)]
[Proposed Rules]
[Pages 27964-27966]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-11998]


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

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).

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

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 https://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 https://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 https://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
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.