Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Models BR700-710A1-10; BR700-710A2-20; and BR700-710C4-11 Turbofan Engines, 51693-51696 [2010-20757]

Download as PDF 51693 Proposed Rules Federal Register Vol. 75, No. 162 Monday, August 23, 2010 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF AGRICULTURE Agricultural Marketing Service 7 CFR Part 46 [Document Number: AMS–FV–09–0047] eligibility requirements to enter into a written scheduled payment agreement for payment of the past due amount while maintaining its trust eligibility. The comment period for the proposed rule ended on August 9, 2010; however, several produce associations have requested an additional 30 days to provide comments that are more thorough. AMS believes it is beneficial to reopen and extend the comment period for an additional 30-days in order to receive input from all interested parties. Authority: 7 U.S.C. 499a–499t. Perishable Agricultural Commodities Act: Impact of Post-Default Agreements on Trust Protection Eligibility Dated: August 17, 2010. David R. Shipman, Acting Administrator, Agricultural Marketing Service. Agricultural Marketing Service, USDA. ACTION: Proposed rule; reopening of comment period. [FR Doc. 2010–20849 Filed 8–20–10; 8:45 am] AGENCY: Due to requests from members of the fruit and vegetable industry, notice is hereby given that the comment period on the proposed rule published on June 8, 2010 [75 FR 32306] titled, Perishable Agricultural Commodities Act: Impact of Post-Default Agreements on Trust Protection Eligibility is reopened and extended for an additional 30 days. Reopening the comment period would allow interested parties time to fully analyze the proposed rule and submit comments. DATES: Comments must be received by September 22, 2010. ADDRESSES: You may submit written or electronic comments to PACA Trust Post-Default Comments, AMS, F&V Programs, PACA Branch, 1400 Independence Avenue, SW., Room 2095–S, Stop 0242, Washington, DC 20250–0242; fax: 202–720–8868; or Internet: https://www.regulations.gov. All comments should reference the document number, date, and page number of this issue and the June 8, 2010, issue of the Federal Register. FOR FURTHER INFORMATION CONTACT: Phyllis L. Hall or Josephine E. Jenkins, Trade Practices Section, 202–720–6873. SUPPLEMENTARY INFORMATION: A proposed rule was published on June 8, 2010 (75 FR 32306). The proposed amendment to the regulations under the Perishable Agricultural Commodities Act (PACA) would allow a seller, supplier, or agent who has met the sroberts on DSKD5P82C1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 15:47 Aug 20, 2010 Jkt 220001 BILLING CODE 3410–02–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0614; Directorate Identifier 2010–NE–24–AD] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Models BR700–710A1–10; BR700–710A2–20; and BR700–710C4–11 Turbofan Engines 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) 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: SUMMARY: Due to manufacturing problems of BR700– 710 HP stage 1 and 2 turbine discs it was necessary to re-calculate the Declared Safe Cyclic Life (DSCL) for all BR700–710 HP turbine discs. The analysis concluded that it is required to reduce the approved life limits for the HP turbine disc part numbers that are listed in Table 1 and Table 2 of this AD (MCAI). Exceeding the revised approved life PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 limits could potentially result in noncontained disc failure. We are proposing this AD to preventfailure of the high-pressure turbine (HPT) stage 1 and stage 2 discs, uncontained engine failure, and damage to the airplane. DATES: We must receive comments on this proposed AD by October 7, 2010. 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. Contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, Dahlewitz, 15827 Blankenfelde-Mahlow, Germany, telephone: +49 (0) 33–7086–1883, fax: +49 (0) 33–7086–3276, for the service information identified in this proposed AD. 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 (phone (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: Tara Chaidez, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: tara.chaidez@faa.gov; telephone (781) 238–7773; 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 E:\FR\FM\23AUP1.SGM 23AUP1 51694 Federal Register / Vol. 75, No. 162 / Monday, August 23, 2010 / Proposed Rules to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2010–0614; Directorate Identifier 2010–NE–24–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). Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, notified us that an unsafe condition may exist on Rolls-Royce Deutschland Ltd & Co KG Models BR700–710A1–10; BR700–710A2–20; and BR700–710C4–11 turbofan engines. The MCAI states: Due to manufacturing problems of BR700– 710 HP stage 1 and 2 turbine discs it was necessary to re-calculate the Declared Safe Cyclic Life (DSCL) for all BR700–710 HP turbine discs. The analysis concluded that it is required to reduce the approved life limits for the HP turbine disc part numbers that are listed in Table 1 and Table 2 of this AD (MCAI). Exceeding the revised approved life limits could potentially result in noncontained disc failure. sroberts on DSKD5P82C1PROD with PROPOSALS 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 VerDate Mar<15>2010 15:47 Aug 20, 2010 Jkt 220001 described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. This proposed AD would require replacing the HPT stage 1 or HPT stage 2 discs with serviceable discs at the DSCL as applicable, as listed in Table 1 or Table 2 of the proposed AD. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 1,026 BR700–710 engines of U.S. registry. We also estimate that no additional labor cost will be incurred to replace the discs. The average labor rate is $85 per work-hour. Required parts would cost about $6,000 per disc. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $6,156,000. Our cost estimate is exclusive of possible warranty coverage. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We 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 00002 Fmt 4702 Sfmt 4702 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 airworthiness directive (AD): Rolls-Royce Deutschland Ltd & Co KG (formerly Rolls-Royce Deutschland GmbH, formerly BMW Rolls-Royce GmbH): Docket No. FAA–2010–0614; Directorate Identifier 2010–NE–24–AD. Comments Due Date (a) We must receive comments by October 7, 2010. Affected ADs (b) None. Applicability (c) This AD applies to Rolls-Royce Deutschland Ltd & Co KG models BR700– 710A1–10, BR700–710A2–20, and BR700– 710C4–11 turbofan engines with any of the high-pressure turbine (HPT) stage 1 and stage 2 discs installed as listed by part number (P/N) in Table 1 and Table 2 of this AD. These engines are installed on, but not limited to, Gulfstream model G–V and GV– SP airplanes, and Bombardier model BD– 700–1A10 and BD–700–1A11 airplanes. E:\FR\FM\23AUP1.SGM 23AUP1 51695 Federal Register / Vol. 75, No. 162 / Monday, August 23, 2010 / Proposed Rules TABLE 1—DECLARED SAFE CYCLIC LIFE OF AFFECTED HPT STAGE 1 DISCS HPT Stage 1 disc p/n Declared safe cyclic life (flight cycles) Engine model BRR21215 BRR21215 BRR22005 BRR22005 BRR22006 BRR22006 BRR22007 BRR22007 BRR22358 BRR22358 BRR23864 BRR23864 BRR23884 BRR23884 BRR23885 BRR23885 BRR23952 BRR23952 BRR23952 ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ BRR23952 BRR23953 BRR23953 BRR23953 BRR23953 BRR23954 BRR23954 ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ BR700–710A1–10 BR700–710A2–20 BR700–710A1–10 BR700–710A2–20 BR700–710A1–10 BR700–710A2–20 BR700–710A1–10 BR700–710A2–20 BR700–710A1–10 BR700–710A2–20 BR700–710A1–10 BR700–710A2–20 BR700–710A1–10 BR700–710A2–20 BR700–710A1–10 BR700–710A2–20 BR700–710A1–10 BR700–710A2–20 BR700–710C4–11 porated). BR700–710C4–11 BR700–710A1–10 BR700–710A2–20 BR700–710C4–11 BR700–710C4–11 BR700–710A1–10 BR700–710A2–20 ........................................................................................................ ........................................................................................................ ........................................................................................................ ........................................................................................................ ........................................................................................................ ........................................................................................................ ........................................................................................................ ........................................................................................................ ........................................................................................................ ........................................................................................................ ........................................................................................................ ........................................................................................................ ........................................................................................................ ........................................................................................................ ........................................................................................................ ........................................................................................................ ........................................................................................................ ........................................................................................................ (Service Bulletin (SB) No. SB–BR700–72–101466 not incor- 6,075 5,950 6,200 6,200 6,200 6,200 6,200 6,200 6,200 6,200 6,200 6,200 6,200 6,200 6,200 6,200 6,200 6,200 6,200 (SB No. SB–BR700–72–101466 incorporated) ............................ ........................................................................................................ ........................................................................................................ (SB No. SB–BR700–72–101466 not incorporated) ...................... (SB No. SB–BR700–72–101466 incorporated) ............................ ........................................................................................................ ........................................................................................................ 3,800 6,200 6,200 6,200 3,800 6,200 6,200 TABLE 2—DECLARED SAFE CYCLIC LIFE OF AFFECTED HPT STAGE 2 DISCS HPT Stage 2 disc p/n BRR18291 BRR21214 BRR21214 BRR22008 BRR22008 BRR22008 BRR22008 BRR22009 BRR22009 BRR22009 BRR22009 BRR22010 BRR22010 BRR22359 BRR22359 ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ ................................................ BR700–710A1–10 BR700–710A1–10 BR700–710A2–20 BR700–710A1–10 BR700–710A2–20 BR700–710C4–11 BR700–710C4–11 BR700–710A1–10 BR700–710A2–20 BR700–710C4–11 BR700–710C4–11 BR700–710A1–10 BR700–710A2–20 BR700–710A1–10 BR700–710A2–20 sroberts on DSKD5P82C1PROD with PROPOSALS Reason (d) 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 states: Due to manufacturing problems of BR700– 710 HP stage 1 and 2 turbine discs it was necessary to re-calculate the Declared Safe Cyclic Life (DSCL) for all BR700–710 HP turbine discs. The analysis concluded that it is required to reduce the approved life limits for the HP turbine disc part numbers that are listed in Table 1 and Table 2 of this AD (MCAI). Exceeding the revised approved life VerDate Mar<15>2010 15:47 Aug 20, 2010 Declared safe cyclic life (flight cycles) Engine model Jkt 220001 ........................................................................................................ ........................................................................................................ ........................................................................................................ ........................................................................................................ ........................................................................................................ (SB No. SB–BR700–72–101466 not incorporated) ...................... (SB No. SB–BR700–72–101466 incorporated) ............................ ........................................................................................................ ........................................................................................................ (SB No. SB–BR700–72–101466 not incorporated) ...................... (SB No. SB–BR700–72–101466 incorporated) ............................ ........................................................................................................ ........................................................................................................ ........................................................................................................ ........................................................................................................ limits could potentially result in noncontained disc failure. We are issuing this AD to prevent failure of the HPT stage 1 and stage 2 discs, uncontained engine failure, and damage to the airplane. Actions and Compliance (e) Unless already done, do the following actions. (1) Within 30 days after the effective date of this AD, or upon accumulating the declared safe cyclic life indicated in Table 1 or Table 2 of this AD as applicable, whichever occurs later, initially replace the HPT stage 1 or HPT stage 2 discs with serviceable discs. PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 9,300 9,600 9,600 10,500 10,500 10,500 3,700 10,500 10,500 10,500 3,700 10,500 10,500 10,500 10,500 (2) Thereafter, upon accumulating the declared safe cyclic life indicated in Table 1 or Table 2 of this AD, as applicable, repetitively replace the HPT stage 1 or HPT stage 2 discs with serviceable discs. FAA AD Differences (f) None. Alternative Methods of Compliance (AMOCs) (g) 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. E:\FR\FM\23AUP1.SGM 23AUP1 51696 Federal Register / Vol. 75, No. 162 / Monday, August 23, 2010 / Proposed Rules Related Information (h) Refer to European Aviation Safety Agency AD 2010–0075, dated April 20, 2010, and AD 