Airworthiness Directives; Rolls-Royce plc RB211 Trent 800 Series Turbofan Engines, 53154-53156 [E9-24855]

Download as PDF 53154 Federal Register / Vol. 74, No. 199 / Friday, October 16, 2009 / Rules and Regulations 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 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 AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (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, Safety. Adoption of the Amendment 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ CPrice-Sewell on DSKDVH8Z91PROD with RULES 2009–21–11 Turbomeca S.A.: Amendment 39–16050. Docket No. FAA–2009–0348; Directorate Identifier 2008–NE–39–AD. Applicability (c) This AD applies to Turbomeca S.A. ARRIUS 1A turboshaft engines with VerDate Nov<24>2008 15:49 Oct 15, 2009 Jkt 220001 14 CFR Part 39 (d) Cycle life limit value for ARRIUS 1A balancing piston Part Number (P/N) 0 319 20 152 0, initially set at 40 000 cycles, has been reduced to 16 000 cycles, following the discovery of a calculation error during a recent review of the ARRIUS 1 engine family files. We are issuing this AD to prevent failure of the balancing piston, which could result in an engine in-flight-shutdown and the release of high-energy debris and damage to the helicopter. [Docket No. FAA–2009–1369; Directorate Identifier 2003–NE–03–AD; Amendment 39– 16048; AD 2009–21–09] Actions and Compliance (e) Unless already done, for ARRIUS 1A engines with a balancing piston, P/N 0 319 20 152 0, installed, remove the engine from service before the balancing piston accumulates 16,000 cycles-since-new (CSN). Installation Prohibition (f) After the effective date of this AD, don’t return to service any engine that has a balancing piston that has accumulated 16,000 or more CSN. FAA AD Differences (g) This AD differs from the Mandatory Continuing Airworthiness Information (MCAI) or service information as follows: (1) This AD requires removing from service, any ARRIUS 1A engine that has a balancing piston, P/N 0 319 20 152 0, with 16,000 CSN installed. (2) We prohibit returning to service any ARRIUS 1A engine that has a balancing piston, P/N 0 319 20 152 0, with 16,000 or more CSN. Related Information ■ Affected Airworthiness Directives (ADs) (b) None. Reason (h) 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. PART 39—AIRWORTHINESS DIRECTIVES Effective Date (a) This airworthiness directive (AD) becomes effective November 20, 2009. DEPARTMENT OF TRANSPORTATION Other FAA AD Provisions Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: ■ § 39.13 balancing pistons, part number (P/N) 0 319 20 152 0, installed. These engines are installed on, but not limited to, Eurocopter AS355N helicopters. (i) Refer to MCAI Airworthiness Directive 2008–0133, dated July 17, 2008 for related information. (j) 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. Material Incorporated by Reference (k) None. Issued in Burlington, Massachusetts, on October 8, 2009. Diane S. Romanosky, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–24853 Filed 10–15–09; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Federal Aviation Administration RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc RB211 Trent 800 Series Turbofan Engines AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce plc RB211 Trent 875–17, Trent 877–17, Trent 884–17, Trent 892– 17, Trent 892B–17, and Trent 895–17 turbofan engines with high-pressure (HP) compressor rotor rear stage 5 and 6 discs and cone shafts, part numbers (P/Ns) FK25230 and FK27899 installed. That AD currently requires removal from service of these HP compressor rotor rear stage 5 and 6 discs and cone shafts before reaching newly reduced life limits. This AD requires removing these parts at new reduced cycle limits. This AD results from Rolls-Royce plc reducing the lives of these parts and changing the life calculating method to use ‘‘Standard Duty Cycles’’ with ‘‘Multiple Flight Profile Monitoring’’ and ‘‘Flight Cycles’’ with ‘‘Heavy Flight Profile Monitoring’’. We are issuing this AD to prevent stage 5 and 6 disc crack initiation and propagation that might lead to uncontained disc failure and damage to the airplane. DATES: This AD becomes effective November 20, 2009. ADDRESSES: You can get the service information identified in this AD from Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, UK, telephone 44 (0) 1332 242424; fax 44 (0) 1332 249936. 