Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG, BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 Turbofan Engines, 6638-6640 [E8-2039]

Download as PDF 6638 Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Proposed Rules Applicability (c) This AD applies to 750XL airplanes, serial numbers 101 through 108, certificated in any category. Subject (d) Air Transport Association of America (ATA) Code 51: Structures. Reason (e) The MCAI describes the unsafe condition as 1⁄8-inch rivets installed in place of the correct 5⁄32-inch rivets that secure the horizontal tail surface load transfer angles to the rearmost fuselage frame at Station 384.62 (Corrected from 369.62 per notification from the Civil Aviation Authority of New Zealand). The MCAI requires you to inspect for the correct size rivets and if the wrong size rivets are installed, replace the rivets with the correct size rivets. Actions and Compliance (f) Unless already done, do the following actions: (1) Within 100 hours time-in-service (TIS) after the effective date of this AD, inspect to ensure that 1⁄8-inch rivets are not installed in place of the correct 5⁄32-inch rivets that secure the horizontal tail surface load transfer angles to the rearmost fuselage frame at Station 384.62 following Pacific Aerospace Corporation Limited Mandatory Service Bulletin No. PACSB/XL/010, dated: July 23, 2004. (2) Before further flight, if you find undersized rivets are installed as a result of the inspection required by paragraph (f)(1) of this AD, replace the undersized rivets with the correct 5⁄32-inch rivets following Pacific Aerospace Corporation Limited Service Mandatory Bulletin No. PACSB/XL/010, dated: July 23, 2004. FAA AD Differences rmajette on PROD1PC64 with PROPOSALS Note: This AD differs from the MCAI and/ or service information as follows: An official of The New Zealand Civil Aviation Authority confirms that the MCAI should reference Station 384.62. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4146; fax: (816) 329–4090. 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 FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required VerDate Aug<31>2005 15:29 Feb 04, 2008 Jkt 214001 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. Related Information (h) Refer to MCAI Civil Aviation Authority of New Zealand AD DCA/750XL/4, effective date: September 30, 2004; and Pacific Aerospace Corporation Limited Mandatory Service Bulletin No. PACSB/XL/010, dated: July 23, 2004, for related information. Issued in Kansas City, Missouri, on January 29, 2008. John Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–2046 Filed 2–4–08; 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] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG, BR700– 715A1–30, BR700–715B1–30, and BR700–715C1–30 Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) issued by another country to identify and correct an unsafe condition on Rolls-Royce Deutschland Ltd & Co KG, BR700–715A1–30, BR700–715B1–30, and BR700–715C1–30 turbofan engines. The MCAI states the following: 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. PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 The proposed AD would require revising the maximum approved life limit for both the BR715 LP compressor (fan) disc assembly P/N BRH10048 and BR715 LP compressor (fan) disc assembly P/N BRH19253, from 33,000 flight cycles to 25,000 flight cycles, if ever operated against the Hawaiian Flight Mission and removing LP compressor (fan) disc assemblies from service that exceed the maximum approved life limit before further flight. This condition, if not corrected, could result in uncontained failure of the LP compressor (fan) disc assembly and damage to the airplane. DATES: We must receive comments on this proposed AD by March 6, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: 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: 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–2007–0169; Directorate Identifier 2007–NE–45–AD’’ at the beginning of E:\FR\FM\05FEP1.SGM 05FEP1 Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Proposed Rules 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. maximum approved life limit before further flight. • Applying the pro rate calculations and completing the Life Limited Part Tracking Sheet, using the revised Hawaiian Flight Mission maximum life limit of 25,000 flight cycles and checking if their consumed life has exceeded maximum approved life of the Flight Mission currently installed in; and • Before further flight, removing LP compressor disc assemblies from service that do not pass the check. Discussion Costs of Compliance We estimate that this proposed AD would affect about 240 engines installed on aircraft of U.S. registry. This proposed 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 proposed AD is, therefore, $7,939,200. The European Aviation Safety Agency (EASA), which is the Technical Agent for the European Community, has issued EASA Airworthiness Directive 2007–0116–E, dated May 4, 2007 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The 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. You may obtain