2010–0076, dated April 20, 2010, for related information. (i) Refer to Rolls-Royce Deutschland Ltd & Co KG SB No. SB–BR700–72–A900492, dated February 12, 2010, and SB No. SB–BR700– 72–A900497, dated February 12, 2010, for related information. Contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, Dahlewitz, 15827 Blankenfelde-Mahlow, Germany, telephone: +49 (0) 33–7086–1883, fax: +49 (0) 33–7086–3276, for a copy of this service information. (j) Contact Tara Chaidez, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: tara.chaidez@faa.gov; telephone (781) 238–7773; fax (781) 238– 7199, for more information about this AD. [FR Doc. 2010–20757 Filed 8–20–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0042; Directorate Identifier 2009–NM–010–AD] RIN 2120–AA64 Airworthiness Directives; Saab AB, Saab Aerosystems Model SAAB 340A (SAAB/SF340A) and SAAB 340B Airplanes Modified in Accordance With Supplemental Type Certificate (STC) SA00224WI–D, ST00146WI–D, or SA984GL–D Federal Aviation Administration (FAA), DOT. ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. AGENCY: We are revising an earlier proposed airworthiness directive (AD) for certain Saab AB, Saab Aerosystems Model SAAB 340A (SAAB/SF340A) and SAAB 340B airplanes. The original NPRM would have required inspecting the fuselage surface for corrosion and cracking behind the external adapter plate of the antennae installation, and repair if necessary. The original NPRM resulted from a report of a crack found behind the external adapter plate of the antennae during inspection. Similar cracking was found on two additional airplanes, and extensive corrosion was found on one airplane. This action sroberts on DSKD5P82C1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 15:47 Aug 20, 2010 Jkt 220001 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 because of 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. Examining the AD Docket Issued in Burlington, Massachusetts, on August 16, 2010. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. revises the original NPRM by correcting an STC number, which would expand the applicability of the original NPRM. We are proposing this supplemental NPRM to detect and correct corrosion and cracking behind the external adapter plate of the antennae of certain damage-tolerant structure, which could result in reduced structural integrity and consequent rapid depressurization of the airplane. DATES: We must receive comments on this supplemental NPRM by September 17, 2010. 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 W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Since we issued the original NPRM, we have determined that STC number SA00244WI–D, identified in the applicability of the NPRM, is an incorrect STC number; the correct number is SA00224WI–D. We have corrected this error, which expands the airplanes affected by the original NPRM. You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility 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 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: William Griffith, Aerospace Engineer, Airframe Branch, ACE–118W, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas 67209; telephone (316) 946–4116; fax (316) 946–4107. 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–2010–0042; Directorate Identifier 2009–NM–010–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 Discussion We issued a notice of proposed rulemaking (NPRM) (the ‘‘original NPRM’’) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to certain Saab AB, Saab Aerosystems Model SAAB 340A (SAAB/SF340A) and SAAB 340B airplanes. That original NPRM was published in the Federal Register on January 19, 2010 (75 FR 2829). That original NPRM proposed to require inspecting the fuselage surface for corrosion and cracking behind the external adapter plate of the antennae installation, and repair if necessary. Actions Since Original NPRM Was Issued Comments We gave the public the opportunity to participate in developing this AD. We considered the comments received. Request To Change the Description of the Unsafe Condition Saab AB/Aerosystems asks that we change the description of the unsafe condition specified in the NPRM. Saab states that the NPRM indicates that the fuselage skin is classified as ‘‘certain safe-life structure.’’ Saab notes that this does not meet the definition of the airframe/fuselage structure; the fuselage skin is damage tolerant structure according to Section 25.571 of the Federal Aviation Regulations (14 CFR 25.571). Saab adds that this definition is included in the fatigue critical baseline structure (FCBS) list. We agree with the commenter for the reasons provided. We have changed the description of the unsafe condition in the Summary section and paragraph (e) of this AD accordingly. E:\FR\FM\23AUP1.SGM 23AUP1