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: James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine and 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: The FAA proposed to amend 14 CFR part 39 by E:\FR\FM\16OCR1.SGM 16OCR1 Federal Register / Vol. 74, No. 199 / Friday, October 16, 2009 / Rules and Regulations superseding AD 2003–15–06, Amendment 39–13249 (68 FR 44610, July 30, 2003), with a proposed AD. The proposed AD applies to Rolls-Royce plc RB211 Trent 875–17, Trent 877–17, Trent 884–17, Trent 892–17, Trent 892B–17, and Trent 895–17 turbofan engines with HP compressor rotor rear stage 5 and 6 discs and cone shafts, P/ Ns FK25230 and FK27899 installed. We published the proposed AD in the Federal Register on April 27, 2009 (74 FR 19025). That action proposed to require changing the life calculating method to use ‘‘Standard Duty Cycles’’ with ‘‘Multiple Flight Profile Monitoring’’ and ‘‘Flight Cycles’’ with ‘‘Heavy Flight Profile Monitoring’’, and reducing the lives of the affected parts to 5,000 ‘‘Standard Duty Cycles’’ or ‘‘5,000 Flight cycles’’, respectively. 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 AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. CPrice-Sewell on DSKDVH8Z91PROD with RULES Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. One commenter, Kenya Airways Limited, requests that in the compliance section, we insert ‘‘Rolls-Royce plc Alert Service Bulletin No. RB.211–72–AE082, Revision 7, dated June 18, 2008, pertains to the subject of this AD.’’ We do not agree. That information already exists in paragraph (k) of the AD. We did not change the AD. One commenter, American Airlines, states that the FAA should include a reasonable schedule for operators to manage the replacement of parts with lives already in excess of the proposed reduced limit, to avoid unnecessary and unreasonable hardship once the final rule becomes effective. We do not agree. We have confirmed that all U.S. operators are already operating to the reduced life limit specified in this AD. There are no U.S. operators with parts lives in excess of the reduced limit. We did not change the AD. VerDate Nov<24>2008 15:49 Oct 15, 2009 Jkt 220001 Conclusion We have carefully reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance We estimate that this AD will affect 94 Rolls-Royce plc RB211 Trent 875–17, Trent 877–17, Trent 884–17, Trent 892– 17, Trent 892B–17, and Trent 895–17 turbofan engines installed on airplanes of U.S. registry. Removal of these HP compressor rotor rear stage 5 and 6 discs and cone shafts will not impose any additional labor costs if performed at the time of scheduled engine overhaul. The prorated life loss is about $225,000 per engine. Based on these figures, we estimate the cost of this AD on U.S. operators to be $21,150,000. 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 have 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 that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 53155 on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends 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 removing Amendment 39–13249 (68 FR 44610, July 30, 2003), and by adding a new airworthiness directive, Amendment 39–16048, to read as follows: ■ 2009–21–09 Rolls-Royce plc: Amendment 39–16048. Docket No. FAA–2009–1369; Directorate Identifier 2003–NE–03–AD. Effective Date (a) This airworthiness directive (AD) becomes effective November 20, 2009. Affected ADs (b) This AD supersedes AD 2003–15–06, Amendment 39–13249. Applicability (c) This AD applies to Rolls-Royce plc RB211 Trent 875–17, Trent 877–17, Trent 884–17, Trent 892–17, Trent 892B–17, and Trent 895–17 turbofan engines with highpressure (HP) compressor rotor rear stage 5 and 6 discs and cone shafts, part numbers FK25230 and FK27899 installed. These engines are installed on, but not limited to, Boeing 777 series airplanes. Unsafe Condition (d) This AD results from Rolls-Royce plc reducing the lives of these parts and changing the life calculating method to use ‘‘Standard Duty Cycles’’ with ‘‘Multiple Flight Profile Monitoring’’, and ‘‘Flight Cycles’’ with ‘‘Heavy Flight Profile Monitoring’’. We are issuing this AD to prevent stage 5 and 6 disc crack initiation and propagation that might lead to uncontained disc failure and damage to the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. E:\FR\FM\16OCR1.SGM 16OCR1 53156 Federal Register / Vol. 74, No. 199 / Friday, October 16, 2009 / Rules and Regulations (f) For operators using ‘‘Multiple Flight Profile