Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG, BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 Turbofan Engines, 7643-7645 [E9-3355]

Download as PDF Federal Register / Vol. 74, No. 32 / Thursday, February 19, 2009 / Rules and Regulations approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Pong Lee, Aerospace Engineer, FAA, New York Aircraft Certification Office, ANE–171, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone: (516) 228–7324; fax: (516) 794–5531. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAAapproved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. yshivers on PROD1PC62 with RULES Related Information (h) Refer to MCAI Transport Canada AD No. CF–2007–31, dated December 17, 2007; Viking DHC–6 Twin Otter Service Bulletins No. V6/540, dated October 1, 2007; No. V6/ 541, dated October 1, 2007; and No. V6/542, dated October 1, 2007; and R.W. Martin, Inc. Service Bulletin No. 00160/2, Revision A, dated November 15, 2007, for related information. Material Incorporated by Reference (i) You must use Viking DHC–6 Twin Otter Service Bulletins No. V6/540, dated October 1, 2007; No. V6/541, dated October 1, 2007; and No. V6/542, dated October 1, 2007; and R.W. Martin, Inc. Service Bulletin No. 00160/ 2, Revision A, dated November 15, 2007, to do the actions required by this AD, unless the AD specifies otherwise. (1) On August 5, 2008 (73 FR 37353, July 1, 2008), the Director of the Federal Register previously approved the incorporation by reference of Viking DHC–6 Twin Otter Service Bulletins No. V6/540, dated October 1, 2007; No. V6/541, dated October 1, 2007; and No. V6/542, dated October 1, 2007; and R.W. Martin, Inc. Service Bulletin No. 00160/ 2, Revision A, dated November 15, 2007. (2) For service information identified in this AD, contact Viking Air Limited, 9574 Hampden Road, Sidney, B.C., Canada V8L 5V5; telephone: (250) 656–7227; fax: (250) 656–0673; Internet: http:// www.vikingair.com; or R.W. Martin, Inc., 37552 Winchester Road, Hangar 20, Murrieta, California 92563; telephone: (951) 600–0009; fax: (951) 600–1005; Internet: http:// www.rwmi.net. (3) You may review copies of the service information incorporated by reference for this AD at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the Central Region, call (816) 329–3768. VerDate Nov<24>2008 14:28 Feb 18, 2009 Jkt 217001 (4) You may also review copies of the service information incorporated by reference for this AD at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: http://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Kansas City, Missouri, on February 6, 2009. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–3115 Filed 2–18–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0169; Directorate Identifier 2007–NE–45–AD; Amendment 39– 15819; AD 2009–04–13] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG, BR700– 715A1–30, BR700–715B1–30, and BR700–715C1–30 Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: The application of most recent 3D FEM modeling has resulted in the need to reconsider the disc lives as currently shown in the Time Limits Manual. The current Post Certification Life Statement for the low pressure (LP) compressor (fan) disc assembly revises the Declared Safe Cyclic Life (DSCL) from 33,000 flight cycles to 25,000 flight cycles for both the BR715 LP (fan) disc assembly Part No. (P/N) BRH10048 and BR715 LP compressor (fan) disc assembly P/N BRH19253, when installed in the BR700–715A1–30 engine model and operated against the Hawaiian Flight Mission. We are issuing this AD to prevent uncontained failure of the LP compressor (fan) disc assembly and damage to the airplane. DATES: This AD becomes effective March 26, 2009. ADDRESSES: The Docket Operations office is located at Docket Management PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 7643 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: Jason Yang, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: Jason.yang@faa.gov; telephone (781) 238–7747; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on February 5, 2008 (73 FR 6638). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states that: The application of most recent 3D FEM modeling has resulted in the need to reconsider the disc lives as currently shown in the Time Limits Manual. The current Post Certification Life Statement for the low pressure (LP) compressor (fan) disc assembly revises the Declared Safe Cyclic Life (DSCL) from 33,000 flight cycles to 25,000 flight cycles for both the BR715 LP (fan) disc assembly P/N BRH10048 and BR715 LP compressor (fan) disc assembly P/N BRH19253, when installed in the BR700– 715A1–30 engine model and operated against the Hawaiian Flight Mission. This AD requires, within 25 flight cycles after the effective date of the AD: • Amending the Airworthiness Limitations Section (ALS) of the Time Limits Manual SUBTASK 05–10–01– 860–016, by revising the ‘‘GIVEN LIFE A1–30 RATING (FLIGHT CYCLES)’’ for both the LP compressor (fan) disc assembly P/N BRH10048 and LP compressor (fan) disc assembly P/N BRH19253 from 33,000 flight cycles to 25,000 flight cycles; and • Checking the lifing of both the LP compressor (fan) disc assembly P/N BRH10048 and LP compressor (fan) disc assembly P/N BRH19253 if the relevant compressor (fan) disc assembly is currently installed or was previously installed, in the BR700–715A1–30 engine model and operated under the Hawaiian Flight Mission; and • Removing the relevant compressor (fan) disc assembly from service before further flight, if the consumed life has exceeded the maximum approved life specified in the ALS. Comments We gave the public the opportunity to participate in developing this AD. We considered the comments received. E:\FR\FM\19FER1.SGM 19FER1 7644 Federal Register / Vol. 74, No. 32 / Thursday, February 19, 2009 / Rules and Regulations Conclusion Request To Change the AD Applicability Rolls-Royce Deutschland requests that we change the AD applicability from ‘‘This AD applies to Rolls-Royce Deutschland Ltd & Co KG (RRD), BR700–715A1–30, BR700–715B1–30, and BR700–715C1–30 turbofan engines, with a low pressure (LP) compressor disc assembly, part number (P/N) BRH10048 or P/N BRH19253, when installed in the BR700–715A1–30 engine model and operated against the Hawaiian Flight Mission’’ to ‘‘This AD applies to Rolls-Royce Deutschland Ltd & Co KG (RRD), BR700–715A1–30, BR700–715B1–30, and BR700–715C1– 30 turbofan engines, with a low pressure (LP) compressor disc assembly, P/N BRH10048 or P/N BRH19253’’. The commenter states that due to fan module mixing between engine models, the AD is applicable to all relevant fan assemblies that have, are, could, or will operate against the Hawaiian Flight Mission, when installed in the BR710– 715A1–30 engine. We agree, and changed the AD applicability. Request To Combine the Compliance Requirements Rolls-Royce Deutschland requests that the AD require the operators check the lifing of the LP compressor disc assemblies, P/N BRH10048 and P/N BRH19253, using the amended Time Limits Manual (TLM), whether currently installed or previously installed in the BR700–715A1–30 engine, and operated under the Hawaiian Flight mission. We partially agree. Operators are responsible for following the applicable ALS of the TLM to ensure that all critical rotating parts are replaced within the life limitations specified in the Manual. However, for clarification purposes, we included this action in the AD. yshivers on PROD1PC62 with RULES Other AD Changes We determined the AD must be complied with, within 25 flight cycles after the effective date of the AD, instead of 100 flight cycles after the effective date, as proposed, to expeditiously amend the ALS of the TLM with life reduction of the relevant fan disk assembly. We also require removing fan disk assemblies from service before the next flight if their consumed life has exceeded the maximum approved life as specified in the ALS of the TLM. All life limited part must be removed from service before reaching its declared life in the ALS. VerDate