further information by examining the MCAI in the AD docket. rmajette on PROD1PC64 with PROPOSALS FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of Germany, and is approved for operation in the United States. Pursuant to our bilateral agreement with Germany, they have notified us of the unsafe condition described in the MCAI AD and service information referenced above. We are proposing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. This proposed AD would require: • Revising the maximum approved life limit for both the BR715 LP compressor (fan) disc assembly P/N BRH10048 and BR715 LP compressor (fan) disc assembly P/N BRH19253, in the Time Limits Manual No. T–715– 3BR; from 33,000 flight cycles to 25,000 flight cycles, if ever operated against the Hawaiian Flight Mission; and • Removing LP compressor (fan) disc assemblies from service that exceed the VerDate Aug<31>2005 15:29 Feb 04, 2008 Jkt 214001 Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 6639 For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Rolls-Royce Deutschland Ltd & Co KG (formerly BMW Rolls-Royce GmbH, and BMW Rolls-Royce Aero Engines): Docket No. FAA–2007–0169; Directorate Identifier 2007–NE–45–AD. Comments Due Date (a) We must receive comments by March 6, 2008. 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 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. These engines are installed on, but not limited to, McDonnell Douglas Corporation model 717–200 airplanes. 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 E:\FR\FM\05FEP1.SGM 05FEP1 6640 Federal Register / Vol. 73, No. 24 / Tuesday, February 5, 2008 / Proposed Rules 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) No later than 100 flight cycles after the effective date of this AD, do the following actions, unless already done. rmajette on PROD1PC64 with PROPOSALS BR700–715A1–30 Turbofan Engines (1) For BR700–715A1–30 turbofan engines, amend the Airworthiness Limitations Section of the Time Limits Manual SUBTASK 05–10– 01–860–016, (Hawaiian Flight Mission Only) 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) Amend any other Reference, where the maximum approved life limit is quoted for the LP compressor (fan) disc assembly P/N BRH10048 or LP compressor (fan) disc assembly P/N BRH19253, when installed in the BR700–715A–30 engine model and operated under the Hawaiian Flight Mission, to the revised maximum approved life limit of 25,000 flight cycles. BR700–715B1–30 and BR700–715C1–30 Turbofan Engines (3) For BR700–715B1–30 and BR700– 715C1–30 turbofan engines: (i) Check to see if the LP compressor (fan) disc assembly P/N BRH10048 or LP compressor (fan) disc assembly P/N BRH19253 is currently, or has previously been, installed in the BR700–715A1–30 engine model and operated under the Hawaiian Flight Mission, by checking the Life Limited Parts (LLP) Tracking Sheet. Information on recording and control of the lives of the parts can be found in the Airworthiness Limitations Section of the Time Limits Manual TASK 05–00–01–800– 001. (ii) If the LP compressor (fan) disc assembly has not operated, and is not going to operate in the Hawaiian Flight Mission, no further action is required. (iii) If the LP compressor (fan) disc assembly has operated in the Hawaiian Flight Mission: (A) Apply the prorate calculations and complete the LLP Tracking Sheet using the revised Hawaiian Flight Mission maximum approved life limit of 25,000 flight cycles. (B) Remove LP compressor (fan) disc assemblies from service before reaching 25,000 flight cycles. Other FAA AD Provisions (f) Alternative Methods of Compliance: The Manager, Engine Certification Office, FAA, has the authority to approve alternative methods of compliance for this AD, if VerDate Aug<31>2005 15:29 Feb 04, 2008 Jkt 214001 requested using the procedures found in 14 CFR 39.19. Related Information (g) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 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 January 28, 2008. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E8–2039 Filed 2–4–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0115; Directorate Identifier 2007–NM–240–AD] RIN 2120–AA64 Airworthiness Directives; Saab Model SAAB 2000 Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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: SUMMARY: One LM–219–92 Centre Bracket from an LM–219-SA28 Aft Engine Mounting assembly was found to be cracked while installed on the aircraft. This reduces the effectiveness of the mounting assembly and could eventually cause it to fail. * * * * * A failed mounting assembly, if not corrected, could result in loss of the engine. 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 March 6, 2008. ADDRESSES: You may send comments by any of the following methods: PO 00000 Frm 00023 Fmt 4702 Sfmt 4702 • 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. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM– 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1112; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2008–0115; Directorate Identifier 2007–NM–240–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 E:\FR\FM\05FEP1.SGM 05FEP1