Monitoring’’ (Flight Profiles ‘‘A’’ through ‘‘F’’), remove HP compressor rotor rear stage 5 and 6 discs and cone shafts from service at or before accumulating 5,000 ‘‘Standard Duty Cycles’’. Guidance on ‘‘Multiple Flight Profile Monitoring’’ can be found in the Aircraft Maintenance Manual, Chapter 70–01–10. (g) For operators using ‘‘Heavy Flight Profile Monitoring’’, remove HP compressor rotor rear stage 5 and 6 discs and cone shafts from service at or before accumulating 5,000 ‘‘Flight Cycles’’. Guidance on ‘‘Heavy Flight Profile Monitoring’’ can be found in the Aircraft Maintenance Manual, Chapter 70– 01–10. Alternative Methods of Compliance (h) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (i) Contact James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803, e-mail james.lawrence@faa.gov; telephone (781) 238–7176; fax (781) 238– 7199, for more information about this AD. (j) European Aviation Safety Agency AD 2007–0004, dated January 8, 2007, also addresses the subject of this AD. (k) Rolls-Royce plc Alert Service Bulletin No. RB.211–72–AE082, Revision 7, dated June 18, 2008, pertains to the subject of this AD. Contact Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, UK, telephone 44 (0) 1332 242424; fax 44 (0) 1332 249936, for a copy of this service information. (l) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124– 2207, for a copy of the Aircraft Maintenance Manual referenced in this AD. Material Incorporated by Reference (m) None. Issued in Burlington, Massachusetts, on October 8, 2009. Diane S. Romanosky, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–24855 Filed 10–15–09; 8:45 am] CPrice-Sewell on DSKDVH8Z91PROD with RULES BILLING CODE 4910–13–P VerDate Nov<24>2008 15:49 Oct 15, 2009 Jkt 220001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Examining the AD Docket [Docket No. FAA–2009–0907; Directorate Identifier 2009–NM–072–AD; Amendment 39–16042; AD 2009–21–05] RIN 2120–AA64 Airworthiness Directives; Airbus Model A340–200 and –300 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated 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: An A340–300 aeroplane experienced the opening of the engine n°3 lower left thrust reverser pivoting door during climb. This event was the result of a primary lock malfunction and non-engagement of the secondary lock. * * * * * Deployment of one thrust reverser door in flight and during the take-off constitutes an unsafe condition. * * * * * Deployment of one thrust reverser door in flight or during take-off could result in reduced controllability of the airplane. This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective November 2, 2009. The Director of the Federal Register approved the incorporation by reference of a certain document listed in the AD as of November 2, 2009. We must receive comments on this AD by November 16, 2009. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://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 PO 00000 Frm 00006 W12–40, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Fmt 4700 Sfmt 4700 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 AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–1138; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2009–0063, dated March 11, 2009, and corrected March 20, 2009 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: An A340–300 aeroplane experienced the opening of the engine n°3 lower left thrust reverser pivoting door during climb. This event was the result of a primary lock malfunction and non-engagement of the secondary lock. Preliminary investigations have revealed two main findings: —The primary lock lever arm of the affected door was contaminated with lubrication fluid, which is a known contributor to incorrect operation; —The actuator of the deployed door was found with 3 shim sets installed whereas the system is designed for a maximum of one shim set. It is considered that installation of three shim sets has a detrimental effect on the secondary lock capacity to engage in case of primary lock failure. Deployment of one thrust reverser door in flight and during the take-off constitutes an unsafe condition. In order to ensure that the fleet is clear from unauthorized actuator shimming configurations which may lead to nonengagement of the secondary lock, EASA AD 2008–0074 required a one-time visual inspection to check that no more than one shim set per pivoting door actuator was installed. E:\FR\FM\16OCR1.SGM 16OCR1