Nov<24>2008 14:28 Feb 18, 2009 Jkt 217001 We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. Costs of Compliance We estimate that this AD will affect about 240 engines installed on aircraft of U.S. registry. This LP compressor (fan) disc assembly removal does not impose any additional labor costs if performed at the time of scheduled engine overhaul. We also estimate that it will take about one work-hour per engine to calculate and re-establish the achieved cyclic life for an LP compressor (fan) disc assembly, and that the average labor rate is $80 per workhour. We estimate that the prorate cost of the life reduction per engine will be $33,000. Total cost of this AD is, therefore, $7,939,200. 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 AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (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 Accordingly, under the authority delegated to me by the Administrator, the FAA 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 adding the following new AD: ■ 2009–04–13 Rolls-Royce Deutschland Ltd & Co KG (formerly BMW Rolls-Royce GmbH, and BMW Rolls-Royce Aero Engines): Amendment 39–15819. Docket No. FAA–2007–0169; Directorate Identifier 2007–NE–45–AD. Effective Date (a) This airworthiness directive (AD) becomes effective March 26, 2009. Affected ADs (b) None. Applicability (c) This AD applies to Rolls-Royce Deutschland Ltd & Co KG (RRD), BR700– 715A1–30, BR700–715B1–30, and BR700– 715C1–30 turbofan engines, with a low pressure (LP) compressor (fan) disc assembly, part number (P/N) BRH10048 or P/N BRH19253. These engines are installed on, but not limited to, McDonnell Douglas Corporation model 717–200 airplanes. E:\FR\FM\19FER1.SGM 19FER1 Federal Register / Vol. 74, No. 32 / Thursday, February 19, 2009 / Rules and Regulations Reason DEPARTMENT OF TRANSPORTATION (d) The mandatory continuous airworthiness information (MCAI) states: The application of most recent 3D FEM modeling has resulted in the need to reconsider the disc lives as currently shown in the Time Limits Manual. The current Post Certification Life Statement for the low pressure (LP) compressor (fan) disc assembly revises the Declared Safe Cyclic Life (DSCL) from 33,000 flight cycles to 25,000 flight cycles for both the BR715 LP (fan) disc assembly P/N BRH10048 and BR715 LP compressor (fan) disc assembly P/N BRH19253, when installed in the BR700– 715A1–30 engine model and operated against the Hawaiian Flight Mission. This condition, if not corrected, could result in uncontained failure of the LP compressor (fan) disc assembly and damage to the airplane. Actions and Compliance (e) Within 25 flight cycles after the effective date of this AD, do the following actions, unless already done. (1) Amend the Airworthiness Limitations Section (ALS) of the Time Limits Manual SUBTASK 05–10–01–860–016, by revising the ‘‘GIVEN LIFE A1–30 RATING (FLIGHT CYCLES)’’ for both the LP compressor (fan) disc assembly P/N BRH10048 and LP compressor (fan) disc assembly P/N BRH19253 from 33,000 flight cycles to 25,000 flight cycles. (2) Check the lifing of both the LP compressor (fan) disc assembly P/N BRH10048 and LP compressor (fan) disc assembly P/N BRH19253 if the relevant compressor (fan) disc assembly is currently installed or was previously installed, in the BR700–715A1–30 engine model and operated under the Hawaiian Flight Mission. (3) Remove the relevant compressor (fan) disc assembly from service before further flight, if the consumed life has exceeded the maximum approved life specified in the ALS. Alternative Methods of Compliance (AMOC) (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 yshivers on PROD1PC62 with RULES (g) Refer to MCAI European Aviation Safety Agency AD 2007–0116–E, dated May 4, 2007, for related information. (h) Contact Jason Yang, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: Jason.yang@faa.gov; telephone (781) 238–7747; 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. E9–3355 Filed 2–18–09; 8:45 am] BILLING CODE 4910–13–P