Agencies

[Federal Register Volume 75, Number 162 (Monday, August 23, 2010)]
[Proposed Rules]
[Pages 51693-51696]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-20757]

=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0614; Directorate Identifier 2010-NE-24-AD]
RIN 2120-AA64

Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG
Models BR700-710A1-10; BR700-710A2-20; and BR700-710C4-11 Turbofan
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

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

Due to manufacturing problems of BR700-710 HP stage 1 and 2
turbine discs it was necessary to re-calculate the Declared Safe
Cyclic Life (DSCL) for all BR700-710 HP turbine discs. The analysis
concluded that it is required to reduce the approved life limits for
the HP turbine disc part numbers that are listed in Table 1 and
Table 2 of this AD (MCAI). Exceeding the revised approved life
limits could potentially result in non-contained disc failure.

We are proposing this AD to prevent-failure of the high-pressure
turbine (HPT) stage 1 and stage 2 discs, uncontained engine failure,
and damage to the airplane.

DATES: We must receive comments on this proposed AD by October 7, 2010.

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.
Contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11,
Dahlewitz, 15827 Blankenfelde-Mahlow, Germany, telephone: +49 (0) 33-
7086-1883, fax: +49 (0) 33-7086-3276, for the service information
identified in this proposed AD.

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 (phone (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: Tara Chaidez, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; e-mail:
tara.chaidez@faa.gov; telephone (781) 238-7773; 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

[[Page 51694]]

to an address listed under the ADDRESSES section. Include ``Docket No.
FAA-2010-0614; Directorate Identifier 2010-NE-24-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).

Discussion

The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, notified us that
an unsafe condition may exist on Rolls-Royce Deutschland Ltd & Co KG
Models BR700-710A1-10; BR700-710A2-20; and BR700-710C4-11 turbofan
engines. The MCAI states:

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 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 replacing the HPT stage 1 or HPT stage 2
discs with serviceable discs at the DSCL as applicable, as listed in
Table 1 or Table 2 of the proposed AD.

Costs of Compliance

Based on the service information, we estimate that this proposed AD
would affect about 1,026 BR700-710 engines of U.S. registry. We also
estimate that no additional labor cost will be incurred to replace the
discs. The average labor rate is $85 per work-hour. Required parts
would cost about $6,000 per disc. Based on these figures, we estimate
the cost of the proposed AD on U.S. operators to be $6,156,000. Our
cost estimate is exclusive of possible warranty coverage.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.

Regulatory Findings

We 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
airworthiness directive (AD):

Rolls-Royce Deutschland Ltd & Co KG (formerly Rolls-Royce
Deutschland GmbH, formerly BMW Rolls-Royce GmbH): Docket No. FAA-
2010-0614; Directorate Identifier 2010-NE-24-AD.

Comments Due Date

(a) We must receive comments by October 7, 2010.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Rolls-Royce Deutschland Ltd & Co KG
models BR700-710A1-10, BR700-710A2-20, and BR700-710C4-11 turbofan
engines with any of the high-pressure turbine (HPT) stage 1 and
stage 2 discs installed as listed by part number (P/N) in Table 1
and Table 2 of this AD. These engines are installed on, but not
limited to, Gulfstream model G-V and GV-SP airplanes, and Bombardier
model BD-700-1A10 and BD-700-1A11 airplanes.

[[Page 51695]]

Table 1--Declared Safe Cyclic Life of Affected HPT Stage 1 Discs
------------------------------------------------------------------------
Declared safe
cyclic life
HPT Stage 1 disc p/n Engine model (flight
cycles)
------------------------------------------------------------------------
BRR21215....................... BR700-710A1-10......... 6,075
BRR21215....................... BR700-710A2-20......... 5,950
BRR22005....................... BR700-710A1-10......... 6,200
BRR22005....................... BR700-710A2-20......... 6,200
BRR22006....................... BR700-710A1-10......... 6,200
BRR22006....................... BR700-710A2-20......... 6,200
BRR22007....................... BR700-710A1-10......... 6,200
BRR22007....................... BR700-710A2-20......... 6,200
BRR22358....................... BR700-710A1-10......... 6,200
BRR22358....................... BR700-710A2-20......... 6,200
BRR23864....................... BR700-710A1-10......... 6,200
BRR23864....................... BR700-710A2-20......... 6,200
BRR23884....................... BR700-710A1-10......... 6,200
BRR23884....................... BR700-710A2-20......... 6,200
BRR23885....................... BR700-710A1-10......... 6,200
BRR23885....................... BR700-710A2-20......... 6,200
BRR23952....................... BR700-710A1-10......... 6,200
BRR23952....................... BR700-710A2-20......... 6,200
BRR23952....................... BR700-710C4-11 (Service 6,200
Bulletin (SB) No. SB-
BR700-72-101466 not
incorporated).
BRR23952....................... BR700-710C4-11 (SB No. 3,800
SB-BR700-72-101466
incorporated).
BRR23953....................... BR700-710A1-10......... 6,200
BRR23953....................... BR700-710A2-20......... 6,200
BRR23953....................... BR700-710C4-11 (SB No. 6,200
SB-BR700-72-101466 not
incorporated).
BRR23953....................... BR700-710C4-11 (SB No. 3,800
SB-BR700-72-101466
incorporated).
BRR23954....................... BR700-710A1-10......... 6,200
BRR23954....................... BR700-710A2-20......... 6,200
------------------------------------------------------------------------