Agencies

[Federal Register Volume 74, Number 199 (Friday, October 16, 2009)]
[Rules and Regulations]
[Pages 53154-53156]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-24855]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-1369; Directorate Identifier 2003-NE-03-AD; 
Amendment 39-16048; AD 2009-21-09]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB211 Trent 800 Series 
Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for Rolls-Royce plc RB211 Trent 875-17, Trent 877-17, Trent 884-
17, Trent 892-17, Trent 892B-17, and Trent 895-17 turbofan engines with 
high-pressure (HP) compressor rotor rear stage 5 and 6 discs and cone 
shafts, part numbers (P/Ns) FK25230 and FK27899 installed. That AD 
currently requires removal from service of these HP compressor rotor 
rear stage 5 and 6 discs and cone shafts before reaching newly reduced 
life limits. This AD requires removing these parts at new reduced cycle 
limits. This AD results from Rolls-Royce plc reducing the lives of 
these parts and changing the life calculating method to use ``Standard 
Duty Cycles'' with ``Multiple Flight Profile Monitoring'' and ``Flight 
Cycles'' with ``Heavy Flight Profile Monitoring''. We are issuing this 
AD to prevent stage 5 and 6 disc crack initiation and propagation that 
might lead to uncontained disc failure and damage to the airplane.

DATES: This AD becomes effective November 20, 2009.

ADDRESSES: You can get the service information identified in this AD 
from Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, UK, telephone 44 
(0) 1332 242424; fax 44 (0) 1332 249936.
    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: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and 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: The FAA proposed to amend 14 CFR part 39 by

[[Page 53155]]

superseding AD 2003-15-06, Amendment 39-13249 (68 FR 44610, July 30, 
2003), with a proposed AD. The proposed AD applies to Rolls-Royce plc 
RB211 Trent 875-17, Trent 877-17, Trent 884-17, Trent 892-17, Trent 
892B-17, and Trent 895-17 turbofan engines with HP compressor rotor 
rear stage 5 and 6 discs and cone shafts, P/Ns FK25230 and FK27899 
installed. We published the proposed AD in the Federal Register on 
April 27, 2009 (74 FR 19025). That action proposed to require changing 
the life calculating method to use ``Standard Duty Cycles'' with 
``Multiple Flight Profile Monitoring'' and ``Flight Cycles'' with 
``Heavy Flight Profile Monitoring'', and reducing the lives of the 
affected parts to 5,000 ``Standard Duty Cycles'' or ``5,000 Flight 
cycles'', respectively.

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 AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is provided in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received.
    One commenter, Kenya Airways Limited, requests that in the 
compliance section, we insert ``Rolls-Royce plc Alert Service Bulletin 
No. RB.211-72-AE082, Revision 7, dated June 18, 2008, pertains to the 
subject of this AD.''
    We do not agree. That information already exists in paragraph (k) 
of the AD. We did not change the AD.
    One commenter, American Airlines, states that the FAA should 
include a reasonable schedule for operators to manage the replacement 
of parts with lives already in excess of the proposed reduced limit, to 
avoid unnecessary and unreasonable hardship once the final rule becomes 
effective.
    We do not agree. We have confirmed that all U.S. operators are 
already operating to the reduced life limit specified in this AD. There 
are no U.S. operators with parts lives in excess of the reduced limit. 
We did not change the AD.

Conclusion

    We have carefully reviewed the available data, including the 
comments received, and determined that air safety and the public 
interest require adopting the AD as proposed.