VerDate Nov<24>2008 14:28 Feb 18, 2009 Jkt 217001 Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2008–1102; Airspace Docket No. 08–AGL–8] Establishment of Class D Airspace; Branson, MO AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: This action establishes Class D airspace at Branson Airport, Branson, MO. The establishment of an air traffic control tower has made this action necessary for the safety of Instrument Flight Rule (IFR) operations at the airport. DATES: Effective Date: 0901 UTC, May 7, 2009. The Director of the Federal Register approves this incorporation by reference action under 1 CFR part 51, subject to the annual revision of FAA Order 7400.9 and publication of conforming amendments. FOR FURTHER INFORMATION CONTACT: Scott Enander, Central Service Center, Operations Support Group, Federal Aviation Administration, Southwest Region, 2601 Meacham Blvd., Ft. Worth, TX 76193–0530; telephone (817) 321– 7716. SUPPLEMENTARY INFORMATION: History On November 20, 2008, the FAA published in the Federal Register a notice of proposed rulemaking to establish Class D airspace at Branson, MO (73 FR 70287, Docket No. FAA– 2008–1102). Interested parties were invited to participate in this rulemaking effort by submitting written comments on the proposal to the FAA. No comments were received. Class D airspace designations are published in paragraph 5000 of FAA Order 7400.9S signed October 3, 2008, and effective October 31, 2008, which is incorporated by reference in 14 CFR 71.1. The Class D airspace designations listed in this document will be published subsequently in that Order. The Rule This action amends Title 14 Code of Federal Regulations (14 CFR) Part 71 by establishing Class D airspace for IFR operations at Branson Airport, Branson, MO, where a new control tower has been installed. The Class D airspace will revert to a Class E surface area during those periods when the control tower is not operating. This area would be PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 7645 depicted on appropriate aeronautical charts. The FAA has determined that this regulation only involves an established body of technical regulations for which frequent and routine amendments are necessary to keep them operationally current. Therefore, this regulation: (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) does not warrant preparation of a regulatory evaluation as the anticipated impact is so minimal. Since this is a routine matter that will only affect air traffic procedures and air navigation, it is certified that this rule, when promulgated, will not have a significant economic impact on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. The FAA’s authority to issue rules regarding aviation safety is found in Title 49 of the U.S. Code. Subtitle 1, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the agency’s authority. This rulemaking is promulgated under the authority described in Subtitle VII, Part A, Subpart I, Section 40103. Under that section, the FAA is charged with prescribing regulations to assign the use of airspace necessary to ensure the safety of aircraft and the efficient use of airspace. This regulation is within the scope of that authority as it establishes controlled airspace at Branson Airport, Branson, MO. List of Subjects in 14 CFR Part 71 Airspace, Incorporation by reference, Navigation (air). Adoption of the Amendment In consideration of the foregoing, the Federal Aviation Administration amends 14 CFR part 71 as follows: ■ PART 71—DESIGNATION OF CLASS A, B, C, D, AND E AIRSPACE AREAS; AIR TRAFFIC SERVICE ROUTES; AND REPORTING POINTS 1. The authority citation for 14 CFR part 71 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40103, 40113, 40120; E. O. 10854, 24 FR 9565, 3 CFR, 1959– 1963 Comp., p. 389. § 71.1 [Amended] 2. The incorporation by reference in 14 CFR 71.1 of the Federal Aviation Administration Order 7400.9S, Airspace Designations and Reporting Points, signed October 3, 2008, and effective ■ E:\FR\FM\19FER1.SGM 19FER1

