Airworthiness Directives; Rolls-Royce plc RB211 Trent 800 Series Turbofan Engines, 7563-7565 [E9-3358]

Download as PDF 7563 Proposed Rules Federal Register Vol. 74, No. 31 Wednesday, February 18, 2009 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF AGRICULTURE Natural Resources Conservation Service 7 CFR Part 625 RIN 0578–AA52 Healthy Forests Reserve Program cprice-sewell on PRODPC61 with PROPOSALS AGENCY: Natural Resources Conservation Service (NRCS), United States Department of Agriculture (USDA). ACTION: Proposed rule; Reopening public comments. SUMMARY: On January 14, 2009, NRCS published in the Federal Register a proposed rule for the Healthy Forests Reserve Program (HFRP) with a public comment period closing on February 13, 2009. The proposed rule included changes to address amendments to HFRP associated with enactment of the Food, Conservation, and Energy Act of 2008. NRCS is hereby reopening the public comment period for the HFRP proposed rule and amending the closing date to March 20, 2009. DATES: Comments to the HFRP proposed rule, published in the Federal Register on January 14, 2009 (74 FR 1954) must be received on or before March 20, 2009. ADDRESSES: You may send comments using any of the following methods: • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending comments electronically. • NRCS Web site: Go to http:// www.nrcs.usda.gov and follow the instructions for sending comments electronically. • Mail: Easements Programs Division, Natural Resources Conservation Service, Healthy Forests Reserve Program Comments, P.O. 2890, Room 6819–S, Washington, DC 20013. • Fax: 1–202–720–4265. • Hand Delivery: Room 6819–S of the USDA South Office Building, 1400 Independence Avenue, SW., Washington, DC 20250, between 9 a.m. VerDate Nov<24>2008 12:15 Feb 17, 2009 Jkt 217001 and 4 p.m., Monday through Friday, except Federal holidays. Please ask the guard at the entrance to the South Office Building to call 202–720–4527 in order to be escorted into the building. • This proposed rule may be accessed via Internet. Users can access the NRCS homepage at http://www.nrcs.usda.gov/; select Farm Bill link from the menu; select the Proposed Rule link from beneath the Rules Index title. Persons with disabilities who require alternative means for communication (Braille, large print, audiotape, etc.) should contact the USDA Target Center at (202) 720–2600 (voice and TDD). FOR FURTHER INFORMATION CONTACT: Director, Easement Programs Division, NRCS, P.O. Box 2890, Washington, DC 20013–2890; Phone: (202) 720–1854; Fax: (202) 720–4265; or e-mail: HFRP@wdc.usda.gov. Persons with disabilities who require alternative means for communication (Braille, large print, audiotape, etc.) should contact the USDA Target Center at (202) 720–2600 (voice and TDD). 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 high-pressure (HP) compressor stage 1 discs, a small number of parts have been rejected due to a machining defect that was found during inspection. Analysis of the possibility of less severe examples having been undetected and passed into service has concluded that action is required to reduce the risk of failure. It is therefore necessary to reduce the life limit from that currently published for the applicable parts. Federal Aviation Administration The HP compressor stage 1 disc is part of the HP compressor stage 1–4 shaft, part number (P/N) FK32580. We are proposing this AD to prevent uncontained failure of the HP compressor stage 1 disc, resulting in an in-flight engine shutdown and possible damage to the airplane. DATES: We must receive comments on this proposed AD by March 20, 2009. 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. 14 CFR Part 39 Examining the AD Docket [Docket No. FAA–2008–1165; Directorate Identifier 2008–NE–38–AD] 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 Signed this 11th day of February 2009, in Washington, DC. Dave White, Acting Vice President, Commodity Credit Corporation and Acting Chief, Natural Resources Conservation Service. [FR Doc. E9–3354 Filed 2–17–09; 8:45 am] BILLING CODE 3410–16–P DEPARTMENT OF TRANSPORTATION RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc RB211 Trent 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) PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 E:\FR\FM\18FEP1.SGM 18FEP1 7564 Federal Register / Vol. 74, No. 31 / Wednesday, February 18, 2009 / Proposed Rules & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: james.lawrence@faa.gov; 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–2008–1165; Directorate Identifier 2008–NE–38–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). cprice-sewell on PRODPC61 with PROPOSALS 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 2008–0099, dated May 21, 2008 (corrected June 12, 2008) (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: During manufacture of HP compressor stage 1 discs, a small number of parts have been rejected due to a machining defect that was found during inspection. Analysis of the possibility of less severe examples having been undetected and passed into service has concluded that action is required to reduce the risk of failure. It is therefore necessary to reduce the life limit from that currently published for the applicable parts. You may obtain further information by examining the MCAI in the AD docket. This proposed AD would require removing HP compressor stage 1–4 shafts, P/N FK32580, from service at reduced life limits based on part assessment using either ‘‘Multiple Flight VerDate Nov<24>2008 12:15 Feb 17, 2009 Jkt 217001 Profile Monitoring’’, or ‘‘Heavy Flight Profile’’ calculations. Relevant Service Information Rolls-Royce plc has issued Alert Service Bulletin RB.211–72–AF825, Revision 1, dated September 8, 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. This proposed AD requires removing HP compressor stage 1–4 shafts, P/N FK32580, from service at reduced life limits based on part assessment using either ‘‘Multiple Flight Profile Monitoring’’, or ‘‘Heavy Flight Profile’’ calculations. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 78 products of U.S. registry. Required parts would cost about $15,095 per product. We estimate that no additional labor costs would be incurred to perform the proposed actions. We anticipate that the removal from service of the HP compressor stage 1–4 shafts will occur while the engine is inducted into the shop for routine maintenance. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $1,177,410. Our cost estimate is exclusive of possible warranty coverage. 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 PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 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, 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–2008– 1165; Directorate Identifier 2008–NE– 38–AD. Comments Due Date (a) We must receive comments by March 20, 2009. Affected Airworthiness Directives (ADs) (b) None. Applicability (c) This airworthiness directive (AD) applies to Rolls-Royce plc (RR) models E:\FR\FM\18FEP1.SGM 18FEP1 Federal Register / Vol. 74, No. 31 / Wednesday, February 18, 2009 / Proposed Rules RB211 Trent 875–17, Trent 877–17, Trent 884–17, Trent 884B–17, Trent 892–17, Trent 892B–17, and Trent 895–17 turbofan engines, with high-pressure (HP) compressor stage 1– 4 shafts, part number (P/N) FK32580, installed. These engines are installed on, but not limited to, Boeing 777 series airplanes. Reason (d) European Aviation Safety Agency (EASA) AD 2008–0099, dated May 21, 2008 (corrected June 12, 2008) states the unsafe condition is as follows: During manufacture of high-pressure (HP) compressor stage 1 discs, a small number of parts have been rejected due to a machining defect that was found during inspection. Analysis of the possibility of less severe examples having been undetected and passed into service has concluded that action is required to reduce the risk of failure. It is therefore necessary to reduce the life limit from that currently published for the applicable parts. The HP compressor stage 1 disc is part of the HP compressor stage 1–4 shaft, P/N FK32580. We are issuing this AD to prevent uncontained failure of the HP compressor stage 1 disc, resulting in an in-flight engine shutdown and possible damage to the airplane. Actions and Compliance (e) Unless already done, do the following actions. (1) RB211 Trent 800 critical part lives may be monitored by one of two methods: ‘‘Multiple Flight Profile Monitoring’’, or ‘‘Heavy Flight Profile’’. Information on these profiles can be found in the RR Engine Manual Airworthiness Limitations Section. (2) Standard Duty Cycles (SDC) is the product of Flight Cycles and Beta Factor. Information on Flight Cycles and Beta Factor can be found in the RR Engine Manual Airworthiness Limitations