Agencies

[Federal Register Volume 73, Number 24 (Tuesday, February 5, 2008)]
[Proposed Rules]
[Pages 6638-6640]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-2039]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0169; Directorate Identifier 2007-NE-45-AD]
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: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed AD results from mandatory 
continuing airworthiness information (MCAI) issued by another country 
to identify and correct an unsafe condition on Rolls-Royce Deutschland 
Ltd & Co KG, BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 
turbofan engines. The MCAI states the following:

    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.

    The proposed AD would require revising the maximum approved life 
limit for both the BR715 LP compressor (fan) disc assembly P/N BRH10048 
and BR715 LP compressor (fan) disc assembly P/N BRH19253, from 33,000 
flight cycles to 25,000 flight cycles, if ever operated against the 
Hawaiian Flight Mission and removing LP compressor (fan) disc 
assemblies from service that exceed the maximum approved life limit 
before further flight. This condition, if not corrected, could result 
in uncontained failure of the LP compressor (fan) disc assembly and 
damage to the airplane.

DATES: We must receive comments on this proposed AD by March 6, 2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue, SE., West Building Ground 
Floor, Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: (202) 493-2251.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
the same as the Mail address provided in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: 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:

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-2007-0169; 
Directorate Identifier 2007-NE-45-AD'' at the beginning of

[[Page 6639]]

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 European Community, has issued EASA Airworthiness 
Directive 2007-0116-E, dated May 4, 2007 (referred to after this as 
``the MCAI''), to correct an unsafe condition for the specified 
products. The 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.

    You may obtain further information by examining the MCAI in the AD 
docket.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of 
Germany, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with Germany, they have notified us of the 
unsafe condition described in the MCAI AD and service information 
referenced above. We are proposing this AD because we evaluated all 
information provided by EASA and determined the unsafe condition exists 
and is likely to exist or develop on other products of the same type 
design. This proposed AD would require:
     Revising the maximum approved life limit for both the 
BR715 LP compressor (fan) disc assembly P/N BRH10048 and BR715 LP 
compressor (fan) disc assembly P/N BRH19253, in the Time Limits Manual 
No. T-715-3BR; from 33,000 flight cycles to 25,000 flight cycles, if 
ever operated against the Hawaiian Flight Mission; and
     Removing LP compressor (fan) disc assemblies from service 
that exceed the maximum approved life limit before further flight.
     Applying the pro rate calculations and completing the Life 
Limited Part Tracking Sheet, using the revised Hawaiian Flight Mission 
maximum life limit of 25,000 flight cycles and checking if their 
consumed life has exceeded maximum approved life of the Flight Mission 
currently installed in; and
     Before further flight, removing LP compressor disc 
assemblies from service that do not pass the check.

Costs of Compliance

    We estimate that this proposed AD would affect about 240 engines 
installed on aircraft of U.S. registry. This proposed 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 proposed 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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

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

Comments Due Date

    (a) We must receive comments by March 6, 2008.

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 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. These engines are installed on, but not limited to, 
McDonnell Douglas Corporation model 717-200 airplanes.

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

[[Page 6640]]

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) No later than 100 flight cycles after the effective date of 
this AD, do the following actions, unless already done.

BR700-715A1-30 Turbofan Engines

    (1) For BR700-715A1-30 turbofan engines, amend the Airworthiness 
Limitations Section of the Time Limits Manual SUBTASK 05-10-01-860-
016, (Hawaiian Flight Mission Only) 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) Amend any other Reference, where the maximum approved life 
limit is quoted for the LP compressor (fan) disc assembly P/N 
BRH10048 or LP compressor (fan) disc assembly P/N BRH19253, when 
installed in the BR700-715A-30 engine model and operated under the 
Hawaiian Flight Mission, to the revised maximum approved life limit 
of 25,000 flight cycles.

BR700-715B1-30 and BR700-715C1-30 Turbofan Engines

    (3) For BR700-715B1-30 and BR700-715C1-30 turbofan engines:
    (i) Check to see if the LP compressor (fan) disc assembly P/N 
BRH10048 or LP compressor (fan) disc assembly P/N BRH19253 is 
currently, or has previously been, installed in the BR700-715A1-30 
engine model and operated under the Hawaiian Flight Mission, by 
checking the Life Limited Parts (LLP) Tracking Sheet. Information on 
recording and control of the lives of the parts can be found in the 
Airworthiness Limitations Section of the Time Limits Manual TASK 05-
00-01-800-001.
    (ii) If the LP compressor (fan) disc assembly has not operated, 
and is not going to operate in the Hawaiian Flight Mission, no 
further action is required.
    (iii) If the LP compressor (fan) disc assembly has operated in 
the Hawaiian Flight Mission:
    (A) Apply the prorate calculations and complete the LLP Tracking 
Sheet using the revised Hawaiian Flight Mission maximum approved 
life limit of 25,000 flight cycles.
    (B) Remove LP compressor (fan) disc assemblies from service 
before reaching 25,000 flight cycles.

Other FAA AD Provisions

    (f) Alternative Methods of Compliance: The Manager, Engine 
Certification Office, FAA, 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

    (g) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 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 January 28, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E8-2039 Filed 2-4-08; 8:45 am]
BILLING CODE 4910-13-P