Airworthiness Directives; Rolls-Royce plc RB211 Trent 800 Series Turbofan Engines, 19025-19027 [E9-9479]

Download as PDF Federal Register / Vol. 74, No. 79 / Monday, April 27, 2009 / Proposed Rules 11. Braked Roll Conditions. The criteria of §§ 25.493(b), (c), and (d) shall be directly applicable. The formula in § 25.493(e) is not applicable to the B747 due to the 4-post gear arrangement. 12. Turning. The criteria of § 25.495 are directly applicable. 13. Nose-Wheel Yaw. The criteria of § 25.499 are directly applicable. The criteria are interpreted to apply braking to all main landing gear wheels on one side of the airplane centerline. 14. Pivoting. The criteria of § 25.503 are applied individually to each wing main landing gear unit. In addition, all main landing gear units must be designed for the scrubbing and/or torsion loads induced by pivoting about the most critical point consistent with the available main gear braking on one side of the airplane and the available thrust and torque on the airplane. Maximum static engine thrust must be considered only on the engines on the opposite side of the airplane centerline from the pivot point. 15. Reversed Braking. The criteria of § 25.507 are directly applicable, except that the phrase ‘‘three point’’ is expanded to include ‘‘five point.’’ 16. Towing Loads. The criteria of § 25.509 are directly applicable. 17. Fatigue Evaluation of Landing Gear. The criteria of § 25.573 at Amendment 25–0 are directly applicable to main landing gear units. 18. Shock Absorption Tests. The criteria of § 25.723 are directly applicable. Compliance may be shown in accordance with AC 25.723–1. 19. Substantiation of the design criteria must include a dynamic taxi and landing analysis. ACTION: Notice of proposed rulemaking (NPRM). Federal Aviation Administration SUMMARY: The FAA proposes to supersede 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. This proposed AD would require removing these parts at new reduced cycle limits. This proposed AD results from RollsRoyce 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 proposing 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: We must receive any comments on this proposed AD by June 26, 2009. ADDRESSES: Use one of the following addresses to comment on this proposed AD. • 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. 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: 14 CFR Part 39 Comments Invited Issued in Renton, Washington, on April 14, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–9529 Filed 4–24–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION dwashington3 on PROD1PC60 with PROPOSALS [Docket No. FAA–2009–1369; Directorate Identifier 2003–NE–03–AD] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc RB211 Trent 800 Series Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. VerDate Nov<24>2008 14:06 Apr 24, 2009 Jkt 217001 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–2009–1369; Directorate Identifier 2003–NE–03–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 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 19025 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). 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 the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. Discussion On July 23, 2003, we issued AD 2003– 15–06, Amendment 39–13249 (68 FR 44610, July 30, 2003). That AD requires removal from service of HP compressor rotor rear stage 5 and 6 discs and cone shafts, P/Ns FK25230 and FK27899, before reaching newly reduced life limits. The Civil Aviation Authority (CAA), which is the airworthiness authority for the United Kingdom (U.K.), had notified the FAA that an unsafe condition may exist on RollsRoyce plc RB211 Trent 875, Trent 877, Trent 884, Trent 892, Trent 892B, and Trent 895 turbofan engines. The CAA advised that three HP compressor rotor rear stage 5 and 6 discs and cone shafts, P/Ns FK25230 and FK27899, were found with crack indications in the stage 5 and 6 blade loading slots, during overhaul inspection. The manufacturer’s analysis had not yet been able to identify the root cause of these cracks, or to fully explain the crack propagation rate. As a result of the analysis, a new lower life limit of 7,500 cycles-sincenew had been assigned by the manufacturer to these HP compressor rotor rear stage 5 and 6 discs and cone shafts. This condition, if not corrected, E:\FR\FM\27APP1.SGM 27APP1 19026 Federal Register / Vol. 74, No. 79 / Monday, April 27, 2009 / Proposed Rules could result in stage 5 and 6 disc crack initiation and propagation that might lead to uncontained disc failure and damage to the airplane. Actions Since AD 2003–15–06 Was Issued Since AD 2003–15–06 was issued, Rolls-Royce plc has further reduced the lives of HP compressor rotor rear stage 5 and 6 discs and cone shafts, P/Ns FK25230 and FK27899, and changed the life calculating method to use ‘‘Standard Duty Cycles’’ with ‘‘Multiple Flight Profile Monitoring’’ and ‘‘Flight Cycles’’ with ‘‘Heavy Flight Profile Monitoring’’. Bilateral Agreement Information This engine model is manufactured in the United Kingdom and is type certificated for operation in the United States under the provisions of Section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Under this bilateral airworthiness agreement, the European Aviation