Costs of Compliance

    We estimate that this AD will affect 94 Rolls-Royce plc RB211 Trent 
875-17, Trent 877-17, Trent 884-17, Trent 892-17, Trent 892B-17, and 
Trent 895-17 turbofan engines installed on airplanes of U.S. registry. 
Removal of these HP compressor rotor rear stage 5 and 6 discs and cone 
shafts will not impose any additional labor costs if performed at the 
time of scheduled engine overhaul. The prorated life loss is about 
$225,000 per engine. Based on these figures, we estimate the cost of 
this AD on U.S. operators to be $21,150,000. 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 have 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 that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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 summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary at the 
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration 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 removing Amendment 39-13249 (68 FR 
44610, July 30, 2003), and by adding a new airworthiness directive, 
Amendment 39-16048, to read as follows:

2009-21-09 Rolls-Royce plc: Amendment 39-16048. Docket No. FAA-2009-
1369; Directorate Identifier 2003-NE-03-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November 
20, 2009.

Affected ADs

    (b) This AD supersedes AD 2003-15-06, Amendment 39-13249.

Applicability

    (c) This AD applies to Rolls-Royce plc RB211 Trent 875-17, Trent 
877-17, Trent 884-17, Trent 892-17, Trent 892B-17, and Trent 895-17 
turbofan engines with high-pressure (HP) compressor rotor rear stage 
5 and 6 discs and cone shafts, part numbers FK25230 and FK27899 
installed. These engines are installed on, but not limited to, 
Boeing 777 series airplanes.

Unsafe Condition

    (d) This AD results from Rolls-Royce plc reducing the lives of 
these parts and changing the life calculating method to use 
``Standard Duty Cycles'' with ``Multiple Flight Profile 
Monitoring'', and ``Flight Cycles'' with ``Heavy Flight Profile 
Monitoring''. We are issuing this AD to prevent stage 5 and 6 disc 
crack initiation and propagation that might lead to uncontained disc 
failure and damage to the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.

[[Page 53156]]

    (f) For operators using ``Multiple Flight Profile Monitoring'' 
(Flight Profiles ``A'' through ``F''), remove HP compressor rotor 
rear stage 5 and 6 discs and cone shafts from service at or before 
accumulating 5,000 ``Standard Duty Cycles''. Guidance on ``Multiple 
Flight Profile Monitoring'' can be found in the Aircraft Maintenance 
Manual, Chapter 70-01-10.
    (g) For operators using ``Heavy Flight Profile Monitoring'', 
remove HP compressor rotor rear stage 5 and 6 discs and cone shafts 
from service at or before accumulating 5,000 ``Flight Cycles''. 
Guidance on ``Heavy Flight Profile Monitoring'' can be found in the 
Aircraft Maintenance Manual, Chapter 70-01-10.

Alternative Methods of Compliance

    (h) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD if 
requested using the procedures found in 14 CFR 39.19.

Related Information

    (i) Contact James Lawrence, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803, e-mail 
james.lawrence@faa.gov; telephone (781) 238-7176; fax (781) 238-
7199, for more information about this AD.
    (j) European Aviation Safety Agency AD 2007-0004, dated January 
8, 2007, also addresses the subject of this AD.
    (k) Rolls-Royce plc Alert Service Bulletin No. RB.211-72-AE082, 
Revision 7, dated June 18, 2008, pertains to the subject of this AD. 
Contact Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, UK, telephone 
44 (0) 1332 242424; fax 44 (0) 1332 249936, for a copy of this 
service information.
    (l) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for a copy of the Aircraft Maintenance Manual 
referenced in this AD.

Material Incorporated by Reference

    (m) None.

    Issued in Burlington, Massachusetts, on October 8, 2009.
Diane S. Romanosky,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-24855 Filed 10-15-09; 8:45 am]
BILLING CODE 4910-13-P