Agencies

[Federal Register Volume 74, Number 32 (Thursday, February 19, 2009)]
[Rules and Regulations]
[Pages 7643-7645]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-3355]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0169; Directorate Identifier 2007-NE-45-AD; 
Amendment 39-15819; AD 2009-04-13]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG, 
BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD results from mandatory continuing 
airworthiness information (MCAI) issued by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    The application of most recent 3D FEM modeling has resulted in 
the need to reconsider the disc lives as currently shown in the Time 
Limits Manual. The current Post Certification Life Statement for the 
low pressure (LP) compressor (fan) disc assembly revises the 
Declared Safe Cyclic Life (DSCL) from 33,000 flight cycles to 25,000 
flight cycles for both the BR715 LP (fan) disc assembly Part No. (P/
N) BRH10048 and BR715 LP compressor (fan) disc assembly P/N 
BRH19253, when installed in the BR700-715A1-30 engine model and 
operated against the Hawaiian Flight Mission.

We are issuing this AD to prevent uncontained failure of the LP 
compressor (fan) disc assembly and damage to the airplane.

DATES: This AD becomes effective March 26, 2009.

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

FOR FURTHER INFORMATION CONTACT: Jason Yang, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
Jason.yang@faa.gov; telephone (781) 238-7747; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on February 5, 2008 (73 
FR 6638). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states that:

    The application of most recent 3D FEM modeling has resulted in 
the need to reconsider the disc lives as currently shown in the Time 
Limits Manual. The current Post Certification Life Statement for the 
low pressure (LP) compressor (fan) disc assembly revises the 
Declared Safe Cyclic Life (DSCL) from 33,000 flight cycles to 25,000 
flight cycles for both the BR715 LP (fan) disc assembly P/N BRH10048 
and BR715 LP compressor (fan) disc assembly P/N BRH19253, when 
installed in the BR700-715A1-30 engine model and operated against 
the Hawaiian Flight Mission.

    This AD requires, within 25 flight cycles after the effective date 
of the AD:
     Amending the Airworthiness Limitations Section (ALS) of 
the Time Limits Manual SUBTASK 05-10-01-860-016, by revising the 
``GIVEN LIFE A1-30 RATING (FLIGHT CYCLES)'' for both the LP compressor 
(fan) disc assembly P/N BRH10048 and LP compressor (fan) disc assembly 
P/N BRH19253 from 33,000 flight cycles to 25,000 flight cycles; and
     Checking the lifing of both the LP compressor (fan) disc 
assembly P/N BRH10048 and LP compressor (fan) disc assembly P/N 
BRH19253 if the relevant compressor (fan) disc assembly is currently 
installed or was previously installed, in the BR700-715A1-30 engine 
model and operated under the Hawaiian Flight Mission; and
     Removing the relevant compressor (fan) disc assembly from 
service before further flight, if the consumed life has exceeded the 
maximum approved life specified in the ALS.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received.

[[Page 7644]]

Request To Change the AD Applicability

    Rolls-Royce Deutschland requests that we change the AD 
applicability from ``This AD applies to Rolls-Royce Deutschland Ltd & 
Co KG (RRD), BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 
turbofan engines, with a low pressure (LP) compressor disc assembly, 
part number (P/N) BRH10048 or P/N BRH19253, when installed in the 
BR700-715A1-30 engine model and operated against the Hawaiian Flight 
Mission'' to ``This AD applies to Rolls-Royce Deutschland Ltd & Co KG 
(RRD), BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 turbofan 
engines, with a low pressure (LP) compressor disc assembly, P/N 
BRH10048 or P/N BRH19253''. The commenter states that due to fan module 
mixing between engine models, the AD is applicable to all relevant fan 
assemblies that have, are, could, or will operate against the Hawaiian 
Flight Mission, when installed in the BR710-715A1-30 engine.
    We agree, and changed the AD applicability.

Request To Combine the Compliance Requirements

    Rolls-Royce Deutschland requests that the AD require the operators 
check the lifing of the LP compressor disc assemblies, P/N BRH10048 and 
P/N BRH19253, using the amended Time Limits Manual (TLM), whether 
currently installed or previously installed in the BR700-715A1-30 
engine, and operated under the Hawaiian Flight mission.
    We partially agree. Operators are responsible for following the 
applicable ALS of the TLM to ensure that all critical rotating parts 
are replaced within the life limitations specified in the Manual. 
However, for clarification purposes, we included this action in the AD.

Other AD Changes

    We determined the AD must be complied with, within 25 flight cycles 
after the effective date of the AD, instead of 100 flight cycles after 
the effective date, as proposed, to expeditiously amend the ALS of the 
TLM with life reduction of the relevant fan disk assembly.
    We also require removing fan disk assemblies from service before 
the next flight if their consumed life has exceeded the maximum 
approved life as specified in the ALS of the TLM. All life limited part 
must be removed from service before reaching its declared life in the 
ALS.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously. We determined that these 
changes will not increase the economic burden on any operator or 
increase the scope of the AD.