Section. cprice-sewell on PRODPC61 with PROPOSALS Multiple Flight Profile Monitoring Parts (3) For RB211 Trent 800 engines being monitored by ‘‘Multiple Flight Profile Monitoring,’’ do the following: (i) On the effective date of this AD, if the life of HP compressor stage 1–4 shaft, P/N FK32580, is equal to or over 5,580 SDC, then the part must be withdrawn from service before exceeding 7,780 SDC. (ii) On the effective date of this AD, if the life of HP compressor stage 1–4 shaft, P/N FK32580, is between 3,380 and 5,580 SDC, then the part must be withdrawn from service before exceeding an additional 2,200 SDC. (iii) On the effective date of this AD, if the life of HP compressor stage 1–4 shaft, P/N FK32580, is equal to or below 3,380 SDC, then the part must be withdrawn from service before exceeding 5,580 SDC. Reassessment of the Revised Life Limit (4) Operators should be aware that reassessment of the revised life limit in accordance with this AD (including possible reassessment per the applicable subparagraph (e)(3)(i), (e)(3)(ii), or (e)(3)(iii) of this AD, will be necessary if, at some time in the future, the operator changes the flight VerDate Nov<24>2008 12:15 Feb 17, 2009 Jkt 217001 7565 profile that was applicable before the Effective Date of this AD, such that parts which are the subject of this AD are affected. To recalculate the revised life limit, the life of the part in SDC at the Effective Date of this AD, must be recalculated from the part’s entry into service (zero life), and must use the Beta Factor(s) for the new Flight Profile(s). DEPARTMENT OF TRANSPORTATION Heavy Flight Profile Parts Airworthiness Directives; BAE Systems (Operations) Limited Model BAe 146 and Avro 146–RJ Airplanes (5) For RB211 Trent 800 engines being monitored by ‘‘Heavy Flight Profile,’’ do the following: (i) On the effective date of this AD, if the life of HP compressor stage 1–4 shaft, P/N FK32580, is equal to or over 5,280 flight cycles, then the part must be withdrawn from service before exceeding 7,480 flight cycles. (ii) On the effective date of this AD, if the life of HP compressor stage 1–4 shaft, P/N FK32580, is between 3,080 flight cycles and 5,280 flight cycles, then the part must be withdrawn from service before exceeding an additional 2,200 flight cycles. (iii) On the effective date of this AD, if the life of HP compressor stage 1–4 shaft, P/N FK32580, is equal to or below 3,080 flight cycles, then the part must be withdrawn from service before exceeding 5,280 flight cycles. 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 EASA Airworthiness Directive 2008–0099, dated May 21, 2008 (corrected June 12, 2008), and Rolls-Royce plc Alert Service Bulletin No. RB.211–72–AF825, Revision 1, dated September 8, 2008, for related information. Contact Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; telephone: 011–44–1332–242424; fax: 011– 44–1332–245418, for a copy of this service information. (h) Contact James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: james.lawrence@faa.gov; telephone (781) 238–7176; fax (781) 238– 7199, for more information about this AD. Issued in Burlington, Massachusetts, on February 10, 2009. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–3358 Filed 2–17–09; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0133; Directorate Identifier 2008–NM–107–AD] RIN 2120–AA64 AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to all BAE Systems (Operations) Limited Model BAe 146 and Avro 146–RJ airplanes. The existing AD currently requires repetitive inspections for corrosion of frames 15, 18, 41, and 43 and applicable related investigative and corrective actions. The existing AD also provides an optional action that would extend the repetitive inspection interval. This proposed AD would add a high frequency eddy current inspection for corrosion of the outer frame flanges and door hinge bosses of frames 15, 18, 41, and 43. This proposed AD results from a report indicating that corrosion has been detected in the outer frame flanges and door hinge bosses during scheduled maintenance. We are proposing this AD to prevent reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by March 20, 2009. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact BAE Systems Regional Aircraft, 13850 McLearen Road, Herndon, Virginia 20171; telephone 703–736–1080; e-mail raebusiness@baesystems.com; Internet E:\FR\FM\18FEP1.SGM 18FEP1