Safety Agency (EASA) kept us informed of the situation described above. We have examined the findings of EASA, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States. FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other products of this same type design. We are proposing this AD, which would 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. dwashington3 on PROD1PC60 with PROPOSALS Costs of Compliance We estimate that this proposed AD would 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 would 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 proposed AD on U.S. operators to be $21,150,000. VerDate Nov<24>2008 14:06 Apr 24, 2009 Jkt 217001 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 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 that the proposed 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. Would 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. See the ADDRESSES section for a location to examine the regulatory evaluation. 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 Federal Aviation Administration 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: PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 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, to read as follows: Rolls-Royce plc: Docket No. FAA–2009– 1369; Directorate Identifier 2003–NE– 03–AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by June 26, 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 (P/ Ns) 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. (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’’. Information 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’’. Information 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. E:\FR\FM\27APP1.SGM 27APP1 Federal Register / Vol. 74, No. 79 / Monday, April 27, 2009 / Proposed Rules 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. [Docket No. FAA–2009–0380; Directorate Identifier 2008–NM–153–AD] The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by May 27, 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 W12–40, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Dassault Falcon Jet, P.O. Box 2000, South Hackensack, New Jersey 07606; telephone 201–440–6700; Internet https://www.dassaultfalcon.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227– 1221 or 425–227–1152. RIN 2120–AA64 Examining the AD Docket Issued in Burlington, Massachusetts, on April 17, 2009. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–9479 Filed 4–24–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Airworthiness Directives; Dassault Model Falcon 2000EX Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). dwashington3 on PROD1PC60 with PROPOSALS 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) 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 internal review of design data has shown that the web of the left hand side (LH) stringer 13 near frame 8 might have been improperly trimmed on a few aircraft. If not corrected, possible crack initiations could occur in the upper stringer web, and therefore could impair the structural strength of the adjacent door stop. This latent failure could ultimately lead to the loss of redundancy of the door stops, thereby affecting the structural integrity of the fuselage. * * * VerDate Nov<24>2008 * * 14:06 Apr 24, 2009 Jkt 217001 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 in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: 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. SUPPLEMENTARY INFORMATION: 19027 2008–NM–153–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 we receive about this proposed AD. 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 2008–0143, dated July 31, 2008 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: An internal review of design data has shown that the web of the left hand side (LH) stringer 13 near frame 8 might have been improperly trimmed on a few aircraft. If not corrected, possible crack initiations could occur in the upper stringer web, and therefore could impair the structural strength of the adjacent door stop. This latent failure could ultimately lead to the loss of redundancy of the door stops, thereby affecting the structural integrity of the fuselage. Computational analysis has revealed a substantial reduced fatigue life for the stringer abutting onto the improperly trimmed web and has determined the need for an inspection and repair action no later than the first ‘‘C’’ check. To address this unsafe condition, the present Airworthiness Directive (AD) mandates an inspection and a conditional rework or replacement of the web of the LH stringer 13 between frames 7 and 8. Required actions include measuring the trimmed length of the web, inspecting for any sharp and unprotected edges of the web, and doing corrective actions if necessary. Corrective actions include reworking the web, applying protection to the web, and replacing the web, if improperly trimmed. You may obtain further information by examining the MCAI in the AD docket. Comments Invited Relevant Service Information 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–2009–0380; Directorate Identifier Dassault has issued Mandatory Service Bulletin F2000EX–178, dated July 1, 2008. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 E:\FR\FM\27APP1.SGM 27APP1