Table 2--Declared Safe Cyclic Life of Affected HPT Stage 2 Discs
------------------------------------------------------------------------
Declared safe
cyclic life
HPT Stage 2 disc p/n Engine model (flight
cycles)
------------------------------------------------------------------------
BRR18291....................... BR700-710A1-10......... 9,300
BRR21214....................... BR700-710A1-10......... 9,600
BRR21214....................... BR700-710A2-20......... 9,600
BRR22008....................... BR700-710A1-10......... 10,500
BRR22008....................... BR700-710A2-20......... 10,500
BRR22008....................... BR700-710C4-11 (SB No. 10,500
SB-BR700-72-101466 not
incorporated).
BRR22008....................... BR700-710C4-11 (SB No. 3,700
SB-BR700-72-101466
incorporated).
BRR22009....................... BR700-710A1-10......... 10,500
BRR22009....................... BR700-710A2-20......... 10,500
BRR22009....................... BR700-710C4-11 (SB No. 10,500
SB-BR700-72-101466 not
incorporated).
BRR22009....................... BR700-710C4-11 (SB No. 3,700
SB-BR700-72-101466
incorporated).
BRR22010....................... BR700-710A1-10......... 10,500
BRR22010....................... BR700-710A2-20......... 10,500
BRR22359....................... BR700-710A1-10......... 10,500
BRR22359....................... BR700-710A2-20......... 10,500
------------------------------------------------------------------------

Reason

(d) 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 states:
Due to manufacturing problems of BR700-710 HP stage 1 and 2
turbine discs it was necessary to re-calculate the Declared Safe
Cyclic Life (DSCL) for all BR700-710 HP turbine discs. The analysis
concluded that it is required to reduce the approved life limits for
the HP turbine disc part numbers that are listed in Table 1 and
Table 2 of this AD (MCAI). Exceeding the revised approved life
limits could potentially result in non-contained disc failure.
We are issuing this AD to prevent failure of the HPT stage 1 and
stage 2 discs, uncontained engine failure, and damage to the
airplane.

Actions and Compliance

(e) Unless already done, do the following actions.
(1) Within 30 days after the effective date of this AD, or upon
accumulating the declared safe cyclic life indicated in Table 1 or
Table 2 of this AD as applicable, whichever occurs later, initially
replace the HPT stage 1 or HPT stage 2 discs with serviceable discs.
(2) Thereafter, upon accumulating the declared safe cyclic life
indicated in Table 1 or Table 2 of this AD, as applicable,
repetitively replace the HPT stage 1 or HPT stage 2 discs with
serviceable discs.

FAA AD Differences

(f) None.

Alternative Methods of Compliance (AMOCs)

(g) 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.

[[Page 51696]]

Related Information

(h) Refer to European Aviation Safety Agency AD 2010-0075, dated
April 20, 2010, and AD 2010-0076, dated April 20, 2010, for related
information.
(i) Refer to Rolls-Royce Deutschland Ltd & Co KG SB No. SB-
BR700-72-A900492, dated February 12, 2010, and SB No. SB-BR700-72-
A900497, dated February 12, 2010, for related information. Contact
Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, Dahlewitz, 15827
Blankenfelde-Mahlow, Germany, telephone: +49 (0) 33-7086-1883, fax:
+49 (0) 33-7086-3276, for a copy of this service information.
(j) Contact Tara Chaidez, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
tara.chaidez@faa.gov; telephone (781) 238-7773; fax (781) 238-7199,
for more information about this AD.

Issued in Burlington, Massachusetts, on August 16, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2010-20757 Filed 8-20-10; 8:45 am]
BILLING CODE 4910-13-P

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