Agencies

[Federal Register Volume 74, Number 31 (Wednesday, February 18, 2009)]
[Proposed Rules]
[Pages 7563-7565]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-3358]


=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1165; Directorate Identifier 2008-NE-38-AD]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB211 Trent 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 high-pressure (HP) compressor stage 1 
discs, a small number of parts have been rejected due to a machining 
defect that was found during inspection. Analysis of the possibility 
of less severe examples having been undetected and passed into 
service has concluded that action is required to reduce the risk of 
failure. It is therefore necessary to reduce the life limit from 
that currently published for the applicable parts.

    The HP compressor stage 1 disc is part of the HP compressor stage 
1-4 shaft, part number (P/N) FK32580. We are proposing this AD to 
prevent uncontained failure of the HP compressor stage 1 disc, 
resulting in an in-flight engine shutdown and possible damage to the 
airplane.

DATES: We must receive comments on this proposed AD by March 20, 2009.

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.

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

[[Page 7564]]

& Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; e-mail: james.lawrence@faa.gov; 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-2008-1165; 
Directorate Identifier 2008-NE-38-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 2008-0099, dated May 21, 2008 (corrected June 
12, 2008) (referred to after this as ``the MCAI''), to correct an 
unsafe condition for the specified products. The MCAI states:

    During manufacture of HP compressor stage 1 discs, a small 
number of parts have been rejected due to a machining defect that 
was found during inspection. Analysis of the possibility of less 
severe examples having been undetected and passed into service has 
concluded that action is required to reduce the risk of failure. It 
is therefore necessary to reduce the life limit from that currently 
published for the applicable parts.

    You may obtain further information by examining the MCAI in the AD 
docket. This proposed AD would require removing HP compressor stage 1-4 
shafts, P/N FK32580, from service at reduced life limits based on part 
assessment using either ``Multiple Flight Profile Monitoring'', or 
``Heavy Flight Profile'' calculations.

Relevant Service Information

    Rolls-Royce plc has issued Alert Service Bulletin RB.211-72-AF825, 
Revision 1, dated September 8, 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. This proposed AD requires removing HP compressor 
stage 1-4 shafts, P/N FK32580, from service at reduced life limits 
based on part assessment using either ``Multiple Flight Profile 
Monitoring'', or ``Heavy Flight Profile'' calculations.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 78 products of U.S. registry. Required parts would 
cost about $15,095 per product. We estimate that no additional labor 
costs would be incurred to perform the proposed actions. We anticipate 
that the removal from service of the HP compressor stage 1-4 shafts 
will occur while the engine is inducted into the shop for routine 
maintenance. Based on these figures, we estimate the cost of the 
proposed AD on U.S. operators to be $1,177,410. Our cost estimate is 
exclusive of possible warranty coverage.

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 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, 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-2008-1165; Directorate Identifier 
2008-NE-38-AD.

Comments Due Date

    (a) We must receive comments by March 20, 2009.

Affected Airworthiness Directives (ADs)

    (b) None.

Applicability

    (c) This airworthiness directive (AD) applies to Rolls-Royce plc 
(RR) models

[[Page 7565]]

RB211 Trent 875-17, Trent 877-17, Trent 884-17, Trent 884B-17, Trent 
892-17, Trent 892B-17, and Trent 895-17 turbofan engines, with high-
pressure (HP) compressor stage 1-4 shafts, part number (P/N) 
FK32580, installed. These engines are installed on, but not limited 
to, Boeing 777 series airplanes.

Reason

    (d) European Aviation Safety Agency (EASA) AD 2008-0099, dated 
May 21, 2008 (corrected June 12, 2008) states the unsafe condition 
is as follows:
    During manufacture of high-pressure (HP) compressor stage 1 
discs, a small number of parts have been rejected due to a machining 
defect that was found during inspection. Analysis of the possibility 
of less severe examples having been undetected and passed into 
service has concluded that action is required to reduce the risk of 
failure. It is therefore necessary to reduce the life limit from 
that currently published for the applicable parts.