Agencies

[Federal Register Volume 74, Number 79 (Monday, April 27, 2009)]
[Proposed Rules]
[Pages 19025-19027]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-9479]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-1369; Directorate Identifier 2003-NE-03-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: The FAA proposes to supersede 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. This proposed AD would require removing these parts at new
reduced cycle limits. This proposed 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 proposing 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: We must receive any comments on this proposed AD by June 26,
2009.

ADDRESSES: Use one of the following addresses to comment on this
proposed AD.
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.

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:

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-2009-1369;
Directorate Identifier 2003-NE-03-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).

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 the same as
the Mail address provided in the ADDRESSES section. Comments will be
available in the AD docket shortly after receipt.

Discussion

On July 23, 2003, we issued AD 2003-15-06, Amendment 39-13249 (68
FR 44610, July 30, 2003). That AD requires removal from service of HP
compressor rotor rear stage 5 and 6 discs and cone shafts, P/Ns FK25230
and FK27899, before reaching newly reduced life limits. The Civil
Aviation Authority (CAA), which is the airworthiness authority for the
United Kingdom (U.K.), had notified the FAA that an unsafe condition
may exist on Rolls-Royce plc RB211 Trent 875, Trent 877, Trent 884,
Trent 892, Trent 892B, and Trent 895 turbofan engines. The CAA advised
that three HP compressor rotor rear stage 5 and 6 discs and cone
shafts, P/Ns FK25230 and FK27899, were found with crack indications in
the stage 5 and 6 blade loading slots, during overhaul inspection. The
manufacturer's analysis had not yet been able to identify the root
cause of these cracks, or to fully explain the crack propagation rate.
As a result of the analysis, a new lower life limit of 7,500 cycles-
since-new had been assigned by the manufacturer to these HP compressor
rotor rear stage 5 and 6 discs and cone shafts. This condition, if not
corrected,

[[Page 19026]]

could result in stage 5 and 6 disc crack initiation and propagation
that might lead to uncontained disc failure and damage to the airplane.

Actions Since AD 2003-15-06 Was Issued

Since AD 2003-15-06 was issued, Rolls-Royce plc has further reduced
the lives of HP compressor rotor rear stage 5 and 6 discs and cone
shafts, P/Ns FK25230 and FK27899, and changed the life calculating
method to use ``Standard Duty Cycles'' with ``Multiple Flight Profile
Monitoring'' and ``Flight Cycles'' with ``Heavy Flight Profile
Monitoring''.

Bilateral Agreement Information

This engine model is manufactured in the United Kingdom and is type
certificated for operation in the United States under the provisions of
Section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Under this bilateral
airworthiness agreement, the European Aviation Safety Agency (EASA)
kept us informed of the situation described above. We have examined the
findings of EASA, reviewed all available information, and determined
that AD action is necessary for products of this type design that are
certificated for operation in the United States.

FAA's Determination and Requirements of the Proposed AD

We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. We are proposing this AD, which would 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.

Costs of Compliance

We estimate that this proposed AD would 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 would 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 proposed AD on U.S. operators to be $21,150,000.

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 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 that the proposed 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. Would 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. See the ADDRESSES section for a location
to examine the regulatory evaluation.

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 Federal Aviation Administration 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 removing Amendment 39-13249 (68 FR
44610, July 30, 2003) and by adding a new airworthiness directive, to
read as follows:

Rolls-Royce plc: Docket No. FAA-2009-1369; Directorate Identifier
2003-NE-03-AD.

Comments Due Date

(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by June 26,
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 (P/Ns) 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.
(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''. Information 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''.
Information 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.

[[Page 19027]]

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.

Issued in Burlington, Massachusetts, on April 17, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E9-9479 Filed 4-24-09; 8:45 am]
BILLING CODE 4910-13-P

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