Costs of Compliance

    We estimate that this AD will affect about 240 engines installed on 
aircraft of U.S. registry. This LP compressor (fan) disc assembly 
removal does not impose any additional labor costs if performed at the 
time of scheduled engine overhaul. We also estimate that it will take 
about one work-hour per engine to calculate and re-establish the 
achieved cyclic life for an LP compressor (fan) disc assembly, and that 
the average labor rate is $80 per work-hour. We estimate that the 
prorate cost of the life reduction per engine will be $33,000. Total 
cost of this AD is, therefore, $7,939,200.

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 AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (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

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2009-04-13 Rolls-Royce Deutschland Ltd & Co KG (formerly BMW Rolls-
Royce GmbH, and BMW Rolls-Royce Aero Engines): Amendment 39-15819. 
Docket No. FAA-2007-0169; Directorate Identifier 2007-NE-45-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective March 
26, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Rolls-Royce Deutschland Ltd & Co KG 
(RRD), BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 turbofan 
engines, with a low pressure (LP) compressor (fan) disc assembly, 
part number (P/N) BRH10048 or P/N BRH19253. These engines are 
installed on, but not limited to, McDonnell Douglas Corporation 
model 717-200 airplanes.

[[Page 7645]]

Reason

    (d) The mandatory continuous airworthiness information (MCAI) 
states:

    The application of most recent 3D FEM modeling has resulted in 
the need to reconsider the disc lives as currently shown in the Time 
Limits Manual. The current Post Certification Life Statement for the 
low pressure (LP) compressor (fan) disc assembly revises the 
Declared Safe Cyclic Life (DSCL) from 33,000 flight cycles to 25,000 
flight cycles for both the BR715 LP (fan) disc assembly P/N BRH10048 
and BR715 LP compressor (fan) disc assembly P/N BRH19253, when 
installed in the BR700-715A1-30 engine model and operated against 
the Hawaiian Flight Mission.

    This condition, if not corrected, could result in uncontained 
failure of the LP compressor (fan) disc assembly and damage to the 
airplane.

Actions and Compliance

    (e) Within 25 flight cycles after the effective date of this AD, 
do the following actions, unless already done.
    (1) Amend the Airworthiness Limitations Section (ALS) of the 
Time Limits Manual SUBTASK 05-10-01-860-016, by revising the ``GIVEN 
LIFE A1-30 RATING (FLIGHT CYCLES)'' for both the LP compressor (fan) 
disc assembly P/N BRH10048 and LP compressor (fan) disc assembly P/N 
BRH19253 from 33,000 flight cycles to 25,000 flight cycles.
    (2) Check the lifing of both the LP compressor (fan) disc 
assembly P/N BRH10048 and LP compressor (fan) disc assembly P/N 
BRH19253 if the relevant compressor (fan) disc assembly is currently 
installed or was previously installed, in the BR700-715A1-30 engine 
model and operated under the Hawaiian Flight Mission.
    (3) Remove the relevant compressor (fan) disc assembly from 
service before further flight, if the consumed life has exceeded the 
maximum approved life specified in the ALS.

Alternative Methods of Compliance (AMOC)

    (f) The Manager, Engine Certification Office, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19.

Related Information

    (g) Refer to MCAI European Aviation Safety Agency AD 2007-0116-
E, dated May 4, 2007, for related information.
    (h) Contact Jason Yang, Aerospace Engineer, Engine Certification 
Office, FAA, Engine and Propeller Directorate, 12 New England 
Executive Park, Burlington, MA 01803; e-mail: Jason.yang@faa.gov; 
telephone (781) 238-7747; 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. E9-3355 Filed 2-18-09; 8:45 am]
BILLING CODE 4910-13-P