The HP compressor stage 1 disc is part of the HP compressor stage 1-
4 shaft, P/N FK32580. We are issuing this AD to prevent uncontained 
failure of the HP compressor stage 1 disc, resulting in an in-flight 
engine shutdown and possible damage to the airplane.

Actions and Compliance

    (e) Unless already done, do the following actions.
    (1) RB211 Trent 800 critical part lives may be monitored by one 
of two methods: ``Multiple Flight Profile Monitoring'', or ``Heavy 
Flight Profile''. Information on these profiles can be found in the 
RR Engine Manual Airworthiness Limitations Section.
    (2) Standard Duty Cycles (SDC) is the product of Flight Cycles 
and Beta Factor. Information on Flight Cycles and Beta Factor can be 
found in the RR Engine Manual Airworthiness Limitations Section.

Multiple Flight Profile Monitoring Parts

    (3) For RB211 Trent 800 engines being monitored by ``Multiple 
Flight Profile Monitoring,'' do the following:
    (i) On the effective date of this AD, if the life of HP 
compressor stage 1-4 shaft, P/N FK32580, is equal to or over 5,580 
SDC, then the part must be withdrawn from service before exceeding 
7,780 SDC.
    (ii) On the effective date of this AD, if the life of HP 
compressor stage 1-4 shaft, P/N FK32580, is between 3,380 and 5,580 
SDC, then the part must be withdrawn from service before exceeding 
an additional 2,200 SDC.
    (iii) On the effective date of this AD, if the life of HP 
compressor stage 1-4 shaft, P/N FK32580, is equal to or below 3,380 
SDC, then the part must be withdrawn from service before exceeding 
5,580 SDC.

Reassessment of the Revised Life Limit

    (4) Operators should be aware that reassessment of the revised 
life limit in accordance with this AD (including possible 
reassessment per the applicable subparagraph (e)(3)(i), (e)(3)(ii), 
or (e)(3)(iii) of this AD, will be necessary if, at some time in the 
future, the operator changes the flight profile that was applicable 
before the Effective Date of this AD, such that parts which are the 
subject of this AD are affected. To recalculate the revised life 
limit, the life of the part in SDC at the Effective Date of this AD, 
must be recalculated from the part's entry into service (zero life), 
and must use the Beta Factor(s) for the new Flight Profile(s).

Heavy Flight Profile Parts

    (5) For RB211 Trent 800 engines being monitored by ``Heavy 
Flight Profile,'' do the following:
    (i) On the effective date of this AD, if the life of HP 
compressor stage 1-4 shaft, P/N FK32580, is equal to or over 5,280 
flight cycles, then the part must be withdrawn from service before 
exceeding 7,480 flight cycles.
    (ii) On the effective date of this AD, if the life of HP 
compressor stage 1-4 shaft, P/N FK32580, is between 3,080 flight 
cycles and 5,280 flight cycles, then the part must be withdrawn from 
service before exceeding an additional 2,200 flight cycles.
    (iii) On the effective date of this AD, if the life of HP 
compressor stage 1-4 shaft, P/N FK32580, is equal to or below 3,080 
flight cycles, then the part must be withdrawn from service before 
exceeding 5,280 flight cycles.

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 EASA Airworthiness Directive 2008-0099, dated May 
21, 2008 (corrected June 12, 2008), and Rolls-Royce plc Alert 
Service Bulletin No. RB.211-72-AF825, Revision 1, dated September 8, 
2008, for related information. Contact Rolls-Royce plc, PO Box 31, 
Derby, England, DE248BJ; telephone: 011-44-1332-242424; fax: 011-44-
1332-245418, for a copy of this service information.
    (h) Contact James Lawrence, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
james.lawrence@faa.gov; telephone (781) 238-7176; fax (781) 238-
7199, for more information about this AD.

    Issued in Burlington, Massachusetts, on February 10, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-3358 Filed 2-17-09; 8:45 am]
BILLING CODE 4910-13-P